TCDS A35EU

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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