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weight and performance calculations for the Airbus A350-900ULR
Singapore Airlines first A350-900ULR, 9V-SVA
Airbus A350-900ULR
role : jumbo jet
importance : **
first flight : 23 April 2018 operational : September 2018
country : EU-consortium
ICAO aircraft type designator : A359
production : 11 aircraft
general information :
Longest range airliner in 2024.
Singapore Airlines is using the ULR version on stop flights from Singapore to New
York, San Francisco and Los Angeles.
primary users : Singapore Airlines
Accommodation:
flight crew : 3 cabin crew : 12
flight crew consist of pilot, co-pilot and relief pilot
passengers : seating for 173 in two class : 80 business class and 93 premium economy class seats ( 40 -in pitch)
exit limit : 440 passengers, high density seating for 423 passengers
engine : 2 Rolls Royce Trent XWB-84 turbofan engines of 374.5 [KN] (84190 [lbf])
dimensions :
wingspan : 64.75 [m], length overall: 66.8 [m], length of fuselage : 65.26 [m]
height : 17.05 [m] wing area gross : 442.0 [m^2] fuselage exterior width : 5.96 [m]
weights :
operating empty weight : 142400 [kg] max. structural payload : 53300 [kg]
Zero Fuel weight (ZFW) : 195700 [kg] max. landing weight (MLW) : 207000 [kg]
max. take-off weight : 280000 [kg] weight usable fuel : 130693 [kg] (166488 [litres])
performance :
Max. operating Mach number (Mmo) : 0.88 [Mach] (950 [km/hr]) at 9450 [m]
critical Mach speed : 0.85 [Mach]
max. cruising speed : 903 [km/hr] (Mach 0.85 ) at 11000 [m] (34 [%] power)
economic cruising speed : 871 [km/hr] (Mach 0.82 ) at 11000 [m]
service ceiling : 13100 [m]
range with max fuel and MTOW : 19600 [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 : two-spar multi-rib fail safe main wing box with CFRP skin with trailing edge
single-slotted Fowler flaps with full-span slotted LE flaps (slats), with spoilers
(outboard) and airbrakes (inboard) and with winglets made from Carbon Fiber
Reinforced Polymer (CFRP) airfoil : Airbus. average thickness/chord ratio : 12.3
[%], sweep angle 3/4 chord: 31.9 [°] incidence : 3.50 [°], dihedral : 6.0 [°]
Fuselage : Pressurized CFRP semi-monocoque fail safe structure of circular section
calculation : *1* (dimensions)
wing chord at root : 13.47 [m]
wing chord at tip : 2.56 [m]
taper ratio : 0.190 [ ]
mean wing chord : 6.83 [m]
wing aspect ratio : 9.49 []
Oswald factor (e): 0.704 []
seize (span*length*height) : 73746 [m^3]
calculation : *2* (fuel consumption)
oil consumption : 3.0 [kg/hr]
fuel consumption (econ. cruise speed) : 5700.2 [kg/hr] (7261.4 [litre/hr]) at 16 [%]
power
distance flown for 1 kg fuel : 0.15 [km/kg] at 11000 [m] height, sfc : 48.6 [kg/KN/h]
total fuel capacity : 166488 [litre] (130693 [kg])
calculation : *3* (weight)
weight engine(s) dry : 14554.0 [kg] = 19.43 [kg/KN]
weight 107.5 litre oil tank : 9.14 [kg]
oil tank filled with 4.7 litre oil : 4.2 [kg]
oil in engine 9.2 litre oil : 8.2 [kg]
weight all fuel lines and pumps containing 136 litres fuel : 190.0 [kg]
weight engine cowling : 1947.4 [kg]
weight thrust reversers : 1123.5 [kg]
total weight propulsion system : 17837 [kg](6.4 [%])
***************************************************************
Accommodation cabin facilities:
typical 2-class cabin layout for 173 passengers : economy : pitch : 101.6 [cm] 40.0 [-in]
( 2+4+2 ) seating in 31.6 rows
weight passenger seats : 1996.3 [kg]
weight cabin crew seats : 60.0 [kg]
weight flight crew seats : 63.0 [kg]
