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weight and performance calculations for the Airbus A340-500 WV000
Azerbaijan A340-542 4K-AZ86 s/n 894
Airbus A340-541 WV000
role : wide-body long-range airliner
importance : **
first flight : 11 February 2002 operational : January 2003 (Emirates)
country : EU-consortium
ICAO aircraft type designator : A345
production : 34 aircraft
general information :
This is an ultra-long-range version. It can fly 15740 km with 313 passengers. The A340-300 was lengthened by 3.19m. -300 extended by 3.19m. Furthermore, the wingspan was increased by 1.6m to increase the wing area and fuel capacity. It has also a bigger tailplane. The centreline main landing gear was changed to a four wheel bogie for the higher weights. It was certified on December 3, 2002. At that moment it was the world’s longest-range commercial airliner. It is capable to fly non-stop from London to Perth, Australia. Emirates used the A340-500 on non-stop services from Dubai to New York and Singapore airlines on the Singapore – Newark route with a 2-class 181 passenger layout. This latter was the longest scheduled non-stop commercial flight in the world. Singapore Airlines suspended this flight from 2013 partly due to high fuel prices. SG changed there A340’s for A350. The higher gross-weight A340-542 first flew on 13 October 2006, with an MTOW of 380t it has a range of 17000 km. First delivery was to Thay Airways on 11 April 2007. It has more powerful Trent 556 engines. The A340-500 was not so popular with its customers; it was not so efficient, with high operating cost. And it had to face tough competition from the 2-engine 777-200LR and 777-300ER who benefitted from the relaxing of the ETOPS twin-engine restriction as the big turbofans proved to be more and more reliable.
Rising fuel prices in 2008 made the A340-500 to expensive to operate on the ultra-long
routes, and many were retired early or returned to Airbus, and in some cases switched for a
A350. By 2024 there are no commercial A340-500’s operational anymore.
primary users : Emirates, Singapore Airlines, Azerbaijan, A340-542 : Thay Airlines, Arik Air
Accommodation:
flight crew : 3 cabin crew : 12
flight crew consist of pilot, co-pilot and relief pilot
passengers : seating for 313 in two class : 48 business class and 265 economy deluxe
class seats ( 33 -in pitch) exit limit : 440 passengers, high density seating for 423
passengers
engine : 4 Rolls Royce Trent 553 turbofan engines of 248.0 [KN] (55752 [lbf])
dimensions :
wingspan : 63.45 [m], length overall: 67.93 [m], length of fuselage : 66.03 [m]
height : 17.53 [m] wing area : 437.3 [m^2] fuselage exterior width : 5.64 [m]
weights :
operating empty weight : 171000 [kg] max. structural payload : 54000 [kg]
Zero Fuel weight (ZFW) : 225000 [kg] max. landing weight (MLW) : 240000 [kg]
max. take-off weight : 368000 [kg] weight usable fuel : 168624 [kg] (214808 [litres])
performance :
Max. operating Mach number (Mmo) : 0.86 [Mach] (930 [km/hr]) at 9450 [m]
critical Mach speed : 0.84 [Mach]
max. cruising speed : 895 [km/hr] (Mach 0.85 ) at 11200 [m] (34 [%] power)
economic cruising speed : 865 [km/hr] (Mach 0.82 ) at 11200 [m]
service ceiling : 12634 [m]
range with max fuel and MTOW : 16670 [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: 31.1 [°]
calculation : *1* (dimensions)
wing chord at root : 12.18 [m]
wing chord at tip : 2.67 [m]
taper ratio : 0.219 [ ]
mean wing chord : 6.89 [m]
wing aspect ratio : 9.21 []
Oswald factor (e): 0.703 []
seize (span*length*height) : 75557 [m^3]
calculation : *2* (fuel consumption)
oil consumption : 8.9 [kg/hr]
fuel consumption (econ. cruise speed) : 8559.9 [kg/hr] (10904.3 [litre/hr]) at 16 [%] power
distance flown for 1 kg fuel : 0.10 [km/kg] at 11200 [m] height, sfc : 55.3 [kg/KN/h]
total fuel capacity : 214808 [litre] (168624 [kg])
calculation : *3* (weight)
