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weight and performance calculations for the Airbus A321-100 (CFM56-5B1)
Austrian Airlines A321-111 OE-LBB “Pinzgau” c/n 570 with CFM56-5B1 engines
Airbus A321-100 (CFM56-5B1)
role : jet airliner
importance : ****
first flight : 11 March 1993 operational : March 1994
country : EU-consortium
ICAO aircraft type designator : A321
production : 90 A321-100 aircraft, total A321 production : status oct.2022 : 2646 aircraft
final assembly in Hamburg, Germany.
general information :
In November 1989, an extended version of the A320 was launched, which has 24% more seats and 40% more cargo space.
A plug of 4.27m in front of the wing and one of 2.67m behind the wing was inserted, bringing the length to 44.51m. The A321-100 had a shorter range then the A320 due to its heavier weight. Soon it was followed on the production line by the A321-200 which had additional fuel tanks to improve range.
Airlines could also choose for the IAE V2530-A5 engine.
primary users : Lufthansa (launch customer 19+1), Austrian Airlines (3+2), Air Macau (4), All Nippon Airways (2+5), Asiana (2+10), CAAC (13), Transasia(6), Air Alfa (2+1), Air France (6+1), Alitalia (20+5), Onur Air (4), Swissair (9+3)
Accommodation:
flight crew : 2 cabin crew : 6
passengers : seating for 185 in two class : 16 business class and 169 economy class seats ( 32 -in pitch) high density seating for max 220 passengers (equal to exit limit)
engine : 2 GE-Snecma CFM56-5B1 turbofan engines of 133.4 [KN] (29989 [lbf])
Tail-angle measured : 9°
dimensions :
wingspan : 34.09 [m], length overall: 44.51 [m], length of fuselage : 44.51 [m] height : 11.8 [m] wing area gross : 122.4 [m^2] fuselage exterior width : 3.95 [m]
weights :
empty weight : 45822 [kg]
operating empty weight : 47775 [kg] max. structural payload : 21725 [kg]
Zero Fuel weight (ZFW) : 69500 [kg] max. landing weight (MLW) : 73500 [kg]
max. take-off weight : 83000 [kg] weight usable fuel : 18879 [kg] (24050 [litres])
performance :
Max. operating Mach number (Mmo) : 0.820 [Mach] (895 [km/hr]) at 9000 [m]
critical Mach speed : 0.78 [Mach]
max. cruising speed : 860 [km/hr] (Mach 0.80 ) at 10000 [m] (29 [%] power)
economic cruising speed : 837 [km/hr] (Mach 0.78 ) at 10000 [m]
service ceiling : 11900 [m]
range with max fuel and MTOW : 4550 [km] (ATA domestic fuel reserves - 370.0 [km] alternate)
description :
*Cantilever low-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 main spar fail-safe wing structure with double slotted trailing edge flaps with full-span slotted LE flaps (slats) ,with spoilers and airbrakes and with wingtip fences
airfoil : Airbus average thickness/chord ratio : 10.0 [%], sweep angle 3/4 chord: 25.0 [°]
incidence at root : 3.00 [°], dihedral : 5.2 [°]
*Fuselage : Pressurized aluminium-alloy stressed-skin structure of elliptical 0 section
calculation : *1* (dimensions)
wing chord at root : 6.07 [m]
wing chord at tip : 1.50 [m]
taper ratio : 0.247 [ ]
mean wing chord : 3.59 [m]
wing aspect ratio : 9.49 []
Oswald factor (e): 0.706 []
seize (span*length*height) : 17905 [m^3]
calculation : *2* (fuel consumption)
oil consumption : 0.8 [kg/hr]
fuel consumption (econ. cruise speed) : 3211.8 [kg/hr] (4091.4 [litre/hr]) at 20 [%] power
distance flown for 1 kg fuel : 0.26 [km/kg] at 10000 [m] height, sfc : 60.8 [kg/KN/h]
