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weight and performance calculations for the Boeing 707-320B
Boeing 707-321B N418PA c/n 18960 “Clipper Yankee Ranger” van de Pan Am landing at RAF Mildenhall. Operating a military charter flight.
Boeing 707-320B
role : jet airliner
importance : ****
first flight : 31 January 1962 operational : July 1962 (Pan-Am)
country : United States of America
design :
production : -320B : 174 aircraft, total 707 : 950 aircraft (average 150 / year)
general information :
Same as -320, only turbojets replaced by more efficient and powerful JT3D turbofans. The wingtips were also changed, making the wingspan 1.01m larger. Slats were applied over the entire wing leading edge. In January 1985, Lufthansa took the last 707s out of service. Lufthansa had been flying 707s since March 1960. The last 707s were the 707-330B
D-ABUL c/n 19315 Dec 1966 in service, 70,000 flight hours in 19,000 flights and the 707-330C D-ABUA c/n 18937 a cargo version that had made no less than 75,000 flight hours. The 707 consumed 0.48 litres of fuel/tonkm, the 747 reaches 0.35 l/tonkm and the A310 0.31 l/tonkm. The 707 became too uneconomical and made too much noise.
The 707-320B could carry a spare engine under the wing in streamlined "pod pacs".
There was also an HGW version with MTOW of 151500 kg (corresponding to the -320C) source: www.boeing.com
primary users : Pan-Am (16), Lufthansa (11), Air France (6), TWA (12), Independent Air,
Avianca, Northwest Orient (5)
Accommodation:
flight crew : 4 cabin crew : 7
flight crew consist of pilot, co-pilot, navigator and flight engineer
passengers : seating for 148 in two class : 16 business class and 132 coach class seats ( 34 -in pitch)
exit limit : 189 passengers, high density seating for 180 passengers
engine : 4 Pratt & Whitney JT3D-3 turbofan engines of 80.07 [KN] (18000.1 [lbf])
chord at root : 10.33 [m] at tip : 2.84 [m]
dimensions :
wingspan : 44.41 [m], length : 46.61 [m], height : 12.93 [m]
wing area : 279.64 [m^2] fuselage exterior width : 3.76 [m]
weights :
empty weight : 62372 [kg]
operating empty weight : 63500 [kg] max. structural payload : 22680 [kg]
Zero Fuel weight (ZFW) : 86180 [kg] max. landing weight (MLW) : 93895 [kg]
max.take-off weight : 148325 [kg] weight fuel : 72239 [kg] (90299 [litres])
performance :
Max. operating Mach number (Mmo) : 0.91 [Mach] (1010 [km/hr]) at 7620 [m]
max. cruising speed : 966 [km/hr] (Mach 0.90 ) at 10000 [m] (41 [%] power)
economic cruising speed : 886 [km/hr] (Mach 0.82 ) at 10000 [m]
service ceiling : 12800 [m]
range with max fuel and Max.TOW : 9723 [km] (ATA domestic fuel reserves - 370.0 [km] alternate)
description :
cantilever low-wing monoplane with retractable landing gear with nose wheel
Wings : all-metal two spar fail-safe wing structure
with two Fowler flaps and one split fillet flap on each wing with full-span leading edge flaps ,with spoilers airfoil : NACA
sweep angle 3/4 chord: 35.0 [°]
engines attached with pylons to the wing, main 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)
wing chord at root : 10.33 [m]
wing chord at tip : 2.84 [m]
taper ratio : 0.275 [ ]
mean wing chord : 6.30 [m]
calculated average wing chord tapered wing with rounded tips: 6.26 [m]
wing aspect ratio : 7.05 []
Oswald factor (e): 0.673 []
seize (span*length*height) : 26764 [m^3]
calculation : *2* (fuel consumption)
oil consumption : 11.5 [kg/hr]
fuel consumption (econ. cruise speed) : 6341.4 [kg/hr] (7926.8 [litre/hr]) at 28 [%] power
