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weight and performance calculations for the Airbus A300B2-100
Air France A300B2-1C F-BVGA c/n 005
Airbus A300B2-100
role : wide-body airliner
importance : ****
first flight : A300B1 : 28 October 1972 (F-WUAB) at Toulouse-Blagnac,
A300B2-100 : 28 June 1973
operational : May 1974 (Air France)
country : EU-consortium
design :
production : 32 aircraft
general information :
The A300 was developed from the HBN-100 design proposal from the 1960s. It was designed for short air lines with a large number of passengers. In May 1969, after many setbacks, the go-ahead was given, but without Great Britain, which had left the consortium. Hawker Siddeley remained in the program and was responsible for the design and production of the wing. On April 18, 1970, Airbus was founded, the participants were Deutsche Airbus (MBB and VFW-Fokker), Aerospatiale, CASA and Hawker Siddeley. The first version was the B1, with a length of 50.97m, of which 2 prototypes were built. It made its maiden flight on October 28, 1972. It had an MTOW of 132000 kg, the range was 2200km with 251 passengers. The length was 50.96m. They both go in service with the Belgian company Trans European Airlines. The third and fourth prototypes had a 2.61m longer fuselage, at the request of Air France. This was the B2-100 version, the first production version, which entered service with this company in May 1974. The A300 was the first 2-engine wide-body aircraft. Sales of the A300 were initially slow, but from 1975 sales picked up. This was partly due to the fact that it was 20% more economical than the DC-10 or Tristar.
The highly efficient wings have double slotted Fowler flaps and slats. T/C ratio 10.5%. Aspect ratio : 7.73 differential pressure at cruising altitude : 0.57 bar.
primary users : Air France, Air Inter (7), Indian Airlines (8), Lufthansa
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 CF6-50C turbofan engines of 226.83 [KN] (50992.6 [lbf])
Measured wing chord : 9.38 [m] at the root, 3.13 [m] at the tips
dimensions :
wingspan : 44.83 [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 : 77062 [kg]
operating empty weight : 85910 [kg] max. structural payload : 34590 [kg]
Zero Fuel weight (ZFW) : 120500 [kg] max. landing weight (MLW) : 130000 [kg]
max.take-off weight : 137000 [kg] weight fuel : 34400 [kg] (43000 [litres])
performance :
Max. operating Mach number (Mmo) : 0.86 [Mach] (937 [km/hr]) at 9000 [m]
critical Mach speed : 0.81 [Mach]
max. cruising speed : 917 [km/hr] (Mach 0.84 ) at 9145 [m] (29 [%] power)
economic cruising speed : 847 [km/hr] (Mach 0.78 ) at 9145 [m]
service ceiling : 10675 [m]
range with max fuel and Max.TOW : 3700 [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 full-span slotted LE flaps (slats),
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
Lufthansa A300B2-1C D-AIAD c/n 048 at London (LHR), August 1977
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) : 39727 [m^3]
calculation : *2* (fuel consumption)
oil consumption : 15.9 [kg/hr]
fuel consumption (econ. cruise speed) : 7158.9 [kg/hr] (8948.6 [litre/hr]) at 41 [%] power
distance flown for 1 kg fuel : 0.12 [km/kg] at 9145 [m] height, sfc : 38.5 [kg/KN/h]
total fuel capacity : 43000 [litre] (34400 [kg])
calculation : *3* (weight)
weight engine(s) dry : 8100.0 [kg] = 17.85 [kg/KN]
weight 111.5 litre oil tank : 9.48 [kg]
oil tank filled with 2.9 litre oil : 2.6 [kg]
oil in engine 5.6 litre oil : 5.0 [kg]
fuel in engine 24.8 litre fuel : 18.15 [kg]
weight fuel lines : 115.4 [kg]
weight engine cowling : 1179.5 [kg]
weight thrust reversers : 680.5 [kg]
total weight propulsion system : 10111 [kg](7.4 [%])
***************************************************************
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 5 lavatories : 161.3 [kg]
weight 2 galleys : 160.3 [kg]
Lufthansa A300B2-1C interior
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]
weight 4 (1.93 x 1.07 [m]) main entry doors : 245.3 [kg]
weight 2 (1.83 x 1.07 [m]) galley service doors : 116.3 [kg]
weight 3 (main door size : 1.71 x 2.44 [m]) freight doors (belly) : 490.2 [kg]*
Underfloor (belly) space for 20 LD3 containers
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 : 3090.9 [kg]
safety facilities:
weight 2 type C emergency exits (0.61 x1.60 cm): 58.0 [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 : 637 [kg]
fuselage construction:
fuselage aluminium frame : 18582 [kg]
floor loading (payload/m2): 168 [kg/m2]
weight rear pressure bulkhead : 414.3 [kg]
fuselage covering ( 719.7 [m2] duraluminium 3.10 [mm]) : 5917.7 [kg]
Airbus A300 fuselage cross-section , showing the passenger compartment above and LD3 cargo containers below. On display at the Deutsches Museum in Munich , Germany.
