weight and performance calculations for the Boeing 767-400ER
Boeing 767-400ER
role : wide-body airliner
importance : **
first flight : 9 October 1999 operational : September 2000 (Continental Airlines)
country : United States of America
ICAO aircraft type designator : B764
production : 37 aircraft
general information :
Stretched version with 10 -15% more passenger seating. Fuselage lengthened 6.43m by inserting a 3.36m plug forward and 3.07m plug after the wing center section. Wing strengthened and span extended with 4.42m with new highly sweptback wingtips.
It has a new landing gear, with 46cm longer main legs and Boeing 777 brakes and tyres.
The FAA granted approval for the 767-400ER to operate 180-minute ETOPS flights before it
entered service.
primary users : United Airlines, Delta Airlines, Continental Airlines
Accommodation:
flight crew : 2 cabin crew : 9
passengers : seating for 296 in two class : 24 business class and 272 economy class seats
( 32 -in pitch) high density seating for 409 passengers
engine : 2 General Electric CF6-80C2B8F turbofan engines of 269.6 [KN] (60607 [lbf])
dimensions :
wingspan : 51.92 [m], length overall: 61.37 [m], length of fuselage : 60.08 [m]
height : 16.87 [m] wing area : 290.7 [m^2] fuselage exterior width : 5.03 [m]
weights :
operating empty weight : 103147 [kg] max. structural payload : 46538 [kg]
Zero Fuel weight (ZFW) : 149685 [kg] max. landing weight (MLW) : 158757 [kg]
max. take-off weight : 204116 [kg] weight usable fuel : 71725 [kg] (91370 [litres])
performance :
Max. operating Mach number (Mmo) : 0.86 [Mach] (940 [km/hr]) at 9000 [m]
critical Mach speed : 0.84 [Mach]
max. cruising speed : 885 [km/hr] (Mach 0.82 ) at 10000 [m] (33 [%] power)
economic cruising speed : 858 [km/hr] (Mach 0.80 ) at 10000 [m]
service ceiling : 13100 [m]
range with max fuel and MTOW : 10000 [km] (ATA domestic fuel reserves - 370.0 [km]
alternate)
description :
cantilever low-wing monoplane with retractable landing gear with nose wheel
engines and 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 on inner wing and
single-slotted flap on outer wing with full-span slotted LE flaps (slats) ,with spoilers
airfoil : Boeing airfoil with supercritical cross-section average thickness/chord ratio : 12.7
[%], sweep angle 3/4 chord: 31.5 [°] incidence : 4.25 [°], dihedral : 6.0 [°]
Fuselage : Pressurized aluminium-alloy stressed-skin structure of elliptical 0 section
calculation : *1* (dimensions)
wing chord at root : 8.57 [m]
wing chord at tip : 2.29 [m]
taper ratio : 0.267 [ ]
mean wing chord : 5.60 [m]
wing aspect ratio : 9.27 []
Oswald factor (e): 0.680 []
seize (span*length*height) : 53753 [m^3]
calculation : *2* (fuel consumption)
oil consumption : 18.9 [kg/hr]
fuel consumption (econ. cruise speed) : 5934.5 [kg/hr] (7559.8 [litre/hr]) at 33 [%] power
distance flown for 1 kg fuel : 0.14 [km/kg] at 10000 [m] height, sfc : 33.1 [kg/KN/h]
total fuel capacity : 91370 [litre] (71725 [kg])
calculation : *3* (weight)
weight engine(s) dry : 8800.0 [kg] = 16.32 [kg/KN]
weight 316.2 litre oil tank : 26.88 [kg]
oil tank filled with 3.4 litre oil : 3.0 [kg]
oil in engine 6.6 litre oil : 5.9 [kg]
weight all fuel lines and pumps containing 109 litres fuel : 165.6 [kg]
weight engine cowling : 1401.9 [kg]
weight thrust reversers : 808.8 [kg]
total weight propulsion system : 11212 [kg](5.5 [%])
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Accommodation cabin facilities:
typical 2-class cabin layout for 296 passengers : economy : pitch : 81.3 [cm] 32.0 [-in]
( 2+3+2 ) seating in 42.9 rows
weight passenger seats : 1580.8 [kg]
weight cabin crew seats : 45.0 [kg]
weight flight crew seats : 42.0 [kg]
high density seating passengers : 409 [pax] at mainly 8 -abreast seating in 52.9 rows,
pitch 74.0 [cm] 29.1 [-in]
pax density, normal seating : 0.74 [m2/pax], high density seating : 0.53 [m2/pax]
