wide-body long range airliner Airbus A330-900 **** November 2018
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weight and performance calculations for the Airbus A330-900
Airbus A330-900
role : wide-body airliner
importance : ****
first flight : 19 October 2017 operational : November 2018 (TAP Portugal)
country : EU-consortium
production : 118 aircraft delivered, March 2024, 284 ordered > backlog 166
general information :
A330 variant with new engines, indicated as A330neo.
primary users : TAP Portugal (19), Corsair (5), Delta Airlines(27), Condor (14),
Cebu Pacific (8), Lion Air (8)
Accommodation:
flight crew : 3 cabin crew : 11
flight crew consist of pilot, co-pilot and relief pilot
passengers : seating for 310 in two class : 40 business class and 270 economy class
seats ( 32 -in pitch) exit limit : 460 passengers, high density seating for 442
passengers
engine : 2 Rolls Royce Trent 7000 turbofan engines of 324.0 [KN] (72836.9 [lbf])
dimensions :
wingspan : 64.0 [m], length overall: 63.66 [m], length of fuselage : 61.77 [m] height :
16.79 [m] wing area : 372.0 [m^2] fuselage exterior width : 5.64 [m]
weights :
operating empty weight : 136000 [kg] max. structural payload : 45000 [kg]
Zero Fuel weight (ZFW) : 181000 [kg] max. landing weight (MLW) : 191000 [kg]
max. take-off weight : 251000 [kg] weight fuel : 109186 [kg] (139090 [litres])
performance :
Max. operating Mach number (Mmo) : 0.85 [Mach] (918 [km/hr]) at 9450 [m]
critical Mach speed : 0.83 [Mach]
max. cruising speed : 880 [km/hr] (Mach 0.83 ) at 11000 [m] (35 [%] power)
economic cruising speed : 871 [km/hr] (Mach 0.82 ) at 11000 [m]
service ceiling : 12634 [m]
range with max fuel and MTOW : 17500 [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 (outboard) and airbrakes (inboard) and sharklets at the wingtips
airfoil: Airbus average thickness/chord ratio: 12.3 [%], sweep angle 3/4 chord: 30.0 [°]
calculation : *1* (dimensions)
wing chord at root : 10.55 [m]
wing chord at tip : 1.78 [m]
taper ratio : 0.169 [ ]
mean wing chord : 5.81 [m]
wing aspect ratio : 11.01 []
Oswald factor (e): 0.717 []
seize (span*length*height) : 68406 [m^3]
calculation : *2* (fuel consumption)
oil consumption : 5.8 [kg/hr]
fuel consumption (econ. cruise speed) : 5321.8 [kg/hr] (6779.4 [litre/hr]) at 28 [%] power
distance flown for 1 kg fuel : 0.16 [km/kg] at 11000 [m] height, sfc : 29.3 [kg/KN/h]
total fuel capacity : 139090 [litre] (109186 [kg])
calculation : *3* (weight)
weight engine(s) dry : 12890.0 [kg] = 19.89 [kg/KN]
weight 173.5 litre oil tank : 14.75 [kg]
oil tank filled with 4.1 litre oil : 3.7 [kg]
oil in engine 7.9 litre oil : 7.1 [kg]
fuel in engine 35.4 litre fuel : 25.92 [kg]
weight fuel lines : 173.4 [kg]
weight engine cowling : 1684.8 [kg]
weight thrust reversers : 972.0 [kg]
total weight propulsion system : 15772 [kg](6.3 [%])
***************************************************************
Accommodation cabin facilities:
typical 2-class cabin layout for 310 passengers : economy : pitch : 81.3 [cm] 32.0 [-in]
( 2+4+2 ) seating in 39.5 rows
weight passenger seats : 1859.1 [kg]
weight cabin crew seats : 55.0 [kg]
weight flight crew seats : 63.0 [kg]
weight 2 jump seats in the cockpit :14.0 [kg]
Cebu Pacific operates the A300-900 at the highest density with 459 seats all-economy
high density seating passengers : 442 [pax] at mainly 9 -abreast seating in 56.0 rows,
pitch 73.8 [cm] 29.1 [-in]
pax density, normal seating : 0.83 [m2/pax], high density seating : 0.58 [m2/pax]
weight 9 lavatories : 278.1 [kg]
weight overhead pilot flight crew rest and optional lower deck mobile crew rest
compartment : 210 [kg]
weight 8 galleys : 962.6 [kg]
weight overhead stowage for hand luggage : 108.5 [kg]
weight 3 wardrobe closets : 31.0 [kg]
weight 310 entertainment LCD screens in back of seats : 155.0 [kg]
weight 81 windows (41 x 28 cm) made of acrylic glass : 221.1 [kg]
weight 4 (1.93 x 1.07 [m]) Type A main entry doors : 318.9 [kg]
weight 2 (1.83 x 1.07 [m]) galley service doors : 151.2 [kg]
weight 3 (main door size : 1.71 x 2.44 [m]) freight doors (belly) : 637.3 [kg]*