weight floor beams : 3199.9 [kg]
weight cabin furbishing : 3034.1 [kg]
weight cabin floor : 2875.5 [kg]
weight (sound proof) isolation : 525.2 [kg]
weight empty 134 [litre] potable water tank : 11.9 [kg]
weight empty waste tank : 12.0 [kg]
weight fuselage structure : 34573.0 [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]
Cockpit of Indian Airlines A300B2-100 VT-EDV
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 6275 [m]
and gives equivalent of 2250 [m] at 11400 [m]. pressure differential : 0.57 [bars] (kg/cm2)
pressurized fuselage volume : 540 [m3]
weight air-conditioning and pressurization system : 324 [kg]
weight APU / engine starter: 113.4 [kg]
weight lighting : 87.5 [kg]
weight triple redundant 207 bar hydraulic systems : 132.4 [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 : 777.2 [kg]
total weight fuselage : 39205 [kg](28.6 [%])
***************************************************************
average Take-off weight : 135677 [kg](99.0 [%])
total weight aluminium ribs (1201 ribs) : 4862 [kg]
weight engine mounts : 227 [kg]
weight 6 wing fuel tanks empty for total 43000 [litre] fuel : 2408 [kg]
weight wing covering (painted aluminium 4.54 [mm]) : 6369 [kg]
total weight aluminium spars (multi-cellular wing structure) : 6439 [kg]
weight wings : 17671 [kg]
weight wing/square meter : 67.96 [kg]
weight thermal leading-edge anti-icing : 49.3 [kg]
weight high& low speed ailerons (10.65 [m2]) : 362.6 [kg]
weight fin (31.94 [m2]) : 1087.8 [kg]
weight rudder (13.28 [m2]) : 434.1 [kg]
weight tailplane (stabilizer) (55.49 [m2]): 2078.7 [kg]
Lufthansa A300B2-1C D-AIAB c/n 022 “Rudesheim am Rhein” at Frankfurt-am-Main airport (FRA)
weight elevators (14.15 [m2]): 260.21 [kg]
weight flight control hydraulic servo actuators: 66.2 [kg]
mean chord :5.80 [m]) , span : 44.83 [m] wing area : 260.00 [m2]
weight trailing-edge double slotted flaps (50.70 [m2]) : 1469.6 [kg]
weight leading edge slats (26.59 [m2]) : 500.2 [kg]
weight spoilers (6.5 [m2]) : 113.9 [kg]
weight airbrakes (3.3 [m2]) : 60.5 [kg]
total weight wing construction : 26789 [kg] (31.2 [%])
*******************************************************************
tire pressure main wheels : 11.60 [Bar] (nitrogen), ply rating : 26 PR
tire speed limit : 364 [km/hr]
total tyre footprint : 0.56 [m2]
Runway LCN at MTOW (0.76m radius of rigidity) : 63 [ ]
Aircraft Classification Number (ACN), MTOW on rigid runway and medium
subgrade strength (B) : 34 [ ]
Can also operate from unpaved runways subgrade B
wheel pressure : 15070.0 [kg]
weight 8 Dunlop main wheels (1170 [mm] by 412 [mm]) : 1083.7 [kg]
weight 2 nose wheels : 135.5 [kg]
weight hydraulic disc wheel-brakes : 120.5 [kg]
weight Duplex anti-skid units : 9.0 [kg]
weight oleo-pneumatic shock absorbers : 160.7 [kg]
weight wheel hydraulic operated retraction system : 1665.6 [kg]
weight undercarriage struts (four-wheel bogies) with axle 5069.9 [kg]
total weight landing gear : 8244.9 [kg] (6.0 [%]
*******************************************************************
********************************************************************
calculated empty weight : 84349 [kg](61.6 [%])
weight oil for 4.8 hours flying : 91.6 [kg]
weight lifejackets : 119.2 [kg]
weight 5 life rafts : 165.6 [kg]
weight catering : 148.4 [kg]
weight water : 118.7 [kg]
weight crew : 810 [kg]
weight crew lugage,nav.chards,flight doc.,miscell.items : 108 [kg]
operational weight empty : 85910 [kg] (62.7 [%])
********************************************************************
weight 265 passengers : 20405 [kg]
weight luggage : 4240 [kg]
weight cargo : 9945 [kg] (cargo+luggage/m3 belly : 94 [kg/m3])
zero fuel weight (ZFW): 120500 [kg](88.0 [%])
weight fuel for landing (1.3 hours flying) : 9500 [kg]
max. landing weight (MLW): 130000 [kg](94.9 [%])
max. fuel weight : 120310 [kg] (87.8 [%])
payload with max fuel : 179 passengers+luggage 16690 [kg]
published maximum take-off weight : 137000 [kg] (100.0 [%])
calculation : * 4 * (engine power)
power loading (Take-off) : 302 [kg/KN]
power loading (Take-off) 1 PUF: 604 [kg/KN]
max. total take-off power : 453.7 [KN]
calculation : *5* (loads)
manoeuvre load : 1.2 [g] at 9000 [m]
limit load : 2.5 [g] ultimate load : 3.8 [g] load factor : 1.6 [g]
A300B1 OO-TEF c/n 002 in service with Belgian TEA (Trans European Airways) from April 1974, it made 14945 flights and 31028 flying hrs till its last flight on 25 November 1990.