weight 2 jump seats in the cockpit :14.0 [kg]
high density seating passengers : 423 [pax] at mainly 10 -abreast seating in 43.8 rows,
pitch 76.2 [cm] 30.0 [-in]
pax density, normal seating : 1.59 [m2/pax], high density seating : 0.65 [m2/pax]
Singapore Airlines A350-900ULR business class
passenger cabin luxurious spaced for good service, enough space for galleys and toilets even at HD seating
weight 8 lavatories : 241.3 [kg]
weight overhead pilot flight crew rest and optional lower deck mobile crew rest compartment : 264.0 [kg]
weight 13 galleys : 700.6 [kg]
weight overhead stowage for hand luggage (total : 35.9 [m3]) : 122.9 [kg]
weight 4 wardrobe closets : 17.3 [kg]
weight 173 entertainment LCD screens in back of seats : 86.5 [kg]
weight 65 windows (41 x 28 cm) made of acrylic glass : 178.3 [kg]
weight 8 (2.16 x 1.26 [m]) Type A+ main entry doors : 664.5 [kg]
weight 3 (main door size : 1.76 x 2.91 [m]) freight doors (belly) : 618.5 [kg]*
total usable belly baggage/cargo hold volume : 111.1 [m3]
underfloor belly hold can accommodate : 16 LD3 containers, netto volume : 71.6 [m3]
and : 11.4 [m3] usable bulk cargo
cabin volume (usable), excluding flight deck : 803 [m3]
passenger compartment volume : 472 [m3]
passenger cabin max width : 5.61 [m] cabin length : 49.76 [m] max cabin height : 2.54
[m] floor area : 275.5 [m2]
weight cabin facilities : 5027.2 [kg]
safety facilities:
evacuation time with 423 passengers : 39 [sec]
weight 9 hand fire extinguisher : 27 [kg]
weight cockpit voice recorder (CVR) and flight data recorder (FDR): 20.0 [kg]
weight oxygen masks & oxygen generators (deploy cabin alt.>4267m): 112.5 [kg]
weight emergency flare installation : 10 [kg]
weight 8 emergency evacuation slides : 234.3 [kg]
weight safety equipment & facilities : 404 [kg]
fuselage construction:
fuselage CFRP frame : 24873 [kg]
floor loading (payload/m2): 193 [kg/m2]
weight rear pressure bulkhead : 358.8 [kg]
fuselage covering ( 937.2 [m2] CFRP 3.89 [mm]) : 5792.7 [kg]
weight paint fuselage : 196.8 [kg]
weight aluminium-lithium alloy floor beams : 4414.4 [kg]
weight cabin furbishing : 4244.6 [kg]
weight cabin floor : 3893.4 [kg]
weight (sound proof) isolation : 563.8 [kg] TO-noise level : 88.8 [EPNdB]
Wing fuel tanks : 29924 litres x 2 = 59848 liter + 107039 litres center tank = 166887 litres total capacity, MSC 166488 litres
weight 107164 [litre] main central fuel tanks empty : 2143.3 [kg]
weight empty 1280 [litre] potable water tanks : 113.3 [kg]
weight empty waste tank : 76.3 [kg]
weight fuselage structure : 46670.7 [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 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 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
7475 [m] and gives equivalent of 1800 [m] at 12200 [m]. pressure differential :
0.64 [bar] (kg/cm2) pressurized fuselage volume : 1219 [m3] cabin air refreshment
time : 4.4 [min]
weight air-conditioning and pressurization system : 472 [kg]
weight APU / engine starter : 187.2 [kg]
weight lighting : 57.1 [kg]
weight triple redundant 207 bar hydraulic system : 245.8 [kg]
weight three engine-driven 90kVA 400 Hertz electricity generators : 43.2 [kg]
weight integrated drive generator (IDG) : 25 [kg]
weight ram air turbine for emergency electric power : 5.0 [kg]
weight three 24V 25Ah Li-ion batteries : 35.5 [kg]
weight controls (sidestick FBW): 17.9 [kg]
weight systems : 1084.2 [kg]
total weight fuselage : 53349 [kg](19.1 [%])
