Aircraft investigation >>>>>>> HOME PAGE
weight and performance calculations for the Boeing 777-200
Thai Airways HS-TJB c/n 27727, Bangkok, Feb 2024
Boeing 777-200
role : wide-body airliner
importance : ****
first flight : 12 June 1994 (commanded by chief test pilot John E. Cashman) operational : June 1995 (United Airlines)
country : United States of America
production : 88 aircraft at Everett (final assembly line)
general information :
The 777-200 fills the gap between the 767 and the 747. Direct competitor is the A330-300.
Diameter PW4077 : 2.845 [m], GE90 : 3.10 [m]. It has a 180-minute ETOPS clearance.
The -200 is especially popular with U.S. carriers that operate domestic flights with it.
It has a fully-digital fly-by-wire controls.
primary users : United Airlines, Japan Air System, Thay Airways, British Airways
Accommodation:
flight crew : 2 cabin crew : 10
passengers : seating for 355 in two class : 30 business class and 325 economy- class seats
( 31 -in pitch) high density seating for 418 passengers
engine : 2 Pratt & Whitney PW4075 turbofan engines of 343.0 [KN] (77108.2 [lbf]), other engine options : Rolls Royce Trent 800 or General Electric GE90
Measured chord at root : 13.14 [m], at tip : 2.63 [m]
dimensions :
wingspan : 60.93 [m], length overall: 63.73 [m], length of fuselage : 61.84 [m] height :
18.44 [m] wing area : 427.8 [m^2] fuselage exterior width : 6.2 [m]
weights :
empty weight : 134800 [kg]
operating empty weight : 134800 [kg] max. structural payload : 55670 [kg]
Zero Fuel weight (ZFW) : 190470 [kg] max. landing weight (MLW) : 201800 [kg]
max. take-off weight : 242630 [kg] weight fuel : 92112 [kg] (117340 [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 : 875 [km/hr] (Mach 0.84 ) at 11890 [m]
service ceiling : 13100 [m]
range with max fuel and MTOW : 12038 [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-fibre-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: 13.14 [m]
measured wing chord at tip : 2.63 [m]
taper ratio : 0.200 [ ]
mean wing chord : 7.02 [m]
wing aspect ratio : 8.68 []
Oswald factor (e): 0.687 []
seize (span*length*height) : 71604 [m^3]
calculation : *2* (fuel consumption)
oil consumption : 17.2 [kg/hr]
fuel consumption (econ. cruise speed) : 6495.6 [kg/hr] (8274.7 [litre/hr]) at 27 [%] power
distance flown for 1 kg fuel : 0.13 [km/kg] at 11890 [m] height, sfc : 35.5 [kg/KN/h]
total fuel capacity : 117340 [litre] (92112 [kg])
calculation : *3* (weight)
weight engine(s) dry : 13694.0 [kg] = 19.96 [kg/KN]
weight 339.5 litre oil tank : 28.86 [kg]
oil tank filled with 4.3 litre oil : 3.9 [kg]
oil in engine 8.4 litre oil : 7.5 [kg]
fuel in engine 37.4 litre fuel : 27.44 [kg]
weight fuel lines : 204.6 [kg]
weight engine cowling : 1783.6 [kg]
weight thrust reversers : 1029.0 [kg]
total weight propulsion system : 16779 [kg](6.9 [%])
***************************************************************
Accommodation cabin facilities:
typical 2-class cabin layout for 355 passengers : economy : pitch : 78.7 [cm] 31.0 [-in]
( 3+3+3 ) seating in 40.4 rows
weight passenger seats : 1835.9 [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 : 418 [pax] at mainly 10 -abreast seating in 47.7 rows,
pitch 77.1 [cm] 30.4 [-in]
pax density, normal seating : 0.71 [m2/pax], high density seating : 0.61 [m2/pax]
weight 9 lavatories : 278.7 [kg]
weight 10 galleys : 862.6 [kg]
weight overhead stowage for hand luggage : 124.2 [kg]
weight 4 wardrobe closets : 35.5 [kg]
weight 3 movie screens : 67.6 [kg]
weight 83 windows (38 x 25 cm) made of acrylic glass : 187.2 [kg]
weight 8 (1.93 x 1.07 [m]) Type A main entry doors : 649.2 [kg]
weight 3 (main door size : 1.75 x 1.78 [m]) freight doors (belly) : 345.9 [kg]*
Space for 32 LD3 ULD containers in the belly + 17 m^3 bulk cargo
total belly baggage/cargo hold volume : 193.0 [m3]
underfloor belly hold can accommodate : 32 LD3 containers, netto volume : 142.9 [m3]
and : 17.0 [m3] bulk cargo
cabin volume (usable), excluding flight deck : 510 [m3]
passenger compartment volume : 317 [m3]
United Airlines 777-200 interior
