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weight and performance calculations for the Airbus A310-300 (WV00)
Balair A310-325 HB-IPL c/n 640 at Zurich-Kloten airport, May 1997
Airbus A310-300 (WV00)
role : wide-body airliner
importance : ****
first flight : 8 July 1985 operational : December 1985 (Swissair, JT9D-7R4E engines)
, March 1986 (Air India, CF6-80C2 engines)
country : EU-consortium
ICAO aircraft type designator : A310
production : -300 ca.183 aircraft, total A310 : 255 aircraft
general information :
Extended-range version. More range optained due to higher MTOW and additional fuel, as standard located in the tail, making in flight CG-control possible for improved fuel efficiency. For extra extended range one or two ACT’s (auxiliary Centre Tank) can be installed in part of the cargo hold.
This version is recognizable by the delta shaped wingtip fences. These were also applied to some -200's. The -300 has a larger fuel capacity of 61100 liters in total, with 2 optional center tanks it even comes to 68300 liters. At the end of 1989, Interflug flew an A310-300 non-stop from Berlin to Havana, a distance of 8360 km, a record for Airbus.
primary users : Swissair, Delta, Royal Jordanian, Aeroflot, Interflug, Air France, Air Kenya,
Tarom, CSA, Ai India, THY, TEA,Hapag-Lloyd, Balair, Air France.
Accommodation:
flight crew : 2 cabin crew : 8
passengers : seating for 220 in two class : 20 business class and 200 coach class seats
( 34 -in pitch) exit limit : 275 passengers, high density seating for 264 passengers
engine : 2 General Electric CF6-80C2A2 turbo
fan engines of 238.0 [KN] (53504 [lbf])
or 2 Pratt & Whitney JT9D-7R4E engines of .
dimensions :
wingspan : 43.89 [m], length overall: 46.66 [m], length of fuselage : 45.13 [m]
height : 15.8 [m] wing area gross : 219.9 [m^2] fuselage exterior width : 5.64 [m]
weights :
operating empty weight : 79207 [kg] max. structural payload : 33793 [kg]
Zero Fuel weight (ZFW) : 113000 [kg] max. landing weight (MLW) : 122970 [kg]
max. take-off weight : 149960 [kg] weight usable fuel : 47940 [kg] (61070 [litres])
performance :
Max. operating Mach number (Mmo) : 0.86 [Mach] (930 [km/hr]) at 9450 [m]
critical Mach speed : 0.81 [Mach]
max. cruising speed : 869 [km/hr] (Mach 0.81 ) at 10000 [m] (28 [%] power)
economic cruising speed : 835 [km/hr] (Mach 0.78 ) at 10000 [m]
service ceiling : 12527 [m]
range with max fuel and MTOW : 7900 [km] (ATA domestic fuel reserves - 370.0 [km] alternate)
description :
cantilever mid-wing monoplane with retractable landing gear with nose wheel
engines attached with pylons to the wing, main landing gear attached to the wings, fuel tanks in the wings and fuselage
Wings : two-spar multi-rib metal fail safe main wing box with aluminium alloy stressed skin
with Fowler-type double slotted trailing edge flaps on inner wing and single-slotted flap on outer wing with full-span slotted LE flaps (slats) ,with spoilers (outboard) and airbrakes (inboard) made of CFRP and with wingtip fences. airfoil : Airbus
average thickness/chord ratio : 12.6 [%], sweep angle 3/4 chord: 28.0 [°]
Dihedral : inboard 11°8’, outboard 4°3’ > average 7.5°, in above drawing average dihedral = 3.96°
incidence : 5.05 [°], dihedral : 4.0 [°]
Fuselage : Pressurized conventional semi-monocoque fail safe structure of circular cross-section built mainly of high-strength aluminium alloy
calculation : *1* (dimensions)
wing chord at root : 8.38 [m]
wing chord at tip : 2.18 [m]
taper ratio : 0.260 [ ]
mean wing chord : 5.01 [m]
wing aspect ratio : 8.76 []
Oswald factor (e): 0.698 []
seize (span*length*height) : 32357 [m^3]
calculation : *2* (fuel consumption)
oil consumption : 16.7 [kg/hr]
fuel consumption (econ. cruise speed) : 4840.4 [kg/hr] (6166.1 [litre/hr]) at 23 [%] power
distance flown for 1 kg fuel : 0.17 [km/kg] at 10000 [m] height, sfc : 45.0 [kg/KN/h]
total fuel capacity : 61070 [litre] (47940 [kg])
calculation : *3* (weight)
weight engine(s) dry : 8600.0 [kg] = 18.07 [kg/KN]
weight 230.6 litre oil tank : 19.60 [kg]
oil tank filled with 3.0 litre oil : 2.7 [kg]
oil in engine 5.8 litre oil : 5.2 [kg]
First Airbus for Eastern Bloc
– East Germany is the first Eastern Bloc country to buy the Western Airbus. The GDR bought three of the intercontinental version, the first of which landed yesterday at Schönefeld, the airport of East Berlin.
