# TCDS A28NM: Airbus SAS - Type: Type certificate data sheet - Status: Current - Holder: Airbus SAS - Revision: 55 - Revised: August 13, 2026 - Product: Aircraft, Large Airplane - Certification basis: Part 25, Part 21 - Registered aircraft: 2,054, by the registry models matched to it (OpenAirDocs) - Data sheet PDF: https://openairdocs.org/files/sha256/ac/72/ac725c7d93db13de607d6f254943857fceb7dd54c63f532ff9a37f9db9162b08 - FAA DRS: https://drs.faa.gov/browse/excelExternalWindow/DRSDOCID197655408720260813185800.0001 - Page: https://openairdocs.org/tcds/A28NM ## Models (50) As the data sheet lists them. - A318-111 - A318-112 - A318-121 - A318-122 - A319-111 - A319-112 - A319-113 - A319-114 - A319-115 - A319-131 - A319-132 - A319-133 - A319-151N - A319-153N - A319-171N - A319-173N - A320-111 - A320-211 - A320-212 - A320-214 - A320-216 - A320-231 - A320-232 - A320-233 - A320-251N - A320-252N - A320-253N - A320-271N - A320-272N - A320-273N - A321-111 - A321-112 - A321-131 - A321-211 - A321-212 - A321-213 - A321-231 - A321-232 - A321-251N - A321-252N - A321-253N - A321-271N - A321-272N - A321-251NX - A321-252NX - A321-253NX - A321-253NY - A321-271NX - A321-271NY - A321-272NX ## What the data sheet says From the PDF's text layer, line by line; tables lose their columns. The PDF is the record. ```text A28NM Page 1 of 103 All models DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION A28NM Revision 55 Airbus A318 Series A320 Series A318-111 A320-111 * A318-112 A320-211 A318-121 A320-212 A318-122 A320-214 A320-216 A320-231 A319 Series A320-232 A319-111 A320-233 A319-112 A320-251N A319-113 A320-252N A319-114 A320-253N A319-115 A320-271N A319-131 A320-272N A319-132 A320-273N A319-133 A319-151N A319-153N A321 Series A319-171N A321-111 A319-173N A321-112 A321-131 A321-211 A321-212 A321-213 A321-231 A321-232 A321-251N A321-252N A321-253N A321-271N A321-272N A321-251NX A321-252NX A321-253NX A321-253NY A321-271NX A321-271NY A321-272NX August 13, 2026 TYPE CERTIFICATION DATA SHEET A28NM This Data Sheet which is part of Type Certificate No. A28NM prescribes conditions and limitations under which the product for which the Type Certificate was issued meets the airworthiness requirements of the Federal Aviation Regulations. Type Certificate Holder: Airbus SAS 2, Rond-Point Emile Dewoitine 31700 Blagnac, France Type Certificate Holder Record Name change from Airbus Industrie to Airbus January 2002 then to Airbus SAS in February 2018 * NOTE: Model A320-111 airplanes have been removed from this type certificate data sheet since there are no more A320-111 airplanes in service and none in storage. Airbus no longer supports Model A320-111 airplanes. A28NM Page 2 of 103 All models I. Type A318-100 Series Transport Category Airplanes Model A318-111, Approved June 4, 2003; Model A318-112, Approved June 4, 2003; Model A318-121, Approved May 25, 2007; Model A318-122, Approved May 25, 2007; Engines: Model A318-111, Two CFMI Model CFM56-5B8/P or CFM56-5B8/3 jet engines Model A318-112, Two CFMI Model CFM56-5B9/P or CFM56-5B9/3 jet engines Model A318-121, Two Pratt & Whitney Model PW6122A Model A318-122, Two Pratt & Whitney Model PW6124A See Note 4 for description of “/3” engine models Fuel: See Installation Manual - Document CFM 2129 or PWA7707 TYPE SPECIFICATION (NAME) FRANCE USA UK Kerosene DCSEA 134-D (F-34) ASTM D 1655 (JET A) (JET A1) DEF STAN 91/91 (AVTUR) (JET A1) MIL-DTL- 83133-H (JP 8) DEF STAN 91/87 iss 7 (AVTUR/FSH) (JET A1) (AIA) Wide cut ASTM D 6615 (JET B) DEF STAN 91/88 (AVTAG/FSH) MIL-DTL-5624 (JP 4) High flash point DCSEA 144-C (F-44) MIL-DTL- 5624-V (JP 5) DEF STAN 91/86 iss 7 (AVCAT) Additives: See CFMI "Specific Operating Instructions," CMF TPOI-13 or P&W Service Bulletin 2016. The above mentioned fuels and additives are also suitable for the APU. Engine Limits: CFMI CFM56-5B8/P or -5B8/3 CFMI CFM56-5B9/P or -5B9/3 PW6122A PW6124A Engine FAA Data Sheets FAA Data Sheets FAA Data Sheet FAA Data Sheet Limitation E37NE E38NE E37NE E38NE E00064EN E00064EN Static Thrust at Sea Level - Take-off (5 min)** (Flat rated 30°C) 9 608 daN (21 600 lb) 10 364 daN (23 300 lb) 9 830 daN (22 100 lbs) 10 587 daN (23 800 lbs) Maximum Continuous (Flat rated 25°C) 8478 daN (19 060 1b) 9 008 daN (20 250 lb) 9 030 daN (20 300 lbs) 9 297 daN (20 900 lbs) Maximum Engine Speed - N1 rpm (%) 5 200 (104) 5 200 (104) 6 350 (99.1) 6 350 (99.1) - N2 rpm (%) 15 183 (105) 15 183 (105) 18 850 (100) 18 850 (100) Max Gas Temperature (°C) - Take-off (5 min)** 940 950 760 760 - Max Continuous 905 915 727 727 - Starting * 725 725 760 760 A28NM Page 3 of 103 All models CFMI CFM56-5B8/P or -5B8/3 CFMI CFM56-5B9/P or -5B9/3 PW6122A PW6124A Engine FAA Data Sheets FAA Data Sheets FAA Data Sheet FAA Data Sheet Limitation E37NE E38NE E37NE E38NE E00064EN E00064EN Max Oil Temperature (supply pump inlet; °C) - Stabilized 140 (Take Off) 140 (Take Off) 163 (Max Continuous) 163 (Max Continuous) - Transient 150 (15 min max) 150 (15 min max) 177 (20 min max) 177 (20 min max) Min. Press. (PSI) 13 13 25 25 Approved Oils See SB See SB See PW SB 238 See PW SB 238 CFMI 79-001-0X CFMI 79-001-0X * 4 consecutive cycles of 2 minutes each. ** 10 minutes at take-off thrust allowed in case of engine failure (at take off and during go around). Airspeed Limits (Indicated Airspeed - IAS - Unless Otherwise Stated: - Maximum Operating Mach - MMO: 0.82 - Maximum Operating Speed - VMO: 350 kt - Maneuvering Speed VA: - See Limitations Section of Aircraft Flight Manual - Extended Flaps/Slats Speed - VFE Airspeed limits Continued: Configuration Slats/Flaps VFE (kt) 1 18/0 230 Intermediate Approach *18/10 215 Take-off 2 22/15 200 Take-off and Approach 3 22/20 185 Take-off, Approach, and Landing Full 27/40 177 Landing * Auto flap retraction at 210 kt in Take-off configuration. Landing Gear: - VLE - Extended: 280 kt/Mach 0.67 - VLO - Extension: 250 kt - Retraction: 220 kt Tire Limit Speed (Ground Speed) = 195.5 kt (225 mph) Maximum Certified Weights: A318‐111/‐112/‐121/‐122 (KG) (LBS) Max. Take-off Weight 64 500 142 197 Max. Landing Weight 57 500 126 765 Max. Zero Fuel Weight 54 500 120 151 Minimum Weight 34 500 76 059 See applicable Airplane Flight Manual (AFM), as listed in ‘Operating and Service Instructions’, for configuration specific mass limitations and aircraft eligibility (Weight Variant). Minimum Crew: 2 Pilots Maximum Passengers: 136 See note 6 A28NM Page 4 of 103 All models Maximum Baggage: CARGO COMPARTMENT MAXIMUM LOAD (KG) (LBS) Forward 1 614 3 558 Aft 2 131 4 698 Rear (Bulk) 1 372 3 025 For the positions and the loading conditions authorized in each position (references of containers, pallets, associated weights), see Weight and Balance Manual, Ref. 00P080A0001/C1S Chapter 1.10. Fuel Capacity (0.8 kg/liter) A318-100 3-Tank Airplane Tank Usable Fuel Unusable Fuel Liters (kgs) Gallons (lbs) Liters (Kgs) Gallons (lbs) Wing 15 609 4 124 58.9 15.6 (12 487) (27 531) (47.1) (103.9) Center 8 250 2 179 23.2 6.5 (6 600) (14 551) (18.6) (41.0) TOTAL 23 859 6 303 82.1 20.8 (19 087) (42 082) (65.7) (144.9) A318-100 with modification 160001 (Structural Provisions for Sharklet – see note 9) 3-Tank Airplane Tank Usable Fuel Unusable Fuel Liters (kgs) Gallons (lbs) Liters (Kgs) Gallons (lbs) Wing 15 568 4 113 58.9 15.6 (12 454) (27 458) (47.1) (103.9) Center 8 248 2 178 23.2 6.5 (6 598) (14 546) (18.6) (41.0) TOTAL 23 816 6 291 82.1 20.8 (19 052) (42 007) (65.7) (144.9) Oil Capacity CFMI CFM56-5B - Engine Oil Capacity, 10 quarts/engine (9.46 liters). Maximum Operating Altitude: - 39 800 feet (12 200 m) clean - 20 000 feet (6 500 m) Slats/Flaps extended. Equipment: The basic equipment as prescribed in the airworthiness regulations (see certification basis) must be installed in the aircraf t for certification. Refer to note 1 for list of A318 airplane model FAA Type Definitions. Import Requirements: A FAA Standard Airworthiness Certificate may be issued based on a German Export Ce rtificate of Airworthiness (Export C of A), signed by a representative of the Luftfahrt -Bundesamt (LBA) of Germany on behalf of the European Community or based on a EASA Export C of A issued by a representative of EASA . The Export C of A should contain the following statement: “The aircraft covered by this certificate has been examined, tested, and found to conform to the FAA Type Design approved under Type Certificate No. A28NM and to be in a condition for safe operation.” Refer to the applicable bilateral agreement to verify eligibility for import into the United States of both new and used aircraft based on the scope of the agreement, to identify any required statements by the exporting authority on the export certificate of airworthiness (or equivalent document), and for procedures for coordinating exceptions to conformity statements on these documents. Refer to FAA Order 8130.2, Airworthiness Certification of Aircraft, for requirements for issuance of an airworthiness certificate for imported aircraft.” A28NM Page 5 of 103 All models Certification Basis: a. Part 25 of the FAR effective February 1, 1965, including Amendments 25-1 through 25-56 thereto. a.1 Plus the following sections of Part 25 as amended by amendments 25-1 through 25-97 applied per the FAA derivative aircraft process to the changes and areas affected by the changes for all A318 models: 25.21, 25.23, 25.25, 25.27, 25.29, 25.31, 25.101, 25.103, 25.105, 25.107, 25.109, 25.111, 25.113, 25.115, 25.117, 25.119, 25.121, 25.123, 25.125, 25.143, 25.145, 25.147, 25.149, 25.161, 25.171, 25.173, 25.175, 25.177, 25.181, 25.201, 25.203, 25.207, 25.231, 25.233, 25.235, 25.237, 25.251(e), 25.253, 25.255, 25.571 (welded structure only), 25.801, 25.803, 25.807, 25.809, 25.810, 25.811, 25.812, 25.813, 25.855, 25.857, 25.858, 25.1501, 25.1517, 25.1583, 25.1587 a.2 Plus the following sections of Part 25 as amended by amendments 25-1 through 25-105 applied per the FAA derivative aircraft process to the changes and areas affected by the changes for the A318-121/-122 models: 25.361, 25.363, 25.367, 25.371, 25.901, 25.903, 25.933, 25.934, 25.939, 25.941, 25.943, 25.945, 25.1041, 25.1043, 25.1045, 25.1091, 25.1093, 25.1103, 25.1105, 25.1107, 25.1121, 25.1123, 25.1125, 25.1127, 25.1141, 25.1143, 25.1163, 25.1165, 25.1167, 25.1181, 25.1182, 25.1183, 25.1185, 25.1187, 25.1189, 25.1191, 25.1193 a.3 Plus the following sections of Part 25 amended as indicated below per Airbus elect to comply: 25.305 Amdt. 86 25.415 Amdt 91 25.321 Amdt. 86 25.427 Amdt 86 25.331 Amdt. 91 25.445 Amdt 86 25.333 Amdt. 86 25.473 Amdt 91 25.335 Amdt. 91 25.479 Amdt 91 25.341 Amdt. 86 25.481 Amdt 91 25.343 Amdt 86 25.483 Amdt 91 25.345 Amdt 91 25.485 Amdt 91 25.349 Amdt. 86 25.491 Amdt 91 25.351 Amdt. 91 25.499 Amdt 91 25.363 Amdt 91 25.561(c) Amdt 91 25.371 Amdt 91 25.571 Amdt 86* 25.373 Amdt 86 25.735 Amdt 92 25.391 Amdt 86 25.853 Amdt 83 25.1533 Amdt 92 * Not applicable to welded structure a.4 Plus Section 25.772 & 25.795 amendment 25-106 per Airbus elect to comply. a.5 Plus portions of Section 25.562, Amendment 64, for the passenger seats only per Airbus elect to comply. FAR paragraphs 25.562(c)(5), (c)(6) do not apply. b. Based on 14 CFR Section 21.29(a) for new import Type Certificates (TCs), (or Section 21.101(g) for changes to TCs), applicable provisions of 14 CFR Part 26 are included in the certification basis. For any future 14 CFR part 26 amendments, the holder of this TC must demonstrate compliance with the applicable sections. c. 14 CFR Part 34, effective September 10, 1990, including Amendments 34-1 through 34-3 thereto. d. 14 CFR Part 36, effective December 1, 1969, including Amendments 36-1 through 36-26 thereto. See Note 7. 14 CFR Part 36 through Amendment 36-31, Stage 5 for models A318-111 and A318-112. The means of implementation of Stage 5 recertification must be provided by Airbus to ensure availability of the revised AFM noise pages for all affected aircraft. AFM CP293 issue 1.0 dated October 2, 2018 or later revision approved by EASA. e. FAA Special Conditions issued for the A320 and A318-121/-122 in accordance with Section 21.16 of the FAR: (1) No. 25-ANM-23, Effective December 15, 1988: • Electronic Flight Controls • Active Controls • Engine Controls and Monitoring • Protection from Lightning and Unwanted Effects of Radio Frequency (RF) Energy • Flight Characteristics • Flight Envelope Protection • Side Stick Controllers • Flight Recorder. A28NM Page 6 of 103 All models (2) No. 25-ANM-29, Effective May 31, 1989: • Computerized Airplane Flight Manual (3) No. 25-299-SC, Effective October 27, 2005: • Sudden Engine Stoppage on Airbus Model A318 airplanes equipped with Pratt and Whitney PW6000 engines (4) No. 25-671-SC, Effective May 16, 2017: • Non-Rechargeable Lithium Batteries – Applicable to Type design changes applied after May 16, 2017. Reference the applicability section of this special condition for more information on which Type design changes must meet it. (5) No. 25-729-SC, Effective June 28, 2018: • Electronic System Security Protection from Unauthorized Internal Access - Applicable to type design changes applied after June 28, 2018. (6) No. 25-730-SC, Effective June 28, 2018: • Electronic System Security Protection from Unauthorized External Access - Applicable to type design changes applied after June 28, 2018. f. For precision approach and landing, the applicable technical requirements are complemented by AC 120-29 and AC 120-28d. For the automatic flight control system, the applicable technical requirements are complemented by AC 20 -57A for automatic landing and by AC 25.1329-1A for cruise. Use of JAR AWO where applicable to the requirements above, is acceptable. g. The following paragraphs of the FAR have been complied with through equivalent safety demonstrations: • 25.783(f) for passenger doors • 25.807(c) for maximum passenger capacity • 25.811(e)(3) Type III emergency exit marking. • 25.813(c) for emergency exit access • 25.831 Ventilation Packs off takeoff • 25.933 for flight critical thrust reverser systems. h. Optional Requirements elected: • 25.801 for ditching. • 25.1419 for icing. i. Exemption No. 8812, dated December 21, 2006: As related to Section 25.901(c) of Part 25 for single failures that may result in uncontrollable high thrust conditions on Airbus Model A318 airplanes equipped with Pratt and Whitney PW6000 Engines. Note 1: The A318 basic type design definition for U.S. import certification is contained in the following documents: - D03007678 for the A318-111 & A318-112 models - D06003309 for the A318-121 - D06003310 for the A318-122 Note 2: All A318 models are basically qualified for Cat IIIB precision approach. This does not constitute operational approval. Note 3: The FAA has concluded that the occurrence of any uncontrollable high thrust failure condition, or any of the associated causal failures listed within the A318PW Trouble Shooting Manual, may endanger the safe operation of an airplane. Consequently, the FAA recommends that operators be encouraged to report such failures in accordance with paragraphs 121.703(c), 125.409(c) and 135.415(c). Note 4: If modification 37147 (Tech insertion program) is embodied in production or 38770 (Tech insertion program retrofit) is embodied in service on A318 airplanes, the engine performance and gaseous emission levels are improved. The engine denomination changes to /3 Note 5: If modification 38573 is embodied in service on A318 airplanes, the engine hardware configurations can be intermixed with one CFM56-5Bx/3 SAC (Tech Insertion) and one CFM56-5Bx/P SAC engine. A28NM Page 7 of 103 All models Note 6: If modification 39673 is embodied on A318 airplanes, the two overwing emergency exits are deactivated. - For overland flights, the aircraft is eligible for maximum capacity of 110 passengers. - For overwater flights, the aircraft is eligible for maximum capacity of 32 passengers. Note 7: For noise, A318-121/-122 models are basically compliant with ICAO Annex 16 Chapter 4 requirements. For A318-111/-112 models, the compliance with ICAO Annex 16 Chapter 4 requirements is achieved when modification 36521 is embodied. Note 8: On series A318-100 airplanes, introduction of standard of wingbox without dry bay (modification 37331) increases the wing fuel capacity by 350 liters. Note 9: If Modification 160001 for installation of structural provisions for new large wingtip device (Sharklet) is embodied on A318 series airplanes the usable fuel quantities are reduced as shown above to account for the loss of volume due to structural reinforcements in the wing and center wing box. Note 10: For A318-100 airplanes performing extended overwater operations, the maximum number of occupants is 119, including passengers, cabin crew and flight crew. Note 11: Serial Numbers Eligible: Until September 26, 2004, A318 aircraft, all series, all models, have been produced in Hamburg (Germany) under approval LBA.G.0009 issued by LBA to Airbus. From September 27, 2004 until July 20, 2008, A318 aircraft, all series, all models, have been produced in Hamburg (Germany) under approval DE.21G.0009 issued by LBA to Airbus. Since July 21, 2008 to April 30, 2011, A318 aircraft, all series, all models, are produced in Hamburg (Germany) under approval EASA 21G.0001 issued by EASA to Airbus. Since May 1, 2011 and in accordance with the TIP, “Technical Implementing Procedure for Airworthiness and Environmental Certification Between the Federal Aviation Administration of the United States of America and the European Union Aviation Safety Agency”, A318 aircraft, all series, all models, produced under approval EASA.21.G.0001 issued by EASA to Airbus are eligible, unless otherwise stated in this TCDS. A28NM Page 8 of 103 All models II. Type A319-100 Series Transport Category Airplanes 1. Model A319-112, Approved August 30, 1996; 2. Model A319-111, Approved June 20, 1997; 3. Model A319-113, Approved June 20, 1997; 4. Model A319-114, Approved June 20, 1997; 5. Model A319-131, Approved June 20, 1997; 6. Model A319-132, Approved June 20, 1997; 7. Model A319-115, Approved October 22, 2002; 8. Model A319-133, Approved October 22, 2002; 9. Model A319-151N Approved December 19, 2018; 10. Model A319-171N Approved December 17, 2019; 11. Model A319-153N Approved January 23, 2020; 12. Model A319-173N Approved April 8, 2024. Engines: Model A319-111, Two CFMI Model CFM56-5B5 or CFM56-5B5/P or CFM56-5B5/3 jet engines; Model A319-112, Two CFMI Model CFM56-5B6 or CFM56-5B6/P or CFM56-5B6/2P or CFM56-5B6/3 jet engines; Model A319-113, Two CFMI Model CFM56-5A4 or CFM56-5A4/F jet engines; Model A319-114, Two CFMI Model CFM56-5A5 or CFM56-5A5/F jet engines; Model A319-115, Two CFMI Model CFM56-5B7 or CFM56-5B7/P or CFM56-5B7/3 jet engines; Model A319-131, Two IAE Model V2522-A5 jet engines; Model A319-132, Two IAE Model V2524-A5 jet engines; Model A319-133, Two IAE Model V2527M-A5 jet engines; Model A319-151N, Two CFMI Model LEAP 1A24 jet engines; Model A319-153N, Two CFMI Model LEAP 1A26 jet engines; Model A319-171N, Two IAE Model PW1124G1-JM jet engines; Model A319-173N, Two IAE Model PW1127G1-JM jet engines See Note 4 for description of “/P” engine models See Note 9 for description of “/2P” engine models See Note 10 for desription of “/F” engine models See Note 12 for description of “/3” engine models See Note 13 for description of “ “ engine models (Select One Package) Fuel: For A319-111,-112,-113,-114,-115,-131,-132,-133 See Installation Manual - Documents CFM 2026 or CFM 2129 or IAE-0043 TYPE SPECIFICATION (NAME) FRANCE USA UK Kerosene DCSEA 134-D (F-34) ASTM D 1655 (JET A) (JET A1) DEF STAN 91/91 (AVTUR) (JET A1) MIL-DTL- 83133-H (JP 8) DEF STAN 91/87 iss 7 (AVTUR/FSH) (JET A1) (AIA) Wide cut ASTM D 6615 (JET B) DEF STAN 91/88 (AVTAG/FSH) MIL-DTL-5624 (JP 4) High flash point DCSEA 144 C (F-44) MIL-DTL- 5624-V (JP 5) DEF STAN 91/86 iss 7 (AVCAT) A28NM Page 9 of 103 All models For A319-151N/-153N/-171N/-173N See Service Bulletin LEAP-1A S/B 73-0001 or PW1000G-D-73 00-0002-00A-930A-D TYPE SPECIFICATION (NAME) USA UK Kerosene ASTM D 1655 (JET A) (JET A1) DEF STAN 91/91 (AVTUR) (JET A1) MIL-DTL- 83133-H (JP 8) DEF STAN 91/87 iss 7 (AVTUR/FSII) (JET A1) (AIA) High flash point MIL-DTL-5624- V (JP 5) DEF STAN 91/86 iss 7 (AVCAT) Additives: See CFMI CFM 56 " Specific Operating Instructions," CMF TPOI-13 or IAE V2500 “Installation and Operating Manual” IAE-0043, 4.5 or the “Standard Practices and Processes Manual” in the IETM or Service Bulletin LEAP-1A S/B 73-0001 or Service Bulletin PW1000G-D-73-00-0002-00A-930A-D. The above mentioned fuels and additives are also suitable for the APU. Engine Limits: CFMI CFM56-5B5*** or - 5B5/P or -5B5/3 CFMI CFM56- 5B6*** or -5B6/P or - 5B6/2P or -5B6/3 CFMI CFM56-5A4 CFMI CFM56-5A4/F Engine FAA Data Sheets FAA Data Sheets FAA Data Sheet FAA Data Sheet Limitation E37NE E38NE E37NE E38NE E28NE E28NE Static Thrust at Sea Level - Take-off (5 min)** (Flat rated 30°C) 9 786 daN (22 000 lb) 10 453 daN (23 500 lb) 9 786 daN (22 000 lb) 9 786 daN (22 000 lb) Maximum Continuous (Flat rated 25°C) 9 008 daN (20 250 1b) 9 008 daN (20 250 1b) 9 195 daN (20 670 1b) 9 195 daN (20 670 1b) Maximum Engine Speed - N1 rpm (%) 5 200 (104) 5 200 (104) 5 100 (102) 5 100 (102) - N2 rpm (%) 15 183 (105) 15 183 (105) 15 183 (105) 15 183 (105) Max Gas Temperature (°C) Eng. Limit/ ECAM - Take-off (5 min)** 950 950 890 915/890 - Max Continuous 915 915 855 880/855 - Starting * 725 725 725 725/725 Max Oil Temperature (supply pump inlet; °C) - Take-off, Stabilized 140 140 140 140 - Transient (15 min max) 155 155 155 155 Min. Press. (PSI) 13 13 13 13 Approved Oils See SB See SB See SB See SB CFMI CFMI 79-001-0X CFMI 79-001-0X CFMI 79-001-0X 79-001-0X CFMI CFM56-5A5 CFMI CFM56-5A5/F IAE V2522-A5 IAE V2524-A5 Engine Limitation FAA Data Sheets FAA Data Sheet FAA Data Sheets FAA Data Sheets E28NE (FAA) E28NE (FAA) E40NE (FAA) E40NE (FAA) Static Thrust at Sea Level - Take-off (5 min)** (Flat rated 30°C) 10 453 daN (23 500 lb) 10 453 daN (23 500 lb) 10 249 daN (23 040 lb) 10 889 daN (24 480 lb) Maximum Continuous (Flat rated 25°C) 9 195 daN (20 670 1b) 9 195 daN (20 670 1b) 8 540 daN (19 200 1b) 8 540 daN (19 200 1b) A28NM Page 10 of 103 All models CFMI CFM56-5A5 CFMI CFM56-5A5/F IAE V2522-A5 IAE V2524-A5 Engine Limitation FAA Data Sheets FAA Data Sheet FAA Data Sheets FAA Data Sheets E28NE (FAA) E28NE (FAA) E40NE (FAA) E40NE (FAA) Maximum Engine Speed - N1 rpm (%) 5 100 (102) 5 100 (102) 5 650 (100) 5 650 (100) - N2 rpm (%) 15 183 (105) 15 183 (105) 14 950 (100) 14 950 (100) Max Gas Temperature (°C) Eng. Limit/ ECAM Eng. Limit/ ECAM Eng. Limit/ ECAM - Take-off (5 min)** 890 915/890 625/635 635/635 - Max Continuous 855 880/855 610/610 610/610 - Starting * 725 725/725 635/635 635/635 Max Oil Temperature (supply pump inlet; °C) - Take-off, Stabilized 140 140 155 155 - Transient (15 min max) 155 155 165 165 Min. Press. (PSI) 13 13 60 60 Approved Oils See SB See SB CFMI See Doc IAE 0043 Sec 4.9 See Doc IAE 0043 Sec 4.9 CFMI 79-001-0X 79-001-0X (MIL-L-23699) (MIL-L-23699) CFMI CFM56-5B7 *** or -5B7/P or - 5B7/3 IAE V2527M-A5 CFMI LEAP-1A24 CFMI LEAP-1A26 Engine Limitation FAA Data Sheets FAA Data Sheet FAA Data Sheet FAA Data Sheet E37NE E38NE E40NE E00089EN E00089EN Static Thrust at Sea Level - Take-off (5 min)** (Flat rated 30°C) 12 010 daN (27 000 lb) 11 031 daN (24 800 lb) 10 680 daN (24 010lb) 12 064 daN (27 120lb) - Maximum Continuous (Flat rated 25°C) 10 840 daN (24 370 1b) 9 893 daN (22 240 1b) 10 676daN (24 000lb) 11 868 daN (26 680lb) Maximum Engine Speed - N1 rpm (%) 5 200 (104) 5 650 (100) 3 894(101) 3 894(101) - N2 rpm (%) 15 183 (105) 14 950 (100) 19 391(116.5) 19 391(116.5) Max Gas Temperature (°C) - Take-off (5 min)** 950 645 1060 1060 - Max Continuous 915 610 1025 1025 - Starting * 725 650 875 875 Max Oil Temperature (supply pump inlet; °C) - Take-off, Stabilized 140 155 140 140 - Transient (15 min max) 155 165 155 155 Min. Press. (PSI) 13 60 29 redline/17.4 idle 29 redline/17.4 idle Approved Oils See SB See Doc IAE 0043 Sec 4.9 See SB See SB CFMI 79-001-0X (MIL-L-23699) 79-0001 79-0001 * 4 consecutive cycles of 2 minutes each. ** 10 minutes at take-off thrust allowed in case of engine failure (at take off and during go around). *** See Note 17 for engine models no longer in production/service A28NM Page 11 of 103 All models Engine Limits Continued: Engine Limitation PW1124G1-JM FAA Data Sheet E00087EN PW1127G1-JM FAA Data Sheet E00087EN Static Thrust at Sea Level - Take-off (5 min)** (Flat rated 30°C) 10 782 daN (24 240lb) 12 043 daN (27 075lb) - Maximum Continuous (Flat rated 25°C) 10 691 daN (24 035lb) 11 718 daN (26 345lb) Maximum Engine Speed - N1 rpm (%) 10 047(105) 10 047 (105) - N2 rpm (%) 22 300(105) 22 300 (105) Max Gas Temp.(°C) - Take-off (5 min)** 1083 1083 - Max Continuous 1043 1043 - Starting* 1083 1083 Maximum Oil Temp. (Supply Pump Inlet; °C) -Takeoff, Stabilized 152 152 -Transient (15 min max) 141 141 Min. Press. (PSI) 63 63 Approved oils See SB See SB PW1000G-D-79-00- 0002-00A-930A-D PW1000G-1000-79-00- 0002-00A-930A-D ** 10 minute at take-off thrust allowed in case of engine failure (at take-off and during go-around) Airspeed Limits (Indicated Airspeed - IAS - Unless Otherwise Stated: - Maximum Operating Mach - MMO: 0.82 - Maximum Operating Speed - VMO: 350 kt - Maneuvering Speed VA: - See the Limitations Section of Aircraft Flight Manual - Extended Flaps/Slats Speed - VFE Configuration Slats/Flaps VFE (kt) 1 18/0 230 Intermediate Approach *18/10 215 Take-off 2 22/15 200 Take-off and Approach 3 22/20 185 Take-off, Approach, and Landing Full 27/40 177 Landing * Auto flap retraction at 210 kt in Take-off configuration. Landing Gear: - VLE - Extended: 280 kt/Mach 0.67 - VLO - Extension: 250 kt - Retraction: 220 kt Tire Limit Speed (Ground Speed) = 195.5 kt (225 mph) Maximum Certified Weights: A319-111/-112/-113/-114/-115/- 131/-132/-133 (KG) (LBS) A319-151N/-153N/-171N/- 173N (KG) (LBS) Max. Take-off Weight 76 500 168 652 75 500 166 447 Max. Landing Weight 62 500 137 787 63 900 140 875 Max. Zero Fuel Weight 58 500 128 969 60 300 132 938 Minimum Weight 35 400 78 042 39 600 87 304 A28NM Page 12 of 103 All models See applicable Airplane Flight Manual (AFM), as listed in ‘Operating and Service Instructions’, for configuration specific mass limitations and aircraft eligibility (Weight Variant). Minimum Crew: 2 Pilots Maximum Passengers: 145 See note 11, 18, 22, 23, 24 and 26 Maximum Baggage: CARGO COMPARTMENT MAXIMUM LOAD (KG) (LBS) Forward 2 268 5 000 Aft 3 021 6 660 Rear (Bulk) 1 497 3 300 For the positions and the loading conditions authorized in each position (references of containers, pallets, associated weights), see Weight and Balance Manual, Ref. 00J080A0001/C1S Chapter 1.10. Fuel Capacity (0.8 kg/liter) For A319-111,-112,-113,-114,-115,-131,-132,-133 3-Tank Airplane Tank Usable Fuel Unusable Fuel Liters (kgs) Gallons (lbs) Liters (Kgs) Gallons (lbs) Wing 15 609 4 124 58.9 15.6 (12 487) (27 531) (47.1) (103.9) Center 8 250 2 179 23.2 6.1 (6 600) (14 551) (18.6) (41.0) TOTAL 23 859 6 303 82.1 20.8 (19 087) (42 082) (65.7) (144.9) 4 to 9-Tank Airplane (*) Tank Usable Fuel Unusable Fuel Liters (kgs) Gallons (lbs) Liters (Kgs) Gallons (lbs) TOTAL 3-Tank 23 859 6 303 82.1 20.8 Airplane (19 087) (42 082) (65.7) (144.9) ACT 1 3 121 824 17 4.3 (2 497) (5 505) (13.6) (28.8) TOTAL 4-Tank 26 980 7 128 99.1 25.1 Airplane (21 584) (47 587) (79.3) (173.7) ACT 2 3 121 824 17 4.3 (2 497) (5 505) (13.6) (28.8) TOTAL 5-Tank 30 101 7 952 116.1 29.4 Airplane (24 081) (53 092) (92.9) (202.5) ACT 3 2 186 577 22 5.6 (1 749) (3 855) (17.6) (37.4) TOTAL 6-Tank 32 287 8 530 138.1 35.0 Airplane (25 830) (56 947) (110.5) (239.9) ACT 4 2 186 577 22 5.6 (1 749) (3 855) (17.6) (37.4) TOTAL 7-Tank 34 473 9 107 160.1 40.6 Airplane (27 579) (60 803) (128.1) (277.3) ACT 5 3 046 804 12 3.1 (2 437) (5 372) (9.6) (20.6) A28NM Page 13 of 103 All models 4 to 9-Tank Airplane (*) Tank Usable Fuel Unusable Fuel Liters (kgs) Gallons (lbs) Liters (Kgs) Gallons (lbs) TOTAL 8-Tank 37 519 9 912 172.1 43.7 Airplane (30 016) (66 176) (137.7) (297.9) ACT 6 3 121 824 17 4.3 (2 497) (5 505) (13.6) (28.8) TOTAL 9-Tank 40 640 10 737 189.1 48.0 Airplane (32 513) (71 681) (151.3) (326.7) (*) See note 7 Fuel Capacity (0.8 kg/liter) continued A319-100 with modification 160001 (Structural Provisions for Sharklet – see note 20): 3-Tank Airplane Tank Usable Fuel Unusable Fuel Liters (kgs) Gallons (lbs) Liters (Kgs) Gallons (lbs) Wing 15 569 4 113 58.9 15.6 (12 455) (27 458) (47.1) (103.9) Center 8 248 2 178 23.2 6.1 (6 598) (14 546) (18.6) (41.0) TOTAL 23 817 6 291 82.1 21.7 (19 054) (42 007) (65.7) (144.9) 4 to 9-Tank Airplane (*) Tank Usable Fuel Unusable Fuel Liters (kgs) Gallons (lbs) Liters (Kgs) Gallons (lbs) TOTAL 3-Tank 23 817 6 291 82.1 21.7 Airplane (19 054) (42 007) (65.7) (144.9) ACT 1 2.992 790 17 4.3 (2 393) (5 275) (13.6) (28.8) TOTAL 4-Tank 26 809 7 082 99.1 25.1 Airplane (21 447) (47 282) (79.3) (173.7) ACT 2 2.992 790 17 4.3 (2 393) (5 275) (13.6) (28.8) TOTAL 5-Tank 29 801 7 872 116.1 29.4 Airplane (23 841) (52.557) (92.9) (202.5) ACT 3 2 186 566 22 5.6 (1 749) (4.313) (17.6) (37.4) TOTAL 6-Tank 32 245 8 518 138.1 35.0 Airplane (25 796) (56 870) (110.5) (239.9) ACT 4 2 186 577 22 5.6 (1 749) (3 855) (17.6) (37.4) TOTAL 7-Tank 34 431 9 095 160.1 40.6 Airplane (27 545) (60 725) (128.1) (277.3) ACT 5 3 046 804 12 3.1 (2 437) (5 372) (9.6) (20.6) TOTAL 8-Tank 37 477 9 899 172.1 43.7 Airplane (29 982) (66 097) (137.7) (297.9) ACT 6 3 121 824 17 4.3 (2 497) (5 505) (13.6) (28.8) A28NM Page 14 of 103 All models 4 to 9-Tank Airplane (*) Tank Usable Fuel Unusable Fuel Liters (kgs) Gallons (lbs) Liters (Kgs) Gallons (lbs) TOTAL 9-Tank 40 598 10 723 189.1 48.0 Airplane (32 479) (71 602) (151.3) (326.7) (*) See note 7 For A319-151N/-153N/-171N/-173N: 3-Tank Airplane Usable Fuel Unusable Fuel Liters (kgs) Gallons (lbs) Liters (kgs) Gallons (lbs) Wing 15 477 (12 428) 4 088 (27 399) 58.9 (47.3) 15.5 (104.3) Center 8 248 (6 623) 2179 (14601) 23.2 (18.6) 6.1 (41.0) Total 23 725 (19 051) 6267 (42000) 82.1 (65.9) 21.6 (145.3) Oil Capacity CFMI CFM56-5B - Engine Oil Capacity, 10 quarts/engine (9.46 liters). IAE V2500-A5 - Engine Oil Capacity, 7 quarts/engine (6.6 liters) CFMI LEAP-1A – Engine Oil Capacity 21.3 quarts/engine (20.1 liters) IAE PW1100G-JM – Engine Oil Capacity 34.9 quarts/engine (33.0 liters) Maximum Operating Altitude: - 41 000 feet (12 600 m) clean if modification 28162 is embodied. - 39 800 feet (12 200 m) clean if modification 30748 is embodied. - 39 100 feet (12 000 m) clean. - 20 000 feet (6 500 m) Slats/Flaps extended. - 26 000 feet (7 900 m) Slats/Flaps extended if modification 164515 is embodied. Equipment: The basic equipment as prescribed in the airworthiness regulations (see certification basis) must be installed in the aircraf t for certification. Equipment approved for installation are listed in the definition of the reference model and the modifications applicable to i t. Refer to Type Certification Standard Equipment Lists: -00J000A0012/C0S for A319-111 Model -00J000A0004/C0S for A319-112 Model -00J000A0113/C0S for A319-113 Model -00J000A0114/C0S for A319-114 Model -00J000A0131/C0S for A319-131 Model -00J000A0132/C0S for A319-132 Model -00J000A0115/C0S for A319-115 Model -00J000A0133/C0S for A319-133 Model There is no Type Certificate Standard Equipment List for the A319-151N/-153N/-171N/-173N. Refer to Note 1 for list of A319 airplane model FAA Type Definitions. Import Requirements: A FAA Standard Airworthiness Certificate may be issued based on a German Export Certificate of Airworthiness (Export C of A), signed by a representative of the Luftfahrt -Bundesamt (LBA) of Germany on behalf of the European Community or based on a EASA Export C of A issued by a representative of EASA . The Export C of A should contain the following statement: “The aircraft covered by this certificate has been examined, tested, and found to conform to the Type Design approved under FAA Type Certificate No. A28NM and to be in a condition for safe operation.” Refer to the applicable bilateral agreement to verify eligibility for import into the United States of both new and used airc raft based on the scope of the agreement, to identify any required statements by the exporting authority on the export certificate of airworthiness (or equivalent document), and for procedures for coordinating exceptions to conformity statements on these documents. Refer to FAA Order 8130.2, Airworthiness Certification of Aircraft , for req uirements for issuance of an airworthiness certificate for imported aircraft.” A28NM Page 15 of 103 All models Certification Basis: a. Part 25 of the FAR effective February 1, 1965, including Amendments 25-1 through 25-56 thereto. a.1 Plus the following sections of Part 25 as amended by amendments 25-1 through: -25-58 (Section 25.812(e)) -25-63 (Section 25.25 (a)(3)) -25-67 (Section 25.807 (c)(7)) (Applied per FAA derivative aircraft policy – reference FAA order 8110.4A) a.2 Airbus elected to comply with the following sections of Part FAR 25 through Amendment 86: 25.305(d), 25.321(c)/(d), 25.331(a)/(d), 25.333(a)/(c),25.335(d), 25.341, 25.343 (b)(1)(ii), 25.345(a)/(c), 25.349(b), 25.351(b),25.371, 25.373(a), 25.391(e), 25.427, 25.445(a), 25.571(b)(2)/(b)(3), 25.1517. a.3 Airbus elected to comply with portions of FAR 25.562, Amendment 64, for the passenger seats only. FAR paragraphs 25.562(c)(5), (c)(6) do not apply. b. Based on 14 CFR Section 21.29(a) for new import Type Certificates (TCs), (or Section 21.101(g) for changes to TCs), applicable provisions of 14 CFR Part 26 are included in the certification basis. For any future 14 CFR part 26 amendments, the holder of this TC must demonstrate compliance with the applicable sections. c. 14 CFR Part 34 of the FAR effective Sept. 10, 1990, including amendment 34-1. d. 14 CFR Part 36 of the FAR effective December 1, 1965, including amendments 36-1 through 36-20 thereto. See Note 16. 14 CFR Part 36 through Amendment 36-31, Stage 5 for models; A319-111, A319-112, A319-131, A319- 132. The means of implementation of Stage 5 recertification must be provided by Airbus to ensure availability of the revised AFM noise pages for all affected aircraft. AFM CP293 issue 1.0 dated October 2, 2018 or later revision approved by EASA. e. FAA Special Conditions issued for the A320 in accordance with Section 21.16 of the FAR: (1) No. 25-ANM-23, Effective December 15, 1988: • Electronic Flight Controls • Active Controls • Engine Controls and Monitoring • Protection from Lightning and Unwanted Effects of Radio Frequency (RF) Energy • Flight Characteristics • Flight Envelope Protection • Side Stick Controllers • Flight Recorder. (2) No. 25-ANM-29, Effective May 31, 1989: • Computerized Airplane Flight Manual (3) No. 25-671-SC, Effective May 16, 2017: • Non-Rechargeable Lithium Batteries – Applicable to Type design changes applied after May 16, 2017. Reference the applicability section of this special condition for more information on which Type design changes must meet it. (4) No. 25-729-SC, Effective June 28, 2018: • Electronic System Security Protection from Unauthorized Internal Access - Applicable to type design changes applied after June 28, 2018. (5) No. 25-730-SC, Effective June 28, 2018: • Electronic System Security Protection from Unauthorized External Access - Applicable to type design changes applied after June 28, 2018. f. For precision approach and landing, the applicable technical requirements are complemented by AC 120 -29 and AC 120 - 28c. For the automatic flight control system, the applicable technical req uirements are complemented by AC 20 -57A for automatic landing and by AC 25.1329-1A for cruise. Use of JAR AWO where applicable to the requirements above, is acceptable. A28NM Page 16 of 103 All models g. The following paragraphs of the FAR have been complied with through equivalent safety demonstrations: - 25.101, 25.105, 25.109, 25.113, 25.115, 25.735, for rejected takeoff and landing performance - 25.783(f) for passenger doors - 25.807(c) for maximum passenger capacity - 25.813(c) emergency exit access for a single 13 inch aisle - 25.933(a), 25.1309(b) for thrust reversing system - 25.811(e)(3) Type III emergency exit marking. h. Optional Requirements elected: - 25.801 for ditching - 25.1419 for icing Certification Basis for Airbus Model A319 series airplanes with modification 160500 or 160080 installation of large wingtip device (Sharklet) see note 21: The original certification basis for the Model A319 shown above for components or areas not affected by the change. Plus the following sections of 14 CFR part 25 as amended by Amendments 25-1 through 25-129 (i.e., the amendment in affect on the date of application April 8, 2010) applied to the components and areas affected by the change: 25.23, 25.25, 25.101, 25.109, 25.113, 25.115, 25.117, 25.161, 25.171, 25.173, 25.203, 25.235, 25.251, 25.301, 25.303, 25.305, 25.307(a)(d), 25.321, 25.331, 25.333, 25.335, 25.337, 25.341(a)(b), 25.343, 25.345, 25.349, 25.351, 25.365(a)(b)(d), 25.367, 25.371, 25.373, 25.391, 25.393(b), 25.427, 25.445, 25.457, 25.459, 25.471(a)(b), 25.473, 25.479(a)(c)(d), 25.481(a)(c), 25.483, 25.485, 25.489, 25.581, 25.601, 25.603, 25.605, 25.607, 25.609, 25.613, 25.619, 25.623, 25.625, 25.629, 25.631, 25.651, 25.671, 25.672, 25.683(b), 25.903(d)(1), 25.1011(b), 25.1385(a)(b)(d), 25.1387(a)(b)(c)(d), 25.1389, 25.1391, 25.1393, 25.1395, 25.1397, 25.1401, 25.1505, 25.1511, 25.1515, 25.1517, 25.1527, 25.1533, 25.1535, 25.1581, 25.1585(a) Plus the following sections of 14 CFR part 25 amended as indicated below applied to the components and areas affected by the change per Airbus reversion justification: 25.21 Amdt 1201 25.181 Amdt 1072 25.103 Amdt 1071&2 25.201 Amdt 1072 25.105 Amdt 1201 25.207 Amdt 1071&2 25.107 Amdt 1071&2 25.231 Amdt 1072 25.111 Amdt 1201 25.233 Amdt 1072 25.119 Amdt 1071&2 25.237 Amdt 107 1&2 25.121 Amdt 1071&2 25.253 Amdt 1201 25.123 Amdt 1201 25.571(a)(b)(e) Amdt 863 25.125 Amdt 1071&2 25.981 Amdt 564 25.143 except (g) Amdt 1071&2 25.1001 Amdt 1071 25.143(g) at Amdt 1081 25.1301 Amdt 565 25.145 Amdt 971&2 25.1309 Amdt 565 25.147 Amdt 1072 25.1419 Amdt 561 25.149 Amdt 1072 25.1587 Amdt 1071 25.175 Amdt 1072 Notes: 1. FAA acceptance of these reversions was based on the fact that Airbus has done additional testing above the requirements incorporated by reference as documented in EASA AMC-F14, dated November 29, 1993, Flight in Icing Conditions, and a determination that compliance with the amendment in effect on the date of application for these rules (i.e., Amendment 25-121) would not materially increase the level of safety exception of 14 CFR 21.101(b)(3). EASA AMC-F14 is incorporated as part of certification basis for this airplane. 