***************************************************************
total weight aluminium-lithium alloy ribs (1961 ribs) : 9346 [kg]
weight titanium engine pylons : 374 [kg]
weight 4 wing fuel tanks empty for total 59847 [litre] fuel : 898 [kg]
weight 666 [litre] vent surge tanks : 80 [kg]
weight wing covering CFRP 3.86 [mm]) : 5463 [kg]
load on front upper spar (clmax) per running metre : 19938.6 [N]
load on rear upper spar (vmax) per running metre : 13071.3 [N]
total weight CFRP spars (multi-cellular wing structure) : 25035 [kg]
weight wings : 39843 [kg]
weight wing/square meter : 90.14 [kg]
weight thermal leading-edge anti-icing : 71.2 [kg]
weight ailerons made of carbon fiber reinforced plastic CFRP (12.00 [m2]) : 433.4 [kg]
weight fin (94.3 [m2]) : 4255.4 [kg]
weight rudder (28.3 [m2]) : 1226.5 [kg]
weight tailplane (stabilizer) (54.8 [m2]): 2722.3 [kg]
weight elevators (23.5 [m2]): 573.3 [kg]
weight paint wing & tail surfaces : 248.3 [kg]
weight flight control hydraulic servo actuators: 122.9 [kg]
weight trailing-edge single slotted Fowler flaps (61.88 [m2]) : 1816.8 [kg]
weight track-mounted light alloy construction leading edge slats (57.35 [m2]) : 1382.2
[kg]
weight spoilers made of CFRP (9.2 [m2]) : 182.8 [kg]
weight airbrakes (21.4 [m2]) : 470.0 [kg]
weight winglets : 200 [kg]
total weight wing construction : 54901 [kg] (38.6 [%])
*******************************************************************
tire pressure main wheels : 17.10 [Bar] (nitrogen), ply rating : 42 PR
tire speed limit : 376 [km/hr]
total tyre footprint : 1.20 [m2]
Runway LCN at MTOW (0.76m radius of rigidity) : 68 [ ]
Aircraft Classification Number (ACN), MTOW on flexible runway and medium
subgrade strength (B) : 83 [ ]
Can only operate from paved runways subgrade A
wheel pressure : 30800.0 [kg]
wheel track : 10.60 [m] wheelbase : 28.66 [m]
weight 8 Dunlop 55 x 21 main wheels (1400 [mm] by 530 [mm]) : 2812.6 [kg]
weight 2 nose wheels : 351.6 [kg]
weight carbon wheel-brakes : 195.7 [kg]
weight Duplex anti-skid units : 9.0 [kg]
weight oleo-pneumatic shock absorbers : 260.9 [kg]
weight wheel hydraulic operated retraction system : 2479.1 [kg]
weight undertail bumper : 20 [kg]
weight titanium undercarriage struts (four-wheel bogies) with axle 6142.5 [kg]
total weight landing gear : 12271.4 [kg] (4.4 [%]
*******************************************************************
********************************************************************
calculated empty weight : 138358 [kg](49.4 [%])
weight oil for 26.0 hours flying : 82.4 [kg]
unusable fuel in engine and tanks 522.8 litre fuel : 410.4 [kg]
weight lifejackets : 77.9 [kg]
weight 3 life rafts : 108.1 [kg]
weight catering : 821.0 [kg]
weight water : 1132.9 [kg]
weight crew : 1215 [kg]
weight crew luggage, navigation chards, flight docs (NOTOC), manuals, miscellaneous
items : 195 [kg]
operational weight empty : 142400 [kg] (50.9 [%])
********************************************************************
weight 173 passengers : 13321 [kg]
weight luggage : 2768 [kg]
weight cargo : 17368 [kg] (cargo + luggage/m3 belly : 175 [kg/m3])
zero fuel weight (ZFW): 195700 [kg](69.9 [%])
weight fuel for landing (2.0 hours flying) : 11300 [kg]
max. landing weight (MLW): 207000 [kg](73.9 [%])
max. fuel weight : 273093 [kg] (97.5 [%])
payload with max fuel : 74 passengers + luggage 6907 [kg]
published maximum take-off weight : 280000 [kg] (100.0 [%])
calculation : * 4 * (engine power)
power loading (Take-off) : 374 [kg/KN]
