# TCDS A46NM: Airbus SAS - Type: Type certificate data sheet - Status: Current - Holder: Airbus SAS - Revision: 42 - Revised: June 2, 2025 - Product: Aircraft, Large Airplane - Certification basis: Part 25, Part 21 - Registered aircraft: 155, by the registry models matched to it (OpenAirDocs) - Data sheet PDF: https://openairdocs.org/files/sha256/f7/92/f7921ce6875fc2fc8c3f765a120e7938eb14ca2bde58743687b0c6913825a0ee - FAA DRS: https://drs.faa.gov/browse/excelExternalWindow/DRSDOCID112116929120250602172051.0001 - Page: https://openairdocs.org/tcds/A46NM ## Models (18) As the data sheet lists them. - A330-201 - A330-341 - A330-342 - A330-223 - A330-223F - A330-243F - A330-941 - A330-301 - A330-321 - A330-302 - A330-322 - A330-323 - A330-202 - A330-243 - A330-303 - A330-203 - A330-343 - A330-841 ## What the data sheet says From the PDF's text layer, line by line; tables lose their columns. The PDF is the record. ```text Page no. 1 2 3 4 5 6 7 8 9 10 11 12 13 14 15 16 17 18 19 20 21 22 23 24 25 26 27 28 29 30 Rev. no. 41 33 42 34 37 34 33 42 33 37 34 33 33 34 42 33 37 33 34 38 34 42 34 41 34 38 36 42 34 42 Page no. 31 32 33 34 35 36 37 38 39 40 41 42 43 44 Rev. no. 41 42 36 38 37 34 34 34 34 36 40 34 39 41 DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION A46NM Revision 42 Airbus A330-200 Series: Models: A330-201, A330-202, A330- 203, A330-223, A330-243 A330-200 Freighter Series: Models: A330-223F, A330-243F A330-300 Series: Models: A330-301, A330-302, A330- 303, A330-321, A330-322, A330-323, A330-341, A330-342, A330-343 A330-800 Series: Model: A330-841 A330-900 Series: Model: A330-941 June 2, 2025 FAA TYPE CERTIFICATE DATA SHEET NO. A46NM This data sheet which is part of Type Certificate No. A46NM prescribes conditions and limitations under which the product for which the Type Certificate was issued meets the airworthiness requirements of the US 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 SAS January 2002 I. Type A330-200 Series Transport Category Airplanes Airbus A330-201 - approved April 1, 2003 Airbus A330-202 - approved March 31, 1998 Airbus A330-203 –approved November 1, 2002 Airbus A330-223 - approved June 21, 1999 Airbus A330-243 - approved December 21, 2000 Model: Definition of Reference Airplane by Airbus Documents: A330-201 FAA A330-201 Type Design, ref. EAL 415.1338/02 Issue 1, dated November 6, 2002, for type definition A330-202 FAA A330-202 Type Design, ref. AI/EA-N 415.0531/98 Issue 3, dated May 25, 1998, for type definition and Type Certification Standard Equipment List, ref. 00G000A0102/C0S. A330-203 FAA A330-203 Type Design, ref. EAL 415.1988/01 Issue 2, dated August 5, 2002, for type definition A330-223 FAA A330-223 Type Design, ref. AI/EA-N 415.1223/98 Issue 2, dated August 20, 1998, for type definition and Type Certification Standard Equipment List, ref. 00G000A0123/C0S. A330-243 FAA A330-243 Type Design, ref. AI/EA -N 415.2406/98 Issue 1, dated December 11, 1998, for type definition and Type Certification Standard Equipment List, ref. 00G000A0143/C0S. A46NM 2 of 44 Engines Airplane Model Engine Model: Engine Type Certificate: A330-201 Two GE-CF6-80E1A2 turbojet engines FAA-Type Certificate E41NE A330-202 Two GE-CF6-80E1A4 turbojet engines FAA-Type Certificate E41NE A330-203 Two GE-CF6-80E1A3 turbojet engines FAA-Type Certificate E41NE A330-223 Two PW 4168A turbojet engines FAA-Type Certificate E36NE A330-223 Two PW 4168A-1D turbojet engines FAA-Type Certificate E36NE A330-223 Two PW 4170 turbojet engines FAA-Type Certificate E36NE A330-243 Two RR 772B-60 turbojet engines FAA-Type Certificate E39NE Note: A330-223 PW engine mixability and interchangeability configurations is covered by MOD 201487 Engine Limits Engine Limitations A330-201 CF6-80E1A2 FAA Data Sheet E41NE A330-202 CF6-80E1A4 FAA Data Sheet E41NE A330-203 CF6-80E1A3 FAA Data Sheet E41NE Static Thrust at Sea Level • Take-off (5 mn)1 (flat rated 30ºC) • Max continuous (flat rated 25ºC) 64,530 lbs 60,400 lbs 66,870 lbs 60,400 lbs 68, 530 lbs 60,400 lbs Maximum Engine Speed • N1 rpm (%) • N2 rpm (%) 3,835 (115.5%) 11,105 (113%) 3,835 (115.5%) 11,105 (113%) 3,835 (115.5%) 11,105 (113%) Maximum Gas Temperature • Take-off (5mn)1 • Maximum Continuous • Starting2 1,787º F (975º C) 1,724º F (940º C) 1,598º F (870º C) 1,787º F (975º C) 1,724º F (940º C) 1,598º F (870º C) 1,787º F (975º C) 1,724º F (940º C) 1,598º F (870º C) Maximum Oil Temperature (Supply Pump Outlet) ºC • Continuous Operation • Transient (15 mn max.) • Minimum Oil Pressure (PSI) 320º F (160º C) 347º F (175º C) 10.0 psid (69 Kpa) 320º F (160º C) 347º F (175º C) 10.0 psid (69 Kpa) 320º F (160º C) 347º F (175º C) 10.0 psid (69 KPa) Approved oils Brand Names: See GE Service Bulletin 79-001 Specification: See GE specification D50TF1, Class B Engine Limitations A330-223 PW 4168A / PW 4168A-1D FAA Data Sheet E36NE A330-223 PW 4170 FAA Data Sheet E36NE A330-243 RR 772B-60 FAA Data Sheet E39NE Static Thrust at Sea Level • Take-off (5 mn)1 (flat rated 30º C) • Max continuous (flat rated 25º C) 68,600 lbs 59,357 lbs 70,000 lbs 59,357 lbs 71,100 lbs 63,560 lbs Maximum Engine Speed • N1 rpm (%) • N2 rpm (%) 3,600 10,450 3,680 10,450 3,861 (99%) 10,611 (100%) Maximum Gas Temperature • Take-off (5mn)1 • Maximum Continuous • Starting2 1,148º F (620º C) 1,112º F (600º C) 1,148º F (620º C) 1,148º F (620º C) 1,112º F (600º C) 1,148º F (620º C) 1,652º F (900º C) 1,562º F (850º C) 1,562º F (850º C) Maximum Oil Temperature (Supply Pump Outlet) ºC • Continuous Operation • Transient (15 mn max.) • Minimum Oil Pressure (PSI) 325º F (163º C) 350º F (177º C) 70.0 psid (482.6 KPa ) 325º F (163º C) 350º F (177º C) 70.0 psid (482.6 KPa ) 374º F (190º C) 374º F (190º C) 24.0 psid Approved oils Oils conforming to P&W Turbojet engine Service Bulletin 238, latest revision Refer to the Engine Operating Instructions for A330/A340 for information on approved oil specifications for Trent700 Table references: (1) 10 minutes at take-off thrust allowed only in case of engine failure (at take-off or during go around). (2) 4 consecutive cycles of 2 minutes each. A46NM 3 of 44 Maximum Weight A330-201: • Maximum Take-Off Weight (MTOW): 238,000 kg / 524,700 lb • Maximum Landing Weight (MLW): 182,000 kg / 401,241 lb • Maximum Zero Fuel Weight (MZFW): 170,000 kg / 374,785 lb All A330-2xx models except A330-201 • Maximum Take-Off Weight (MTOW): 242,000 kg / 533,518 lb • Maximum Landing Weight (MLW): 182,000 kg / 401,241 lb • Maximum Zero Fuel Weight (MZFW): 170,000 kg / 374,785 lb Note: See applicable Airplane Flight Manual (AFM), as listed in ‘Operating and Service Instructions’, for configuration specific weight limitations and aircraft eligibility (Weight Variant). Number of Seats The maximum number of passengers approved for emergency evacuation is: - 375 passengers with a 3 pairs of Type A and 1 pair Type 1 exits configuration, and - 406 passengers with a 4 pairs of Type A exits configuration. Maximum Baggage Cargo Compartment Maximum Load (kg / lb) Forward 18,869 / 41,599 Aft 15,241 / 33,600 Rear 3,468 / 7,646 For the positions and the loading conditions authorized in each position (references of containers, pallets and associated weight) see weight and Balance Manual: - A330-200 Airbus Document ref. 00G080A0006/C2S Fuel Capacity 3 Tank Airplane Usable Fuel Unusable Fuel (without MOD 205749) (with MOD 205749) Tank liters (kg) gallons (lb) liters (kg) gallons (lb) liters (kg) gallons (lb) Wing 91,300 (73,040) 24,119 (161,026) 348 (279) 92 (615) 190 (152) 50 (335) Center 41,560 (33,248) 10,980 (73,311) 83 (67) 22 (148) 83 (67) 22 (148) Trim Tank 6,230 (4,984) 1,646 (10,988) 6 (5) 1.6 (11) 6 (5) 1.6 (11) Total 139,090 (111,272) 36,744 (245,313) 437 (351) 116 (774) 279 (224) 74 (494) A46NM 4 of 44 Certification Basis (A330-200) a. 14CFR part 25 effective February 1, 1965, including the following: • Amendments 25-1 through 25-63, Amendments 25-65, 25-66, 25-68, 25-69, 25-73, 25-75, 25-77, 25-78, 25-81, 25-82, 25- 84 and 25-85 • Amendment 25-72 for the following 14 CFR part 25 sections: 25.21, 25.29, 25.111, 25.147, 25.177, 25.181, 25.205, 25.307, 25.331, 25.341, 25.343, 25.345, 25.351, 25.361, 25.373, 25.395, 25.397, 25.415, 25.459, 25.571 (b), 25.613 (Vertical stabilizer only), 25.615 (Vertical stabilizer only), 25.693, 25.723, 25.729, 25.731, 25.733, 25.735, 25.772, 25.779, 25.783, 25.791, 25.933, 25.979, 25.1093, 25.1381, 25.1419, 25.1522, 25.1533, 25.1543, 25.1551, 25.1581, 25.1583, 25.1587 • Amendment 25-74 for § 25.851 b. 14 CFR part 25 Amendment 25-64 with the following exceptions: • Cockpit seats will not meet § 25.562 Amendment 25-64 but will meet § 25.561 • Compliance with § 25.785(a), at Amendment 25-64 for front row seats directly behind a bulkhead will be based on ensuring a 35inch free head strike envelope. c. 14 CFR part 34, effective September 10, 1990, including Amendment 34-1. d. 14 CFR part 36, effective December 1, 1969, including Amendments 36-1 through 36-21. e Special conditions in accordance with § 21.16. 1. Special Conditions No. 25 -ANM-77 published in the Federal Register on October 19, 1993, (Docket No. NM 86, Special Conditions No. 25-ANM-77) (Special conditions originally written for the A330-300 certification basis that are also included in the A330-200 certification basis): (1) Operation without Normal Electrical Power (8) Limit Pilot Forces (2) Electronic Flight Control System (EFCS) failures and Mode Annunciation (9) Tail plane Tank Emergency Landing Loads (3) Command Signal Integrity (10) Limit Engine Torque (4) Protection From Lightning and Unwanted Effects of High Intensity Radiated Fields (HIRF) (11) Flight Characteristics (5) Interaction of Systems and Structures (12) Flight Envelope Protection (6) Design Dive Speed (13) Side Stick Controllers (7) Design Maneuver Requirements (14) Computerized Airplane Flight Manual (AFM) Performance Information 2. Special Condition 25-281-SC published in the Federal Register on January 6, 2005 (Docket No. NM287): Lower Deck Mobile Crew Rest (LD-MCR) Compartment – Optional modification # 206615. 3. Special Condition 25-395-SC published in the Federal Register November 03, 2009 (Docket No. NM-418): Seats With Inflatable Lap Belts. 4. Special Condition 25-400 -SC published in the Federal Register January 4, 2010 (Docket No. NM-424): Seats with Non-Traditional, Large, Non-Metallic Panels. 5. Special Condition 25-678-SC published in the Federal Register May 26, 2017 (Docket No. FAA-2017-0369): Non-Rechargeable Lithium Batteries This Special condition is effective to design changes applied for after May 26, 2017. See the applicability section of this special condition for more information on which design changes must meet it. 6. Special Condition 25-739-SC published in the Federal Register on December 26, 2018 (Docket No. FAA–2018–1053): Electronic System Security Protection from Unauthorized External Access. This Special Condition apply to installation and activation of electronic network system architecture or Flight Operations and Maintenance Exchanger (FOMAX) equipment (Airbus modification # 207456). 7. Special Condition 25-740-SC published in the Federal Register on December 26, 2018 (Docket No. FAA–2018–1054): Electronic System Security Protection from Unauthorized Internal Access. This Special Condition apply to installation and activation of electronic network system architecture or Flight Operations and Maintenance Exchanger (FOMAX) equipment (Airbus modification # 207456). A46NM 5 of 44 f. The technical requirements are complemented by the following guidance material: For precision approach and landing, 1. AC 120-29 2. AC 120-28C and for the automatic flight control system 1. AC 20-57A for automatic landing 2. AC 25.1329-1A for cruise g. Equivalent safety findings (ELOS) have been made in accordance with § 21.21(b)(1) for the following sections: (1) § 25.335(d) for design airspeeds* (2) § 25.341 for gust loads* (3) § 25.345 for high lift devices* (4) § 25.349 for control surface loads* (5) § 25.351(b) for unsymmetrical loads* (6) § 25.371 for gyroscopic loads* (7) § 25.373 for speed control devices* (8) § 25.391 for control surface loads * *These ELOS findings do not apply where the corresponding requirements of Amendment 25-141 are applied. (9) §§ 25.101(I); 25.105(c)(1); 25.109(a)(b)(c)(d)(e)(f); 25.113(a)(b)(c); 25.115(a); 25.735(f)(g)(h)(b) for rejected takeoff and landing performance (10) §§ 25.933(a)(1)(ii), 25.1309(b)(1) for flight critical thrust reverser (11) § 25.1203(d) for turbine overheat detection (RR Trent 700 powered A330-243 only) (12) § 25.1305(c)(6) Warning means for engine fuel filter contamination (RR Trent 700 powered A330-243 only) (13) §§ 25.1305; 25.1501(b) for APU system flight deck instrumentation (14) § 25.856(b), Improved Flammability standards for Thermal/acoustic insulation materials (documented in ELOS Memo TD0609IB-T-CI-5; Memo TD0609IB-T-CI-6 and Memo TD0609IB-T-CI-7). (15) § 25.785(d), Forward Facing Seat, over 18 degrees to aircraft centerline (documented in ELOS Memo TD0643IB-T-CI-9). (16) § 25.1457(d)(5) Cockpit Voice Recorder – Equivalent Level of Safety for 10 minute independent backup power requirement (documented in ELOS Memo TD0774IB-T-SA-1). (17) §§ 26.33, 26.35 Fuel Center Tank Flammability Reduction System (documented in ELOS Memo TD0547IB-T-P-1 (18) § 25.981(a)(3) Amendment. 25-102 Installation of Fuel Pump Ground Fault Interrupter (GFI) Devices (documented in ELOS Memo TD0764IB-T-P-1) (19) § 25.1443(c) Minimum mass flow of supplemental oxygen on model A330 and A340 airplanes (documented in ELOS Memo AT10356IB-T-S-1) (20) § 25.1441(c) Crew determination of quantity of oxygen in passenger oxygen system on model A330 and A340 airplanes (documented in ELOS Memo AT10356IB-T-S-2) (21) §§ 25.811(g); 25.812(b)(1) Symbolic Exit Signs on Models A330 and A340 airplanes (documented in ELOS Memo TD00918IB-T-CS-1). For airplanes equipped with pictograms on exit marking signs and on exit location signs, the cabin crew in charge of the safety briefing should highlight these pictograms to the passengers prior to each takeoff and each landing. (22) § 25.811(e)(4) Emergency Exit Marking on model A330 and A340 airplanes (documented in ELOS Memo AT10899IB-T- CS-1) for airplanes with Airbus modification # 206893. h. Optional requirements elected: • § 25.801 for ditching. • § 25.1419 for icing. i. Exemptions: • Exemption No. 17129 dated October 26, 2016. This Exemption from 14 CFR 25.98 l(a)(3) is granted to Airbus as it relates to the Model A330-200 fuel trim tank structural lightning protection (Airbus modification # 204495 “Stabilizers – Horizontal Stabilizer – Define lateral box for weight reduction”). • Exemption No. 17601, dated October 13, 2017. This exemption is granted for the requirements of 14 CFR part 25, appendix K, section K25.1.4(a)(2) as they relate to concurrent power of the fuel boost pumps in each main fuel tank and will allow to show that t he airplanes are capable of continuously providing fuel pressure to all engines when only powered by an A46NM 6 of 44 independent electrical power source other than the three power sources required in section K25.1.3(b) of appendix K, without maintaining simultaneous power to all individual fuel boost pumps. This exemption relates to Model A330 series airplanes ETOPS beyond 180 minutes approval. The Direction Generale de l'Aviation Civile (DGAC) of France originally type certificated the Airbus Model A330-200 series airplanes under its type certificate number DGAC -F TC 184. The FAA validated this product under U.S. Type Certificate Number A46NM. Effective September 28, 2003, the European Union Aviation Safety Agency (EASA) began oversight of this product on behalf of DGAC. Part 26 – Continued Airworthiness and Safety Improvements for Transport Category Airplanes: Based on § 21.29(a) for new import TCs, or § 21.101(g) for changes to TCs, applicable provisions of part 26 are included in t he certification basis. For any future part 26 amendments, the holder of this TC must demonstrate compliance with the applicable sections. FAA Required Modification List Compliance with the FAA Required Modification List for Airbus Model A330-200 Aircraft as included under the Import Requirements section of TCDS Revision 4, dated March 21, 2000 or later TCDS revision is necessary for an A330-200 aircraft to be found in a condition for safe operation. The FAA has accepted: • Model A330-223 aircraft in the Airbus as-delivered configuration for MSN 343 and from MSN 609 and on as compliant with the applicable modifications of the A330 RML. FAA acceptance is based on the Airbus statement to the FAA (ref. Airbus letters EAL G03D0415493, dated July 9, 2004 , and G01ME1249802 Issue 2, dated July 26, 2012) that the RML modifications applicable to model A330-223 aircraft are either part of the FAA approved type design (ref. AI/EA -N 415.1223/98 Issue 2, dated August 20, 1998), required t o be installed at aircraft delivery by DGAC/EASA AD, or required to be installed by Airbus on all A330 -223 aircraft at time of delivery. • Model A330-202 aircraft in the Airbus as -delivered configuration (except for MSN’s 205, 211, 269 and 272) as compliant with the applicable modifications of the A330 RML. FAA acceptance is based on the Airbus statement to the FAA (ref. Airbus letter EAL LR01M08013880, dated June 20, 2008) that the RML modifications applicable to model A330-202 aircraft are either part of the FAA approved type design (ref. AI/EA-N 415.0531/98 Issue 3, dated May 25, 1998), required to be installed at aircraft delivery by DGAC/EASA AD, or required to be installed by Airbus on all A330-202 aircraft at time of delivery. • Model A330-243 aircraft in the Airbus as-delivered configuration (except for MSN’s 248, 250, 251, 254, 261, 265, 271 and 276) as compliant with the applicable modifications of the A330 RML. FAA acceptance is based on the Airbus statement to the FAA (ref. Airbus letter EAL LR01M0819406, dated August 07, 2008) that the RML modifications applicable to model A330-243 aircraft are either part of the FAA approved type design (ref. AI/EA -N 415.2406/98 Issue 1, dated December 11, 1998), required to be installed at aircraft delivery by DGAC/EASA AD, or required to be installed by Airbus on all A330-243 aircraft at time of delivery. Equipment • The basic required equipment as prescribed in the applicable airworthiness regulations (see Certification Basis) must be installed in the aircraft for certification. • The following Airbus Documents defines the set of modifications which comprise the FAA certificated type design. These documents contain certain modifications determined necessary for FAA certification, including installation of ozone converters, fuel system improvements and thrust reverser modifications. - A330-201: EAL 415.1338/02 Issue 1, dated November 6, 2002 - A330-202: AI/EA-N 415.0531/98 Issue 3, dated May 25, 1998 - A330-203: AI/EAL 415.1988/01 Issue 2, dated August 5, 2001 - A330-223: AI/EA-N 415.1223/98 Issue 2, dated August 20, 1998 - A330-243: AI/EA-N 415.2406/98 Issue 1, dated December 11, 1998 • Equipment approved for installation is listed in the Certification Standard Equipment List - A330-202: 