2. FAA acceptance of these reversions was based on fact that Airbus will show compliance with FAA Special Condition 25-ANM-23 for VSR and a determination that compliance with the amendment in effect on the date of application for these rules (i.e., Amendment 25-108) would not materially increase the level of safety exception of 14 CFR 21.101(b)(3). A28NM Page 17 of 103 All models 3. FAA acceptance of this reversion was based on a determination that compliance with the amendment in affect on the dated of application for this rule (i.e., Amendment 25-96) would not materially increase the level of safety exception of 14 CFR 21.101(b)(3). 4. FAA acceptance of this reversion was based on a determination that compliance with the amendment in effect on the date of application for this rule (i.e., Amendment 25-102) would not materially increase the level of safety exception of 14 CFR 21.101(b)(3). 5. FAA acceptance of this reversion was based on a determination that compliance with the amendment in effect on the date of application for this rule (i.e., Amendment 25-123) would not materially increase the level of safety exception of 14 CFR 21.101(b)(3). Plus the following sections of part 25 amended as indicated below based on Airbus elect to comply: 25.107(e)(1)(iv) Amendment 25-135 25.177 Amendment 25-135 Special conditions: The FAA Special Conditions applicable to each model as defined above remain applicable to aircraft equipped with Sharklet, except Paragraph 2 – Active Controls of FAA Special Condition 25-ANM-23 is replaced with the following special conditions: • No. 25-469-SC Effective October 11, 2012 - “Interaction of Systems and Structures” • No. 25-470-SC Effective October 11, 2012 - “Design Dive Speed” • No. 25-471-SC Effective October 11, 2012 - “Design Roll Maneuver Conditions” Equivalent Safety Findings (ESFs): The original ESFs applicable to each model as defined above remain effective for aircraft equipped with Sharklet plus the following ESF for aircraft equipped with Sharklet: 25.331 – Use of EASA Certification Specification (CS) 25.331 in lieu of 14 CFR 25.331 for checked pitch maneuver (reference ELOS memorandum TD000885IB-T-A-5) 25.1419 – Analysis instead of flight testing in natural icing conditions (reference ELOS memorandum TD00885IB-T-SE-1) Noise standards 14 CFR 21.93(b) – No acoustical change Fuel venting and exhaust emissions standards Not affected by the change. The initial requirements remain applicable. Optional Requirements elected • 25.801 for ditching. • 25.1419 for icing. • 25.1535 for ETOPS Part 26 14 CFR part 26 effective December 10, 2007, including Amendments 26-1 through 26-3. Certification basis for the Airbus Model A319-111, -112, -113, -114, -115, -131, -132 & -133 installed with Wing Tip Fence (WTF) and Modification 157777 (Max Pax), for the certification of a Maximum Passenger Seating Capacity (MPSC) of 150 passengers: The original certification basis for the Model A319-111, -112, -113, -114, -115, -131, -132 and -133 installed with WTF plus the following sections of 14 CFR part 25 as amended by Amendments 25-1 through 25-141 applied to the components and areas affected by the change, equivalent level of safety finding, Optional Design Regulations, 14 CFR part 26, Additional Design Requirements and Conditions: 14 CFR Section FAA Accepted Amendment Level System/Component/Area Affected by the Change 25.23 141 Fuselage Structure 25.321 141 Fuselage Structure 25.331(a)(b)(c)(1) 141 Fuselage Structure 25.341(a) 141 Fuselage Structure A28NM Page 18 of 103 All models 14 CFR Section FAA Accepted Amendment Level System/Component/Area Affected by the Change 25.351 141 Fuselage Structure 25.473 141 Fuselage Structure 25.479(a)(c)(d) 141 Fuselage Structure 25.481(a)(c) 141 Fuselage Structure 25.489 141 Fuselage Structure 25.801(d) 141 Entire Airplane 25.803(c) 141 Cabin Interior 25.807 141 Cabin Interior 25.810 141 Cabin Interior 25.811 141 Cabin Interior 25.813 141 Cabin Interior 25.815 141 Cabin Interior 25.1447(c)(1) 141 Passenger equipment associated with increased MPSC 25.1529 141 ICA associated with increased MPSC 25.1541(a)(b) 141 Marking & Placards associated with increased MPSC 25.1557(a) 141 Marking & Placards associated with increased MPSC The following sections of 14 CFR part 25 amended as indicated below and applied to the components and areas affected by the change, have been determined in accordance with the § 21.101(b)(3) that compliance with the Amendment 25 -141 would not materially increase the level of safety: 14 CFR Section FAA Accepted Amendment Level 25.305(a)(b), 25.307(a), 25.331(c)(2), 25.365(a), 25.341(b), 25.561, 25.571(a)(b), 25.785, 25.787(a)(b), 25.789(a), 25.791, 25.809, 25.812(e)(k)(l), 25.853(a)(b), 25.1301, 25.1309, 25.1351(a), 25.1353(a)(b), 25.1357(a)(c)(e)(g), 25.1359(a)(d), 25.1413, 25.1415(b)(c)(d), 25.1431(c), 25.1561 56 25.562 64 25.853(c)(d)(e) 116 Equivalent Safety Findings: In accordance with the provisions of § 21.21(b)(1) the following new ELOS finding is applicable to Modification 157777 (MaxPax): AT10438IB-T-CS-2 § 25.807 Emergency Exits Finding for Increase of the Maximum Passenger Capacity (MPSC) from 145 passengers to 150 passengers Optional Design Regulations: ETOPS: Modification 157777 (MaxPax) has not been evaluated for extended operations (ETOPS) type design approval on Models A319-111, -112, -113, -114, -115, -131, -132 and -133 airplanes installed with Wing Tip Fence (WTF). Part 26: Based on 14 CFR § 21.101(g), applicable provisions of 14 CFR part 26 are included in the certification basis. For any future 14 CFR part 26 amendments, the holder of this TC must demonstrate compliance with the applicable sections. The type design complies with the following 14 CFR part 26 Amendments 26-1 through 26-6 regulations: §§ 26.11, 26.33, 26.43, and 26.45. Additional Design Requirements and Conditions: A28NM Page 19 of 103 All models Limitation: • The exit passageway width, starting at the aircraft aisle centerline and extending 21 inches outboard from the aircraft aisle centerline, must be a minimum of 23.2 inches. Any attendant seat/fixture installed on the side of the exit passageway must not result in a passageway less than 23.2 inches for the inboard portion of the passageway. The remaining passageway (starting 21 inches from the aircraft centerline to the emergency exit) must be a minimum of 20 inches. The height of the attendant seat/fixture is limited to a maximum height of 56.5 inches. • The unobstructed exit dimensions of the floor level emergency exits must not be less than 32 inches x 73 inches. • A wide slide (sliding surface width 82.75 inches (+3.0 inches, -2.0 inches)) must be installed at doors 1 and 4. • The wide slides installed at doors 1 and 4 must have a beam strength meeting the requirements of TSO C69c. Certification basis for the Airbus Model A319-111, -112, -113, -114, -115, -131, -132 & -133 installed with Wing Tip Fence (WTF) and modification 159535 (Max Pax), for the certification of a Maximum Passenger Seating Capacity (MPSC) of 160 passengers: The original certification basis for the Model A319-111, -112, -113, -114, -115, -131, -132 & -133 plus the following sections of 14 CFR part 25 as amended by Amendments 25-1 through 25-143 applied to the components and areas affected by the change, equivalent level of safety finding, Optional Design Regulations, 14 CFR part 26, Additional Design Requirements and Conditions: 14 CFR Section FAA Accepted Amendment Level System/Component/Area Affected by the Change 25.23 143 Fuselage Structure 25.321 143 Fuselage Structure 25.331(a)(b)(c)(1) 143 Fuselage Structure 25.341(a) 143 Fuselage Structure 25.351 143 Fuselage Structure 25.473 143 Fuselage Structure 25.479(a)(c)(d) 143 Fuselage Structure 25.481(a)(c) 143 Fuselage Structure 25.489 143 Fuselage Structure 25.795(d) 143 Cabin Interior excl lavatories 25.801(d) 143 Entire Airplane 25.803(c) 143 Cabin Interior 25.807(g) 143 Cabin Interior 25.810 143 Cabin Interior 25.815 143 Cabin Interior 25.1447(c)(1) 143 Passenger equipment associated with increased MPSC 25.1519 143 Entire Airplane 25.1529 143 ICA associated with increased MPSC 25.1541(a)(b) 143 Marking & Placards associated with increased MPSC 25.1557(a) 143 Marking & Placards associated with increased MPSC The following sections of 14 CFR part 25 amended as indicated below and applied to the components and areas affected by the change, have been determined in accordance with the § 21.101(b)(3) that comp liance with the Amendment 25 -143 would not materially increase the level of safety: 14 CFR Section FAA Accepted Amendment Level 25.305(a)(b),25.307(a),25.331(c)(2),25.341(b) 25.365(a), 25.561, 25.571(a)(b), 25.785, 25.787(a)(b), 25.789(a), 25.791, 25.809, 25.811, 25.812(e)(k)(l), 25.813, 25.853(a)(b), 25.1301, 25.1309, 25.1351(a), 25.1353(a)(b), 25.1357(a)(c)(g), 25.1359(a)(d), 25.1413, 25.1415(b)(c)(d), 25.1431(c), 25.1561 56 A28NM Page 20 of 103 All models 25.562 64 25.853(c)(d)(e) 116 25.365(a), 25.901(c) 136 Equivalent Safety Findings: In accordance with the provisions of § 21.21(b)(1) the following new ELOS finding is applicable to Modification 159535 (MaxPax): CS-7 § 25.807 Emergency Exits Finding for Increase of the Maximum Passenger Capacity (MPSC) from 145 passengers to 160 passengers Optional Design Regulations: ETOPS: Modification 159535 (MaxPax) has not been evaluated for extended operations (ETOPS) type design approval on Models 319-111, - 112, -113, -114, 115, 131, -132 & 133 airplanes installed with Wing Tip Fence (WTF). Part 26: Based on 14 CFR § 21.101(g), applicable provisions of 14 CFR part 26 are included in the certification basis. For any future 14 CFR part 26 amendments, the holder of this TC must demonstrate compliance with the applicable sections. The type design complies with the following 14 CFR part 26 Amendments 26-1 through 26-6 regulations: §§ 26.11, 26.33, 26.43, and 26.45. Additional Design Requirements and Conditions: Limitation: • The exit passageway width must meet the regulatory minimum of 20 inches. The height of the attendant seat or other assembly is limited to a maximum height of 57 inches. • The unobstructed exit dimensions of the forward and aft most floor level emergency exits must not be less than 32 inches x 73 inches. • A wide slide (sliding surface width 82.75 inches (+3.0 inches, -2.0 inches)) must be installed at the forward and aft most exits. • The wide slides installed at the forward and aft most floor level exits must have a beam strength meeting the requirements of TSO-C69c. Certification basis for the Airbus Model A319-151N/-153N/-171N/-173N (Single Aisle New Engine Option): The certification basis for the Airbus Model A319 series airplanes with Modification 160500 - installation of large wingtip device (Sharklet) for components or areas not affected by the change. Plus the following sections of 14 CFR part 25 as amended by Amendments 25-1 through 25-136 (i.e., the amendment in affect on the date of application) applied to the components and areas affected by the change: 25.3, 25.23(a)(b), 25.25(a)(b), 25.27, 25.101, 25.107(e)(1)(iv), 25.109, 25.113, 25.115, 25.117, 25.147, 25.149, 25.161, 25.171, 25.173, 25.175, 25.177, 25.181, 25.201, 25.203, 25.231, 25.233, 25.235, 25.251(a)(b)(c)(d)(e), 25.253(a)(b), 25.255, 25.301*, 25.303*, 25.305(a)(b)(c)*, 25.307(a)(d)*, 25.321(a)(b)(c)(d), 25.331(a)(b)(c), 25.333(a)(b), 25.335(a)(b)(c)(d)(e)(f), 25.337, 25.341(a)(b), 25.343(a)(b), 25.345(a)(b)(d), 25.349(a)(b), 25.351, 25.361, 25.363, 25.365(a)(b)(c)(d)(e)*, 25.367(a)(b), 25.371, 25.373, 25.391(a)(b)(c)(d)(e), 25.427(a)(b)(c)(d), 25.445(a)(b), 25.457, 25.459, 25.471(a)(b), 25.473, 25.479(a)(c)(d), 25.481(a)(c), 25.483, 25.485(a)(b), 25.489, 25.491, 25.493(b)(c)(d), 25.495, 25.499(a)(b)(c)(d)(e), 25.503(a)(b), 25.507(a)(b)(c), 25.509(a)(c)(d), 25.511, 25.519(a)(b)(c), 25.563, 25.581, 25.601*, 25.603, 25.605, 25.607, 25.609*, 25.613, 25.619*, 25.623*, 25.625, 25.629, 25.631*, 25.651*, 25.671, 25.672(a)(b)(c), 25.683(b), 25.703(a)(b)(c), 25.721(a)(b)(c), 25.777, 25.779(b), 25.789, 25.801, 25.841(a), 25.843(b), 25.851(b), 25.855(c), 25.863 (a)(b)(c)(d), 25.865, 25.867(a)(b)*, 25.869(a)(b)(c), 25.901(a)(b)(c), 25.903, 25.904, 25.933(a), 25.934, 25.939 (a)(c), 25.943, 25.951(a)(b)(c)(d)*, 25.952(a)(b), 25.954, 25.955(a), 25.959, 25.961, 25.963(a)(d), 25.969, 25.971, 25.975, 25.981 except 25.981(a)(3)**, 25.993(a)(b)(c)(d)(e), 25.994, 25.995, 25.997(a)(b)(c)(d), 25.999(a)(b), 25.1001, 25.1011(a)(b), 25.1013(a)(b)(c)(d)(e)(f), 25.1015(a)(b), 25.1017(a)(b), 25.1019(a), 25.1021(a)(b), 25.1023(a)(b), 25.1025(a)(c), 25.1041, 25.1043(a)(b)(c), 25.1045(a)(b)(c), 25.1091(a)(b)(c)(d)(e), 25.1093(b), 25.1103(b)(c)(d), 25.1121, 25.1123, 25.1141, 25.1143, 25.1145, 25.1155, 25.1163, 25.1165, 25.1167, 25.1181, 25.1182, 25.1183, 25.1185, 25.1187, 25.1189, 25.1191, 25.1193, 25.1195, 25.1197, 25.1199, 25.1201, 25.1203, 25.1207, 25.1301*, 25.1305, 25.1309*, 25.1316, 25.1317, 25.1337, 25.1353(a)(b)*, 25.1355(c), 25.1357(a)*, 25.1363, 25.1401(b), 25.1403, 25.1431*, 25.1438, 25.1461, 25.1501, 25.1503, 25.1507, 25.1511, 25.1513, 25.1515, 25.1517, 25.1519, 25.1521(a)(c)(d), 25.1525, 25.1527, 25.1529, 25.1531, 25.1533, 25.1535*, 25.1549(a)(b)(c), 25.1553, 25.1581, 25.1583, 25.1585, 25.1587, 25.1591, A28NM Page 21 of 103 All models 25.1701(a)*, 25.1703(a)(b)(d)*, 25.1705*, 25.1707*, 25.1709*, 25.1711*, 25.1713*, 25.1715*, 25.1717*, 25.1719*, 25.1723*, 25.1725*, 25.1727*, 25.1731* * For new and modified parts only (engine, pylon, nacelle, bleed air system, wing structural changes in area of pylon and landing gear reinforcement) ** FAA acceptance of this exception is for the Fuel Quantity Indicating System (FQIS) and Fuel Level Sensor System (FLSS) wiring installation changes and fuel tank structural fastener changes only and is based on the following design features incorporated on the NEO: The FQIS/FLSS wiring is within the S-routes in pressurized areas and is isolated with protective textile sleeving with CAUTION, FUEL TANK HARNESS ONLY" labels. The FQIS/FLSS wiring is within the S-routes in non-pressurized areas and is isolated with protective heat shrink sleeving and routed with the rest of the S-route bundle in PTFE conduit up to fuel tank walls penetration with "CAUTION, FUEL TANK HARNESS INSIDE" labels. Wiring production breaks from Avionic bays to the tank walls is done through dedicated connectors. The fuel tank structural fastener changes meet the criteria for the use of exceptions in FAA policy ANM-112-08-002 “Policy on Issuance of Special Conditions and Exemptions Related to Lightning Protection of Fuel Tank Structure,” dated May 26, 2009. Plus the following sections of 14 CFR part 25 amended as indicated below applied to the components and areas affected by the change per Airbus reversion justification: 25.21 Amdt. 1201 25.561(a)(b)(c)(d) Amdt. 642 25.103 Amdt. 1201 25.571(a)(b)(e)(1) Amdt. 863 25.105 Amdt. 1201 25.611 Amdt. 564 25.107 (except (e)(1)(iv)) Amdt 1201 25.677(b) Amdt. 565 25.111 Amdt. 1201 25.899 Amdt. 566 25.119 Amdt. 1201 25.1317 Amdt. 567 25.121 Amdt. 1201 25.1322 Amdt. 568 25.123 Amdt. 1201 25.1329 Amdt. 569 25.125 Amdt. 1201 25.1351 Amdt. 5610 25.143 Amdt. 1201 25.1419 Amdt. 1201 25.145 Amdt. 971 25.1435 Amdt. 5611 25.207 Amdt. 1201 25.1459(a) Amdt. 5612 25.237 Amdt. 1201 Appendix H at amdt 5613 25.253(c) Amdt. 1201 Notes: 1. FAA acceptance of these reversions was based on the fact that Airbus has done additional testing above the requirements incorporated by reference as documented in the summary of EASA CRI B-06, issue 2, dated April 11, 2013, Flight in Icing Conditions, and a determination that compliance with the amendment in effect on the date of application for these rules (i.e., Amendment 25-121) would not materially increase the level of safety exception, or in some cases, would be impractical in accordance with 14 CFR 21.101(b)(3). EASA CRI B-06 is incorporated as part of the certification basis for this airplane. 2. FAA acceptance of this reversion was based on a determination that compliance with the amendment in effect on the date of application for this rule (i.e., Amendment 25-91) would not materially increase the level of safety in accordance with14 CFR 21.101(b)(3). 3. FAA acceptance of this reversion was based on a determination that compliance with the amendment in effect on the date of application for this rule (i.e., Amendment 25-132) would not materially increase the level of safety in accordance with14 CFR 21.101(b)(3). 4. FAA acceptance of this reversion was based on a determination that compliance with the amendment in effect on the date of application for this rule (i.e., Amendment 25-123) would not materially increase the level of safety in accordance with 14 CFR 21.101(b)(3). 5. FAA acceptance of this reversion was based on a determination that the changes in this area are considered secondary and compliance with the amendment in effect on the date of application for this rule (i.e., Amendment 25-115) would not materially increase the level of safety in accordance with 14 CFR 21.101(b)(3). A28NM Page 22 of 103 All models 6. FAA acceptance of this reversion was based on a determination that changes in this area are considered secondary and compliance with the amendment in effect on the date of application for this rule (i.e., Amendment 25-123) would not materially increase the level of safety in accordance with 14 CFR 21.101(b)(3). 7. FAA acceptance of this reversion was based on a determination that the changes in this area are considered secondary and compliance with the amendment in effect on the date of application for this rule (i.e., Amendment 25-122) would not materially increase the level of safety above Special Condition 25-ANM-23 in accordance with 14 CFR 21.101(b)(3). 8. FAA acceptance of this reversion was based on a determination that compliance with the amendment in effect on the date of application for this rule (i.e., Amendment 25-131) would be impractical in accordance with 14 CFR 21.101(b)(3). 9. FAA acceptance of this reversion was based on a determination that changes in this area are considered secondary and compliance with the amendment in effect on the date of application for this rule (i.e., Amendment 25-119) would not materially increase the level of safety in accordance with 14 CFR 21.101(b)(3). 10. FAA acceptance of this reversion was based on a determination that the changes in this area are considered secondary and compliance with the amendment in effect on the date of application for this rule (i.e., Amendment 25-72) would not materially increase the level of safety in accordance with 14 CFR 21.101(b)(3). 11. FAA acceptance of this reversion was based on a determination that changes in this area are considered secondary and compliance with the amendment in effect on the date of application for this rule (i.e., Amendment 25-104) would not materially increase the level of safety in accordance with 14 CFR 21.101(b)(3). 12. FAA acceptance of this reversion was based on a determination that changes in this area are considered secondary and compliance with the amendment in effect on the date of application for this rule (i.e., Amendment 25-124) would not materially increase the level of safety in accordance with 14 CFR 21.101(b)(3). 13. FAA acceptance of this reversion was based on a determination that compliance with the amendment in effect on the date of application for this rule (i.e., Amendment 25-123) would not materially increase the level of safety in accordance with 14 CFR 21.101(b)(3). Plus the following sections of 14 CFR part 25 amended as indicated below per Airbus elect to comply: 25.853(a)(1) at Amendment 25-66 25.853(c) at Amendment 25-59 Special conditions: FAA Special Condition 25-ANM-23 applicable to each model as defined in FAA TCDS A28NM remains applicable, except: Paragraph 2 – Active Controls is replaced with the following special conditions: • No. 25-469-SC Effective October 11, 2012 - “Interaction of Systems and Structures” • No. 25-470-SC Effective October 11, 2012 - “Design Dive Speed” • No. 25-471-SC Effective October 11, 2010- “Design Roll Maneuver Conditions” Paragraph 4 – Protection from Lightning and Unwanted Effects of Radio Frequency is replaced with the following later requirements: • 25.1316 thru amendment 25-136 • 25.1317 thru amendment 25-136 In addition the following FAA Special Condition applies specifically to the Airbus SA NEO program: • Non. 25-582-SC Effective April 30, 2015 - “Transient Engine Failure Loads” Equivalent Safety Findings (ESFs): The ESFs applicable to each model as defined in FAA TCDS A28NM remain applicable plus the following ESFs applied specifically to the Airbus SA NEO program: ELOS Memo Regulation Subject AT00949IB-T-P-10 25.779(b)(1) Throttle Motion During Reduced (Flexible) Takeoff Thrust Operations and/or Go-Around AT00949IB-T-P-11 25.1549(a), (b) and (c) Digital Display of High Pressure Rotor Speed (N2) AT00949IB-T-P-12 25.1549(a) Oil Temperature Indication AT00949IB-T-P-1 25.997(d) & 25.1305(c)(6) Fuel Filter Bypass Indication AT00949IB-T-P-14 25.1193(e)(3) Resistance to Fire of Cowling A28NM Page 23 of 103 All models AT00949IB-T-P-15 25.1181(a)(6) & (b), & 25.1195 thru 25.1203 Fan Zone Non-fire Zone (PW only) AT00949IB-T-P-17 25.933(a)(1)(ii) Flight Critical Thrust Reverser AT00949IB-T-P-19 25.934 Thrust Reverser Testing AT00949IB-T-P-21 25.1181(a)(6) & (b), 25.1182 and 25.1195 through 25.1203 PW1100G-JM 2.5 Bleed & Track lock Areas and PW1100G-JM and LEAP-1A Areas Adjacent to Designated Fire Zones AT00949IB-T-SA-1 25.1301 and 25.1309 Equipment, Systems, and Installation Requirements: Use of ARAC Recommendations Exemptions: The Exemptions applicable to each model as defined in TCDS A28NM remain applicable plus the following exemption applied specifically to the Airbus SA NEO models: Exemption No. 13048 for 25.841(a) dated September 25, 2015 (13048A dated February 22, 2018, 13048B dated March 6, 2019.) Optional Requirements elected • § 25.801 for ditching. • § 25.1419 for icing. • § 25.1535 for ETOPS Noise standards 14 CFR part 36 Stage 4 as amended by Amendment 36-1 through Amendment 36-30. 14 CFR part 36 Amendments 36-1 through Amendment 36-31, for Stage 5, for the following models: A319-111, A319-112, A391-131, A319-132, and A319-133. The means of implementation of Stage 5 recertification must be provided by Airbus to ensure availability of the revised AFM noise pages for all affected aircraft. AFM CP293 issue 1.0 dated October 2, 2018 or later revision approved by EASA. Fuel venting and exhaust emissions standards 14 CFR part 34 as amended by Amendment 34-1 through 34-5. Part 26 14 CFR part 26 as amended by Amendment 26-1 through 26-5. Additional Design Requirements and Conditions Compliance with the established basis for type certification notwithstanding, § 21.21(b)(2) precludes issuance of a type certificate if there is any feature or characteristic that would make the product unsafe. The following design details or information must be maintained to ensure that an unsafe design condition is not present: In-flight Engine Restart 1. A minimum restart capability after an all engines out scenario must be established under the following conditions using procedures provided in the airplane flight manual (AFM): a) During the take-off and the initial climb-out portion of the flight, the airplane should have the capability for the flightcrew to restore engine power when the fuel source to the engine is interrupted. b) During the high altitude portion of the flight at cruise speed and maximum altitude, the airplane should have the capability for the flightcrew to restart from a stabilized windmill speed those engines required to maintain level flight or should have the capability for the flightcrew to restart all but one of the engines and produce maximum continuous thrust or power by an altitude of 15 000 feet. c) During flight at speeds greater than the minimum flaps-up “holding speed” and at altitudes below 20 000 feet, the airplane should have the capability for the flightcrew to restart with the engines at stabilized windmill speed those engines necessary to maintain safe flight and arrest the airplane descent within a total altitude loss of 5 000 feet prior to exceeding an airspeed of 300 knots. Certification basis for the Airbus Model A319-151N, -153N & -171N installed with modification 159533 (Max Pax), for the certification of a Maximum Passenger Seating Capacity (MPSC) of 160 passengers: The original certification basis for the Model A319-151N, -153N & -171N plus the following sections of 14 CFR part 25 as amended by Amendments 25-1 through 25-143 applied to the components and areas affected by the change, equivalent level of safety finding, Optional Design Regulations, 14 CFR part 26, Additional Design Requirements and Conditions: A28NM Page 24 of 103 All models 14 CFR Section FAA Accepted Amendment Level System/Component/Area Affected by the Change 25.23 143 Fuselage Structure 25.321 143 Fuselage Structure 25.331(a)(b)(c)(1) 143 Fuselage Structure 25.341(a) 143 Fuselage Structure 25.351 143 Fuselage Structure 25.473 143 Fuselage Structure 25.479(a)(c)(d) 143 Fuselage Structure 25.481(a)(c) 143 Fuselage Structure 25.489 143 Fuselage Structure 25.795(d) 143 Cabin Interior excl lavatories 25.801(d) 143 Entire Airplane 25.803(c) 143 Cabin Interior 25.807(g) 143 Cabin Interior 25.810 143 Cabin Interior 25.815 143 Cabin Interior 25.1447(c)(1) 143 Passenger equipment associated with increased MPSC 25.1519 143 Entire Airplane 25.1529 143 ICA associated with increased MPSC 25.1541(a)(b) 143 Marking & Placards associated with increased MPSC 25.1557(a) 143 Marking & Placards associated with increased MPSC The following sections of 14 CFR part 25 amended as indicated below and applied to the components and areas affected by the change, have been determined in accordance with the § 21.101(b)(3) that comp liance with the Amendment 25 -143 would not materially increase the level of safety: 14 CFR Section FAA Accepted Amendment Level 25.305(a)(b),25.307(a),25.331(c)(2),25.341(b) 25.365(a), 25.561, 25.571(a)(b), 25.785, 25.787(a)(b), 25.789(a), 25.791, 25.809, 25.811, 25.812(e)(k)(l), 25.813, 25.853(a)(b), 25.1301, 25.1309, 25.1351(a), 25.1353(a)(b), 25.1357(a)(c)(g), 25.1359(a)(d), 25.1413, 25.1415(b)(c)(d), 25.1431(c), 25.1561 56 25.562 64 25.853(c)(d)(e) 116 25.365(a), 25.901(c) 136 Equivalent Safety Findings: In accordance with the provisions of § 21.21(b)(1) the following new ELOS finding is applicable to Modification 159533 (MaxPax): CS-7 § 25.807 Emergency Exits Finding for Increase of the Maximum Passenger Capacity (MPSC) from 145 passengers to 160 passengers Optional Design Regulations: ETOPS: Modification 159533 (MaxPax) has not been evaluated for extended operations (ETOPS) type design approval on Models A319- 153N airplanes. A28NM Page 25 of 103 All models Part 26: Based on 14 CFR § 21.101(g), applicable provisions of 14 CFR part 26 are included in the certification basis. For any future 14 CFR part 26 amendments, the holder of this TC must demonstrate compliance with the applicable sections. The type design complies with the following 14 CFR part 26 Amendments 26-1 through 26-6 regulations: §§ 26.11, 26.33, 26.43, and 26.45. Additional Design Requirements and Conditions: Limitation: • The exit passageway width must meet the regulatory minimum of 20 inches. The height of the attendant seat or other assembly is limited to a maximum height of 57 inches. • The unobstructed exit dimensions of the forward and aft most floor level emergency exits must not be less than 32 inches x 73 inches. • A wide slide (sliding surface width 82.75 inches (+3.0 inches, -2.0 inches)) must be installed at the forward and aft most exits. • The wide slides installed at the forward and aft most floor level exits must have a beam strength meeting the requirements of TSO-C69c. Note 1: The A319 basic type design definition for U.S. import certification is contained in the following documents: -AI/EA-S 413.0969/96 for A319-111 model -AI/EA-S 413.1012/96 for A319-112 model -AI/EA-S 413.3100/96 (Mod 25699 supplement) for A319-112 model -AI/EA-S 413.2504/96 for A319-113 model -AI/EA-S 413.2505/96 for A319-114 model -AI/EA-S 413.2127/99 for A319-115 model -AI/EA-S 413.0393/97 for A319-131 model -AI/EA-S 413.0396/97 for A319-132 model -AI/EA-S 413.2128/99 for A319-133 model - 00J000A5074/C20 iss 01 for A319-151N model - 00J000A5242/C00 iss 01 for A319-153N model - 00J000A5071/C20 iss 01 for A319-171N model - 00J000A5294/C20 iss 01 for A319-173N model Note 2: For models A319-111, A319-112, A319-113 and A319-114, modification 26799 (FM without ACARS) or 26968 (FM with ACARS) is the minimum standard to be qualified for Cat IIIB precision approach. For models A319-131 and A319-132, modification 26716 (FM without ACARS) or 26717 (FM with ACARS) is the minimum standard to be qualified for Cat IIIB precision approach. A319-115 &A319-133 are basically qualified for Cat IIIB precision approach. This does not constitute operational approval. Note 3: Modification 25303 (thrust reverser third line of defense for CFM 56 engine) or 25302 (thrust reverser third line of defense for IAE engine) are part of the FAA Type Design and shall be implemented on any A319 aircraft entered on the U.S. register, before the individual U.S. standard Certificate of Airworthiness can be issued. Note 4: If modification 25800 is embodied on models with CFM56-5B engines, the engine performance is improved. The engine denomination changes to /P. CFM56-5B/”non-P” engine can be intermixed with CFM56-5B/P engine on the same aircraft. Note 5: The type design definitions and certification standard equipment lists as referenced in Note 1 are complemented by document 00D000A0546/C0S “A319-100/A321-200 FMGC Type Standard Evolution” and document 00J000A0067/C0S “A319-111/112 ATC Transponder Type Standard Evolution”. Note 6: A319 for Corporate Jet use are defined through the following set of modifications: - Modification 28238 (0 to 6 ACTs) - Modification 28162 (extension of flight envelope up to 41 000 ft) - Modification 28342 (modification of CG limits) A28NM Page 26 of 103 All models Note 7: On A319 for Corporate Jet use, the certification of installing up to six Additional Center Tanks (ACT) in bulk version is defined by modification 28238. The approval together with structural and system provisions was subject of compliance demonstrated to Advisory Circular AC 25-8. Note 8: On A319 for Corporate Jet use, exemptions to the following paragraphs of the FAR have been granted when the airplane is not operated for hire or for public transport (Granted APR 9, 2001, Exemption No. 7489): 25.785(h)(2) Flight Attendant seat locations which do not provide for direct view of the cabin 25.807(d)(7) Distance between exits 25.813(e) Installation of Interior Doors in between passenger compartments Note 9: If modification 26610 is embodied on A319 airplanes, the engine performance and gaseous emission levels are improved. The engine denomination changes to /2P (DAC IIC Dual Annual Combustor). • CFM56-5B6/P engine can be intermixed with CFM56-5B6/2P (DAC IIC Dual Annual Combustor) engine on the same aircraft (AFM Supplement). • CFM 56-5B/2 "non P" (DAC) engine can be intermixed with CFM 56-5B/2P (DAC II C) engine on the same aircraft (AFM supplement). • CFM 56-5B/P or / "non P" (SAC) engine can be intermixed with CFM 56-5B/2P (DAC II C) engine on the same aircraft (AFM supplement). Note 10: If modification 23755 is embodied on A319 airplanes, the maximum permissible gas temperature for take-off and max. continuous operation is extended to 915° C and 880° C, respectively. However, the ECAM indication remains at 890° C and 855° C, respectively. The engine denomination changes to /F. On A319-113, CFM 56-5A4 engines can be intermixed with CFM 56-5A4/F engine on the same aircraft. On A319-114, CFM 56-5A5 engines can be intermixed with CFM 56-5A5/F engine on the same aircraft. Note 11: If modification 32208 is embodied in production on A319 airplanes, the aircraft is eligible for maximum capacity of 160 passengers. This modification consists in structural and system provision for the installation of second pair of overwing emergency exits. Note 12: If modification 37147 (Tech insertion program) is embodied in production or 38770 (Tech insertion program retrofit) is embodied in service on A319 airplanes, the engine performance and gaseous emission levels are improved. The engine denomination changes to /3 Note 13: If modification 37868 (Select One Package) is embodied in production or if modification 38554 (Select One Package for retrofit) is embodied on in-service A319 airplanes, the engine performance and gaseous emission levels are improved. The engine denomination itself does not change. Note 14: If modification 38573 is embodied in service on A319 airplanes, engine hardware configurations can be intermixed with one CFM56-5Bx/3 SAC (Tech Insertion) and one CFM56-5Bx/P SAC engine. Note 15: If modification 34119 is embodied in production on A319 airplanes, CFM56-5B SAC (Single Annular Combustor) and CFM56-5B DAC (Double Annular Combustor) engines can be intermixed on the same aircraft. Note 16: Further to “D/E/J Noise” Project approval, from November, 05th, 2009, all A319 airplane/engine configurations are eligible to be in compliance with ICAO Annex 16, Chapter 4 and FAR Part 36, Stage 4 (including Amdt 36-28). Note 17: From March 31, 2008, there is no longer any CFM56-5B5 non /P in field or in production. From March 31, 2008, there is no longer any CFM56-5B6 non /P in field or in production. From March 31, 2008, there is no longer any CFM56-5B7 non /P in field or in production. Note 18: For aircraft models A319-115, A319-132 and A319-133, the Type III emergency exit hatches can be de-activated by embodiment of modification 152777. In this case, the maximum number of occupants in the passenger cabin is limited to zero during taxi, take-off, flight and landing, unless terms and conditions to occupy specific cabin areas have been approved by operator's competent airworthiness authority A28NM Page 27 of 103 All models Note 19: On series A319-100 airplanes equipped with CFM56 engines, introduction of a standard of wingbox without dry bay (modification 37331) increases the wing fuel capacity by 350 liters. Note 20: If Modification 160001 for installation of structural provisions for new large wingtip device (Sharklet) is embodied on A319 series airplanes the usable fuel quantities are reduced as shown above to account for the loss of volume due to structural reinforcements in the wing and center wing box. Note 21: If Modification 160500 for installation of new large wingtip devices (Sharklet) is embodied on A319 series airplanes the eco efficiency and payload-range performance is improved. MOD 160500 is approved for weight variants 000 through 005 on the A319- 111,-112,-113,-114,-115,-131,-132,-133. If modification 160080 for retrofit installation of new large wingtip devices (Sharklet) is embodied on in-service A319 series airplanes the eco efficiency and payload-range performance is improved. Modification 160080 is approved for MSN 1200 and above only without Airbus Modification 160001 reinforced center wingbox, and for WV 000 to 005 only. The certification basis for Modification 160500 and 160080 is shown above. Note 22: If Modification 157777 (MAX PAX) is installed on Models A319-111, -112, -113, -114, -115, -131, -132 and -133 with Wing Tip Fence (WTF), the airplane is eligible for Maximum Passenger Seating Capacity (MPSC) of 150 passengers. Note 23: Limitations associated with installation of MAX PAX Modification 159115 are referenced in ELOS Memo AT10769IB -T-CS-6 dated May 16, 2017. Note 24: If Modification 159535 (MAX PAX) is installed on Models A319-111, -112, -113, -114, -115, -131, -132 and -133 with Wing Tip Fence (WTF), the airplane is eligible for Maximum Passenger Seating Capacity (MPSC) of 160 passengers. Note 25: For A319-111,-112,-113,-114,-115,-131,-132,-133 models, the embodiment of modification 155789 leads to change the maintenance program and its associated Maintenance Programme Publication Trigger from 48 000FC/60 000FH to 60 000FC/120 000FH (whichever occurs first). Note 26: If modification 167900 is installed on A319-111, -112, -113, -114, -115, -131, -132, and -133 models, the forward over-wing emergency exits are deactivated. The maximum number of occupants in the cabin is then limited to 0 (zero) unless a separate approved modification is embodied to remove the limitation. Note 27: If Modification 159533 is installed on Model A319-151N, -153N & -171N, the airplane is eligible for Maximum Passenger Seating Capacity (MPSC) of 160 passengers. Note 28: Serial Numbers Eligible: Until September 26, 2004, A319 aircraft, all series, all models, have been produced in Hamburg (Germany) under approval LBA.G.0009 or I-A9 issued by LBA to Airbus. From September 27, 2004 until July 20, 2008, A319 aircraft, all series, all models, have been produced in Hamburg (Germany) under approval DE.21G.0009 issued by LBA to Airbus. From July 21, 2008 until May 5, 2009, A319 aircraft, all series, all models, have been produced in Hamburg (Germany) under approval EASA.21G.0001 issued by EASA to Airbus. Since May 6, 2009 to April 30, 2011, All A319 aircraft, all series, all models, are produced in Hamburg (Germany) or Tianjin (People’s Republic of China) under approval EASA.21G.0001 issued by EASA to Airbus. Since May 1, 2011 and in accordance with the TIP, “Technical Implementing Procedure for Airworthiness and Environmental Certification Between the Federal Aviation Administration of the United States of America and the European Union Aviation Safety Agency”, A319 aircraft, all series, all models, produced under approval EASA.21.G.0001 issued by EASA to Airbus are eligible, unless otherwise stated in this TCDS. A28NM Page 28 of 103 All models III. Type A320-200 Series Transport Category Airplanes * Model A320-211, Approved December 15, 1988; Model A320-231, Approved July 6, 1989; Model A320-212, Approved November 26, 1990; Model A320-232, Approved November 12, 1993; Model A320-233, Approved November 17, 1995; Model A320-214, Approved December 12, 1996. Model A320-271N, Approved November 24, 2015 Model A320-251N, Approved May 31, 2016 Model A320-216, Approved December 19, 2016 Model A320-252N. Approved February 21, 2018 Model A320-272N. Approved April 4, 2019 Model A320-253N, Approved May 9, 2019 Model A320-273N, Approved May 9, 2019 Engines: Model A320-211, Two CFMI Model CFM56-5A1 or CFM56-5A1/F jet engines; Model A320-212, Two CFMI Model CFM56-5A3 jet engines; Model A320-214, Two CFMI Model CFM56-5B4 or CFM56-5B4/P or CFM56-5B4/2P or CFM56-5B4/P1 or CFM56-5B4/2P1 or CFM56-5B4/3 or CFM56-5B4/3B1 or jet engines; Model A320-231, Two IAE Model V2500-A1 jet engines; Model A320-232, Two IAE Model V2527–A5 jet engines; Model A320-233, Two IAE Model V2527E–A5 jet engines; Model A320-271N, Two IAE Model PW1127G-JM or PW1127GA-JM or PW1127G1A-JM Alt Climb C jet engines; Model A320-251N, Two CFMI Model LEAP-1A26 jet engines Model A320-216, Two CFMI CFM 56-5B6/P or CFM56-5B6/3 jet engines Model A320-252N, Two CFMI Model LEAP-1A24 jet engines Model A320-272N, Two IAE Model PW1124G1-JM jet engines Model A320-253N, Two CFMI Model LEAP-1A29 jet engines Model A320-273N, Two IAE Model PW1129G-JM jet engines See Note 4 for description of “/P” engine models See Note 5 for description of “/2P” engine models See Note 7 for description of “/F” engine models See Note 11 for description of “/3” engine models See Note 12 for description of “ “ engine models (Select One Package) See Note 19 for description of “/P1” or “/2P1” or “/3B1” engine models Fuel: See Installation Manual - Documents CFM 2026 or CFM 2129 or Service Bulletin 73-0001 or IAE-0043 or Service Bulletin PW1000G-1000-73-00-0002 00A930AD A320-211/-212/-214/-216/-231/-232/-233 TYPE SPECIFICATION (NAME) FRANCE USA UK Kerosene DCSEA 134-D (F-34) ASTM D 1655 (JET A) (JET A1) DEF STAN 91/91 (AVTUR) (JET A1) MIL-DTL- 83133-H (JP 8) DEF STAN 91/87 iss 7 (AVTUR/FSH) (JET A1) (AIA) Wide cut ASTM D 6615 (JET B) DEF STAN 91/88 (AVTAG/FSH) MIL-DTL-5624 (JP 4) High flash point DCSEA 144-C (F-44) MIL-DTL- 5624-V (JP 5) DEF STAN 91/86 iss 7 (AVCAT) A28NM Page 29 of 103 All models A320-251N/-252N/-253N/-271N/-272N/-273N TYPE SPECIFICATION (NAME) USA UK Kerosene ASTM D 1655 (JET A) (JET A1) DEF STAN 91/91 (AVTUR) (JET A1) MIL-DTL- 83133-H (JP 8) DEF STAN 91/87 iss 7 (AVTUR/FSII) (JET A1) (AIA) High flash point MIL-DTL-5624- V (JP 5) DEF STAN 91/86 iss 7 (AVCAT) Additives: See CFMI " Specific Operating Instructions," CMF TPOI-13 or Service Bulletin 73-0001 or IAE V2500 “Installation and Operating Manual” IAE-0043, 4.5 or the “Standard Practices and Processes Manual” in IETM or Service Bulletin PW1000G-1000- 73-00-0002-00A-930A-D. The above mentioned fuels and additives are also suitable for the APU. Engine Limits: CFMI CFM56-5A1 CFMI CFM56- 5A1/F CFMI CFM56-5A3 CFMI CFM56- 5B4*** or -5B4/P or 5B4/2P or -5B4/P1 or 5B4/2P1 or -5B4/3 or 5B4/3B1 CFMI CFM56 - 5B6/P *** or -5B6/3 IAE V2500-A1 Engine Limitation Data Sheets Data Sheets Data Sheets Data Sheets FAA Data Sheets Data Sheets E28NE (FAA) E28NE (FAA) E28NE (FAA) E37NE (FAA) E38NE (FAA) E37NE E38NE E31NE (FAA) Static Thrust at Sea Level - Take-off (5 min)** (Flat rated 30°C) 11 120 daN (25 000 lb) 11 120 daN (25 000 lb) 11 787 daN (26 500 lb) 12 010 daN (27 000 lb) 10 453 daN (23 500 lb) 11 030 daN (24 800 lb) - Maximum Continuous (Flat rated 25°C) 10 542 daN (23 600 lb) 10 542 daN (23 600 lb) 10 542 daN (23 600 lb) 10 840daN (24 370 lb) 9 008 daN (20 250 1b) 9 890 daN (22 240lb) Maximum Engine Speed - N1 rpm (%) 5 100 (102) 5 100 (102) 5 100 (102) 5 200 (104) 5 200 (104) 5 465 (100) - N2 rpm (%) 15 183(105) 15 183(105) 15 183(105) 15 183(105) 15 183 (105) 14 915(100) Eng. limit/ Eng. limit/ Max Gas Temp.