weight engine(s) dry : 19960.0 [kg] = 20.12 [kg/KN]
weight 255.9 litre oil tank : 21.75 [kg]
oil tank filled with 6.2 litre oil : 5.6 [kg]
oil in engine 12.2 litre oil : 10.9 [kg]
unusable fuel in engine and tanks 1313.6 litre fuel : 1031.14 [kg]
weight all fuel lines and pumps containing 133 litres fuel : 282.7 [kg]
weight engine cowling : 2579.2 [kg]
weight thrust reversers : 1488.0 [kg]
total weight propulsion system : 25379 [kg](6.9 [%])
***************************************************************
Accommodation cabin facilities:
typical 2-class cabin layout for 313 passengers : economy : pitch : 83.8 [cm] 33.0 [-in]
( 2+4+2 ) seating in 40.0 rows
weight passenger seats : 2021.9 [kg]
weight cabin crew seats : 60.0 [kg]
weight flight crew seats : 63.0 [kg]
weight 2 jump seats in the cockpit :14.0 [kg]
high density seating passengers : 423 [pax] at mainly 9 -abreast seating in 53.5 rows,
pitch 83.8 [cm] 33.0 [-in]
pax density, normal seating : 0.89 [m2/pax], high density seating : 0.66 [m2/pax]
weight 10 lavatories : 307.3 [kg]
Crew rest compartment can be located as an option in the bulk cargo area in the rear fuselage
weight overhead pilot flight crew rest and optional lower deck mobile crew rest compartment
: 264.0 [kg]
weight 11 galleys : 1394.4 [kg]
weight overhead stowage for hand luggage : 109.5 [kg]
weight 3 wardrobe closets : 31.3 [kg]
Singapore Airlines A340-541 9V-SGD
weight 313 entertainment LCD screens in back of seats : 156.5 [kg]
weight 82 windows (41 x 28 cm) made of acrylic glass : 223.9 [kg]
weight 6 (1.93 x 1.07 [m]) Type A main entry doors : 590.7 [kg]
weight 3 (main door size : 1.70 x 2.70 [m]) freight doors (belly) : 865.8 [kg]*
total belly baggage/cargo hold volume : 186.4 [m3]
underfloor belly hold can accommodate : 30 LD3 containers, netto volume : 135.4 [m3]
and : 19.7 [m3] bulk cargo
cabin volume (usable), excluding flight deck : 718 [m3]
passenger compartment volume : 489 [m3]
passenger cabin max width : 5.26 [m] cabin length : 53.66 [m] max cabin height : 2.54 [m]
floor area : 279.0 [m2]
weight cabin facilities : 6102.5 [kg]
safety facilities:
weight 2 type I emergency exits (0.61 x 1.60 [m]): 93.1 [kg]
evacuation time with 423 passengers : 59 [sec]
weight 15 hand fire extinguisher : 44 [kg]
weight cockpit voice recorder (CVR) and flight data recorder (FDR): 20.0 [kg]
weight oxygen masks & oxygen generators (deploy cabin alt.>4267m): 203.5 [kg]
weight emergency flare installation : 10 [kg]
weight 8 emergency evacuation slides : 534.9 [kg]
weight safety equipment & facilities : 905 [kg]
fuselage construction:
fuselage aluminium frame : 38896 [kg]
floor loading (payload/m2): 194 [kg/m2]
weight rear pressure bulkhead : 494.5 [kg]
fuselage covering ( 938.2 [m2] duraluminium 3.83 [mm]) : 9596.2 [kg]
weight floor beams : 3874.0 [kg]
weight cabin furbishing : 4045.8 [kg]
weight cabin floor : 4003.9 [kg]
weight (sound proof) isolation : 606.1 [kg] TO-noise level : 91.0 [EPNdB]
weight 54968 [litre] main central fuel tanks empty : 1099.4 [kg]
weight 21987 [litre] additional central fuel tank (ACT) empty : 549.7 [kg]
weight empty 2008 [litre] potable water tanks : 177.7 [kg]
weight empty waste tank : 66.4 [kg]
weight fuselage structure : 63409.1 [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]
Cockpit of Hi-Fly CS-TFX
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 LCD screens PFD+ND displays) : 16 [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 : 169.0 [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 : 1120 [m3] cabin air refreshment time : 3.7 [min]
weight air-conditioning and pressurization system : 514 [kg]
weight APU / engine starter: 124.0 [kg]
weight lighting : 103.3 [kg]
weight triple redundant 207 bar hydraulic system : 251.9 [kg]
weight engine-driven 40kVA electricity generators : 78.2 [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): 18.0 [kg]
