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weight and performance calculations for the Airbus A300B4-600 CF6

LaTur (Lineas Aereas La Tur) F-ODTK A300B4-622 c/n 252, it was built in 1983 as A300-600 prototype, sold to LaTur in 1989, who operated the aircraft only till January 1990.

Airbus A300B4-600 CF6

role : wide-body airliner

importance : **

first flight : 20 maart 1985 operational : September 1985 (Thai Airways)

country : EU-consortium

ICAO aircraft type designator : A306

production : 40 aircraft

general information :

On March 20, 1985, an improved version made its maiden flight, equipped with CF6-80C2

turbofans of 262 KN, carbon brakes, wingtip fences and a "New World" cockpit. This version

can also be equipped with PW4156 turbofans of 249 KN. The first was delivered to Thai

Airways on September 26, 1985

primary users : Thai Airways, LaTur, Iran Airtours, Afriqiyah

Accommodation:

flight crew : 2 cabin crew : 9

passengers : seating for 247 in two class : 46 business class and 201 coach class seats

( 34 -in pitch) high density seating for 345 passengers, exit limit : 375

engine : 2 General Electric CF6-80C2A1 turbofan engines of 262.4 [KN] (58989 [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 : 86727 [kg] max. structural payload : 43273 [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] (895 [km/hr]) at 9150 [m]

critical Mach speed : 0.81 [Mach]

max. cruising speed : 863 [km/hr] (Mach 0.81 ) 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 : 6482 [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)

and with wingtip fences 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): 0.691 []

seize (span*length*height) : 40303 [m^3]

calculation : *2* (fuel consumption)

oil consumption : 18.4 [kg/hr]

fuel consumption (econ. cruise speed) : 5916.8 [kg/hr] (7537.4 [litre/hr]) at 25 [%] power

distance flown for 1 kg fuel : 0.14 [km/kg] at 11000 [m] height, sfc : 45.0 [kg/KN/h]

total fuel capacity : 62000 [litre] (48670 [kg])

calculation : *3* (weight)

weight engine(s) dry : 8800.0 [kg] = 16.77 [kg/KN]

weight 213.0 litre oil tank : 18.10 [kg]

oil tank filled with 3.3 litre oil : 3.0 [kg]

oil in engine 6.4 litre oil : 5.8 [kg]

weight all fuel lines and pumps containing 94 litres fuel : 143.5 [kg]

weight engine cowling : 1364.5 [kg]

weight thrust reversers : 787.2 [kg]

total weight propulsion system : 11122 [kg](6.7 [%])

***************************************************************

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 : 45.0 [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 7 lavatories : 198.2 [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 : 357.9 [kg]

weight 3 (main door size : 1.71 x 2.69 [m]) freight doors (belly) : 525.8 [kg]*

total usable belly baggage/cargo hold volume : 158.5 [m3]

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 : 3369.9 [kg]

safety facilities:

weight 2 type I emergency exits (0.61 x 1.60 [m]): 56.4 [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 : 704 [kg]

fuselage construction:

fuselage aluminium frame : 18481 [kg]

floor loading (payload/m2): 207 [kg/m2]

weight rear pressure bulkhead : 366.1 [kg]

fuselage covering ( 735.7 [m2] duraluminium 2.81 [mm]) : 5527.6 [kg]

weight floor beams : 3198.2 [kg]

weight cabin furbishing : 3042.5 [kg]

weight cabin floor : 2925.3 [kg]

weight (sound proof) isolation : 588.1 [kg] TO-noise level : 97.7 [EPNdB]

weight 17600 [litre] main central fuel tanks empty : 352.0 [kg]

weight empty 460 [litre] potable water tanks : 40.7 [kg]

weight empty waste tank : 20.8 [kg]

weight fuselage structure : 34542.2 [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 Thai Airways A300B4-601 HS-TAA

weight VOR/ILS,RMI,DME,radio altimeter, ASI, time clock : 20.0 [kg]

weight Avionic Flight Control System : 33.0 [kg]

weight CAT IIIB 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 : 131.2 [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 : 856.5 [kg]

total weight fuselage : 39627 [kg](24.0 [%])

***************************************************************

total weight aluminium ribs (1387 ribs) : 5613 [kg]

weight engine mounts : 262 [kg]