(°C) ECAM ECAM - Take-off (5 min)** 890 915/890 915/890 950 950 635 - Max Continuous 855 880/855 880/855 915 915 610 - Starting* 725 725/725 725/725 725 725 635 Maximum Oil Temp. (Supply Pump Inlet; °C) -Takeoff, Stabilized 140 140 140 140 140 155 -Transient (15 min max) 155 155 155 155 155 165 Min. Press. (PSI) 13 13 13 13 13 60 Approved oils See SB See SB See SB See SB See SB See doc IAE CFMI 79-001- 0X CFMI 79-001- 0X CFMI 79-001- 0X CFMI 79-001-0X CFMI 79- 001-0X 0043 (MIL-L 23699) * 4 consecutive cycles of 2 minutes each. ** 10 minute at take-off thrust allowed in case of engine failure (at take-off and during go-around) A28NM Page 30 of 103 All models *** See Note 17 for engine models no longer in production/service Engine Limits Continued: Engine Limitation IAE V2527-A5 or V2527E-A5 Data Sheet E40NE (FAA) PW1127G-JM or PW1127GA-JM or PW1127G1A- JM Alt Climb C Data Sheet E00087EN (FAA) PW1124G1-JM Data Sheet E00087EN (FAA) CFMI LEAP- 1A26 Data Sheet E00089EN (FAA) CFMI LEAP- 1A24 Data Sheet E00089EN (FAA) Static Thrust at Sea Level - Take-off (5 min)** (Flat rated 30°C) 11 030 daN (24 800 lb) 12 043 daN (27 075lb) 10 782 daN (24 240lb) 12 064 daN (27 120lb) 10 680 daN (24 010lb) - Maximum Continuous (Flat rated 25°C) 9 890 daN (22 240lb) 11 718 daN (26 345lb) 10 691 daN (24 035lb) 11 868 daN (26 680lb) 10 676daN (24 000lb) Maximum Engine Speed - N1 rpm (%) 5 650 (100) 10 047 (105) 10 047(105) 3 894(101) 3 894(101) - N2 rpm (%) 14 950 (100) 22 300 (105) 22 300 (105) 19 391 (116.5) 19 391 (116.5) Eng. limit/ Max Gas Temp.(°C) ECAM - Take-off (5 min)** 645/635 1083 1083 1060 1060 - Max Continuous 610/610 1043 1043 1025 1025 - Starting* 635/635 1083 1083 875 875 Maximum Oil Temp. (Supply Pump Inlet; °C) -Takeoff, Stabilized 155 152 152 140 140 -Transient (15 min max) 165 141 141 155 155 Min. Press. (PSI) 60 63 63 29 redline/17.4 idle 29 redline/17.4 idle Approved oils See doc IAE See SB See SB See SB 79-0001 See SB 79-0001 0043 (MIL-L 23699) PW1000G-1000- 79-00-0002-00A- 930A-D PW1000G-1000- 79-00-0002-00A- 930A-D ** 10 minute at take-off thrust allowed in case of engine failure (at take-off and during go-around) Engine Limits Continued: Engine Limitation PW1129G-JM Data Sheet E00087EN (FAA) CFMI LEAP-1A29 Data Sheet E00089EN (FAA) Static Thrust at Sea Level - Take-off (5 min)** (Flat rated 30°C) 13 000 daN (29 245 lbs) 13 029 daN (29 290 lbs) - Maximum Continuous (Flat rated 25°C) 11 719 daN (26 345 lbs) 11 868 daN (26 680 lbs) Maximum Engine Speed - N1 rpm (%) 10 047 (105) 3 894 - N2 rpm (%) 22 300 (105) 19 391 Eng. limit/ Max Gas Temp.(°C) Take-off (5 min)** 1083 1060 - Max Continuous 1043 1025 - Starting* 1083 875 A28NM Page 31 of 103 All models Engine Limitation PW1129G-JM Data Sheet E00087EN (FAA) CFMI LEAP-1A29 Data Sheet E00089EN (FAA) Maximum Oil Temp. (Supply Pump Inlet; °C) -Takeoff, Stabilized 152 140 -Transient (15 min max) 141 155 Min. Press. (PSI) 63 29 redline/17.4 idle Approved oils See SB See SB 79-0001 PW1000G-1000- 79-00-0002-00A- 930A-D ** 10 minute at take-off thrust allowed in case of engine failure (at take-off and during go-around) Airspeed Limits (Indicated Airspeed - IAS - Unless otherwise Stated: - Maximum Operating Mach - MMO: 0.82 - Maximum Operating Speed - VMO: 350 kt - Maneuvering Speed VA: - See Limitations Section of Aircraft Flight Manual - Extended Flaps/Slats Speed - VFE Configuration Slats/Flaps VFE (Kt) 1 18/0 230 Intermediate Approach *18/10 215 Take-off 2 22/15 200 Take-off and Approach 3 22/20 185 Take-off, Approach, and Landing Full **27/35 177 Landing * Auto flap retraction at 210 kt in Take-off configuration. **27/40 for A320 equipped with IAE engines or CFMI LEAP-1A engines Landing Gear: - VLE - Extended 280 Kt/Mach 0.67 - VLO - Extension 250 kt - Retraction 220 kt Tire Limit Speed (Ground Speed) = 195.5 kt (225 mph) Maximum Certified Weights: A320-211-212-231 (KG) (LBS) A320-214/-232/-233 (KG) (LBS) A320-216 (KG) (LBS) Max. Take-off Weight 77 000 169 785 78 000 171 958 75 500 166 478 Max. Landing Weight 66 000 145 505 66 000 145 505 66 000 145 505 Max. Zero Fuel Weight 62 500 137 789 62 500 137 789 62 500 137 789 Minimum Weight 37 230 82 080 37 230 82 080 37 230 82 080 A320-271N/-272N/-273N/- 251N/-252N/-253N (KG) (LBS) Max. Take-off Weight 79 000 174 163 Max. Landing Weight 68 400 150 796 Max. Zero Fuel Weight 65 300 143 962 Minimum Weight 40 300 88 847 (PW) 40 600 89 508 (CFM) See applicable Airplane Flight Manual (AFM), as listed in ‘Operating and Service Instructions’, for configuration specific mass limitations and aircraft eligibility (Weight Variant). A28NM Page 32 of 103 All models Minimum Crew: 2 Pilots Maximum Passengers: 179 See Notes 15, 20, 27, 28, 30, 32 and 34 Maximum Baggage: CARGO COMPARTMENT MAXIMUM LOAD (KG) (LBS) Forward 3 402 7 500 Aft 4 536 10 000 Rear (Bulk) 1 497 3 300 For the positions and the loading conditions authorized in each position (references of containers, pallets, and associated w eights), see Weight and Balance Manual, ref. 00D080A0001/C1S Chapter 1.10. Fuel Capacity (0.8 kg/liter): A320-211/-212/-214/-216/-231/-232/-233: 3-Tank Airplane 4-Tank Airplane (*) Usable Fuel Unusable Fuel Usable Fuel Unusable Fuel Liters (kgs) Gallons (lbs) Liters (kgs) Gallons (lbs) Liters (kgs) Gallons (lbs) Liters (kgs) Gallons (lbs) Wing 15 609 4 123 58.9 15.6 15 609 4 123 58.9 15.6 (12 487) (27 529) (47.1) (103.9) (12 487) (27 529) (47.1) (103.9) Center 8 250 2 179 23.2 6.1 8 250 2 179 23.2 6.1 (6 600) (14 550) (18.6) (41.0) (6 600) (14 550) (18.6) (41.0) ACT (*) 2 992 790 17.0 4.4 (2 393) (5276) (13.6) (29.9) Total 23 859 6 302 82.1 21.7 26 851 7 092 99.1 26.1 (19 087) (42 079) (65.7) (144.9) (21 480) (47 355) (79.3) (174.7) (*) see note 8 4 to 5-Tank Airplane (**) (low pressure ACT system) Tank Usable Fuel Unusable Fuel Liters (kgs) Gallons (lbs) Liters (Kgs) Gallons (lbs) TOTAL 23 859 6 302 82.1 21.7 3-Tank (19 087) (42 079) (65.7) (144.9) Airplane 2 992 790 17 4.5 ACT 1 (2 393) (5 274) (13.6) (30.0) TOTAL 26 851 7 092 99.1 26.2 4-Tank (21 480) (47 346) (79.3) (174.9) Airplane ACT 2 2 992 (2 393) 790 (5 274) 17 (13.6) 4.5 (30.0) TOTAL 29 843 7 882 116.1 30.7 5-Tank (23 874) (52 620) (92.9) (204.9) Airplane (**) see note 26 A28NM Page 33 of 103 All models A320-211/-212/-214/-216/-231/-232/-233 with Modification 160001 (Structural Provisions for Sharklet - see note 22): 3-Tank Airplane 4-Tank Airplane (*) Usable Fuel Unusable Fuel Usable Fuel Unusable Fuel Liters (kgs) Gallons (lbs) Liters (kgs) Gallons (lbs) Liters (kgs) Gallons (lbs) Liters (kgs) Gallons (lbs) Wing 15 569 4 113 58.9 15.6 15 569 4 113 58.9 15.6 (12 445) (27 436) (47.1) (103.9) (12 445) (27 436) (47.1) (103.9) Center 8 248 2 179 23.2 6.1 8 248 2 179 23.2 6.1 (6 598) (14 546) (18.6) (41.0) (6 598) (14 546) (18.6) (41.0) ACT (*) 2 992 790 17.0 4.4 (2 393) (5 276) (13.6) (29.9) Total 23 817 6 292 82.1 21.7 26 809 7082 99.1 26.1 (19 043) (41 982) (65.7) (144.9) (21 447) (47 258) (79.3) (174.7) (*) see note 8 Fuel Capacity Continued (0.8 kg/liter): 4 to 5-Tank Airplane (**) (low pressure ACT system) Tank Usable Fuel Unusable Fuel Liters (kgs) Gallons (lbs) Liters (Kgs) Gallons (lbs) TOTAL 23 816 6 292 82.1 21.7 3-Tank (19 052) (42 005) (65.7) (144.9) Airplane 2 992 790 17 4.5 ACT 1 (2 393) (5 274) (13.6) (30.0) TOTAL 26 808 7 082 99.1 26.2 4-Tank (21 425) (47 279) (79.3) (174.9) Airplane ACT 2 2 992 (2 393) 790 (5 274) 17 (13.6) 4.5 (30.0) TOTAL 29 800 7 872 116.1 30.7 5-Tank (23 839) (52 553) (92.9) (204.9) Airplane (**) see note 26 A320-251N/-252N/-253N/-271N/-272N/-273N 3-Tank Airplane Usable Fuel Unusable Fuel Liters (kgs) Gallons (lbs) Liters (kgs) Gallons (lbs) Wing 15 477 (12 428) 4 088 (27 399) 58.9 (47.3) 15.5 (104.3) Center 8 248 (6 623) 2 179 (14 601) 23.2 (18.6) 6.1 (41.0) Total 23 725 (19 051) 6 267 (42 000) 82.1 (65.9) 21.6 (145.3) Oil Capacity: CFMI CFM56-5A/5B - Engine Oil Capacity, 10 quarts/engine (9.46 liters). IAE V2500-A5 - Engine Oil Capacity, 7 quarts/engine (6.6 liters) IAE PW1100G-JM – Engine Oil Capacity 34.9 quarts/engine (33.0 liters) CFMI LEAP-1A – Engine Oil Capacity 21.3 quarts/engine (20.1 liters) Maximum Operating Altitude: - 39 800 feet (12 200 m) clean if modification 30748 is embodied. - 39 100 feet (12 000 m) clean. A28NM Page 34 of 103 All models - 20 000 feet (6 500 m) Slats/Flaps extended. Equipment: The basic equipment as prescribed in the airworthiness regulations (see certification basis) must be installed in the aircraf t for certification. Equipment approved for installation are listed in the definition of the reference model and the modification applicable to it . Refer to Type Certification Standard Equipment List 00D000A0101/C1S. Refer to Note 1 for list of A320 airplane model FAA Type Definitions. Import Requirements: A FAA Standard Airworthiness Certificate may be issued based on a French "Certificat de Navigabilite pour Exportation," (Export C of A) signed by a representative of the Direction Generale de 1'Aviation Civile (DGAC) of France on behalf of the European Community or based on a German Export C of A issued by a representative of LBA or based on a EASA Export C of A issued by a representative of EASA. The Export C of A should contain, containing the following statement: "The aircraft covered by this certificate has bee n examined, tested, and found to conform to the Type Design approved under FAA Type Certificate No. A28NM and to be in a condition for safe operation." Refer to the applicable bilateral agreement to verify eligibility for import into the United States of both new and used airc raft based on the scope of the agreement, to identify any required statements by the exporting authority on the export certificate of airworthiness (or equivalent document), and for procedures for coordinating exceptions to conformity statements on these documents. Refer to FAA Order 8130.2, Airworthiness Certification of Aircraft , for requirements for issuance of an airworthiness certificate for imported aircraft.” Note: In order for the FAA to make the finding that Airbus Model A320-216 aircraft that was produced before December 19, 2016 to be registered in the US is in a condition for safe operation, the FAA certificating inspector or other authorized person must assure the aircraft conforms to the Required Airworthiness Action List (RAAL) document number D000A5108/C00 Issue 2 dated December 19, 2016. The RAAL contains a list of type design modifications and inspections that have been determined by the Director General of Civil Aviation (DGAC) France or European Aviation Safety Agency (EASA), which is the state of design authority for the Airbus A320- 216, to be required to correct unsafe conditions discovered on the original type design of the A320-216. DGAC France and EASA issued Airworthiness Directives that require the accomplishment of these modifications and inspections to correct the identified unsafe conditions, and has advised the FAA of this mandatory continuing airworthiness information (MCAIs). Based on these MCAIs the FAA has determined that for Model A320-216 aircraft produced before December 19, 2016 the airworthiness actions identified in RAAL document number D16037131 Issue 1, are required in the interest of safety and are necessary for this airplane to be in a condition for safe operation. Prior to issuance of a Standard Certificate of Airworthiness (C of A) on any Airbus A320-216 model aircraft produced before December 19, 2016 all airworthiness actions shown in the RAAL document number D16037131 Issue 1, must be accomplished. The airworthiness limitations associated with the type design of A320-216 must be included in the operator’s airplane maintenance or inspection program. Any deviation from the RAAL must be approved by the Manager of the International Branch ANM-116, FAA Transport Airplane Directorate.” Certification Basis a. Part 25 of the FAR effective February 1, 1965, including Amendments 25-1 through 25-56 thereto. b. Based on 14 CFR Section 21.29(a) for new import Type Certificates (TCs), (or Section 21.101(g) for changes to TCs), applicable provisions of 14 CFR Part 26 are included in the certification basis. For any future 14 CFR part 26 amendments, the holder of this TC must demonstrate compliance with the appicacble sections. c. Special Federal Aviation Regulation (SFAR) No.27 effective February 1, 1974, including Amendments 27-1 through 27-5. d. Part 36 of the FAR effective December 1, 1969, including Amendments 36-1 through 36-12. See Note 16. 14 CFR part 36 through 36-31, Stage 5 for models: A320-216, A320-232, and A320-233. The means of implementation of Stage 5 recertification must be provided by Airbus to ensure availability of the revised AFM noise pages for all affected aircraft. AFM CP293 issue 1.0 dated October 2, 2018 or later revision approved by EASA. e. FAA Special Conditions issued for the A320 in accordance with Section 21.16 of the FAR: (1) No. 25-ANM-23, Effective December 15, 1988: • Electronic Flight Controls • Active Controls A28NM Page 35 of 103 All models • Engine Controls and Monitoring • Protection from Lightning and Unwanted Effects of Radio Frequency (RF) Energy • Flight Characteristics • Flight Envelope Protection • Side Stick Controllers • Flight Recorder. (2) No. 25-ANM-29, Effective May 31, 1989: • Computerized Airplane Flight Manual (3) No. 25-671-SC, Effective May 16, 2017: • Non-Rechargeable Lithium Batteries – Applicable to Type design changes applied after May 16, 2017. Reference the applicability section of this special condition for more information on which Type design changes must meet it. (4) No. 25-729-SC, Effective June 28, 2018: • Electronic System Security Protection from Unauthorized Internal Access - Applicable to type design changes applied after June 28, 2018. (5) No. 25-730-SC, Effective June 28, 2018: • Electronic System Security Protection from Unauthorized External Access - Applicable to type design changes applied after June 28, 2018. f. For precision approach and landing, the applicable technical requirements are complemented by AC 120-29 and AC 120-28c. For the automatic flight control system, the applicable technical requirements are complemented by AC 20 -57A for automatic landing and by AC 25.1329-1A for cruise. Use of JAR AWO where applicable to the requirements above, is acceptable. g. The following paragraphs of the FAR have been complied with through equivalent safety demonstrations: - 25.783(e) for cargo doors - 25.783(f) for passenger doors and bulk cargo door - 25.813(c) for emergency exit access - 25.811(e)(3) Type III emergency exit marking. h. Optional Requirements elected: - 25.801 for ditching. - 25.1419 for icing. Certification Basis for Airbus Model A320 series airplanes with modification 160500 or 160080 installation of large wingtip device (Sharklet) see note 23: The original certification basis for the Model A320 shown above for components or areas not affected by the change. Plus the following sections of 14 CFR part 25 as amended by Amendments 25-1 through 25-129 (i.e., the amendment in affect on the date of application April 8, 2010) applied to the components and areas affected by the change: 25.23, 25.25, 25.101, 25.109, 25.113, 25.115, 25.117, 25.161, 25.171, 25.173, 25.203, 25.235, 25.251, 25.301, 25.303, 25.305, 25.307(a)(d), 25.321, 25.331, 25.333, 25.335, 25.337, 25.341(a)(b), 25.343, 25.345, 25.349, 25.351, 25.365(a)(b)(d), 25.367, 25.371, 25.373, 25.391, 25.393(b), 25.427, 25.445, 25.457, 25.459, 25.471(a)(b), 25.473, 25.479(a)(c)(d), 25.481(a)(c), 25.483, 25.485, 25.489, 25.581, 25.601, 25.603, 25.605, 25.607, 25.609, 25.613, 25.619, 25.623, 25.625, 25.629, 25.631, 25.651, 25.671, 25.672, 25.683(b), 25.903(d)(1), 25.1011(b), 25.1385(a)(b)(d), 25.1387(a)(b)(c)(d), 25.1389, 25.1391, 25.1393, 25.1395, 25.1397, 25.1401, 25.1505, 25.1511, 25.1515, 25.1517, 25.1527, 25.1533, 25.1535, 25.1581, 25.1585(a) Plus the following sections of 14 CFR part 25 amended as indicated below applied to the components and areas affected by the change per Airbus reversion justification: 25.21 Amdt 1201 25.181 Amdt 1072 25.103 Amdt 1071&2 25.201 Amdt 1072 A28NM Page 36 of 103 All models 25.105 Amdt 1201 25.207 Amdt 1071&2 25.107 Amdt 1071&2 25.231 Amdt 1072 25.111 Amdt 1201 25.233 Amdt 1072 25.119 Amdt 1071&2 25.237 Amdt 107 1&2 25.121 Amdt 1071&2 25.253 Amdt 1201 25.123 Amdt 1201 25.571(a)(b)(e) Amdt 863 25.125 Amdt 1071&2 25.981 Amdt 564 25.143 except (g) Amdt 1071&2 25.1001 Amdt 1071 25.143(g) at Amdt 1081 25.1301 Amdt 565 25.145 Amdt 971&2 25.1309 Amdt 565 25.147 Amdt 1072 25.1419 Amdt 561 25.149 Amdt 1072 25.1587 Amdt 1071 25.175 Amdt 1072 Notes: 1. FAA acceptance of these reversions was based on the fact that Airbus has done additional testing above the requirements incorporated by reference as documented in EASA AMC-F14, dated November 29, 1993, Flight in Icing Conditions, and a determination that compliance with the amendment in effect on the date of application for these rules (i.e., Amendment 25-121) would not materially increase the level of safety exception of 14 CFR 21.101(b)(3). EASA AMC-F14 is incorporated as part of the certification basis for this airplane. 2. FAA acceptance of these reversions was based on fact that Airbus will show compliance with FAA Special Condition 25-ANM-23 for VSR and a determination that compliance with the amendment in effect on the date of application for these rules (i.e., Amendment 25-108) would not materially increase the level of safety exception of 14 CFR 21.101(b)(3). 3. FAA acceptance of this reversion was based on a determination that compliance with the amendment in effect on the date of application for this rule (i.e., Amendment 25-96) would not materially increase the level of safety exception of 14 CFR 21.101(b)(3). 4. FAA acceptance of this reversion was based on a determination that compliance with the amendment in effect on the date of application for this rule (i.e., Amendment 25-102) would not materially increase the level of safety exception of 14 CFR 21.101(b)(3). 5. FAA acceptance of this reversion was based on a determination that compliance with the amendment in effect on the date of application for this rule (i.e., Amendment 25-123) would not materially increase the level of safety exception of 14 CFR 21.101(b)(3). Plus the following sections of part 25 amended as indicated below based on Airbus elect to comply: 25.107(e)(1)(iv) Amendment 25-135 25.177 Amendment 25-135 Special conditions: The FAA Special Conditions applicable to each model as defined above remain applicable to aircraft equipped with Sharklet, except Paragraph 2 – Active Controls of FAA Special Condition 25-ANM-23 is replaced with the following special conditions: • No. 25-469-SC Effective October 11, 2012 - “Interaction of Systems and Structures” • No. 25-470-SC Effective October 11, 2012 - “Design Dive Speed” • No. 25-471-SC Effective October 11, 2012 - “Design Roll Maneuver Conditions” Equivalent Safety Findings (ESFs): The original ESFs applicable to each model as defined above remain effective for aircraft equipped with Sharklet plus the following ESF for aircraft equipped with Sharklet: 25.331 – Use of EASA Certification Specification (CS) 25.331 in lieu of 14 CFR 25.331 for checked pitch maneuver (reference ELOS memorandum TD000885IB-T-A-5) 25.1419 – Analysis instead of flight testing in natural icing conditions (reference ELOS memorandum TD00885IB-T-SE-1) Noise standards 14 CFR 21.93(b) – No acoustical change A28NM Page 37 of 103 All models Fuel venting and exhaust emissions standards Not affected by the change. The initial requirements remain applicable. Optional Requirements elected • 25.801 for ditching. • 25.1419 for icing. • 25.1535 for ETOPS Part 26 14 CFR part 26 effective December 10, 2007, including Amendments 26-1 through 26-3. Certification basis for the Airbus Model A320-214, -232 and -233 installed with large wingtip device (Sharklet Modification 160500) and Modification 156723 (Max Pax), for the certification of a Maximum Passenger Seating Capacity (MPSC) of 190 passengers: The original certification basis for the Model A320-214, -232 and -233 installed with large wingtip device (Sharklet Modification 160500) plus the following sections of 14 CFR part 25 as amended by Amendments 25-1 through 25-139 applied to the components and areas affected by the change, equivalent level of safety finding, Optional Design Regulations, 14 CFR part 26, Additional Design Requirements and Conditions: 14 CFR Section FAA Accepted Amendment Level System/Component/Area Affected by the Change 25.23 139 Fuselage Structure 25.321 139 Fuselage Structure 25.331 139 Fuselage Structure 25.341(a)(b) 139 Fuselage Structure 25.351 139 Fuselage Structure 25.473 139 Fuselage Structure 25.479(a)(c)(d) 139 Fuselage Structure 25.481(a)(c) 139 Fuselage Structure 25.489 139 Fuselage Structure 25.801(d) 139 Entire Airplane 25.803(c) 139 Cabin Interior 25.807 139 Cabin Interior 25.810 139 Cabin Interior 25.815 139 Cabin Interior 25.1447(c)(1) 139 Passenger equipment associated with increased MPSC 25.1519 139 Entire Airplane 25.1529 139 ICA associated with increased MPSC 25.1541(a)(b) 139 Marking & Placards associated with increased MPSC 25.1557(a) 139 Marking & Placards associated with increased MPSC The following sections of 14 CFR part 25 amended as indicated below and applied to the components and areas affected by the change, have been determined in accordance with the § 21.101(b)(3) that compliance with the Amendment 25 -139 would not materially increase the level of safety: 14 CFR Section FAA Accepted Amendment Level 25.305(a)(b),25.307(a),25.365(a) 129 25.562 64 A28NM Page 38 of 103 All models 25.571(a)(b) 86 25.561, 25.787(a)(b), 25.789(a), 25.791, 25.809, 25.811, 25.812(e)(k)(l), 25.813(c), 25.853(a)(b), 25.1301, 25.1309, 25.1351(a), 25.1353(a)(b), 25.1357(a)(c)(g), 25.1359(a)(d), 25.1413, 25.1415(b)(c)(d), 25.1431(c), 25.1561 56 25.853(c)(d)(e) 116 Equivalent Safety Findings: In accordance with the provisions of § 21.21(b)(1) the following new ELOS finding is applicable to Modification 156723 (MaxPax): AT10259IB-T-CS-2 § 25.807 Emergency Exits Finding for Increase of the Maximum Passenger Capacity (MPSC) from 179 passengers to 190 passengers Optional Design Regulations: ETOPS: Modification 156723 (MaxPax) has not been evaluated for extended operations (ETOPS) type design approval on Models A320-214, -232 and -233 airplanes installed with large wingtip device (Sharklet Modification 160500). Part 26: Based on 14 CFR § 21.101(g), applicable provisions of 14 CFR part 26 are included in the certification basis. For any future 14 CFR part 26 amendments, the holder of this TC must demonstrate compliance with the applicable sections. The type design complies with the following 14 CFR part 26 Amendments 26-1 through 26-6 regulations: §§ 26.11, 26.33, 26.43, and 26.45. Additional Design Requirements and Conditions: Limitation: • The exit passageway width, starting at the aircraft aisle centerline and extending 21 inches outboard from the aircraft aisle centerline, must be a minimum of 23.2 inches. Any a ttendant seat/fixture installed on the side of the exit passageway must not result in a passageway less than 23.2 inches for the inboard portion of the passageway. The remaining passageway (starting 21 inches from the aircraft centerline to the emergency exit) must be a minimum of 20 inches. The height of the attendant seat/fixture is limited to a maximum height of 56.5 inches. • The unobstructed exit dimensions of the floor level emergency exits must not be less than 32 inches x 73 inches. • A wide slide (sliding surface width 82.75 inches (+3.0 inches, -2.0 inches)) must be installed at doors 1 and 4. • The wide slides installed at doors 1 and 4 must have a beam strength meeting the requirements of TSO C69c. Certification basis for the Airbus Model A320-211, -212, -214, -231, -232 and -233 installed with Wing Tip Fence (WTF) and Max Pax Modification 158708 & 157968, for the certification of a Maximum Passenger Seating Capacity (MPSC) of 180 for 157968 or 190 for 158708 passengers: The original certification basis for the Model A320-211, -212, -214, -231, -232 and -233 installed with WTF plus the following sections of 14 CFR part 25 as amended by Amendments 25-1 through 25-141 applied to the components and areas affected by the change, equivalent level of safety finding, Optional Design Regulations, 14 CFR part 26, Additional Design Requirements and Conditions: 14 CFR Section FAA Accepted Amendment Level System/Component/Area Affected by the Change 25.23 141 Fuselage Structure 25.321 141 Fuselage Structure 25.331(a)(b)(c)(1) 141 Fuselage Structure 25.341(a) 141 Fuselage Structure 25.351 141 Fuselage Structure 25.473 141 Fuselage Structure 25.479(a)(c)(d) 141 Fuselage Structure 25.481(a)(c) 141 Fuselage Structure A28NM Page 39 of 103 All models 14 CFR Section FAA Accepted Amendment Level System/Component/Area Affected by the Change 25.489 141 Fuselage Structure 25.801(d) 141 Entire Airplane 25.803(c) 141 Cabin Interior 25.807 141 Cabin Interior 25.810 141 Cabin Interior 25.815 141 Cabin Interior 25.1447(c)(1) 141 Passenger equipment associated with increased MPSC 25.1529 141 ICA associated with increased MPSC 25.1541(a)(b) 141 Marking & Placards associated with increased MPSC 25.1557(a) 141 Marking & Placards associated with increased MPSC The following sections of 14 CFR part 25 amended as indicated below and applied to the components and areas affected by the change, have been determined in accordance with the § 21.101(b)(3) that compliance with the Amendment 25 -141 would not materially increase the level of safety: 14 CFR Section FAA Accepted Amendment Level 25.305(a)(b),25.307(a), 25.331(c)(2), 25.341(b), 25.365(a),25.561, 25.571(a)(b), 25.785, 25.787(a)(b), 25.789(a), 25.791, 25.809, 25.811, 25.812(e)(k)(l), 25.813, 25.853(a)(b), 25.1301, 25.1309, 25.1351(a), 25.1353(a)(b), 25.1357(a)(c)(g), 25.1359(a)(d), 25.1413, 25.1415(b)(c)(d), 25.1431(c), 25.1561 56 25.562 64 25.853(c)(d)(e) 116 Equivalent Safety Findings: In accordance with the provisions of § 21.21(b)(1) the following new ELOS finding is applicable to Modification 157968 (MaxPax): AT10482IB-T-CS-2 § 25.807 Emergency Exits Finding for Increase of the Maximum Passenger Capacity (MPSC) from 179 passengers to 180 passengers In accordance with the provisions of § 21.21(b)(1) the following new ELOS finding is applicable to Modification 158708 (MaxPax): AT10621IB-T-CS-2 § 25.807 Emergency Exits Finding for Increase of the Maximum Passenger Capacity (MPSC) from 179 passengers to 190 passengers Optional Design Regulations: ETOPS: Modifications 157968 and 158708 (MaxPax) have not been evaluated for extended operations (ETOPS) type design approval on Model A320-211, -212, -214, -231, -232 and -233 installed with Wing Tip Fence (WTF). Part 26: Based on 14 CFR § 21.101(g), applicable provisions of 14 CFR part 26 are included in the certification basis. For any future 14 CFR part 26 amendments, the holder of this TC must demonstrate compliance with the applicable sections. The type design complies with the following 14 CFR part 26 Amendments 26-1 through 26-6 regulations: §§ 26.11, 26.33, 26.43, and 26.45. Additional Design Requirements and Conditions: Limitation: • The exit passageway width, starting at the aircraft aisle centerline and extending 21 inches outboard from the aircraft aisle centerline, must be a minimum of 23.2 inches. Any attendant seat/fixture installed on the side of the exit passageway must not result in a passageway less than 23.2 inches for the inboard portion of the passageway. The remaining passageway (starting 21 inches from the aircraft centerline to the emergency exit) must be a minimum of 20 inches. The height of the attendant seat/fixture is limited to a maximum height of 56.5 inches. A28NM Page 40 of 103 All models • The unobstructed exit dimensions of the floor level emergency exits must not be less than 32 inches x 73 inches. • A wide slide (sliding surface width 82.75 inches (+3.0 inches, -2.0 inches)) must be installed at doors 1 and 4. • The wide slides installed at doors 1 and 4 must have a beam strength meeting the requirements of TSO C69c. Certification basis for the Airbus Model A320-251N,-252N,-271N, -272N and -273N (Single Aisle New Engine Option): The certification basis for the Airbus Model A320 series airplanes with Modification 160500, installation of large wingtip device (Sharklet) shown above for components or areas not affected by the change. Plus the following sections of 14 CFR part 25 as amended by Amendments 25-1 through 25-136 (i.e., the amendment in effect on the date of application) applied to the components and areas affected by the change: 25.3, 25.23(a)(b), 25.25(a)(b), 25.27, 25.101, 25.107(e)(1)(iv), 25.109, 25.113, 25.115, 25.117, 25.147, 25.149, 25.161, 25.171, 25.173, 25.175, 25.177, 25.181, 25.201, 25.203, 25.231, 25.233, 25.235, 25.251(a)(b)(c)(d)(e), 25.253(a)(b), 25.255, 25.301*, 25.303*, 25.305(a)(b)(c)*, 25.307(a)(d)*, 25.321(a)(b)(c)(d), 25.331(a)(b)(c), 25.333(a)(b), 25.335(a)(b)(c)(d)(e)(f), 25.337, 25.341(a)(b), 25.343(a)(b), 25.345(a)(b)(d), 25.349(a)(b), 25.351, 25.361, 25.363, 25.365(a)(b)(c)(d)(e)*, 25.367(a)(b), 25.371, 25.373, 25.391(a)(b)(c)(d)(e), 25.427(a)(b)(c)(d), 25.445(a)(b), 25.457, 25.459, 25.471(a)(b), 25.473, 25.479(a)(c)(d), 25.481(a)(c), 25.483, 25.485(a)(b), 25.489, 25.491, 25.493(b)(c)(d), 25.495, 25.499(a)(b)(c)(d)(e), 25.503(a)(b), 25.507(a)(b)(c), 25.509(a)(c)(d), 25.511, 25.519(a)(b)(c), 25.563, 25.581, 25.601*, 25.603, 25.605, 25.607, 25.609*, 25.613, 25.619*, 25.623*, 25.625, 25.629, 25.631*, 25.651*, 25.671, 25.672(a)(b)(c), 25.683(b), 25.703(a)(b)(c), 25.721(a)(b)(c), 25.777, 25.779(b), 25.789, 25.801, 25.841(a), 25.843(b), 25.851(b), 25.855(c), 25.863 (a)(b)(c)(d), 25.865, 25.867(a)(b)*, 25.869(a)(b)(c), 25.901(a)(b)(c), 25.903, 25.904, 25.933(a), 25.934, 25.939 (a)(c), 25.943, 25.951(a)(b)(c)(d)*, 25.952(a)(b), 25.954, 25.955(a), 25.959, 25.961, 25.963(a)(d), 25.969, 25.971, 25.975, 25.981 except 25.981(a)(3)**, 25.993(a)(b)(c)(d)(e), 25.994, 25.995, 25.997(a)(b)(c)(d), 25.999(a)(b), 25.1001, 25.1011(a)(b), 25.1013(a)(b)(c)(d)(e)(f), 25.1015(a)(b), 25.1017(a)(b), 25.1019(a), 25.1021(a)(b), 25.1023(a)(b), 25.1025(a)(c), 25.1041, 25.1043(a)(b)(c), 25.1045(a)(b)(c), 25.1091(a)(b)(c)(d)(e), 25.1093(b), 25.1103(b)(c)(d), 25.1121, 25.1123, 25.1141, 25.1143, 25.1145, 25.1155, 25.1163, 25.1165, 25.1167, 25.1181, 25.1182, 25.1183, 25.1185, 25.1187, 25.1189, 25.1191, 25.1193, 25.1195, 25.1197, 25.1199, 25.1201, 25.1203, 25.1207, 25.1301*, 25.1305, 25.1309*, 25.1316, 25.1317, 25.1337, 25.1353(a)(b)*, 25.1355(c), 25.1357(a)*, 25.1363, 25.1401(b), 25.1403, 25.1431*, 25.1438, 25.1461, 25.1501, 25.1503, 25.1507, 25.1511, 25.1513, 25.1515, 25.1517, 25.1519, 25.1521(a)(c)(d), 25.1525, 25.1527, 25.1529, 25.1531, 25.1533, 25.1535*, 25.1549(a)(b)(c), 25.1553, 25.1581, 25.1583, 25.1585, 25.1587, 25.1591, 25.1701(a)*, 25.1703(a)(b)(d)*, 25.1705*, 25.1707*, 25.1709*, 25.1711*, 25.1713*, 25.1715*, 25.1717*, 25.1719*, 25.1723*, 25.1725*, 25.1727*, 25.1731* * For new and modified parts only (engine, pylon, nacelle, bleed air system, wing structural changes in area of pylon and landing gear reinforcement) ** FAA acceptance of this exception is for the Fuel Quantity Indicating System (FQIS) and Fuel Level Sensor System (FLSS) wiring installation changes and fuel tank structural fastener changes only and is based on the following design features incorporated on the NEO: The FQIS/FLSS wiring is within the S-routes in pressurized areas and is isolated with protective textile sleeving with CAUTION, FUEL TANK HARNESS ONLY" labels. The FQIS/FLSS wiring is within the S-routes in non-pressurized areas and is isolated with protective heat shrink sleeving and routed with the rest of the S-route bundle in PTFE conduit up to fuel tank walls penetration with "CAUTION, FUEL TANK HARNESS INSIDE" labels. Wiring production breaks from Avionic bays to the tank walls is done through dedicated connectors. The fuel tank structural fastener changes meet the criteria for the use of exceptions in FAA policy ANM-112-08-002 “Policy on Issuance of Special Conditions and Exemptions Related to Lightning Protection of Fuel Tank Structure,” dated May 26, 2009. Plus the following sections of 14 CFR part 25 amended as indicated below applied to the components and areas affected by the change per Airbus reversion justification: 25.21 Amdt. 1201 25.561(a)(b)(c)(d) Amdt. 642 25.103 Amdt. 1201 25.571(a)(b)(e)(1) Amdt. 863 25.105 Amdt. 1201 25.611 Amdt. 564 25.107 (except (e)(1)(iv)) Amdt 1201 25.677(b) Amdt. 565 25.111 Amdt. 1201 25.899 Amdt. 566 25.119 Amdt. 1201 25.1317 Amdt. 567 25.121 Amdt. 1201 25.1322 Amdt. 568 25.123 Amdt. 1201 25.1329 Amdt. 569 A28NM Page 41 of 103 All models 25.125 Amdt. 1201 25.1351 Amdt. 5610 25.143 Amdt. 1201 25.1419 Amdt. 1201 25.145 Amdt. 971 25.1435 Amdt. 5611 25.207 Amdt. 1201 25.1459(a) Amdt. 5612 25.237 Amdt. 1201 Appendix H at amdt 5613 25.253(c) Amdt. 1201 Notes: 1. FAA acceptance of these reversions was based on the fact that Airbus has done additional testing above the requirements incorporated by reference as documented in the summary of EASA CRI B-06, issue 2, dated April 11, 2013, Flight in Icing Conditions, and a determination that compliance with the amendment in effect on the date of application for these rules (i.e., Amendment 25-121) would not materially increase the level of safety exception, or in some cases, would be impractical in accordance with 14 CFR 21.101(b)(3). EASA CRI B-06 is incorporated as part of certification basis for this airplane. 