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weight and performance calculations for the McDonnel Douglas MD-83
***** PRELIMINARY FILE ****
ATA airlines MD-83 EP-TAR c/n 53198 at Tabriz airport (TBZ), Iran
McDonnel Douglas MD-83
role : jet airliner
importance : ****
first flight : 17 December 1984 operational : November 1985 (Finnair)
country : United States of America
design :
production : 265 aircraft
general information :
Has a longer range due to additional auxiliary fuel tanks in the cargo hold. Nov 14, 1985, the 1st MD-83 was handed over to Finnair. It was flown non-stop from Montreal to Helsinki in 6.43 hours, a distance of 6308 km. On arrival there was still 2700 kg of fuel left.
To cope with the higher operating weights, the MD-83 incorporates strengthened landing gear including new wheels, tires, and brakes, changes to the wing skins, front spar web and elevator spar cap, and strengthened floor beams and panels to carry the auxiliary fuel tanks.
primary users : Finnair, Alaska Airlines (delivered as MD-82 February 1985 later
re-engined and re-certified as MD-83), Spanair, American Airlines, Avianca, Crossair,
British Island Airways, Austrian
Accommodation:
flight crew : 2 cabin crew : 5
passengers : seating for 148 in two class : 12 business class and 136 economy class seats
( 32 -in pitch) exit limit : 172 passengers
engine : 2 Pratt & Whitney JT8D-219 turbofan engines of 93.0 [KN] (20906.9 [lbf])
dimensions :
wingspan : 32.89 [m], length : 45.05 [m], height : 8.97 [m]
wing area : 112.3 [m^2] fuselage exterior width : 3.34 [m]
weights :
operating empty weight : 36145 [kg] max. structural payload : 19193 [kg]
Zero Fuel weight (ZFW) : 55338 [kg] max. landing weight (MLW) : 63276 [kg]
max.take-off weight : 72575 [kg] weight fuel : 21141 [kg] (26426 [liter])
performance :
Max. operating Mach number (Mmo) : 0.83 [Mach] (927 [km/hr]) at 7620 [m]
normal cruise speed : 873 [km/hr] (Mach 0.80 ) at 9150 [m] (34 [%] power)
economic cruise speed : 830 [km/hr] (Mach 0.76 ) at 9150 [m]
service ceiling : 11278 [m]
range with max fuel : 4720 [km] (ATA domestic fuel reserves - 370.0 [km] alternate)
description :
low-wing cantilever monoplane with retractable landing gear with nose wheel
two main spar fail-safe wing structure
with double slotted flaps with full-span slotted LE flaps (slats) ,with spoilers
airfoil : NACA with supercritical cross-section sweep angle 3/4 chord: 24.5 [°]
engines attached to the tail, landing gear attached to the wings, fuel tanks in the wings
fuselage shape : 0 construction : all-metal aluminium-alloy stressed-skin construction
with pressurized fuselage
calculation : *1* (dimensions)
wing chord at root : 7.05 [m]
mean wing chord : 3.41 [m]
calculated average wing chord tapered wing with rounded tips: 3.39 [m]
wing aspect ratio : 9.63 []
seize (span*length*height) : 13291 [m^3]
calculation : *2* (fuel consumption)
oil consumption : 18.6 [kg/hr]
fuel consumption (econ. cruise speed) : 3447.3 [kg/hr] (4309.2 [litre/hr]) at 30 [%] power
distance flown for 1 kg fuel : 0.24 [km/kg] at 9150 [m] height, sfc : 61.0 [kg/KN/h]
total fuel capacity : 26426 [litre] (21141 [kg])
calculation : *3* (weight)
weight engine(s) dry : 4250.0 [kg] = 22.85 [kg/KN]
weight 156 litre oil tank : 13.29 [kg]
oil tank filled with 1.2 litre oil : 1.1 [kg]
oil in engine 2.3 litre oil : 2.0 [kg]
fuel in engine 10.2 litre fuel : 7.44 [kg]
weight fuel lines 42.7 [kg]
weight engine cowling 483.6 [kg]
weight thrust reversers 74.4 [kg]
total weight propulsion system : 4875 [kg](6.7 [%])
***************************************************************
Accommodation cabin facilities:
