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weight and performance calculations for the Airbus A350-1000 (WV001)
Cathay Pacific Airbus A350-1041 B-LXC c/n 188 November 2023 RW 18L Schiphol, delivered July 2018. © bvdz
Airbus A350-1000 (WV002)
role : jumbo jet
importance : ***
first flight : 24 November 2016 operational : February 2018 (Qatar Airways)
country : EU-consortium
ICAO aircraft type designator : A35K
production : 88 aircraft
general information :
The A350-1000 is a stretched version, with 11 frames more than the A350-900. It is
intended as replacement for the A340-600 and to compete with the
Boeing 777- 300ER and Boeing 777-8 . It has a slightly larger wing with trailing
edge extensions. It has a six-wheel bogie main landing gear. It has more powerful RR
Trent XWB engines.
In 2018, the unit cost of the A350-900 was US$ 317.4 million and the A350-1000 was
US$366.5 million.
The Airbus A350 XWB is built of 53% CFRP including wing spars and fuselage components, overtaking the Boeing 787 Dreamliner , for the aircraft with the highest weight ratio for CFRP, which is 50%. This was one of the first commercial aircraft to have wing spars made from composites.
primary users : Qatar Airways, Cathay Pacific, French Bee, Cebu Pacific, Virgin
Atlantic, British Airways
Accommodation:
flight crew : 2 cabin crew : 12
passengers : seating for 369 in two class : 54 business class and 315 economy class
seats ( 32 -in pitch) exit limit : 480 passengers, high density seating for 461 passengers
engine : 2 Rolls Royce Trent XWB-97 turbofan engines of 431.0 [KN] (96891 [lbf])
dimensions :
wingspan : 64.75 [m], length overall: 73.79 [m], length of fuselage : 72.25 [m]
height : 17.08 [m] wing area gross : 464.3 [m^2] fuselage exterior width : 5.96 [m]
weights :
operating empty weight : 155700 [kg] max. structural payload : 67300 [kg]
Zero Fuel weight (ZFW) : 223000 [kg] max. landing weight (MLW) : 236000 [kg]
max. take-off weight : 316000 [kg] weight usable fuel : 124650 [kg] (158790 [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] (33 [%] power)
economic cruising speed : 871 [km/hr] (Mach 0.82 ) at 11000 [m]
service ceiling : 12630 [m]
range with max fuel and MTOW : 15740 [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 Plastic (CFRP). airfoil : Airbus. average thickness/chord
ratio : 12.3 [%], sweep angle 3/4 chord: 31.9 [°] incidence : 5.05 [°], dihedral : 4.0 [°]
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 : 7.17 [m]
wing aspect ratio : 9.03 []
Oswald factor (e): 0.704 []
seize (span*length*height) : 81607 [m^3]
calculation : *2* (fuel consumption)
oil consumption : 3.4 [kg/hr]
fuel consumption (econ. cruise speed) : 6739.3 [kg/hr] (8585.1 [litre/hr]) at 16 [%]
power
distance flown for 1 kg fuel : 0.13 [km/kg] at 11000 [m] height, sfc : 48.6 [kg/KN/h]
total fuel capacity : 158790 [litre] (124650 [kg])
calculation : *3* (weight)
weight engine(s) dry : 15100.0 [kg] = 17.52 [kg/KN]
weight 103.3 litre oil tank : 8.78 [kg]
oil tank filled with 5.4 litre oil : 4.9 [kg]
oil in engine 10.6 litre oil : 9.5 [kg]
weight all fuel lines and pumps containing 136 litres fuel : 231.7 [kg]
weight engine cowling : 2241.2 [kg]
weight thrust reversers : 1293.0 [kg]
total weight propulsion system : 18889 [kg](6.0 [%])
***************************************************************
Accommodation cabin facilities:
typical 2-class cabin layout for 369 passengers : economy : pitch : 81.3 [cm] 32.0 [-in]
( 3+3+3 ) seating in 44.0 rows
weight passenger seats : 2280.5 [kg]
weight cabin crew seats : 60.0 [kg]
weight flight crew seats : 42.0 [kg]
weight 2 jump seats in the cockpit :14.0 [kg]
high density seating passengers : 461 [pax] at mainly 10 -abreast seating in
