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weight and performance calculations for the Douglas DC-8-55CF Jet Trader
Martinair PH-MAU at Dusseldorf airport, 1975
Douglas DC-8-55CF Jet Trader
role : jet airliner
importance : ****
first flight : 29 October 1962 operational : August 1963
country : United States of America
design :
production : -54CF/-54AF/-55CF : 54 aircraft total DC-8 : 556 aircraft
general information :
Douglas built three cargo versions, the -54AF (All Freighter) for United, the -54CF and -55CF (Convertible Freighter) all equipped with JT3D-3 turbofans of 8165kg of thrust. They have a reinforced floor, a cargo door of 3.56x2.16 [m] and a higher MTOW. Max. payload as a freighter : 40247kg on 13 pallets of 3.18x2.75 [m]. Through balls and rollers in the floor, the load could easily be pushed in and out.
In addition to the -55CF convertible, there was also the regular -55 passenger version that could not be converted into a freighter. During the construction of the -54 and -55 models, Dougals succeeded in moving the rear pressure bulkhead 2.1 [m] more to the rear. As a result, passenger capacity increased from 179 to 189 passengers. Douglas was going to offer the passenger versions in 2 versions, one with the pressure bulkhead still in its old place, internally designated as -55L, which was ordered by KLM, and one with the pressure bulkhead further back, designated as -55AB, which were ordered by the SAS (DC-8-55) and the VARIG (DC-8-53).
From September 1964, KLM flew 2 DC-8-55s. These aircraft were flown to New York 5 times a week. In mid-1965, KLM ordered a third -55CF due to the sharp increase in cargo traffic across the Atlantic. A few more followed later. In June 1981, the -55CF PH-DCZ made the last DC-8 cargo flight for KLM. The aircraft had made 54000 flight hours for KLM in 11 years, an average of 13.44 hours a day !
primary users : KLM, SAS, Martinair, Japan Air Lines, Surinam airways, Garuda, VARIG,
VIASA
registrations :
KLM DC-8-55’s :
PH-DCS DC-8-55CF c/n 45683 "Alfred B.Nobel" delivered July 1964
PH-DCT DC-8-55CF c/n 45691 "Pierre de Coubertin » August 1964 delivered
PH-DCU DC-8-55CF c/n 45859 « Sir Winston Churchill" delivered February 1966
PH-DCV DC-8-55 c/n 45766 "Bali" delivered August 1966, this is not a CF but a regular passenger version, factory designation -55L*
PH-DCW DC-8-55CF c/n 45762 "Gerard Mercato" purchased from Philipine airlines, December 1967
PH-DCY DC-8-55 c/n 45765 "Anthony Fokker" leased from Garuda March 1969, this is not a CF but a regular passenger version, factory designation -55L*
PH-DCZ DC-8-55CF c/n 45804 “Hans Christianson Andersen”
Martinair DC-8-55’s :
PH-MAS DC-8-55CF c/n 45824 “Sydney”
PH-MAU DC-8-55CF c/n 45856 « Toronto »
PH-MBH DC-8-55CF c/n 45818
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)
high density seating for 189 passengers
engine : 4 Pratt & Whitney JT3D-3B turbofan engines of 80.17 [KN] (18022.6 [lbf])
chord at root : 9.67 [m] at tip : 2.22 [m]
dimensions :
wingspan : 43.41 [m], length : 45.87 [m], height : 12.91 [m]
wing area : 267.84 [m^2] fuselage exterior width : 3.73 [m]
weights :
empty weight : 62717 [kg]
operating empty weight : 65375 [kg] max. structural payload : 36225 [kg]
Zero Fuel weight (ZFW) : 101600 [kg] max. landing weight (MLW) : 108860 [kg]
max.take-off weight : 147418 [kg] weight fuel : 70842 [kg] (88552 [litres])
performance :
Max. operating Mach number (Mmo) : 0.88 [Mach] (960 [km/hr]) at 9150 [m]
max. cruising speed : 933 [km/hr] (Mach 0.86 ) at 9144 [m] (41 [%] power)
