TCDS A46NM

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