AIRBUS TYPE CERTIFICATE DATA SHEET Nº EA-8002-01

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MINISTÉRIO DA AERONÁUTICA DEPARTAMENTO DE PESQUISAS E DESENVOLVIMENTO CENTRO TÉCNICO AEROESPACIAL TYPE CERTIFICATE DATA SHEET Nº EA-8002-01 Type Certificate Holder: AIRBUS INDUSTRIE 1, Rond-point Maurice Bellonte 31707 Blagnac FRANCE EA-8002-01 Sheet 01 AIRBUS A300B2-203, A300B4-203; A310-203, -204, -221, -222, A310-304, -308, -322, -324, -325 March 1999 This data sheet, which is part of Type Certificate No. 8002, prescribes conditions and limitations under which the product, for which the Type Certificate was issued, meets the airworthiness requirements of the Brazilian Aeronautical Regulations. I - Model A300B2-203 (Transport Category), approved 13 August 1982. ENGINE Two General Electric model CF6-50C2 turbofan engines. MAXIMUM WEIGHT (kg) VARIANT Basic Model 001 with SB 34.025 embodied (mod. 1569) Max. Ramp Weight 142 900 137 900 Max. Take-off Weight 142 000 137 000 Max. Landing Weight 130 000 130 000 Max. Zero Fuel Weight 120 500 120 500 CG RANGE Forward Aft Takeoff 18% MAC 33% MAC Landing 15% below 120 500 kg 18% above 125 500 kg 35% Linear variation between 120 500 kg and 125 500 kg. FUEL QUANTITY (0.782kg/l) Usable Fuel Tanks Unusable Fuel Normal preselected refueling Refueling with high level shut off (kg) (kg) (kg) (liters) Outer 12 7 000 7 218 9 230 Inner 40 27 000 27 190 34 770 Total 52 34 000 34 408 44 000 AIRBUS March 1999 EA-8002-01 Sheet 2 II - Model A300B4-203 (Transport Category), approved 16 June 1980. ENGINE Two General Electric model CF6-50C2. turbojet engines. MAXIMUM WEIGHT (kg) Max. Ramp 165 900 Max. Take-off 165 000 Max. Landing 134 000 Max. Zero Fuel 124 000 CG RANGE Forward Aft Takeoff 18% MAC 33% MAC Landing 15% below 124 000 kg 18% above 130 000 kg 35% Linear variation between 124 000 kg and 130 000 kg. FUEL QUANTITY (0.782kg/l) Usable Fuel Unusable Without SB N° 28.021 (Mod. 1664) With SB N° 28.021 (Mod. 1664) Tanks fuel Normal preselected refueling Refueling with high level shut off Normal preselected refueling Refueling with high level shut off (kg) (kg) (kg) (liters) (kg) (kg) (liters) Outer 12 7 000 7 202 9 210 7 000 7 241 9 260 Inner 130 27 000 27 026 34 560 27 000 27 480 35 140 Center 48 11 000 11 206 14 330 13 500 13 763 17 600 Total 190 45 000 45 434 58 100 47 500 48 484 62 000 III - DATA PERTINENT TO ALL A300 SERIES FUEL See General Electric Specification D50 TF2. This specification is also applicable to the APU. Additives: - anti-icing: PHILLIPS PFA-55MB to MIL I 27686 specification, 0,15% by volume maximum concentration - biocide: SOHI0 BIOBOR JF at 270 PPM maximum concentration; - anti-static: SHELL ASA-3 at 1 PPM maximum concentration. For operating conditions specific to each fuel, refer to corresponding Flight Manual. ENGINE LIMITS (2.2482 lb/daN) Static thrust at sea level: Take-off (5min.)* (Up to 30°C) Maximum continuous (Up to 30ºC) 23 050 daN (51 800 lb) 20 600 daN (46 300 lb) AIRBUS March 1999 EA-8002-01 Sheet 3 ENGINE LIMITS (2.2482 lb/daN) (Cont.) Maximum engine speed: N1 rpm (%) N2 rpm (%) 4 068 (118.5%) 10 761 (109.5%) Maximum gas temperature: Take-off (5min.)* Maximum continuous Maximum acceleration (2 min) Starting 945oC 910oC 960oC 900/750oC Maximum oil temperature (supply pump inlet): Take-off, stabilized Transient (15 mn max.) 160oC 175oC Approved oils See Specification GE D50TF1 called for in SB GE N° 79-1 * 10 minutes at take-off thrust allowed only in case of engine failure (at take-off or during go-around). ** Up to 40 sec/above 40 sec. AUXILIARY POWER UNIT Airesearch TS CP 700-5 (Specification SC 6203). Operating limitations: - Maximum power rating at sea level: 105.8 kW (142 hp) - Maximum operating speed - N1: 30 910 rpm (110%) - N2: 38 845 rpm (110%) - Maximum gas temperature