economic cruising speed : 880 [km/hr] (Mach 0.81 ) at 9144 [m]
service ceiling : 12000 [m]
range with max fuel and Max.TOW : 9260 [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 trailing edge flaps with leading edge slots ,with spoilers airfoil : NACA sweep angle 3/4 chord: 30.0 [°]
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 : 9.67 [m]
wing chord at tip : 2.22 [m]
taper ratio : 0.230 [ ]
mean wing chord : 6.17 [m]
calculated average wing chord tapered wing with rounded tips: 6.14 [m]
wing aspect ratio : 7.04 []
Oswald factor (e): 0.687 []
seize (span*length*height) : 25707 [m^3]
calculation : *2* (fuel consumption)
oil consumption : 11.7 [kg/hr]
fuel consumption (econ. cruise speed) : 6473.6 [kg/hr] (8092.0 [litre/hr]) at 31 [%] power
distance flown for 1 kg fuel : 0.14 [km/kg] at 9144 [m] height, sfc : 65.0 [kg/KN/h]
total fuel capacity : 88552 [litre] (70842 [kg])
calculation : *3* (weight)
weight engine(s) dry : 8200.0 [kg] = 25.57 [kg/KN]
weight 177 litre oil tank : 15.09 [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 : 12.83 [kg]
weight fuel lines : 145.7 [kg]
weight engine cowling : 833.8 [kg]
weight double thrust reversers : 545.2 [kg]
total weight propulsion system : 9758 [kg](6.6 [%])
***************************************************************
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 : 189 [pax] at 6 -abreast seating in 31.5 rows, pitch 86.4 [cm] 34.0 [-in]
pax density, normal seating : 0.69 [m2/pax], high density seating : 0.54 [m2/pax]
weight 5 lavatories : 69.8 [kg]
weight lounge : 35 [kg]
weight 4 buffets : 258.0 [kg]
Japan Air Lines DC-8 interior
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 (47x38cm) : 47.2 [kg]
weight 2 (1.83 x 0.88 [m]) main entry doors : 123.9 [kg]
weight 2 (1.63 x 0.85 [m]) service doors : 107.0 [kg]
weight 2 (1.12 x 0.91 [m]) freight doors (belly) : 68.5 [kg]
total belly baggage/cargo hold volume : 43.02 [m3]
cabin volume (usable), excluding flight deck : 231 [m3]
passenger compartment volume : 156 [m3]
passenger cabin max.width : 3.51 [m] cabin length : 33.20 [m] cabin height : 2.21 [m]
floor area : 102.5 [m2]
weight cabin facilities : 1670.3 [kg]
safety facilities:
weight 4 type III over wing emergency exits (51x91 cm): 75.8 [kg]
evacuation time with 189 passengers : 48 [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 : 125.5 [kg]
weight safety equipment & facilities : 330 [kg]
fuselage construction:
fuselage aluminium frame : 13027 [kg]
floor loading (payload/m2): 353 [kg/m2]
weight rear pressure bulkhead : 205.3 [kg]
fuselage covering ( 387.6 [m2] duraluminium 3.57 [mm]) : 3643.1 [kg]
convertible pax/freighter strengtened floor
Drawing of the upper deck main cargo door, 3.56 x 2.16m
weight 2.16 x 3.56 [m] upper deck cargo door : 258.4 [kg]
weight floor beams : 806.0 [kg]
weight cabin furbishing : 903.7 [kg]
weight cabin floor : 1748.5 [kg]
weight (sound proof) isolation : 280.8 [kg]
weight 26362 [litre] main central fuel tanks empty : 1476.3 [kg]
weight empty 221 [litre] potable water tank : 19.5 [kg]
weight empty waste tank : 15.8 [kg]
weight fuselage structure : 22384.7 [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 Sperry automatic flight control system, with SP-30 auto-pilot : 25.0 [kg]
weight artificial horizons, compass, alti-meters : 7 [kg]
weight engine monitoring gauges & control switches : 12 [kg]
weight avionics : 87.0 [kg]
Systems:
Air-conditioning and pressurization system maintains sea level conditions up to 7100 [m]
