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weight and performance calculations for the Airbus A300B4-600 JT9D
Saudi Arabian Airlines A300-600 HZ-AJC c/n 301
Airbus A300B4-600 JT9D
role : wide-body airliner
importance : **
first flight : 8 July 1983 (F-WZLR) operational : March 1984 (Saudi Arabian Airlines)
country : EU-consortium
ICAO aircraft type designator : A306
production : 15 aircraft
general information :
This is an advanced version of the A300B4. This variant features many of the novelties that were developed for the A310. It has a new tail, inherited from the A310, which allows for an additional 2 rows of seats. The two-man cockpit has CRT screens and new digital avionics. The construction weight was reduced, partly due to the use of composites. It now has a better payload/range ratio and is more fuel efficient. The A300-600 has a risk figure of 1.58 accidents per million flights.
A300-600 prototype F-WZLR c/n 252
primary users : Saudi Arabian Airlines (11), Kuwait airlines (2)
Accommodation:
flight crew : 2 cabin crew : 8
passengers : seating for 247 in two class : 46 business class and 201 coach class seats
( 34 -in pitch)
high density seating for 345 passengers
engine : 2 Pratt & Whitney JT9D-7R4H1 turbofan engines of 249.0 [KN] (55976 [lbf])
dimensions :
wingspan : 44.84 [m], length overall: 54.08 [m], length of fuselage : 53.30 [m]
height : 16.62 [m] wing area gross : 260.0 [m^2] fuselage exterior width : 5.64 [m]
weights :
empty weight : 79210 [kg]
operating empty weight : 87100 [kg] max. structural payload : 42900 [kg]
Zero Fuel weight (ZFW) : 130000 [kg] max. landing weight (MLW) : 138000 [kg]
max. take-off weight : 165000 [kg] weight usable fuel : 48670 [kg] (62000 [litres])
performance :
Max. operating Mach number (Mmo) : 0.82 [Mach] (890 [km/hr]) at 9450 [m]
critical Mach speed : 0.81 [Mach]
max. cruising speed : 847 [km/hr] (Mach 0.80 ) at 11000 [m] (29 [%] power)
economic cruising speed : 833 [km/hr] (Mach 0.79 ) at 11000 [m]
service ceiling : 12200 [m]
range with max fuel and MTOW : 5741 [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 trailing edge single-slotted Fowler flaps with Kruger 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 [°]
incidence : 5.05 [°], dihedral : 7.5 [°]
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]
wing aspect ratio : 7.73 []
Oswald factor (e): 0.681 []
seize (span*length*height) : 40303 [m^3]
calculation : *2* (fuel consumption)
oil consumption : 17.4 [kg/hr]
fuel consumption (econ. cruise speed) : 6634.3 [kg/hr] (8451.3 [litre/hr]) at 28 [%] power
distance flown for 1 kg fuel : 0.13 [km/kg] at 11000 [m] height, sfc : 47.2 [kg/KN/h]
total fuel capacity : 62000 [litre] (48670 [kg])
calculation : *3* (weight)
weight engine(s) dry : 8088.0 [kg] = 16.24 [kg/KN]
weight 181.4 litre oil tank : 15.42 [kg]
oil tank filled with 3.1 litre oil : 2.8 [kg]
oil in engine 6.1 litre oil : 5.5 [kg]
weight all fuel lines and pumps containing 94 litres fuel : 160.9 [kg]
weight engine cowling : 1294.8 [kg]
weight thrust reversers : 747.0 [kg]
total weight propulsion system : 10314 [kg](6.3 [%])
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Accommodation cabin facilities:
typical 2-class cabin layout for 247 passengers : economy : pitch : 86.4 [cm] 34.0 [-in]
( 2+4+2 ) seating in 31.7 rows
weight passenger seats : 1515.0 [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 : 345 [pax] at mainly 9 -abreast seating in 39.7 rows,
pitch 78.6 [cm] 30.9 [-in]
pax density, normal seating : 0.85 [m2/pax], high density seating : 0.61 [m2/pax]
passenger cabin luxurious spaced for good service, enough space for galleys and toilets
even at HD seating
weight 6 lavatories : 192.4 [kg]
weight 4 galleys : 313.4 [kg]
weight overhead stowage for hand luggage (total : 27.3 [m3]) : 93.3 [kg]
