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weight and performance calculations for the Airbus A340-300 WV000
Edelweiss A340-313 HB-JMF c/n 561 at Zurich Kloten (ZRH), August 2023
Airbus A340-300 WV000
role : wide-body long-range airliner
importance : ***
first flight : 25 October 1991 operational : March 1993 (Air France)
country : EU-consortium
ICAO aircraft type designator : A343
production : 218 aircraft at Colomiers, near Toulouse, the wings were produced by BAE in
Broughton, UK.
general information :
This is the 2nd version of the A340. The fuselage is 4.26m longer and it can now carry more passengers, but over a shorter distance. The airframe and wing are similar to the A330. With its four engines it can bypass twin-jetliner ETOPS regulations for crossing oceans. It has a “glass cockpit” with fly-by-wire controls. The A340 was the first long range Airbus. The wings were designed and manufactured by BAe, which developed a long slender wing with a high aspect ratio for a higher aerodynamic efficiency. During testing it was noticed that the wings were not stiff enough to carry the outboard engines at cruising speed without warping and fluttering . To alleviate this, an underwing bulge called a plastron was developed to correct airflow problems around the engine pylons and to add stiffness. Airliners used the A340 often as replacement for there aging Boeing 747’s. By 2005 sales for the A340 started to decline due to the relaxing of the twin-engine ETOPS requirements and the A340 got more competition from the Boeing 777 and A330, the twin-engine airliners having lower operating cost. In 2008 jet fuel prices doubled making ultra long range flights more expensive, and airlines cancelled there plus 15 hour flying time routes. For this long routes the A340 was more a “flying tanker with a few passengers”, as Air France-KLM chief executive Pierre-Henri Courgeon referred to the A340. In November 2011 Airbus announced the end of the A340 program, all firm orders had been delivered at that moment. The unit cost of an A340-300 was US$238.0M in 2011 ($322.4M today). By the end of 2021, the global A340 fleet had completed more than 2.5 million flights over 20 million block hours (8 hours per flight) and carried over 600 million passengers with no fatalities (average 240 pax/flight) . As of March 2023, there were 203 A340 aircraft in service with 45 operators worldwide. Lufthansa is the largest A340 operator with 27 aircraft in its fleet.
At first the A340 was indicated as B11 and later TA11, TA standing for “Twin Aisle”. In January 1986 the final name A340 was given to the design. The A330 and A340 programmes were jointly launched on 5 June 1987, just prior to the Paris Air Show.
primary users : Lufthansa (30 A340-300E’s) , Air France, Swiss, Air Canada, Iberia, TAP Air
Portugal, Cathay Pacific, China Airlines, SriLankan Airlines, SAS, THY, Virgin Atlantic,
Gulf Air, Aerolineas Argentinas, Air Belgium, Kuwait Airways, Singapore Airways (20)
Accommodation:
flight crew : 2 cabin crew : 9
passengers : seating for 335 in two class : 30 business class and 305 economy class seats
( 32 -in pitch) exit limit : 440 passengers, high density seating for 423 passengers
engine : 4 CFM International CFM56-5C2 turbofan engines of 138.8 [KN] (31203 [lbf])
dimensions :
wingspan : 60.3 [m], length overall: 63.66 [m], length of fuselage : 62.84 [m]
height : 16.74 [m] wing area : 363.1 [m^2] fuselage exterior width : 5.64 [m]
weights :
operating empty weight : 123000 [kg] max. structural payload : 51000 [kg]
Zero Fuel weight (ZFW) : 174000 [kg] max. landing weight (MLW) : 186000 [kg]
max. take-off weight : 253430 [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 : 12500 [m]
range with max fuel and MTOW : 13705 [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 : 2.50 [m]
taper ratio : 0.238 [ ]
Kuwait Airways A340-313 9K-ANA c/n 089 at Schiphol airport, it was taken into service on the route Schiphol – Frankfurt – Karachi in July 1995.
