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weight and performance calculations for the Airbus A300B4-200 (WV006)
Air France A300B4-203 F-BVGN c/n 100
Airbus A300B4-200 (WV006)
role : wide-body airliner
importance : ****
first flight : operational : June 1979
country : EU-consortium
production : 136 aircraft
general information :
Stronger construction for increased MTOW of 165.000 kg. Additional fuel tank in its belly
for longer range. Strengthened landing gear with bigger main tyres (49 x 17 in.)
In 1982 Garuda Indonesia became the first airline to fly the A300B4-200FFCC with the newly Forward-Facing Crew Cockpit concept, the world's first wide-body aircraft that only operated by two-man cockpit crew. By 1981, Airbus was growing rapidly, with over 400 aircraft sold to over forty airlines.
primary users : Air France, Alitalia (8+3), Finnair, Quantas, Laker Airways (10), Pan Am, Singapore Airlines, China Airlines, American Airlines, Garuda Indonesia (6+6), Malaysia Airline System (MAS), Anatolia, Iran Air, Pakistan Int’l
Accommodation:
flight crew : 2 cabin crew : 7
passengers : seating for 267 in two class : 16 business class and 251 coach class seats ( 34 -in pitch)
high density seating for 336 passengers
engine : 2 General Electric CF6-50C1 turbofan engines of 233.5 [KN] (52492.0 [lbf])
engine options : B4-201 CF6-50C 227 KN, B4-202 CF6-50C1 234 KN, B4-203 CF6-50C2
234 KN, B4-200 JT9D-59A 236 KN, B4-221 JT9D-59B 236 KN turbofans
dimensions :
wingspan : 44.84 [m], length overall: 53.61 [m], length of fuselage : 52.02 [m] height : 16.53 [m]
Laker Airways A300B4-203 G-BIMB c/n 131, Manchester airport, March 1981
wing area : 260.0 [m^2] fuselage exterior width : 5.64 [m]
weights :
empty weight : 79833 [kg]
operating empty weight : 88505 [kg] max. structural payload : 35495 [kg]
Zero Fuel weight (ZFW) : 124000 [kg] max. landing weight (MLW) : 134000 [kg]
max.take-off weight : 165000 [kg] weight fuel : 48670 [kg] (62000 [litres])
performance :
Max. operating Mach number (Mmo) : 0.84 [Mach] (911 [km/hr]) at 9450 [m]
critical Mach speed : 0.81 [Mach]
max. cruising speed : 889 [km/hr] (Mach 0.82 ) at 9450 [m] (33 [%] power)
economic cruising speed : 847 [km/hr] (Mach 0.78 ) at 9450 [m]
service ceiling : 10675 [m]
range with max fuel and Max.TOW : 5375 [km] (ATA domestic fuel reserves - 370.0 [km] alternate)
description :
cantilever mid-wing monoplane with retractable landing gear with nose wheel
Wings : primary two-spar box-type fail-safe wing structure of high-strength aluminium
alloy with Fowler-type double slotted trailing edge flaps with Krueger flaps on the LE
wing root and slotted LE flaps (slats) on outer wing ,with spoilers (outboard) and airbrakes
(inboard) airfoil : Airbus average thickness/chord ratio : 10.5 [%], sweep angle 3/4
chord: 28.0 [°]
engines attached with pylons to the wing, main landing gear attached to the wings, fuel tanks
in the wings and fuselage
Fuselage : Pressurized conventional semi-monocoque fail safe structure of circular cross-
section built mainly of high-strength aluminium alloy
Garuda Indonesia A300B4-220FF PK-GAA c/n 159 with JT9D-59A turbofan engines
calculation : *1* (dimensions)
measured wing chord at root: 9.38 [m]
wing chord at tip : 3.13 [m]
taper ratio : 0.334 [ ]
mean wing chord : 5.80 [m]
calculated average wing chord tapered wing with rounded tips: 5.94 [m]
wing aspect ratio : 7.73 []
Oswald factor (e): 0.681 []
seize (span*length*height) : 39736 [m^3]
calculation : *2* (fuel consumption)
oil consumption : 16.3 [kg/hr]
fuel consumption (econ. cruise speed) : 7175.5 [kg/hr] (9140.8 [litre/hr]) at 40 [%] power
distance flown for 1 kg fuel : 0.12 [km/kg] at 9450 [m] height, sfc : 38.5 [kg/KN/h]