and gives equivalent of 2000 [m] at 12200 [m]. pressure differential : 0.62 [bars] (kg/cm2)
pressurized fuselage volume : 394 [m3]
weight air-conditioning and pressurization system : 214 [kg]
weight APU / engine starter: 40.1 [kg]
weight lighting : 48.8 [kg]
weight 210 bar hydraulic system : 85.7 [kg]
weight engine-driven 40kVA electricity generators : 37.0 [kg]
weight 22Ah battery : 12.0 [kg]
weight controls : 19.8 [kg]
weight systems : 456.9 [kg]
total weight fuselage : 24929 [kg](16.9 [%])
***************************************************************
average Take-off weight : 129436 [kg](87.8 [%])
total weight aluminium ribs (1146 ribs) : 4936 [kg]
weight engine mounts : 160 [kg]
weight 6 wing fuel tanks empty for total 62190 [litre] fuel : 3483 [kg]
weight wing covering (painted aluminium 3.31 [mm]) : 4788 [kg]
Martinair DC-8-55CF PH-MAU “Toronto” in front of the ATC tower at Schiphol airport
total weight aluminium spars (multi-cellular wing structure) : 4427 [kg]
weight wings : 14152 [kg]
weight wing/square meter : 52.84 [kg]
weight thermal leading-edge anti-icing : 47.8 [kg]
weight ailerons (10.98 [m2]) : 291.0 [kg]
weight fin (29.11 [m2]) : 771.1 [kg]
weight rudder (9.25 [m2]) : 235.4 [kg]
weight tailplane (stabilizer) (57.15 [m2]): 1665.6 [kg]
weight elevators (13.72 [m2]): 196.24 [kg]
weight flight control hydraulic servo actuators: 42.8 [kg]
weight trailing-edge double slotted flaps (45.67 [m2]) : 1030.6 [kg]
weight leading-edge slots (1.91 [m2]) : 31.0 [kg]
weight spoilers (12.8 [m2]) : 169.2 [kg]
total weight wing construction : 22244 [kg] (34.0 [%])
*******************************************************************
DC-8-55 main gear tire pressure : 13.1 kg/cm2
tire pressure main wheels : 13.10 [Bar] (nitrogen), ply rating : 23 PR
tire speed limit : 364 [km/hr]
total tyre footprint : 0.53 [m2]
Aircraft Classification Number, MTOW on rigid runway and medium subgrade strength (B) : 44 [ ]
Can also operate from unpaved runways subgrade B
wheel pressure : 16216.0 [kg]
weight 8 Dunlop main wheels (1130 [mm] by 420 [mm]) : 1102.6 [kg]
weight 2 nose wheels : 137.8 [kg]
weight multi-disc wheel-brakes : 101.6 [kg]
weight Hydro-air flywheel detector type anti-skid units : 9.0 [kg]
weight oleo-pneumatic shock absorbers : 135.5 [kg]
weight wheel hydraulic operated retraction system : 1353.5 [kg]
weight undercarriage struts (four-wheel bogies) with axle 3860.0 [kg]
total weight landing gear : 6700.1 [kg] (4.5 [%]
*******************************************************************
********************************************************************
calculated empty weight : 63631 [kg](43.2 [%])
weight oil for 11.9 hours flying : 153.3 [kg]
weight lifejackets : 66.6 [kg]
weight 3 life rafts : 92.5 [kg]
weight catering : 244.2 [kg]
weight water : 195.4 [kg]
weight crew : 891 [kg]
weight crew lugage,nav.chards,flight doc.,miscell.items : 101 [kg]
operational weight empty : 65375 [kg] (44.3 [%])
********************************************************************
weight 148 passengers : 11396 [kg]
weight luggage : 2368 [kg]
weight cargo : 22461 [kg] (cargo+luggage/m3 belly : 563 [kg/m3])
zero fuel weight (ZFW): 101600 [kg](68.9 [%])
weight fuel for landing (1.1 hours flying) : 7260 [kg]
max. landing weight (MLW): 108860 [kg](73.8 [%])
max. fuel weight : 136217 [kg] (92.4 [%])
payload with max fuel : 120 passengers+luggage 11201 [kg]
published maximum take-off weight : 147418 [kg] (100.0 [%])
JAL DC-8-55CF JA8014 “Asama” c/n 45678 March 1976 being serviced at Tokyo-Haneda (HND) apt.