mean wing chord : 6.02 [m]
wing aspect ratio : 10.01 []
Oswald factor (e): 0.704 []
seize (span*length*height) : 64260 [m^3]
calculation : *2* (fuel consumption)
oil consumption : 16.7 [kg/hr]
fuel consumption (econ. cruise speed) : 6832.0 [kg/hr] (8703.2 [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 371.4 litre oil tank : 31.57 [kg]
oil tank filled with 3.5 litre oil : 3.1 [kg]
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 : 213.5 [kg]
weight engine cowling : 1443.5 [kg]
weight thrust reversers : 832.8 [kg]
total weight propulsion system : 13782 [kg](5.4 [%])
***************************************************************
Accommodation cabin facilities:
typical 2-class cabin layout for 335 passengers : economy : pitch : 81.3 [cm] 32.0 [-in]
( 2+4+2 ) seating in 42.4 rows
weight passenger seats : 1859.1 [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 : 423 [pax] at mainly 9 -abreast seating in 53.5 rows,
pitch 77.2 [cm] 30.4 [-in]
pax density, normal seating : 0.77 [m2/pax], high density seating : 0.61 [m2/pax]
weight 8 lavatories : 250.9 [kg]
weight overhead pilot flight crew rest and optional lower deck mobile crew rest compartment
: 228.0 [kg]
weight 8 galleys : 1311.5 [kg]
weight overhead stowage for hand luggage : 117.2 [kg]
weight 3 wardrobe closets : 33.5 [kg]
SAS A340-300 cabin interior 2+4+2 seating
weight 335 entertainment LCD screens in back of seats : 223.4 [kg]
weight 87 windows (41 x 28 cm) made of acrylic glass : 237.2 [kg]
weight 6 (1.93 x 1.07 [m]) Type A main entry doors : 431.4 [kg]
weight 3 (main door size : 1.70 x 2.70 [m]) freight doors (belly) : 632.3 [kg]*
total belly baggage/cargo hold volume : 196.7 [m3]
underfloor belly hold can accommodate : 32 LD3 containers, netto volume : 143.7 [m3]
and : 19.7 [m3] bulk cargo
cabin volume (usable), excluding flight deck : 661 [m3]
passenger compartment volume : 372 [m3]
passenger cabin max width : 5.26 [m] cabin length : 49.39 [m] max cabin height : 2.54 [m]
floor area : 256.6 [m2]
weight cabin facilities : 5425.7 [kg]
safety facilities:
weight 2 type I emergency exits (0.61 x 1.60 [m]): 68.0 [kg]
evacuation time with 423 passengers : 59 [sec]
weight 16 hand fire extinguisher : 47 [kg]
weight cockpit voice recorder (CVR) and flight data recorder (FDR): 20.0 [kg]
weight oxygen masks & oxygen generators (deploy cabin alt.>4267m): 217.8 [kg]
weight emergency flare installation : 10 [kg]
weight 8 emergency evacuation slides : 572.5 [kg]
weight safety equipment & facilities : 935 [kg]
fuselage construction:
fuselage aluminium frame : 26459 [kg]
floor loading (payload/m2): 199 [kg/m2]
weight rear pressure bulkhead : 436.5 [kg]
fuselage covering ( 873.9 [m2] duraluminium 3.38 [mm]) : 7879.2 [kg]
weight floor beams : 3877.9 [kg]
weight cabin furbishing : 3719.6 [kg]
weight cabin floor : 3681.6 [kg]
weight (sound proof) isolation : 637.4 [kg] TO-noise level : 94.8 [EPNdB]
weight 42422 [litre] main central fuel tanks empty : 848.4 [kg]
weight empty 1888 [litre] potable water tanks : 167.1 [kg]
weight empty waste tank : 50.1 [kg]
weight fuselage structure : 47756.9 [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]
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]
Lufthansa A340-300 cockpit
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 : 1057 [m3] cabin air refreshment time : 3.5 [min]
weight air-conditioning and pressurization system : 513 [kg]
weight APU / engine starter: 69.4 [kg]
weight lighting : 110.6 [kg]
Lufthansa A340-311 D-AIGK c/n 056 at Boston, May 2009
weight triple redundant 207 bar hydraulic system : 214.2 [kg]
weight engine-driven 40kVA electricity generators : 83.8 [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): 17.1 [kg]
weight systems : 1039.7 [kg]
total weight fuselage : 55317 [kg](21.8 [%])
***************************************************************
total weight aluminium ribs (2052 ribs) : 8626 [kg]
weight engine mounts : 278 [kg]
Center tank : 42420 litre, inner tank 42775 litre, outer tank 3650 litre > total wing tanks = 92850 litre, trim tank 6230 litre > total : 42420 + 2x(42775+3650) + 6230 = 141500 litre.
