# TCDS A35EU: Airbus SAS - Type: Type certificate data sheet - Status: Current - Holder: Airbus SAS - Revision: 34 - Revised: October 16, 2023 - Product: Aircraft, Large Airplane - Certification basis: Part 25, Part 21 - Registered aircraft: 124, by the registry models matched to it (OpenAirDocs) - Data sheet PDF: https://openairdocs.org/files/sha256/af/eb/afebc1408bfb8ac33f841a0395b599dcffde75b09bbc118f297ee7fe6fe94253 - FAA DRS: https://drs.faa.gov/browse/excelExternalWindow/DRSDOCID122684811520260429214657.0001 - Page: https://openairdocs.org/tcds/A35EU ## Models (17) As the data sheet lists them. - A310-203 - A300 B4-622R - A300 F4-605R - A300 B4-601 - A310-204 - A310-221 - A300 B4-603 - A300 B4-622 - A310-324 - A300 F4-622R - A300 B4-620 - A300 C4-605R Variant F - A310-322 - A300 B4-605R - A310-325 - A310-304 - A310-222 ## 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 Rev. No. 34 33 20 20 33 19 20 9 20 9 20 33 20 22 20 34 27 20 20 20 33 Page No. 22 23 24 25 26 27 28 29 30 31 32 33 34 35 36 37 38 39 40 41 42 Rev. No. 20 20 34 20 22 20 21 27 27 27 20 20 29 20 20 20 29 20 20 20 20 Page No. 43 44 45 46 47 48 49 50 51 52 53 54 55 56 57 58 59 60 61 62 63 Rev. No. 20 29 21 20 19 29 32 31 30 27 27 20 20 20 20 20 20 22 22 27 22 Page No. 64 65 66 67 68 69 Rev. No. 25 27 32 27 29 28 DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION A35EU Revision 34 Airbus A300 A300, Model B2-1A(Surrendered) A300, Model B2-1C(Surrendered) A300, Model B4-2C(Surrendered) A300, Model B2K-3C(Surrendered) A300, Model B4-103(Surrendered) A300, Model B2-203(Surrendered) A300, Model B4-203(Surrendered) A310 A310, Model 204 A310, Model 221 A310, Model 222 A310, Model 203 A310, Model 322 A310, Model 324 A310, Model 304 A310, Model 325 A300-600 A300, Model B4-601 A300, Model B4-603 A300, Model B4-620 A300, Model B4-605R A300, Model B4-622R A300, Model F4-605R A300, Model F4-622R A300, Model C4-605R Variant F A300, Model B4-622 April 16, 2026 TYPE CERTIFICATE DATA SHEET No. A35EU This Data Sheet which is part of Type Certificate No. A35EU prescribes conditions and limitations under which the product for which the Type Certificate was issued meets the airworthiness requirements of the Federal Aviation Regulations. Type Certificate Holder. Airbus SAS 2 rond-point Emile Dewoitine 31700 Blagnac France Type Certificate Holder Record Name change from Airbus Industrie to Airbus January 2002. Name change from Airbus to Airbus SAS August 2017. To be considered eligible for operation in the United States, each aircraft manufactured under this type certificate must be accompanied by a certificate of airworthiness for export or certifying statement endorsed by the exporting foreign civil airworthiness authority which states (in the English language): This aircraft conforms to its U.S. type design (Type Certificate Number A35EU) and is in a condition for safe operation. The U.S. airworthiness certification basis for aircraft type certificated under FAR Section 21.29 and exported by the country of manufacture is FAR Sections 21.183(c) or 21.185(c). The U.S. airworthiness certification basis for aircraft type certificated under FAR Section 21.29 exported from countries other than the country of manufacture (e.g., third party country) is FAR Sections 21.183(d) or 21.183(b). A35EU Page 2 of 71 Notwithstanding that the FAR referenced in the above paragraph does not specifically address or require a foreign civil airworthiness authority certification, such certification is the only practical way for an applicant to show, and the Federal Aviation Administration (FAA) to find conformity to the FAA-approved type design and condition for safe operation. Additional guidance is contained in FAA Advisory Circular 21-23, Airworthiness Certification of Civil Aircraft, Engine, Propellers, and Related Products Imported into the United States. I. Type 300, Model B2-1A, (Transport Category Airplane), approved May 30, 1974. TC Surrendered on August 9, 2023 Engines. 2 - General Electric Turbofan, Model CF6-50A (Data Sheet FAA: No E 23 EA3 - Part B) APU. Airesearch TS CP 700-5 (TSO C77 8C 6203) Fuel. (a) The following fuels are eligible for engines and APU: MIL-T-5624H Grades JP-4 or JP-5 AST-MD-1655-65T Grades Jet A, A1 (JP1) and Jet B AST-ES-2-74 Grades Jet A, A1 and Jet B French specifications are: Air 3404 Air 3407 Air 3405 With JP-4 or Jet B fuel, the following limitations apply: (1) Maximum altitude of 15,000 ft with gravity fuel supply from inboard tanks. (2) Maximum altitude of 20,000 ft with gravity fuel supply from outboard tanks. (b) The following additives may be used in approved fuels for engines and APU: (1) Phillips PFA-55MB or anti-icing additive to specifications MIL-I-27686E at a concentration not in excess of 0.15 percent by volume. (2) Sohio Bibor JF biocide additive at a concentration not in excess of 20 ppm elemental boron (270 ppm total additive). (3) Shell ASA-3 anti-static additive at a concentration that will provide not in excess of 300 conductivity units which is approximately equivalent to one ppm. Oil. (a) The following oils are eligible for the CF6-50 engine: Synthetic type conforming to GE Specifications D 50 T F1, Classes A or B. (GE Service Bulletin No. 79-1 lists approved brand oils) (b) The following oil is eligible for the APU: See Maintenance Manual TS CP 70, Chap. 49.20.00 Table 303. Engine Limits. Static thrust, sea level Takeoff (5 min) - (flat to 87ºF) 48,400 lb Maximum continuous (flat to 85ºF) 46,300 lb Maximum permissible engine rotor operating speeds. N1 (Low compressor) 4,068 rpm (118.5%) N2 (High compressor) 10,761 rpm (109.5%) Maximum permissible engine temperature. Turbine exhaust gas temperature at turbine outlet Takeoff (5 min) 945ºC Maximum continuous 910ºC Maximum acceleration (2 min) 960ºC Starting: up to 40 sec. 1,652ºF (900ºC) above 40 sec. 1,382ºF (750ºC) A35EU Page 3 of 71 I. Type 300, Model B2-1A, (Transport Category Airplane) (cont'd) Oil maximum permissible outlet temperature Continuous operation 320ºF (160ºC) Transient operation listed to 15 min. 347ºF (175ºC) APU Limits. Power rating Maximum at sea level 142 hp. Maximum rotor speeds Low pressure speed (N1) 30,910 rpm (110%) High pressure speed (N2) 38,845 rpm (110%) Maximum exhaust gas temp. 1,085ºF (585º) Airspeed Limits (IAS). VMO (Maximum Operating) up to 25,400 ft 360 K. MMO (Maximum Operating) at and over 25,400 ft 0.86 M VA (Maneuvering) See EASA Approved US Airplane Flight Manual VFE Slat Positions Flap Positions Takeoff 20 0 250 K Takeoff 20 8 215 K Approach 20 15 205 K Landing 25 25 180 K Enroute 20 0 210 K (M=0.47) VLO (Landing Gear) Extension 270 K Retraction 240 K VLE (Landing Gear Extended) 270 K (M=0.59) VMC (Minimum Control) Speed with the Critical Engine Inoperative In flight - VMCA 110 KIAS - 105 KCAS Takeoff and Landing - VMCG 106 KIAS - 101.5 KCAS V (Tires Limitation) 182.5 KCAS C.G. Range. (Landing Gear Extended) FORWARD AFT Gross Weight Enroute & Takeoff Enroute & Takeoff Landing Landing 137,900 kg 304,017 lb 18% MAC to to (Sta.1162.82) All All All 125,000 kg 275,575 lb weights weights weights 125,000 kg 275,575 lb Linear varia- 18% MAC 35% MAC 33% MAC to to tion between (Sta. (Sta. (Sta. 120,000 kg 264,550 lb 18% MAC and 1162.82) 1202.13) 1201.92) 15% MAC Below Below 15% MAC 120,000 kg 264,550 lb (Sta.1155.07) Landing gear retraction moment is 68,686 in lb., gear retraction moves c.g. forward. A35EU Page 4 of 71 I. Type 300, Model B2-1A, (Transport Category Airplane) (cont'd) Maximum Weights. kg lb Taxi Weight 137,900 304,017 Takeoff Weight 137,000 302,033 Landing Weight 127,500 281,089 Zero Fuel Weight 116,500 256,838 Gear Jacking Weight 137,000 302,033 Minimum Crew. For all Flights: Pilot, Copilot and Flight Engineer. Maximum Passengers. 345 - Based on compliance with FAR 25 emergency exit requirements. Emergency evacuation demonstration of 25.803 (c) has been performed with 330 passengers. See DGAC approved interior arrangement drawing for maximum passenger capacity approved for each airplane as delivered. Maximum Baggage. Forward freight compartment with containers: 12 x 2,830 lb. Middle freight compartment with containers: 8 x 2,830 lb. Aft freight compartment: Maximum loading: 5,512 lb. Fuel Capacity. Fuel Tank Capacity (lb) Usable Fuel (6.676 lb/gal) Location Arm (inches) Preselector Tank high Level Setting cut-off Sensor cut-off (lb) (US gal) Outboard 1 7,716 1,155 1327.04 Outboard 2 7,716 1,155 1327.04 Inboard 1 29,762 4,458 1156.88 Inboard 2 29,762 4,458 1156.88 Total 74,956 11,226 Fuel Management. Fuel must be loaded symmetrically in outboard tanks first; fuel must be used from inboard tanks first. Maximum allowable wing fuel asymmetry is 8,820 lb (refere to latest EASA approved AFM revision). Oil Capacity. Engine oil capacity 24.4 lb/engine usable (at 8.1 lb/gal.) with engine moment arm 1011.10 in. Maximum Operating Altitude. 40,000 ft. Equipment. The basic required equipment as prescribed in the applicable Federal Aviation Regulations must be installed. Airbus equipment list document AI/V 339/75 as revised identifies all required equipment and all optional equipment approved by the Direction General de l'Aviation Civile (D.G.A.C.) of France. In addition the following is required: EASA Approved US Airplane Flight Manual Other Information. See "Data Pertinent to All A300 Models (except the A300B4-600, A300B4-600R, A300F4-600R and A300C4-600R Series)" A35EU Page 5 of 71 II. Type A300, Model B2-1C (Transport Category Airplane), approved June 19, 1975. TC Surrendered on August 9, 2023 Engines. 2 - General Electric Turbofan, Model CF6-50C (Data Sheet FAA No. FAA E 23 EA 3 part B) APU. Airsearch TS CP 700-5 (TSO C77 SC 6203) Fuel. (a) The following fuels are eligible for engines and APU: MIL-T-5624H Grades JP-4 or JP-5 AST-MD-1655-65T Grades Jet A, A1 (JP-1) and Jet B AST-ES-2-74 Grades Jet A, A1 and Jet B French specifications are: Air 3404 Air 3407 Air 3405 With JP-4 or Jet B fuel, the following limitations apply: (1) Maximum altitude of 15,000 ft with gravity fuel supply from inboard tanks. (2) Maximum altitude of 20,000 ft with gravity fuel supply from outboard tanks. (b) The following additives may be used in approved fuels for engine and APU: (1) Phillips PFA-55MB or anti-icing additive to specifications MIL-I-27686E at a concentration not in excess of 0.15 percent by volume. (2) Sohio Biobor JF biocide additive at a concentration not in excess of 20 ppm elemental boron (270 ppm total additive). (3) Shell ASA-3 anti-static additive at a concentration that will provide not in excess of 300 conductivity units which is approximately equivalent to one ppm. Oil. (a) The following oils are eligible for the CF6-50 engine. Synthetic type conforming to GE specification D 50 T F1, Classes A or B. (GE Service Bulletin No. 79-1 lists approved brand oils). (b) The following oil is eligible for the APU: See Maintenance Manual TSCP 700, Chap. 49.20.00 Table 303 Engine Limits. Static thrust, sea level Takeoff (5 min) - (Flat to 86ºF) 50,400 lb Maximum continuous (Flat to 85ºF) 46,300 lb Maximum permissible engine rotor operating speeds N1 (Low compressor) 4,068 rpm (118.5%) N2 (High compressor) 10,761 rpm (109.5%) Maximum permissible engine temperature Turbine exhaust gas temperature at turbine outlet Takeoff (5 min) 945ºC Maximum Continuous 910ºC Maximum acceleration (2 min) 960ºC Starting: Up to 40 sec. 1,652ºF (900ºC) Above 40 sec. 1,382ºF (750ºC) Oil Maximum permissible outlet temperature Continuous operation 320ºF (160ºC) Transient operation limited to 15 min. 347ºF (175ºC) A35EU Page 6 of 71 II. Type A300, Model B2-1C (Transport Category Airplane) (cont’d) APU Limits. Power rating Maximum at sea level 142 hp. Maximum rotor speeds Low pressure speed (N1) 30,910 rpm (110%) High pressure speed (N2) 38,845 rpm (110%) Maximum exhaust gas temperature 1,085ºF (585ºC) Airspeed Limits (IAS). VMO (Maximum Operating) up to 25,400 ft 360 K. MMO (Maximum Operating) at and over 25,400 ft 0.86 M VA (Maneuvering) See EASA Approved US Airplane Flight Manual VFE Slat Positions Flap Positions Takeoff 20 0 250 K Takeoff 20 8 215 K Approach 20 15 205 K Landing 25 25 180 K Enroute 20 0 210 K (M=0.47) VLO (Landing Gear) Extension 270 K Retraction 240 K VLE (Landing Gear Extended) 270 K (M=0.59) VMC (Minimum Control) Speed with the Critical Engine Inoperative In flight - VMCA 110 KIAS - 105 KCAS Takeoff and Landing - VMCG 106 KIAS - 101.5 KCAS V (Tires Limitation) 182.5 KCAS C.G. Range. (Landing Gear Extended) FORWARD AFT Gross Weight Enroute & Takeoff Enroute & Takeoff Landing Landing 137,900 kg 304,017 lb 18% MAC to to (Sta.1162.82) All All All 125,000 kg 275,575 lb weights weights weights 125,000 kg 275,575 lb Linear varia- 18% MAC 35% MAC 33% MAC to to tion between (Sta. (Sta. (Sta. 120,000 kg 264,550 lb 18% MAC and 1162.82) 1202.13) 1201.92) 15% MAC Below Below 15% MAC 120,000 kg 264,550 lb (Sta.1162.82) Landing gear retraction moment is 68,686 in lb., gear retraction moves c.g. forward. A35EU Page 7 of 71 II. Type A300, Model B2-1C (Transport Category Airplane) (cont’d) Maximum Weights. BASIC MODEL VARIANT 02 with mod 1357 kg lb kg lb Taxi Weight Takeoff Weight Landing Weight Zero Fuel Weight Gear Jacking Weight 137,900 137,000 127,500 116,500 137,000 304,017 302,033 281,089 256,838 302,033 142,900 142,000 130,000 120,500 142,000 315,040 313,056 286,601 265,657 313,056 Minimum Crew. For all Flights: Pilot, Copilot and Flight Engineer Maximum Passengers. 345 - Based on compliance with FAR 25 emergency exit requirements. Emergency evacuation demonstration of 25.803(c) has been performed with 330 passengers. See DGAC approved interior arrangement drawing for maximum passenger capacity approved for each airplane as delivered. Maximum Baggage. Forward freight compartment with containers: 12 x 2,830 lb. Middle freight compartment with containers: 8 x 2,830 lb. Aft freight compartment: Maximum loading: 5,512 lb. Fuel Capacity. Fuel Tank Capacity (lb) Usable Fuel (6.676 lb/gal) Location Arm (inches) Preselector Tank high Level Setting cut-off Sensor cut-off (lb) (US gal) Outboard 1 7,716 1,155 1327.04 Outboard 2 7,716 1,155 1327.04 Inboard 1 29,762 4,458 1156.88 Inboard 2 29,762 4,458 1156.88 Total 74,956 11226 Fuel Management. Fuel must be loaded symmetrically in outboard tanks first; fuel must be used from inboard tanks first. Maximum allowable wing fuel asymmetry is 8,820 lb (refere to latest EASA approved AFM revision). . Oil Capacity. Engine oil capacity 24.4 lb/engine usable (at 8.1 lb/gal) with engine moment arm 1011.10 in. Maximum Operating Altitude. 40,000 ft. Equipment. The basic required equipment as prescribed in the applicable Federal Aviation Regulations must be installed. Airbus equipment list document AI/V 341/75 as revised identifies all required equipment and all optional equipment approved by the Direction General de l'Aviation Civile (D.G.A.C.) of France. In addition the following is required. EASA-approved US Airplane Flight Manual. Other Information. See "Data Pertinent to all A300 Models (except the A300B4-600, A300B4-600R, A300F4-600R and A300C4-600R series)" A35EU Page 8 of 71 III. Type A300, Model B4-2C (Transport Category Airplane), approved June 30, 1976. TC Surrendered on February 1, 2026 Engine. 