typical 2-class cabin layout for 148 passengers : economy : pitch : 81.3 [cm] 32.0 [-in]
( 3+2 ) seating in 30.2 rows
American Airlines MD-83 N597AA interior
weight seats : 775.0 [kg]
high density seating passengers : 169 [pax] at 5 -abreast seating in 33.7 rows,
pitch 73.7 [cm] 29.0 [-in]
pax density, normal seating : 0.63 [m2/pax], high density seating : 0.55 [m2/pax]
weight 3 lavatories : 47.9 [kg]
weight 2 galleys : 168.8 [kg]
weight overhead stowage for hand luggage : 51.8 [kg]
weight 3 wardrobe closets : 29.6 [kg]
weight 62 windows : 56.2 [kg]
weight 4 1.83x0.86 [m] entrance/exit doors : 162.3 [kg]
weight tail entrance stairs : 83.5 [kg]
weight 3 (134.6x127 cm) freight doors (belly) : 132.2 [kg]
belly baggage/cargo hold volume front : 12.34 [m3]
belly baggage/cargo hold volume middle : 10.60 [m3]
belly baggage/cargo hold volume rear : 12.52 [m3]
passenger compartment volume : 111 [m3]
passenger cabin max.width : 3.11 [m] cabin length : 30.78 [m] cabin height : 2.06 [m]
floor area : 92.8 [m2]
weight cabin facilities : 1423.7 [kg]
safety facilities:
weight 4 over wing emergency exits (91x51 cm): 77.3 [kg]
weight 7 hand fire extinguisher : 22 [kg]
weight cockpit voice recorder (CVR) and flight data recorder (FDR): 20.0 [kg]
weight oxygen masks & oxygen generators : 96.2 [kg]
weight emergency flare installation : 10 [kg]
weight 3 emergency evacuation slides : 84.3 [kg]
weight safety equipment & facilities : 394 [kg]
fuselage construction:
fuselage aluminium frame : 8252 [kg]
floor loading (payload/m2): 207 [kg/m2]
weight rear pressure bulkhead : 106.8 [kg]
fuselage covering ( 320.1 [m2] duraluminium 2.36 [mm]) : 1978.1 [kg]
weight floor beams : 344.4 [kg]
weight cabin furbishing : 682.6 [kg]
weight cabin floor : 1237.4 [kg]
fuselage (sound proof) isolation : 230.0 [kg]
weight empty waste tank : 15 [kg]
weight engine mounts : 93 [kg]
weight fuselage structure : 12939.3 [kg]
Avionics:
weight HF and UHF radio : 7.0 [kg]
weight dual cloud-collision radar : 25.0 [kg]
weight VOR/ILS,RMI,Doppler,radio altimeter : 12.0 [kg]
weight Integrated Flight System / auto-pilot : 23.0 [kg]
weight artificial horizons, compass, alti-meters : 7 [kg]
weight engine monitoring gauges & control switches : 6 [kg]
weight avionics : 80.0 [kg]
Systems:
Air-conditioning and pressurisation system maintains sea level conditions up to 5900 [m]
and gives equivalent of 2250 [m] at 10700 [m]. pressure differential : 0.54 [bars] (kg/cm2)
pressurized fuselage volume : 318 [m3]
weight air-conditioning and pressurisation system : 181 [kg]
weight APU / engine starter: 46.5 [kg]
weight lighting : 48.8 [kg]
weight engine-driven 40kVA electricity generators : 37.0 [kg]
weight controls : 18.2 [kg]
weight systems : 331.9 [kg]
total weight fuselage : 15168 [kg](20.9 [%])
***************************************************************
total weight aluminium ribs (1086 ribs) : 2588 [kg]
weight 7 fuel tanks empty for total 26426 [litre] fuel : 1480 [kg]
weight wing covering (painted aluminium 3.27 [mm]) : 1984 [kg]
total weight aluminium spars (multi-cellular wing structure) : 2005 [kg]
weight wings : 6577 [kg]
weight wing/square meter : 58.56 [kg]
weight thermal leading-edge anti-icing : 36.2 [kg]
Lion Air MD-83 PK-LMK interior
weight ailerons (3.5 [m2]) : 103.8 [kg]
weight fin (15.1 [m2]) : 884.6 [kg]
weight rudder (6.1 [m2]) : 171.5 [kg]
weight tailplane (stabilizer) (29.2 [m2]): 1200.0 [kg]
weight elevators (9.8 [m2]): 155.1 [kg]
weight flight control hydraulic servo actuators: 59.0 [kg]
weight trailing-edge double slotted flaps (19.6 [m2]) : 493.4 [kg]
weight leading edge slats (11.2 [m2]) : 183.4 [kg]
