TCDS A43NM

Page no. 1 2 3 4 5 6 7 14 9 10 11 12 13 14 15 16 17 18 19 20 21 22 Rev. no. 14 12 12 12 12 12 12 12 12 12 12 12 12 12 12 12 14 14 12 13 14 12 DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION A43NM Revision 14 Airbus A340-200 Series: Models: A340-211, -212, -213 A340-300 Series: Models: A340-311, -312, -313 A340-500 Series: Models: A340-541 A340-600 Series: Models: A340-642 October 22, 2024 FAA TYPE CERTIFICATE DATA SHEET NO. A43NM This data sheet which is part of Type Certificate No. A43NM 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 A340-200 Series Transport Category Airplanes Airbus A340-211 - approved May 27, 1993 Airbus A340-212 - approved July 7, 1994 Airbus A340-213 - approved October 2, 1994 Model: Definition of Reference Airplane by Airbus Documents: A340-211 FAA A340-211 Type Design, ref. AI/EA -N 415.0266/96 Issue 4, dated June 11, 1997, for type definition and Type Certification Standard Equipment List, ref. 00F000A0101/C0S. A340-212 FAA A340-212 Type Design, ref. AI/EA -N 415.0269/96 Issue 4, dated June 11, 1997, for type definition and Type Certification Standard Equipment List, ref. 00F000A0102/C0S. A340-213 FAA A340-213 Type Design, ref. AI/EA -N 415.0271/96 Issue 4, dated June 11, 1997, for type definition and Type Certification Standard Equipment List, ref. 00F000A0103/C0S. Engines Airplane Model Engine Model: Engine Type Certificate: A340-211 Four CFMI-CFM 56-5C2 or four CFM 56 -5C2/F or four CFM 56-5C2/G. Engine intermix between 5C2 and 5C2/F and 5C2/G on the same aircraft is allowed. FAA-Type Certificate E37NE A340-212 Four CFMI -CFM 56 -5C3/F or four CFM 56 -5C3/G. Engine intermix between 5C3/F and 5C3/G on the same aircraft is allowed. FAA-Type Certificate E37NE A340-213 Four CFMI-CFM56-5C4 FAA-Type Certificate E37NE A43NM Page 2 of 22 Maximum Weight Model A340-200 Airplane A340-211/-212/-213 Weight Variant 000 (Basic) kg / lb 001 (MOD 41302) kg / lb Maximum Taxi Weight 254,400 / 560,855 257,900 / 568,572 Maximum Take-off Weight, MTOW 253,500 / 558,871 257,000 / 566,588 Maximum Landing Weight, MLW 181,000 / 399,037 181,000 / 399,037 Maximum Zero Fuel Weight, MZFW 169,000 / 372,581 169,000 / 372,581 Model A340-200 Airplane A340-213 Weight Variant 021 (MOD 44281) kg / lb Maximum Taxi Weight 275,900 / 608,255 Maximum Take-off Weight, MTOW 275,000 / 606,271 Maximum Landing Weight, MLW 185,000 / 407,855 Maximum Zero Fuel Weight, MZFW 173,000 / 381,400 Maximum Baggage Cargo Compartment Maximum Load (kg / lb) Forward 18,507 / 40,800 Aft 15,241 / 33,600 Rear 3,468 / 7,645 For the positions and the loading conditions authorized in each position (references of containers, pallets and associated we ight) see weight and Balance Manual: - A340-211/-212 Airbus Document ref. 00F080A0002/C2S - A340-213 Airbus Document ref. 00F080A0004/C0S 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 A340-200: Airbus Document Refr. Revision No. Date A340-211 AI/EV-O 34000 1 May 27, 1993 A340-212 AI/EV-O 34000 1 February 3, 1997 A340-213 AI/EV-O 34000 1 February 3, 1997 Data Pertinent to All Model See Section III, Data Pertinent to All Model A340-200 and A340-300 Series Airplanes. for information on Fuel, Engine Limits, Airspeed Limits, Center of Gravity Limits, Datum, Leveling Means, Minimum Crew, Number Seats, Fuel Capacity, Maximum Operating Altitude, Control Surface Movements, Certification Basis, Production Basis, Equipment , Hydraulic Fluids, Auxiliary Power Unit (APU), Tires and Environmental requirements for noise. See section VII, Data Pertinent to All Model