2 - General Electric Turbofan, Model CF6-50C (Data Sheet FAA No. FAA E 23 EA3 part B) APU. Airesearch TS CP 700-5 (TSOC77 SC 6203) Fuel. (a) The following fuels are eligible for engines and APU: MIL-T-5624 H Grades JP-4 or JP-5 AST-MD-1655-65T Grades Jet A, A1 (JP-1) and Jet B AST-ES-2-74 Grades Jet A, A1 and Jet B French specifications are: Air 3404 Air 3407 Air 3405 With JP-4 or Jet B fuel, the following limitation apply (1) Maximum altitude of 15,000 ft with gravity fuel supply from inboard tanks. (2) Maximum altitude of 20,000 ft with gravity fuel supply from outboard tanks. (b) The following additives may be used as approved fuels for engine and APU: (1) Phillips PFA-55MB or anti-icing additive to specifications MIL-I-27686 E at a concentration not in excess of 0.15 percent by volume. (2) Sohio Biobor JF biocide additive at a concentration not in excess of 20 ppm elemental boron (270 ppm total additive) (3) Shell ASA anti-static additive at a concentration that will provide not in excess of 300 conductivity units which is approximately equivalent to one ppm. Oil. (a) The following oils are eligible for the CF6-50 Engines: Synthetic type conforming to GE specification D 50 T F1, Classes A or B. (GE Service Bulletin No. 79-1 lists approved brand oils.) (b) The following oil is eligible for APU: See Maintenance Manual TSCP 700, Chap. 49.20.00 Table 303 Engine Limits. Static thrust, sea level Takeoff (5 Min) - (flat to 86ºF) 50,400 lb Maximum Continuous (flat to 86ºF) 46,300 lb Maximum permissible engine rotor operating speeds N1 (Low Compressor) 4,068 rpm (118.5%) N2 (Low Compressor) 10,761 rpm (109.5%) Maximum permissible engine temperature Turbine exhaust gas temperature at turbine outlet Takeoff (5 min) 945ºC Maximum Continuous 910ºC Maximum acceleration (2 min) 960ºC Starting: Up to 40 Sec. 1652ºF (900ºC) Above 40 Sec. 1382ºF (750ºC) A35EU Page 9 of 71 III. Type A300, Model B4-2C (Transport Category Airplane), (cont'd) Oil Maximum permissible outlet temperature Continuous operation 320ºF (160ºC) Transient operation limited to 15 min. 347ºF (175ºC) APU Limits. Power rating Maximum at sea level 142 hp. Maximum rotor speeds Low pressure speed (N1) 30,910 rpm (110%) High pressure speed (N2) 38,845 rpm (110%) Maximum exhaust gas temperature 1,085ºF (585ºC) Airspeed Limits (IAS). BASIC MODEL VARIANTS 02, 03 and 14 Max. Takeoff Weight 150,000 kg 157,500 kg VMO (Maximum Operating) Up to MMO (Maximum Operating) At and over 360K 25,400 ft 0.86 25,400 ft 345 K 25,000 ft 0.86/0.82 (See Note 3) 25,000 ft VA (Maneuvering) See EASA Approved US Airplane Flight Manual VFE Slat Positions Flap Positions Takeoff 16 0 250 K Takeoff & Approach 16 8 215 K Takeoff, Approach Land 16 15 205 K Landing 25 25 180 K Enroute 16 0 210 K (M=0.47) VLO (Landing Gear) Extension 270 K Retraction 240 K VLE (Landing Gear Extended) 270 K (M=0.59) VMC (Minimum Control) Speed with the Critical Engine Inoperative In flight - VMCA 110 KIAS - 105 KCAS Takeoff and Landing - VMCG 106 KIAS - 101.5 KCAS V (Tires Limitation) 195.5 KCAS A35EU Page 10 of 71 III. Type A300, Model B4-2C (Transport Category Airplane), (cont'd) C.G. Range. (Landing Gear Extended) FORWARD AFT Gross Weight Enroute & Takeoff Enroute & Takeoff Landing Landing Max taxi Max taxi 18% MAC to to (Sta.1162.82) All All All 128,000 kg 282,187 lb weights weights weights 128,000 kg 282,187 lb Linear varia- 18% MAC 35% MAC 33% MAC to to tion between (Sta. (Sta. (Sta. 122,000 kg 268,960 lb 18% MAC and 1162.82) 1202.13) 1201.83) 15% MAC Below Below 15% MAC 122,000 kg 268,960 lb (Sta.1155.07) Landing gear retraction moment is 74,772 in lb., gear retraction moves c.g. forward. Maximum Weights. Basic Model Variant 02 with mod 1652 Variant 03 with Mods 1652 & 2032 Variant 14 with mod 6193 kg lb kg lb kg lb kg lb Taxi Weight Takeoff Weight Landing Weight Zero Fuel Weight Gear Jacking Weight 150,900 150,000 133,000 122,000 150,000 332,672 330,687 293,210 268,960 330,687 158,400 157,500 133,000 122,000 157,500 349,206 347,222 293,210 268,960 347,222 158,400 157,500 134,000 124,000 157,500 349,206 347,222 295,410 273,370 347,222 158,400 157,500 134,000 126,000 157,500 349,206 347,222 295,410 277,780 347,222 Minimum Crew. For all Flights: Pilot, Copilot and Flight Engineer Maximum Passengers. 345 - Based on compliance with FAR 25 emergency exit requirements. Emergency evacuation demonstration of 25.803(c) has been performed with 330 passengers. See DGAC approved interior arrangement drawing for maximum passenger capacity approved for each airplane as delivered. Maximum Baggage. Forward freight compartment: max admissible load 23,980 lb. - With containers: 12 x 2,030 lb. or 6 x 5,660 lb. when Mod. 1844 is incorporated - A maximum container weight of 3,500 lb each side or 7000 lb both sides is permitted at station 22, 23 and 24 when Mod. 2317 is incorporated. - With pallets: 4 x 8,300 lb. - Split engine transport: - When Mod. 2001 is incorporated - Maximum weight of each pallet must not exceed 8,200 lb. - Pallets, engine stands and pallet net must be in accordance with specification AI/TI-431/77 Middle freight compartment: max admissible load 23,980 lb. with containers 8 x 2,830 lb or 4 x 5,660 lb. when Mod. 1844 is incorporated A maximum of 3,500 lb. each side or 7,000 lb. both sides is permitted at station 42 when Mod. 0470 is incorporated and at station 42 when Mod. 2317 is incorporated. Aft freight compartment: Maximum loading 5,512 lb. A35EU Page 11 of 71 III. Type A300, Model B4-2C (Transport Category Airplane), (cont'd) Fuel Capacity. Usable fuel tank capacity (lb) - Density 6.676 lb./US gal. Without Mod 1664 Without Mod 1664 Location Preselector Tank high level Preselector Tank high level Arm (in.) Cutoff sensor cutoff cutoff sensor cutoff (lb) lb/U.S. gal (lb) lb/U.S. gal Outboard 1 7,716 7,942 7,710 7,994 1327.04 1,189 1,197 Outboard 2 7,716 7,942 7,710 79,941 1327.04 1,189 1,197 Inboard 1 29,762 29,791 29,760 30,281 1156.88 4,462 4,535 Inboard 2 29,762 29,791 29,760 30,281 1156.88 4,462 4,535 Central 24,251 24,701 29,760 30,346 1106.10 3,699 4,545 Total 99,207 100,167 104,700 106,896 15,001 16,009 Fuel Management. Fuel must be loaded symmetrically in outboard tanks first; fuel must be used from inboard tanks first. Maximum allowable wing fuel asymmetry is 8,820 lb (refer to latest EASA approved AFM revision). . Oil Capacity. Engine oil capacity 24.4 lb/engine usable (at 8.1 lb/gal.) with engine moment arm 1011.10 in. Maximum Operating Altitude. 40,000 ft. Equipment. The basic required equipment as prescribed in the applicable Federal Aviation Regulations must be installed. Airbus equipment list document AI/V 333/75 as revised identifies all required equipment and all optional equipment approved by the Direction General de l'Aviation Civile (D.G.A.C.) of France. In addition the following is required: EASA-Approved US Airplane Flight Manual. Other Information. See "Data Pertinent to All 300 Model (except the A300B4-600, A300B4-600R, A300F4-600R and A300C4-600R series)" A35EU Page 12 of 71 IV. Type A300, Model B2K-3C (Transport Category Airplane) approved June 30, 1976. TC Surrendered on August 9, 2023 Engines. 2 - General Electric Turbofan, Model CF6-50C (Data Sheet FAA No. FAA E 23 EA3 part B) APU. Airesearch TS CP 700-5 (TSO C77 SC6203) Fuel. (a) The following fuels are eligible for engines and APU. MIL-T-5624 H Grades JP-4 or JP-5 AST-MD-1655-65T Grades Jet A, A1 (JP-1) and Jet B AST-TS-2-74 Grades Jet A, A1 and Jet B French specifications are: Air 3404 Air 3407 Air 3405 With JP-4 or Jet B fuel, the following limitations apply: (1) Maximum altitude of 15,000 ft with gravity fuel supply from outboard tanks. (2) Maximum altitude of 20,000 ft with gravity fuel supply from outboard tanks. (b) The following additives may be used in approved fuels for engine and APU: (1) Phillips PFA-55MB or anti-icing additive to specifications MIL-I-27686 E at a concentration not in excess of 0.15 percent by volume. (2) Sohio Biobor JF biocide additive at a concentration not in excess of 20 ppm elemental boron (270 ppm total additive). (3) Shell ASA-3 anti-static additive at a concentration that will provide not in excess of 300 conductivity units which is approximately equivalent to one ppm. Oil. (a) The following oils are eligible for the CF6-50 engine: Synthetic type conforming to GE specification D 50 T F1, Classes A or B. (GE Service Bulletin No. 79-1 list approved brand oils). (b) The following oil is eligible for APU: See Maintenance Manual TSCP 700, Chap. 49.20.00 Table 303. Engine Limits. Static thrust, sea level Takeoff (5 Min) - (flat to 86ºF) 50,400 lb Maximum continuous (flat to 85ºF) 46,300 lb Maximum permissible engine rotor operating speeds N1 (Low compressor) 4,068 rpm (118.5%) N2 (High compressor) 10,761 rpm (109.5%) Maximum permissible engine temperature Turbine exhaust gas temperature at turbine outlet Takeoff (5 min) 945ºC Maximum continuous 910ºC Maximum acceleration (2 min) 960ºC Starting: Up to 40 sec. 1,652ºF (900ºC) Above 40 sec. 1,382ºF (750ºC) A35EU Page 13 of 71 IV. Type A300, Model B2K-3C (Transport Category Airplane) (cont'd) Engine Limits. (cont’d) Oil Maximum permissible outlet temperature Continuous operation 320ºF (160ºC) Transient operation limited to 15 min. 347ºF (175ºC) APU Limits. Power rating Maximum at sea level 142 hp. Maximum rotor speeds Low pressure speed (N1) 30,910 rpm (110%) High pressure speed (N2) 38,845 rpm (110%) Maximum Exhaust gas temperature 1,085ºF (585ºC) Airspeed Limits (IAS). VMO (Maximum Operating) up to 25,400 ft 360 K. MMO (Maximum Operating at and over 25,400 ft 0.86 M VA (Maneuvering) See EASA Approved US Airplane Flight Manual VFE Slat Positions Flap Positions Takeoff 16 0 250 K Takeoff 16 8 215 K Approach 16 15 205 K Landing 25 25 180 K Enroute 20 0 210 K (M=0.47) VLO (Landing Gear) Extension 270 K Retraction 240 K VLE (Landing Gear Extended) 270 K (M=0.59) VMC (Minimum Control) Speed with the Critical Engine Inoperative In flight - VMCA 110 KIAS - 105 KCAS Takeoff and Landing - VMCG 106 KIAS - 101.5 KCAS V (Tires Limitation) 182.5 KCAS A35EU Page 14 of 71 IV. Type A300, Model B2K-3C (Transport Category Airplane) (cont'd) C.G. Range. (Landing Gear Extended) FORWARD AFT Gross Weight Enroute & Takeoff Enroute & Takeoff Landing Landing 142,900 kg 315,040 lb 18% MAC to to (Sta.1162.82) All All All 125,500 kg 277,042 lb weights weights weights 125,000 kg 277,042 lb Linear varia- 18% MAC 35% MAC 33% MAC to to tion between (Sta. (Sta. (Sta. 120,500 kg 265,657 lb 18% MAC and 1162.82) 1202.13) 1201.92) 15% MAC Below Below 15% MAC 120,500 kg 265,657 lb (Sta.1155.07) Landing gear retraction moment is 68,686 in lb., gear retraction moves c.g. forward. Maximum Weights. kg lb Taxi Weight 142,900 315,040 Takeoff Weight 142,000 313,056 Landing Weight 130,000 286,601 Zero Fuel Weight 120,500 256,657 Gear Jacking Weight 142,000 313,056 Minimum Crew. For all Flights: Pilot, Copilot and Flight Engineer Maximum Passengers. 345 - Based on compliance with FAR 25 emergency exit requirements. Emergency evacuation demonstration of 25.803(c) has been performed with 330 passengers. See DGAC approved interior arrangement drawing for maximum passenger capacity approved for each airplane as delivered. Maximum Baggage. Forward freight compartment with containers: 12 x 2,830 lb. Middle freight compartment with containers: 8 x 2,830 lb. Aft freight compartment: Maximum loading: 5,512 lb. Fuel Capacity. Fuel Tank Capacity (lb.) Usable Fuel (6.676 lb/gal) Location Arm (inches) Preselector Tank high Level Setting cut-off Sensor cut-off (lb) (US gal) Outboard 1 7,716 1,155 1327.04 Outboard 2 7,716 1,155 1327.04 Inboard 1 29,762 4,458 1156.88 Inboard 2 29,762 4,458 1156.88 Total 74,956 11,226 A35EU Page 15 of 71 IV. Type A300, Model B2K-3C (Transport Category Airplane) (cont'd) Fuel Management. Fuel must be loaded symmetrically in outboard tanks first; fuel must be used from inboard tanks first. Maximum allowable wing fuel asymmetry is 8,820 lb (refere to latest EASA approved AFM revision). . Oil Capacity. Engine oil capacity 24.4 lb/engine usable (at 8.1 lb/gal.) with engine moment arm 1011.10 in. Maximum Operating Altitude. 40,000 ft. Equipment. The basic required equipment as prescribed in the applicable Federal Aviation Regulations must be installed. Airbus equipment list document AI/V 760/76 as revised identifies all required equipment and all optional equipment approved by the Direction General de l'Aviation Civile (D.G.A.C.) of France. In addition the following is required. EASA-approved US Airplane Flight Manual. Other Information. See "Data Pertinent to All A300 Models (except the A300B4-600, A300B4-600R, A300F4-600R and A300C4-600R series)" A35EU Page 16 of 71 V. Type A300, Model B4-103 (Transport Category Airplane), approved October 4, 1979. TC Surrendered on February 1, 2026 Engines. 2 - General Electric Turbofan, Model CF-6-50C2 (See Note 7). (Data Sheet FAA No. FAA E 23 EA3 Part B) APU. Airesearch TS CP 700-5 (TSO C77 SC 6203) Fuel. (a) The following fuels are eligible for engines and APU: MIL-T-5624 H Grades JP-4 or JP-5 AST-MD-1655-65T Grades Jet A, A1 (JP-1) and Jet B AST-ES-2-74 Grades Jet A, A1 and Jet B French specifications are: Air 3404 Air 3407 Air 3405 With JP-4 or Jet B fuel, the following limitations apply: (1) Maximum altitude of 15,000 ft with gravity fuel supply from inboard tanks. (2) Maximum altitude of 20,000 ft with gravity fuel supply from outboard tanks. (b) The following additives may be used in apporved fuels for engine and APU: (1) Phillips PFA-55MB or anti-icing additive to specifications MIL-I-27686 E at a concentration not in excess of 0.15 percent by volume. (2) Sohio Biobor JF biocide additive at a concentration not in excess of 20 ppm elemental boron (270 ppm total additive). (3) Shell ASA anti-static additive at a concentration that will provide not in excess of 300 conductivity units which is approximately equivalent to one ppm. (a) The following oils are eligible for the CF6-50 engine: Synthetic type conforming to GE specification D 50 T F1, Classes A or B. (b) The following oil is eligible for the APU: See Maintenance Manual TSCP 700 Chap. 49.20.00 Table 303. Engine Limits. Static thrust, sea level Takeoff (5 Min) - (flat to 86ºF) 51,800 lb Maximum Continuous - (flat to 86ºF) 46,300 lb Maximum permissible engine rotor operating speeds N1 (Low Compressor) 4,068 rpm (118.5%) N2 (High Compressor) 10,761 rpm (109.5%) Maximum permissible engine temperature Turbine exhaust gas temperature at turbine outlet Takeoff (5 min) 945ºC Maximum Continuous 910ºC Maximum acceleration (2 min) 960ºC Starting: Up to 40 Sec. 1,652ºF (900ºC) Above 40 Sec. 1,382ºF (750ºC) Oil Maximum permissible outlet temperature Continuous operation 320ºF (160ºC) Transient operation limited to 15 min. 347ºF (175ºC) A35EU Page 17 of 71 V. Type A300, Model B4-103 (Transport Category Airplane) (cont'd). APU Limits. Power rating Maximum at sea level 142 hp. Maximum rotor speeds Low pressure speed (N1) 30,910 rpm (110%) High pressure speed (N2) 38,845 rpm (110%) Maximum Exhaust gas temperature 1,085ºF (585ºC) Airspeed Limits (IAS). Basic Model Variants 02, 03, 14 Max. Takeoff Weight 150,000 kg 157,500 kg VMO (Maximum Operating) Up to MMO (Maximum Operating) At and over 360 K 25,400 ft 0.86 25,400 ft 345 K 25,000 ft 0.86/0.82 (See Note 4) 25,000 ft VA (Maneuvering) See EASA Approved US Airplane Flight Manual VFE Slat Positions Flap Positions Takeoff 16 0 250 K Takeoff 16 8 215 K Approach 16 15 205 K Landing 25 25 180 K Enroute 16 0 210 K (M=0.47) VLO (Landing Gear) Extension 270 K Retraction 240 K Airspeed Limits (cont'd) VLE (Landing Gear Extended) 270 K (M=0.59) VMC (Minimum Control) Speed with the Critical Engine Inoperative In flight - VMCA 112 KIAS – 107.5 KCAS Takeoff and Landing - VMCG 107 KIAS - 102.5 KCAS V (Tires Limitation) 195.5 KCAS (225 mph) A35EU Page 18 of 71 V. Type A300, Model B4-103 (Transport Category Airplane) (cont'd) C.G. Range. (Landing Gear Extended) FORWARD AFT Gross Weight Enroute & Takeoff Enroute & Takeoff Landing Landing Max Taxi Max Taxi 18% MAC to to (Sta.1162.82) All All All 128,000 kg 282,187 lb weights weights weights 128,000 kg 282,187 lb Linear varia- 18% MAC 35% MAC 33% MAC to to tion between (Sta. (Sta. (Sta. 122,000 kg 268,960 lb 18% MAC and 1162.82) 1202.13) 1201.83) 15% MAC Below Below 15% MAC 122,000 kg 268,960 lb (Sta.1155.07) Landing gear retraction moment is 74,772 in lb., gear retraction moves c.g. forward. Maximum Weights. Basic Model Variant 02 with mod 1652 Variant 03 with Mods 1652 & 2032 Variant 14 with mod 6193 kg lb kg lb lb kg lb kg Taxi Weight Takeoff Weight Landing Weight Zero Fuel Weight Gear Jacking Weight 150,900 150,000 133,000 122,000 150,000 332,672 330,687 293,210 268,960 330,687 158,400 157,500 133,000 122,000 157,500 349,206 347,222 293,210 268,960 347,222 158,400 157,500 134,000 124,000 157,500 349,206 347,222 295,410 273,370 347,222 158,400 157,500 134,000 126,000 157,500 349,206 347,222 295,410 277,780 347,222 Minimum Crew. For all Flights: Pilot, Copilot and Flight Engineer. Maximum Passengers. 345 - Based on compliance with FAR 25 emergency exit requirements. Emergency evacuation demonstration of 25.803(c) has been performed with 330 passengers. See DGAC approved interior arrangement drawing for maximum passenger capacity approved for each airplane as delivered. Maximum Baggage. Forward freight compartment: Max admissible load 36,600 lb. - With containers: 12 x 2830 lb. or 6 x 5660 lb. when Mod. 1844 is incorporated - A maximum container weight of 3500 lb each side or 7000 lb both sides is permitted at station 22, 23 and 24 when Mod. 2317 is incorporated. - With pallets: 4 x 8,300 lb. A maximum pallet weight of 10,200 lb is permitted at station 22 when Mod. 2,488 is incorporated, OR 6 x 5,660 lb. when Mod. 1844 and 4171 are incorporated. A35EU Page 19 of 71 V. Type A300, Model B4-103 (Transport Category Airplane) (cont'd). Maximum Baggage (cont'd) A maximum pallet weight 7,000 lb is permitted at stations 22, 23, 24 when Mods. 1844, 2317 and 4171 are incorporated. - Split engine transport: - When Mod. 2001 is incorporated - Maximum weight of each pallet must not exceed 8200 lb. - Pallets, engine stands and pallet net must be in accordance with specification AI/TI-431/77 Middle freight compartment: Max admissible load 23,980 lb. - With containers: 8 x 2,830 lb or 4 x 5,660 lb. when Mod. 1844 is incorporated - With pallets: 2 x 5,660 lb. 2 x 7,000 lb. when Mods 1844, 2317 and 4171 are incorporated. A maximum of 3,500 lb. each side or 7,000 lb. both sides is permitted at station 41 when Mod. 0470 is incorporated and at station 42 when Mod. 2317 is incorporated. Aft freight compartment: Maximum loading 5,512 lb. Fuel Capacity. Usable fuel tank capacity (lb) - Density 6,676 lb./US gal. Without Mod 1664 With Mod 1664 Location Preselector Tank high level Preselector Tank high level Arm (in.) cutoff sensor cutoff cutoff sensor cutoff (lb) lb/U.S. gal (lb) lb/U.S. gal Outboard 1 7,716 7,942 7,710 7,994 1327.04 1,189 1,197 Outboard 2 7,716 7,942 7,710 7,994 1327.04 1,189 1,197 Inboard 1 29,762 29,791 29,760 30,281 1156.88 4,462 4,535 Inboard 2 29,762 29,791 29,760 30,281 1156.88 4,462 4,535 Central 24,251 24,701 29,760 30,346 1106.10 3,699 4,545 Total 99,207 100,167 104,700 106,896 15.001 16,009 Fuel Management. Fuel must be loaded symmetrically in outboard tanks first; fuel must be used from inboard tanks first. Maximum allowable wing fuel asymmetry is 8,820 lb (refere to latest EASA approved AFM revision). . Oil Capacity. Engine oil capacity 24.4 lb/engine usable (at 8.1 lb/gal.) with engine moment arm 1011.10 in. A35EU Page 20 of 71 V. Type A300, Model B4-103 (Transport Category Airplane) (cont'd). Maximum Operating Altitude. 