國(guó)產(chǎn)自拍??_登錄禁毒網(wǎng)站www2一c1ass_.手.動(dòng).輸.入.網(wǎng).址.聯(lián).系.客.服.人.員.lanan_shell
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). www.aero.cn 航空翻譯 www.aviation.cn 本文鏈接地址：航空資料9
