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weight and performance calculations for the Boeing 777-200LR
PIA 777-200LR AP-BGY c/n 33781, delivered February 2006 to PIA
Boeing 777-200LR
role : wide-body airliner
importance : ****
first flight : 8 March 2005 operational : March 2006 (AP-BGY PIA)
country : United States of America
design :
production : 61 aircraft
general information :
This version of the 777 is the airliner with the longest range in the world. It can fly 17446 km with 301 passengers !
On February 2, 2006, it was awarded the certificate of airworthiness. It is a competitor to the A340-500. To demonstrate its long range, the -200LR (Longer Range) made a flight on November 9, 2005 from Hong Kong to London, but not according to the normal shortest route but in the other direction over the Pacific Ocean, North America and the Atlantic Ocean. The distance of 21601 km was covered non-stop in 22 hours and 42 minutes! Already in February 2000 Boeing decided to build the -200LR, but due to the crisis after the 9/11 attacks the project was stopped in October 2001. It was not until March 2003 that development continued.
To reach the maximum range of 17446 km, 3 additional tanks must be placed in the rear cargo hold, each with a capacity of 7000 liters.
Without these tanks, the -200LR can carry 181286 liters of fuel, what gives a range of 16021 km.
primary users : PIA, Air India, Emirates (10)
Accommodation:
flight crew : 3 cabin crew : 11
flight crew consist of pilot, co-pilot and relief pilot
passengers : seating for 317 in two class : 30 business class and 287 economy class seats
( 32 -in pitch) high density seating for 418 passengers
engine : 2 General Electric GE90-110B1L turbofan engines of 489.0 [KN] (109929.7 [lbf])
dimensions :
wingspan : 64.8 [m], length overall: 63.73 [m], length of fuselage : 61.84 [m] height : 18.6 [m]
wing area : 436.8 [m^2] fuselage exterior width : 6.2 [m]
weights :
operating empty weight : 145150 [kg] max. structural payload : 63956 [kg]
Zero Fuel weight (ZFW) : 209106 [kg] max. landing weight (MLW) : 223168 [kg]
max. take-off weight : 341105 [kg] weight fuel : 159587 [kg] (203295 [litres])
performance :
Max. operating Mach number (Mmo) : 0.86 [Mach] (945 [km/hr]) at 8500 [m]
critical Mach speed : 0.85 [Mach]
max. cruising speed : 892 [km/hr] (Mach 0.85 ) at 11890 [m] (32 [%] power)
economic cruising speed : 879 [km/hr] (Mach 0.84 ) at 11890 [m]
service ceiling : 13100 [m]
range with max fuel and MTOW : 17446 [km] (ATA domestic fuel reserves - 370.0 [km] alternate)
description :
cantilever low-wing monoplane with retractable landing gear with nose wheel
Wings : tapered multi-cellular fail safe wing with improved 2324 and 7150 aluminium alloy
stressed skin, with carbon-fiber-reinforced polymer composite material wing surfaces and
Kevlar fairings with Fowler-type double slotted trailing edge flaps with full-span slotted
LE flaps (slats) ,with spoilers (outboard) and airbrakes (inboard) airfoil : NACA with
supercritical cross-section average thickness/chord ratio : 10.0 [%], sweep angle 3/4 chord:
31.6 [°]
engines attached with pylons to the wing, main landing gear attached to the wings, fuel tanks in the wings and fuselage
calculation : *1* (dimensions)
measured wing chord at root: 13.36 [m]
measured wing chord at tip : 2.37 [m]
taper ratio : 0.177 [ ]
mean wing chord : 6.74 [m]
wing aspect ratio : 9.61 []
Oswald factor (e): 0.689 []
seize (span*length*height) : 76812 [m^3]
calculation : *2* (fuel consumption)
oil consumption : 24.4 [kg/hr]
fuel consumption (econ. cruise speed) : 7873.6 [kg/hr] (10030.1 [litre/hr]) at 17 [%] power
