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weight and performance calculations for the McDonnell Douglas DC-10-40
McDonnell Douglas DC-10-40
role : wide-body airliner
importance : **
first flight : 28 February 1972 operational : March 1973
country : United States of America
production : 42 aircraft
general information :
Extended range version for intercontinental operations. 22 DC-10-40’s were built for Northwest Orient Airlines powered by P&W JT9D-20 engines of 220 KN with water-injection. Japan Airlines was the only other airline who ordered the DC-10-40, they received 20 aircraft with 236 KN JT9D-59A engines. Making the first flight 25 July 1975.
primary users : Northwest Airlines, Japan Airlines, American Trans Air
Accommodation:
flight crew : 3 cabin crew : 9
flight crew consist of pilot, co-pilot and flight engineer
passengers : seating for 255 in two class : 24 first class and 231 coach class seats
( 34 -in pitch) high density seating for 380 passengers
engine : 3 Pratt & Whitney JT9D-20 turbofan engines of 220.5 [KN] (49569.5 [lbf])
dimensions :
wingspan : 50.41 [m], length overall: 55.5 [m], length of fuselage : 51.97 [m]
height : 17.7 [m] wing area : 367.7 [m^2] fuselage exterior width : 6.02 [m]
weights :
operating empty weight : 122566 [kg] max. structural payload : 44356 [kg]
Zero Fuel weight (ZFW) : 166922 [kg] max. landing weight (MLW) : 182798 [kg]
max. take-off weight : 251744 [kg] weight fuel : 108149 [kg] (137770 [litres])
performance :
Never-exceed speed : 0.95 [Mach] (1052 [km/hr]) at 7620 [m]
critical Mach speed : 0.88 [Mach]
max. cruising speed : 955 [km/hr] (Mach 0.88 ) at 9145 [m] (34 [%] power)
economic cruising speed : 906 [km/hr] (Mach 0.83 ) at 9145 [m]
service ceiling : 9660 [m]
range with max fuel and MTOW : 10186 [km] (ATA domestic fuel reserves –
370.0 [km] alternate)
description :
cantilever low-wing monoplane with retractable landing gear with nose wheel
Wings : primary two-spar box-type fail-safe wing structure of high-strength
aluminium alloy with Fowler-type double slotted trailing edge flaps with full-span
slotted LE flaps (slats) ,with spoilers airfoil : Douglas
average thickness/chord ratio : 10.3 [%], sweep angle 3/4 chord: 35.0 [°]
2 engines attached to the wings 1 in the tail, landing gear attached to the wings, fuel
tanks in the wings and in the fuselage
Fuselage : Pressurized all-metal aluminium-alloy stressed-skin structure of elliptical
0 section
calculation : *1* (dimensions)
wing chord at root : 10.71 [m]
wing chord at tip : 2.73 [m]
taper ratio : 0.255 [ ]
mean wing chord : 7.29 [m]
wing aspect ratio : 6.91 []
Oswald factor (e): 0.675 []
seize (span*length*height) : 49520 [m^3]
calculation : *2* (fuel consumption)
oil consumption : 3.3 [kg/hr]
fuel consumption (econ. cruise speed) : 9282.2 [kg/hr] (11824.5 [litre/hr]) at 26 [%]
power
distance flown for 1 kg fuel : 0.10 [km/kg] at 9145 [m] height, sfc : 55.0 [kg/KN/h]
total fuel capacity : 137770 [litre] (108149 [kg])
calculation : *3* (weight)
weight engine(s) dry : 11499.0 [kg] = 17.38 [kg/KN]
weight 2270 litre de-mineralized water tank for engine injection : 192.97 [kg]
weight 65.4 litre oil tank : 5.56 [kg]
oil tank filled with 4.2 litre oil : 3.7 [kg]
oil in engine 8.1 litre oil : 7.3 [kg]
fuel in engine 36.1 litre fuel : 26.46 [kg]
weight fuel lines : 245.7 [kg]
weight engine cowling : 1719.9 [kg]
weight thrust reversers : 992.2 [kg]
total weight propulsion system : 14693 [kg](5.8 [%])
***************************************************************
Accommodation cabin facilities:
typical 2-class cabin layout for 255 passengers : economy : pitch : 86.4 [cm] 34.0 [-in]
( 2+5+2 ) seating in 29.7 rows
weight passenger seats : 1547.9 [kg]
weight cabin crew seats : 45.0 [kg]
weight flight crew seats : 63.0 [kg]
weight 2 jump seats in the cockpit :14.0 [kg]
high density seating passengers : 380 [pax] at mainly 10 -abreast seating in
43.3 rows, pitch 80.1 [cm] 31.5 [-in]
pax density, normal seating : 0.84 [m2/pax], high density seating : 0.56 [m2/pax]
weight 7 lavatories : 197.4 [kg]
weight 5 galleys : 523.3 [kg]
weight overhead stowage for hand luggage : 89.2 [kg]
weight 3 wardrobe closets : 25.5 [kg]
weight 3 movie screens : 63.8 [kg]
Cabin window is made of two layers of acrylic glass, the outer panel is ca. 12mm thick and takes most of the load, the inner panner is only 4mm thick, and its main role is to protect the outer panel.
