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weight and performance calculations for the Boeing 757-300
Condor was the first operator of the stretched 757-300, starting operations in March 1999. Seen here is D-ABOH s/n 30030
Boeing 757-300
role : jet airliner
importance : ****
first flight : 2 August 1998 operational : March 1999 (Condor)
country : United States of America
design :
production : 55 aircraft
general information :
Fuselage extended by 7.11m compared to the 757-200. It can carry up to 289 passengers at
71-74cm pitch. It can also be supplied with the PW2043 motor of 195.1 KN. With this engine
it has a range of 6455 km with 240 passengers. The OWE is then 64460 kg
primary users : Condor, Icelandair, Arkia, Northwest, American Trans Air, Continental,
JMC air, Delta, United Airlines
Accommodation:
flight crew : 2 cabin crew : 7
passengers : seating for 243 in two class : 12 business class and 231 economy class seats ( 32 -in pitch)
high density seating for 279 passengers
engine : 2 Rolls Royce RB211-535E4B turbofan engines of 191.7 [KN] (43095.1 [lbf])
dimensions :
wingspan : 38.05 [m], length : 54.47 [m], height : 13.56 [m]
wing area : 185.25 [m^2] fuselage exterior width : 3.76 [m]
weights :
operating empty weight : 64570 [kg] max. structural payload : 30690 [kg]
Zero Fuel weight (ZFW) : 95260 [kg] max. landing weight (MLW) : 101610 [kg]
max.take-off weight : 122470 [kg] weight fuel : 34796 [kg] (43495 [liter])
performance :
Max. operating Mach number (Mmo) : 0.86 [Mach] (960 [km/hr]) at 7500 [m]
normal cruise speed : 885 [km/hr] (Mach 0.82 ) at 10000 [m] (28 [%] power)
economic cruise speed : 863 [km/hr] (Mach 0.80 ) at 10000 [m]
service ceiling : 11000 [m]
range with max fuel and Max.TOW : 6295 [km] (ATA domestic fuel reserves - 370.0 [km] alternate)
description :
cantilever low-wing monoplane with retractable landing gear with nose wheel
Wings : two main spar fail-safe wing structure
with double slotted flaps with slotted LE flaps (slats) ,with spoilers airfoil : NACA with
supercritical cross-section sweep angle 3/4 chord: 25.0 [°]
Delta airlines 757-300 N583NW taking off
engines and landing gear attached to the wings, fuel tanks in the wings and fuselage
Fuselage : Pressurized all-metal aluminium-alloy stressed-skin structure
of elliptical 0 section
calculation : *1* (dimensions)
measured wing chord at root: 8.51 [m]
measured wing chord at tip : 2.13 [m]
taper ratio : 0.250 [ ]
mean wing chord : 4.87 [m]
calculated average wing chord tapered wing with rounded tips: 4.87 [m]
wing aspect ratio : 7.82 []
oswald factor (e): 0.695 []
seize (span*length*height) : 28104 [m^3]
calculation : *2* (fuel consumption)
oil consumption : 7.3 [kg/hr]
fuel consumption (econ. cruise speed) : 4505.5 [kg/hr] (5631.8 [litre/hr]) at 30 [%] power
distance flown for 1 kg fuel : 0.19 [km/kg] at 10000 [m] height, sfc : 38.9 [kg/KN/h]
total fuel capacity : 43495 [litre] (34796 [kg])
calculation : *3* (weight)
weight engine(s) dry : 7500.0 [kg] = 19.56 [kg/KN]
weight 83 litre oil tank : 7.08 [kg]
oil tank filled with 2.4 litre oil : 2.2 [kg]
oil in engine 4.7 litre oil : 4.2 [kg]
fuel in engine 20.9 litre fuel : 15.34 [kg]
weight fuel lines 98.5 [kg]
weight engine cowling 996.8 [kg]
weight thrust reversers 575.1 [kg]
total weight propulsion system : 9199 [kg](7.5 [%])
***************************************************************
Accommodation cabin facilities:
typical 2-class cabin layout for 243 passengers : economy : pitch : 81.3 [cm] 32.0 [-in]
( 3+3 ) seating in 40.9 rows
weight seats : 1260.0 [kg]
high density seating passengers : 279 [pax] at 6 -abreast seating in 46.5 rows,
pitch 78.2 [cm] 30.8 [-in]
pax density, normal seating : 0.62 [m2/pax], high density seating : 0.54 [m2/pax]
weight 5 lavatories : 76.4 [kg]
weight 5 galleys : 383.5 [kg]
Condor 757-300 interior
weight overhead stowage for hand luggage : 85.0 [kg]
weight 5 wardrobe closets : 48.6 [kg]
