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weight and performance calculations for the Airbus A300B4-100 (WV003)
Eastern Airlines A300B4-103 N207EA c/n 067, delivered in December 1978
Airbus A300B4-100 (WV003)
role : wide-body airliner
importance : ****
first flight : 26 December 1974 (F-WLGA) operational : June 1975 (Germanair D-AMAX)
country : EU-consortium
design :
production : 47 aircraft
general information :
The A300B4 is the most commonly built A300 version. It was equipped with a centre section fuel tank, which increased the capacity and thus the range. It got Kruger flaps for better take-off performance. Some B2's were converted to this standard.
The A300C4 is a combined freight/passenger version (combi) with large cargo door and reinforced floor. It made its maiden flight in mid-1979 and was delivered to Hapag-Lloyd in January 1980. Empty weight : 79833 kg max. payload : 41000 kg
B4-101 : CF6-50C 227 KN engines, B4-102 : CF6-50C1 234 KN engines, B4-103 : CF6-50C2 234 KN engines, B4-120 : JT9D-59A 236 KN engines. Wing T/C Ratio : 10.5
In 1977, the A300B4 became the first ETOPS compliant aircraft, qualifying for Extended Twin Engine Operations over water, providing operators with more versatility in routing.
primary users : Eastern Airlines (34), Germanair (4), Iberia (4+4), Thai airways (10+4), Philippine (2+2), Olympic (5+5), KAL (8), SAS
Accommodation:
flight crew : 3 cabin crew : 7
flight crew consist of pilot, co-pilot and flight engineer
passengers : seating for 265 in two class : 25 business class and 240 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])
dimensions :
wingspan : 44.84 [m], length overall: 53.61 [m], length of fuselage : 52.02 [m] height : 16.53 [m]
wing area : 260.0 [m^2] fuselage exterior width : 5.64 [m]
weights :
empty weight : 79070 [kg]
operating empty weight : 88100 [kg] max. structural payload : 35900 [kg]
Zero Fuel weight (ZFW) : 124000 [kg] max. landing weight (MLW) : 134000 [kg]
max.take-off weight : 157500 [kg] weight fuel : 45608 [kg] (58100 [litres])
performance :
Max. operating Mach number (Mmo) : 0.84 [Mach] (917 [km/hr]) at 9145 [m]
critical Mach speed : 0.81 [Mach]
max. cruising speed : 889 [km/hr] (Mach 0.82 ) at 9450 [m] (31 [%] power)
economic cruising speed : 847 [km/hr] (Mach 0.78 ) at 9450 [m]
service ceiling : 10675 [m]
range with max fuel and Max.TOW : 5200 [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 alluminium 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
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) : 6935.4 [kg/hr] (8835.0 [litre/hr]) at 39 [%] power
distance flown for 1 kg fuel : 0.12 [km/kg] at 9450 [m] height, sfc : 38.5 [kg/KN/h]
total fuel capacity : 58100 [litre] (45608 [kg])
calculation : *3* (weight)
weight engine(s) dry : 8200.0 [kg] = 17.56 [kg/KN]
weight 153.5 litre oil tank : 13.05 [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 : 167.7 [kg]
weight engine cowling : 1214.2 [kg]
weight thrust reversers : 700.5 [kg]
total weight propulsion system : 10322 [kg](6.6 [%])
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Accommodation cabin facilities:
typical 2-class cabin layout for 265 passengers : economy : pitch : 86.4 [cm] 34.0 [-in]
( 2+4+2 ) seating in 33.6 rows
weight passenger seats : 1493.5 [kg]
weight cabin crew seats : 35.0 [kg]
weight flight crew seats : 63.0 [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 : 0.78 [m2/pax], high density seating : 0.61 [m2/pax]
weight 6 lavatories : 172.0 [kg]
weight 2 galleys : 214.7 [kg]
weight overhead stowage for hand luggage : 92.8 [kg]
weight 3 wardrobe closets : 26.5 [kg]
weight 7 movie screens : 130.5 [kg]
weight 69 windows (47x38cm) : 62.2 [kg]
c/n 067 on the production line at Toulouse – Blagnac,
a A300B4-103 later delivered to Eastern Airlines as N207EA
weight 4 (1.93 x 1.07 [m]) main entry doors : 253.3 [kg]