calculation : * 4 * (engine power)
power loading (Take-off) : 460 [kg/KN]
power loading (Take-off) 1 PUF: 613 [kg/KN]
max. total take-off power : 320.7 [KN]
calculation : *5* (loads)
manoeuvre load : 7.5 [g] at 1000 [m]
limit load : 2.5 [g] ultimate load : 3.8 [g] load factor : 1.1 [g]
design flight time : 3.30 [hours]
design cycles : 14025 sorties, design hours : 46282 [hours]
max. wing loading (MTOW & flaps retracted) : 550 [kg/m2]
wing stress (2 g) during operation : 177 [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) : 13.47 ["]
max. angle of attack (full flaps) : 12.67 ["]
angle of attack at max. speed : 1.67 ["]
calculation : *7* (lift & drag ratios
lift coefficient at angle of attack 0° : 0.15 [ ]
lift coefficient at max. speed : 0.29 [ ]
lift coefficient at max. angle of attack : 1.27 [ ]
max. lift coefficient full flaps : 1.71 [ ]
drag coefficient at max. speed : 0.0267 [ ]
drag coefficient at econ. cruise speed : 0.0272 [ ]
induced drag coefficient at econ. cruise speed : 0.0059 [ ]
drag coefficient (zero lift) : 0.0212 [ ]
lift/drag ratio at max. speed : 10.78 [ ]
calculation : *8* (speeds
take-off safety speed (V2) : 276 [km/u]
take-off (initial climb) speed (Vto) : 326 [km/u]
stalling speed clean at sea-level (OW loaded : 140944 [kg]): 294 [km/u]
max. rate of climb speed : 572 [km/hr] at sea-level
max. endurance speed (Vbe): 554 [km/u] min. fuel/hr : 5341 [kg/hr] at height : 6706 [m]
max. range speed (Vbr) = economic cruise speed : 880 [km/u] min.fuel cons. : 7.356 [kg/km] at cruise height : 9144 [m]
max. cruising speed : 933 [km/hr] at 9144 [m] (power:33 [%])
max. operational speed (Mmo) : 960 [km/hr] (Mach 0.88 ) at 9150 [m] (power:34.6 [%])
airflow at cruise speed per engine : 170.0 [kg/s]
speed of thrust jet : 1499 [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 : 108860 [kg]): 264 [km/u]
final approach speed (landing speed) at sea-level with full flaps (max. landing weight) (Vapp): 267 [km/u]
ICAO Aircraft Approach Category (APC) : D
stalling speed at sea-level with full flaps (max. landing weight): 205 [km/u]
rate of climb at sea-level ROC (loaded, 74 % power) : 954 [m/min]
rate of climb at sea-level ROC (loaded, 75% power) : 966 [m/min]
rate of climb at 1000 [m] with 1 engine out (PUF/MTOW, 100 % power on remaining engines) : 784 [m/min]
rate of climb at 1000 [m] with 2 engines out (2xPUF / MTOW) : 234 [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
FAR takeoff RW at MTOW 325000 lbs = 147420 kg, JT3D-3B engines, sea-level : 10000 ft > 3048 [m] (Jane’s : 3220 [m] !)