power loading (Take-off) 1 PUF: 748 [kg/KN]
max. total take-off power : 749.0 [KN]
calculation : *5* (loads)
manoeuvre load : 1.1 [g] at 9000 [m]
limit load : 2.5 [g] ultimate load : 3.8 [g] load factor : 1.1 [g]
design flight time : 7.50 [hours]
design cycles : 12190 sorties, design hours : 91425 [hours]
max. wing loading (MTOW & flaps retracted) : 633 [kg/m2]
wing stress (2 g) during operation : 120 [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) : 12.45 ["]
max. angle of attack (full flaps) : 16.65 ["]
angle of attack at economic cruise speed : 3.34 ["]
calculation : *7* (lift & drag ratios
lift coefficient at angle of attack 0° : 0.15 [ ]
lift coefficient at max. speed : 0.35 [ ]
lift coefficient at max. angle of attack (clean): 1.26 [ ]
max. lift coefficient full flaps : 2.04 [ ]
drag coefficient at max. speed : 0.0232 [ ]
drag coefficient at econ. cruise speed : 0.0249 [ ]
induced drag coefficient at econ. cruise speed : 0.0095 [ ]
drag coefficient (zero lift) : 0.0154 [ ]
lift/drag ratio at econ. speed : 15.15 [ ]
calculation : *8* (speeds
take-off decision speed (V1) : 255 [km/u] (138 [kt])
take-off rotation speed (VR) : 268 [km/u] (145 [kt])
minimum unstick speed (Vmu) at TO angle 13.5 ° : 280 [km/u] (151 [kt])
lift-off speed (VLOF) : 302 [km/u] (163 [kt]) at pitch angle : 11.8 [°]
take-off safety speed (V2) : 304 [km/u] (164 [kt])
flap retraction speed (V3) at 500m (OW loaded : 274300 [kg]): 341 [km/u] (184 [kt])
steady initial climb speed (V4) : 330 [km/u] (178 [kt])
climb speed (to FL150 with 56 [%] power) : 679 [km/hr] (367 [kt])
max. endurance speed (Vbe): 742 [km/u] min. fuel/hr : 5540 [kg/hr] at height : 10363 [m]
max. range speed (Vbr): 881 [km/u] (0.84 [mach]) min. fuel consumption : 6.40 [kg/km]
at cruise height : 11582 [m]
max. cruising speed : 903 [km/hr] (488 [kt]) at 11000 [m] (power:16 [%])
max. operational speed (Mmo) : 950 [km/hr] (Mach 0.88 ) at 9450 [m] (power:20 [%])
airflow at cruise speed per engine : 645.2 [kg/s]
speed of thrust jet : 1247 [km/hr]
initial descent speed 10000 - 7315 [m]: Mach 0.72
descent speed 7315 - 3048 [m]: 537 [km/u] (290 [kt])
approach speed 3048 - 500 [m] (clean): 426 [km/u] (230 [kt])
minimum control speed (MCS) Vmca (clean): 342 [km/u] (184 [kt])
stalling speed clean at 500 [m] height at Max.Landing Weight : 207000 [kg]): 285
[km/u] (154 [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] (108
[kt]
rate of climb at sea-level ROC (loaded, 56 % power) : 1138 [m/min]
rate of climb at sea-level ROC (loaded, 75 % power) : 1877 [m/min]
rate of climb at 1000 [m] with 1 engine out (PUF/MTOW, 100 % power on remaining
engines) : 749 [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 : 4141 [KW]
FAR TO runway length (TOFL) requirement at TOW 280000 [kg] standard day at SL
(PUF after V1): 2800 [m]
+++ FAA certification landing distance : +++
landing weight : 207000 [kg], TE flap setting : 40 [°]
runway condition : dry , landing over 50ft (15m) at threshold at sea-level
without use of thrust reversers
FAA approved landing field length at SL, dry runway : 1972 [m] (6471 [ft])
landing distance (C.A.R.) from 15 [m] at SL, wet runway: 2238 [m] (7342 [ft])
max. lift/drag ratio : 18.47 [ ]
climb to 5000 [m] with max payload : 4.07 [min]
climb to 10000 [m] with max payload : 12.52 [min]
descent time from 10000 [m] to 250 [m] : 24.33 [min]
max. ceiling fully loaded (mtow- 60 min.fuel): 274300 [kg] ) : 15400 [m]
ceiling limited by max. pressure differential 17475 [m]