at turbine: 585oC Approved oils: see AIRESEARCH maintenance manual TSCP 700 49.20.00 table 303. AIRSPEED LIMITS Maximum Operating Mach (MMO) (IAS, unless otherwise stated) At and over 12 700 m (28 000 ft) : 0.86/0.82 (see Note 5) Maximum Operating Speed (VMO) Up to 12 882 m (28 400 ft) : 345 kt: Maneuvering Speed (VA): see DGAC approved Brazilian Flight Manual. Extended Flaps/Slats Speed (VFE): see table below: Slats/Flaps (°) VFE (kt) Take-off 16/0 250 Take-off 16/8 215 Approach 16/15 205 Landing 25/25 180 Enroute 16/0 210 (M=0.47) Minimum Control Speed: - In flight (VMCA): 112 kt - Takeoff/Landing (VMCG): 107 kt Landing gear: (VLE) - Extended: 270 kt/ Mach 0.59 (VLO) - Extension 270 kt (VLO) - Retraction 240 kt Tyres Limit Speed (Ground Speed): 195.5 kcas AIRBUS March 1999 EA-8002-01 Sheet 4 DATUM Station 0 - 6.38 m (251.26 in) forward of the fuselage nose. MEAN AERODYNAMIC CHORD 6.6080 m (250.15 in); leading edge of MAC: Sta. 1116. LEVELING MEANS Clinometer on the cabin rails. MINIMUM FLIGHT CREW 2 pilots and 1 flight engineer. 2 pilots for aircraft identified FF (See Note 6). MAXIMUM PASSENGERS 345 in compliance with the requirements of FAR 25 Amdt. 32, covering emergency exits. Emergency evacuation demonstration in compliance with FAR 25 para. 25.803 (c) was conducted with 330 passengers. For the number of passengers authorized for each aircraft, see the corresponding interior arrangement drawing approved by the DGAC. MAXIMUM BAGGAGE Cargo compartment maximum load: Forward: 16 620 kg Mid: 10 280 kg Aft (bulk): 2 500 kg For the positions and the loading conditions authorized in each position (references of containers, pallets and associated weights) see Approved Flight Manual (chapter 6 - Annex 02). The aircraft must be loaded according to instructions included in the Weight and Balance Manual HYDRAULIC FLUIDS Specification NSA 30-7110. TYRES See SB A300-32-002. MAX. OPERATING ALTITUDE 12 200 m (40 000 ft) TEMPERATURE OPERATING See DGAC approved Brazilian AFM. LIMITS CONTROL SURFACE MOVEMENTS 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 Industrie Reports A300B 8.27.010, .011, .012, .013, .014 and .015. Rigging procedure: Airbus Industrie Reports A007-10.063, -10.094, -10.095, -10.100, -10.102, -10.103, -10.105 and - 10.123. SERIAL NUMBERS ELIGIBLE A Certificate of Airworthiness for Export endorsed as Noted under "Import Requirements" must be submitted for each individual aircraft for which application for a Brazilian Certificate of Airworthiness is made. AIRBUS March 1999 EA-8002-01 Sheet 5 IMPORT ELIGIBILITY A Brazilian Certificate of Airworthiness may be issued on the basis of on a DGAC Export Certificate on Airworthiness (or a third country Export Certificate on Airworthiness, in case of used aircraft imported from such country), including the following statement: “The aircraft covered by this certificate has been inspected, tested and found to be in conformity with the Brazilian approved type design as defined by the Brazilian Type Certificate no. 8002 and in condition of safe operation”. The CTA Report H.10-015-01, dated 19 May 80 or further revisions, contains the Brazilian requirements for the acceptance of these airplanes. (See Note 4) CERTIFICATION BASIS RBHA 25 (corresponding to Franco/German requirements of FAR Part 25 including Amdts. 