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weight and performance calculations for the Boeing 707-120B
Transavia 707-123B PH-TVA c/n 17646, early airliners made a lot of noise and ground crew needed ear protection.
Boeing 707-120B
role : jet airliner
importance : ****
first flight : 22 June 1960 operational : March 1961 (Panam)
country : United States of America
design :
production : 707-120B : 72 aircraft
general information :
The -120B is a version with the JT3D-1 turbofan engines of 7711 kg of thrust. The turbofan was more economical than the turbojet but also resulted in a 60km/h higher cruising speed, better climbing performance and an approx. 400m shorter take-off run. The development of the JT3D was very simple, they just stuck a fan of larger centerline against the single-flow JT3C. The turbofan engine sucks in 2.5 times as much air as the previous turbojets. More effective jet reversers shortened the landing distance by 20%. Because the turbofans were about 20% more economical, the range was also considerably increased. In many -120s, the turbojets were later replaced by the JT3D turbofan, these were designated as 707-120(B)
The 707-138 was a version for Quantas with a shorter hull (41.00m).
The 707-220 was a version equipped with JT4A-3 engines of 7167 kg thrust.
The JT3D did not require water injection, eliminating both the system and 5000–6000 lb of water.
primary users : Panam, American Airlines(24), TWA(23)
Accommodation:
flight crew : 4 cabin crew : 6
flight crew consist of pilot, co-pilot, navigator and flight engineer
passengers : seating for 137 in two class : 32 business class and 105 coach class seats ( 34 -in pitch)
exit limit : 181 passengers, high density seating for 174 passengers
engine : 4 Pratt & Whitney JT3D-1 turbofan engines of 75.71 [KN] (17020.0 [lbf])
Chord at root : 8.58 [m] at tip 2.84 [m]
dimensions :
wingspan : 39.87 [m], length : 44.22 [m], height : 11.79 [m]
wing area : 234.2 [m^2] fuselage exterior width : 3.76 [m]
weights :
empty weight : 55861 [kg]
operating empty weight : 57600 [kg] max. structural payload : 19600 [kg]
Zero Fuel weight (ZFW) : 77200 [kg] max. landing weight (MLW) : 86300 [kg]
max.take-off weight : 116575 [kg] weight fuel : 52711 [kg] (65889 [liter])
performance :
Max. operating Mach number (Mmo) : 0.91 [Mach] (1010 [km/hr]) at 7620 [m]
normal cruise speed : 897 [km/hr] (Mach 0.85 ) at 11000 [m] (34 [%] power)
economic cruise speed : 880 [km/hr] (Mach 0.83 ) at 11000 [m]
service ceiling : 9880 [m]
range with max fuel and Max.TOW : 7685 [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
calculation : *1* (dimensions)
wing chord at root : 8.58 [m]
wing chord at tip : 2.84 [m]
taper ratio : 0.331 [ ]
mean wing chord : 5.87 [m]
calculated average wing chord tapered wing with rounded tips: 5.90 [m]
wing aspect ratio : 6.79 []
oswald factor (e): 0.667 []
seize (span*length*height) : 20786 [m^3]
calculation : *2* (fuel consumption)
oil consumption : 30.3 [kg/hr]
fuel consumption (econ. cruise speed) : 5758.6 [kg/hr] (7198.3 [litre/hr]) at 24 [%] power
distance flown for 1 kg fuel : 0.15 [km/kg] at 11000 [m] height, sfc : 79.2 [kg/KN/h]
total fuel capacity : 65889 [litre] (52711 [kg])
calculation : *3* (weight)
weight engine(s) dry : 7556.0 [kg] = 24.95 [kg/KN]
weight 3210 litre water tank for engine injection : 272.86 [kg]
weight 91 litre oil tank : 7.78 [kg]
oil tank filled with 1.9 litre oil : 1.7 [kg]
oil in engine 3.7 litre oil : 3.3 [kg]
fuel in engine 16.5 litre fuel : 12.11 [kg]
weight fuel lines 120.9 [kg]
weight engine cowling 787.4 [kg]
total weight propulsion system : 8786 [kg](7.5 [%])
***************************************************************
Accommodation cabin facilities:
typical 2-class cabin layout for 137 passengers : economy : pitch : 86.4 [cm] 34.0 [-in] ( 3+3 )
seating in 23.9 rows
weight seats : 735.0 [kg]
high density seating passengers : 174 [pax] at 6 -abreast seating in 29.0 rows, pitch 86.4 [cm]
34.0 [-in]
pax density, normal seating : 0.74 [m2/pax], high density seating : 0.58 [m2/pax]
weight 4 lavatories : 61.7 [kg]
weight 4 galleys : 168.5 [kg]
American Airlines 707-123B with closed overhead luggage storage.