weight 61 windows (41x28cm) made of acrylic glass : 167.6 [kg]
weight 8 (1.93 x 1.07 [m]) Type A main entry doors : 526.3 [kg]
weight 3 (main door size : 1.75 x 1.78 [m]) freight doors (belly) : 280.4 [kg]*
Extended cargo compartment gives place for two more LD3 containers, reducing bulk cargo space from 22.80 [m3] to 14.44 [m3], containerized netto volume 26 LD3 containers x 4.47 [m3] = 116.3 [m3]
total belly baggage/cargo hold volume : 155.4 [m3]
underfloor belly hold can accommodate : 26 LD3 containers, netto volume : 116.3 [m3]
and : 14.4 [m3] bulk cargo
cabin volume (usable), excluding flight deck : 447 [m3]
passenger compartment volume : 292 [m3]
passenger cabin max width : 5.72 [m] cabin length : 41.45 [m] max cabin height :
2.41 [m]
floor area : 213.6 [m2]
weight cabin facilities : 3543.3 [kg]
safety facilities:
evacuation time with 380 passengers : 49 [sec]
weight 12 hand fire extinguisher : 36 [kg]
weight cockpit voice recorder (CVR) and flight data recorder (FDR): 20.0 [kg]
weight oxygen masks & oxygen generators : 165.8 [kg]
weight emergency flare installation : 10 [kg]
weight 8 emergency evacuation slides : 348.9 [kg]
weight safety equipment & facilities : 581 [kg]
fuselage construction:
fuselage aluminium frame : 22560 [kg]
floor loading (payload/m2): 208 [kg/m2]
weight rear pressure bulkhead : 472.9 [kg]
fuselage covering ( 814.4 [m2] duraluminium 3.09 [mm]) : 6745.7 [kg]
weight floor beams : 5082.7 [kg]
weight cabin furbishing : 3188.2 [kg]
weight cabin floor : 3020.9 [kg]
weight (sound proof) isolation : 658.1 [kg] TO-noise level : 98.0 [EPNdB]
weight 18953 [litre] main central fuel tanks empty : 1061.4 [kg]
weight 15596 [litre] additional central fuel tank (ACT) empty : 873.4 [kg]
weight empty 438 [litre] potable water tank : 38.8 [kg]
weight empty waste tank : 30.1 [kg]
weight engine mount in tail : 110 [kg]
weight fuselage structure : 43841.9 [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 monochromatic weather X-band (3.2cm wavelength) radar system : 25.0 [kg]
Upgraded DC-10-40 cockpit
weight VOR/ILS,RMI,DME,radio altimeter, ASI, time clock : 20.0 [kg]
weight Avionic Flight Control System : 33.0 [kg]
weight CAT IIIA auto-landing system : 10.0 [kg]
weight artificial horizons, compass, alti-meters : 7 [kg]
weight ground proximity warning system (GPWS) : 6 [kg]
weight engine monitoring gauges & control switches : 21 [kg]
weight reserve ADI, ASI, alti-meter, compass, engine temp. and rpm indicators :
15 [kg]
weight avionics : 151.0 [kg]
Systems:
Air-conditioning and pressurization system maintains sea level conditions up to
6400 [m] and gives equivalent of 2440 [m] at 12200 [m]. pressure differential : 0.58
[bar] (kg/cm2) pressurized fuselage volume : 576 [m3] cabin air refreshment time :
3.0 [min]
weight air-conditioning and pressurization system : 328 [kg]
weight APU / engine starter: 110.2 [kg]
weight lighting : 84.2 [kg]
weight triple redundant 207 bar hydraulic system : 167.5 [kg]
weight three engine-driven 90kVA 400 Hertz electricity generators : 63.8 [kg]
weight integrated drive generator (IDG) : 25 [kg]
weight three 24V 25Ah nickel-cadmium batteries : 36.2 [kg]
weight controls : 22.3 [kg]
weight systems : 837.1 [kg]
total weight fuselage : 48954 [kg](19.4 [%])
***************************************************************
total weight aluminium ribs (1622 ribs) : 8259 [kg]
weight engine mounts : 220 [kg]
weight 6 wing fuel tanks empty for total 103221 [litre] fuel : 5780 [kg]
weight wing covering (painted aluminium 3.87 [mm]) : 7693 [kg]
