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weight and performance calculations for the Boeing 777-300ER
KLM 777-306ER PH-BVU taking off from Schiphol, RW 18L, jan24 © bvdz
Boeing 777-300ER
role : wide-body airliner
importance : ****
first flight : operational : May 2004 (Air France)
country : United States of America
production : 837 aircraft at Everett, Washington
general information :
10.2m longer than the -200. Can carry 365 passengers over 14594 km.
Has raked wingtips which increases the wingspan by 1.98m. The fuselage and wings are strengthened and the main landing gear is modified. It is powered by the 513 KN GE90-115B turbofan, the world’s most powerful jet engine. It is a direct competitor of the Airbus A340-600 and A350-1000. Airlines required the 777-300ER as replacement for its 747-400’s giving a 20% fuel burn saving. Operating cost per seat hour : 44 USD (total DOC 26000 usd/hour). 777-300ER value at its peak : 150 mln USD. The 777-300ER was the best selling 777 variant.
primary users : various
Accommodation:
flight crew : 2 cabin crew : 10
passengers : seating for 378 in two class : 28 first class and 350 economy- class seats
( 31 -in pitch). exit limit : 550 passengers, high density seating for 528 passengers
engine : 2 General Electric GE90-115B turbofan engines of 513.0 [KN] (115325.0 [lbf])
dimensions :
wingspan : 64.8 [m], length overall: 73.86 [m], length of fuselage : 71.67 [m]
height : 18.51 [m] wing area : 436.8 [m^2] fuselage exterior width : 6.2 [m]
weights :
operating empty weight : 168560 [kg] max. structural payload : 69123 [kg]
Zero Fuel weight (ZFW) : 237683 [kg] max. landing weight (MLW) : 251290 [kg]
max. take-off weight : 351534 [kg] weight fuel : 142307 [kg] (181283 [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] (31 [%] power)
economic cruising speed : 879 [km/hr] (Mach 0.84 ) at 11890 [m]
service ceiling : 13100 [m]
range with max fuel and MTOW : 14492 [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) : 88591 [m^3]
calculation : *2* (fuel consumption)
oil consumption : 25.7 [kg/hr]
fuel consumption (econ. cruise speed) : 8416.6 [kg/hr] (10721.8 [litre/hr]) at 17 [%]
power
distance flown for 1 kg fuel : 0.10 [km/kg] at 11890 [m] height, sfc : 48.0 [kg/KN/h]
total fuel capacity : 181283 [litre] (142307 [kg])
KLM Boeing 777-306ER PH-BVW taking off from runway 18L (Aalsmeerbaan) at Schiphol, January 2024 © bvdz
calculation : *3* (weight)
weight engine(s) dry : 17524.0 [kg] = 17.08 [kg/KN]
weight 601.3 litre oil tank : 51.11 [kg]
oil tank filled with 6.5 litre oil : 5.8 [kg]
oil in engine 12.6 litre oil : 11.3 [kg]
fuel in engine 56.0 litre fuel : 41.04 [kg]
weight fuel lines : 289.6 [kg]
weight engine cowling : 2667.6 [kg]
weight thrust reversers : 1539.0 [kg]
total weight propulsion system : 22129 [kg](6.3 [%])
***************************************************************
Accommodation cabin facilities:
typical 2-class cabin layout for 378 passengers : economy : pitch : 78.7 [cm] 31.0 [-in]
( 3+3+3 ) seating in 43.6 rows
weight passenger seats : 2253.2 [kg]
weight cabin crew seats : 50.0 [kg]
weight flight crew seats : 42.0 [kg]
weight 2 jump seats in the cockpit :14.0 [kg]
high density seating passengers : 528 [pax] at mainly 10 -abreast seating in 60.2 rows,
pitch 74.7 [cm] 29.4 [-in]
pax density, normal seating : 0.82 [m2/pax], high density seating : 0.59 [m2/pax]
weight 10 lavatories : 307.6 [kg]
weight overhead pilot crew rest : 160 [kg]
weight 11 galleys : 1020.6 [kg]
weight overhead stowage for hand luggage : 132.3 [kg]
weight 4 wardrobe closets : 37.8 [kg]
weight 378 entertainment LCD screens in back of seats : 189.0 [kg]
weight 89 windows (38 x 25 cm) made of acrylic glass : 201.5 [kg]
weight 10 (1.93 x 1.07 [m]) Type A main entry doors : 807.9 [kg]
weight 3 (main door size : 1.75 x 1.78 [m]) freight doors (belly) : 344.4 [kg]*
total belly baggage/cargo hold volume : 259.7 [m3]
underfloor belly hold can accommodate : 44 LD3 containers, netto volume : 197.1 [m3]
and : 17.0 [m3] bulk cargo