A340-200, A340-300, A340-500 and A340-600 Series Airplanes. for information on Import Requirements, Service Information and General Notes. A43NM Page 3 of 22 II. Type A340-300 Series Transport Category Airplanes Airbus A340-311 - approved May 27, 1993 Airbus A340-312 - approved July 7, 1994 Airbus A340-313 - approved October 2, 1997 The A340-300 series differs from the A340-200 series aircraft by the addition of 8 fuselage frames. Model: Definition of Reference Airplane by Airbus Documents: A340-311 FAA A340-311 Type Design, ref. AI/EA-N 415.02695/96 Issue 4, dated June 11, 1997, for type definition and Type Certification Standard Equipment List, ref. 00F000A0101/C0S. A340-312 FAA A340-312 Type Design, ref. AI/EA -N 415.0270/96 Issue 4, dated June 11, 1997, for type definition and Type Certification Standard Equipment List, ref. 00F000A0102/C0S. A340-313 FAA A340-313 Type Design, ref. AI/EA -N 415.0272/96 Issue 4, dated June 11, 1997, for type definition and Type Certification Standard Equipment List, ref. 00F000A0103/C0S. Engines Airplane Model Engine Model: Engine Type Certificate: A340-311 Four CFMI-CFM 56-5C2 or four CFM 56 -5C2/F or four CFM 56-5C2/G. Engine intermix between 5C2 and 5C2/F and 5C2/G on the same aircraft is allowed. FAA-Type Certificate E37NE A340-312 Four CFMI -CFM 56 -5C3/F or four CFM 56 -5C3/G. Engine intermix between 5C3/F and 5C3/G on the same aircraft is allowed. FAA-Type Certificate E37NE A340-313 Four CFMI -CFM56-5C4 or four CFM 56-5C4/P or four CFM 56-5C4/1P. Engine intermix between 5C4 and 5C4/P on the same aircraft is allowed. FAA-Type Certificate E37NE Maximum Weight Model A340-300 Airplane A340-311/-312/-313 Weight Variant 000 (Basic) kg / lb 001 (MOD 41302) kg / lb Maximum Taxi Weight 254,400 / 560,855 257,900 / 568,572 Maximum Take-off Weight, MTOW 253,500 / 558,871 257,000 / 566,588 Maximum Landing Weight, MLW 186,000 / 410,059 186,000 / 410,059 Maximum Zero Fuel Weight, MZFW 174,000 / 383,604 174,000 / 383,604 Model A340-300 Airplane A340-313 Weight Variant 002 (MOD 44228) kg / lb 003 (MOD 44102) kg / lb 004 (MOD 44230) kg / lb Maximum Taxi Weight 260,900/ 575,186 257,900 / 568,572 260,900/ 575,186 Maximum Take-off Weight, MTOW 260,000 / 573,201 257,000 / 606,588 260,000 / 573,201 Maximum Landing Weight, MLW 186,000 / 410,059 188,000 / 414,469 188,000 / 414,469 Maximum Zero Fuel Weight, MZFW 174,000 / 383,604 178,000 / 392,422 178,000 / 392,422 A43NM Page 4 of 22 Model A340-300 Airplane A340-313 Weight Variant 020 (MOD 43500) kg / lb 021 (MOD 44135) kg / lb 023 (MOD 44625) kg / lb 024 (MOD 45738) kg / lb Maximum Taxi Weight 271,900 / 599,436 275,900 / 608,255 262,900 / 579,595 275,900 / 608,255 Maximum Take-off Weight, MTOW 271,000 / 597,452 275,000 / 606,271 262,000 / 577,611 275,000 / 606,271 Maximum Landing Weight, MLW 190,000 / 418,878 190,000 / 418,878 190,000 / 418,878 192,000 / 423,287 Maximum Zero Fuel Weight, MZFW 178,000 / 392,422 178,000 / 392,422 178,000 / 392,422 180,000 / 396,832 Model A340-300 Airplane A340-313 Weight Variant 025 (MOD 44791) kg / lb 026 (MOD 46613) kg / lb 028 (MOD 49529) kg / lb Maximum Taxi Weight 260,900 / 575,186 275,900 / 608,255 277,400 / 611,562 Maximum Take-off Weight, MTOW 260,000 / 573,201 275,000 / 606,271 276,500 / 609,578 Maximum Landing Weight, MLW 190,000 / 418,878 192,000 / 423,287 190,000 / 418,878 Maximum Zero Fuel Weight, MZFW 178,000 / 392,422 181,000 / 399,036 178,000 / 392,422 Maximum Baggage Cargo Compartment Maximum Load (kg / lb) Forward 22,861 / 50,399 Aft 18,507 / 40,800 Rear 3,468 / 7,645 For the positions