distance flown for 1 kg fuel : 0.14 [km/kg] at 10000 [m] height, sfc : 70.0 [kg/KN/h]
total fuel capacity : 90299 [litre] (72239 [kg])
calculation : *3* (weight)
weight engine(s) dry : 7440.0 [kg] = 23.23 [kg/KN]
weight 182 litre oil tank : 15.50 [kg]
oil tank filled with 2.0 litre oil : 1.8 [kg]
oil in engine 3.9 litre oil : 3.5 [kg]
fuel in engine 17.5 litre fuel : 12.81 [kg]
weight fuel lines 145.7 [kg]
weight engine cowling 832.7 [kg]
weight double thrust reversers 544.5 [kg]
total weight propulsion system : 8997 [kg](6.1 [%])
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Accommodation cabin facilities:
typical 2-class cabin layout for 148 passengers : economy : pitch : 86.4 [cm] 34.0 [-in] ( 3+3 ) seating in 25.2 rows
weight seats : 795.0 [kg]
high density seating passengers : 180 [pax] at 6 -abreast seating in 29.9 rows, pitch 86.4 [cm] 34.0 [-in]
pax density, normal seating : 0.72 [m2/pax], high density seating : 0.59 [m2/pax]
weight 5 lavatories : 71.2 [kg]
weight auxiliary service bar : 35 [kg]
weight 4 galleys : 255.4 [kg]
Boeing 717-321B 9Q-ZBL Scibe Airlift Zaire – SBZ interior, former Pan-Am N421PA “Clipper Charmer” c/n 19266
weight overhead stowage for hand luggage : 51.8 [kg]
weight 3 wardrobe closets : 29.6 [kg]
weight 11 movie screens : 84.6 [kg]
weight 52 windows : 47.2 [kg]
weight 2 (1.83 x 0.88 [m]) main entry doors : 119.7 [kg]
weight 2 (1.22 x 0.61 [m]) service doors : 55.6 [kg]
weight 2 (127x122 cm) freight doors (belly) : 103.0 [kg]
total belly baggage/cargo hold volume : 50.28 [m3]
cabin volume (usable), excluding flight deck : 225 [m3]
passenger compartment volume : 149 [m3]
passenger cabin max.width : 3.55 [m] cabin length : 33.99 [m] cabin height : 2.19 [m]
floor area : 106.2 [m2]
weight cabin facilities : 1648.1 [kg]
safety facilities:
weight 4 type III over wing emergency exits (51x91 cm): 73.3 [kg]
evacuation time with 180 passengers : 54 [sec]
weight 7 hand fire extinguisher : 22 [kg]
weight oxygen masks & oxygen generators : 96.2 [kg]
weight emergency flare installation : 10 [kg]
weight 4 emergency evacuation slides : 126.5 [kg]
weight safety equipment & facilities : 328 [kg]
fuselage construction:
fuselage aluminium frame : 12964 [kg]
floor loading (payload/m2): 214 [kg/m2]
weight rear pressure bulkhead : 202.8 [kg]
fuselage covering ( 399.0 [m2] duraluminium 3.45 [mm]) : 3632.0 [kg]
weight floor beams : 631.5 [kg]
weight cabin furbishing : 936.8 [kg]
weight cabin floor : 1563.6 [kg]
weight (sound proof) isolation : 289.9 [kg]
weight 40082 [litre] main central fuel tanks empty : 2244.6 [kg]
weight empty 219 [litre] potable water tank : 19.4 [kg]
weight empty waste tank : 17.0 [kg]
weight fuselage structure : 22501.3 [kg]
Avionics:
weight radio transceiver equipment : 7.0 [kg]
weight dual cloud-collision radar : 25.0 [kg]
weight Doppler & radio direction finding (RDF) equipment : 5.0 [kg]
weight Integrated Flight System / auto-pilot : 23.0 [kg]
weight artificial horizons, compass, alti-meters : 7 [kg]
weight engine monitoring gauges & control switches : 12 [kg]
weight avionics : 85.0 [kg]
Systems:
Air-conditioning and pressurization system maintains sea level conditions up to 6775 [m]
and gives equivalent of 2000 [m] at 11600 [m]. pressure differential : 0.60 [bars] (kg/cm2)
pressurized fuselage volume : 408 [m3]
weight air-conditioning and pressurization system : 214 [kg]
weight lighting : 48.8 [kg]
weight 210 bar hydraulic system : 89.2 [kg]
