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weight and performance calculations for the McDonnell Douglas DC-10-30CF

Overseas National Airways DC-10-30CF N1032F c/n 46826

McDonnell Douglas DC-10-30CF

role : wide-body convertible freighter /airliner

importance : ****

first flight : 28 February 1973 operational : April 1973

country : United States of America

production : 27 aircraft

general information :

, Federa Convertible freighter version. It could be changed overnight from passenger configuration to freighter configuration by removing the seats, overhead baggage racks, food service center, cloakroom and carpeting and then installing freight loading tracks ,rollers, tiedown system and restraint nets. As a freighter it could take 30 standard 2.24 x 2.27 [m] pallets with max payload weight 69383 [kg]

primary users : Overseas National Airways, Trans International Airlines, Martinair,

World Airways, Spantax

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 General Electric CF6-50C turbofan engines of 226.83 [KN] (50992.6 [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 : 121904 [kg] max. structural payload : 55451 [kg]

Zero Fuel weight (ZFW) : 177355 [kg] max. landing weight (MLW) : 186427 [kg]

max. take-off weight : 251744 [kg] weight fuel : 107945 [kg] (137509 [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] (33 [%] 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 conventional semi-monocoque fail safe structure of circular

cross-section built mainly of high-strength aluminium alloy

calculation : *1* (dimensions)

wing chord at root : 10.71 [m]

wing chord at tip : 2.73 [m]

taper ratio : 0.255 [ ]

World Airways N103WA c/n 46975

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 : 1.5 [kg/hr]

fuel consumption (econ. cruise speed) : 9264.7 [kg/hr] (11802.1 [litre/hr]) at 35 [%]

power

distance flown for 1 kg fuel : 0.10 [km/kg] at 9145 [m] height, sfc : 38.5 [kg/KN/h]

total fuel capacity : 137509 [litre] (107945 [kg])

calculation : *3* (weight)

weight engine(s) dry : 12150.0 [kg] = 17.85 [kg/KN]

weight 37.6 litre oil tank : 3.20 [kg]

oil tank filled with 4.3 litre oil : 3.8 [kg]

oil in engine 8.3 litre oil : 7.5 [kg]

fuel in engine 37.1 litre fuel : 27.22 [kg]

weight fuel lines : 245.3 [kg]

weight engine cowling : 1769.3 [kg]

weight thrust reversers : 1020.7 [kg]

total weight propulsion system : 15227 [kg](6.0 [%])

***************************************************************

Accommodation cabin facilities:

typical 2-class cabin layout for 255 passengers : economy : pitch : 86.4 [cm] 34.0 [-in]

( 2+5+2 ) seating in 29.1 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 : 550.8 [kg]

weight overhead stowage for hand luggage : 89.2 [kg]

weight 3 wardrobe closets : 25.5 [kg]

weight 3 movie screens : 63.8 [kg]

weight 60 windows (41x28cm) made of acrylic glass : 164.5 [kg]

weight 8 (1.93 x 1.07 [m]) Type A main entry doors : 519.0 [kg]

weight 3 (main door size : 1.68 x 1.78 [m]) freight doors (belly) : 265.5 [kg]*

total belly baggage/cargo hold volume : 155.4 [m3]

underfloor belly hold can accommodate : 26 LD3 containers, netto volume : 114.5 [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 : 3545.6 [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 : 22248 [kg]

floor loading (payload/m2): 260 [kg/m2]

weight rear pressure bulkhead : 466.5 [kg]

fuselage covering ( 814.4 [m2] duraluminium 3.05 [mm]) : 6655.9 [kg]

weight 2.59 x 3.56 [m] upper deck cargo door : 251.9 [kg]

weight floor beams : 5864.1 [kg]

weight cabin furbishing : 3188.3 [kg]

weight cabin floor : 3485.4 [kg]

weight (sound proof) isolation : 638.3 [kg] TO-noise level : 97.0 [EPNdB]

weight 18953 [litre] main central fuel tanks empty : 1061.4 [kg]

weight 15335 [litre] additional central fuel tank (ACT) empty : 858.8 [kg]

weight empty 461 [litre] potable water tank : 40.8 [kg]

weight empty waste tank : 30.1 [kg]

weight engine mount in tail : 113 [kg]

weight fuselage structure : 44902.8 [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]

weight VOR/ILS,RMI,DME,radio altimeter, ASI, time clock : 20.0 [kg]

digital air data computer meeting ARINC 576 requirements : 33 [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)

