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weight and performance calculations for the Boeing 777-300
Cathay Pacific 777-367 B-HNK c/n 27510 at Narita, Japan, November 2023
Boeing 777-300
role : wide-body airliner
importance : ****
first flight : 16 October 1997 operational : May 1998
country : United States of America
design :
production : 60 aircraft at Everett
general information :
Boeing plans to develop an entire family out of the 777. In June 1995 it was decided to build a 777 lengthened by 10.1m, designated 777-300. It was due to be delivered in mid-1998. It can carry 368 to 451 passengers. In June 1995 Boeing had 31 orders on this version. The clients were Cathay Pacific, Thai Airways, Korean Air, All Nippon Airways. The 777-300 has the same range and passenger capacity as the 747-100 and -200, but uses 30% less fuel and maintenance costs are 40% lower. An intermediate piece of 5.3m in front of the wing and one of 4.8m behind the wing will be placed, in addition, the fuselage will be reinforced at a number of points. The aircraft is now even longer than the 747-400 ! The MTOW is 263090 kg to 299370 kg and there might be a 326819 kg HGW version, which is probably the highest weight for the current wing, with engines of 436+ KN. The normal 777-300 gets engines from 374 to 400 KN from GW, P&W or RR. The range is 10575 km with 368 passengers. It is scheduled to make its maiden flight in October 1997 and the first to Cathay Pacific in May 1998.
primary users : Cathay Pacific, Thai Airways, Korean Air, All Nippon Airways, Singapore
Airlines
Accommodation:
flight crew : 2 cabin crew : 11
passengers : seating for 396 in two class : 80 business class and 316 economy class seats
( 32 -in pitch) exit limit : 550 passengers, high density seating for 528 passengers
engine : 2 Pratt & Whitney PW4090 turbofan engines of 400.5 [KN] (90034.5 [lbf])
dimensions :
wingspan : 60.93 [m], length overall: 73.8 [m], length of fuselage : 71.61 [m] height :
18.44 [m] wing area : 427.8 [m^2] fuselage exterior width : 6.2 [m]
weights :
operating empty weight : 159570 [kg] max. structural payload : 64960 [kg]
Zero Fuel weight (ZFW) : 224530 [kg] max. landing weight (MLW) : 237680 [kg]
max. take-off weight : 299370 [kg] weight fuel : 134368 [kg] (171170 [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] (34 [%] power)
economic cruising speed : 879 [km/hr] (Mach 0.84 ) at 11890 [m]
service ceiling : 13100 [m]
range with max fuel and MTOW : 15279 [km] (ATA domestic fuel reserves - 370.0 [km]
alternate)
777-300 prototype
description :
cantilever low-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 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 [°]
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 : 7.02 [m]
wing aspect ratio : 8.68 []
Oswald factor (e): 0.689 []
seize (span*length*height) : 82918 [m^3]
calculation : *2* (fuel consumption)
oil consumption : 20.0 [kg/hr]
fuel consumption (econ. cruise speed) : 7547.4 [kg/hr] (9614.6 [litre/hr]) at 27 [%] power
distance flown for 1 kg fuel : 0.12 [km/kg] at 11890 [m] height, sfc : 35.5 [kg/KN/h]
total fuel capacity : 171170 [litre] (134368 [kg])
calculation : *3* (weight)
weight engine(s) dry : 14100.0 [kg] = 17.60 [kg/KN]
weight 493.4 litre oil tank : 41.94 [kg]
oil tank filled with 5.0 litre oil : 4.5 [kg]
Korean Air 777-3B5 HL7533 c/n 27948 at Bangkok, December 2022
