JAL MD-90-30 JA8020 c/n 53360 taking off at Tokyo-Haneda apt., January 2011
McDonnell Douglas MD-90-30
JAL MD-90-30 JA8020 c/n 53360 taking off at Tokyo-Haneda apt., January 2011
McDonnell Douglas MD-90-30
role : medium-range jet airliner
importance : ****
first flight : 22 February 1993 operational : April 1995 (Delta Airlines)
country : United States of America
design :
production : 113 aircraft at Long Beach till 2000
general information :
Stretched derivative of the MD-80 family. First delivery February 1995 to Delta
Airlines. It competed with the Airbus A320 and Boeing 737-800. On 2 June 2020 Delta
Airlines flew the final MD-90 passenger flight.
primary users : Delta Airlines (50), JAL, Uni Air, Lion Air, Saudi Arabian Airlines (29), Blue1.com
Accommodation:
flight crew : 2 cabin crew : 5
passengers : seating for 153 in two class : 12 business class and 141 economy class
seats ( 32 -in pitch). high density seating for 172 passengers
engine : 2 IAE V2525-D5 turbofan engines of 111.2 [KN] (24998.3 [lbf])
dimensions :
wingspan : 32.86 [m], length : 46.51 [m], height : 9.33 [m]
wing area : 112.3 [m^2] fuselage exterior width : 3.34 [m]
weights :
operating empty weight : 39994 [kg] max. structural payload : 18973 [kg]
Zero Fuel weight (ZFW) : 58967 [kg] max. landing weight (MLW) : 64410 [kg]
max.take-off weight : 70760 [kg] weight fuel : 17683 [kg] (22104 [liter])
performance :
Max. operating Mach number (Mmo) : 0.85 [Mach] (937 [km/hr]) at 8303 [m]
normal cruise speed : 898 [km/hr] (Mach 0.84 ) at 10600 [m] (28 [%] power)
economic cruise speed : 812 [km/hr] (Mach 0.76 ) at 10600 [m]
service ceiling : 11278 [m]
range with max fuel : 3950 [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 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
calculation : *1* (dimensions)
measured wing chord : 6.85 [m] at root
mean wing chord : 3.42 [m]
calculated average wing chord tapered wing with rounded tips: 3.39 [m]
wing aspect ratio : 9.62 []
seize (span*length*height) : 14259 [m^3]
calculation : *2* (fuel consumption)
oil consumption : 6.7 [kg/hr]
fuel consumption (econ. cruise speed) : 3323.8 [kg/hr] (4154.7 [litre/hr])
at 27 [%] power
distance flown for 1 kg fuel : 0.24 [km/kg] at 10600 [m] height, sfc : 55.4 [kg/KN/h]
total fuel capacity : 22104 [litre] (17683 [kg])
calculation : *3* (weight)
weight engine(s) dry : 4800.0 [kg] = 21.58 [kg/KN]
weight 52 litre oil tank : 4.43 [kg]
oil tank filled with 1.4 litre oil : 1.3 [kg]
oil in engine 2.7 litre oil : 2.4 [kg]
fuel in engine 12.1 litre fuel : 8.90 [kg]
weight fuel lines 41.7 [kg]
weight engine cowling 578.2 [kg]
weight thrust reversers 333.6 [kg]
total weight propulsion system : 5771 [kg](8.2 [%])
***************************************************************
Accommodation cabin facilities:
typical 2-class cabin layout for 153 passengers : economy : pitch : 81.3 [cm] 32.0 [-in]
( 3+2 ) seating in 31.2 rows
weight seats : 800.0 [kg]
high density seating passengers : 172 [pax] at 5 -abreast seating in 34.5 rows,
pitch 73.7 [cm] 29.0 [-in]
pax density, normal seating : 0.63 [m2/pax], high density seating : 0.56 [m2/pax]
weight 3 lavatories : 46.7 [kg]
weight 2 galleys : 131.5 [kg]
JAL JA8029 interior
weight overhead stowage for hand luggage : 53.5 [kg]
weight 3 wardrobe closets : 30.6 [kg]
weight 64 windows : 58.0 [kg]
weight 4 1.83x0.86 [m] entrance/exit doors : 184.1 [kg]
weight ventral stairway : 83.5 [kg]
weight 3 (134.6x127 cm) freight doors (belly) : 150.0 [kg]
total belly baggage/cargo hold volume : 37.67 [m3]
passenger compartment volume : 116 [m3]