2. FAA acceptance of this reversion was based on a determination that compliance with the amendment in effect on the date of application for this rule (i.e., Amendment 25-91) would not materially increase the level of safety in accordance with14 CFR 21.101(b)(3). 3. FAA acceptance of this reversion was based on a determination that compliance with the amendment in effect on the date of application for this rule (i.e., Amendment 25-132) would not materially increase the level of safety in accordance with14 CFR 21.101(b)(3). 4. FAA acceptance of this reversion was based on a determination that compliance with the amendment in effect on the date of application for this rule (i.e., Amendment 25-123) would not materially increase the level of safety in accordance with 14 CFR 21.101(b)(3). 5. FAA acceptance of this reversion was based on a determination that the changes in this area are considered secondary and compliance with the amendment in effect on the date of application for this rule (i.e., Amendment 25-115) would not materially increase the level of safety in accordance with 14 CFR 21.101(b)(3). 6. FAA acceptance of this reversion was based on a determination that changes in this area are considered secondary and compliance with the amendment in effect on the date of application for this rule (i.e., Amendment 25-123) would not materially increase the level of safety in accordance with 14 CFR 21.101(b)(3). 7. FAA acceptance of this reversion was based on a determination that the changes in this area are considered secondary and compliance with the amendment in effect on the date of application for this rule (i.e., Amendment 25-122) would not materially increase the level of safety above Special Condition 25-ANM-23 in accordance with 14 CFR 21.101(b)(3). 8. FAA acceptance of this reversion was based on a determination that compliance with the amendment in effect on the date of application for this rule (i.e., Amendment 25-131) would be impractical in accordance with 14 CFR 21.101(b)(3). 9. FAA acceptance of this reversion was based on a determination that changes in this area are considered secondary and compliance with the amendment in effect on the date of application for this rule (i.e., Amendment 25-119) would not materially increase the level of safety in accordance with 14 CFR 21.101(b)(3). 10. FAA acceptance of this reversion was based on a determination that the changes in this area are considered secondary and compliance with the amendment in effect on the date of application for this rule (i.e., Amendment 25-72) would not materially increase the level of safety in accordance with 14 CFR 21.101(b)(3). 11. FAA acceptance of this reversion was based on a determination that changes in this area are considered secondary and compliance with the amendment in effect on the date of application for this rule (i.e., Amendment 25-104) would not materially increase the level of safety in accordance with 14 CFR 21.101(b)(3). 12. FAA acceptance of this reversion was based on a determination that changes in this area are considered secondary and compliance with the amendment in effect on the date of application for this rule (i.e., Amendment 25-124) would not materially increase the level of safety in accordance with 14 CFR 21.101(b)(3). 13. FAA acceptance of this reversion was based on a determination that compliance with the amendment in effect on the date of application for this rule (i.e., Amendment 25-123) would not materially increase the level of safety in accordance with 14 CFR 21.101(b)(3). A28NM Page 42 of 103 All models Plus the following sections of 14 CFR part 25 amended as indicated below per Airbus elect to comply: 25.853(a)(1) at Amendment 25-66 25.853(c) at Amendment 25-59 Special conditions: FAA Special Condition 25-ANM-23 applicable to each model as defined in FAA TCDS A28NM remains applicable, except: Paragraph 2 – Active Controls is replaced with the following special conditions: • No. 25-469-SC Effective October 11, 2012 - “Interaction of Systems and Structures” • No. 25-470-SC Effective October 11, 2012 - “Design Dive Speed” • No. 25-471-SC Effective October 11, 2012 - “Design Roll Maneuver Conditions” Paragraph 4 – Protection from Lightning and Unwanted Effects of Radio Frequency is replaced with the following later requirements: • 25.1316 thru amendment 25-136 • 25.1317 thru amendment 25-136 In addition the following FAA Special Condition applies specifically to the Airbus SA NEO program: • No. 25-582-SC Effective April 30, 2015 - “Transient Engine Failure Loads” Equivalent Safety Findings (ESFs): The ESFs applicable to each model as defined in FAA TCDS A28NM remain applicable plus the following ESFs applied specifically to the Airbus SA NEO program: ELOS Memo Regulation Subject AT00949IB-T-P-10 25.779(b)(1) Throttle Motion During Reduced (Flexible) Takeoff Thrust Operations and/or Go-Around AT00949IB-T-P-11 25.1549(a), (b) and (c) Digital Display of High Pressure Rotor Speed (N2) AT00949IB-T-P-12 25.1549(a) Oil Temperature Indication AT00949IB-T-P-13 25.997(d) & 25.1305(c)(6) Fuel Filter Bypass Indication (CFMI only) AT00949IB-T-P-14 25.1193(e)(3) Resistance to Fire of Cowling AT00949IB-T-P-15 25.1181(a)(6) & (b), & 25.1195 thru 25.1203 Fan Zone Non-fire Zone (PW only) AT00949IB-T-P-17 25.933(a)(1)(ii) Flight Critical Thrust Reverser AT00949IB-T-P-19 25.934 Thrust Reverser Testing AT00949IB-T-P-21 25.1181(a)(6) & (b), 25.1182 and 25.1195 through 25.1203 PW1100G-JM 2.5 Bleed & Track lock Areas and PW1100G-JM and LEAP-1A Areas Adjacent to Designated Fire Zones AT00949IB-T-SA-1 25.1301 and 25.1309 Equipment, Systems, and Installation Requirements: Use of ARAC Recommendations Exemptions: The Exemptions applicable to each model as defined in TCDS A28NM remain applicable plus the following exemption applied specifically to the Airbus SA NEO models: Exemption No. 13048 for 25.841(a) dated September 25, 2015 (13048A dated February 22, 2018, 13048B dated March 6, 2019.) Optional Requirements elected • § 25.801 for ditching. • § 25.1419 for icing. • § 25.1535 for ETOPS Noise standards 14 CFR part 36 through Amendment 36-30, Stage 4. 14 CFR part 36 through amendment 36-31, Stage 5 for models A320-251N, -252N, -253N, -271N, -272N, and -273N. The means of implementation of Stage 5 recertification must be provided by Airbus to ensure availability of the revised AFM noise pages for all affected aircraft. AFM CP293 issue 1.0 dated October 2, 2018 or later revision approved by EASA. A28NM Page 43 of 103 All models Fuel venting and exhaust emissions standards 14 CFR part 34 as amended by Amendment 34-1 through 34-5. Part 26 14 CFR part 26 as amended by Amendment 26-1 through 26-5. Additional Design Requirements and Conditions Compliance with the established basis for type certification notwithstanding, § 21.21(b)(2) precludes issuance of a type certificate if there is any feature or characteristic that would make the product unsafe. The following design details or information must be maintained to ensure that an unsafe design condition is not present: In-flight Engine Restart 1. A minimum restart capability after an all engines out scenario must be established under the following conditions using procedures provided in the airplane flight manual (AFM): a) During the take-off and the initial climb-out portion of the flight, the airplane should have the capability for the flightcrew to restore engine power when the fuel source to the engine is interrupted. b) During the high altitude portion of the flight at cruise speed and maximum altitude, the airplane should have the capability for the flightcrew to restart from a stabilized windmill speed those engines required to maintain level flight or should have the capability for the flightcrew to restart all but one of the engines and produce maximum continuous thrust or power by an altitude of 15 000 feet. c) During flight at speeds greater than the minimum flaps-up “holding speed” and at altitudes below 20 000 feet, the airplane should have the capability for the flightcrew to restart with the engines at stabilized windmill speed those engines necessary to maintain safe flight and arrest the airplane descent within a total altitude loss of 5 000 feet prior to exceeding an airspeed of 300 knots. Certification basis for the Airbus Models A320-251N, A320-271N installed with modification 156723 (Max Pax), for the certification of a Maximum Passenger Seating Capacity (MPSC) of 190 passengers: The original certification basis for the Models A320-251N, A320-271N plus the following sections of 14 CFR part 25 as amended by Amendments 25-1 through 25-141 applied to the components and areas affected by the change, equivalent level of safety finding, Optional Design Regulations, 14 CFR part 26, Additional Design Requirements and Conditions: 14 CFR Section FAA Accepted Amendment Level System/Component/Area Affected by the Change 25.23 141 Fuselage Structure 25.321 141 Fuselage Structure 25.331 141 Fuselage Structure 25.341(a)(b) 141 Fuselage Structure 25.351 141 Fuselage Structure 25.473 141 Fuselage Structure 25.479(a)(c)(d) 141 Fuselage Structure 25.481(a)(c) 141 Fuselage Structure 25.489 141 Fuselage Structure 25.801(d) 141 Entire Airplane 25.803(c) 141 Cabin Interior 25.807 141 Cabin Interior 25.810 141 Cabin Interior 25.815 141 Cabin Interior 25.1447(c)(1) 141 Passenger equipment associated with increased MPSC 25.1519 141 Entire Airplane 25.1529 141 ICA associated with increased MPSC A28NM Page 44 of 103 All models 14 CFR Section FAA Accepted Amendment Level System/Component/Area Affected by the Change 25.1541(a)(b) 141 Marking & Placards associated with increased MPSC 25.1557(a) 141 Marking & Placards associated with increased MPSC The following sections of 14 CFR part 25 amended as indicated below and applied to the components and areas affected by the change, have been determined in accordance with the § 21.101(b)(3) that compliance with the Amendment 25 -141 would not materially increase the level of safety: 14 CFR Section FAA Accepted Amendment Level 25.561, 25.785, 25.787(a)(b), 25.789(a), 25.791, 25.809, 25.811, 25.812(e)(k)(l), 25.813, 25.853(a)(b), 25.1301, 25.1309, 25.1351(a), 25.1353(a)(b), 25.1357(a)(c)(g), 25.1359(a)(d), 25.1413, 25.1415(b)(c)(d), 25.1431(c), 25.1561 56 25.562 64 25.571(a)(b) 86 25.853(c)(d)(e) 116 25.305(a)(b), 25.307(a), 25.365(a), 25.901(c), 136 Special Conditions: The special conditions applied to the baseline Models A320-251N, A320-271N are also applicable to modification 156723 (MaxPax). Equivalent Safety Findings: The ELOS findings applied to the baseline Models A320-251N, A320-271N are also applicable to modification 156723 (MaxPax). In accordance with the provisions of § 21.21(b)(1) the following new ELOS finding is applicable to modification 156723 (MaxPax): AT10555IB-T-CS-3 § 25.807 Emergency Exits Finding for Increase of the Maximum Passenger AT10627IB-T-CS-4 Capacity (MPSC) from 179 passengers to 190 passengers Exemptions: The exemptions applied to the baseline Model A320-271N are also applicable to modification 156723 (MaxPax). Optional Design Regulations: Ditching & Flight in Icing Conditions: Original design approvals for the Models A320-251N, A320-271N are also applicable to modification 156723 (MaxPax). Noise Standards: The Models A320-251N, A320-271N airplanes with Modification 156723 (MaxPax), does not increase the noise levels of the airplane and therefore does not constitute an "acoustical change". 14 CFR 21.93(b) – no acoustical change. Fuel Venting and Exhaust Emissions Standards: 14 CFR 21.93(c) – no emissions change Part 26: The type design complies with the following 14 CFR part 26 Amendments 26-1 through 26-6 regulations: §§ 26.11, 26.33, 26.43, and 26.45 Additional Design Requirements and Conditions: A28NM Page 45 of 103 All models Limitations: • The exit passageway width, starting at the aircraft aisle centerline and extending 21 inches outboard from the aircraft aisle centerline, must be a minimum of 23.2 inches. Any attendant seat/fixture installed on the side of the exit passageway must not result in a passagewa y less than 23.2 inches for the inboard portion of the passageway. The remaining passageway (starting 21 inches from the aircraft centerline to the emergency exit) must be a minimum of 20 inches. The height of the attendant seat/fixture is limited to a maximum height of 56.5 inches. • The unobstructed exit dimensions of the floor level emergency exits must not be less than 32 inches x 73 inches” • A wide slide (sliding surface width 82.75 inches (+3.0 inches, -2.0 inches) must be installed at the forward most and aft most floor level Type I exits (generally designated as doors 1 and 4). • The wide slides installed at the forward most and aft most floor level Type I exits (generally designated as doors 1 and 4) must have a beam strength meeting the requirements of TSO C69c. Certification basis for the Airbus Model A320-214, -216, -232 & -233 installed with modification 160080 (Sharklet In Service Retrofit) and modification 158819 (Max Pax), for the certification of a Maximum Passenger Seating Capacity (MPSC) of 190 passengers: The original certification basis for the Model A320-214, -216, -232 & -233 plus the following sections of 14 CFR part 25 as amended by Amendments 25-1 through 25-143 applied to the components and areas affected by the change, equivalent level of safety finding, Optional Design Regulations, 14 CFR part 26, Additional Design Requirements and Conditions: 14 CFR Section FAA Accepted Amendment Level System/Component/Area Affected by the Change 25.23 143 Fuselage Structure 25.321 143 Fuselage Structure 25.331(a)(b)(c)(1)(c)(2) 143 Fuselage Structure 25.341(a) 143 Fuselage Structure 25.351 143 Fuselage Structure 25.473 143 Fuselage Structure 25.479(a)(c)(d) 143 Fuselage Structure 25.481(a)(c) 143 Fuselage Structure 25.489 143 Fuselage Structure 25.795(d) 143 Cabin Interior excl lavatories 25.801(d) 143 Entire Airplane 25.803(c) 143 Cabin Interior 25.807(g) 143 Cabin Interior 25.810 143 Cabin Interior 25.815 143 Cabin Interior 25.1447(c)(1) 143 Passenger equipment associated with increased MPSC 25.1519 143 Entire Airplane 25.1529 143 ICA associated with increased MPSC 25.1541(a)(b) 143 Marking & Placards associated with increased MPSC 25.1557(a) 143 Marking & Placards associated with increased MPSC The following sections of 14 CFR part 25 amended as indicated below and applied to the components and areas affected by the change, have been determined in accordance with the § 21.101(b)(3) that comp liance with the Amendment 25 -143 would not materially increase the level of safety: A28NM Page 46 of 103 All models 14 CFR Section FAA Accepted Amendment Level 25.305(a)(b),25.307(a),25.341(b) 25.365(a), 25.561, 25.785, 25.787(a)(b), 25.789(a), 25.791, 25.809, 25.811, 25.812(e)(k)(l), 25.813, 25.853(a)(b), 25.1301, 25.1309, 25.1351(a), 25.1353(a)(b), 25.1357(a)(c)(g), 25.1359(a)(d), 25.1413, 25.1415(b)(c)(d), 25.1431(c), 25.1561 56 25.571(a)(b) 86 25.562 64 25.853(c)(d)(e) 116 25.365(a), 25.901(c) 136 Equivalent Safety Findings: In accordance with the provisions of § 21.21(b)(1) the following new ELOS finding is applicable to Modification 158819 (MaxPax): CS-2 § 25.807 Emergency Exits Finding for Increase of the Maximum Passenger Capacity (MPSC) from 179 passengers to 190 passengers CS-6 § 25.807 Emergency Exits Finding for Increase of the Maximum Passenger Capacity (MPSC) Optional Design Regulations: ETOPS: Modification 158819 (MaxPax) has not been evaluated for extended operations (ETOPS) type design approval on Model A320-214, -216, -232 & -233 airplanes installed with large wingtip device (Sharklet In Service Retrofit modification 160080). Part 26: Based on 14 CFR § 21.101(g), applicable provisions of 14 CFR part 26 are included in the certification basis. For any future 14 CFR part 26 amendments, the holder of this TC must demonstrate compliance with the applicable sections. The type design complies with the following 14 CFR part 26 Amendments 26-1 through 26-6 regulations: §§ 26.11, 26.33, 26.43, and 26.45. Additional Design Requirements and Conditions: Limitation: • The exit passageway width must meet the regulatory minimum of 20 inches. The height of the attendant seat or other assembly is limited to a maximum height of 57 inches. • The unobstructed exit dimensions of the forward and aft most floor level emergency exits must not be less than 32 inches x 73 inches. • A wide slide (sliding surface width 82.75 inches (+3.0 inches, -2.0 inches)) must be installed at the forward and aft most exits. • The wide slides installed at the forward and aft most floor level exits must have a beam strength meeting the requirements of TSO-C69c. Certification basis for the Airbus Models A320-252N, A320-253N, A320-272N, A320-273N installed with modification 156723 (Max Pax), for the certification of a Maximum Passenger Seating Capacity (MPSC) of 190 passengers: The original certification basis for the Models A320-252N, A320-253N, A320-272N, A320-273N plus the following sections of 14 CFR part 25 as amended by Amendments 25-1 through 25-145 applied to the components and areas affected by the change, equivalent level of safety finding, Optional Design Regulations, 14 CFR part 26, Additional Design Requirements and Conditions: 14 CFR Section FAA Accepted Amendment Level System/Component/Area Affected by the Change 25.23 141 Fuselage Structure 25.321 141 Fuselage Structure 25.331 141 Fuselage Structure 25.341(a)(b) 141 Fuselage Structure 25.351 141 Fuselage Structure 25.473 141 Fuselage Structure A28NM Page 47 of 103 All models 14 CFR Section FAA Accepted Amendment Level System/Component/Area Affected by the Change 25.479(a)(c)(d) 141 Fuselage Structure 25.481(a)(c) 141 Fuselage Structure 25.489 141 Fuselage Structure 25.801(d) 141 Entire Airplane 25.803(c) 141 Cabin Interior 25.807/ IP-CS3/CS4 141 Cabin Interior 25.810 141 Cabin Interior 25.815 141 Cabin Interior 25.1447(c)(1) 141 Passenger equipment associated with increased MPSC 25.1519 141 Entire Airplane 25.1529 141 ICA associated with increased MPSC 25.1541(a)(b) 141 Marking & Placards associated with increased MPSC 25.1557(a) 141 Marking & Placards associated with increased MPSC The following sections of 14 CFR part 25 amended as indicated below and applied to the components and areas affected by the change, have been determined in accordance with the § 21.101(b)(3) that compliance with the Amendment 25 -141 would not materially increase the level of safety: 14 CFR Section FAA Accepted Amendment Level 25.561, 25.785, 25.787(a)(b), 25.789(a), 25.791, 25.809, 25.811, 25.812(e)(1)(2)(k)(l), 25.813, 25.853(a)(b), 25.1301, 25.1309, 25.1351(a), 25.1353(a)(b), 25.1357(a)(c)(g), 25.1359(a)(d), 25.1413, 25.1415(b)(c)(d), 25.1431(c), 25.1561 56 25.562 64 25.571(a)(b) 86 25.853(c)(d)(e))/IP CI-10 116 25.305(a)(b), 25.307(a), 25.365(a), 25.901(c), 136 Special Conditions: The special conditions applied to the baseline Models A320-252N, A320-253N, A320-272N, A320-273N are also applicable to modification 156723 (MaxPax). Equivalent Safety Findings: The ELOS findings applied to the baseline Models A320-252N, A320-253N, A320-272N, A320-273N are also applicable to modification 156723 (MaxPax). In accordance with the provisions of § 21.21(b)(1) the following new ELOS finding is applicable to modification 156723 (MaxPax): AT11084IB-T-CS-4 § 25.807 Emergency Exits Finding for Increase of the Maximum Passenger Capacity (MPSC) from 179 passengers to 190 passengers Exemptions: The exemptions applied to the baseline Models A320-252N, A320-253N, A320-272N, A320-273N are also applicable to modification 156723 (MaxPax). A28NM Page 48 of 103 All models Optional Design Regulations: Ditching & Flight in Icing Conditions: Original design approvals for the Models A320-252N, A320-253N, A320-272N, A320-273N are also applicable to modification 156723 (MaxPax). Noise Standards: The Models A320-252N, A320-253N, A320-272N, A320-273N airplanes with Modification 156723 (MaxPax), does not increase the noise levels of the airplane and therefore does not constitute an "acoustical change". 14 CFR 21.93(b) – no acoustical change. Fuel Venting and Exhaust Emissions Standards: 14 CFR 21.93(c) – no emissions change Part 26: The type design complies with the following 14 CFR part 26 Amendments 26-1 through 26-6 regulations: §§ 26.11, 26.33, 26.43, and 26.45 Additional Design Requirements and Conditions: Limitations: • The exit passageway width, starting at the aircraft aisle centerline and extending 21 inches outboard from the aircraft aisle centerline, must be a minimum of 23.2 inches. Any attendant seat/fixture installed on the side of the exit passageway must not result in a passageway less than 23.2 inches for the inboard portion of the passageway. The remaining passageway (starting 21 inches from the aircraft centerline to the emergency exit) must be a minimum of 20 inches. The height of the attendant seat/fixture is limited to a maximum height of 56.5 inches. • The unobstructed exit dimensions of the floor level emergency exits must not be less than 32 inches x 73 inches” • A wide slide (sliding surface width 82.75 inches (+3.0 inches, -2.0 inches) must be installed at the forward most and aft most floor level Type I exits (generally designated as doors 1 and 4). • The wide slides installed at the forward most and aft most floor level Type I exits (generally designated as doors 1 and 4) must have a beam strength meeting the requirements of TSO C69c. Note 1: The A320 basic type design definition for U.S. import certification is contained in the following documents: - AI/A 414.282/88 for the A320 Models -111 and -211 - AI/EA-A 413.628/89 for the A320 Model -231 - AI/EA-A 412.1631/90 for the A320 Model -212 - AI/EA-A 414.0665/93 for the A320 Model -232 - AI/EA-S 413.2143/95 for the A320 Model -233 - AI/EA-S 413.0150/95 for the A320 Model -214 - AI/EA-S 413.3004/96 (supplement) for the A320 Model -214 - 00D000A5070/C20. for the A320-271N - 00D000A5073/C20 for the A320-251N - 00D000A5086/C20 for the A320 Model -216 - 00D000A5191/C00 for the A320-252N - 00D000A5207/C00 for the A320-272N - 00D000A5232/C00 for the A320-253N - 00D000A5234/C00 for the A320-273N Note 2: For models, A320-211 and A320-212, modification 21038 is the minimum standard to be qualified for Cat IIIB precision approach. For models A320-231 modification 21039 is the minimum standard to be qualified for Cat IIIB precision approach. A320-214, A320-232, A320-233 are qualified for Cat IIIB precision approach per basic design definition. This does not constitute an operational approval. For models A320-251N, A320-252N, A320-271N & A320-272N modification 161765 is the minimum standard to be qualified for CAT IIIB precision approach. A28NM Page 49 of 103 All models Note 3: All Models of A320 airplanes manufactured after January 1, 1997 must have either modification 25302 (thrust reverser third line of defense for IAE V2500 engines) or 25303 (thrust reverser third line of defense for CFM engines) installed, before the individual U.S. standard Certificate of Airworthiness can be issued. Note 4: If modification 25800 is embodied on models with CFM56-5B engines, the engine performance is improved. The engine denomination changes to /P. CFM56-5B/”non-P” engine can be intermixed with CFM56-5B/P engine on the same aircraft. Note 5: If modification 26610 is embodied on A320-214 airplanes, the engine performance and gaseous emission levels are improved. The engine denomination changes to /2P (DAC IIC Dual Annual Combustor). • CFM56-5B4/P engine can be intermixed with CFM56-5B4/2P (DAC IIC Dual Annual Combustor) engine on the same aircraft (AFM Supplement). • CFM 56-5B/2 "non P" (DAC) engine can be intermixed with CFM 56-5B/2P (DAC II C) engine on the same aircraft (AFM supplement). • CFM 56-5B/P or / "non P" (SAC) engine can be intermixed with CFM 56-5B/2P (DAC II C) engine on the same aircraft (AFM supplement). Note 6: For A320-200 series airplanes with OCTOPUS Airplane Flight Manual, Airbus elected to comply with Part 25 Amendment 25-92. Note 7: If modification 23755 is embodied on A320 airplanes, the maximum permissible gas temperature for take-off and max. continuous operation is extended to 915° C and 880° C, respectively. However, the ECAM indication remains at 890° C and 855° C, respectively. The engine denomination changes to /F. A320-211 CFM 56-5A1 engine can be intermixed with CFM 56-5A1/F engine on the same aircraft. Note 8: On A320-200 series aircraft, one Additional Center Tank (ACT) in bulk version is defined by modification 34456 (low pressure system). The approval together with structural and system provisions was subject of compliance demonstrated to Advisory Circular AC 25-8. Note 9: A320-231 with modification 23872 (EGT redline increase for IAE V2500 engines) : • for consolidated bump rating operation (mod 22461 or 23408), the maximum permissible gas temperature is extend ed to 650° C at take-off. The ECAM indication remains at 635°; • for non rating bump operation, the maximum permissible gas temperature is extended to 640° C at take -off. The ECAM indication remains at 635° C; • for maximum continuous and take -off operation, the maximum permissible gas temperature is extended to 615° C. The ECAM indication remains at 610° C. Note 10: A320-231 with modification 25000 (FADEC Standard SCN12C for IAE engines) : • for take-off operation, the maximum permissible gas temperature is ext ended to 650°C. The ECAM indication remains at 635°C; • for maximum continuous operation, the maximum permissible gas temperature is extended to 625°C. The ECAM indication remains at 610°C. Note 11: If modification 37147 (Tech insertion program) is embodied in production or 38770 (Tech insertion program retrofit) is embodied in service on A320 airplanes, the engine performance and gaseous emission levels are improved. The engine denomination changes to /3. Note 12: If modification 37868 (Select One Package) is embodied in production or if modification 38554 (Select One Package for Retrofit) is embodied on in-service A320 airplanes the engine performance and gaseous emission levels are improved. The engine denomination itself does not change. Note 13: If modification 38573 is embodied in service on A320 airplanes, engine hardware configurations can be intermixed with one CFM56-5Bx/3 SAC (Tech Insertion) and one CFM56-5Bx/P SAC engine. A28NM Page 50 of 103 All models Note 14: If modification 34119 is embodied in production on A320 airplanes, CFM56-5B SAC (Single Annular Combustor) and CFM56-5B DAC (Double Annular Combustor) engines can be intermixed on the same aircraft. Note 15: If modification 150016 (structural and system provision for deactivation of the second pair of overwing emergency exits) is embodied on A320 airplanes, the aircraft is eligible for a maximum capacity of 145 passengers. The maximum number of passengers between any of the overwing exit doors and rear door is 90. Note 16: Further to “D/E/J Noise” Project approval, from November, 05th, 2009, all A320 airplane/engine configurations are eligible to be in compliance with ICAO Annex 16, Chapter 4 and FAR Part 36, Stage 4 (including Amdt 36-28). Note 17: From March 31, 2008, there are no longer any CFM56-5B4 non /P in field or in production. Note 18: For A320-211, -212, -231, -232 and –233 models, the embodiment of modification 37734 leads to change the maintenance program and its associated Maintenance Programme Publication Trigger from 48 000FC/60 000FH to 37 500FC/80 000FH (whichever occurs first). Note 19: If modification 38946 (“BUMP” function) is embodied on models with CFM-5B engines, the engine denomination changes to /P1 (SAC) or /2P1(DAC) or /3B1 (Tech Insertion). The engine characteristics defined in this section remain unchanged. Intermix at aircraft level between “Non Bump” engine and “Bump” engine is not allowed. Note 20: If modification 150206 is embodied on A320 airplanes, the aircraft is eligible for a maximum capacity of 150. The airplane is fully compliant with: - FAR121-311 Amdt 121-315 - Section 25.562 Amendment 25-64 for all passenger seats and flight attendant seats and - FAA Special Condition 25-375-SC for installation of inflatable restraints. Note 21: If modification 151226 is embodied on A320 airplanes the airplane is fully compliant with: - FAA Special Condition No. 25-403-SC for seat backs with large non-metallic panels and - Section 25.562 Amendment 25-64 for all passenger seats and flight attendant seats. Note 22: If Modification 160001 for installation of structural provisions for new large wingtip device (Sharklet) is embodied on A320 airplanes equipped with either CFM 56 or IAE V2500 engines the usable fuel quantities are reduced as shown above to account for the loss of volume due to structural reinforcements in the wing and center wing box. Note 23: If Modification 160500 for installation of new large wingtip devices (Sharklet) is embodied on A320 series airplanes the eco efficiency and payload-range performance is improved. Modification 160500 is approved for WV 008 to WV 019, only. If modification 160080 for retrofit installation of new large wingtip devices (Sharkelt) is embodied on in-service A320series airplanes the eco efficiency and payload-range performance is improved. Modification 160080 is approved for MSN 1200 and above only without Airbus Modification 160001 reinforced center wingbox, and for WV 008 to 014, 016, 018 and 019 only. The certification basis for Modification 160500 and 160080 is shown above. Note 24: On series A320-200 airplanes equipped with CFM 56 engines, introduction of a standard of wingbox without dry bay (modification 37331) increases the wing fuel capacity by 350 liters. Note 25: If Modification 150364 is embodied on A320 airplanes the aircraft can be operated with 150 passengers and with 3 cabin attendants for increased cabin operational flexibility. Note 26: On series A320-200 airplanes, one or two Additional Center Tanks (ACT) in bulk version are defined by modification 28378 (low pressure system). Their approval together with structural and system provisions was subject of compliance demonstrated to AC 25-8. A28NM Page 51 of 103 All models Note 27: If Modifications 156723 (MAX PAX) is installed on Models A320-214,-232 and -233 with large wingtip devices (Sharklets - Modification 160500), the airplane is eligible for Maximum Passenger Seating Capacity (MPSC) of 190 passengers. Note 28: If Modifications 157968 (MAX PAX) is installed on Models A320-211, -212, -214, -231, -232 and -233 with Wing Tip Fence (WTF), the airplane is eligible for Maximum Passenger Seating Capacity (MPSC) of 180 passengers. Note 29: If modification 161562 (Alternate climb) is installed on the Model A320-271N the engine designation changes to PW1127GA-JM. Note 30: If Modifications 158708 (MAX PAX) is installed on Models A320-211, -212, -214, -231, -232 and -233 with Wing Tip Fence (WTF), the airplane is eligible for Maximum Passenger Seating Capacity (MPSC) of 190 passengers. Note 31: Limitations associated with installation of MAX PAX Modification 159115 are referenced in ELOS Memo AT10769IB -T-CS-6 dated May 16, 2017. Note 32: If Modifications 158819 (MAX PAX) is installed on Models A320-214, -216, -232 & -233 with modification 160080 (sharklet in service retrofit), the airplane is eligible for Maximum Passenger Seating Capacity (MPSC) of 190 passengers. Note 33: For A320 -211, -212, -214, -231, -232 and –233 models, the embodiment of modification 3 9020 leads to change the maintenance program and its associated Maintenance Programme Publication Tr igger from 48 000FC/60 000FH or 37 500FC/80 000FH to 60 000FC/120 000FH (whichever occurs first). Note 34: If Modifications 156723 (MAX PAX) is installed on Models A320-251N, -252N, -253N, -271N, -272N, and -273N, the airplane is eligible for Maximum Passenger Seating Capacity (MPSC) of 190 passengers. Note 35: Serial Numbers Eligible: Until September 26, 2004, A320 aircraft, all series, all models, have been produced in Blagnac (France) under approval P09 or F.G.035 issued by DGAC to Airbus. From September 27, 2004 until April 14, 2008 , A320 aircraft, all series, all models, have been produced in Blagnac (France) under approval FR.21G.0035 issued by DGAC to Airbus. From April 15, 2008 until July 20, 2008, A320 aircraft, all series, all models, have been produced in Blagnac (France) under approval FR.21G.0035 issued by DGAC to Airbus or in Hamburg (Germany) under approval DE.21G.0009 issued by LBA to Airbus. From July 21, 2008 until May 5, 2009, A320 aircraft, all series, all models, have been produced in Blagnac (France) or Hamburg (Germany) under approval EASA.21G.0001 issued by EASA to Airbus. From May 06, 2009 to April 30, 2011 , A320 aircraft, all series, all models, are produced in Blagnac (France), Hamburg (Germany) or Tianjin (People’s Republic of China) under approval EASA.21G.0001 issued by EASA to Airbus. Since May 1, 2011 and in accordance with the TIP, “Technical Implementing Procedure for Airworthiness and Environmental Certification Between the Federal Aviation Administration of the United States of America and the European Union Aviation Safety Agency”, A320 aircraft, all series, all models, produced under approval EASA.21.G.0001 issued by EASA to Airbus are eligible, unless otherwise stated in this TCDS. Note 36: If modification 174714 (engine rating) is installed on the Model A320-271N, the engine designation changes to PW1127G1A-JM Alternate Climb C. Note 37: If modification 167791 is installed on the Model A320-271N, A320-272N, A320-273N equipped with PW1100G-JM base engine, then the engine model is changed to PW1100G/2-JM rating. A28NM Page 52 of 103 All models IV. Type A321-100/200 Series Transport Category Airplanes 1. Model A321-111, Approved December 20, 1995; 2. Model A321-112, Approved December 20, 1995; 3. Model A321-131, Approved December 20, 1995; 4. Model A321-211, Approved September 18, 1997; 5. Model A321-231, Approved September 18, 1997: 6. Model A321-212, Approved May 20, 2005; 7. Model A321-213, Approved May 20, 2005; 8. Model A321-232, Approved May 20, 2005. 9. Model A321-271N, Approved December 15, 2016. 