oil in engine 9.8 litre oil : 8.8 [kg]
fuel in engine 43.7 litre fuel : 32.04 [kg]
weight fuel lines : 249.1 [kg]
weight engine cowling : 2082.6 [kg]
weight thrust reversers : 1201.5 [kg]
total weight propulsion system : 17721 [kg](5.9 [%])
***************************************************************
Accommodation cabin facilities:
typical 2-class cabin layout for 396 passengers : economy : pitch : 81.3 [cm] 32.0 [-in]
( 3+3+3 ) seating in 46.5 rows
weight passenger seats : 2250.8 [kg]
weight cabin crew seats : 55.0 [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
74.6 [cm] 29.4 [-in]
pax density, normal seating : 0.78 [m2/pax], high density seating : 0.59 [m2/pax]
weight 11 lavatories : 322.8 [kg]
weight 11 galleys : 962.3 [kg]
weight overhead stowage for hand luggage : 138.6 [kg]
weight 4 wardrobe closets : 39.6 [kg]
weight 396 entertainment LCD screens in back of seats : 198.0 [kg]
weight 95 windows (38 x 25 cm) made of acrylic glass : 215.0 [kg]
weight 10 (1.93 x 1.07 [m]) Type A main entry doors : 829.8 [kg]
777-300 under floor cargo space for 44 LD-3 ULD’s
weight 3 (main door size : 1.75 x 1.78 [m]) freight doors (belly) : 353.7 [kg]*
total belly baggage/cargo hold volume : 259.4 [m3]
underfloor belly hold can accommodate : 44 LD3 containers, netto volume : 196.8 [m3]
and : 17.0 [m3] bulk cargo
cabin volume (usable), excluding flight deck : 641 [m3]
passenger compartment volume : 388 [m3]
passenger cabin max width : 5.86 [m] cabin length : 53.69 [m] max cabin height : 2.41 [m]
floor area : 310.6 [m2]
weight cabin facilities : 5421.6 [kg]
safety facilities:
evacuation time with 528 passengers : 51 [sec]
weight 18 hand fire extinguisher : 55 [kg]
weight cockpit voice recorder (CVR) and flight data recorder (FDR): 20.0 [kg]
weight oxygen masks & oxygen generators : 257.4 [kg]
weight emergency flare installation : 10 [kg]
weight 10 emergency evacuation slides : 558.0 [kg]
weight safety equipment & facilities : 900 [kg]
fuselage construction:
fuselage aluminium frame : 36551 [kg]
floor loading (payload/m2): 209 [kg/m2]
weight rear pressure bulkhead : 623.1 [kg]
fuselage covering ( 1046.0 [m2] duraluminium 3.88 [mm]) : 10876.1 [kg]
weight floor beams : 6770.4 [kg]
weight cabin furbishing : 4730.8 [kg]
weight cabin floor : 4392.8 [kg]
weight (sound proof) isolation : 794.5 [kg] TO-noise level : 96.0 [EPNdB]
weight 32022 [litre] main central fuel tanks empty : 1793.2 [kg]
weight 19056 [litre] additional central fuel tank (ACT) empty : 1067.2 [kg]
weight empty 1611 [litre] potable water tank : 142.6 [kg]
weight empty waste tank : 66.8 [kg]
weight fuselage structure : 67808.0 [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 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 : 141.0 [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 : 925 [m3] cabin air refreshment time : 3.0 [min]
weight air-conditioning and pressurization system : 517 [kg]
weight APU / engine starter: 200.2 [kg]
weight lighting : 130.7 [kg]
weight triple redundant 207 bar hydraulic system : 280.4 [kg]
weight three engine-driven 90kVA 400 Hertz electricity generators : 99.0 [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 : 28.7 [kg]
weight systems : 1319.8 [kg]
total weight fuselage : 75590 [kg](25.2 [%])
***************************************************************
total weight aluminium ribs (2057 ribs) : 10081 [kg]