weight all fuel lines and pumps containing 92 litres fuel : 110.4 [kg]
weight engine cowling : 1237.6 [kg]
weight thrust reversers : 714.0 [kg]
total weight propulsion system : 10689 [kg](7.1 [%])
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Accommodation cabin facilities:
typical 2-class cabin layout for 220 passengers : economy : pitch : 86.4 [cm] 34.0 [-in]
( 2+4+2 ) seating in 27.9 rows
weight passenger seats : 1248.2 [kg]
weight cabin crew seats : 40.0 [kg]
weight flight crew seats : 42.0 [kg]
weight 2 jump seats in the cockpit :14.0 [kg]
high density seating passengers : 264 [pax] at mainly 9 -abreast seating in 31.9 rows,
pitch 80.7 [cm] 31.8 [-in]
pax density, normal seating : 0.78 [m2/pax], high density seating : 0.65 [m2/pax]
passenger cabin luxurious spaced for good service, enough space for galleys and toilets even
at HD seating
weight 5 lavatories : 154.5 [kg]
weight 6 galleys : 421.7 [kg]
Lufthansa A310-300 interior
weight overhead stowage for hand luggage (total : 22.5 [m3]) : 76.8 [kg]
weight 2 wardrobe closets : 22.0 [kg]
weight 3 movie screens : 51.1 [kg]
weight 58 windows (41 x 28 cm) made of acrylic glass : 157.7 [kg]
weight 4 (1.93 x 1.07 [m]) Type A main entry doors : 232.1 [kg]
weight 3 (main door size : 1.71 x 2.69 [m]) freight doors (belly) : 511.4 [kg]*
total usable belly baggage/cargo hold volume : 112.2 [m3]
underfloor belly hold can accommodate : 14 LD3 containers, netto volume : 62.6 [m3]
and : 21.0 [m3] bulk cargo
cabin volume (usable), excluding flight deck : 448 [m3]
passenger compartment volume : 209 [m3]
passenger cabin max width : 5.28 [m] cabin length : 33.24 [m] max cabin height : 2.33 [m]
floor area : 172.3 [m2]
weight cabin facilities : 2971.6 [kg]
safety facilities:
weight 2 type I emergency exits (0.67 x 1.39 [m]): 52.3 [kg]
evacuation time with 264 passengers : 52 [sec]
weight 11 hand fire extinguisher : 32 [kg]
weight cockpit voice recorder (CVR) and flight data recorder (FDR): 20.0 [kg]
weight oxygen masks & oxygen generators (deploy cabin alt.>4267m): 143.0 [kg]
weight emergency flare installation : 10 [kg]
weight 6 emergency evacuation slides : 423.0 [kg]
weight safety equipment & facilities : 680 [kg]
fuselage construction:
fuselage aluminium frame : 15409 [kg]
floor loading (payload/m2): 196 [kg/m2]
weight rear pressure bulkhead : 356.3 [kg]
fuselage covering ( 630.7 [m2] duraluminium 2.74 [mm]) : 4610.7 [kg]
weight floor beams : 2457.4 [kg]
weight cabin furbishing : 2299.2 [kg]
weight cabin floor : 2410.1 [kg]
weight (sound proof) isolation : 504.0 [kg] TO-noise level : 97.7 [EPNdB]
weight 19635 [litre] main central fuel tanks empty : 392.7 [kg]
weight empty 353 [litre] potable water tanks : 31.2 [kg]
weight empty waste tank : 20.6 [kg]
weight fuselage structure : 28491.3 [kg]
Avionics:
weight VHF radio and Selcal : 9.0 [kg]
weight flight and service attendants intercom : 5.0 [kg]
weight monochromatic weather X-band (3.2cm wavelength) radar system : 25.0 [kg]
Cockpit of Iran Air A310-304 EP-IBK, June 2018
weight VOR/ILS,RMI,DME,radio altimeter, ASI, time clock : 20.0 [kg]
weight Avionic Flight Control System : 33.0 [kg]
weight CAT IIIA auto-landing system : 10.0 [kg]