10. Model A321-251N Approved March 1, 2017 11. Model A321-253N Approved March 3, 2017 12. Model A321-272N Approved July 6, 2017 13. Model A321-252N Approved February 21, 2018 14. Model A321-251NX Approved March 22, 2018 15. Model A321-252NX Approved March 22, 2018 16. Model A321-253NX Approved March 22, 2018 17. Model A321-271NX Approved March 22, 2018 18. Model A321-272NX Approved March 22, 2018 19. Model A321-253NY Approved October 2, 2024 20. Model A321-271NY Approved February 21, 2025 Engines: Model A321-111 & A321-212, Two CFMI Model CFM56-5B1 or CFM56-5B1/P or CFM56-5B1/2P or CFM56-5B1/3 jet engines; Model A321-112 & A321-213, Two CFMI Model CFM56-5B2 or CFM56-5B2/P or CFM56-5B2/3 jet engines; Model A321-131 & A321-232, Two IAE Model V2530-A5 jet engines Model A321-211, Two CFMI Model CFM56-5B3/P or CFM56-5B3/2P or CFM56-5B3/P1 or CFM56-5B3/2P1 or CFM56-5B3/3 or CFM56-5B3/3B1 jet engines Model A321-231, Two IAE Model V2533-A5 jet engines Model A321-271N, -271NX, Two IAE Model PW1133G-JM or PW1133GA-JM or PW1133G1-JM jet engines Model A321-251N, -251NX; Two CFMI model LEAP 1A32 jet engines Model A321-253N, -253NX; Two CFMI model LEAP 1A33 or LEAP 1A35 jet engines Model A321-272N, -272NX; Two IAE Model PW1130G-JM jet engines Model A321-252N, -252NX; Two CFMI model LEAP 1A30 jet engines Model A321-253NY; Two CFMI model LEAP-1A33X or LEAP-1A33B2X jet engines Model A321-271NY; Two IAE Model PW1133GR-JM or PW1133GAR-JM jet engines See Note 6 for description of “/P” engine models See Notes 11 and 12 for description of “/2P” engine models See Note 13 for description of “/3” engine models See Note 14 for description of “ “ engine models (Select One Package) See Note 19 for description of “/P1” or “/2P1” or “/3B1” engine models Fuel: See Installation Manual - Documents CFM 2026 or CFM 2129 or Service Bulletin 73-0001 or IAE-0043 or Service Bulletin PW1000G-1000-73-00-0002 00A930AD A321-111/-112/-131/-211/-231/-212/-213/-232 TYPE SPECIFICATION (NAME) FRANCE USA UK Kerosene DCSEA 134-D (F-34) ASTM D 1655 (JET A) (JET A1) DEF STAN 91/91 (AVTUR) (JET A1) MIL-DTL- 83133-H (JP 8) DEF STAN 91/87 iss 7 (AVTUR/FSH) (JET A1) (AIA) Wide cut ASTM D 6615 (JET B) DEF STAN 91/88 (AVTAG/FSH) MIL-DTL-5624 (JP 4) High flash point DCSEA 144-C (F-44) MIL-DTL- 5624-V (JP 5) DEF STAN 91/86 iss 7 (AVCAT) A28NM Page 53 of 103 All models A321-271N/-272N/-251N/-252N/-253N/-271NX/-272NX/-251NX/-252NX/-253NX/-253NY TYPE SPECIFICATION (NAME) USA UK Kerosene ASTM D 1655 (JET A) (JET A1) DEF STAN 91/91 (AVTUR) (JET A1) MIL-DTL- 83133-H (JP 8) DEF STAN 91/87 iss 7 (AVTUR/FSII) (JET A1) (AIA) High flash point MIL-DTL-5624- V (JP 5) DEF STAN 91/86 iss 7 (AVCAT) Additives: See CFMI " Specific Operating Instructions," CMF TPOI-13 or Service Bulletin 73-0001 or IAE V2500 “Installation and Operating Manual” IAE-0043, 4.5 or the “Standard Practices and Processes Manual” in IETM or Service Bulletin PW1000G-1000-73-00-0002-00A-930A-D. The above mentioned fuels and additives are also suitable for the APU. Engine Limits: CFMI CFM56-5B1*** or - 5B1/P or –5B1/2P or -5B1/3 CFMI CFM56-5B2 or -5B2/P or -5B2/3 CFMI CFM56-5B3/P or –5B3/2P or -5B3/P1 or – 5B3/2P1 or -5B3/3 or - 5B3/3B1 Engine Limitation Data Sheets Data Sheets Data Sheets E37NE E38NE (FAA) E37NE E38NE (FAA) E37NE E38NE (FAA) Static Thrust at Sea Level - Take-off (5 min)** 13 344 daN (30 000 lb) 13 789 daN (31 000 lb) 14 234 daN (32 000 lb) (Flat rated 30°C) Maximum Continuous 12 940 daN (29 090 1b) 12 940 daN (29 090 1b) 12940 daN (29 090 lb) (Flat rated 25°C) Maximum Engine Speed - N1 rpm (%) 5 200 (104) 5 200 (104) 5 200 (104) - N2 rpm (%) 15 183 (105) 15 183 (105) 15 183 (105) Max Gas Temperature (°C) - Take-off (5 min)** 950 950 950 - Max Continuous 915 915 915 - Starting * 725 725 725 Max Oil Temperature (Supply Pump Inlet; °C) - Take-off, Stabilized 140 140 140 - Transient (15 min max) 155 155 155 Min. Press. (PSI) 13 13 13 Approved Oils See SB CFMI 79-001-OX See SB CFMI 79-001-OX See SB CFMI 79-001-OX IAE V2530-A5 IAE V2533-A5 PW1133G-JM/ PW1133GA- JM / PW1133G1-JM / PW1130G-JM Engine Limitation FAA Data Sheets E40NE FAA Data Sheets E40NE FAA Data Sheet E00087EN Static Thrust at Sea Level - Take-off (5 min)** 13 300 daN (29 900 lb) 14 055 daN (31 600 lb) 14 728 daN (33 110lb) (Flat rated 30°C) Maximum Continuous 11 988 daN (26 950 1b) 11 988 daN (26 950 lb) 14 581 daN (32 780lb) (Flat rated 25°C) 13 527 daN (30 410lb) (PW1130G-JM) Maximum Engine Speed - N1 rpm (%) 5 650 (100) 5 650 (100) 10 047(105) - N2 rpm (%) 14 950 (100) 14 950 (100) 22300(105) Max Gas Temperature (°C) Eng. Limit/ ECAM Eng. Limit/ ECAM - Take-off (5 min)** 650/650 670/650 1083 A28NM Page 54 of 103 All models IAE V2530-A5 IAE V2533-A5 PW1133G-JM/ PW1133GA- JM / PW1133G1-JM / PW1130G-JM Engine Limitation FAA Data Sheets E40NE FAA Data Sheets E40NE FAA Data Sheet E00087EN - Max Continuous 610/610 610/610 1043 - Starting * 635/635 635/635 1083 Max Oil Temperature (Supply Pump Inlet; °C) - Take-off, Stabilized 155 155 152 - Transient (15 min max) 165 165 141 Min. Press. (PSI) 60 60 63 Approved Oils See Doc IAE 0043 Sec 4.9 (MIL-L-23699) See Doc IAE 0043 Sec 4.9 (MIL-L-23699) See SB PW1000G-1000-79-00-0002- 00A-930A-D Engine Limits Continued: Engine Limitation CFMI LEAP-1A32 Data Sheet E00089EN (FAA) CFMI LEAP-1A33 /-1A35A Data Sheet E00089EN (FAA) CFMI LEAP-1A30 Data Sheet E00089EN (FAA) Static Thrust at Sea Level - Take-off (5 min)** 14 305 daN (32 160lb) 14 305 daN (32 160lb) 14 305 daN (32 160lb) (Flat rated 30°C) Maximum Continuous 14 096 daN (31 690lb) 14 096 daN (31 690lb) 14 096 daN (31 690lb) (Flat rated 25°C) Maximum Engine Speed - N1 rpm (%) 3 894 (101.0) 3 894 (101.0) 3 894 (101.0) - N2 rpm (%) 19 391 (116.5) 19 391 (116.5) 19 391 (116.5) Max Gas Temperature (°C) - Take-off (5 min)** 1060 1060 1060 - Max Continuous 1025 1025 1025 - Starting (ground) 750 750 750 Max Oil Temperature (Supply Pump Inlet; °C) - Take-off, Stabilized 140 140 140 - Transient (15 min max) 155 155 155 Min. Press. (PSI) 29 redline/17.4 idle 29redline/17.4 idle 29redline/17.4 idle Approved Oils See SB 79-0001 See SB 79-0001 See SB 79-0001 Engine Limits Continued: Engine Limitation CFMI LEAP-1A33X Data Sheet E00089EN (FAA) CFMI LEAP-1A33B2X Data Sheet E00089EN (FAA) Static Thrust at Sea Level - Take-off (5 min)** 14 305 daN (32 160lb) 14 305 daN (32 160lb) (Flat rated 30°C) Maximum Continuous 11 054 daN (24 850lb) 11 054 daN (24 850lb) (Flat rated 25°C) Approved Oils See SB 79-0001 See SB 79-0001 * 4 Consecutive cycles of 2 minutes each. **10 minutes at take-off thrust allowed only in case of engine failure (at take-off or during go-around) *** See Note 18 for engine models no longer in production/service A28NM Page 55 of 103 All models Engine Limitation PW1133GR-JM Data Sheet E00087EN (FAA) PW1133GAR-JM Data Sheet E00087EN (FAA) Static Thrust at Sea Level - Take-off (5 min)** 14728 daN (33110 lb) 14728 daN (33110 lb) (Flat rated 30°C) Maximum Continuous 10342 daN (23250 lb) 10342 daN (23250 lb) (Flat rated 25°C) Approved Oils See SB PW1000G-D- 79-00-0002-930A-D See SB PW1000G-D- 79-00-0002-930A-D **10 minutes at take-off thrust allowed only in case of engine failure (at take-off or during go-around) Airspeed Limits (Indicated Airspeed - IAS - Unless otherwise Stated: - Maximum Operating Mach - MMO: 0.82 - Maximum Operating Speed - VMO: 350 kt - Maneuvering Speed VA: - See the Limitations Section of Aircraft Flight Manual - Extended Flaps/Slats Speed - VFE For A321-111/-112/-131/-211/-212/-213/-231/-232 the following table applies: Configuration Slats/Flaps VFE (Kt) 1 18/0 230** Intermediate Approach 18/10 215** Take-off 2 22/14 205 Take-off and Approach 215* 3 22/21 195 Take-off, Approach, and Landing Full 27/25 190 Landing * See Note 4 ** See Note 10 For A321-271N/-272N/-251N/-252N/-253N the following table applies: Slats/Flaps Configuration (°) VFE (kt) 1 18/0 238/243* Intermediate approach 18/10 225 Take-off 2 22/14 215 Take-off and approach 3 22/21 195 Take-off, approach, landing Full 27/34 186 Landing *For A321-251NX,-252NX,-253NX,-271NX,-272NX For A321-253NY/-271NY the following table applies: Slats/Flaps Configuration (°) VFE (kt) 1 18/0 18/10 260 218 Intermediate approach Take-off 22/14 22/14 206 206 Approach Take-off 2 22/16 201 Take-off 3 22/23 22/26 195 191 Take-off Full 27/34 180 Landing A28NM Page 56 of 103 All models Landing Gear: - VLE - Extended: 280 Kt/Mach 0.67 - VLO - Extension: 250 kt - Retraction: 220 kt Tire Limit Speed (Ground Speed) = 204.2 kt (235 mph) Maximum Certified Weights: A321-111-/112 A321-131 (KG) (LBS) A321-211/-231 (KG) (LBS) A321-212/-213/-232 (KG) (LBS) Max. Take-off Weight 85 000 187 391 93 500 206 132 93 500 206 132 Max. Landing Weight 74 500 164 243 77 800 171 517 77 800 171 517 Max. Zero Fuel Weight 70 500 155 424 73 800 162 699 73 800 162 699 Minimum Weight 47 500 104 718 47 500 104 718 47 500 104 718 A321-271N/-272N/-251N/- 252N/-253N (KG) (LBS) A321-271NX/ -272NX/ - 251NX/ -252NX/ -253NX/ (KG) (LBS) A321-253NY -271NY (KG) (LBS) Max. Take-off Weight 93 500 206 132 97 000 213 848 101 000 222 667 Max. Landing Weight 79 200 174 606 79 200 174 606 79 200 174 606 Max. Zero Fuel Weight 75 600 166 669 75 600 166 669 75 600 166 669 Minimum Weight 46 300 102 075 (PW) 46 600 102 736 (CFM) 46 300 102 075 (PW) 46 600 102 736 (CFM) 46 300 102 075 (PW) 46 600 102 736 (CFM) See applicable Airplane Flight Manual (AFM), as listed in ‘Operating and Service Instructions’, for configuration specific mass limitations and aircraft eligibility (Weight Variant). Minimum Crew: 2 Pilots Maximum Passengers: A321-111/-112/-131/-211/-231/-212/-213/-232/-271N/-272N/-251N/-252N/-253N: 220 see note 20 and 24, 29, 32 A321-251NX/-252NX/-253NX/-253NY/-271NX/-272NX/-271NY: 244 Maximum Baggage: A321-111/-112/-131/-211/-231/-212/-213/-232/-271N/-272N/-251N/-252N/-253N CARGO COMPARTMENT MAXIMUM LOAD (KG) (LBS) Forward 5 670 12 500 Aft 5 670 12 500 Rear (Bulk) 1 497 3 300 A321-251NX/-252NX/-253NX/-253NY/-271NX/-272NX/-271NY CARGO COMPARTMENT MAXIMUM LOAD (KG) (LBS) Forward 5 670 12 500 Aft 5 670 12 500 Rear (Bulk) 800 1 764 For the positions and the loading conditions authorized in each position (references of containers, pallets, and associated weights), see Weight and Balance Manual, ref. 00E080A0001/C1S Chapter 1.10. A28NM Page 57 of 103 All models Fuel Capacity (0.8 kg/liter): A321-111/-112/-131/-211/-231/-212/-213/-232: 3-Tank Airplane Tank Usable Fuel Unusable Fuel Liters (kgs) Gallons (lbs) Liters (Kgs) Gallons (lbs) Wing 15 500 4 094 22.6 6 (12 400) (27 331) (18) (39.6) Center 8 200 2 166 23.2 6.1 (6 560) (14 460) (18.6) (40.97) TOTAL 23 700 6 260 45.8 12.1 (18 960) (41 791) (36.6) (80.62) A321-200 4-Tank Airplane (high pressure ACT system) (*) Tank Usable Fuel Unusable Fuel Liters (kgs) Gallons (lbs) Liters (Kgs) Gallons (lbs) Wing 15 500 4 094 22.6 6 (12 400) (27 331) (18) (39.6) Center 8 200 2 166 23.2 6.1 (6 560) (14 460) (18.6) (40.97) ACT 2 900 766 17 4.5 (2 320) (5 114) (13.6) (29.96) TOTAL 26 600 7 026 62.8 16.6 (21 280) (46 905) (50.2) (110.58) (*) see note 7 4 to 5-Tank Airplane (**) (low pressure ACT system) Tank Usable Fuel Unusable Fuel Liters (kgs) Gallons (lbs) Liters (Kgs) Gallons (lbs) TOTAL 3-Tank 23 700 6 260 45.8 12.1 Airplane (18 960) (41 791) (36.6) (80.62) ACT 1 2 992 790 17 4.5 (2 393) (5 274) (13.6) (29.96) TOTAL 4-Tank 26 692 7 050 62.8 16.6 Airplane (21 353) (47 065) (50.2) (110.58) ACT 2 2 992 790 17 4.5 (2 393) (5 274) (13.6) (29.96) TOTAL 5-Tank 29 684 7 840 79.8 21.1 Airplane (23 746) (52 339) (63.8) (140.54) (**) See note 9 A321-271N/-272N/-251N/-252N/-253N 3-Tank Airplane Tank Usable Fuel Unusable Fuel Liters (kgs) Gallons (lbs) Liters (Kgs) Gallons (lbs) Wing 15 380 4063 22.6 6 (12 073) (26 616) (18) (39.6) Center 8 200 2 166 23.2 6.1 (6 437) (14 189) (18.6) (40.97) TOTAL 23 580 6 229 45.8 12.1 (18 510) (40 805) (36.6) (80.62) A28NM Page 58 of 103 All models A321-271N/-251N/-252N/-253N/-272N 4 to 5-Tank Airplane (**) (low pressure ACT system) Tank Usable Fuel Unusable Fuel Liters (kgs) Gallons (lbs) Liters (Kgs) Gallons (lbs) TOTAL 3-Tank 23 580 6 229 45.8 12.1 Airplane (18 510) (40 805) (36.6) (80.62) ACT 1 2 992 790 17 4.5 (2 393) (5 274) (13.6) (29.96) TOTAL 4-Tank 26 572 7 019 62.8 16.6 Airplane (20 903) (46 079) (50.2) (110.58) ACT 2 2 992 790 17 4.5 (2 393) (5 274) (13.6) (29.96) TOTAL 5-Tank 29 564 7 809 79.8 21.1 Airplane (23 296) (51 353) (63.8) (140.54) A321-271NX/-272NX/-251NX/-252NX/-253NX 3-Tank Airplane Tank Usable Fuel Unusable Fuel Liters (kgs) Gallons (lbs) Liters (Kgs) Gallons (lbs) Wing 15 380 4063 22.6 6 (12 073) (26 616) (18) (39.6) Center 8 200 2 166 23.2 6.1 (6 437) (14 189) (18.6) (40.97) TOTAL 23 580 6 229 45.8 12.1 (18 510) (40 805) (36.6) (80.62) 4 to 6-Tank Airplane Tank Usable Fuel Unusable Fuel Liters (kgs) Gallons (lbs) Liters (Kgs) Gallons (lbs) TOTAL 3-Tank 23 580 6 229 45.8 12.1 Airplane (18 510) (40 807) (36.6) (80.62) ACT AFT 1 3 121 824 17 4.5 (2 450) (5 401) (13.6) (29.96) TOTAL 4-Tank 26 701 7 053 62.8 16.6 Airplane (20 960) (46 209) (50.2) (110.58) ACT AFT 2 3 121 824 17 4.5 (2 450) (5 401) (13.6) (29.96) TOTAL 5-Tank 29 822 7 877 79.8 21.1 Airplane (23 410) (51 609) (63.8) (140.54) ACT FWD 3 121 824 17 4.5 (2 450) (5 401) (13.6) (29.96) TOTAL 6-Tank 32 943 8 701 96.8 25.6 Airplane (25 860) (57 010) (77.4) (170.50) A28NM Page 59 of 103 All models A321-253NY/-271NY 4-Tank Airplane Tank Usable Fuel Unusable Fuel Liters (kgs) Gallons (lbs) Liters (Kgs) Gallons (lbs) Wing 15 380 4063 22.6 6 (12 073) (26 616) (18) (39.6) Center 8 150 2 153 23.2 6.1 (6 397) (14 103) (18.6) (40.97) Rear Center Tank (RCT) 12961 (10 174) 3424 (22 429) 205 (164) 54 (361) TOTAL 36 491 9640 251 66.3 (28 645) (63 151) (201) (443) 5-Tank Airplane Tank Usable Fuel Unusable Fuel Liters (kgs) Gallons (lbs) Liters (Kgs) Gallons (lbs) Total 4-tank Airplane 36 491 9640 251 66.3 (28 645) (63 151) (201) (443) FWD ACT 3121 824 17 4.5 (2 449) (5 401) (13.6) (29.96) TOTAL 39 612 10 464 268 70.8 (31 094) (68 552) (214.6) (472.96) Oil Capacity: CFMI CFM56-5B - Engine Oil Capacity, 10 quarts/engine (9.46 liters). IAE V2500-A5 - Engine Oil Capacity, 7 quarts/engine (6.6 liters) IAE PW1100G-JM – Engine Oil Capacity 34.9 quarts/engine (33.0 liters) CFMI LEAP-1A – Engine Oil Capacity 21.3 quarts/engine (20.1 liters) Maximum Operating Altitude: - 39 800 feet (12 200 m) clean if modification 30748 is embodied. - 39 100 feet (12 000 m) clean. - 20 000 feet (6 500 m) Slats/Flaps extended. Equipment: The basic equipment as prescribed in the airworthiness regulations (see certification basis) must be installed in the aircraf t for certification. Equipment approved for installation are listed in the definition of the reference model and the modification applicable to it. Refer to Type Certification Standard Equipment Schedule Lists: - 00E000A0007/C1S for A321-111 Model - 00E000A0006/C1S for A321-112 Model - 00E000A0004/COS for A321-131 Model - 00E000A0211/COS for A321-211 Model - 00E000A0231/COS for A321-231 Model - 00E000A0212/C0S for A321-212 Model - 00E000A0213/C0S for A321-213 Model - 00E000A0232/C0S for A321-232 Model Refer to Note 1 for list of A321 airplane model FAA Type Definitions. Import Requirements: A FAA Standard Airworthiness Certificate may be issued based on a German Export Certificate of Airworthiness (Export C of A), signed by a representative of the Luftfahrt -Bundesamt (LBA) of Germany on behalf of the European Community or based on a EASA Export C of A issued by a representative of EASA. The Export C of A should contain the following statement: “The aircraft covered by this certificate has been examined, tested, and found to conform to the Type Design approved under FAA Type Certificate No. A28NM and to be in a condition for safe operation.” Refer to the applicable bilateral agreement to verify eligibility for import into the United States of both new and used aircraft based on the scope of the agreement, to identify any required statements by the exporting authority on the export certificate of airworthiness (or equivalent document), and for procedures for coordinating exceptions to conformity statements on these documents. Refer to FAA Order 8130.2, Airworthiness Certification of Aircraft, for requirements for issuance of an airworthiness certificate for imported aircraft.” A28NM Page 60 of 103 All models Certification Basis (A321-100 and A321-200) a. Part 25 of the FAR effective February 1, 1965, including amendments 25-1 through 25-56 thereto. a.1. Plus the following sections of Part 25 as amended by amendments 25-1 through: - 25-58 (Section 25.812(e)) - 25-63 (Section 25.25(a)(3)) - 25-67 (Section 25.807(c)(7)) - 25-70 (Section 25.1411(a)(2)) (Applied per FAA derivative aircraft policy – reference FAA order 8110.4A) a.2. Airbus elected to comply with portions of FAR 25.562, Amendment 64, for the passenger seats only. FAR paragraphs 25.562(c)(5) and 25.562(c)(6) do not apply. b. Based on 14 CFR Section 21.29(a) for new import Type Certificates (TCs), (or Section 21.101(g) for changes to TCs), applicable provisions of 14 CFR Part 26 are included in the certification basis. For any future 14 CFR part 26 amendments, the holder of this TC must demonstrate compliance with the applicable sections. c. 14 CFR Part 34 of the FAR effective September 10, 1960, including amendments 34-1. d. 14 CFR Part 36 of the FAR effective December 1, 1965, including amendments 36-1 through 36-20 thereto. See Note 17. 14 CFR Part 36 through Amendment 36-31, Stage 5 for models; A321-251N, A321-252N, A321-253N, A321-271N, and A321-272N. The means of implementation of Stage 5 recertification must be provided by Airbus to ensure availability of the revised AFM noise pages for all affected aircraft. AFM CP293 issue 1.0 dated October 2, 2018 or later revision approved by EASA. e. FAA Special Conditions issued for the A320 in accordance with Section 21.16 of the FAR: (1) No. 25-ANM-23, Effective December 15, 1988: • Electronic Flight Controls • Active Controls • Engine Controls and Monitoring • Protection from Lightning and Unwanted Effects of Radio Frequency (RF) Energy • Flight Characteristics • Flight Envelope Protection • Side Stick Controllers • Flight Recorder. (2) No. 25-ANM-29, Effective May 31, 1989: • Computerized Airplane Flight Manual (3) No. 25-671-SC, Effective May 16, 2017: • Non-Rechargeable Lithium Batteries – Applicable to Type design changes applied after May 16, 2017. Reference the applicability section of this special condition for more information on which Type design changes must meet it. (4) No. 25-729-SC, Effective June 28, 2018: • Electronic System Security Protection from Unauthorized Internal Access - Applicable to type design changes applied after June 28, 2018. (5) No. 25-730-SC, Effective June 28, 2018: • Electronic System Security Protection from Unauthorized External Access - Applicable to type design changes applied after June 28, 2018. f. For precision approach and landing, the applicable technical requirements are complemented by AC 120-29 and AC 120-28c. For the automatic flight control system, the applicable technical requirements are complemented by AC 20 -57A for automatic landing and by AC 25.1329-1A for cruise. Use of JAR AWO where applicable to the requirements above, is acceptable. g. The following sections of the FAR have been complied with through equivalent safety demonstrations in addition to the equivalent safety findings applicable from the original A320 certification basis: - 25.101, 25.105, 25.109, 25.113, 25.115, 25.735, for rejected take-off and landing performance - 25.305, 25.331, 25.333, 25.335, 25.341, 25.345, 25.349, 25.351, 25.371, 25.373, 25.391, 25.427, for design gust A28NM Page 61 of 103 All models criteria - 25.783(e) bulk cargo door - 25.783(f) for passenger doors - 25.807(c) for maximum passenger capacity - 25.933(a) for thrust reversing system. h. Optional requirements elected: - 25.801 for ditching. - 25.1419 for icing. Certification Basis for Airbus Model A321 series airplanes with modification 160023 installation of large wingtip device (Sharklet): The original certification basis for the Model A321 shown above for components or areas not affected by the change. Plus the following sections of 14 CFR part 25 as amended by Amendments 25-1 through 25-129 (i.e., the amendment in effect on the date of application April 8, 2010) applied to the components and areas affected by the change: 25.23, 25.25, 25.101, 25.109, 25.113, 25.115, 25.117, 25.161, 25.171, 25.173, 25.203, 25.235, 25.251, 25.301, 25.303, 25.305, 25.307(a)(d), 25.321, 25.331, 25.333, 25.335, 25.337, 25.341(a)(b), 25.343, 25.345, 25.349, 25.351, 25.365(a)(b)(d), 25.367, 25.371, 25.373, 25.391, 25.393(b), 25.427, 25.445, 25.457, 25.459, 25.471(a)(b), 25.473, 25.479(a)(c)(d), 25.481(a)(c), 25.483, 25.485, 25.489, 25.581, 25.601, 25.603, 25.605, 25.607, 25.609, 25.613, 25.619, 25.623, 25.625, 25.629, 25.631, 25.651, 25.671, 25.672, 25.683(b), 25.903(d)(1), 25.1011(b), 25.1385(a)(b)(d), 25.1387(a)(b)(c)(d), 25.1389, 25.1391, 25.1393, 25.1395, 25.1397, 25.1401, 25.1505, 25.1511, 25.1515, 25.1517, 25.1527, 25.1533, 25.1535, 25.1581, 25.1585(a) Plus the following sections of 14 CFR part 25 amended as indicated below applied to the components and areas affected by the change per Airbus reversion justification: 25.21 Amdt 1201 25.181 Amdt 1072 25.103 Amdt 1071&2 25.201 Amdt 1072 25.105 Amdt 1201 25.207 Amdt 1071&2 25.107 Amdt 1071&2 25.231 Amdt 1072 25.111 Amdt 1201 25.233 Amdt 1072 25.119 Amdt 1071&2 25.237 Amdt 107 1&2 25.121 Amdt 1071&2 25.253 Amdt 1201 25.123 Amdt 1201 25.571(a)(b)(e) Amdt 863 25.125 Amdt 1071&2 25.981 Amdt 564 25.143 except (g) Amdt 1071&2 25.1001 Amdt 1071 25.143(g) at Amdt 1081 25.1301 Amdt 565 25.145 Amdt 971&2 25.1309 Amdt 565 25.147 Amdt 1072 25.1419 Amdt 561 25.149 Amdt 1072 25.1587 Amdt 1071 25.175 Amdt 1072 Notes: 1. FAA acceptance of these reversions was based on the fact that Airbus has done additional testing above the requirements incorporated by reference as documented in EASA AMC-F14, dated November 29, 1993, Flight in Icing Conditions, and a determination that compliance with the amendment in effect on the date of application for these rules (i.e., Amendment 25-121) would not materially increase the level of safety exception of 14 CFR 21.101(b)(3). EASA AMC-F14 is incorporated as part of the certification basis for this airplane. 2. FAA acceptance of these reversions was based on fact that Airbus will show compliance with FAA Special Condition 25-ANM-23 for VSR and a determination that compliance with the amendment in effect on the date of application for these rules (i.e., Amendment 25-108) would not materially increase the level of safety exception of 14 CFR 21.101(b)(3). 3. FAA acceptance of this reversion was based on a determination that compliance with the amendment in effect on the date of application for this rule (i.e., Amendment 25-96) would not materially increase the level of safety exception of 14 CFR 21.101(b)(3). A28NM Page 62 of 103 All models 4. FAA acceptance of this reversion was based on a determination that compliance with the amendment in effect on the date of application for this rule (i.e., Amendment 25-102) would not materially increase the level of safety exception of 14 CFR 21.101(b)(3). 5. FAA acceptance of this reversion was based on a determination that compliance with the amendment in effect on the date of application for this rule (i.e., Amendment 25-123) would not materially increase the level of safety exception of 14 CFR 21.101(b)(3). Plus the following sections of part 25 amended as indicated below based on Airbus elect to comply: 25.107(e)(1)(iv) Amendment 25-135 25.177 Amendment 25-135 Special conditions: The FAA Special Conditions applicable to each model as defined above remain applicable to aircraft equipped with Sharklet, except Paragraph 2 – Active Controls of FAA Special Condition 25-ANM-23 is replaced with the following special conditions: • No. 25-469-SC Effective October 11, 2012 - “Interaction of Systems and Structures” • No. 25-470-SC Effective October 11, 2012 - “Design Dive Speed” • No. 25-471-SC Effective October 11, 2012 - “Design Roll Maneuver Conditions” Equivalent Safety Findings (ESFs): The original ESFs applicable to each model as defined above remain effective for aircraft equipped with Sharklet plus the following ESF for aircraft equipped with Sharklet: 25.331 – Use of EASA Certification Specification (CS) 25.331 in lieu of 14 CFR 25.331 for checked pitch maneuver (reference ELOS memorandum TD000885IB-T-A-5) 25.1419 – Analysis instead of flight testing in natural icing conditions (reference ELOS memorandum TD00885IB-T-SE-1) Noise standards 14 CFR 21.93(b) – No acoustical change Fuel venting and exhaust emissions standards Not affected by the change. The initial requirements remain applicable. Optional Requirements elected • 25.801 for ditching. • 25.1419 for icing. • 25.1535 for ETOPS Part 26 14 CFR part 26 effective December 10, 2007, including Amendments 26-1 through 26-3. Certification basis for the Airbus Model A321-211, -212, -213, -231 and -232 installed with large wingtip device (Sharklet Modification 160023) and Modification 157272(Max Pax), for the certification of a Maximum Passenger Seating Capacity (MPSC) of 230 passengers: The original certification basis for the Model A321-211, -212, -213, -231 and -232 installed with large wingtip device (Sharklet Modification 160023) plus the following sections of 14 CFR part 25 as amended by Amendments 25-1 through 25-139 applied to the components and areas affected by the change, equivalent level of safety finding, Optional Design Regulations, 14 CFR part 26, Additional Design Requirements and Conditions: 14 CFR Section FAA Accepted Amendment Level System/Component/Area Affected by the Change 25.23 139 Fuselage Structure 25.321 139 Fuselage Structure 25.331 139 Fuselage Structure 25.341(a)(b) 139 Fuselage Structure 25.351 139 Fuselage Structure A28NM Page 63 of 103 All models 14 CFR Section FAA Accepted Amendment Level System/Component/Area Affected by the Change 25.473 139 Fuselage Structure 25.479(a)(c)(d) 139 Fuselage Structure 25.481(a)(c) 139 Fuselage Structure 25.489 139 Fuselage Structure 25.801(d) 139 Entire Airplane 25.803(c) 139 Cabin Interior 25.807 139 Cabin Interior 25.810 139 Cabin Interior 25.811 139 Cabin Interior 25.813 139 Cabin Interior 25.815 139 Cabin Interior 25.1447(c)(1) 139 Passenger equipment associated with increased MPSC 25.1519 139 Entire Airplane 25.1529 139 ICA associated with increased MPSC 25.1541(a)(b) 139 Marking & Placards associated with increased MPSC 25.1557(a) 139 Marking & Placards associated with increased MPSC The following sections of 14 CFR part 25 amended as indicated below and applied to the components and areas affected by the change, have been determ ined in accordance with the § 21.101(b)(3) that compliance with the Amendment 25 -139 would not materially increase the level of safety: 14 CFR Section FAA Accepted Amendment Level 25.305(a)(b),25.307(a),25.365(a) 129 25.562 64 25.571(a)(b) 86 25.561, 25.785, 25.787(a)(b), 25.789(a), 25.791, 25.809, 25.812(e)(k)(l), 25.853(a)(b), 25.1301, 25.1309, 25.1351(a), 25.1353(a)(b), 25.1357(a)(c)(g)(e), 25.1359(a)(d), 25.1413, 25.1415(b)(c)(d), 25.1431(c), 25.1561 56 25.853(c)(d)(e) 116 Equivalent Safety Findings: In accordance with the provisions of § 21.21(b)(1) the following new ELOS finding is applicable to Modification 157272 (MaxPax): AT10407IB-T-CS-2 § 25.807 Emergency Exits Finding for Increase of the Maximum Passenger Capacity (MPSC) from 220 passengers to 230 passengers Optional Design Regulations: ETOPS: Modification 157272 (MaxPax) has not been evaluated for extended operations (ETOPS) type design approval on Models A321-211, -212, -213, -231 and -232 airplanes installed with large wingtip device (Sharklet Modification 160023).. Part 26: Based on 14 CFR § 21.101(g), applicable provisions of 14 CFR part 26 are included in the certification basis. For any future 14 CFR part 26 amendments, the holder of this TC must demonstrate compliance with the applicable sections. The type design complies with the following 14 CFR part 26 Amendments 26-1 through 26-6 regulations: §§ 26.11, 26.33, 26.43, and 26.45. A28NM Page 64 of 103 All models Additional Design Requirements and Conditions: Limitation: • The exit passageway width, starting at the aircraft aisle centerline and extending 21 inches outboard from the aircraft aisle centerline, must be a minimum of 23.2 inches. Any attendant seat/fixture installed on the side of the exit passageway must not result in a passageway less than 23.2 inches for the inboard portion of the passageway. The remaining passageway (starting 21 inches from the aircraft centerline to the emergency exit) must be a minimum of 20 inches. The height of the attendant seat/fixture is limited to a maximum height of 56.5 inches. • The unobstructed exit dimensions of the floor level emergency exits must not be less than 32 inches x 73 inches. • A wide slide (sliding surface width 82.75 inches (+3.0 inches, -2.0 inches)) must be installed at doors 1 and 4. • The wide slides installed at doors 1 and 4 must have a beam strength meeting the requirements of TSO C69c Certification basis for the Airbus Model A321-271N/-272N/-251N/-252N/-253N (Single Aisle New Engine Option): The certification basis for the Airbus Model A321 series airplanes with Modification 160023 - installation of large wingtip device (Sharklet) for components or areas not affected by the change. Plus the following sections of 14 CFR part 25 as amended by Amendments 25-1 through 25-136 (i.e., the amendment in affect on the date of application) applied to the components and areas affected by the change: 25.3, 25.23(a)(b), 25.25(a)(b), 25.27, 25.101, 25.107(e)(1)(iv), 25.109, 25.113, 25.115, 25.117, 25.147, 25.149, 25.161, 25.171, 25.173, 25.175, 25.177, 25.181, 25.201, 25.203, 25.231, 25.233, 25.235, 25.251(a)(b)(c)(d)(e), 25.253(a)(b), 25.255, 25.301*, 25.303*, 25.305(a)(b)(c)*, 25.307(a)(d)*, 25.321(a)(b)(c)(d), 25.331(a)(b)(c), 25.333(a)(b), 25.335(a)(b)(c)(d)(e)(f), 25.337, 25.341(a)(b), 25.343(a)(b), 25.345(a)(b)(d), 25.349(a)(b), 25.351, 25.361, 25.363, 25.365(a)(b)(c)(d)(e)*, 25.367(a)(b), 25.371, 25.373, 25.391(a)(b)(c)(d)(e), 25.427(a)(b)(c)(d), 25.445(a)(b), 25.457, 25.459, 25.471(a)(b), 25.473, 25.479(a)(c)(d), 25.481(a)(c), 25.483, 25.485(a)(b), 25.489, 25.491, 25.493(b)(c)(d), 25.495, 25.499(a)(b)(c)(d)(e), 25.503(a)(b), 25.507(a)(b)(c), 25.509(a)(c)(d), 25.511, 25.519(a)(b)(c), 25.563, 25.581, 25.601*, 25.603, 25.605, 25.607, 25.609*, 25.613, 25.619*, 25.623*, 25.625, 25.629, 25.631*, 25.651*, 25.671, 25.672(a)(b)(c), 25.683(b), 25.703(a)(b)(c), 25.721(a)(b)(c), 25.777, 25.779(b), 25.789, 25.801, 25.841(a), 25.843(b), 25.851(b), 25.855(c), 25.863 (a)(b)(c)(d), 25.865, 25.867(a)(b)*, 25.869(a)(b)(c), 25.901(a)(b)(c), 25.903, 25.904, 25.933(a), 25.934, 25.939 (a)(c), 25.943, 25.951(a)(b)(c)(d)*, 25.952(a)(b), 25.954, 25.955(a), 25.959, 25.961, 25.963(a)(d), 25.969, 25.971, 25.975, 25.981 except 25.981(a)(3)**, 25.993(a)(b)(c)(d)(e), 25.994, 25.995, 25.997(a)(b)(c)(d), 25.999(a)(b), 25.1001, 25.1011(a)(b), 25.1013(a)(b)(c)(d)(e)(f), 25.1015(a)(b), 25.1017(a)(b), 25.1019(a), 25.1021(a)(b), 25.1023(a)(b), 25.1025(a)(c), 25.1041, 25.1043(a)(b)(c), 25.1045(a)(b)(c), 25.1091(a)(b)(c)(d)(e), 25.1093(b), 25.1103(b)(c)(d), 25.1121, 25.1123, 25.1141, 25.1143, 25.1145, 25.1155, 25.1163, 25.1165, 25.1167, 25.1181, 25.1182, 25.1183, 25.1185, 25.1187, 25.1189, 25.1191, 25.1193, 25.1195, 25.1197, 25.1199, 25.1201, 25.1203, 25.1207, 25.1301*, 25.1305, 25.1309*, 25.1316, 25.1317, 25.1337, 25.1353(a)(b)*, 25.1355(c), 25.1357(a)*, 25.1363, 25.1401(b), 25.1403, 25.1431*, 25.1438, 25.1461, 25.1501, 25.1503, 25.1507, 25.1511, 25.1513, 25.1515, 25.1517, 25.1519, 25.1521(a)(c)(d), 25.1525, 25.1527, 25.1529, 25.1531, 25.1533, 25.1535*, 25.1549(a)(b)(c), 25.1553, 25.1581, 25.1583, 25.1585, 25.1587, 25.1591, 25.1701(a)*, 25.1703(a)(b)(d)*, 25.1705*, 25.1707*, 25.1709*, 25.1711*, 25.1713*, 25.1715*, 25.1717*, 25.1719*, 25.1723*, 25.1725*, 25.1727*, 25.1731* * For new and modified parts only (engine, pylon, nacelle, bleed air system, wing structural changes in area of pylon and landing gear reinforcement) ** FAA acceptance of this exception is for the Fuel Quantity Indicating System (FQIS) and Fuel Level Sensor System (FLSS) wiring installation changes and fuel tank structural fastener changes only and is based on the following design features incorporated on the NEO: The FQIS/FLSS wiring is within the S-routes in pressurized areas and is isolated with protective textile sleeving with CAUTION, FUEL TANK HARNESS ONLY" labels. The FQIS/FLSS wiring is within the S-routes in non-pressurized areas and is isolated with protective heat shrink sleeving and routed with the rest of the S-route bundle in PTFE conduit up to fuel tank walls penetration with "CAUTION, FUEL TANK HARNESS INSIDE" labels. Wiring production breaks from Avionic bays to the tank walls is done through dedicated connectors. The fuel tank structural fastener changes meet the criteria for the use of exceptions in FAA policy ANM-112-08-002 “Policy on Issuance of Special Conditions and Exemptions Related to Lightning Protection of Fuel Tank Structure,” dated May 26, 2009. Plus the following sections of 14 CFR part 25 amended as indicated below applied to the components and areas affected by the change per Airbus reversion justification: 25.21 Amdt. 1201 25.561(a)(b)(c)(d) Amdt. 642 25.103 Amdt. 1201 25.571(a)(b)(e)(1) Amdt. 863 A28NM Page 65 of 103 All models 25.105 Amdt. 1201 25.611 Amdt. 564 25.107 (except (e)(1)(iv)) Amdt 1201 25.677(b) Amdt. 565 25.111 Amdt. 1201 25.899 Amdt. 566 25.119 Amdt. 1201 25.1317 Amdt. 567 25.121 Amdt. 1201 25.1322 Amdt. 568 25.123 Amdt. 1201 25.1329 Amdt. 569 25.125 Amdt. 1201 25.1351 Amdt. 5610 25.143 Amdt. 1201 25.1419 Amdt. 1201 25.145 Amdt. 971 25.1435 Amdt. 5611 25.207 Amdt. 1201 25.1459(a) Amdt. 5612 25.237 Amdt. 1201 Appendix H at amdt 5613 25.253(c) Amdt. 1201 Notes: 1. FAA acceptance of these reversions was based on the fact that Airbus has done additional testing above the requirements incorporated by reference as documented in the summary of EASA CRI B-06, issue 2, dated April 11, 2013, Flight in Icing Conditions, and a determination that compliance with the amendment in effect on the date of application for these rules (i.e., Amendment 25-121) would not materially increase the level of safety exception, or in some cases, would be impractical in accordance with 14 CFR 21.101(b)(3). EASA CRI B-06 is incorporated as part of the certification basis for this airplane. 2. FAA acceptance of this reversion was based on a determination that compliance with the amendment in effect on the date of application for this rule (i.e., Amendment 25-91) would not materially increase the level of safety in accordance with 14 CFR 21.101(b)(3). 3. FAA acceptance of this reversion was based on a determination that compliance with the amendment in effect on the date of application for this rule (i.e., Amendment 25-132) would not materially increase the level of safety in accordance with14 CFR 21.101(b)(3). 4. FAA acceptance of this reversion was based on a determination that compliance with the amendment in effect on the date of application for this rule (i.e., Amendment 25-123) would not materially increase the level of safety in accordance with 14 CFR 21.101(b)(3). 5. FAA acceptance of this reversion was based on a determination that the changes in this area are considered secondary and compliance with the amendment in effect on the date of application for this rule (i.e., Amendment 25-115) would not materially increase the level of safety in accordance with 14 CFR 21.101(b)(3). 6. FAA acceptance of this reversion was based on a determination that changes in this area are considered secondary and compliance with the amendment in effect on the date of application for this rule (i.e., Amendment 25-123) would not materially increase the level of safety in accordance with 14 CFR 21.101(b)(3). 7. FAA acceptance of this reversion was based on a determination that the changes in this area are considered secondary and compliance with the amendment in effect on the date of application for this rule (i.e., Amendment 25-122) would not materially increase the level of safety above Special Condition 25-ANM-23 in accordance with 14 CFR 21.101(b)(3). 8. FAA acceptance of this reversion was based on a determination that compliance with the amendment in effect on the date of application for this rule (i.e., Amendment 25-131) would be impractical in accordance with 14 CFR 21.101(b)(3). 9. FAA acceptance of this reversion was based on a determination that changes in this area are considered secondary and compliance with the amendment in effect on the date of application for this rule (i.e., Amendment 25-119) would not materially increase the level of safety in accordance with 14 CFR 21.101(b)(3). 10. FAA acceptance of this reversion was based on a determination that the changes in this area are considered secondary and compliance with the amendment in effect on the date of application for this rule (i.e., Amendment 25-72) would not materially increase the level of safety in accordance with 14 CFR 21.101(b)(3). 11. FAA acceptance of this reversion was based on a determination that changes in this area are considered secondary and compliance with the amendment in effect on the date of application for this rule (i.e., Amendment 25-104) would not materially increase the level of safety in accordance with 14 CFR 21.101(b)(3). A28NM Page 66 of 103 All models 12. FAA acceptance of this reversion was based on a determination that changes in this area are considered secondary and compliance with the amendment in effect on the date of application for this rule (i.e., Amendment 25-124) would not materially increase the level of safety in accordance with 14 CFR 21.101(b)(3). 13. FAA acceptance of this reversion was based on a determination that compliance with the amendment in effect on the date of application for this rule (i.e., Amendment 25-123) would not materially increase the level of safety in accordance with 14 CFR 21.101(b)(3). Plus the following sections of 14 CFR part 25 amended as indicated below per Airbus elect to comply: 25.853(a)(1) at Amendment 25-66 25.853(c) at Amendment 25-59 Special conditions: FAA Special Condition 25-ANM-23 applicable to each model as defined in FAA TCDS A28NM remains applicable, except: Paragraph 2 – Active Controls is replaced with the following special conditions: • No. 25-469-SC Effective October 11, 2012 - “Interaction of Systems and Structures” • No. 25-470-SC Effective October 11, 2012 - “Design Dive Speed” • No. 25-471-SC Effective October 11, 2012 - “Design Roll Maneuver Conditions” Paragraph 4 – Protection from Lightning and Unwanted Effects of Radio Frequency is replaced with the following later requirements: • 25.1316 thru amendment 25-136 • 25.1317 thru amendment 25-136 In addition the following FAA Special Condition applies specifically to the Airbus SA NEO program: • No. 25-582-SC Effective April 30, 2015- “Transient Engine Failure Loads” Equivalent Safety Findings (ESFs): The ESFs applicable to each model as defined in FAA TCDS A28NM remain applicable plus the following ESFs applied specifically to the Airbus SA NEO program: ELOS Memo Regulation Subject AT00949IB-T-P-10 25.779(b)(1) Throttle Motion During Reduced (Flexible) Takeoff Thrust Operations and/or Go-Around AT00949IB-T-P-11 25.1549(a), (b) and (c) Digital Display of High Pressure Rotor Speed (N2) AT00949IB-T-P-12 25.1549(a) Oil Temperature Indication AT00949IB-T-P-14 25.1193(e)(3) Resistance to Fire of Cowling AT00949IB-T-P-15 25.1181(a)(6) & (b), & 25.1195 thru 25.1203 Fan Zone Non-fire Zone (PW only) AT00949IB-T-P-17 25.933(a)(1)(ii) Flight Critical Thrust Reverser AT00949IB-T-P-19 25.934 Thrust Reverser Testing AT00949IB-T-P-21 25.1181(a)(6) & (b), 25.1182 and 25.1195 through 25.1203 PW1100G-JM 2.5 Bleed & Track lock Areas and PW1100G-JM and LEAP-1A Areas Adjacent to Designated Fire Zones AT00949IB-T-SA-1 25.1301 and 25.1309 Equipment, Systems, and Installation Requirements: Use of ARAC Recommendations Exemptions: The Exemptions applicable to each model as defined in TCDS A28NM remain applicable plus the following exemption applied specifically to the Airbus SA NEO models: Exemption No. 13048 for 25.841(a) dated September 25, 2015 (13048A dated February 22, 2018, 13048B dated March 6, 2019.) Optional Requirements elected • § 25.801 for ditching. • § 25.1419 for icing. • § 25.1535 for ETOPS A28NM Page 67 of 103 All models Noise standards 14 CFR part 36 Stage 4 as amended by Amendment 36-1 through Amendment 36-30. 