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weight and performance calculations for the Airbus A330-200 WV020
KLM A330-203 PH-AOD c/n 738 at Schiphol, Amsterdam, December 2022, it has GE CF6-80E1A3 engines
Airbus A330-200 WV020
role : wide-body long-range airliner
importance : ****
first flight : 13 August 1997 operational : April 1998 (Canada 3000)
country : EU-consortium
production : 645 aircraft
general information :
Has a shortened fuselage and therefore a longer range. Follow-up of the A300-600R and
competitor of the 767-300ER.
primary users : Canada 3000, KLM, Sabena
Accommodation:
flight crew : 2 cabin crew : 9
passengers : seating for 246 in two class : 36 business class and 210 economy class seats ( 32 -in pitch)
exit limit : 406 passengers, high density seating for 390 passengers
engine : 2 General Electric CF6-80E1A2 turbofan engines of 310.0 [KN] (69689.6 [lbf])
dimensions :
wingspan : 60.3 [m], length overall: 58.82 [m], length of fuselage : 57.07 [m] height : 17.39 [m]
wing area : 363.1 [m^2] fuselage exterior width : 5.64 [m]
weights :
operating empty weight : 120150 [kg] max. structural payload : 47850 [kg]
Zero Fuel weight (ZFW) : 168000 [kg] max. landing weight (MLW) : 180000 [kg]
max. take-off weight : 229800 [kg] weight fuel : 109194 [kg] (139100 [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] (34 [%] power)
economic cruising speed : 860 [km/hr] (Mach 0.81 ) at 11000 [m]
service ceiling : 12500 [m]
range with max fuel and MTOW : 16575 [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 with winglets
made from Carbon Fiber Reinforced Plastic (CFRP)
airfoil : Airbus
average thickness/chord ratio : 12.3 [%], sweep angle 3/4 chord: 30.0 [°]
calculation : *1* (dimensions)
wing chord at root : 10.56 [m]
wing chord at tip : 2.46 [m]
taper ratio : 0.233 [ ]
mean wing chord : 6.02 [m]
wing aspect ratio : 10.01 []
Oswald factor (e): 0.704 []
seize (span*length*height) : 61680 [m^3]
calculation : *2* (fuel consumption)
oil consumption : 16.7 [kg/hr]
fuel consumption (econ. cruise speed) : 5541.8 [kg/hr] (7059.7 [litre/hr]) at 26 [%] power
distance flown for 1 kg fuel : 0.16 [km/kg] at 11000 [m] height, sfc : 33.8 [kg/KN/h]
total fuel capacity : 139100 [litre] (109194 [kg])
calculation : *3* (weight)
weight engine(s) dry : 10184.0 [kg] = 16.43 [kg/KN]
weight 453.9 litre oil tank : 38.58 [kg]
oil tank filled with 3.9 litre oil : 3.5 [kg]
oil in engine 7.6 litre oil : 6.8 [kg]
fuel in engine 33.8 litre fuel : 24.80 [kg]
weight fuel lines : 169.2 [kg]
weight engine cowling : 1612.0 [kg]
weight thrust reversers : 930.0 [kg]
total weight propulsion system : 12969 [kg](5.6 [%])
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Accommodation cabin facilities:
typical 2-class cabin layout for 246 passengers : economy : pitch : 81.3 [cm] 32.0 [-in]
( 2+4+2 ) seating in 31.4 rows
weight passenger seats : 1692.9 [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 : 390 [pax] at mainly 9 -abreast seating in 49.4 rows,
pitch 76.3 [cm] 30.0 [-in]
pax density, normal seating : 0.95 [m2/pax], high density seating : 0.60 [m2/pax]
weight 7 lavatories : 206.2 [kg]
weight overhead pilot flight crew rest and optional lower deck mobile crew rest
compartment : 210 [kg]