total fuel capacity : 62000 [litre] (48670 [kg])
calculation : *3* (weight)
weight engine(s) dry : 8200.0 [kg] = 17.56 [kg/KN]
weight 158.0 litre oil tank : 13.43 [kg]
oil tank filled with 2.9 litre oil : 2.6 [kg]
oil in engine 5.7 litre oil : 5.1 [kg]
fuel in engine 25.5 litre fuel : 18.68 [kg]
weight fuel lines : 173.5 [kg]
weight engine cowling : 1214.2 [kg]
weight thrust reversers : 700.5 [kg]
total weight propulsion system : 10328 [kg](6.3 [%])
***************************************************************
Accommodation cabin facilities:
Air France A300 cabin layout
typical 2-class cabin layout for 267 passengers : economy : pitch : 86.4 [cm] 34.0 [-in]
( 2+4+2 ) seating in 33.7 rows
weight passenger seats : 1493.5 [kg]
weight cabin crew seats : 35.0 [kg]
weight flight crew seats : 42.0 [kg]
weight 2 jumpseats in the cockpit :14.0 [kg]
high density seating passengers : 336 [pax] at mainly 9 -abreast seating in 42.6 rows,
pitch 77.0 [cm] 30.3 [-in]
pax density, normal seating : 0.77 [m2/pax], high density seating : 0.61 [m2/pax]
weight 6 lavatories : 174.2 [kg]
weight 3 galleys : 304.2 [kg]
weight overhead stowage for hand luggage : 93.4 [kg]
weight 3 wardrobe closets : 26.7 [kg]
weight 7 movie screens : 130.5 [kg]
weight 69 windows (47x38cm) : 62.4 [kg]
Malaysian Airline System A300B4-203 9M-MHC c/n 095
weight 4 (1.93 x 1.07 [m]) main entry doors : 251.1 [kg]
weight 2 (1.83 x 1.07 [m]) galley service doors : 119.0 [kg]
weight 3 (main door size : 1.71 x 2.44 [m]) freight doors (belly) : 501.8 [kg]*
total belly baggage/cargo hold volume : 126.0 [m3]
underfloor belly hold can accommodate : 18 LD3 containers
cabin volume (usable), excluding flight deck : 542 [m3]
passenger compartment volume : 272 [m3]
passenger cabin max width : 5.35 [m] cabin length : 39.15 [m] max cabin height : 2.54 [m]
floor area : 206.1 [m2]
weight cabin facilities : 3248.0 [kg]
safety facilities:
weight 2 type C emergency exits (0.61 x1.60 cm): 59.3 [kg]
evacuation time with 336 passengers : 48 [sec]
weight 13 hand fire extinguisher : 38 [kg]
weight cockpit voice recorder (CVR) and flight data recorder (FDR): 20.0 [kg]
weight oxygen masks & oxygen generators : 173.6 [kg]
weight emergency flare installation : 10 [kg]
weight 6 emergency evacuation slides : 342.2 [kg]
weight safety equipment & facilities : 643 [kg]
fuselage construction:
fuselage aluminium frame : 19023 [kg]
floor loading (payload/m2): 172 [kg/m2]
weight rear pressure bulkhead : 395.5 [kg]
fuselage covering ( 719.7 [m2] duraluminium 2.96 [mm]) : 5649.8 [kg]
weight floor beams : 3199.9 [kg]
Finnair A400B4-203FF OH-LAB c/n 302
weight cabin furbishing : 3034.1 [kg]
weight cabin floor : 2957.6 [kg]
weight (sound proof) isolation : 525.2 [kg]
weight 13507 [litre] main central fuel tanks empty : 756.4 [kg]
weight 4500 [litre] additional central fuel tank (ACT) empty : 252.0 [kg]
weight empty 255 [litre] potable water tank : 22.5 [kg]
weight empty waste tank : 16.9 [kg]
weight fuselage structure : 35833.3 [kg]
Avionics:
weight VHF radio and Selcal : 9.0 [kg]
weight flight and service attendants intercom : 5.0 [kg]
weight dual cloud-collision radar : 25.0 [kg]
Iran Air A300B4-203 cockpit EP-IBH
weight VOR/ILS,RMI,DME,radio altimeter, ASI, time clock : 20.0 [kg]
weight Integrated Flight System / auto-pilot : 23.0 [kg]
weight CAT IIIA auto-landing system : 10.0 [kg]
weight artificial horizons, compass, alti-meters : 7 [kg]
weight ground proximity warning system (GPWS) : 6 [kg]
weight engine monitoring gauges & control switches : 6 [kg]
weight reserve ADI, ASI, alti-meter, compass, engine temp.and rpm indicators : 15 [kg]
weight avionics : 126.0 [kg]
Systems:
Air-conditioning and pressurization system maintains sea level conditions up to 6525 [m]