total fuel capacity : 24050 [litre] (18879 [kg])
calculation : *3* (weight)
weight engine(s) dry : 4760.0 [kg] = 17.84 [kg/KN]
weight 11.9 litre oil tank : 1.01 [kg]
oil tank filled with 1.7 litre oil : 1.5 [kg]
oil in engine 3.3 litre oil : 2.9 [kg]
weight all fuel lines and pumps containing 72 litres fuel : 60.9 [kg]
weight engine cowling : 693.7 [kg]
weight thrust reversers : 400.2 [kg]
total weight propulsion system : 5920 [kg](7.1 [%])
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Accommodation cabin facilities:
typical 2-class cabin layout for 185 passengers : economy : pitch : 81.3 [cm] 32.0 [-in] ( 3+3 ) seating in 32.2 rows
business class pitch : 91.4 [cm] 36.0 [-in] at 4 -abreast
weight passenger seats (width 53.7 [cm]) : 936.9 [kg]
weight cabin crew seats : 30.0 [kg]
weight flight crew seats : 42.0 [kg]
high density seating passengers : 220 [pax] at mainly 6 -abreast seating in 37.9 rows, pitch 73.7 [cm] 29.0 [-in]
pax density, normal seating : 0.689 [m2/pax], high density seating : 0.579 [m2/pax]
weight 4 lavatories : 117.2 [kg]
weight 3 galleys : 132.3 [kg]
Lufthansa A321 interior
weight overhead stowage for hand luggage (total : 10.5 [m3] = 218 55x35x25cm carry-on trolleys) : 163.5 [kg]
weight 185 entertainment LCD screens in back of seats : 92.5 [kg]
weight 66 windows (47x38cm) made of acrylic glass: 282.0 [kg]
weight 4 (1.85 x 0.81 [m]) main entry doors : 167.5 [kg]
The A321 can take 10 AKH type ULD (unit load device) in it’s belly.
weight 2 (main door size : 1.25 x 1.82 [m]) freight doors (belly) : 138.2 [kg]*
total usable belly baggage/cargo hold volume : 52.0 [m3]
cabin volume (usable), excluding flight deck : 248 [m3]
passenger compartment volume : 155 [m3]
passenger cabin max width : 3.70 [m] cabin length : 34.44 [m] max cabin height : 2.22 [m]
floor area : 115.7 [m2]
weight cabin facilities : 2102.2 [kg]
safety facilities:
weight 4 type I emergency exits (0.76 x 1.52 [m]): 129.2 [kg]
evacuation time with 220 passengers : 41 [sec]
weight 4 hand fire extinguisher : 13 [kg]
weight cockpit voice recorder (CVR) and flight data recorder (FDR): 20.0 [kg]
weight oxygen masks & oxygen generators (deploy cabin alt.>4267m): 120.2 [kg]
weight emergency flare installation : 10 [kg]
weight 8 emergency evacuation slides : 166.1 [kg]
weight safety equipment & facilities : 459 [kg]
fuselage construction:
fuselage aluminium frame : 10379 [kg]
floor loading (payload/m2): 188 [kg/m2]
weight rear pressure bulkhead : 174.2 [kg]
fuselage covering ( 427.0 [m2] duraluminium 2.72 [mm]) : 3053.7 [kg]
weight paint fuselage : 89.7 [kg]
weight aluminium floor beams : 671.5 [kg]
weight cabin furbishing : 1068.4 [kg]
weight cabin floor : 1636.3 [kg]
weight (sound proof) isolation : 328.2 [kg] TO-noise level : 97.0 [EPNdB]
weight 8250 [litre] main central fuel tank empty : 161.8 [kg]
weight empty 180 [litre] potable water tanks : 15.9 [kg]
weight empty waste tank : 9.2 [kg]
weight fuselage structure : 17587.9 [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]
weight VOR/ILS,RMI,DME,radio altimeter, ASI, time clock : 20.0 [kg]
weight Cat IIIB auto-landing system : 10.0 [kg]
Cockpit of Lufthansa A321-131 D-AIRF
weight EFIS (4 Rockwell Collins CRT screens ADI/PFD+HSI/ND displays) : 20 [kg]
weight ground proximity warning system (GPWS) : 6 [kg]
weight engine monitoring system ECAM : 24 [kg]
weight EICAS + 1 LCD display : 18 [kg]