weight overhead stowage for hand luggage : 47.9 [kg]
weight 3 wardrobe closets : 27.4 [kg]
Speed 595 mph = 957 km/h, range 3970 statute miles = 6388 km, length 145 ft 1 in = 44.22 [m], wingspan 130’10” = 39.88 [m]
weight 10 movie screens : 78.3 [kg]
weight 50 windows : 44.8 [kg]
weight 2 (1.83 x 0.88 [m]) main entry doors : 105.0 [kg]
weight 2 (1.22 x 0.61 [m]) service doors : 48.8 [kg]
weight 2 (127x122 cm) freight doors (belly) : 90.4 [kg]
total belly baggage/cargo hold volume : 47.15 [m3]
cabin volume (usable), excluding flight deck : 212 [m3]
passenger compartment volume : 140 [m3]
passenger cabin max.width : 3.55 [m] cabin length : 31.94 [m] cabin height : 2.19 [m]
floor area : 101.5 [m2]
weight cabin facilities : 1407.8 [kg]
safety facilities:
weight 4 type III over wing emergency exits (51x91 cm): 64.2 [kg]
evacuation time with 174 passengers : 52 [sec]
weight 7 hand fire extinguisher : 21 [kg]
weight oxygen masks & oxygen generators : 89.0 [kg]
weight emergency flare installation : 10 [kg]
weight 4 emergency evacuation slides : 117.1 [kg]
weight safety equipment & facilities : 301 [kg]
fuselage construction:
fuselage aluminium frame : 10782 [kg]
floor loading (payload/m2): 193 [kg/m2]
weight rear pressure bulkhead : 178.4 [kg]
fuselage covering ( 378.5 [m2] duraluminium 3.03 [mm]) : 3030.5 [kg]
weight floor beams : 600.7 [kg]
weight cabin furbishing : 894.4 [kg]
weight cabin floor : 1494.8 [kg]
weight (sound proof) isolation : 274.9 [kg]
weight 27652 [litre] main central fuel tanks empty : 1548.5 [kg]
weight empty 127 [litre] potable water tank : 11.2 [kg]
weight empty waste tank : 13.1 [kg]
weight fuselage structure : 18829.0 [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 : 381 [m3]
weight air-conditioning and pressurization system : 199 [kg]
weight lighting : 45.2 [kg]
weight three independent 207 bar hydraulic systems : 69.3 [kg]
weight engine-driven 40kVA electricity generators : 34.2 [kg]
weight 22Ah battery : 12.0 [kg]
weight controls : 18.9 [kg]
weight systems : 378.6 [kg]
total weight fuselage : 21002 [kg](18.0 [%])
***************************************************************
average Take-off weight : 94764 [kg](81.3 [%])
total weight aluminium ribs (919 ribs) : 3768 [kg]
weight engine mounts : 151 [kg]
One 7306 gallon (27653 litre) centre tank+6 wing tanks (2x2283)+(2x2333)+(2x434) = 17406 US gallon = 65889 litres. Reserve tanks contain 2x434 US gallon = 3285 litres, enough for 17 mins. flight. Looking at the engines, this is a 707-120, but the -120B had the same fuel tank arrangement. The wing can contain 65889 – 27653 = 38236 litre of kerosine. Useable fuel is 65560 litres, so 300 litre is unusable.
