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weight and performance calculations for the Airbus A340-200 WV001
Austrian A340-211 OE-LAH c/n 081 taking off from Vienna (VIE), October 2005
Airbus A340-200 WV001
role : wide-body long-range airliner
importance : **
first flight : 1 April 1992 operational : March 1993 (Lufthansa)
country : EU-consortium
ICAO aircraft type designator : A342
production : 28 aircraft
general information :
The unique feature of the A330 and A340 is that a medium-haul aircraft (A330) and an extremely long-haul aircraft (A340) were developed from the same basic design.
On 16 June 1993, A340-200 prototype F-WWBA c/n 004 dubbed the World Ranger flew from the Paris Air Show to Auckland , New Zealand in 21 hours 32 minutes and back in 21 hours 46 minutes after a five-hour stop; this was the first non-stop flight between Europe and New Zealand and the longest non-stop flight by an airliner at the time. The 19,277 km (10,409 nmi; 11,978 mi) flight from Paris to Auckland broke six world records with 22 persons and five center tanks. Taking off at 11:58 local time, it arrived back in Paris 48 hours and 22 minutes later, at 12:20. This record held until 1997 when a Boeing 777-200ER flew 20,044 km (10,823 nmi; 12,455 mi) from Seattle to Kuala Lumpur.
Nowadays, an aircraft manufacturer can only be successful if it can offer a whole family of aircraft, which have a large community, which facilitates maintenance, training and use for the customer. Airbus saw a gap in the market for long-haul routes with a relatively small number of passengers, for which the Boeing 747 is too large. The cost per seat could not be much higher than that of the 747. A smaller aircraft consumes more fuel per passenger, and the unladen weight-to-payload ratio is less favourable than a larger aircraft. Modern technologies had to keep operating costs low and by developing the A330 and A340 at the same time from the same basic design, the development costs and therefore the price per aircraft were kept low. It is estimated that Airbus saved about a billion guilders in this way. The total development costs for the two aircraft amounted to 7 billion guilders. The development of the wing by British Aerospace was a technical tour de force, it had to be suitable for two engines and for four. For short distances, a twin-engine aircraft is more efficient because the fuel consumption and maintenance costs are relatively low, for the long haul a four-engine aircraft is better, the weight of the engines is better distributed over the wing, so that the wing can be made lighter. In a four-engine aircraft, the engines don't need to be as powerful either. If one engine fails in a twin-engine aircraft, the other engine has to provide all the thrust on its own. The maximum power of the engine must therefore be relatively large, sufficient to be able to accelerate the aircraft sufficiently in the event of an engine failure during take-off.
A four-engine aircraft is also allowed to fly over oceans without restriction and is not affected by ETOPS restrictions that apply to two engine jetliners. The biggest problem was the placement of the engines, the power distribution of the twin-engine A330 had to be almost the same as the four-engine A340. The wing has been made as slim as possible, with a relatively high t/c ratio for sufficient strength and space for fuel. The CFM56 engines are very environmentally friendly. Efficient combustion has led to a significant reduction in emissions of nitrogen oxides in particular. The control is done by means of fly-by-wire (FBW), the pilot no longer has a steering column but a side-stick. The passenger cabin is luxuriously equipped, due to the long flights (+ 13 hours). There is an "on board business centre", with telephone, fax and computer. Each passenger has an "Inflight Entertainment System", a video screen in the backrest. A rest room can be provided for the pilots, the long flights make it increasingly necessary for an extra crew to accompany them. Two versions of the A340 were built, the A340-200 (262 passengers over 14000 km), the A340-300 (295 passengers over 12490 km). The A340-300X a higher MTOW version, later indicated as A340-300E, with 275t MTOW and a range of 13240 km was also offered. The A340-400X on the drawing board in 1991 was an extended version, 335 passengers over 10290 km, later became the A340-500 and A340-600. Airbus also offered the A340 to the French Air Force as a replacement for its DC-8 freighters. This was the A340M cargo version, with a large cargo door and a reinforced floor. It could carry 53t over 7000km, similar to the American C-17, which however requires a much shorter runway and is easier to load. The A340M could also be used as a tanker. But the A340M was never realized. The direct cost per seat for the A340 is 9% lower than for the MD-11 and only 1% higher than for the larger Boeing 747. The A340 is therefore very flexible (few passengers are needed to make a flight profitable. However, the Boeing 777 will be the biggest competitor and the future will tell which of the two is the best. Because the A340 is relatively small with a long flight range, intercontinental flights can now also be operated from smaller airports with a smaller number of passengers, making the large hubs less important. Until now, for example, a Boeing 747 flew from a large hub to another large hub, and then a smaller aircraft flew to the final destination, with the A340 it can be flown directly to the final destination.