cabin volume (usable), excluding flight deck : 648 [m3]
passenger compartment volume : 388 [m3]
passenger cabin max width : 5.86 [m] cabin length : 53.75 [m] max cabin height : 2.41
[m] floor area : 310.9 [m2]
weight cabin facilities : 5560.3 [kg]
safety facilities:
evacuation time with 528 passengers : 51 [sec]
weight 17 hand fire extinguisher : 52 [kg]
weight cockpit voice recorder (CVR) and flight data recorder (FDR): 20.0 [kg]
weight oxygen masks & oxygen generators : 245.7 [kg]
weight emergency flare installation : 10 [kg]
weight 10 emergency evacuation slides : 532.6 [kg]
weight safety equipment & facilities : 861 [kg]
fuselage construction:
fuselage aluminium frame : 35617 [kg]
floor loading (payload/m2): 222 [kg/m2]
weight rear pressure bulkhead : 606.9 [kg]
fuselage covering ( 1047.0 [m2] duraluminium 3.78 [mm]) : 10609.7 [kg]
weight floor beams : 6770.3 [kg]
weight cabin furbishing : 4736.3 [kg]
weight cabin floor : 4397.6 [kg]
weight (sound proof) isolation : 655.7 [kg] TO-noise level : 90.0 [EPNdB]
weight 31686 [litre] main central fuel tanks empty : 1774.4 [kg]
weight 26979 [litre] additional central fuel tank (ACT) empty : 1510.8 [kg]
weight empty 2136 [litre] potable water tank : 189.0 [kg]
weight empty waste tank : 63.5 [kg]
weight fuselage structure : 66931.4 [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]
Cockpit of Emirates 777-31HER A6-EBT c/n 32730
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 : 926 [m3] cabin air refreshment time :
3.1 [min]
weight air-conditioning and pressurization system : 505 [kg]
weight APU / engine starter: 256.5 [kg]
weight lighting : 124.7 [kg]
weight triple redundant 207 bar hydraulic system : 299.6 [kg]
weight three engine-driven 90kVA 400 Hertz electricity generators : 94.5 [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 : 29.3 [kg]
weight systems : 1372.9 [kg]
total weight fuselage : 74875 [kg](21.3 [%])
***************************************************************
total weight aluminium ribs (2464 ribs) : 11594 [kg]
weight engine mounts : 513 [kg]
weight 6 wing fuel tanks empty for total 122618 [litre] fuel : 6867 [kg]
weight wing covering (painted aluminium 3.65 [mm]) : 8598 [kg]
total weight aluminium spars (multi-cellular wing structure) : 12700 [kg]
weight wings : 32892 [kg]
weight wing/square meter : 75.30 [kg]
weight thermal leading-edge anti-icing : 71.3 [kg]
weight ailerons made of graphite hybrid composites (17.89 [m2]) : 539.8 [kg]
weight fin (66.73 [m2]) : 2517.6 [kg]
weight rudder (27.74 [m2]) : 1004.8 [kg]
weight tailplane (stabilizer) (74.17 [m2]): 3078.1 [kg]
weight elevators (18.91 [m2]): 385.33 [kg]
weight flight control hydraulic servo actuators: 147.7 [kg]
China Eastern 777-39PER B-2025 landing at Schiphol June 2023 © bvdz
weight trailing-edge double slotted flaps (85.18 [m2]) : 2731.0 [kg]
weight track-mounted light alloy construction leading edge slats (43.44 [m2]) : 875.9
[kg]
weight fly-by-wire operated spoilers of graphite composite construction (17.1 [m2]) :
281.5 [kg]
weight airbrakes (8.6 [m2]) : 161.7 [kg]
total weight wing construction : 52066 [kg] (30.9 [%])
*******************************************************************
tire pressure main wheels : 15.20 [Bar] (nitrogen), ply rating : 36 PR
tire speed limit : 376 [km/hr]
total tyre footprint : 1.54 [m2]
Runway LCN at MTOW (0.76m radius of rigidity) : 59 [ ]
Aircraft Classification Number (ACN), MTOW on rigid runway and medium subgrade
strength (B) : 47 [ ] Can also operate from unpaved runways subgrade B
wheel pressure : 25779.2 [kg]
weight 12 Dunlop 52 x 21 main wheels (1320 [mm] by 528 [mm]) : 2873.3 [kg]
weight 2 nose wheels : 239.4 [kg]
weight hydraulic disc wheel-brakes : 237.7 [kg]
weight Duplex anti-skid units : 12.6 [kg]
weight oleo-pneumatic shock absorbers : 316.9 [kg]
weight wheel hydraulic operated retraction system : 2902.1 [kg]
weight undercarriage struts (six-wheel bogies) with axle 7783.3 [kg]
total weight landing gear : 14365.3 [kg] (4.1 [%]