Two class arrangement has 7 lavatories and 8 galley’s, high density one class seating at 8 abreast in 53 rows
weight 7 lavatories : 133.6 [kg]
weight 8 galleys : 679.3 [kg]
weight overhead stowage for hand luggage : 103.6 [kg]
weight 5 wardrobe closets : 59.2 [kg]
Continental Airlines 767-400ER interior
weight 296 entertainment LCD screens in back of seats : 148.0 [kg]
weight 88 windows (41 x 28 cm) made of acrylic glass : 239.7 [kg]
weight 6 (1.88 x 1.07 [m]) Type A main entry doors : 465.4 [kg]
weight 2 (main door size : 1.75 x 1.78 [m]) freight doors (belly) : 261.1 [kg]*
total belly baggage/cargo hold volume : 180.8 [m3]
underfloor belly hold can accommodate : 38 LD2 containers, netto volume : 129.2 [m3]
and : 9.8 [m3] bulk cargo
cabin volume (usable), excluding flight deck : 599 [m3]
passenger compartment volume : 358 [m3]
passenger cabin max width : 4.72 [m] cabin length : 46.77 [m] max cabin height : 2.87 [m]
floor area : 218.2 [m2]
weight cabin facilities : 3757.6 [kg]
safety facilities:
The doors directly behind the wing are not used as service doors, they are only type I emergency exits
weight 2 type I over wing emergency exits (0.61x1.60 [m]): 75.2 [kg]
evacuation time with 409 passengers : 58 [sec]
weight 14 hand fire extinguisher : 42 [kg]
weight cockpit voice recorder (CVR) and flight data recorder (FDR): 20.0 [kg]
weight oxygen masks & oxygen generators (deploy cabin alt.>4267m): 192.4 [kg]
weight emergency flare installation : 10 [kg]
weight 6 emergency evacuation slides : 338.4 [kg]
weight safety equipment & facilities : 640 [kg]
fuselage construction:
fuselage aluminium frame : 24530 [kg]
floor loading (payload/m2): 213 [kg/m2]
weight rear pressure bulkhead : 388.4 [kg]
fuselage covering ( 731.6 [m2] duraluminium 3.73 [mm]) : 7271.5 [kg]
weight floor beams : 2641.6 [kg]
weight cabin furbishing : 3232.1 [kg]
weight cabin floor : 3130.4 [kg]
weight (sound proof) isolation : 582.8 [kg] TO-noise level : 97.7 [EPNdB]
weight 0 [litre] main central fuel tanks empty : 0.0 [kg]
weight empty 978 [litre] potable water tanks : 86.6 [kg]
weight empty waste tank : 31.8 [kg]
weight fuselage structure : 41894.9 [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]
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 6525 [m]
and gives equivalent of 2250 [m] at 11885 [m]. pressure differential : 0.59 [bar] (kg/cm2)
pressurized fuselage volume : 931 [m3] cabin air refreshment time : 3.5 [min]
weight air-conditioning and pressurization system : 452 [kg]
weight APU / engine starter : 134.8 [kg]
weight lighting : 97.7 [kg]
weight triple redundant 207 bar hydraulic system : 181.8 [kg]
weight two engine-driven 120kVA 400 Hz 3-phase AC electricity generators : 74.0 [kg]
weight ram air turbine for emergency electric power : 5.0 [kg]
weight 22Ah battery : 25.3 [kg]
weight controls : 24.6 [kg]
weight systems : 990.5 [kg]
total weight fuselage : 47424 [kg](23.2 [%])
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total weight aluminium ribs (1756 ribs) : 6864 [kg]
weight engine mounts : 270 [kg]
weight 6 wing fuel tanks empty for total 91370 [litre] fuel : 1371 [kg]
weight 365 [litre] vent surge tanks : 44 [kg]
weight wing covering (painted aluminium 4.49 [mm]) : 7054 [kg]
total weight aluminium spars (multi-cellular wing structure) : 8636 [kg]
weight wings : 22554 [kg]
weight wing/square meter : 77.59 [kg]
weight thermal leading-edge anti-icing : 57.1 [kg]
weight high & low speed ailerons made of graphite hybrid composites (11.90 [m2]) :
370.2 [kg]
weight fin (30.33 [m2]) : 1178.7 [kg]
weight rudder (15.89 [m2]) : 592.7 [kg]
weight tailplane (stabilizer) (59.90 [m2]): 2560.9 [kg]
weight elevators (17.79 [m2]): 373.38 [kg]
weight flight control hydraulic servo actuators: 89.6 [kg]
United Airlines N77066 c/n 29461 landing at RW 24R at Barcelona El Prat (BCN), January 2024, with single slotted flaps on the outside wing and double slotted flaps on the inner wing deployed.