primary users : Air France, Lufthansa, Sabena, Austrian
Accommodation:
flight crew : 2 cabin crew : 9
passengers : seating for 303 in two class : 30 business class and 273 economy class seats
( 32 -in pitch) exit limit : 420 passengers, high density seating for 404 passengers
engine : 4 CFM International CFM56-5C2 turbofan engines of 138.8 [KN] (31203 [lbf])
dimensions :
wingspan : 60.3 [m], length overall: 59.42 [m], length of fuselage : 58.57 [m]
height : 17.03 [m] wing area : 363.1 [m^2] fuselage exterior width : 5.64 [m]
weights :
operating empty weight : 119558 [kg] max. structural payload : 49442 [kg]
Zero Fuel weight (ZFW) : 169000 [kg] max. landing weight (MLW) : 181000 [kg]
max. take-off weight : 257000 [kg] weight usable fuel : 110402 [kg] (140640 [litres])
performance :
Max. operating Mach number (Mmo) : 0.86 [Mach] (930 [km/hr]) at 9450 [m]
critical Mach speed : 0.83 [Mach]
max. cruising speed : 880 [km/hr] (Mach 0.83 ) at 11000 [m] (42 [%] power)
economic cruising speed : 871 [km/hr] (Mach 0.82 ) at 11000 [m]
service ceiling : 12527 [m]
range with max fuel and MTOW : 14000 [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 : tapered multi-cellular fail safe wing with aluminium alloy stressed skin
with Fowler-type double slotted trailing edge flaps with full-span slotted LE flaps (slats) ,with spoilers and with winglets
made from Carbon Fiber Reinforced Plastic (CFRP)
airfoil : Airbus
average thickness/chord ratio : 12.3 [%], sweep angle 3/4 chord: 29.7 [°]
calculation : *1* (dimensions)
wing chord at root : 10.50 [m]
wing chord at tip : 2.57 [m]
taper ratio : 0.245 [ ]
mean wing chord : 6.02 [m]
wing aspect ratio : 10.01 []
Oswald factor (e): 0.703 []
seize (span*length*height) : 61019 [m^3]
calculation : *2* (fuel consumption)
oil consumption : 16.7 [kg/hr]
fuel consumption (econ. cruise speed) : 6691.8 [kg/hr] (8524.5 [litre/hr]) at 22 [%] power
distance flown for 1 kg fuel : 0.13 [km/kg] at 11000 [m] height, sfc : 55.4 [kg/KN/h]
total fuel capacity : 140640 [litre] (110402 [kg])
calculation : *3* (weight)
weight engine(s) dry : 10576.0 [kg] = 19.05 [kg/KN]
weight 379.0 litre oil tank : 32.21 [kg]
oil tank filled with 3.5 litre oil : 3.1 [kg]
Royal Jordanian A340-212 JY-AID c/n 022 at Franfurt (FRA), October 2014
oil in engine 6.8 litre oil : 6.1 [kg]
unusable fuel in engine and tanks 860.0 litre fuel : 675.11 [kg]
weight all fuel lines and pumps containing 127 litres fuel : 204.9 [kg]
weight engine cowling : 1443.5 [kg]
weight thrust reversers : 832.8 [kg]
total weight propulsion system : 13774 [kg](5.4 [%])
***************************************************************
Accommodation cabin facilities:
typical 2-class cabin layout for 303 passengers : economy : pitch : 81.3 [cm] 32.0 [-in]
( 2+4+2 ) seating in 38.4 rows
weight passenger seats : 1715.8 [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 : 404 [pax] at mainly 9 -abreast seating in 51.1 rows, pitch
74.7 [cm] 29.4 [-in]
pax density, normal seating : 0.78 [m2/pax], high density seating : 0.59 [m2/pax]
weight 7 lavatories : 222.7 [kg]
weight overhead pilot flight crew rest and optional lower deck mobile crew rest compartment : 228.0 [kg]
weight 6 galleys : 1227.1 [kg]
weight overhead stowage for hand luggage : 106.0 [kg]
weight 3 wardrobe closets : 30.3 [kg]
weight 303 entertainment LCD screens in back of seats : 151.5 [kg] (optional)
weight 79 windows (41 x 28 cm) made of acrylic glass : 215.4 [kg]