40,000 ft. Equipment. The basic required equipment as prescribed in the applicable Federal Aviation Regulations must be installed. Airbus equipment list document AI/V 549/79 as revised identifies all required equipment and all optional equipment approved by the Direction General de l'Aviation Civile (D.G.A.C.) of France. In addition the following is required: EASA-Approved US Airplane Flight Manual. Other Information. See "Data Pertinent to All A300 Models (except the A300B4-600, A300B4-600R, A300F4-600R and A300C4-600R Series)" A35EU Page 21 of 71 VI. Type A300, Model B2-203 (Transport Category Airplane) approved October 1, 1980. TC Surrendered on August 9, 2023 Engines. 2 - General Electric Turbofan, Model CF6-50C2 (See Note 7). Data Sheet FAA: No. E 23 EA3 - Part B. APU. Airesearch TS CP 700-5 (TSO C77 SC 6203) Fuel. (a) The following fuels are eligible for engines and APU: MIL-T-5624H Grades JP-4 or JP-5 AST-MD-1665-65T Grades Jet A, A1 (JP-1) and Jet B AST-ES-2-74 Grades Jet A, A1 and Jet B French specifications are: Air 3404 Air 3407 Air 3405 With JP-4 or Jet B fuel, the following limitations apply: (1) Maximum altitude of 15,000 ft with gravity fuel supply from inboard tanks. (2) Maximum altitude of 20,000 ft with gravity fuel supply from outboard tanks. (b) The following additives may be used in approved fuels for engines and APU: (1) Philips PFA-55MB or anti-icing additive to specifications MIL-I-27686 E at a concentration not in excess of 0.15 percent by volume. (2) Sohio Biobor JF biocide additive at a concentration not in excess of 20 ppm elemental boron (270 ppm total additive). (3) Shell ASA-3 anti-static additive at a concentration that will provide not in excess of 300 conductivity units which is approximately equivalent to one ppm. Oil. (a) The following oils are eligible for the CF6-50 engine: Synthetic type conforming to GE specifications D 50 T F1, Classes A or B. (GE Service Bulletin No. 79-1 lists approved brand oils.) (b) The following oil is eligible for the APU: See Maintenance Manual TS CP 700, Chap. 49.20.00 Table 303. Engine Limits. Static thrust, sea level Takeoff (5 min) - (flat to 86ºF) 51,800 lb Maximum Continuous (flat to 85ºF) 46,300 lb Maximum permissible engine rotor operating speeds N1 (Low compressor) 4068 rpm (118.5%) N2 (High compressor) 10,761 rpm (109.5%) Maximum permissible engine temperature Turbine exhaust gas temperature at turbine outlet Takeoff (5 min) 945ºC Maximum Continuous 910ºC Maximum acceleration (2 min) 960ºC Starting: Up to 40 Sec. 1652ºF (900ºC) Above 40 Sec. 1382ºF (750ºC) Oil Maximum permissible outlet temperature Continuous operation 320ºF (160ºC) Transient operation limited to 15 min. 347º (175ºC) A35EU Page 22 of 71 VI. Type A300, Model B2-203 (Transport Category Airplane) (cont'd) APU Limits. Power rating Maximum at sea level 142 hp. Maximum rotor speeds Low pressure speed (N1) 30,910 rpm (110%) High pressure speed (N2) 38,845 rpm (110%) Maximum exhaust gas temperature 1,085ºF (585ºC) VA (Maneuvering) See EASA Approved US Airplane Flight Manual Airspeed Limits (IAS). VMO (Maximum Operating) up to 28,400 ft 345 K. MMO (Maximum Operating) at and over 28,000 ft 0.86 VA (Maneuvering) See EASA Approved US Airplane Flight Manual VFE Slat Positions Flap Positions Takeoff 16 0 250 K Takeoff 16 8 215 K Approach 16 15 205 K Landing 25 25 180 K Enroute 16 0 210 K (M=0.47) VLO (Landing Gear) Extension 270 K Retraction 240 K VLE (Landing Gear Extended) 270 K (M=0.59) VMC (Minimum Control) Speed with the Critical Engine Inoperative In flight - VMCA 112 KIAS - 105 KCAS Takeoff and Landing - VMCG 107 KIAS - 102.5 KCAS V (Tires Limitation) 195.5 KCAS C.G. Range. (Landing Gear Extended) FORWARD AFT Gross Weight Enroute & Takeoff Enroute & Takeoff Landing Landing 142,900 kg 315,040 lb 18% MAC to to (Sta.1162.82) All All All 125,500 kg 277,042 lb weights weights weights 125,500 kg 277,042 lb Linear varia- 18% MAC 35% MAC 33% MAC to to tion between (Sta. (Sta. (Sta. 120,500 kg 265,657 lb 18% MAC and 1162.82) 1202.13) 1201.92) 15% MAC Below Below 15% MAC 120,500 kg 265,657 lb (Sta.1155.07) Landing gear retraction moment is 68,686 in lb., gear retraction moves c.g. forward. A35EU Page 23 of 71 VI. Type A300, Model B2-203 (Transport Category Airplane) (cont'd) Maximum Weights. kg lb Taxi Weight 142,900 315,040 Takeoff Weight 142,000 313,056 Landing Weight 130,000 286,601 Zero Fuel Weight 120,500 265,657 Gear Jacking Weight 142,000 313,056 Minimum Crew. For all Flight: Pilot, Copilot and Flight Engineer Maximum Passengers. 345 - Based on compliance with FAR 25 emergency exit requirements. Emergency evacuation demonstration of 25.803(c) has been performed with 330 passengers. See DGAC approved interior arrangement drawing for maximum passenger capacity approved for each airplane as delivered. Maximum Baggage. Forward freight compartment with containers: 12 x 2,830 lb. Middle freight compartment with containers: 8 x 2,830 lb. Aft freight compartment: Maximum loading: 5,512 lb. Fuel Capacity. Fuel Tank Capacity (lb.) Usable Fuel (6.676 lb/gal) Location Arm (inches) Preselector Tank high Level Setting cut-off Sensor cut-off (lb) (US gal) Outboard 1 7,716 1,155 1327.04 Outboard 2 7,716 1,155 1327.04 Inboard 1 29,762 4,458 1156.88 Inboard 2 29,762 4,458 1156.88 Total 74,956 11,226 Fuel Management. Fuel must be loaded symmetrically in outboard tanks first; fuel must be used from inboard tanks first. Maximum allowable wing fuel asymmetry is 8,820 lb (refer to latest EASA approved AFM revision). Oil Capacity. Engine oil capacity 24.4 lb/engine usable (at 8.1 lb/gal.) with engine moment arm 1011.10 in. Maximum Operating Altitude. 40,000 ft. Equipment. The basic required equipment as prescribed in the applicable Federal Aviation Regulations must be installed. Airbus equipment list document AI/V 947/80 as revised identifies all required equipment and all optional equipment approved by the Direction General de l'Aviation Civile (D.G.A.C.) of France. In addition the following is required. EASA-approved US Airplane Flight Manual plus Document AI/V-F 902/79, Instrument Markings and Placards. Other Information. See "Data Pertinent to All A300 Models (except the A300B4-600, A300B4-600R, A300F4-600R and A300C4-600R Series)" A35EU Page 24 of 71 VII. Type A300, Model B4-203 (Transport Category Airplane) approved October 2, 1981. TC Surrendered on February 1, 2026 Engines. 2 - General Electric Turbofan, Model CF6-50C2 (See Note 7). (Data Sheet FAA No. E23EA3 - Part B) APU. Airesearch TS CP 700-5 (TSO C77 SC 6203) Fuel. (a) The following fuels are eligible for engines and APU: MIL-T-5624H Grades JP-4 or JP-5 AST-MD-1655-65T Grades Jet A, A1 (JP-1) and Jet B AST-ES-2-74 Grades Jet A, A1 and Jet B French specifications are: Air 3404 Air 3407 Air 3405 With JP-4 or Jet B fuel, the following limitations apply: (1) Maximum altitude of 15,000 ft with gravity fuel supply from inboard tanks. (2) Maximum altitude of 20,000 ft with gravity fuel supply from outboard tanks. (b) The following additives may be used in approved fuels for engines and APU: (1) Philips PFA-55MB or anti-icing additive to specifications MIL-I-27686 E at a concentration not in excess of 0.15 percent by volume. (2) Sohio Biobor JF biocide additive at a concentration not in excess of 20 ppm elemental boron (270 ppm total additive). (3) Shell ASA-3 anti-static additive at a concentration that will provide not in excess of 300 conductivity units which is approximately equivalent to one ppm. Oil. (a) The following oils are eligible for the CF6-50 engine: Synthetic type conforming to GE specifications D 50 T F1, Classes A or B. (GE Service Bulletin No. 79-1 lists approved brand oils.) (b) The following oil is eligible for the APU: See Maintenance Manual TS CP 700, Chap. 49.20.00 Table 303. Engine Limits. Static thrust, sea level Takeoff (5 min) - (flat to 86ºF) 51,800 lb Maximum Continuous (flat to 85ºF) 46,300 lb Maximum permissible engine rotor operating speeds N1 (Low compressor) 4068 rpm (118.5%) N2 (High compressor) 10,761 rpm (109.5%) Maximum permissible engine temperature Turbine exhaust gas temperature at turbine outlet Takeoff (5 min) 945ºC Maximum Continuous 910ºC Maximum acceleration (2 min) 960ºC Starting: Up to 40 Sec. 1,652ºF (900ºC) Above 40 Sec. 1,382ºF (750ºC) Oil Maximum permissible outlet temperature Continuous operation 320ºF (160ºC) Transient operation limited to 15 min. 347ºF (175ºC) A35EU Page 25 of 71 VII. Type A300, Model B4-203 (Transport Category Airplane) (cont'd) APU Limits. Power rating Maximum at sea level 142 hp. Maximum rotor speeds Low pressure speed (N1) 30,910 rpm (110%) High pressure speed (N2) 38,845 rpm (110%) Maximum exhaust gas temperature 1,085ºF (585ºC) Airspeed Limits (IAS). VMO (Maximum Operating) up to 25,000 ft 345 K. MMO (Maximum Operating) at and over 25,400 ft 0.86/0.82 (See Note 3) VA (Maneuvering) See EASA Approved US Airplane Flight Manual VFE Slat Positions Flap Positions Takeoff 16 0 250 K Takeoff 16 8 215 K Approach 16 15 205 K Landing 25 25 180 K Enroute 16 0 210 K (M=0.47) VLO (Landing Gear) Extension 270 K Retraction 240 K VLE (Landing Gear Extended) 270 K (M=0.59) VMC (Minimum Control) Speed with the Critical Engine Inoperative In flight - VMCA 112 KIAS - 105 KCAS Takeoff and Landing - VMCG 107 KIAS - 102.5 KCAS V (Tires Limitation) 195.5 KCAS C.G. Range. (Landing Gear Extended) FORWARD AFT Gross Weight Enroute & Takeoff Enroute & Takeoff Landing Landing Max Taxi Max Taxi 18% MAC to to (Sta.1162.82) All All All 130,000 kg 286,600 lb weights weights weights 130,000 kg 286,642 lb Linear varia- 18% MAC 35% MAC 33% MAC to to tion between (Sta. (Sta. (Sta. 124,000 kg 273,370 lb 18% MAC and 1162.82) 1202.13) 1201.83) 15% MAC Below Below 15% MAC 124,000 kg 273,370 lb (Sta.1155.07) Landing gear retraction moment is 74,772 in lb., gear retraction moves c.g. forward. A35EU Page 26 of 71 VII. Type A300, Model B4-203 (Transport Category Airplane) (cont'd) Maximum Weights. Basic Model Variant 07 with mod 3195 kg lb kg lb Taxi Weight Takeoff Weight Landing Weight Zero Fuel Weight Gear Jacking Weight 165,900 165,000 134,000 124,000 165,000 365,740 363,760 295,410 273,370 363,750 165,900 165,000 136,000(1) 134,000(2) 126,000 165,000 365,740 363,760 299,820(1) 295,410(2) 277,782 363,750 (1) 136,000 kg slats 16º/flaps 15º (2) 134,000 kg slats 25º/flaps 25º Minimum Crew. For all Flights: Pilot, Copilot and Flight Engineer Maximum Passengers. 345 - Based on compliance with FAR 25 emergency exit requirements. Emergency evacuation demonstration of 25.803(c) has been performed with 330 passengers. See DGAC approved interior arrangement drawing for maximum passenger capacity approved for each airplane as delivered. Maximum Baggage. Forward freight compartment: Max admissible load 36,600 lb. - With containers: 12 x 2,030 lb. or 6 x 5,660 lb. when Mod. 1844 is incorporated - A maximum container weight of 3,500 lb each side or 7,000 lb both sides is permitted at station 22, 23 and 24 when Mod. 2317 is incorporated. - With pallets: 4 x 8,300 lb. A maximum pallet weight of 10,200 lb is permitted at station 22 when Mod. 2488 is incorporated, OR 6 x 5,660 lb. when Mods. 1844 and 4171 are incorporated. A maximum pallet weight 7,000 lb is permitted at stations 22, 23, 24 when Mods. 1844, 2317 and 4171 are incorporated. - Split engine transport - When Mod. 2001 is incorporated - Maximum weight of each pallet must not exceed 8,200 lb. - Pallets, engine stands and pallet net must be in accordance with specification AI/TI-431/77 Middle freight compartment: Max admissible load 23,980 lb. - With containers 8 x 2,830 lb or 4 x 5,660 lb. when Mod. 1844 is incorporated - With pallets: 2 x 5,660 lb. 2 x 7,000 lb. when Mods 1844, 2317 and 4171 are incorporated. A maximum of 3,500 lb. each side or 7000 lb. both sides is permitted at station 41 when Mod. 0470 is incorporated and at station 42 when mod. 2317 is incorporated. Aft freight compartment: Maximum loading 5512 lb. A35EU Page 27 of 71 VII. Type A300, Model B4-203 (Transport Category Airplane) (cont'd) Fuel Capacity. Usable fuel tank capacity (lb) - Density 6.676 lb./US gal. Without Mod 1664 With Mod 1664 Location Preselector Tank high level Preselector Tank high level Arm (in.) cutoff sensor cutoff cutoff sensor cutoff (lb) lb/U.S. gal (lb) lb/U.S. gal Outboard 1 7,716 7,942 7,710 7,994 1327.04 1,189 1,197 Outboard 2 7,716 7,942 7,710 7,994 1327.04 1,189 1,197 Inboard 1 29,762 29,791 29,760 30,281 1156.88 4,462 4,535 Inboard 2 29,762 29,791 29,760 30,281 1156.88 4,462 4,535 Central 24,251 24,701 29,760 30,346 1106.10 3,699 4,545 Total 99,207 100,167 104,700 106,896 15,001 16,009 Fuel Management. Fuel must be loaded symmetrically in outboard tanks first; fuel must be used from inboard tanks first. Maximum allowable wing fuel asymmetry is 8,820 lb (refere to latest EASA approved AFM revision). . Oil Capacity. Engine oil capacity 24.4 lb/engine usable (at 8.1 lb/gal.) with engine moment arm 1011.10 in. Maximum Operating Altitude. 40,000 ft. Equipment. The basic required equipment as prescribed in the applicable Federal Aviation Regulations must be installed. Airbus equipment list document AI/V-C 379/81 as revised identifies all required equipment and all optional equipment approved by the Direction General de l'Aviation Civile (D.G.A.C.) of France. In addition the following is required: EASA-Approved US Airplane Flight Manual, plus for Model B4-203, document AI/V-F 902/79. Other Information. See "Data Pertinent to All A300 Models (except the A300B4-600, A300B4-600R, A300F4-600R and A300C4-600R Series)" A35EU Page 28 of 71 DATA PERTINENT TO ALL A300 MODELS (EXCEPT THE A300B4-600, A300B4-600R, A300F4-600R AND A300C4- 600R SERIES) Datum. Station 0 (251.26 inches forward of fuselage nose) MAC. 260.15 inches (Leading edge of MAC: Sta. 1116) Leveling Means. Clinometer on the cabin rails. Control Surface Movements. To insure operation of the airplane, the movement of the various control surfaces must be carefully controlled by proper rigging of the flight control systems. The airplane must therefore be rigged in accordance with the following DGAC-approved information and data: Control surface movement inspection - Airbus Reports A300B 8.27.010 011 012 013 014 015 Rigging procedure - Airbus Reports A 007 10.063 10.094 10.095 10.100 10.102 10.103 10.105 10.114 (for type B2-1A & B2-1C) 10.123 (for type B4-2C, B2K-3C. B2-203, B4-103, & B4-203) Serial Numbers Eligible. A French "Certificat de Navigabilite pour Exportation" endorsed as noted under "Import Requirements" must be submitted for each individual aircraft for which application for U.S. certification is made. Import Requirements. An FAA Standard Airworthiness Certificate may be issued on the basis of a French "Certificat de Navigabilite pour Exportation" signed by a representative of the Direction Generale de 'Aviation Civile (D.G.A.C.) of France, containing the following statement: "The airplane covered by this certificate has been examined, tested and found to conform to the type design approved under Type Certificate No. A35EU and to be in condition for safe operation".Refer to the applicable bilateral agreement to verify eligibility for import into the United States of both new and used aircraft based on the scope of the agreement, to identify any required statements by the exporting authority on the export certificate of airworthiness (or equivalent document), and for procedures for coordinating exceptions to conformity statements on these documents. Refer to FAA Order 8130.2, Airworthiness Certification of Aircraft, for requirements for issuance of an airworthiness certificate for imported aircraft. A35EU Page 29 of 71 Certification Basis. FAR 21.29 (a)(1), based upon France/German requirements of FAR Part 25 effective February 1, 1965, including Amendments 25-1 through 25-20, plus Amendment 25-23 for Paragraphs 25.145, 25.1305, 25.1321, 23.1331, 25.1333, Amendment 25-24 for Paragraph 25.1303; Amendment 25-23 for Paragraphs 25.785 through 25.791, 25.809 through 25.812, 25.853 through 25.857, and 25.1557; Conditions Techniques Complementares as listed in DGAC documents 4080 DTA/M dated August 8, 1970, 3904 DTA/M dated July 20, 1972, and 2060 DTA/M dated March 30, 1973; Corresponding FAA certification requirements are FAR Part 25 as detailed above plus Special Conditions No. 25-52-EU-16, plus FAA Part 36 including appropriate amendments (See NOTE 8). SFAR-27 through 27-3 (see NOTE 9). Compliance has been shown with the following optional requirements: Ditching 25.801 Ice Protection 25.1419 Date of Application: February 4, 1970 Type Certificate No. A35EU, issued May 30, 1974. DGAC originally