weight trailing-edge double + single slotted flaps (43.29 [m2]) : 1432.6 [kg]
weight track-mounted light alloy construction leading edge slats (28.94 [m2]) : 602.0 [kg]
weight spoilers made of CFRP (16.3 [m2]) : 276.0 [kg]
total weight wing construction : 31772 [kg] (30.8 [%])
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tire pressure main wheels : 14.70 [Bar] (nitrogen), ply rating : 32 PR
tire speed limit : 389 [km/hr]
total tyre footprint : 0.89 [m2]
Runway LCN at MTOW (0.76m radius of rigidity) : 60 [ ]
Aircraft Classification Number (ACN), MTOW on rigid runway and medium subgrade
strength (B) : 45 [ ] Can only operate from unpaved runways with reduced weight and
reduced tyre pressure
wheel pressure : 22453.2 [kg]
weight 8 Dunlop 50 x 20 main wheels (1270 [mm] by 508 [mm]) : 1598.2 [kg]
weight 2 nose wheels : 199.8 [kg]
weight multi-disc wheel-brakes : 149.7 [kg]
weight Hydro-air flywheel detector type anti-skid units : 9.0 [kg]
weight oleo-pneumatic shock absorbers : 199.6 [kg]
weight wheel hydraulic operated retraction system : 1932.4 [kg]
weight undercarriage struts (four-wheel bogies) with axle 5476.7 [kg]
total weight landing gear : 9565.4 [kg] (4.7 [%]
*******************************************************************
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calculated empty weight : 99973 [kg](49.0 [%])
weight oil for 13.6 hours flying : 273.7 [kg]
unusable fuel in engine and tanks 137.1 litre fuel : 107.6 [kg]
weight lifejackets : 133.2 [kg]
weight 5 life rafts : 185.0 [kg]
weight catering : 629.0 [kg]
weight water : 865.5 [kg]
weight crew : 891 [kg]
weight crew luggage, nav. chards, flight doc., miscell. items : 89 [kg]
operational weight empty : 103147 [kg] (50.5 [%])
********************************************************************
weight 296 passengers : 22792 [kg]
weight luggage : 4736 [kg]
weight cargo : 19010 [kg] (cargo + luggage/m3 belly : 125 [kg/m3])
zero fuel weight (ZFW): 149685 [kg](73.3 [%])
weight fuel for landing (1.5 hours flying) : 9075 [kg]
max. landing weight (MLW): 158760 [kg](77.8 [%])
max. fuel weight : 174872 [kg] (85.7 [%])
payload with max fuel : 314 passengers + luggage 29248 [kg]
published maximum take-off weight : 204120 [kg] (100.0 [%])
calculation : * 4 * (engine power)
power loading (Take-off) : 379 [kg/KN]
power loading (Take-off) 1 PUF: 757 [kg/KN]
max. total take-off power : 539.2 [KN]
calculation : *5* (loads)
manoeuvre load : 0.7 [g] at 9000 [m]
limit load : 2.5 [g] ultimate load : 3.8 [g] load factor : 1.2 [g]
design flight time : 4.25 [hours]
design cycles : 14315 sorties, design hours : 60839 [hours]
max. wing loading (MTOW & flaps retracted) : 702 [kg/m2]
wing stress (2 g) during operation : 157 [N/kg] at 2g emergency manoeuvre
calculation : *6* (angles of attack)
angle of attack zero lift : -1.81 ["]
max. angle of attack (stalling angle, clean) : 10.72 ["]
max. angle of attack (full flaps) : 14.92 ["]
angle of attack at economic cruise speed : 3.66 ["]
calculation : *7* (lift & drag ratios
lift coefficient at angle of attack 0° : 0.16 [ ]
lift coefficient at max. speed : 0.39 [ ]
lift coefficient at max. angle of attack (clean): 1.11 [ ]
max. lift coefficient full flaps : 2.08 [ ]
drag coefficient at max. speed : 0.0514 [ ]
drag coefficient at econ. cruise speed : 0.0526 [ ]