weight 6 wing fuel tanks empty for total 38237 [litre] fuel : 2141 [kg]
weight wing covering (painted aluminium 3.26 [mm]) : 4125 [kg]
total weight aluminium spars (multi-cellular wing structure) : 3772 [kg]
weight wings : 11664 [kg]
weight wing/square meter : 49.81 [kg]
weight thermal leading-edge anti-icing : 43.9 [kg]
weight ailerons (11.16 [m2]) : 278.8 [kg]
weight fin (30.46 [m2]) : 760.8 [kg]
weight rudder (9.48 [m2]) : 227.3 [kg]
weight tailplane (stabilizer) (50.62 [m2]): 1390.9 [kg]
weight elevators (10.95 [m2]): 147.69 [kg]
weight flight control hydraulic servo actuators: 34.6 [kg]
weight Fowler flaps (33.63 [m2]) : 548.2 [kg]
weight leading edge flaps (3.53 [m2]) : 51.6 [kg]
weight spoilers (10.8 [m2]) : 135.8 [kg]
total weight wing construction : 17577 [kg] (30.5 [%])
*******************************************************************
Turkish Airlines Boeing 707-120B TC-JBN
tire pressure main wheels : 9.50 [Bar] (nitrogen), ply rating : 20 PR
tire speed limit : 364 [km/hr]
total tyre footprint : 0.58 [m2]
Aircraft Classification Number, MTOW on rigid runway and medium subgrade strength (B) : 24 [ ]
good soft ground capabilities
wheel pressure : 12823.2 [kg]
weight 8 Dunlop main wheels (1170 [mm] by 407 [mm]) : 749.6 [kg]
weight 2 nose wheels : 93.7 [kg]
weight multi-disc wheel-brakes : 77.2 [kg]
weight Hydro-air flywheel detector type anti-skid units : 9.0 [kg]
weight oleo-pneumatic shock absorbers : 102.9 [kg]
weight wheel hydraulic operated retraction system : 1093.9 [kg]
weight undercarriage struts (four-wheel bogies) with axle 3288.5 [kg]
total weight landing gear : 5414.9 [kg] (4.6 [%]
*******************************************************************
********************************************************************
calculated empty weight : 52780 [kg](45.3 [%])
weight oil for 10.3 hours flying : 332.6 [kg]
weight engine injection water : 3210.1 [kg]
weight lifejackets : 61.6 [kg]
weight 2 life rafts : 85.6 [kg]
weight catering : 140.4 [kg]
weight water : 112.3 [kg]
weight crew : 810 [kg]
weight crew lugage,nav.chards,flight doc.,miscell.items : 68 [kg]
operational weight empty : 57600 [kg] (49.4 [%])
********************************************************************
weight 137 passengers : 10549 [kg]
weight luggage : 2192 [kg]
weight cargo : 6859 [kg] (cargo+luggage/m3 belly : 180 [kg/m3])
zero fuel weight (ZFW): 77200 [kg](66.2 [%])
weight fuel for landing (1.6 hours flying) : 9100 [kg]
max. landing weight (MLW): 86300 [kg](74.0 [%])
max. fuel weight : 110311 [kg] (94.6 [%])
payload with max fuel : 67 passengers+luggage 6264 [kg]
published maximum take-off weight : 116575 [kg] (100.0 [%])
Commercial featuring TWA Boeing 707-131B N754TW
calculation : * 4 * (engine power)
power loading (Take-off) : 385 [kg/KN]
power loading (Take-off) 1 PUF: 513 [kg/KN]
max. total take-off power : 302.8 [KN]
calculation : *5* (loads)
manoeuvre load : 9.4 [g] at 1000 [m]
limit load : 2.5 [g] ultimate load : 3.8 [g] load factor : 1.2 [g]
design flight time : 2.05 [hours]
design cycles : 16475 sorties, design hours : 33774 [hours]
max. wing loading (MTOW & flaps retracted) : 498 [kg/m2]
wing stress (2 g) during operation : 170 [N/kg] at 2g emergency manoeuvre