weight engine mounts : 400 [kg]
weight 6 wing fuel tanks empty for total 120092 [litre] fuel : 6725 [kg]
weight wing covering (painted aluminium 3.79 [mm]) : 8760 [kg]
total weight aluminium spars (multi-cellular wing structure) : 11557 [kg]
weight wings : 30398 [kg]
weight wing/square meter : 71.06 [kg]
weight thermal leading-edge anti-icing : 67.0 [kg]
weight ailerons made of graphite hybrid composites (17.52 [m2]) : 499.0 [kg]
weight fin (59.00 [m2]) : 2100.7 [kg]
weight rudder (24.53 [m2]) : 838.4 [kg]
weight tailplane (stabilizer) (74.11 [m2]): 2902.6 [kg]
weight elevators (18.90 [m2]): 363.35 [kg]
weight flight control hydraulic servo actuators: 138.2 [kg]
Japan airlines Boeing 777-346 JA8943 c/n 28395 at Tokyo, May 2013
weight trailing-edge double slotted flaps (83.42 [m2]) : 2524.3 [kg]
weight track-mounted light alloy construction leading edge slats (42.55 [m2]) : 809.7 [kg]
weight fly-by-wire operated spoilers of graphite composite construction (16.7 [m2]) : 260.6
[kg]
weight airbrakes (8.4 [m2]) : 150.0 [kg]
total weight wing construction : 48177 [kg] (30.2 [%])
*******************************************************************
tire pressure main wheels : 14.80 [Bar] (nitrogen), ply rating : 32 PR
tire speed limit : 389 [km/hr]
total tyre footprint : 1.24 [m2]
Runway LCN at MTOW (0.76m radius of rigidity) : 62 [ ]
Aircraft Classification Number (ACN), MTOW on rigid runway and medium subgrade
strength (B) : 44 [ ]. Can also operate from unpaved runways subgrade B
wheel pressure : 21953.8 [kg]
weight 12 Dunlop 50 x 20 main wheels (1270 [mm] by 508 [mm]) : 2673.2 [kg]
weight 2 nose wheels : 222.8 [kg]
weight hydraulic disc wheel-brakes : 224.5 [kg]
weight Duplex anti-skid units : 12.6 [kg]
weight oleo-pneumatic shock absorbers : 299.4 [kg]
weight wheel hydraulic operated retraction system : 2765.1 [kg]
weight undercarriage struts (six-wheel bogies) with axle 7489.5 [kg]
total weight landing gear : 13687.1 [kg] (4.6 [%]
*******************************************************************
********************************************************************
calculated empty weight : 155175 [kg](51.8 [%])
weight oil for 20.6 hours flying : 427.8 [kg]
weight lifejackets : 178.2 [kg]
weight 7 life rafts : 247.5 [kg]
weight catering : 891.0 [kg]
weight water : 1425.6 [kg]
weight crew : 1053 [kg]
weight crew luggage, nav. chards, flight doc., miscell. items : 171 [kg]
operational weight empty : 159570 [kg] (53.3 [%])
********************************************************************
weight 396 passengers : 30492 [kg]
weight luggage : 6336 [kg]
weight cargo : 28132 [kg] (cargo + luggage/m3 belly : 130 [kg/m3])
zero fuel weight (ZFW): 224530 [kg](75.0 [%])
weight fuel for landing (1.7 hours flying) : 13150 [kg]
max. landing weight (MLW): 237680 [kg](79.4 [%])
max. fuel weight : 293938 [kg] (98.2 [%])
payload with max fuel : 58 passengers + luggage 5432 [kg]
published maximum take-off weight : 299370 [kg] (100.0 [%])
calculation : * 4 * (engine power)
power loading (Take-off) : 374 [kg/KN]
power loading (Take-off) 1 PUF: 747 [kg/KN]
max. total take-off power : 801.0 [KN]
calculation : *5* (loads)
manoeuvre load : 1.0 [g] at 9000 [m]
limit load : 2.5 [g] ultimate load : 3.8 [g] load factor : 1.0 [g]
design flight time : 4.50 [hours]
design cycles : 12455 sorties, design hours : 56048 [hours]
max. wing loading (MTOW & flaps retracted) : 700 [kg/m2]