00G000A0102/C0S - A330-223: 00G000A0123/C0S - A330-243: 00G000A0143/C0S • Cabin furnishings, equipment and arrangement shall conform to the following specification: - 00F252K0005/C01 for cabin seats, - 00F252K0006/C01 for galley, - 00F252K0020/C01 for cabin attendant seat A46NM 7 of 44 Airplane Flight Manual Airplane operation must be in accordance with the EASA Approved Airplane Flight Manual (AFM), US version, listed below, or la ter EASA approved revision applicable to the specific airplane model, modification status and serial number. Model A330-200 Airbus Document Reference Revision No. Date -201 STL 33000 1 March 10, 2003 -202 AI/ST-F 33000 2 January 6, 1999 -203 AI/ST-F 33000 1 October 24, 2002 -223 AI/ST-F 33000 2 January 6, 1999 -243 AI/ST-F 33000 2 March 15, 2000 Data Pertinent to All Model See Section VI, Data Pertinent to All Model A330-200, A330-200 Freighter, A330-300, A330-800 and A330-900 Series airplanes. For information on Fuel, Airspeed Limits, Center of Gravity Limits, Datum, Leveling Means, Minimum Crew, Maximum Operating Altitude, Control Surface Movements, Production Basis , Hydraulic Fluids, Auxiliary Power Unit (APU), Tires, Environmental requirements for noise, Manufacturer’s Serial Numbers, Service Information, information on Import Requirements and General Notes A46NM 8 of 44 II. Type A330-200 Freighter Series Transport Category Airplanes: Airbus A330-223F - approved August 12, 2010 Airbus A330-243F - approved August 12, 2010 Model: Definition of Reference Airplane by Airbus Documents: A330-223F FAA A330-223F Type Design, ref. AI/EA-LR01D10010034 Issue 3, dated August 03, 2010, for type definition. A330-243F FAA A330-243F Type Design, ref. AI/EA-LR01D10010035 Issue 3, dated August 03, 2010, for type definition. Engines Airplane Model Engine Model: Engine Type Certificate: A330-223F Two PW 4170 turbojet engines Two PW 4168A-1D turbojet engines (MOD # 58344 Issue 3) FAA-Type Certificate E36NE A330-243F Two RR 772B-60 turbojet engines FAA-Type Certificate E39NE Engine Limits Engine Limitations A330-223F PW 4170 FAA Data Sheet E36NE A330-223F PW 4168A-1D FAA Data Sheet E36NE A330-243F RR 772B-60 FAA Data Sheet E39NE Static Thrust at Sea Level • Take-off (5 mn)1 (flat rated 30ºC) • Max continuous (flat rated 25ºC) 70,000 lbs 59,357 lbs 68,600 lbs 59,357 lbs 71,100 lbs 63,560 lbs Maximum Engine Speed • N1 rpm (%) • N2 rpm (%) 3,680 10,450 3,600 10450 3,861 (99%) 10,611 (100%) Maximum Gas Temperature • Take-off (5mn)1 • Maximum Continuous • Starting2 1,148º F (620º C) 1,112º F (600º C) 1,148º F (620º C) 1,148º F (620º C) 1,112º F (600º C) 1,148º F (620º C) 1,652º F (900º C) 1,562º F (850º C) 1,562º F (850º C) Maximum Oil Temperature (Supply Pump Outlet) ºC • Continuous Operation • Transient (15 mn max.) • Minimum Oil Pressure (PSI) 325º F (163º C) 350º F (177º C) 70.0 psid (482.6 KPa ) 325º F (163º C) 350º F (177º C) 70.0 psid (482.6 KPa ) 374º F (190º C) 374º F (190º C) 24.0 psid Approved oils Oils conforming to P&W Turbojet engine Service Bulletin 238, latest revision. Refer to the Engine Operating Instructions for A330/A340 for information on approved oil specifications for Trent700 Table references: (1) 10 minutes at take-off thrust allowed only in case of engine failure (at take-off or during go around). (2) 4 consecutive cycles of 2 minutes each. Maximum Weight • Maximum Take-Off Weight (MTOW): 233,000 kg / 513,677 lb • Maximum Landing Weight (MLW): 187,000 kg / 412,264 lb • Maximum Zero Fuel Weight (MZFW): 178,000 kg / 392,422 lb Note: See applicable Airplane Flight Manual (AFM), as listed in ‘Operating and Service Instructions’, for configuration specific weight limitations and aircraft eligibility (Weight Variant). Number of Seats A maximum of 12 supernumeraries may occupy the courier area located aft of the flight deck compartment. The total occupancy of the airplane is limited to 16 persons including flight crew. A46NM 9 of 44 Maximum Baggage Cargo Compartment Maximum Load (kg / lb) Forward 18,869 / 41,606 Aft 15,241 / 33,606 Rear 3,468 / 7,646 MDC Compartment 64,000 / 141,119 (range mode) For the positions and the loading conditions authorized in each position (references of containers, pallets and associated weight) see weight and Balance Manual: A330-200F Airbus Document ref. 00G080A0006/C2S Fuel Capacity 3 Tank Airplane Usable Fuel Unusable Fuel (without MOD 205749) (with MOD 205749) Tank liters (kg) gallons (lb) liters (kg) gallons (lb) liters (kg) gallons (lb) Wing 91,300 (73,040) 24,119 (161,026) 348 (279) 92 (615) 190 (152) 50 (335) Center 41,560 (33,248) 10,980 (73,311) 83 (67) 22 (148) 83 (67) 22 (148) Trim Tank 6,230 (4,984) 1,646 (10,988) 6 (5) 1.6 (11) 6 (5) 1.6 (11) Total 139,090 (111,272) 36,746 (245,313) 437 (351) 116 (774) 279 (224) 74 (494) Certification Basis (A330-200 Freighter) a. 14 CFR part 25 effective February 1, 1965, including the following: • Amendments 25-1 through 25-63, Amendments 25-65, 25-66, 25-68, 25-69, 25-73, 25-75, 25-77, 25-78, 25-81, 25-82, 25- 84, 25-85, 25-99 and 25-105 • Amendment 25-72 for the following 14 CFR part 25 sections: § 25.21, 25.29, 25.111, 25.147, 25.177, 25.181, 25.205, 25.307, 25.361, 25.373, 25.395, 25.397, 25.415, 25.459, 25.571 (b), 25.613 (Vertical stabilizer only), 25.615 (Vertical stabilizer only), 25.625 (Courier area), 25.693, 25.723, 25.729, 25.731, 25.733, 25.735, 25.772, 25.779, 25.783, 25.791 (Courier area), 25.803 (Courier area), 25.810 (Courier area), 25.933, 25.979, 25.1093, 25.1381, 25.1419, 25.1522, 25.1533, 25.1543, 25.1551, 25.1581, 25.1583, 25.1587 • Amendment 25-74 for § 25-851 for Main Deck Cargo Compartment and courier area • Amendment 25-80 for § 25.1316 for Main Deck Cargo Compartment, Main Deck Cargo Door • Amendment 25-86 for §§ 25.305, 25.321, 25.331, 25.333, 25.335, 25.341, 25.343, 25.345, 25.349, 25.351, 25.371, 25.373, 25.391, 25.427 • Amendment 25-88 for §§ 25.783, 25.785, 25.811 for courier area • Amendment 25-91 for § 25.561 for barrier wall, supernumerary seats and attachments • Amendment 25-93 for §§ 25.857, 25.858 for the Main Deck Cargo Compartment • Amendment 25-111 for § 25.856(a) • Amendment 25.112 for § 25.613 for Main Deck Cargo Door, barrier wall, Main Deck Cargo Compartment • Amendment 25.113 for §§ 25.869, 25.1353, 25.1431 for Main Deck Cargo Compartment, Courier area • Amendment 25-114 for § 25.783 for Main Deck Cargo Door • Amendment 25-114 for §§ 25.807, 25.809, 25.820 for Courier area • Amendment 25-115 for § 25.1439 for courier area • Amendment 25-116 for §§ 25.853, 25.855 for Main Deck Cargo Compartment • Amendment 25-116 for §§ 25.812, 25.813, 25.853, 25.1411, 25.1447 for Courier area • Amendment 25-122 for § 25.1317 A46NM 10 of 44 Note: The class E cargo compartment on the A330 -200F is required to ensure protection of critical systems and equipment from the fire itself and from the residual heat after the airplane has been depressurized (see FAA Advisory Circular (AC) 25 -9a). The following design details must be maintained to ensure that at an unsafe design feature is not present: Critical systems located in the main deck Class E cargo compartment must be protected from cargo fires occurring therein and the associated effects. Critical systems include, but are not limited to, flight controls, critical wiring, and windows (if loss of a window could contribute to loss of suppression capability). The flight data recorder and the cockpit voice recorder should also be protected for subsequent investigative purposes if they are installed in the affected cargo compartment. If protective covers are used, they must be constructed of materials that meet the flame penetration resistance requirements of 14 CFR part 25, Appendix F, part III at Amendment 25-60. b. 14 CFR part 25 Amendment 25-64 with the following exceptions: • Cockpit seats will not meet § 25.562 Amendment 25-64 but will meet § 25.561 • Compliance with § 25.785(a), at Amendment 25-64 for front row seats directly behind a bulkhead will be based on ensuring a 35inch free head strike envelope. c. 14 CFR part 34, effective September 10, 1990, including Amendment 34-1. d. 14 CFR part 36, effective December 1, 1969, including Amendments 36-1 through 36-28. e Special conditions in accordance with § 21.16. 1. The following special conditions published in the Federal Register April 15, 1993, (Docket No. NM -75, Special Conditions No. 25-ANM-69) are part of the original A330-200 certification basis and remain applicable to A330-200F: (1) Operation without Normal Electrical Power (8) Limit Pilot Forces (2) Electronic Flight Control System (EFCS) failures and Mode Annunciation (9) Tail plane Tank Emergency Landing Loads (3) Command Signal Integrity (10) Limit Engine Torque (4) Protection From Lightning and Unwanted Effects of High Intensity Radiated Fields (HIRF) (11) Flight Characteristics (5) Interaction of Systems and Structures (12) Flight Envelope Protection (6) Design Dive Speed (13) Side Stick Controllers (7) Design Maneuver Requirements (14) Computerized Airplane Flight Manual (AFM) Performance Information 2. Special Condition 25-678-SC published in the Federal Register May 26, 2017 (Docket No. FAA-2017-0369): Non-Rechargeable Lithium Batteries This Special condition is effective to design changes applied for after May 26, 2017. See the applicability section of this special condition for more information on which design changes must meet it. 3. Special Condition 25-739-SC published in the Federal Register on December 26, 2018 (Docket No. FAA–2018–1053): Electronic System Security Protection from Unauthorized External Access. This Special Condition apply to installation and activation of electronic network system architecture or Flight Operations and Maintenance Exchanger (FOMAX) equipment (Airbus modification # 207456). 4. Special Condition 25-740-SC published in the Federal Register on December 26, 2018 (Docket No. FAA–2018–1054): Electronic System Security Protection from Unauthorized Internal Access. This Special Condition apply to installation and activation of electronic network system architecture or Flight Operations and Maintenance Exchanger (FOMAX) equipment (Airbus modification # 207456). f. The technical requirements are complemented by the following guidance material: For precision approach and landing, 1. AC 120-29 2. AC 120-28C and for the automatic flight control system 2. AC 25.1329-1A for cruise g. Equivalent safety findings: The following Equivalent safety findings (ELOS) are part of the original A330-200 certification basis and remain applicable to the A330-200F: A46NM 11 of 44 (1) §§ 25.101(i); 25.105(c)(1); 25.109(a)(b)(c)(d)(e)(f); 25.113(a)(b)(c); 25.115(a); 25.735(f)(g)(h)(b) for rejected takeoff and landing performance (2) §§ 25.933(a)(1)(ii), 25.1309(b)(1) for flight critical thrust reverser (3) § 25.1203(d) for turbine overheat detection (RR Trent 700 powered A330-243F only) (4) § 25.1305(c)(6) Warning means for engine fuel filter contamination (RR Trent 700 powered A330-243F only) (5) §§ 25.1305; 25.1501(b) for APU system flight deck instrumentation (6) § 25.981(a)(3) Amendment. 25-102 Installation of Fuel Pump Ground Fault Interrupter (GFI) Devices (documented in ELOS Memo TD0764IB-T-P-1) (7) § 25.1457(d)(5) Cockpit Voice Recorder – Equivalent Level of Safety for 10 minute independent backup power requirement (documented in ELOS Memo TD0774IB-T-SA-1) (8) § 25.1443(c) Minimum mass flow of supplemental oxygen on model A330 and A340 airplanes (documented in ELOS Memo AT10356IB-T-S-1) (9) § 25.1441(c) Crew determination of quantity of oxygen in passenger oxygen system on model A330 and A340 airplanes (documented in ELOS Memo AT10356IB-T-S-2) h. Optional requirements elected: • § 25.801 for ditching. • § 25.1419 for icing. i. Exemptions: • Exemption No. 9894 corrected (partial), dated July 01, 2009. As related to §§ 25.785(j), 25.813(b), 25.857(e) and 25.1447(c)(1). This exemption was granted to the extent necessary to allow carriage of supernumeraries, but limits the supernumeraries' Class E cargo compartment access to specific types of operation. The total occupancy of the airplane is limited to sixteen persons, including the flight crew (two on -duty flight crew members, and up to fourteen off -duty flight crew members, observers or supernumeraries). • Exemption No. 17129 dated October 26, 2016. This Exemption from 14 CFR 25.98 l(a)(3) is granted to Airbus as it relates to the Model A330-200 fuel trim tank structural lightning protection (Airbus modification # 204495 “Stabilizers – Horizontal Stabilizer – Define lateral box for weight reduction”). j. 14 CFR part 26 effective December 10, 2007, including Amendment 26-1. Part 26 – Continued Airworthiness and Safety Improvements for Transport Category Airplanes: Based on § 21.29(a) for new import TCs, or § 21.101(g) for changes to TCs, applicable provisions of part 26 are included in t he certification basis. For any future part 26 amendments, the holder of this TC must demonstrate compliance with the applicable sections. FAA Required Modification List Compliance with the FAA Required Modification List for Airbus Model A330-200 Aircraft as included under the Import Requirements section of TCDS Revision 4, dated March 21, 2000 or later TCDS revision is necessary for an A330-200 aircraft to be found in a condition for safe operation. The FAA has accepted: • Models A330-223F and A330-243F aircraft in the Airbus as-delivered configuration as compliant with the applicable modifications of the A330 RML. FAA acceptance is based on the Airbus statement to the FAA (ref. Airbus letter EIA _LR02M13000541 issue 2, dated January 09, 2013 for A330 -223F and EIA_LR02M12055271, dated December 11, 2012 for A330 -243F) that the RML modifications applicable to models A330 -223F and A330 -243F aircraft are part of the FAA approved type design (ref. EIA_LR01D10010034 issue 3, dated August 03, 2010 for A330-223F and EIA_LR01D10010035 issue 3, dated August 03, 2010 for A330-243F). Equipment • The basic required equipment as prescribed in the applicable airworthiness regulations (see Certification Basis) must be inst alled in the aircraft for certification. • Cabin furnishings, equipment and arrangement shall conform to the following specification: - 00F252K0005/C01 for cabin seats, - 00F252K0006/C01 for galley, - 00F252K0020/C01 for cabin attendant seat A46NM 12 of 44 Airplane Flight Manual Airplane operation must be in accordance with the EASA Approved Airplane Flight Manual (AFM), US version, listed below, or la ter EASA approved revision applicable to the specific airplane model, modification status and serial number. Model A330-200F Airbus Document Reference Revision No. Date -223F STL 33000 1 April 08, 2010 -243F STL 33000 1 April 08, 2010 Data Pertinent to All Model See Section VI, Data Pertinent to All Model A330-200, A330-200 Freighter, A330-300, A330-800 and A330-900 Series airplanes. For information on Fuel, Airspeed Limits, Center of Gravity Limits, Datum, Leveling Means, Minimum Crew, Maximum Operating Altitude, Control Surf ace Movements, Production Basis , Hydraulic Fluids, Auxiliary Power Unit (APU), Tires, Environmental requirements for noise, Manufacturer’s Serial Numbers, Service Information, information on Import Requirements and General Notes A46NM 13 of 44 III. Airbus A330-300 Series Transport Category Airplanes Airbus A330-301 - approved October 21, 1993 Airbus A330-323 - approved October 8, 1999 Airbus A330-302 - approved November 13, 2007 Airbus A330-341 – approved December 21, 2000 Airbus A330-303 - approved November 13, 2007 Airbus A330-342 - approved December 21, 2000 Airbus A330-321 - approved June 21, 1999 Airbus A330-343 - approved December 21, 2000 Airbus A330-322 - approved June 21, 1999 Model: Definition of Reference Airplane by Airbus Documents: A330-301 FAA A330-301 Type Design, ref. AI/EA-N 415.1181/96 Issue 3, dated July 16, 1997 for type definition and Type Certification Standard Equipment list, ref. 00G000A0101/C0S. A330-321 FAA A330-321 Type Design, ref. AI/EA-N 415.1184/96 Issue 3, dated June 25, 1998 for type definition and Type Certification Standard Equipment list, ref. 00G000A0121/C0S. A330-302 FAA A330-302 Type Design, ref. EAL M05000400 Issue 03 dated May 2006 for type definition A330-303 FAA A330-303 Type Design, ref. EAL M05000401 Issue 03 dated May 2006 for type definition A330-322 FAA A330-322 Type Design, ref. AI/EA-N 415.1183/99 Issue 3, dated June 25, 1998 for type definition and Type Certification Standard Equipment list, ref. 00G000A0121/C0S. A330-323 FAA A330-323 Type Design, ref. AI/EA-N 415.1630/99 Issue 1, dated July 20, 1999 for type definition and Type Certification Standard Equipment list, ref. 00G000A0123/C3S. A330-341 FAA A330-341 Type Design, ref. AI/EA-N 415.1187/96 Issue 2, dated December 11, 1998 for type definition and Type Certification Standard Equipment list, ref. 00G000A0141/C0S. A330-342 FAA A330-341 Type Design, ref. AI/EA-N 415.1182/96 Issue 2, dated December 11, 1998 for type definition and Type Certification Standard Equipment list, ref. 00G000A0141/C0S. A330-343 FAA A330-343 Type Design, ref. AI/EA-N 415.2027/99 Issue 1, dated October 22, 1999 for type definition and Type Certification Standard Equipment list, ref. 00G000A0143/C3S. Engines Airplane Model: Engine Model: Engine Type Certificate: A330-301 Two GE-CF6-80E1A2 turbojet engines FAA-Type Certificate E41NE A330-321 Two PW 4164 turbojet engines FAA-Type Certificate E36NE A330-321 Two PW4164-1D turbojet engines FAA Type Certificate E36NE A330-302 Two GE-CF6-80E1A4 turbojet engines FAA-Type Certificate E41NE A330-303 Two GE-CF6-80E1A3 turbojet engines FAA-Type Certificate E41NE A330-322 Two PW 4168 turbojet engines FAA-Type Certificate E36NE A330-322 Two PW 4168-1D turbojet engines FAA Type Certificate E36NE A330-323 Two PW 4168A turbojet engines FAA-Type Certificate E36NE A330-323 Two PW 4168A-1D turbojet engines FAA-Type Certificate E36NE A330-323 Two PW 4170 turbojet engines FAA-Type Certificate E36NE A330-341 Two RR Trent 768-60 turbojet engines FAA-Type Certificate E39NE A330-342 Two RR Trent 772-60 turbojet engines FAA-Type Certificate E39NE A330-343 Two RR Trent 772B-60 turbojet engines FAA-Type Certificate E39NE Note: A330-321/-322/-323 PW engine Mixability and interchangeability configurations are covered by MOD 201487 Engine Limits Engine Limitations A330-301 CF6-80E1A2 FAA Data Sheet E41NE A330-302 CF6-80E1A4 FAA Data Sheet E41NE A330-303 CF6-80E1A3 FAA Data Sheet E41NE Static Thrust at Sea Level • Take-off (5 mn)1 (flat rated 30ºC) • Max continuous (flat rated 25ºC) 64,530 lbs 60,400 lbs 66,870 lbs 60,400 lbs 68,530 lbs 60,400 lbs Maximum Engine Speed • N1 rpm (%) • N2 rpm (%) 3,835 (115.5%) 11,105 (113%) 3,835 (115.5%) 11,105 (113%) 3,835 (115.5%) 11,105 (113%) Maximum Gas Temperature • Take-off (5mn)1 • Maximum Continuous • Starting2 1,787º F (975º C) 1,724º F (940º C) 1,598º F (870º C) 1,787º F (975º C) 1,724º F (940º C) 1,598º F (870º C) 1,787º F (975º C) 1,724º F (940º C) 1,598º F (870º C) A46NM 14 of 44 Engine Limitations A330-301 CF6-80E1A2 FAA Data Sheet E41NE A330-302 CF6-80E1A4 FAA Data Sheet E41NE A330-303 CF6-80E1A3 FAA Data Sheet E41NE Maximum Oil Temperature (Supply Pump