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weight and performance calculations for the Airbus A320neo
Air Malta Airbus A320-251N 9H-NED c/n 10106 taking off from Schiphol, May 2025 © bvdz It has CFMI LEAP-1A26 turbofans.
Airbus A320neo (WV055).
role : jet airliner
importance : ****
first flight : 25 September 2014 operational : January 2016 (Lufthansa)
country : EU-consortium
ICAO aircraft type designator : A320
production : May 2025 4054 A320neo’s ordered, 2193 delivered
general information :
New A320 version with new engines (neo = New Engine Option) giving 15% fuel burn
reduction and 20% less maintenance. There are two engine
options : CFM LEAP-1A or the Pratt&Whitney PW1000G with geared turbofan.
Airbus A320neo prototype
The A320neo is half as loud as an A320 at take-off, with an 85 decibel noise footprint .
Besides the new engines it
has winglets (sharklets called by Airbus) fitted as standard. The sharklets add 200kg
to the weight of the aircraft but gives 3.5% fuel burn reduction. It has 60% market
share compared to its competitor the Boeing 737MAX.
In 2018, an A320neo list price was US$110.6 million.
primary users : Lufthansa, Indigo (87), Frontier Airlines (33), China Southern (26),
Spirit Airlines, Avianca, Air Arabia, Norwegian, Pegasus Airlines, Lion Air, Turkish
Airlines, Delta Airlines, China Eastern, Air China, Air India
Accommodation :
flight crew : 2 cabin crew : 5
passengers : seating for 150 in two class : 12 business class and 138 economy class
seats ( 32 -in pitch) exit limit : 195 passengers, high density single-class seating for
180 passengers
engine : 2 CFM International LEAP-1A26 turbofan engines of 120.64 [KN] (27120
[lbf])
Tail-angle measured : 10°
dimensions :
wingspan : 35.8 [m], length overall: 37.57 [m], length of fuselage : 37.57 [m] height :
11.76 [m] wing area gross : 122.4 [m^2] fuselage exterior width : 3.95 [m]
weights :
operating empty weight : 44300 [kg] max. structural payload : 20000 [kg]
Zero Fuel weight (ZFW) : 64300 [kg] max. landing weight (MLW) : 67400 [kg]
max. take-off weight : 79000 [kg] weight usable fuel : 18636 [kg] (23740 [litres])
performance :
Max. operating Mach number (Mmo) : 0.822 [Mach] (884 [km/hr]) at 10000 [m]
critical Mach speed : 0.78 [Mach]
max. cruising speed : 870 [km/hr] (Mach 0.809 ) at 10000 [m] (31 [%] power)
economic cruising speed : 837 [km/hr] (Mach 0.78 ) at 10000 [m]
service ceiling : 11900 [m]
range with max fuel and MTOW : 6000 [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 sharklets at the
wingtips. airfoil : Airbus, average thickness/chord ratio : 10.0 [%], sweep angle ¾
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 : 1.64 [m]
taper ratio : 0.270 [ ]
mean wing chord : 3.42 [m]
wing aspect ratio : 10.47 []
Oswald factor (e): 0.717 []
seize (span*length*height) : 15817 [m^3]
calculation : *2* (fuel consumption)
oil consumption : 0.3 [kg/hr]
fuel consumption (econ. cruise speed) : 2448.7 [kg/hr] (3119.4 [litre/hr]) at 20 [%]
power
fuel burn per seat per hour (average seating) : 18.91 [litre], sfc : 51.8 [kg/KN/h]
total fuel capacity : 23740 [litre] (18636 [kg])
calculation : *3* (weight)
weight engine(s) dry : 5200.0 [kg] = 21.55 [kg/KN]
weight 8.0 litre oil tank : 0.68 [kg]
oil tank filled with 1.5 litre oil : 1.4 [kg]
oil in engine 3.0 litre oil : 2.7 [kg]
weight all fuel lines and pumps containing 75 litres fuel : 45.4 [kg]
weight engine cowling : 627.3 [kg]
weight thrust reversers : 361.9 [kg]
total weight propulsion system : 6239 [kg](7.9 [%])
***************************************************************
Accommodation cabin facilities:
The new "Space-Flex" optional cabin configuration increases space-efficiency with a new rear galley configuration and a "Smart-Lav" modular lavatory design – allowing an in-flight change of two lavatories into one accessible toilet . The rearranged cabin allows up to 20 more passengers for the A321neo without "putting more sardines in the can" with the larger "Cabin-Flex" modified exits described below. Total fuel consumption per seat is reduced by over 20%, while the rearranged cabin allows up to nine more passengers for the A320neo.