Air Florida DC-10-30CF NT101TV c/n46800 at London Gatwick, May 1982

pressurized fuselage volume : 576 [m3] cabin air refreshment time : 3.0 [min]

weight air-conditioning and pressurization system : 328 [kg]

weight APU / engine starter: 113.4 [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 : 840.2 [kg]

total weight fuselage : 50021 [kg](19.9 [%])

***************************************************************

total weight aluminium ribs (1665 ribs) : 8477 [kg]

weight engine mounts : 227 [kg]

weight 6 wing fuel tanks empty for total 103221 [litre] fuel : 5780 [kg]

weight wing covering (painted aluminium 3.82 [mm]) : 7579 [kg]

total weight aluminium spars (multi-cellular wing structure) : 10835 [kg]

weight wings : 26891 [kg]

weight wing/square meter : 73.13 [kg]

weight thermal leading-edge anti-icing : 55.5 [kg]

weight high & low speed ailerons (17.44 [m2]) : 639.1 [kg]

weight fin (45.92 [m2]) : 1682.7 [kg]

weight rudder (10.28 [m2]) : 361.5 [kg]

weight tailplane (stabilizer) (96.61 [m2]): 3894.0 [kg]

weight elevators (27.70 [m2]): 548.06 [kg]

weight flight control hydraulic servo actuators: 82.5 [kg]

weight trailing-edge double slotted flaps (62.07 [m2]) : 1934.3 [kg]

weight leading edge slats made of aluminium alloy honeycomb (43.82 [m2]) : 858.1 [kg]

weight spoilers (12.7 [m2]) : 230.3 [kg]

total weight wing construction : 43184 [kg] (35.4 [%])

*******************************************************************

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) : 33 [ ]

Can also operate from unpaved runways subgrade B

wheel pressure : 22153.5 [kg]

weight 10 Dunlop main wheels (1320 [mm] by 528 [mm]) : 1698.3 [kg]

weight 2 nose wheels : 169.8 [kg]

weight hydraulic disc wheel-brakes : 177.4 [kg]

weight Duplex anti-skid units : 10.8 [kg]

weight oleo-pneumatic shock absorbers : 236.5 [kg]

weight wheel hydraulic operated retraction system : 2265.8 [kg]

total weight landing gear : 11215.6 [kg] (4.5 [%]

*******************************************************************

World Airways DC-10-30CF N108WA c/n 46837 at Frankfurt Rhein-Main apt (FRA), June 1984

********************************************************************

calculated empty weight : 119647 [kg](47.5 [%])

weight oil for 12.8 hours flying : 20.9 [kg]

weight lifejackets : 114.8 [kg]

weight 5 life rafts : 159.4 [kg]

weight catering : 510.0 [kg]

weight water : 408.0 [kg]

weight crew : 972 [kg]

weight crew luggage, nav. chards, flight doc., miscell. items : 71 [kg]

operational weight empty : 121904 [kg] (48.4 [%])