and the loading conditions authorized in each position (references of containers, pallets and associated weight) see weight and Balance Manual: - A340-311/-312 Airbus Document ref. 00F080A0002/C3S - A340-313 Airbus Document ref. 00F080A0004/C0S 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 A340-300 Airbus Document Refr. Revision No. Date A340-311 AI/EV-O 34000 1 May 27, 1993 A340-312 AI/EV-O 34000 1 February 3, 1997 A340-313 AI/EV-O 34000 1 February 3, 1997 Data Pertinent to All Model See Section III, Data Pertinent to All Model A340-200 and A340-300 Series Airplanes. for information on Fuel, Engine Limits, Airspeed Limits, Center of Gravity Limits, Datum, Leveling Means, Minimum Crew, Number Seats, Fuel Capacity, Maximum Operating Altitude, Control Surface Movements, Certification Basis, Production Basis, Equipment , Hydraulic Fluids, Auxiliary Power Unit (APU), Tires and Environmental requirements for noise. See section VII, Data Pertinent to All Model A340-200, A340-300, A340-500 and A340-600 Series Airplanes. for information on Import Requirements, Service Information and General Notes. A43NM Page 5 of 22 III. Data Pertinent to All Model A340-200 and A340-300 Series Airplanes Fuel Specification Nomenclature United Sates France United Kingdom Kerosene ASTM D 1655 (JET A) (JET A1) AIR 3405C DERD 2494/2453 Wide Cut ASTM D 1655 (JET B) AIR 3407B DERD 2454/2486 MIL-T 5624 (JP4) MIL-T 83133 (JP8) AIR 3407B DERD 2454/2486 Additives: According to CFMI "Specific Operating Instructions", installation manual. The above-mentioned fuels are also suitable for the APU. Engine Limits Engine Limitations CFMI CFM 56 -5C2 -5C2/4 -5C2/F -5C2/F4 -5C2/G -5C2/G4 CFMI CFM 56 -5C3/F -5C3/F4 -5C3/G -5C3/G4 CFMI CFM 56 -5C4 -5C4/P -5C4/1P See FAA Data Sheet E37NE Static Thrust at Sea Level • Take-off (5 mn)1 (flat rated 30º C) • Maximum continuous (flat rated 25º C) 13878 daN (31,200 lbs) 12588 daN (28,300lbs) 14456 daN (32,500 lbs) 13077 daN (29,400 lbs) 15123 daN (34,000 lbs) 13371 daN (30,060 lbs) Maximum Engine Speed • N1 rpm (%) • N2 rpm (%) 4800 (100.3%) 15,183 (105%) 4800 (100.3%) 15,183 (105%) 4985 (104.2%) 15,183 (105%) Maximum Gas Temperature • Take-off (5mn)1 • Maximum Continuous • Starting2 950º C 915º C 725º C 965º C 930º C 725º C 975º C 940º C 725º C Maximum Oil Temperature (Supply Pump Outlet) ºC • Take-off, Stabilized • Transient (15 mn max.) Minimum Pressure 140º C 155º C 89.6 KPa differential 140º C 155º C 89.6 KPa differential 140º C 155º C 89.6 KPa differential Approved oils See CFMI Service Bulletin CFMI 79-001 or GE specification D50TF1, Type I and II 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 Airspeed Limits (Indicated Airspeed, IAS, unless otherwise stated) • Maximum Operating Limit Speed/Mach, VMO/MMO 330 KIAS / .86 M • Design Diving Speed, VD 365 KIAS / .93 M • Design Maneuvering Speed, VA Refer to AFM performance Section • Maximum Flaps/Slats Extended Speed or Operating Speed, VFE Configuration Slats/Flaps º VFE (kt) 1 20/0 20/17 240 215 Intermediate Approach Take-off 2 24/22 196 Take-off and Approach 3 24/26 186 Take-off, Approach, and Landing FULL 24/32 180 Landing A43NM Page 6 of 22 • 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), VL0 250 KIAS / .55 M • Maximum Speed with Landing Gear Locked Down, VLE 250 KIAS / .55M • Tire Limit Speed (Ground Speed) 204 KTS Center of Gravity Limits Refer to EASA-Approved AFM, US Version, Limitations Section for center of gravity envelope. Note: 0% MAC is located 1275.51 in from the datum line. Datum The aircraft reference