weight 84 windows : 75.4 [kg]
weight 7 1.83x0.88 [m] main entry doors : 366.3 [kg]
weight 1 1.62x0.85 [m] service doors : 45.2 [kg]
weight 2 (130x122 cm) freight doors (belly) : 90.1 [kg]
total belly baggage/cargo hold volume : 71.48 [m3]
cabin volume (usable), excluding flight deck : 285 [m3]
passenger compartment volume : 190 [m3]
passenger cabin max.width : 3.53 [m] cabin length : 43.44 [m] cabin height : 2.20 [m]
floor area : 149.6 [m2]
weight cabin facilities : 2430.5 [kg]
safety facilities:
weight 4 type III over wing emergency exits (51x91 cm): 64.0 [kg]
evacuation time with 279 passengers : 38 [sec]
weight 12 hand fire extinguisher : 35 [kg]
weight cockpit voice recorder (CVR) and flight data recorder (FDR): 20.0 [kg]
weight oxygen masks & oxygen generators : 158.0 [kg]
weight emergency flare installation : 10 [kg]
weight 8 emergency evacuation slides : 207.7 [kg]
weight safety equipment & facilities : 475 [kg]
fuselage construction:
fuselage aluminium frame : 14027 [kg]
floor loading (payload/m2): 205 [kg/m2]
weight rear pressure bulkhead : 184.7 [kg]
fuselage covering ( 494.0 [m2] duraluminium 3.17 [mm]) : 4113.6 [kg]
weight floor beams : 875.0 [kg]
weight cabin furbishing : 1308.6 [kg]
weight cabin floor : 2152.6 [kg]
Landing United 757-300 N56859
weight (sound proof) isolation : 356.5 [kg]
weight 15436 [litre] main central fuel tanks empty : 864.4 [kg]
weight empty 289 [litre] potable water tank : 25.6 [kg]
weight empty waste tank : 16.3 [kg]
weight fuselage structure : 23924.6 [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 weather radar : 25.0 [kg]
Condor 757-300 cockpit D-ABOA June 2012
weight VOR/ILS,RMI,DME,radio altimeter : 12.0 [kg]
weight Integrated Flight System / auto-pilot : 23.0 [kg]
weight EFIS (CRT PFD+ND) : 8 [kg]
weight ground proximity warning system (GPWS) : 6 [kg]
weight engine monitoring system ECAM : 6 [kg]
weight avionics : 94.0 [kg]
Systems:
Air-conditioning and pressurization system maintains sea level conditions up to 6550 [m]
and gives equivalent of 2000 [m] at 11200 [m]. pressure differential : 0.59 [bars] (kg/cm2)
pressurized fuselage volume : 495 [m3]
weight air-conditioning and pressurization system : 301 [kg]
weight APU / engine starter: 95.8 [kg]
weight lighting : 80.2 [kg]
weight three independent 207 bar hydraulic systems : 93.7 [kg]
weight engine-driven 40kVA electricity generators : 60.8 [kg]
weight 22Ah battery : 12.0 [kg]
weight controls : 21.3 [kg]
weight systems : 664.6 [kg]
total weight fuselage : 27588 [kg](22.5 [%])
***************************************************************
average Take-off weight : 111615 [kg](91.1 [%])
total weight aluminium ribs (1228 ribs) : 4174 [kg]
weight engine mounts : 192 [kg]
weight 6 fuel tanks empty for total 28059 [litre] fuel : 1571 [kg]
weight wing covering (painted aluminium 4.56 [mm]) : 4563 [kg]
total weight aluminium spars (multi-cellular wing structure) : 4565 [kg]
weight wings : 13302 [kg]
weight wing/square meter : 71.80 [kg]
weight thermal leading-edge anti-icing : 41.9 [kg]
weight ailerons (6.1 [m2]) : 220.4 [kg]
weight fin (24.6 [m2]) : 883.6 [kg]
weight rudder (12.9 [m2]) : 446.5 [kg]
weight tailplane (stabilizer) (42.9 [m2]): 1697.2 [kg]
weight elevators (10.9 [m2]): 212.5 [kg]
weight flight control hydraulic servo actuators: 46.8 [kg]
weight trailing-edge double slotted flaps (31.3 [m2]) : 960.5 [kg]
weight leading edge slats (10.1 [m2]) : 202.0 [kg]
weight spoilers (9.2 [m2]) : 165.5 [kg]
total weight wing construction : 19941 [kg] (30.9 [%])
*******************************************************************
tire pressure main wheels : 13.70 [Bar] (nitrogen), ply rating : 26 PR
tire speed limit : 364 [km/hr]
total tyre footprint : 0.34 [m2]
Aircraft Classification Number, MTOW on rigid runway and medium subgrade
strength (B) : 52 [ ]
Can only operate from unpaved runways with reduced weight and reduced tyre pressure