weight EFIS (4 Rockwell Collins CRT screens ADI/PFD+HSI/ND displays) : 20 [kg]
weight ground proximity warning system (GPWS) : 6 [kg]
weight engine monitoring system ECAM : 24 [kg]
weight reserve ADI, ASI, alti-meter, compass, engine temp. and rpm indicators : 15 [kg]
weight avionics : 154.0 [kg]
Systems:
Air-conditioning and pressurization system maintains sea level conditions up to 6300 [m]
and gives equivalent of 2400 [m] at 11885 [m]. pressure differential : 0.57 [bar] (kg/cm2)
pressurized fuselage volume : 680 [m3] cabin air refreshment time : 3.5 [min]
weight air-conditioning and pressurization system : 329 [kg]
weight APU / engine starter : 119.0 [kg]
weight lighting : 72.6 [kg]
weight triple redundant 207 bar hydraulic system : 107.9 [kg]
weight two engine-driven 90kVA 400 Hz 3-phase AC electricity generators : 55.0 [kg]
weight ram air turbine for emergency electric power : 5.0 [kg]
weight three 24V 25Ah nickel-cadmium batteries : 31.8 [kg]
weight controls : 19.6 [kg]
weight systems : 734.7 [kg]
total weight fuselage : 33032 [kg](22.0 [%])
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total weight aluminium ribs (1453 ribs) : 5081 [kg]
weight engine mounts : 238 [kg]
weight 6 wing fuel tanks empty for total 35300 [litre] fuel : 530 [kg]
weight 244 [litre] vent surge tanks : 29 [kg]
weight wing covering (painted aluminium 4.94 [mm]) : 5872 [kg]
total weight aluminium spars (multi-cellular wing structure) : 6391 [kg]
weight wings : 17344 [kg]
weight wing/square meter : 78.87 [kg]
weight thermal leading-edge anti-icing : 48.3 [kg]
weight high & low speed ailerons (6.86 [m2]) : 216.9 [kg]
weight fin (45.20 [m2]) : 1785.9 [kg]
weight rudder (13.55 [m2]) : 514.1 [kg]
Inner fuel tank 13950 litre, outer fuel tank 3700 litre > total wing : 35300 litre, central tank : 19640 litre > makes total 54940 litre, A310-300 has the tail trim tank > 6440 litre > total 61380 litre, additional two 7200 litre auxiliary center tanks can be installed as option at the cost of belly cargo volume, adding around 2000 km range (range with max fuel ca 5200 nm > 9630 km)
weight 6445 [litre] tail fuel trim tank empty : 322.3 [kg]
weight tailplane (stabilizer) (44.80 [m2]): 1947.1 [kg]
weight elevators (19.22 [m2]): 410.07 [kg]
weight flight control hydraulic servo actuators: 53.9 [kg]
Double slotted inboard, single slotted TE flaps, full span LE slats, Air Transat A310-304 C-GTSF c/n 472
weight trailing-edge double + single slotted flaps (36.67 [m2]) : 1234.2 [kg]
weight track-mounted light alloy construction leading edge slats (28.53 [m2]) : 603.5 [kg]
weight fly-by-wire operated spoilers of graphite composite construction (7.3 [m2]) : 130.2 [kg]
weight airbrakes (6.2 [m2]) : 123.8 [kg]
weight wingtip fences : 50 [kg]
total weight wing construction : 25731 [kg] (32.5 [%])
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tire pressure main wheels : 14.30 [Bar] (nitrogen), ply rating : 23 PR
tire speed limit : 364 [km/hr]
total tyre footprint : 0.50 [m2]
Runway LCN at MTOW (0.76m radius of rigidity) : 81 [ ]
Aircraft Classification Number (ACN), MTOW on rigid runway and medium
subgrade strength (B) : 46 [ ] Can only operate from unpaved runways with reduced
weight and reduced tyre pressure