distance flown for 1 kg fuel : 0.11 [km/kg] at 11890 [m] height, sfc : 48.0 [kg/KN/h]
total fuel capacity : 203295 [litre] (159587 [kg])
calculation : *3* (weight)
weight engine(s) dry : 17524.0 [kg] = 17.92 [kg/KN]
weight 683.0 litre oil tank : 58.05 [kg]
oil tank filled with 6.2 litre oil : 5.5 [kg]
oil in engine 12.0 litre oil : 10.8 [kg]
fuel in engine 53.4 litre fuel : 39.12 [kg]
weight fuel lines : 258.9 [kg]
weight engine cowling : 2542.8 [kg]
weight thrust reversers : 1467.0 [kg]
total weight propulsion system : 21906 [kg](6.4 [%])
***************************************************************
Accommodation cabin facilities:
typical 2-class cabin layout for 317 passengers : economy : pitch : 81.3 [cm] 32.0 [-in]
( 3+3+3 ) seating in 36.2 rows
weight passenger seats : 1835.9 [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]
high density seating passengers : 418 [pax] at mainly 10 -abreast seating in 47.7 rows,
pitch 77.1 [cm] 30.4 [-in]
pax density, normal seating : 0.80 [m2/pax], high density seating : 0.61 [m2/pax]
weight 11 lavatories : 324.5 [kg]
weight overhead pilot crew rest : 160 [kg]
weight 10 galleys : 903.8 [kg]
Emirates 777-200LR interior
weight overhead stowage for hand luggage : 110.9 [kg]
weight 4 wardrobe closets : 31.7 [kg]
weight 317 entertainment LCD screens in back of seats : 158.5 [kg]
weight 74 windows (38 x 25 cm) made of acrylic glass : 168.1 [kg]
weight 8 (1.93 x 1.07 [m]) Type A main entry doors : 561.4 [kg]
weight 3 (main door size : 1.75 x 1.78 [m]) freight doors (belly) : 299.2 [kg]*
total belly baggage/cargo hold volume : 191.7 [m3]
underfloor belly hold can accommodate : 32 LD3 containers, netto volume : 141.8 [m3]
and : 17.0 [m3] bulk cargo
cabin volume (usable), excluding flight deck : 509 [m3]
passenger compartment volume : 317 [m3]
passenger cabin max width : 5.86 [m] cabin length : 43.92 [m] max cabin height : 2.41 [m]
floor area : 253.3 [m2]
weight cabin facilities : 4686.0 [kg]
safety facilities:
evacuation time with 418 passengers : 51 [sec]
weight 15 hand fire extinguisher : 44 [kg]
weight cockpit voice recorder (CVR) and flight data recorder (FDR): 20.0 [kg]
weight oxygen masks & oxygen generators : 206.1 [kg]
weight emergency flare installation : 10 [kg]
weight 8 emergency evacuation slides : 446.7 [kg]
weight safety equipment & facilities : 727 [kg]
fuselage construction:
fuselage aluminium frame : 26130 [kg]
floor loading (payload/m2): 252 [kg/m2]
weight rear pressure bulkhead : 528.7 [kg]
fuselage covering ( 884.3 [m2] duraluminium 3.30 [mm]) : 7806.9 [kg]
weight floor beams : 5370.9 [kg]
weight cabin furbishing : 3859.2 [kg]
weight cabin floor : 3583.0 [kg]
weight (sound proof) isolation : 553.8 [kg] TO-noise level : 90.0 [EPNdB]
weight 31686 [litre] main central fuel tanks empty : 1774.4 [kg]
weight 48991 [litre] additional central fuel tank (ACT) empty : 2743.5 [kg]
weight empty 1891 [litre] potable water tank : 167.4 [kg]
weight empty waste tank : 62.0 [kg]
weight fuselage structure : 52579.4 [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 dual digital Flight Management System (FMS) for navigation/auto-pilot : 20.0 [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 : 150.0 [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 : 761 [m3] cabin air refreshment time : 3.1 [min]
weight air-conditioning and pressurization system : 420 [kg]
weight APU / engine starter: 244.5 [kg]
weight lighting : 104.6 [kg]
weight triple redundant 207 bar hydraulic system : 259.8 [kg]
weight three engine-driven 90kVA 400 Hertz electricity generators : 79.2 [kg]