With optional additional center tank 11400 litre > total 152900 litre
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 3.69 [mm]) : 7243 [kg]
total weight aluminium spars (multi-cellular wing structure) : 9996 [kg]
weight wings : 25865 [kg]
weight wing/square meter : 71.23 [kg]
weight thermal leading-edge anti-icing : 66.3 [kg]
weight ailerons made of carbon fiber reinforced plastic CFRP (15.26 [m2]) : 435.6 [kg]
weight fin (61.68 [m2]) : 2201.6 [kg]
weight rudder (32.47 [m2]) : 1112.4 [kg]
weight 6230 [litre] tail fuel trim tank empty : 155.7 [kg]
weight tailplane (stabilizer) (79.32 [m2]): 3114.2 [kg]
weight elevators (19.04 [m2]): 366.90 [kg]
weight flight control hydraulic servo actuators: 107.1 [kg]
weight trailing-edge double slotted flaps (70.80 [m2]) : 2148.6 [kg]
weight track-mounted light alloy construction leading edge slats (36.64 [m2]) : 699.5 [kg]
weight fly-by-wire operated spoilers of graphite composite construction (12.9 [m2]) : 202.3
[kg]
weight winglets : 200 [kg]
total weight wing construction : 38413 [kg] (31.2 [%])
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tire pressure main wheels : 13.1 [Bar] (nitrogen), ply rating : 27 PR
tire speed limit : 389 [km/hr]
total tyre footprint : 1.28 [m2]
Runway LCN at MTOW (0.76m radius of rigidity) : 51 [ ]
Aircraft Classification Number (ACN), MTOW on rigid runway and medium subgrade strength (B) : 34 [ ]
Can also operate from unpaved runways subgrade B
wheel pressure : 22301.8 [kg]
weight 10 Dunlop 55 x 21 main wheels (1400 [mm] by 530 [mm]) : 2089.6 [kg]
weight 2 nose wheels : 209.0 [kg]
weight hydraulic disc wheel-brakes : 174.0 [kg]
weight Duplex anti-skid units : 10.8 [kg]
weight oleo-pneumatic shock absorbers : 232.0 [kg]
weight wheel hydraulic operated retraction system : 2208.6 [kg]
total weight landing gear : 10932.6 [kg] (4.3 [%]
*******************************************************************
********************************************************************
calculated empty weight : 118444 [kg](46.7 [%])
weight oil for 18.7 hours flying : 323.0 [kg]
weight lifejackets : 150.8 [kg]
weight 6 life rafts : 209.4 [kg]
weight catering : 1214.4 [kg]
weight water : 1671.0 [kg]
weight crew : 891 [kg]
weight crew luggage, nav. chards, flight doc., miscell. items : 96 [kg]
operational weight empty : 123000 [kg] (48.5 [%])
********************************************************************
weight 335 passengers : 25795 [kg]
weight luggage : 5360 [kg]
weight cargo : 19845 [kg] (cargo + luggage/m3 belly : 121 [kg/m3])
zero fuel weight (ZFW): 174000 [kg](68.7 [%])
weight fuel for landing (1.8 hours flying) : 12000 [kg]
max. landing weight (MLW): 186000 [kg](73.4 [%])
max. fuel weight : 233402 [kg] (92.1 [%])
payload with max fuel : 215 passengers + luggage 20028 [kg]
published maximum take-off weight : 253430 [kg] (100.0 [%])
calculation : * 4 * (engine power)
power loading (Take-off) : 456 [kg/KN]
power loading (Take-off) 1 PUF: 609 [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 : 7.25 [hours]
design cycles : 11090 sorties, design hours : 80402 [hours]
max. wing loading (MTOW & flaps retracted) : 698 [kg/m2]
wing stress (2 g) during operation : 166 [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 : 2.81 ["]
