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weight and performance calculations for the Boeing 767-200ER
Air New Zealand Boeing 767-200ER ZK-NBC c/n 23328
Boeing 767-200ER
role : wide-body airliner
importance : ****
first flight : 6 March 1984 operational : May 1984 (Ethiopian)
country : United States of America
ICAO aircraft type designator :
production : 121 aircraft
general information :
Extended range version, made possible by a higher MTOW and a larger fuel capacity. It was fitted with one or two additional 14,000-litre tanks in the fuselage. This required the fuselage to be strengthened and more powerful engines were installed. The total fuel capacity now comes to 77000 liters or 91,000 liters when two additional center tanks are fitted, which can be used to fly nonstop from AMS to SIN.
The passenger capacity has become slightly smaller. It is one of the first twin-engine jet commercial aircraft with ETOPS license for flying over oceans.
The failure factor (MTBF) needed for 120 minutes ETOPS is 0.05 per 1000 flight hours (= once every 20000 flight hours). In 1984, 12000 commercial aircraft flew over the Atlantic Ocean in about 1 million flight hours. If these were all twin-engine airplanes, this means 2 million engine running hours; Theoretically, 100 engine failures occur in 1 year (with Mean Time Between Failure (MTBF) 20000 hr). Over the years MTBF has improved a lot, FAA now (2024) indicates MTBF for turbofan engines is 375000 hr !
Service ceiling, one engine out : 7200m.
Airlines can choose between two engines, the General Electric CF6-80A2 or the Pratt & Whitney JT9D-7R4E
Balkan Bulgarian 767-27EER F-GHGD or F-GHGE
primary users : TWA, ElAl, Ethiopian, American Airlines, Varig, Egypt air.
Accommodation:
flight crew : 2 cabin crew : 7
passengers : seating for 216 in two class : 18 first class and 198 coach class seats
( 34 -in pitch) exit limit : 255 passengers, high density seating for 245 passengers
engine : 2 General Electric CF6-80A2 turbofan engines of 221.9 [KN] (49884 [lbf]) or Pratt & Whitney JT9D-7R4E turbofan engine
Measured tail-angle : 10°
dimensions :
wingspan : 47.57 [m], length overall: 48.51 [m], length of fuselage : 47.24 [m] height : 15.85 [m]
wing area gross : 283.3 [m^2] fuselage exterior width : 5.03 [m]
weights :
operating empty weight : 82213 [kg] max. structural payload : 32545 [kg]
Zero Fuel weight (ZFW) : 114758 [kg] max. landing weight (MLW) : 126098 [kg]
max. take-off weight : 156489 [kg] weight usable fuel : 60768 [kg] (77412 [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] (31 [%] power)
economic cruising speed : 858 [km/hr] (Mach 0.80 ) at 10000 [m]
service ceiling : 12800 [m]
range with max fuel and MTOW : 11050 [km] (ATA domestic fuel reserves - 370.0 [km] alternate)
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 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 : 5.96 [m]
wing aspect ratio : 7.99 []
Oswald factor (e): 0.680 []
seize (span*length*height) : 36576 [m^3]
El Al 767-258ER 4X-EAD c/n 22975 was delivered to El Al in June 1984
calculation : *2* (fuel consumption)
oil consumption : 0.9 [kg/hr]
fuel consumption (econ. cruise speed) : 4565.6 [kg/hr] (5816.1 [litre/hr]) at 23 [%] power
distance flown for 1 kg fuel : 0.19 [km/kg] at 10000 [m] height, sfc : 45.0 [kg/KN/h]
total fuel capacity : 77412 [litre] (60768 [kg])
calculation : *3* (weight)
weight engine(s) dry : 7954.0 [kg] = 17.92 [kg/KN]
weight 25.1 litre oil tank : 2.13 [kg]
oil tank filled with 2.8 litre oil : 2.5 [kg]
oil in engine 5.4 litre oil : 4.9 [kg]
weight all fuel lines and pumps containing 100 litres fuel : 111.4 [kg]