type cerificated this A300 under its type certificate number N°72, TCDS N°145. The FAA validated this product under U.S. Type Certificate Number A35EU. Effective September 28, 2003, the European 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 14 CFR § 21.29(a) for new import TCs, or § 21.101(g) for changes to TCs, applicable provisions of part 26 are included in the certification basis. For any future 14 CFR part 26 amendments, the holder of this TC must demonstrate compliance with the applicable sections Exemption 9969 This exemption grants partial relief from having to meet the requirements of § 26.11 See NOTE(10) A35EU Page 30 of 71 NOTES TO ALL A300 MODELS (EXCEPT THE A300B4-600, A300B4-600R, A300F4-600R AND A300C4-600R SERIES) NOTE 1 Reserved NOTE 2. Placards - Model A300B2-1A, B2-1C, B4-2C, B2K-3C: All placards listed in the EASA-approved US Airplane Flight Manual must be installed in the appropriate locations. Model A300B4-103, B2-203, B4-203; Instrument markings and placards must be in accordance with Document AI/V-F 902/79. NOTE 3. Airworthiness limitations/ Maintenance Instructions • Safe Life Airworthiness Limitations items are provided in the EASA approved Airworthines Limitations Section (ALS) Part 1 ref. A300 ALS Part 1. • Damage Tolerance Airworthiness Limitaion Items are provided in the EASA approved Airbus documents ref SEM2/95A-1090/05 • Fuel Airworthiness Limitations are provided in the EASA approved FAL Airbus document ref SEM2/95A1928/05 • Maintenance Review Board Report NOTE 4. For models B4-2C and B4-103 aircraft incorporating modification no. 1652 and for model B4-203 aircraft, the MMO warning selector of modification no. 1688 allows an MMO switching. MMO is 0.86 M for takeoff weights up to 153,000 kg (337,302 lb) and 0.82 M for takeoff weight greater than 153,000 kg (337,302 lb) provided the airplane is operated in accordance with the corresponding EASA approved US Airplane Flight Manual page 2.03.00 page 1. NOTE 5. Cabin Equipment Seats, galleys and other cabin equipment aft of fuselage station 28.768m (94.38 ft) must be designed for upward load factor not less than 3.0 g. NOTE 6. Cat III Maintenance Requirements Autoland Maintenance tasks and associated intervals are listed in Airbus document AI/V-C 387/79 dated March 27, 1979 Revision 1 dated April 20, 1979, and Revision 2, dated October 19, 1984. NOTE 7. Alternate Engine Installations A - Alternate Engine Models eligible 2 General Electric Model CF6-50C1 or 2 General Electric Model CF6-50C B - Engine Model Intermix 1 General Electric CF6-50C2 and 1 General Electric CF6-50C1 or 1 General Electric CF6-50C2 and 1 General Electric CF6-50C The above engine configurations are permitted when installation is in accordance with Airbus Service Bulletin No. A300-71-011 and the engines are operated in accordance with Supplement No. 4 to the EASA-approved AFM. A35EU Page 31 of 71 NOTE 8. The following FAR 36 Noise Certification by Model reflects required as well as Airbus voluntary updated compliance to later FAR-36 amendments. Model B2-1A Amendment 36-1 B2-1C 36-12 B4-2C 36-3 B2K-3C 36-3 B2-203 36-12 B4-103 36-12 B4-203 36-12 NOTE 9. Model A300 series airplanes comply with SFAR 27 through 27-3 when Airbus's Modifications No. 1024, 1318 and 1351 are installed. NOTE 10. The following models may be converted in accordance with Airbus Service Bulletin No. A300-00-001: Model A300 B2K-3C to Model A300 B2-203 Model A300 B4-2C to Model A300 B4-103 Model A300 B4-2C to Model A300 B4-203 Model A300 B4-103 to Model A300 B4-203 NOTE 11 This exemption does not grant relief from the related operational requirements. Should a person choose to operate one of the airplane models covered by this exemption under 14 CFR Part 121 or 129 beyond the operational compliance deadlines as stated in § 121.1111 or § 129.111 (EWIS ICA) that person will be required to comply with those operational requirements. A35EU Page 32 of 71 VIII. A300-B4-600 Series (A300B4-601 approved March 28, 1988; A300B4-603 and A300B4-620 approved September 19, 1988 and A300B4-622 approved January 21, 2003 ) (Transport Aircraft) Engines. 2 - General Electric CF6-80C2A1 (A300B4-601) or 2 General Electric CF6-80C2A3 (A300B4-603) (FAA Data Sheet E13NE). or 2 Pratt and Whitney JT9D-7R4H1 (A300B4-620) (FAA Data Sheet E3NE) 2 Pratt and Whitney PW 4158 (A300B4-622) (FAA Data Sheet E24NE) APU. Airesearch GTCP 331-250 (Specification 31-2891) Fuel. (a) The following fuels are eligible for engines and APU: MIL-T-5624H Grades JP-4 or JP-5 AST-MD-1655-65T Grades Jet A1 (JP-1) and Jet B AST-ES-2-74 Grades Jet A, A1 and Jet B French specifications are: Air 3404 Air 3407 Air 3405 With JP-4 or Jet B fuel, the following limitations apply: (1) Maximum altitude of 15,000 ft with gravity fuel supply from inboard tanks. (2) Maximum altitude of 20,000 ft with gravity fuel supply from outboard tanks. (b) The following additives may be used in approved fuels for engines and APU: (1) Philips PFA-55MB or anti-icing additive to specifications MIL-I-278686 E at a concentration not in excess of 0.15 percent by volume. (2) Sohio Biobor JF biocide additive at a concentration not in excess of 20 ppm elemental boron (270 ppm total additive). (3) Shell ASA-3 anti-static additive at a concentration that will provide not in excess of 300 conductivity units which is approximately equivalent to one ppm. Oil. (a) The following oils are eligible for the engines: Synthetic type conforming to GE specifications D50TF1, Classes A or B. (GE Service Bulletin No. 79-1 lists approved brand oils.) Synthetic type conforming to PW specification 521C (PW Service Bulletin No. 238 lists approved brand oils). (b) The following oil is eligible for the APU: See Maintenance Manual AIRESEARCH GTCP 331-250, Chapter 49.21.00 Table 2. A35EU Page 33 of 71 VIII. A300-B4-600 Series (A300B4-601, A300B4-603 and A300B4-620, and A300B4-622) (Transport Aircraft) (cont'd) Engine Limits. PRATT AND WHTINEY GENERAL ELECTRIC JT9D-7R4H1 PW 4158 CF6-80C2A1 CF6-80C2A3 Static Thrust, Sea Level Takeoff (5 min-up to 87 F) 56,000 lb 58,000 57,860 lb 58,950 lb Max. Cont. (up to 87 F) 50,000 lb 49,580 53,390 lb 58,780 lb Max. permissible engine rotor operating speeds N1 (Low compressor) 3,810 rpm (105.8%) 4,012 (111.4%) 3,854 rpm (117.5%) 3,854 rpm (117.5%) N2 (High compressor) 8,080 rpm (103.5%) 10,450 (105.5%) 11,055 rpm 11,055 rpm Max. permissible engine temperature – Turbine exhaust temperature at turbine outlet Takeoff (5 min) 680ºC 650ºC 960ºC 960ºC Maximum Continuous 635ºC 625ºC 925ºC 925ºC Acceleration (2 min) 680ºC 925ºC - - Starting up to 40 sec 535ºC 535ºC 870ºC 870ºC above 40 sec 535ºC 535ºC 750ºC 750ºC Oil Maximum. Permissible outlet temperature Continuous Operation 135ºC 163ºC 160ºC 160ºC Transient operation Limited to 15 min. 163ºC 177ºC 175ºC 175ºC Limited to 20 min. APU Limits. - Power rating maximum at sea level: 98.5 KW - Maximum operating speed: 43,562 rpm - Maximum gas temperature at turbine outlet: 585ºC Airspeed Limits (IAS) BASIC MODEL MAXIMUM OPERATING MACH MMO 0.82 MAXIMUM OPERATING SPEED VMO (Kt) 335 VA (Maneuvering speed): refer to EASA-approved US Airplane Flight Manual Chapter 2.03. A35EU Page 34 of 71 VIII. A300-B4-600 Series (A300B4-601, A300B4-603 and A300B4-620, and A300B4-622) (Transport Aircraft) (cont'd) VFE SLATS (º) FLAPS (º) VFE (kt) 15 0 250 15 15 215 15 20 205 30 40 175 VLO Gear extension . . . . . . . . . . . . . . 270 Kt Gear retraction . . . . . . . . . . . . . . 240 Kt VLE Landing gear extended . . . . . . . 270 Kt or M=0.59 VMC (Minimum control speed with the critical engine inoperative) B4-620 B4-601 B4-603 B4-622 Inflight - VMCA 109 KCAS 115 KCAS 115.5 KCAS 111 KCAS Take off - VMCG 107.5 KCAS 113.5 KCAS 114 KCAS 109.5 KCAS Tire Speed Limit (Ground speed limit): 195.5 kt (225 mph) C.G. Range. For C.G. envelopes, see EASA Approved US Flight Manual. Maximum Weights. BASIC MODEL kg lb Taxi Weight 165,900 365,740 Take-off weight 165,000 363,760 Landing weight 138,000 304,230 Zero fuel weight 130,000 286,600 Minimum Flight Weight. 90,000 kg. (198,410 lb) Minimum Crew. For all flights: 2 pilots Maximum Passengers. 345. For seating arrangement refer to AIRBUS specification TL 25/1110/74 Maximum Baggage. Forward compartment - Maximum load: 40,800 lbs Aft compartment - Maximum load: 28,300 lbs Bulk compartment - Maximum load: 6,110 lbs Fuel Capacity. Location Usable fuel 6.676 lb/gal (lb) (US gal) (inches) Outboard Tanks 16,332 2,446 1325.99 Inboard Tanks 61,976 9,284 1158.27 Center Tank 31,041 4,649 1102.68 TOTAL 109,349 16,379 1167.52 A35EU Page 35 of 71 VIII. A300-B4-600 Series (A300B4-601, A300B4-603 and A300B4-620, and A300B4-622) (Transport Aircraft) (cont'd) Fuel Management. Fuel must be loaded symmetrically in outboard tanks first; fuel must be used from inboard tank first. Maximum allowable wing fuel asymmetry is 4,410 lb (refere to latest EASA approved AFM revision). . Oil Capacity. GE Engine oil capacity 25.02 lb/engine usable (at 8.1 lb/gal) with engine mount arm 965.15 inches. PW - Engine oil capacity 33.40 lb/engine usable (at 8.1 lb/gal) with engine moment arm 1022.6 inches. Maximum Operating Altitude. 40,000 ft. Equipment. The basic required equipment as prescribed in the applicable Federal Aviation Regulations must be installed in the aircraft. Airbus Equipment List A1/V-C No. 401/84 as revised identifies all required equipment and all optional equipment approved by the Direction General de l'Aviation Civile (D.G.A.C.) of France. In addition, the following is required: EASA-Approved US Airplane Flight Manual. Other Information. See "Data Pertinent to all A300B4-600, A300B4-600R, A300F4-600R and A300C4-600R Series". A35EU Page 36 of 71 IX. A300B4-600R Series (A300B4-605R approved March 28, 1988, A300B4-622R approved August 1, 1991) (Transport Aircraft) Engines. 2 General Electric CF6-80C2A5 (A300B4-605R) (FAA Data Sheet E13 NE) or 2 Pratt & Whitney PW 4158 (A300B4-622R) (FAA Data Sheet E24NE) APU. Airesearch GTCP 331-250 (Specification 31-2891) Fuel. (a) The following fuels are eligible for engines and APU: MIL-T-5624H Grades JP-4 or JP-5 AST-MD-1655-65T Grades Jet A1 (JP-1) and Jet B AST-ES-2-74 Grades Jet A, A1 and Jet B Fuel (cont'd) French specifications are: Air 3404 Air 3407 Air 3405 With JP-4 or Jet B fuel, the following limitations apply: (1) Maximum altitude of 15,000 ft with gravity fuel supply from inboard tanks. (2) Maximum altitude of 20,000 ft with gravity fuel supply from outboard tanks. (b) The following additives may be used in approved fuels for engines and APU: (1) PHILLIPS PFA-55MB or anti-icing additive to specifications MIL-I-278686 E at a concentration not in excess of 0.15 percent by volume. (2) Sohio Biobor JF biocide additive at a concentration not in excess of 20 ppm elemental boron (270 ppm total additive). (3) Shell ASA-3 anti-static additive at a concentration that will provide not in excess of 300 conductivity units which is approximately equivalent to one ppm. Oil. (a) The following oils are eligible for the CF6-80C2A5 and PW 4158 engines respectively: - Synthetic type conforming to GE specifications D50TF1, Classes A or B. (GE Service Bulletin No. 79-1 lists approved brand oils.) - Synthetic type conforming to PW specification 521C (PW Service Bulletin No. 238 lists approved brand oils). (b) The following oil is eligible for the APU: See Maintenance Manual AIRESEARCH GTCP 331-250, Chapter 49.21.00 Table 2. A35EU Page 37 of 71 IX. A300B4-600R Series (A300B4-605R, A300B4-622R) (Transport Aircraft) (cont'd) Engine Limits. GENERAL ELECTRIC CF6-80C2A5 PRATT & WHITNEY PW 4158 Static Thrust, Sea Level Takeoff (5 min-up to 87ºF) Maximum Continuous (up to 87ºF) Maximum Permissible Engine Rotor Operating Speeds N1 (Low compressor) N2 (High compressor) Maximum permissible engine temperature Turbine exhaust temperature at turbine outlet Takeoff (5 min) Maximum Continuous Acceleration (2 min) Starting º up to 40 sec º above 40 sec Oil maximum permissible outlet temperature Continuous Operation Transient operation º Limited to 15 min. º Limited to 20 min. 60,100 lb. 56,210 lb. 3,854 rpm (117.5%) 10,055 rpm (112.5%) 960ºC 925ºC - 870ºC 750ºC 160ºC 175ºC 58,000 lb. 49,580 lb. 4,012 rpm (111.4%) 10,450 rpm (105.5%) 650ºC 625ºC 925ºC 535ºC 535ºC 163ºC - 177ºC APU Limits. - Power rating maximum at sea level: 98.5 KW - Maximum operating speed: 43,562 rpm - Maximum gas temperature at turbine outlet: 585ºC Airspeed Limits (IAS). MAXIMUM OPERATING MACH MMO 0.82 MAXIMUM OPERATING SPEED VMO (Kt) 335 VA (Maneuvering speed): refer to EASA-approved US Airplane Flight Manual Chapter 2.03. VFE SLATS (º) FLAPS (º) VFE (kt) 15 0 250 15 15 215 15 20 205 30 40 175 A35EU Page 38 of 71 IX. A300B4-600R Series (A300B4-605R, A300B4-622R) (Transport Aircraft) (cont'd) Airspeed Limits (IAS) (cont'd) VLO Gear extension . . . . . . . . . . . . . . 270 Kt Gear retraction . . . . . . . . . . . . . . 240 Kt VLE Landing gear extended . . . . . . . 270 Kt or M=0.59 VMC (Minimum control speed with the critical engine inoperative) A300B4-605R A300B4-622R Inflight - VMCA 117 KCAS 111 KCAS Take off - VMCG 115.5 KCAS 109,5 KCAS Tire Speed Limit (Ground speed limit): 195.5 KCAS (225 mph) C.G. Range. For C.G. envelopes, see EASA Approved US Flight Manual. Maximum Weights. BASIC MODEL VARIANT 01** VARIANT 02** VARIANT 03** kg lb kg lb kg lb kg lb Taxi Weight 171,400 377,930 172,600 380,520 172,600 380,520 168,700 371,920 Take-off Weight 170,500 375,890 171,700 378,530 171,700 378,530 167,800 369,930 Landing Weight 140,000 308,650 140,000 308,650 138,000 304,235 140,000 308,650 Zero Fuel Weight 130,000 286,600 123,000* 271,170 123,000* 271,170 131,000 288,800 *Linear variation from 130T at MTOW 170.5T to 123T at MTOW 171.7T. **Variant 01: With modification 7047 applicable only for A300B4-605R **Variant 02: With modification 7486 applicable only for A300B4-605R **Variant 03: With modification 7619 applicable only for A300B4-605R Minimum Flight Weight. 90,000 kg. (198,410 lb) Minimum Crew. For all flights: 2 pilots Maximum Passengers. 345. For seating arrangement refer to AIRBUS specification TL 25/1110/74 Maximum Baggage. Forward compartment - Maximum load: 40,800 lbs Aft compartment - Maximum load: 28,300 lbs Bulk compartment - Maximum load: 6,110 lbs Fuel Capacity. Location Usable fuel 6.676 lb/gal (lb) (US gal) (inches) Outboard Tanks 16,332 2,446 1325.99 Inboard Tanks 61,976 9,284 1158.27 Center Tank 31,041 4,649 1102.68 2182.56 Trim Tank 10,864 1627 1259.46 A35EU Page 39 of 71 IX. A300B4-600R Series (A300B4-605R, A300B4-622R) (Transport Aircraft) (cont'd) Fuel Management. Fuel must be loaded symmetrically in outboard tanks first; fuel must be used from inboard tank first. Maximum allowable wing fuel asymmetry is 4,410 lb (refere to latest EASA approved AFM revision). . Oil Capacity. GE CF6-80C2A5 - Engine Oil Capacity 25.02 lb/engine usable (at 8.1 lb/gal) with engine moment arm 965.15 inches. PW 4158 - Engine Oil Capacity 28.44 lb/engine usable (at 8.1 lb/gal) with engine moment arm 1023.80 inches. Maximum Operating Altitude. 40,000 ft. Equipment. The basic required equipment as prescribed in the applicable Federal Aviation Regulations must be installed in the aircraft. Airbus Equipment List A1/EA-A No. 413-288/88 as revised identifies all required equipment and all optional equipment approved by the Direction General de l'Aviation Civile (D.G.A.C.) of France. In addition, the following is required: EASA-Approved US Airplane Flight Manual. Other Information. See "Data Pertinent to all A300B4-600, A300B4-600R, A300F4-600R and A300C4-600R Series". A35EU Page 40 of 71 X. A300 F4-600R Series (A300F4-605R approved April 27, 1994, A300F4-622R approved July 14, 2000) (Transport Aircraft) Engines. 