47.7 rows, pitch 78.7 [cm] 31.0 [-in]
pax density, normal seating : 0.85 [m2/pax], high density seating : 0.68 [m2/pax]
passenger cabin luxurious spaced for good service, enough space for galleys and toilets
even at HD seating
weight 13 lavatories : 389.6 [kg]
weight overhead pilot flight crew rest and optional lower deck mobile crew rest
compartment : 264.0 [kg]
weight 12 galleys : 1225.4 [kg]
weight overhead stowage for hand luggage (total : 41.0 [m3]) : 140.4 [kg]
weight 4 wardrobe closets : 36.9 [kg]
weight 369 entertainment LCD screens in back of seats : 184.5 [kg]
weight 90 windows (41 x 28 cm) made of acrylic glass : 245.9 [kg]
2.16m x 1.26m type A+ main doors
weight 8 (2.16 x 1.26 [m]) Type A+ main entry doors : 694.7 [kg]
weight 3 (main door size : 1.76 x 2.91 [m]) freight doors (belly) : 646.5 [kg]*
total usable belly baggage/cargo hold volume : 288.1 [m3]
Total 44 LD3 containers
underfloor belly hold can accommodate : 44 LD3 containers, netto volume : 196.9 [m3]
and : 11.4 [m3] usable bulk cargo
cabin volume (usable), excluding flight deck : 916 [m3]
passenger compartment volume : 538 [m3]
Cabin width trim-to-trim : 5.51m, cabin width max. 5.61m
passenger cabin max width : 5.61 [m] cabin length : 56.75 [m] max cabin height : 2.54
[m] floor area : 314.7 [m2]
weight cabin facilities : 6224.5 [kg]
safety facilities:
evacuation time with 461 passengers : 42 [sec]
weight 10 hand fire extinguisher : 31 [kg]
weight cockpit voice recorder (CVR) and flight data recorder (FDR): 20.0 [kg]
weight oxygen masks & oxygen generators (deploy cabin alt.>4267m): 239.8 [kg]
weight emergency flare installation : 10 [kg]
weight 8 emergency evacuation slides : 499.8 [kg]
weight safety equipment & facilities : 800 [kg]
fuselage construction:
fuselage CFRP frame : 29090 [kg]
floor loading (payload/m2): 214 [kg/m2]
weight rear pressure bulkhead : 373.4 [kg]
fuselage covering ( 1048.5 [m2] CFRP 4.05 [mm]) : 6730.6 [kg]
weight paint fuselage : 220.2 [kg]
weight floor beams : 3685.9 [kg]
![Inside the Airbus A350-1000, in the Economy cabin [OC] : r/aviation](images/Airbus_A350-1000/image10.png)
weight cabin furbishing : 4847.6 [kg]
weight cabin floor : 4032.5 [kg]
weight (sound proof) isolation : 629.5 [kg] TO-noise level : 88.8 [EPNdB]
weight 78435 [litre] main central fuel tanks empty : 1568.7 [kg]
weight empty 1452 [litre] potable water tanks : 128.5 [kg]
weight empty waste tank : 70.3 [kg]
weight fuselage structure : 51376.7 [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]
Cathay Pacific A350-1000 cockpit
weight VOR/ILS,RMI,DME,radio altimeter, ASI, time clock : 20.0 [kg]
weight Avionic Flight Control System : 33.0 [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 6450
[m] and gives equivalent of 2400 [m] at 12200 [m]. pressure differential : 0.58 [bar]
(kg/cm2) pressurized fuselage volume : 1383 [m3] cabin air refreshment time : 3.8
[min]
weight air-conditioning and pressurization system : 620 [kg]
weight APU / engine starter : 215.5 [kg]
weight lighting : 121.8 [kg]
weight triple redundant 207 bar hydraulic system : 272.0 [kg]
weight three engine-driven 90kVA 400 Hertz electricity generators : 92.2 [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): 19.1 [kg]
weight systems : 1400.8 [kg]
total weight fuselage : 59965 [kg](19.0 [%])
***************************************************************
total weight CFRP ribs (2091 ribs) : 10470 [kg]
weight titanium engine pylons : 431 [kg]
Wing tanks 2x 29434 litre = 58868 litre + center tank 78435 litre = 137303 litre, useful fuel 158790, additional optional tank needed for 21487 litre (not in this drawing). Expected wing fuel capacity, estimation = 464 m2 x 250 = 116000 litres. The center tank in this drawing extends into the wing.