calculation : *6* (angles of attack)
angle of attack zero lift : -1.83 ["]
max. angle of attack (stalling angle, clean) : 13.81 ["]
max. angle of attack (full flaps) : 15.11 ["]
angle of attack at max. speed : 0.57 ["]
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 : 1.28 [ ]
max. lift coefficient full flaps : 1.67 [ ]
drag coefficient at max. speed : 0.0228 [ ]
drag coefficient at econ. cruise speed : 0.0286 [ ]
induced drag coefficient at econ. cruise speed : 0.0085 [ ]
drag coefficient (zero lift) : 0.0201 [ ]
lift/drag ratio at max. speed : 8.63 [ ]
calculation : *8* (speeds
take-off safety speed (V2) : 259 [km/u]
take-off (initial climb) speed (Vto) : 309 [km/u]
stalling speed clean at sea-level (OW loaded : 110816 [kg]): 277 [km/u]
max. rate of climb speed : 570 [km/hr] at sea-level
max. endurance speed (Vbe): 436 [km/u] min. fuel/hr : 5264 [kg/hr] at height : 2438 [m]
max. range speed (Vbr): 832 [km/u] min. fuel consumption : 7.303 [kg/km] at cruise height : 9144 [m]
cruising speed : 897 [km/hr] at 11000 [m] (power:24 [%])
max. operational speed (Mmo) : 1010 [km/hr] (Mach 0.91 ) at 7620 [m] (power:37.1 [%])
airflow at cruise speed per engine : 129.8 [kg/s]
speed of thrust jet : 1409 [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 : 86300 [kg]): 250 [km/u]
final approach speed at sea-level with full flaps (normal landing weight) (Vapp): 259 [km/u]
ICAO Aircraft Approach Category (APC) : C
landing speed at sea-level (normal landing weight(Vtd): 86174 [kg]): 229 [km/hr]
stalling speed at sea-level with full flaps (max. landing weight): 199 [km/u]
rate of climb at sea-level ROC (loaded, 65 % power) : 1006 [m/min]
rate of climb at 1000 [m] with 1 engine out (PUF/MTOW, 100 % power on remaining engines) : 1092 [m/min]
rate of climb at 1000 [m] with 2 engines out (2xPUF / MTOW) : 412 [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 runway length requirements JT3D-1 take-off thrust 7718 kg (75.71 KN), MTOW 116575 kg (257000 lb) standard day, sea-level : 8075 ft = 2461 [m]. According Jane’s all the world aircraft 1970-71 is C.A.R. take-off to 10.7 [m] : 2270 [m]
take-off distance at sea-level concrete runway : 2162 [m]
take-off distance at sea-level gravel/packed earth field : 3020 [m]
ICAO Aerodrome Reference Code : 4D
take-off distance (C.A.R) at sea-level over 10.7 [m] height : 2263 [m]
FAR TO runway length requirment at MTOW, standard day at SL (ASDA): 2452 [m]
Final approach speed at MLW 86300 kg (190255 lb) : 140 kts (259 km/h), runway length,
dry, sea-level : 6500 ft : 1981 [m]. Jane’s all the world aircraft 1970-71 : Landing run 925 [m],
CAR landing from 15m : 1995 [m]
landing distance (MLW) : 925 [m]
landing distance (C.A.R.) from 15 [m] at SL, dry runway : 1995 [m]
landing distance (C.A.R.) from 15 [m] at SL, wet runway : 2295 [m]
landing runway length requirements at SL : 1980 [m]
lift/drag ratio : 13.31 [ ]
climb to 5000 [m] with max payload : 4.60 [min]
climb to 10000 [m] with max payload : 14.15 [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: 110816 [kg] ) : 17300 [m]
calculation *10* (action radius & endurance)
Range with max fuel : 4350 nm = 8055 km – 370 km reserve = 7685 [km]