weight engine-driven 40kVA electricity generators : 37.0 [kg]
weight 22Ah battery : 12.0 [kg]
weight controls : 20.1 [kg]
weight systems : 421.0 [kg]
total weight fuselage : 24984 [kg](16.8 [%])
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average Take-off weight : 113258 [kg](76.4 [%])
total weight aluminium ribs (1061 ribs) : 4664 [kg]
weight engine mounts : 160 [kg]
weight 6 wing fuel tanks empty for total 50217 [litre] fuel : 2812 [kg]
weight wing covering (painted aluminium 3.16 [mm]) : 4770 [kg]
total weight aluminium spars (multi-cellular wing structure) : 4938 [kg]
weight wings : 14372 [kg]
weight wing/square meter : 51.40 [kg]
weight thermal leading-edge anti-icing : 48.9 [kg]
weight ailerons (11.24 [m2]) : 289.6 [kg]
weight fin (30.46 [m2]) : 785.2 [kg]
weight rudder (9.69 [m2]) : 239.6 [kg]
weight tailplane (stabilizer) (58.08 [m2]): 1646.5 [kg]
weight elevators (13.94 [m2]): 193.99 [kg]
weight flight control hydraulic servo actuators: 44.6 [kg]
weight Fowler flaps (44.19 [m2]) : 742.0 [kg]
N421PA 707-321B c/n 19266 may 1974 Glasgow – Prestwick. Note the leading edge flaps on the outer wing.
weight leading edge flaps (14.27 [m2]) : 205.0 [kg]
weight spoilers (12.8 [m2]) : 165.6 [kg]
total weight wing construction : 21706 [kg] (34.2 [%])
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707-320B main tyre pressure 12.68 kg/cm2, according Jane’s all the world aircraft 1970-71 tyre pressure : 11.95 kg/cm2
tire pressure main wheels : 11.95 [Bar] (nitrogen), ply rating : 23 PR
tire speed limit : 364 [km/hr]
total tyre footprint : 0.59 [m2]
Aircraft Classification Number, MTOW on rigid runway and medium subgrade strength (B) : 39 [ ]
Can also operate from unpaved runways subgrade B
wheel pressure : 16315.8 [kg]
weight 8 Dunlop main wheels (1170 [mm] by 407 [mm]) : 1274.3 [kg]
weight 2 nose wheels : 159.3 [kg]
weight multi-disc wheel-brakes : 86.2 [kg]
weight Hydro-air flywheel detector type anti-skid units : 9.0 [kg]
weight oleo-pneumatic shock absorbers : 114.9 [kg]
weight wheel hydraulic operated retraction system : 1223.8 [kg]
weight undercarriage struts (four-wheel bogies) with axle 3190.2 [kg]
total weight landing gear : 6057.6 [kg] (4.1 [%]
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calculated empty weight : 61743 [kg](41.6 [%])
weight oil for 12.1 hours flying : 157.6 [kg]
weight lifejackets : 66.6 [kg]
weight 3 life rafts : 92.5 [kg]
weight catering : 242.0 [kg]
weight water : 193.6 [kg]
weight crew : 891 [kg]
weight crew lugage,nav.chards,flight doc.,miscell.items : 113 [kg]
operational weight empty : 63500 [kg] (42.8 [%])
********************************************************************
weight 148 passengers : 11396 [kg]
weight luggage : 2368 [kg]
weight cargo : 8916 [kg] (cargo+luggage/m3 belly : 213 [kg/m3])
zero fuel weight (ZFW): 86180 [kg](58.1 [%])
weight fuel for landing (1.2 hours flying) : 7715 [kg]
max. landing weight (MLW): 93895 [kg](63.3 [%])
max. fuel weight : 135739 [kg] (91.5 [%])
payload with max fuel : 135 passengers+luggage 12586 [kg]
published maximum take-off weight : 148325 [kg] (100.0 [%])
Boeing 707-384B (or -C) “City of Athens” SX-DBA
calculation : * 4 * (engine power)
power loading (Take-off) : 463 [kg/KN]
power loading (Take-off) 1 PUF: 617 [kg/KN]
max. total take-off power : 320.3 [KN]
calculation : *5* (loads)
manoeuvre load : 9.5 [g] at 1000 [m]
limit load : 2.5 [g] ultimate load : 3.8 [g] load factor : 1.1 [g]