weight 4 wing fuel tanks empty for total 80853 [litre] fuel : 1213 [kg]
weight 635 [litre] vent surge tanks : 76 [kg]
weight wing covering CFRP 3.93 [mm]) : 5840 [kg]
load on front upper spar (clmax) per running metre : 21315.4 [N]
load on rear upper spar (vmax) per running metre : 14929.2 [N]
total weight CFRP spars (multi-cellular wing structure) : 26134 [kg]
weight wings : 42444 [kg]
weight wing/square meter : 91.42 [kg]
weight thermal leading-edge anti-icing : 71.2 [kg]
weight ailerons made of carbon fiber reinforced plastic CFRP (12.61 [m2]) : 461.7 [kg]
weight fin (94.3 [m2]) : 4315.4 [kg]
weight rudder (28.3 [m2]) : 1243.8 [kg]
weight tailplane (stabilizer) (60.7 [m2]): 3056.4 [kg]
weight elevators (26.0 [m2]): 643.7 [kg]
weight paint wing & tail surfaces : 260.1 [kg]
weight flight control hydraulic servo actuators: 136.0 [kg]
weight trailing-edge single slotted Fowler flaps (65.00 [m2]) : 1935.1 [kg]
weight track-mounted light alloy construction leading edge slats (60.24 [m2]) : 1472.2
[kg]
weight spoilers made of CFRP (9.6 [m2]) : 194.3 [kg]
weight airbrakes (22.5 [m2]) : 500.2 [kg]
weight winglets : 200 [kg]
total weight wing construction : 58654 [kg] (37.7 [%])
*******************************************************************
tire pressure main wheels : 15.60 [Bar] (nitrogen), ply rating : 34 PR
tire speed limit : 389 [km/hr]
total tyre footprint : 1.25 [m2]
Runway LCN at MTOW (0.76m radius of rigidity) : 74 [ ]
Aircraft Classification Number (ACN), MTOW on flexible runway and medium
subgrade strength (B) : 72 [ ] Can only operate from paved runways subgrade A
wheel pressure : 23173.3 [kg]
wheel track : 10.73 [m] wheelbase : 32.48 [m]
weight 12 Dunlop 50 x 20 main wheels (1270 [mm] by 508 [mm]) : 2870.5 [kg]
weight 2 nose wheels : 239.2 [kg]
weight carbon wheel-brakes : 223.0 [kg]
weight Duplex anti-skid units : 12.6 [kg]
weight oleo-pneumatic shock absorbers : 297.3 [kg]
weight wheel hydraulic operated retraction system : 2789.7 [kg]
weight undertail bumper : 20 [kg]
weight undercarriage struts (six-wheel bogies) with axle 7356.6 [kg]
total weight landing gear : 13808.9 [kg] (4.4 [%]
*******************************************************************
********************************************************************
calculated empty weight : 151318 [kg](47.9 [%])
weight oil for 20.9 hours flying : 76.5 [kg]
unusable fuel in engine and tanks 498.6 litre fuel : 391.4 [kg]
weight lifejackets : 166.1 [kg]
weight 7 life rafts : 230.6 [kg]
weight catering : 931.4 [kg]
weight water : 1285.4 [kg]
weight crew : 1134 [kg]
weight crew luggage, navigation chards, flight docs (NOTOC), manuals, miscellaneous
items : 167 [kg]
operational weight empty : 155700 [kg] (49.3 [%])
********************************************************************
weight 369 passengers : 28413 [kg]
weight luggage : 5904 [kg]
weight cargo : 32983 [kg] (cargo + luggage/m3 belly : 130 [kg/m3])
zero fuel weight (ZFW): 223000 [kg](70.6 [%])
weight fuel for landing (1.9 hours flying) : 13000 [kg]
max. landing weight (MLW): 236000 [kg](74.7 [%])
max. fuel weight : 280350 [kg] (88.7 [%])
payload with max fuel : 383 passengers + luggage 35650 [kg]
published maximum take-off weight : 316000 [kg] (100.0 [%])
calculation : * 4 * (engine power)
power loading (Take-off) : 367 [kg/KN]
power loading (Take-off) 1 PUF: 733 [kg/KN]
max. total take-off power : 862.0 [KN]
![[FrenchBee] First Airbus A350-1000 F-HMIX, RTO & First flight at Toulouse Blagnac, [Airbus Factory]](images/Airbus_A350-1000/image15.png)
French Bee A350-1041 F-HMIX c/n 539, it was delivered December 2021
calculation : *5* (loads)
manoeuvre load : 1.0 [g] at 9000 [m]