total belly baggage/cargo hold volume : 196.4 [m3]
underfloor belly hold can accommodate : 32 LD3 containers, netto volume : 143.5 [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 : 5064.8 [kg]
Lion Air A330-900 flight attendants demonstrate flight safety instructions
safety facilities:
weight 2 type I emergency exits (0.61 x 1.60 [m]): 75.4 [kg]
evacuation time with 442 passengers : 63 [sec]
weight 14 hand fire extinguisher : 43 [kg]
weight cockpit voice recorder (CVR) and flight data recorder (FDR): 20.0 [kg]
weight oxygen masks & oxygen generators : 201.5 [kg]
weight emergency flare installation : 10 [kg]
weight 8 emergency evacuation slides : 397.4 [kg]
weight safety equipment & facilities : 748 [kg]
fuselage construction:
fuselage aluminium frame : 29338 [kg]
floor loading (payload/m2): 175 [kg/m2]
weight rear pressure bulkhead : 498.5 [kg]
fuselage covering ( 873.9 [m2] duraluminium 3.86 [mm]) : 9004.9 [kg]
weight floor beams : 4054.1 [kg]
weight cabin furbishing : 3719.9 [kg]
weight cabin floor : 3681.6 [kg]
weight (sound proof) isolation : 510.3 [kg] TO-noise level : 88.0 [EPNdB]
Fuel : (innertank 42000 litre + outertank 3650 litre ) x 2 + trimtank 6230 litre = 97530 litre, optional fuel center tank 41560 litre make total capacity 139090 litre
weight 41560 [litre] main central fuel tanks empty : 831.2 [kg]
weight empty 1386 [litre] potable water tanks : 122.6 [kg]
weight empty waste tank : 63.6 [kg]
weight fuselage structure : 51824.7 [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]
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 reserve ADI, ASI, alti-meter, compass, engine temp. and rpm indicators : 15
[kg]
weight avionics : 163.0 [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 : 1055 [m3] cabin air refreshment time : 3.6
[min]
weight air-conditioning and pressurization system : 495 [kg]
weight APU / engine starter: 162.0 [kg]
weight lighting : 102.3 [kg]
weight triple redundant 207 bar hydraulic system : 228.0 [kg]
weight engine-driven 40kVA electricity generators : 77.5 [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): 17.3 [kg]
weight systems : 1113.9 [kg]
total weight fuselage : 58914 [kg](23.5 [%])
***************************************************************
total weight aluminium ribs (2056 ribs) : 8343 [kg]
weight engine mounts : 324 [kg]
weight 6 wing fuel tanks empty for total 91300 [litre] fuel : 1369 [kg]
weight 556 [litre] vent surge tanks : 67 [kg]
Cebu Pacific A330-941 F-WWKP c/n 2001
weight wing covering (painted aluminium 4.78 [mm]) : 9604 [kg]
total weight aluminium spars (multi-cellular wing structure) : 13925 [kg]
weight wings : 31872 [kg]
weight wing/square meter : 85.68 [kg]
weight thermal leading-edge anti-icing : 70.4 [kg]
weight ailerons made of carbon fiber reinforced plastic CFRP (15.23 [m2]) : 523.0 [kg]
weight fin (65.10 [m2]) : 2793.6 [kg]
weight rudder (27.06 [m2]) : 1114.9 [kg]
weight 6230 [litre] tail fuel trim tank empty : 155.8 [kg]
weight tailplane (stabilizer) (63.93 [m2]): 3017.9 [kg]
weight elevators (16.30 [m2]): 377.79 [kg]
weight flight control hydraulic servo actuators: 114.0 [kg]
weight trailing-edge double slotted flaps (72.54 [m2]) : 2646.5 [kg]
weight track-mounted light alloy construction leading edge slats (37.45 [m2]) : 859.2
[kg]
weight fly-by-wire operated spoilers of graphite composite construction (9.2 [m2]) :
175.0 [kg]
weight airbrakes (4.6 [m2]) : 101.9 [kg]
weight sharklets : 200 [kg]
total weight wing construction : 45783 [kg] (33.7 [%])
*******************************************************************
tire pressure main wheels : 15.60 [Bar] (nitrogen), ply rating : 36 PR
tire speed limit : 376 [km/hr]
total tyre footprint : 1.18 [m2]
Runway LCN at MTOW (0.76m radius of rigidity) : 55 [ ]
Aircraft Classification Number (ACN), MTOW on rigid runway and medium subgrade
strength (B) : 46 [ ] Can only operate from unpaved runways with reduced weight
and reduced tyre pressure
wheel pressure : 27610.0 [kg]
weight 8 Dunlop 55 x 21 main wheels (1400 [mm] by 530 [mm]) : 2113.8 [kg]