zero datum point is located 251.37 in. (6.38 m) forward of the fuselage nose, 275.8 in. (7 m) under the fuselage centerline (datum line). Leveling Means Inclinometer on cabin seat track rails (refer to AMM chapter 08.20.00). Minimum Crew 2 - Pilot and copilot Number of Seats The maximum number of passengers approved for emergency evacuation is: 375 passengers with a 3 pair Type A and 1 pair Type 1 exits configuration, and A340-200: 420 passengers with 4 pair Type A exits configuration. A340-300: 440 passengers with 4 pair Type A exits configuration. Fuel Capacity 3 Tank Airplane Usable Fuel Unusable Fuel Tank Liters (kg) gallons (lb) Liters (kg) gallons (lb) Wing 91,056 (72,845) 24,054 (164,052) 245 (196) 70 (41) Center 41,468 (33,174) 10,955 (74,173) 83 (66) 22 (150) Trim Tank 6,114 (4,891) 1,615 (11,014) 6 (5) 1.6 (11) Total 138,638 (110,910) 36,627 (249,796) 334 (267) 88 (600) Maximum Operating Altitude • Basic: 41,100 feet (12,527m) slats and flaps retracted (clean) • Option: 41,450 feet (12,634m) slats and flaps retracted (clean) with modification 52536 • 20,000 feet (6,096 m) slats or slats/flaps extended A43NM Page 7 of 22 Control Surface Movements (Total one-way travel in each direction of each movable control surface on the aircraft.) Control Surface Maximum Travel Aileron +25/-25 #1 Spoiler Speed Brake 25 Lift Dumper 35 #2,3 Spoilers Roll 35 Speed Brake 30 Lift Dumper 50 #4,5 Spoilers Roll 35 Speed Brake 30 Lift Dumper 50 Aileron Droop 10 Flaps 32 Slats 1 21 Slats 2 to 7 24 Stabilizers +2/-14 Elevator +15/-30 Rudder +31.6/-31.6 Certification Basis (A340-200 and A340-300) a. 14 CFR part 25 effective February 1, 1965, including the following: • Amendments 25-1 through 25-63 and Amendments 25-65, 25-66 and 25-77. • §25.791 at Amendment 25-72 b. 14 CFR part 25 at 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 35 inch free head strike envelope. c. 14 CFR part 34, effective September 10, 1990. d. 14 CFR part 36 of the as amended by Amendments 36-1 through 36-20. e. Special conditions in accordance with 14 CFR part 21.16: 1. FAA Special conditions issued for the A340 in accordance with 14 CFR part 21.16 and published in the Federal Register April 15, 1993, (Docket No. NM-75, Special Conditions No. 25-ANM-69), as follows: (1) Electronic Flight Control System (EFCS) failures and Mode Annunciation (8) Tail plane Tank Emergency Landing Loads (2) Command Signal Integrity (9) Limit Engine Torque (3) Protection From Lightning and Unwanted Effects of High Intensity Radiated Fields (HIRF) (10) Ground Load Conditions for Center Landing Gear (4) Interaction of Systems and Structures (11) Flight Characteristics (5) Design Dive Speed (12) Flight Envelope Protection (6) Design Maneuver Requirements (13) Side Stick Controllers (7) Limit Pilot Forces (14) Computerized Airplane Flight Manual (AFM) Performance Information 2. Special Conditions 25-281-SC published in the Federal Register January 6, 2005 (Docket No. NM287: Lower Deck Mobile Crew Rest (LD–MCR) Compartment 3. Special Conditions 25-396-SC published in the Federal Register November 03, 2009 (Docket No. NM-419): Seats With Inflatable Lap Belts. A43NM Page 8 of 22 4. Special Conditions 25-399-SC published in the Federal Register January 4, 2010 (Docket No. NM-423): Seats with Non-Traditional, Large, Non-Metallic Panels. 