total weight aluminium spars (multi-cellular wing structure) : 11032 [kg]
weight wings : 26985 [kg]
weight wing/square meter : 73.39 [kg]
weight thermal leading-edge anti-icing : 55.5 [kg]
weight high & low speed ailerons (17.44 [m2]) : 641.3 [kg]
weight fin (45.92 [m2]) : 1688.5 [kg]
weight rudder (10.28 [m2]) : 362.8 [kg]
weight tailplane (stabilizer) (96.61 [m2]): 3907.6 [kg]
weight elevators (27.70 [m2]): 549.97 [kg]
weight flight control hydraulic servo actuators: 82.5 [kg]
Japan Airlines DC-10-40 JA8532 c/n 46660 landing at Hong Kong, Kai Tak apt., jan.2016
weight trailing-edge double slotted flaps (62.07 [m2]) : 1941.0 [kg]
weight leading edge slats made of aluminium alloy honeycomb (43.82 [m2]) : 861.1 [kg]
weight spoilers (12.7 [m2]) : 231.1 [kg]
total weight wing construction : 43307 [kg] (35.3 [%])
*******************************************************************
tire pressure main wheels : 12.41 [Bar] (nitrogen), ply rating : 23 PR
tire speed limit : 389 [km/hr]
total tyre footprint : 1.37 [m2]
Runway LCN at MTOW (0.76m radius of rigidity) : 48 [ ]
Aircraft Classification Number (ACN), MTOW on rigid runway and medium subgrade
strength (B) : 59 [ ] Can only operate from unpaved runways with reduced weight
and reduced tyre pressure
wheel pressure : 22153.5 [kg]
weight 10 Dunlop main wheels (1320 [mm] by 528 [mm]) : 1685.8 [kg]
weight 2 nose wheels : 168.6 [kg]
weight hydraulic disc wheel-brakes : 166.9 [kg]
weight Duplex anti-skid units : 10.8 [kg]
weight oleo-pneumatic shock absorbers : 222.6 [kg]
weight wheel hydraulic operated retraction system : 2225.7 [kg]
total weight landing gear : 11017.1 [kg] (4.4 [%]
*******************************************************************
********************************************************************
calculated empty weight : 117971 [kg](46.9 [%])
weight oil for 12.8 hours flying : 46.2 [kg]
weight engine injection water : 2270.3 [kg]
weight lifejackets : 114.8 [kg]
weight 5 life rafts : 159.4 [kg]
weight catering : 484.5 [kg]
weight water : 387.6 [kg]
weight crew : 972 [kg]
weight crew luggage, nav. chards, flight doc., miscell. items : 160 [kg]
operational weight empty : 122566 [kg] (48.7 [%])
********************************************************************
weight 255 passengers : 19635 [kg]
weight luggage : 4080 [kg]
weight cargo : 20641 [kg] (cargo + luggage/m3 belly : 153 [kg/m3])
zero fuel weight (ZFW): 166922 [kg](66.3 [%])
weight fuel for landing (1.7 hours flying) : 15876 [kg]
max. landing weight (MLW): 182798 [kg](72.6 [%])
max. fuel weight : 230715 [kg] (91.6 [%])
payload with max fuel : 226 passengers + luggage 21029 [kg]
published maximum take-off weight : 251744 [kg] (100.0 [%])
calculation : * 4 * (engine power)
power loading (Take-off) : 381 [kg/KN]
power loading (Take-off) 1 PUF: 571 [kg/KN]
max. total take-off power : 661.5 [KN]
calculation : *5* (loads)
manoeuvre load : 1.3 [g] at 9000 [m]
limit load : 2.5 [g] ultimate load : 3.8 [g] load factor : 1.0 [g]
design flight time : 3.80 [hours]
design cycles : 13000 sorties, design hours : 49400 [hours]
max. wing loading (MTOW & flaps retracted) : 685 [kg/m2]
wing stress (2 g) during operation : 158 [N/kg] at 2g emergency manoeuvre
Japan Air Lines DC-10-40 JA8530 c/n 46920
calculation : *6* (angles of attack)
angle of attack zero lift : -1.82 ["]
max. angle of attack (stalling angle, clean) : 13.76 ["]
max. angle of attack (full flaps) : 17.96 ["]
angle of attack at max. speed : 1.18 ["]
calculation : *7* (lift & drag ratios
lift coefficient at angle of attack 0° : 0.15 [ ]