Average 1870 hrs a year, average flight time 2.08 hrs
design flight time : 1.12 [hours]
design cycles : 23900 sorties, design hours : 26768 [hours]
max. wing loading (MTOW & flaps retracted) : 527 [kg/m2]
Lufthansa A300B2-1C D-AIAC c/n 026 “Luneburg” at London Heathrow (LHR), July 1976
wing stress (2 g) during operation : 148 [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) : 17.27 ["]
angle of attack at max. speed : 1.99 ["]
calculation : *7* (lift & drag ratios
lift coefficient at angle of attack 0° : 0.15 [ ]
lift coefficient at max. speed : 0.32 [ ]
lift coefficient at max. angle of attack : 1.26 [ ]
max. lift coefficient full flaps : 2.20 [ ]
drag coefficient at max. speed : 0.0630 [ ]
drag coefficient at econ. cruise speed : 0.0564 [ ]
induced drag coefficient at econ. cruise speed : 0.0077 [ ]
drag coefficient (zero lift) : 0.0487 [ ]
lift/drag ratio at econ. speed : 5.06 [ ]
calculation : *8* (speeds
take-off decision speed (V1) : 216 [km/u] (117 [kt])
lift-off speed (VLOF) : 242 [km/u] (131 [kt])
take-off safety speed (V2) : 259 [km/u] (140 [kt])
steady initial climb speed (V4) : 285 [km/u] (154 [kt])
flap retraction speed (V3) at 500m (OW loaded : 129841 [kg]): 313 [km/u] (169 [kt])
climb speed (to FL150 with 78 [%] power) : 467 [km/hr] (252 [kt])
max. endurance speed (Vbe): 479 [km/u] min. fuel/hr : 4912 [kg/hr] at height : 7315 [m]
max. range speed (Vbr): 715 [km/u] (0.66 [mach]) min. fuel consumption : 7.93 [kg/km] at cruise height : 9449 [m]
max. cruising speed : 917 [km/hr] (495 [kt]) at 9145 [m] (power:51 [%])
max. operational speed (Mmo) : 937 [km/hr] (Mach 0.86 ) at 9000 [m] (power:56 [%])
airflow at cruise speed per engine : 439.7 [kg/s]
speed of thrust jet : 1867 [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): 353 [km/u] (190 [kt])
A300B2 approach speed (VREF) at MLW 130000 [kg] : 134 kts = 248 km/h.
