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weight and performance calculations for the Airbus A310-200 (WV011)

KLM A310-203 PH-AGA “Rembrandt” c/n 241

Airbus A310-200 (WV011)

role : wide-body airliner

importance : **

first flight : 3 April 1982 (P&W JT9D-7R4 engines) operational : July 1983

country : EU-consortium

ICAO aircraft type designator :

production : -200 39 ? needs more research, in total 255 A310 models have been built, not

clear how many were A310-200’s..

general information :

Shorter version of the A300 with new supercritical wing which set new standards for lift-

drag ratio, fuel capacity and weight.

primary users : KLM (10) , Martinair, PanAm, Nigeria Airways, Delta Airlines, Turkish

Airlines, Lufthansa, Swissair

Accommodation:

flight crew : 2 cabin crew : 8

Flying the A-310 with two men; It's an easy task?

passengers : seating for 220 in two class : 20 business class and 200 coach class seats

( 34 -in pitch) exit limit : 275 passengers, high density seating for 264 passengers

engine : 2 General Electric CF6-80A3 turbofan engines of 222.4 [KN] (49997 [lbf]) or Pratt & Whitney JT9D-7R4 turbofans

dimensions :

wingspan : 43.89 [m], length overall: 46.66 [m], length of fuselage : 45.89 [m]

height : 15.8 [m] wing area gross : 219.9 [m^2] fuselage exterior width : 5.64 [m]

weights :

operating empty weight : 79207 [kg] max. structural payload : 32293 [kg]

Zero Fuel weight (ZFW) : 111500 [kg] max. landing weight (MLW) : 121500 [kg]

max. take-off weight : 144000 [kg] weight usable fuel : 43128 [kg] (54940 [litres])

performance :

Max. operating Mach number (Mmo) : 0.86 [Mach] (930 [km/hr]) at 9450 [m]

critical Mach speed : 0.81 [Mach]

max. cruising speed : 869 [km/hr] (Mach 0.81 ) at 10000 [m] (29 [%] power)

economic cruising speed : 835 [km/hr] (Mach 0.78 ) at 10000 [m]

service ceiling : 12527 [m]

range with max fuel and MTOW : 6500 [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 Fowler-type double slotted trailing edge flaps on inner wing and single-slotted flap on

outer wing with full-span slotted LE flaps (slats) ,with spoilers (outboard) and airbrakes

(inboard) airfoil : Airbus average thickness/chord ratio : 12.6 [%], sweep angle 3/4

chord: 28.0 [°] incidence : 5.05 [°], dihedral : 7.5 [°]

Minister of State Dr. M. Ruppert has given his name to KLM's Airbus A310, PH-AGD. With a paint-spray he put his name on the nose of the plane. From 1947 to 1983 Dr. Ruppert was a member of the Board of Commissioners of KLM.

Fuselage : Pressurized conventional semi-monocoque fail safe structure of circular cross-

section built mainly of high-strength aluminium alloy

calculation : *1* (dimensions)

wing chord at root : 8.38 [m]

wing chord at tip : 2.18 [m]

taper ratio : 0.260 [ ]

mean wing chord : 5.01 [m]

wing aspect ratio : 8.76 []

Oswald factor (e): 0.688 []

seize (span*length*height) : 32357 [m^3]

calculation : *2* (fuel consumption)

oil consumption : 15.6 [kg/hr]

fuel consumption (econ. cruise speed) : 5241.9 [kg/hr] (6677.6 [litre/hr]) at 26 [%] power

distance flown for 1 kg fuel : 0.16 [km/kg] at 10000 [m] height, sfc : 45.0 [kg/KN/h]

total fuel capacity : 54940 [litre] (43128 [kg])

calculation : *3* (weight)

weight engine(s) dry : 7954.0 [kg] = 17.88 [kg/KN]

weight 180.6 litre oil tank : 15.35 [kg]

oil tank filled with 2.8 litre oil : 2.5 [kg]