wheel pressure : 13471.7 [kg]
weight 8 Dunlop main wheels (1020 [mm] by 379 [mm]) : 1256.0 [kg]
weight 2 nose wheels : 157.0 [kg]
weight multi-disc wheel-brakes : 95.3 [kg]
weight flywheel detector type anti-skid units : 9.0 [kg]
weight oleo-pneumatic shock absorbers : 127.0 [kg]
weight wheel hydraulic operated retraction system : 1244.5 [kg]
weight undercarriage struts (four-wheel bogies) with axle 3271.7 [kg]
total weight landing gear : 6160.5 [kg] (5.0 [%]
*******************************************************************
********************************************************************
calculated empty weight : 62890 [kg](51.4 [%])
weight oil for 8.5 hours flying : 67.5 [kg]
weight lifejackets : 109.4 [kg]
weight 4 life rafts : 151.9 [kg]
weight catering : 319.5 [kg]
weight water : 255.6 [kg]
weight crew : 729 [kg]
weight crew lugage,nav.chards,flight doc.,miscell.items : 48 [kg]
operational weight empty : 64570 [kg] (52.7 [%])
********************************************************************
weight 243 passengers : 18711 [kg]
weight luggage : 3888 [kg]
weight cargo : 8091 [kg] (cargo+luggage/m3 belly : 154 [kg/m3])
zero fuel weight (ZFW): 95260 [kg](77.8 [%])
weight fuel for landing (1.4 hours flying) : 6350 [kg]
max. landing weight (MLW): 101610 [kg](83.0 [%])
max. fuel weight : 99366 [kg] (81.1 [%])
payload with max fuel : 248 passengers+luggage 23104 [kg]
published maximum take-off weight : 122470 [kg] (100.0 [%])
calculation : * 4 * (engine power)
power loading (Take-off) : 319 [kg/KN]
power loading (Take-off) 1 PUF: 639 [kg/KN]
max. total take-off power : 383.4 [KN]
calculation : *5* (loads)
manoeuvre load : 5.8 [g] at 1000 [m]
limit load : 2.5 [g] ultimate load : 3.8 [g] load factor : 1.3 [g]
design flight time : 2.63 [hours]
design cycles : 16400 sorties, design hours : 43132 [hours]
max. wing loading (MTOW & flaps retracted) : 661 [kg/m2]
wing stress (2 g) during operation : 165 [N/kg] at 2g emergency manoeuvre
calculation : *6* (angles of attack)
angle of attack zero lift : -1.76 ["]
max. angle of attack (stalling angle, clean) : 12.89 ["]
max. angle of attack (full flaps) : 17.09 ["]
angle of attack at max. speed : 1.76 ["]
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 : 1.25 [ ]
max. lift coefficient full flaps : 2.24 [ ]
drag coefficient at max. speed : 0.0451 [ ]
drag coefficient at econ. cruise speed : 0.0528 [ ]
induced drag coefficient at econ. cruise speed : 0.0129 [ ]
drag coefficient (zero lift) : 0.0399 [ ]
lift/drag ratio at max. speed : 6.64 [ ]
calculation : *8* (speeds
take-off safety speed (V2) : 293 [km/u]
take-off (initial climb) speed (Vto) : 343 [km/u]
stalling speed clean at sea-level (OW loaded : 117965 [kg]): 325 [km/u]
max. rate of climb speed : 517 [km/hr] at sea-level
max. endurance speed (Vbe): 545 [km/u] min. fuel/hr : 3872 [kg/hr] at height : 7010 [m]
max. range speed (Vbr): 876 [km/u] min. fuel consumption : 5.1 [kg/km] at cruise height
cruising speed : 885 [km/hr] at 10000 [m] (power:31 [%])
max. operational speed (Mmo) : 960 [km/hr] (Mach 0.86 ) at 7500 [m] (power:42.5 [%])
airflow at cruise speed per engine : 281.6 [kg/s]
speed of thrust jet : 1646 [km/hr]
initial descent speed 10000 - 7315 [m]: Mach 0.75
descent speed 7315 - 3048 [m]: 537 [km/u]
approach speed 3048 - 500 [m] (clean): 463 [km/u]
stalling speed clean at 500 [m] height at Max.Landing Weight : 101610 [kg]): 309 [km/u]
final approach speed at sea-level with full flaps (normal landing weight) (Vapp): 265 [km/u]
ICAO Aircraft Approach Category (APC) : D
landing speed at sea-level (normal landing weight(Vtd): 101322 [kg]): 234 [km/hr]
stalling speed at sea-level with full flaps (max. landing weight): 204 [km/u]
rate of climb at sea-level ROC (loaded, 65 % power) : 986 [m/min]
rate of climb at 1000 [m] with 1 engine out (PUF/MTOW, 100 % power on remaining
engines) : 404 [m/min]
rate of descent: 457 [m/min]