typical 2-class cabin layout for 150 passengers : economy : pitch : 81.3 [cm] 32.0 [-in]
( 3+3 ) seating in 26.0 rows
business class pitch : 91.4 [cm] 36.0 [-in] at 4 -abreast
weight passenger seats (width 53.7 [cm]) : 748.0 [kg]
weight cabin crew seats : 25.0 [kg]
weight flight crew seats : 42.0 [kg]
high density seating passengers : 180 [pax] at mainly 6 -abreast seating in 31.0 rows,
pitch 73.7 [cm] 29.0 [-in]
pax density, normal seating : 0.678 [m2/pax], high density seating : 0.565 [m2/pax]
weight 3 lavatories : 89.2 [kg]
weight 2 galleys : 120.0 [kg]
Vietnam Bamboo Airways A320neo stewardess
weight overhead stowage for hand luggage (total : 8.4 [m3] = 174 55x35x25cm carry-on
trolleys) : 130.6 [kg]
*note : possible not enough overhead stowage in high density configuration*
weight 150 entertainment LCD screens in back of seats : 75.0 [kg]
weight 54 windows (47x38cm) made of acrylic glass: 229.5 [kg]
weight 4 (1.85 x 0.81 [m]) main entry doors : 163.9 [kg]
weight 2 (main door size : 1.25 x 1.82 [m]) freight doors (belly) : 135.3 [kg]*
total usable belly baggage/cargo hold volume : 37.4 [m3]
cabin volume (usable), excluding flight deck : 198 [m3]
passenger compartment volume : 139 [m3]
passenger cabin max width : 3.70 [m] cabin length : 27.50 [m] max cabin height : 2.22
[m] floor area : 92.4 [m2]
weight cabin facilities : 1758.5 [kg]
safety facilities:
weight 4 type III over wing emergency exits (0.51 x 1.02 [m]): 61.9 [kg]
evacuation time with 180 passengers : 45 [sec]
weight 4 hand fire extinguisher : 11 [kg]
weight cockpit voice recorder (CVR) and flight data recorder (FDR): 20.0 [kg]
weight oxygen masks & oxygen generators (deploy cabin alt.>4267m): 97.5 [kg]
weight emergency flare installation : 10 [kg]
weight 4 emergency evacuation slides : 134.7 [kg]
weight safety equipment & facilities : 335 [kg]
fuselage construction:
fuselage aluminium frame : 8414 [kg]
floor loading (payload/m2): 217 [kg/m2]
weight rear pressure bulkhead : 174.7 [kg]
fuselage covering ( 353.8 [m2] duraluminium 2.73 [mm]) : 2538.8 [kg]
weight paint fuselage : 74.3 [kg]
weight aluminium floor beams : 549.4 [kg]
weight cabin furbishing : 852.9 [kg]
weight cabin floor : 1306.4 [kg]
weight (sound proof) isolation : 189.6 [kg] TO-noise level : 86.0 [EPNdB]
weight 8249 [litre] main central fuel tank empty : 165.0 [kg]
weight empty 226 [litre] potable water tanks : 20.0 [kg]
weight empty waste tank : 9.5 [kg]
weight fuselage structure : 14294.1 [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]
Lufthansa Airbus A320neo D-AINA cockpit
weight Integrated Modular Avionics (IMA), with AFDSE, an implementation of ARINC
664 : 35 [kg]
weight Network Systems Server with digital manuals and chards (paperless cockpit): 7
[kg]
weight Cat IIIB 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 : 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 : 167.0 [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 : 330 [m3] cabin air refreshment time : 2.9
[min]
weight air-conditioning and pressurization system : 191 [kg]