weight 7 galleys : 697.4 [kg]
Qatar airways A330-200 interior
weight overhead stowage for hand luggage : 86.1 [kg]
weight 2 wardrobe closets : 24.6 [kg]
weight 246 entertainment LCD screens in back of seats : 123.0 [kg]
weight 65 windows (41 x 28 cm) made of acrylic glass : 177.0 [kg]
weight 4 (1.93 x 1.07 [m]) Type A main entry doors : 324.1 [kg]
weight 2 (1.83 x 1.07 [m]) galley service doors : 153.6 [kg]
weight 3 (main door size : 1.71 x 2.44 [m]) freight doors (belly) : 647.7 [kg]*
total belly baggage/cargo hold volume : 162.7 [m3]
underfloor belly hold can accommodate : 26 LD3 containers, netto volume : 116.1 [m3]
and : 19.7 [m3] bulk cargo
cabin volume (usable), excluding flight deck : 603 [m3]
passenger compartment volume : 339 [m3]
passenger cabin max width : 5.26 [m] cabin length : 45.03 [m] max cabin height : 2.54 [m]
floor area : 233.6 [m2]
weight cabin facilities : 4443.6 [kg]
safety facilities:
weight 2 type I emergency exits (0.61 x 1.60 [m]): 76.6 [kg]
evacuation time with 390 passengers : 55 [sec]
weight 12 hand fire extinguisher : 35 [kg]
weight cockpit voice recorder (CVR) and flight data recorder (FDR): 20.0 [kg]
weight oxygen masks & oxygen generators : 159.9 [kg]
weight emergency flare installation : 10 [kg]
weight 8 emergency evacuation slides : 420.4 [kg]
weight safety equipment & facilities : 722 [kg]
fuselage construction:
fuselage aluminium frame : 27572 [kg]
floor loading (payload/m2): 205 [kg/m2]
weight rear pressure bulkhead : 490.6 [kg]
fuselage covering ( 808.2 [m2] duraluminium 3.80 [mm]) : 8208.3 [kg]
weight floor beams : 3582.6 [kg]
weight cabin furbishing : 3388.0 [kg]
weight cabin floor : 3352.4 [kg]
weight (sound proof) isolation : 640.8 [kg] TO-noise level : 97.4 [EPNdB]
weight 41655 [litre] main central fuel tanks empty : 833.1 [kg]
weight empty 1004 [litre] potable water tanks : 88.9 [kg]
weight empty waste tank : 55.6 [kg]
weight fuselage structure : 48212.6 [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 Air Transat A330-200 C-GITS at Amsterdam, July 2011
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 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 reserve ADI, ASI, alti-meter, compass, engine temp. and rpm indicators : 15 [kg]
weight avionics : 154.0 [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 : 950 [m3] cabin air refreshment time : 3.8 [min]
weight air-conditioning and pressurization system : 422 [kg]
weight APU / engine starter: 155.0 [kg]
weight lighting : 81.2 [kg]
weight triple redundant 207 bar hydraulic system : 205.6 [kg]
weight engine-driven 40kVA electricity generators : 61.5 [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): 16.2 [kg]
weight systems : 973.6 [kg]
total weight fuselage : 54506 [kg](23.7 [%])
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total weight aluminium ribs (1834 ribs) : 7710 [kg]
weight engine mounts : 310 [kg]
weight 6 wing fuel tanks empty for total 91301 [litre] fuel : 1370 [kg]
weight 556 [litre] vent surge tanks : 67 [kg]
weight wing covering (painted aluminium 4.22 [mm]) : 8268 [kg]
total weight aluminium spars (multi-cellular wing structure) : 11026 [kg]
weight wings : 27004 [kg]
weight wing/square meter : 74.37 [kg]
weight thermal leading-edge anti-icing : 66.3 [kg]