5. Special Conditions 25-759-SC published in the Federal Register October 31, 2019 (Docket No. FAA-2019-0814: Seats With Inertia Locking Devices f. For precision approach and landing, the applicable technical requirements are complemented by AC 120-29 and AC 120-28C. g. For the automatic flight control system, the applicable technical requirements are complemented by AC 20-57A for automatic landing and by AC 25.1329-1A for cruise. h. Equivalent safety findings have been made in accordance with § 21.21(b)(1) for the following paragraphs of the 14 CFR part 25: (1) § 25.335(d) for design airspeeds (7) §§ 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) § 25.345 for high lift devices (8) § 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). (3) § 25.349 for control surface loads (9) §§ 26.33, 26.35 Fuel Center Tank Flammability Red uction System (documented in ELOS Memo TD0547IB-T-P-1 (4) § 25.351(b) for unsymmetrical loads (10) § 25.981(a)(3) Amendment. 25 -102 Fuel tank igniti on prevention (documented in ELOS Memo TD0764IB-T-P-1) (5) § 25.371 for gyroscopic loads (11) § 25.1443(c) Minimum mass flow of supplemental oxygen on model A330 and A340 airplanes (documented in ELOS Memo AT10356IB - T-S-1) (6) § 25.373 for speed control devices (12) § 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) (13) § 25.811(e)(4) Emergency Exit Marking on Airbus Model A330 and A340 airplanes (documented in ELOS Memo AT10899IB-T-CS-1) i. Optional requirements elected: • § 25.801 at Amendment 25-72 for ditching. • § 25.1419 at Amendment 25-72 for icing. j. Exemptions: Exemptions from the applicable regulations has been processed in accordance with the provisions of 14 CFR 11.25. - Exemption18136, dated February 28, 2019, granted to Airbus for 14 CFR 25.813(e), amendment 25 -116, and 14 CFR 121.310(f)(5) and (6) to the extent necessary to allow the installation of doors on mini-suites. The Direction Générale de l'Aviation Civile (DGAC) of France originally type certificated the Airbus Model A340 -200 and A340-300 series airplanes under its type certificate number DGAC-F TC 183. The FAA validated this product under U.S. Type Certificate Number A43NM. 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. Production Basis From July 21, 2008, A340 aircraft, all series and models, are produced in France under production approval reference EASA.21G .0001 issued by EASA, prior that date all A340 aircraft, all series and models, are produced in France under production approval FR.21G.0035 (formerly FG 035) issued by the DGAC (on behalf of EASA) to Airbus. A43NM Page 9 of 22 Equipment • The basic required equipment as prescribed in the applicable airworthiness regulations (see Certification Basis) must be installed in the aircraft for certification. • Equipment approved for installation is listed in the Type Certification Standard Equipment Lists; - A340-211 and A340-311: 00F000A0101/C0S, - A340-212 and A340-312: 00F000A0102/C0S, - A340-213 and A340-313: 00F000A0103/C0S. • Cabin furnishings, equipment and arrangement shall conform to the following specification: - 00F252K0010/C01for cabin seats. - 00F252K0006/C01for galley. - 00F252K0020/C01for cabin attendant seats Hydraulic Fluids Fluid specifications: TYPE IV and TYPE V (NSA 307110) Auxiliary Power Unit (APU) Garrett Airesearch (Company name changed to Honywell 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 Garrett report GT-7800 or Garrett Maintenance Manual. Tires Refer to Airbus Service Bulletin (SB) A340-32-4007. Environmental requirements for noise 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. A340-213 fitted with CFM56-5C4 engines are compliant with Stage 5 noise requirements of 14 CFR part 36 as amended by Amendments 36-1 through 36-31. A340 -313 fitted with