weight spoilers (3.2 [m2]) : 52.0 [kg]
total weight wing surfaces & bracing : 11395 [kg] (15.7 [%])
*******************************************************************
tyre pressure main wheels : 13.70 [Bar] (nitrogen), ply rating : 28 PR
tyre speed limit : 364 [km/hr]
Aircraft Classification Number, MTOW on rigid RW and medium subgrade strength : 47
Can only operate from paved runways
wheel pressure : 15966.5 [kg]
weight 4 Dunlop main wheels (1130 [mm] by 420 [mm]) : 858.0 [kg]
weight 2 nose wheels : 214.5 [kg]
weight multi-disc wheel-brakes : 55.3 [kg]
weight flywheel detector type anti-skid units : 5.4 [kg]
weight oleo-pneumatic shock absorbers : 73.8 [kg]
weight wheel hydraulic operated retraction system : 660.0 [kg]
weight undercarriage struts with axle 1400.0 [kg]
total weight landing gear : 3267.0 [kg] (4.5 [%]
*******************************************************************
********************************************************************
calculated empty weight : 34705 [kg](47.8 [%])
weight oil for 6.5 hours flying : 136.9 [kg]
weight lifejackets : 66.6 [kg]
weight 3 life rafts : 92.5 [kg]
weight catering : 281.4 [kg]
weight water : 225.1 [kg]
weight crew : 567 [kg]
weight crew lugage,nav.chards,flight doc.,miscell.items : 70 [kg]
operational weight empty : 36145 [kg] (49.8 [%])
********************************************************************
weight 148 passengers : 11396 [kg]
weight luggage : 2368 [kg]
weight cargo : 5429 [kg] (cargo+luggage/m3 belly : 203 [kg/m3])
zero fuel weight (ZFW): 55338 [kg](76.2 [%])
weight fuel for landing (2.3 hours flying) : 7938 [kg]
max. landing weight (MLW): 63276 [kg](87.2 [%])
max. fuel weight : 57286 [kg] (78.9 [%])
payload with max fuel : 164 passengers+luggage 15289 [kg]
published maximum take-off weight : 72575 [kg] (100.0 [%])
calculation : * 4 * (engine power)
power loading (Take-off) : 390 [kg/KN]
power loading (Take-off) 1 PUF: 780 [kg/KN]
max. total take-off power : 186.0 [KN]
calculation : *5* (loads)
manoeuvre load : 6.2 [g] at 1000 [m]
limit load : 3.0 [g] ultimate load : 4.5 [g] load factor : 0.9 [g]
design flight time : 3.80 [hours]
design cycles : 12468 sorties, design hours : 47407 [hours]
max. wing loading (MTOW & flaps retracted) : 646 [kg/m2]
wing stress (2 g) during operation : 202 [N/kg] at 2g emergency manoeuvre
Guiness Peat Aviation MD-83 EI-BTV c/n 49620 on Maastricht airport October 1990 after a promotional tour to the Soviet Union.
calculation : *6* (angles of attack)
angle of attack zero lift : -1.68 ["]
max. angle of attack (stalling angle, clean) : 13.29 ["]
max. angle of attack (full flaps) : 17.49 ["]
angle of attack at max. speed : 1.97 ["]
calculation : *7* (lift & drag ratios
lift coefficient at angle of attack 0° : 0.15 [ ]
lift coefficient at max. speed : 0.33 [ ]
lift coefficient at max. angle of attack : 1.34 [ ]
max. lift coefficient full flaps : 2.36 [ ]
drag coefficient at max. speed : 0.0373 [ ]
drag coefficient at econ. cruise speed : 0.0413 [ ]
induced drag coefficient at econ. cruise speed : 0.0087 [ ]
drag coefficient (zero lift) : 0.0326 [ ]
lift/drag ratio at max. speed : 8.74 [ ]
calculation : *8* (speeds
take-off safety speed (V2) : 268 [km/u]
take-off (initial climb) speed (Vto) : 319 [km/u]
stalling speed clean at sea-level (OW loaded : 69128 [kg]): 309 [km/u]
max. rate of climb speed : 510 [km/hr] at sea-level
max. endurance speed (Vbe): 631 [km/u] min. fuel/hr : 2813 [kg/hr] at height : 10058 [m]
max. range speed (Vbr): 862 [km/u] min. fuel consumption : 3.765 [kg/km] at cruise height : 10668 [m]
cruising speed : 873 [km/hr] at 9150 [m] (power:32 [%])