take-off distance at sea-level concrete runway : 3080 [m]
ICAO Aerodrome Reference Code : 4D
take-off distance (C.A.R) at sea-level over 10.7 [m] height : 3187 [m]
FAR TO runway length requirement at MTOW, standard day at SL (ASDA): 3386 [m]
landing distance (MLW) : 835 [m]
Landing field length, sea level, dry runway with MLW 108860 kg (240000 lb) : 6050 ft = 1844 [m]
landing distance (C.A.R.) from 15 [m] at SL, dry runway : 1893 [m]
landing distance (C.A.R.) from 15 [m] at SL, wet runway : 2193 [m]
FAR landing runway length requirements at SL : 1844 [m]
lift/drag ratio : 13.37 [ ]
climb to 5000 [m] with max payload : 4.85 [min]
climb to 10000 [m] with max payload : 14.92 [min]
descent time from 10000 [m] to 250 [m] : 24.33 [min]
ceiling limited by max. pressure differential 16225 [m]
theoretical ceiling fully loaded (mtow- 60 min.fuel: 140944 [kg] ) : 16300 [m]
calculation *10* (action radius & endurance)
range with max. payload: 5924 [km] with 36225.0 [kg] max. useful load (64.7 [%] fuel)*
range with high density pax: 8655 [km] with 189 passengers (91.0 [%] fuel)*
range with typical two-class pax: 9235 [km] with 148 passengers (96.4 [%] fuel)*
Range with max fuel 23393 US gallon = 88550 litre : 5000 nm > 9260 km, mtow 325000 lb = 147420 kg, 32000 lb payload = 14515 kg. Ferry range 5850 nm = 10834 km. OEW 138266 = 62717 kg
range with max.fuel : 9630 [km] with 11 crew and 120 passengers and 100.0 [%] fuel*
ferry range : 10082 [km] with 4 crew and zero payload (100.0 [%] fuel)*
max range theoretically with additional fuel tanks total 103812 [litre] fuel : 11556 [km]*
* calculated ranges without fuel reserves
Available Seat Kilometres (ASK) : 1548421 [paskm]
useful load with range 1000km : 36225 [kg]
useful load with range 1000km : 189 passengers
production (theor.max load): 33798 [tonkm/hour]
production (useful load): 33798 [tonkm/hour]
production (passengers): 162115 [paskm/hour]
combi aircraft mail/freight/passengers
oil and fuel consumption per tonkm : 0.192 [kg]
calculation *11* (operating cost)
fuel cost per hour (8092 [litre]):4855 [eur] (20 [pax-km/litre fuel])
fuel cost per seat 1000km flight (174 [pax] 2-class seating): 29.95 [eur/1000PK]
oil cost per hour: 48 [eur]
crew cost per hour : 1500 [eur]
list price 2023 : 169 [mln USD]
average flying hours in 1 year : 3260 [hours] technical life : 14 [year]
real average service life : 14 [years]
economic hours (average real flown hours): 45640 [hours] is 1 [%] less then design hours
financing interest per flying hour : 1207 [EUR]
write off per flying hour : 3183 [EUR]
time between engine failure : 10307 [hr]
can continue fly on 3 engines, low risk for emergency landing for PUF
workhours per day : 10.96 [hr]
average flight hours till crash : 0.82 [mln hr] (252 service years)
DC-8-55CF PH-DCU "Sir Winston Churchill", crashed on 31 March 1988 in service with Arax Airlines reg. 5N-ARH at Cairo, killing 4.
safe flight hours till fatality : 7899 [hr] (2.4 service years)
reservation pax liability/flying hour : 16.31 [SDR*] (20.39 [eur])
insurance cost per hour : 227 [eur]
engine maintenance cost per hour : 225.0 [eur]
wing maintenance cost per hour : 178.6 [eur]
fuselage maintenance cost per hour : 71.19 [eur]
tire life (time till worn out) : 114 [cycles]
maintenance cost per hour (excluding engines): 1224 [eur]
direct operating cost per hour: 12489 [eur]
DOC per seat 1000km flight (174 [pax] 2-class seating): 77.04 [eur/1000PK]
DOC per seat 1000km flight (high density seating): 70.83 [eur/1000PK]
DOC per kg cargo for a 1000km flight : 0.37 [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 : 5.07 [eur/pax]
airport landing fee / passenger : 5.07 [eur/pax]
retour ticket price 1000km trip : 238.90 [eur/pax]
price retour ticket Schiphol-Barcelona : 281.27 [eur/pax]
accidents with fatalities > see the accident file
Literature :
KIJK verkeersvliegtuigen page 33
Jane’s all the world aircraft 1970-71 page
De Nederlandse DC-8 vliegtuigen page 1, 11
Wikipedia
https://www.boeing.com/resources/boeingdotcom/commercial/airports/acaps/dc8.pdf
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/
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(c) B van der Zalm 16 September 2023 contact : info.aircraftinvestigation@gmail.com ac jetpax 2020.py python 3.7.4