weight 6 (1.93 x 1.07 [m]) Type A main entry doors : 435.3 [kg]
weight 3 (main door size : 1.70 x 2.70 [m]) freight doors (belly) : 638.0 [kg]*
total belly baggage/cargo hold volume : 161.8 [m3]
underfloor belly hold can accommodate : 26 LD3 containers, netto volume : 115.4 [m3]
and : 19.7 [m3] bulk cargo
cabin volume (usable), excluding flight deck : 611 [m3]
passenger compartment volume : 344 [m3]
Egypt Air A340-212 SU-GBN c/n 159 interior, note there are no LCD screens in the back of the seats, but still large video screens. The LCD screens in the back of the seats are optional.
passenger cabin max width : 5.26 [m] cabin length : 45.63 [m] max cabin height : 2.54 [m]
floor area : 236.8 [m2]
weight cabin facilities : 5071.1 [kg]
safety facilities:
weight 2 type I emergency exits (0.61 x 1.60 [m]): 68.6 [kg]
evacuation time with 404 passengers : 56 [sec]
weight 14 hand fire extinguisher : 43 [kg]
weight cockpit voice recorder (CVR) and flight data recorder (FDR): 20.0 [kg]
weight oxygen masks & oxygen generators (deploy cabin alt.>4267m): 197.0 [kg]
weight emergency flare installation : 10 [kg]
weight 8 emergency evacuation slides : 517.9 [kg]
weight safety equipment & facilities : 856 [kg]
fuselage construction:
fuselage aluminium frame : 24967 [kg]
floor loading (payload/m2): 209 [kg/m2]
weight rear pressure bulkhead : 440.4 [kg]
fuselage covering ( 817.3 [m2] duraluminium 3.41 [mm]) : 7435.7 [kg]
weight floor beams : 3705.5 [kg]
weight cabin furbishing : 3433.0 [kg]
weight cabin floor : 3397.7 [kg]
weight (sound proof) isolation : 596.3 [kg] TO-noise level : 94.8 [EPNdB]
weight 42422 [litre] main central fuel tanks empty : 848.4 [kg]
weight empty 1767 [litre] potable water tanks : 156.3 [kg]
weight empty waste tank : 47.2 [kg]
weight fuselage structure : 45027.0 [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]
weight monochromatic weather X-band (3.2cm wavelength) radar system : 25.0 [kg]
Aerolineas Argentinas Airbus A340-211 LV-ZPX c/n 080 cockpit
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 : 30 [kg]
weight reserve ADI, ASI, alti-meter, compass, engine temp. and rpm indicators : 15 [kg]
weight avionics : 160.0 [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 [bar] (kg/cm2)
pressurized fuselage volume : 946 [m3] cabin air refreshment time : 3.5 [min]
weight air-conditioning and pressurization system : 461 [kg]
weight APU / engine starter: 69.4 [kg]
weight lighting : 100.0 [kg]
weight triple redundant 207 bar hydraulic system : 203.4 [kg]
weight engine-driven 40kVA electricity generators : 75.8 [kg]
weight ram air turbine for emergency electric power : 5.0 [kg]
weight three 24V 25Ah nickel-cadmium batteries : 31.8 [kg]
weight controls (sidestick FBW): 16.4 [kg]
weight systems : 958.1 [kg]
total weight fuselage : 52072 [kg](20.3 [%])
***************************************************************
total weight aluminium ribs (2048 ribs) : 8610 [kg]
weight engine mounts : 278 [kg]
weight 4 wing fuel tanks empty for total 92848 [litre] fuel : 1393 [kg]
weight 563 [litre] vent surge tanks : 68 [kg]
weight wing covering (painted aluminium 3.74 [mm]) : 7340 [kg]
total weight aluminium spars (multi-cellular wing structure) : 10197 [kg]
weight wings : 26147 [kg]
weight wing/square meter : 72.01 [kg]
weight thermal leading-edge anti-icing : 66.3 [kg]
weight ailerons made of carbon fiber reinforced plastic CFRP (15.26 [m2]) : 440.3 [kg]