weight 2 nose wheels : 264.2 [kg]
weight hydraulic disc wheel-brakes : 181.0 [kg]
weight Duplex anti-skid units : 9.0 [kg]
weight oleo-pneumatic shock absorbers : 241.3 [kg]
weight wheel hydraulic operated retraction system : 2352.8 [kg]
weight undercarriage struts (four-wheel bogies) with axle 6484.0 [kg]
total weight landing gear : 11646.1 [kg] (4.6 [%]
*******************************************************************
********************************************************************
calculated empty weight : 132115 [kg](52.6 [%])
weight oil for 23.9 hours flying : 143.6 [kg]
weight lifejackets : 139.5 [kg]
weight 6 life rafts : 193.8 [kg]
weight catering : 891.2 [kg]
weight water : 1226.4 [kg]
weight crew : 1134 [kg]
weight crew luggage, nav. chards, flight doc., miscell. items : 157 [kg]
operational weight empty : 136000 [kg] (54.2 [%])
********************************************************************
weight 310 passengers : 23870 [kg]
weight luggage : 4960 [kg]
weight cargo : 16170 [kg] (cargo + luggage/m3 belly : 101 [kg/m3])
zero fuel weight (ZFW): 181000 [kg](72.1 [%])
weight fuel for landing (1.9 hours flying) : 10000 [kg]
max. landing weight (MLW): 191000 [kg](76.1 [%])
max. fuel weight : 245186 [kg] (97.7 [%])
payload with max fuel : 63 passengers + luggage 5814 [kg]
published maximum take-off weight : 251000 [kg] (100.0 [%])
calculation : * 4 * (engine power)
power loading (Take-off) : 387 [kg/KN]
power loading (Take-off) 1 PUF: 775 [kg/KN]
max. total take-off power : 648.0 [KN]
calculation : *5* (loads)
manoeuvre load : 0.9 [g] at 9000 [m]
limit load : 2.5 [g] ultimate load : 3.8 [g] load factor : 1.3 [g]
design flight time : 5.75 [hours]
design cycles : 14680 sorties, design hours : 84410 [hours]
max. wing loading (MTOW & flaps retracted) : 675 [kg/m2]
wing stress (2 g) during operation : 136 [N/kg] at 2g emergency manoeuvre
calculation : *6* (angles of attack)
angle of attack zero lift : -1.64 ["]
max. angle of attack (stalling angle, clean) : 11.66 ["]
max. angle of attack (full flaps) : 15.86 ["]
angle of attack at max. speed : 2.79 ["]
calculation : *7* (lift & drag ratios
lift coefficient at angle of attack 0° : 0.15 [ ]
lift coefficient at max. speed : 0.41 [ ]
lift coefficient at max. angle of attack (clean): 1.22 [ ]
max. lift coefficient full flaps : 2.07 [ ]
drag coefficient at max. speed : 0.0458 [ ]
drag coefficient at econ. cruise speed : 0.0458 [ ]
induced drag coefficient at econ. cruise speed : 0.0095 [ ]
drag coefficient (zero lift) : 0.0363 [ ]
lift/drag ratio at econ. speed : 8.87 [ ]
calculation : *8* (speeds
take-off decision speed (V1) : 253 [km/u] (137 [kt])
take-off rotation speed (VR) : 266 [km/u] (144 [kt])
lift-off speed (VLOF) : 285 [km/u] (154 [kt]) at pitch angle : 14.6 [°]
take-off safety speed (V2) : 289 [km/u] (156 [kt])
flap retraction speed (V3) at 500m (OW loaded : 245678 [kg]): 357 [km/u] (193 [kt])
steady initial climb speed (V4) : 315 [km/u] (170 [kt])
climb speed (to FL150 with 63 [%] power) : 487 [km/hr] (263 [kt])
max. endurance speed (Vbe): 474 [km/u] min. fuel/hr : 4320 [kg/hr] at height : 6401 [m]
max. range speed (Vbr): 835 [km/u] (0.79 [mach]) min. fuel consumption : 5.97 [kg/km]
at cruise height : 11278 [m]
max. cruising speed : 880 [km/hr] (475 [kt]) at 11000 [m] (power:29 [%])
max. operational speed (Mmo) : 918 [km/hr] (Mach 0.85 ) at 9450 [m] (power:36 [%])
airflow at cruise speed per engine : 567.5 [kg/s]
speed of thrust jet : 1477 [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): 364 [km/u] (196 [kt])
stalling speed clean at 500 [m] height at Max.Landing Weight : 191000 [kg]): 303
[km/u] (164 [kt])
final approach speed (landing speed) at sea-level with full flaps VREF (max. landing
weight): 272 [km/u] (147 [kt])
ICAO Aircraft Approach Category (APC) : D
stalling speed at sea-level with full flaps VSO (max. landing weight): 209 [km/u]
(113 [kt]
rate of climb at sea-level ROC (loaded, 63 % power) : 795 [m/min]
rate of climb at sea-level ROC (loaded, 75 % power) : 1095 [m/min]