and gives equivalent of 2250 [m] at 11885 [m]. pressure differential : 0.59 [bars] (kg/cm2)
pressurized fuselage volume : 540 [m3]
weight air-conditioning and pressurization system : 329 [kg]
weight APU / engine starter: 116.8 [kg]
weight lighting : 88.1 [kg]
weight triple redundant 207 bar hydraulic systems : 132.5 [kg]
weight engine-driven 40kVA electricity generators : 66.8 [kg]
weight three 24V 25Ah nickel-cadmium batteries : 31.8 [kg]
weight controls : 22.0 [kg]
weight systems : 787.1 [kg]
total weight fuselage : 40637 [kg](24.6 [%])
***************************************************************
average Take-off weight : 146316 [kg](88.7 [%])
total weight aluminium ribs (1371 ribs) : 5551 [kg]
weight engine mounts : 234 [kg]
weight 6 wing fuel tanks empty for total 43993 [litre] fuel : 2464 [kg]
weight wing covering (painted aluminium 4.32 [mm]) : 6061 [kg]
total weight aluminium spars (multi-cellular wing structure) : 6550 [kg]
weight wings : 18161 [kg]
weight wing/square meter : 69.85 [kg]
weight thermal leading-edge anti-icing : 49.3 [kg]
weight high& low speed ailerons (10.65 [m2]) : 372.7 [kg]
weight fin (31.95 [m2]) : 1118.4 [kg]
weight rudder (13.28 [m2]) : 446.4 [kg]
weight tailplane (stabilizer) (55.49 [m2]): 2136.3 [kg]
weight elevators (14.15 [m2]): 267.42 [kg]
weight flight control hydraulic servo actuators: 66.2 [kg]
mean chord :5.80 [m]) , span : 44.84 [m] wing area : 260.00 [m2]
weight trailing-edge double slotted flaps (50.70 [m2]) : 1510.2 [kg]
weight leading edge krueger flaps and slats (26.20 [m2]) : 543.4 [kg]
weight spoilers (6.5 [m2]) : 116.8 [kg]
weight airbrakes (3.3 [m2]) : 62.0 [kg]
total weight wing construction : 27548 [kg] (31.1 [%])
*******************************************************************
A300B4-200 MTOW 165000 [kg] tires : 49x17 in., pressure : 12.4 bar
tire pressure main wheels : 12.41 [Bar] (nitrogen), ply rating : 23 PR
tire speed limit : 364 [km/hr]
total tyre footprint : 0.70 [m2]
Runway LCN at MTOW (0.76m radius of rigidity) : 61 [ ]
Aircraft Classification Number (ACN), MTOW on rigid runway and medium subgrade strength (B) : 38 [ ]
Can also operate from unpaved runways subgrade B
wheel pressure : 18150.0 [kg]
weight 8 Dunlop main wheels (1240 [mm] by 431 [mm]) : 1173.5 [kg]
weight 2 nose wheels : 146.7 [kg]
weight hydraulic disc wheel-brakes : 124.0 [kg]
weight Duplex anti-skid units : 9.0 [kg]
weight oleo-pneumatic shock absorbers : 165.3 [kg]
weight wheel hydraulic operated retraction system : 1674.5 [kg]
weight undercarriage struts (four-wheel bogies) with axle 4995.7 [kg]
total weight landing gear : 8288.7 [kg] (5.0 [%]
*******************************************************************
Quantas A300B4-203 VH-TAC c/n 157 “John Forrest” at Brisbane airport, December 1993
********************************************************************
calculated empty weight : 86802 [kg](52.6 [%])
weight oil for 7.3 hours flying : 133.0 [kg]
weight lifejackets : 120.2 [kg]
weight 5 life rafts : 166.9 [kg]
weight catering : 281.7 [kg]
weight water : 225.3 [kg]
weight crew : 729 [kg]
weight crew lugage,nav.chards,flight doc.,miscell.items : 47 [kg]
operational weight empty : 88505 [kg] (53.6 [%])
********************************************************************
weight 267 passengers : 20559 [kg]
weight luggage : 4272 [kg]
weight cargo : 10664 [kg] (cargo+luggage/m3 belly : 99 [kg/m3])
zero fuel weight (ZFW): 124000 [kg](75.2 [%])
weight fuel for landing (1.4 hours flying) : 10000 [kg]
max. landing weight (MLW): 134000 [kg](81.2 [%])
max. fuel weight : 137175 [kg] (83.1 [%])
payload with max fuel : 299 passengers+luggage 27825 [kg]
published maximum take-off weight : 165000 [kg] (100.0 [%])