lift coefficient at max. speed : 0.25 [ ]
lift coefficient at max. angle of attack (clean): 1.28 [ ]
max. lift coefficient full flaps : 1.84 [ ]
drag coefficient at max. speed : 0.0316 [ ]
drag coefficient at econ. cruise speed : 0.0316 [ ]
induced drag coefficient at econ. cruise speed : 0.0090 [ ]
drag coefficient (zero lift) : 0.0226 [ ]
lift/drag ratio at econ. speed : 7.82 [ ]
calculation : *8* (speeds
take-off decision speed (V1) : 284 [km/u] (153 [kt])
lift-off speed (VLOF) : 323 [km/u] (174 [kt])
take-off safety speed (V2) : 346 [km/u] (187 [kt])
flap retraction speed (V3) at 500m (OW loaded : 242462 [kg]): 351 [km/u] (189 [kt])
steady initial climb speed (V4) : 372 [km/u] (201 [kt])
climb speed (to FL150 with 56 [%] power) : 596 [km/hr] (322 [kt])
max. endurance speed (Vbe): 658 [km/u] min. fuel/hr : 8380 [kg/hr] at height : 7620 [m]
max. range speed (Vbr): 913 [km/u] (0.83 [mach]) min. fuel consumption : 10.59 [kg/km]
at cruise height : 8534 [m]
max. cruising speed : 955 [km/hr] (516 [kt]) at 9145 [m] (power:27 [%])
max. operational speed (Mmo) : 1052 [km/hr] (Mach 0.95 ) at 7620 [m] (power:40 [%])
airflow at cruise speed per engine : 559.2 [kg/s]
speed of thrust jet : 1341 [km/hr]
initial descent speed 10000 - 7315 [m]: Mach 0.72
descent speed 7315 - 3048 [m]: 519 [km/u] (280 [kt])
approach speed 3048 - 500 [m] (clean): 389 [km/u] (210 [kt])
minimum control speed (MCS) Vmca (clean): 334 [km/u] (180 [kt])
stalling speed clean at 500 [m] height at Max.Landing Weight : 182798 [kg]):
290 [km/u] (157 [kt])
Approach speed DC-10-40 JT9D-20, MLW 182798 kg (403000 lbs) : 147 kts = 271 km/h
final approach speed (landing speed) at sea-level with full flaps VREF (max.
landing weight): 271 [km/u] (147 [kt])
ICAO Aircraft Approach Category (APC) : D
stalling speed at sea-level with full flaps VSO (max. landing weight): 209 [km/u]
rate of climb at sea-level ROC (loaded, 56 % power) : 830 [m/min]
rate of climb at sea-level ROC (loaded, 75 % power) : 1467 [m/min]
rate of climb at 1000 [m] with 1 engine out (PUF/MTOW, 100 % power on remaining
engines) : 939 [m/min]
Northwest Orient DC-10-40 N160US c/n 46769 landing at London February 1989
rate of descent from FL240 to FL100 (7315m > 3048m): 1067 [m/min] (3501 [ft/min])
rate of descent during approach with landing gear extended, with use of spoilers: 457
[m/min] (1499 [ft/min])
calculation : *9* (regarding various performances)
high wheel pressure, can only take off from paved runways
take-off distance at sea-level concrete runway : 3548 [m]
ICAO Aerodrome Reference Code : 4D
Take-off distance, standard day, sea level, mtow 251744 kg , dry take-off thrust : 4100 [m], jane’s all the world aircraft FAR TO-distance to 10.7 [m] : 3734 [m]
take-off distance at sea-level over 15 [m] height : 3728 [m]
FAR TO runway length requirement at MTOW, standard day at SL (ASDA): 3932 [m]
FAR landing runway length at MLW 182798 kg at sea level : 6100 [ft] = 1859 [m]
landing run (MLW) : 929 [m]
landing distance (C.A.R.) from 15 [m] at SL, dry runway : 1784 [m]
landing distance (C.A.R.) from 15 [m] at SL, wet runway : 2052 [m]
FAR landing runway length requirements at SL : 1857 [m]
max. lift/drag ratio : 12.72 [ ]
climb to 5000 [m] with max payload : 5.58 [min]
climb to 10000 [m] with max payload : 17.16 [min]
descent time from 10000 [m] to 250 [m] : 24.33 [min]
ceiling limited by max. pressure differential 14125 [m]
theoretical ceiling fully loaded (mtow- 60 min.fuel: 242462 [kg] ) : 16000 [m]
calculation *10* (action radius & endurance)
range with max. payload: 8002 [km] with 44356.0 [kg] max. useful load (78.4 [%] fuel)*