Outlet) ºC • Continuous Operation • Transient (15 mn max.) • Minimum Oil Pressure (PSI) 320º F (160º C) 347º F (175º C) 10.0 psid (69 KPa ) 320º F (160º C) 347º F (175º C) 10.0 psid (69 KPa ) 320º F (160º C) 347º F (175º C) 10.0 psid (69 KPa ) Approved oils See SB CFMI 79-001 or GE specification D50TF1 Class B Engine Limitations A330-321 PW 4164 PW 4164-1D FAA Data Sheet E36NE A330-322 PW 4168 PW 4168-1D FAA Data Sheet E36NE A330-323 PW 4168A PW 4168A-1D FAA Data Sheet E36NE A330-323 PW 4170 FAA Data Sheet E36NE Static Thrust at Sea Level • Take-off (5 mn)1 (flat rated 30ºC) • Max continuous (flat rated 25ºC) 64,500 lbs 55,800 lbs 68,600 lbs 59,357 lbs 68,600 lbs 59,357 lbs 70,000 lbs 59,357 lb Maximum Engine Speed • N1 rpm (%) • N2 rpm (%) 3,600 (101%) 10,450 (103%) 3,600 (101%) 10,450 (103%) 3,600 (101%) 10,450 (103%) 3,680 (101%) 10,450 (103%) Maximum Gas Temperature • Take-off (5mn)1 • Maximum Continuous • Starting2 1,148º F (620º C) 1,112º F (600º C) 1,148º F (620º C) 1,148º F (620º C) 1,112º F (600º C) 1,148º F (620º C) 1,148º F (620º C) 1,112º F (600º C) 1,148º F (620º C) 1,148º F (620º C) 1,112º F (600º C) 1,148º F (620º C) Maximum Oil Temperature (Supply Pump Outlet) ºC • Continuous Operation • Transient (15 mn max.) • Minimum Oil Pressure (PSI) 325º F (163º C) 350º F (177º C) 70 psid (482.6 KPa) 325º F (163º C) 350º F (177º C) 70 psid (482.6 KPa) 325º F (163º C) 350º F (177º C) 70 psid (482.6 KPa) 325º F (163º C) 350º F (177º C) 70 psid (482.6 KPa) Approved oils See P&W Service Bulletin 238, latest revision. Engine Limitations A330-341 Trent 768-60 FAA Data Sheet E39NE A330-342 Trent 772-60 FAA Data Sheet E39NE A330-343 Trent 772B-60 FAA Data Sheet E39NE Static Thrust at Sea Level • Take-off (5 mn)1 (flat rated 30ºC) • Max continuous (flat rated 25ºC) 67,500 lbs 60,410 lbs 71,100 lbs 63,560 lbs 71,100 lbs 63,560 lbs Maximum Engine Speed • N1 rpm (%) • N2 rpm (%) 3,861 (99%) 10,611 (100%) 3,861 (99%) 10,611 (100%) 3,861 (99%) 10,611 (100%) Maximum Gas Temperature • Take-off (5mn)1 • Maximum Continuous • Starting2 1,652º F (900º C) 1,562º F (850º C) 1,562º F (850º C) 1,652º F (900º C) 1,562º F (850º C) 1,562º F (850º C) 1,652º F (900º C) 1,562º F (850º C) 1,562º F (850º C) Maximum Oil Temperature (Supply Pump Outlet) ºC • Continuous Operation • Transient (15 mn max.) • Minimum Oil Pressure (PSI) 374º F (160º C) 374º F (175º C) 24.0 psid 374º F (160º C) 374º F (175º C) 24.0 psid 374º F (160º C) 374º F (175º C) 24.0 psid Approved oils Refer to the Engine Operating Instructions for A330/A340 for information on approved oil specifications for Trent 700 Table references: (1) 10 minutes at take-off thrust allowed only in case of engine failure (at take-off or during go-around). (2) 4 consecutive cycles of 2 minutes each. A46NM 15 of 44 Maximum Weight A330-301, A330-321: • Maximum Take-off Weight (MTOW): 217,000 kg / 478,403 lb • Maximum Landing Weight (MLW): 179,000 kg / 394,627 lb • Maximum Zero Fuel Weight (MZFW): 169,000 kg / 372,581 lb A330-322 and A330-341 • Maximum Take-off Weight (MTOW): 218,000 kg / 480,607 lb • Maximum Landing Weight (MLW): 182,000 kg / 401,241 lb • Maximum Zero Fuel Weight (MZFW): 172,000 kg / 379,195 lb A330-342, A330-343 • Maximum Take-off Weight (MTOW): 242,000 kg / 533,518 lb • Maximum Landing Weight (MLW): 187,000 kg / 412,264 lb • Maximum Zero Fuel Weight (MZFW): 175,000 kg / 385,808 lb Note: See applicable Airplane Flight Manual (AFM), as listed in ‘Operating and Service Instructions’, for configuration specific mass limitations and aircraft eligibility’ (Weight Variant). Number of Seats The maximum number of passengers approved for emergency evacuation is: - 375 passengers with a 3 pairs Type A and 1 pair Type 1 exit configuration, and - 440 passengers with a 4 pairs Type A exit configuration. Maximum Baggage Cargo Compartment Maximum Load (kg / lb) Forward 22,861 / 50,408 Aft 18,507 / 40,808 Rear 3,468 / 7,647 For the positions and the loading conditions authorized in each position (references of containers, pallets and associated we ight) see Weight and Balance Manual: - A330-300 Airbus Document ref. 00G080A0006/C3S Fuel Capacity Without optional Center Fuel Tank Two Tank Airplane Usable Fuel Unusable Fuel (without MOD 204579) Unusable Fuel (with MOD 204579) Model A330-301/-321/-322/-341/-342 A330-302/-303/-323/-343 All Models Tank liters (kg) gallons (lb) liters (kg) gallons (lb) liters (kg) gallons (lb) liters (kg) gallons (lb) Wing 91,764 (73,411) 24,244 (161,871) 91,300 (73,040) 24,122 (161,053) 348 (279) 92 (615) 190 (152) 50 (335) Trim Tank 6,121 (4,897) 1,617 (10,798) 6,230 (4,984) 1,646 (10,990) 6 (5) 1.6 (11) 6 (5) 1.6 (11) Total 97,885 (78,308) 25,861 (172,669) 97,530 (78,024) 25,768 (172,043) 354 (284) 94 (626) 196 (157) 52 (346) A46NM 16 of 44 Optional Center Fuel Tank Three Tank Airplane Usable Fuel Unusable Fuel (without MOD 204579) Unusable Fuel (with MOD 204579) Model A330-302/-303/-323/-342/-343 Tank liters (kg) gallons (lb) liters (kg) gallons (lb) liters (kg) gallons (lb) Wing 91,764 (73,411) 24,244 (161,871) 348 (279) 92 (615) 190 (152) 50 (335) Center 41,560 (33,248) 10,980 (73,311) 83 (67) 22 (148) 83 (67) 22 (148) Trim Tank 6,121 (4,897) 1,617 (10,798) 6 (5) 1.6 (11) 6 (5) 1.6 (11) Total 139,445 (111,556) 36,841 (245,980) 437 (351) 116 (774) 279 (224) 73.7 (494) Certification Basis (A330-300) a. 14 CFR part 25 effective February 1, 1965, including the following: • Amendments 25-1 through 25-63, Amendments 25-65, 25-66, 25-77 • § 25.791 at Amendment 25-72 b. 14 CFR part 25 Amendment 25-64 with the following exceptions: • Cockpit seats will not meet § 25.562 Amendment 25-64 but will meet § 25.561 • Compliance with § 25.785(a), (b), and (c) at Amendment 25-64 for front row seats in front of a bulkhead will be based on ensuring a 35 inch free head strike envelope. c. 14 CFR part 34, effective September 10, 1990. d. 14 CFR part 36 as amended by Amendments 36-1 through 36-20. e. Special conditions in accordance with § 21.16. 1. Special conditions published in the Federal Register on October 19, 1993, ( Docket No. NM-86, Special Conditions No. 25- ANM-77) (1) Operation without Normal Electrical Power (8) Limit Pilot Forces (2) Electronic Flight Control System (EFCS) failures and Mode Annunciation (9) Tail plane Tank Emergency Landing Loads (3) Command Signal Integrity (10) Limit Engine Torque (4) Protection From Lightning and Unwanted Effects of High Intensity Radiated Fields (HIRF) (11) Flight Characteristics (5) Interaction of Systems and Structures (12) Flight Envelope Protection (6) Design Dive Speed (13) Side Stick Controllers (7) Design Maneuver Requirements (14) Computerized Airplane Flight Manual (AFM) Performance Information 2. Special Condition 25-281-SC published in the Federal Register on January 6, 2005 (Docket No. NM287): Lower Deck Mobile Crew Rest (LD-MCR) Compartment – Optional modification # 206615. 3. Special Condition 25-395-SC published in the Federal Register November 03, 2009 (Docket No. NM-418): Seats With Inflatable Lap Belts. 4. Special Condition 25-400 -SC published in the Federal Register January 4, 2010 (Docket No. NM-424): Seats with Non-Traditional, Large, Non-Metallic Panels. 5. Special Condition 25-678-SC published in the Federal Register May 26, 2017 (Docket No. FAA-2017-0369): Non-Rechargeable Lithium Batteries This Special condition is effective to design changes applied for after May 26, 2017. See the applicability section of this special condition for more information on which design changes must meet it. A46NM 17 of 44 6. Special Condition 25-739-SC published in the Federal Register on December 26, 2018 (Docket No. FAA–2018–1053): Electronic System Security Protection from Unauthorized External Access. This Special Condition apply to installation and activation of electronic network system architecture or Flight Operations and Maintenance Exchanger (FOMAX) equipment (Airbus modification # 207456). 7. Special Condition 25-740-SC published in the Federal Register on December 26, 2018 (Docket No. FAA–2018–1054): Electronic System Security Protection from Unauthorized Internal Access. This Special Condition apply to installation and activation of electronic network system architecture or Flight Operations and Maintenance Exchanger (FOMAX) equipment (Airbus modification # 207456). f. The technical requirements are complemented by the following guidance material: For precision approach and landing, 1. AC 120-29 2. AC 120-28C and for the automatic flight control system 1. AC 20-57A for automatic landing 2. AC 25.1329-1A for cruise g. Equivalent safety findings (ELOS) have been made in accordance with § 21.21(b)(1) for the following sections: (1) § 25.335(d) for design airspeeds* (2) § 25.341 for gust loads* (3) § 25.345 for high lift devices* (4) § 25.349 for control surface loads* (5) § 25.351(b) for unsymmetrical loads* (6) § 25.371 for gyroscopic loads* (7) § 25.373 for speed control devices* (8) § 25.391 for control surface loads * *These ELOS findings do not apply where the corresponding requirements of Amendment 25-141 are applied. (9) §§ 25.101(I); 25.105(c)(1); 25.109(a)(b)(c)(d)(e)(f); 25.113(a)(b)(c); 25.115(a); 25.735(f)(g)(h)(b) for rejected takeoff and landing performance (10) §§ 25.933(a)(1)(ii), 25.1309(b)(1) for flight critical thrust reverser (11) § 25.1203(d) for turbine overheat detection (RR Trent 700 powered A330-341, -342, -343 only) (12) § 25.1305(c)(6) Warning means for engine fuel filter contamination (RR Trent 700 powered A330-341, -342 and -343 only) (13) §§ 25.1305: 25.1501(b) for APU system flight deck instrumentation. (14) § 25.856(b), Improved Flammability standards for Thermal/acoustic insulation materials (documented in ELOS Memo TD0609IB-T-CI-5; Memo TD0609IB-T-CI-6 and Memo TD0609IB-T-CI-7). (15) § 25.785(d), Forward Facing Seat, over 18 degrees to aircraft centerline (documented in ELOS Memo TD0643IB-T-CI-9). (16) § 25.1457(d)(5) Cockpit Voice Recorder – Equivalent Level of Safety for 10 minute independent backup power requirement (documented in ELOS Memo TD0774IB-T-SA-1). (17) § 25.1443(c) Minimum mass flow of supplemental oxygen on model A330 and A340 airplanes (documented in ELOS Memo AT10356IB-T-S-1) (18) § 25.1441(c) Crew determination of quantity of oxygen in passenger oxygen system on model A330 and A340 airplanes (documented in ELOS Memo AT10356IB-T-S-2). (19) § 25.785 (d) Installation of seats that make angle of more than 18° with aircraft longitudinal axis (documented in TAD ELOS Memo AT10434IB-T-CS-1). Applicable only to A330-302 with Airbus modification # 204087 Issue 1. (20) §§ 25.811(g); 25.812(b)(1) Symbolic Exit Signs on Models A330 and A340 airplanes (documented in ELOS Memo TD00918IB-T-CS-1). For airplanes equipped with pictograms on exit marking signs and on exit location signs, the cabin crew in charge of the safety briefing should highlight these pictograms to the passengers prior to each takeoff and each landing (21) § 25.811(e)(4) Emergency Exit Marking on model A330 and A340 airplanes (documented in ELOS Memo AT10899IB-T- CS-1) for airplanes with Airbus modification # 206893. h. Optional requirements elected: • § 25.801 for ditching. • § 25.1419 for icing. A46NM 18 of 44 i. Certification requirements for A330-302, A330-303, A330 -323, A330 -342, A330 -343 with Airbus modifications ## 203897 (WV080); 203898 (WV081); 203900 (WV 082) and 203899 (WV 083): • 14 CFR part 25 as listed here-above in § a. through § h. plus the following regulations at their amendment level as defined in the table below: Section No. Title Amendment 25.3 Special provisions for ETOPS type design approvals 25-120 25.21(d) Proof of compliance 25-72 25.29 Empty weight and corresponding center of gravity 25-72 25.107(e)(1)(iv) Takeoff speeds 25-135 25.111 Takeoff path 25-72 25.119 Landing climb: All-engines-operating 25-84 25.121 Climb: One engine inoperative 25-84 25.145 Longitudinal control 25-84 25.253(a)(1), (a)(2), (a)(4), (a)(5) High-speed characteristics 25-135 25.519 Jacking and tie-down provisions 25-81 25.611(a) Accessibility provisions 25-123 25.629 Aeroelastic stability requirements 25-77 25.1329(g) Flight guidance system 25-119 25.1535 ETOPS approval 25-120 25.1581 Airplane flight manual: General 25-72 25.1583 Operating limitations 25-105 25.1585 Operating procedures 25-105 25.1587 Performance information 25-105 26.11 Electrical wiring interconnection systems (EWIS) maintenance program 26-0 26.21 Limit of validity 26-6 26.45(c) Holders of type certificates – Alterations and repairs to alterations 26-4 • 14 CFR part 36 as amended by 36-1 through 36-29 j. Certification requirements for A330 -302; A330 -303; A330 -323, A330 -342 and A330 -343 with Airbus modification # Project G3ActCT: “Fuel - Tanks - Activation of Center Tank on A330-300”: • 14 CFR part 25 as listed here-above in § a. through § h. plus the following regulations at their amendment level and affected airplane systems and areas as defined in the table below: Section No. Title Amendment System/Area 25.1 Applicability 25-0 A330-300 airplane with center tank 25.3 Special provisions for ETOPS type design approvals 25-120 A330-300 airplane with center tank 25.101(c)(2) Performance, General 25-38 A330-300 airplane with center tank 25.611 Accessibility provisions 25-123 A330-300 center tank, its structural elements and systems, center fuel tank inerting system, fuel system including pumps, valves, sensors, drain and ventilation system, and Fuel Quantity Indicating System (FQIS)/Fuel Level Sensing System (FLSS) EWIS installation 25.899 Electrical bonding and protection against static electricity 25-123 A330-300 airplane with center tank 25.901(c) Installation 25-126 A330-300 center tank fuel system, including pumps, valves, sensors, EWIS installation, control, indication and information displays 25.903(d)(1) Engines 25-100 A330-300 center tank fuel system, including pumps, valves, sensors, EWIS installation, drain and ventilation system, center fuel tank inerting system, controls and indications. 25.951 Fuel system: General 25-73 A330-300 center tank fuel system, including pumps, valves, EWIS installation, drain and ventilation system, center fuel tank inerting system, controls and indications.. 25.963 Fuel tanks: general 25-69 A330-300 center tank structure A46NM 19 of 44 Section No. Title Amendment System/Area 25.979 Pressure fueling system 25-72 A330-300 center tank refuel system 25.981 Fuel tank ignition prevention 25-125 A330-300 center tank and its fuel system, including pumps, valves, sensors, EWIS installation, drain and ventilation system, center fuel tank inerting system, controls and indication. 25.1141(a), (f) Powerplant controls: general 25-115 Cockpit fuel controls for A330-300 center tank 25.1301(b) Function and installation 25-123 A330-300 center tank fuel system FQIS/FLSS EWIS installation 25.1305(a)( 2) Powerplant instruments 25-115 Fuel quantity indication for A330-300 center tank 25.1309(a), (b), (c), (d), (e), (f) Equipment, systems, and installations 25-123 A330-300 center tank and its fuel system, including pumps, valves, sensors, EWIS installation, drain and ventilation system, center fuel tank inerting system, controls and indications. 25.1351(d) Electrical systems and equipment: general 25-72 A330-300 center tank fuel system, including pumps, valves, sensors, EWIS installation, drain and ventilation system, center fuel tank inerting system, controls and indications. 25.1535 ETOPS approval 25-120 A330-300 airplane with center tank 25.1581 Airplane flight manual: General 25-72 A330-300 airplane with center tank 25.1583 Operating limitations 25-105 A330-300 airplane with center tank 25.1585 Operating procedures 25-105 A330-300 airplane with center tank 25.1587 Performance information 25-105 A330-300 airplane with center tank 25.1703(a)( 3), (a)(4), (d) Function and installation: EWIS 25-123 A330-300 center tank FQIS/FLSS EWIS installation 25.1705(a), (b)(2) Systems and functions: EWIS 25-123 A330-300 center tank fuel system FQIS/FLSS EWIS installation 25.1707(a), (b), (c), (l) Systems separation: EWIS 25-123 A330-300 center tank fuel system FQIS/FLSS EWIS installation 25.1709(a), (b) System safety: EWIS 25-123 A330-300 center tank fuel system FQIS/FLSS EWIS installation 25.1711(a), (b) Component identification: EWIS 25-123 A330-300 center tank fuel system FQIS/FLSS EWIS installation 25.1719 Accessibility provisions: EWIS 25-123 A330-300 center tank fuel system FQIS/FLSS EWIS installation 25.1721(b) Protection of EWIS 25-123 A330-300 center tank fuel system FQIS/FLSS EWIS installation • Exemption No. 17129 dated October 26, 2016. This Exemption from 14 CFR 25.98 l(a)(3) is granted to Airbus as it relates to the Model A330-300 fuel trim tank structural lightning protection (Airbus modification # 204495 “Stabilizers – Horizontal Stabilizer – Define lateral box for weight reduction”). • Exemption No. 17601, dated October 13, 2017. This exemption is granted for the requirements of 14 CFR part 25, appendix K, section K25.1.4(a)(2) as they relate to concurrent power of the fuel boost pumps in each main fuel tank and will allow to show that the airplanes are capable of continuously providing fuel pressure to all engines when only powered by an independent electrical power source other than the three power sources required in section K25.1.3(b) of appendix K, without maintaining simultaneous power to all individual fuel boost pumps. This exemption relates to Model A330 series airplanes ETOPS beyond 180 minutes approval. • Equivalent safety findings have been made in accordance with § 21.21(b)(1) for the following sections: 14 CFR part 26.33 “Holders of type certificates: Fuel tank flammability” and 26.35 “Changes to type certificates affecting fuel tank flammability”, (documented in TAD ELOS Memo TD0547IB-T-P-1). • 14 CFR part 36, effective December 1, 1969, as amended by Amendments 36-1 through 36-29. A46NM 20 of 44 The Direction Generale de l'Aviation Civile (DGAC) of France originally type certificated the Airbus Model A330 -200 series airplanes under its type certificate number DGAC -F TC 184. The FAA validated this product under U.S. Type Certificate Number A46NM. Effective September 28, 2003, the European Union Aviation Safety Agency (EASA) began oversight of this product on behalf of DGAC. Part 26 – Continued Airworthiness and Safety Improvements for Transport Category Airplanes: Based on § 21.29(a) for new import TCs, or § 21.101(g) for changes to TCs, applicable provisions of part 26 are included in t he certification basis. For any future part 26 amendments, the holder of this TC must demonstrate compliance with the applicable sections. FAA Required Modification List Compliance with the FAA Required Modification List for Airbus Model A330-300 Aircraft as included under the Import Requirements section of TCDS Revision 4, dated March 21, 2000 or later TCDS revision is necessary for an A330-300 aircraft to be found in a condition for safe operation. The FAA has accepted: • Model A330 -323 aircraft in the Airbus as -delivered configuration for MSN 524 and on as compliant with the applicable modifications of the A330 RML. FAA acceptance is based on the Airbus statement to