design flight time : 3.27 [hours]
design cycles : 13750 sorties, design hours : 44962 [hours]
max. wing loading (MTOW & flaps retracted) : 530 [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 : -1.81 ["]
max. angle of attack (stalling angle, clean) : 13.70 ["]
max. angle of attack (full flaps) : 15.02 ["]
angle of attack at max. speed : 0.56 ["]
calculation : *7* (lift & drag ratios
lift coefficient at angle of attack 0° : 0.15 [ ]
lift coefficient at max. speed : 0.20 [ ]
lift coefficient at max. angle of attack : 1.29 [ ]
max. lift coefficient full flaps : 1.80 [ ]
drag coefficient at max. speed : 0.0219 [ ]
drag coefficient at econ. cruise speed : 0.0259 [ ]
induced drag coefficient at econ. cruise speed : 0.0067 [ ]
drag coefficient (zero lift) : 0.0193 [ ]
lift/drag ratio at max. speed : 8.99 [ ]
calculation : *8* (speeds
take-off safety speed (V2) : 264 [km/u]
take-off (initial climb) speed (Vto) : 315 [km/u]
stalling speed clean at sea-level (OW loaded : 141984 [kg]): 286 [km/u]
max. rate of climb speed : 583 [km/hr] at sea-level
max. endurance speed (Vbe): 766 [km/u] min. fuel/hr : 5539 [kg/hr] at height : 11887 [m]
max. range speed (Vbr): 1008 [km/u] min. fuel consumption : 6.345 [kg/km] at cruise height : 11887 [m]
cruising speed : 966 [km/hr] at 10000 [m] (power:31 [%])
max. operational speed (Mmo) : 1010 [km/hr] (Mach 0.91 ) at 7620 [m] (power:40.5 [%])
airflow at cruise speed per engine : 158.5 [kg/s]
speed of thrust jet : 1532 [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 : 93895 [kg]): 238 [km/u]
final approach speed at sea-level with full flaps (normal landing weight) (Vapp): 232 [km/u]
ICAO Aircraft Approach Category (APC) : C
landing speed at sea-level (normal landing weight(Vtd): 93677 [kg]): 206 [km/hr]
stalling speed at sea-level with full flaps (max. landing weight): 179 [km/u]
rate of climb at sea-level ROC (loaded, 74 % power) : 1072 [m/min]
rate of climb at 1000 [m] with 1 engine out (PUF/MTOW, 100 % power on remaining engines) : 814 [m/min]
rate of climb at 1000 [m] with 2 engines out (2xPUF / MTOW) : 258 [m/min]
max.rate of descent with landing gear extended, with use of spoilers: 457 [m/min]
calculation : *9* (regarding various performances)
low wheel pressure, can also take off from unpaved runways
take-off distance at sea-level concrete runway : 3059 [m]
ICAO Aerodrome Reference Code : 4D
Take-off runway length at MTOW 148325 kg, standard day, sea level : 10800 ft > 3290m. CAR T-O to 10.7m : 3155m
take-off distance (C.A.R) at sea-level over 10.7 [m] height : 3156 [m]
FAR TO runway length requirement at MTOW, standard day at SL (ASDA): 3291 [m]
Landing runway length on dry runway at MLW 94000 [kg] > 5900 ft > 1800 [m]
Approach speed : 126 kts = 233 [km/h], Jane’s all the world aircraft 1970-71 : stalling speed (flaps down, MLW) : 179 km/h x 1.3 = 233 km/h = final approach speed. Landing run : 750 [m], CAR landing from 15[m] : 1807 [m]
landing distance (MLW) : 748 [m]
landing distance (C.A.R.) from 15 [m] at SL, dry runway : 1806 [m]
landing distance (C.A.R.) from 15 [m] at SL, wet runway : 2106 [m]
landing runway length requirements at SL : 1803 [m]
lift/drag ratio : 13.90 [ ]
climb to 5000 [m] with max payload : 4.32 [min]
climb to 10000 [m] with max payload : 13.29 [min]
descent time from 10000 [m] to 250 [m] : 24.33 [min]
ceiling limited by max. pressure differential 15200 [m]
theoretical ceiling fully loaded (mtow- 60 min.fuel: 141984 [kg] ) : 16900 [m]