weight engine cowling : 1153.9 [kg]
weight thrust reversers : 665.7 [kg]
total weight propulsion system : 9895 [kg](6.3 [%])
***************************************************************
Accommodation cabin facilities:
Possible max seating for 290 passengers (two additional overwing emergency exits needed), mainly at 8-seat abreast at 76 cm (30-in) pitch
typical 2-class cabin layout for 216 passengers : economy : pitch : 86.4 [cm] 34.0 [-in]
( 2+3+2 ) seating in 31.3 rows
first class pitch : 96.5 [cm] 38.0 [-in] at 6 -abreast
weight passenger seats (width 53.7 [cm]) : 1121.6 [kg]
weight cabin crew seats : 35.0 [kg]
weight flight crew seats : 42.0 [kg]
high density seating passengers : 245 [pax] at mainly 8 -abreast seating in 33.3 rows,
pitch 81.3 [cm] 32.0 [-in]
pax density, normal seating : 0.72 [m2/pax], high density seating : 0.63 [m2/pax]
weight 5 lavatories : 109.0 [kg]
weight 3 galleys : 349.9 [kg]
weight overhead stowage for hand luggage (total : 20.2 [m3]) : 69.0 [kg]
weight 1 wardrobe closets : 43.2 [kg]
weight 2 movie screens : 45.2 [kg]
weight 65 windows (41 x 28 cm) made of acrylic glass : 176.4 [kg]
weight 2 (1.88 x 1.07 [m]) Type A main entry doors : 150.0 [kg]
weight 2 (1.83 x 1.07 [m]) galley service doors : 146.0 [kg]
weight 2 (main door size : 1.75 x 1.78 [m]) freight doors (belly) : 252.4 [kg]*
total usable belly baggage/cargo hold volume : 111.2 [m3]
underfloor belly hold can accommodate : 22 LD2 containers, netto volume : 74.8 [m3]
and : 12.2 [m3] usable bulk cargo
cabin volume (usable), excluding flight deck : 434 [m3]
passenger compartment volume : 259 [m3]
Quantas Boeing 767-238ER VH-EAM c/n 23309 interior
passenger cabin max width : 4.72 [m] cabin length : 33.91 [m] max cabin height : 2.87 [m]
floor area : 154.8 [m2]
weight cabin facilities : 2539.8 [kg]
safety facilities:
weight 2 type III over wing emergency exits (51x91 cm): 36.5 [kg]
evacuation time with 245 passengers : 55 [sec]
weight 6 hand fire extinguisher : 17 [kg]
weight cockpit voice recorder (CVR) and flight data recorder (FDR): 20.0 [kg]
weight oxygen masks & oxygen generators (deploy cabin alt.>4267m): 140.4 [kg]
weight emergency flare installation : 10 [kg]
weight 4 emergency evacuation slides : 246.9 [kg]
weight safety equipment & facilities : 471 [kg]
fuselage construction:
fuselage aluminium frame : 18117 [kg]
floor loading (payload/m2): 210 [kg/m2]
weight rear pressure bulkhead : 375.8 [kg]
fuselage covering ( 558.9 [m2] duraluminium 3.61 [mm]) : 5376.9 [kg]
weight paint fuselage : 117.4 [kg]
weight aluminium floor beams : 1617.1 [kg]
weight cabin furbishing : 2295.1 [kg]
weight cabin floor : 2221.0 [kg]
weight (sound proof) isolation : 458.9 [kg] TO-noise level : 98.7 [EPNdB]
weight 31461 [litre] main central fuel tanks empty : 629.2 [kg]
weight empty 477 [litre] potable water tanks : 42.2 [kg]
weight empty waste tank : 24.9 [kg]
weight fuselage structure : 31275.2 [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]
LOT 767-200ER SP-LOA cockpit
weight dual digital Flight Management System (FMS) for navigation/auto-pilot : 20.0 [kg]
weight Cat IIIA 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 2 Rockwell Collins CRT screens to display EICAS information : 30 [kg]
weight reserve ADI, ASI, alti-meter, compass, engine temp. and rpm indicators : 15 [kg]
weight avionics : 147.0 [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 : 676 [m3] cabin air refreshment time : 3.5 [min]
weight air-conditioning and pressurization system : 329 [kg]
weight APU / engine starter : 111.0 [kg]
weight lighting : 71.3 [kg]
weight triple redundant 207 bar hydraulic system : 185.5 [kg]