weight 2 wardrobe closets : 24.7 [kg]
weight 3 movie screens : 61.9 [kg]
weight 65 windows (41 x 28 cm) made of acrylic glass : 178.7 [kg]
weight 6 (1.93 x 1.07 [m]) Type A main entry doors : 370.7 [kg]
weight 3 (main door size : 1.71 x 2.69 [m]) freight doors (belly) : 544.4 [kg]*
total usable belly baggage/cargo hold volume : 158.5 [m3]
Belly space for 22 LD3 containers
underfloor belly hold can accommodate : 22 LD3 containers, netto volume : 98.4 [m3]
and : 21.0 [m3] bulk cargo
cabin volume (usable), excluding flight deck : 575 [m3]
passenger compartment volume : 276 [m3]
passenger cabin max width : 5.28 [m] cabin length : 40.22 [m] max cabin height : 2.54 [m]
floor area : 209.1 [m2]
weight cabin facilities : 3390.5 [kg]
safety facilities:
weight 2 type I emergency exits (0.61 x 1.60 [m]): 58.4 [kg]
evacuation time with 345 passengers : 48 [sec]
weight 12 hand fire extinguisher : 35 [kg]
weight cockpit voice recorder (CVR) and flight data recorder (FDR): 20.0 [kg]
weight oxygen masks & oxygen generators (deploy cabin alt.>4267m): 160.6 [kg]
weight emergency flare installation : 10 [kg]
weight 8 emergency evacuation slides : 422.1 [kg]
weight safety equipment & facilities : 706 [kg]
fuselage construction:
fuselage aluminium frame : 19138 [kg]
floor loading (payload/m2): 205 [kg/m2]
weight rear pressure bulkhead : 378.8 [kg]
fuselage covering ( 735.7 [m2] duraluminium 2.91 [mm]) : 5719.1 [kg]
weight floor beams : 3198.2 [kg]
weight cabin furbishing : 3042.5 [kg]
weight cabin floor : 2925.3 [kg]
weight (sound proof) isolation : 600.8 [kg] TO-noise level : 98.4 [EPNdB]
weight 17600 [litre] main central fuel tanks empty : 352.0 [kg]
weight empty 407 [litre] potable water tanks : 36.0 [kg]
weight empty waste tank : 18.5 [kg]
weight fuselage structure : 35409.0 [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]
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 : 861 [m3] cabin air refreshment time : 3.7 [min]
weight air-conditioning and pressurization system : 394 [kg]
weight APU / engine starter : 124.5 [kg]
weight lighting : 81.5 [kg]
weight triple redundant 207 bar hydraulic system : 134.3 [kg]
weight two engine-driven 90kVA 400 Hz 3-phase AC electricity generators : 61.8 [kg]
weight ram air turbine for emergency electric power : 5.0 [kg]
weight three 24V 25Ah nickel-cadmium batteries : 31.8 [kg]
weight controls : 21.9 [kg]
weight systems : 849.8 [kg]
total weight fuselage : 40510 [kg](24.6 [%])
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total weight aluminium ribs (1397 ribs) : 5656 [kg]
weight engine mounts : 249 [kg]
Inner fuel tank 17570 litre, outer fuel tank 4630 litre > total fuel wings > 44400 litre, fuel center tank : 17600 litre, makes total 62000 litre for A300-600, the tail trim tank was only later installed in the A300-600R version
weight 4 wing fuel tanks empty for total 44400 [litre] fuel : 666 [kg]
weight 248 [litre] vent surge tanks : 30 [kg]
weight wing covering (painted aluminium 4.30 [mm]) : 6039 [kg]
total weight aluminium spars (multi-cellular wing structure) : 6543 [kg]
weight wings : 18239 [kg]
weight wing/square meter : 70.15 [kg]
weight thermal leading-edge anti-icing : 49.3 [kg]
weight all-speed ailerons (7.06 [m2]) : 198.5 [kg]
weight fin (45.20 [m2]) : 1588.9 [kg]
weight rudder (13.57 [m2]) : 458.0 [kg]
weight tailplane (stabilizer) (44.77 [m2]): 1731.1 [kg]
weight elevators (19.21 [m2]): 364.56 [kg]
weight flight control hydraulic servo actuators: 67.2 [kg]
Early A300-600 did not have wingtip fences, seen here Kuwait Airways A300C4-620 9K-AHG with JT9D-7R4H1 engines. In December 1984 the aircraft was hijacked to Tehran . When Iraq invaded Kuwait they seized 10 commercial airliners, among 9K-AHG. The aircraft was flown to Mosul, Iraq. It was destroyed by coalition bombing in operation “Desert storm” in February 1991.