passenger cabin max.width : 3.11 [m] cabin length : 32.05 [m] cabin height : 2.06 [m]
floor area : 96.8 [m2]
weight cabin facilities : 1454.4 [kg]
safety facilities:
weight 4 over wing emergency exits (91x51 cm): 87.8 [kg]
weight 8 hand fire extinguisher : 23 [kg]
weight cockpit voice recorder (CVR) and flight data recorder (FDR): 20.0 [kg]
weight oxygen masks & oxygen generators : 99.5 [kg]
weight emergency flare installation : 10 [kg]
weight 3 emergency evacuation slides : 87.1 [kg]
weight safety equipment & facilities : 411 [kg]
fuselage construction:
fuselage aluminium frame : 9696 [kg]
floor loading (payload/m2): 196 [kg/m2]
weight rear pressure bulkhead : 121.0 [kg]
fuselage covering ( 331.5 [m2] duraluminium 2.68 [mm]) : 2320.0 [kg]
weight floor beams : 351.5 [kg]
weight cabin furbishing : 711.7 [kg]
weight cabin floor : 1333.6 [kg]
fuselage (sound proof) isolation : 238.2 [kg]
weight empty 70 [litre] potable water tank : 6.2 [kg]
weight empty waste tank : 15.3 [kg]
weight engine mounts : 111 [kg]
weight fuselage structure : 14904.6 [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 weather radar : 25.0 [kg]
weight VOR/ILS,RMI,DME,radio altimeter : 12.0 [kg]
weight Integrated Flight System / auto-pilot : 23.0 [kg]
Delta Airlines MD-90-30 cockpit
weight EFIS (CRT PFD+ND) : 8 [kg]
weight ground proximity warning system (GPWS) : 6 [kg]
weight engine monitoring system ECAM : 6 [kg]
weight avionics : 94.0 [kg]
Systems:
Air-conditioning and pressurization system maintains sea level conditions up to
6175 [m] and gives equivalent of 2250 [m] at 11200 [m]. pressure differential :
0.56 [bars] (kg/cm2). pressurized fuselage volume : 331 [m3]
weight air-conditioning and pressurization system : 191 [kg]
weight APU / engine starter: 55.6 [kg]
weight lighting : 50.5 [kg]
weight three independent 207 bar hydraulic systems : 47.5 [kg]
weight engine-driven 40kVA electricity generators : 38.2 [kg]
weight 22Ah battery : 12.0 [kg]
weight controls : 18.6 [kg]
weight systems : 413.1 [kg]
total weight fuselage : 17277 [kg](24.4 [%])
***************************************************************
total weight aluminium ribs (1058 ribs) : 2523 [kg]
weight 7 fuel tanks empty for total 22104 [litre] fuel : 1238 [kg]
weight wing covering (painted aluminium 3.72 [mm]) : 2256 [kg]
total weight aluminium spars (multi-cellular wing structure) : 2352 [kg]
weight wings : 7131 [kg]
weight wing/square meter : 63.50 [kg]
weight thermal leading-edge anti-icing : 36.1 [kg]
weight ailerons (5.3 [m2]) : 168.4 [kg]
weight fin (33.0 [m2]) : 1364.1 [kg]
weight rudder (6.1 [m2]) : 185.6 [kg]
weight tailplane (stabilizer) (24.8 [m2]): 869.8 [kg]
weight elevators (6.3 [m2]): 108.9 [kg]
weight flight control hydraulic servo actuators: 23.8 [kg]
weight trailing-edge double slotted flaps (19.6 [m2]) : 534.6 [kg]
weight leading edge slats (11.2 [m2]) : 198.6 [kg]
weight spoilers (3.2 [m2]) : 55.8 [kg]
total weight wing surfaces & bracing : 11915 [kg] (16.8 [%])
*******************************************************************
tire pressure main wheels : 13.40 [Bar] (nitrogen), ply rating : 26 PR
tire speed limit : 364 [km/hr]
total tyre footprint : 0.28 [m2]
Aircraft Classification Number, MTOW on rigid runway and medium subgrade
strength (B) : 48 [ ]
Can also operate from unpaved runways subgrade B
wheel pressure : 15567.2 [kg]
weight 4 Dunlop main wheels (1130 [mm] by 420 [mm]) : 755.0 [kg]
weight 2 nose wheels : 188.7 [kg]
weight multi-disc wheel-brakes : 59.0 [kg]
weight flywheel detector type anti-skid units : 5.4 [kg]