weight systems : 1121.4 [kg]
total weight fuselage : 71707 [kg](19.5 [%])
***************************************************************
total weight aluminium ribs (2491 ribs) : 11985 [kg]
weight engine mounts : 496 [kg]
Innertank 2 34757 litre + innertank 1 24501 litre + outer tank 6145 litre = 65403 x 2 = 130806 liter fuel in the wings. Center tank 54969 litre + rear center tank 19930 litre + optional extra center tank 7970 litre = 82869 litre in the fuselage , tail trim tank : 8361 litre, total : wing tanks 130806 litre + center tanks 82869 + tail trim tank 8361 litre = 222036 litre, without extra tank : 214066 litre (weight variant WV003)
weight 6 wing fuel tanks empty for total 130805 [litre] fuel : 1962 [kg]
weight 859 [litre] vent surge tanks : 103 [kg]
weight wing covering (painted aluminium 4.30 [mm]) : 10149 [kg]
total weight aluminium spars (multi-cellular wing structure) : 14716 [kg]
weight wings : 36851 [kg]
weight wing/square meter : 84.27 [kg]
weight thermal leading-edge anti-icing : 69.8 [kg]
weight ailerons made of carbon fiber reinforced plastic CFRP (16.05 [m2]) : 542.1 [kg]
weight fin (68.30 [m2]) : 2882.7 [kg]
weight rudder (35.95 [m2]) : 1456.5 [kg]
weight 8361 [litre] tail fuel trim tank empty : 209.0 [kg]
weight tailplane (stabilizer) (84.64 [m2]): 3929.9 [kg]
weight elevators (20.31 [m2]): 463.01 [kg]
weight flight control hydraulic servo actuators: 125.9 [kg]
weight trailing-edge double slotted flaps (109.32 [m2]) : 3920.5 [kg]
weight track-mounted light alloy construction leading edge slats (41.48 [m2]) : 935.5 [kg]
weight fly-by-wire operated spoilers of graphite composite construction (15.3 [m2]) : 282.6
[kg]
weight winglets : 200 [kg]
total weight wing construction : 54429 [kg] (31.8 [%])
*******************************************************************
tire pressure main wheels : 16.10 [Bar] (nitrogen), ply rating : 40 PR
tire speed limit : 392 [km/hr]
total tyre footprint : 1.62 [m2]
Runway LCN at MTOW (0.76m radius of rigidity) : 59 [ ]
Aircraft Classification Number (ACN), MTOW on rigid runway and medium
strength (B) : 46 [ ] Can only operate from unpaved runways with reduced weight and
reduced tyre pressure
wheel pressure : 26986.7 [kg]
weight 12 Dunlop 55 x 21 main wheels (1400 [mm] by 530 [mm]) : 3664.7 [kg]
weight 2 nose wheels : 305.4 [kg]
weight hydraulic disc wheel-brakes : 225.0 [kg]
weight Duplex anti-skid units : 12.6 [kg]
weight oleo-pneumatic shock absorbers : 300.0 [kg]
weight wheel hydraulic operated retraction system : 2932.4 [kg]
weight undercarriage struts (six-wheel bogies) with axle 7075.4 [kg]
total weight landing gear : 14515.6 [kg] (3.9 [%]
*******************************************************************
********************************************************************
calculated empty weight : 166032 [kg](45.1 [%])
weight oil for 22.4 hours flying : 211.1 [kg]
weight lifejackets : 140.8 [kg]
weight 6 life rafts : 195.6 [kg]
weight catering : 1291.1 [kg]
weight water : 1776.6 [kg]
weight crew : 1215 [kg]
weight crew luggage, nav. chards, flight doc., miscell. items : 138 [kg]
operational weight empty : 171000 [kg] (46.5 [%])
********************************************************************
weight 313 passengers : 24101 [kg]
weight luggage : 5008 [kg]
weight cargo : 24891 [kg] (cargo + luggage/m3 belly : 154 [kg/m3])
zero fuel weight (ZFW): 225000 [kg](61.1 [%])
weight fuel for landing (1.8 hours flying) : 15000 [kg]
max. landing weight (MLW): 240000 [kg](65.2 [%])
max. fuel weight : 339624 [kg] (92.3 [%])
payload with max fuel : 305 passengers + luggage 28376 [kg]
published maximum take-off weight : 368000 [kg] (100.0 [%])
State of Kuwait A340-541
calculation : * 4 * (engine power)
power loading (Take-off) : 371 [kg/KN]
power loading (Take-off) 1 PUF: 495 [kg/KN]
max. total take-off power : 992.0 [KN]
calculation : *5* (loads)