weight integrated drive generator (IDG) : 25 [kg]
weight ram air turbine for emergency electric power : 5.0 [kg]
weight three 24V 25Ah nickel-cadmium batteries : 38.4 [kg]
weight controls : 26.7 [kg]
weight systems : 1197.8 [kg]
total weight fuselage : 59340 [kg](17.4 [%])
***************************************************************
total weight aluminium ribs (2311 ribs) : 10877 [kg]
weight engine mounts : 489 [kg]
weight 6 wing fuel tanks empty for total 122618 [litre] fuel : 6867 [kg]
weight wing covering (painted aluminium 3.10 [mm]) : 7313 [kg]
total weight aluminium spars (multi-cellular wing structure) : 10727 [kg]
weight wings : 28917 [kg]
weight wing/square meter : 66.20 [kg]
weight thermal leading-edge anti-icing : 71.3 [kg]
weight ailerons made of graphite hybrid composites (17.89 [m2]) : 474.7 [kg]
weight fin (66.73 [m2]) : 2214.0 [kg]
weight rudder (27.74 [m2]) : 883.6 [kg]
Emirates 777-200LR A6-EWC
weight tailplane (stabilizer) (64.00 [m2]): 2335.6 [kg]
weight elevators (16.32 [m2]): 292.38 [kg]
weight flight control hydraulic servo actuators: 128.0 [kg]
weight trailing-edge double slotted flaps (85.18 [m2]) : 2401.6 [kg]
weight track-mounted light alloy construction leading edge slats (43.44 [m2]) : 770.4 [kg]
weight fly-by-wire operated spoilers of graphite composite construction (17.1 [m2]) : 248.2
[kg]
weight airbrakes (8.6 [m2]) : 143.0 [kg]
total weight wing construction : 46235 [kg] (31.9 [%])
*******************************************************************
tire pressure main wheels : 15.00 [Bar] (nitrogen), ply rating : 36 PR
tire speed limit : 376 [km/hr]
total tyre footprint : 1.51 [m2]
Runway LCN at MTOW (0.76m radius of rigidity) : 59 [ ]
Aircraft Classification Number (ACN), MTOW on rigid runway and medium subgrade
strength (B) : 45 [ ] Can also operate from unpaved runways subgrade B
wheel pressure : 25014.4 [kg]
weight 12 Dunlop 52 x 21 main wheels (1320 [mm] by 528 [mm]) : 2705.8 [kg]
weight 2 nose wheels : 225.5 [kg]
weight hydraulic disc wheel-brakes : 209.1 [kg]
weight Duplex anti-skid units : 12.6 [kg]
weight oleo-pneumatic shock absorbers : 278.8 [kg]
weight wheel hydraulic operated retraction system : 2582.9 [kg]
weight undercarriage struts (six-wheel bogies) with axle 6770.8 [kg]
total weight landing gear : 12785.5 [kg] (3.7 [%]
*******************************************************************
********************************************************************
calculated empty weight : 140267 [kg](41.1 [%])
weight oil for 23.5 hours flying : 594.7 [kg]
weight lifejackets : 142.7 [kg]
weight 6 life rafts : 198.1 [kg]
weight catering : 1046.1 [kg]
weight water : 1673.8 [kg]
weight crew : 1134 [kg]
weight crew luggage, nav. chards, flight doc., miscell. items : 93 [kg]
operational weight empty : 145150 [kg] (42.6 [%])
********************************************************************
weight 317 passengers : 24409 [kg]
weight luggage : 5072 [kg]
weight cargo : 34475 [kg] (cargo + luggage/m3 belly : 200 [kg/m3])
zero fuel weight (ZFW): 209106 [kg](61.3 [%])
weight fuel for landing (1.8 hours flying) : 14062 [kg]
max. landing weight (MLW): 223168 [kg](65.4 [%])
max. fuel weight : 304737 [kg] (89.3 [%])
payload with max fuel : 391 passengers + luggage 36368 [kg]
published maximum take-off weight : 341105 [kg] (100.0 [%])
calculation : * 4 * (engine power)
power loading (Take-off) : 349 [kg/KN]
power loading (Take-off) 1 PUF: 698 [kg/KN]
max. total take-off power : 978.0 [KN]
calculation : *5* (loads)
manoeuvre load : 0.9 [g] at 9000 [m]
limit load : 2.5 [g] ultimate load : 3.8 [g] load factor : 0.7 [g]