weight 2 (1.83 x 1.07 [m]) galley service doors : 120.1 [kg]
weight 3 (main door size : 1.71 x 2.44 [m]) freight doors (belly) : 506.2 [kg]*
total belly baggage/cargo hold volume : 140.25 [m3]
underfloor belly hold can accommodate : 20 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 : 3183.6 [kg]
safety facilities:
weight 2 type C emergency exits (0.61 x1.60 cm): 59.9 [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 : 172.2 [kg]
weight emergency flare installation : 10 [kg]
weight 6 emergency evacuation slides : 339.7 [kg]
weight safety equipment & facilities : 639 [kg]
fuselage construction:
fuselage aluminium frame : 19188 [kg]
floor loading (payload/m2): 174 [kg/m2]
weight rear pressure bulkhead : 398.9 [kg]
fuselage covering ( 719.7 [m2] duraluminium 2.98 [mm]) : 5697.8 [kg]
weight floor beams : 3199.9 [kg]
weight cabin furbishing : 3034.1 [kg]
weight cabin floor : 2957.6 [kg]
weight (sound proof) isolation : 525.2 [kg]
weight 14100 [litre] main central fuel tanks empty : 789.6 [kg]
weight empty 180 [litre] potable water tank : 15.9 [kg]
weight empty waste tank : 16.4 [kg]
weight fuselage structure : 35823.3 [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]
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 : 328 [kg]
weight APU / engine starter: 116.8 [kg]
weight lighting : 87.5 [kg]
weight triple redundant 207 bar hydraulic systems : 132.5 [kg]
weight engine-driven 40kVA electricity generators : 66.2 [kg]
weight three 24V 25Ah nickel-cadmium batteries : 31.8 [kg]
weight controls : 22.0 [kg]
weight systems : 784.5 [kg]
total weight fuselage : 40557 [kg](25.8 [%])
***************************************************************
average Take-off weight : 141339 [kg](89.7 [%])
total weight aluminium ribs (1316 ribs) : 5328 [kg]
weight engine mounts : 234 [kg]
weight 6 wing fuel tanks empty for total 44000 [litre] fuel : 2464 [kg]
weight wing covering (painted aluminium 4.35 [mm]) : 6109 [kg]
total weight aluminium spars (multi-cellular wing structure) : 6493 [kg]
weight wings : 17930 [kg]
weight wing/square meter : 68.96 [kg]
weight thermal leading-edge anti-icing : 49.3 [kg]
weight high& low speed ailerons (10.65 [m2]) : 367.9 [kg]
weight fin (31.95 [m2]) : 1104.2 [kg]
weight rudder (13.28 [m2]) : 440.7 [kg]
weight tailplane (stabilizer) (55.49 [m2]): 2109.1 [kg]
weight elevators (14.15 [m2]): 264.02 [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]) : 1491.0 [kg]
weight leading edge krueger flaps and slats (26.20 [m2]) : 536.6 [kg]
weight spoilers (6.5 [m2]) : 115.5 [kg]
weight airbrakes (3.3 [m2]) : 61.3 [kg]
total weight wing construction : 27233 [kg] (30.9 [%])
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According Jane’s atwa 79-80 main tire pressure : 13.3 bar, with higher loods it is 13.65 bar
tire pressure main wheels : 13.65 [Bar] (nitrogen), ply rating : 23 PR
tire speed limit : 364 [km/hr]
total tyre footprint : 0.55 [m2]
Runway LCN at MTOW (0.76m radius of rigidity) : 74 [ ]
Aircraft Classification Number (ACN), MTOW on rigid runway and medium subgrade strength (B) : 46 [ ]
Can also operate from unpaved runways subgrade B
wheel pressure : 17325.0 [kg]
weight 8 Dunlop main wheels (1170 [mm] by 412 [mm]) : 1266.5 [kg]
weight 2 nose wheels : 158.3 [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 : 1685.1 [kg]
weight undercarriage struts (four-wheel bogies) with axle 4933.0 [kg]
total weight landing gear : 8341.2 [kg] (5.3 [%]
*******************************************************************
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calculated empty weight : 86453 [kg](54.9 [%])
weight oil for 7.0 hours flying : 129.0 [kg]
weight lifejackets : 119.2 [kg]
weight 5 life rafts : 165.6 [kg]
weight catering : 198.8 [kg]
weight water : 159.0 [kg]
Bavaria Germanair A300B4-103 D-AMAX c/n 012 at Munich-Riem, March 1977. It was the first B4-100 that entered service, in June 1975.