max. operational speed (Mmo) : 927.00 [km/hr] (Mach 0.83 ) at 7620 [m] (power:40.1 [%])
Avianca Colombia MD-83 EI-CBY c/n 49944
airflow at cruise speed per engine : 136.3 [kg/s]
speed of thrust jet : 1667 [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 : 63276 [kg]): 303 [km/u]
final approach speed at sea-level with full flaps (normal landing weight-Vapp):256 [km/u]
ICAO Aircraft Approach Category (APC) : C
landing speed at sea-level (normal landing weight(Vtd): 63023 [kg]): 226 [km/hr]
stalling speed at sea-level with full flaps (normal landing weight): 197 [km/u]
rate of climb at sea-level ROC (loaded) : 787 [m/min]
rate of climb at 1000 [m] with 1 engine out (PUF / MTOW) : 349 [m/min]
rate of descent: 457 [m/min]
calculation : *9* (regarding various performances)
high wheel pressure, can only take off from paved runways
take-off distance at sea-level concrete runway : 2925 [m]
Take-off runway length : 2450m at MTOW, sea level, standard day. Is less than calculated, needs more investigation
ICAO Aerodrome Reference Code : 4C
take-off distance at sea-level over 15 [m] height : 3087 [m]
landing run : 1089 [m]
Landing runway length at max.landing weight: 1400m, standard day, sea level, dry runway, full flaps 40°
landing run (C.A.R.) from 15 [m] at SL, dry runway : 1451 [m]
landing run (C.A.R.) from 15 [m] at SL, wet runway : 1751 [m]
lift/drag ratio : 13.19 [ ]
climb to 5000 [m] with max payload : 5.88 [min]
climb to 10000 [m] with max payload : 18.08 [min]
descent time from 10000 [m] to 250 [m] : 24.33 [min]
ceiling limited by max. pressure differential 12850 [m]
theoretical ceiling fully loaded (mtow- 60 min.fuel: 69128 [kg] ) : 15200 [m]
Aero lloyd MD-83 at Berlin Tegel airport
calculation *10* (action radius & endurance)
range with max. payload: 4095 [km] with 19193.0 [kg] max. useful load (81.5 [%] fuel)
range with high density pax: 4986 [km] with 169 passengers (98.1 [%] fuel)
range with typical two-class pax: 5143 [km] with 148 passengers (100.0 [%] fuel)
range with max.fuel : 5090 [km] with 7 crew and 164 passengers and 100.0 [%] fuel
ferry range : 5629 [km] with 2 crew and zero payload (100.0 [%] fuel)
max range theoretically with additional fuel tanks total 46676.8 [litre] fuel : 9479 [km]
Available Seat Kilometres (ASK) : 761119 [paskm]
useful load with range 1000km : 19193 [kg]
useful load with range 1000km : 169 passengers
production (theor.max load): 16755 [tonkm/hour]
production (useful load): 16755 [tonkm/hour]
production (passengers): 129204 [paskm/hour]
oil and fuel consumption per tonkm : 0.207 [kg]
fuel cost per paskm : 0.027 [eur]
crew cost per paskm : 0.007 [eur]
economic hours : 22300 [hours] is less then design hours
time between engine failure : 1012 [hr]
can continue fly on 1 engine, low risk for emergency landing for PUF
writing off per paskm : 0.010 [eur]
insurance per paskm : 0.0006 [eur]
maintenance cost per paskm : 0.015 [eur]
direct operating cost per paskm : 0.059 [eur]
direct operating cost per tonkm (max. load): 0.457 [eur]
direct operating cost per tonkm (normal useful load): 0.457 [eur]
Spanair MD-83 landing at Rotterdam Zestienhoven airport
4 accidents with fatalities > see the accident file
Literature :
McDonnell Douglas MD-80 - Wikipedia
https://contentzone.eurocontrol.int/aircraftperformance/default.aspx?
https://www.boeing.com/search/results.html?q=airplane+characteristics
Luchtvaart dec’89 page 353 - 359
Luchtvaart jan’90 page 378
Verkeersvliegtuigen page 66
McDonnell Douglas MD-80 (airwar.ru)
British Island Airways MD-83 G-BNSA c/n 49643
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 22 October 2022 contact : info.aircraftinvestigation@gmail.com python 3.7.4