2 General Electric CF6-80C2A5 or 2 General Electric CF6-80C2A5F (A300F4-605R) (FAA Data Sheet E13NE) or 2 Pratt & Whitney PW 4158 (A300F4-622R) (FAA Data Sheet E24NE) APU. Airesearch GTCP 331-250 (Specification 31-2891) Fuel. (a) The following fuels are eligible for engines and APU: MIL-T-5624H Grades JP-4 or JP-5 AST-MD-1655-65T Grades Jet A1 (JP-1) and Jet B AST-ES-2-74 Grades Jet A, A1 and Jet B French specifications are: Air 3404 Air 3407 Air 3405 With JP-4 or Jet B fuel, the following limitations apply: (1) Maximum altitude of 15,000 ft with gravity fuel supply from inboard tanks. (2) Maximum altitude of 20,000 ft with gravity fuel supply from outboard tanks. (b) The following additives may be used in approved fuels for engines and APU: (1) PHILLIPS PFA-55MB or anti-icing additive to specifications MIL-I-278686 E at a concentration not in excess of 0.15 percent by volume. (2) Sohio Biobor JF biocide additive at a concentration not in excess of 20 ppm elemental boron (270 ppm total additive). (3) Shell ASA-3 anti-static additive at a concentration that will provide not in excess of 300 conductivity units which is approximately equivalent to one ppm. Oil. (a) The following oils are eligible for the CF6-80C2A5/CF6-80C2A5F and PW 4158 engines respectively: - Synthetic type conforming to GE specifications D50TF1, Classes A or B. (GE Service Bulletin No. 79-1 lists approved brand oils.) - Synthetic type conforming to PW specification 521C (PW Service Bulletin No. 238 lists approved brand oils). (b) The following oil is eligible for the APU: See Maintenance Manual AIRESEARCH GTCP 331-250, Chapter 49.21.00 Table 2. A35EU Page 41 of 71 X. A300 F4-600R Series (A300F4-605R, A300F4-622R), (Transport Aircraft ) (cont’d) Engine Limits. GENERAL ELECTRIC CF6-80C2A5 or CF6-80C2A5F PRATT & WHITNEY PW 4158 Static Thrust, Sea Level Takeoff (5 min-up to 87ºF) Maximum Continuous (up to 87ºF) Maximum permissible engine Rotor Operating Speeds N1 (Low compressor) N2 (High compressor) Maximum permissible engine temperature Turbine exhaust temperature at turbine outlet Takeoff (5 min) Maximum Continuous Acceleration (2 min) Starting º up to 40 sec º above 40 sec Oil Maximum permissible outlet temperature Continuous Operation Transient operation º Limited to 15 min. º Limited to 20 min. 60,100 lb. 56,210 lb. 3,854 rpm (117.5%) 10,055 rpm (112.5%) 960ºC 925ºC - 870ºC 750ºC 160ºC 175ºC 58,000 lb. 49,580 lb. 4,012 rpm (111.4%) 10,450 rpm (105.5%) 650ºC 625ºC 650ºC 535ºC 535ºC 163ºC - 177ºC APU Limits. - Power rating maximum at sea level: 98.5 KW - Maximum operating speed: 43,562 rpm - Maximum gas temperature at turbine outlet: 585ºC A35EU Page 42 of 71 X. A300 F4-600R Series (A300F4-605R, A300F4-622R), (Transport Aircraft) (cont’d) Airspeed Limit (IAS). BASIC MODEL VARIANT 06 VARIANT 09 MAXIMUM OPERATING MACH MMO 0.82 0.82 0.82 MAXIMUM OPERATING SPEED VMO (Kt) 335 335 335 VA (Maneuvering speed): refer to EASA-approved US Airplane Flight Manual Chapter 2.03. VFE SLATS (º) FLAPS (º) VFE (kt) 15 0 250 15 15 215 15 20 205 30 40 175 VLO Gear extension .............................270 Kt Gear retraction .............................240 Kt VLE Landing gear extended ..............270 Kt or M=0.59 VMC (Minimum control speed with the critical engine inoperative) A300F4-605R A300F4-622R Inflight – VMCA Take off – VMCG 117 KCAS 115.5 KCAS 111 KCAS 109.5 KCAS Tire Speed Limit (Ground speed limit): 195.5 KCAS (225 mph) C.G. Range. For C.G. envelopes, see EASA Approved US Flight Manual. Maximum Weights. BASIC MODEL VARIANT 06* VARIANT 09* kg Lb kg lb kg lb Taxi Weight 171,400 377,930 166,000 365,960 168,900 372,360 Take-off Weight 170,500 375,890 165,100 363,980 168,000 370,375 Landing Weight 140,000 308,650 140,600 303,970 143,300 315,900 Zero Fuel Weight 130,000 286,600 133,800 294,980 136,500 300,930 *With trim and center fuel tanks deactivated Variant 06: With modification 10395 for A300F4-605R Variant 09: With modification 12199 for A300F4-622R Minimum Flight Weight. 90,000 kg* (198,410 lb) *With mod 11392 for A300F4-605R and A300F4-622R minimum flight weight: 80,000kg (176,360 lb) Minimum Crew. For all flights: 2 pilots Maximum Passengers. Six (6) persons on the main deck per Exemption 5864 or four (4) persons on the main deck per Exemption No. 7260. (see certification basis paragraph (g) for applicability and details) A35EU Page 43 of 71 X. A300 F4-600R Series (A300F4-605R, A300F4-622R), (Transport Aircraft ) (cont’d) Maximum Baggage. Lower Forward compartment - Maximum load: 40,800 lbs Lower Aft compartment - Maximum load: 28,300 lbs Lower Bulk compartment - Maximum load: 6,110 lbs Main Deck Cargo compartment - Maximum load: 100,970 lbs For general freighter A300F4-605R: Lower Forward compartment - Maximum load: 40,800 lbs Lower Aft compartment - Maximum load: 30,400 lbs Lower Bulk compartment - Maximum load: 3,900 lbs Main Deck Cargo compartment - Maximum load: 100,900 lbs Fuel Capacity. Location Usable fuel 6.676 lb/gal (lb) (US gal) (inches) Outboard Tanks 16,332 2,446 1325.99 Inboard Tanks 61,976 9,284 1158.27 Center Tank 31,041 4,649 1102.68 Trim Tank 10,864 1627 2182.56 TOTAL 120,213 18,006 1259.46 Fuel Management. Fuel must be loaded symmetrically in outboard tanks first; fuel must be used from inboard tank first. If cargo is symmetrically loaded, maximum allowable wing fuel asymmetry is 4,410 lb (refere to latest EASA approved AFM revision). In cases of asymmetrical loading configurations, reference must be made to Weight and Balance Manual. Oil Capacity. GE CF6-80C2A5 and GE CF6-80C2A5F: Engine Oil Capacity 25.02 lb/engine usable (at 8.1 lb/gal) with engine moment arm 965.15 inches. PW 4158: Engine Oil Capacity 28.44 lb/engine usable fuel (at 8.1 lb/gal) with engine moment arm 1023.8 inches. Maximum Operating Altitude. 40,000 ft (Basic model) 35,000 ft (Variant 06) 35,000 ft (Variant 09) Equipment. The basic required equipment as prescribed in the applicable Federal Aviation Regulations must be installed in the aircraft. Airbus Equipment Lists, as revised, identifiy all required equipment and all optional equipment approved by the Direction Generale de l'Aviation Civile (D.G.A.C.) of France: - 00X00009102/C3S for A300F4-605R - 00X00009622/C3S for A300F4-622R In addition, the following is required: EASA-Approved US Airplane Flight Manual AI/ST-F3000. Other Information. See "Data Pertinent to all A300B4-600, A300B4-600R, A300F4-600R and A300C4-600R Series ". A35EU Page 44 of 71 XI. A300 C4-600R Series (A300C4-605R Variant F approved June 21, 2002), (Transport Aircraft) Engines 2 General Electric CF6-80C2A5 (FAA Data Sheet E13NE), APU. Airesearch GTCP 331-250 (Specification 31-2891) Fuel. (a) The following fuels are eligible for engines and APU: MIL-T-5624H Grades JP-4 or JP-5 AST-MD-1655-65T Grades Jet A1 (JP-1) and Jet B AST-ES-2-74 Grades Jet A, A1 and Jet B French specifications are: Air 3404 Air 3407 Air 3405 With JP-4 or Jet B fuel, the following limitations apply: (1) Maximum altitude of 15,000 ft with gravity fuel supply from inboard tanks. (2) Maximum altitude of 20,000 ft with gravity fuel supply from outboard tanks. (b) The following additives may be used in approved fuels for engines and APU: (1) PHILLIPS PFA-55MB or anti-icing additive to specifications MIL-I-278686 E at a concentration not in excess of 0.15 percent by volume. (2) Sohio Biobor JF biocide additive at a concentration not in excess of 20 ppm elemental boron (270 ppm total additive). (3) Shell ASA-3 anti-static additive at a concentration that will provide not in excess of 300 conductivity units which is approximately equivalent to one ppm. Oil. (a) The following oils are eligible for the CF6-80C2A5 Engines: - Synthetic type conforming to GE specifications D50TF1, Classes A or B. (GE Service Bulletin No. 79-1 lists approved brand oils.) (b) The following oil is eligible for the APU: See Maintenance Manual AIRESEARCH GTCP 331-250, Chapter 49.21.00 Table 2. A35EU Page 45 of 71 XI. A300 C4-600R Series (A300C4-605R Variant F), (Transport Aircraft) (cont’d) Engine Limits GENERAL ELECTRIC CF6-80C2A5 Static Thrust, Sea Level Takeoff (5 min-up to 87ºF) Maximum Continuous (up to 87ºF) 60,100 lb. 56,210 lb. Maximum permissible engine rotor operating speeds N1 (Low compressor) N2 (High compressor) 3,854 rpm (117.5%) 10,055 rpm (112.5%) Maximum permissible engine temperature Turbine exhaust temperature at turbine outlet Takeoff (5 min) Maximum Continuous Acceleration (2 min) Starting º up to 40 sec º above 40 sec 960ºC 925ºC - 870ºC 750ºC Oil Maximum Permissible Outlet Temperature Continuous Operation Transient operationº Limited to 15 min. Limited to 20 min. 320oF (160ºC) 347oF (175ºC) - APU Limits. Power rating maximum at sea level: 98.5 KW Maximum operating speed: 43,562 rpm Maximum gas temperature at turbine outlet: 1,085oF (585ºC) A35EU Page 46 of 71 XI. A300 C4-600R Series (A300C4-605R Variant F) (Transport Aircraft) (cont’d) Airspeed Limits (IAS). Basic Model MAXIMUM OPERATING MACH MMO 0.82 MAXIMUM OPERATING SPEED VMO (Kt) 335 V A (Maneuvering speed): refer to EASA-approved US Airplane Flight Manual Chapter 2.03. V FE SLATS (º) FLAPS (º) VFE (kt) 15 0 250 15 15 215 15 20 205 30 40 175 V LO Gear extension . . . . . . . . . . . . . . 270 Kt Gear retraction . . . . . . . . . . . . . . 240 Kt V LE Landing gear extended . . . . .. . . 270 Kt or M=0.59 V MC (Minimum control speed with the critical engine inoperative) A300C4-605R Variant F Inflight - VMCA 117 KCAS Take off - VMCG 115.5 KCAS Tire Speed Limit (Ground speed limit): 195.5 KCAS (225 mph) C.G. Range For C.G. envelopes, see EASA Approved US Flight Manual. Maximum Weights. Basic Model kg Lb Taxi Weight 171,400 377,930 Take-off Weight 170,500 375,890 Landing Weight 140,000 308,650 Zero Fuel Weight 130,000 286,600 Minimum Flight Weight. 90,000 kg (198,410 lb) Minimum Crew. For all flights: 2 pilots Maximum Passengers. Six (6) persons on the main deck per Exemption No. 7799 (See Certification Basis (g) paragraph) Maximum Baggage. Lower Forward compartment - Maximum load: 40,800 lbs Lower Aft compartment - Maximum load: 28,300 lbs Lower Bulk compartment - Maximum load: 6,110 lbs Main Deck Cargo compartment - Maximum load: 100,970 lbs A35EU Page 47 of 71 XI. A300 C4-600R Series (A300C4-605R Variant F) (Transport Aircraft) (cont’d) Fuel Capacity. Location Usable fuel 6.676 lb/gal (lb) (US gal) (inches) Outboard Tanks 16,332 2,446 1325.99 Inboard Tanks 61,976 9,284 1158.27 Center Tank 31,041 4,649 1102.68 Trim Tank 10,864 1627 2182.56 TOTAL 120,213 18,006 1259.46 Fuel Management. Fuel must be loaded symmetrically in outboard tanks first; fuel must be used from inboard tank first. If cargo is symmetrically loaded, maximum allowable wing fuel asymmetry is 4,410 lb. (refere to latest EASA approved AFM revision). In cases of asymmetrical loading configurations, reference must be made to Weight and Balance Manual. Oil Capacity. GE CF6-80C2A5 Engine Oil Capacity 25.02 lb/engine usable (at 8.1 lb/gal) with engine moment arm 965.15 inches. Maximum Operating Altitude. 40,000 ft Equipment. The basic required equipment as prescribed in the applicable Federal Aviation Regulations must be installed in the aircraft. Airbus Equipment Lists, as revised identifies all required equipment and all optional equipment approved by the Direction Generale de l'Aviation Civile (D.G.A.C.) of France: - 00X0009605/C3S for A300C4-605R Variant F In addition, the following is required: EASA-Approved US Airplane Flight Manual AI/ST-F3000 adapted to aircraft model. Other Information. See "Data Pertinent to all A300B4-600, A300B4-600R, A300F4-600R and A300C4-600R Series". A35EU Page 48 of 71 DATA PERTINENT TO ALL A300 B4-600, A300 B4-600R, A300 F4-600R AND A300C4-600R SERIES. Datum. Station 0 (251.26 inches forward of fuselage nose) MAC. 260.16 inches (leading edge of MAC: Sta. 1116.06 inches). Leveling Means. Clinometer on the cabin seat track rails. Serial Numbers Eligible. A French "Certificat de Navigabilite pour Exportation" endorsed as noted under "Import Requirements" must be submitted for each individual aircraft for which application for U.S. certification is made. Import Requirements. An FAA Standard Airworthiness Certificate may be issued on the basis of a French "Certificat de Navigabilite pour Exportation" signed by a representative of the Direction Generale de 'Aviation Civile (D.G.A.C.) of France, containing the following statement: "The airplane covered by this certificate has been examined, tested and found to conform to the type design approved under Type Certificate No. A35EU and to be in condition for safe operation".Refer to the applicable bilateral agreement to verify eligibility for import into the United States of both new and used aircraft based on the scope of the agreement, to identify any required statements by the exporting authority on the export certificate of airworthiness (or equivalent document), and for procedures for coordinating exceptions to conformity statements on these documents. Refer to FAA Order 8130.2, Airworthiness Certification of Aircraft, for requirements for issuance of an airworthiness certificate for imported aircraft. Certification Basis. (a) For all A300 B4-600, A300 B4-600R, A300 F4-600R and A300C4-600R series airplanes, the certification basis is FAR Part 25 at the following amendments: Amendment 1 through 21 Amendment 22 through 44 (elected) except for, 25.301 Amendment 23, 25.305(d) Amendment 23, 25.331(a)(2) Amendment 23, 25.109 Amendment 42; Amendment 45 (Elected) for paragraph 25.571; Amendment 46 (Elected) for paragraph 25.803(c), (d) and 25.809(f)(1)(iv)(v); Amendment 47 (Elected) for paragraph 25.809(f) (1) (iii); Amendment 49 (Elected) for paragraph 25.733; Amendment 54 (Elected) for paragraph 25.365(e)(i) and (e)(2). Additional later amendment Part 25 FARs for Models A300F4-605R , A300F4-622R and A300C4-605R Variant F: Amendment 54 (Elected) for paragraph 25.365(e)(3); Amendment 54 for paragraph 25.858; Amendment 72 (Elected) for paragraph 25.723; Amendment 72 for paragraph 25.783; Amendment 74 for paragraph 25.851(a)(3). Model A300F4-622R airplanes incorporating modifications for Main Deck Cargo Compartment Rearrangement (modifications 12047, 12048, 12049, 12054, 12055, 12063, 12103, 12118, 12139, 12194, 12227). For parts of the airplane that are changed or affected by these modifications, the certification basis includes the following later amendment Part 25 FARs: Amendment 86 for FAR Part 25 §§ 25.305, 25.321, 25.333, 25.341, 25.349 Amendment 91 for FAR Part 25 §§ 25.331, 25.335, 25.351, 25.473, 25.479, 25.481, 25.483, 25.485, 25.491 Amendment 91 for FAR Part 25 § 25.561 applicable to modified parts (L-shaped barrier, supemumerary seats and attachments) Amendment 86 for FAR Part 25 § 25.571 for modified parts Amendment 83 for FAR Part 25 §§ 25.853(a), (b) and (c) Amendment 51 for FAR Part 25 § 25.787 Amendment 93 for FAR Part 25 §§ 25.855, 25.857, 25.858 A35EU Page 49 of 71 Amendment 64 for FAR Part 25 § 25.561 for cockpit seats See also pargraph (g) for the exemption applicable to A300F4-622R airplanes with the above modifications incorporated. A35EU Page 50 of 71 Model A300F4-622R airplanes incorporating modifications for Lower Deck Cargo Compartment Rearrangement (modifications 12046, 12133, 12183). For parts of the airplane that are changed or affected by these modifications, the certification basis includes the following later amendment Part 25 FARs: Amendment 86 for FAR Part 25 §§ 25.305, 25.321, 25.333, 25.341, 25.349 Amendment 91 for FAR Part 25 §§ 25.331, 25.335, 25.351, 25.473, 25.479, 25.481, 25.483, 25.485, 25.491 Amendment 86 for FAR Part 25 § 25.571 for modified parts Amendment 83 for FAR Part 25 §§ 25.853(a), (b) and (c) Amendment 51 for FAR Part 25 § 25.787 Amendment 93 for FAR Part 25 §§ 25.855, 25.857, 25.858 Model A300F4-622R airplanes incorporating modifications for Weight Variant 09 (Modifications 12050, 12102, 12181, 12199). For parts of the airplane that are changed or affected by these modifications, the certification basis includes the following later amendment Part 25 FARs: Amendment 86 for FAR Part 25 §§ 25.305, 25.321, 25.333, 25.341, 25.349 Amendment 91 for FAR Part 25 §§ 25.331, 25.335, 25.351, 25.473, 25.479, 25.481, 25.483, 25.485, 25.491 Model A300F4-622R airplanes incorporating partial avionics upgrade (Modifications 13829, 13831, 13836, 13838 and 13839) For parts of the airplane that are changed or affected by these modifications, the certification basis includes the following later amendment Part 25 FARs: Amendment 144 for FAR 25.869(a)(1) FAR 25.899 FAR 25.1301(a) FAR 25.1302 FAR 25.1303(b)(5) FAR 25.1309(a)(b)(c) FAR 25.1316 FAR 25.1317 FAR 25.1329(i) FAR 25.1360 FAR 25.1362 FAR 25.1431(d) FAR 25.1457(a)(6) FAR 25.1459(e) FAR K.25.1.1 FAR K.25.1.2 FAR 25.1543(b) Amendment 98 for FAR 25.1529 Model A300F4-605R airplanes incorporating modifications for Main Deck Cargo Compartment Rearrangement (modifications 12054, 12118, 12227). For parts of the airplane that are changed or affected by these modifications, the certification basis includes the following later amendment Part 25 FARs: Amendment 86 for FAR Part 25 §§ 25.305, 25.321, 25.333, 25.341, 25.349 Amendment 91 for FAR Part 25 §§ 25.331, 25.335, 25.351, 25.473, 25.479, 25.481, 25.483, 25.485, 25.491 Amendment 86 for FAR Part 25 § 25.571 for modified parts Amendment 83 for FAR Part 25 §§ 25.853(a), (b) and (c) A35EU Page 51 of 71 Amendment 51 for FAR Part 25 § 25.787 Amendment 93 for FAR Part 25 §§ 25.855, 25.857, 25.858 Amendment 64 for FAR Part 25 § 25.561 for cockpit seats See also pargraph (g) for the exemption applicable to A300F4-605R airplanes with the above modifications incorporated. Model A300F4-605R airplanes incorporating modifications for Lower Deck Cargo Compartment Rearrangement (modifications 12046, 12133, 12183,12860). For parts of the airplane that are changed or affected by these modifications, the certification basis includes the following later amendment Part 25 FARs: Amendment 86 for FAR Part 25 §§ 25.305, 25.321, 25.333, 25.341, 25.349 Amendment 91 for FAR Part 25 §§ 25.331, 25.335, 25.351, 25.473, 25.479, 25.481, 25.483, 25.485, 25.491 Amendment 86 for FAR Part 25 § 25.571 for modified parts Amendment 83 for FAR Part 25 §§ 25.853(a), (b) and (c) Amendment 51 for FAR Part 25 § 25.787 Amendment 93 for FAR Part 25 §§ 25.855, 25.857, 25.858 A35EU Page 52 of 71 Model A300F4-605R airplanes incorporating modifications for Structural provisions for operations at Weight Variant 09 (Modifications 12050, 12102). For parts of the airplane that are changed or affected by these modifications, the certification basis includes the following later amendment Part 25 FARs: Amendment 86 for FAR Part 25 §§ 25.305, 25.321, 25.333, 25.341, 25.349 Amendment 91 for FAR Part 25 §§ 25.331, 25.335, 25.351, 25.473, 25.479, 25.481, 25.483, 25.485, 25.491 Note: FAR paragraphs at amendment 25-86 and 25-91 are revised by Vf definition used for the earlier FAA certified freighter, the A300F4-605R, through application of FAA issue paper A-101, dated May 18, 2000. (b) For precision approach and landing, the applicable technical requirements are complemented by AC 120-29 and AC 120-28C. For airplanes equipped with modification 12210, the applicable guidance material is AC 120-28D. For the automatic flight control system, the applicable technical requirements are complemented by AC 20-57A for automatic landing and by AC 25.1329-1A for cruise. (c) FAR Part 36. [See Note 4 for specific models and Amendment Levels] (d) FAR Part 34. ICAO Annex 16, Vol II, Aircraft Engine Emissions (fuel venting requirements). (e) Compliance with the following optional requirements has been established: Ditching provisions FAR 25.801 Ice Protection Provisions FAR 25.1419. (f) Special Conditions: For the Model A300F4-605R and A300F4-622R: FAA Special Conditions as published in the Federal Register 17 June 1987 through Special Condition 25-ANM-12 on lightning protection (Special Condition P-8, dated June 10, 1987), protection from unwanted effects of radio frequency energy (Special condition P-10, dated June 10, 1987), and the propulsion control system (Special Condition P-11, dated June 10, 1987). (g) Exemptions: For the Model A300F4-605R: Exemption granted in accordance with FAR 11 from FAR Part 25: No. 5864 dated March 30, 1994, allows carriage of a maximum of six (6) non- crewmembers between the flight deck and the main deck class E cargo compartment. These 6 non-crewmembers are in addition to the maximum 4 flight deck occupants for a total of 10 occupants. For the Model A300F4-622R incorporating modifications for Main Deck Cargo Compartment Rearrangement (modifications 12047, 12048, 12049, 12054, 12055, 12063, 12103, 12118, 12139, 12194, 12227): Exemption granted in accordance with FAR 11 from FAR Part 25: No. 7260 dated June 30, 2000, allows carriage of a maximum of four (4) non- crewmembers in the courier area on the main deck. These 4 non-crewmembers are in addition to the maximum 3 flight deck occupants for a total of 7 occupants. A35EU Page 53 of 71 For the model A300C4-605R Variant F model; Exemption granted in accordance with FAR 11 from FAR Part 25: No. 7799 dated June 6, 2002, allows carriage of maximum six (6) non crew members between the flight deck and the main deck Class E cargo compartment. These 6 non crewmembers are in addtion to the maximum 4 flight deck occupants for a total of 10 occupants. (h) Equivalent Safety Findings exist with respect to the following FARs: FAR part 25 § 25.841(b)(6) Amendment 38 applicable to A300F4-622R airplanes with the modification 12210 and 12211 incorporated FAR part 25 § 25.933(a) Amendment 25-40 applicable to model A300-600/A310 airplanes equipped with Pratt&Whitney engines and modifications 12262, 12263 and 12265 installed (Thrust Reverser Third Line of Defense) or airplanes equipped with General Electric engines and modifications 12349, 12350, 12511, 12514 installed (Thrust Reverser Third Line of Defence). Part 26: Continued Airworthiness and Safety Improvements for Transport Category Airplanes: Based on 14 CFR § 21.29(a) for new import TCs, or § 21.101(g) for changes to TCs, applicable provisions of part 26 are included in the certification basis. For any future 14 CFR part 26 amendments, the holder of this TC must demonstrate compliance with the applicable sections Exemption 9950 This exemption grants relief from having to meet the requirements of § 26.33 See NOTE(5) DGAC originally type cerificated this A300-600 under its type certificate number N°72, TCDS N°145. The FAA validated this product under U.S. Type Certificate Number A35EU. Effective September 28, 2003, the European Aviation Safety Agency (EASA) began oversight of this product on behalf of DGAC. A35EU Page 54 of 71 NOTES TO ALL A300B4-600, A300B4-600R, A300F4-600R, AND A300C4-600R SERIES NOTE 1 NOTE 2 NOTE 3. Airworthines Limitations/Maintenance Instructions - Safe Life Airworthiness Limitations are provided in the A300-600 Airworthiness Limitation Section (ALS) Part 1 EASA approvedref. A300-600 ALS Part 1 - Damage Tolerance Airworthiness Limitations items are provided in the EASA approved Airbus document ref. AI/SE-M2/95A.0502/06 -Maintenance Tasks to comply with Certification Maintenance Requirements (CMR’s) are listed in the A300- 600 EASA approved Airbus document AI/ST5/829/85, which is included in appendix 1 of the Maintenance Review Board Report.were is the A300/310 language. - Ageing system maintenance items are provided in the EASA approved A300-600 Airworthiness Limitation Section (ALS) Part 4 ref A300-600 ALS Part 4 - Fuel Airworthiness Limitations are provided in the EASA approved FAL document ref. 95A.1929/05 -Mandatory structural inspections (Airworthiness Limitations Items) for models A300-600 series are quoted in the March 2000issue of the A300-600 Maintenance Review Bords Report Appendix1. Additional inspections ares detailed in the EASA approved Airbus document SE-M2/95A.0575/98 issue4 dated June 2000. NOTE 4. The A300 B4-600 basic definition for US Import Certification is contained in document A1/EA-A No. 413-347/88. The A300B4-600R basic definition for US Import Certification is contained in document A1/EA-A No. 413-346/88. The A300F4-605R basic definition for US Import Certification is contained in document AI/EA-T 414-0326/94. The A300F4-622R basic definition for US Import Certification is contained in document AI/EA-N 415-1229/00 issue 2, dated July 7, 2000. The A300C4-605R Variant F basic definition for US Import Certification is contained in document EAW 414.0186/02. NOTE 5 ETOPS: The type design, reliability and performance of the following airframe-engine combinations have been evaluated in accordance with AC120-42A and found suitable for (180 minute maximum diversion time) Extended Range Operations with the incorporation of the corresponding approved airplane configuration CMP document listed below: A300B4-605R: AI/EA3001, Revision 3, approved July 27, 1990 A300F4-605R: AI/EA3001, Revision 4, approved Sept. 15, 1995 A300F4-622R: AI/EA3001, Revision 5, approved July 14, 2000 This finding does not constitute approval to conduct extended range operations. Operational approval must be obtained from the FAA by the operator. Any ETOPS approval for new aircraft model wherein the application was sent to FAA prior to February 15, 2007 is to be proceeded with the ETOPS approval against 14 CFR 25.1535 that have not yet already been approved under the provisions of AC120-42A. A35EU Page 55 of 71 NOTE 6. The following FAR 36 Noise Certification by Model reflects required as well as Airbus voluntary updated compliance to later FAR-36 amendments. - If modifications 13219 (New Noise Chapter 4 Requirements) is embodied on a Type A300 Model B4- 605R, F4-622R, F4-605R, C4-605R the aircraft is compliant with amendment 36-27 and certificated to Stage 4 Noise requirements. Group Series Specific Model Date Certified Amendment Level VIII A300-B4-600 A300B4-601 3/28/1988 36-14 A300B4-603 9/19/1988 36-15 A300B4-620 9/19/1988 36-15 A300B4-622 1/21/2003 36-24 IX A300-B4- 600R A300B4-605R 3/28/1988 36-14 A300B4-622R 8/01/1991 36-18 X A300-F4-600R A300F4-605R 4/27/1994 36-20 A300F4-622R 7/14/2000 36-22 XI A300-C4- 600R A300C4-605R Variant F 6/21/2002 36-23 NOTE 7 This exemption does not grant relief from the related operational requirements contained in §§ 121.1117, 125.509, or 129.117. Should a person choose to operate an Airbus A300, Model B4-605R or B4-622R airplane under part 129 (U.S. registered only), 121 or 125 beyond the operational compliance deadlines as stated in §§ 121.1117, 125.509, or 129.117, (Fuel Tank Flammability) that person will be required to comply with those operational requirements. Those operational requirements require a design change to the center fuel tank that either reduces its flammability to the level required by § 26.33(c)(1)(i) or provides a means to mitigate the effects of an ignition of fuel vapors to the level required by § 26.33(c)(2). See Exemption 9950 for background information on this issue. A35EU Page 56 of 71 XII. A310-200 Series (A310-221, A310-222 and A310-203 approved February 21, 1985, A310-204 approved January 8, 2001) (Transport Aircraft) Engines. 2 Pratt & Whitney JT90-7R4D1 (A310-221) (FAA Data Sheet E3NE), 2 Pratt & Whitney JT9D-7R4E1 (A310-222) (FAA Data Sheet E3NE), 2 General Electric CF6-80A3 (A310-203) (FAA Data Sheet E13NE), 2 General Electric CF6-80C2A2 (A310-204) (FAA Data Sheet E13NE). APU. Airesearch GTCP 331-250(F) (Specification 31-2891) Fuel. (a) The following fuels are eligible for engines and APU: MIL-T-5624H Grades JP-4 or JP-5 AST-MD-1655-65T Grades Jet A1 (JP-1) and Jet B AST-ES-2-74 Grades Jet A, A1 and Jet B GOST 10227-86 Grade TS-1 GOST 10227-86 Grade RT-1 French specifications are: Air 3404 Air 3407 Air 3405 With JP-4 or Jet B fuel, the following limitations apply: (1) Maximum altitude of 15,000 ft with gravity fuel supply from inboard tanks. (2) Maximum altitude of 20,000 ft with gravity fuel supply from outboard tanks. (b) The following additives may be used in approved fuels for engines and APU: (1) Philips PFA-55MB or anti-icing additive to specifications MIL-I-278686 E at a concentration not in excess of 0.15 percent by volume. (2) Sohio Biobor JF biocide additive at a concentration not in excess of 20 ppm elemental boron (270 ppm total additive). (3) Shell ASA-3 anti-static additive at a concentration that will provide not in excess of 300 conductivity units which is approximately equivalent to one ppm. (4) For Pratt & Whitney engines following additives may be used in RT or TS-1 fuel grades: I and I-M TGF and TGF-M Oil. (a) The following oils are eligible for the CF6-80A3 engine and for the JT9D-7R4D1/E1 engines, respectively. Synthetic type conforming to GE specifications D50TF1, Classes A or B. (GE Service Bulletin No. 79-1 lists approved brand oils.) Synthetic type conforming to PW specification 521C (PW Service Bulletin No. 238 lists approved brand oils). (b) The following oil is eligible for the APU: See Maintenance Manual AIRESEARCH GTCP 331-250, Chapter 49.21.00 Table 2. A35EU Page 57 of 71 XII. A310-200 Series (A310-221, A310-222, A310-203, A310-204 ) (Transport Aircraft) (cont’d) Engine Limits. GENERAL ELECTRIC CF6-80A3 GENERAL ELECTRIC CF6-80C2A2 PRATT & WHITNEY JT90-7R4D1 PRATT& WHITNEY JT9D-7R4E1 Static Thrust, Sea Level Takeoff (5 min-up to 87ºF) Max. Cont. (up to 87ºF) Max. permissible engine rotor operating speeds N1 (Low compressor) N2 (High compressor) Max. permissible engine temperature Turbine exhaust temperature at turbine outlet Takeoff (5 min) Maximum Continuous Acceleration (2 min) Starting º up to 40 sec º above 40 sec Oil maximun permissible outlet temperature Continuous Operation Transient operation º Limited to 15 min. º Limited to 20 min. 48,970 lb 45,800 lb 4,016 rpm (117%) 10,859 rpm (110.5%) 940ºC 895ºC 870ºC 750ºC 160ºC 175ºC 52,460 lb 48,080 lb 3,854 rpm (117.5%) 11,055 rpm (112.5%) 960ºC 925ºC 870ºC 750ºC 160ºC 175ºC 48,000 lb 45,800 lb 3,810rpm (105.8%) 8,000 rpm (102.5%) 625ºC 600ºC 625ºC 535ºC 535ºC 135ºC 163ºC 50,000 lb 47,500 lb 3,810 rpm (105.8%) 8,000 rpm (102.5%) 635ºC 610ºC 636ºC 535ºC 535ºC 135ºC 163ºC APU Limits. - Power rating maximum at sea level: 98.5 KW - Maximum operating speed: 43,562 rpm - Maximum gas temperature at turbine outlet: 585ºC A35EU Page 58 of 71 XII. A310-200 Series (A310-221, A310-222, A310-203, A310-204 ) (Transport Aircraft) (cont’d) Airspeed Limits (IAS) BASIC MODEL VARIANT 01 VARIANT 04 VARIANT 101 VARIANT 104 VARIANT 107 MAXIMUM OPERATING MACH MMO 0.84 0.84 0.84 0.84 0.84 MAXIMUM OPERATING SPEED VMO (Kt) 360* 340 360* 340 360* *VMO = 340 Kt for A310-203 and –204 models with less than 2 tons fuel in one of the outer tanks. VA (Maneuvering speed): refer to EASA-approved US Airplane Flight Manual Chapter 2.03. VFE SLATS (º) FLAPS (º) VFE (kt) 15 0 245 15 15 210 20 20 195 30 40 180 VLO Gear extension . . . . . . . . . . . . . . 270 Kt Gear retraction . . . . . . . . . . . . . . 270 Kt VLE Landing gear extended . . . . . . . 270 Kt or M=0.59 VMC (Minimum control speed with the critical engine inoperative) A310-203 A310-204 A310-221 A310-222 Inflight - VMCA 109 KCAS 115 KCAS 106 KCAS 109 KCAS Take off - VMCG 105 KCAS 111 KCAS 103 KCAS 105KCAS Tire Speed Limit (Ground speed limit): 195.5 kt (225 mph) C.G. Range. For C.G. envelopes, see EASA Approved US Flight Manual. A35EU Page 59 of 71 XII. A310-200 Series (A310-221, A310-222, A310-203, A310-204 ) (Transport Aircraft) (cont’d) Maximum Weights. A310-203, A310-221 A310-222 A310-203, A310-221, A310-222 BASIC MODEL VARIANT 01 (with Mod. 3703) VARIANT 04 (with Mod. 5124) kg lb kg lb kg lb Taxi Weight 132,900 292,991 139,500 307,542 142,900 315,037 Take-off Weight 132,000 291,007 138,600 305,558 142,000 313,053 Landing Weight 118,000 261,247 121,500 267,859 121,500 267,859 Zero Fuel Weight 108,500 239,201 111,500 245,813 111,500 245,813 XII. A310-200 Series (A310-221, A310-222, A310-203 and A310-204) (continued) A310-204 A310-204 A310-204 VARIANT 101 (with Mod. 6527) VARIANT 104 (with Mod. 6528) VARIANT 107 (with Mods. 6527 and 7290) kg lb kg lb kg lb Taxi Weight 139,500 307,500 142,900 315,000 134,900 297,450 Take-off Weight 138,600 305,600 142,000 313,100 134,000 295,470 Landing Weight 122,000 269,000 122,000 269,000 122,000 269,000 Zero Fuel Weight 112,000 246,960 112,000 246,960 112,000 246,960 Minimum Flight Weight. 80,000 kg (176,400lb). Minimum Crew. For all flights: 2 pilots Maximum Passengers. 265 or 255 when overwing exit is configured as a Type III. For seating arrangement refer to AIRBUS specification TL 25/1110/74 Maximum Baggage. Forward compartment - Maximum load: 27,999 lbs Aft compartment - Maximum load: 20,999 lbs Bulk compartment - Maximum load: 6,107 lbs Fuel Capacity. Location (Usable fuel 6.676 lb/gal) Arm (lb) (US gal) (inches) Outboard Tanks 13,220 1,980 1181.5 Inboard Tanks 49,300 7,384 1019.53 Center Tanks 34,680 5,194 963.3 TOTAL 97,200 14558 1021.5 Fuel Management. Fuel must be loaded symmetrically in outboard tanks first; fuel must be used from inboard tank first. Maximum allowable wing fuel asymmetry is 4,410 lb (refere to latest EASA approved AFM revision). Oil Capacity. GE Engine oil capacity 25.02 lb/engine usable (at 8.1 lb/gal) with engine mount arm 842.8 inches. PW - Engine oil capacity 33.40 lb/engine usable (at 8.1 lb/gal) with engine moment arm 899.7 inches. A35EU Page 60 of 71 XII. A310-200 Series (A310-221, A310-222, A310-203, A310-204 ) (Transport Aircraft) (cont’d) Maximum Operating Altitude. 41,000 ft. Equipment. The basic required equipment as prescribed in the applicable Federal Aviation Regulations must be installed in the aircraft. Airbus Equipment List AI/V-C 895/85 as revised identifies all required equipment and all optional equipment approved by the Direction General de l'Aviation Civile (D.G.A.C.) of France. In addition, the following is required: EASA-Approved US Airplane Flight Manual. Other Information. See "Data Pertinent to all A310 Models" A35EU Page 61 of 71 XIII. A310-300 Series (A310-322 Approved June 10, 1987; A310-324 Approved June 10, 1987; A310-304 Approved February 12, 1988, A310-325 Approved March 22, 1996) (Transport Aircraft) Engines. 