weight ailerons made of carbon fiber reinforced plastic CFRP (14.87 [m2]) : 443.2 [kg]
weight fin (57.79 [m2]) : 2153.2 [kg]
weight rudder (24.02 [m2]) : 859.3 [kg]
weight 6144 [litre] tail fuel trim tank empty : 153.6 [kg]
weight tailplane (stabilizer) (59.07 [m2]): 2421.1 [kg]
weight elevators (15.06 [m2]): 303.08 [kg]
weight flight control hydraulic servo actuators: 102.8 [kg]
weight trailing-edge double slotted flaps (70.80 [m2]) : 2243.1 [kg]
weight track-mounted light alloy construction leading edge slats (36.56 [m2]) : 728.5 [kg]
weight fly-by-wire operated spoilers of graphite composite construction (9.0 [m2]) : 149.3 [kg]
weight airbrakes (4.5 [m2]) : 87.5 [kg]
weight winglets : 200 [kg]
total weight wing construction : 38661 [kg] (32.2 [%])
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A330-200 at mtow 230.000 kg wheel size 140x53 cm, pressure 14.2 bar
tire pressure main wheels : 14.20 [Bar] (nitrogen), ply rating : 30 PR
tire speed limit : 376 [km/hr]
total tyre footprint : 1.19 [m2]
Runway LCN at MTOW (0.76m radius of rigidity) : 50 [ ]
Aircraft Classification Number (ACN), MTOW on rigid runway and medium
subgrade strength (B) : 38 [ ] Can also operate from unpaved runways subgrade B
wheel pressure : 25278.0 [kg]
weight 8 Dunlop 55 x 21 main wheels (1400 [mm] by 530 [mm]) : 1988.8 [kg]
weight 2 nose wheels : 248.6 [kg]
weight hydraulic disc wheel-brakes : 168.0 [kg]
weight Duplex anti-skid units : 9.0 [kg]
weight oleo-pneumatic shock absorbers : 224.0 [kg]
weight wheel hydraulic operated retraction system : 2178.5 [kg]
weight undercarriage struts (four-wheel bogies) with axle 5966.7 [kg]
total weight landing gear : 10783.7 [kg] (4.7 [%]
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Windrose airlines stewardesses on board A330-200 UR-WRQ
********************************************************************
calculated empty weight : 116920 [kg](50.9 [%])
weight oil for 22.6 hours flying : 395.8 [kg]
weight lifejackets : 110.7 [kg]
weight 4 life rafts : 153.8 [kg]
weight catering : 645.8 [kg]
weight water : 888.6 [kg]
weight crew : 891 [kg]
weight crew luggage, nav. chards, flight doc., miscell. items : 145 [kg]
operational weight empty : 120150 [kg] (52.3 [%])
********************************************************************
weight 246 passengers : 18942 [kg]
weight luggage : 3936 [kg]
weight cargo : 24972 [kg] (cargo + luggage/m3 belly : 172 [kg/m3])
zero fuel weight (ZFW): 168000 [kg](73.1 [%])
weight fuel for landing (2.2 hours flying) : 12000 [kg]
max. landing weight (MLW): 180000 [kg](78.3 [%])
max. fuel weight : 229344 [kg] (99.8 [%])
payload with max fuel : 5 passengers + luggage 456 [kg]
published maximum take-off weight : 229800 [kg] (100.0 [%])
calculation : * 4 * (engine power)
power loading (Take-off) : 371 [kg/KN]
power loading (Take-off) 1 PUF: 741 [kg/KN]
max. total take-off power : 620.0 [KN]
calculation : *5* (loads)
manoeuvre load : 1.0 [g] at 9000 [m]
limit load : 2.5 [g] ultimate load : 3.8 [g] load factor : 1.3 [g]
design flight time : 5.25 [hours]
On 24 July 2001 Tamil Tiger rebels launched a suicide attack on Colombo airport (CMB), Sri lanka. SriLankan Airlines A330-243 4R-ALF and 4R-ALE were destroyed in the attack.