1 thru 19). FAR 25 Amdt. 23 for the following paragraphs : 25.145, 25.1305, 25.1321, 23.1331, and 25.1333. FAR 25 Amdt. 24 for paragraph 25.1303. FAR 25 Amdt. 32 for paragraphs 25.785, 25.787, 25.789, 25.791, 25.809, 25.811, 25.812, 25.853, 25.855, 25.857, 25.1557, and Appendix F. Franco/German “Conditions Techniques Complémentaires” as listed in DGAC documents 4080 DTA/M dated 6 August 1970, and 2060 DTA/M dated 30 March 1973. Operation at take-off thrust extended to 10 minutes in case of engine failure, as per SGAC letter 16233 DTA/SDT/M of 7 March 1974. Endurance flight campaign called for as per paragraph 6.4 of SGAC/LBA document on the organization of the A300 B Certification, dated 6 October 1970. For the Automatic Flight Control System, the applicable technical requirements are complemented by: - AC.25 1329-1A for category 1 cruise and approach; - Circulars DTA/M 3938 and AC 20-57A for category II approach and automatic landing; - AC 120-28 A for category III a precision approach; The requirements are established in SGAC letter 3904 DTA/M; dated 20 July 1972. Use of flexible take-off thrust as per SGAC letter 1694, dated 12 March 1974. Noise Standard: ICAO Annex 16. REQUIRED EQUIPMENT The basic required equipment, as prescribed in the applicable airworthiness regulations (see Certification Basis) must be installed in the airplane. Equipment approved for installation is listed in the following Certification Standard Equipment List: - A300B2-203: AI/V-C N° 149/ 80; and - A300B4-203: AI/V-C N° 13/79. AIRBUS March 1999 EA-8002-01 Sheet 6 REQUIRED EQUIPMENT (Cont.) Cabin furnishings equipment shall be in conformance to the following frame specifications: - For Galleys: TL 25/1109/74; and - For Passenger Seats: TL 25/1110/74. NOTES NOTE 1: Weight and Balance. Current weight balance report, including list of equipment included in certificate empty weight and loading instructions when necessary, must be in each aircraft at the time of original certification and at all times thereafter (except in the case of air carrier operators having an approved weight control system). The certificate empty weight and the corresponding center of gravity location must include unusable fuel, engine oil, hydraulic fluid in tanks and in the systems. The certificate empty weight does not include the lifting jack carried on board, the entrance steps, the tools kit, the life jackets and the fluid to be injected into the engine. NOTE 2: Markings and Placards. All markings and placards for passenger information under normal or emergency conditions must be in English and Portuguese. All markings and placards for flight attendants information under emergency conditions must be in English and Portuguese. External markings for emergency operation of doors and normal ground operations of cargo doors must be in English and Portuguese. NOTE 3: Continuing Airworthiness. Life limitations are provided in the Chapter 05 of the A300 Maintenance Manual, approved by DGAC. NOTE 4: The differences of the Brazilian airplanes in relation to the basic DGAC type design are summarized below: 1. The DGAC approved Brazilian Airplane Flight Manual; 2. Markings and placards in Portuguese language: see Note 2; 3. ADF1 powered by the emergency bus bars; 4. APU fire extinguisher handle “pull and turn” inscription; and 5. Autothrottle control panel identification. NOTE 5 For model B4-203, the MMO warning selector of modification no. 1688 allows an MMO switching. MMO is 0.86 for takeoff weights up to 153 000 kg (337 302 lb) and 0.82 for takeoff weight greater than 153 000 kg (337 302 lb) provided the airplane is operated in accordance with the corresponding DGAC approved Airplane Flight Manual page 2.03.00 page 1. NOTE 6 Aircraft identified by the letters FF added to the designation of the model have forward facing crew cockpit and digital autopilot with associated subsystems. The definition of FF aircraft is detailed in AI/V-C document 1045/81. FF aircraft are to be used with a Flight Manual incorporating the FF revision approved by DGAC. NOTE 7 If modifications 0904, 1022 and 1023 are embodied, the aircraft has Category IIIa precision approach capability. AIRBUS March 1999 EA-8002-01 Sheet 7 IV -Model A310-203 (Transport Category), approved 17 October 1998 Model