calculation *10* (action radius & endurance)
range with max. payload: 8482 [km] with 22680.0 [kg] max. useful load (86.0 [%] fuel)*
range with high density pax: 9429 [km] with 180 passengers (94.3 [%] fuel)*
Range with max fuel 90290 litre and 26000 lb payload, 151500 kg TOW : 5250 NM > 9723 km
range with typical two-class pax: 9902 [km] with 148 passengers (98.4 [%] fuel)*
range with max.fuel : 10093 [km] with 11 crew and 135 passengers and 100.0 [%] fuel*
ferry range : 10719 [km] with 4 crew and zero payload (100.0 [%] fuel)*
max range theoretically with additional fuel tanks total 107284 [litre] fuel : 12364 [km]*
* calculated ranges without fuel reserves
Available Seat Kilometres (ASK) : 1704431 [paskm]
useful load with range 1000km : 22680 [kg]
useful load with range 1000km : 180 passengers
production (theor.max load): 21909 [tonkm/hour]
production (useful load): 21909 [tonkm/hour]
production (passengers): 173445 [paskm/hour]
oil and fuel consumption per tonkm : 0.290 [kg]
calculation *11* (operating cost)
fuel cost per hour (7927 [litre]):4756 [eur] (22 [pax-km/litre fuel])
fuel cost per seat 1000km flight (180 [pax] 2-class seating): 27.42 [eur/1000PK]
oil cost per hour: 48 [eur]
crew cost per hour : 1500 [eur]
list price 2023 : 164 [mln USD]
average flying hours in 1 year : 3450 [hours] technical life : 13 [year]
real average service life : 15 [years]
Boeing 707-330B D-ABUL c/n 19315, Lufthansa's workhorse with 70,000 flight hours.
economic hours (average real flown hours) : 51750 [hours]
financing interest per flying hour : 1107 [EUR]
write off per flying hour : 2724 [EUR]
time between engine failure : 10275 [hr]
can continue fly on 3 engines, low risk for emergency landing for PUF
workhours per day : 11.62 [hr]
average flight hours till crash : 0.90 [mln hr] (261 service years)
safe flight hours till fatality : 12301 [hr] (3.6 service years)
reservation pax liability/flying hour : 10.47 [SDR*] (13.09 [eur])
insurance cost per hour : 201 [eur]
engine maintenance cost per hour : 225.4 [eur]
wing maintenance cost per hour : 188.1 [eur]
fuselage maintenance cost per hour : 74.64 [eur]
maintenance cost per hour (excluding engines): 1544 [eur]
direct operating cost per hour: 12117 [eur]
DOC per seat 1000km flight (180 [pax] 2-class seating): 69.86 [eur/1000PK]
DOC per seat 1000km flight (high density seating): 69.86 [eur/1000PK]
DOC per kg cargo for a 1000km flight : 0.55 [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 : 4.93 [eur/pax]
airport landing fee / passenger : 4.93 [eur/pax]
retour ticket price 1000km trip : 222.52 [eur/pax]
price retour ticket Schiphol-Barcelona : 260.95 [eur/pax]
accidents with fatalities > see the accident file
Notes :
Literature :
https://www.boeing.com/search/results.html?q=airplane+characteristics
verkeersvliegtuigen (Moussault) page153
wat is dat voor een vliegtuig page 47
praktisch handboek vliegtuigen deel 5 page 58 - 62
verkeersvliegtuigen page 22
Jane’s commercial transport aircraft page 53
Jane’s all the world aircraft ’64-’65 page187,188
Jane’s all the world aircraft ’1970-’71 page 285,286
www.boeing.com detailed technical characteristics
Verkehrsflugzeuge page 30
Observers airliners page 37
confidence rating regarding source data : medium – high
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 August 2023 contact : info.aircraftinvestigation@gmail.com ac jetpax 2020.py python 3.7.4
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