range with max. payload: 5755 [km] with 19600.0 [kg] max. useful load (74.7 [%] fuel)*
range with high density pax: 6331 [km] with 174 passengers (81.2 [%] fuel)*
range with typical two-class pax: 6915 [km] with 137 passengers (87.7 [%] fuel)*
range with max.fuel : 8055 [km] with 10 crew and 67 passengers and 100.0 [%] fuel*
ferry range : 8429 [km] with 4 crew and zero payload (100.0 [%] fuel)*
max range theoretically with additional fuel tanks total 74642 [litre] fuel : 9336 [km]*
* calculated ranges without fuel reserves
Available Seat Kilometres (ASK) : 1105741 [paskm]
useful load with range 1000km : 19600 [kg]
useful load with range 1000km : 174 passengers
production (theor.max load): 17581 [tonkm/hour]
production (useful load): 17581 [tonkm/hour]
production (passengers): 154307 [paskm/hour]
oil and fuel consumption per tonkm : 0.329 [kg]
calculation *11* (operating cost)
fuel cost per hour (7198 [litre]):4319 [eur] (21 [pax-km/litre fuel])
fuel cost per seat 1000km flight (172 [pax] 2-class seating): 27.99 [eur/1000PK]
oil cost per hour: 126 [eur]
crew cost per hour : 1350.000 [eur]
list price 2023 : 140 [mln USD]
average flying hours in 1 year : 2866 [hours] technical life : 12 [year]
real average service life : 13 [years]
economic hours (average real flown hours) : 37258 [hours]
financing interest per flying hour : 1139 [EUR]
write off per flying hour : 3234 [EUR]
time between engine failure : 13096 [hr]
can continue fly on 3 engines, low risk for emergency landing for PUF
workhours per day : 10.72 [hr]
PanAm flight attendants, early 707 interior with open overhead luggage racks
average flight hours till crash : 0.67 [mln hr] (234 service years)
safe flight hours till fatality : 17419 [hr] (6.1 service years)
reservation pax liability/flying hour : 7.40 [SDR*] (9.24 [eur])
insurance cost per hour : 230 [eur]
engine maintenance cost per hour : 150.5 [eur]
wing maintenance cost per hour : 251.3 [eur]
fuselage maintenance cost per hour : 180.12 [eur]
maintenance cost per hour (excluding engines): 1810 [eur]
direct operating cost per hour: 12367 [eur]
DOC per seat 1000km flight (172 [pax] 2-class seating): 80.14 [eur/1000PK]
DOC per seat 1000km flight (high density seating): 79.34 [eur/1000PK]
DOC per kg cargo for a 1000km flight : 0.70 [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 : 4.05 [eur/pax]
retour ticket price 1000km trip : 241.24 [eur/pax]
price retour ticket Schiphol-Barcelona : 285.32 [eur/pax]
accidents with fatalities > see the accident file
notes :
Literature :
https://www.boeing.com/search/results.html?q=airplane+characteristics
Photo of Boeing 707-121 N708PA - Aviation Safety Network (aviation- safety.net)
Verkeersvliegtuigen (Moussault) page 151
Praktisch handboek vliegtuigen deel 5 page 58-62
Straalverkeersvliegtuigen page 80-105
Verkeersvliegtuigen page 22,23
Jane’s commercial transport aircraft page 51
Op weg naar het noodlot page 96
Jane’s all the world aircraft 1964-1965
Jane’s all the world aircraft 1970-71 page 286
The 707 Family (michaelprophet.com)
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 August 2023 contact : info.aircraftinvestigation@gmail.com ac jetpax 2020.py python 3.7.4