*******************************************************************
********************************************************************
calculated empty weight : 163436 [kg](46.5 [%])
weight oil for 19.5 hours flying : 520.4 [kg]
weight lifejackets : 170.1 [kg]
weight 7 life rafts : 236.2 [kg]
weight catering : 1181.2 [kg]
weight water : 1890.0 [kg]
weight crew : 972 [kg]
weight crew luggage, nav. chards, flight doc., miscell. items : 154 [kg]
operational weight empty : 168560 [kg] (47.9 [%])
********************************************************************
weight 378 passengers : 29106 [kg]
weight luggage : 6048 [kg]
weight cargo : 33969 [kg] (cargo + luggage/m3 belly : 148 [kg/m3])
zero fuel weight (ZFW): 237683 [kg](67.6 [%])
weight fuel for landing (1.6 hours flying) : 13607 [kg]
max. landing weight (MLW): 251290 [kg](71.5 [%])
max. fuel weight : 310867 [kg] (88.4 [%])
payload with max fuel : 437 passengers + luggage 40667 [kg]
published maximum take-off weight : 351534 [kg] (100.0 [%])
calculation : * 4 * (engine power)
power loading (Take-off) : 343 [kg/KN]
power loading (Take-off) 1 PUF: 685 [kg/KN]
max. total take-off power : 1026.0 [KN]
calculation : *5* (loads)
manoeuvre load : 0.9 [g] at 9000 [m]
limit load : 2.5 [g] ultimate load : 3.8 [g] load factor : 0.9 [g]
design flight time : 6.25 [hours]
design cycles : 10040 sorties, design hours : 62750 [hours]
Air France 777-328ER F-GSQX c/n 32963 taking off from Paris – Orly in 2018
max. wing loading (MTOW & flaps retracted) : 805 [kg/m2]
wing stress (2 g) during operation : 179 [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 : 2.77 ["]
calculation : *7* (lift & drag ratios
lift coefficient at angle of attack 0° : 0.15 [ ]
lift coefficient at max. speed : 0.40 [ ]
lift coefficient at max. angle of attack (clean): 1.25 [ ]
max. lift coefficient full flaps : 1.95 [ ]
drag coefficient at max. speed : 0.0303 [ ]
drag coefficient at econ. cruise speed : 0.0415 [ ]
induced drag coefficient at econ. cruise speed : 0.0204 [ ]
drag coefficient (zero lift) : 0.0212 [ ]
lift/drag ratio at econ. speed : 13.09 [ ]
calculation : *8* (speeds
take-off decision speed (V1) : 316 [km/u] (170 [kt])
take-off rotation speed (VR) : 331 [km/u] (179 [kt])
lift-off speed (VLOF) : 347 [km/u] (187 [kt]) at pitch angle : 14.5 [°]
take-off safety speed (V2) : 360 [km/u] (194 [kt])
flap retraction speed (V3) at 500m (OW loaded : 343117 [kg]): 383 [km/u] (207 [kt])
steady initial climb speed (V4) : 386 [km/u] (208 [kt])
climb speed (to FL150 with 56 [%] power) : 685 [km/hr] (370 [kt])
max. endurance speed (Vbe): 837 [km/u] min. fuel/hr : 8415 [kg/hr] at height : 11278 [m]
max. range speed (Vbr): 883 [km/u] (0.84 [mach]) min. fuel consumption : 9.58
[kg/km] at cruise height : 11278 [m]
max. cruising speed : 892 [km/hr] (482 [kt]) at 11890 [m] (power:18 [%])
max. operational speed (Mmo) : 945 [km/hr] (Mach 0.86 ) at 8500 [m] (power:21 [%])
airflow at cruise speed per engine : 687.3 [kg/s]
speed of thrust jet : 1370 [km/hr]
initial descent speed 10000 - 7315 [m]: Mach 0.82
descent speed 7315 - 3048 [m]: 550 [km/u] (297 [kt])
approach speed 3048 - 500 [m] (clean): 463 [km/u] (250 [kt])
minimum control speed (MCS) Vmca (clean): 411 [km/u] (222 [kt])
stalling speed clean at 500 [m] height at Max.Landing Weight : 251290 [kg]): 316
[km/u] (171 [kt])
final approach speed (landing speed) at sea-level with full flaps VREF (max. landing
weight): 283 [km/u] (153 [kt])
ICAO Aircraft Approach Category (APC) : D
stalling speed at sea-level with full flaps VSO (max. landing weight): 218 [km/u] (118
[kt]
rate of climb at sea-level ROC (loaded, 56 % power) : 1245 [m/min]
rate of climb at sea-level ROC (loaded, 75 % power) : 2069 [m/min]
rate of climb at 1000 [m] with 1 engine out (PUF/MTOW, 100 % power on remaining engines) : 786 [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
Brake kinetic energy capacity : 4552 [KW]
FAR take-off length at mtow 351534 kg at s/l : 10000 ft = 3048m
FAR TO runway length (TOFL) requirement at TOW 351534 [kg] standard day at SL
(PUF after V1): 3046 [m]