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 4.17 [mm]) : 5857 [kg]

total weight aluminium spars (multi-cellular wing structure) : 6328 [kg]

weight wings : 17798 [kg]

weight wing/square meter : 68.46 [kg]

weight thermal leading-edge anti-icing : 49.3 [kg]

weight all-speed ailerons (7.06 [m2]) : 193.7 [kg]

weight fin (45.20 [m2]) : 1550.6 [kg]

weight rudder (13.57 [m2]) : 446.9 [kg]

weight tailplane (stabilizer) (44.77 [m2]): 1689.4 [kg]

weight elevators (19.21 [m2]): 355.78 [kg]

weight flight control hydraulic servo actuators: 67.2 [kg]

weight trailing-edge single slotted Fowler flaps (47.32 [m2]) : 1056.7 [kg]

weight leading edge kruger flaps and slats (31.42 [m2]) : 638.0 [kg]

weight spoilers made of CFRP (5.4 [m2]) : 85.2 [kg]

weight airbrakes (12.6 [m2]) : 213.9 [kg]

weight wingtip fences : 50 [kg]

total weight wing construction : 25303 [kg] (29.2 [%])

*******************************************************************

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 carbon 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 : 1690.7 [kg]

weight undertail bumper : 20 [kg]

weight undercarriage struts (four-wheel bogies) with axle 5010.1 [kg]

total weight landing gear : 8369.1 [kg] (5.1 [%]

*******************************************************************

********************************************************************

calculated empty weight : 84421 [kg](51.2 [%])

weight oil for 9.0 hours flying : 181.3 [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]

Catering aboard Mahan Air A300-600

weight catering : 294.8 [kg]

weight water : 406.8 [kg]

weight crew : 891 [kg]

weight crew luggage, nav. chards, flight doc., miscell. items : 72 [kg]

operational weight empty : 86727 [kg] (52.6 [%])

********************************************************************

weight 247 passengers : 19019 [kg]

weight luggage : 3952 [kg]

weight cargo : 20302 [kg] (cargo + luggage/m3 belly : 147 [kg/m3])

zero fuel weight (ZFW): 130000 [kg](78.8 [%])

weight fuel for landing (1.4 hours flying) : 8000 [kg]

max. landing weight (MLW): 138000 [kg](83.6 [%])

max. fuel weight : 135397 [kg] (82.1 [%])

payload with max fuel : 318 passengers + luggage 29603 [kg]

published maximum take-off weight : 165000 [kg] (100.0 [%])

calculation : * 4 * (engine power)

power loading (Take-off) : 314 [kg/KN]

power loading (Take-off) 1 PUF: 629 [kg/KN]

max. total take-off power : 524.8 [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 : 16765 sorties, design hours : 39398 [hours]

max. wing loading (MTOW & flaps retracted) : 635 [kg/m2]

wing stress (2 g) during operation : 167 [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 ["]

Iran Airtours A300B4-603 EP-MNI c/n 408 at Theran (THR), Iran March 2021

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 (clean): 1.26 [ ]

max. lift coefficient full flaps : 2.37 [ ]

drag coefficient at max. speed : 0.0463 [ ]

drag coefficient at econ. cruise speed : 0.0519 [ ]

induced drag coefficient at econ. cruise speed : 0.0177 [ ]

drag coefficient (zero lift) : 0.0342 [ ]

lift/drag ratio at econ. speed : 8.72 [ ]

calculation : *8* (speeds

take-off decision speed (V1) : 265 [km/u] (143 [kt])

take-off rotation speed (VR) : 278 [km/u] (150 [kt])

minimum unstick speed (Vmu) at TO angle 16.1 ° : 271 [km/u] (146 [kt])

lift-off speed (VLOF) : 298 [km/u] (161 [kt]) at pitch angle : 13.6 [°]

take-off safety speed (V2) : 304 [km/u] (164 [kt])

flap retraction speed (V3) at 500m (OW loaded : 159083 [kg]): 341 [km/u] (184 [kt])

steady initial climb speed (V4) : 330 [km/u] (178 [kt])

climb speed (to FL150 with 63 [%] power) : 540 [km/hr] (291 [kt])

max. endurance speed (Vbe): 565 [km/u] min. fuel/hr : 5608 [kg/hr] at height : 7315 [m]

max. range speed (Vbr): 848 [km/u] (0.80 [mach]) min. fuel consumption : 7.07 [kg/km] at

cruise height : 10973 [m]

max. cruising speed : 863 [km/hr] (466 [kt]) at 11000 [m] (power:27 [%])

max. operational speed (Mmo) : 895 [km/hr] (Mach 0.82 ) at 9150 [m] (power:31 [%])

airflow at cruise speed per engine : 381.6 [kg/s]

speed of thrust jet : 1520 [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])

Afriqiyah A300B4-620 5A-IAY c/n 354 landing at Hamburg, Fuhlsbuettel (HAM), July 2007. The aircraft was destroyed 25 August 2011 at Tripoli airport (TIP) during a battle between Libyan rebels and Gaddafi loyalists.