design flight time : 6.60 [hours]
design cycles : 8935 sorties, design hours : 58971 [hours]
max. wing loading (MTOW & flaps retracted) : 781 [kg/m2]
wing stress (2 g) during operation : 191 [N/kg] at 2g emergency manoeuvre
calculation : *6* (angles of attack)
angle of attack zero lift : -1.68 ["]
max. angle of attack (stalling angle, clean) : 12.38 ["]
max. angle of attack (full flaps) : 16.58 ["]
angle of attack at max. speed : 2.48 ["]
calculation : *7* (lift & drag ratios
lift coefficient at angle of attack 0° : 0.15 [ ]
lift coefficient at max. speed : 0.37 [ ]
lift coefficient at max. angle of attack (clean): 1.25 [ ]
max. lift coefficient full flaps : 1.95 [ ]
drag coefficient at max. speed : 0.0293 [ ]
drag coefficient at econ. cruise speed : 0.0388 [ ]
induced drag coefficient at econ. cruise speed : 0.0177 [ ]
drag coefficient (zero lift) : 0.0211 [ ]
lift/drag ratio at econ. speed : 12.66 [ ]
calculation : *8* (speeds
take-off decision speed (V1) : 305 [km/u] (165 [kt])
take-off rotation speed (VR) : 320 [km/u] (173 [kt])
Air India 777-200LR VT-ALH taking off
lift-off speed (VLOF) : 336 [km/u] (181 [kt]) at pitch angle : 14.7 [°]
take-off safety speed (V2) : 348 [km/u] (188 [kt])
flap retraction speed (V3) at 500m (OW loaded : 333231 [kg]): 377 [km/u] (204 [kt])
steady initial climb speed (V4) : 374 [km/u] (202 [kt])
climb speed (to FL150 with 56 [%] power) : 667 [km/hr] (360 [kt])
max. endurance speed (Vbe): 564 [km/u] min. fuel/hr : 7842 [kg/hr] at height : 5182 [m]
max. range speed (Vbr): 879 [km/u] (0.84 [mach]) min. fuel consumption : 9.00 [kg/km] at
cruise height : 11582 [m]
max. cruising speed : 892 [km/hr] (482 [kt]) at 11890 [m] (power:17 [%])
max. operational speed (Mmo) : 945 [km/hr] (Mach 0.86 ) at 8500 [m] (power:22 [%])
airflow at cruise speed per engine : 687.3 [kg/s]
speed of thrust jet : 1340 [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): 357 [km/u] (193 [kt])
stalling speed clean at 500 [m] height at Max.Landing Weight : 223168 [kg]): 298 [km/u] (161
[kt])
final approach speed (landing speed) at sea-level with full flaps VREF (max. landing weight):
267 [km/u] (144 [kt])
ICAO Aircraft Approach Category (APC) : D
stalling speed at sea-level with full flaps VSO (max. landing weight): 205 [km/u] (111 [kt]
rate of climb at sea-level ROC (loaded, 56 % power) : 1243 [m/min]
rate of climb at sea-level ROC (loaded, 75 % power) : 2062 [m/min]
rate of climb at 1000 [m] with 1 engine out (PUF/MTOW, 100 % power on remaining
engines) : 746 [m/min]
rate of descent from FL240 to FL100 (7315m > 3048m): 1067 [m/min] (3501 [ft/min])
rate of descent during approach with landing gear extended, with use of spoilers: 457
[m/min] (1499 [ft/min])
calculation : *9* (regarding various performances)
high wheel pressure, can only take off from paved runways
Brake kinetic energy capacity : 4286 [KW]
FAR take-off runway at TOW 341t (751995 lb) at S/L : 9200 ft = 2804 [m], at 347t : 10100 ft > 3078 [m]
FAR TO runway length (TOFL) requirement at TOW 341105 [kg] standard day at SL (PUF
after V1): 2805 [m]
FAR landing runway , MLW 223168 kg (492000 lbs) : 5200 ft (= 1585 m)
+++ FAA certification landing distance : +++
landing weight : 223168 [kg], TE flap setting : 50 [°]
runway condition : dry , landing over 50ft (15m) at threshold at sea-level
FAA approved landing field length : 1607 [m] (5272 [ft])
landing distance (C.A.R.) from 15 [m] at SL, wet runway: 1845 [m] (6054 [ft])
max. lift/drag ratio : 15.68 [ ]
climb to 5000 [m] with max payload : 3.72 [min]
climb to 10000 [m] with max payload : 11.45 [min]
descent time from 10000 [m] to 250 [m] : 24.33 [min]