FAR landing field length, Flaps 30, mlw 251290 kg : 5800 ft ( = 1768m)
+++ FAA certification landing distance : +++
landing weight : 251290 [kg], TE flap setting : 50 [°]
runway condition : dry , landing over 50ft (15m) at threshold at sea-level
with use of thrust reversers
FAA approved landing field length : 1769 [m] (5804 [ft])
landing distance (C.A.R.) from 15 [m] at SL, wet runway: 2037 [m] (6684 [ft])
max. lift/drag ratio : 15.68 [ ]
climb to 5000 [m] with max payload : 3.72 [min]
climb to 10000 [m] with max payload : 11.44 [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: 343117 [kg] ) : 13800 [m]
calculation *10* (action radius & endurance)
range with max. payload: 11213 [km] with 69123.0 [kg] max. useful load (80.0 [%]
fuel)*
range with high density pax: 13649 [km] with 528 passengers (94.0 [%] fuel)*
range with typical two-class pax: 15017 [km] with 378 passengers (100.0 [%] fuel)*
Range with max. payload : 5700 nm = 10556 km Range with max fuel : 7825 nm = 14492 km, Max. range with 17416 kg payload : 8400 nm = 15557 km
range with max.fuel : 14731 [km] with 12 crew and 437 passengers and 100.0 [%]
fuel*
ferry range (calculated): 17199 [km] with 2 crew and zero payload (100.0 [%] fuel)*
max range theoretically with additional fuel tanks total 238032 [litre] fuel : 20907
[km]*
* calculated ranges without fuel reserves
Available Seat Kilometres (ASK) : 6708471 [paskm]
useful load with range 1000km : 69123 [kg]
useful load with range 1000km : 528 passengers
production (theor.max load): 61658 [tonkm/hour]
production (useful load): 61658 [tonkm/hour]
production (passengers): 401979 [paskm/hour]
oil and fuel consumption per tonkm : 0.137 [kg]
calculation *11* (operating cost)
fuel cost per hour (10722 [litre]):6433 [eur] (37 [pax-km/litre fuel])
fuel cost per seat 1000km flight (451 [pax] 2-class seating): 16.00 [eur/1000PK]
oil cost per hour: 107 [eur]
crew cost per hour : 1650 [eur]
list price 2023 : 150 [mln USD]
average flying hours in 1 year : 4400 [hours] technical life : 14 [year]
real average service life : 16 [years]
depreciation - 24 [years] to 10% residual value
economic hours (expected total flying hours) : 105600 [hours]
financing interest per flying hour : 2215 [EUR]
write off per flying hour : 5111 [EUR]
time between engine failure : 18081 [hr]
can continue fly on 1 engine, low risk for emergency landing for PUF
workhours per day : 13.50 [hr]
no fatalities during service life > 100%% safe
average flight hours till crash : 58.92 [mln hr] (13392 service years)
safe flight hours till fatality : 58924800 [hr] (13392.0 service years)
reservation pax liability/flying hour : 0.00 [SDR*] (0.00 [eur])
insurance cost per hour : 34 [eur] insurance rate : 0.1 [%]
engine maintenance cost per hour : 4413.9 [eur]
wing maintenance cost per hour : 153.8 [eur]
fuselage maintenance cost per hour : 53.61 [eur]
tire life (time till worn out) : 103 [cycles]
maintenance cost per hour (excluding engines): 4842 [eur]
direct operating cost per hour: 24804 [eur], DOC per km : 28.22 [eur]
DOC per seat 1000km flight (451 [pax] 2-class seating): 61.70 [eur/1000PK]
DOC per seat 1000km flight (high density seating): 52.62 [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]
security service charge (depart at Schiphol): 10.08 [eur]
airport take-off fee / passenger : 4.79 [eur/pax]
airport landing fee / passenger : 4.79 [eur/pax]
retour ticket price 1000km trip : 203.93 [eur/pax]
price retour ticket Schiphol-Barcelona : 237.87 [eur/pax]
accidents with fatalities :
There were no fatal flight accidents with a 777-300ER. Only there was one non-flight accident when a flight attendant fall out off an open door of Emirates A6-EGU door while the aircraft was parked at the apron at Entebbe airport. She died of the injuries sustained in the fall.
Literature :
Aircraft Performance Database > B77W (eurocontrol.int)
Front Matter Template 5.0 (boeing.com)
Air International mrt’06 blz.53
www.boeing.com
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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