Pan Am A310-222 N805PA c/n 339 at Zurich Kloten, June 1991

oil in engine 5.5 litre oil : 4.9 [kg]

weight all fuel lines and pumps containing 92 litres fuel : 119.5 [kg]

weight engine cowling : 1156.5 [kg]

weight thrust reversers : 667.2 [kg]

total weight propulsion system : 9920 [kg](6.9 [%])

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Accommodation cabin facilities:

Lufthansa A310-200 cabin seat plan

typical 2-class cabin layout for 220 passengers : economy : pitch : 86.4 [cm] 34.0 [-in]

( 2+4+2 ) seating in 27.9 rows

weight passenger seats : 1247.7 [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 : 264 [pax] at mainly 9 -abreast seating in 31.9 rows,

pitch 80.7 [cm] 31.8 [-in]

pax density, normal seating : 0.78 [m2/pax], high density seating : 0.65 [m2/pax]

passenger cabin luxurious spaced for good service, enough space for galleys and toilets

even at HD seating

weight 5 lavatories : 143.0 [kg]

weight 4 galleys : 267.3 [kg]

weight overhead stowage for hand luggage (total : 22.5 [m3]) : 76.8 [kg]

weight 2 wardrobe closets : 22.0 [kg]

weight 3 movie screens : 51.1 [kg]

weight 58 windows (41 x 28 cm) made of acrylic glass : 157.7 [kg]

weight 4 (1.93 x 1.07 [m]) Type A main entry doors : 247.9 [kg]

weight 3 (main door size : 1.71 x 2.69 [m]) freight doors (belly) : 546.2 [kg]*

total usable belly baggage/cargo hold volume : 112.1 [m3]

underfloor belly hold can accommodate : 14 LD3 containers, netto volume : 62.6 [m3]

and : 21.0 [m3] bulk cargo

cabin volume (usable), excluding flight deck : 448 [m3]

passenger compartment volume : 209 [m3]

passenger cabin max width : 5.28 [m] cabin length : 33.23 [m] max cabin height : 2.33 [m]

floor area : 172.2 [m2]

weight cabin facilities : 2855.8 [kg]

safety facilities:

weight 2 type I emergency exits (0.67 x 1.39 [m]): 55.9 [kg]

evacuation time with 264 passengers : 52 [sec]

weight 11 hand fire extinguisher : 32 [kg]

weight cockpit voice recorder (CVR) and flight data recorder (FDR): 20.0 [kg]

weight oxygen masks & oxygen generators (deploy cabin alt.>4267m): 143.0 [kg]

weight emergency flare installation : 10 [kg]

weight 6 emergency evacuation slides : 423.0 [kg]

weight safety equipment & facilities : 684 [kg]

fuselage construction:

fuselage aluminium frame : 16454 [kg]

floor loading (payload/m2): 188 [kg/m2]

weight rear pressure bulkhead : 380.0 [kg]

fuselage covering ( 630.5 [m2] duraluminium 2.92 [mm]) : 4915.3 [kg]

weight floor beams : 2457.4 [kg]

weight cabin furbishing : 2298.3 [kg]

Nigeria Airways A310-221 5N-AUF c/n 285 at London LHR, 1993, in April 1991 the aircraft overran at landing at Lagos airport, and the nose gear collapsed but the aircraft was repaired and flew on.

weight cabin floor : 2409.1 [kg]

weight (sound proof) isolation : 519.1 [kg] TO-noise level : 98.7 [EPNdB]

weight 19640 [litre] main central fuel tanks empty : 392.8 [kg]

weight empty 224 [litre] potable water tanks : 19.8 [kg]

weight empty waste tank : 17.1 [kg]

weight fuselage structure : 29863.2 [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]

A310 forward facing crew cockpit, with the flight engineer also facing forward, seated between the captain and co-pilot, soon the flight engineer was not needed any more. The A310 was the first wide-body with an FFCC from the start, the A300B4-200 had this option down on the production line with Garuda flying with this cockpit layout in 1982 as first.