weight oleo-pneumatic shock absorbers : 78.6 [kg]
weight wheel hydraulic operated retraction system : 820.4 [kg]
weight undercarriage struts with axle 2154.0 [kg]
total weight landing gear : 4061.2 [kg] (5.7 [%]
*******************************************************************
********************************************************************
calculated empty weight : 39023 [kg](55.1 [%])
weight oil for 5.3 hours flying : 42.6 [kg]
weight lifejackets : 68.9 [kg]
weight 3 life rafts : 95.6 [kg]
weight catering : 77.3 [kg]
weight water : 61.9 [kg]
weight crew : 567 [kg]
weight crew lugage,nav.chards,flight doc.,miscell.items : 57 [kg]
operational weight empty : 39994 [kg] (56.5 [%])
********************************************************************
weight 153 passengers : 11781 [kg]
weight luggage : 2448 [kg]
weight cargo : 4744 [kg] (cargo+luggage/m3 belly : 175 [kg/m3])
zero fuel weight (ZFW): 58967 [kg](83.3 [%])
weight fuel for landing (1.6 hours flying) : 5443 [kg]
max. landing weight (MLW): 64410 [kg](91.0 [%])
max. fuel weight : 57677 [kg] (81.5 [%])
payload with max fuel : 141 passengers+luggage 13083 [kg]
published maximum take-off weight : 70760 [kg] (100.0 [%])
calculation : * 4 * (engine power)
power loading (Take-off) : 318 [kg/KN]
power loading (Take-off) 1 PUF: 636 [kg/KN]
max. total take-off power : 222.4 [KN]
calculation : *5* (loads)
manoeuvre load : 5.3 [g] at 1000 [m]
limit load : 3.0 [g] ultimate load : 4.5 [g] load factor : 1.1 [g]
design flight time : 1.01 [hours]
design cycles : 37461 sorties, design hours : 37867 [hours]
max. wing loading (MTOW & flaps retracted) : 630 [kg/m2]
wing stress (2 g) during operation : 186 [N/kg] at 2g emergency manoeuvre
Delta Airlines MD-90-30 N908DA
calculation : *6* (angles of attack)
angle of attack zero lift : -1.68 ["]
max. angle of attack (stalling angle, clean) : 12.07 ["]
max. angle of attack (full flaps) : 16.27 ["]
angle of attack at max. speed : 2.17 ["]
calculation : *7* (lift & drag ratios
lift coefficient at angle of attack 0° : 0.15 [ ]
lift coefficient at max. speed : 0.34 [ ]
lift coefficient at max. angle of attack : 1.23 [ ]
max. lift coefficient full flaps : 2.24 [ ]
drag coefficient at max. speed : 0.0465 [ ]
drag coefficient at econ. cruise speed : 0.0549 [ ]
induced drag coefficient at econ. cruise speed : 0.0136 [ ]
drag coefficient (zero lift) : 0.0412 [ ]
lift/drag ratio at max. speed : 7.40 [ ]
calculation : *8* (speeds
take-off safety speed (V2) : 275 [km/u]
take-off (initial climb) speed (Vto) : 325 [km/u]
stalling speed clean at sea-level (OW loaded : 67436 [kg]): 319 [km/u]
max. rate of climb speed : 493 [km/hr] at sea-level
max. endurance speed (Vbe): 427 [km/u] min. fuel/hr : 2871 [kg/hr] at height : 4267 [m]
max. range speed (Vbr): 814 [km/u] min. fuel consumption : 4.076 [kg/km] at cruise
height : 10668 [m]
cruising speed : 898 [km/hr] at 10600 [m] (power:30 [%])
max. operational speed (Mmo) : 937 [km/hr] (Mach 0.85 ) at 8303 [m] (power:39.6 [%])
airflow at cruise speed per engine : 194.4 [kg/s]
speed of thrust jet : 1521 [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 : 64410 [kg]): 319 [km/u]
final approach speed at sea-level with full flaps (MLW) (Vapp): 266 [km/u]
ICAO Aircraft Approach Category (APC) : D
landing speed at sea-level (normal landing weight(Vtd): 64340 [kg]): 235 [km/hr]
stalling speed at sea-level with full flaps (max. landing weight): 204 [km/u]
rate of climb at sea-level ROC (loaded) : 946 [m/min]
rate of climb at 1000 [m] with 1 engine out (PUF / MTOW) : 465 [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 : 1595 [m]