limit load : 2.5 [g] ultimate load : 3.8 [g] load factor : 1.1 [g]
design flight time : 6.15 [hours]
design cycles : 12030 sorties, design hours : 73984 [hours]
max. wing loading (MTOW & flaps retracted) : 681 [kg/m2]
wing stress (2 g) during operation : 127 [N/kg] at 2g emergency manoeuvre
calculation : *6* (angles of attack)
angle of attack zero lift : -1.70 ["]
max. angle of attack (stalling angle, clean) : 12.67 ["]
max. angle of attack (full flaps) : 16.87 ["]
angle of attack at economic cruise speed : 4.01 ["]
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): 1.26 [ ]
max. lift coefficient full flaps : 2.07 [ ]
drag coefficient at max. speed : 0.0246 [ ]
drag coefficient at econ. cruise speed : 0.0280 [ ]
induced drag coefficient at econ. cruise speed : 0.0127 [ ]
drag coefficient (zero lift) : 0.0154 [ ]
lift/drag ratio at econ. speed : 15.40 [ ]
calculation : *8* (speeds
take-off decision speed (V1) : 266 [km/u] (143 [kt])
take-off rotation speed (VR) : 279 [km/u] (151 [kt])
minimum unstick speed (Vmu) at TO angle 14.1 ° : 289 [km/u] (156 [kt])
lift-off speed (VLOF) : 312 [km/u] (168 [kt]) at pitch angle : 12.3 [°]
take-off safety speed (V2) : 314 [km/u] (170 [kt])
flap retraction speed (V3) at 500m (OW loaded : 309261 [kg]): 352 [km/u] (190 [kt])
steady initial climb speed (V4) : 340 [km/u] (184 [kt])
climb speed (to FL150 with 56 [%] power) : 712 [km/hr] (384 [kt])
max. endurance speed (Vbe): 688 [km/u] min. fuel/hr : 6708 [kg/hr] at height : 7925 [m]
max. range speed (Vbr): 886 [km/u] (0.84 [mach]) min. fuel consumption : 7.61 [kg/km]
at cruise height : 11278 [m]
max. cruising speed : 903 [km/hr] (488 [kt]) at 11000 [m] (power:17 [%])
max. operational speed (Mmo) : 950 [km/hr] (Mach 0.88 ) at 9450 [m] (power:19 [%])
airflow at cruise speed per engine : 645.2 [kg/s]
speed of thrust jet : 1306 [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): 385 [km/u] (208 [kt])
stalling speed clean at 500 [m] height at Max.Landing Weight : 236000 [kg]): 296
[km/u] (160 [kt])
final approach speed (landing speed) at sea-level with full flaps VREF (max. landing weight): 273 [km/u] (147 [kt])
ICAO Aircraft Approach Category (APC) : D
stalling speed at sea-level with full flaps VSO (max. landing weight): 210 [km/u]
(113 [kt]
Qatar airways was the launch customer for the A350-1000. Here is seen A350-1041 A7-ANA c/n 088, it was delivered February 2018
rate of climb at sea-level ROC (loaded, 56 % power) : 1207 [m/min]
rate of climb at sea-level ROC (loaded, 75 % power) : 1994 [m/min]
rate of climb at 1000 [m] with 1 engine out (PUF/MTOW, 100 % power on remaining
engines) : 798 [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 : 3475 [KW]
Take-off field length at MTOW 316000 kg, sea-level, standard day : 2900m
FAR TO runway length (TOFL) requirement at TOW 316000 [kg] standard day at SL
(PUF after V1): 2908 [m]
+++ FAA certification landing distance : +++
landing weight : 236000 [kg], TE flap setting : 25 [°]
runway condition : dry , landing over 50ft (15m) at threshold at sea-level
without use of thrust reversers
Landing field length at MLW 236000 kg at sea level, dry runway : 2100m (6890 ft)
FAA approved landing field length at SL, dry runway : 2098 [m] (6882 [ft])
landing distance (C.A.R.) from 15 [m] at SL, wet runway: 2394 [m] (7854 [ft])
max. lift/drag ratio : 18.02 [ ]
climb to 5000 [m] with max payload : 3.83 [min]
climb to 10000 [m] with max payload : 11.80 [min]
descent time from 10000 [m] to 250 [m] : 24.33 [min]
max. ceiling fully loaded (mtow- 60 min.fuel): 309261 [kg] ) : 15000 [m]
ceiling limited by max. pressure differential 14275 [m]
max. theoretical ceiling (OWE + 60 min.fuel) : 18400 [m] with flying weight :162439