2 Pratt and Whitney JT9D-7R4E1 (A310-322) (FAA Data Sheet E3NE) or 2 Pratt and Whitney PW 4152 (A310-324) (FAA Data Sheet E24NE) or 2 General Electric CF6-80C2A2 (A310-304) (FAA Data Sheet E-13NE) 2 Pratt and Whitney PW4156A (A310-325) (FAA Data Sheet E24NE) APU. Airesearch GTCP 331-250(H) (Specification 31-2891) Fuel. (a) The following fuels are eligible for engines and APU: MIL-T-5624H Grades JP-4 or JP-5 AST-MD-1655-65T Grades Jet A1 (JP-1) and Jet B AST-ES-2-74 Grades Jet A, A1 and Jet B GOST 10227-86 Grades TS-1 GOST 10227-86 Grades RT French specifications are: Air 3404 Air 3407 Air 3405 With JP-4 or Jet B fuel, the following limitations apply: (1) Maximum altitude of 15,000 ft with gravity fuel supply from inboard tanks. (2) Maximum altitude of 20,000 ft with gravity fuel supply from outboard tanks. (b) The following additives may be used in approved fuels for engines and APU: (1) Philips PFA-55MB or anti-icing additive to specifications MIL-I-278686 E at a concentration not in excess of 0.15 percent by volume. (2) Sohio Biobor JF biocide additive at a concentration not in excess of 20 ppm elemental boron (270 ppm total additive). (3) Shell ASA-3 anti-static additive at a concentration that will provide not in excess of 300 conductivity units which is approximately equivalent to one ppm. (4) For Pratt & Whitney engines and APU, the following additives may be used in RT or TS-1 fuel grades: anti-ice additives 1 and 1-M TGF and TGF-M A35EU Page 62 of 71 XIII. A310-300 Series (A310-322, A310-324, A310-304, A310-325) (Transport Aircraft) (cont’d) Oil. (a) The following oils are eligible for the CF6-80C2A2 engines, for the PW JT9D-7R4E1 and for the PW 4152 and PW 4156A engines respectively: Synthetic type conforming to GE specification D50TF1, (GE Service Bulletin No. 79-1 lists approved brand oils.) Synthetic type conforming to PW specification 521C (PW Service Bulletin No. 238 lists approved brand oils). (b) The following oil is eligible for the APU: See Maintenance Manual AIRESEARCH GTCP 331-250, Chapter 49.21.00 Table 2. Engine Limits. PRATT AND WHITNEY PW 4156A PRATT AND WHITNEY PW 4152 PRATT & WHITNEY JT9D-7R4E1 GENERAL ELECTRIC CF6-8C2A2 Static Thrust, Sea Level Takeoff (5 min-up to 87ºF) Max. Cont. (up to 87ºF) Max. permissible engine rotor operating speeds N1 (Low compressor) N2 (High compressor) Max. permissible engine temperature Turbine exhaust temperature at turbine outlet Takeoff (5 min) Maximum Continuous Acceleration (2 min) Starting º up to 40 sec º above 40 sec Oil maximum. permissible outlet temperature Continuous Operation Transient operation º Limited to 15 min. º Limited to 20 min. 56,000 lb 49,200 lb 4,012 rpm (111.4%) 10,450 rpm (105.5%) 650ºC 625ºC 650ºC 535ºC 535ºC 163ºC 177ºC 52,000 lb 49,200 lb 4,012 rpm (111.4%) 10,300 rpm (104%) 625ºC 600ºC 625ºC 510ºC 510ºC 163ºC 177ºC 50,000 lb 47,500 lb 3,810rpm (105.8%) 8,000 rpm (102.5%) 635ºC 610ºC 635ºC 535ºC 535ºC 135ºC 163ºC 52,460 lb 48,080 lb 3,854 rpm (117.5%) 11,055 rpm (112.5%) 960ºC 925ºC 870ºC 750ºC 160ºC 175ºC APU Limits. - Power rating maximum at sea level: 98.5 KW - Maximum operating speed: 43,562 rpm - Maximum gas temperature at turbine outlet: 585ºC A35EU Page 63 of 71 XIII. A310-300 Series (A310-322, A310-324, A310-304, A310-325) (Transport Aircraft) (cont’d) Airspeed Limits (IAS) BASIC MODEL VARIANT 08 VARIANT 01 VARIANT 05 VARIANT 12 MAXIMUM OPERATING MACH MMO 0.84 0.84 MAXIMUM OPERATING SPEED VMO (Kt) 360 340 VA(Maneuvering speed): refer to EASA-approved US Airplane Flight Manual Chapter 2.03. VFE SLATS (º) FLAPS (º) VFE (kt) 15 0 245 15 15 210 20 20 195 40 40 180 VLO Gear extension . . . . . . . . . . . . . . 270 Kt Gear retraction . . . . . . . . . . . . . . 270 Kt VLE Landing gear extended . . . . . . . 270 Kt or M=0.9 VMC (Minimum control speed with the critical engine inoperative) A310-322 A310-324 A310-304 A310-325 Inflight - VMC Take off - VMCG 109 KCAS 105 KCAS 115 KCAS 111 KCAS 115.5 KCAS 111 KCAS 121 KCAS (*) 117 KCAS (*) Values at Zp = 0 ft. m the AFM, these values are scheduled with altitude. Tire Speed Limit (Ground speed limit): 195.5 kt (255 mph) C.G. Range. For C.G. envelopes, see EASA Approved US Flight Manual. Maximum Weights. BASIC MODEL VARIANT 01 (with Mod. 5616) VARIANT 05 (with Mod. 7088) VARIANT 08 (with Mod. 8130, only for model A310-325) VARIANT 12 (with Mod. 11103, only for model A310- 324) kg lb kg lb kg Lb kg lb kg Lb Taxi Weight Take-off Weight Landing Weight Zero Fuel Weight 150,900 150,000 123,000 113,000 332,735 330,750 271,215 249,165 153,900 153,000 123,000 113,000 339,350 337,365 271,215 249,165 157,900 157,000 124,000 114,000 363,604 361,620 273,420 251,370 164,900 164,000 124,000 114,000 348,170 346,185 273,420 251,370 160,900 160,000 124,000 114,000 354,784 352,800 273,420 251,370 A35EU Page 64 of 71 XIII. A310-300 Series (A310-322, A310-324, A310-304, A310-325) (Transport Aircraft) (cont’d) Minimum Flight Weight. 80,000 kg. (176,400 lb) Minimum Crew. For all flights: 2 pilots Maximum Passengers. 265 - For seating arrangement refer to AIRBUS specification TL 25/1110/74 Maximum Baggage. Forward compartment - Maximum load: 27,999 lbs Aft compartment - Maximum load: 20,999 lbs Bulk compartment - Maximum load: 6,107 lbs Fuel Capacity. Location (Usable fuel 6.676 lb/gal) Arm (lb) (US gal) (inches) Outboard Tanks 13,051 1,955 1181.1 Inboard Tanks 49,209 7,371 1018.9 Center Tanks Trim Tank 34,642 10,848 5,189 1,625 963.3 1890.5 TOTAL 107,750 16,140 1108.4 For aircraft equipped with Auxiliary Centre Tank, refer to Note 8. Fuel Management. Fuel must be loaded symmetrically in outboard tanks first; fuel must be used from inboard tank first. Maximum allowable wing fuel asymmetry is 4,410 lb (refere to latest EASA approved AFM revision). Oil Capacity. PW - JT9D-7R4E1 - Engine oil capacity 33.40 lb/engine usable (at 8.1 lb/gal) with engine moment arm 899.7 inches. PW 4152 and PW 4156A - Engine oil capacity 28.44 lb/engines usable (at 8.1 lb gal) with engine moment arm 900.24 inches. GE CF6-80C2A2 - Engine oil capacity 25.02 lb/engine usable (at 8.l lb/gal) with engine moment arm 840.4 inches. Maximum Operating Altitude. 41,000 ft. Equipment. The basic required equipment as prescribed in the applicable Federal Aviation Regulations must be installed in the aircraft. Airbus Equipment List Document A1/EA- A No. 413.601/87 as revised identifies all required equipment and all optional equipment approved by the Direction General de l'Aviation Civile (D.G.A.C.) of France. In addition, the following is required: EASA-Approved US Airplane Flight Manual. Other Information. See "Data Pertinent to all A310 Models" A35EU Page 65 of 71 DATA PERTINENT TO ALL A310 MODELS Datum. Station 0 (251.26 inches forward of fuselage nose) MAC. 229.48 inches (leading edge of MAC: Sta. 992) Leveling Means. Clinometer on the cabin seat track rails. Serial Numbers Eligible. A French "Certificat de Navigabilite pour Exportation" endorsed as noted under "Import Requirements" must be submitted for each individual aircraft for which application for U.S. certification is made. Import Requirements. An FAA Standard Airworthiness Certificate may be issued on the basis of a French "Certificat de Navigabilite pour Exportation" signed by a representative of the Direction Generale de 'Aviation Civile (D.G.A.C.) of France, containing the following statement: "The airplane covered by this certificate has been examined, tested and found to conform to the type design approved under Type Certificate No. A35EU and to be in condition for safe operation".Refer to the applicable bilateral agreement to verify eligibility for import into the United States of both new and used aircraft based on the scope of the agreement, to identify any required statements by the exporting authority on the export certificate of airworthiness (or equivalent document), and for procedures for coordinating exceptions to conformity statements on these documents. Refer to FAA Order 8130.2, Airworthiness Certification of Aircraft, for requirements for issuance of an airworthiness certificate for imported aircraft. Certification Basis. (a) FAR Part 25: Amendment 1 through 21 Basic; Amendment 22 through 45 (elected) except for 25.109 and 25.631; Amendment 46 (elected) for paragraph 25.803, and 25.809(f)(1)(v); Amendment 47 (elected) for paragraph 25-809(f)(1)(iii); Amendment 49 (elected) for paragraph 25.733; Amendment 54 (elected) for paragraph 25.365(e)(1) and (e)(2). For the A310-300 series and the Model A310-204 (vertical stabilizer only): FAR 25.631, Amendment 25-23 is included in the above certification basis. (b) For precision approach and landing, the applicable technical requirements are complemented by AC 120-29 and AC 120-28C. For the automatic flight control system, the applicable technical requirements are complemented by AC 20-57A for automatic landing and by AC 25.1329-1A for cruise. (c) ICAO Annex 16, Vol II, Aircraft Engine Emissions (fuel venting requirements). (d) Compliance with the following optional requirements has been established: Ditching provisions FAR 25.801 Ice Protection Provisions FAR 25.1419. (e) An equivalent level of safety was found for FAR 25.813(c), 25.807 and 25.809 through A310 issue paper CI-3. This finding is applicable to both the A310-200 and A310-300 series. (f) An equivalent level of safety was found for FAR 25.173(c) and 25.175(c) through A310 issue paper F-1. This finding is applicable to both the A310-200 and A310- 300 series. (g) For the A310-200 series: The French/German complementary conditions (DGAC letter 53781). A35EU Page 66 of 71 (h) Aircraft Noise: - For the A310-200 series (except the Model A310-204): FAR Part 36 through Amendment 36-12. - For the Model A310-204: FAR Part 36 through Amendment 36-22. - For the A310-300 series : FAR Part 36 through Amendement 36-12 - If modifications 13219 (New Noise Chapter 4 Requirements) is embodied on a Type A310 Model -204, -304 the aircraft is compliant with amendment 36-27 and certificated to Stage 4 Noise requirements. (i) For the A310-300 model: FAA Special Conditions for the A310-300 published in the Federal Register 17 June 1987 through Special Conditions 25-ANM-12 on lightning protection, protection from unwanted effects of radio frequency energy, and the propulsion control system. (j) For the A310-300 model: Environmental Standards except Noise : (1) SFAR 27-5 Part 26: Continued Airworthiness and Safety Improvements for Transport Category Airplanes: Based on 14 CFR § 21.29(a) for new import TCs, or § 21.101(g) for changes to TCs, applicable provisions of part 26 are included in the certification basis. For any future 14 CFR part 26 amendments, the holder of this TC must demonstrate compliance with the applicable sections Exemption 10070 This exemption grants relief from having to meet the requirements of § 26.33 See NOTE(7) DGAC originally type cerificated this A310 under its type certificate number N°72, TCDS N°145. The FAA validated this product under U.S. Type Certificate Number A35EU. Effective September 28, 2003, the European Aviation Safety Agency (EASA) began oversight of this product on behalf of DGAC. A35EU Page 67 of 71 NOTES TO ALL A310 MODELS NOTE 1 NOTE 2 NOTE 3. Airworthines Limitations/Maintenance Instructions - Safe Life Airworthiness Limitations items are provided in the A310 Ariworthiness Limitations Section (ALS) Part 1 approved by EASA ref A310 ALS document - Damage Tolerance Airworthiness Limitations items are provided in the EASA approved Airbus document ref Airbus document AI/SE-M2/95A.0263/06. - Mandatory systems related tasks (Certification Maintenance Requirements) for the A310-200 and A310-300 series are quoted in the EASAapproved Airbus document AI/ST5/849/85, Section 1. - Ageing system maintenance items are provided in the A310 Airworthiness Limitation Section (ALS) Part 4 approved by EASA ref. A310 ALS document. - Fuel Airworthiness Limitations are provided in the EASA approved FAL document ref. Airbus document 95A.1930/05. - Maintenance Review Board Report NOTE 4. Cabin Equipment: Seats and galleys must be designed in accordance with AIRBUS specifications: TL 25/1110/74 and TL 25/1109/74. NOTE 5. If modifications 4941, 5502, 5429, 5428, 5757, 5953 are embodied, the aircraft is certificated for Category III precision approach (fail operational system). NOTE 6. The A310-200 series basic definition for U.S. import certification, except Model A310- 204, is contained Document AI/V-C131/85. The Model A310-204 basic definition for U.S. import certification is contained Document AI/EA-N No. 415.2342/00. The A310-300 basic definition for U.S. import certification is contained in Document AI/EA-A No. 948/86. NOTE 7. ETOPS for the A310-221 and A310-222: The type design, reliability and performance of these airframe-engine combinations has been evaluated in accordance with AC120-42A and found suitable for (180 minute maximum diversion time) Extended Range Operations with the incorporation of the corresponding approved airplane configuration CMP document (AI/EA3001, Revision 3, approved July 27, 1990 + TR approved Feb. 27, 1991). This finding does not constitute approval to conduct extended range operations. Operational approval must be obtained from the FAA by the operator. ETOPS for the A310-324: The type design, reliability and performance of these airframe- engine combinations has been evaluated in accordance with AC120-42A and found suitable for (120 minute maximum diversion time) Extended Range Operations with the incorporation of the corresponding approved airplane configuration CMP document (AI/EA3001, Revision 2, approved March 1, 1990). This finding does not constitute approval to conduct extended range operations. Operational approval must be obtained from the FAA by the operator. Any ETOPS approval for new aircraft model wherein the application was sent to FAA prior to February 15, 2007 is to be proceeded with the ETOPS approval against 14 CFR 25.1535 that have not yet already been approved under the provisions of AC120-42A. A35EU Page 68 of 71 NOTE 8. For A310 -300 series airplanes: Modifications 6920 and 7468 provide for installation in the aft cargo compartment of respectively 1 and 2 Auxiliary Center Tanks (ACT) with the following characteristics : Tank Unusable fuel Usable fuel ACT 1 59.5 lb (27 kg) 12,698.5 lb (5760 kg) ACT 2 59.5 lb (27 kg) 12,698.5 lb (5760 kg) For corresponding limitations and associated procedures refer to the US Airplane Flight Manual. NOTE 9. This exemption does not grant relief from the related operational requirements contained in §§ 121.1117, 125.509, or 129.117. Should a person choose to operate an Airbus A310, Models 304, 322, 324, and 325 airplanes under part 129 (U.S. registered only), 121 or 125 beyond the operational compliance deadlines as stated in §§ 121.1117, 125.509, or 129.117, (Fuel Tank Flammability) that person will be required to comply with those operational requirements. Those operational requirements require a design change to the center fuel tank that either reduces its flammability to the level required by § 26.33(c)(1)(i) or provides a means to mitigate the effects of an ignition of fuel vapors to the level required by § 26.33(c)(2). See Exemption 10070 for background information on this issue. A35EU Page 69 of 71 GENERAL NOTES: APPLICABLE TO ALL AIRCRAFT NOTE 1 WEIGHT AND BALANCE (a) Current weight and balance report including list of equipment, entitled "Aircraft Inspection Report," included in certificated empty weight, and loading instructions, must be in each aircraft at the time of original certification and at all times thereafter except in the case of operators having an approved weight control system. Airbus Report, "Weight and Balance Manual," contains loading information for each airplane and interior arrangement configuration as delivered. This report contains, or refers to, information relative to location of all passengers and crew member seats, location and capacity of all cargo and baggage compartments, buffets, storage spaces and coat rooms, location and capacity of lounges, lavatories, and the required placards in the passenger compartment. (b) The airplane must be loaded so that the C.G. is within specified limits at all times, considering fuel loading and usage, gear retraction and movement of crew and passengers from their assigned positions. (c) The weights of system fuel and oil, as defined below, and hydraulic fluid, all of which must be included in the airplane empty weight, are listed for each airplane in the Weight and Balance Manual specified in paragraph (a) above. (d) System fuel is the weight of all fuel required to fill all lines and tanks up to the zero-fuel point on the fuel gages in the most critical flight attitude, including the unusable tank fuel as defined by FAR Part 25.959. (The usable fuel in the crossfeed manifold lines, manifolds, and engine that is not part of the system fuel, must be included in the total usable fuel to obtain correct weight and C.G. for takeoff). (e) The unusable fuel is that amount of fuel in the tanks which is unavailable to the engines under critical flight conditions as defined in FAR Part 25.959. This "unusable" fuel is included in System Fuel as indicated in (d) above and need not be accounted for separately. (f) System oil is the weight of oil remaining in the engine, constant speed drive, lines and tanks after subtracting the oil in the tanks which is above the standpipe (zero gauge) levels. The engine oil capacities shown elsewhere in this data sheet includes only the usable oil for which the tanks must be placarded. NOTE 2 Reserved NOTE 3 SERVICE INFORMATION Each of the documents listed below must state that it is approved by the European Aviation Safety Agency (EASA) or – for approvals made before September 28, 2003 – by the DGAC France, are accepted by the FAA and are considered FAA approved. Additionally, approvals issued by Airbus under the Authority of EASA approved Design Organization EASA.21J.031 - or for approvals made before September 28, 2003- under the authority of DGAC Design Organization Approval No. 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 Aircraft flight manuals, • Repair Instructions Note: Airbus Service Bulletins which contain design changes classified as Level 1 Major or Non-Basic in accordance with the US/France Bilateral Aviation Safety Agreement A35EU Page 70 of 71 Implementation Procedures for Airworthiness must be approved by the FAA in accordance with those procedures. NOTE 4 IMPORT REQUIREMENTS: The FAA can issue a U.S. airworthiness certificate based on an NAA Export Certificate of Airworthiness (Export C of A) signed by a representative of [insert name of the State of Design/Manufacture National Aviation Authority] on behalf of the European Community. The Export C of A should contain the following statement: ‘The aircraft covered by this certificate has been examined, tested, and found to comply with [insert document identifier, title revision, etc.] approved under U.S. Type Certificate No. A35EU and to be in a condition for safe operation.’ NOTE 5 AIRWORTHINESS DIRECTIVES: Some airworthiness directives refer to Model A300 B4-600, B4-600R, C4-600R and F4- 600R series airplanes as "Model A300-600 series airplanes." The Model A300-600 is the common model designation. The phrase "Model A300 B4-600, B4-600R, F4-600R and C4-600R series airplanes" collectively refers to Model A300B4-601, B4-603, B4-620, B4-622, B4-605R, B4-622R, F4-605R, F4-622R and C4-605R Variant F airplanes. Some airworthiness directives refer to Model A300 B2 and B4 series airplanes simply as "Model A300" series airplanes. The phrase "Model A300 B2 and B4 series airplanes" collectively refers to Model A300 B2-1A, B2-1C, B4-2C, B2K-3C, B4-103, B2-203 and B4-203 airplanes. Some airworthiness directives refer to Model A310-200 and A310-300 series airplanes as “Model A310 series airplanes,” the common model designation. The phrase “Model A310-200 and A310-300 series airplanes” collectively refers to Model A310-221, 222, 203, 204, and Model A310-322, 324, 304, and 325 airplanes. NOTE 6 A300/A310 Airworthiness Limitations Sections (ALS): A/C Model ALS Part Revision Approval Date A300 ALS 02-dec-2008 A300 ALS Part 1 01 05-sep-2013 A300 ALS Part 2 02 03-oct-2014 A300 ALS Part 5 00 27-may-2014 A300-600 ALS 18-apr-2012 A300-600 ALS Part 1 01 05-sep-2013 A300-600 ALS Part 2 01 07-aug-2015 A300-600 ALS Part 3 00 18-apr-2012 A300-600 ALS Part 4 02 18-apr-2012 A300-600 ALS Part 5 00 27-may-2014 A310 ALS 02-dec-2008 A310 ALS Part 1 01 05-sep-2013 A310 ALS Part 2 01 07-aug-2015 A310 ALS Part 3 00 30-nov-2012 A310 ALS Part 4 02 30-nov-2012 A310 ALS Part 5 00 27-may-2014 For all these documents, “EASA-approved" is considered equivalent to "FAA-approved". FAA approved variations to these documents associated with the type design of the airplane are normally included in next scheduled revision cycle by design approval holder (DAH). 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Effective Jan 6, 2023 - [AD 2022-25-12](https://openairdocs.org/ad/2022-25-12): Time Limits/Maintenance Checks · Airbus A310-203, A310-204, A310-221 and 5 more. Effective Jan 6, 2023 - [AD 2022-21-02](https://openairdocs.org/ad/2022-21-02): Fuselage · Airbus A300 B2-1C, A300 B2K-3C, A300 B2-203 and 8 more. Effective Dec 14, 2022 - [AD 2022-19-06](https://openairdocs.org/ad/2022-19-06): Time Limits/Maintenance Checks · Airbus A310-203, A310-204, A310-221 and 5 more. Effective Oct 4, 2022 - [AD 2022-01-08](https://openairdocs.org/ad/2022-01-08): Hydraulic power · Airbus A300 B2-1A, A300 B2K-3C, A300 B2-1C and 21 more. Effective Mar 8, 2022 - [AD 2021-19-18](https://openairdocs.org/ad/2021-19-18): Time Limits/Maintenance Checks · Airbus A310-203, A310-204, A310-221 and 5 more. Effective Oct 20, 2021 - [AD 2021-11-18](https://openairdocs.org/ad/2021-11-18): Landing Gear · Airbus A300 B2-1A, A300 B2-1C, A300 B2-203 and 13 more. Effective Jul 16, 2021 - [AD 2020-26-11](https://openairdocs.org/ad/2020-26-11): Equipment/furnishings · Airbus A300 F4-605R and A310-324. Effective Jan 27, 2021 - [AD 2020-22-11](https://openairdocs.org/ad/2020-22-11): Fuselage · Airbus A300 B4-603, A300 B4-605R, A300 B4-620 and 5 more. Effective Dec 14, 2020 - [AD 2020-21-04](https://openairdocs.org/ad/2020-21-04): Fuselage · Airbus A300 F4-605R and A300 F4-622R. Effective Nov 18, 2020 - [AD 2020-16-18](https://openairdocs.org/ad/2020-16-18): Fuselage · Airbus A310-203, A310-204, A310-221 and 5 more. Effective Sep 9, 2020 - [AD 2020-02-22](https://openairdocs.org/ad/2020-02-22): Hydraulic power · Airbus A300 B4-601, A300 B4-603, A300 B4-605R and 14 more. Effective Mar 19, 2020 - [AD 2020-01-15](https://openairdocs.org/ad/2020-01-15): Fuel · Airbus A300 B4-601, A300 B4-603, A300 B4-605R and 9 more. Effective Mar 17, 2020 - [AD 2019-20-06](https://openairdocs.org/ad/2019-20-06): Time Limits/ Maintenance Checks · Airbus A310-203, A310-204, A310-221 and 5 more. Effective Nov 22, 2019 - [AD 2019-19-17](https://openairdocs.org/ad/2019-19-17): Wings · Airbus A300 B4-601, A300 B4-603, A300 B4-605R and 5 more. Effective Nov 14, 2019 - [AD 2019-19-07](https://openairdocs.org/ad/2019-19-07): Flight controls · Airbus A300 B2-1A, A300 B2-1C, A300 B2-203 and 21 more. Effective Nov 5, 2019 - [AD 2019-18-04](https://openairdocs.org/ad/2019-18-04): Stabilizers · Airbus A300 B2-1A, A300 B2-1C, A300 B2-203 and 21 more. Effective Oct 30, 2019 - [AD 2019-14-08](https://openairdocs.org/ad/2019-14-08): Electrical power · Airbus A300 B4-601, A300 B4-603, A300 B4-605R and 14 more. Effective Oct 2, 2019 - [AD 2019-14-14](https://openairdocs.org/ad/2019-14-14): Stabilizers · Airbus A300 B4-601, A300 B4-603, A300 B4-605R and 14 more. Effective Sep 19, 2019 - [AD 2019-15-08](https://openairdocs.org/ad/2019-15-08): Fuselage · Airbus A300 B2-1A, A300 B2-1C, A300 B2-203 and 13 more. Effective Sep 19, 2019 - [AD 2019-12-04](https://openairdocs.org/ad/2019-12-04): Wings · Airbus A300 B4-603, A300 B4-605R, A300 B4-620 and 5 more. Effective Aug 7, 2019 - [AD 2019-03-09](https://openairdocs.org/ad/2019-03-09): Wings · Airbus A310-304, A310-322, A310-324 and 1 more. Effective Mar 29, 2019 All 545: https://openairdocs.org/tcds/A35EU/ads.md ## Registered aircraft by registry model (OpenAirDocs) - [Airbus Industrie A300 F4-605R](https://openairdocs.org/model/airbus-industrie-a300-f4-605r): 36 aircraft (registry code 3930327) - [Airbus A300 F4-622R](https://openairdocs.org/model/airbus-a300-f4-622r): 31 aircraft (registry code 3940003) - [Airbus Industrie A300 F4-622R](https://openairdocs.org/model/airbus-industrie-a300-f4-622r): 21 aircraft (registry code 3930360) - [Airbus A300 B4-622R](https://openairdocs.org/model/airbus-a300-b4-622r): 11 aircraft (registry code 3940322) - [Airbus Industrie A300 B4-622R](https://openairdocs.org/model/airbus-industrie-a300-b4-622r): 10 aircraft (registry code 3930312) - [Airbus A300 F4-605R](https://openairdocs.org/model/airbus-a300-f4-605r): 6 aircraft (registry code 3930343) - [Airbus Industrie A300 B4-605R](https://openairdocs.org/model/airbus-industrie-a300-b4-605r): 3 aircraft (registry code 3930308) - [Airbus Industrie A300 B4-622](https://openairdocs.org/model/airbus-industrie-a300-b4-622): 2 aircraft (registry code 3930401) - [Airbus Industrie A310-203](https://openairdocs.org/model/airbus-industrie-a310-203): 2 aircraft (registry code 3930313) - [Airbus Industrie A310-222](https://openairdocs.org/model/airbus-industrie-a310-222): 2 aircraft (registry code 3930315) - [Airbus A300 B4-103](https://openairdocs.org/model/airbus-a300-b4-103): 0 aircraft (registry code 3940020) - [Airbus A300 B4-200F](https://openairdocs.org/model/airbus-a300-b4-200f): 0 aircraft (registry code 3940021) - [Airbus A300 B4-622](https://openairdocs.org/model/airbus-a300-b4-622): 0 aircraft (registry code 3940012) - [Airbus A310-203](https://openairdocs.org/model/airbus-a310-203): 0 aircraft (registry code 3940008) - [Airbus A310-300](https://openairdocs.org/model/airbus-a310-300): 0 aircraft (registry code 3940007) - [Airbus A310-304](https://openairdocs.org/model/airbus-a310-304): 0 aircraft (registry code 3940061) - [Airbus A310-322](https://openairdocs.org/model/airbus-a310-322): 0 aircraft (registry code 3940016) - [Airbus A310-324](https://openairdocs.org/model/airbus-a310-324): 0 aircraft (registry code 3940014) - [Airbus Industrie A300 B2-1C](https://openairdocs.org/model/airbus-industrie-a300-b2-1c): 0 aircraft (registry code 3930302) - [Airbus Industrie A300 B2-203](https://openairdocs.org/model/airbus-industrie-a300-b2-203): 0 aircraft (registry code 3930300) - [Airbus Industrie A300 B2K-3C](https://openairdocs.org/model/airbus-industrie-a300-b2k-3c): 0 aircraft (registry code 3930500) - [Airbus Industrie A300 B4](https://openairdocs.org/model/airbus-industrie-a300-b4): 0 aircraft (registry code 3930333) - [Airbus Industrie A300 B4-103](https://openairdocs.org/model/airbus-industrie-a300-b4-103): 0 aircraft (registry code 3930331) - [Airbus Industrie A300 B4-203](https://openairdocs.org/model/airbus-industrie-a300-b4-203): 0 aircraft (registry code 3930306) - [Airbus Industrie A300 B4-2C](https://openairdocs.org/model/airbus-industrie-a300-b4-2c): 0 aircraft (registry code 3930301) - [Airbus Industrie A300 B4-600](https://openairdocs.org/model/airbus-industrie-a300-b4-600): 0 aircraft (registry code 3930319) - [Airbus Industrie A300 B4-600R](https://openairdocs.org/model/airbus-industrie-a300-b4-600r): 0 aircraft (registry code 3930309) - [Airbus Industrie A300 B4-601](https://openairdocs.org/model/airbus-industrie-a300-b4-601): 0 aircraft (registry code 3930321) - [Airbus Industrie A300 B4-620](https://openairdocs.org/model/airbus-industrie-a300-b4-620): 0 aircraft (registry code 3930345) - [Airbus Industrie A300-600](https://openairdocs.org/model/airbus-industrie-a300-600): 0 aircraft (registry code 3930344) - [Airbus Industrie A300-605R](https://openairdocs.org/model/airbus-industrie-a300-605r): 0 aircraft (registry code 3930361) - [Airbus Industrie A300F4-203](https://openairdocs.org/model/airbus-industrie-a300f4-203): 0 aircraft (registry code 3930349) - [Airbus Industrie A310-200](https://openairdocs.org/model/airbus-industrie-a310-200): 0 aircraft (registry code 3930310) - [Airbus Industrie A310-221](https://openairdocs.org/model/airbus-industrie-a310-221): 0 aircraft (registry code 3930314) - [Airbus Industrie A310-300](https://openairdocs.org/model/airbus-industrie-a310-300): 0 aircraft (registry code 3930305) - [Airbus Industrie A310-304](https://openairdocs.org/model/airbus-industrie-a310-304): 0 aircraft (registry code 3930339) - [Airbus Industrie A310-322](https://openairdocs.org/model/airbus-industrie-a310-322): 0 aircraft (registry code 3930334) - [Airbus Industrie A310-324](https://openairdocs.org/model/airbus-industrie-a310-324): 0 aircraft (registry code 3930318) - [Airbus Industrie A310-325](https://openairdocs.org/model/airbus-industrie-a310-325): 0 aircraft (registry code 3930303) ## STCs approved under this data sheet (328, first 50) - [STC ST12461IB](https://openairdocs.org/stc/ST12461IB): Installation of Cockpit Voice Recorder with optional RIPS Upgrade. Mid- Canada Mod Center - [STC ST00885LA](https://openairdocs.org/stc/ST00885LA): Installation of fire extinguisher cartridges as replacements for Pacific Scientific fire extinguisher cartridges in fire extinguisher bottles.. AMETEK AMERON, LLC d/b/a MASS Systems - [STC ST00374AT](https://openairdocs.org/stc/ST00374AT): Installation of Collins SAT-906 SATCOM system.. 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 SA2622NM](https://openairdocs.org/stc/SA2622NM): Installation of Precise Flight Pulselite Control Unit in landing/taxi system. (767-200 B17) (DHC-8 101). Precise Flight Inc. - [STC SA5040NM](https://openairdocs.org/stc/SA5040NM): Installation of cargo pallet and net.. Satco Inc. - [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 SA3481NM](https://openairdocs.org/stc/SA3481NM): Installation of C&D closet.. Safran Cabin Inc. - [STC ST01414SE](https://openairdocs.org/stc/ST01414SE): Installation of interior components. Safran Cabin Inc. - [STC SA3400NM](https://openairdocs.org/stc/SA3400NM): Installation of floor proximity emergency escape path marking system.. Bruce Aerospace Inc. - [STC ST01999AT](https://openairdocs.org/stc/ST01999AT): This installation adds three recording parameters (pitch control, lateral control, and rudder) to the existing A300 and A310 Digital Flight Data Recorder (DFDR) to meet the requirements of 14 CFR 121.344. Acron Aviation 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 ST00982CH](https://openairdocs.org/stc/ST00982CH): Installation of dual Universal Avionics UNS-1C GPS Flight Management Systems.. Amphenol Cable and Interconnect Technologies Inc. - [STC ST01113CH](https://openairdocs.org/stc/ST01113CH): Installation of dual Universal Avionics UNS-1K GPS flight management systems.. Amphenol Cable and Interconnect Technologies, Inc. - [STC ST01233CH](https://openairdocs.org/stc/ST01233CH): Installation of dual Honeywell Super Attitude heading Reference Systems (SAHRS).. Amphenol Cable and Interconnect Technologies, Inc. - [STC ST01235CH](https://openairdocs.org/stc/ST01235CH): Installation of dual Honeywell HT-9100 GPS flight management systems.. Amphenol Cable and Interconnect Technologies, Inc. - [STC ST01430CH](https://openairdocs.org/stc/ST01430CH): Installation of Universal Avionics System Corporation Electronic Horizontal Situation Indicators.. Amphenol Cable and Interconnect Technologies, Inc. - [STC ST01694CH](https://openairdocs.org/stc/ST01694CH): Installation of Honeywell International Enhanced Ground Proximity Warning System.. Amphenol Cable and Interconnect Technologies, Inc. - [STC ST01754CH](https://openairdocs.org/stc/ST01754CH): Installation of an Airshow 420 system IAW ECS MDL ECS-201346, Rev. A, dtd 1/24/03 or later FAA approved revision.. Amphenol Cable and Interconnect Technologies, Inc. - [STC ST02075CH](https://openairdocs.org/stc/ST02075CH): Installation of a Universal Avionics Systems Corporation Terrain Awareness and Warning System (TAWS).. Amphenol Cable and Interconnect Technologies Inc. - [STC ST02161CH](https://openairdocs.org/stc/ST02161CH): Installation of GPS wiring and antenna provisions.. Amphenol Cable and Interconnect Technologies Inc. - [STC ST02169CH](https://openairdocs.org/stc/ST02169CH): Installation of elementary and enhanced Mode S transponders. Amphenol Cable and Interconnect Technologies Inc. - [STC ST02866CH](https://openairdocs.org/stc/ST02866CH): Upgrade of the internal core software of the ACARS Data Link Management Unit (DLM-900). Amphenol Cable and Interconnect Technologies Inc. - [STC ST11861AT](https://openairdocs.org/stc/ST11861AT): Installation of a new Control Wheel Push-to-Talk (PTT) switch with three positions and latchable in accordance with the MDL shown in the attached AML No. ST11861AT.. FedEx Express - [STC ST00079IB](https://openairdocs.org/stc/ST00079IB): Integration of Halon-free Portable Fire Extinguisher HAFEX. UMLAUT ENGINEERING GMBH - [STC ST01550LA](https://openairdocs.org/stc/ST01550LA): 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 ST00691SE](https://openairdocs.org/stc/ST00691SE): Installation of lightweight window plugs. LiteAir Aviation Products Inc - [STC ST02691AT](https://openairdocs.org/stc/ST02691AT): Installation of SAF-T-GLO Inc. Photoluminescent floor proximity emergency escape path marking system (FPEEPMS). STG Aerospace Inc. - [STC ST02302CH](https://openairdocs.org/stc/ST02302CH): Install ERDA model 7004 HI-LO table with slide top. Collins Aerospace - [STC ST04562NY](https://openairdocs.org/stc/ST04562NY): Installation of saf-Tglo® SuperSeal UltraLite-X (SSUL-X) Photoluminescent Floor Proximity Emergency Escape Path Marking Systems. STG AEROSPACE GERMANY GmbH - [STC ST02487LA](https://openairdocs.org/stc/ST02487LA): Installation of main deck cargo loading system. Ancra International LLC - [STC ST02022AT](https://openairdocs.org/stc/ST02022AT): Installation of a Dual Canadian Marconi CMA-900 Flight Management System. Woven Electronics, LLC - [STC ST02297AT](https://openairdocs.org/stc/ST02297AT): This installation added three additional parameters to be recorded by the existing Flight Data Recorder. Woven Electronics LLC - [STC ST02896AT](https://openairdocs.org/stc/ST02896AT): Installation of a Kannad Model 406-AF Emergency Locator Transmittter (ELT).. Woven Electronics LLC - [STC ST01940CH](https://openairdocs.org/stc/ST01940CH): Installation of a Honeywell RESCU 406AF Emergency Locator Transmitter (ELT) System.. Honeywell International Inc. - [STC ST02166CH](https://openairdocs.org/stc/ST02166CH): Installation of a Honeywell RESCU 406AF/AFN Emergency Locator Transmitter (ELT) System. Honeywell International Inc. - [STC ST04445CH](https://openairdocs.org/stc/ST04445CH): Installation of Honeywell ADG-300 Wireless Data Loader. Honeywell International Inc. - [STC ST02929AT](https://openairdocs.org/stc/ST02929AT): Installation of an Artex Model C406-1 Emergency Locator Transmitter (ELT).. Woven Electronics LLC - [STC SA3025SO](https://openairdocs.org/stc/SA3025SO): Installation of dual TRA-67A Mode S transponder system.. Honeywell International Inc - [STC SA3026SO](https://openairdocs.org/stc/SA3026SO): Installation Of an CAS-81 TCAS II system.. Honeywell International Inc - [STC SA3168SO](https://openairdocs.org/stc/SA3168SO): Installation of dual TRA-67A Mode 'S' transponder system.. Honeywell International Inc - [STC ST00140AT](https://openairdocs.org/stc/ST00140AT): Installation of a MUA-45 Data Link System.. Honeywell International Inc - [STC ST00181SE](https://openairdocs.org/stc/ST00181SE): Installation of Model 4033, 4034 and 4038 Transient Suppression Units. Honeywell International Inc - [STC ST00440SE](https://openairdocs.org/stc/ST00440SE): Installation of the Honeywelll Enhanced Ground Proximity Warning System.. Honeywell International Inc All 328: https://openairdocs.org/tcds/A35EU/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.