take-off distance at sea-level over 15 [m] height : 1726 [m]
balanced runway length at MTOW and at SL (FAR) : 3042 [m]
landing run (MLW) : 1036 [m]
landing run (C.A.R.) from 15 [m] at SL, dry runway : 1485 [m]
landing run (C.A.R.) from 15 [m] at SL, wet runway : 1785 [m]
lift/drag ratio : 11.72 [ ]
climb to 5000 [m] with max payload : 4.89 [min]
climb to 10000 [m] with max payload : 15.05 [min]
descent time from 10000 [m] to 250 [m] : 24.33 [min]
ceiling limited by max. pressure differential 13525 [m]
theoretical ceiling fully loaded (mtow- 60 min.fuel: 67436 [kg] ) : 15100 [m]
calculation *10* (action radius & endurance)
range with max. payload: 2813 [km] with 18973.0 [kg] max. useful load (66.7 [%] fuel)*
range with high density pax: 3556 [km] with 172 passengers (83.3 [%] fuel)*
2200 nm = 4075 km range with max. fuel and 13000 kg payload (200 nm = 370 km FAR 121.639 reserves) =
range with typical two-class pax: 4021 [km] with 153 passengers (93.5 [%] fuel)*
range with max.fuel : 4320 [km] with 7 crew and 141 passengers and 100.0 [%] fuel*
ferry range : 4785 [km] with 2 crew and zero payload (100.0 [%] fuel)*
max range theoretically with additional fuel tanks total 39137 [litre] fuel : 8065 [km] *
* calculated ranges without fuel reserves
Available Seat Kilometres (ASK) : 616165 [paskm]
useful load with range 1000km : 18973 [kg]
useful load with range 1000km : 172 passengers
production (theor.max load): 17038 [tonkm/hour]
production (useful load): 17038 [tonkm/hour]
production (passengers): 147298 [paskm/hour]
oil and fuel consumption per tonkm : 0.195 [kg]
calculation *11* (operating cost)
fuel cost per hour (4155 [litre]):2493 [eur] (35 [pax-km/litre fuel])
fuel cost per seat 1000km flight (164 [pax] 2-class seating): 16.92 [eur/1000PK]
oil cost per hour: 28 [eur]
crew cost per hour : 900.000 [eur]
list price 2023 : 103 [mln USD]
average flying hours in 1 year : 1600 [hours] technical life : 24 [year]
economic hours : 37867 [hours] is limited by technical life
financing interest per flying hour : 1508 [EUR]
write off per flying hour : 2353 [EUR]
time between engine failure : 836 [hr]
can continue fly on 1 engine, low risk for emergency landing for PUF
safe flight hours till fatality : 4520000 [hr] (2825 service years)
reservation pax liability/flying hour : 0.03 [SDR*] (0.04 [eur])
insurance cost per hour : 34 [eur]
engine maintenance cost per hour : 897 [eur]
maintenance cost per hour (excluding engines): 2093 [eur]
direct operating cost per hour: 10305 [eur]
DOC per seat 1000km flight (164 [pax] 2-class seating): 69.96 [eur/1000PK]
DOC per seat 1000km flight (high density seating): 66.55 [eur/1000PK]
DOC per kg cargo for a 1000km flight : 0.60 [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 : 2.58 [eur/pax]
airport landing fee / passenger : 2.58 [eur/pax]
retour ticket price 1000km trip : 212.37 [eur/pax]
price retour ticket Schiphol-Barcelona : 250.85 [eur/pax]
Uni Air MD-90-30 B-17926
accidents with fatalities > see the accident file
Only 1 passenger died on an MD-90 and that was not an aeronautical accident.
Literature :
McDonnell Douglas MD-90 - Wikipedia
https://contentzone.eurocontrol.int/aircraftperformance/default.aspx?
https://www.boeing.com/search/results.html?q=airplane+characteristics
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 14 April 2022 contact : info.aircraftinvestigation@gmail.com python 3.7.4
notes :
*SDR = special drawing rights info : https://www.citizensinformation.ie/en/travel_and_recreation/air_travel/airline_liability.html