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 : 4492.9 [kg]
safety facilities:
evacuation time with 418 passengers : 51 [sec]
weight 16 hand fire extinguisher : 49 [kg]
weight cockpit voice recorder (CVR) and flight data recorder (FDR): 20.0 [kg]
weight oxygen masks & oxygen generators : 230.8 [kg]
weight emergency flare installation : 10 [kg]
weight 8 emergency evacuation slides : 500.2 [kg]
weight safety equipment & facilities : 810 [kg]
fuselage construction:
fuselage aluminium frame : 30217 [kg]
floor loading (payload/m2): 220 [kg/m2]
weight rear pressure bulkhead : 609.6 [kg]
fuselage covering ( 884.3 [m2] duraluminium 3.80 [mm]) : 8992.8 [kg]
weight floor beams : 5370.9 [kg]
weight cabin furbishing : 3858.8 [kg]
weight cabin floor : 3583.0 [kg]
weight (sound proof) isolation : 671.5 [kg] TO-noise level : 96.0 [EPNdB]
weight -2752 [litre] main central fuel tanks empty : -154.1 [kg]
weight empty 1444 [litre] potable water tank : 127.8 [kg]
weight empty waste tank : 43.4 [kg]
weight fuselage structure : 53320.1 [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]
Cockpit of Thai airways 777-200 HS-TJC c/n 27728
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 : 761 [m3] cabin air refreshment time : 2.9 [min]
weight air-conditioning and pressurization system : 446 [kg]
weight APU / engine starter: 171.5 [kg]
weight lighting : 117.2 [kg]
weight triple redundant 207 bar hydraulic system : 242.1 [kg]
weight three engine-driven 90kVA 400 Hertz electricity generators : 88.8 [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 : 26.2 [kg]
weight systems : 1155.3 [kg]
total weight fuselage : 59920 [kg](24.7 [%])
***************************************************************
total weight aluminium ribs (1705 ribs) : 8359 [kg]
weight engine mounts : 343 [kg]
weight 6 wing fuel tanks empty for total 120092 [litre] fuel : 6725 [kg]
weight wing covering (painted aluminium 3.59 [mm]) : 8299 [kg]
total weight aluminium spars (multi-cellular wing structure) : 9783 [kg]
weight wings : 26441 [kg]
weight wing/square meter : 61.81 [kg]
United Airlines 777-200 N769UA, c/n26921, taking off from LAX, March 2023
weight thermal leading-edge anti-icing : 67.0 [kg]
weight ailerons made of graphite hybrid composites (17.52 [m2]) : 434.2 [kg]
weight fin (59.00 [m2]) : 1827.8 [kg]
weight rudder (24.53 [m2]) : 729.5 [kg]
weight tailplane (stabilizer) (64.00 [m2]): 2180.9 [kg]
weight elevators (16.32 [m2]): 273.01 [kg]
weight flight control hydraulic servo actuators: 119.3 [kg]
weight trailing-edge double slotted flaps (83.42 [m2]) : 2196.4 [kg]
weight track-mounted light alloy construction leading edge slats (42.55 [m2]) : 704.7 [kg]
weight fly-by-wire operated spoilers of graphite composite construction (16.7 [m2]) : 227.5
[kg]
weight airbrakes (8.4 [m2]) : 131.4 [kg]
total weight wing construction : 42401 [kg] (31.5 [%])
*******************************************************************
tire pressure main wheels : 12.50 [Bar] (nitrogen), ply rating : 32 PR
tire speed limit : 364 [km/hr]
total tyre footprint : 1.19 [m2]
Runway LCN at MTOW (0.76m radius of rigidity) : 53 [ ]
Aircraft Classification Number (ACN), MTOW on rigid runway and medium
subgrade strength (B) : 30 [ ]
Can also operate from unpaved runways subgrade B
wheel pressure : 17792.9 [kg]
weight 12 Dunlop 50 x 20 main wheels (1270 [mm] by 508 [mm]) : 1936.4 [kg]
weight 2 nose wheels : 161.4 [kg]
weight hydraulic disc wheel-brakes : 190.5 [kg]
weight Duplex anti-skid units : 12.6 [kg]
weight oleo-pneumatic shock absorbers : 254.0 [kg]
weight wheel hydraulic operated retraction system : 2396.3 [kg]
weight undercarriage struts (six-wheel bogies) with axle 6910.7 [kg]
total weight landing gear : 11861.8 [kg] (4.9 [%]
*******************************************************************
********************************************************************
calculated empty weight : 130961 [kg](54.0 [%])
weight oil for 16.2 hours flying : 291.8 [kg]
weight lifejackets : 159.8 [kg]
weight 6 life rafts : 221.9 [kg]
weight catering : 798.8 [kg]
weight water : 1278.0 [kg]
weight crew : 972 [kg]