********************************************************************

weight 255 passengers : 19635 [kg]

weight luggage : 4080 [kg]

weight cargo : 31736 [kg] (cargo + luggage/m3 belly : 224 [kg/m3])

zero fuel weight (ZFW): 177355 [kg](70.5 [%])

weight fuel for landing (1.0 hours flying) : 9072 [kg]

max. landing weight (MLW): 186427 [kg](74.1 [%])

max. fuel weight : 229849 [kg] (91.3 [%])

payload with max fuel : 235 passengers + luggage 21895 [kg]

published maximum take-off weight : 251744 [kg] (100.0 [%])

calculation : * 4 * (engine power)

power loading (Take-off) : 370 [kg/KN]

power loading (Take-off) 1 PUF: 555 [kg/KN]

max. total take-off power : 680.5 [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 : 4.00 [hours]

design cycles : 12725 sorties, design hours : 50900 [hours]

max. wing loading (MTOW & flaps retracted) : 685 [kg/m2]

wing stress (2 g) during operation : 160 [N/kg] at 2g emergency manoeuvre

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 : 1.20 ["]

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 : 1.87 [ ]

drag coefficient at max. speed : 0.0475 [ ]

drag coefficient at econ. cruise speed : 0.0451 [ ]

induced drag coefficient at econ. cruise speed : 0.0090 [ ]

drag coefficient (zero lift) : 0.0361 [ ]

lift/drag ratio at econ. speed : 5.24 [ ]

calculation : *8* (speeds

take-off decision speed (V1) : 297 [km/u] (160 [kt])

take-off rotation speed (VR) : 312 [km/u] (168 [kt])

lift-off speed (VLOF) : 326 [km/u] (176 [kt]) at pitch angle : 14.7 [°]

take-off safety speed (V2) : 333 [km/u] (180 [kt])

flap retraction speed (V3) at 500m (OW loaded : 242479 [kg]): 351 [km/u] (189 [kt])

steady initial climb speed (V4) : 359 [km/u] (194 [kt])

climb speed (to FL150 with 66 [%] power) : 524 [km/hr] (283 [kt])

max. endurance speed (Vbe): 585 [km/u] min. fuel/hr : 7414 [kg/hr] at height : 7620 [m]

max. range speed (Vbr): 813 [km/u] (0.74 [mach]) min. fuel consumption : 10.53 [kg/km]

at cruise height : 8534 [m]

max. cruising speed : 955 [km/hr] (516 [kt]) at 9145 [m] (power:38 [%])

max. operational speed (Mmo) : 1052 [km/hr] (Mach 0.95 ) at 7620 [m] (power:59 [%])

airflow at cruise speed per engine : 457.9 [kg/s]

speed of thrust jet : 1638 [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): 337 [km/u] (182 [kt])

stalling speed clean at 500 [m] height at Max.Landing Weight : 186427 [kg]): 293

[km/u] (158 [kt])

Approach speed at MLW 186427 kg (411000 lb) : 147 kt (272 km/h)

final approach speed (landing speed) at sea-level with full flaps VREF (max. landing

weight): 272 [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]

(113 [kt]

rate of climb at sea-level ROC (loaded, 66 % power) : 858 [m/min]

rate of climb at sea-level ROC (loaded, 75 % power) : 1113 [m/min]

rate of climb at 1000 [m] with 1 engine out (PUF/MTOW, 100 % power on remaining engines) : 658 [m/min]

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)

low wheel pressure, can also take off from unpaved runways

ICAO Aerodrome Reference Code : 4D

Brake kinetic energy capacity : 4672 [KW]

FAR takeoff runway length requirements with MTOW 251744 [kg] (555000 lb) CF6-50C engines : 3290 [m] (10800 ft)

FAR TO balanced runway length (TOFL) requirement at TOW 251744 [kg] standard

day at SL (distance to 10.7m height x 1.15): 3291 [m]

FAR landing runway at MLW 186427 kg (411000 lb) : 6000 ft > 1829 [m]

FAR landing runway at 165564 kg (365000 lb) : 5467 ft > 1666 [m]

FAR landing runway at 190965 kg (421000 lb) : 6164 ft > 1878 [m]