14 CFR Part 36 through Amendment 36-31, Stage 5 for models; A321-251N, A321-252N, A321-253N, A321-271N, and A321- 272N. The means of implementation of Stage 5 recertification must be provided by Airbus to ensure availability of the revised AFM noise pages for all affected aircraft. AFM CP293 issue 1.0 dated October 2, 2018 or later revision approved by EASA. Fuel venting and exhaust emissions standards 14 CFR part 34 as amended by Amendment 34-1 through 34-5. Part 26 14 CFR part 26 as amended by Amendment 26-1 through 26-5. Additional Design Requirements and Conditions Compliance with the established basis for type certification notwithstanding, § 21.21(b)(2) precludes issuance of a type certificate if there is any feature or characteristic that would make the product unsafe. The following design details or information must be maintained to ensure that an unsafe design condition is not present: In-flight Engine Restart 1. A minimum restart capability after an all engines out scenario must be established under the following conditions using procedures provided in the airplane flight manual (AFM): a) During the take-off and the initial climb-out portion of the flight, the airplane should have the capability for the flightcrew to restore engine power when the fuel source to the engine is interrupted. b) During the high altitude portion of the flight at cruise speed and maximum altitude, the airplane should have the capability for the flightcrew to restart from a stabilized windmill speed those engines required to maintain level flight or should have the capability for the flightcrew to restart all but one of the engines and produce maximum continuous thrust or power by an altitude of 15 000 feet. c) During flight at speeds greater than the minimum flaps-up “holding speed” and at altitudes below 20 000 feet, the airplane should have the capability for the flightcrew to restart with the engines at stabilized windmill speed those engines necessary to maintain safe flight and arrest the airplane descent within a total altitude loss of 5 000 feet prior to exceeding an airspeed of 300 knots. Certification basis for the Airbus Model A321- 271N, -251N & -253N installed with Modification 157272(Max Pax), for the certification of a Maximum Passenger Seating Capacity (MPSC) of 230 passengers: The original certification basis for the Model A321- 271N, -251N & -253N plus the following sections of 14 CFR part 25 as amended by Amendments 25-1 through 25-143 applied to the components and areas affected by the change, equivalent level of safety finding, Optional Design Regulations, 14 CFR part 26, Additional Design Requirements and Conditions: 14 CFR Section FAA Accepted Amendment Level System/Component/Area Affected by the Change 25.23 143 Fuselage Structure 25.321 143 Fuselage Structure 25.331 143 Fuselage Structure 25.341 143 Fuselage Structure 25.351 143 Fuselage Structure 25.473 143 Fuselage Structure 25.479(a)(c)(d) 143 Fuselage Structure 25.481(a)(c) 143 Fuselage Structure 25.489 143 Fuselage Structure 25.795(d) 143 Cabin Interior excl lavatories 25.801(d) 143 Entire Airplane 25.803(c) 143 Cabin Interior 25.807(g) 143 Cabin Interior 25.810 143 Cabin Interior A28NM Page 68 of 103 All models 14 CFR Section FAA Accepted Amendment Level System/Component/Area Affected by the Change 25.815 143 Cabin Interior 25.1447(c)(1) 143 Passenger equipment associated with increased MPSC 25.1519 143 Entire Airplane 25.1529 143 ICA associated with increased MPSC 25.1541(a)(b) 143 Marking & Placards associated with increased MPSC 25.1557(a) 143 Marking & Placards associated with increased MPSC The following sections of 14 CFR part 25 amended as indicated below and applied to the components and areas affected by the change, have been determined in accordance with the § 21.101(b)(3) that comp liance with the Amendment 25 -143 would not materially increase the level of safety: 14 CFR Section FAA Accepted Amendment Level ,25.561, 25.785, 25.787(a)(b), 25.789(a), 25.791, 25.809, 25.811, 25.812(e)(k)(l), 25.813, 25.853(a)(b), 25.1301, 25.1309, 25.1351(a), 25.1353(a)(b), 25.1357(a)(c)(g), 25.1359(a)(d), 25.1413, 25.1415(b)(c)(d), 25.1431(c), 25.1561 56 25.562 64 25.571(a)(b) 86 25.853(c)(d)(e) 116 25.305(a)(b),25.307(a), 25.365(a), 25.901(c) 136 Equivalent Safety Findings: In accordance with the provisions of § 21.21(b)(1) the following new ELOS finding is applicable to Modification 157272 (MaxPax): CS-2 § 25.807 Emergency Exits Finding for Increase of the Maximum Passenger Capacity (MPSC) from 220 passengers to 230 passengers CS-6 § 25.807 Emergency Exits Finding for Increase of the Maximum Passenger Capacity (MPSC) Optional Design Regulations: Part 26: Based on 14 CFR § 21.101(g), applicable provisions of 14 CFR part 26 are included in the certification basis. For any future 14 CFR part 26 amendments, the holder of this TC must demonstrate compliance with the applicable sections. The type design complies with the following 14 CFR part 26 Amendments 26-1 through 26-6 regulations: §§ 26.11, 26.33, 26.43, and 26.45. Additional Design Requirements and Conditions: Limitation: • The exit passageway width must meet the regulatory minimum of 20 inches. The height of the attendant seat or other assembly is limited to a maximum height of 57 inches. • The unobstructed exit dimensions of the forward and aft most floor level emergency exits must not be less than 32 inches x 73 inches. • A wide slide (sliding surface width 82.75 inches (+3.0 inches, -2.0 inches)) must be installed at the forward and aft most exits. • The wide slides installed at the forward and aft most floor level exits must have a beam strength meeting the requirements of TSO-C69c. A28NM Page 69 of 103 All models Certification basis for the Airbus Model A321-271NX/-272NX/-251NX/-252NX/-253NX (A321 NEO Airbus Cabin Flex (ACF))): The certification basis for the Airbus Model A321 New engine Option for components or areas not affected by the change. Plus the following sections of 14 CFR part 25 as amended by Amendments 25-1 through 25-141 (i.e., the amendment in affect on the date of application) applied to the components and areas affected by the change: 14 CFR Section FAA accepted amendment level System/Component/Area Affected by the Change 25.3 25-141 aircraft level 25.23 25-141 aircraft level 25.25 25-141 aircraft level 25.101(c)(d)(e)(f)(h), 25-141 aircraft level 25.109 25-141 aircraft level 25.113 25-141 aircraft level 25.115 25-141 aircraft level 25.117 25-141 aircraft level 25.147 (c)(d) 25-141 aircraft level 25.201 25-141 aircraft level 25.203 25-141 aircraft level 25.251 (d)(e) 25-141 aircraft level 25.301 25-141 aircraft level 25.303 25-141 aircraft level 25.305(a)(b) 25-141 A321neo ACF Structure Changes within section 13/14/14A/15/16/17/21 & wing local reinforcement 25.305(c)(e)(f) 25-141 aircraft level 25.307 (a) 25-141 A321neo ACF Structure Changes within section 13/14/14A/15/16/17/21 & wing local reinforcement 25.321 (a)(b)(c)(d) 25-141 aircraft level 25.331(a)(b)(c) 25-141 aircraft level 25.333(a)(b) 25-141 aircraft level 25.335 25-141 aircraft level 25.337 25-141 aircraft level 25.341(a)(b) 25-141 aircraft level 25.341(c) 25-141 aircraft level 25.343(a) 25-141 aircraft level 25.343(b)(1)(2) 25-141 aircraft level 25.343(b)(3) 25-141 aircraft level 25.345 (a)(b)(d) 25-141 high lift 25.349(a)(1)(b) 25-141 aircraft level 25.351(a)(b)(c)(d) 25-141 aircraft level 25.361(a)(b) 25-141 aircraft level 25.362(a)(b) 25-141 aircraft level 25.363(a)(b) 25-141 aircraft level 25.365(a)(b) 25-141 fuselage 25.365(d) 25-141 fuselage 25.365 (e)(1)(2)(3)(f) 25-141 cabin & cargo compartments 25.367(a)(b) 25-141 aircraft level 25.371 25-141 aircraft level 25.373 (a)(b) 25-141 aircraft level 25.391(a)(b)(d)(e); 25-141 aircraft level 25.427 (a)(b)(d) 25-141 aircraft level 25.445(a) 25-141 aircraft level 25.457 25-141 aircraft level 25.459 25-141 aircraft level 25.471 (a)(b) 25-141 aircraft level 25.473 25-141 aircraft level A28NM Page 70 of 103 All models 14 CFR Section FAA accepted amendment level System/Component/Area Affected by the Change 25.479 (a)(c)(d) 25-141 aircraft level 25.481(a)(c) 25-141 aircraft level 25.483(a)(b) 25-141 aircraft level 25.485(a)(b) 25-141 aircraft level 25.489 25-141 aircraft level 25.491 25-141 aircraft level 25.493(b)(c)(d)(e) 25-141 aircraft level 25.495 25-141 aircraft level 25.499 25-141 aircraft level 25.503 25-141 aircraft level 25.507 (a)(b) 25-141 aircraft level 25.509 (a)(b)(c)(d) 25-141 aircraft level 25.511 25-141 aircraft level 25.519 25-141 aircraft level 25.561(a)(b)(c)(d) 25-141 A321neo ACF Structure Changes within section 13/14/14A/15/16/17/21 new slides at OWDs/ Door 3 25.571 (c)(e) 25-141 A321neo ACF Structure Changes within section 13/14/14A/15/16/17/21 & wing local reinforcement 25.581 25-141 A321neo ACF Structure Changes within section 13/14/14A/15/16/17/21 & wing local reinforcement MLG local reinforcement New OWDs system Additional over-wing Emergency lights implementation/ EPSU relocation 25.601 25-141 A321neo ACF Structure Changes within section 13/14/14A/15/16/17/21 & wing local reinforcement MLG local reinforcement 25.603 25-141 A321neo ACF Structure Changes within section 13/14/14A/15/16/17/21 & wing local reinforcement MLG local reinforcement 25.605 25-141 A321neo ACF Structure Changes within section 13/14/14A/15/16/17/21 & wing local reinforcement MLG local reinforcement 25.607 25-141 New OWDs System 25.609 25-141 A321neo ACF Structure Changes within section 13/14/14A/15/16/17/21 & wing local reinforcement MLG local reinforcement 25.611 (a) 25-141 aircraft level 25.611 (b) 25-141 New slides at OWDs/Door 3 25.613 25-141 A321neo ACF Structure Changes within section 13/14/14A/15/16/17/21 & wing local reinforcement MLG local reinforcement 25.619 25-141 A321neo ACF Structure Changes within section 13/14/14A/15/16/17/21 & wing local reinforcement MLG local reinforcement 25.621 25-141 New OWDs System 25.623 25-141 New OWDs System 25.625 25-141 A321neo ACF Structure Changes within section 13/14/14A/15/16/17/21 & wing local reinforcement MLG local reinforcement 25.629 (a)(b)(c)(d)(e) 25-141 aircraft level 25. 631 25-141 aircraft level 25.703(b)(c) 25-141 FWS 25.723(a)(b)(c) 25-141 Main Landing gear 25.729 (a)(b)(d)(e) 25-141 Main Landing gear A28NM Page 71 of 103 All models 14 CFR Section FAA accepted amendment level System/Component/Area Affected by the Change 25.729 (f) 25-141 Main Landing gear 25.731(a) (b)(c) 25-141 Main and Nose Landing gear wheels 25.733(b)(c)(d) 25-141 Main and Nose Landing gear tires 25.735(a)(f)(2) 25-141 MLG brakes (RTO) 25.783 25-141 New OWDs System 25.783(e)(4) 25-141 Door 3 relocated- Aural warning 25.787(c) 25-141 cargo compartment: light relocation 25.795 (c)(1)(c)(3)(i) 25-141 aircraft level 25.795(d) 25-141 cabin interior 25.801(a)(d) 25-141 aircraft level 25.803 (a)(c) 25-141 cabin interior: cabin arrangement at D3/ OWDs, New slides at door 3/OWDs, wide slides at D1&4 25.807(a)(3)(9) (b) (c) (e) (f) (h)(1) (g) (i) 25-141 cabin interior arrangement: New slides at door 3/OWDs wide slide at door 1&4 25.809(b) (c) (e) (f) (i) 25-141 New OWDs system 25.809 (g) 25-141 all doors 25.810(a)(1)(c)(d) 25-141 New OWDs System New slides at door 3/ OWDs wide slide at door 1 &4 25.811 25-141 OWDs & Door 3 Marking / identification 25.812 (a)(b)(1)(c )(d)(e )(f)(g)(h)(i)(j)(k)(l) 25-141 emergency lighting at new OWD/ door 3 /New slides at door 3/ OWDs 25.813 (a)(b)(c) 25-141 Cabin interior: interior arrangement at door 3 and OWD 25.843(a) 25-141 A321neo ACF Structure Changes within section 13/14/14A/15/16/17/21 25.843(b)(4) 25-141 New OWDs system 25.853(a)(d)(1) 25-141 New OWDs System 25.855(a) 25-141 cargo compartment 25.855(c) 25-141 cargo compartment: lining adaptation 25.856 25-141 New OWDs System 25.857 25-141 cargo compartments 25.858 25-141 forward cargo compartment linked to the relocation of smoke detection cavity 25.863(a)(b)(d) 25-141 flammable fluid A/C Zoning: smoke cavity relocation cargo compartment 25.869(a)(1) 25-141 Additional over wing Emergency lights implementation/ EPSU relocation 25.899 25-141 A321neo ACF Structure Changes within section 13/14/14A/15/16/17/21 and local wing reinforcement MLG local reinforcement New OWDs system new slides at OWD and door 3 Additional Emergency lights implementation/ EPSU relocation 25.903(c) 25-141 aircraft level 25.903(d)(1) 25-141 A321neo ACF Structure Changes within section 13/14/14A/15/16/17/21 & wing local reinforcement New OWDs system and associated slides 25.951(a) 25-141 secondary change: APU fuel line rerouted 25.952(a) 25-141 secondary change: APU fuel line rerouted 25.955(a)(1) 25-141 secondary change: APU fuel line rerouted 25.963(a) 25-141 All fuel tank 25.993 25-141 secondary change: APU fuel line relocated A28NM Page 72 of 103 All models 14 CFR Section FAA accepted amendment level System/Component/Area Affected by the Change 25.994 25-141 secondary change: APU fuel line relocated 25.1001(a)(b)(c)(d) 25-141 aircraft level 25.1301(a) 25-141 New OWDs OWD/Door 3 New slides Additional Over Wing Emergency Lights Emergency lights/EPSU relocation smoke detector cavity relocated FWC software change EIS software change 25.1301(b) 25-141 New slides at OWD/Door 3 25.1309 (a) 25-141 OWDs System Door 3-Aural warning New slides at OWDs/Door 3 new Emergency lights/ EPSU relocation smoke detector cavity relocated FWC software EIS software 25.1309 (b) 25-141 OWDs System New slides at OWDs/Door 3 new Emergency lights/ EPSU relocation performance analysis due to tire pressure increase FWS EIS 25.1309 (c) 25-141 OWDs system FWC software EIS software 25.1309 (d) 25-141 OWDs system 25.1309 (f) 25-141 New slides at OWDs/Door 3 25.1316 25-141 OWDs system 25.1317 25-141 OWDs system 25.1353 25-141 OWDs system New slides at door 3/OWDs 25.1360 25-141 cabin and cargo: Additional lights / Emergency light & EPSU relocation OWDs system OWE & D3 Evacuation Systems 25.1411(a)(b)(c)(d)(e)(f)(g) 25-141 New slides at OWDs/Door 3 liferaft installation long range signaling device installation life preserver installation 25.1431(a)(c)(d) 25-141 OWDs system Additional over wing Emergency lights implementation/connection to EPSU 25.1441 25-141 cabin interior 25.1447 (a)(c)(1)(4) 25-141 cabin interior 25.1450 25-141 cabin interior 25.1511 25-141 aircraft level 25.1519 25-141 aircraft level 25.1529 25-141+ app H at amdt 56 /14 CFR Part 26 aircraft level 25.1533(a)(b) 25-141 aircraft level 25.1535, Appendix K to Part 25 25-141 aircraft level A28NM Page 73 of 103 All models 14 CFR Section FAA accepted amendment level System/Component/Area Affected by the Change 25.1541 25-141 Markings/ Placards OWE / Door 3 operation, cargo placards 25.1545 25-141 Limit speed placard 25.1557(a)(c) 25-141 cabin interior / External marking 25.1561(a) 25-141 New slides at OWD & Door 3 25.1581 25-141 aircraft level 25.1583 25-141 aircraft level 25.1587 25-141 aircraft level 25.1703 (a)(b)(d) 25-141 New slides at OWDs/Door 3 25.1705 (a) 25-141 New slides at OWDs/Door 3 25.1707 (a) 25-141 New slides at OWDs/Door 3 25.1707 (d) 25-141 New slides at OWDs/Door 3 25.1707(l) 25-141 New slides at OWDs/Door 3 25.1709 25-141 New slides at OWDs/Door 3 25.1711 (a) 25-141 New slides at OWDs/Door 3 25.1711 (c) 25-141 New slides at OWDs/Door 3 25.1711 (d) 25-141 New slides at OWDs/Door 3 25.1711 (e) 25-141 New slides at OWDs/Door 3 25.1713 (a) 25-141 New slides at OWDs/Door 3 25.1713 (c) 25-141 New slides at OWDs/Door 3 25.1715(a)(b) 25-141 New slides at OWDs/Door 3 25.1717 25-141 New slides at OWDs/Door 3 25.1719 25-141 New slides at OWDs/Door 3 25.1721(a) 25-141 New slides at OWD & Door 3 25.1721(b) 25-141 New slides at OWDs/Door 3 25.1725 (b) 25-141 New slides at OWDs/Door 3 Plus the following sections of 14 CFR part 25 amended as indicated below applied to the components and areas affected by the change per Airbus reversion justification: The following sections of 14 CFR part 25 amended as indicated below and applied to the cabin interior adaptations, have been determined in accordance with the § 21.101(b)(3) that compliance with the Amendment 25-141 would not materially increase the level of safety: 14 CFR Section FAA Accepted Amendment Level 25.853(c)(d)(e)(f)(g)(h) 116 25.562 except (c)(5)(c)(6) 64 25.561, 25.785, 25.787(a)(b), 25.789(a), 25.791, 25.793, 25.811(marking at door1&4), 25.815, 25.817, 25.851(a)(1), 25.853(a)(b), 25.1301, 25.1309, 25.1351(a)(1), 25.1353(a)(b), 25.1357(a)(c)(g), 25.1359(a)(d), 25.1413, 25.1415 (a)(b)(c)(d), 25.1431(c), 25.1561 56 The following section of 14 CFR part 25 amended as indicated below and applied to the outside viewing requirement at door 1, 3 & 4 as described has been determined in accordance with the § 21.101(b)(3) that compliance with the Amendment 25-141 would not materially increase the level of safety. 14 CFR Section FAA Accepted Amendment Level 25.809 (a) 25-115 FAA acceptance of this reversion was based on a determination that compliance with the amendment in effect on the date of application for this rule (i.e., Amendment 25-132) would not materially increase the level of safety in accordance with 14 CFR 21.101(b)(3). 14 CFR Section FAA Accepted Amendment Level 25.571(a)(b) 25-86 A28NM Page 74 of 103 All models The following section of 14 CFR part 25 has been determined in accordance with the § 21.101(b)(3) that compliance with the Amendment 25-141 would not materially increase the level of safety or in some cases, would be impractical. 14 CFR Section FAA Accepted Amendment Level 25.21(a)(d) 120 25.103 25.105 25.107 25.111 25.121 25.123 25.143 (a)(b)(3)(g) FAA acceptance of this reversion was based on a determination that compliance with the amendment in effect on the date of application for this rule (i.e., Amendment 25-131) would be impractical in accordance with 14 CFR 21.101(b)(3). 14 CFR Section FAA Accepted Amendment Level 25.1322 56 The following sections of 14 CFR part 25 amended as indicated below and applied to the Main Landing Gear structural adaptations, have been determined in accordance with the § 21.101(b)(3) that compliance with the Amendment 25-141 would not materially increase the level of safety: 14 CFR Section FAA Accepted Amendment Level 25.1301 56 FAA determined, in accordance with the § 21.101(b)(3) that applying EWIS regulations to the wiring adaptations in the cabin and to the wiring adaptation linked to the implementation of the new OWDs, relocation of the door 3 and associated lights, would not materially increase the level of safety. Special Conditions: In accordance with § 21.16, the special conditions applied to the baseline Model airplanes as listed in FAA TCDS A28NM Revision 34 are retained and applicable to the components and areas affected by these changes. In addition the following FAA Special Condition applies to the Airbus Model A321neo ACF Airplane: • Special Conditions No. 25-779-SC Effective January 11, 2021 - “Dynamic Test Requirements for Single-Occupant Oblique (Side-Facing) Seats with 3-point Restraint” Equivalent Safety Findings: The equivalent level of Safety (ESF) applied to the baseline Model airplanes as listed in FAA TCDS A28NM Revision 34 remains applicable; In addition following ELOS IPs have been raised: AT10637IB-T-CS-3 25.807(a)(3), (b) & (c) Emergency Exit Increased Stepdown Dimension and Passageway 25.813(c)(1) & (c)(2) Emergency exit access Displacement for Type III Exits AT10637IB-T-CS-4 § 25.807 Emergency Exits Increased Passenger Credit for Type III Over-Wing Exits Exemptions: The Exemptions applicable to each model as defined in TCDS A28NM remain applicable plus the following exemptions applied specifically to the Airbus A321-271NX,-272NX,-251NX,-252NX and -253NX: Exemption No.17122: A321neo ACF Over Wing Exit exemption from 14 CFR Part 25.809(a) Extension of Exemption No. 13048 FAA partial grant of exemption from Section 25.841(a)(2)(i) and (ii) and (a)(3) Amendment 25- 87 of A320N family. A28NM Page 75 of 103 All models Exemption No. 18016: A321 neo ACF exemption from 14 CFR Part 25.807(g)(7) Note: Airbus has elected to comply with 25.807 (h)(1). If for a specific layout, the Door 3 is considered in addition to the minimum required as per 25.807 (h)(1), the Exemption is not applicable. Exemption No. 18016A: A321 neo ACF exemption from 14 CFR Part 25.807(g)(7) Note: Exemption 18016 amended by deletion condition number 1.b.iv., which incorrectly required removal of the outboard seats located at Door 3. Exemption No. 18016B: A321 neo ACF exemption from 14 CFR Part 25.807(g)(7) Note: Exemption 18016A amended to add the A321-253NY and A321-271NY a/c models Exemption No. 18674: A321 neo A321neoACF exemption from 14 CFR Part §§ 25.813(e), 121.310(f)(5), and 121.310(f)(6). Exemption No. 18674A: A321 neo A321neoACF exemption from 14 CFR Part §§ 25.813(e), 121.310(f)(5), and 121.310(f)(6). Note: 18674A updated to add mini-suites installation for passengers (including those with reduced mobility (PRM-suites), with doors and movable aisle walls) Optional Design Regulations: Original design approvals for the reference airplane are retained. • Ditching • Flight in Icing Conditions • ETOPS Airworthiness and Environmental Standards for components and areas affected by the change Noise Standards 14 CFR part 36 as amended by Amendment 36-1 through amendment 36-30 is applicable. 14 CFR Part 36 through Amendment 36-31, Stage 5 for models; A321-251N, A321-252N, A321-253N, A321-271N, and A321- 272N. The means of implementation of Stage 5 recertification must be provided by Airbus to ensure availability of the revised AFM noise pages for all affected aircraft. AFM CP293 issue 1.0 dated October 2, 2018 or later revision approved by EASA. Fuel Venting and Exhaust Emissions Standards No emissions change according to §21.93(c) / 14 CFR part 34 as amended by Amendment 34-1 through amendment 34-4 stay applicable. Part 26: 14 CFR part 26 as amended by Amendment 26-1 through amendment 26-6 is applicable. 14 CFR Section FAA accepted amendment level System/Component/Area Affected by the Change 26.11 26-6 aircraft level 26.21 26-6 aircraft level 26.43(b)(c) 26-6 A321neo ACF Structure Changes within section 13/14/14A/15/16/17/21 & wing local reinforcement 26.45(b) 26-6 A321neo ACF Structure Changes within section 13/14/14A/15/16/17/21 & wing local reinforcement Additional Design requirements and Conditions: Compliance with the established basis for type certification notwithstanding §21.21(b)(2) preclude issuance of a type certificate if there is any feature or characteristic that would make the product unsafe. No unsafe design condition is considered. Certification basis for the Airbus Model A321-251NX, -252NX, -253NX, -271NX, -272NX installed with up to 3 additional center tanks (Modification 163213): The original certification basis for the A321-251NX, -252NX, -253NX, -271NX, -272NX -plus the following sections of 14 CFR part 25 as amended by Amendments 25-1 through 25-141 applied to the components and areas affected by the change, 14 CFR part 26, Additional Design Requirements and Conditions: A28NM Page 76 of 103 All models 14 CFR Section FAA accepted amendment level System/Component/Area Affected by the Change 25.3 25-141 aircraft level 25.23 25-141 aircraft level 25.25 25-141 aircraft level 25.303 25-141 aircraft level 25.305 (a)(b) 25-141 cargo compartment: adaptation linked to ACTs installations ACTs installation structure Changes in lower lobe fuselage 25.307 (a) 25-141 cargo compartment: adaptation linked to ACTs installations ACTs installation structure Changes in lower lobe fuselage 25.321 (a)(b)(c)(d) 25-141 aircraft level 25.331(a)(b)(c) 25-141 aircraft level 25.341(a)(b) 25-141 aircraft level 25.343(a) 25-141 aircraft level 25.343(b)(3) 25-141 aircraft level 25.351(a)(b)(c)(d) 25-141 aircraft level 25.365(a)(b) 25-141 aircraft level 25.365 (e)(1)(2)(3)(f) 25-141 Cabin and cargo compartments 25.473 25-141 aircraft level 25.479 (a)(c)(d) 25-141 aircraft level 25.481(a)(c) 25-141 aircraft level 25.489 25-141 aircraft level 25.561(b)(c)(d) 25-141 ACTs installation structure Changes in lower lobe fuselage 25.571 (c)(e) 25-141 ACTs installation structure Changes in lower lobe fuselage 25.581 25-141 Additional Service area light installation between FWD ACT and the centre wing box ACT fuel system installation 25.601 25-141 ACTs installation structure Changes in lower lobe fuselage cargo compartment 25.603 25-141 ACTs installation structure Changes in lower lobe fuselage 25.605 25-141 ACTs installation structure Changes in lower lobe fuselage 25.609 25-141 ACTs installation structure Changes in lower lobe fuselage 25.611 (a) 25-141 aircraft level 25.611 (b) 25-141 ACT fuel system installation 25.613 25-141 ACTs installation structure Changes in lower lobe fuselage 25.619 25-141 ACTs installation structure Changes in lower lobe fuselage 25.625 25-141 ACTs installation structure Changes in lower lobe fuselage 25.629 (a)(b)(c)(d)(e) 25-141 aircraft level 25.721(b) 25-141 ACTs installation in lower lobe fuselage 25.777(a) 25-141 ACTs fuel system installation: new overhead panel 25.787(c) 25-141 cargo compartment: light relocation 25.810(a)(1) 25-141 ACT: Relocation of the slide inflation system of the Off- Wing Evacuation Systems into OHSC 25.851(b)(2) 25-141 fwd and aft cargo linked to the reduction of cargo volume associated with ACTs installation 25.855(a) 25-141 cargo compartment 25.855(c) 25-141 cargo compartment: lining adaptation 25.855(e)(f)(g)(h) 25-141 cargo compartment associated with ACTs installation 25.856 (b) 25-141 ACT Provision Installation 25.857 25-141 cargo compartments 25.858 25-141 fwd and aft cargo linked to the reduction of cargo volume associated with ACTs installation 25.863(a)(b) 25-141 flammable fluid A/C Zoning: smoke cavity relocation ACT fuel system installation 25.863(c) 25-141 ACT fuel system installation 25.863(d) 25-141 flammable fluid A/C Zoning: smoke cavity relocation ACT fuel system installation 25.869(a)(1) 25-141 Additional Cargo light relocation Service area light installation for FWD ACT ACTs FQIS/FLSS wiring segregation and protection 25.869(a)(3) 25-141 ACTs FQIS/FLSS wiring segregation and protection Fire extinguishing system adaptation when ACT installed in A28NM Page 77 of 103 All models 14 CFR Section FAA accepted amendment level System/Component/Area Affected by the Change Cargo compartment 25.899 25-141 Additional Service area light installation for FWD ACT ACT fuel system installation 25.901(c) 25-141 ACT fuel system installation 25.903(c) 25-141 aircraft level 25.903(d)(1) 25-141 ACTs installation structure Changes in lower lobe fuselage ACT fuel system installation 25.943 25-141 ACT transfer system ACT pressurization system 25.951(c) 25-141 ACT refuel/transfer system 25.952(a) 25-141 ACT refuel/transfer system ACT pressurization system ACT fuel venting system 25.954 25-141 ACT fuel system installation 25.957 25-141 ACT refuel/transfer system ACT pressurization system ACT fuel venting system 25.959 25-141 ACT fuel system installation 25.963(a) 25-141 All fuel tanks 25.963(b)(c)(e)(f) 25-141 ACT fuel system installation 25.963(d) 25-141 new ACTs installation 25.965(a) (b)(c)(d) 25-141 ACT fuel system installation 25.967(a)(b)(e) 25-141 ACT fuel system installation 25.969 25-141 ACT fuel system installation 25.971 25-141 ACT fuel system installation 25.975(a) 25-141 ACT fuel venting system 25.977(a)(c)(d) 25-141 ACT fuel system installation 25.979(b)(c)(d)(e) 25-141 ACT refuel system 25.981(a)(b)(d) 25-141 ACT fuel system installation 25.993 25-141 ACT fuel system installation 25.994 25-141 ACT refuel/transfer system 25.995(b) 25-141 ACT refuel/transfer system 25.999(a)(b) 25-141 ACT fuel system installation 25.1011(b) 25-141 aircraft level 25.1141(a)(b)(c)(d)(f) 25-141 ACTs Fuel System installation: new overhead panel ACTs transfer system 25.1189(h) 25-141 ACT pressurization system 25.1301(a) 25-141 FWC software change EIS software change ACT fuel system installation fire extinguishing system adaptation within cargo compartment when ACT installed ATA 330 service area light, light relocation, in cargo compartment linked to ACT installation 25.1301(b) 25-141 ACT fuel system installation 25.1302(a)(b)(c) 25-141 ACT installation: New overhead panel 25.1305(a)(2) 25-141 ACTs fuel system installation 25.1309(a) 25-141 fire extinguishing system adaptation within cargo compartment when ACT installed FWC software EIS software ACT fuel system installation ATA 330 service area light, light relocation, in cargo compartment linked to ACT installation 25.1309(b) 25-141 Fire extinguishing system adaptation within cargo compartment when ACT installed FWS EIS ACT fuel system installation A28NM Page 78 of 103 All models 14 CFR Section FAA accepted amendment level System/Component/Area Affected by the Change ACT Cargo restraint System 25.1309(c) 25-141 FWC software EIS software ACT fuel system installation 25.1309(d) (f) 25-141 ACT fuel system installation 25.1310 25-141 ACTs fuel system installation 25.1316 25-141 ACT fuel system installation 25.1317 25-141 ACT fuel system installation 25.1337(b) 25-141 ACTs fuel system installation 25.1353 25-141 ACT fuel system installation 25.1360 25-141 cargo: Additional lights 25.1381 25-141 ACT installation: New overhead panel Fire extinguishing system cockpit panel adaptation when ACT installed 25.1431(a)(c)(d) 25-141 ACT fuel system installation 25.1519 25-141 aircraft level 25.1529 25-141+ app H at amdt 56 /14 CFR Part 26 aircraft level 25.1535, Appendix K to Part 25 25-141 aircraft level 25.1541 25-141 cargo placards 25.1543(b) 25-141 ACT fuel system installation: overhead panel 25.1553 25-141 Common Fuel Quantity Indication system adaptation for ACT system 25.1555(a) 25-141 ACT fuel system installation: overhead panel fire extinguishing system cockpit panel adaptation 25.1555(c) 25-141 ACT fuel system installation: overhead panel 25.1557(a) 25-141 cargo compartment linked to ACTs installation 25.1581 25-141 aircraft level 25.1583 25-141 aircraft level 25.1585 25-141 aircraft level 25.1703 (a)(b)(d) 25-141 ACTs fuel system wiring installation 25.1705(a) (b) 25-141 ACTs fuel system wiring installation 25.1707(a) (b) (c) (l) 25-141 ACTs fuel system wiring installation 25.1709 25-141 ACTs fuel system installation 25.1711(a) (b) (c) (d) (e) 25-141 ACTs fuel system wiring installation 25.1713(a) (c) 25-141 ACTs fuel system wiring installation 25.1715(a)(b) 25-141 ACTs fuel system wiring installation 25.1717 25-141 ACTs fuel system wiring installation 25.1719 25-141 ACTs fuel system wiring installation 25.1721(b) 25-141 ACTs fuel system wiring installation 25.1723 25-141 ACTs fuel system wiring installation 25.1725(b) 25-141 ACTs fuel system wiring installation FAA acceptance of this reversion was based on a determination that compliance with the amendment in effect on the date of application for this rule (i.e., Amendment 25-141) would not materially increase the level of safety in accordance with 14 CFR 21.101(b)(3). 14 CFR Section FAA Accepted Amendment Level 25.571(a)(b) 25-86 FAA acceptance of this reversion was based on a determination that compliance with the amendment in effect on the date of application for this rule (i.e., Amendment 25-141) would be impractical in accordance with 14 CFR 21.101(b)(3). 14 CFR Section FAA Accepted Amendment Level 25.1322 56 Special Conditions: In accordance with § 21.16, no additional special conditions have been identified. The special conditions applied to the baseline Model airplanes as listed in FAA TCDS A28NM Revision 37 are retained and applicable to the components and areas affected by these changes. A28NM Page 79 of 103 All models Equivalent Safety Findings: The equivalent level of Safety (ESF) applied to the baseline Model airplanes as listed in FAA TCDS A28NM Revision 34 remains applicable; Airworthiness and Environmental Standards for components and areas affected by the change Noise Standards 14 CFR part 36 as amended by Amendment 36-1 through amendment 36-30 is applicable. 14 CFR Part 36 through Amendment 36-31, Stage 5 for models; A321-251NX, A321-252NX, A321-253NX, A321-271NX, and A321-272NX. The means of implementation of Stage 5 recertification must be provided by Airbus to ensure availability of the revised AFM noise pages for all affected aircraft. AFM CP293 issue 1.0 dated October 2, 2018 or later revision approved by EASA. Fuel Venting and Exhaust Emissions Standards No emissions change according to §21.93(c) / 14 CFR part 34 as amended by Amendment 34-1 through amendment 34-4 stay applicable. Part 26: 14 CFR part 26 as amended by Amendment 26-1 through amendment 26-6 is applicable. 