weight trailing-edge single slotted Fowler flaps (47.32 [m2]) : 1082.7 [kg]
weight leading edge Kruger flaps and slats (31.42 [m2]) : 653.7 [kg]
weight spoilers made of CFRP (5.4 [m2]) : 87.2 [kg]
weight airbrakes (12.6 [m2]) : 219.1 [kg]
total weight wing construction : 25683 [kg] (29.5 [%])
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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 flexible runway and medium subgrade
strength (B) : 56 [ ]
Can only operate from unpaved runways with reduced weight and reduced tyre pressure
wheel pressure : 18150.0 [kg]
wheel track : 9.60 [m] wheelbase : 18.60 [m]
weight 8 Dunlop 49 x 17 main wheels (1240 [mm] by 431 [mm]) : 1187.4 [kg]
weight 2 nose wheels : 148.4 [kg]
weight hydraulic disc wheel-brakes : 130.0 [kg]
weight Duplex anti-skid units : 9.0 [kg]
weight oleo-pneumatic shock absorbers : 173.3 [kg]
weight wheel hydraulic operated retraction system : 1709.5 [kg]
weight undertail bumper : 20 [kg]
weight undercarriage struts (four-wheel bogies) with axle 5084.3 [kg]
total weight landing gear : 8462.0 [kg] (5.1 [%]
*******************************************************************
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calculated empty weight : 84970 [kg](51.5 [%])
weight oil for 8.1 hours flying : 153.4 [kg]
unusable fuel in engine and tanks 248.0 litre fuel : 194.7 [kg]
weight lifejackets : 111.2 [kg]
weight 4 life rafts : 154.4 [kg]
weight catering : 260.9 [kg]
weight water : 360.0 [kg]
weight crew : 810 [kg]
weight crew luggage, nav. chards, flight doc., miscell. items : 86 [kg]
operational weight empty : 87100 [kg] (52.8 [%])
********************************************************************
weight 247 passengers : 19019 [kg]
weight luggage : 3952 [kg]
weight cargo : 19929 [kg] (cargo + luggage/m3 belly : 144 [kg/m3])
zero fuel weight (ZFW): 130000 [kg](78.8 [%])
weight fuel for landing (1.2 hours flying) : 8000 [kg]
max. landing weight (MLW): 138000 [kg](83.6 [%])
max. fuel weight : 135770 [kg] (82.3 [%])
payload with max fuel : 314 passengers + luggage 29230 [kg]
published maximum take-off weight : 165000 [kg] (100.0 [%])
calculation : * 4 * (engine power)
power loading (Take-off) : 331 [kg/KN]
power loading (Take-off) 1 PUF: 663 [kg/KN]
max. total take-off power : 498.0 [KN]
calculation : *5* (loads)
manoeuvre load : 0.9 [g] at 9000 [m]
limit load : 2.5 [g] ultimate load : 3.8 [g] load factor : 1.3 [g]
design flight time : 2.35 [hours]
design cycles : 17240 sorties, design hours : 40514 [hours]
max. wing loading (MTOW & flaps retracted) : 635 [kg/m2]
wing stress (2 g) during operation : 163 [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 economic cruise speed : 4.65 ["]
calculation : *7* (lift & drag ratios
lift coefficient at angle of attack 0° : 0.15 [ ]
lift coefficient at max. speed : 0.42 [ ]
lift coefficient at max. angle of attack (clean): 1.26 [ ]
max. lift coefficient full flaps : 2.37 [ ]
drag coefficient at max. speed : 0.0509 [ ]
drag coefficient at econ. cruise speed : 0.0555 [ ]