wing stress (2 g) during operation : 173 [N/kg] at 2g emergency manoeuvre
calculation : *6* (angles of attack)
angle of attack zero lift : -1.72 ["]
max. angle of attack (stalling angle, clean) : 12.81 ["]
max. angle of attack (full flaps) : 17.01 ["]
angle of attack at max. speed : 2.42 ["]
Thai Airways 777-3D7 HS-TKA c/n 29150 at Bangkok, February 2001
calculation : *7* (lift & drag ratios
lift coefficient at angle of attack 0° : 0.15 [ ]
lift coefficient at max. speed : 0.36 [ ]
lift coefficient at max. angle of attack (clean): 1.27 [ ]
max. lift coefficient full flaps : 1.97 [ ]
drag coefficient at max. speed : 0.0445 [ ]
drag coefficient at econ. cruise speed : 0.0514 [ ]
induced drag coefficient at econ. cruise speed : 0.0161 [ ]
drag coefficient (zero lift) : 0.0352 [ ]
lift/drag ratio at econ. speed : 8.10 [ ]
calculation : *8* (speeds
take-off decision speed (V1) : 294 [km/u] (159 [kt])
take-off rotation speed (VR) : 309 [km/u] (167 [kt])
lift-off speed (VLOF) : 323 [km/u] (175 [kt]) at pitch angle : 14.6 [°]
take-off safety speed (V2) : 335 [km/u] (181 [kt])
flap retraction speed (V3) at 500m (OW loaded : 291823 [kg]): 356 [km/u] (192 [kt])
steady initial climb speed (V4) : 361 [km/u] (195 [kt])
climb speed (to FL150 with 66 [%] power) : 527 [km/hr] (285 [kt])
max. endurance speed (Vbe): 447 [km/u] min. fuel/hr : 7006 [kg/hr] at height : 3658 [m]
max. range speed (Vbr): 879 [km/u] (0.84 [mach]) min. fuel consumption : 8.72 [kg/km] at
cruise height : 11582 [m]
max. cruising speed : 892 [km/hr] (482 [kt]) at 11890 [m] (power:28 [%])
max. operational speed (Mmo) : 945 [km/hr] (Mach 0.86 ) at 8500 [m] (power:39 [%])
airflow at cruise speed per engine : 509.1 [kg/s]
speed of thrust jet : 1681 [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): 371 [km/u] (200 [kt])
stalling speed clean at 500 [m] height at Max.Landing Weight : 237680 [kg]): 309 [km/u]
(167 [kt])
final approach speed (landing speed) at sea-level with full flaps VREF (max. landing weight):
276 [km/u] (149 [kt])
ICAO Aircraft Approach Category (APC) : D
stalling speed at sea-level with full flaps VSO (max. landing weight): 212 [km/u] (115 [kt]
rate of climb at sea-level ROC (loaded, 66 % power) : 884 [m/min]
rate of climb at sea-level ROC (loaded, 75 % power) : 1131 [m/min]
rate of climb at 1000 [m] with 1 engine out (PUF/MTOW, 100 % power on remaining
engines) : 320 [m/min]
rate of descent from FL240 to FL100 (7315m > 3048m): 914 [m/min] (3000 [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
Brake kinetic energy capacity : 3615 [KW]
FAR take-off runway length at s/l, mtow 299370 kg (660000 lb): 10500 ft (= 3200m)
FAR TO runway length (TOFL) requirement at TOW 299370 [kg] standard day at SL (PUF
after V1): 3186 [m]
Landing runway length at s/l, mlw 237680 kg (524000 lb):6000 ft (= 1829 m)
+++ FAA certification landing distance : +++
landing weight : 237680 [kg], TE flap setting : 50 [°]
runway condition : dry , landing over 50ft (15m) at threshold at sea-level
without use of thrust reversers
FAA approved landing field length : 1825 [m] (5987 [ft])
landing distance (C.A.R.) from 15 [m] at SL, wet runway: 2097 [m] (6878 [ft])
max. lift/drag ratio : 11.54 [ ]
climb to 5000 [m] with max payload : 5.23 [min]
climb to 10000 [m] with max payload : 16.11 [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: 291823 [kg] ) : 14700 [m]