weight reserve ADI, ASI, alti-meter, compass, engine temp. and rpm indicators : 15 [kg]
weight avionics : 138.0 [kg]
Systems:
Air-conditioning and pressurization system maintains sea level conditions up to 6400 [m]
and gives equivalent of 2440 [m] at 12200 [m]. pressure differential : 0.58 [bar] (kg/cm2)
pressurized fuselage volume : 418 [m3] cabin air refreshment time : 3.0 [min]
weight air-conditioning and pressurization system : 238 [kg]
weight APU / engine starter : 66.7 [kg]
weight lighting : 61.1 [kg]
weight 207 bar hydraulic system : 89.5 [kg]
weight engine-driven 40kVA electricity generators : 46.2 [kg]
weight ram air turbine for emergency electric power : 5.0 [kg]
weight 22Ah battery : 28.5 [kg]
weight controls (sidestick FBW): 11.8 [kg]
weight systems : 541.9 [kg]
total weight fuselage : 20829 [kg](25.1 [%])
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total weight aluminium ribs (44 ribs) : 2862 [kg]
weight engine mounts : 133 [kg]
8250 litre central tank + 2x 7750 litre wing tanks = 23750 liter totall
Total Fuel with CFM engines : 24050 liter, with IAE engines 23700 liter
weight 2 wing fuel tanks empty for total 15500 [litre] fuel : 239 [kg]
weight 96 [litre] vent surge tanks : 12 [kg]
weight wing covering (painted aluminium 6.22 [mm]) : 4109 [kg]
total weight aluminium spars (multi-cellular wing structure) : 3120 [kg]
weight wings : 10091 [kg]
weight wing/square meter : 82.44 [kg]
weight bleed air thermal leading-edge anti-icing : 37.5 [kg]
weight ailerons (2.7 [m2]) : 90.6 [kg]
weight fin (16.3 [m2]) : 672.8 [kg]
weight rudder (5.2 [m2]) : 205.7 [kg]
weight tailplane (horizontal stabilizer) (29.4 [m2]): 1336.5 [kg]
TransAsia Airways A321-131 B-22606 c/n 731 at Taipei Airport (TPE, June 2016. The aircraft was delivered to TransAsia in January 1998. It has IAE V2530-A5 engines.
weight elevators (7.3 [m2]): 162.7 [kg]
weight paint wing & tail surfaces : 70.6 [kg]
weight flight control hydraulic servo actuators: 29.8 [kg]
weight trailing-edge double slotted flaps (21.1 [m2]) : 745.4 [kg]
weight leading edge slats (12.6 [m2]) : 289.7 [kg]
weight aluminium honeycomb spoilers (8.6 [m2]) : 165.9 [kg]
weight airbrakes (2.4 [m2]) : 53.8 [kg]
weight wingtip fences : 50 [kg]
total weight wing construction : 14536 [kg] (30.4 [%])
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tire pressure main wheels : 13.60 [Bar] (nitrogen), ply rating : 23 PR
tire speed limit : 364 [km/hr]
total tyre footprint : 0.38 [m2]
Runway LCN at MTOW (0.76m radius of rigidity) : 56 [ ]
Aircraft Classification Number (ACN), MTOW on rigid runway and medium subgrade strength (B) : 39 [ ]
Can also operate from unpaved runways subgrade B
wheel pressure : 18260.0 [kg]
wheel track : 7.59 [m] wheelbase : 16.92 [m]
weight 4 Dunlop 49.0 x 18.0 main wheels (1245 [mm] by 457 [mm]) : 668.8 [kg]
weight 2 nose wheels : 167.2 [kg]
weight multi-disc wheel-brakes : 81.8 [kg]
weight Hydro-air flywheel detector type anti-skid units : 5.4 [kg]
weight oleo-pneumatic shock absorbers : 92.7 [kg]
weight wheel hydraulic operated retraction system : 1040.7 [kg]
weight undercarriage struts with axle 3095.0 [kg]
total weight landing gear : 5151.5 [kg] (6.2 [%]
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Swissair A321-111 HB-IOA at Geneva (GVA), August 1996. The aircraft was delivered to Swissair Januari 1995. It has CFM56-5B1 engines.