induced drag coefficient at econ. cruise speed : 0.0179 [ ]
drag coefficient (zero lift) : 0.0376 [ ]
lift/drag ratio at econ. speed : 8.33 [ ]
calculation : *8* (speeds
take-off decision speed (V1) : 259 [km/u] (140 [kt])
take-off rotation speed (VR) : 272 [km/u] (147 [kt])
minimum unstick speed (Vmu) at TO angle 16.1 ° : 264 [km/u] (143 [kt])
lift-off speed (VLOF) : 291 [km/u] (157 [kt]) at pitch angle : 13.5 [°]
take-off safety speed (V2) : 295 [km/u] (160 [kt])
flap retraction speed (V3) at 500m (OW loaded : 158366 [kg]): 341 [km/u] (184 [kt])
steady initial climb speed (V4) : 321 [km/u] (174 [kt])
climb speed (to FL150 with 63 [%] power) : 507 [km/hr] (274 [kt])
max. endurance speed (Vbe): 653 [km/u] min. fuel/hr : 6206 [kg/hr] at height : 10058 [m]
max. range speed (Vbr) = economic cruise speed : 833 [km/u] min.fuel cons. : 7.964 [kg/km] at
cruise height : 11000 [m]
max. cruising speed : 847 [km/hr] (457 [kt]) at 11000 [m] (power:29 [%])
max. operational speed (Mmo) : 890 [km/hr] (Mach 0.82 ) at 9450 [m] (power:35 [%])
airflow at cruise speed per engine : 377.7 [kg/s]
speed of thrust jet : 1525 [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): 363 [km/u] (196 [kt])
stalling speed clean at 500 [m] height at Max.Landing Weight : 138000 [kg]): 303 [km/u]
(164 [kt])
Final approach speed at MLW 138000 kg (304233 lbs) : 134 kts
final approach speed (landing speed) at sea-level with full flaps VREF (max. landing weight):
249 [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] (103 [kt]
rate of climb at sea-level ROC (loaded, 63 % power) : 872 [m/min]
rate of climb at sea-level ROC (loaded, 75 % power) : 1222 [m/min]
rate of climb at 1000 [m] with 1 engine out (PUF/MTOW, 100 % power on remaining
engines) : 371 [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 : 2494 [KW]
FAR take-off runway length, standard day, sea level, at MTOW 165000 kg (363756 lbs) : 7200 ft (2195m)
FAR TO runway length (TOFL) requirement at TOW 165000 [kg] standard day at SL
(PUF after V1): 2194 [m]
+++ FAA certification landing distance : +++
landing weight : 138000 [kg], TE flap setting : 40 [°]
runway condition : dry , landing over 50ft (15m) at threshold at sea-level
with use of thrust reversers
Landing runway length at MLW 138000 kg (304233 lbs), sea level, 40° flaps : 5075 ft (1545 m)
FAA approved landing field length : 1544 [m] (5064 [ft])
landing distance (C.A.R.) from 15 [m] at SL, wet runway: 1766 [m] (5794 [ft])
max. lift/drag ratio : 10.49 [ ]
climb to 5000 [m] with max payload : 5.31 [min]
climb to 10000 [m] with max payload : 16.32 [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: 158366 [kg] ) : 14700 [m]
calculation *10* (action radius & endurance)
range with max. payload: 4258 [km] with 42900.0 [kg] max. useful load (71.9 [%] fuel)*
range with high density pax: 5715 [km] with 345 passengers (94.1 [%] fuel)*
range with typical two-class pax: 6288 [km] with 247 passengers (100.0 [%] fuel)*
m
Range with max payload : 1900 nm > 3519 km, with max fuel : 3100 nm > 5741 km, ferry range : 3830 nm > 7100 km