weight APU / engine starter : 60.3 [kg]
weight lighting (LED): 49.5 [kg]
weight 207 bar hydraulic system : 79.1 [kg]
weight engine-driven 40kVA electricity generators : 37.5 [kg]
weight ram air turbine for emergency electric power : 5.0 [kg]
weight 22Ah battery : 28.5 [kg]
weight controls (sidestick FBW): 10.8 [kg]
weight systems : 456.3 [kg]
total weight fuselage : 17011 [kg](21.5 [%])
***************************************************************
wing construction :
total weight aluminium ribs (44 ribs) : 2686 [kg]
weight engine mounts : 121 [kg]
Fuel capacity : wing tanks 6925 + 880 = 7805 litre x 2 = 15610 litre + center tank 8250 litre = 23860 litre, usable fuel according Airbus airplane characteristics 23740 litre
weight 4 wing fuel tanks empty for total 15610 [litre] fuel : 234 [kg]
weight 95 [litre] vent surge tanks : 11 [kg]
weight wing covering (painted aluminium 6.97 [mm]) : 4608 [kg]
total weight aluminium spars (multi-cellular wing structure) : 3209 [kg]
weight wings : 10503 [kg]
weight wing/square meter : 85.81 [kg]
weight bleed air thermal leading-edge anti-icing : 39.4 [kg]
weight ailerons (2.9 [m2]) : 99.0 [kg]
weight fin (18.0 [m2]) : 772.2 [kg]
weight rudder (5.7 [m2]) : 236.1 [kg]
weight tailplane (horizontal stabilizer) (24.8 [m2]): 1174.1 [kg]
weight elevators (6.2 [m2]): 142.9 [kg]
weight paint wing & tail surfaces : 69.4 [kg]
weight flight control hydraulic servo actuators: 26.4 [kg]
weight trailing-edge double slotted flaps (21.1 [m2]) : 775.6 [kg]
weight leading edge slats (12.6 [m2]) : 301.3 [kg]
weight spoilers made of CFRP with Spoiler Electro-Mechanical Actuators (SEMA) (8.6
[m2]) : 161.2 [kg]
weight airbrakes (2.4 [m2]) : 55.7 [kg]
weight sharklets : 200 [kg]
total weight wing construction : 14922 [kg] (33.7 [%])
*******************************************************************
Indigo is a large A320neo user with 125 aircraft ordered in June 2023.
landing gear :
tire pressure main wheels : 14.40 [Bar] (nitrogen), ply rating : 23 PR
tire speed limit : 364 [km/hr]
total tyre footprint : 0.30 [m2]
Runway LCN at MTOW (0.76m radius of rigidity) : 67 [ ]
Aircraft Classification Number (ACN), MTOW on rigid runway and medium subgrade
strength (B) : 47 [ ]. Can only operate from unpaved runways with reduced weight
and reduced tyre pressure
wheel pressure : 17380.0 [kg]
wheel track : 7.59 [m] wheelbase : 12.64 [m]
weight 4 Dunlop 46.0 x 17.0 main wheels (1168 [mm] by 432 [mm]) : 669.6 [kg]
weight 2 nose wheels : 167.4 [kg]
weight multi-disc wheel-brakes : 75.6 [kg]
weight Hydro-air flywheel detector type anti-skid units : 5.4 [kg]
weight oleo-pneumatic shock absorbers : 85.7 [kg]
weight wheel hydraulic operated retraction system : 979.4 [kg]
weight undercarriage struts with axle 2864.9 [kg]
total weight landing gear : 4848.1 [kg] (6.1 [%]
*******************************************************************
Easyjet A320-251N OE-LSW c/n 11989 landing at Schiphol April 2025 © bvdz
