TCDS A28NM

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