VREF = 1.3*Vs (stalling speed). VREF with MLW 127500 [kg] : 131 kts = 243 km/h
final approach speed (landing speed) at sea-level with full flaps VREF (max. landing
weight): 248 [km/u] (134 [kt])
ICAO Aircraft Approach Category (APC) : C
stalling speed at sea-level with full flaps VSO (max. landing weight): 191 [km/u]
rate of climb at sea-level ROC (loaded, 78 % power) : 1093 [m/min]
rate of climb at sea-level ROC (loaded, 75% power) : 1018 [m/min]
rate of climb at 1000 [m] with 1 engine out (PUF/MTOW, 100 % power on
remaining engines) : 966 [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 : 1402 [m]
take-off distance at sea-level over 15 [m] height : 1509 [m]
FAR TO runway length requirement at MTOW, standard day at SL (ASDA): 1727 [m]
landing run (MLW) : 986 [m]
landing distance (C.A.R.) from 15 [m] at SL, dry runway : 1938 [m]
landing distance (C.A.R.) from 15 [m] at SL, wet runway : 2238 [m]
Landing runway length at MLW 130.000 kg at sea level, VREF 134 kts (248 km/h), zero tail wind, gross : 1000 [m] / 0.6 = 1650 [m] reglementary length
FAR landing runway length requirements at SL : 1643 [m]
max. lift/drag ratio : 9.21 [ ]
climb to 5000 [m] with max payload : 4.23 [min]
climb to 10000 [m] with max payload : 13.03 [min]
descent time from 10000 [m] to 250 [m] : 24.33 [min]
ceiling limited by max. pressure differential 13800 [m]
theoretical ceiling fully loaded (mtow- 60 min.fuel: 129841 [kg] ) : 16300 [m]
calculation *10* (action radius & endurance)
range with max. payload: 1912 [km] with 34590.0 [kg] max. useful load (48.0 [%] fuel)*
range with high density pax: 2308 [km] with 336 passengers (57.7 [%] fuel)*
range with typical two-class pax: 3100 [km] with 265 passengers (76.9 [%] fuel)*
Range with max fuel : 3700 [km], ferry range 4225 [km]
range with max.fuel : 4070 [km] with 10 crew and 179 passengers and 100.0 [%] fuel*
ferry range : 4226 [km] with 3 crew and zero payload (100.0 [%] fuel)*
max range theoretically with additional fuel tanks total 64905 [litre] fuel : 6264 [km]*
* calculated ranges without fuel reserves
Available Seat Kilometres (ASK) : 816303 [paskm]
useful load with range 1000km : 34590 [kg]
useful load with range 1000km : 336 passengers
production (theor.max load): 31719 [tonkm/hour]
production (useful load): 31719 [tonkm/hour]
production (passengers): 273916 [paskm/hour]
oil and fuel consumption per tonkm : 0.226 [kg]
calculation *11* (operating cost)
fuel cost per hour (8949 [litre]):5369 [eur] (31 [pax-km/litre fuel])
fuel cost per seat 1000km flight (299 [pax] 2-class seating): 19.60 [eur/1000PK]
oil cost per hour: 66 [eur]
crew cost per hour : 1350 [eur]
list price 2023 : 224 [mln USD]
average flying hours in 1 year : 1520 [hours] technical life : 18 [year]
real average service life : 16 [years]
economic hours (average real flown hours): 24320 [hours] is 9 [%] less then design hours
financing interest per flying hour : 3431 [EUR]
write off per flying hour : 7918 [EUR]
time between engine failure : 25247 [hr]
can continue fly on 1 engine, low risk for emergency landing for PUF
workhours per day : 6.95 [hr]
Air Inter A300B2-1C F-BUAM c/n 021
average flight hours till crash : 0.78 [mln hr] (512 service years)
safe flight hours till fatality : 111177 [hr] (73.1 service years)
reservation pax liability/flying hour : 1.16 [SDR*] (1.45 [eur])
insurance cost per hour : 319 [eur]
engine maintenance cost per hour : 1011.9 [eur]
wing maintenance cost per hour : 510.7 [eur]
fuselage maintenance cost per hour : 1147.44 [eur]
tire life (time till worn out) : 107 [cycles]
maintenance cost per hour (excluding engines): 3778 [eur]
direct operating cost per hour: 23245 [eur]
DOC per seat 1000km flight (299 [pax] 2-class seating): 84.86 [eur/1000PK]
DOC per seat 1000km flight (high density seating): 75.44 [eur/1000PK]
DOC per kg cargo for a 1000km flight : 0.73 [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 : 2.74 [eur/pax]
airport landing fee / passenger : 2.74 [eur/pax]
retour ticket price 1000km trip : 245.87 [eur/pax]
price retour ticket Schiphol-Barcelona : 292.54 [eur/pax]
A300B2-100 F-GBEC c/n 104 at London (LHR), May 1980
accidents with fatalities > no fatal accidents with a A300B2-100, only a couple hijacking incidents.
Literature :
https://contentzone.eurocontrol.int/aircraftperformance/default.aspx ?
https://www.airbus.com/en/airport-operations-and-technical-data/aircraft-characteristics
Jane’s all the world aircraft 1979-80 page 87
Air International okt’97 page 253
Air international apr’94 page 199
Flugzeuge der Welt page 16,17
Verkeersvliegtuigen page 13,14
Jane’s commercial transport aircraft page 23
Luchtvaart sep´90 page 255
Luchtvaart nov’93 page 414
Indian Airlines A300B2-100 VT-EFW
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 29 October 2023 contact : info.aircraftinvestigation@gmail.com ac jetpax 2020.py python 3.7.4
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