********************************************************************
calculated empty weight : 43021 [kg](54.5 [%])
aircraft equipment and service utensils:
weight oil for 8.3 hours flying : 2.6 [kg]
unusable fuel in engine and tanks 118.7 litre fuel : 93.2 [kg]
weight lifejackets : 67.5 [kg]
weight 3 life rafts : 93.8 [kg]
weight catering : 144.7 [kg]
weight water : 199.7 [kg]
weight crew : 567 [kg]
weight crew luggage, navigation chards, flight docs (NOTOC), manuals, miscellaneous
items : 111 [kg]
operational weight empty : 44300 [kg] (56.1 [%])
********************************************************************
useful load breakdown :
weight 150 passengers : 11550 [kg]
weight luggage : 2400 [kg]
weight cargo : 6050 [kg] (cargo + luggage/m3 belly : 185 [kg/m3])
Citilink A320-251N PK-GTE c/n 7603 with CFM LEAP-1A26 engines
zero fuel weight (ZFW): 64300 [kg](81.4 [%])
weight fuel for landing (1.3 hours flying) : 3100 [kg]
max. landing weight (MLW): 67400 [kg](85.3 [%])
max. fuel weight : 62936 [kg] (79.7 [%])
payload with max fuel : 173 passengers + luggage 16064 [kg]
the aircraft can operate with high density seating even with max.fuel, for that reason it
has a higher density passenger seating layout to make full use of the higher MTOW
published maximum take-off weight : 79000 [kg] (100.0 [%])
calculation : * 4 * (engine power)
power loading (Take-off) : 327 [kg/KN]
power loading (Take-off) 1 PUF: 655 [kg/KN]
max. total take-off power : 241.3 [KN]
calculation : *5* (loads)
manoeuvre load : 0.8 [g] at 9000 [m]
limit load : 2.5 [g] ultimate load : 3.8 [g] load factor : 2.0 [g]
design flight time : 2.00 [hours]
design cycles : 34650 sorties, design hours : 69300 [hours]
max. wing loading (MTOW & flaps retracted) : 645 [kg/m2]
wing stress (2 g) during operation : 137 [N/kg] at 2g emergency manoeuvre
calculation : *6* (angles of attack)
angle of attack zero lift : -1.65 ["]
max. angle of attack (stalling angle, clean) : 11.70 ["]
max. angle of attack (full flaps) : 19.24 ["]
angle of attack at economic cruise speed : 3.86 ["]
Lufthansa A320neo (A320-271N) D-AINX c/n 9229 taking of from Schiphol, January 2025 © bvdz.
calculation : *7* (lift & drag ratios)
lift coefficient at angle of attack 0° : 0.15 [ ]
lift coefficient at max. speed : 0.47 [ ]
lift coefficient at max. angle of attack (clean): 1.21 [ ]
max. lift coefficient 50 [° ] flap setting : 2.27 [ ]
drag coefficient at max. speed : 0.0370 [ ]
drag coefficient at econ. cruise speed : 0.0346 [ ]
induced drag coefficient at econ. cruise speed : 0.0106 [ ]
drag coefficient (zero lift) : 0.0240 [ ]
lift/drag ratio at econ. speed : 12.72 [ ]
calculation : *8* (speeds)
Risk of tailstrike when taking off with OEI (engine failure), pilot must not rotate to fast
minimum control speed (Vmc): 256 [km/u] (138.1 [kt])
take-off decision speed (V1) : 265 [km/u] (143 [kt])
take-off rotation speed (VR) : 279 [km/u] (151 [kt])
minimum unstick speed (Vmu) at TO angle 13.0 ° : 281 [km/u] (152 [kt])
Lufthansa A320neo (A320-271N) D-AINA taking off, it has Pratt & Whitney PW1127G-JM engines.