Air Belgium OO-ABB A340-313 c/n 844 at Martinique, Fort-de-France (FDF), March 2022
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 : 0.0306 [ ]
drag coefficient at econ. cruise speed : 0.0319 [ ]
induced drag coefficient at econ. cruise speed : 0.0114 [ ]
drag coefficient (zero lift) : 0.0205 [ ]
lift/drag ratio at econ. speed : 13.15 [ ]
calculation : *8* (speeds
take-off decision speed (V1) : 257 [km/u] (139 [kt])
take-off rotation speed (VR) : 270 [km/u] (146 [kt])
lift-off speed (VLOF) : 291 [km/u] (157 [kt]) at pitch angle : 14.9 [°]
take-off safety speed (V2) : 293 [km/u] (158 [kt])
flap retraction speed (V3) at 500m (OW loaded : 246598 [kg]): 360 [km/u] (194 [kt])
steady initial climb speed (V4) : 319 [km/u] (172 [kt])
climb speed (to FL150 with 56 [%] power) : 573 [km/hr] (309 [kt])
max. endurance speed (Vbe): 449 [km/u] min. fuel/hr : 6551 [kg/hr] at height : 1829 [m]
max. range speed (Vbr): 866 [km/u] (0.82 [mach]) min. fuel consumption : 7.87 [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:28 [%])
airflow at cruise speed per engine : 236.5 [kg/s]
speed of thrust jet : 1367 [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): 330 [km/u] (178 [kt])
stalling speed clean at 500 [m] height at Max.Landing Weight : 186000 [kg]): 300 [km/u]
(162 [kt])
final approach speed (landing speed) at sea-level with full flaps VREF (max. landing weight):
266 [km/u] (144 [kt])
ICAO Aircraft Approach Category (APC) : D
stalling speed at sea-level with full flaps VSO (max. landing weight): 205 [km/u] (111 [kt]
rate of climb at sea-level ROC (loaded, 56 % power) : 692 [m/min]
rate of climb at sea-level ROC (loaded, 75 % power) : 1203 [m/min]
rate of climb at 1000 [m] with 1 engine out (PUF/MTOW, 100 % power on remaining engines) : 1008 [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 : 3117 [KW]
Take-off runway length at mtow 253430 kg (= 558700 lb), at sea level, standard day : 9000 ft > 2743 m
FAR TO balanced runway length (TOFL) requirement at TOW 253430 [kg] standard day at
SL (distance to 10.7m height x 1.15): 2743 [m]
Landing field length at MLW 186000 kg (410000 lb): 6250 ft > 1905 m
+++ FAA certification landing distance : +++
landing weight : 186000 [kg], TE flap setting : 37 [°]
runway condition : dry , landing over 50ft (15m) at threshold at sea-level
without use of thrust reversers
FAA approved landing field length : 1908 [m] (6260 [ft])
landing distance (C.A.R.) from 15 [m] at SL, wet runway: 2189 [m] (7181 [ft])
max. lift/drag ratio : 16.45 [ ]
climb to 5000 [m] with max payload : 6.68 [min]
climb to 10000 [m] with max payload : 20.56 [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: 246598 [kg] ) : 14500 [m]
calculation *10* (action radius & endurance)
range with max. payload: 9459 [km] with 51000.0 [kg] max. useful load (71.9 [%] fuel)*
range with high density pax: 11085 [km] with 423 passengers (82.5 [%] fuel)*
range with typical two-class pax: 12259 [km] with 335 passengers (89.9 [%] fuel)*
Range with max fuel : 7400 nm > 13705 km, max structural payload : 112000 lbs > 50803 kg, zfw 377500 lbs = 171234 kg > OEW = 120431 kg. Range without additional 11400 litre center tank.