range with max.fuel : 6111 [km] with 10 crew and 314 passengers and 100.0 [%] fuel*
ferry range (calculated): 6984 [km] with 2 crew and zero payload (100.0 [%] fuel)*
max range theoretically with additional fuel tanks total 100852 [litre] fuel : 10646 [km]*
* calculated ranges without fuel reserves
Available Seat Kilometres (ASK) : 1978775 [paskm]
useful load with range 1000km : 42900 [kg]
useful load with range 1000km : 345 passengers
production (theor.max load): 36336 [tonkm/hour]
production (useful load): 36336 [tonkm/hour]
production (passengers): 267060 [paskm/hour]
oil and fuel consumption per tonkm : 0.183 [kg]
calculation *11* (operating cost)
fuel cost per hour (8451 [litre]):5070 [eur] (32 [pax-km/litre fuel])
fuel cost per seat 1000km flight (315 [pax] 2-class seating): 18.99 [eur/1000PK]
oil cost per hour: 72 [eur]
crew cost per hour : 1350 [eur]
list price 2024 : 225 [mln USD]
average flying hours in 1 year : 2470 [hours] technical life : 16 [year]
real average service life : 16 [years]
depreciation - 18 [years] to 10% residual value
economic hours (expected total flying hours) : 44460 [hours]
financing interest per flying hour : 2051 [EUR]
write off per flying hour : 4733 [EUR]
time between engine failure : 20203 [hr]
can continue fly on 1 engine, low risk for emergency landing for PUF
workhours per day : 8.93 [hr]
no fatalities during service life > 100%% safe
average flight hours till crash : 0.59 [mln hr] (240 service years)
safe flight hours till fatality : 592800 [hr] (240.0 service years)
reservation pax liability/flying hour : 0.22 [SDR*] (0.27 [eur])
insurance cost per hour : 1750 [eur] insurance rate : 5.2 [%]
engine maintenance cost per hour : 1752.6 [eur]
wing maintenance cost per hour : 243.4 [eur]
fuselage maintenance cost per hour : 266.44 [eur]
tire life (time till worn out) : 79 [cycles]
maintenance cost per hour (excluding engines): 1866 [eur]
direct operating cost per hour: 18646 [eur], DOC per km : 22.38 [eur]
DOC per seat 1000km flight (315 [pax] 2-class seating): 69.82 [eur/1000PK]
DOC per seat 1000km flight (high density seating): 63.81 [eur/1000PK]
DOC per kg cargo for a 1000km flight : 0.51 [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 : 2.99 [eur/pax]
airport landing fee / passenger : 2.99 [eur/pax]
retour ticket price 1000km trip : 213.89 [eur/pax]
price retour ticket Schiphol-Barcelona : 252.30 [eur/pax]
accidents with fatalities > there have been no fatal accidents with an A300-600
Literature :
Aviation Safety Network > > ASN Aviation Safety Database results (flightsafety.org)
https://contentzone.eurocontrol.int/aircraftperformance/default.aspx?
https://www.airbus.com/en/airport-operations-and-technical-data/aircraft-characteristics
Volkskrant 19july 1996
Luchtvaart sep’90 page 257
Air International apr’94 page 199
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 03 June 2024 contact : info.aircraftinvestigation@gmail.com ac jetpax 2020.py python 3.7.4
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