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) : 1041 [m/min]

rate of climb at sea-level ROC (loaded, 75 % power) : 1433 [m/min]

rate of climb at 1000 [m] with 1 engine out (PUF/MTOW, 100 % power on remaining

engines) : 494 [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 : 2558 [KW]

FAR take-off runway length at MTOW 165000 kg (363756 lbs) : 7150 ft > 2180m

FAR TO runway length (TOFL) requirement at TOW 165000 [kg] standard day at SL

(PUF after V1): 2178 [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

FAA approved landing field length : 1549 [m] (5082 [ft])

landing distance (C.A.R.) from 15 [m] at SL, wet runway: 1773 [m] (5815 [ft])

max. lift/drag ratio : 11.07 [ ]

climb to 5000 [m] with max payload : 4.45 [min]

climb to 10000 [m] with max payload : 13.68 [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: 159083 [kg] ) : 14700 [m]

calculation *10* (action radius & endurance)

range with max. payload: 4766 [km] with 43273.0 [kg] max. useful load (71.9 [%] fuel)*

range with high density pax: 6464 [km] with 345 passengers (94.9 [%] fuel)*

range with typical two-class pax: 7074 [km] with 247 passengers (100.0 [%] fuel)*

Range with max payload (43273 kg) : 2175 nm > 4028 km, with max fuel : 3500 nm > 6482 km, ferry range 4500 nm > 8334 km

range with max.fuel : 6852 [km] with 11 crew and 318 passengers and 100.0 [%] fuel*

ferry range (calculated): 7909 [km] with 2 crew and zero payload (100.0 [%] fuel)*

max range theoretically with additional fuel tanks total 101533 [litre] fuel : 12078 [km]*

* calculated ranges without fuel reserves

Available Seat Kilometres (ASK) : 2254412 [paskm]

useful load with range 1000km : 43273 [kg]

useful load with range 1000km : 345 passengers

production (theor.max load): 37345 [tonkm/hour]

production (useful load): 37345 [tonkm/hour]

production (passengers): 275566 [paskm/hour]

oil and fuel consumption per tonkm : 0.159 [kg]

calculation *11* (operating cost)

fuel cost per hour (7537 [litre]):4522 [eur] (37 [pax-km/litre fuel])

fuel cost per seat 1000km flight (319 [pax] 2-class seating): 16.41 [eur/1000PK]

oil cost per hour: 76 [eur]

crew cost per hour : 1500 [eur]

list price 2024 : 224 [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 : 2038 [EUR]

write off per flying hour : 4702 [EUR]

time between engine failure : 14744 [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 : 1.58 [mln hr] (640 service years)

safe flight hours till fatality : 1580800 [hr] (640.0 service years)

reservation pax liability/flying hour : 0.08 [SDR*] (0.10 [eur])

insurance cost per hour : 652 [eur] insurance rate : 1.9 [%]

engine maintenance cost per hour : 3120.1 [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): 1883 [eur]

direct operating cost per hour: 18494 [eur], DOC per km : 22.20 [eur]

DOC per seat 1000km flight (319 [pax] 2-class seating): 67.11 [eur/1000PK]

DOC per seat 1000km flight (high density seating): 62.12 [eur/1000PK]

DOC per kg cargo for a 1000km flight : 0.50 [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 : 2.93 [eur/pax]

airport landing fee / passenger : 2.93 [eur/pax]

retour ticket price 1000km trip : 207.68 [eur/pax]

price retour ticket Schiphol-Barcelona : 244.59 [eur/pax]

Thai Airways A300B4-601 HS-TAE c/n 395 at Singapore (SIN), March 2006. On 26 October 1986 it was substantial damaged when an improvised bomb exploded in a rear toilet. A rapid decompression followed. The crew initiated a quick descent, exceeding the aircraft limits, at 13600 ft/min > 4145 m/min > 69 m/s. During recovery the aircraft was stressed with an acceleration of +2.6 g. The crew got the airplane under control and made a successful emergency landing at Osaka runway 32L. It was repaired and continued in service beyond March 2006 with Thai Airlines

accidents with fatalities > there have been no fatal accidents with an A300-600 CF6

Literature :

Airbus A300 - Wikipedia

https://contentzone.eurocontrol.int/aircraftperformance/default.aspx ?

Jane’s all the world aircraft

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

(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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