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calculated empty weight : 46437 [kg](55.9 [%])
weight oil for 6.3 hours flying : 5.6 [kg]
unusable fuel in engine and tanks 96.2 litre fuel : 75.5 [kg]
weight lifejackets : 83.2 [kg]
weight 3 life rafts : 115.6 [kg]
weight catering : 115.4 [kg]
weight water : 159.3 [kg]
weight crew : 648 [kg]
weight crew luggage, navigation chards, flight docs (NOTOC), manuals, miscellaneous items : 136 [kg]
operational weight empty : 47775 [kg] (57.6 [%])
********************************************************************
weight 185 passengers : 14245 [kg]
weight luggage : 2960 [kg]
weight cargo : 4520 [kg] (cargo + luggage/m3 belly : 120 [kg/m3])
zero fuel weight (ZFW): 69500 [kg](83.7 [%])
weight fuel for landing (1.2 hours flying) : 4000 [kg]
max. landing weight (MLW): 73500 [kg](88.6 [%])
max. fuel weight : 66654 [kg] (80.3 [%])
payload with max fuel : 176 passengers + luggage 16346 [kg]
published maximum take-off weight : 83000 [kg] (100.0 [%])
calculation : * 4 * (engine power)
power loading (Take-off) : 311 [kg/KN]
power loading (Take-off) 1 PUF: 622 [kg/KN]
max. total take-off power : 266.8 [KN]
calculation : *5* (loads)
manoeuvre load : 0.8 [g] at 9000 [m]
limit load : 2.5 [g] ultimate load : 3.8 [g] load factor : 1.7 [g]
design flight time : 1.49 [hours]
design cycles : 32800 sorties, design hours : 48872 [hours]
max. wing loading (MTOW & flaps retracted) : 678 [kg/m2]
wing stress (2 g) during operation : 152 [N/kg] at 2g emergency manoeuvre
calculation : *6* (angles of attack)
angle of attack zero lift : -1.69 ["]
max. angle of attack (stalling angle, clean) : 12.15 ["]
max. angle of attack (full flaps) : 19.99 ["]
angle of attack at economic cruise speed : 4.25 ["]
calculation : *7* (lift & drag ratios
lift coefficient at angle of attack 0° : 0.15 [ ]
lift coefficient at max. speed : 0.44 [ ]
lift coefficient at max. angle of attack (clean): 1.23 [ ]
max. lift coefficient 50 [° ] flap setting : 2.32 [ ]
drag coefficient at max. speed : 0.0380 [ ]
drag coefficient at econ. cruise speed : 0.0387 [ ]
induced drag coefficient at econ. cruise speed : 0.0133 [ ]
drag coefficient (zero lift) : 0.0254 [ ]
lift/drag ratio at econ. speed : 11.45 [ ]
calculation : *8* (speeds
Risk of tailstrike when taking off with OEI (engine failure), pilot must not rotate to fast
minimum control speed (Vmc): 264 [km/u] (142.5 [kt])
minimum unstick speed (Vmu) at TO angle 12.0 ° : 300 [km/u] (162 [kt])
take-off decision speed (V1) : 285 [km/u] (154 [kt])
take-off rotation speed (VR) : 304 [km/u] (164 [kt])
Lufthansa Airbus A321-131 c/n 560 taking off, IAE V2530-A5 engines.