the FAA (ref. Airbus letter EAL G01M03003568 issue 2, dated June 24, 2003) that the RML modifications applicable to model A330 -323 aircraft are either part of the FAA approved type design (ref. AI/EA -N 415.1630/99 Issue 1, dated July 20, 1999), required to be installed at aircraft delivery by DGAC AD, or required to be installed by Airbus on all Model A330-323 aircraft at time of delivery. • Model A330-302 and -303 aircraft in the Airbus as-delivered configuration as compliant with the applicable modifications of the A330 RML. FAA acceptance is based on the Airbus statement to the FAA (ref. Airbus letter EAL G03D07012703 (for the -302) and EAL G03D07012712 (for the -303), each dated June 8, 2007) that the RML modifications applicable to model A330-302 and -303 aircraft are either part of the FAA approved type design (ref. EAL M05000400 and EAL M05000401; both at Issue 03 and dated May 2006), required to be installed at aircraft delivery by DGAC AD, or required to be installed by Airbus on all Model A330-302 and -303 aircraft at time of delivery. • Model A330-343 aircraft in the Airbus as -delivered configuration as compliant with the applicable modifications of the A330 RML. FAA acceptance is based on the Airbus statement to the FAA (ref. Airbus letter EAL_LR01M10004733, dated March 03, 2010) that t he RML modifications applicable to model A330 -343 aircraft are either part of the FAA approved type design (ref. AIAI/EA-N 415.2027/99 Issue 1, dated October 22, 1999), required to be installed at aircraft delivery by DGAC/EASA AD, or required to be installed by Airbus on all A330-343 aircraft at time of delivery. Equipment • The basic required equipment as prescribed in the applicable airworthiness regulations (see Certification Basis) must be inst alled in the aircraft for certification. • The following Airbus Documents defines the set of modifications, which comprise the FAA certificated type design. This document contains certain modifications determined necessary for FAA certification, including installation of ozone converters, fuel s ystem improvements and thrust reverser modifications. - AI/EA-N 415.1181/96 Issue 3, dated July 16, 1997 for the A330-301 - EAL M05000400 Issue 3, dated May 2006 for the A330-302 - EAL M05000401 Issue 3, dated May 2006 for the A330-303 - AI/EA-N 415.1184/96 Issue 3, dated June 25, 1998 for the A330-321 - AI/EA-N 415.1183/96 Issue 3, dated July 25, 1998 for the A330-322 - AI/EA-N 415.1630/99 Issue 1, dated July 20, 1999 for the A330-323 - AI/EA-N 415.1187/96 Issue 2, dated December 11, 1998 for the A330-341 - AI/EA-N 415.1182/99 Issue 2, dated December 11, 1998 for the A330-342 - AI/EA-N 415.2027/99 Issue 1, dated October 22, 1999 for the A330-343 • Equipment approved for installation is listed in the Certification Standard Equipment List - 00G000A0101/C0S for the A330-301. - 00G000A0121/C0S for the A330-321 and -322. - 00G000A0123/C3S for the A330-323. - 00G000A0141/C0S for the A330-341 and -342. - 00G000A0143/C3S for the A330-343. • Cabin furnishings, equipment and arrangement shall conform to the following specification: - 00F252K0005/C01 for cabin seats, - 00F252K0006/C01 for galley, - 00F252K0020/C01 for cabin attendant seats A46NM 21 of 44 Airplane Flight Manual Airplane operation must be in accordance with the EASA-Approved Airplane Flight Manual (AFM), US version, listed below, or later EASA approved revision applicable to the specific airplane model, modification status and serial number. Aircraft A330-300 Airbus Document Reference. Revision No. Date -301 AI/EV-O 33000 3 January 6, 1999 -321, -322 AI/ST-F 33000 2 January 6, 1999 -302, -303 STL 33000 4 November 21, 2006 -323 AI/ST-F 33000 4 May 18, 2001 -341, -342 AI/ST-F 33000 3 March 15, 2000 -343 AI/ST-F 33000 2 March 15, 2000 Data Pertinent to All Model See Section VI, Data Pertinent to All Model A330-200, A330-200 Freighter, A330-300, A330-800 and A330-900 Series airplanes. for information on Fuel, Airspeed Limits, Center of Gravity Limits, Datum, Leveling Means, Minimum Crew, Maximum Operating Altitude, Control Surf ace Movements, Production Basis , Hydraulic Fluids, Auxiliary Power Unit (APU), Tires, Environmental requirements for noise, Manufacturer’s Serial Numbers, Service Information, information on Import Requirements and General Notes A46NM 22 of 44 IV. Type A330-800 Series Transport Category Airplanes Airbus A330-841 - approved February 12th, 2020 Model: Definition of Reference Airplane by Airbus Documents: A330-841 A330-841 Type Design, ref. 00G000A0841/C00 Issue 1, dated January 29, 2020, for type definition Engines Airplane Model Engine Model: Engine Type Certificate: A330-841 Two RR Trent 7000 turbojet engines FAA-Type Certificate E00076EN (EASA.E.036) Engine Limits Engine Limitations A330-841 RR 7000 FAA Data Sheet E00076EN Static Thrust at Sea Level • Take-off (5 mn)1 (flat rated 30ºC) • Max continuous (flat rated 25ºC) 72,834 lbs 65,005 lbs Maximum Engine Speed • N1 rpm (%) • N2 rpm (%) 2,683 (101.5%) 8,937 (103.5%) Maximum Gas Temperature • Take-off (5mn)1 • Maximum Continuous • Starting2 1,652º F (900º C) 1,562º F (850º C) 1,292º F (700º C) Maximum Oil Temperature (Supply Pump Outlet) ºC • Continuous Operation • Transient (15 mn max.) • Minimum Oil Pressure (PSI) 376º F (191º C) 385º F (196º C) 30.0 psid Approved oils Refer to the Engine Operating Instructions for A330/A340 for information on approved oil specifications for Trent 7000 Table references: (1) 10 minutes at take-off thrust allowed only in case of engine failure (at take-off or during go around). (2) 4 consecutive cycles of 2 minutes each. Maximum Weight • Maximum Take-Off Weight (MTOW): 251,000 kg / 553,360 lb • Maximum Landing Weight (MLW): 186,000 kg / 410,059 lb • Maximum Zero Fuel Weight (MZFW): 176,000 kg / 388,013 lb See applicable Airplane Flight Manual (AFM), as listed in ‘Operating and Service Instructions’, for configuration specific mass limitations and aircraft eligibility (Weight Variant). Number of Seats The maximum number of passengers approved for emergency evacuation is: - 375 passengers with a 3 pairs of Type A and 1 pair Type 1 exits configuration, and - 406 passengers with a 4 pairs of Type A exits configuration. A46NM 23 of 44 Maximum Baggage Cargo Compartment Maximum Load (kg / lb) Forward 18,869 / 41,599 Aft 15,241 / 33,600 Rear 3,468 / 7,646 For the positions and the loading conditions authorized in each position (references of containers, pallets and associated we ight) see weight and Balance Manual: A330-800 Airbus Document 00G080A3WBM/C8S Fuel Capacity 3 Tank Airplane Usable Fuel Unusable Fuel Tank liters (kg) gallons (lb) liters (kg) gallons (lb) Wing 91,300 (73,040) 24,119 (161,026) 190 (152) 50 (335) Center 41,560 (33,248) 10,980 (73,311) 83 (67) 22 (148) Trim Tank 6,230 (4,984) 1,646 (10,988) 6 (5) 1.6 (11) Total 139,090 (111,272) 36,744 (245,313) 279 (224) 74 (494) Certification Basis (A330-800) The FAA Certification basis for the Airbus Model A330-841 airplanes is defined as: The original certification basis for the Airbus Model A330 -200 series airplanes as defined in FAA TCDS A46NM for components or areas not affected by the change. Plus the following sections of 14 CFR part 25, for which Airbus elects to comply to bring the certification basis up to the s ame level as for the A330-300 series airplanes with Modification 203897, 203898, 203900 or 203899 (WV 080-083) and with Modification G3ActCT (Activation of center fuel tank) for components or areas not affected by the change and for secondary changes: 14 CFR part 25 as amended by Amendment 25-1 through 25-63: 25.335 (a), (b),(f); 25.1001(c), (d), (e), (f), (g), (h), (i); 14 CFR part 25 as amended by Amendment 25-1 through 25-123: 25.1705(a), (b)(5), (b)(9), (b)(12); 25.1721(c); 14 CFR part 25 as amended by Amendment 25-1 through 25-105: 25.1583 Plus the following sections of 14 CFR part25. Amendments 25-1 through 25-141 (i.e., the amendment in effect on the date of application extension) applied to the components and areas affected by the change: Paragraphs applicable to all A/C: 25.3, 25.21(a)(b)(c)(d)(e)(f), 25.23, 25.25, 25.27, 25.29, 25.101, 25.103(a)(c)(d), 25.105(b)(c)(d), 25.107 (a)(b)(c)(d)(e)(f )(g), 25.109, 25.111(a)(b)(d)(e), 25.113, 25.115, 25.117, 25.121(a), 25.123(a)(c), 25.145, 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, 25.253(a)(b), 25.255, 25.305(a)(b)(c)(f), 25.307(a), 25.321, 25.331, 25.333, 25.335(c)(d)(e), 25.337, 25.341, 25.343 (a)(b1)(b2)(b3), 25.345(a)(b)(d), 25.349, 25.351, 25.361 (a), 25.36 2, 25.365(a)(b)(d), 25.367, 25.371, 25.373, 25.427, 25.457, 25.471(a)(b), 25.473, 25.479, 25.481(a)(c), 25.483, 25.485, 25.489, 25.491, 25.493, 25.495, 25.499, 25.503, 25.507, 25.509, 25.511, 25.519, 25.623, 25.629, 25.683(a)(b)(c), 25.703, 25.809(g), 25.841, 25.843, 25.901(c), 25.963 (Center Tank Structure Only), 25.967, 25.969, 25.971, 25.975, 25.1316, 25.1317, 25.1329(g), 25.1337, 25.1355, 25.1501, 25.1503, 25.1505, 25.1507, 25.1511, 25.1513, 25.1515, 25.1516, 25.1517, 25.1519, 25.1529, 25.1531, 25.1533(a) (b), 25.1535, 25.1553, 25.1581, 25.1583, 25.1585, 25.1587. A46NM 24 of 44 Paragraphs applicable to the engine installation (New Engine, Pylon, pre -cooler, air inlet and nacelle, Structural adaptation of the wing at the wing/pylon interface, Electro Pneumatic Bleed Air System): 25.301(b)(c), 25.303, 25.363, 25.365(e)(1), 25.561(c), 25.581, 25.601, 25.603, 25.605, 25.607, 25.609, 25.611, 25.613, 25.619 , 25.621, 25.625, 25.631, 25.721(b), 25.723(b) 25.733(b)(c)(d), 25.779(b), 25.851(b), 25.863, 25.865, 25.867, 25.869, 25.899, 25.901, 25.903, 25.933, 25.934, 25.939(a)(c), 25.943, 25.951(a)(b)(2)(c), 25.952, 25.954, 25.955(a), 25.959, 25.961(a), 25.963, 25.98 1 (except for fuel system wiring changes outside the pylon area and fuel tank structural fastener changes), 25.993(a)(b)(c)(d)(e), 25.994, 25.995, 25.997, 25.999(b), 25.1001(a)(b), 25.1011, 25.1013, 25.1015, 25.1017, 25.1019, 25.1021, 25.1023, 25.1025, 25.1041, 25.1043, 25.1045, 25.1091(a)(c)(d)(e), 25.1093(b), 25.1103, 25.1121, 25.1123, 25.1141, 25.1143, 25.1145, 25.1155, 25.1163, 25.1165(a)(b)(c)(e)(f)(g)(h), 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, 25.1351, 25.1353, 25.1357, 25.1360(a), 25.1363, 25.1419 (for powerplant installation only), 25.1431, 25.1435(a), 25.1438, 25.1461, 25.1521, 25.1527, 25.1549, 25.1551, 25.1557(b), 25.1701, 25.1703, 25.1705, 25.1707, 25.1709, 25.1711, 25.1713, 25.1715, 25.1717, 25.1719, 25.1721(a)(b), 25.1723, 25.1725, 25.1727, 25.1729, 25.1731, Appendix C. Paragraphs applicable to aerodynamic changes (New winglet with wing span increase, Wing Aerodynamic clean up, Wing twist change, Wing engine interference, new navigation and strobe lights): 25.301(b)(c), 25.303, 25.363, 25.391 (for modified control surfaces only), 25.393, 25.415 (for modified control surfaces only ), 25.581, 25.601, 25.603, 25.605, 25.607, 25.609, 25.611, 25.613, 25.619, 25.625, 25.631, 25.723(b), 25.863, 25.869, 25.899, 25.954, 25.959, 25.1001(a)(b), 25.1301, 25.1305, 25.1309, 25.1353, 25.1357, 25.1360(a), 25.1383(a), 25.1385(a)(b)(c)(d), 25.1387, 25.1389, 25.1391, 25.1393, 25.1395, 25.1397, 25.1401 (a)(b)(c)(d)(e)(f), 25.1403, 25.1431, 25.1438, 25.1525 Plus the following sections of 14 CFR part 25 amended as indicated below applied to the components and areas affected by the chang e per Airbus exception justifications in accordance with 14 CFR 21.101: • 25.103(b), 25.105(a), 25.111(c), 25.119, 25.121(b)(c)(d), 25.123(b), 25.125, 25.143, 25.207, 25.237, and 25.1419, Amendments 25-1 through 25-120, for “Flight in icing conditions.” FAA acceptance of this exception is based on compliance with EASA CRI B-07 Flight in Icing Conditions. • 25.571, Amendments 25-1 through 25-86, for “Damage tolerance and fatigue evaluation of structure.” FAA acceptance of this exception is based on compliance with 14 CFR part 26. • 25.981, Amendments 25-1 through 25-11, for the fuel system wiring changes outside the pylon area and the fuel tank structural fastener changes. FAA acceptance of this exception is based on Fuel Quantity Indicating System (FQIS) and Fuel Level Sensor System (FLSS) wiring isolation with protective sleeving and closely spaced ties in the S-routes with labels identifying the fuel system wiring and Airbus compliance with FAA Policy Statement ANM-112-08-002 “Policy on Issuance of Special Conditions and Exemptions Related to Lightning Protection of Fuel Tank Structure,” dated May 26, 2009, for the fuel tank structural fastener changes. • Appendix H to part 25, Amendments 25 -1 through 25-54, for Instructions for Continued Airworthiness. FAA acceptance of this exception is based on compliance with 14 CFR part 26. Plus the following optional sections of 14 CFR part 25 for which Airbus elects to comply as indicated below: 25.1535, Amendments 25-1 through 25-141 Plus the following optional requirements for which Airbus elects to comply to 14 CFR part 25 Amendment 25-1 through 25-143: 25.975(a)(7) for compliance with the operational rules §121.1119 and §129.119 related to fuel tank vent explosion protection. Special Conditions The full list of Special Conditions applicable to the A330-841 is defined below: 1. Special Conditions No. 25 -ANM-77 published in the Federal Register on October 19, 1993, (Docket No. NM 86, Special Conditions No. 25-ANM-77): (1) Operation without Normal Electrical Power (8) Limit Pilot Forces (2) Electronic Flight Control System (EFCS) failures and Mode Annunciation (9) Tail plane Tank Emergency Landing Loads - (3) Command Signal Integrity (10) Limit Engine Torque (4) Protection From Lightning and Unwanted Effects of High Intensity Radiated Fields (HIRF) (11) Flight Characteristics (6) Design Dive Speed (12) Flight Envelope Protection (7) Design Maneuver Requirements (13) Side Stick Controllers A46NM 25 of 44 2. Special Condition 25-281-SC published in the Federal Register on January 6, 2005 (Docket No. NM287): Lower Deck Mobile Crew Rest (LD-MCR) Compartment – Optional modification # 206615. 3. Special Condition 25-395-SC published in the Federal Register November 03, 2009 (Docket No. NM-418): Seats With Inflatable Lap Belts. 4. Special Condition 25-400 -SC published in the Federal Register January 4, 2010 (Docket No. NM-424): Seats with Non-Traditional, Large, Non-Metallic Panels. 5. Special Condition 25-678-SC published in the Federal Register May 26, 2017 (Docket No. FAA-2017-0369): Non-Rechargeable Lithium Batteries This Special condition is effective to design changes applied for after May 26, 2017. See the applicability section of this special condition for more information on which design changes must meet it. 6. Special Condition 25-696-SC published in Federal Register on August 4, 2017 (Docket No. FAA–2017–0356): Interaction of Systems and Structure. 7. Special Condition 25-708-SC published in Federal Register on January 16, 2018 (Docket No. FAA–2017–0483): Electronic Flight Control System Lateral-Directional and Longitudinal Stability and Low Energy Awareness. 8. Special Condition 25-709-SC published in Federal Register on January 4, 2018 (Docket No. FAA–2017–0482): Use of High Incidence Protection and Alpha Floor Systems. 9. Special Condition 25-739-SC published in the Federal Register on December 26, 2018 (Docket No. FAA–2018–1053): Electronic System Security Protection from Unauthorized External Access. This Special Condition apply to installation and activation of electronic network system architecture or Flight Operations and Maintenance Exchanger (FOMAX) equipment (Airbus modification # 207456). 10. Special Condition 25-740-SC published in the Federal Register on December 26, 2018 (Docket No. FAA–2018–1054): Electronic System Security Protection from Unauthorized Internal Access. This Special Condition apply to installation and activation of electronic network system architecture or Flight Operations and Maintenance Exchanger (FOMAX) equipment (Airbus modification # 207456). 11. Special Condition 25-747-SC published in the Federal Register on May 29, 2019 (Docket No. FAA–2019–0235): Seats with Inertia Locking Devices (Airbus modification # 207317). Equivalent Safety Findings (ELOS) The full list of ELOS applicable to the A330-841 is defined below: (1) § 25.335(d) for design airspeeds* (2) § 25.341 for gust loads* (3) § 25.345 for high lift devices* (4) § 25.349 for control surface loads* (5) § 25.351(b) for unsymmetrical loads* (6) § 25.371 for gyroscopic loads* (7) § 25.373 for speed control devices* (8) § 25.391 for control surface loads * *These ELOS findings do not apply where the corresponding requirements of Amendment 25-141 are applied. (9) §§ 25.101(I); 25.105(c)(1); 25.109(a)(b)(c)(d)(e)(f); 25.113(a)(b)(c); 25.115(a); 25.735(f)(g)(h)(b) for rejected takeoff and landing performance (10) §§ 25.933(a)(1)(ii), 25.1309(b)(1) for flight critical thrust reverser (11) §§ 25.1305; 25.1501(b) for APU system flight deck instrumentation (12) § 25.856(b), Improved Flammability standards for Thermal/acoustic insulation materials (documented in ELOS Memo TD0609IB-T-CI-5; Memo TD0609IB-T-CI-6 and Memo TD0609IB-T-CI-7). (13) § 25.785(d), Forward Facing Seat, over 18 degrees to aircraft centerline (documented in ELOS Memo TD0643IB-T-CI-9). (14) § 25.1457(d)(5) Cockpit Voice Recorder – Equivalent Level of Safety for 10 minute independent backup power requirement (documented in ELOS Memo TD0774IB-T-SA-1). (15) §§ 26.33, 26.35 Fuel Center Tank Flammability Reduction System (documented in ELOS Memo TD0547IB-T-P-1 (16) § 25.981(a)(3) Amendment. 