[kg]
calculation *10* (action radius & endurance)
range with max. payload: 11359 [km] with 67300.0 [kg] max. useful load (74.6 [%]
fuel)*
range with high density pax: 14980 [km] with 461 passengers (94.2 [%] fuel)*
range with typical two-class pax: 16187 [km] with 369 passengers (100.0 [%] fuel)*
Range with max payload 67300 kg : 5600nm (10370 km)
Range with max fuel : 8500nm (15740 km)
Ferry range without payload : 9650nm (17870 km)
range with max.fuel : 16110 [km] with 14 crew and 383 passengers and 100.0 [%] fuel*
ferry range (calculated): 18469 [km] with 2 crew and zero payload (100.0 [%] fuel)*
max range theoretically with additional fuel tanks total 208266 [litre] fuel : 22635
[km]*
* calculated ranges without fuel reserves
Available Seat Kilometres (ASK) : 6981888 [paskm]
useful load with range 1000km : 67300 [kg]
useful load with range 1000km : 461 passengers
production (theor.max load): 60772 [tonkm/hour]
production (useful load): 60772 [tonkm/hour]
production (passengers): 411857 [paskm/hour]
oil and fuel consumption per tonkm : 0.111 [kg]
calculation *11* (operating cost)
fuel cost per hour (8585 [litre]):5151 [eur] (48 [pax-km/litre fuel])
fuel cost per seat 1000km flight (456 [pax] 2-class seating): 12.51 [eur/1000PK]
oil cost per hour: 14 [eur]
Cebu Pacific A350-1000 cabin crew
crew cost per hour : 1950 [eur]
list price 2024 : 365 [mln USD]
average flying hours in 1 year : 4000 [hours] technical life : 18 [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 : 979 [EUR]
write off per flying hour : 1643 [EUR]
time between engine failure : 13633 [hr]
can continue fly on 1 engine, low risk for emergency landing for PUF
workhours per day : 12.30 [hr]
no fatalities during service life > 100%% safe
average flight hours till crash : 1.75 [mln hr] (438 service years)
safe flight hours till fatality : 1752960 [hr] (438.2 service years)
reservation pax liability/flying hour : 0.07 [SDR*] (0.09 [eur])
insurance cost per hour : 457 [eur] insurance rate : 2.8 [%]
engine maintenance cost per hour : 5738.2 [eur]
wing maintenance cost per hour : 166.1 [eur]
fuselage maintenance cost per hour : 55.44 [eur]
tire life (time till worn out) : 102 [cycles]
maintenance cost per hour (excluding engines): 4530 [eur]
direct operating cost per hour: 20462 [eur], DOC per km : 23.49 [eur]
DOC per seat 1000km flight (456 [pax] 2-class seating): 49.68 [eur/1000PK]
DOC per seat 1000km flight (high density seating): 49.13 [eur/1000PK]
DOC per kg cargo for a 1000km flight : 0.34 [eur/kg] (= DOC/tonkm)
passenger service charge (depart at Schiphol): 11.34 [eur]
security service charge (depart at Schiphol): 10.08 [eur]
Cathay Pacific Airbus A350-1041 B-LXH c/n 258 SPL nov’23 RW 18L, delivered December 2018. © bvdz
airport take-off fee / passenger : 4.19 [eur/pax]
airport landing fee / passenger : 4.19 [eur/pax]
retour ticket price 1000km trip : 174.88 [eur/pax]
price retour ticket Schiphol-Barcelona : 202.20 [eur/pax]
accidents with fatalities > there have been no fatal accidents with an A350-1000
Literature :
Aviation Safety Network > > ASN Aviation Safety Database results (flightsafety.org)
Wide-body aircraft - Wikipedia
Airbus A350 - Aircraft Recognition Guide
UPDATED: This is how the crew rest areas of the A350-1000 & A350-900 look like — Allplane
Aircraft Performance Database > A35K (eurocontrol.int)
https://www.airbus.com/en/airport-operations-and-technical-data/aircraft-characteristics
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 30 October 2024 contact : info.aircraftinvestigation@gmail.com ac jetpax 2020.py python 3.7.4
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