design cycles : 14280 sorties, design hours : 74970 [hours]
max. wing loading (MTOW & flaps retracted) : 633 [kg/m2]
wing stress (2 g) during operation : 149 [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) : 12.12 ["]
max. angle of attack (full flaps) : 16.32 ["]
angle of attack at max. speed : 2.51 ["]
calculation : *7* (lift & drag ratios
lift coefficient at angle of attack 0° : 0.15 [ ]
lift coefficient at max. speed : 0.38 [ ]
lift coefficient at max. angle of attack (clean): 1.24 [ ]
max. lift coefficient full flaps : 2.10 [ ]
drag coefficient at max. speed : 0.0324 [ ]
drag coefficient at econ. cruise speed : 0.0327 [ ]
induced drag coefficient at econ. cruise speed : 0.0094 [ ]
drag coefficient (zero lift) : 0.0233 [ ]
Friday 24 August 2001 Air Transat A330-243 C-GITS c/n 271
ISP Flight TS236 from Toronto (YYZ) to Lisboa (LIS) with 13 crew and 293 passengers. En route at FL390 a fuel imbalance was discovered. The crew diverted to Lajes Airport, Azores as a fuel leak was suspected. At a distance of 135 miles from Lajes the right engine flamed out. 13 minutes later also the left engine flamed out, at FL345, 85nm from Lajes as the aircraft run out of fuel. (10515m height, distance 157.4 km > L/D ratio needed 14.97 !) Max. L/D ratio calculated 15.42. Again 13 min later, at 06:39 it was at 13.000 ft and 8 miles from RW33. (77nm in 13 min = 658 km/h) It landed successfully at RW33. Touched down with 200 kts, with only LE slats deployed. Eight tires burst, 18 people got injured during the emergency evacuation. First flight : 1999. Airframe hrs : 10433 cycles : 2390 engines : Trent 772B
location : +-100m 38°45’29”N 27°05’13”W
lift/drag ratio at econ. speed : 11.57 [ ]
calculation : *8* (speeds
take-off decision speed (V1) : 249 [km/u] (134 [kt])
take-off rotation speed (VR) : 261 [km/u] (141 [kt])
Belgian Delsey (VG Airlines) A330-223 OO-SFR, former Sabena, c/n 296 taking off at Schiphol with its PW4168A engines at full power, Amsterdam, July 2002
lift-off speed (VLOF) : 280 [km/u] (151 [kt]) at pitch angle : 14.7 [°]
take-off safety speed (V2) : 284 [km/u] (153 [kt])
flap retraction speed (V3) at 500m (OW loaded : 224258 [kg]): 343 [km/u] (185 [kt])
steady initial climb speed (V4) : 309 [km/u] (167 [kt])
climb speed (to FL150 with 58 [%] power) : 480 [km/hr] (259 [kt])
max. endurance speed (Vbe): 366 [km/u] min. fuel/hr : 4561 [kg/hr] at height : 1524 [m]
max. range speed (Vbr): 819 [km/u] (0.77 [mach]) min. fuel consumption : 6.43 [kg/km] at cruise height : 10973 [m]
max. cruising speed : 880 [km/hr] (475 [kt]) at 11000 [m] (power:28 [%])
max. operational speed (Mmo) : 930 [km/hr] (Mach 0.86 ) at 9450 [m] (power:37 [%])
airflow at cruise speed per engine : 416.0 [kg/s]
speed of thrust jet : 1626 [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): 354 [km/u] (191 [kt])
stalling speed clean at 500 [m] height at Max.Landing Weight : 180000 [kg]): 295 [km/u]
(159 [kt])
final approach speed (landing speed) at sea-level with full flaps VREF (max. landing weight):
259 [km/u] (140 [kt])
ICAO Aircraft Approach Category (APC) : C
stalling speed at sea-level with full flaps VSO (max. landing weight): 199 [km/u] (107 [kt]
rate of climb at sea-level ROC (loaded, 58 % power) : 702 [m/min]
rate of climb at sea-level ROC (loaded, 75 % power) : 1156 [m/min]
rate of climb at 1000 [m] with 1 engine out (PUF/MTOW, 100 % power on remaining
engines) : 375 [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 : 3326 [KW]
Take-off field length at MTOW 230.000 kg at sea level 2450 [m]
FAR TO runway length (TOFL) requirement at TOW 229800 [kg] standard day at SL
(PUF after V1): 2445 [m]
+++ FAA certification landing distance : +++
landing weight : 180000 [kg], TE flap setting : 40 [°]
runway condition : dry , landing over 50ft (15m) at threshold at sea-level