A310-204 (Transport Category), approved 17 October 1998 Model A310-221 (Transport Category), approved 17 October 1998 Model A310-222 (Transport Category), approved 17 October 1998 ENGINE Model A310-203: Two General Electric model CF6-80A3 Model A310-204: Two General Electric model CF6-80C2A2 Model A310-221: Two Pratt & Whitney model JT9D-7R4D1 Model A310-222: Two Pratt & Whitney model JT9D-7R4E1 MAXIMUM WEIGHT (kg) A310-203/-221 A310-203/-221/-222 A310-203 VARIANT Basic Model Variant 03 with mod. 4008 Variant 01 with mod. 3703 * Variant 04 with mod. 5124 ** Variant 06 with mod. 6395 Variant 08 with mod. 7415 Max. Ramp 132 900 125 900 139 500 142 900 135 900 139 500 Max. Take-off 132 000 125 000 138 600 142 000 135 000 138 600 Max. Landing 118 500 118 500 121 500 121 500 118 500 122 000 Max. Zero Fuel 108 500 108 500 111 500 111 500 111 500 112 000 * SB 00-2003 ** SB 00-2002 A310-221 A310-204/-222 A310-204 A310-222 VARIANT Variant 07 with mod. 6764 * Variant 101 with mod. 6527 Variant 104 with mod. 6528 Variant 107 with mod. 7290 Variant 11 with mod. 10685 Max. Ramp 132 900 139 500 142 900 134 900 144 900 Max. Take-off 132 000 138 600 142 000 134 000 144 000 Max. Landing 119 500 122 000 122 000 122 000 121 500 Max. Zero Fuel 111 500 112 000 112 000 112 000 111 500 * SB 00-2006 FUEL QUANTITY (0.8kg/l) Unusable Usable Fuel (kg) Tanks Fuel (kg) Variant XX Variant 1XX Outer 41 5 992 5 920 Inner 40 22 360 22 320 Central 14 15 728 15 728 Total 95 44 080 43 968 AIRBUS March 1999 EA-8002-01 Sheet 8 V - Model A310-304 (Transport Category), approved 17 October 1998 Model A310-308 (Transport Category), approved 17 October 1998 Model A310-322 (Transport Category), approved 17 October 1998 Model A310-324 (Transport Category), approved 24 October 1997 Model A310-325 (Transport Category), approved 24 October 1997 ENGINE Model A310-304: Two General Electric model CF6-80C2A2 Model A310-308: Two General Electric model CF6-80C2A8 or CF6-80C2A2 (See Note 8) Model A310-322: Two Pratt & Whitney model JT9D-7R4E1 Model A310-324: Two Pratt & Whitney model PW 4152 Model A310-325: Two Pratt & Whitney model PW 4156A MAXIMUM WEIGHT (kg) A310-304/-322/-324 A310-304/-308/-324 VARIANT Basic Model Variant 01 with mod. 5616 * Variant 03 with mod. 8144 Variant 05 with mod. 7088 Max. Ramp 150 900 153 900 153 900 157 900 Max. Take-off 150 000 153 000 153 000 157 000 Max. Landing 123 000 123 000 124 000 124 000 Max. Zero Fuel 113 000 113 000 114 000 114 000 * SB A310-00-2007 A310-304 A310-308/-325 A310-308 A310-324 VARIANT Variant 06 with mod. 7614 Variant 07 with mod. 7659 Variant 08 with mod. 8130 Variant 09 with mod. 8469 * Variant 12 with mod. 11103 ** Max. Ramp 139 500 134 900 164 900 161 900 160 900 Max. Take-off 138 600 134 000 164 000 161 000 160 000 Max. Landing 123 000 124 000 124 000 124 000 124 000 Max. Zero Fuel 113 000 114 000 114 000 114 000 114 000 * SB A310-00-2018 ** SB A310-00-2029 (See Note 9) FUEL QUANTITY (0.8kg/l) Unusable Usable Fuel (kg) Tanks Fuel (kg) Variant XX Variant 1XX Outer 41 5 992 5 920 Inner 40 22 360 22 320 Central 14.4 15 728 15 712 Trim 32 15 728 4 920 Total 127.4 44 080 48 872 AIRBUS March 1999 EA-8002-01 Sheet 9 VI - DATA PERTINENT TO ALL A310 SERIES FUEL See General Electric Specification D50 TF2 or Pratt & Whitney Specification TM522 given in P&W S.B. No. 2016. Additives: - anti-icing: PHILLIPS PFA-55MB to MIL-I-27686 specification, 0,15 % by volume maximum concentration - biocide: SOHI0 BIOBOR JF at 270 PPM maximum concentration; - anti-static: SHELL ASA-3 at 1 PPM maximum concentration. For operating conditions specific to each fuel, refer to corresponding Flight Manual. ENGINE LIMITS (2.2482 lb/daN) ENGINE CF6-80A3 CF6-50C2A2 CF6-50C2A8 Static thrust at sea level, up to 30°C (lb): Take-off (5min.)