1. ASI – Air Speed Indicator 2. RMI – Radio Magnetic Indicator 3. PFD- Primary Flight Display CRT screen 4. ND – navigation display CRT screen 5. Altimeter 6. Climb speed indicator 7. second RMI 8. Barometric altimeter 9. Chronometer 10. Artificial horizon 11. Reserve altimeter . 12 control panel flaps & slats 13. Control panel wheel brakes 14. ECAM CRT screen crew alerts 15. Engine instruments 16. Control panel landing gear 17. ECAM CRT-screen systems overview 18. Control panel auto-pilot 19. Control panel PFD & ND.

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]

Primary flight display and navigation display. According the PFD (left) the aircraft makes a slight climbing turn to the right during a CAT 2 landing approach (runway must be visible from 100ft height). Speed 127 kts, increasing to set speed of 138 kts. Radio-altimeter altitude 250ft, barometric altitude 290ft. The ND (right) shows some storm-area’s with the coloured patches. Compass heading 228° (yellow triangle at top), line of course 237°, wind 20ts form the east (indicated bottom left), ground speed 225 kts, TAS 210 kts. Next waypoint is Korinthos (KOR) at 14nm distance. Planned speed 240 kts and height FL110 at KOR.

weight EFIS (4 Rockwell Collins CRT screens ADI/PFD+HSI/ND displays) : 20 [kg]

weight ground proximity warning system (GPWS) : 6 [kg]

Centre console with ECAM (Electronic Centralised Aircraft Monitor) and engine instruments

weight ECAM CRT screens to display engine and system information : 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 6300 [m]

and gives equivalent of 2400 [m] at 11885 [m]. pressure differential : 0.57 [bar] (kg/cm2)

pressurized fuselage volume : 672 [m3] cabin air refreshment time : 3.5 [min]

weight air-conditioning and pressurization system : 327 [kg]

weight APU / engine starter : 111.2 [kg]

weight lighting : 72.6 [kg]

weight triple redundant 207 bar hydraulic system : 107.9 [kg]

Martinar PH-MCA “Prins Bernhard”

weight two engine-driven 90kVA 400 Hz 3-phase AC electricity generators : 55.0 [kg]

weight ram air turbine for emergency electric power : 5.0 [kg]

weight three 24V 25Ah nickel-cadmium batteries : 31.8 [kg]

weight controls : 19.8 [kg]

weight systems : 724.9 [kg]

total weight fuselage : 34288 [kg](23.8 [%])

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total weight aluminium ribs (1389 ribs) : 4859 [kg]

weight engine mounts : 222 [kg]

Inner fuel tank 13950 litre, outer fuel tank 3700 litre > total wing : 35300 litre, central tank : 19640 litre > makes total 54940 litre, A310-300 has the tail trim tank > 6440 litre > total 61380 litre, for A310-200 is optional.

weight 6 wing fuel tanks empty for total 35300 [litre] fuel : 530 [kg]

weight 220 [litre] vent surge tanks : 26 [kg]

weight wing covering (painted aluminium 5.19 [mm]) : 6159 [kg]

total weight aluminium spars (multi-cellular wing structure) : 6650 [kg]

weight wings : 17669 [kg]

weight wing/square meter : 80.35 [kg]

weight thermal leading-edge anti-icing : 48.3 [kg]

weight high & low speed ailerons (6.86 [m2]) : 220.9 [kg]

weight fin (45.20 [m2]) : 1819.3 [kg]

weight rudder (13.55 [m2]) : 523.7 [kg]

weight tailplane (stabilizer) (44.79 [m2]): 1983.0 [kg]

weight elevators (19.21 [m2]): 417.61 [kg]

weight flight control hydraulic servo actuators: 53.9 [kg]

weight trailing-edge double + single slotted flaps (36.67 [m2]) : 1257.2 [kg]

weight track-mounted light alloy construction leading edge slats (28.53 [m2]) : 614.7 [kg]

weight fly-by-wire operated spoilers of graphite composite construction (7.3 [m2]) : 132.5 [kg]

weight airbrakes (6.2 [m2]) : 125.9 [kg]

total weight wing construction : 25644 [kg] (32.4 [%])