weight fin (61.68 [m2]) : 2225.5 [kg]
weight rudder (32.47 [m2]) : 1124.5 [kg]
weight 6230 [litre] tail fuel trim tank empty : 155.7 [kg]
weight tailplane (stabilizer) (74.04 [m2]): 2938.4 [kg]
weight elevators (17.77 [m2]): 346.20 [kg]
weight flight control hydraulic servo actuators: 101.7 [kg]
weight trailing-edge double slotted flaps (70.80 [m2]) : 2172.0 [kg]
weight track-mounted light alloy construction leading edge slats (36.64 [m2]) : 707.1 [kg]
weight fly-by-wire operated spoilers of graphite composite construction (12.9 [m2]) : 204.5 [kg]
weight winglets : 200 [kg]
total weight wing construction : 38567 [kg] (32.3 [%])
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tire pressure main wheels : 13.20 [Bar] (nitrogen), ply rating : 27 PR
tire speed limit : 389 [km/hr]
total tyre footprint : 1.40 [m2]
Runway LCN at MTOW (0.76m radius of rigidity) : 48 [ ]
Aircraft Classification Number (ACN), MTOW on rigid runway and medium subgrade strength (B) : 32 [ ]
Can also operate from unpaved runways subgrade B
wheel pressure : 22616.0 [kg]
weight 10 Dunlop 55 x 21 main wheels (1400 [mm] by 530 [mm]) : 1892.4 [kg]
weight 2 nose wheels : 189.2 [kg]
weight hydraulic disc wheel-brakes : 169.0 [kg]
weight Duplex anti-skid units : 10.8 [kg]
weight oleo-pneumatic shock absorbers : 225.3 [kg]
weight wheel hydraulic operated retraction system : 2176.0 [kg]
total weight landing gear : 10771.2 [kg] (4.2 [%]
*******************************************************************
********************************************************************
calculated empty weight : 115184 [kg](44.8 [%])
weight oil for 19.1 hours flying : 329.8 [kg]
weight lifejackets : 136.3 [kg]
weight 5 life rafts : 189.4 [kg]
weight catering : 1136.2 [kg]
weight water : 1563.5 [kg]
weight crew : 891 [kg]
weight crew luggage, nav. chards, flight doc., miscell. items : 128 [kg]
operational weight empty : 119558 [kg] (46.5 [%])
********************************************************************
weight 303 passengers : 23331 [kg]
weight luggage : 4848 [kg]
weight cargo : 21263 [kg] (cargo + luggage/m3 belly : 154 [kg/m3])
zero fuel weight (ZFW): 169000 [kg](65.8 [%])
weight fuel for landing (1.8 hours flying) : 12000 [kg]
max. landing weight (MLW): 181000 [kg](70.4 [%])
max. fuel weight : 229960 [kg] (89.5 [%])
payload with max fuel : 291 passengers + luggage 27040 [kg]
published maximum take-off weight : 257000 [kg] (100.0 [%])
calculation : * 4 * (engine power)
power loading (Take-off) : 463 [kg/KN]
power loading (Take-off) 1 PUF: 617 [kg/KN]
max. total take-off power : 555.2 [KN]
calculation : *5* (loads)
manoeuvre load : 0.9 [g] at 9000 [m]
limit load : 2.5 [g] ultimate load : 3.8 [g] load factor : 1.0 [g]
design flight time : 7.50 [hours]
design cycles : 11000 sorties, design hours : 82500 [hours]
max. wing loading (MTOW & flaps retracted) : 708 [kg/m2]
wing stress (2 g) during operation : 164 [N/kg] at 2g emergency manoeuvre
calculation : *6* (angles of attack)
angle of attack zero lift : -1.67 ["]
max. angle of attack (stalling angle, clean) : 12.11 ["]
max. angle of attack (full flaps) : 16.31 ["]
angle of attack at max. speed : 2.80 ["]
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): 1.24 [ ]
max. lift coefficient full flaps : 2.10 [ ]
drag coefficient at max. speed : 0.0294 [ ]
drag coefficient at econ. cruise speed : 0.0312 [ ]