weight two engine-driven 90kVA 400 Hz 3-phase AC electricity generators : 54.0 [kg]
weight ram air turbine for emergency electric power : 5.0 [kg]
weight 22Ah battery : 28.5 [kg]
weight controls : 20.7 [kg]
weight systems : 800.1 [kg]
total weight fuselage : 35233 [kg](22.5 [%])
***************************************************************
total weight aluminium ribs (50 ribs) : 5162 [kg]
weight engine mounts : 222 [kg]
weight 6 wing fuel tanks empty for total 45951 [litre] fuel : 689 [kg]
Wing 2x 22977 litres = 45954 litres + centre tank 31457 liters = total 77411 liter
weight 310 [litre] vent surge tanks : 37 [kg]
weight wing covering (painted aluminium 4.42 [mm]) : 6767 [kg]
total weight aluminium spars (multi-cellular wing structure) : 7613 [kg]
weight wings : 19542 [kg]
weight wing/square meter : 68.98 [kg]
weight bleed air thermal leading-edge anti-icing : 52.3 [kg]
weight high & low speed ailerons (11.6 [m2]) : 320.8 [kg]
weight fin (30.2 [m2]) : 1044.7 [kg]
weight rudder (16.0 [m2]) : 531.0 [kg]
weight tailplane (horizontal stabilizer) (59.9 [m2]): 2276.0 [kg]
weight elevators (17.8 [m2]): 331.8 [kg]
weight paint wing & tail surfaces : 156.8 [kg]
weight flight control hydraulic servo actuators: 61.0 [kg]
weight trailing-edge double + single slotted flaps (36.9 [m2]) : 1087.3 [kg]
TACA 767-2S1ER N767TA
weight track-mounted light alloy construction leading edge slats (28.3 [m2]) : 523.9 [kg]
weight fly-by-wire operated spoilers of graphite composite construction (15.9 [m2]) : 240.0
[kg]
total weight wing construction : 27116 [kg] (33.0 [%])
*******************************************************************
tire pressure main wheels : 12.10 [Bar] (nitrogen), ply rating : 28 PR
tire speed limit : 364 [km/hr]
total tyre footprint : 0.69 [m2]
Runway LCN at MTOW (0.76m radius of rigidity) : 59 [ ]
Aircraft Classification Number (ACN), MTOW on rigid runway and medium subgrade
strength (B) : 37 [ ] Can also operate from unpaved runways subgrade B
wheel pressure : 17213.8 [kg]
wheel track : 9.30 [m] wheelbase : 19.69 [m]
weight 8 Dunlop 46 x 18 main wheels (1170 [mm] by 458 [mm]) : 1150.0 [kg]
weight 2 nose wheels : 143.7 [kg]
weight multi-disc wheel-brakes : 135.0 [kg]
weight Hydro-air flywheel detector type anti-skid units : 9.0 [kg]
weight oleo-pneumatic shock absorbers : 153.0 [kg]
weight wheel hydraulic operated retraction system : 1599.4 [kg]
weight undercarriage struts (four-wheel bogies) with axle 4727.0 [kg]
total weight landing gear : 7917.2 [kg] (5.1 [%]
*******************************************************************
********************************************************************
calculated empty weight : 80160 [kg](51.2 [%])
weight oil for 15.0 hours flying : 14.2 [kg]
unusable fuel in engine and tanks 309.6 litre fuel : 243.1 [kg]
weight lifejackets : 97.2 [kg]
weight 4 life rafts : 135.0 [kg]
weight catering : 305.7 [kg]
weight water : 421.8 [kg]
weight crew : 729 [kg]
weight crew luggage, navigation chards, flight docs (NOTOC), manuals, miscellaneous items
: 107 [kg]
operational weight empty : 82213 [kg] (52.5 [%])
********************************************************************
weight 216 passengers : 16632 [kg]
weight luggage : 3456 [kg]
weight cargo : 12457 [kg] (cargo + luggage/m3 belly : 135 [kg/m3])
zero fuel weight (ZFW): 114758 [kg](73.3 [%])
weight fuel for landing (2.5 hours flying) : 11340 [kg]
max. landing weight (MLW): 126098 [kg](80.6 [%])
max. fuel weight : 142981 [kg] (91.4 [%])
payload with max fuel : 145 passengers + luggage 13508 [kg]
published maximum take-off weight : 156489 [kg] (100.0 [%])
calculation : * 4 * (engine power)
power loading (Take-off) : 353 [kg/KN]