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tire pressure main wheels : 13.30 [Bar] (nitrogen), ply rating : 23 PR

tire speed limit : 364 [km/hr]

total tyre footprint : 0.52 [m2]

Runway LCN at MTOW (0.76m radius of rigidity) : 72 [ ]

Aircraft Classification Number (ACN), MTOW on rigid runway and medium

subgrade strength (B) : 41 [ ]

Can only operate from unpaved runways with reduced weight and reduced tyre pressure

wheel pressure : 15840.0 [kg]

wheel track : 9.60 [m] wheelbase : 15.21 [m]

weight 8 Dunlop 46 x 16 main wheels (1170 [mm] by 412 [mm]) : 1175.9 [kg]

weight 2 nose wheels : 147.0 [kg]

weight hydraulic disc wheel-brakes : 111.5 [kg]

weight Duplex anti-skid units : 9.0 [kg]

weight oleo-pneumatic shock absorbers : 148.7 [kg]

weight wheel hydraulic operated retraction system : 1529.5 [kg]

weight undertail bumper : 20 [kg]

weight undercarriage struts (four-wheel bogies) with axle 4429.6 [kg]

total weight landing gear : 7571.2 [kg] (5.3 [%]

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

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

calculated empty weight : 77422 [kg](53.8 [%])

weight oil for 9.0 hours flying : 153.7 [kg]

unusable fuel in engine and tanks 82.4 litre fuel : 64.7 [kg]

weight lifejackets : 99.0 [kg]

weight 4 life rafts : 137.5 [kg]

weight catering : 247.5 [kg]

weight water : 198.0 [kg]

weight crew : 810 [kg]

weight crew luggage, nav. chards, flight doc., miscell. items : 74 [kg]

operational weight empty : 79207 [kg] (55.0 [%])

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

weight 220 passengers : 16940 [kg]

weight luggage : 3520 [kg]

weight cargo : 11833 [kg] (cargo + luggage/m3 belly : 129 [kg/m3])

zero fuel weight (ZFW): 111500 [kg](77.4 [%])

weight fuel for landing (1.9 hours flying) : 10000 [kg]

max. landing weight (MLW): 121500 [kg](84.4 [%])

max. fuel weight : 122335 [kg] (85.0 [%])

payload with max fuel : 233 passengers + luggage 21665 [kg]

published maximum take-off weight : 144000 [kg] (100.0 [%])

calculation : * 4 * (engine power)

power loading (Take-off) : 324 [kg/KN]

power loading (Take-off) 1 PUF: 647 [kg/KN]

max. total take-off power : 444.8 [KN]

calculation : *5* (loads)

manoeuvre load : 1.0 [g] at 9000 [m]

limit load : 2.5 [g] ultimate load : 3.8 [g] load factor : 1.5 [g]

design flight time : 2.25 [hours]

design cycles : 19370 sorties, design hours : 43582 [hours]

max. wing loading (MTOW & flaps retracted) : 655 [kg/m2]

wing stress (2 g) during operation : 147 [N/kg] at 2g emergency manoeuvre

calculation : *6* (angles of attack)

angle of attack zero lift : -1.72 ["]

max. angle of attack (stalling angle, clean) : 12.61 ["]

max. angle of attack (full flaps) : 16.81 ["]

angle of attack at economic cruise speed : 3.91 ["]

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): 1.25 [ ]

max. lift coefficient full flaps : 2.45 [ ]

Prince Bernhard 'flew' a bit yesterday but remained firmly on the ground. He officially inaugurated the flight simulator for the Airbus A310 at Schiphol. The thing means a huge cost saving because the pilots can learn a lot in it while they don't really have to take to the air. When the training in the fake cabin (cost 29.8 million guilders) is completed, the pilots who will be on duty on the new aircraft will only have to experience six more training hours before they can actually transport passengers. In the simulator, they will have experienced twelve lessons of four hours each.