manoeuvre load : 0.8 [g] at 9000 [m]
limit load : 2.5 [g] ultimate load : 3.8 [g] load factor : 1.0 [g]
design flight time : 8.25 [hours]
design cycles : 10490 sorties, design hours : 86542 [hours]
max. wing loading (MTOW & flaps retracted) : 842 [kg/m2]
wing stress (2 g) during operation : 161 [N/kg] at 2g emergency manoeuvre
calculation : *6* (angles of attack)
angle of attack zero lift : -1.70 ["]
max. angle of attack (stalling angle, clean) : 12.55 ["]
max. angle of attack (full flaps) : 16.50 ["]
angle of attack at max. speed : 3.54 ["]
calculation : *7* (lift & drag ratios
lift coefficient at angle of attack 0° : 0.15 [ ]
lift coefficient at max. speed : 0.46 [ ]
lift coefficient at max. angle of attack (clean): 1.26 [ ]
max. lift coefficient full flaps : 2.11 [ ]
drag coefficient at max. speed : 0.0278 [ ]
drag coefficient at econ. cruise speed : 0.0346 [ ]
induced drag coefficient at econ. cruise speed : 0.0190 [ ]
drag coefficient (zero lift) : 0.0156 [ ]
lift/drag ratio at econ. speed : 16.63 [ ]
calculation : *8* (speeds
take-off decision speed (V1) : 263 [km/u] (142 [kt])
take-off rotation speed (VR) : 312 [km/u] (168 [kt])
Thay Airlines A340-542 HS-TLC c/n 698, the A340-542 had an higher gross-weight of 380t and more strong engines.
minimum unstick speed (Vmu) at TO angle 11.0 ° : 319 [km/u] (172 [kt])
lift-off speed (VLOF) : 344 [km/u] (186 [kt]) at pitch angle : 9.3 [°]
take-off safety speed (V2) : 347 [km/u] (187 [kt])
flap retraction speed (V3) at 500m (OW loaded : 359440 [kg]): 390 [km/u] (211 [kt])
steady initial climb speed (V4) : 372 [km/u] (201 [kt])
climb speed (to FL150 with 56 [%] power) : 779 [km/hr] (421 [kt])
max. endurance speed (Vbe): 552 [km/u] min. fuel/hr : 8518 [kg/hr] at height : 2438 [m]
max. range speed (Vbr): 893 [km/u] (0.83 [mach]) min. fuel consumption : 9.60 [kg/km] at
cruise height : 10058 [m]
max. cruising speed : 895 [km/hr] (483 [kt]) at 11200 [m] (power:16 [%])
max. operational speed (Mmo) : 930 [km/hr] (Mach 0.86 ) at 9450 [m] (power:17 [%])
airflow at cruise speed per engine : 422.6 [kg/s]
speed of thrust jet : 1236 [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): 339 [km/u] (183 [kt])
stalling speed clean at 500 [m] height at Max.Landing Weight : 240000 [kg]): 308 [km/u]
(166 [kt])
final approach speed (landing speed) at sea-level with full flaps VREF (max. landing weight):
275 [km/u] (148 [kt])
ICAO Aircraft Approach Category (APC) : D
stalling speed at sea-level with full flaps VSO (max. landing weight): 212 [km/u] (114 [kt]
rate of climb at sea-level ROC (loaded, 56 % power) : 1399 [m/min]
rate of climb at sea-level ROC (loaded, 75 % power) : 2300 [m/min]
rate of climb at 1000 [m] with 1 engine out (PUF/MTOW, 100 % power on remaining
engines) : 1878 [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)
high wheel pressure, can only take off from paved runways
ICAO Aerodrome Reference Code : 4E
Brake kinetic energy capacity : 4009 [KW]
Take-off runway length at MTOW 368000 kg, sea level : 3150 [m]
FAR TO balanced runway length (TOFL) requirement at TOW 368000 [kg] standard day at
SL (distance to 10.7m height x 1.15): 3151 [m]
Landing filed length at MLW 240.000 kg at sea-level : 2050 [m]
+++ FAA certification landing distance : +++
landing weight : 240000 [kg], TE flap setting : 30 [°]
runway condition : dry , landing over 50ft (15m) at threshold at sea-level
without use of thrust reversers
FAA approved landing field length : 2058 [m] (6751 [ft])
landing distance (C.A.R.) from 15 [m] at SL, wet runway: 2363 [m] (7751 [ft])
max. lift/drag ratio : 18.06 [ ]
climb to 5000 [m] with max payload : 3.31 [min]
climb to 10000 [m] with max payload : 10.17 [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: 359440 [kg] ) : 13500 [m]
calculation *10* (action radius & endurance)
range with max. payload: 13753 [km] with 54000.0 [kg] max. useful load (84.8 [%] fuel)*
