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).
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