ceiling limited by max. pressure differential 14125 [m]
theoretical ceiling fully loaded (mtow- 60 min.fuel: 333231 [kg] ) : 14000 [m]
calculation *10* (action radius & endurance)
range with max. payload: 13919 [km] with 63956.0 [kg] max. useful load (82.7 [%] fuel)*
range with high density pax: 17305 [km] with 418 passengers (98.4 [%] fuel)*
range with typical two-class pax: 18087 [km] with 317 passengers (100.0 [%] fuel)*
Range with max fuel, mtow 347t, with 3 aux.fuel tanks : 9420 nm : 17446 [km], with TOW 341t range with max fuel : 9750 nm > 18057 km, ferry range : 10400 nm = 19260 km (OEW + payload = 350000 lb = 158760 kg > OEW = 145150 kg > payload = 13610 kg, range with max payload (341t tow) : 7250 nm = 13427 km
range with max.fuel : 17658 [km] with 14 crew and 391 passengers and 100.0 [%] fuel*
ferry range (calculated): 20268 [km] with 3 crew and zero payload (100.0 [%] fuel)*
max range theoretically with additional fuel tanks total 254224 [litre] fuel : 23669 [km]*
* calculated ranges without fuel reserves
Available Seat Kilometres (ASK) : 6641077 [paskm]
useful load with range 1000km : 63956 [kg]
useful load with range 1000km : 418 passengers
production (theor.max load): 57049 [tonkm/hour]
production (useful load): 57049 [tonkm/hour]
production (passengers): 327518 [paskm/hour]
combi aircraft mail/freight/passengers
oil and fuel consumption per tonkm : 0.138 [kg]
calculation *11* (operating cost)
fuel cost per hour (10030 [litre]):6018 [eur] (33 [pax-km/litre fuel])
fuel cost per seat 1000km flight (367 [pax] 2-class seating): 18.37 [eur/1000PK]
oil cost per hour: 102 [eur]
crew cost per hour : 1950 [eur]
list price 2023 : 372 [mln USD]
average flying hours in 1 year : 4200 [hours] technical life : 14 [year]
real average service life : 18 [years]
depreciation - 24 [years] to 10% residual value
economic hours (expected total flying hours) : 100800 [hours]
financing interest per flying hour : 1991 [EUR]
write off per flying hour : 4084 [EUR]
time between engine failure : 18081 [hr]
can continue fly on 1 engine, low risk for emergency landing for PUF
workhours per day : 12.81 [hr]
no fatalities during service life > 100%% safe
average flight hours till crash : 4.35 [mln hr] (1035 service years)
safe flight hours till fatality : 4347714 [hr] (1035.2 service years)
reservation pax liability/flying hour : 0.03 [SDR*] (0.04 [eur])
insurance cost per hour : 394 [eur] insurance rate : 1.2 [%]
engine maintenance cost per hour : 4207.4 [eur]
wing maintenance cost per hour : 145.6 [eur]
fuselage maintenance cost per hour : 40.60 [eur]
tire life (time till worn out) : 103 [cycles]
maintenance cost per hour (excluding engines): 4090 [eur]
direct operating cost per hour: 22836 [eur], DOC per km : 25.98 [eur]
DOC per seat 1000km flight (367 [pax] 2-class seating): 69.72 [eur/1000PK]
DOC per seat 1000km flight (high density seating): 61.25 [eur/1000PK]
DOC per kg cargo for a 1000km flight : 0.40 [eur/kg] (= DOC/tonkm)
passenger service charge (depart at Schiphol): 11.34 [eur]
Emirates 777-200LR A6-EMA
security service charge (depart at Schiphol): 10.08 [eur]
airport take-off fee / passenger : 5.70 [eur/pax]
airport landing fee / passenger : 5.70 [eur/pax]
retour ticket price 1000km trip : 225.60 [eur/pax]
price retour ticket Schiphol-Barcelona : 263.94 [eur/pax]
accidents with fatalities > there were no fatal accidents with a 777-200LR
Literature :
http://nl.wikipedia.org/wiki/Boeing_777
https://www.boeing.com/commercial/airports/plan-manuals
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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