calculation : * 4 * (engine power)
power loading (Take-off) : 353 [kg/KN]
power loading (Take-off) 1 PUF: 707 [kg/KN]
Anatolia A300B4-203, probably TC-GTB at Schiphol airport, June 2001
max. total take-off power : 467.0 [KN]
calculation : *5* (loads)
manoeuvre load : 1.0 [g] at 9000 [m]
limit load : 2.5 [g] ultimate load : 3.8 [g] load factor : 1.3 [g]
design flight time : 2.11 [hours]
design cycles : 17450 sorties, design hours : 36820 [hours]
max. wing loading (MTOW & flaps retracted) : 635 [kg/m2]
wing stress (2 g) during operation : 161 [N/kg] at 2g emergency manoeuvre
calculation : *6* (angles of attack)
angle of attack zero lift : -1.77 ["]
max. angle of attack (stalling angle, clean) : 13.07 ["]
max. angle of attack (full flaps) : 16.57 ["]
angle of attack at max. speed : 2.93 ["]
calculation : *7* (lift & drag ratios
lift coefficient at angle of attack 0° : 0.15 [ ]
lift coefficient at max. speed : 0.40 [ ]
lift coefficient at max. angle of attack : 1.26 [ ]
max. lift coefficient full flaps : 2.13 [ ]
drag coefficient at max. speed : 0.0626 [ ]
drag coefficient at econ. cruise speed : 0.0586 [ ]
China Airlines A300B4-220 B-190, landing at Hong Kong, Kai Tak int’l apt (HKG) June 1998
induced drag coefficient at econ. cruise speed : 0.0114 [ ]
drag coefficient (zero lift) : 0.0472 [ ]
lift/drag ratio at econ. speed : 6.37 [ ]
calculation : *8* (speeds
take-off decision speed (V1) : 251 [km/u] (135 [kt])
lift-off speed (VLOF) : 277 [km/u] (150 [kt])
take-off safety speed (V2) : 293 [km/u] (158 [kt])
steady initial climb speed (V4) : 319 [km/u] (172 [kt])
flap retraction speed (V3) at 500m (OW loaded : 157824 [kg]): 341 [km/u] (184 [kt])
climb speed (to FL150 with 67 [%] power) : 456 [km/hr] (246 [kt])
max. endurance speed (Vbe): 514 [km/u] min. fuel/hr : 5679 [kg/hr] at height : 7010 [m]
max. range speed (Vbr): 782 [km/u] (0.72 [mach]) min. fuel consumption : 8.39 [kg/km] at cruise height : 9449 [m]
max. cruising speed : 889 [km/hr] (480 [kt]) at 9450 [m] (power:44 [%])
max. operational speed (Mmo) : 911 [km/hr] (Mach 0.84 ) at 9450 [m] (power:48 [%])
airflow at cruise speed per engine : 410.8 [kg/s]
speed of thrust jet : 1800 [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): 463 [km/u] (250 [kt])
minimum control speed (MCS) Vmca (clean): 358 [km/u] (193 [kt])
final approach speed (landing speed) at sea-level with full flaps VREF (max. landing weight): 256 [km/u] (138 [kt])
ICAO Aircraft Approach Category (APC) : C
stalling speed at sea-level with full flaps VSO (max. landing weight): 197 [km/u]
rate of climb at sea-level ROC (loaded, 67 % power) : 723 [m/min]
rate of climb at sea-level ROC (loaded, 75% power) : 931 [m/min]
rate of climb at 1000 [m] with 1 engine out (PUF/MTOW, 100 % power on remaining engines) : 825 [m/min]
rate of descent from FL240 to FL100 (7315m > 3048m): 1067 [m/min] (3501 [ft/min])
rate of descent during approach with landing gear extended, with use of spoilers: 457 [m/min] (1499 [ft/min])
calculation : *9* (regarding various performances)
low wheel pressure, can also take off from unpaved runways
take-off distance at sea-level concrete runway : 1848 [m]
ICAO Aerodrome Reference Code : 4D
take-off distance at sea-level over 15 [m] height : 2006 [m]
FAR takeoff runway length at MTOW 165.000 [kg], sea level, standard day : 2300 [m]
FAR TO runway length requirement at MTOW, standard day at SL (ASDA): 2312 [m]
landing run (MLW) : 1101 [m]
landing distance (C.A.R.) from 15 [m] at SL, dry runway : 2218 [m]
landing distance (C.A.R.) from 15 [m] at SL, wet runway : 2518 [m]
FAR landing runway length at MLW 134.000 [kg], sea level, dry runway : 1835 [m]
FAR landing runway length requirements at SL : 1836 [m]