25-102 Installation of Fuel Pump Ground Fault Interrupter (GFI) Devices (documented in ELOS Memo TD0764IB-T-P-1) A46NM 26 of 44 (17) § 25.1443(c) Minimum mass flow of supplemental oxygen on model A330 and A340 airplanes (documented in ELOS Memo AT10356IB-T-S-1) (18) § 25.1441(c) Crew determination of quantity of oxygen in passenger oxygen system on model A330 and A340 airplanes (documented in ELOS Memo AT10356IB-T-S-2) (19) §§ 25.811(g); 25.812(b)(1) Symbolic Exit Signs on Models A330 and A340 airplanes (documented in ELOS Memo TD00918IB-T-CS-1). For airplanes equipped with pictograms on exit marking signs and on exit location signs, the cabin crew in charge of the safety briefing should highlight these pictograms to the passengers prior to each takeoff and each landing. (20) § 25.811(e)(4) Emergency Exit Marking on model A330 and A340 airplanes (documented in ELOS Memo AT10899IB-T- CS-1) for airplanes with Airbus modification # 206893. (21) § 25.779(b)(1) Throttle Motion During Reduced (Flexible) Takeoff Thrust Operations and/or Go-Around documented in ELOS Memo TC0544IB-T-P-7 (22) § 25.1193(e)(3) Cowling and Nacelle Skin Fireproof Regions documented in ELOS Memo TC0544IB-T-P-31 (23) § 25.1549(a) Oil Temperature Indication documented in ELOS Memo AT10413IB-T-P-6 (24) § 25.1203(d) Rolls Royce Engine Turbine Overheat Detection (documented in ELOS Memo AT10413IB-T-P-7) (25) § 25.934 Thrust Reverser Testing documented in ELOS Memo AT10413IB-T-P-9 (26) § 25.1195(c) Fire Extinguishing Agent concentration documented in ELOS Memo AT10413IB-T-P-11 (27) §§ 25.1549(a), (b) and (c) Digital Only Display of Turbine Engine Intermediate (N2) and High (N3) Rotor Speeds documented in ELOS Memo AT10413IB-T-P-12 (28) §§ 25.1182(a) and 25.1195 through 25.1203 Nacelle Areas Behind Firewalls documented in ELOS Memo AT10413IB-T-P- 13 (29) § 25.1191(b)(1) Firewall Caps and Seals Fire Withstanding Capability documented in ELOS Memo AT10413IB-T-P-15 (30) §§ 25.1301 and 25.1309 Function and Installation, and Equipment, Systems, and Installation Requirements: Use of ARAC Recommendations documented in ELOS Memo AT10413IB-T-SA-1 (31) § 25.1383(b) Single Landing Light Switch documented in ELOS Memo AT10413IB-T-SE-1 (32) § K25.2.2(g) of Part 25 Appendix K, Early Extended Operations (ETOPS) Airplane Demonstration Tests documented in ELOS Memo AT11032IB-T-EE-5 Exemptions The full list of Exemptions applicable to the A330-841 is defined below: Exemption No. 17129 dated October 26, 2016. This Exemption from 14 CFR 25.98 l(a)(3) is granted to Airbus as it relates to the Model A330-300 fuel trim tank structural lightning protection (Airbus modification # 204495 “Stabilizers – Horizontal Stabilizer – Define lateral box for weight reduction”). Exemption No. 17581, dated September 29, 2017. This partial grant of exemption from Section §§ 25.841(a)(2)(i) and (ii), and (a)(3), Amendment 25-87, will permit cabin pressure altitude to exceed 40,000 feet for 1 minute, but not to exceed 41,500 feet for any duration, and permit cabin pressure altitude to exceed 25,000 feet for more than 2 minutes, but not more than 3 minutes, after decompression. Exemption No. 17601, dated October 13, 2017. This exemption is granted for the requirements of 14 CFR part 25, appendix K, se ction K25.1.4(a)(2) as they relate to concurrent power of the fuel boost pumps in each main fuel tank and will allow to show that the airplanes are capable of continuously providing fuel pressure to all engines when only powered by an independent electrical power sourc e other than the three power sources required in section K25.1.3(b) of appendix K, without maintaining simultaneous po wer to all individual fuel boost pumps. This exemption relates to Model A330 series airplanes ETOPS beyond 180 minutes approval. Airbus will comple te this under a post TC type design change. Exemption No. 18136, dated February 28, 2019. This exemption is granted for the requirements of 14 CFR 25.813(e), amendment 2 5- 116, and 14 CFR 121.310(f)(5) and (6) to the extent necessary to allow the installation of doors on mini-suites. Exemption No. 23131, dated November 06, 2024. This time limited exemption is granted for the requirements of 14 CFR 25.1438(b) to introduce the new bleed monitoring computer (BMC) software (SW) 5.0 (Airbus Modification # 210504). This exemption does not apply to airplanes on which both the BMC SW 5.0 (MOD 210504) and the high pressure bleed valve ( HPV) P/N 71070A030001 (MOD 210503) have been incorporated. This exemption terminates on September 30, 2027, unless sooner superseded or rescinded. Noise standards 14 CFR part 36. Amendments 36-1 through Amendment 36-31, for Stage 5. A46NM 27 of 44 Fuel venting and exhaust emissions standards 14 CFR part 34, Amendments 34-1 through 34-5A. Part 26 14 CFR part 26. Amendments 26-1 through 26-6. 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. At this time, the FAA identified the following subject for further review and evaluation: a) In-Flight Engine Restart 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 th e 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. Equipment • The basic required equipment as prescribed in the applicable airworthiness regulations (see Certification Basis) must be inst alled in the aircraft for certification. • Cabin furnishings, equipment and arrangement shall conform to the following specification: - 00F252K0005/C01 for cabin seats, - 00F252K0006/C01 for galley, - 00F252K0020/C01 for cabin attendant seat Airplane Flight Manual Airplane operation must be in accordance with the EASA Approved Airplane Flight Manual (AFM), US version, listed below, or la ter EASA approved revision applicable to the specific airplane model, modification status and serial number. Model A330-800 Airbus Document Reference Revision No. Date -841 STL 33000 1 February 12, 2020 Data Pertinent to All Model See Section VI, Data Pertinent to All Model A330-200, A330-200 Freighter, A330-300, A330-800 and A330-900 Series airplanes. For information on Fuel, Airspeed Limits, Center of Gravity Limits, Datum, Leveling Means, Minimum Crew, Maximum Operating Altitude, Control Surface Movements, Production Basis, Hydraulic Fluids, Auxiliary Power Unit (APU), Tires, Environmental requirements for noise, Manufacturer’s Serial Numbers, Service Information, information on Import Requirements and General Notes A46NM 28 of 44 V. Type A330-900 Series Transport Category Airplanes Airbus A330-941 - approved December 21, 2018 Model: Definition of Reference Airplane by Airbus Documents: A330-941 A330-941 Type Design, ref. 00G000A0941/C00 Issue 1, dated September 8, 2018, for type definition Engines Airplane Model Engine Model: Engine Type Certificate: A330-941 Two RR Trent 7000 turbojet engines FAA-Type Certificate E00076EN (EASA.E.036) Engine Limits Engine Limitations A330-941 RR 7000 FAA Data Sheet E00076EN Static Thrust at Sea Level • Take-off (5 mn)1 (flat rated 30ºC) • Max continuous (flat rated 25ºC) 72,834 lbs 65,005 lbs Maximum Engine Speed • N1 rpm (%) • N2 rpm (%) 2,683 (101.5%) 8,937 (103.5%) Maximum Gas Temperature • Take-off (5mn)1 • Maximum Continuous • Starting2 1,652º F (900º C) 1,562º F (850º C) 1,292º F (700º C) Maximum Oil Temperature (Supply Pump Outlet) ºC • Continuous Operation • Transient (15 mn max.) • Minimum Oil Pressure (PSI) 376º F (191º C) 385º F (196º C) 30.0 psid Approved oils Refer to the Engine Operating Instructions for A330/A340 for information on approved oil specifications for Trent 7000 Table references: (1) 10 minutes at take-off thrust allowed only in case of engine failure (at take-off or during go around). (2) 4 consecutive cycles of 2 minutes each. Maximum Weight • Maximum Take-Off Weight (MTOW): 251,000 kg / 553,360 lb • Maximum Landing Weight (MLW): 191,000 kg / 421,082 lb • Maximum Zero Fuel Weight (MZFW): 181,000 kg / 399,036 lb See applicable Airplane Flight Manual (AFM), as listed in ‘Operating and Service Instructions’, for configuration specific mass limitations and aircraft eligibility (Weight Variant). Number of Seats The maximum number of passengers approved for emergency evacuation is: - 375 passengers with a 3 pairs of Type A and 1 pair Type 1 exits configuration, and - 440 passengers with a 4 pairs of Type A exits configuration. A46NM 29 of 44 Maximum Baggage Cargo Compartment Maximum Load (kg / lb) Forward 22,861/ 50,400 Aft 18,507 / 40,801 Rear 3,468 / 7,646 For the positions and the loading conditions authorized in each position (references of containers, pallets and associated we ight) see weight and Balance Manual: A330-900 Airbus Document 00G080A3WBM/C9S Fuel Capacity 3 Tank Airplane Usable Fuel Unusable Fuel Tank liters (kg) gallons (lb) liters (kg) gallons (lb) Wing 91,300 (73,040) 24,119 (161,026) 190 (152) 50 (335) Center 41,560 (33,248) 10,980 (73,311) 83 (67) 22 (148) Trim Tank 6,230 (4,984) 1,646 (10,988) 6 (5) 1.6 (11) Total 139,090 (111,272) 36,744 (245,313) 279 (224) 73.7 (494) Certification Basis (A330-900) The FAA Certification basis for the Airbus Model A330-941 airplanes is defined as: The certification basis for the baseline Airbus Model A330 -300 series airplanes with Modification 203897, 203898, 203900 or 203899 (WV 080-083) and with Modification G3ActCT (Activation of center fuel tank ) as defined in Section III of this FAA TCDS A46NM for components or areas not affected by the change. Plus the following sections of 14 CFR part 25, Amendments 25-1 through 25-72, for which Airbus elects to comply to bring the baseline certification basis up to the same level as the A330-200 for components or areas not affected by the change and for secondary changes: 25.307(b)(c)(d), 25.343(b)(2) and (b)(3), 25.361(b)(c), 25.397, 25.459, 25.615 (Vertical Stabilizer Only), 25.693, 25.723(a)( c), 25.729, 25.731, 25.733(a)(e), 25.735, 25.772, 25.779, 25.783, 25.791, 25.1093, 25.1381, 25.1385, 25.1415, 25.1522, 25.1543 Plus the following sections of 14 CFR part25. Amendments 25-1 through 25-138 (i.e., the amendment in effect on the date of application) applied to the components and areas affected by the change: Paragraphs applicable to all A/C: 25.3, 25.21(a)(b)(c)(d)(e)(f), 25.23, 25.25, 25.27, 25.29, 25.101, 25.103(a)(c)(d), 25.105(b)(c)(d), 25.107 (a)(b)(c)(d)(e)(f)(g), 25.109, 25.111(a)(b)(d)(e), 25.113, 25.115, 25.117, 25.121(a), 25.123(a)(c), 25.145, 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, 25.253(a)(b), 25.255, 25.305(a)(b)(c)(f), 25.321, 25.333, 25.335(c)(d)(e), 25.337, 25.345(a)(b)(d), 25.349, 25.351, 25.365(a)(b)(d), 25.367, 25.427, 25.457, 25.471(a)(b), 25.473, 25.4 79, 25.481(a)(c), 25.483, 25.485, 25.489, 25.491, 25.493, 25.495, 25.499, 25.503, 25.507, 25.509, 25.511, 25.519, 25.623, 25.629, 25.683(a)(c), 25.703, 25.809(g), 25.841, 25.843, 25.901(c), 25.963 (Center Tank Structure Only), 25.967, 25.969, 25.971, 25.9 75, 25.1316, 25.1317, 25.1329(g), 25.1337, 25.1355, 25.1501, 25.1503, 25.1505, 25.1507, 25.1511, 25.1513, 25.1515, 25.1516, 25.1519, 25.1529, 25.1531, 25.1533, 25.1535, 25.1553, 25.1581, 25.1583, 25.1585, 25.1587. Paragraphs applicable to the engine installation (New Engine, Pylon, pre -cooler, air inlet and nacelle, Structural adaptation of the wing at the wing/pylon interface, Electro Pneumatic Bleed Air System): 25.301(b)(c), 25.303, 25.363, 25.365(e)(1), 25.561(c), 25.581, 25.601, 25.603, 25.605, 25.607, 25.609, 25.611, 25.613, 25.619 , 25.621, 25.625, 25.631, 25.721(b), 25.733(b)(c)(d), 25.779(b), 25.809(f)(1)(iii)(iv), 25.851(b), 25.863, 25.865, 25.867, 25.8 69, 25.899, 25.901, 25.903, 25.933(a), 25.934, 25.939(a)(c), 25.943, 25.951(a)(b)(2)(c), 25.952, 25.954, 25.955(a), 25.959, 25.96 1(a), 25.963, 25.981 (except for fuel system wiring changes outside the pylon area and fuel tank structural fastener changes), 25.993(a)(b)(c)(d)(e), 25.994, 25.995, 25.997, 25.999(b), 25.1001(a)(b), 25.1011, 25.1013, 25.1015, 25.1017, 25.1019, 25.1021, A46NM 30 of 44 25.1023, 25.1025, 25.1041, 25.1043, 25.1045, 25.1091(a)(c)(d)(e), 25.1093(b), 25.1103, 25.1121, 25.1123, 25.1141, 25.1143, 25.1145, 25.1155, 25.1163, 25.1165(a)(b)(c)(e)(f)(g)(h), 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, 25.1351, 25.1353, 25.1357, 25.1360(a), 25.1363, 25.1419 (for powerplant installation only), 25.1431, 25.1435(a), 25.1438, 25.1461, 25.1521, 25.1527, 25.1549, 25.1551, 25.1557(b), 25.1701, 25.1703, 25.1705, 25.1707, 25.1709, 25.1711, 25.1713, 25.1715, 25.1717, 25.1719, 25.1721(a)(b), 25.1723, 25.1725, 25.1727, 25.1729, 25.1731. Paragraphs applicable to aerodynamic changes (New winglet with wing span increase, Wing Aerodynamic clean up, Wing twist change, Wing engine interference, new navigation and strobe lights): 25.301(b)(c), 25.303, 25.363, 25.393, 25.581, 25.601, 25.603, 25.605, 25.607, 25.609, 25.611, 25.613, 25.619, 25.625, 25.631, 25.723(b), 25.863, 25.869, 25.899, 25.954, 25.959, 25.1001(a)(b), 25.1301, 25.1305, 25.1309, 25.1353, 25.1357, 25.1360(a), 25.1383(a), 25.1385(a)(b)(c)(d), 25.1387, 25.1389, 25.1391, 25.1393, 25.1395, 25.1397, 25.1401 (a)(b)(c)(d)(e)(f), 25.1403, 25.1431, 25.1438, 25.1525. 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 exception justifications in accordance with 14 CFR 21.101: • 25.103(b), 25.105(a), 25.111(c), 25.119, 25.121(b)(c)(d), 25.123(b), 25.125, 25.143, 25.207, 25.237, and 25.1419, Amendments 25-1 through 25-120, for “Flight in icing conditions.” FAA acceptance of this exception is based on compliance with EASA CRI B-07 Flight in Icing Conditions. • 25.571, Amendments 25-1 through 25-86, for “Damage tolerance and fatigue evaluation of structure.” FAA acceptance of this exception is based on compliance with 14 CFR part 26. • 25.981, Amendments 25-1 through 25-11, for the fuel system wiring changes outside the pylon area and the fuel tank structural fastener changes. FAA acceptance of this exception is based on Fuel Quantity Indicating System (FQIS) and Fuel Level Sensor System (FLSS) wiring isolation with protective sleeving and closely spaced ties in the S-routes with labels identifying the fuel system wiring and Airbus compliance with FAA Policy Statement ANM-112-08-002 “Policy on Issuance of Special Conditions and Exemptions Related to Lightning Protection of Fuel Tank Structure,” dated May 26, 2009, for the fuel tank structural fastener changes. • Appendix H to part 25, Amendments 25 -1 through 25-54, for Instructions for Continued Airworthiness. FAA acceptance of this exception is based on compliance with 14 CFR part 26. Plus the following sections of 14 CFR part 25, Amendments 25-1 through 25-139, for which Airbus elects to comply for harmonization reasons: 25.307(a) and 25.683(b) Plus the following sections of 14 CFR part 25, Amendments 25-1 through 25-141, for which Airbus elects to comply for harmonization reasons: 25.331, 25.341, 25.343(a) and (b)(1), 25.361(a), 25.362, 25.371, 25.373, 25.391 (for modified control surfaces only), 25.415 (for modified control surfaces only), and 25.1517 Plus the following optional sections of 14 CFR part 25 for which Airbus elects to comply as indicated below: 25.1535, Amendments 25-1 through 25-138 Plus the following optional sections of 14 CFR part 25 for which Airbus elects to comply as indicated below for A/C with MOD 210548: 25.1302, Amendments 25-1 through 25-138 Special Conditions The full list of Special Conditions applicable to the A330-941 is defined below: 1. Special Conditions No. 25 -ANM-77 published in the Federal Register on October 19, 1993, (Docket No. NM 86, Special Conditions No. 25-ANM-77): (1) Operation without Normal Electrical Power (8) Limit Pilot Forces (2) Electronic Flight Control System (EFCS) failures and Mode Annunciation (9) Tail plane Tank Emergency Landing Loads - (3) Command Signal Integrity (10) Limit Engine Torque (4) Protection From Lightning and Unwanted Effects of High Intensity Radiated Fields (HIRF) (11) Flight Characteristics A46NM 31 of 44 (6) Design Dive Speed (12) Flight Envelope Protection (7) Design Maneuver Requirements (13) Side Stick Controllers 2. Special Condition 25-281-SC published in the Federal Register on January 6, 2005 (Docket No. NM287): Lower Deck Mobile Crew Rest (LD-MCR) Compartment – Optional modification # 206615. 3. Special Condition 25-395-SC published in the Federal Register November 03, 2009 (Docket No. NM-418): Seats With Inflatable Lap Belts. 4. Special Condition 25-400 -SC published in the Federal Register January 4, 2010 (Docket No. NM-424): Seats with Non-Traditional, Large, Non-Metallic Panels. 5. Special Condition 25-678-SC published in the Federal Register May 26, 2017 (Docket No. FAA-2017-0369): Non-Rechargeable Lithium Batteries This Special condition is effective to design changes applied for after May 26, 2017. See the applicability section of this special condition for more information on which design changes must meet it. 6. Special Condition 25-696-SC published in Federal Register on August 4, 2017 (Docket No. FAA–2017–0356): Interaction of Systems and Structure. 7. Special Condition 25-708-SC published in Federal Register on January 16, 2018 (Docket No. FAA–2017–0483): Electronic Flight Control System Lateral-Directional and Longitudinal Stability and Low Energy Awareness. 8. Special Condition 25-709-SC published in Federal Register on January 4, 2018 (Docket No. FAA–2017–0482): Use of High Incidence Protection and Alpha Floor Systems. 9. Special Condition 25-739-SC published in the Federal Register on December 26, 2018 (Docket No. FAA–2018–1053): Electronic System Security Protection from Unauthorized External Access. This Special Condition apply to installation and activation of electronic network system architecture or Flight Operations and Maintenance Exchanger (FOMAX) equipment (Airbus modification # 207456). 10. Special Condition 25-740-SC published in the Federal Register on December 26, 2018 (Docket No. FAA–2018–1054): Electronic System Security Protection from Unauthorized Internal Access. This Special Condition apply to installation and activation of electronic network system architecture or Flight Operations and Maintenance Exchanger (FOMAX) equipment (Airbus modification # 207456). 