calculation : *9* (regarding various performances)
high wheel pressure, can only take off from paved runways
Take off distance at mtow 122470 [kg] at s/l : 2500 [m]
take-off distance at sea-level concrete runway : 1789 [m]
take-off distance at sea-level over 15 [m] height : 1920 [m]
balanced runway length at MTOW and at SL (FAR) : 3447 [m]
FAR runway length requirment at MTOW, standard day at SL : 2618 [m]
landing distance (MLW) : 995 [m]
Runway length at MLW 101610 [kg] : 1700 [m]
landing distance (C.A.R.) from 15 [m] at SL, dry runway : 1302 [m]
landing distance (C.A.R.) from 15 [m] at SL, wet runway : 1602 [m]
landing runway length requirements at SL : 1658 [m]
lift/drag ratio : 10.35 [ ]
climb to 5000 [m] with max payload : 4.69 [min]
climb to 10000 [m] with max payload : 14.44 [min]
descent time from 10000 [m] to 250 [m] : 24.33 [min]
ceiling limited by max. pressure differential 14550 [m]
theoretical ceiling fully loaded (mtow- 60 min.fuel: 117965 [kg] ) : 15000 [m]
calculation *10* (action radius & endurance)
range with max. payload: 5120 [km] with 30690.0 [kg] max. useful load (78.2 [%] fuel)*
range with high density pax: 6080 [km] with 279 passengers (91.8 [%] fuel)*
Range with max.fuel at mtow 122470 [kg] : 3200 [NM] (5925 [km])
range with typical two-class pax: 6681 [km] with 243 passengers (100.0 [%] fuel)*
range with max.fuel : 6665 [km] with 9 crew and 248 passengers and 100.0 [%] fuel*
ferry range : 7404 [km] with 2 crew and zero payload (100.0 [%] fuel)*
max range theoretically with additional fuel tanks total 73803 [litre] fuel : 11944 [km]*
* calculated ranges without fuel reserves
Available Seat Kilometres (ASK) : 1670738 [paskm]
useful load with range 1000km : 30690 [kg]
useful load with range 1000km : 279 passengers
production (theor.max load): 27161 [tonkm/hour]
production (useful load): 27161 [tonkm/hour]
production (passengers): 224407 [paskm/hour]
oil and fuel consumption per tonkm : 0.166 [kg]
calculation *11* (operating cost)
fuel cost per hour (5632 [litre]):3379 [eur] (40 [pax-km/litre fuel])
fuel cost per seat 1000km flight (254 [pax] 2-class seating): 15.06 [eur/1000PK]
oil cost per hour: 30 [eur]
crew cost per hour : 1200.000 [eur]
list price 2023 : 167 [mln USD]
average flying hours in 1 year : 3275 [hours] technical life : 13 [year]
real average service life : 22 [years]
economic hours (average real flown hours) : 72050 [hours]
financing interest per flying hour : 1187 [EUR]
write off per flying hour : 1993 [EUR]
time between engine failure : 26034 [hr]
can continue fly on 1 engine, low risk for emergency landing for PUF
workhours per day : 11.53 [hr]
no fatalities during service life > 100% safe
average flight hours till crash : 3.96 [mln hr] (1210 service years)
safe flight hours till fatality : 3962750 [hr] (1210.0 service years)
reservation pax liability/flying hour : 0.03 [SDR*] (0.04 [eur])
insurance cost per hour : 46 [eur]
engine maintenance cost per hour : 563.6 [eur]
maintenance cost per hour (excluding engines): 2302 [eur]
direct operating cost per hour: 10701 [eur]
DOC per seat 1000km flight (254 [pax] 2-class seating): 47.68 [eur/1000PK]
DOC per seat 1000km flight (high density seating): 43.34 [eur/1000PK]
DOC per kg cargo for a 1000km flight : 0.39 [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 : 2.88 [eur/pax]
airport landing fee / passenger : 2.88 [eur/pax]
retour ticket price 1000km trip : 164.72 [eur/pax]
price retour ticket Schiphol-Barcelona : 190.94 [eur/pax]
accidents with fatalities > no fatal accidents have been recorded with 757-300’s
Literature :
Wikipedia
Boeing 757-300 (753) (united.com)
Air International maart’99 page 136
Air International sep’98 page 137
Air International mrt’00 page 137 https://www.boeing.com/search/results.html?q=airplane+characteristics
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 10 June 2023 contact : info.aircraftinvestigation@gmail.com ac jetpax 2020.py python 3.7.4