max. lift/drag ratio : 9.36 [ ]
climb to 5000 [m] with max payload : 6.40 [min]
climb to 10000 [m] with max payload : 19.69 [min]
descent time from 10000 [m] to 250 [m] : 24.33 [min]
ceiling limited by max. pressure differential 14475 [m]
theoretical ceiling fully loaded (mtow- 60 min.fuel: 157824 [kg] ) : 15000 [m]
calculation *10* (action radius & endurance)
range with max. payload: 4788 [km] with 35495.0 [kg] max. useful load (84.2 [%] fuel)*
range with high density pax: 5316 [km] with 336 passengers (93.0 [%] fuel)*
range with typical two-class pax: 5792 [km] with 267 passengers (100.0 [%] fuel)*
Range with max fuel : 4825 [km] range with 269 pax + luggage : 5095 [km], ferry range : 5930 [km]. Looks like this is without the extra optional fuel tank as it has the same ferry range as the A300B4-100
range with max.fuel : 5745 [km] with 9 crew and 299 passengers and 100.0 [%] fuel*
ferry range : 6189 [km] with 2 crew and zero payload (100.0 [%] fuel)*
max range theoretically with additional fuel tanks total 98814 [litre] fuel : 9517 [km]*
* calculated ranges without fuel reserves
Available Seat Kilometres (ASK) : 1735526 [paskm]
useful load with range 1000km : 35495 [kg]
useful load with range 1000km : 336 passengers
production (theor.max load): 31555 [tonkm/hour]
production (useful load): 31555 [tonkm/hour]
production (passengers): 266872 [paskm/hour]
oil and fuel consumption per tonkm : 0.228 [kg]
calculation *11* (operating cost)
fuel cost per hour (9141 [litre]):5484 [eur] (29 [pax-km/litre fuel])
fuel cost per seat 1000km flight (300 [pax] 2-class seating): 20.55 [eur/1000PK]
oil cost per hour: 68 [eur]
crew cost per hour : 1200 [eur]
list price 2023 : 230 [mln USD]
average flying hours in 1 year : 2470 [hours] technical life : 15 [year]
real average service life : 16 [years]
economic hours (average real flown hours) : 39520 [hours]
financing interest per flying hour : 2173 [EUR]
PAN AM A300B4-203 c/n 195
write off per flying hour : 5014 [EUR]
time between engine failure : 25362 [hr]
can continue fly on 1 engine, low risk for emergency landing for PUF
workhours per day : 9.17 [hr]
average flight hours till crash : 1.79 [mln hr] (725 service years)
safe flight hours till fatality : 13238 [hr] (5.4 service years)
reservation pax liability/flying hour : 9.73 [SDR*] (12.16 [eur])
insurance cost per hour : 142 [eur]
engine maintenance cost per hour : 1036.9 [eur]
Iran Air A300B4-203 EP-IBH c/n 302 landing at Mumbai (BOM), India, March 2013
wing maintenance cost per hour : 271.1 [eur]
fuselage maintenance cost per hour : 323.30 [eur]
tire life (time till worn out) : 97 [cycles]
maintenance cost per hour (excluding engines): 2548 [eur]
direct operating cost per hour: 17678 [eur]
DOC per seat 1000km flight (300 [pax] 2-class seating): 66.24 [eur/1000PK]
DOC per seat 1000km flight (high density seating): 59.18 [eur/1000PK]
DOC per kg cargo for a 1000km flight : 0.56 [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 : 3.28 [eur/pax]
airport landing fee / passenger : 3.28 [eur/pax]
retour ticket price 1000km trip : 207.29 [eur/pax]
price retour ticket Schiphol-Barcelona : 243.73 [eur/pax]
accidents with fatalities > see the accident file
Literature :
Aircraft Performance Database > A30B (eurocontrol.int)
https://www.airbus.com/en/airport-operations-and-technical-data/aircraft-characteristics
Jane’s all the world aircraft 1979-80
China Airlines A300B4-220 B-192 c/n 197 landing at Hong Kong, December 1996
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
(c) B van der Zalm 18 November 2023 contact : info.aircraftinvestigation@gmail.com ac jetpax 2020.py python 3.7.4
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