induced drag coefficient at econ. cruise speed : 0.0118 [ ]
drag coefficient (zero lift) : 0.0194 [ ]
lift/drag ratio at econ. speed : 13.66 [ ]
calculation : *8* (speeds
take-off decision speed (V1) : 256 [km/u] (138 [kt])
take-off rotation speed (VR) : 269 [km/u] (145 [kt])
Air Leisure A340-212
lift-off speed (VLOF) : 290 [km/u] (156 [kt]) at pitch angle : 15.0 [°]
take-off safety speed (V2) : 292 [km/u] (157 [kt])
flap retraction speed (V3) at 500m (OW loaded : 250308 [kg]): 362 [km/u] (196 [kt])
steady initial climb speed (V4) : 318 [km/u] (171 [kt])
climb speed (to FL150 with 56 [%] power) : 587 [km/hr] (317 [kt])
max. endurance speed (Vbe): 547 [km/u] min. fuel/hr : 6494 [kg/hr] at height : 5182 [m]
max. range speed (Vbr): 866 [km/u] (0.82 [mach]) min. fuel consumption : 7.71 [kg/km] at cruise height : 10973 [m]
max. cruising speed : 880 [km/hr] (475 [kt]) at 11000 [m] (power:23 [%])
max. operational speed (Mmo) : 930 [km/hr] (Mach 0.86 ) at 9450 [m] (power:27 [%])
airflow at cruise speed per engine : 236.5 [kg/s]
speed of thrust jet : 1357 [km/hr]
initial descent speed 10000 - 7315 [m]: Mach 0.82
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): 326 [km/u] (176 [kt])
stalling speed clean at 500 [m] height at Max.Landing Weight : 181000 [kg]): 296 [km/u] (160 [kt])
final approach speed (landing speed) at sea-level with full flaps VREF (max. landing weight): 261 [km/u] (141 [kt])
ICAO Aircraft Approach Category (APC) : D
stalling speed at sea-level with full flaps VSO (max. landing weight): 201 [km/u] (108 [kt]
rate of climb at sea-level ROC (loaded, 56 % power) : 724 [m/min]
rate of climb at sea-level ROC (loaded, 75 % power) : 1248 [m/min]
rate of climb at 1000 [m] with 1 engine out (PUF/MTOW, 100 % power on remaining engines) : 1026 [m/min]
rate of climb at 1000 [m] with 2 engines out (2xPUF / MTOW) : 0 [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)
low wheel pressure, can also take off from unpaved runways
ICAO Aerodrome Reference Code : 4E
Brake kinetic energy capacity : 3143 [KW]
Take-off distance at MTOW 257000 kg (566578 lb) at sea level : 9000 ft > 2743m
FAR TO balanced runway length (TOFL) requirement at TOW 257000 [kg] standard day at
SL (distance to 10.7m height x 1.15): 2743 [m]
+++ FAA certification landing distance : +++
landing weight : 181000 [kg], TE flap setting : 37 [°]
runway condition : dry , landing over 50ft (15m) at threshold at sea-level
without use of thrust reversers
Landing distance at MLW 181000 kg (399000 lb), sea level, dry runway : 6000 ft : 1829 [m]
FAA approved landing field length : 1828 [m] (5996 [ft])
landing distance (C.A.R.) from 15 [m] at SL, wet runway: 2091 [m] (6859 [ft])
max. lift/drag ratio : 16.90 [ ]
climb to 5000 [m] with max payload : 6.39 [min]
climb to 10000 [m] with max payload : 19.67 [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: 250308 [kg] ) : 14400 [m]
calculation *10* (action radius & endurance)
range with max. payload: 10851 [km] with 49442.0 [kg] max. useful load (79.7 [%] fuel)*
range with high density pax: 12602 [km] with 404 passengers (90.5 [%] fuel)*
range with typical two-class pax: 14026 [km] with 303 passengers (99.0 [%] fuel)*
Range with max payload 109000 lb (49442 kg) : 5500 nm > 10186 km Range with max fuel : 14000 km. MTOW 257000 kg. Ferry range 8550 nm > 15835 km
range with max.fuel : 14203 [km] with 11 crew and 291 passengers and 100.0 [%] fuel*