wheel pressure : 16495.6 [kg]
wheel track : 9.60 [m] wheelbase : 15.21 [m]
weight 8 Dunlop 46 x 16 main wheels (1170 [mm] by 412 [mm]) : 1275.4 [kg]
weight 2 nose wheels : 159.4 [kg]
weight hydraulic disc wheel-brakes : 113.0 [kg]
weight Duplex anti-skid units : 9.0 [kg]
weight oleo-pneumatic shock absorbers : 150.7 [kg]
weight wheel hydraulic operated retraction system : 1512.4 [kg]
weight undertail bumper : 20 [kg]
weight undercarriage struts (four-wheel bogies) with axle 4246.3 [kg]
total weight landing gear : 7486.2 [kg] (5.0 [%]
*******************************************************************
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calculated empty weight : 76938 [kg](51.3 [%])
weight oil for 10.9 hours flying : 198.0 [kg]
unusable fuel in engine and tanks 310.0 litre fuel : 243.3 [kg]
weight lifejackets : 99.0 [kg]
weight 4 life rafts : 137.5 [kg]
S7 Airlines A310-304 VP-BTJ
weight catering : 390.5 [kg]
weight water : 312.4 [kg]
weight crew : 810 [kg]
weight crew luggage, nav. chards, flight doc., miscell. items : 78 [kg]
operational weight empty : 79207 [kg] (52.8 [%])
********************************************************************
weight 220 passengers : 16940 [kg]
weight luggage : 3520 [kg]
weight cargo : 13333 [kg] (cargo + luggage/m3 belly : 142 [kg/m3])
zero fuel weight (ZFW): 113000 [kg](75.4 [%])
weight fuel for landing (2.1 hours flying) : 9970 [kg]
max. landing weight (MLW): 122970 [kg](82.0 [%])
max. fuel weight : 127147 [kg] (84.8 [%])
payload with max fuel : 245 passengers + luggage 22813 [kg]
published maximum take-off weight : 149960 [kg] (100.0 [%])
calculation : * 4 * (engine power)
power loading (Take-off) : 315 [kg/KN]
power loading (Take-off) 1 PUF: 630 [kg/KN]
max. total take-off power : 476.0 [KN]
calculation : *5* (loads)
manoeuvre load : 0.9 [g] at 9000 [m]
limit load : 2.5 [g] ultimate load : 3.8 [g] load factor : 1.4 [g]
design flight time : 3.55 [hours]
design cycles : 16460 sorties, design hours : 58433 [hours]
max. wing loading (MTOW & flaps retracted) : 682 [kg/m2]
wing stress (2 g) during operation : 154 [N/kg] at 2g emergency manoeuvre
calculation : *6* (angles of attack)
angle of attack zero lift : -1.72 ["]
max. angle of attack (stalling angle, clean) : 12.61 ["]
max. angle of attack (full flaps) : 16.81 ["]
angle of attack at economic cruise speed : 4.07 ["]
calculation : *7* (lift & drag ratios
lift coefficient at angle of attack 0° : 0.15 [ ]
lift coefficient at max. speed : 0.41 [ ]
lift coefficient at max. angle of attack (clean): 1.25 [ ]
max. lift coefficient full flaps : 2.45 [ ]
drag coefficient at max. speed : 0.0455 [ ]
drag coefficient at econ. cruise speed : 0.0441 [ ]
induced drag coefficient at econ. cruise speed : 0.0133 [ ]
drag coefficient (zero lift) : 0.0307 [ ]
lift/drag ratio at econ. speed : 9.07 [ ]
calculation : *8* (speeds
take-off decision speed (V1) : 256 [km/u] (138 [kt])
take-off rotation speed (VR) : 269 [km/u] (145 [kt])
minimum unstick speed (Vmu) at TO angle 17.6 ° : 269 [km/u] (145 [kt])
East-German Interflug bought 3 A310-304 > probably this is the first one : DDR-ABA c/n 498, here still with France registration F-WWCT. It has GE CF6-80C2A2 engines.