weight crew luggage, nav. chards, flight doc., miscell. items : 117 [kg]
operational weight empty : 134800 [kg] (55.6 [%])
Cathay Pacific 777-200 B-HNL c/n 27116 at Hong Kong, January 2018, with RR Trent engines
********************************************************************
weight 355 passengers : 27335 [kg]
weight luggage : 5680 [kg]
weight cargo : 22655 [kg] (cargo + luggage/m3 belly : 139 [kg/m3])
zero fuel weight (ZFW): 190470 [kg](78.5 [%])
weight fuel for landing (1.7 hours flying) : 11330 [kg]
max. landing weight (MLW): 201800 [kg](83.2 [%])
max. fuel weight : 226912 [kg] (93.5 [%])
payload with max fuel : 169 passengers + luggage 15718 [kg]
published maximum take-off weight : 242630 [kg] (100.0 [%])
Two class layout 30+163+116 = 309 Thay Airways
calculation : * 4 * (engine power)
power loading (Take-off) : 354 [kg/KN]
power loading (Take-off) 1 PUF: 707 [kg/KN]
max. total take-off power : 686.0 [KN]
calculation : *5* (loads)
manoeuvre load : 1.2 [g] at 9000 [m]
limit load : 2.5 [g] ultimate load : 3.8 [g] load factor : 1.2 [g]
design flight time : 4.50 [hours]
design cycles : 14230 sorties, design hours : 64035 [hours]
max. wing loading (MTOW & flaps retracted) : 567 [kg/m2]
wing stress (2 g) during operation : 164 [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 : 1.70 ["]
calculation : *7* (lift & drag ratios
lift coefficient at angle of attack 0° : 0.15 [ ]
lift coefficient at max. speed : 0.30 [ ]
lift coefficient at max. angle of attack (clean): 1.27 [ ]
max. lift coefficient full flaps : 1.97 [ ]
drag coefficient at max. speed : 0.0397 [ ]
drag coefficient at econ. cruise speed : 0.0446 [ ]
induced drag coefficient at econ. cruise speed : 0.0118 [ ]
drag coefficient (zero lift) : 0.0328 [ ]
lift/drag ratio at econ. speed : 7.53 [ ]
calculation : *8* (speeds
take-off decision speed (V1) : 265 [km/u] (143 [kt])
take-off rotation speed (VR) : 278 [km/u] (150 [kt])
lift-off speed (VLOF) : 293 [km/u] (158 [kt]) at pitch angle : 14.6 [°]
take-off safety speed (V2) : 302 [km/u] (163 [kt])
flap retraction speed (V3) at 500m (OW loaded : 236134 [kg]): 323 [km/u] (174 [kt])
steady initial climb speed (V4) : 328 [km/u] (177 [kt])
The 777 was the first commercial aircraft to be developed using an entirely computer-aided design (CAD) process. Each design drawing was created on a three-dimensional CAD software system known as CATIA , sourced from Dassault Systemes and IBM . This allowed engineers to virtually assemble the 777 aircraft on a computer system to check for interference and verify that the thousands of parts fit properly before the actual assembly process—thus reducing costly rework .
climb speed (to FL150 with 63 [%] power) : 493 [km/hr] (266 [kt])
max. endurance speed (Vbe): 426 [km/u] min. fuel/hr : 5732 [kg/hr] at height : 3962 [m]
max. range speed (Vbr): 875 [km/u] (0.83 [mach]) min. fuel consumption : 7.57 [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:41 [%])
airflow at cruise speed per engine : 509.1 [kg/s]
speed of thrust jet : 1576 [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): 342 [km/u] (184 [kt])
stalling speed clean at 500 [m] height at Max.Landing Weight : 201800 [kg]): 285 [km/u]
(154 [kt])
final approach speed (landing speed) at sea-level with full flaps VREF (max. landing weight):
254 [km/u] (137 [kt])
ICAO Aircraft Approach Category (APC) : C
stalling speed at sea-level with full flaps VSO (max. landing weight): 196 [km/u] (106 [kt]
rate of climb at sea-level ROC (loaded, 63 % power) : 830 [m/min]
rate of climb at sea-level ROC (loaded, 75 % power) : 1149 [m/min]
rate of climb at 1000 [m] with 1 engine out (PUF/MTOW, 100 % power on remaining
engines) : 378 [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)
low wheel pressure, can also take off from unpaved runways
take-off distance at sea-level gravel/packed earth field : 2010 [m]
Brake kinetic energy capacity : 3530 [KW]
Take-off field length at 242000 kg : 7400 ft = 2256 [m]
FAR TO runway length (TOFL) requirement at TOW 242630 [kg] standard day at SL
: 2252 [m]
FAR landing runway requirement at MLW 201800 kg : 5030 ft > 1533 [m]