* Maximum continuous 48 970 lb 45 800 lb 52 460 lb 48 080 lb 46 300 lb 51 800 lb Maximum engine speed: N1 rpm (%) N2 rpm (%) 4 016 (117) 10 859 (110.5) 3 854 (117.5) 11 055 (112.5) 4.068 (118.5) 10.761 (109.5) Maximum gas temperature (oC): Take-off (5min.)* Maximum continuous Starting: 940 895 870/750** 960 910 870/750 ** 945 910 900/750** Maximum oil temperature (oC): (supply pump inlet): Take-off, stabilized Transient (15 mn max.) 160 175 160 175 160 175 Approved oils See Specification GE D50TF1 called in SB GE N° 79-1 * 10 minutes at take-off thrust allowed only in case of engine failure (at take-off or during go-around) (see letter SGAC N° 1623 DTA/SDT/M of 7 March 1974 for General Electric engines) ** Up to 40 s/above 40 s. ENGINE JT9D-7R4D1 JT9D-7R4E1 PW 4152 PW 4156A Static thrust at sea level, up to 30°C (lb): Take-off (5min.)* Maximum continuous 48 000 lb 45 800 lb 50 000 lb 47 500 lb 52 000 lb 49 200 lb 56 000 lb 49 200 lb Maximum engine speed: N1 rpm (%) N2 rpm (%) 3 810 (105.8) 8 000 (102.5) 3 810 (105.8) 8 000 (102.5) 4 012 (111.4) 10 300 (104.0) 4 012 (111.4) 10 450 (105.5) Maximum gas temperature (oC): Take-off (5 min.)* Acceleration (2 min) Maximum continuous Starting 625 625 600 535 635 635 610 535 625 625 600 510 650 650 625 535 AIRBUS March 1999 EA-8002-01 Sheet 10 ENGINE LIMITS (Cont.) ENGINE JT9D-7R4D1 JT9D-7R4E1 PW 4152 PW 4156A Maximum oil temperature(oC): (supply pump inlet): Take-off, stabilized Transient (15 min max.) 135 163 135 163 163 177 163 177 Approved oils See Specification P&W 521C called for in SB PWA N° 238 * 10 minutes at take-off thrust allowed only in case of engine failure (at take-off or during go-around). AUXILIARY POWER UNIT AIRESEARCH GTCP 331-250(F) for models A310-200. AIRESEARCH GTCP 331-250(H) for models A310-200 Variant 100 and A310-300. Operating imitations: Maximum power rating at sea level: 98.5 kW Maximum operating speed: 43 562 rpm Maximum gas temperature at turbine: 585oC Approved oils: see AIRESEARCH maintenance manual GTCP 331-250 Chapter 49-21-00 table 2. AIRSPEED LIMITS Maximum Operating Mach (MMO): 0.84 (IAS, unless otherwise stated) Maximum Operating Speed (VMO): 360/340 kt * Maneuvering Speed (VA): see DGAC approved Brazilian Flight Manual. Extended Flaps/Slats Speed (VFE): see table below: Slats/Flaps (°) VFE (kt) Take-off 15/0 245 Take-off and approach 15/15 210 Take-off, approach and landing 20/20 195 Landing 30/40 180 Holding and En-route 15/0 245 (M=0.54) Minimum Control Speed: see DGAC approved Brazilian Flight Manual. Landing gear: (VLE) - 270 kt/ Mach 0.65 (VLO) - 270 kt/ Mach 0.59 Tyres Limit Speed (Ground Speed): 195.5 kcas * 360 kt: - Basic model and variants 04, 06 and 07. 340 kt : - Variants 01, 03, 05, 08 and 09; and - All models with less than 2 t in one of the outer tanks. CENTER OF GRAVITY RANGE See CTA Airplane Flight Manual DATUM Station 0 - 6.38 m (251.26 in) forward of the fuselage nose. MEAN AERODYNAMIC CHORD 5.8280 m (229.45); leading edge of MAC: Sta. 992. AIRBUS March 1999 EA-8002-01 Sheet 11 LEVELING MEANS Clinometer on the cabin seat track rails. MINIMUM FLIGHT CREW 2 pilots MAXIMUM PASSENGERS 265, as limited by passenger emergency exit requirements. (See Note 11). MAXIMUM BAGGAGE Cargo compartment maximum load: Forward: 12 700 kg Aft: 9 525 kg (11 110 kg with mod. 3656). Bulk: 2 770 kg (1 442 kg with mod. 3656). For the positions and the loading conditions authorized in each position (references of containers, pallets and associated weights) see Weight and Balance Manual Chapter 1.10.05. HYDRAULIC FLUIDS Specification NSA 30-7110. TYRES See SB A310-32-2006 MAXIMUM OPERATING ALTITUDE 12 530 m (41 100 ft) TEMPERATURE OPERATING See DGAC approved Brazilian AFM. LIMITS CONTROL SURFACE MOVEMENTS 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 Industrie Reports A300B 8.27.010, .011, .012, .013, .014 