weight crew : 810 [kg]
weight crew lugage,nav.chards,flight doc.,miscell.items : 65 [kg]
operational weight empty : 88100 [kg] (55.9 [%])
********************************************************************
weight 265 passengers : 20405 [kg]
weight luggage : 4240 [kg]
weight cargo : 11255 [kg] (cargo+luggage/m3 belly : 103 [kg/m3])
zero fuel weight (ZFW): 124000 [kg](78.7 [%])
weight fuel for landing (1.4 hours flying) : 10000 [kg]
max. landing weight (MLW): 134000 [kg](85.1 [%])
max. fuel weight : 133708 [kg] (84.9 [%])
payload with max fuel : 256 passengers+luggage 23792 [kg]
published maximum take-off weight : 157500 [kg] (100.0 [%])
calculation : * 4 * (engine power)
power loading (Take-off) : 337 [kg/KN]
power loading (Take-off) 1 PUF: 675 [kg/KN]
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 : 1.4 [g]
design flight time : 1.50 [hours]
design cycles : 19525 sorties, design hours : 29288 [hours]
max. wing loading (MTOW & flaps retracted) : 606 [kg/m2]
wing stress (2 g) during operation : 159 [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 : 2.59 ["]
calculation : *7* (lift & drag ratios
lift coefficient at angle of attack 0° : 0.15 [ ]
lift coefficient at max. speed : 0.37 [ ]
lift coefficient at max. angle of attack : 1.26 [ ]
Alitalia A300B4-103 I-BUSP c/n 067, Alitalia took it over from Eastern Airlines November 1988
max. lift coefficient full flaps : 2.13 [ ]
drag coefficient at max. speed : 0.0603 [ ]
drag coefficient at econ. cruise speed : 0.0567 [ ]
induced drag coefficient at econ. cruise speed : 0.0104 [ ]
drag coefficient (zero lift) : 0.0462 [ ]
lift/drag ratio at econ. speed : 6.14 [ ]
calculation : *8* (speeds
take-off decision speed (V1) : 245 [km/u] (132 [kt])
lift-off speed (VLOF) : 271 [km/u] (146 [kt])
take-off safety speed (V2) : 287 [km/u] (155 [kt])
steady initial climb speed (V4) : 313 [km/u] (169 [kt])
Continental airlines A300B4-103 N29981 c/n 087
flap retraction speed (V3) at 500m (OW loaded : 150565 [kg]): 334 [km/u] (180 [kt])
climb speed (to FL150 with 67 [%] power) : 459 [km/hr] (248 [kt])
max. endurance speed (Vbe): 584 [km/u] min. fuel/hr : 5380 [kg/hr] at height : 9449 [m]
max. range speed (Vbr): 769 [km/u] (0.71 [mach]) min. fuel consumption : 8.08 [kg/km] at cruise height : 9449 [m]
max. cruising speed : 889 [km/hr] (480 [kt]) at 9450 [m] (power:43 [%])
max. operational speed (Mmo) : 917 [km/hr] (Mach 0.84 ) at 9145 [m] (power:49 [%])
airflow at cruise speed per engine : 410.8 [kg/s]
speed of thrust jet : 1771 [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])
Approach speed B4-100 at MLW 134.000 kg : 138 kts > 256 km/h, volgens Jane’s atwa 79-80 is VREF 128 kts > 237 km/hr, this can only be possible with landing weight of around 120.000 kg…
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) : 769 [m/min]
rate of climb at sea-level ROC (loaded, 75% power) : 984 [m/min]
rate of climb at 1000 [m] with 1 engine out (PUF/MTOW, 100 % power on
remaining engines) : 885 [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)
high wheel pressure, can only take off from paved runways
take-off distance at sea-level concrete runway : 2239 [m]
ICAO Aerodrome Reference Code : 4D
take-off distance at sea-level over 15 [m] height : 2388 [m]
Takeoff runway length at MTOW 157500 kg, standard day, sea level, 227 KN CF6-50C engines : 2700 [m] Jane’s atwa 79-80 T-O filed length S/L ISA + 15°C : 2750 [m]. With 234 KN CF6-50C1 engines runway length ca. 2625 [m] SL/standard day
FAR TO runway length requirement at MTOW, standard day at SL (ASDA): 2623 [m]
landing run (MLW) : 1101 [m]
landing distance (C.A.R.) from 15 [m] at SL, dry runway : 2052 [m]