range with high density pax: 15601 [km] with 423 passengers (93.5 [%] fuel)*
range with typical two-class pax: 16942 [km] with 313 passengers (99.6 [%] fuel)*
Range with max payload 54000 kg : 7000nm > 13000 km, range with max fuel : 9000nm > 16670km (payload 25000 kg > MTOW 364000 kg), ferry range : 9800 nm > 18150 km. Range with assumed usable fuel capacity 214808 litre WV000
range with max.fuel : 17040 [km] with 15 crew and 305 passengers and 100.0 [%] fuel*
ferry range (calculated): 19328 [km] with 3 crew and zero payload (100.0 [%] fuel)*
max range theoretically with additional fuel tanks total 256102 [litre] fuel : 21635 [km]*
* calculated ranges without fuel reserves
Available Seat Kilometres (ASK) : 6504092 [paskm]
useful load with range 1000km : 54000 [kg]
useful load with range 1000km : 423 passengers
production (theor.max load): 48330 [tonkm/hour]
production (useful load): 48330 [tonkm/hour]
production (passengers): 361916 [paskm/hour]
oil and fuel consumption per tonkm : 0.177 [kg]
calculation *11* (operating cost)
fuel cost per hour (10904 [litre]):6542 [eur] (33 [pax-km/litre fuel])
fuel cost per seat 1000km flight (404 [pax] 2-class seating): 18.08 [eur/1000PK]
oil cost per hour: 37 [eur]
crew cost per hour : 2100 [eur]
list price 2024 : 191 [mln USD]
average flying hours in 1 year : 4500 [hours] technical life : 19 [year]
real average service life : 20 [years]
Hi-Fly A340-500 CS-TFX at Vantaa, Finland, January 2016
depreciation - 24 [years] to 10% residual value
economic hours (expected total flying hours) : 108000 [hours]
financing interest per flying hour : 955 [EUR]
write off per flying hour : 1762 [EUR]
time between engine failure : 6296 [hr]
can continue fly on 3 engines, low risk for emergency landing for PUF
workhours per day : 13.45 [hr]
no fatalities during service life > 100%%safe
average flight hours till crash : 3.06 [mln hr] (680 service years)
safe flight hours till fatality : 3058470 [hr] (679.7 service years)
reservation pax liability/flying hour : 0.04 [SDR*] (0.05 [eur])
insurance cost per hour : 287 [eur] insurance rate : 1.8 [%]
engine maintenance cost per hour : 2293.3 [eur]
wing maintenance cost per hour : 116.6 [eur]
fuselage maintenance cost per hour : 27.57 [eur]
tire life (time till worn out) : 122 [cycles]
maintenance cost per hour (excluding engines): 3437 [eur]
direct operating cost per hour: 17414 [eur], DOC per km : 20.13 [eur]
DOC per seat 1000km flight (404 [pax] 2-class seating): 48.12 [eur/1000PK]
DOC per seat 1000km flight (high density seating): 46.02 [eur/1000PK]
DOC per kg cargo for a 1000km flight : 0.36 [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 : 5.65 [eur/pax]
airport landing fee / passenger : 5.65 [eur/pax]
retour ticket price 1000km trip : 177.82 [eur/pax]
price retour ticket Schiphol-Barcelona : 204.28 [eur/pax]*
* this needs more calculation, with the ultra-long range, DOC calculations don’t compare with shorthaul airliners.
Emirates A340-541 A6-ERG c/n 608 landing at Hong Kong Chek Lap Kok (HKG), July 2014.
The aircraft had a tail strike while taking of from Melbourne (MEL), Canada on 20 March 2009. The take-off weight was incorrect entered into the electronic flight bag. With the long fuselage a tail strike can happen rather easy when rotating premature.
accidents with fatalities > there have been no fatal accidents with an A340-500
Literature :
A340_TCDS_EASA.A.015_-_Issue_27.pdf
https://contentzone.eurocontrol.int/aircraftperformance/default.aspx ?
https://www.airbus.com/en/airport-operations-and-technical-data/aircraft-characteristics
ac_a340-500_600_jul2023.pdf (airbus.com)
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
Nigerian Arik Air A340-542 CS-TFW c/n 910 landing at London (LHR), May 2011
(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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