induced drag coefficient at econ. cruise speed : 0.0118 [ ]
drag coefficient (zero lift) : 0.0408 [ ]
lift/drag ratio at econ. speed : 7.50 [ ]
calculation : *8* (speeds
take-off decision speed (V1) : 302 [km/u] (163 [kt])
take-off rotation speed (VR) : 305 [km/u] (165 [kt])
minimum unstick speed (Vmu) at TO angle 11.8 ° : 299 [km/u] (162 [kt])
United 767-400ER N78060 taking off with trailing edge flaps extended, with the long fuselage the aircraft cannot rotate to quickly on take-off for risking a tail strike, so lot of lift needs to come from the flaps. It has a retractable tailskid to protect the tail.
lift-off speed (VLOF) : 329 [km/u] (178 [kt]) at pitch angle : 9.7 [°]
take-off safety speed (V2) : 332 [km/u] (179 [kt])
flap retraction speed (V3) at 500m (OW loaded : 198186 [kg]): 380 [km/u] (205 [kt])
steady initial climb speed (V4) : 358 [km/u] (193 [kt])
climb speed (to FL150 with 69 [%] power) : 499 [km/hr] (270 [kt])
max. endurance speed (Vbe): 620 [km/u] min. fuel/hr : 4956 [kg/hr] at height : 9754 [m]
max. range speed (Vbr): 877 [km/u] (0.83 [mach]) min. fuel consumption : 6.26 [kg/km] at
cruise height : 11582 [m]
max. cruising speed : 885 [km/hr] (478 [kt]) at 10000 [m] (power:34 [%])
max. operational speed (Mmo) : 940 [km/hr] (Mach 0.86 ) at 9000 [m] (power:43 [%])
airflow at cruise speed per engine : 443.8 [kg/s]
speed of thrust jet : 1638 [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): 393 [km/u] (212 [kt])
stalling speed clean at 500 [m] height at Max.Landing Weight : 158760 [kg]): 327 [km/u]
(177 [kt])
Delta airlines 767-432ER N845MH landing, the inner trailing edge flaps are double slotted
final approach speed (landing speed) at sea-level with full flaps VREF (max. landing weight):
278 [km/u] (150 [kt])
ICAO Aircraft Approach Category (APC) : D
stalling speed at sea-level with full flaps VSO (max. landing weight): 214 [km/u] (115 [kt]
rate of climb at sea-level ROC (loaded, 69 % power) : 869 [m/min]
rate of climb at sea-level ROC (loaded, 75 % power) : 1023 [m/min]
rate of climb at 1000 [m] with 1 engine out (PUF/MTOW, 100 % power on remaining
engines) : 257 [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 : 4D
Brake kinetic energy capacity : 3533 [KW]
FAR take-off field length at MTOW 204120 kg : 10250 ft (3125m)
FAR TO runway length (TOFL) requirement at TOW 204120 [kg] standard day at SL (PUF
after V1): 3171 [m]
+++ FAA certification landing distance : +++
landing weight : 158760 [kg], TE flap setting : 30 [°]
runway condition : dry , landing over 50ft (15m) at threshold at sea-level
without use of thrust reversers
FAR landing runway length at MLW 158760 kg, at se-level, dry runway, 30° flaps, no thrust reversers : 6150ft > 1875m
FAA approved landing field length : 1877 [m] (6157 [ft])
landing distance (C.A.R.) from 15 [m] at SL, wet runway: 2151 [m] (7057 [ft])
max. lift/drag ratio : 11.03 [ ]
climb to 5000 [m] with max payload : 5.32 [min]
climb to 10000 [m] with max payload : 16.38 [min]
descent time from 10000 [m] to 250 [m] : 24.33 [min]
ceiling limited by max. pressure differential 14475 [m]
theoretical ceiling fully loaded (mtow- 60 min.fuel: 198186 [kg] ) : 13900 [m]
calculation *10* (action radius & endurance)
range with max. payload: 7688 [km] with 46538.0 [kg] max. useful load (75.9 [%] fuel)*