landing distance (C.A.R.) from 15 [m] at SL, wet runway : 2352 [m]
FAR landing field length at 134.000 kg MLW and 25° flaps : 1835 [m]
FAR landing runway length requirements at SL : 1836 [m]
max. lift/drag ratio : 9.46 [ ]
climb to 5000 [m] with max payload : 6.02 [min]
climb to 10000 [m] with max payload : 18.52 [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: 150565 [kg] ) : 15300 [m]
calculation *10* (action radius & endurance)
range with max. payload: 4023 [km] with 35900.0 [kg] max. useful load (73.5 [%] fuel)*
range with high density pax: 4612 [km] with 336 passengers (83.7 [%] fuel)*
range with typical two-class pax: 5459 [km] with 265 passengers (98.1 [%] fuel)*
Range with max fuel : 5200 [km] (with 370 km reserve) ,ferry range : 6100 [km]
range with max.fuel : 5570 [km] with 10 crew and 256 passengers and 100.0 [%] fuel*
ferry range : 5935 [km] with 3 crew and zero payload (100.0 [%] fuel)*
max range theoretically with additional fuel tanks total 89586 [litre] fuel : 8875 [km]*
* calculated ranges without fuel reserves
Available Seat Kilometres (ASK) : 1516535 [paskm]
useful load with range 1000km : 35900 [kg]
useful load with range 1000km : 336 passengers
production (theor.max load): 31915 [tonkm/hour]
production (useful load): 31915 [tonkm/hour]
production (passengers): 265552 [paskm/hour]
oil and fuel consumption per tonkm : 0.218 [kg]
calculation *11* (operating cost)
fuel cost per hour (8835 [litre]):5301 [eur] (30 [pax-km/litre fuel])
fuel cost per seat 1000km flight (299 [pax] 2-class seating): 19.96 [eur/1000PK]
oil cost per hour: 68 [eur]
crew cost per hour : 1350 [eur]
list price 2023 : 229 [mln USD]
average flying hours in 1 year : 1800 [hours] technical life : 16 [year]
real average service life : 17 [years]
economic hours (average real flown hours) : 30600 [hours]
financing interest per flying hour : 2970 [EUR]
write off per flying hour : 6450 [EUR]
time between engine failure : 25362 [hr]
can continue fly on 1 engine, low risk for emergency landing for PUF
workhours per day : 7.40 [hr]
no fatalities during service life > 100%% safe
average flight hours till crash : 1.44 [mln hr] (799 service years)
safe flight hours till fatality : 1438200 [hr] (799.0 service years)
reservation pax liability/flying hour : 0.09 [SDR*] (0.11 [eur])
Thai Airways A300B4-103 were used on the route Bangkok (BKK), Taiwan, Japan and Hong Kong (HKG)
insurance cost per hour : 177 [eur]
engine maintenance cost per hour : 1036.9 [eur]
wing maintenance cost per hour : 381.3 [eur]
fuselage maintenance cost per hour : 639.71 [eur]
tire life (time till worn out) : 97 [cycles]
maintenance cost per hour (excluding engines): 3134 [eur]
direct operating cost per hour: 20485 [eur]
DOC per seat 1000km flight (299 [pax] 2-class seating): 77.14 [eur/1000PK]
DOC per seat 1000km flight (high density seating): 68.58 [eur/1000PK]
DOC per kg cargo for a 1000km flight : 0.64 [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 : 3.15 [eur/pax]
airport landing fee / passenger : 3.15 [eur/pax]
retour ticket price 1000km trip : 230.69 [eur/pax]
price retour ticket Schiphol-Barcelona : 273.12 [eur/pax]
accidents with fatalities > see the accident file
Literature :
Aircraft Performance Database > A30B (eurocontrol.int)
Airbus-Commercial-Aircraft-AC-A300-Dec-2009.pdf
Air International apr’94 page 199
Flugzeuge der Welt page16,17
Verkeersvliegtuigen page 13,14
Jane’s commercial transport aircraft page 23
Luchtvaart sep’90 page 255
Luchtvaart nov’93 page 414
Jane’s all the world aircraft 1979-1980 page 87
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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