max. theoretical ceiling (OWE + 60 min.fuel) : 18600 [m] with flying weight : 148100
[kg]
calculation *10* (action radius & endurance)
range with max. payload: 11849 [km] with 53300.0 [kg] max. useful load (64.5 [%]
fuel)*
range with high density pax: 14169 [km] with 423 passengers (75.2 [%] fuel)*
range with typical two-class pax: 18265 [km] with 173 passengers (93.0 [%] fuel)*
Range with 173 pax (15570 kg payload) : 9700nm (17964km)
Range with max fuel (5000 kg payload) : 10780nm > 19970km
Ferry range : 11000nm > 20370km
range with max.fuel : 19970 [km] with 15 crew and 74 passengers and 100.0 [%] fuel*
ferry range (calculated): 20678 [km] with 3 crew and zero payload (100.0 [%] fuel)*
max range theoretically with additional fuel tanks total 179014 [litre] fuel : 21851
[km]*
* calculated ranges without fuel reserves
Available Seat Kilometres (ASK) : 6029693 [paskm]
useful load with range 1000km : 53300 [kg]
useful load with range 1000km : 423 passengers
production (theor.max load): 48130 [tonkm/hour]
production (useful load): 48130 [tonkm/hour]
production (passengers): 360538 [paskm/hour]
oil and fuel consumption per tonkm : 0.118 [kg]
calculation *11* (operating cost)
fuel cost per hour (7261 [litre]):4357 [eur] (50 [pax-km/litre fuel])
fuel cost per seat 1000km flight (399 [pax] 2-class seating): 12.08 [eur/1000PK]
oil cost per hour: 12 [eur]
crew cost per hour : 2100 [eur]
list price 2024 : 317 [mln USD]
average flying hours in 1 year : 4000 [hours] technical life : 23 [year]
real average service life : 22 [years]
depreciation : 24 [years] to 10% residual value
economic hours (expected total flying hours) : 96000 [hours]
financing interest per flying hour : 1784 [EUR]
write off per flying hour : 2993 [EUR]
time between engine failure : 13573 [hr]
can continue fly on 1 engine, low risk for emergency landing for PUF
workhours per day : 12.05 [hr]
no fatalities during service life > 100%% safe
average flight hours till crash : 0.22 [mln hr] (54 service years)
safe flight hours till fatality : 216040 [hr] (54.0 service years)
reservation pax liability/flying hour : 0.60 [SDR*] (0.75 [eur])
insurance cost per hour : 6757 [eur] insurance rate : 23.0 [%]
engine maintenance cost per hour : 5008.3 [eur]
wing maintenance cost per hour : 129.7 [eur]
fuselage maintenance cost per hour : 33.32 [eur]
tire life (time till worn out) : 110 [cycles]
maintenance cost per hour (excluding engines): 2714 [eur]
direct operating cost per hour: 25726 [eur], DOC per km : 29.54 [eur]
DOC per seat 1000km flight (399 [pax] 2-class seating): 71.36 [eur/1000PK]
DOC per seat 1000km flight (high density seating): 67.39 [eur/1000PK]
DOC per kg cargo for a 1000km flight : 0.53 [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 : 4.25 [eur/pax]
airport landing fee / passenger : 4.25 [eur/pax]
retour ticket price 1000km trip : 222.78 [eur/pax]
price retour ticket Schiphol-Barcelona : 262.03 [eur/pax]
accidents with fatalities > there have been no fatal accidents with an A350-900ULR
Literature :
Singapore Airlines’ first Airbus A350-900ULR delivered – Australian Aviation
https://contentzone.eurocontrol.int/aircraftperformance/default.aspx ?
https://www.airbus.com/en/airport-operations-and-technical-data/aircraft-characteristics
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 30 October 2024 contact : info.aircraftinvestigation@gmail.com ac jetpax 2020.py python 3.7.4
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