without use of thrust reversers
Landing field length at MLW 180.000 kg at sea level : 1700 [m]
FAA approved landing field length : 1702 [m] (5584 [ft])
landing distance (C.A.R.) from 15 [m] at SL, wet runway: 1943 [m] (6375 [ft])
max. lift/drag ratio : 15.42 [ ]
climb to 5000 [m] with max payload : 6.59 [min]
climb to 10000 [m] with max payload : 20.28 [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: 224258 [kg] ) : 15100 [m]
calculation *10* (action radius & endurance)
range with max. payload: 9027 [km] with 47850.0 [kg] max. useful load (56.6 [%] fuel)*
Range with max payload 45000 kg : 4700 nm > 8700 km, range with max fuel : 8950 nm > 16575 km, ferry range 9250 nm > 17130 km. Note > MTOW in this graph is 242.000 kg
range with high density pax: 10881 [km] with 390 passengers (67.2 [%] fuel)*
range with typical two-class pax: 13092 [km] with 246 passengers (79.5 [%] fuel)*
range with max.fuel : 16945 [km] with 11 crew and 5 passengers and 100.0 [%] fuel*
ferry range (calculated): 17058 [km] with 2 crew and zero payload (100.0 [%] fuel)*
max range theoretically with additional fuel tanks total 142565 [litre] fuel : 17425 [km]*
* calculated ranges without fuel reserves
Available Seat Kilometres (ASK) : 3992916 [paskm]
useful load with range 1000km : 47850 [kg]
useful load with range 1000km : 390 passengers
production (theor.max load): 42108 [tonkm/hour]
production (useful load): 42108 [tonkm/hour]
production (passengers): 297952 [paskm/hour]
oil and fuel consumption per tonkm : 0.132 [kg]
calculation *11* (operating cost)
fuel cost per hour (7060 [litre]):4235 [eur] (42 [pax-km/litre fuel])
fuel cost per seat 1000km flight (339 [pax] 2-class seating): 14.22 [eur/1000PK]
oil cost per hour: 70 [eur]
Canada 3000 A330-202 C-GGWC c/n 272
crew cost per hour : 1500 [eur]
list price 2024 : 134 [mln USD]
average flying hours in 1 year : 4000 [hours] technical life : 19 [year]
real average service life : 18 [years]
depreciation - 20 [years] to 10% residual value
economic hours (expected total flying hours) : 80000 [hours]
financing interest per flying hour : 756 [EUR]
write off per flying hour : 1551 [EUR]
time between engine failure : 14901 [hr]
can continue fly on 1 engine, low risk for emergency landing for PUF
workhours per day : 12.52 [hr]
average flight hours till crash : 23.22 [mln hr] (5805 service years)
safe flight hours till fatality : 140302 [hr] (35.1 service years)
reservation pax liability/flying hour : 0.92 [SDR*] (1.15 [eur])
insurance cost per hour : 27 [eur] insurance rate : 0.2 [%]
engine maintenance cost per hour : 2828.2 [eur]
wing maintenance cost per hour : 152.2 [eur]
fuselage maintenance cost per hour : 58.65 [eur]
tire life (time till worn out) : 96 [cycles]
maintenance cost per hour (excluding engines): 2022 [eur]
direct operating cost per hour: 12990 [eur], DOC per km : 15.11 [eur]
DOC per seat 1000km flight (339 [pax] 2-class seating): 43.60 [eur/1000PK]
DOC per seat 1000km flight (high density seating): 37.84 [eur/1000PK]
DOC per kg cargo for a 1000km flight : 0.31 [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 : 4.51 [eur/pax]
airport landing fee / passenger : 4.51 [eur/pax]
retour ticket price 1000km trip : 162.87 [eur/pax]
price retour ticket Schiphol-Barcelona : 186.85 [eur/pax]
accidents with fatalities > see the accident file
Windrose A330-223 UR-WRQ c/n 296 at Malpensa, Italy, January 2014
Literature :
ac_a330_jul2023_0.pdf (airbus.com)
Airbus-Commercial-Aircraft-ARFC-A330-200-300 (1).pdf
Aircraft Performance Database > A332 (eurocontrol.int)
A330-200 | A330 | Aircraft | Airbus Aircraft
Air international okt’97 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
(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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