and .015. Rigging procedure: Airbus Industrie Reports A007-10.063, -10.094, -10.095, -10.100, -10.102, -10.103, -10.105 and -10.123. S/N’S ELIGIBLE A Certificate of Airworthiness for Export endorsed as Noted under "Import Requirements" must be submitted for each individual aircraft for which application for a Brazilian Certificate of Airworthiness is made. IMPORT ELEGIBILITY A Brazilian Certificate of Airworthiness may be issued on the basis of on a DGAC Export Certificate on Airworthiness (or a third country Export Certificate on Airworthiness, in case of used aircraft imported from such country), including the following statement: “The aircraft covered by this certificate has been inspected, tested and found to be in conformity with the Brazilian approved type design as defined by the Brazilian Type Certificate No. 8002 and in condition of safe operation”. AIRBUS March 1999 EA-8002-01 Sheet 12 IMPORT ELEGIBILITY (Cont.) The CTA Report H.10-0153-02, dated 22 Mar. 1999 or further revisions, contains the Brazilian requirements for the acceptance of these airplanes. (See Note 4) CERTIFICATION BASIS RBHA 25 . RBHA 36 , plus any addition or deletion established in paragraphs 6, 8 and 9 of this report and including the following special requirements listed in DGAC certification basis and endorsed by CTA: 01. French-German technical complementary conditions: - CB2-Minimum Stalling Speed - CB7-1-Flight in Rough Air - CC4-1-“En Route” Design Conditions with High Lift Devices Extended - CC5-1-Design Manoeuvre Conditions - CC6-1-Design Gust Conditions (except for A310-300 variant 08) - CC6-3-Design Gust Conditions (for A310-300 variant 08 only) - CC8-1-Bird Impact - CC9-1-Asymmetric Load on the Horizontal Stabilizers - CC10-1-Ground Loads - CC11-Jacking Loads - CC12-1-Crash Design Conditions - CD1-1-General Design of Systems - CD8-1-Operation of Landing Gear - CD9-2-Protection of Equipment installed on LG and LG Wheel Wells - CE0-Engine Installation - Application JAR E - CE2-1-Windmilling without Oil - CE4-1-Engine Vibration Levels - CE10-1-Auxiliary Power Unit (APU) and its installation on the Aircraft - CF3-1-Functioning of the Systems under Negative Acceleration - CF7-1-Electrics --Endurance demonstration 02. Special condition applicable to A310-300 Series related to Center of Gravity Control Systems. 03. Discrete gust requirements for A310-308 variants 08 and 09 approved in accordance with JAR NPA 25C-205. 04. Extended Range Twin Engine Airplane Operations approval in accordance with AC 120-42. AIRBUS March 1999 EA-8002-01 Sheet 13 CERTIFICATION BASIS (Cont.) 05. Precision Approach and Landing requirements complemented by CTC 25-2 for category II and category I approach, JAR AWO Section III NPA no 25G-142 (June 83) for category III precision approach with and without decision height (fail operational system); the Automatic Flight Control System complies with AC 25.1329-1A for cruise and AC 20-57A for automatic landing. 06. Special conditions related to the use of FADEC on the Pratt & Whitney engines for A310-324 and A310-325: - S12-FADEC Lightning Protection - S13-FADEC Engine Isolation - S14-Thrust Reverser Deletion of Mechanical Interlock - S15-FADEC - S16-FADEC - Effect of External Radiation REQUIRED EQUIPMENT The basic required equipment, as prescribed in the applicable airworthiness regulations (see Certification Basis) must be installed in the airplane. Equipment approved for installation is listed in the following Certification Standard Equipment List: - A310-200: AI/V-C N° 5/83; - A310-200 Variant 100: AI/EA-A N° 251/86; and - A310-300: AI/EA N° 1901/85; Cabin furnishings equipment shall be in conformance to the following frame specifications: - Galleys : TL 25/1109/74 - Passenger Seats: TL 25/1110/74 NOTES NOTE 1: Weight and