11. Special Condition 25-747-SC published in the Federal Register on May 29, 2019 (Docket No. FAA–2019–0235): Seats with Inertia Locking Devices (Airbus modification # 207317). Equivalent Safety Findings (ELOS) The full list of ELOS applicable to the A330-941 is defined below: *(1) § 25.335(d) for design airspeeds *(2) § 25.341 for gust loads *(3) § 25.345 for high lift devices *(4) § 25.349 for control surface loads *(5) § 25.351(b) for unsymmetrical loads *(6) § 25.371 for gyroscopic loads *(7) § 25.373 for speed control devices *(8) § 25.391 for control surface loads * These ELOS findings do not apply where the corresponding requirements of Amendment 25-141 are applied. (9) §§ 25.101(I); 25.105(c)(1); 25.109(a)(b)(c)(d)(e)(f); 25.113(a)(b)(c); 25.115(a); 25.735(f)(g)(h)(b) for rejected takeoff and landing performance (10) §§ 25.1305: 25.1501(b) for APU system flight deck instrumentation. (11) § 25.856(b), Improved Flammability standards for Thermal/acoustic insulation materials (documented in ELOS Memo TD0609IB-T-CI-5; Memo TD0609IB-T-CI-6 and Memo TD0609IB-T-CI-7). (12) § 25.785(d), Forward Facing Seat, over 18 degrees to aircraft centerline (documented in ELOS Memo TD0643IB-T-CI-9). (13) § 25.1457(d)(5) Cockpit Voice Recorder – Equivalent Level of Safety for 10 minute independent backup power requirement (documented in ELOS Memo TD0774IB-T-SA-1). A46NM 32 of 44 (14) § 25.1443(c) Minimum mass flow of supplemental oxygen on model A330 and A340 airplanes (documented in ELOS Memo AT10356IB-T-S-1) (15) § 25.1441(c) Crew determination of quantity of oxygen in passenger oxygen system on model A330 and A340 airplanes (documented in ELOS Memo AT10356IB-T-S-2). (16) §§ 25.811(g); 25.812(b)(1) Symbolic Exit Signs on Models A330 and A340 airplanes (documented in ELOS Memo TD00918IB-T-CS-1). For airplanes equipped with pictograms on exit marking signs and on exit location signs, the cabin crew in charge of the safety briefing should highlight these pictograms to the passengers prior to each takeoff and each landing (17) § 25.811(e)(4) Emergency Exit Marking on model A330 and A340 airplanes (documented in ELOS Memo AT10899IB-T- CS-1) for airplanes with Airbus modification # 206893. (18) §§ 26.33 and 26.35 Fuel Tank Flammability Reduction Airplane Descent Profile documented in ELOS Memo TD0547IB- T-P-1; (19) § 25.779(b)(1) Throttle Motion During Reduced (Flexible) Takeoff Thrust Operations and/or Go-Around documented in ELOS Memo TC0544IB-T-P-7 (20) § 25.933(a)(1)(ii) Flight Critical Thrust Reverser documented in ELOS Memo TC0544IB-T-P-10 (21) § 25.1193(e)(3) Cowling and Nacelle Skin Fireproof Regions documented in ELOS Memo TC0544IB-T-P-31 (22) § 25.1549(a) Oil Temperature Indication documented in ELOS Memo AT10413IB-T-P-6 (23) § 25.934 Thrust Reverser Testing documented in ELOS Memo AT10413IB-T-P-9 (24) § 25.1195(c) Fire Extinguishing Agent concentration documented in ELOS Memo AT10413IB-T-P-11 (25) §§ 25.1549(a), (b) and (c) Digital Only Display of Turbine Engine Intermediate (N2) and High(N3) Rotor Speeds documented in ELOS Memo AT10413B-T-P-12 (26) § 25.1203(d) Rolls Royce Engine Turbine Overheat Detection (documented in ELOS Memo AT10413IB-T-P-7) (27) §§ 25.1182(a) and 25.1195 through 25.1203 Nacelle Areas Behind Firewalls documented in ELOS Memo AT10413IB-T-P- 13 (28) § 25.1191(b)(1) Firewall Caps and Seals Fire Withstanding Capability documented in ELOS Memo AT10413IB-T-P-15 (29) §§ 25.1301 and 25.1309 Function and Installation, and Equipment, Systems, and Installation Requirements: Use of ARAC Recommendations documented in ELOS Memo AT10413IB-T-SA-1 (30) § 25.1383(b) Single Landing Light Switch documented in ELOS Memo AT10413IB-T-SE-1 (31) § K25.2.2(g) of Part 25 Appendix K, Early Extended Operations (ETOPS) Airplane Demonstration Tests documented in ELOS Memo AT11032IB-T-EE-5 (32) § 25.1563 Airspeed Placard documented in ELOS Memorandum AT11145IB-T-25.1563-1 Exemptions The full list of Exemptions applicable to the A330-941 is defined below: Exemption No. 17129 dated October 26, 2016. This Exemption from 14 CFR 25.98 l(a)(3) is granted to Airbus as it relates to the Model A330-300 fuel trim tank structural lightning protection (Airbus modification # 204495 “Stabilizers – Horizontal Stabilizer – Define lateral box for weight reduction”). Exemption No. 17581, dated September 29, 2017. This partial grant of exemption from Section §§ 25.841(a)(2)(i) and (ii), and (a)(3), Amendment 25-87, will permit cabin pressure altitude to exceed 40,000 feet for 1 minute, but not to exceed 41,500 feet for any duration, and permit cabin pressure altitude to exceed 25,000 feet for more than 2 minutes, but not more than 3 minutes, after decompression. Exemption No. 17601, dated October 13, 2017. This exemption is granted for the requirements of 14 CFR part 25, appendix K, se ction K25.1.4(a)(2) as they relate to concurrent power of the fuel boost pumps in each main fuel tank and will allow to show that the airplanes are capable of continuously providing fuel pressure to all engines when only powered by an independent electrical power sourc e other than the three power sources required in section K25.1.3(b) of appendix K, without maintaining simultaneous po wer to all individual fuel boost pumps. This exemption relates to Model A330 series airplanes ETOPS beyond 180 minutes approval. Airbus will comple te this under a post TC type design change. Exemption No. 18136, dated February 28, 2019. This exemption is granted for the requirements of 14 CFR 25.813(e), amendment 2 5- 116, and 14 CFR 121.310(f)(5) and (6) to the extent necessary to allow the installation of doors on mini-suites. Exemption No. 23131, dated November 06, 2024. This time limited exemption is granted for the requirements of 14 CFR 25.1438(b) to introduce the new bleed monitoring computer (BMC) software (SW) 5.0 (Airbus Modification # 210504). This exemption does not apply A46NM 33 of 44 to airplanes on which both the BMC SW 5.0 (MOD 210504) and the high pressure bleed valve ( HPV) P/N 71070A030001 (MOD 210503) have been incorporated. This exemption terminates on September 30, 2027, unless sooner superseded or rescinded. Noise standards 14 CFR part 36. Amendments 36-1 through Amendment 36-31. for Stage 5. Fuel venting and exhaust emissions standards 14 CFR part 34, Amendments 34-1 through 34-5A. Part 26 14 CFR part 26. Amendments 26-1 through 26-6. Additional Design Requirements and Conditions Compliance with the established basis for type certification notwithstanding, § 21.21 (b)(2) precludes issuance of a type cer tificate if there is any feature or characteristic that would make the product unsafe. At this time, the FAA identified the following subject for further review and evaluation: a) In-Flight Engine Restart A minimum restart capability after an all engines out scenario must be established under the following conditions using proce dures 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. Equipment • The basic required equipment as prescribed in the applicable airworthiness regulations (see Certification Basis) must be inst alled in the aircraft for certification. • Cabin furnishings, equipment and arrangement shall conform to the following specification: - 00F252K0005/C01 for cabin seats, - 00F252K0006/C01 for galley, - 00F252K0020/C01 for cabin attendant seat Airplane Flight Manual Airplane operation must be in accordance with the EASA Approved Airplane Flight Manual (AFM), US version, listed below, or later EASA approved revision applicable to the specific airplane model, modification status and serial number. Model A330-900 Airbus Document Reference Revision No. Date -941 STL 33000 1 September, 2018 Data Pertinent to All Model See Section VI, Data Pertinent to All Model A330-200, A330-200 Freighter, A330-300, A330-800 and A330-900 Series airplanes. For information on Fuel, Airspeed Limits, Center of Gravity Limits, Datum, Leveling Means, Minimum Crew, Maximum Operating Altitude, Control Surf ace Movements, Production Basis , Hydraulic Fluids, Auxiliary Power Unit (APU), Tires, Environmental requirements for noise, Manufacturer’s Serial Numbers, Service Information, information on Import Requirements and General Notes A46NM 34 of 44 VI. Data Pertinent to All Model A330-200, A330-200 Freighter, A330-300, A330-800 and A330-900 Series airplanes: Fuel Specification Aircraft Nomenclature United States France United Kingdom A330-201 A330-202 A330-203 A330-301 A330-302 A330-303 Kerosene (conform to GE specification D50TF2 with current exception of JP4 and JET B) ASTM D 1655 (JET A) (JET A1) AIR 3405C DERD 2494/2453 A330-223 A330-223F A330-321 A330-322 A330-323 Fuel and fuel additives conforming to the latest applicable issue of FAA approved Pratt & Whitney Turbojet Engine Service Bulletin 2016 may be used separately or mixed in any proportions without adversely affecting the engine operation or power output. A330-243 A330-243F A330-341 A330-342 A330-343 A330-841 A330-941 Approved fuel and additives are identified in the relevant Operating instructions defined in the Rolls Royce Manual F-Trent – A330 (a) Additives: According to GE "Specific Operating Instructions", installation manual. The above mentioned fuels are also suitable for the APU. Airspeed Limits (Indicated Airspeed, IAS, unless otherwise stated) • Maximum Operating Limit Speed/Mach, VMO/MMO 330 KIAS / .86 • Design Diving Speed, VD/MD 365 KIAS / .93 • Design Maneuvering Speed, VA Refer to AFM Performance Section • Maximum Flaps/Slats Extended Speed or Operating Speed, VFE Configuration Slats / Flaps / Ailerons (º) VFE (kt) A330-200/-200F/-300 A330-800/-900 1 1 + F 16/0/0 16/8/0 16/8/5 240 215 205 240 215 205 Intermediate Approach Take-off Take-off 2 20/14/10 20/14/10 20/14/0 196 - - - 196 196 Take-off and Approach Take-off Approach 3 23/22/10 23/22/10 23/22/0 186 - - - 186 186 Take-off, Approach, and Landing Take-off Approach FULL 23/32/10 23/22/0 180 - - 180 Landing • Minimum Control Speed, VMC Refer to AFM performance Section. (Performance Engineering Program/OCTOPUS) • Landing Gear Speeds: - Maximum Speed with Landing Gear Operating (Extension and Retraction) VLO 250 KIAS / .55M - Maximum Speed with Landing Gear Locked Down, VLE 250 KIAS / .55M - Tire Limit Speed (Ground Speed) 203 KIAS (235mph) A46NM 35 of 44 Center of Gravity Limits Refer to EASA-Approved Airplane Flight Manual, US Version, Limitations Section for center of gravity envelope. Note: 0% MAC is located 1359.59 in. (34.532m) from the datum line Datum The aircraft reference zero datum point is located 251.29 in. (6.3825 m) forward of the nose section, 275.6 in. (7m) under th e fuselage centerline (datum line). Leveling Means Inclinometer on cabin seat track rails (refer to WBM chapter 1.80). Minimum Crew 2 – Pilots Maximum Operating Altitude Basic: 41,100 feet (12,527 m) slats and flaps retracted (clean) Option: 41,450 feet (12,634 m) slats and flaps retracted (clean) with modification 52536 20,000 feet (6,096 m) slats or slats/flaps extended. Control Surface Movements Total one-way travel in each direction of each movable control surface on the aircraft: Control Surface Maximum Travel A330-200/-200F/-300 A330-800/-900 Aileron +25 /- 25º +25 /- 25º #1 Spoilers Speed Brake 23º Speed Brake 23º Lift Dumper 35º Lift Dumper 35º #2,3 Spoilers Roll 35º Roll 35º Speed Brake 30º Speed Brake 30º Emergency Descent: up to 40° Lift Dumper 50º Lift Dumper 50º #4,5,6 Spoilers Roll 35º Roll 35º Speed Brake 30º Speed Brake 30º Emergency Descent: up to 40° Lift Dumper 50º Lift Dumper 50º Aileron Droop 10º 10º take-off 0° approach Flaps 32º 32º Slats 23º 23º Stabilizers +2º/-14º +2º/-14º Elevator +15º/-30º +15º/-30º Rudder +30º/-30º +30º/-30º Environmental requirements for noise A330-201, A330-202, A330-203 and A330-223 14 CFR Part 36, effective December 1, 1969, including Amendments 36-1 through 36-21. Recertified to 14 CFR part 36 Stage 4, effective December 1, 1969, as amended by amendments 36-1 through 36-28. A330-243 fitted with RR Trent 772B-60 engines are compliant with Stage 5 noise requirements of 14 CFR part 36. A330-301, A330-302, A330-303, A330-321, A330-322, and A330-323 14 CFR Part 36 as amended by amendments 36-1 through 36-20. Recertified to 14 CFR part 36 Stage 4, effective December 1, 1969, as amended by amendments 36-1 through 36-28. A330-341 fitted with RR Trent 768 -60 engines, A330 -342 fitted with RR Trent 772 -60 engines and A330 -343 fitted with RR Trent 772B-60 engines are compliant with Stage 5 noise requirements of 14 CFR part 36. A46NM 36 of 44 A330-200 Freighter A330-223F fitted with PW4170 engines are compliant with Stage 4 noise requirements of 14 CFR part 36 as amended by 36-1 through 36-28. A330-243F fitted with RR Trent 772B-60 engines are compliant with Stage 5 noise requirements of 14 CFR part 36. A330-800 14 CFR Part 36 as amended by amendments 36-1 through 36-31, compliant with Stage 5 noise requirements of 14 CFR part 36. A330-900 14 CFR Part 36 as amended by amendments 36-1 through 36-31, compliant with Stage 5 noise requirements of 14 CFR part 36. Manufacturer’s Serial Numbers/Production Basis From July 21, 2008, A330 aircraft, all series and models, are produced in France under production approval reference EASA.21G.0001 issued by EASA on July 21, 2008, prior that date all A330 aircraft, all series and models, are produced in France under produ ction approval FR.21G.0035 (formerly FG 035) issued by the DGAC (on behalf of EASA) to Airbus. Import Requirements The FAA can issue a U.S. airworthiness certificate based on either an EASA Export Certificate of Airworthiness (Export C of A) signed by a representative of the European Union Aviation Safety Agency (EASA), or a French "Certificat de Navigabilite pour Exportation" signed by a representative of the Direction Generale de 'Aviation Civile (DGAC) of France on behalf of the European Community. Refer to the applicable bilateral agreement to verify eligibility for import based on the scope of the agreement, to identify any required statements on the export certificate of airworthiness (or equivalent document), and for procedures for coordinating e xceptions to conformity statements on these documents. Refer to FAA Order 8130.2, Airworthiness Certification of Aircraft , provisions for Import Aircraft, for requirements for issuance of an airworthiness certificate. The U.S. airworthiness certification basis for aircraft type certificated under 14CFR 21.29 and exported by the country of manufacture is §§ 21.183(c) or 21.185(c). The U.S. airworthiness certification basis for aircraft type certificated under § 21.29 exported from countries other than the country manufacture (e.g., third party country) is §§ 21.183(d) or 21.185(b). These sections provide that U.S. airworthiness certificates are issued only if the Administrator finds “that the aircraft conforms to the type design and is in a condition for safe operation.” Notwithstanding that §§ 21.183(d) and 21.185(b) do not specifically address or require certification by the foreign civil airworthiness authority of the country of manufacture, such certification is the only practical way for an applicant to show, and the FAA t o find conformity to the FAA-approved type design and condition for safe operation. FAA Required Modification List for Airbus Model A330 Aircraft Prior to issuance of a Standard Airworthiness Certificate on Airbus A330 -200 or A330-300 model aircraft, all modifications shown on the (Model A330) Required Modification List (RML) with compliance times already past, must be accomplished before the aircraft can be found to be in a condition for safe operation. RML modifications with compliance times already past means that relative to the date of issuance of an Airworthiness Certificate for an individual aircraft, the compliance time of the RML item in calendar time and/or flight hours and/or flight cycles has been exceeded. All future required modifications shown on the RML must be incorporated into the operator’s maintenance or inspection program pri or to placement of the aircraft into operation [just as for future airworthiness limitations listed in the Airworthiness Limitat ion Section (ALS)]. These future RML modifications must be incorporated prior to the compliance time specified in the RML and must remain with the airplane records. In the event of any transfer of the airplane to another operator these RML requirements must continue to be complied with and incorporated into the new operator’s maintenance program. Future RML modifications means that relative to the date of issuance of an Airworthiness Certificate for an individual aircra ft, the compliance time of the RML item in calendar time and/or flight hours and/or flight cycles has not yet been exceeded. The RML was finalized through its publication in TCDS Revision 4 and requirements will not be added by later TCDS revisions. Therefore, the RML in TCDS A46NM Revision 4 or any later TCDS revision are equivalent and acceptable for compliance. All future modifications that the FAA determines must be accomplished on U.S. registered aircraft will be addressed by issuance of an Airworthiness Directive (AD). A46NM 37 of 44 Authority for these required modifications is given per the airworthiness certification provisions of 49 U.S.C. 44704 (c), wh ich states "the Administrator may include in an airworthiness certificate terms required in the interest of safety". “Terms requir ed in the interest of safety” include actions to correct unsafe conditions issued by the foreign authority of the state of design that also meet FAA criteria for corrective action. This law also gives the FAA the authority to adopt § 21.183(c) and (d), wh ich form the regulatory basis for the issue of standard U.S. airworthiness certificates on imported products. The modifications identified in the list below are required in the interest of safety and are necessary for this airplane to be in a condition for safe operation. A Notice of Policy Statement announcing the FAA’s policy with respect to foreign mandatory continued airworthiness informatio n, when no aircraft of the affected design are currently operating in the U.S. was published in the Federal Register on May 11, 1998, docket 98-11648. Additional guidance is contained in FAA Advisory Circular (AC) 21 -23, Airworthiness Certification of Civil Aircraft, Engines, Propellers, and Related Products Imported into the United States. Alternative Methods of Compliance to an RML modification: For each RML modification, an alternative method of compliance (AMOC) or adjustment of the compliance time may be used if approved by the Manager, Large Aircraft Section, International Validations Branch, Compliance & Airworthiness Division, Aircraft Certification Service, 2200 South 216th Street Des Moines, Washington 98198, telephone (206)-231-3219. Operators shall submit their request through an appropriate FAA Principle Maintenance Inspector, who may add comments and then send it to the Manager, Large Aircraft Section, International Validations Branch. FAA Compliance findings to the A330 RML: The FAA has accepted: (1) Model A330 -323 aircraft in the Airbus as -delivered configuration for MSN 524 and on as compliant with the applicable modifications of the A330 RML. FAA acceptance is based on the Airbus statement to the FAA (ref. Airbus letter EAL G01M03003568 issue 2, dated June 24, 2003) that the RML modifications applicable to model A330 -323 aircraft are either part of the FAA approved type design (ref. AI/EA -N 415.1630/99 Issue 1, dated July 20, 1999), required to be installed at aircraft delivery by DGAC/EASA AD, or required to be installed by Airbus on all A330-323 aircraft at time of delivery. (2) Model A330-223 aircraft in the Airbus as-delivered configuration for MSN 343 and from MSN 609 and on as compliant with the applicable modifications of the A330 RML. FAA acceptance is based on the Airbus statement to the FAA (ref. Airbus letters EAL G03D0415493, dated July 9, 2004 and G01ME1249802 Issue 2, dated July 26, 2012) that the RML modifications applicable to model A330-223 aircraft are either part of the FAA approved type design (ref. AI/EA -N 415.1223/98 Issue 2, dated August 20, 1998), required to be installed at aircraft delivery by DGAC/EASA AD, or required to be installed by Airbus on all A330 -223 aircraft at time of delivery. (3) Model A330-302 and -303 aircraft in the Airbus as-delivered configuration as compliant with the applicable modifications of the A330 RML. FAA acceptance is based on the Airbus statement to the FAA (ref. Airbus letter EAL G03D07012703 (for the -302) and EAL G03D07012712 (for the -303), each dated June 8, 2007) that the RML modifications applicable to model A330-302 and -303 aircraft are either part of the FAA approved type design (ref. EAL M05000400 and EAL M05000400; both at Issue 03 and dated May 2006) , required to be installed at aircraft delivery by DGAC AD, or required to be installed by Airbus on all Model A330-302 and -303 aircraft at time of delivery. (4) Model A330-202 aircraft in the Airbus as -delivered configuration (except for MSN’s 205, 211, 269 and 272) as compliant with the applicable modifications of the A330 RML. FAA acceptance is based on the Airbus statement to the FAA (ref. Airbus letter EAL LR01M08013880, dated June 20, 2008) that the RML modifications applicable to model A330-202 aircraft are either part of the FAA approved type design (ref. AI/EA-N 415.0531/98 Issue 3, dated May 25, 1998), required to be installed at aircraft delivery by DGAC/EASA AD, or required to be installed by Airbus on all A330-202 aircraft at time of delivery. (5) Model A330-243 aircraft in the Airbus as-delivered configuration (except for MSN’s 248, 250, 251, 254, 261, 265, 271 and 276) as compliant with the applicable modifications of the A330 RML. FAA acceptance is based on the Airbus statement to the FAA (ref. Airbus letter EAL LR01M08019406, dated August 07, 2008) that the RML modifications applicable to model A330 -243 aircraft are either part of the FAA approved type design (ref. AI/EA -N 415.2406/98 Issue 1, dated December 11, 1998), required to be installed at aircraft delivery by DGAC/EASA AD, or required to be installed by Airbus on all A330 -243 aircraft at time of delivery. (6) Model A330-343 aircraft in the Airbus as -delivered configuration as compliant with the applicable modifications of the A330 RML. FAA acceptance is based on the Airbus statement to the FAA (ref. Airbus letter EAL_LR01M10004733, dated March 03, 2010) that th e RML modifications applicable to model A330 -343 aircraft are either part of the FAA approved type design (ref. AIAI/EA-N 415.2027/99 Issue 1, dated October 22, 1999), required to be installed at aircraft delivery by DGAC/EASA AD, or required to be installed by Airbus on all A330-343 aircraft at time of delivery. FAA Required Modification List(RML) for the Airbus Model A330 Aircraft: The RML for the A330 is composed of items 1A through 40B as listed on the following pages. A46NM 38 of 44 RML # DGAC CN # Mod # Mandatory Action Applicable To: S/B # S/B REV(s) Compliance Time 1A 1996-006- 024(B)R1 42409 FUSELAGE - REINFORCE JOINT AT FRAMES 48 - 53.2 Airplanes without mod 43475 or without SB A330- 21-3027 53-3015 1 or higher Frames 53/53.1/53.2: Prior to 5800 total flight cycles. For frames 48 to 52: Prior to 15600 total flight cycles. 