lift-off speed (VLOF) : 306 [km/u] (165 [kt]) at pitch angle : 10.9 [°]
take-off safety speed (V2) : 308 [km/u] (167 [kt])
flap retraction speed (V3) at 500m (OW loaded : 76551 [kg]): 351 [km/u] (189 [kt])
steady initial climb speed (V4) : 334 [km/u] (181 [kt])
climb speed (to FL150 with 66 [%] power) : 635 [km/hr] (343 [kt])
max. endurance speed (Vbe): 726 [km/u] min. fuel/hr : 2259 [kg/hr] at height : 10973 [m]
max. range speed (Vbr): 820 [km/u] (0.78 [mach]) min. fuel consumption : 2.79 [kg/km]
at cruise height : 11582 [m]
max. cruising speed : 870 [km/hr] (470 [kt]) at 10000 [m] (power:22 [%])
max. operational speed (Mmo) : 884 [km/hr] (Mach 0.82 ) at 10000 [m] (power:23 [%])
airflow at cruise speed per engine : 307.1 [kg/s]
speed of thrust jet : 1177 [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): 378 [km/u] (204 [kt])
stalling speed clean at 500 [m] height at Max.Landing Weight : 67400 [kg]): 315 [km/u]
(170 [kt])
Vapproach 131.5 kts for the A320neo is only attainable with bigger flaps and higher Clmax with 50° flap setting. Compared to A320ceo : calculated approach speed : 135 kts at MLW 64500 kg, so this is in line with above 136 kts at MLW 66000 kg. For the A320neo with the higher MLW, Vapproach = VREF = Vstall full flaps * 1.30 is calculated at 139 kts. In the information above is mentioned “final approach speed at threshold”, for the calculations, I use for Threshold speed = Vstall full flaps * 1.25
taking into account this part from Wikipedia Airbus A320neo family - Wikipedia :
Of these 4,000 hours flown, 2,250 were with PW GTFs and 1,770 with CFM LEAPs. The flight test programme was to conclude in 2018 with the completion of A319neo testing. The changes impact flying qualities , performance and system integration; they entailed retuning the fly-by-wire controls and meeting type certification requirements which have evolved since 1988, and helped decrease the minimum V speeds . The neo is 1.8 t heavier than the ceo, but take-off and landing performance is the same with a modified rotation law, adjusted wing flap and wing slat angles and rudder deflection increased by 5° to cope with the higher thrust.
type certification requirements have changed since 1988..
So can be that Threshold speed = Vstall full flaps * 1.25 is in line with new type certification requirements and allowed with the use of retuned fly-by-wire.
final approach speed (landing speed) at sea-level with 50 [°] flaps VREF (max. landing
weight): 257 [km/u] (139 [kt])
ICAO Aircraft Approach Category (APC) : C
SAS A320-251N SE-ROE c/n 7791 landing at Schiphol March 2025 © bvdz
threshold speed Vth (landing weight): 67400 [kg]): 244 [km/hr] (131.5 [kt]
stalling speed at sea-level with full flaps VSO (max. landing weight): 198 [km/u] (107
[kt]
rate of climb (max. continuous power) at sea-level ROC (loaded, 66 % power) : 1374
[m/min]
rate of climb at sea-level ROC (loaded, 75 % power) : 1715 [m/min]
rate of climb at 1000 [m] with 1 engine out (PUF/MTOW, 66 % power on remaining
engines) : 251 [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)
Brake kinetic energy capacity : 2042 [KW]
FAR TO runway length (TOFL) requirement at TOW 79000 [kg] standard day at SL
(PUF after V1): 1939 [m]
I guess the A320neo is only classified as 3C with MTOW 73500 kg, for MTOW 79000 kg it can only be 4C as the take-off field length is more than 1800m, see below table and take-off field graph :
Take-off field length with MTOW 79000 kg (174160 lb), standard day, sea level , dry runway : 6250 ft > 1905 m
ICAO Aerodrome Reference Code : 4C
Take-off flap setting : 15 [° ]
+++ FAA certification landing distance : +++
landing weight : 67400 [kg], TE flap setting : 50 [°]
runway condition : dry , landing over 50ft (15m) at threshold at sea-level
with use of thrust reversers, glideslope : 3.5 [°]
Landing field length at MLW 67400 kg / 148590 lb, standard day, sea level, dry runway : 4550 ft > 1390m, calculation lowest possible is 1400m with higher brake coefficient and 3.5° glideslope.