14 CFR Section FAA accepted amendment level System/Component/Area Affected by the Change 26.11 26-6 aircraft level 26.21 26-6 aircraft level 26.35 26-6 ACT Fuel system installation 26.43(b)(c) 26-6 ACTs installation structure Changes in lower lobe fuselage 26.45(b) 26-6 ACTs installation structure Changes in lower lobe fuselage Additional Design requirements and Conditions: Compliance with the established basis for type certification notwithstanding §21.21(b)(2) preclude issuance of a type certificate if there is any feature or characteristic that would make the product unsafe. No unsafe design condition is considered. Certification basis for the Airbus Model A321- 211, -212, -213, -231 & -232 installed with Modification 159536 (Max Pax), for the certification of a Maximum Passenger Seating Capacity (MPSC) of 230 passengers: The original certification basis for the Model A321- 211, -212, -213, -231 & -232 plus the following sections of 14 CFR part 25 as amended by Amendments 25-1 through 25-143 applied to the components and areas affected by the change, equivalent level of safety finding, Optional Design Regulations, 14 CFR part 26, Additional Design Requirements and Conditions: 14 CFR Section FAA Accepted Amendment Level System/Component/Area Affected by the Change 25.23 143 Fuselage Structure 25.321 143 Fuselage Structure 25.331(a)(b)(c)(1) 143 Fuselage Structure 25.341(a) 143 Fuselage Structure 25.351 143 Fuselage Structure 25.473 143 Fuselage Structure 25.479(a)(c)(d) 143 Fuselage Structure 25.481(a)(c) 143 Fuselage Structure 25.489 143 Fuselage Structure 25.795(d) 143 Cabin Interior excl lavatories 25.801(d) 143 Entire Airplane A28NM Page 80 of 103 All models 14 CFR Section FAA Accepted Amendment Level System/Component/Area Affected by the Change 25.803(c) 143 Cabin Interior 25.807(g) 143 Cabin Interior 25.810 143 Cabin Interior 25.815 143 Cabin Interior 25.1447(c)(1) 143 Passenger equipment associated with increased MPSC 25.1519 143 Entire Airplane 25.1529 143 ICA associated with increased MPSC 25.1541(a)(b) 143 Marking & Placards associated with increased MPSC 25.1557(a) 143 Marking & Placards associated with increased MPSC The following sections of 14 CFR part 25 amended as indicated below and applied to the components and areas affected by the change, have been determined in accordance with the § 21.101(b)(3) that comp liance with the Amendment 25 -143 would not materially increase the level of safety: 14 CFR Section FAA Accepted Amendment Level 25.305(a)(b),25.307(a),25.331(c)(2),25.341(b) 25.365(a), 25.561, 25.571(a)(b), 25.785, 25.787(a)(b), 25.789(a), 25.791, 25.809, 25.811, 25.812(e)(k)(l), 25.813, 25.853(a)(b), 25.1301, 25.1309, 25.1351(a), 25.1353(a)(b), 25.1357(a)(c)(g), 25.1359(a)(d), 25.1413, 25.1415(b)(c)(d), 25.1431(c), 25.1561 56 25.562 64 25.853(c)(d)(e) 116 25.365(a), 25.901(c) 136 Equivalent Safety Findings: In accordance with the provisions of § 21.21(b)(1) the following new ELOS finding is applicable to Modification 159536 (MaxPax): CS-2 § 25.807 Emergency Exits Finding for Increase of the Maximum Passenger Capacity (MPSC) from 220 passengers to 230 passengers CS-6 § 25.807 Emergency Exits Finding for Increase of the Maximum Passenger Capacity (MPSC) Optional Design Regulations: ETOPS: Modification 159536 (MaxPax) has not been evaluated for extended operations (ETOPS) type design approval on Models A321- 211, -212, -213, -231 & -232 with Wing Tip Fences (WTF). Part 26: Based on 14 CFR § 21.101(g), applicable provisions of 14 CFR part 26 are included in the certification basis. For any future 14 CFR part 26 amendments, the holder of this TC must demonstrate compliance with the applicable sections. The type design complies with the following 14 CFR part 26 Amendments 26-1 through 26-6 regulations: §§ 26.11, 26.33, 26.43, and 26.45. Additional Design Requirements and Conditions: Limitation: • The exit passageway width must meet the regulatory minimum of 20 inches. The height of the attendant seat or other assembly is limited to a maximum height of 57 inches. • The unobstructed exit dimensions of the forward and aft most floor level emergency exits must not be less than 32 inches x 73 inches. A28NM Page 81 of 103 All models • A wide slide (sliding surface width 82.75 inches (+3.0 inches, -2.0 inches)) must be installed at the forward and aft most exits. • The wide slides installed at the forward and aft most floor level exits must have a beam strength meeting the requirements of TSO-C69c. Certification basis for the Airbus Model A321-272N, A321-252N installed with Modification 157272(Max Pax), for the certification of a Maximum Passenger Seating Capacity (MPSC) of 230 passengers: The original certification basis for the Model A321-272N, A321-252N plus the following sections of 14 CFR part 25 as amended by Amendments 25-1 through 25-145 applied to the components and areas affected by the change, equivalent level of safety finding, Optional Design Regulations, 14 CFR part 26, Additional Design Requirements and Conditions: 14 CFR Section FAA Accepted Amendment Level System/Component/Area Affected by the Change 25.23 143 Fuselage Structure 25.321 143 Fuselage Structure 25.331 143 Fuselage Structure 25.341(a)(b) 143 Fuselage Structure 25.351 143 Fuselage Structure 25.473 143 Fuselage Structure 25.479(a)(c)(d) 143 Fuselage Structure 25.481(a)(c) 143 Fuselage Structure 25.489 143 Fuselage Structure 25.795(d) 143 Cabin Interior excl lavatories 25.801(d) 143 Entire Airplane 25.803(c) 143 Cabin Interior 25.807(g) 143 Cabin Interior 25.810 143 Cabin Interior 25.815 143 Cabin Interior 25.1447(c)(1) 143 Passenger equipment associated with increased MPSC 25.1519 143 Entire Airplane 25.1529 143 ICA associated with increased MPSC 25.1541(a)(b) 143 Marking & Placards associated with increased MPSC 25.1557(a) 143 Marking & Placards associated with increased MPSC The following sections of 14 CFR part 25 amended as indicated below and applied to the components and areas affected by the change, have been determined in accordance with the § 21.101(b)(3) that comp liance with the Amendment 25 -145 would not materially increase the level of safety: 14 CFR Section FAA Accepted Amendment Level ,25.561, 25.785, 25.787(a)(b), 25.789(a), 25.791, 25.809, 25.811, 25.812(e)(k)(l), 25.813, 25.853(a)(b), 25.1301, 25.1309, 25.1351(a), 25.1353(a)(b), 25.1357(a)(c)(g), 25.1359(a)(d), 25.1413, 25.1415(b)(c)(d), 25.1431(c), 25.1561 56 25.562 64 25.571(a)(b) 86 25.853(c)(d)(e)/ IP CI-10 116 25.305(a)(b),25.307(a), 25.365(a), 25.901(c) 136 A28NM Page 82 of 103 All models Equivalent Safety Findings: In accordance with the provisions of § 21.21(b)(1) the following new ELOS finding is applicable to Modification 157272 (MaxPax): CS-2 § 25.807 Emergency Exits Finding for Increase of the Maximum Passenger Capacity (MPSC) from 220 passengers to 230 passengers CS-6 § 25.807 Emergency Exits Finding for Increase of the Maximum Passenger Capacity (MPSC) Optional Design Regulations: Part 26: Based on 14 CFR § 21.101(g), applicable provisions of 14 CFR part 26 are included in the certification basis. For any future 14 CFR part 26 amendments, the holder of this TC must demonstrate compliance with the applicable sections. The type design complies with the following 14 CFR part 26 Amendments 26-1 through 26-6 regulations: §§ 26.11, 26.33, 26.43, and 26.45. Limitation: • The exit passageway width must meet the regulatory minimum of 20 inches. The height of the attendant seat or other assembly is limited to a maximum height of 57 inches. • The unobstructed exit dimensions of the forward and aft most floor level emergency exits must not be less than 32 inches x 73 inches. • A wide slide (sliding surface width 82.75 inches (+3.0 inches, -2.0 inches)) must be installed at the forward and aft most exits. • The wide slides installed at the forward and aft most floor level exits must have a beam strength meeting the requirements of TSO-C69c. Certification basis for the Airbus Model A321-253NY/-271NY (XLR): The certification basis for the A321neo ACF for components or areas not affected by the change. Plus the following sections of 14 CFR part 25 as amended by Amendments 25-1 through 25-146 (i.e., the amendment in affect on the date of application) applied to the components and areas affected by the change: 14 CFR Section FAA accepted amendment level System/Component/Area Affected by the Change 25.1 146 Aircraft level 25.21 (a)(b)(c)(d) (e)(f) 146 plus SC 25-854-SC Aircraft level 25.23(a) 146 Aircraft level 25.23 146 Aircraft level 25.25 146 Aircraft level 25.27 (a)(b)(c) 146 Aircraft level 25.27 (c) 146 Aircraft level 25.29 146 Aircraft level 25.101 (a)(b)(i) 146 Aircraft level 25.101 (c)(d)(e)(f)(h) 146 Aircraft level 25.101 (g) 146 Aircraft level 25.103 (a)(c)(d) 146 plus SC 25-854-SC Aircraft level 25.105 (b)(c)(d) 146 Aircraft level 25.107 (e) 146 Aircraft level 25.107 (a)(b)(c)(d) (e)(f)(g) 146 Aircraft level 25.109 (a)(b)(c)(d)(e)(f) (g)(h)(i) 146 Aircraft level 25.111 (a)(b)(d) 146 Aircraft level 25.111 (c) 120 Aircraft level A28NM Page 83 of 103 All models 14 CFR Section FAA accepted amendment level System/Component/Area Affected by the Change 25.113 (a)(b)(c) 146 Aircraft level 25.115 (a)(b)(c) 146 Aircraft level 25.117 146 Aircraft level 25.121 (a) 146 Aircraft level 25.123 (a) 146 Aircraft level 25.125 (f)(g) 146 Aircraft level 25.143 (a)(b)(d)(e)(f) (g)(h)(k)(l)(m)(n) 146 plus SC 25-819-SC, 25-820- SC, and 25-799-SC Aircraft level 25.145 (a)(b)(c) 146 Aircraft level 25.147 (a)(c)(d)(f) 146 Aircraft level 25.149 (a)(b)(c)(d) (e)(f)(h) 146 Aircraft level 25.161 (a)(b)(c)(d) 146 Aircraft level 25.161(a) 146 ATA 220 Auto Flight 25.171 N/A plus SC 25-857- SC Aircraft level 25.173 (a)(b)(c)(d) N/A plus SC 25-857-SC Aircraft level 25.175 (a)(b)(c)(d) N/A plus SC 25-857- SC Aircraft level 25.177 (a)(b)(c)(d) 146 plus SC 25-857-SC Aircraft level 25.181 (a)(b) 146 Aircraft level 25.201 (a)(b)(c)(d) N/A plus SC 25-854-SC Aircraft level 25.203 (a)(b)(c) N/A plus SC 25-854-SC Aircraft level 25.231 (a) 146 Aircraft level 25.233 (a)(b)(c) 146 Aircraft level 25.235 146 Aircraft level 25.251 (b) 146 Aircraft level 25.251 (a)(b) 146 ATA 275 High-Lift System 25.251 (a)(b)(c)(d)(e) 146 Aircraft level 25.253 (a)(b) 146 Aircraft level 25.253 (a)(1)(a)(2) 146 ATA 220 Auto Flight 25.255 146 Aircraft level 25.301 (a)(b)(c) 146 Aircraft level 25.301 (a) 146 ATA 02x Airframe - Section 15 (Center Fuselage - Section 17 (Aft Fuselage) and - Extended belly fairing with substructure 25.303 146 ATA 02x Airframe - Section 15 (Center Fuselage - Section 17 (Aft Fuselage) and - Extended belly fairing with substructure 25.305 (a)(b)(c) 146 ATA 02x Airframe - Section 15 (Center Fuselage - Section 17 (Aft Fuselage) and - Extended belly fairing with substructure 25.305 (c)(e)(f) 146 Aircraft level 25.307 (a) 146 ATA 02x Airframe - Section 15 (Center Fuselage - Section 17 (Aft Fuselage) and - Extended belly fairing with substructure 25.321 (a)(b)(c)(d) 146 Aircraft level 25.331 (a)(b)(c) 146 Aircraft level 25.333 (a)(b) 146 Aircraft level 25.335 (b)(e) 146 Aircraft level A28NM Page 84 of 103 All models 14 CFR Section FAA accepted amendment level System/Component/Area Affected by the Change 25.335 (a)(b)(c)(d)(e)(f) 146 plus SC 25-470- SC Aircraft level 25.337 (a)(b)(c) 146 Aircraft level 25.341 (a)(b)(c) 146 Aircraft level 25.343 (b)(2) 146 Aircraft level 25.343 (b)(3) 146 Aircraft level 25.343 (a)(b)(1)(b)(2) 146 Aircraft level 25.345 (a)(b)(d) 146 Aircraft level 25.349 (a)(1)(a)(5)(b) 146 Aircraft level 25.351 (a)(b)(c)(d) 146 Aircraft level 25.353 (a)(b)(c)(d)(e) 146 ATA 270 Flight Control 25.361 (a) 146 Aircraft level 25.362 (a)(b) 146 Aircraft level 25.365 (a)(b)(d) (e)(1) 146 ATA 02x Airframe - Section 15 (Center Fuselage - Section 17 (Aft Fuselage) and - Extended belly fairing with substructure 25.365(e)(f) 146 ATA 026 Rapid Decompression - Cabin, cargo compartment and belly fairing 25.367 (a)(b) 146 Aircraft level 25.371 146 Aircraft level 23.373 (a)(b) 146 Aircraft level 25.391 (a)(b)(d)(e) 146 Aircraft level 25.393 (a)(b) 146 ATA 010 Aircraft Loads due to RCT integration ATA 275 High-Lift System 25.393 (b) 146 ATA 02x Airframe - Section 15 (Center Fuselage - Section 17 (Aft Fuselage) and - Extended belly fairing with substructure 25.405 146 ATA 275 High-Lift System ATA 320 Landing Gear 25.427 (a)(b)(d) 146 Aircraft level 25.445 (a) 146 Aircraft level 25.457 146 Aircraft level 25.459 146 Aircraft level 25.471 (a)(b) 146 Aircraft level 25.473 (a)(b)(c)(d)(e) 146 Aircraft level 25.477 146 ATA 320 Landing Gear 25.479 (a)(c)(d) 146 Aircraft level 25.481 (a)(c) 146 Aircraft level 25.483 (a)(b) 146 Aircraft level 25.485 (a)(b) 146 Aircraft level 25.487 (a)(b) 146 Aircraft level 25.489 146 Aircraft level 25.491 146 Aircraft level 25.493 (b)(c)(d)(e) 146 Aircraft level 25.495 146 Aircraft level 25.499 (a)(b)(c)(d)(e) 146 Aircraft level 25.503 (a)(b) 146 Aircraft level 25.507 (a)(b) 146 Aircraft level 25.509 (a)(c)(d) 146 Aircraft level 25.511 (a)(b)(c)(d)(e)(f) 146 Aircraft level 25.519 (a)(b)(c) 146 Aircraft level 25.519 (a)(b) 146 Aircraft level 25.561 (a)(b)(c)(d) 146 Aircraft level 25.561 (b)(c)(d) 146 ATA 02x Airframe - Section 15 (Center Fuselage - Section 17 (Aft Fuselage) and - Extended belly fairing with substructure A28NM Page 85 of 103 All models 14 CFR Section FAA accepted amendment level System/Component/Area Affected by the Change 25.561 (b)(c) 146 ATA 380 Water and Waste 25.561 (c) 146 ATA 210 Ventilation of RCT ATA 470 Fuel Inerting: - New Flammability Reduction System 25.581 (b) 146 ATA 210 Ventilation of RCT 25.581 (a)(b)(c) 146 ATA 275 High-Lift System ATA 280 Fuel: Additional RCT ATA 470 Fuel Inerting: - New Flammability Reduction System ATA 390 Lightning Indirect effects, HIRF and EMI for the complete aircraft ATA 391 Lightning Direct Effects for the complete aircraft 25.601 146 ATA 02x Airframe - Section 15 (Center Fuselage - Section 17 (Aft Fuselage) and - Extended belly fairing with substructure 25.603 146 ATA 02x Airframe - Section 15 (Center Fuselage - Section 17 (Aft Fuselage) and - Extended belly fairing with substructure 25.603(c) 146 Aircraft level 25.605 146 ATA 02x Airframe - Section 15 (Center Fuselage - Section 17 (Aft Fuselage) and - Extended belly fairing with substructure 25.607 (a)(b) 146 ATA 380 Water and Waste 25.607 146 ATA 02x Airframe - Section 15 (Center Fuselage - Section 17 (Aft Fuselage) and - Extended belly fairing with substructure 25.609 146 ATA 02x Airframe - Section 15 (Center Fuselage - Section 17 (Aft Fuselage) and - Extended belly fairing with substructure 25.611 (a) 146 ATA 207 Instruction for Continued Airworthiness ATA 210 Ventilation of RCT 25.613 146 ATA 02x Airframe - Section 15 (Center Fuselage - Section 17 (Aft Fuselage) and - Extended belly fairing with substructure 25.619 146 ATA 02x Airframe - Section 15 (Center Fuselage - Section 17 (Aft Fuselage) and - Extended belly fairing with substructure 25.625 146 ATA 02x Airframe - Section 15 (Center Fuselage - Section 17 (Aft Fuselage) and - Extended belly fairing with substructure 25.629 (d)(4) 146 ATA 270 Flight Control 25.629 (a)(b)(c)(d)(e) 146 Aircraft level 25.631 146 ATA 02x Airframe - Section 15 (Center Fuselage - Section 17 (Aft Fuselage) and - Extended belly fairing with substructure ATA 320 Landing Gear ATA 360 Pneumatic System 25.671 (b)(c)(d) 146 ATA 275 High-Lift System 25.671 (a)(b)(d) 146 ATA 275 High-Lift System 25.671 (a)(d) 146 Aircraft level 25.671 (a) 146 ATA 220 Auto Flight 25.672 (a)(c) 146 ATA 070 Aircraft Handling Qualities A28NM Page 86 of 103 All models 14 CFR Section FAA accepted amendment level System/Component/Area Affected by the Change ATA 270 Flight Control 25.672 (a) 146 ATA 315 Flights Warning System 25.675 (a)(b)(c) 146 ATA 275 High-Lift System 25.683 (b) 146 ATA 270 Flight Control ATA 275 High-Lift System 25.685 (a)(c) 146 ATA 275 High-Lift System 25.693 146 ATA 275 High-Lift System 25.697 (a)(c)(d) 146 ATA 275 High-Lift System 25.699 (a)(b)(c) 146 ATA 275 High-Lift System 25.701 (a)(b)(c)(d) 146 ATA 275 High-Lift System 25.703 (a)(b)(c) 146 ATA 315 Flight Warning System 25.721 (b) 146 Aircraft level 25.721 (a)(b)(c) 146 Aircraft level 25.723 (a)(b)(c) 146 Aircraft level 25.723 (b) 146 ATA 02x Airframe - Section 15 (Center Fuselage - Section 17 (Aft Fuselage) and - Extended belly fairing with substructure 25.729 (a) 146 Aircraft level 25.729 (a)(b)(d) (e)(1) 146 ATA 320 Landing Gear 25.729(c)(e)(2)(e)(3)(e)(4)(e)( 5)(e)(6) (e)(7) 146 ATA 320 Landing Gear 25.729(e)(2)(e)(3)(e)(4)(e)(5)( e)(6) (e)(7) 146 ATA 315 Flight Warning System 25.729(f)(1)(f)(2) (f)(3) 146 ATA 320 Landing Gear 25.731 (a)(b)(c)(d)(e) 146 ATA 320 Landing Gear 25.733 (b)(c)(d)(e) 146 ATA 320 Landing Gear 25.735 (a) 146 ATA 320 Landing Gear 25.735 (b)(1)(c)(1)(d)(e) 146 ATA 320 Landing Gear 25.735 (b)(2)(c)(2) 146 ATA 320 Landing Gear 25.735 (f)(1) 146 ATA 320 Landing Gear 25.735 (f)(2) 146 ATA 320 Landing Gear 25.735 (f)(3) 146 ATA 320 Landing Gear 25.735 (g)(i)(j)(k) 146 ATA 320 Landing Gear 25.777 (a) 146 ATA 251 Cockpit layout 25.777 (i) 146 ATA 070 Aircraft Handling Qualities ATA 251 Cockpit layout 25.795 (b)(3) N/A ATA 204 Survivability of Systems 25.795 (c)(2) N/A plus ADRC Aircraft level 25.801 (d) 146 ATA 025 Ditching - Unplanned ditching analysis ATA 256 Emergency evacuation analysis 25.807 (i) 146 ATA 256 Emergency evacuation analysis 25.809 (g) 146 Aircraft level 25.843 (a) 146 ATA 02x Airframe - Section 15 (Center Fuselage - Section 17 (Aft Fuselage) and - Extended belly fairing with substructure 25.851 (b)(2) 146 ATA 260 Fire protection in un-pressurized areas: - Main Landing Gear Bay - Aft belly fairing Fire protection in pressurized areas: - Triangle area - RCT roof - Aft RCT area 25.853 (a) 146 ATA 210 Ventilation of RCT 25.855 (f)(h) 146 ATA 260 Fire protection in un-pressurized areas: - Main Landing Gear Bay - Aft belly fairing Fire protection in pressurized areas: A28NM Page 87 of 103 All models 14 CFR Section FAA accepted amendment level System/Component/Area Affected by the Change - Triangle area - RCT roof - Aft RCT area 25.856 (a)(b) 146 plus SC 25-825-SC for (b) ATA 210 Ventilation of RCT ATA 258 Thermal Acoustic Insulation 25.857 (c) 146 ATA 315 Flight Warning System 25.857 146 ATA 260 Fire protection in un-pressurized areas: - Main Landing Gear Bay - Aft belly fairing Fire protection in pressurized areas: - Triangle area - RCT roof - Aft RCT area 25.858 146 ATA 260 Fire protection in un-pressurized areas: - Main Landing Gear Bay - Aft belly fairing Fire protection in pressurized areas: - Triangle area - RCT roof - Aft RCT area 25.863 (a)(b) 146 ATA 260 Fire protection in un-pressurized areas: - Main Landing Gear Bay - Aft belly fairing Fire protection in pressurized areas: - Triangle area - RCT roof - Aft RCT area ATA 360 Pneumatic System 25.863 (c) 146 ATA 260 Fire protection in un-pressurized areas: - Main Landing Gear Bay - Aft belly fairing Fire protection in pressurized areas: - Triangle area - RCT roof - Aft RCT area 25.863 (b)(3) 146 ATA 920 Electrical Wiring Interconnect System (EWIS) 25.863 (a)(b) 146 ATA 470 Fuel Inerting: - New Flammability Reduction System 25.863 (a) 146 ATA 210 Ventilation of RCT 25.869 (a)(1) 146 ATA 260 Fire protection in un-pressurized areas: - Main Landing Gear Bay - Aft belly fairing Fire protection in pressurized areas: - Triangle area - RCT roof - Aft RCT area ATA 380 Water and Waste 25.899 (a)(1)(a)(3)(b) 146 ATA 380 Water and Waste 25.899 (b) 146 ATA 210 Ventilation of RCT 25.899 (a)(b) 146 ATA 280 Fuel: Additional RCT ATA 470 Fuel Inerting: - New Flammability Reduction System ATA 390 Lightning Indirect effects, HIRF and EMI for the complete aircraft ATA 391 Lightning Direct Effects for the complete aircraft 25.901 (a)(b) 146 ATA 280 Fuel: Additional RCT 25.901(c) 146 ATA 010 Aircraft Loads due to RCT integration ATA 02x Airframe - Section 15 (Center Fuselage - Section 17 (Aft Fuselage) and - Extended belly fairing with substructure A28NM Page 88 of 103 All models 14 CFR Section FAA accepted amendment level System/Component/Area Affected by the Change ATA 070 Aircraft Handling Qualities ATA 204 Sustained Engine Imbalance ATA 210 Ventilation of RCT ATA 220 Auto Flight ATA 270 Flight Control ATA 275 High-Lift System ATA 280 Fuel: Additional RCT ATA 320 Landing Gear ATA 380 Water and Waste ATA 470 Fuel Inerting: - New Flammability Reduction System ATA 920 Electrical Wiring Interconnect System (EWIS) 25.903 (d) 146 ATA 470 Fuel Inerting: - New Flammability Reduction System 25.903 (c) 146 ATA 02x Airframe - Section 15 (Center Fuselage - Section 17 (Aft Fuselage) and - Extended belly fairing with substructure 25.903 (d)(1) 146 ATA 02x Airframe - Section 15 (Center Fuselage - Section 17 (Aft Fuselage) and - Extended belly fairing with substructure ATA 280 Fuel: Additional RCT ATA 220 Auto Flight ATA 270 Flight Control ATA 275 High-Lift System ATA 720 Rotor Burst analysis for the RCT area only 25.943 146 ATA 280 Fuel: Additional RCT 25.951 (c) 146 ATA 280 Fuel: Additional RCT 25.952 (a) 146 ATA 280 Fuel: Additional RCT 25.954 (a)(b)(c) 146 ATA 280 Fuel: Additional RCT ATA 390 Lightning Indirect effects, HIRF and EMI for the complete aircraft ATA 391 Lightning Direct Effects for the complete aircraft ATA 470 Fuel Inerting: - New Flammability Reduction System 25.957 146 ATA 280 Fuel: Additional RCT 25.959 146 ATA 280 Fuel: Additional RCT 25.963(a) 146 Aircraft level 25.963(b) 146 ATA 024 Aircraft Crashworthiness 25.963(a)(d)(e) (1)(e)(2) 146 ATA 02x Airframe - Section 15 (Center Fuselage - Section 17 (Aft Fuselage) and - Extended belly fairing with substructure 25.963(a)(c)(d)(1)(d)(3)(d)(4) (d)(5) (e)(1)(e)(2) 146 ATA 280 Fuel: Additional RCT 25.963 (d) 146 Aircraft level 25.963 (e)(1) 146 ATA 720 Rotor Burst analysis for the RCT area only 25.963 (e)(2) 146 ATA 260 Fire protection in un-pressurized areas: - Main Landing Gear Bay - Aft belly fairing Fire protection in pressurized areas: - Triangle area - RCT roof - Aft RCT area 25.965 (a) 146 ATA 010 Aircraft Loads due to RCT integration ATA 02x Airframe - Section 15 (Center Fuselage - Section 17 (Aft Fuselage) and A28NM Page 89 of 103 All models 14 CFR Section FAA accepted amendment level System/Component/Area Affected by the Change - Extended belly fairing with substructure 25.965 (a) 146 ATA 470 Fuel Inerting: - New Flammability Reduction System 25.965 (a)(b)(c)(d) 146 ATA 280 Fuel: Additional RCT 25.967 (a)(b)(e) 146 ATA 280 Fuel: Additional RCT 25.967 (e) 146 ATA 02x Airframe - Section 15 (Center Fuselage - Section 17 (Aft Fuselage) and - Extended belly fairing with substructure 25.969 146 ATA 280 Fuel: Additional RCT 25.971 (a)(b)(c) 146 ATA 280 Fuel: Additional RCT 25.975 (a) 146 ATA 280 Fuel: Additional RCT ATA 470 Fuel Inerting: - New Flammability Reduction System 25.977 (a)(c)(d)(e) 146 ATA 280 Fuel: Additional RCT 25.979 (b)(c)(d)(e) 146 ATA 280 Fuel: Additional RCT 25.981 (a) 146 ATA 360 Pneumatic System 25.981 (a)(b) 146 ATA 390 Lightning Indirect effects, HIRF and EMI for the complete aircraft 25.981 (a)(b)(d) 146 ATA 280 Fuel: Additional RCT ATA 470 Fuel Inerting: - New Flammability Reduction System 25.981 (b)(3) 146 ATA 210 Ventilation of RCT 25.981 (a)(3) 146 ATA 391 Lightning Direct Effects for the complete aircraft ATA 920 Electrical Wiring Interconnect System (EWIS) analysis 25.993 (a)(b)(c)(d)(e)(f) 146 ATA 280 Fuel: Additional RCT 25.993 (a)(b)(c)(d)(f) 146 ATA 470 Fuel Inerting: - New Flammability Reduction System 25.994 146 ATA 024 Aircraft Crashworthiness ATA 280 Fuel: Additional RCT ATA 470 Fuel Inerting: - New Flammability Reduction System 25.995 (b) 146 ATA 280 Fuel: Additional RCT 25.999 (a)(b) 146 ATA 280 Fuel: Additional RCT 25.1001 (a)(b) 146 Aircraft level 25.1103 (d) 146 ATA 210 Ventilation of RCT ATA 470 Fuel Inerting: - New Flammability Reduction System 25.1141 (a)(c)(d) 146 ATA 251 Cockpit layout 25.1141 (a)(c)(d)(f) 146 ATA 280 Fuel: Additional RCT 25.1185 (c) 146 ATA 280 Fuel: Additional RCT 25.1189 (f)(h) 146 ATA 280 Fuel: Additional RCT 25.1301 146 ATA 200 System Safety, ATA 210 Air Conditioning - Ventilation of RCT ATA 260 Fire protection in un-pressurized areas: - Main Landing Gear Bay - Aft belly fairing Fire protection in pressurized areas: - Triangle area - RCT roof - Aft RCT area ATA 280 Fuel: Additional RCT ATA 315 Flight Warning System ATA 320 Landing Gear ATA 380 Water and Waste: ATA 470 Fuel Inerting: - New Flammability Reduction System 25.1302 (a)(b)(c)(d) 146 ATA 275 High-lift System ATA 280 Fuel: Additional RCT A28NM Page 90 of 103 All models 14 CFR Section FAA accepted amendment level System/Component/Area Affected by the Change 25.1305(a)(2) 146 ATA 280 Fuel: Additional RCT ATA 316 Electronic Instrument Systems - Enhanced Electronic System 25.1309 146 ATA 200 System Safety, ATA 210 Air Conditioning - Ventilation of RCT ATA 260 Fire protection in un-pressurized areas: - Main Landing Gear Bay - Aft belly fairing Fire protection in pressurized areas: - Triangle area - RCT roof - Aft RCT area ATA 280 Fuel: Additional RCT ATA 315 Flight Warning System ATA 320 Landing Gear ATA 380 Water and Waste ATA 390 Lightning Indirect effects, HIRF and EMI for the complete aircraft ATA 470 Fuel Inerting: - New Flammability Reduction System 25.1310 146 ATA 280 Fuel: Additional RCT 25.1315 146 ATA 280 Fuel: Additional RCT 25.1316 146 ATA 280 Fuel: Additional RCT 25.1316 (b) 146 ATA 210 Ventilation of RCT 25.1316 (a)(b) 146 ATA 275 High-Lift System ATA 380 Water and Waste ATA 390 Lightning Indirect effects, HIRF and EMI for the complete aircraft 25.1317 146 ATA 280 Fuel: Additional RCT 25.1317 (c) 146 ATA 210 Air Conditioning - Ventilation of RCT 25.1317 (a)(b)(c) 146 ATA 275 High-lift System ATA 380 Water and Waste ATA 390 Lightning Indirect effects, HIRF and EMI for the complete aircraft 25.1322 146 ATA 280 Fuel: Additional RCT ATA 315 Flight Warning System ATA 316 Electronic Instrument Systems - Enhanced Electronic System 25.1323 (c)(d) 146 ATA 341 Navigation 25.1325 (e) 146 ATA 341 Navigation 25.1337 (b) 146 ATA 280 Fuel: Additional RCT ATA 316 Electronic Instrument Systems - Enhanced Electronic System 25.1353 (a) 146 ATA 210 Air Conditioning - Ventilation of RCT ATA 380 Water and Waste 25.1353 (a)(b) 146 ATA 390 Lightning Indirect effects, HIRF and EMI for the complete aircraft. 25.1381 (a)(2)(ii)(b) 146 ATA 251 Cockpit layout 25.1419 (a) 146 Aircraft level 25.1419 (c) 146 ATA 315 Flight Warning System 25.1419(a)(b) 146 Aircraft level 25.1419 146 ATA 300 Icing is an area not affected 25.1431 (a)(b)(c) 146 ATA 275 High-lift System 25.1431 (a)(c) 146 ATA 210 Air Conditioning - Ventilation of RCT 25.1431 (a)(c)(d) 146 ATA 380 Water and Waste ATA 390 Lightning Indirect effects, HIRF and EMI for the complete aircraft. 25.1435 (a)(1)(a)(2)(a)((3)(a)(4)(a)(5)( b)(2) (b)(5)(c)(1) 146 ATA 320 Landing Gear 25.1438 146 ATA 210 Air Conditioning - Ventilation of RCT ATA 470 Fuel Inerting: - New Flammability Reduction System A28NM Page 91 of 103 All models 14 CFR Section FAA accepted amendment level System/Component/Area Affected by the Change 25.1501 (a)(b) 146 Aircraft level 25.1503 146 Aircraft level 25.1505 146 Aircraft level 25.1507 146 Aircraft level 25.1511 146 Aircraft level 25.1513 146 Aircraft level 25.1515 (a)(b) 146 Aircraft level 25.1516 146 Aircraft level 25.1517 (a)(b)(c) 146 Aircraft level 25.1519 146 Aircraft level 25.1521 (a)(d) 146 Aircraft level 25.1523 (a)(b)(c) 146 Aircraft level 25.1525 146 ATA 101 Airplane Flight Manual (AFM) ATA 380 Water and Waste 25.1527 146 ATA 070 Aircraft Handling Qualities ATA 101 Airplane Flight Manual (AFM) ATA 380 Water and Waste 25.1531 146 Aircraft level 25.1533 (a)(b) 146 Aircraft level 25.1535 146 Aircraft level 25.1541 (a)(b) 146 ATA 380 Water and Waste ATA 470 Fuel Inerting: - New Flammability Reduction System 25.1541 (a) 146 ATA 251 Cockpit layout 25.1543 (b) 146 ATA 280 Fuel: Additional RCT 25.1553 146 ATA 280 Fuel: Additional RCT ATA 316 Electronic Instrument Systems - Enhanced Electronic System 25.1555 (a)(c)(3) 146 ATA 251 Cockpit layout 25.1555 (c) 146 ATA 280 Fuel: Additional RCT 25.1563 146 ATA 101 Airplane Flight Manual (AFM) ATA 251 Cockpit layout ATA 275 High-lift System ATA 316 Electronic Instrument Systems - Enhanced Electronic System 25.1581 (a)(2) 146 ATA 344 Navigation Surveillance 25.1581 (a)(b) 146 Aircraft level 25.1581 (a)(b)(d) 146 ATA 101 Airplane Flight Manual (AFM) ATA 270 Flight Control 25.1583 (b)(c) 146 ATA 280 Fuel: Additional RCT 25.1583 (h)(k) 146 Aircraft level 25.1583 (f) 146 ATA 344 Navigation Surveillance 25.1583 (c) 146 Aircraft level 25.1583 146 Aircraft level 25.1585 (a) 146 ATA 060 Aircraft Performance ATA 070 Aircraft Handling Qualities 25.1585 146 ATA 101 Airplane Flight Manual (AFM) ATA 280 Fuel: Additional RCT 25.1585 (a)(b) 146 ATA 270 Flight Control 25.1587 (b)(c) 146 Aircraft level 25.1591 (a)(b)(c) 146 Aircraft level 25.1701 (a)(b)(c) 146 ATA 320 Landing Gear ATA 380 Water and Waste ATA 470 Fuel Inerting: - New Flammability Reduction System ATA 920 Electrical Wiring Interconnect System (EWIS) 25.1701 (a)(b) 146 ATA 280 Fuel: Additional RCT 25.1703 (a) 146 ATA 275 High-lift System ATA 470 Fuel Inerting: - New Flammability Reduction System 25.1703 (a)(1)(a)(2)(a)(3) 146 ATA 280 Fuel: Additional RCT A28NM Page 92 of 103 All models 14 CFR Section FAA accepted amendment level System/Component/Area Affected by the Change 25.1703 (a)(1)(b) 146 ATA 380 Water and Waste 25.1703 (a)(b)(d)(e) 146 ATA 920 Electrical Wiring Interconnect System (EWIS) 25.1705 (a) 146 ATA 275 High-lift System ATA 320 Landing Gear ATA 470 Fuel Inerting: - New Flammability Reduction System limited ATA 920 Electrical Wiring Interconnect System (EWIS) 25.1705 (a)(b)(4) 146 ATA 280 Fuel: Additional RCT 25.1705 (b)(2)(b)(5)(b)(12) 146 ATA 390 Lightning Indirect effects, HIRF and EMI for the complete aircraft 25.1707 (a)(b)(c)(e) (f)(h)(k)(l) 146 ATA 920 Electrical Wiring Interconnect System (EWIS) 25.1707 (a)(b)(e)(1) 146 ATA 280 Fuel: Additional RCT 25.1707 (a) 146 ATA 275 High-lift System ATA 470 Fuel Inerting: - New Flammability Reduction System 25.1707 (b) 146 ATA 390 Lightning Indirect effects, HIRF and EMI for the complete aircraft. 25.1707 (b)(c)(h) 146 ATA 380 Water and Waste 25.1709 146 ATA 280 Fuel: Additional RCT 25.1709 (a)(b) 146 ATA 320 Landing Gear ATA 380 Water and Waste: ATA 470 Fuel Inerting: - New Flammability Reduction System ATA 275 High-lift System ATA 920 Electrical Wiring Interconnect System (EWIS) 25.1711 146 ATA 920 Electrical Wiring Interconnect System (EWIS) 25.1711 (a)(b)(c)(d) 146 ATA 280 Fuel: Additional RCT 25.1713 (a)(c) 146 ATA 280 Fuel: Additional RCT ATA 920 Electrical Wiring Interconnect System (EWIS) 25.1715 (b) 146 ATA 275 High-lift System ATA 380 Water and Waste ATA 470 Fuel Inerting: - New Flammability Reduction System. 25.1715 (a)(b) 146 ATA 280 Fuel: Additional RCT ATA 390 Lightning Indirect effects, HIRF and EMI for the complete aircraft ATA 920 Electrical Wiring Interconnect System (EWIS) 25.1717 146 ATA 275 High-lift System ATA 280 Fuel: Additional RCT ATA 380 Water and Waste ATA 470 Fuel Inerting: - New Flammability Reduction System ATA 920 Electrical Wiring Interconnect System (EWIS) 25.1719 146 ATA 920 Electrical Wiring Interconnect System (EWIS) 25.1721 (b) 146 ATA 920 Electrical Wiring Interconnect System (EWIS) 25.1723 146 ATA 920 Electrical Wiring Interconnect System (EWIS) 25.1725 (b) 146 ATA 920 Electrical Wiring Interconnect System (EWIS) 25.1727 146 ATA 920 Electrical Wiring Interconnect System (EWIS) Note: For a certain number of requirements which are not impacted by the significant change, Airbus decided to upgrade to FAR 25 Amdt 146. Special Conditions: In accordance with § 21.16, the special conditions applied to the baseline Model airplanes as listed in FAA TCDS A28NM Revision 38 are retained and applicable to the components and areas affected by these changes. In addition the following FAA Special Conditions apply to the Airbus Model A321neo XLR Airplane: A28NM Page 93 of 103 All models Special Condition No. Subject 25-825-SC Passenger Protection from External Fire. 25-857-SC Electronic Flight-Control System: Lateral- Directional and Longitudinal Stability, and Low-Energy Awareness. 25-854-SC Flight Envelope Protection, Icing and Non- Icing Conditions; High Incidence Protection. 25-820-SC Flight Envelope Protection Functions General 25-819-SC Side Stick Controller – Controllability and Maneuverability. 25-799-SC Flight Control Awareness and Mode Annunciation 25-868-SC Cabin Evacuation Protection from Fuel Tank Explosion Due to External Fuel Fed Ground Fire Equivalent Safety Findings: The equivalent level of Safety (ESF) applied to the baseline Model airplanes as listed in FAA TCDS A28NM Revision 38 remains applicable; In addition, following ELOS IPs have been raised: ELOS Memo No. Regulations Title AT11031IB-T-25.1563-1 § 25.1563 Airspeed Placard AT10637IB-T-CS-4 § 25.807(g) Increased Passenger Credit for Type III Over-Wing Exits AT10637IB-T-CS-3 §§ 25.807(a)(3)(b) & (c); 25.813(c)(1) & (c)(2). Passageway Displacement for Type III Exits AT11031IB-T-ES-1 § 25.1438 Pneumatic Systems AT18777IB-T-25.979-1 § 25.979(b)(1) Pressure Fueling System Shut -off Operation Check on Airbus Mo del A321neo Extra -Long Range (XLR) Airplanes with Optional Forward Additional Center Tank (ACT) Exemptions: The Exemptions applicable to each model as defined in TCDS A28NM remain applicable plus the following exemptions applied specifically to the Airbus A321-253NY/-271NY: Exemption No. Regulation Title 13048D § 25.841(a)(2)(i) &(ii) Cabin Pressurization 17122A § 25.809(a) at Amendment 25-116 Outside viewing of the flight deck emergency exit 18016B § 25.807(g)(7) Allows more than the regulatory combined maximum number of passenger seats for all Type II exits when the mid-cabin door (Door 3) is de-rated to a Type III exit for Airbus Model A321neo ACF airplanes. 18674A § 25.813(e), 121.310(f)(5), and 121.310(f)(6) Installation of mini-suites for passengers (including those with reduced mobility (PRM-suites), with doors and movable aisle walls Exceptions: Below are the exceptions* that were accepted: A28NM Page 94 of 103 All models 14 CFR Section FAA accepted amendment level System/Component/Area Affected by the Change 25.103 (b) 120 plus SC 25-854-SC Aircraft level 25.105 (a) 120 plus SC 25-854-SC Aircraft level 25.111 (c) 120 Aircraft level 25.119 (a)(b) 120 Aircraft level 25.121 (b)(c)(d) 120 plus SC 25-854-SC Aircraft level 25.123 (b) 120 plus SC 25-854-SC Aircraft level 25.125 (a)(b) 120 Aircraft level 25.207 120 plus SC 25-854-SC Aircraft level 25.237 (a) 120 Aircraft level 25.571 (a)(b)(c)(e)(1)(e)(2)(e)(3)(e)(4) 86 Airframe - Section 15 (Center Fuselage) - Section 17 (Aft Fuselage) - Extended belly fairing. 25.795 (b)(3) N/A ATA 204 Sustained Engine Imbalance - Survivability of Systems 25.795 (c)(2) N/A plus ADRC Aircraft level 25.1529 54 plus Appendix H and FAR 26.11 for Electrical Wiring Interconnection System (EWIS) ICA ATA 207 Instruction for Continued Airworthiness 25.1729 54 plus Appendix H and FAR 26.11 for Electrical Wiring Interconnection System (EWIS) ICA ATA 207 Instruction for Continued Airworthiness Optional Design Regulations: Original design approvals for the reference airplane are retained. • Ditching • Flight in Icing Conditions • ETOPS Airworthiness and Environmental Standards for components and areas affected by the change Noise Standards: 14 CFR part 36, as amended by Amendment 36-1 through Amendment 36-31. Fuel Venting and Exhaust Emissions Standards No emissions change according to § 21.93(c) / 14 CFR part 34, as amended by Amendment 34-1 through Amendment 34-5A.. Part 26: 14 CFR part 26 as amended by Amendment 26-1 through amendment 26-7 is applicable. Additional Design requirements and Conditions: Compliance with the established basis for type certification notwithstanding, § 21.21(b)(2) precludes issuance of a type certificate or amended type certificate if there is any feature or characteristic that would make the produce unsafe. No unsafe design condition was identified. A28NM Page 95 of 103 All models Note 1: The A321 basic type design definition for U.S. import certification is contained in the following documents: - 00E000A0010/C11 for A321-111 model - 00E000A0011/C11 for A321-112 model - 00E000A0012/C11 for A321-131 model - AI/EA-S 413.3365/96 (supplement) for A321-111/112/131 models - AI/EA-S 413.0401/97 for A321-211 model - AI/EA-S 413.0399/97 for A321-231 model - AI/EA-S 413.1641/01 for A321-212 Model - AI/EA-S 413.1642/01 for A321-213 Model - AI/EA-S 413.1639/01 for A321-232 Model - 00D000A5072/C20 for A321-271N Model - 00E000A5075/C20 for A312-251N Model - 00E000A5115/C20 for A321-253N Model - 00E000A5116/C20 for A321-272N Model - 00E000A5195/C00 for A321-252N Model - 00E000A5132/C00 for A321-271NX Model - 00E000A5134/C00 for A312-251NX Model - 00E000A5136/C00 for A321-253NX Model - 00E000A5133/C00 for A321-272NX Model - 00E000A5135/C00 for A321-252NX Model - 00E000A5277/C00 for A321-253NY Model - 00E000A5305/C00 for A321-271NY Model Note 2: For A321-111,-112,-131,-211,-212,-213,-231,-232,-271N,-272N,-251N,-252N,-253N Door 2 and/or Door 3 may be derated to Type III. Note 3: For models A321-111 and A321-112, modification 25199 is the minimum standard to be qualified for Cat IIIB precision approach. For models A321-131, modification 25200 is the minimum standard to be qualified for Cat IIIB precision approach. A321-211, A321-212, A321-213, A321-231 & A321-232 are basically qualified for Cat IIIB precision approach. For models A321-251N, -252N, -253N, -271N, -272N, 271NX, -272NX, -251NX,-252NX, -253NX modification 161765 is the minimum standard to be qualified for CAT IIIB precision approach. Note 4: If FWC Standard D2 and FAC standard BAM 0510 are fitted on A321 aircraft, VFE speed in configuration 2 i s increased from 205kts to 215kts (as identified by speed limitation placard installed by modification 24641). Note 5: Modifications 25302 (thrust reverser third line of defen se for IAE engine) and 25303 ( thrust reverser third line of defens e for CFM engine) are part of the FAA Type Design, and shall be implemented on any A321 aircraft entered on the U.S. register, before t he individual U.S. standard Certificate of Airworthiness be issued. Note 6: If modification 25800 is embodied on models with CFM56 -5B engines, the engine performance is improved. The engine denomination changes to /P. CFM56-5B/”non-P” engine can be intermixed with CFM56-5B/P engine on the same aircraft. Note 7: On the A321-211,-212,-213,-231,-232,-271N,-272N,-251N,-252N,-253N, one Additional Center Tank (ACT) in bulk version is defined by modification 25453 (high pressure system). Its approval together with structural and system provisions was subject of compliance demonstrated to Advisory Circular (AC) 25-8. Note 8: The type design definitions and certification standard equipment lists as referenced in Note 1 above are complemented by document 00D000A0546/C0S “A319-100/A321-200 FMGC Type Standard Evolution”. Note 9: On the A321-211,-212,-213,-231,-232,-271N,-272N,-251N,-252N,-253N, one or two Additional Center Tanks (ACT) in bulk version are defined by modification 30422 (low pressure system). Their approval together with structural and system provisions was subject of compliance demonstrated to AC 25-8. A28NM Page 96 of 103 All models Note 10: On the series A321-200, Weight Variant 001, 002 & 011, VFE speed in Configuration 1 is increased from 230 to 235 kts, and in Configuration 1+F increased from 215 to 225 kts (as identified by speed limitation placard installed by modification 28960, 28721 or 32456). Note 11: If modification 26610 is embodied on A321-111 & -212 airplanes, the engine performance and gaseous emission levels are improved. The engine denomination changes to /2P (DAC IIC Dual Annual Combustor). • CFM56-5B1/P engine can be intermixed with CFM56-5B1/2P (DAC IIC Dual Annual Combustor) engine on the same aircraft (AFM Supplement). • CFM 56-5B/2 "non P" (DAC) engine can be intermixed with CFM 56-5B/2P (DAC II C) engine on the same aircraft (AFM supplement). • CFM 56-5B/P or / "non P" (SAC) engine can be intermixed with CFM 56-5B/2P (DAC II C) engine on the same aircraft (AFM supplement). Note 12: If modification 27640 is embodied on A321-211airplanes, the engine performance and gaseous emission levels are improved. The engine denomination changes to /2P (DAC IIC Dual Annual Combustor). CFM56-5B3/P engine can be intermixed with CFM56-5B3/2P (DAC IIC Dual Annual Combustor) engine on the same aircraft (AFM Supplement). Note 13: If modification 37147 (Tech insertion program) is embodied in production or 38770 (Tech insertion program for retrofit) is embodied in service on A321 airplanes, the engine performance and gaseous emission levels are improved. The engine denomination changes to /3. Note 14: If modification 37868 (Select One Package) is embodied in production or if modification 38554 (Select One Package for Retrofit) is embodied on in-service A321 airplanes the engine performance and gaseous emission levels are improved. The engine denomination itself does not change. Note 15: If modification 38573 is embodied in service on A321 airplanes, engine hardware configurations can be intermixed with one CFM56-5Bx/3 SAC (Tech Insertion) and one CFM56-5Bx/P SAC engines. Note 16: If modification 34119 is embodied in production on A321 airplanes, CFM56-5B SAC (Single Annular Combustor) and CFM56 -5B DAC (Double Annular Combustor) engines can be intermixed on the same aircraft. Note 17: Further to “D/E/J Noise” Project approval, from November, 05th, 2009, all A321 airplane/engine configurations are eligible to be in compliance with ICAO Annex 16, Chapter 4 and FAR Part 36, Stage 4 (including Amdt 36-28), except the following : - A321-111 CFM56-5B1/2P DAC II C WV 008 (mod 30334) - A321-212 CFM56-5B1/2P DAC II C with or without mod 27772 Weight Variants 000 (Basic) / 001 (mod 28960) / 002 (mod 28721) / 003 (mod 31613) / 011 (mod 32456) - A321-212 CFM56-5B1/P or CFM56-5B1/3 