1B 1996-006- 024(B)R1 42409 FUSELAGE - REINFORCE JOINT AT FRAMES 48 - 53.2 Airplanes with mod 43475 or with SB A330-21-3027 53-3015 1 or higher Frames 53/53.1/53.2 prior to 5300 total flight cycles. For frames 48 to 52 prior to 14100 total flight cycles. 2 1997-265- 056(B)R1 N/A REVISE AMM AIRWORTHINESS LIMITS. ALL Model A330 Airplanes AMM CHAPTER 5 8 or higher Prior to C of A Issuance 3 1998-539- 088(B) N/A REPLACE FRANKENJURA EYE- END ON ELEVATOR SERVOCONTRLS ALL Model A330 Airplanes AOT 27-24 1 or higher Prior to 7/09/99 or C of A Issuance; whichever occurs later 4 1999-111- 093(B) 45870 AND 46231 AND 46891 INSTALL WIRING FOR E-BRAKE SHUTOFF VALVE ALL Model A330 Airplanes 29-3054 AND 32- 3083R2 3054: 0 or higher 3083: 2 or higher Prior to 7/31/01 or C of A Issuance; whichever occurs later 5 1999-123- 092(B) 43724, OR 44661, OR 44662 FLIGHT MANAGEMENT COMPUTER REPLACEMENT ALL Model A330 Airplanes 22-3011, OR 22- 3009, OR 22-3010 All SB’s revision 1 or higher Prior to 6/30/99 or C of A Issuance; whichever occurs later 6 1999-142- 097(B) 46170, OR 46596 FLIGHT CONTROL UNIT CHANGE Airplanes with Mod. 44887 OR with SB 22-3012 22-3021, OR 22-3020 1 or higher Prior to 6/30/99 or C of A Issuance; whichever occurs later 7 1999-144- 094(B)R1 45977 REPLACE RAT ACTUATOR Airplanes with Sundstrand RAT 29-3057 1 or higher Prior to 12/31/00 or C of A Issuance; whichever occurs later 8 1999-331- 098(B) 42447 REPLACE NLG HINGE FITTING BRACKETS ALL Model A330 Airplanes 52-3046 1 or higher Prior to 01/21/01 or C of A Issuance; whichever occurs later 9A 1999-350- 100(B)R1 46904, AND 46905 REPLACE PIVOT PINS & BELLCRANK ASSEMBLIES -202, -223,-243, - 323, -343 32-3095 1 or higher The Later of (a) and (b): (a) Prior to 4800 total flight cycles or within 5 years since new; which ever occurs first; and (b) Prior to 06/08/01 9B 1999-350- 100(B)R1 46902, AND 46903 REPLACE PIVOT PINS & BELLCRANK ASSEMBLIES ALL Model A330 Airplanes 32-3096 1 or higher Prior to 10 years since new or C of A Issuance; whichever occurs later 9C 1999-350- 100(B)R1 46904, AND 46905 REPLACE PIVOT PINS & BELLCRANK ASSEMBLIES -301, -321, -322, - 341, -342 32-3095 1 or higher The Later of (a) and (b): (a) Prior to 6500 total flight cycles or within 5 years since new; which ever occurs first; and (b) Prior to 06/08/01 10A 1999-406- 103(B) 45307 REPLACE HORIZONTAL HYDRAULIC BRACKET All Airplanes, except –202, with mod 43475 OR with SB 21-3027 53-3088 0 or higher Prior to 7880 total flight cycles or 30700 total flight hrs; whichever occurs first 10B 1999-406- 103(B) 45307 REPLACE HORIZONTAL HYDRAULIC BRACKET All Airplanes, except –202, without mod 43475 OR without SB 21- 3027 53-3088 0 or higher Prior to 8620 total flight cycles or 33600 total flight hrs; whichever occurs first A46NM 39 of 44 RML # DGAC CN # Mod # Mandatory Action Applicable To: S/B # S/B REV(s) Compliance Time 10C 1999-406- 103(B) 45307 REPLACE HORIZONTAL HYDRAULIC BRACKET -202 53-3088 0 or higher Prior to 8540 total flight cycles or 33300 total flight hrs, whichever occurs first 11 1999-442- 104(B) 46820, OR 46865 PASSENGER/ CREW DOOR FRAME LININGS ALL Airplanes with mod 44461 OR 44462 OR 44463 OR 44464 OR 44465 25-3096 1 or higher Prior to 11/03/05 or C of A Issuance; whichever occurs later 12A 1999-449- 105(B) 45899 REINFORCE FRAME 40 -202, -223 53-3093 2 or higher Prior to 9700 Total flight cycles or 28800 total flight hours; whichever occurs first 12B 1999-449- 105(B) 45899 REINFORCE FRAME 40 -301, -321,-322, -341, -342 53-3093 1 or higher Prior to 7320 total flight cycles or 26130 total flight Hours; whichever occurs first 13 1999-508- 106(B) 41652, OR 43904 MODIFY LOWER SECTIONS OF FRAME 48 TO 53.2 ALL Model A330 Airplanes 53-3062 0 or higher Prior to 2300 Total flight cycles or C of A Issuance; whichever occurs later 14 95-053- 009(B)R3 44049 REPLACE HYDRAULIC SENSE LINES Airplanes equipped with PW model 4164 or 4168 engines 29-3019 1 or higher Prior to 10/31/97 or C of A Issuance; whichever occurs later 15 95-248- 022(B) 42607 MOD - FUSELAGE STRINGER 39 ALL Model A330 Airplanes 53-3021 0 or higher Prior to 3800 total flight cycles 16 96-106- 030(B) 41849 OR 43364 AFT CARGO COMPARTMENT DOOR ALL Model A330 Airplanes 52-3023 0 or higher Prior to 6000 total flight cycles 17 96-134- 031(B)R2 AND 97-266- 057(B) [45271]; OR [44143 AND SB- A330- 32- 3070R0] LANDING GEAR FREE FALL EXTENSION ELECTRIC CIRCUIT ALL Model A330 Airplanes [32- 3048R3] OR [32- 3048R0, R1 or R2 AND 32-3070R0) -3048:3 or higher, OR 3048: 0,1, or 2 AND 3070: 0 or higher Prior to 3/23/99 or C of A Issuance; whichever occurs later 18 96-136- 032(B)R1 43689 AND 44603 ELECTRICAL POWER- APU FUEL PUMPS ELEC SUPPLY ALL Model A330 Airplanes 28-3041 3 or higher Prior to 3/1/98 or C of A Issuance; whichever occurs later 19 96-159- 033(B)R2 44173, OR 44237 MLG- SHORTENING MECHANISM BELLCRANK ALL Model A330 Airplanes without Mod 43029 installed 32-3047 2 or higher Prior to 1/07/99 or C of A Issuance; whichever occurs later 20 96-184- 036(B)R2 46558 ICE PROTECTION- WING ANTI ICE VALVES ALL Model A330 Airplanes S/B 30- 3020 -3020: 0 or higher Prior to C of A Issuance 21 97-004- 041(B) 43697, OR 43761 REAR FUSELAGE CARGO DOOR FRAME ALL Model A330 Airplanes 53-3048 0 or higher Prior to 7000 total flight cycles 22 97-154- 049(B)R1 44457 AND 45022 RADIO ANTENNA ALTIMETER "THOMSON" ALL Model A330 Airplanes fitted with Radio Altimeter P/N 9599-607-19501 34-3044 AND 21-3053 AND 92-3017 All S/Bs: 0 or higher Prior to 10/31/98 or C of A Issuance; whichever occurs later 23 97-178- 051(B) 44918 A/C RAM AIR OUTLET DUCT ALL Model A330 Airplanes 21-3059 0 or higher Prior to 6/30/98 or C of A Issuance; whichever occurs later 24 97-179- 052(B) 45088, OR 45087 FWD FLAP TRACKS ALL Model A330 Airplanes 57-3048 1 or higher Prior to 3500 total flight hours A46NM 40 of 44 RML # DGAC CN # Mod # Mandatory Action Applicable To: S/B # S/B REV(s) Compliance Time 25 97-204- 053(B) 41856, OR 45224 FWD FUSELAGE- REINFORCE DBLR/OUTFLOW VALVE ALL Model A330 Airplanes 53-3084 0 or higher Prior to 7500 total flight cycles 26 97-361- 058(B)R2 44511 AND 41671 MLG-SHORTENING MECHANISM BELLCRANK BOLTS ALL Model A330 Airplanes without Mod 43029 installed 32-3056 1 or higher Prior to12000 total flight cycles on the MLG 27 97-386- 060(B) 45077 OR 45564 HOT TRANSFO- RECTIFIERS OPERATION ALL Model A330 Airplanes 24-3019 1 or higher Prior to 12/31/98 or C of A Issuance; whichever occurs later 28 98-022- 062(B)R1 46115 PNEUMATIC LEAK DETECTION SYSTEM WIRING ALL Model A330 Airplanes AOT 36-04 OR SB 36-3012 AOT: 0 or higher -3012: 0 or higher Prior to 12/16/98 or C of A Issuance; whichever occurs later 29 98-023- 063(B) 43441, OR 41848 CENTER FUSELAGE REINFORCE FR 53.3/53.5 ALL Model A330 Airplanes with Mod. 40161 53-3039 1 or higher Prior to 10000 total flight cycles 30 98-024- 064(B) 44360, OR 44440 REINFORCE KEEL ANGLE OF FRONT SPAR FR40 All Airplanes with Mod. 41652 57-3046 0 or higher Prior to 4000 total flight cycles 31 98-098- 065(B) [42351A ND 42353 AND 43438]; OR 41848 REINFORCE DOORFRAMES/ EMERGENCY EXITS Airplanes with Mod. 40161 53-3023 0 or higher Prior to 10000 total flight cycles 32 98-099- 066(B) 42969 AND 45580 FUEL DENSITOMETERS - ATA 28 ALL Model A330 Airplanes 28-3044R1 OR 28-3053 and 28-3044R0 3044:1 or higher 3053: 0 or higher Prior to 6 Years since new 33 98-101- 068(B) 43306 MODIFY DOOR STOP FITTING ON PASS DOORS ALL Model A330 Airplanes 53-3044 1 or higher Prior to 10000 total flight cycles 34 98-268- 073(B)R1 45534 REPLACE MLG DOOR All Airplanes with MLG door S/N AA1001 to AA1196; or SPAA001 to SPAA015 52-3049 0 or higher Prior to 2/18/00 or C of A Issuance; whichever occurs later 35 98-291- 074(B) 44030, OR 43761 REINFORCE FRAME 65 REAR FUSELAGE ALL Model A330- 300 Airplanes 53-3058 2 or higher Prior to 10000 total flight cycles 36 98-352- 076(B) 46416 MOD MLG O/B PIN / BRAKE ROD TO MAIN STRUT ALL Model A330 Airplanes 32-3084 2 or higher Prior to 1/19/99 or C of A Issuance; whichever occurs later 37 98-454- 082(B) [43577]; OR [41652 AND 44440]; OR [41652 AND 44360] LOWER KEELBEAM FITTING/FWD LOWER SHELL ALL Model A330 Airplanes 57-3032 3 or higher Prior to 6600 Total flight cycles or 21800 Total Flight Hrs, whichever occurs first 38A 98-484- 081(B)R1 46472 REPLACE PIVOT PINS OF SLIDE LOCKING MECHANISM All Airplanes with 44860 (Type 1 Emerg Exits) 52-3050 1 or higher Prior to 3/12/00 or C of A Issuance; whichever occurs later A46NM 41 of 44 RML # DGAC CN # Mod # Mandatory Action Applicable To: S/B # S/B REV(s) Compliance Time 38B 98-484- 081(B)R1 46471 REPLACE PIVOT PINS OF SLIDE LOCKING MECHANISM All Airplanes with 44330 (Mid & Aft Pax Doors) 52-3050 1 or higher Prior to 3/12/00 or C of A Issuance; whichever occurs later 38C 98-484- 081(B)R1 46473 REPLACE PIVOT PINS OF SLIDE LOCKING MECHANISM All Airplanes with 44332 (Type A Emerg Exits) 52-3050 1 or higher Prior to 3/12/00 or C of A Issuance; whichever occurs later 39 98-507- 085(B) [45090], OR [45155], OR [45197], OR [45904], OR [45904 and 45905] REPLACE- DIAPHRAGM FOR EMERGENCY ACTUATOR ALL Model A330 Airplanes 52-3048 1 or higher Prior to 12/16/01 or C of A Issuance; whichever occurs later 40A 40B 98-538- 087(B)R1 98-538- 087(B)R1 46353 46352 MODIFY DOOR STAY MECHANISM EMERG EXITS MODIFY DOOR STAY MECHANISM MID/AFT EXITS All Airplanes with 44332 (Type A Emerg Exits) All Airplanes with 44330 (Mid & Aft Pax Doors) 52-3051 52-3051 1 or higher 1 or higher Prior to 3/31/00 or C of A Issuance; whichever occurs later Prior to 3/31/00 or C of A Issuance; whichever occurs later Hydraulic Fluids Fluid specifications: TYPE IV and TYPE V (NSA 307110) Auxiliary Power Unit (APU) Garrett AiResearch (Company name changed to Honeywell International Inc. in 1999) GTCP 331-350C (Specification 31-7677A) Maximum Allowable Speed (107%) 41,730 RPM Maximum Gas Temperature: Turbine Outlet Temperature Starting 650 C 1250 C Approved oils: See report GT-7800 or APU Maintenance Manual. Tires Refer to Service Bulletin (SB) A330-32-3004. Service Information Each of the documents listed below that contain a statement that it is approved by the European Union 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 Organizatio n EASA.21J.031 - or for approvals made before September 28, 2003 - under the authority of by DGAC Design Organization Approval No. C01 or JAA Design Org anization 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 • US version of Aircraft flight manuals, • Repair Instructions. Design changes that are contained in Airbus Service Bulletins and that are classified as Level 1 Major, or Non-Basic, in accordance with the Technical implementation procedures for airworthiness and environmental certification between the FAA of the USA and the EASA of the European Union must be approved by the FAA. A46NM 42 of 44 VII. General Notes: (All Models of A330 Series Airplanes) Note 1: A current Weight and Balance report including list of the equipment included in the certificated empty weight , and loading instructions, when necessary, must be provided for each aircraft at the time of original airworthiness certification and at all times thereafter. Refer to Documents: - 00G080A0006/C2S for A330-200 and A330-200F series aircraft, - 00G080A0006/C3S for A330-300 series aircraft - 00G080A3WBM/C8S for A330-800 series aircraft. - 00G080A3WBM/C9S for A330-900 series aircraft. Note 2: All placards required by either the AFM, the applicable operating rules, or the certification basis must be installed in the airplane. Note 3: Instructions for Continued Airworthiness required under § 21.50: • Initial minimum maintenance requirements and their frequencies to be used in the development of an approved maintenance program for the aircraft: - A330 Maintenance Review Board Report (Certification Document 00G050A0002/C01), and 00G050A17MA/C01 for the A330-841/-941 approved by the FAA. • Instructions for Continued Airworthiness and airworthiness limitations: - Instructions and airworthiness limitations applicable to Safe Life Airworthiness Limitation Items (SL ALI) are provided in the A330 Airworthiness Limitations Section (ALS) Part 1: ALS Part 1: Safe Life Airworthiness Limitation Items (SL-ALI). - Instructions and airworthiness l imitations applicable to Damage Tolerant Airworthiness Limitation Items (DT ALI) are provided in the A330 Airworthiness Limitations Section (ALS) Part 2: ALS Part 2: Damage Tolerant Airworthiness Limitation Items (DT - ALI). - Certification Maintenance Requirements (CMR’s) are provided in the A330 Airworthiness Limitations Section (ALS) Part 3: ALS Part 3: Certification Maintenance Requirements (CMR). - Instructions and airworthiness l imitations applicable to Aging Systems Maintenance (ASM) are provided in the A330 Airworthiness Limitations Section (ALS) Part 4: ALS Part 4: System Equipment Maintenance Requirements (SEMR). - Fuel Airworthiness Limitations (FAL) are provided in the A330 Airworthiness Limitations Section (ALS) Part 5: ALS Part 5: Fuel Airworthiness Limitations (FAL). Note 4: Compliance with the FAA Required Modification List for Airbus Model A330 Aircraft as included under the Import Requirements section of TCDS Revision 4, dated March 21, 2000 or later TCDS revision, is necessary for an A330 aircraft to be found in a condition for safe operation. The FAA has accepted: - Model A330-323 aircraft in the Airbus as-delivered configuration for MSN 524 and on as compliant with the applicable modifications of the A330 RML. - Model A330-223 aircraft in the Airbus as-delivered configuration for MSN 343 and from MSN 609 and on as compliant with the applicable modifications of the A330 RML. - Model A330-302 and -303 aircraft in the Airbus as-delivered configuration as compliant with the applicable modifications of the A330 RML. - Model A330-202 aircraft in the Airbus as-delivered configuration (except for MSN’s 205, 211, 269 and 272) as compliant with the applicable modifications of the A330 RML. - Model A330-243 aircraft in the Airbus as -delivered configuration (except for MSN’s 248, 250, 254, 261, 265, 271 and 276) as compliant with the applicable modifications of the A330 RML. - Model A330-343 aircraft in the Airbus as -delivered configuration as compliant with the applicable modifications of the A330 RML. A46NM 43 of 44 Note 5: A330-301: If modification 42792, “Autoflight-FMGEC-Introduce L5 Standard on A330 Aircraft,” is embodied the aircraft is qualified for CAT III precision approach and autoland. This does not constitute operational approval. Note 6: A330-321 and A330 -322: If modification 43397, “Autoflight -FMGEC-Certify CAT III Autoland for A330 with P&W engines,” is embodied, the aircraft is qualified for CAT III precision approach and autoland. This does not constitute an operational approval. Note 7: A330-201, A330-202, A330-203, A330-223, A330-223F, A330-243, A330-243F, A330-302, A330-303, A330-323, A330- 341, A330-342, A330-343 and A330-941: The aircraft Type Design is qualified for CAT III precision approach and autoland. This does not constitute an operational approval. Note 8: ETOPS: The Type Design reliability and performance of the airplane -engine combinations listed below have been evaluated in accordance with AC 120-42A or 14 CFR 25.1535 and found suitable for 180 -minute extended operations (ETOPS) when the configuration, ma intenance and procedures (CMP) standard contained in the following listed documents are met. This finding does not constitute operational approval to conduct ETOPS. - Model A330-323. The CMP document AI/EA 5001, Revision 1, dated October 21, 1999 or document LR2/FAA: 14 CFR 25.1535/CMP, Revision 2, dated October 15, 2009. - Model A330-223. The CMP document AI/EA 5001, Revision 2, dated July 12, 2004 or document LR2/FAA: 14 CFR 25.1535/CMP, Revision 2, dated October 15, 2009. - Models A330-201, A330-202, A330-203, A330-243, A330-301, A330-302, A330-303, A330-341, A330-342 and A330- 343. The CMP document LR2/FAA: 14 CFR 25.1535/CMP, Revision 1, dated November 9, 2007. - Models A330-321 and A330-322. The CMP document LR2/FAA: 14 CFR 25.1535/CMP, Revision 1, dated November 9, 2007 or LR2/FAA: 14 CFR 25.1535/CMP, Revision 3, dated December 6, 2012 when equipped with PW4164-1D or PW4168-1D. - Models A330-223F and A330-243F. The CMP document LR2/FAA: 14 CFR 25.1535/CMP, Revision 3, dated December 6, 2012. - Models A330-302, A330-303, A330-323 and A330-343 with optional Airbus modification # Project G3ActCT: “Fuel - Tanks - Activation of Center Tank on A330-300”. The CMP document LR2/FAA: 14 CFR 25.1535/CMP, Revision 04, dated May 7, 2015. - Model A330-941. The CMP document LR2/FAA: 14 CFR 25.1535/CMP, Revision 07, dated January 14, 2019. - Model A330-841. The CMP document LR2/FAA: 14 CFR 25.1535/CMP, Revision 10, dated February 12, 2020. For Model A330 -201, A330-202, A330-203, A330-301, A330-302 and A330 -303 equipped with Modification 205455 t he type design reliability and performance has been evaluated in accordance with 14 CFR 25.1535 and found suitable for greater than 180-minute extended operations (ETOPS) when the configuration, maintenance, and procedures standard contained in the CMP document LR2/FAA: 14 CFR 25.1535/CMP, Revision 06, dated October 26, 2018, are met. Note 9: “Enhanced” refers to those model A330 aircraft identified by Weight Variant (WV) 050 or WV 052. Aircraft with either of these WV’s have the modifications defined by Level 1 major change project: “Fly By Wire (FBW) and Structural Enhanced Changes installed in production.” Note 10: If modification FG-FRS 58723 Issue 2 “Install fuel tank flammability reduction system on A330/A340” is embodied on A330- 201/-202/-203/-223/-243 airplanes, the airplane is compliant with 14 CFR Part 25 appendix M & N at amendment 25 -125, and Section 26.33 at amendment 26 -3, and