+++ FAA certification landing distance : +++
landing weight : 201800 [kg], TE flap setting : 50 [°]
runway condition : dry , landing over 50ft (15m) at threshold at sea-level
FAA approved landing field length : 1568 [m] (5145 [ft])
landing distance (C.A.R.) from 15 [m] at SL, wet runway: 1791 [m] (5875 [ft])
max. lift/drag ratio : 11.95 [ ]
climb to 5000 [m] with max payload : 5.58 [min]
climb to 10000 [m] with max payload : 17.16 [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: 236134 [kg] ) : 15800 [m]
calculation *10* (action radius & endurance)
range with max. payload: 6650 [km] with 55670.0 [kg] max. useful load (56.6 [%] fuel)*
range with high density pax: 9000 [km] with 418 passengers (74.9 [%] fuel)*
range with typical two-class pax: 9844 [km] with 355 passengers (81.2 [%] fuel)*
Range with max fuel : 6500 nm > 12038 km, ferry range : 7000 nm > 12964 km
range with max.fuel : 12408 [km] with 12 crew and 169 passengers and 100.0 [%] fuel*
ferry range : 13030 [km] with 2 crew and zero payload (100.0 [%] fuel)*
max range theoretically with additional fuel tanks total 141040 [litre] fuel : 15288 [km]*
* calculated ranges without fuel reserves
Available Seat Kilometres (ASK) : 3559606 [paskm]
useful load with range 1000km : 55670 [kg]
useful load with range 1000km : 418 passengers
production (theor.max load): 49658 [tonkm/hour]
production (useful load): 49658 [tonkm/hour]
production (passengers): 327518 [paskm/hour]
oil and fuel consumption per tonkm : 0.131 [kg]
calculation *11* (operating cost)
fuel cost per hour (8275 [litre]):4964 [eur] (40 [pax-km/litre fuel])
fuel cost per seat 1000km flight (367 [pax] 2-class seating): 15.16 [eur/1000PK]
oil cost per hour: 71 [eur]
crew cost per hour : 1650 [eur]
list price 2023 : 347 [mln USD]
average flying hours in 1 year : 3200 [hours] technical life : 18 [year]
real average service life : 18 [years]
depreciation - 20 [years] to 10% residual value
economic hours (expected total flying hours) : 64000 [hours]
financing interest per flying hour : 2440 [EUR]
write off per flying hour : 5005 [EUR]
time between engine failure : 12767 [hr]
can continue fly on 1 engine, low risk for emergency landing for PUF
workhours per day : 10.23 [hr]
no fatalities during service life > 100%% safe
average flight hours till crash : 5.07 [mln hr] (1584 service years)
safe flight hours till fatality : 5068800 [hr] (1584.0 service years)
reservation pax liability/flying hour : 0.03 [SDR*] (0.03 [eur])
insurance cost per hour : 315 [eur] insurance rate : 0.8 [%]
JAS 777-200 JA8979 c/n 27638
engine maintenance cost per hour : 4414.5 [eur]
wing maintenance cost per hour : 209.1 [eur]
fuselage maintenance cost per hour : 87.33 [eur]
tire life (time till worn out) : 114 [cycles]
maintenance cost per hour (excluding engines): 2673 [eur]
direct operating cost per hour: 21534 [eur], DOC per km : 24.61 [eur]
DOC per seat 1000km flight (367 [pax] 2-class seating): 65.75 [eur/1000PK]
DOC per seat 1000km flight (high density seating): 57.75 [eur/1000PK]
DOC per kg cargo for a 1000km flight : 0.43 [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 : 4.32 [eur/pax]
airport landing fee / passenger : 4.32 [eur/pax]
retour ticket price 1000km trip : 210.80 [eur/pax]
price retour ticket Schiphol-Barcelona : 246.96 [eur/pax]
British Airways 777-200 G-ZZZB c/n 27106
accidents with fatalities > there were none fatal accidents with an 777-200
Literature :
Air international dec’96 blz.349, apr’94 blz.180
Flight International apr’95 blz.26 Wayback Machine (archive.org)
www.boeing.com
www.wikepedia.org/wiki/Boeing_777
777 AIRPORT PLANNING DOCUMENT (boeing.com)
https://contentzone.eurocontrol.int/aircraftperformance/default.aspx?
confidence rating regarding source data : medium - all information is only available from news, social media or unofficial sources
Ron Woodward, president of the Boeing Commercial Airplane group 1994-1998
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 01 Januari 2024 contact : info.aircraftinvestigation@gmail.com ac jetpax 2020.py python 3.7.4