ferry range (calculated): 15885 [km] with 2 crew and zero payload (100.0 [%] fuel)*
max range theoretically with additional fuel tanks total 179453 [litre] fuel : 19179 [km]*
* calculated ranges without fuel reserves
Available Seat Kilometres (ASK) : 4648640 [paskm]
useful load with range 1000km : 49442 [kg]
useful load with range 1000km : 404 passengers
production (theor.max load): 43509 [tonkm/hour]
production (useful load): 43509 [tonkm/hour]
production (passengers): 301977 [paskm/hour]
oil and fuel consumption per tonkm : 0.154 [kg]
calculation *11* (operating cost)
fuel cost per hour (8525 [litre]):5114 [eur] (35 [pax-km/litre fuel])
fuel cost per seat 1000km flight (343 [pax] 2-class seating): 16.94 [eur/1000PK]
oil cost per hour: 69 [eur]
Air Bourbon A340-211 F-OITN c/n 031 with its crew
crew cost per hour : 1500 [eur]
list price 2024 : 132 [mln USD]
average flying hours in 1 year : 4500 [hours] technical life : 18 [year]
real average service life : 20 [years]
depreciation - 20 [years] to 10% residual value
economic hours (expected total flying hours): 90000 [hours] is 0 [%] less then cor. design
hours 90000 [hours]
financing interest per flying hour : 662 [EUR]
Sabena Airbus A340-211 OO-SCX, was delivered June 1993, and seen here at Brussels airport (BRU) in July 1996.
write off per flying hour : 1223 [EUR]
time between engine failure : 5713 [hr]
can continue fly on 3 engines, low risk for emergency landing for PUF
workhours per day : 13.56 [hr]
no fatalities during service life > 100%% safe
average flight hours till crash : 2.52 [mln hr] (560 service years)
safe flight hours till fatality : 2520000 [hr] (560.0 service years)
reservation pax liability/flying hour : 0.05 [SDR*] (0.06 [eur])
insurance cost per hour : 242 [eur] insurance rate : 2.2 [%]
engine maintenance cost per hour : 957.9 [eur]
wing maintenance cost per hour : 106.5 [eur]
fuselage maintenance cost per hour : 29.06 [eur]
tire life (time till worn out) : 83 [cycles]
maintenance cost per hour (excluding engines): 2076 [eur]
direct operating cost per hour: 11844 [eur], DOC per km : 13.60 [eur]
DOC per seat 1000km flight (343 [pax] 2-class seating): 39.22 [eur/1000PK]
DOC per seat 1000km flight (high density seating): 33.35 [eur/1000PK]
DOC per kg cargo for a 1000km flight : 0.27 [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 : 4.58 [eur/pax]
airport landing fee / passenger : 4.58 [eur/pax]
retour ticket price 1000km trip : 153.54 [eur/pax]
price retour ticket Schiphol-Barcelona : 175.12 [eur/pax]*
* This needs recalculation for ultra long range aircraft
Air France A340-211 F-GNIA c/n 010 was destroyed by fire. When the aircraft was pulled out of the maintenance hangar at Paris CDG airport on 20 January 1994, a fire broke out. The fire brigade could not prevent that the aircraft was destroyed by the fire.
accidents with fatalities > there have been no fatal accidents with an A340.
Literature :
wikipedia
https://contentzone.eurocontrol.int/aircraftperformance/default.aspx?
https://www.airbus.com/en/airport-operations-and-technical-data/aircraft-characteristics
Luchtvaart mrt’92 page 81
Luchtvaart nov’93 page 412
Luchtvaart jun’92 page 173
Luchtvaart sep’90 page 257
Air International apr’94 page 200
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 25 February 2024 contact : info.aircraftinvestigation@gmail.com ac jetpax 2020.py python 3.7.4
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