power loading (Take-off) 1 PUF: 705 [kg/KN]
max. total take-off power : 443.8 [KN]
calculation : *5* (loads)
manoeuvre load : 1.0 [g] at 9000 [m]
limit load : 2.5 [g] ultimate load : 3.8 [g] load factor : 1.5 [g]
design flight time : 3.00 [hours]
design cycles : 19000 sorties, design hours : 57000 [hours]
max. wing loading (MTOW & flaps retracted) : 552 [kg/m2]
wing stress (2 g) during operation : 142 [N/kg] at 2g emergency manoeuvre
calculation : *6* (angles of attack)
angle of attack zero lift : -1.87 ["]
max. angle of attack (stalling angle, clean) : 11.30 ["]
max. angle of attack (full flaps) : 17.89 ["]
angle of attack at economic cruise speed : 2.48 ["]
calculation : *7* (lift & drag ratios
lift coefficient at angle of attack 0° : 0.16 [ ]
lift coefficient at max. speed : 0.31 [ ]
lift coefficient at max. angle of attack (clean): 1.13 [ ]
max. lift coefficient 30 [° ] flap setting : 1.96 [ ]
drag coefficient at max. speed : 0.0298 [ ]
drag coefficient at econ. cruise speed : 0.0306 [ ]
induced drag coefficient at econ. cruise speed : 0.0081 [ ]
drag coefficient (zero lift) : 0.0224 [ ]
lift/drag ratio at econ. speed : 10.33 [ ]
calculation : *8* (speeds
minimum unstick speed (Vmu) at TO angle 14.2 ° : 263 [km/u] (142 [kt])
take-off decision speed (V1) : 284 [km/u] (153 [kt])
take-off rotation speed (VR) : 288 [km/u] (155 [kt])
US Airways 767-201ER N245AY c/n 23897
lift-off speed (VLOF) : 306 [km/u] (165 [kt]) at pitch angle : 10.0 [°]
take-off safety speed (V2) : 308 [km/u] (166 [kt])
flap retraction speed (V3) at 500m (OW loaded : 151923 [kg]): 337 [km/u] (182 [kt])
steady initial climb speed (V4) : 334 [km/u] (180 [kt])
climb speed (to FL150 with 92 [%] power) : 688 [km/hr] (371 [kt])
max. endurance speed (Vbe): 464 [km/u] min. fuel/hr : 4034 [kg/hr] at height : 3658 [m]
max. range speed (Vbr): 881 [km/u] (0.83 [mach]) min. fuel consumption : 4.95 [kg/km] at cruise height : 11278 [m]
max. cruising speed : 885 [km/hr] (478 [kt]) at 10000 [m] (power:24 [%])
max. operational speed (Mmo) : 940 [km/hr] (Mach 0.86 ) at 9000 [m] (power:29 [%])
airflow at cruise speed per engine : 382.2 [kg/s]
speed of thrust jet : 1378 [km/hr]
Varig Boeing 767-241ER PP-VNN c/n 23803
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): 352 [km/u] (190 [kt])
stalling speed clean at 500 [m] height at Max.Landing Weight : 126098 [kg]): 293 [km/u]
(158 [kt])
final approach speed (landing speed) at sea-level with full flaps VREF (max. landing weight):
259 [km/u] (140 [kt])
ICAO Aircraft Approach Category (APC) : C
stalling speed at sea-level with full flaps VSO (max. landing weight): 199 [km/u] (108 [kt]
rate of climb at sea-level ROC (loaded, 92 % power) : 2056 [m/min]
rate of climb at sea-level ROC (loaded, 75 % power) : 1459 [m/min]
rate of climb at 1000 [m] with 1 engine out (PUF/MTOW, 92 % power on remaining engines)
: 435 [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)
Brake kinetic energy capacity : 2572 [KW]
Take-off field length at mtow 156489 kg (345000 lb), standard day, sea level : 7500 ft > 2285m
FAR TO runway length (TOFL) requirement at TOW 156489 [kg] standard day at SL
(= ASDA) : 2290 [m] Take-off flap setting : 10 [° ]
+++ FAA certification landing distance : +++
landing weight : 126098 [kg], TE flap setting : 30 [°]
runway condition : dry , landing over 50ft (15m) at threshold at sea-level
without use of thrust reversers
Landing field length at MLW 126098 kg (278000 lbs), sea-level, dry runway, 30° flap-setting, no thrust reverser : 4800 ft > 1465m, calculated 1658m. unclear why this difference. 1465m looks short compared to other widebody airliners.