lift-off speed (VLOF) : 296 [km/u] (160 [kt]) at pitch angle : 14.8 [°]
take-off safety speed (V2) : 299 [km/u] (161 [kt])
flap retraction speed (V3) at 500m (OW loaded : 145120 [kg]): 354 [km/u] (191 [kt])
steady initial climb speed (V4) : 325 [km/u] (175 [kt])
climb speed (to FL150 with 56 [%] power) : 554 [km/hr] (299 [kt])
max. endurance speed (Vbe): 405 [km/u] min. fuel/hr : 4447 [kg/hr] at height : 610 [m]
max. range speed (Vbr): 847 [km/u] (0.80 [mach]) min. fuel consumption : 5.53 [kg/km] at
cruise height : 10973 [m]
max. cruising speed : 869 [km/hr] (469 [kt]) at 10000 [m] (power:24 [%])
max. operational speed (Mmo) : 930 [km/hr] (Mach 0.86 ) at 9450 [m] (power:30 [%])
Royal Jordanian Airbus A310-304 F-ODVE “Princess Iman” c/n 422 at Maastricht airport (MST)
airflow at cruise speed per engine : 435.8 [kg/s]
speed of thrust jet : 1338 [km/hr]
initial descent speed 10000 - 7315 [m]: Mach 0.75
descent speed 7315 - 3048 [m]: 537 [km/u] (290 [kt])
approach speed 3048 - 500 [m] (clean): 426 [km/u] (230 [kt])
minimum control speed (MCS) Vmca (clean): 374 [km/u] (202 [kt])
stalling speed clean at 500 [m] height at Max.Landing Weight : 122970 [kg]): 312 [km/u]
(168 [kt])
Final approach speed at MLW 122970 kg (271100 lbs) : 137 kts
final approach speed (landing speed) at sea-level with full flaps VREF (max. landing weight):
251 [km/u] (136 [kt])
ICAO Aircraft Approach Category (APC) : C
stalling speed at sea-level with full flaps VSO (max. landing weight): 193 [km/u] (104 [kt]
rate of climb at sea-level ROC (loaded, 56 % power) : 948 [m/min]
rate of climb at sea-level ROC (loaded, 75 % power) : 1629 [m/min]
rate of climb at 1000 [m] with 1 engine out (PUF/MTOW, 100 % power on remaining engines) : 612 [m/min]
rate of descent from FL240 to FL100 (7315m > 3048m): 914 [m/min] (2999 [ft/min])
rate of descent during approach with landing gear extended, with use of spoilers: 457
[m/min] (8 [m/s])
calculation : *9* (regarding various performances)
high wheel pressure, can only take off from paved runways
ICAO Aerodrome Reference Code : 4D
Brake kinetic energy capacity : 2255 [KW]
Runway length at MTOW 149960 kg (330600 lbs) : 7500 ft > 2285m
FAR TO runway length (TOFL) requirement at TOW 149960 [kg] standard day at SL (PUF
after V1): 2285 [m]
+++ FAA certification landing distance : +++
landing weight : 122970 [kg], TE flap setting : 40 [°]
runway condition : dry , landing over 50ft (15m) at threshold at sea-level
with use of thrust reversers
Landing distance at MLW 122970 kg (271100 lbs), sea-level, standard day, dry runway : 5050 ft > 1539m
FAA approved landing field length : 1566 [m] (5136 [ft])
landing distance (C.A.R.) from 15 [m] at SL, wet runway: 1799 [m] (5903 [ft])
max. lift/drag ratio : 12.50 [ ]
climb to 5000 [m] with max payload : 4.88 [min]
climb to 10000 [m] with max payload : 15.02 [min]
descent time from 10000 [m] to 250 [m] : 24.33 [min]
ceiling limited by max. pressure differential 13875 [m]
theoretical ceiling fully loaded (mtow- 60 min.fuel: 145120 [kg] ) : 14800 [m]
calculation *10* (action radius & endurance)
range with max. payload: 6209 [km] with 33793.0 [kg] max. useful load (77.1 [%] fuel)*
range with high density pax: 7933 [km] with 264 passengers (96.3 [%] fuel)*
range with typical two-class pax: 8364 [km] with 220 passengers (100.0 [%] fuel)*
Range with max payload 35000 kg : 3000 nm > 5556 km, range with max fuel : 7900 km (4265 nm). OEW 77160 kg + 47964 kg fuel (61000 litre) + payload 24836 kg > MTOW 149960 kg
range with max.fuel : 8270 [km] with 10 crew and 245 passengers and 100.0 [%] fuel*
ferry range (calculated): 9239 [km] with 2 crew and zero payload (100.0 [%] fuel)*
max range theoretically with additional fuel tanks total 91852 [litre] fuel : 13166 [km]*
* calculated ranges without fuel reserves