Weight Variants 001 (mod 28960) / 003 (mod 31613) / 011 (mod 32456) - A321-213 CFM56-5B2/P or CFM56-5B2/3 with mod 27772 Weight Variants 001 (mod 28960) / 002 (mod 28721) / 003 (mod 31613) / 011 (mod 32456) - A321-213 CFM56-5B2/P or CFM56-5B2/3 without mod 27772 all Weight Variants - A321-112 CFM56-5B2/P or CFM56-5B2/3 without mod 27772 all Weight Variants which are eligible to be in compliance with ICAO Annex 16, Vol. I, Chapter 3 and FAR 36, Stage 3. Note 18: From March 31 2008, there is no longer any CFM56-5B1 non /P in field or in production. Note 19: If modification 38946 (“BUMP” function) is embodied on models with CFM-5B engines, the engine denomination changes to /P1 (SAC) or /2P1 (DAC) or /3B1 (Tech Insertion). The engine characteristics defined in this section remain unchanged. Intermix at aircraft level between “Non Bump” engine and “Bump” engine is not allowed. Note 20: If modification 150223 is embodied on A321 airplanes, the aircraft is eligible for a maximum capacity of 183 passengers. A28NM Page 97 of 103 All models The aircraft is fully compliant with: - FAR121-311 Amdt 121-315, - Section 25.562 Amendment 25-64 for all passenger seats and flight attendant seats and - FAA Special Condition 25-375-SC for installation of inflatable restraints. Note 21: On series A321-200 equipped with CFM56 engines, introduction of standard of wingbox without dry bay (modification 38616) increases the wing tank fuel capacity by 350 liters. Note 22: If Modification 160021 for installation of structural provisions for new large wingtip device (Sharklet) is embodied on A321 airplanes there is no appreciable effect on usable fuel quantities. Note 23: If Modification 160023 for installation of new large wingtip devices (Sharklet) is embodied on A321 ariplanes the eco efficiency and payload-range performance is improved. MOD 160023 is approved for WV 000 to WV11. The certification basis is updated as shown above. Note 24: If modifications 157272 (MAX PAX) is installed on airplanes with large wingtip devices (Sharklets - Modification 160023), the airplane is eligible for Maximum Passenger Seating Capacity (MPSC) of 230 passengers. Note 25: Limitations associated with installation of MAX PAX Modification 159115 are referenced in ELOS Memo AT10769IB -T-CS-6 dated May 16, 2017. Note 26: If modification 160684 (Alternate climb) is installed on the Model A321-271N/-271NX the engine designation changes to PW1133GA-JM. Note 27: If modification 160820 (High altitude thrust increase) is installed on the Model A321-253N the engine designation changes to LEAP-1A35A. Note 28: On the A321-251NX, - 252NX, -253NX, 271NX, -272NX up to 3 Additional Center Tanks (ACT) are defined by modification 163213. Note 29: If Modifications 159536 (MAX PAX) is installed on airplanes with wing tip fences, the airplane is eligible for Maximum Passenger Seating Capacity (MPSC) of 230 passengers. Note 30: A321-111,-112,-131,-211,-212,-213,-231,-232 models, the embodiment of modification 156130 leads to change the maintenance program and its associated Maintenance Programme Publication Trigger from 48 000FC/60 000FH to 60 000FC/120 000FH (whichever occurs first). Note 31: If modification 166872 is embodied on Airbus A321-251NX, - 252NX, -253NX, 271NX, -272NX airplanes, the aircraft design is compliant with “Emergency Exit Marking” requirements addressed by paragraph 14 CFR Part 25.811(e)(4). The FAA issued an equivalent level of safety finding memorandum AT11151IB-T-C-5 dated March 19, 2021 for this subject. Note 32: If modification 157272 (MAX PAX) is installed on the A321-251N, -252N, -253N, -271N, and -272N models, the airplane is eligible for Maximum Passenger Seating Capacity (MPSC) of 230 passengers. Note 33: If modification 173264 (engine rating) is installed on the Model A321-253NY, the engine designation changes to LEAP-1A33B2X. Note 34: If modification 170415 (engine rating) is installed on the Model A321-271NY, the engine designation changes to PW1133GAR-JM. Note 35: On the A321-253NY and A321-271NY, ozone filter converter is installed for compliance with 14 CFR Part 25 §25.832 via MOD 21215 or later standards. A28NM Page 98 of 103 All models Note 36: Serial Numbers Eligible: Until September 26 , 2004, A321 aircraft, all series, all models, have been produced in Hamburg (Germany) under approval LBA.G.0009 or I-A9 issued by LBA to Airbus. From September 27, 2004 until July 20, 2008, A321 aircraft, all series, all models, have been produced in Hamburg (Germany) under approval DE.21G.0009 issued by LBA to Airbus. Since July 21, 2008 to April 30, 2011, A321 aircraft, all series, all models, are produced in Hamburg (Germany) under approval EASA.21G.0001 issued by EASA to Airbus. Since May 1, 2011 and in accordance with the TIP, “Technical Implementing Procedure for Airworthiness and Environmental Certification Between the Federal Aviation Administration of the United States of America and the European Union Aviation Safety Agency”, A321 aircraft, all series, all models, produced under approval EASA.21.G.0001 issued by EASA to Airbus are eligible, unless otherwise stated in this TCDS. Note 37: If modification 172209 (“BUMP” function) is embodied on A321-271 or A321-271NX equipped with PW1133G-JM engines, the engine designation changes to PW1133G1-JM. This change has no impact on previously certified noise levels. Intermix at aircraft level between “non-Bump” engine and “Bump” engine is not allowed. Note 38: On the A321-253NY and A321-271NY, the optional FWD ACT (Forward Additional Center Tank) is defined by modification 170281. Note 39: If modification 174715 (engine rating) is installed on the Model A321-271N or A321-271NX, the engine designation changes to PW1133GA-JM Alternate Climb C. Note 40: If modification 167791 is installed on the Model A321-271N, A321-272N, A321-271NX, A321-272NX A321-271NY equipped with PW1100G-JM base engine, then the engine model is changed to PW1100G/2-JM rating. A28NM Page 99 of 103 All models DATA PERTINENT TO ALL MODELS Auxiliary Power Unit (APU) APU GARRETT The APU GARRETT AIRESEARCH GTCP 36-300 (A) installation is defined by MOD 20020 (Specification 31-5306B) APU Pratt & Whitney Rzeszow S.A. The APU Pratt & Whitney Rzeszow S.A. installation is defined by MOD 22562 or MOD 35864. Pratt & Whitney Rzeszow S.A. APS 3200 (Specification ESR 0802, Rev. A) APU AlliedSignal The APU Honeywell International installation is defined by MOD 25888 or 37987 Honeywell International 131-9[A] (Specification 4900 M1E 03 19 01) APU Limits: GTCP 36-300 (A) - Maximum Allowable Speed 69 204 rpm (107 %) - Maximum Gas Temperature at turbine outlet (ISA + 35°C) rated output 638°C overtemp. shutdown 711°C Maximum on starting 1038°C APS 3200 - Maximum Rotor Speed 49 300 rpm (105 %) - Maximum EGT 742°C - Maximum for Start 900°C at altitudes below 25000 ft 982°C at altitudes above 25000 ft 131-9[A] - Maximum Allowable Speed Nominal 51 728 rpm (106 %) Overshoot 53 875 rpm (110 %) - Maximum Gas Temperature at turbine outlet 675°C rated output (ISA + 23°C) 585°C overtemp. shutdown (ISA) 706°C maximum on starting (ISA) 1080°C below 35000 ft, 1108°C above 35000 ft (ISA + 40°C) 1090°C below 35000 ft, 1120°C above 35000 ft APU Approved oils: See GARRETT Report GT-7800 or in conformity with MIL-L-IAS, MIL-L23699 or DERD 2487 for the GTCP 36-300, Usable Capacity: 5.8 liters See Pratt & Whitney Maintenance Manual for approved oils for the APS 3200 See Model Specification 31-12048A-3B for Honeywell International 131-9[A] Center of Gravity Range (% Mean Aerodynamic Chord): See EASA/DGAC-Approved Airplane Flight Manual, U.S. Version. Hydraulic Fluids: - Type IV or Type V - Specification NSA 30.7110. - Capacity (Reservoirs and Systems): System Liters Gallons Green 100 26 Yellow 75 20 Blue 60 16 A28NM Page 100 of 103 All models Pressure: 3000 ± 200 PSI (207 ± 4 bar) Tires: - See Airbus Service Bulletin (SB) A320-32-1007 for CEO and A320-32-1439 for NEO Datum: Station 0 (100 inches forward of fuselage nose). Reference Mean Aerodynamic Chord (MAC): 165.10 inches / 4.1935 m (leading edge of MAC: Sta. 700.85 inches). Leveling Means: Clinometer on the cabin seat track rails. Service Information: Each of the documents listed below that contain a statement that it is approved by the European Aviation Safety Agency (EASA) - or for approvals made before September 28, 2003 - by the DGAC France, are accepted by the FAA and are considered FAA approved. Additionally, approvals issued by Airbus under the authority of EASA approved Design Organization EASA.21J.031 – or for approvals made before September 28, 2003 – under the authority of DGAC Design Organization Approval No. C01, or JAA Design Organization Approval No. F.JA.02 are considered FAA approved. These approvals pertain to the type design only. • Airbus Service bulletins, except as noted below • Structural repair manuals • Vendor manuals referenced in Airbus Service Bulletins • Aircraft flight manuals, and • Repair Instructions Design changes that are contained in Airbus service bulletins and that are classified as Non Basic/Level 1 Major in accordance with either the US/French or US/EASA Bilateral Aviation Safety Agreement Implementation Procedures for Airworthiness must be approved by the FAA. Historical Transition Statement: The Direction Generale de l’Aviation Civile (DGAC) of France originally type certified these aircraft under its Type Certificate Number 180. The FAA validated these products under U.S. Type Certificate Number A28NM. Effective September 28, 2003, EASA began oversight of these products on behalf of France under EASA Type Certificate Number EASA.A.064. Note 1 - Weight and Balance a. Current weight and balance report including list of equipment, entitled "Aircraft Inspection Report" included in certificated empty weight, and loading instructions, must be in each aircraft at the time of original certification and at all times thereafter, except in the case of operators having an approved weight control system. Airbus report, " Weight and Balance Manual," contains loading information for each airplane and interior arrangement configuration as delivered. This report contains, or refers to, information relative to location of all passengers and crew member seats, location and capacity of all cargo and baggage compartments, buffets, storage spaces and coat rooms, location and capacity of lounges, lavatories, and the required placards in the passenger compartment. b. The airplane must be loaded so that the CG is within specified limits at all times, considering fuel loading usage, gear retraction and movement of crew and passengers from their assigned positions. c. The weights of system fuel and oil, as defined below, and hydraulic fluid, all of which must be included in the airplane empty weight, are listed for each airplane in the Weight and Balance Manual specified in paragraph a. above. d. System fuel is the weight of all fuel required to fill a lines and tanks up to zero-fuel point on the fuel gauges in the most critical flight attitude, including the unusable tank fuel as defined by FAR part 25.959. (The usable fuel in the crossfeed manifold lines, manifolds, and engine that is not part of the system fuel must be included in the total usable fuel to obtain correct weight and CG for take-off.) e. The unusable fuel is that amount of fuel in the tanks which is unavailable to the engines under critical flight conditions as defined in FAR Part 25.959. This "unusable" fuel is included in System Fuel as indicated in paragraph d. above, and need not be accounted for separately. f. System oil is the weight of all remaining in the engine, constant speed drive, lines, and tanks after subtracting the oil in the tanks which is above the standpipe (zero gauge) levels. The engine oil capacities shown elsewhere in this data sheet include only the usable oil for which the tanks must be placarded. A28NM Page 101 of 103 All models Note 2: The aircraft must be operated in accordance with the DGAC or EASA -approved FAA Airplane Flight Manual. ("DGAC or EASA- approved" is considered equivalent to "FAA-approved".) Note 3: A318/A319/A320/A321 Airworthiness Limitations Sections (ALS): • ALS Part 1 - Safe Life Airworthiness Limitation Items (SL – ALI) • ALS Part 2 - Damage Tolerant Airworthiness Limitation Items (DT - ALI). • ALS Part 3 - Certification Maintenance Requirements (CMR). • ALS part 4 - System Equipment Maintenance Requirements (SEMR). • ALS Part 5 - Fuel Airworthiness Limitations. For all these documents, “EASA-approved" is considered equivalent to "FAA-approved". FAA approved variations to these documents associated with the type design of the airplane are normally included in next scheduled revision cycle by design approval holder (DAH). Note 4: If modification 25910 is embodied on A319, A320, and A321 series aircraft, or if modifications 25570 and 25861 are embodied o n A319 and A320 series aircraft, or if modifications 25570 and 25952 are embodied on A321 series aircraft, the aircraft is qual ified for operation in conditions of reduced vertical separation minimum (RVSM) of 1000 ft between flight levels 290 and 410 using ADIR U 1 and 2 only. If modifica tion 28913 and 31528 are embodied on A319, A320, and A321 series aircraft, the aircraft is qualified for operation in conditions of RVSM using ADIRU 1, and ADIRU 2 or 3. All A318 series aircraft are qualified for operation in conditions of RVSM using ADIRU 1, and ADIRU 2 or 3. This does not constitute operational approval. Note 5: ETOPS: The Type Design and Reliability of the airplane -engine combinations listed below have been evaluated in accordance with AC 120-42A or 14 CFR 25.1535 as applicable (see b elow) and found suitable for Extended Operations (ETOPS) up to 180 -minute maximum diversion time, when configured, maintained and operated in accordance with the standards contained in the latest applicable issue of the approved Airbus CMP document as listed below . This finding does not constitute operational approval to conduct ETOPS. A319 models: A319-111, A319-112, A319-113, A319-114, A319-115, A319-131, A319-132, A319-133 A320 models: A320-211, A320-212, A320-214, A320-231, A320-232, A320-233 A321 models: A321-111, A321-112, A321-211, A321-212, A321-213, A321-131, A321-231, A321-232 For these models, the applicable minimum standards are listed in the approved Airbus CMP document referenced “SA/FAA: AC 120-42A/CMP”. A318 models: A318-111, A318-112 A319neo models: A319-151N, A319-171N, A319-173N A320 models: A320-216 A320neo models: A320-251N, A320-252N, A320-253N, A320-271N, A320-272N, and A320-273N A321neo models: A321-251N, A321-252N, A321-253N, A321-271N and A321-272N, A321-251NX, A321-252NX, A321-253NX, A321-253NY, A321-271NX, A321-271NY and A321-272NX For these models, the applicable minimum standards are listed in the approved Airbus CMP document referenced “SA/FAA: 14 CFR 25.1535/CMP”. The ETOPS capability of individual aircraft is managed via the following Airbus modifications: - Modification 36664: when embodied on A318, A319, A320, and /or A321 series aircraft, the aircraft is delivered with ETOPS 180 min capability; - Modification 36667: when embodied on A318, A319, A320, and /or A321 series aircra ft, the aircraft is delivered with ETOPS 120 min capability. Embodiment of these modifications does not constitute an operational approval to conduct ETOPS. From September 29, 2025, all changes affecting ETOPS should use 14 CFR 25.1535 at amendment 25-120, or later, to ensure an adequate certification basis. Note 6: The design of the slide rafts does not allow survival equipment to be attached as required by 25.1415(c). The FAA issued ELOS Memo TD00839IB-T-CI-14 to 25.1415(c) for this subject. A28NM Page 102 of 103 All models Note 7: If modification 35944 (FADEC Standard “SCN19” for aircraft equipped with IAE engines) or modification 36462 (FADEC Standard “5BM” for aircraft equipped with CFM engines) is embodied the aircraft is eligible for the following improvements of thrust management: • Derate Take-Off (DTO) capability up to 40% (Modification 35932 (IAE) or Modification 36481 (CFM)) • Flexible Take-Off capability up to 40% (Modification 36750) Note 8: If modification 37986 is incorporated on Airbus Model A318, A319, or A320 airplanes, the Head Up Display is activated. Note 9: If modification 150700, and 37270 (with CLS option only), 37048 and 36985 are embodied in production on A318, A319, A320, or A321 airplanes, the airplane is compliant with Fuselage Flame Penetration “Burnthrough” requirements addressed by paragraph 14 CFR Part 25.856(b) Amdt 25-111. The FAA issued an equivalent level of safety finding memorandum TD0669IB -T-CI-12 for this subject. Note 10: If modification 150628 is embodied on Airbus Model A318, A319, A320 or A321 airplanes, the aircraft design is compliant with the new operating regulation FAR §121.359(j) which requires the compliance to amended FAR 25.1457 implemented by FAA to increase the Solid State Cockpit Voice Recorder (SSCVR) availability. The FAA issued an equivalent level of safety finding memorandum TD0781IB-T-SE-26 for this subject . Note 11: If modification 38062 (Fuel Tank Inerting System (FTIS)) is embodied on A318, A319, A320, or A321 airplanes, the airplane is compliant with Part 25 appendix M & N at amendment 25-125, and Section 26.33 at amendment 26-3, and the changes introduced with the FTIS are compliant with 14 CFR Section 25.981(a) & (b) at amendment 25-102. Reference, ELOS memo TD0550IB-T-P- 17. Note 12: Cabin seats shall conform to the specification ref. 00D252K0004/C01. Plus technical note SA2521ME1619350 issue 5 (technical note applicable to A321-251NX, -252NX, -253NX, -271NX,-271NX) Note 13: If modification 157393 Issue 1 is embodied on Model A318, A319, A320 or A321 series airplanes, the following limitation apply: “For airplanes equipped with pictograms on exit marking signs and on exit location signs, the cabin crew in charge of the safety briefing must highlight these pictograms to the passengers prior to each takeoff and each landing.” The FAA issued an equivalent level of safety finding memorandum TD01046IB-T-CS-1 dated October 26, 2015 for this subject. Note 14: If Modification 34829 is embodied on Model A319, A320 or A321 series airplanes the no smoking signs are controlled by a software device independent of cockpit switch position and is compliant with Title 14 CFR §25.791 at amendment 25-32 and § 25.791(a) at amendment 25-72. The FAA issued an equivalent level of safety finding/policy memorandum ANM-03-115-05 dated July 07, 2003 for this subject. Note 15: If modification 167557 is embodied on Airbus Model A318, A319, A320 or A321 airplanes, the aircraft design is compliant with “Security considerations protection of flightcrew compartment” requirements addressed by paragraph 14 CFR Part 25.795(a)(1). The FAA issued an equivalent level of safety finding memorandum AT11113IB-T-C-4 dated February 22, 2021 for this subject. Note 16: For A318, A319 and A320 aircraft equipped with Overwing Exits, the aircraft design is compliant with “Emergency Exit Access” requirements addressed by paragraph 14 CFR Part 25.813(c)(1). The FAA issued an equivalent level of safety finding memorandum CT5555NM-CI-1 dated August 5, 2021 for this subject. Note 17: For an A318, A319, A320 and A321 aircraft equipped with a Large Antenna, GoGo (HBCS) KU Band, the aircraft design is compliant with “Vibration and buffeting” requirements addressed by paragraph 14 CFR Part 25.251(b). The FAA issued an equivalent level of safety finding memorandum AT11425IB-T-F-1 dated October 13, 2022 for this subject. A28NM Page 103 of 103 All models Note 18: If modification 172043 is embodied on Airbus A319, A320 or A321 airplanes, the aircraft design is compliant with “Compartment interiors” requirements addressed by paragraph 14 CFR Part 25.8531(b). The FAA issued an equivalent level of safety finding memorandum AT11469IB-T-25.853(b) dated August 29, 2022 for this subject. Note 19: For an A320-251N, -252N, -253N, -271N, -272N and -273N as well as A321-251NX, -252NX, -253NX, -271NX and -272NX, if a flight attendant seat is mounted on a hinged lavatory door, the aircraft design is compliant with FAA Special Condition No. 25-835- SC dated February 28, 2023. Note 20: For an A318, A319, A320 and A321 equipped with rechargeable Lithium Ion, the aircraft is compliant with FAA Special Condition No. 25-837-SC dated June 4, 2023. Note 21: For the A320 and A321 series aircraft, all changes installing lavatory or galley adjacent to flight crew compartment on aircraft delivered after June 2026, where application for change is received by the TC holder’s State of Design (EASA) after 02 June 2023, the aircraft design is compliant with “Security considerations protection of flightcrew compartment” requirements addressed by paragraph 14 CFR Part 25.795(a)(1), 25.795(a)(3) at amendment 145. Note 22: When MOD 175660 (IPSB) is embodied on Model A319, A320 or A321 series airplanes, 14 CFR Part 25.795(a)(4) is applicable at Amendment 150. Note 23: For A321neo ACF and A321neo XLR airplanes with interiors containing oblique (side-facing) passenger seats which may include a 3-point restraint system with pretensioner and are installed at an angle of 18° to 45° to the aircraft centerline, IP 25-870-SC is applicable. Note 24: For A321neo ACF and A321neo XLR airplanes with interiors containing single-occupant oblique seat with an airbag and 3-point or pretensioner restraint system and are installed at an angle of 49° from the cabin centerline, IP 25-875-SC is applicable. Note 25: For all changes installing lavatory or galley adjacent to flight crew compartment on aircraft delivered after June 2026, where application for change is received after 02 June 2023, 14 CFR Part 25.795(a)(1), 25.795(a)(3) are at Amendment 145. Note 26: From 26 June 2025, for each Minor/Major Change on the A318, A319, A320 and A321 model, except those changes of design to TC, which are reconducted from other model(s) and where the change on this new model does not introduce any design-related human performance change, 14 CFR Part 25.1302 at amendment 146 is applicable. -----END---- ``` ## ADs (663, first 50, in force first) - [AD 2026-17-01](https://openairdocs.org/ad/2026-17-01): Fuselage · Airbus A320-211, A320-212, A320-214 and 12 more. Effective Oct 1, 2026 - [AD 2026-17-04](https://openairdocs.org/ad/2026-17-04): Landing Gear · Airbus A318-111, A318-112, A318-121 and 46 more. Effective Oct 1, 2026 - [AD 2026-18-03](https://openairdocs.org/ad/2026-18-03): Wings · Airbus A318-112, A319-115, A319-132 and 14 more. Effective Sep 18, 2026 - [AD 2026-15-13](https://openairdocs.org/ad/2026-15-13): Pneumatic · Airbus A319-151N, A319-153N, A319-171N and 19 more. 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Effective Nov 26, 2024 - [AD 2024-19-07](https://openairdocs.org/ad/2024-19-07): Engine Fuel and Control · CFM International LEAP-1A32 and A321-251NX. Effective Oct 7, 2024 - [AD 2024-12-01](https://openairdocs.org/ad/2024-12-01): Wings · Airbus A318-111, A318-112, A318-121 and 25 more. Effective Aug 13, 2024 - [AD 2024-11-01](https://openairdocs.org/ad/2024-11-01): Electrical Power · Airbus A300 B4-2C, A300 B4-103, A300 B4-203 and 94 more. Effective Jul 3, 2024 All 663: https://openairdocs.org/tcds/A28NM/ads.md ## Registered aircraft by registry model (OpenAirDocs) - [Airbus A321-231](https://openairdocs.org/model/airbus-a321-231): 248 aircraft (registry code 3940032) - [Airbus S A S A321-271NX](https://openairdocs.org/model/airbus-s-a-s-a321-271nx): 202 aircraft (registry code 3930916) - [Airbus A320-232](https://openairdocs.org/model/airbus-a320-232): 189 aircraft (registry codes 3940004, 3940304) - [Airbus A320-214](https://openairdocs.org/model/airbus-a320-214): 160 aircraft (registry code 3940006) - [Airbus A321-271NX](https://openairdocs.org/model/airbus-a321-271nx): 123 aircraft (registry code 3930915) - [Airbus A320-251N](https://openairdocs.org/model/airbus-a320-251n): 120 aircraft (registry codes 3940325, 3940310) - [Airbus A320-271N](https://openairdocs.org/model/airbus-a320-271n): 111 aircraft (registry codes 3940320, 3940307) - [Airbus Industrie A320-232](https://openairdocs.org/model/airbus-industrie-a320-232): 109 aircraft (registry code 3930326) - [Airbus A321-211](https://openairdocs.org/model/airbus-a321-211): 106 aircraft (registry codes 3940005, 3940305) - [Airbus A321-253NX](https://openairdocs.org/model/airbus-a321-253nx): 70 aircraft (registry code 3940051) - [Airbus A321-213](https://openairdocs.org/model/airbus-a321-213): 65 aircraft (registry code 3940028) - [Airbus Industrie A319-112](https://openairdocs.org/model/airbus-industrie-a319-112): 54 aircraft (registry code 3930323) - [Airbus Industrie A319-131](https://openairdocs.org/model/airbus-industrie-a319-131): 50 aircraft (registry code 3930317) - [Airbus A319-115](https://openairdocs.org/model/airbus-a319-115): 42 aircraft (registry code 3940034) - [Airbus Industrie A320-212](https://openairdocs.org/model/airbus-industrie-a320-212): 39 aircraft (registry code 3930322) - [Airbus A319-132](https://openairdocs.org/model/airbus-a319-132): 37 aircraft (registry code 3940015) - [Airbus A319-114](https://openairdocs.org/model/airbus-a319-114): 31 aircraft (registry code 3940002) - [Airbus Industrie A321-231](https://openairdocs.org/model/airbus-industrie-a321-231): 31 aircraft (registry code 3930402) - [Airbus Industrie A319-132](https://openairdocs.org/model/airbus-industrie-a319-132): 30 aircraft (registry code 3930340) - [Airbus A319-112](https://openairdocs.org/model/airbus-a319-112): 27 aircraft (registry code 3940009) - [Airbus Industrie A319-114](https://openairdocs.org/model/airbus-industrie-a319-114): 27 aircraft (registry code 3930350) - [Airbus Industrie A320-214](https://openairdocs.org/model/airbus-industrie-a320-214): 26 aircraft (registry code 3930316) - [Airbus Industrie A321-211](https://openairdocs.org/model/airbus-industrie-a321-211): 26 aircraft (registry code 3930370) - [Airbus A321-271N](https://openairdocs.org/model/airbus-a321-271n): 24 aircraft (registry code 3930910) - [Airbus A319-111](https://openairdocs.org/model/airbus-a319-111): 23 aircraft (registry code 3940000) - [Airbus A320-233](https://openairdocs.org/model/airbus-a320-233): 21 aircraft (registry code 3940329) - [Airbus A321-253N](https://openairdocs.org/model/airbus-a321-253n): 10 aircraft (registry code 3940045) - [Airbus A321-253NY](https://openairdocs.org/model/airbus-a321-253ny): 10 aircraft (registry code 3940899) - [Airbus S A S A321-253NX](https://openairdocs.org/model/airbus-s-a-s-a321-253nx): 8 aircraft (registry code 3930898) - [Airbus Industrie A320-211](https://openairdocs.org/model/airbus-industrie-a320-211): 6 aircraft (registry code 3930320) - [Airbus A319-131](https://openairdocs.org/model/airbus-a319-131): 5 aircraft (registry code 3940001) - [Airbus A321-232](https://openairdocs.org/model/airbus-a321-232): 4 aircraft (registry code 3940036) - [Airbus A320-211](https://openairdocs.org/model/airbus-a320-211): 3 aircraft (registry code 3940025) - [Airbus S A S A321-271NY](https://openairdocs.org/model/airbus-s-a-s-a321-271ny): 3 aircraft (registry code 3930917) - [Airbus A319-133](https://openairdocs.org/model/airbus-a319-133): 2 aircraft (registry code 3930351) - [Airbus A320-212](https://openairdocs.org/model/airbus-a320-212): 2 aircraft (registry code 3940010) - [Airbus A320-231](https://openairdocs.org/model/airbus-a320-231): 2 aircraft (registry code 394032A) - [Airbus Industrie A320-231](https://openairdocs.org/model/airbus-industrie-a320-231): 2 aircraft (registry code 3930325) - [Airbus S A S A320-214](https://openairdocs.org/model/airbus-s-a-s-a320-214): 2 aircraft (registry code 3940303) - [Airbus A321-212](https://openairdocs.org/model/airbus-a321-212): 1 aircraft (registry code 3940308) - [Airbus A321-252NX](https://openairdocs.org/model/airbus-a321-252nx): 1 aircraft (registry code 3940318) - [Airbus Industrie A320-111](https://openairdocs.org/model/airbus-industrie-a320-111): 1 aircraft (registry code 3930369) - [Airbus Industrie A320-233](https://openairdocs.org/model/airbus-industrie-a320-233): 1 aircraft (registry code 3930329) - [Airbus A318-111](https://openairdocs.org/model/airbus-a318-111): 0 aircraft (registry code 3940019) - [Airbus A318-112](https://openairdocs.org/model/airbus-a318-112): 0 aircraft (registry code 3940037) - [Airbus A319](https://openairdocs.org/model/airbus-a319): 0 aircraft (registry code 3930307) - [Airbus A320-216](https://openairdocs.org/model/airbus-a320-216): 0 aircraft (registry code 3940017) - [Airbus A321-100](https://openairdocs.org/model/airbus-a321-100): 0 aircraft (registry code 3940301) - [Airbus A321-131](https://openairdocs.org/model/airbus-a321-131): 0 aircraft (registry code 3940300) - [Airbus A321-251N](https://openairdocs.org/model/airbus-a321-251n): 0 aircraft (registry code 3940041) All 58: https://openairdocs.org/tcds/A28NM/aircraft.md ## STCs approved under this data sheet (554, first 50) - [STC ST03438NY](https://openairdocs.org/stc/ST03438NY): Installation of Adams Rite Lavatory Equipment. Delta Engineering Corporation - [STC ST12434AC](https://openairdocs.org/stc/ST12434AC): Replacement of the wing fuel tank access panel gasket. Aviation Devices & Electronic Components, LLC - [STC ST02714CH](https://openairdocs.org/stc/ST02714CH): Modify the aircraft interior to match standard passenger configurations. Atin OOH LLC - [STC ST12461IB](https://openairdocs.org/stc/ST12461IB): Installation of Cockpit Voice Recorder with optional RIPS Upgrade. Mid- Canada Mod Center - [STC ST00885LA](https://openairdocs.org/stc/ST00885LA): Installation of fire extinguisher cartridges as replacements for Pacific Scientific fire extinguisher cartridges in fire extinguisher bottles.. AMETEK AMERON, LLC d/b/a MASS Systems - [STC ST12464DE](https://openairdocs.org/stc/ST12464DE): Installation of ARI Aerospace replacement back seat cushion part number 139-00-618-83-EZY, bottom seat cushion part number 139-00-634-5X-EZY, and dress covers 944-00-703-02-EZY and 944-00-7XX-02-EZY (listed on page 4) onto Recaro 3510H944-( )-( ) FAA TSO-C127a / ETSO-C127a seats. ARI Aerospace, LLC - [STC ST09841DS](https://openairdocs.org/stc/ST09841DS): A321XLR Crew rest installation. United Airlines - [STC ST01432LA](https://openairdocs.org/stc/ST01432LA): Installation of Air Works Cockpit Door Surveillance Systems.. Aero Technik Inc. - [STC ST04493NY](https://openairdocs.org/stc/ST04493NY): Conversion of Passenger to Freighter configuration by installing a large Main Deck Cargo Door and Frame Shell Structure, Class "E" Cargo Compartment, Crew Entry Door and Surround Structure, Rigid Cargo Barrier, Floor reinforcements, and other associated modifications. ELBE Flugzeugwerke GmbH - [STC ST02528LA](https://openairdocs.org/stc/ST02528LA): Installation of the Thales Avionics, Inc. Data Transfer Device (DTD) or Solid State Drive (SSD) into the existing Cabin Media Loader (CML). Thales Avionics Inc. - [STC ST04498AT](https://openairdocs.org/stc/ST04498AT): Interior Reconfiguration of an Airbus A321-271NX. AIRCRAFT RECONFIG TECHNOLOGIES, LLC - [STC ST02228SE](https://openairdocs.org/stc/ST02228SE): Installation of Bin NuLook. Safran Cabin, Inc. - [STC ST12401IB](https://openairdocs.org/stc/ST12401IB): The Installation of Airbus A319/A320/A321 cockpit door e-strike improvement. Adams Rite Aerospace Inc. - [STC ST12089CH](https://openairdocs.org/stc/ST12089CH): Premium Economy Class Seat Relocation. Global Aerospace Design Corp - [STC ST04474NY](https://openairdocs.org/stc/ST04474NY): Activation of Wireless Local Area Network (WLAN) system. Jet Aviation AG - [STC ST09829DS](https://openairdocs.org/stc/ST09829DS): Cabin interiors reconfiguration on Airbus A320 fleet. United Airlines - [STC ST11269DS](https://openairdocs.org/stc/ST11269DS): Installation of cross aisle curtains, a Pre-Recorded Announcement Machine (PRAM) with associated wiring, forward windscreens, first class and main cabin seats with associated wiring, a hanging soft divider, a mid-cabin closet, a window plug, a sidewall literature pocket.. American Airlines, Inc., Maintenance and Engineering (M&E) Division - [STC ST09828DS](https://openairdocs.org/stc/ST09828DS): Cabin interiors reconfiguration on Airbus A319 fleet. United Airlines - [STC ST04254NY](https://openairdocs.org/stc/ST04254NY): Installation of Viasat Satcom Software. ALOFT AeroArchitects - [STC ST09850DS](https://openairdocs.org/stc/ST09850DS): Series Starlink to IFE & AID Interface Installation. United Airlines - [STC ST02159SE-D](https://openairdocs.org/stc/ST02159SE-D): Installation of an interior reconfiguration. B/E Aerospace, Inc. - FSI - [STC ST00197IB](https://openairdocs.org/stc/ST00197IB): Installation of the Universal Quick Access Recorder (uQAR). Flight Data Technologies Inc. - [STC ST03416NY](https://openairdocs.org/stc/ST03416NY): Installation of Intelsat Connectivity Antenna (with demod option). Delta Engineering Corporation - [STC ST02913NY](https://openairdocs.org/stc/ST02913NY): Installation of a Panasonic Avionics Corporation Global Communications Suite (GCS) and/or In-Flight Entertainment System. Delta Engineering Corporation - [STC ST04209AT](https://openairdocs.org/stc/ST04209AT): Installation of a passenger interior configuration. Aero Design Services, Inc - [STC ST01700AT-D](https://openairdocs.org/stc/ST01700AT-D): Installation of Airshow 420 System.. AIRCRAFT RECONFIG TECHNOLOGIES, LLC - [STC ST04170AT](https://openairdocs.org/stc/ST04170AT): Installation / Activation of an IFE System. AIRCRAFT RECONFIG TECHNOLOGIES, LLC - [STC ST04370AT](https://openairdocs.org/stc/ST04370AT): Cabin Interior Reconfiguration. AIRCRAFT RECONFIG TECHNOLOGIES, LLC - [STC ST04386AT](https://openairdocs.org/stc/ST04386AT): Description of Type Design Change: Interior Reconfiguration in an Airbus A320 Series Aircraft. AIRCRAFT RECONFIG TECHNOLOGIES, LLC - [STC ST04387AT](https://openairdocs.org/stc/ST04387AT): Class Divider Installation. AIRCRAFT RECONFIG TECHNOLOGIES, LLC - [STC ST04394AT](https://openairdocs.org/stc/ST04394AT): Interior Reconfiguration installation. AIRCRAFT RECONFIG TECHNOLOGIES, LLC - [STC ST12107NY](https://openairdocs.org/stc/ST12107NY): Update of Cabin Interior. Delta Engineering Corporation - [STC ST12369IB](https://openairdocs.org/stc/ST12369IB): Replacement of flight attendant seat restraints, dress covers and cushion assemblies. Avianor Inc. - [STC ST00952LA](https://openairdocs.org/stc/ST00952LA): Installation of Mass Systems fire extinguisher cartridges as replacements for Kidde fire extinguisher cartridges in fire extinguisher bottles.. AMETEK AMERON LLC d/b/a MASS Systems - [STC ST04328NY](https://openairdocs.org/stc/ST04328NY): The Manufacture and Installation of Exterior Placards, Labels and Signs is to be performed, installed. Libellule Monde Inc - [STC ST03741NY](https://openairdocs.org/stc/ST03741NY): Viasat KA SATCOM Antenna System Installation, approve configurations. ALOFT AeroArchitects - [STC ST03875NY](https://openairdocs.org/stc/ST03875NY): Installation of interior placards, signs and markings. Libellule Monde Inc. - [STC ST12325SE](https://openairdocs.org/stc/ST12325SE): Installation of the SpaceX Starlink Aero Terminal. Space Exploration Technologies Corp./Starlink Aviation - [STC ST12326SE](https://openairdocs.org/stc/ST12326SE): SpaceX Starlink Aviation System Installation and Activation. Space Exploration Technologies Corp./Starlink Aviation - [STC ST03742NY](https://openairdocs.org/stc/ST03742NY): Viasat KA Cabin Distribution System Installation. ALOFT AeroArchitects - [STC ST11288DS](https://openairdocs.org/stc/ST11288DS): Interior reconfiguration increasing passenger count from 190 to 196 passengers. VT DRB Aviation Consultants - [STC ST00142NY](https://openairdocs.org/stc/ST00142NY): Cargo floorboard installation.. American Airlines, Inc., Maintenance and Engineering (M&E) Division - [STC ST02890NY](https://openairdocs.org/stc/ST02890NY): Installation of a Panasonic Avionics Corporation Global Communications Suite Antenna. Delta Engineering Corporation - [STC ST04759NY](https://openairdocs.org/stc/ST04759NY): Installation of a single cockpit USB charger. Eirtech Aviation Services Inc. - [STC ST12289IB](https://openairdocs.org/stc/ST12289IB): Airbus STC Solutions Modification AI0315 "Install Monuments & Emergency Equipment" installs a Galley and a Stowage with associated Emergency Equipment. Airbus SAS - [STC ST02356LA](https://openairdocs.org/stc/ST02356LA): Installation of Inflight Warning Systems Fan Vibration Monitor Unit. Astronics Advanced Electronic Systems (AES) - [STC ST11268DS](https://openairdocs.org/stc/ST11268DS): Installation of a Pre-Recorded Announcement Machine (PRAM), hanging soft dividers, and sidewall mounted literature pockets. American Airlines, Inc. Maintenance and Engineering (M&E) Division - [STC ST02699LA](https://openairdocs.org/stc/ST02699LA): Installation of Vogt Aero Nickel Cadmium Battery P/N 2758-LMVA or 2758-RMVA. Vogt Aero LLC - [STC ST03189CH](https://openairdocs.org/stc/ST03189CH): Installation of an advertisement container on the bottom of a seat back tray table. Atin OOH LLC - [STC ST01739NY](https://openairdocs.org/stc/ST01739NY): Electromagnetic Compatibility Testing of Aircraft Transmitting Portable Electronic Devices (T-PEDs) as non-interference tolerance testing. Anuvu IFC Corporation All 554: https://openairdocs.org/tcds/A28NM/stcs.md --- OpenAirDocs.org is an independent research project of [Contrail Labs](https://contraillabs.com/). It is not affiliated with the FAA or the NTSB. Source documents are U.S. government works in the public domain.