lift-off speed (VLOF) : 330 [km/u] (178 [kt]) at pitch angle : 9.8 [°]
take-off safety speed (V2) : 333 [km/u] (180 [kt])
flap retraction speed (V3) at 500m (OW loaded : 79788 [kg]): 356 [km/u] (192 [kt])
steady initial climb speed (V4) : 359 [km/u] (194 [kt])
climb speed (to FL150 with 63 [%] power) : 639 [km/hr] (345 [kt])
max. endurance speed (Vbe): 756 [km/u] min. fuel/hr : 3049 [kg/hr] at height : 10973 [m]
max. range speed (Vbr): 819 [km/u] (0.78 [mach]) min. fuel consumption : 3.73 [kg/km] at cruise height : 11582 [m]
max. cruising speed : 860 [km/hr] (464 [kt]) at 10000 [m] (power:21 [%])
max. operational speed (Mmo) : 895 [km/hr] (Mach 0.82 ) at 9000 [m] (power:24 [%])
airflow at cruise speed per engine : 231.8 [kg/s]
speed of thrust jet : 1298 [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): 463 [km/u] (250 [kt])
minimum control speed (MCS) Vmca (clean): 391 [km/u] (211 [kt])
stalling speed clean at 500 [m] height at Max.Landing Weight : 73500 [kg]): 326 [km/u] (176 [kt])
final approach speed (landing speed) at sea-level with 50 [°] 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 (max. continuous power) at sea-level ROC (loaded, 63 % power) : 1342 [m/min]
rate of climb at sea-level ROC (loaded, 75 % power) : 1797 [m/min]
rate of climb at 1000 [m] with 1 engine out (PUF/MTOW, 63 % power on remaining engines) : 217 [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)
ICAO Aerodrome Reference Code : 4C
Brake kinetic energy capacity : 2306 [KW]
Take-off field length at MTOW (83000 kg / 183000 lbs), sea-level, standard day, dry runway : 5900 ft > 1798m, looks very low, according to eurocontrol T-O distance is 2210m, according to Jane’s all the world aircraft 2000-2001 T-O distance ISA+ 15°C : 2280m
FAR TO runway length (TOFL) requirement at TOW 83000 [kg] standard day at SL (PUF after V1): 2187 [m]
Take-off flap setting : 15 [° ]
+++ FAA certification landing distance : +++
landing weight : 73500 [kg], TE flap setting : 50 [°]
runway condition : dry , landing over 50ft (15m) at threshold at sea-level
with use of thrust reversers, glideslope : 3.0 [°]
Landing field length at sea level, dry runway, MLW 73500 [kg] (162037 lb) : 5245 ft > 1599 [m]
FAA approved landing field length at SL, dry runway : 1598 [m] (5243 [ft])
FAA approved landing field length at SL, wet runway: 1820 [m] (5971 [ft])
max. lift/drag ratio : 14.39 [ ]
climb to 5000 [m] with max payload : 3.45 [min]
climb to 10000 [m] with max payload : 10.61 [min]
descent time from 10000 [m] to 250 [m] : 24.33 [min]
max. ceiling fully loaded (mtow- 60 min.fuel): 79788 [kg] ) : 14200 [m]
ceiling limited by max. pressure differential 14125 [m]
max. theoretical ceiling (OWE + 60 min.fuel) : 16700 [m] with flying weight :50987 [kg]
calculation *10* (action radius & endurance)
range with max. payload: 3431 [km] with 21725.0 [kg] max. useful load (71.5 [%] fuel)*
range with high density pax: 3774 [km] with 220 passengers (78.2 [%] fuel)*
range with typical two-class pax: 4677 [km] with 185 passengers (95.4 [%] fuel)*
Unfortunately, this table gives values for MTOW 89000 – 93500 kg, so it is somewhat difficult to deduce the values for MTOW 83000 kg from his table, but this are the approx.. values :
Range with max payload (MTOW 93500 kg ) : 2200 nm > 4075m
Ferry range : 3200 nm > 5925 km
Jane’s all the world aircraft 2000-2001 range with 185 pax , reserves 370 km diversion) : 4181 km
range with max.fuel and MTOW : 4920 [km] with 8 crew and 176 passengers and 0 [kg] cargo*
ferry range (calculated): 5727 [km] with 2 crew and zero payload (100.0 [%] fuel)*
max range theoretically with additional fuel tanks total 45842 [litre] fuel : 10139 [km]*
* calculated ranges without fuel reserves
Available Seat Kilometres (ASK) : 864770 [paskm]
useful load with range 1000km : 21725 [kg]
useful load with range 1000km : 220 passengers
production (theor.max load): 18684 [tonkm/hour]
production (useful load): 18684 [tonkm/hour]
production (passengers): 161152 [paskm/hour]
oil and fuel consumption per tonkm : 0.172 [kg]
Alitalia A321-112 I-BIXD c/n 532 at Hamburg Fuhlsbuettel (HAM), May 1997. This aircraft was delivered to Alitalia June 1995. It has CFM56-5B2 engines.