Balance. Current weight balance report, including list of equipment included in certificate empty weight and loading instructions when necessary, must be in each aircraft at the time of original certification and at all times thereafter (except in the case of air carrier operators having an approved weight control system). The certificate empty weight and the corresponding center of gravity location must include unusable fuel, engine oil, hydraulic fluid in tanks and in the systems. The certificate empty weight does not include the lifting jack carried on board, the entrance steps, the tools kit, the life jackets and the fluid to be injected into the engine. NOTE 2: Markings and Placards. All placards specified in the approved Brazilian Airplane Flight Manual must be displayed in the airplane in the appropriate locations. In addition, all markings and placards for passenger information, external markings for emergency, load limits in cargo/baggage compartments must be presented in Portuguese or bilingual (Portuguese/English). The translations acceptable to CTAm are listed in the CTA Report H.10-0153-02, dated 22 Mar. 1999 or further revisions. NOTE 3: Continuing Airworthiness. Life limitations are provided in the Chapter 05 of the A310 Maintenance Manual, approved by DGAC. Structures and Systems Certification Maintenance Requirements are listed in Airbus Industrie document AI/ST 5/849/85. AIRBUS March 1999 EA-8002-01 Sheet 14 NOTE 4: The differences of the Brazilian airplanes in relation to the basic DGAC type design are summarized below: 1. The DGAC approved Brazilian Airplane Flight Manual; 2. Markings and placards in Portuguese language or bilingual (see Note 2); 3. Operational requirements - the following modifications must be installed: - cabin ozone filter: Mod. 6159; - cargo/baggage compartment fire protection: Mods. 8265 and 10452; - DFDR: Mod. 8500 and 8705; - ELT: TSO C91a; - Floor emergency escape path marking: Mod. 6515 (MBB System, 6934 (Bruce System) or 6812 (LSI System);GPWS: Mod. 8960; - TCAS, if required: Mods. 8616 and 10928 (Bendix System) or Mods. 10664 and 11049 (Honeywell System); - Windshear detection and guidance system: Mod. 7187; and - Second ADF: Mod. 4536. 4. MMEL categorized. NOTE 5: If the modification 4941 is embodied, the aircraft is approved for CAT III Precision Approach. NOTE 6: The definition of the aircraft for extended twin engine airplane operations is precised in the document AI/EA 3000 - “Configuration, Maintenance and Procedures Standards According to AC 120-42A”, Ref. CMP DGAC. NOTE 7: Modifications 6920 and 7468 provide for installation in aft cargo compartment of respectively 1 and 2 Auxiliary Center Tanks with the following characteristics: Tanks Unusable Fuel Usable Fuel ACT 1 27 kg (34 l) 5 760 kg (7 200 l) ACT 2 27 kg (34 l) 5 760 kg (7 200 l) NOTE 8: On A310-308 model, the engine General Electric CF6-80C2A2 may be used after embodiment of Service Bulletin A310-71-2003 and with the corresponding revision of the AFM supplement 11. NOTE 9: Weight variant 12 to A310-324 model only applies to individual MSN 442, 453, 456 and 467. NOTE 10: If the modification 11469 (for GE engines) or 11468 (for P&W engines) is installed, the aircraft is approved in accordance with AC 91-RVSM Reduced Vertical Separation Minimum operation. NOTE 11: High density configuration up to 275 passengers can be appreciated by CTA, upon request and justification provided by Airbus. LUIZ ALBERTO C. MUNARETTO – Ten.-Cel.-Av. Maj.-Brig.-do-Ar REGINALDO DOS SANTOS Chefe da Divisão de Homologação Aeronáutica Diretor do Centro Técnico Aeroespacial (Chief, Divisão de Homologação Aeronáutica) (Director, Centro Técnico Aeroespacial)

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AIRBUS TYPE CERTIFICATE DATA SHEET Nº EA-8002-01