range with high density pax: 8992 [km] with 409 passengers (87.7 [%] fuel)*
range with typical two-class pax: 10418 [km] with 296 passengers (100.0 [%] fuel)*
Range with max payload (46538 kg): 3750nm (6945 km), with max. fuel : 5400nm (10000 km), ferry range : 6500nm (12038 km)
range with max.fuel : 10370 [km] with 11 crew and 314 passengers and 100.0 [%] fuel*
ferry range (calculated): 11227 [km] with 2 crew and zero payload (100.0 [%] fuel)*
max range theoretically with additional fuel tanks total 131461 [litre] fuel : 15544 [km]*
* calculated ranges without fuel reserves
Available Seat Kilometres (ASK) : 3286520 [paskm]
useful load with range 1000km : 46538 [kg]
useful load with range 1000km : 409 passengers
production (theor.max load): 41186 [tonkm/hour]
production (useful load): 41186 [tonkm/hour]
production (passengers): 279802 [paskm/hour]
oil and fuel consumption per tonkm : 0.145 [kg]
calculation *11* (operating cost)
fuel cost per hour (7560 [litre]):4536 [eur] (37 [pax-km/litre fuel])
fuel cost per seat 1000km flight (316 [pax] 2-class seating): 16.21 [eur/1000PK]
oil cost per hour: 78 [eur]
crew cost per hour : 1500 [eur]
list price 2024 : 265 [mln USD]
average flying hours in 1 year : 3600 [hours] technical life : 17 [year]
real average service life : 18 [years]
depreciation - 24 [years] to 10% residual value
economic hours (expected total flying hours) : 86400 [hours]
financing interest per flying hour : 1656 [EUR]
write off per flying hour : 3396 [EUR]
time between engine failure : 14722 [hr]
can continue fly on 1 engine, low risk for emergency landing for PUF
workhours per day : 11.60 [hr]
no fatalities during service life > 100%% safe
average flight hours till crash : 2.40 [mln hr] (666 service years)
safe flight hours till fatality : 2397600 [hr] (666.0 service years)
reservation pax liability/flying hour : 0.05 [SDR*] (0.07 [eur])
insurance cost per hour : 509 [eur] insurance rate : 1.9 [%]
engine maintenance cost per hour : 3210.6 [eur]
wing maintenance cost per hour : 150.5 [eur]
fuselage maintenance cost per hour : 81.01 [eur]
tire life (time till worn out) : 89 [cycles]
maintenance cost per hour (excluding engines): 2279 [eur]
direct operating cost per hour: 17164 [eur], DOC per km : 20.01 [eur]
DOC per seat 1000km flight (316 [pax] 2-class seating): 61.34 [eur/1000PK]
DOC per seat 1000km flight (high density seating): 47.42 [eur/1000PK]
DOC per kg cargo for a 1000km flight : 0.42 [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 : 4.30 [eur/pax]
airport landing fee / passenger : 4.30 [eur/pax]
retour ticket price 1000km trip : 201.00 [eur/pax]
price retour ticket Schiphol-Barcelona : 234.74 [eur/pax]
accidents with fatalities > no fatal accident happened with a 767-400ER
Literature :
wikipedia
Jane’s all the world aircraft 2000-2001 page 624,625,626,627
https://contentzone.eurocontrol.int/aircraftperformance/default.aspx ?
Aviation Safety Network > > ASN Aviation Safety Database results (aviation-safety.net)
https://www.boeing.com/commercial/airports/plan-manuals
arff_complete.pdf (boeing.com)
Air international okt’99 blz.194
Air international nov’99 blz.258
www.airliners.net
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 13 May 2024 contact : info.aircraftinvestigation@gmail.com ac jetpax 2020.py python 3.7.4
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