drag coefficient at max. speed : 0.0500 [ ]

drag coefficient at econ. cruise speed : 0.0477 [ ]

induced drag coefficient at econ. cruise speed : 0.0128 [ ]

drag coefficient (zero lift) : 0.0349 [ ]

lift/drag ratio at econ. speed : 8.04 [ ]

calculation : *8* (speeds

take-off decision speed (V1) : 251 [km/u] (135 [kt])

take-off rotation speed (VR) : 263 [km/u] (142 [kt])

minimum unstick speed (Vmu) at TO angle 17.6 ° : 258 [km/u] (139 [kt])

lift-off speed (VLOF) : 284 [km/u] (153 [kt]) at pitch angle : 14.8 [°]

take-off safety speed (V2) : 287 [km/u] (155 [kt])

flap retraction speed (V3) at 500m (OW loaded : 138758 [kg]): 347 [km/u] (188 [kt])

steady initial climb speed (V4) : 313 [km/u] (169 [kt])

climb speed (to FL150 with 63 [%] power) : 534 [km/hr] (289 [kt])

max. endurance speed (Vbe): 508 [km/u] min. fuel/hr : 4642 [kg/hr] at height : 5791 [m]

max. range speed (Vbr): 848 [km/u] (0.80 [mach]) min. fuel consumption : 5.94 [kg/km] at

cruise height : 10973 [m]

max. cruising speed : 869 [km/hr] (469 [kt]) at 10000 [m] (power:28 [%])

max. operational speed (Mmo) : 930 [km/hr] (Mach 0.86 ) at 9450 [m] (power:35 [%])

airflow at cruise speed per engine : 375.3 [kg/s]

speed of thrust jet : 1462 [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): 372 [km/u] (201 [kt])

stalling speed clean at 500 [m] height at Max.Landing Weight : 121500 [kg]): 310 [km/u]

(167 [kt])

Final Approach speed (1.3 x Vs) at 50ft, gear down at MLW 121500 kg (267857 lb), 40° flaps : 135 kts

final approach speed (landing speed) at sea-level with full flaps VREF (max. landing weight):

250 [km/u] (135 [kt])

ICAO Aircraft Approach Category (APC) : C

stalling speed at sea-level with full flaps VSO (max. landing weight): 192 [km/u] (104 [kt]

rate of climb at sea-level ROC (loaded, 63 % power) : 1004 [m/min]

rate of climb at sea-level ROC (loaded, 75 % power) : 1380 [m/min]

rate of climb at 1000 [m] with 1 engine out (PUF/MTOW, 100 % power on remaining engines) : 488 [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

Brake kinetic energy capacity : 2121 [KW]

Take-off runway length at MTOW 144000 kg (317460 lb), standard day, sea level : 6725 ft = 2050m. According jane’s atwa 91-92 page 111 TO field length is 1860m, unclear with what TO weight..

FAR TO runway length (TOFL) requirement at TOW 144000 [kg] standard day at SL (PUF after V1): 2049 [m]

Landing field length at MLW 121500 kg (267857 lb), 40° flaps : 1495 m (4900ft)

+++ FAA certification landing distance : +++

landing weight : 121500 [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 : 1537 [m] (5044 [ft])

landing distance (C.A.R.) from 15 [m] at SL, wet runway: 1766 [m] (5792 [ft])

max. lift/drag ratio : 11.64 [ ]

climb to 5000 [m] with max payload : 4.61 [min]

climb to 10000 [m] with max payload : 14.18 [min]

Martinair A310-203 PH-MCA c/n 281, here pictured still with France registration F-WZET

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: 138758 [kg] ) : 15000 [m]

calculation *10* (action radius & endurance)

range with max. payload: 5057 [km] with 32293.0 [kg] max. useful load (75.4 [%] fuel)*

range with high density pax: 6366 [km] with 264 passengers (93.3 [%] fuel)*

range with typical two-class pax: 6906 [km] with 220 passengers (100.0 [%] fuel)*