Available Seat Kilometres (ASK) : 2070316 [paskm]
useful load with range 1000km : 33793 [kg]
useful load with range 1000km : 264 passengers
production (theor.max load): 29366 [tonkm/hour]
production (useful load): 29366 [tonkm/hour]
production (passengers): 216935 [paskm/hour]
oil and fuel consumption per tonkm : 0.165 [kg]
calculation *11* (operating cost)
fuel cost per hour (6166 [litre]):3699 [eur] (35 [pax-km/litre fuel])
fuel cost per seat 1000km flight (250 [pax] 2-class seating): 17.05 [eur/1000PK]
oil cost per hour: 69 [eur]
Cabin crew of May 17, 2013, PIA flight PK-206 from Kuwait to Lahore operated with Airbus A310-324ET (AP-BGN)
crew cost per hour : 1350 [eur]
list price 2024 : 204 [mln USD]
average flying hours in 1 year : 3150 [hours] technical life : 19 [year]
real average service life : 19 [years]
depreciation - 19 [years] to 10% residual value
economic hours (expected total flying hours): 59850 [hours]
financing interest per flying hour : 1456 [EUR]
write off per flying hour : 2830 [EUR]
time between engine failure : 14744 [hr]
can continue fly on 1 engine, low risk for emergency landing for PUF
workhours per day : 10.45 [hr]
average flight hours till crash : 1.71 [mln hr] (543 service years)
safe flight hours till fatality : 16533 [hr] (5.2 service years)
reservation pax liability/flying hour : 7.79 [SDR*] (9.74 [eur])
insurance cost per hour : 549 [eur] insurance rate : 2.3 [%]
engine maintenance cost per hour : 2830.0 [eur]
wing maintenance cost per hour : 136.3 [eur]
Royal Jordanian Airbus A310-304 F-ODVE “Princess Iman” c/n 422 at Beek; Maastricht airport (MST), at the end of 1990.
fuselage maintenance cost per hour : 100.09 [eur]
tire life (time till worn out) : 91 [cycles]
maintenance cost per hour (excluding engines): 1051 [eur]
direct operating cost per hour: 13845 [eur], DOC per km : 16.58 [eur]
DOC per seat 1000km flight (250 [pax] 2-class seating): 63.82 [eur/1000PK]
DOC per seat 1000km flight (high density seating): 60.30 [eur/1000PK]
DOC per kg cargo for a 1000km flight : 0.47 [eur/kg] (= DOC/tonkm)
passenger service charge (depart at Schiphol): 11.34 [eur]
security service charge (depart at Schiphol): 10.08 [eur]
airport take-off fee / passenger : 3.41 [eur/pax]
airport landing fee / passenger : 3.41 [eur/pax]
retour ticket price 1000km trip : 202.54 [eur/pax]
price retour ticket Schiphol-Barcelona : 237.64 [eur/pax]
Unclear which Balair 88 Airbus was involved in this incident. Looking into the
Balair fleet history
, the aircraft involved should be a A310-300 HB-IPL or HB-IPM
accidents with fatalities > see the accident file
Literature :
Air international apr’94 page 200
Air International dec’97 page 382
luchtvaart sep’90 page 256/257
https://contentzone.eurocontrol.int/aircraftperformance/default.aspx?
https://www.airbus.com/en/airport-operations-and-technical-data/aircraft-characteristics
rescue :
confidence rating regarding source data : medium - all information is only available from news, social media or unofficial sources
DISCLAIMER Above calculations are based on published data, they must be
regarded as indication not as facts.
Calculated performance and weight may not correspond with actual weights
and performances and are assumptions for which no responsibility can be taken.
Calculations are as accurate as possible, they can be fine-tuned when more data
is available, you are welcome to give suggestions and additional information
so we can improve our program. For copyright on drawings/photographs/
content please mail to below mail address
Air India A310-324 VT-EVE c/n 501 at Hong Kong, June 2006.
(c) B van der Zalm 03 June 2024 contact : info.aircraftinvestigation@gmail.com ac jetpax 2020.py python 3.7.4
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