FAA approved landing field length at SL, dry runway : 1400 [m] (4592 [ft])
FAA approved landing field length at SL, wet runway: 1601 [m] (5252 [ft])
Easyjet Airbus A320-251N OE-LSI c/n 9105 landing Schiphol, May 2025 © bvdz, nose-up attitude measured at 8°
max. lift/drag ratio : 15.67 [ ]
climb to 5000 [m] with max payload : 3.37 [min]
climb to 10000 [m] with max payload : 10.36 [min]
descent time from 10000 [m] to 250 [m] : 24.33 [min]
max. ceiling fully loaded (mtow- 60 min.fuel): 76551 [kg] ) : 14400 [m]
ceiling limited by max. pressure differential 14125 [m]
max. theoretical ceiling (OWE + 60 min.fuel) : 17100 [m] with flying weight :46749 [kg]
calculation *10* (action radius & endurance)
range with max. payload: 4938 [km] with 20000.0 [kg] max. useful load (78.9 [%] fuel)*
range with high density pax: 6121 [km] with 180 passengers (96.4 [%] fuel)*
range with typical two-class pax: 6489 [km] with 150 passengers (100.0 [%] fuel)*
Range with max fuel (MTOW 79.000 [kg]):
green line : 3450 [nm] = 6389 [km] with 23740 [litre] with no reserves,
brown line : 4000 [nm] = 7408 [km] this is with one 3121 [litre] additional centre tank (1 ACT)
ferry range (green line) : 4275 nm > 7915 km
range with max.fuel and MTOW : 6370 [km] with 7 crew and 173 passengers and 0
[kg] cargo*
ferry range (calculated): 7324 [km] with 2 crew and zero payload (100.0 [%] fuel)*
max range theoretically with additional fuel tanks total 45159 [litre] fuel : 13023 [km]*
* calculated ranges without fuel reserves
Available Seat Kilometres (ASK) : 1100701 [paskm]
useful load with range 1000km : 20000 [kg]
useful load with range 1000km : 180 passengers
production (theor.max load): 17400 [tonkm/hour]
production (useful load): 17400 [tonkm/hour]
production (passengers): 151147 [paskm/hour]
oil and fuel consumption per tonkm : 0.141 [kg]
calculation *11* (operating cost)
fuel cost per hour at econ.speed (3119 [litre]):1871 [eur] (47 [pax-km/litre fuel])
fuel cost per seat 1000km flight (174 [pax] 2-class seating): 12.87 [eur/1000PK]
oil cost per hour: 1 [eur]
crew cost per hour : 900 [eur]
list price 2024 : 102 [mln USD]
average flying hours in 1 year : 3000 [hours] technical life : 23 [year]
real average service life : 23 [years]
depreciation : 24 [years] to 10% residual value
financing interest per flying hour : 768 [EUR]
write off per flying hour : 1233 [EUR]
mean time between engine failure (MTBF) : 21776 [hr]
approved for 120-min. ETOPS flights
can continue fly on 1 engine, low risk for emergency landing for PUF
March 2017 the A320neo in service had an average flight time of 1.54 hour. Making 10 cycles a day with Lufthansa and 8.4 block hours. China Southern airlines operates the A320neo near to 6 hr sectors, an indication for the versatility of the aircraft.
workhours per day : 11.30 [hr]
average flight hours till crash : 59.15 [mln hr] (19715 service years)
safe flight hours till fatality : 29572605 [hr] (9857.5 service years)
reservation pax liability/flying hour : 0.00 [SDR*] (0.01 [eur])
insurance cost per hour : 8 [eur] insurance rate : 0.1 [%]
engine maintenance cost per hour : 1081.4 [eur]
wing maintenance cost per hour : 134.6 [eur]
fuselage maintenance cost per hour : 176.90 [eur]
tire life (time till worn out) : 89 [cycles]
maintenance cost per hour (excluding engines): 777 [eur]
direct operating cost per hour: 6641 [eur], DOC per km : 7.93 [eur]
DOC per seat 1000km flight (174 [pax] 2-class seating): 43.93 [eur/1000PK]
DOC per seat 1000km flight (high density seating): 42.41 [eur/1000PK]
DOC per kg cargo for a 1000km flight : 0.38 [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 : 2.43 [eur/pax]
airport landing fee / passenger : 2.43 [eur/pax]
retour ticket price 1000km trip : 154.48 [eur/pax]
price retour ticket Schiphol-Barcelona : 178.64 [eur/pax]
accidents with fatalities > see the accident file
notes : of all classic jetliners : lowest fuel consumption with 2383 kg/hr, highest lift coe-efficient at max speed : Clvmax : 0.471. Highest aspect ratio 10.47, same as for A321neo.
Literature :
https://contentzone.eurocontrol.int/aircraftperformance/default.aspx?
Aircraft Characteristics | Airbus
Airbus A320neo family - Wikipedia
Airbus voert productie van populaire A320neo-serie verder op | Luchtvaartnieuws
Citilink Airbus A320-251N - SkyTeam Virtual
Air Portugal A320-251N CS-TVB c/ 8749 parked at the gate at Schiphol 01 February 2025 © bvdz
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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