A310-200 MTOW 142.000 kg, range with max.payload : 4000 km, with max fuel : 6500 km, ferry range 8000 km

range with max.fuel : 6870 [km] with 10 crew and 233 passengers and 100.0 [%] fuel*

ferry range (calculated): 7552 [km] with 2 crew and zero payload (100.0 [%] fuel)*

max range theoretically with additional fuel tanks total 83932 [litre] fuel : 11018 [km]*

* calculated ranges without fuel reserves

Available Seat Kilometres (ASK) : 1661758 [paskm]

useful load with range 1000km : 32293 [kg]

Dwarf among the giants – A business jet from the National Aviation School is almost dwarfed by the tail of a KLM Airbus. Such a picture is rarely to be taken at the airport.

PH-AGC KLM A310-203 c/n 248 “Albert Cuyp”. The business jet is probably RLS Cessna Citation PH-CTC

useful load with range 1000km : 264 passengers

production (theor.max load): 28063 [tonkm/hour]

production (useful load): 28063 [tonkm/hour]

production (passengers): 216851 [paskm/hour]

oil and fuel consumption per tonkm : 0.187 [kg]

calculation *11* (operating cost)

fuel cost per hour (6678 [litre]):4006 [eur] (32 [pax-km/litre fuel])

fuel cost per seat 1000km flight (250 [pax] 2-class seating): 18.47 [eur/1000PK]

oil cost per hour: 65 [eur]

crew cost per hour : 1350 [eur]

list price 2024 : 205 [mln USD]

average flying hours in 1 year : 2000 [hours] technical life : 22 [year]

real average service life : 18 [years]

depreciation - 18 [years] to 10% residual value

economic hours (expected total flying hours): 36000 [hours] is 0 [%] less then cor. design hours 36000 [hours]

Martinair A310-203C PH-MCB c/n 349 “Prins Maurits” , seen here still with France registration F-WZEP upon delivery.

financing interest per flying hour : 2308 [EUR]

write off per flying hour : 4734 [EUR]

time between engine failure : 15010 [hr]

can continue fly on 1 engine, low risk for emergency landing for PUF

workhours per day : 7.31 [hr]

average flight hours till crash : 1.30 [mln hr] (648 service years)

safe flight hours till fatality : 12832 [hr] (6.4 service years)

reservation pax liability/flying hour : 10.04 [SDR*] (12.55 [eur])

insurance cost per hour : 730 [eur] insurance rate : 1.9 [%]

Martinair PH-MCA “Prins Bernhard” taking off from Schiphol airport

engine maintenance cost per hour : 2225.1 [eur]

wing maintenance cost per hour : 215.0 [eur]

fuselage maintenance cost per hour : 249.08 [eur]

tire life (time till worn out) : 90 [cycles]

maintenance cost per hour (excluding engines): 1380 [eur]

direct operating cost per hour: 16811 [eur], DOC per km : 20.13 [eur]

DOC per seat 1000km flight (250 [pax] 2-class seating): 77.52 [eur/1000PK]

DOC per seat 1000km flight (high density seating): 73.21 [eur/1000PK]

DOC per kg cargo for a 1000km flight : 0.60 [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 : 3.31 [eur/pax]

airport landing fee / passenger : 3.31 [eur/pax]

retour ticket price 1000km trip : 232.23 [eur/pax]

price retour ticket Schiphol-Barcelona : 274.87 [eur/pax]

F-WZLI A310-200 prototype at finals

accidents with fatalities > see the accident file

Literature :

Airbus A310 - Wikipedia

Aircraft Door & Emergency Exit Types and Role ConsiderationsSasSofia

Volkskrant 19 juli 1996

Air International apr’94 page 200

Air International dec’97 page 382

KLM gegevens page 11,18

Luchtvaart sep’90 page 256

KIJK Dec.1986 page 72-73

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

https://www.boeing.com/commercial/airports/plan-manuals

https://www.airbus.com/en/airport-operations-and-technical-data/aircraft-characteristics

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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