+++ FAA certification landing distance : +++

landing weight : 186427 [kg], TE flap setting : 50 [°]

runway condition : dry , landing over 50ft (15m) at threshold at sea-level

FAA approved landing field length : 1826 [m] (5989 [ft])

landing distance (C.A.R.) from 15 [m] at SL, wet runway: 2102 [m] (6896 [ft])

max. lift/drag ratio : 10.08 [ ]

climb to 5000 [m] with max payload : 5.39 [min]

climb to 10000 [m] with max payload : 16.60 [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: 242479 [kg] ) : 16000 [m]

calculation *10* (action radius & endurance)

range with max. payload: 7026 [km] with 55451.0 [kg] max. useful load (68.9 [%] fuel)*

range with high density pax: 9115 [km] with 380 passengers (87.5 [%] fuel)*

range with typical two-class pax: 10359 [km] with 255 passengers (98.3 [%] fuel)*

Range 5500 nm > 10186 km with max fuel, ferry range 6500 nm > 12038 [km]

range with max.fuel : 10556 [km] with 12 crew and 235 passengers and 100.0 [%]

fuel*

ferry range : 11051 [km] with 3 crew and zero payload (100.0 [%] fuel)*

max range theoretically with additional fuel tanks total 167499 [litre] fuel : 13162

[km]*

* calculated ranges without fuel reserves

Available Seat Kilometres (ASK) : 3053508 [paskm]

useful load with range 1000km : 55451 [kg]

useful load with range 1000km : 380 passengers

production (theor.max load): 52956 [tonkm/hour]

production (useful load): 52956 [tonkm/hour]

production (passengers): 295645 [paskm/hour]

combi aircraft mail/freight/passengers

oil and fuel consumption per tonkm : 0.175 [kg]

calculation *11* (operating cost)

fuel cost per hour (11802 [litre]):7081 [eur] (25 [pax-km/litre fuel])

fuel cost per seat 1000km flight (310 [pax] 2-class seating): 23.95 [eur/1000PK]

oil cost per hour: 6 [eur]

crew cost per hour : 1650 [eur]

list price 2023 : 317 [mln USD]

average flying hours in 1 year : 3445 [hours] technical life : 17 [year]

real average service life : 17 [years]

depreciation - 17 [years] to 10% residual value

economic hours (expected total flying hours): 58565 [hours] is 0 [%] less then cor. design hours 58565 [hours]

financing interest per flying hour : 2071 [EUR]

write off per flying hour : 4497 [EUR]

time between engine failure : 16831 [hr]

can continue fly on 2 engines, low risk for emergency landing for PUF

workhours per day : 11.21 [hr]

average flight hours till crash : 0.53 [mln hr] (153 service years)

safe flight hours till fatality : 14641 [hr] (4.2 service years)

reservation pax liability/flying hour : 8.80 [SDR*] (11.00 [eur])

insurance cost per hour : 2769 [eur] insurance rate : 8.1 [%]

engine maintenance cost per hour : 1011.9 [eur]

wing maintenance cost per hour : 202.2 [eur]

fuselage maintenance cost per hour : 101.80 [eur]

tire life (time till worn out) : 93 [cycles]

maintenance cost per hour (excluding engines): 2564 [eur]

direct operating cost per hour: 21661 [eur], DOC per km : 23.91 [eur]

DOC per seat 1000km flight (310 [pax] 2-class seating): 73.27 [eur/1000PK]

DOC per seat 1000km flight (high density seating): 59.69 [eur/1000PK]

DOC per kg cargo for a 1000km flight : 0.41 [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 : 229.67 [eur/pax]

price retour ticket Schiphol-Barcelona : 269.97 [eur/pax]

accidents with fatalities > see the accident file

Martinair DC-10-30CF PH-MBT c/n 46985, starting operations with Martinair December 1978.

Literature :

McDonnell Douglas DC-10 - Wikipedia

https://contentzone.eurocontrol.int/aircraftperformance/default.aspx?

https://www.boeing.com/commercial/airports/plan-manuals

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

Federatieband C.J.V. Den Haag in front of a Martinair DC-10-30CF

(c) B van der Zalm 01 Januari 2024 contact : info.aircraftinvestigation@gmail.com ac jetpax 2020.py python 3.7.4

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