CFM56-5C4, or CFM56-5C4/P, or CFM56-5C4/1P engines are compliant with Stage 5 noise requirements of 14 CFR part 36 as amended by Amendments 36-1 through 36-31. A43NM Page 10 of 22 IV. Type A340-600 Series Transport Category Airplanes Airbus Model A340-642 - approved July 22, 2002 The A340-600 series differs from the A340 -300 series aircraft by the addition of 20 fuselage frames with corresponding increases in weight, thrust, horizontal stabilizer area and wing area. Full electrical control of the rudder replaces the previous mechan ical linkage between computer and actuators for both primary and backup systems Model: Definition of Reference Airplane by Airbus Documents: A340-642 FAA A340-642 Type Design, ref. EAL 415.0363/02 Issue 02, dated July 19, 2002, for type definition. Engines Airplane Model Engine Model: Engine Type Certificate: A340-642 Four Rolls-Royce– Trent 556-61 turbojet engines FAA-Type Certificate E00066NE Maximum Weight Model A340-600 Airplane A340-642 Weight Variant 000 (Basic) kg / lb 001 (Mod 50312) kg / lb Maximum Taxi Weight 366,200 / 807,332 369,200 / 813,946 Maximum Take-off Weight, MTOW 365,000 / 804,687 368,000 / 811,301 Maximum Landing Weight, MLW 256,000 / 564,383 259,000 / 570,997 Maximum Zero Fuel Weight, MZFW 242,000 / 533,518 245,000 / 540,132 Model A340-600 Airplane A340-642 Weight Variant 101 (MOD 53043) kg / lb 102 (Mod 54805) kg / lb Maximum Taxi Weight 381,200 / 840,401 369,200 / 813,946 Maximum Take-off Weight, MTOW 380,000 / 837,756 368,000 / 811,301 Maximum Landing Weight, MLW 265,000 / 584,224 259,000 / 570,997 Maximum Zero Fuel Weight, MZFW 251,000 / 553,360 245,000 / 540,132 Number of Seats The maximum number of passengers approved for emergency evacuation is 440 passengers with a 4 pair of Type A and 1 pair of oversize Type III exits configuration. Maximum Baggage Cargo Compartment Maximum Load (kg / lb) Forward 30,482 / 67,201 Aft 22,861 / 50,399 Rear 3,468 / 7,645 For the positions and the loading conditions authorized in each position (references of containers, pallets and associated we ight) see weight and Balance Manual: - A340-642 Airbus Document ref. 00F080A0601/C6S A43NM Page 11 of 22 Fuel Capacity Tank Capacity Usable Fuel Unusable Fuel Tank Liters (kg) gallons (lb) Liters (kg) gallons (lb) Wing Tank 1 / 4 49,002 (39,202) 12,945 (86,426) 68 (54) 18 (120) Tank 2 / 3 69,514 (55,611) 18,364 (122,601) 230 (184) 61 (406) Outer 12,290 (9,832) 3,247 (21,676) 34 (27) 9 (60) Total 130,806 (104,645) 34,556 (230,703) 332 (266) 88 (586) Center 54,969 (43,975) 14,521 (96,842) 404 (323) 107 (713) Trim Tank 8,361 (6,689) 2,209 (14,747) 25 (20) 7 (44) Total 194,136 (155,309) 51,286 (342,386) 761 (609) 201 (1,343) 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 A340-600 Airbus Document Refr. Revision No. Date A340-642 STL 34000 1 July 22, 2002 Data Pertinent to All Model See Section VI, Data Pertinent to All Model A340-500 and A340-600 Series Airplanes. for information on Fuel, Engine Limits, Airspeed Limits, Center of Gravity Limits, Datum, Leveling Means, Minimum Crew, Maximum Operating Altitude, Control Surface Movements, Certification Basis, Production Basis, Equipment, Hydraulic Fluids, Auxiliary Power Unit (APU), Tires and Environmental requirements for noise. See section VII, Data Pertinent to All Model A340-200, A340-300, A340-500 and A340-600 Series Airplanes. for information on Import Requirements, Service Information and General Notes. A43NM Page 12 of 22 V. Type A340-500 Series Transport Category Airplanes Airbus A340-541 - approved January 27, 2003