design changes to the fuel system introduced with modification FG -FRS 58723 Issue 2 are in compliance with 14 CFR Section 25.981(a) & (b) at amendment 25-102. Note 11: If modification 46549 (intermix between CF6-80E1A4 (derated) and CF6-80E1A2 engines, which are physically identical) is embodied on A330-202 Model aircraft, the engine denomination changes to CF6-80E1A4/A2. A46NM 44 of 44 Note 12: If modification 52776 (increase thrust from 70.000 lbs to 72.000 lbs, corresponding to the CF6 -80E1A3 nominal thrust) is embodied on A330-202 or A330-302 Model aircraft, the engine denomination changes to CF6-80E1A4/B. Note 13: If modifications ## 52873 issue 1, 53321 issue 1, 53322 issue 1, 53323 issue 1, 53324 issue 2, 53325 issue 4, 53326 issue 1, 53541 issue 1, 53815 issue 2, 54302 issue 1 and 54566 issue 1 are embodied on A330-201/-202/-203/-223/-243 airplanes or on A330-301/-302/-303/-321/-322/-323/-341/-342/-343 airplanes, the airplane is compliant with 14 CFR Section 25.856 (a) at Amendment 25 -111, Improved Flammability standards for Thermal/acoustic insulation mater ials. ( FAA p roject AT10215IB-T). Note 14: If modification # 204093 Issue1 is embodied, only one HF remains available on the aircraft instead of two as defined in the applicable Type design definition. Note 15: If modification # 204323 is embodied on A330-302 Model equipped with GE CF6-80E1A4 engine and with Weight Variant 050 and 052 thrust rating of GE CF6-80E1A2 engine (64,530 lbs.) can be applied. Note 16: If modification # 204324 is embodied on A330-323 Model equipped with PW 4170 engine and with Weight Variant 050 and 052 thrust rating of PW 4164-1D engine (64,500 lbs.) can be applied. Note 17: If modification # 204325 is embodied on A330-343 Model equipped with RR Trent 772B-60 engine and with Weight Variant 050 and 052 thrust rating of RR Trent 768-60 engine (67,500 lbs.) can be applied. Note 18: A330-841: If modification 208875 “Certification of the automatic approaches and Autoland capabilities in ILS CAT II, CAT IIIA, CAT IIIB on A330-841” is embodied, the aircraft is qualified for automatic approaches and autoland capabilities in ILS CAT II, CAT IIIA/B. This does not constitute operational approval. Note 19: A330-941: If modification 206292 “Auto Flight – General – Introduce automatic approach and autoland on NEO -900” is embodied, the aircraft is qualified for automatic approaches and autoland capabilities in ILS CAT II, CAT IIIA/B. This does not constitute operational approval. - END - ``` ## ADs (486, first 50, in force first) - [AD 2026-20-15](https://openairdocs.org/ad/2026-20-15): Pneumatic · Airbus A330-941 and A330-841. Effective Nov 23, 2026 - [AD 2026-21-03](https://openairdocs.org/ad/2026-21-03): Fuel · Airbus A330-243, A330-243F, A330-341 and 12 more. Effective Nov 23, 2026 - [AD 2026-18-09](https://openairdocs.org/ad/2026-18-09): Power Plant · Airbus A330-243, A330-243F, A330-341 and 2 more. Effective Oct 22, 2026 - [AD 2026-15-01](https://openairdocs.org/ad/2026-15-01): Oxygen · Conversion of passenger to Freighter configuration (ELBE Flugzeugwerke STC ST04038NY). Effective Sep 3, 2026 - [AD 2026-15-10](https://openairdocs.org/ad/2026-15-10): Wings · Airbus A330-841 and A330-941. Effective Sep 3, 2026 - [AD 2026-14-04](https://openairdocs.org/ad/2026-14-04): Fuselage · Airbus A319-111, A319-112, A319-113 and 56 more. Effective Aug 14, 2026 - [AD 2026-10-05](https://openairdocs.org/ad/2026-10-05): Equipment/furnishings · Goodrich A340-641, A340-542, A330-743L and 27 more. Effective Jul 6, 2026 - [AD 2026-10-13](https://openairdocs.org/ad/2026-10-13): Fuselage · Airbus A330-202, A330-203, A330-223 and 15 more. Effective Jul 6, 2026 - [AD 2026-13-02](https://openairdocs.org/ad/2026-13-02): Navigation · Airbus Canada Limited Partnership 18, 49-46, 80-A and 555 more. Effective Jul 1, 2026 - [AD 2026-10-19](https://openairdocs.org/ad/2026-10-19): Fuel · Airbus A330-202, A330-203, A330-223 and 15 more. Effective Jun 8, 2026 - [AD 2026-03-07](https://openairdocs.org/ad/2026-03-07): Time Limits/Maintenance Checks · Airbus A330-201, A330-202, A330-203 and 15 more. Effective Mar 30, 2026 - [AD 2025-25-09](https://openairdocs.org/ad/2025-25-09): Doors · Airbus A330-201, A330-202, A330-203 and 23 more. Effective Feb 9, 2026 - [AD 2025-19-04](https://openairdocs.org/ad/2025-19-04): Time Limits/Maintenance Checks · Airbus A330-201, A330-202, A330-203 and 15 more. Effective Oct 31, 2025 - [AD 2025-20-16](https://openairdocs.org/ad/2025-20-16): Auto flight · Airbus A330-223, A330-223F, A330-243 and 7 more. Effective Oct 30, 2025 - [AD 2025-18-03](https://openairdocs.org/ad/2025-18-03): Oxygen · Airbus A318-111, A318-112, A318-121 and 70 more. Effective Oct 20, 2025 - [AD 2025-20-13](https://openairdocs.org/ad/2025-20-13): Landing Gear · Airbus A330-201, A330-202, A330-203 and 21 more. Effective Oct 17, 2025 - [AD 2025-17-06](https://openairdocs.org/ad/2025-17-06): Time Limits/Maintenance Checks · Airbus A330-201, A330-202, A330-203 and 15 more. Effective Oct 1, 2025 - [AD 2025-17-04](https://openairdocs.org/ad/2025-17-04): Fuselage · Airbus A330-201, A330-202, A330-203 and 15 more. Effective Sep 29, 2025 - [AD 2025-09-07](https://openairdocs.org/ad/2025-09-07): Communications · Airbus A330-243, A330-243F, A330-841 and 1 more. Effective May 15, 2025 - [AD 2025-04-07](https://openairdocs.org/ad/2025-04-07): Fire protection · Airbus A330-201, A330-202, A330-203 and 13 more. Effective Apr 8, 2025 - [AD 2025-04-05](https://openairdocs.org/ad/2025-04-05): Pneumatic · Airbus A330-841 and A330-941. Effective Apr 4, 2025 - [AD 2024-26-05](https://openairdocs.org/ad/2024-26-05): Oxygen · Airbus A300 B4-601, A300 B4-603, A300 B4-620 and 87 more. Effective Mar 11, 2025 - [AD 2024-26-06](https://openairdocs.org/ad/2024-26-06): Flight Controls · Airbus A330-201, A330-202, A330-203 and 20 more. Effective Mar 11, 2025 - [AD 2024-25-11](https://openairdocs.org/ad/2024-25-11): Time Limits/Maintenance Checks · Airbus A330-201, A330-202, A330-203 and 15 more. Effective Mar 7, 2025 - [AD 2025-03-08](https://openairdocs.org/ad/2025-03-08): Flight Controls · Airbus A318-111, A318-112, A318-121 and 70 more. Effective Feb 26, 2025 - [AD 2024-19-15](https://openairdocs.org/ad/2024-19-15): Oxygen · Safran Aerosystems Oxygen Cylinder, Valve Assembly, Oxygen Valve and 103 more. Effective Nov 26, 2024 - [AD 2024-10-01](https://openairdocs.org/ad/2024-10-01): Fire Protection · Airbus A330-841 and A330-941. Effective Nov 25, 2024 - [AD 2024-16-12](https://openairdocs.org/ad/2024-16-12): Equipment/furnishings · Airbus A330-243, A330-302, A330-343 and 1 more. Effective Nov 4, 2024 - [AD 2024-16-15](https://openairdocs.org/ad/2024-16-15): Landing Gear · Airbus A330-201, A330-202, A330-203 and 14 more. Effective Oct 30, 2024 - [AD 2024-17-05](https://openairdocs.org/ad/2024-17-05): Stabilizers · Airbus A330-201, A330-202, A330-203 and 21 more. Effective Sep 20, 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 - [AD 2024-08-08](https://openairdocs.org/ad/2024-08-08): Electrical Power · Airbus A300 B4-2C, A300 B4-103, A300 B4-203 and 94 more. Effective Jun 6, 2024 - [AD 2023-25-16](https://openairdocs.org/ad/2023-25-16): Fuel · Airbus A330-201, A330-202, A330-203 and 15 more. Effective Feb 27, 2024 - [AD 2024-01-10](https://openairdocs.org/ad/2024-01-10): Fuel · Airbus A330-201, A330-202, A330-203 and 17 more. Effective Feb 6, 2024 - [AD 2023-23-03](https://openairdocs.org/ad/2023-23-03): Fuselage · Airbus A330-223F and A330-243F. Effective Jan 16, 2024 - [AD 2023-20-02](https://openairdocs.org/ad/2023-20-02): Engine Fuel and Control · Airbus A330-841 and A330-941. Effective Nov 9, 2023 - [AD 2023-20-06](https://openairdocs.org/ad/2023-20-06): Fuselage · Airbus A330-202, A330-203, A330-223 and 2 more. Effective Nov 9, 2023 - [AD 2023-19-03](https://openairdocs.org/ad/2023-19-03): Airborne Auxiliary Power · Airbus A330-201, A330-202, A330-203 and 18 more. Effective Nov 6, 2023 - [AD 2023-19-01](https://openairdocs.org/ad/2023-19-01): Airborne auxiliary power · Airbus A330-201, A330-202, A330-203 and 21 more. Effective Oct 30, 2023 - [AD 2023-17-03](https://openairdocs.org/ad/2023-17-03): Pneumatic · Airbus A330-201, A330-223, A330-203 and 19 more. Effective Oct 19, 2023 - [AD 2023-08-08](https://openairdocs.org/ad/2023-08-08): Powerplant · Airbus A330-201, A330-202, A330-203 and 3 more. Effective Sep 20, 2023 - [AD 2023-12-19](https://openairdocs.org/ad/2023-12-19): Landing gear · Airbus A330-201, A330-202, A330-203 and 21 more. Effective Aug 23, 2023 - [AD 2023-13-04](https://openairdocs.org/ad/2023-13-04): Fuel · Airbus A330-223F, A330-243F, A330-201 and 23 more. Effective Aug 23, 2023 - [AD 2023-12-01](https://openairdocs.org/ad/2023-12-01): Nacelles/pylons · Airbus A330-223, A330-321, A330-322 and 1 more. Effective Aug 7, 2023 - [AD 2023-10-06](https://openairdocs.org/ad/2023-10-06): Wings · Airbus A330-223F, A330-243F, A330-201 and 21 more. Effective Jul 11, 2023 - [AD 2023-07-02](https://openairdocs.org/ad/2023-07-02): Equipment/furnishings · Airbus A330-201, A330-202, A330-203 and 15 more. Effective May 30, 2023 - [AD 2023-10-02](https://openairdocs.org/ad/2023-10-02): Indicating/Recording System, Navigation · Boeing 18, 23, 35 and 1,060 more. Effective May 26, 2023 - [AD 2023-06-07](https://openairdocs.org/ad/2023-06-07): Airborne Auxiliary Power · Airbus A330-202, A330-203, A330-223 and 18 more. Effective May 18, 2023 - [AD 2023-05-10](https://openairdocs.org/ad/2023-05-10): Windows · Airbus A330-201, A330-202, A330-203 and 23 more. Effective May 12, 2023 - [AD 2023-01-03](https://openairdocs.org/ad/2023-01-03): Landing gear · Airbus A330-201, A330-202, A330-203 and 21 more. Effective Mar 9, 2023 All 486: https://openairdocs.org/tcds/A46NM/ads.md ## Registered aircraft by registry model (OpenAirDocs) - [Airbus A330-243](https://openairdocs.org/model/airbus-a330-243): 40 aircraft (registry codes 3940018, 3940311) - [Airbus A330-941](https://openairdocs.org/model/airbus-a330-941): 40 aircraft (registry codes 3940314, 3940098) - [Airbus A330-323](https://openairdocs.org/model/airbus-a330-323): 21 aircraft (registry code 3940030) - [Airbus A330-343](https://openairdocs.org/model/airbus-a330-343): 17 aircraft (registry code 3940035) - [Airbus A330-223](https://openairdocs.org/model/airbus-a330-223): 11 aircraft (registry code 3940031) - [Airbus A330-302](https://openairdocs.org/model/airbus-a330-302): 10 aircraft (registry code 3940070) - [Airbus A330-243F](https://openairdocs.org/model/airbus-a330-243f): 6 aircraft (registry codes 3940024, 3940312) - [Airbus A330-300](https://openairdocs.org/model/airbus-a330-300): 3 aircraft (registry code 3940099) - [Airbus A330-202](https://openairdocs.org/model/airbus-a330-202): 2 aircraft (registry code 3930347) - [Airbus Industrie A330-223](https://openairdocs.org/model/airbus-industrie-a330-223): 2 aircraft (registry code 3930374) - [Airbus Industrie A330-202](https://openairdocs.org/model/airbus-industrie-a330-202): 1 aircraft (registry code 3930342) - [Airbus Industrie A330-323](https://openairdocs.org/model/airbus-industrie-a330-323): 1 aircraft (registry code 3930335) - [Airbus Industrie A330-343](https://openairdocs.org/model/airbus-industrie-a330-343): 1 aircraft (registry code 3930356) - [Airbus A330-203](https://openairdocs.org/model/airbus-a330-203): 0 aircraft (registry code 3940023) - [Airbus A330-232](https://openairdocs.org/model/airbus-a330-232): 0 aircraft (registry code 3940033) - [Airbus A330-301](https://openairdocs.org/model/airbus-a330-301): 0 aircraft (registry code 3940011) - [Airbus A330-322](https://openairdocs.org/model/airbus-a330-322): 0 aircraft (registry code 3940029) - [Airbus Industrie A330-200](https://openairdocs.org/model/airbus-industrie-a330-200): 0 aircraft (registry code 3930371) - [Airbus Industrie A330-342](https://openairdocs.org/model/airbus-industrie-a330-342): 0 aircraft (registry code 3930354) - [Airbus S A S A330-302](https://openairdocs.org/model/airbus-s-a-s-a330-302): 0 aircraft (registry code 3940313) ## STCs approved under this data sheet (233, first 50) - [STC ST03438NY](https://openairdocs.org/stc/ST03438NY): Installation of Adams Rite Lavatory Equipment. Delta Engineering Corporation - [STC ST09893AC](https://openairdocs.org/stc/ST09893AC): Installation of an Iridium Communication System (ICS). L2 Aviation - [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 ST04077NY](https://openairdocs.org/stc/ST04077NY): Installation of a gogo 2Ku Cabin Connectivity System. Delta Engineering Corporation - [STC ST04474NY](https://openairdocs.org/stc/ST04474NY): Activation of Wireless Local Area Network (WLAN) system. Jet Aviation AG - [STC ST04254NY](https://openairdocs.org/stc/ST04254NY): Installation of Viasat Satcom Software. ALOFT AeroArchitects - [STC ST02164SE](https://openairdocs.org/stc/ST02164SE): 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 ST03939AT](https://openairdocs.org/stc/ST03939AT): Installation of TIMCO Aerosystems lavatories. AIRCRAFT RECONFIG TECHNOLOGIES, LLC - [STC ST03940AT](https://openairdocs.org/stc/ST03940AT): Installation of TIMCO Aerosystems lavatories. AIRCRAFT RECONFIG TECHNOLOGIES, LLC - [STC ST04161AT](https://openairdocs.org/stc/ST04161AT): Interior Reconfiguration. AIRCRAFT RECONFIG TECHNOLOGIES, LLC - [STC ST04199AT](https://openairdocs.org/stc/ST04199AT): Interior Reconfiguration. AIRCRAFT RECONFIG TECHNOLOGIES, LLC - [STC ST04230AT](https://openairdocs.org/stc/ST04230AT): Interior Reconfiguration. AIRCRAFT RECONFIG TECHNOLOGIES, LLC - [STC ST04497AT](https://openairdocs.org/stc/ST04497AT): Interior Reconfiguration. AIRCRAFT RECONFIG TECHNOLOGIES, LLC - [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 ST03875NY](https://openairdocs.org/stc/ST03875NY): Installation of interior placards, signs and markings. Libellule Monde Inc. - [STC ST02884NY](https://openairdocs.org/stc/ST02884NY): Installation or removal of a Panasonic Global Communication Suite (GCS) Antenna. Delta Engineering Corporation - [STC ST02926NY](https://openairdocs.org/stc/ST02926NY): Installation of a Panasonic Global Communication Suite (GCS). Delta Engineering Corporation - [STC ST04732NY](https://openairdocs.org/stc/ST04732NY): Installation of Dual SpaceX Starlink Aviation System. Space Exploration Technologies Corp./Starlink Aviation - [STC ST03009CH](https://openairdocs.org/stc/ST03009CH): Installation of an advertisement container on the bottom of a seat back tray table. Atin OOH LLC - [STC ST11280DS](https://openairdocs.org/stc/ST11280DS): Interior reconfiguration increasing passenger count from 285 to 297 passengers. VT DRS Aviation Consultants - [STC ST00892LA](https://openairdocs.org/stc/ST00892LA): Installation of Emergency Vision Assurance System (EVAS).. VisionSafe LLC - [STC ST00030IB](https://openairdocs.org/stc/ST00030IB): Installation of Test Tech ELT. APTOZ EHF - [STC ST03885AT](https://openairdocs.org/stc/ST03885AT): Installation of an Avionica, Inc. avCM Cellular Module. Aircraft Systems and Manufacturing Inc. - [STC ST00928LA](https://openairdocs.org/stc/ST00928LA): Installation of a stowage unit.. Safran Cabin Inc. - [STC ST01169SE](https://openairdocs.org/stc/ST01169SE): Installation of interior kits. Safran Cabin Inc. - [STC ST02072SE](https://openairdocs.org/stc/ST02072SE): J Class Crew Rest installation. Safran Cabin Inc. - [STC ST02408NY-D](https://openairdocs.org/stc/ST02408NY-D): Installation of a Thales i4500 In-Flight Passenger Entertainment System and Astronics In-Seat Power Supply System.. Safran Cabin Inc. - [STC ST03184NY](https://openairdocs.org/stc/ST03184NY): Installation of a Panasonic In-Flight Entertainment System and/or Global Communication Suite System. Delta Engineering Corporation - [STC ST12056IB](https://openairdocs.org/stc/ST12056IB): The Manufacture and Installation of External Printed Aircraft Graphics Film. Libellule Monde Inc. - [STC ST03747NY](https://openairdocs.org/stc/ST03747NY): Viasat KA SATCOM Antenna System Installation. ALOFT AeroArchitects - [STC ST03193NY](https://openairdocs.org/stc/ST03193NY): Installation of a Panasonic eXLite In-Flight Entertainment System. Delta Engineering Corporation - [STC ST00675DE](https://openairdocs.org/stc/ST00675DE): Installation of LED Floor Proximity Emergency Escape Path Marking System. Bruce Aerospace Inc. - [STC ST02472AT](https://openairdocs.org/stc/ST02472AT): Installation of a mini Quick Access Recorder (QAR) model MKI, MKII, or MKIII. Aircraft Systems and Manufacturing Inc. - [STC ST11936LA](https://openairdocs.org/stc/ST11936LA): Installation of passenger window plug. Ancra International LLC - [STC ST02819CH](https://openairdocs.org/stc/ST02819CH): Installation of Rosemount Aerospace Smart Display Electronic Flight Bag (EFB) System. Rosemount Aerospace Inc. - [STC ST04332CH](https://openairdocs.org/stc/ST04332CH): The Certification for Portable Electronic Device (PED) Tolerance in accordance with CarlisleIT Master Data List, Document Number, 900-104182, Revision NC, dated February 5, 2019, or later FAA approved revision.. Amphenol Cable and Interconnect Technologies Inc. - [STC ST11913IB](https://openairdocs.org/stc/ST11913IB): Installation of Automatic Dependent Surveillance - Broadcast (ADS-B) Out. PMV Engineering - [STC ST11851IB](https://openairdocs.org/stc/ST11851IB): Removal and Maintenance of Panasonic GCS Antenna. ELBE FLUGZEUGWERKE GmbH - [STC ST00079IB](https://openairdocs.org/stc/ST00079IB): Integration of Halon-free Portable Fire Extinguisher HAFEX. UMLAUT ENGINEERING GMBH - [STC ST01585LA](https://openairdocs.org/stc/ST01585LA): Installation of AirWorks Cockpit Door Surveillance Systems.. Aero Technik Inc. - [STC ST00215IB](https://openairdocs.org/stc/ST00215IB): Installation of saf-Tglo ECO Photoluminescent Aisle Path Marking Systems. STG AEROSPACE GERMANY GmbH - [STC ST01936WI](https://openairdocs.org/stc/ST01936WI): Installation of LED lights. AeroLED's Holdings LLC - [STC ST04590AT](https://openairdocs.org/stc/ST04590AT): Installation of Ignition Mitigation Means (IMM. Jetaire Aerospace LLC - [STC ST00691SE](https://openairdocs.org/stc/ST00691SE): Installation of lightweight window plugs. LiteAir Aviation Products Inc - [STC ST00185IB](https://openairdocs.org/stc/ST00185IB): Installation of KANNAD 406 portable emergency locator transmitter (ELT) part number (PN) S1820502-() and/or survival ELT PN S1823502-(). AMES Aerospace & Mechanical Engineering Services Ing. Walter Starzacher GesmbH - [STC ST04038NY](https://openairdocs.org/stc/ST04038NY): Conversion of passenger to Freighter configuration by installing a large Main Deck Cargo door and frame shell, class "E" cargo compartment, floor reinforcement, and other associated modifications,. ELBE Flugzeugwerke GmbH - [STC ST02248AT](https://openairdocs.org/stc/ST02248AT): Installation of photoluminescent floor proximity emergency escape path marking system (FPEEPMS).. STG Aerospace Inc. - [STC ST00126IB](https://openairdocs.org/stc/ST00126IB): Replacement of Halon agent with alternate Halon-free Portable Fire Extinguisher agent. AMAC Aerospace Switzerland AG All 233: https://openairdocs.org/tcds/A46NM/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.