range with high density pax: 8971 [km] with 380 passengers (86.8 [%] fuel)*
range with typical two-class pax: 10254 [km] with 255 passengers (97.5 [%] fuel)*
Range with max fuel : 5500 nm = 10186 [km]
range with max.fuel : 10556 [km] with 12 crew and 226 passengers and 100.0 [%]
fuel*
ferry range : 11248 [km] with 3 crew and zero payload (100.0 [%] fuel)*
max range theoretically with additional fuel tanks total 166598 [litre] fuel : 13182
[km]*
* calculated ranges without fuel reserves
Available Seat Kilometres (ASK) : 3021604 [paskm]
useful load with range 1000km : 44356 [kg]
useful load with range 1000km : 380 passengers
production (theor.max load): 42360 [tonkm/hour]
production (useful load): 42360 [tonkm/hour]
production (passengers): 295645 [paskm/hour]
oil and fuel consumption per tonkm : 0.219 [kg]
calculation *11* (operating cost)
fuel cost per hour (11825 [litre]): 7094 [eur] (25 [pax-km/litre fuel])
fuel cost per seat 1000km flight (310 [pax] 2-class seating): 24.00 [eur/1000PK]
oil cost per hour: 14 [eur]
crew cost per hour : 1650 [eur]
list price 2023 : 313 [mln USD]
average flying hours in 1 year : 3250 [hours] technical life : 18 [year]
real average service life : 18 [years]
depreciation - 18 [years] to 10% residual value
economic hours (expected total flying hours): 58500 [hours]
financing interest per flying hour : 2164 [EUR]
write off per flying hour : 4439 [EUR]
time between engine failure : 22606 [hr]
can continue fly on 2 engines, low risk for emergency landing for PUF
workhours per day : 10.66 [hr]
no fatalities during service life > 100%% safe
average flight hours till crash : 2.46 [mln hr] (756 service years)
safe flight hours till fatality : 2457000 [hr] (756.0 service years)
reservation pax liability/flying hour : 0.05 [SDR*] (0.07 [eur])
insurance cost per hour : 586 [eur] insurance rate : 1.6 [%]
engine maintenance cost per hour : 708.2 [eur]
wing maintenance cost per hour : 212.9 [eur]
fuselage maintenance cost per hour : 112.80 [eur]
tire life (time till worn out) : 95 [cycles]
maintenance cost per hour (excluding engines): 2611 [eur]
direct operating cost per hour: 19267 [eur], DOC per km : 21.27 [eur]
DOC per seat 1000km flight (310 [pax] 2-class seating): 65.17 [eur/1000PK]
DOC per seat 1000km flight (high density seating): 53.09 [eur/1000PK]
DOC per kg cargo for a 1000km flight : 0.45 [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 : 4.85 [eur/pax]
airport landing fee / passenger : 4.85 [eur/pax]
retour ticket price 1000km trip : 211.86 [eur/pax]
price retour ticket Schiphol-Barcelona : 247.70 [eur/pax]
accidents with fatalities > there were no fatal accidents with an DC-10-40
Burned out American Trans Air DC-10-40 at Chicago O’Hare airport, Sunday 10 August 1986. N184AT c/n 46751. While parked a mechanic was checking some seatbacks containing solid-state chemical oxygen generators, by accident a generator went off generating a heat of 430°C igniting other seat covers. The fire spread rapidly and the aircraft was destroyed by the fire. There were no casualties
Literature :
McDonnell Douglas DC-10 - Wikipedia
https://contentzone.eurocontrol.int/aircraftperformance/default.aspx?
https://www.boeing.com/search/results.html?q=airplane+characteristics
Jane’s all the world aircraft 1979-80 page 390
Advanced jetliners page 21
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 24 December 2023 contact : info.aircraftinvestigation@gmail.com ac jetpax 2020.py python 3.7.4
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