calculation *10* (action radius & endurance)
range with max. payload: 7957 [km] with 64960.0 [kg] max. useful load (55.7 [%] fuel)*
range with high density pax: 9855 [km] with 528 passengers (67.5 [%] fuel)*
range with typical two-class pax: 11387 [km] with 396 passengers (76.6 [%] fuel)*
Range with max fuel : 8250 nm = 15279 km, useful load with max fuel is low, only 5432 kg, just enough for 58 passengers with luggage, this is in contrast with the 777-200LR which can take a payload with max fuel of 391 passengers + luggage total 36368 [kg]. ferry range : 8300 nm (15371 km)
range with max.fuel : 15511 [km] with 13 crew and 58 passengers and 100.0 [%] fuel*
ferry range (calculated): 15875 [km] with 2 crew and zero payload (100.0 [%] fuel)*
max range theoretically with additional fuel tanks total 182175 [litre] fuel : 16701 [km]*
* calculated ranges without fuel reserves
Available Seat Kilometres (ASK) : 4875003 [paskm]
useful load with range 1000km : 64960 [kg]
useful load with range 1000km : 528 passengers
production (theor.max load): 57944 [tonkm/hour]
production (useful load): 57944 [tonkm/hour]
production (passengers): 401538 [paskm/hour]
oil and fuel consumption per tonkm : 0.131 [kg]
calculation *11* (operating cost)
fuel cost per hour (9615 [litre]):5768 [eur] (42 [pax-km/litre fuel])
fuel cost per seat 1000km flight (450 [pax] 2-class seating): 14.37 [eur/1000PK]
oil cost per hour: 83 [eur]
crew cost per hour : 1800 [eur]
list price 2023 : 411 [mln USD]
average flying hours in 1 year : 4400 [hours] technical life : 13 [year]
real average service life : 16 [years]
depreciation - 20 [years] to 10% residual value
economic hours (expected total flying hours) : 88000 [hours]
financing interest per flying hour : 2103 [EUR]
write off per flying hour : 4852 [EUR]
time between engine failure : 12805 [hr]
can continue fly on 1 engine, low risk for emergency landing for PUF
workhours per day : 14.06 [hr]
no fatalities during service life > 100%% safe
average flight hours till crash : 4.22 [mln hr] (960 service years)
safe flight hours till fatality : 4224000 [hr] (960.0 service years)
reservation pax liability/flying hour : 0.03 [SDR*] (0.04 [eur])
insurance cost per hour : 448 [eur] insurance rate : 1.3 [%]
engine maintenance cost per hour : 5139.0 [eur]
wing maintenance cost per hour : 209.1 [eur]
fuselage maintenance cost per hour : 103.31 [eur]
tire life (time till worn out) : 99 [cycles]
maintenance cost per hour (excluding engines): 5055 [eur]
direct operating cost per hour: 25249 [eur], DOC per km : 28.72 [eur]
DOC per seat 1000km flight (450 [pax] 2-class seating): 62.88 [eur/1000PK]
DOC per seat 1000km flight (high density seating): 53.56 [eur/1000PK]
DOC per kg cargo for a 1000km flight : 0.44 [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 : 4.35 [eur/pax]
airport landing fee / passenger : 4.35 [eur/pax]
retour ticket price 1000km trip : 204.61 [eur/pax]
price retour ticket Schiphol-Barcelona : 239.19 [eur/pax]
Emirates 777-31H A6-EMW c/n 32700 landing at Mauritius, April 2013
accidents with fatalities > see the accident file
Literature :
https://contentzone.eurocontrol.int/aircraftperformance/default.aspx?
https://www.boeing.com/commercial/airports/plan-manuals
Air International dec’96 page 349, apr’94 page 180
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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