rate of climb at 1000 [m] with 1 engine out (PUF/MTOW, 100 % power on remaining engines) : 342 [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 : 3631 [KW]
Take-off field length with mtow at sea level : 3000 [m]
FAR TO runway length (TOFL) requirement at TOW 251000 [kg] standard day at SL (PUF after V1): 2998 [m]
Landing field length at MLW 191000 kg , at sea level : 2000 [m] (higher then calculated)
+++ FAA certification landing distance : +++
landing weight : 191000 [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 : 1918 [m] (6294 [ft])
landing distance (C.A.R.) from 15 [m] at SL, wet runway: 2206 [m] (7238 [ft])
max. lift/drag ratio : 13.07 [ ]
climb to 5000 [m] with max payload : 5.82 [min]
climb to 10000 [m] with max payload : 17.92 [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: 245678 [kg] ) : 14400 [m]
calculation *10* (action radius & endurance)
range with max. payload: 10930 [km] with 45000.0 [kg] max. useful load (64.1 [%]
fuel)*
range with high density pax: 11589 [km] with 442 passengers (67.7 [%] fuel)*
range with typical two-class pax: 13698 [km] with 310 passengers (78.9 [%] fuel)*
Range with max payload : 8900 km Range with max. Fuel : 17500 km, ferry range 18000 km
range with max.fuel : 17792 [km] with 14 crew and 63 passengers and 100.0 [%] fuel*
ferry range (calculated): 18123 [km] with 3 crew and zero payload (100.0 [%] fuel)*
max range theoretically with additional fuel tanks total 150329 [litre] fuel : 19409
[km]*
* calculated ranges without fuel reserves
Available Seat Kilometres (ASK) : 4753370 [paskm]
useful load with range 1000km : 45000 [kg]
useful load with range 1000km : 442 passengers
production (theor.max load): 39600 [tonkm/hour]
production (useful load): 39600 [tonkm/hour]
production (passengers): 327205 [paskm/hour]
oil and fuel consumption per tonkm : 0.135 [kg]
calculation *11* (operating cost)
fuel cost per hour (6779 [litre]):4067 [eur] (48 [pax-km/litre fuel])
fuel cost per seat 1000km flight (372 [pax] 2-class seating): 12.43 [eur/1000PK]
oil cost per hour: 24 [eur]
crew cost per hour : 1950 [eur]
list price 2024 : 152 [mln USD]
average flying hours in 1 year : 3500 [hours] technical life : 24 [year]
real average service life : 22 [years]
depreciation - 28 [years] to 10% residual value
economic hours (expected total flying hours) : 98000 [hours]
financing interest per flying hour : 977 [EUR]
Delta Airlines A330-900 N405DX at Schiphol, November 2020
write off per flying hour : 1639 [EUR]
time between engine failure : 12828 [hr]
can continue fly on 1 engine, low risk for emergency landing for PUF
workhours per day : 10.84 [hr]
no fatalities during service life > 100%% safe
average flight hours till crash : 2.02 [mln hr] (577 service years)
safe flight hours till fatality : 2019570 [hr] (577.0 service years)
reservation pax liability/flying hour : 0.06 [SDR*] (0.08 [eur])
insurance cost per hour : 346 [eur] insurance rate : 2.2 [%]
engine maintenance cost per hour : 3547.7 [eur]
wing maintenance cost per hour : 142.3 [eur]
fuselage maintenance cost per hour : 52.86 [eur]
engine repair cost per hour : 5.46 [eur]
tire life (time till worn out) : 108 [cycles]
maintenance cost per hour (excluding engines): 2325 [eur]
direct operating cost per hour: 16551 [eur], DOC per km : 19.00 [eur]
DOC per seat 1000km flight (372 [pax] 2-class seating): 50.58 [eur/1000PK]
DOC per seat 1000km flight (high density seating): 42.56 [eur/1000PK]
DOC per kg cargo for a 1000km flight : 0.42 [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 : 4.05 [eur/pax]
airport landing fee / passenger : 4.05 [eur/pax]
retour ticket price 1000km trip : 176.23 [eur/pax]
price retour ticket Schiphol-Barcelona : 204.05 [eur/pax]
accidents with fatalities > there are none
Literature :
https://contentzone.eurocontrol.int/aircraftperformance/default.aspx?
ac_a330_jul2023_0.pdf (airbus.com)
A330-900 | A330 | Aircraft | Airbus Aircraft
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 25 February 2024 contact : info.aircraftinvestigation@gmail.com ac jetpax 2020.py python 3.7.4
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