FAA approved landing field length at SL, dry runway : 1658 [m] (5439 [ft])
landing distance (C.A.R.) from 15 [m] at SL, wet runway: 1903 [m] (6245 [ft])
max. lift/drag ratio : 13.79 [ ]
climb to 5000 [m] with max payload : 2.25 [min]
climb to 10000 [m] with max payload : 6.93 [min]
descent time from 10000 [m] to 250 [m] : 24.33 [min]
max. ceiling fully loaded (mtow- 60 min.fuel): 151923 [kg] ) : 15400 [m]
ceiling limited by max. pressure differential 14475 [m]
max. theoretical ceiling (OWE + 60 min.fuel) : 18300 [m] with flying weight :86779 [kg]
calculation *10* (action radius & endurance)
range with max. payload: 7529 [km] with 32545.0 [kg] max. useful load (68.7 [%] fuel)*
range with high density pax: 9487 [km] with 245 passengers (84.7 [%] fuel)*
range with typical two-class pax: 10042 [km] with 216 passengers (89.2 [%] fuel)*
Range with max. payload : 4950 nm > 9165 km
Range with max fuel : 6800 nm > 12590 km
Ferry range : 8000 nm > 14815 km
This range with max.fuel is not possible with 63210 liters, must be probably 91000 liter...for the calculations I use 77412 liter, with a range with max fuel of 11050 km > 5965 nm..
range with max.fuel : 11420 [km] with 9 crew and 145 passengers and 100.0 [%] fuel*
ferry range (calculated): 12133 [km] with 2 crew and zero payload (100.0 [%] fuel)*
max range theoretically with additional fuel tanks total 96268 [litre] fuel : 14645 [km]*
* calculated ranges without fuel reserves
Available Seat Kilometres (ASK) : 2220445 [paskm]
useful load with range 1000km : 32545 [kg]
useful load with range 1000km : 245 passengers
production (theor.max load): 28802 [tonkm/hour]
production (useful load): 28802 [tonkm/hour]
production (passengers): 198515 [paskm/hour]
oil and fuel consumption per tonkm : 0.159 [kg]
calculation *11* (operating cost)
fuel cost per hour (5816 [litre]):3489 [eur] (34 [pax-km/litre fuel])
fuel cost per seat 1000km flight (224 [pax] 2-class seating): 17.58 [eur/1000PK]
oil cost per hour: 4 [eur]
crew cost per hour : 1200 [eur]
list price 2024 : 181 [mln USD]
average flying hours in 1 year : 3655 [hours] technical life : 16 [year]
real average service life : 16 [years]
depreciation : 18 [years] to 10% residual value
financing interest per flying hour : 1114 [EUR]
write off per flying hour : 2653 [EUR]
time between engine failure : 15033 [hr]
can continue fly on 1 engine, low risk for emergency landing for PUF
workhours per day : 12.52 [hr]
average flight hours till crash : 2.28 [mln hr] (625 service years)
safe flight hours till fatality : 19812 [hr] (5.4 service years)
reservation pax liability/flying hour : 6.50 [SDR*] (8.13 [eur])
insurance cost per hour : 365 [eur] insurance rate : 2.0 [%]
engine maintenance cost per hour : 2216.7 [eur]
wing maintenance cost per hour : 207.8 [eur]
fuselage maintenance cost per hour : 124.20 [eur]
tire life (time till worn out) : 93 [cycles]
maintenance cost per hour (excluding engines): 1432 [eur]
direct operating cost per hour: 12482 [eur], DOC per km : 14.55 [eur]
DOC per seat 1000km flight (224 [pax] 2-class seating): 62.88 [eur/1000PK]
DOC per seat 1000km flight (high density seating): 57.57 [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 : 4.00 [eur/pax]
airport landing fee / passenger : 4.00 [eur/pax]
retour ticket price 1000km trip : 203.05 [eur/pax]
price retour ticket Schiphol-Barcelona : 237.64 [eur/pax]
accidents with fatalities > see the accident file
notes :
Has the smallest floor area of all widebody airliners and least number of passengers.
Literature :
https://contentzone.eurocontrol.int/aircraftperformance/default.aspx?
https://www.boeing.com/commercial/airports/plan-manuals
rescue : https://www.boeing.com/commercial/airports/rescue-fire
Air international apr’94 page 202
Verkeersvliegtuigen page 88,98
KIJK feb’81, mei’83, jan’86
Luchtvaart feb’95
Flugrevue nov’84 www.boeing.com
Jane’s all the world aircraft 1991-92 page 379,380
Turbine engine failure - Wikipedia
Turbofan & Turboprop Engines – Introduction to Aerospace Flight Vehicles
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 15 December 2024 contact : info.aircraftinvestigation@gmail.com ac jetpax 2020.py python 3.7.4
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