calculation *11* (operating cost)
fuel cost per hour at econ.speed (4091 [litre]):2455 [eur] (38 [pax-km/litre fuel])
fuel cost per seat 1000km flight (187 [pax] 2-class seating): 15.65 [eur/1000PK]
oil cost per hour: 3 [eur]
crew cost per hour : 1050 [eur]
list price 2024 : 120 [mln USD]
average flying hours in 1 year : 2250 [hours] technical life : 22 [year]
real average service life : 21 [years]
depreciation : 21 [years] to 10% residual value
financing interest per flying hour : 1198 [EUR]
write off per flying hour : 2106 [EUR]
mean time between engine failure (MTBF) : 20009 [hr]
approved for 120-min. ETOPS flights
can continue fly on 1 engine, low risk for emergency landing for PUF
workhours per day : 9.27 [hr]
average flight hours till crash : 4.25 [mln hr] (1890 service years)
safe flight hours till fatality : 4252500 [hr] (1890.0 service years)
reservation pax liability/flying hour : 0.03 [SDR*] (0.04 [eur])
insurance cost per hour : 130 [eur] insurance rate : 0.7 [%]
engine maintenance cost per hour : 801.4 [eur]
wing maintenance cost per hour : 180.7 [eur]
fuselage maintenance cost per hour : 384.70 [eur]
tire life (time till worn out) : 80 [cycles]
maintenance cost per hour (excluding engines): 1241 [eur]
direct operating cost per hour: 8985 [eur], DOC per km : 10.73 [eur]
DOC per seat 1000km flight (187 [pax] 2-class seating): 55.75 [eur/1000PK]
DOC per seat 1000km flight (high density seating): 47.49 [eur/1000PK]
DOC per kg cargo for a 1000km flight : 0.48 [eur/kg] (= DOC/tonkm)
passenger service charge (depart at Schiphol): 11.34 [eur]
security service charge (depart at Schiphol): 10.08 [eur]
airport take-off fee / passenger : 2.99 [eur/pax]
airport landing fee / passenger : 2.99 [eur/pax]
retour ticket price 1000km trip : 182.92 [eur/pax]
price retour ticket Schiphol-Barcelona : 213.58 [eur/pax]`
Lufthansa A321-131 D-AIRE c/n 484 at Frankfurt (FRA), October 2018. The aircraft was delivered in April 1994 to Lufthansa. It has IAE V2530-A5 engines. On 9 October 2000 it suffered a tailstrike upon landing at London Heathrow (LHR) on runway 27L in gusty cross wind conditions. It flew from FRA to LHR with 8 crew and 170 passengers. It landed with a nose-up attitude around 10°. Nobody was hurt in the incident and the aircraft was repaired. Information taken from the final accident report : Data from the aircraft manufacturer indicated that tail scrape damage would occur over a pitch attitude range of 9.7° (with the main landing gear oleos fully compressed) to 11.4° (with the main landing gear oleos uncompressed, but with the tyres in ground contact).
The landing technique requires a stabilised approach as essential to achieve consistent successful landings and it is described as imperative to reach the flare height at the appropriate speed and flight path which is given as -3°. The flare should be started at approximately 20 feet and thrust reduction should be between 20 feet and 15 feet. It should be co-ordinated with pitch rate especially during cross winds. The attitude increase between the start of the flare and touchdown is given as approximately 4.5°, assuming the correct airspeed decay of 8 kt and the reduction in flight path of -1° (3 feet/second) is achieved.
accidents with fatalities > see the accident file
Literature :
luchtvaart sept’90 page 256, 257
Air international dec’97 page 383
Jane's all the world aircraft 2000-2001 page 198,199
Jane's all the world aircraft 2000-2001 page 112,113
Flugrevue june’97 page 9
Flight international 18/24 nov’98 page 45
Aircraft Characteristics | Airbus
https://contentzone.eurocontrol.int/aircraftperformance/default.aspx ?
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 14 April 2025 contact : info.aircraftinvestigation@gmail.com ac jetpax 2020.py python 3.7.4
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