range with max.fuel : 13911 [km] with 11 crew and 215 passengers and 100.0 [%] fuel*
ferry range (calculated): 15126 [km] with 2 crew and zero payload (100.0 [%] fuel)*
max range theoretically with additional fuel tanks total 170757 [litre] fuel : 17620 [km]*
* calculated ranges without fuel reserves
Available Seat Kilometres (ASK) : 4401020 [paskm]
useful load with range 1000km : 51000 [kg]
useful load with range 1000km : 423 passengers
production (theor.max load): 44880 [tonkm/hour]
production (useful load): 44880 [tonkm/hour]
production (passengers): 327205 [paskm/hour]
oil and fuel consumption per tonkm : 0.153 [kg]
calculation *11* (operating cost)
fuel cost per hour (8703 [litre]):5221 [eur] (38 [pax-km/litre fuel])
fuel cost per seat 1000km flight (372 [pax] 2-class seating): 15.96 [eur/1000PK]
oil cost per hour: 69 [eur]
crew cost per hour : 1500 [eur]
list price 2024 : 136 [mln USD]
average flying hours in 1 year : 4500 [hours] technical life : 18 [year]
SriLankan Airlines made the last flight with the A340-300 in Januari 2016 after 21 years in service
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 : 681 [EUR]
write off per flying hour : 1257 [EUR]
time between engine failure : 5713 [hr]
can continue fly on 3 engines, low risk for emergency landing for PUF
workhours per day : 13.60 [hr]
no fatalities during service life > 100%% safe
average flight hours till crash : 19.62 [mln hr] (4360 service years)
Singapore Airlines A340-313 9V-SJA c/n 123, this is an A340-300E with higher MTOW at 275t and more powerful CFM56-5C4 engines. Range with 295 passengers is 13500 km.
safe flight hours till fatality : 19620000 [hr] (4360.0 service years)
reservation pax liability/flying hour : 0.01 [SDR*] (0.01 [eur])
insurance cost per hour : 32 [eur] insurance rate : 0.3 [%]
engine maintenance cost per hour : 957.9 [eur]
wing maintenance cost per hour : 110.2 [eur]
fuselage maintenance cost per hour : 33.25 [eur]
tire life (time till worn out) : 89 [cycles]
maintenance cost per hour (excluding engines): 2384 [eur]
direct operating cost per hour: 12103 [eur], DOC per km : 13.90 [eur]
DOC per seat 1000km flight (372 [pax] 2-class seating): 36.99 [eur/1000PK]
DOC per seat 1000km flight (high density seating): 32.53 [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 : 4.16 [eur/pax]
airport landing fee / passenger : 4.16 [eur/pax]
retour ticket price 1000km trip : 146.82 [eur/pax]
price retour ticket Schiphol-Barcelona : 167.17 [eur/pax]
Air France A340-313 F-GLZQ c/n 289, it was written of in a landing accident at Toronto, August 2005
accidents with fatalities > there have been no fatal accidents with an A340-300
Literature :
Aircraft Performance Database > A343 (eurocontrol.int)
ac_a340-200_300_jul2023.pdf (airbus.com)
Luchtvaart March’92 page 81, sep’90 page 257, jun’92 page 173, nov’93 page 414
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
“Red nose” Swiss A340-313 HB-JMA c/n 538
(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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