Cubana operated a few Il-96’s, coming in here is CU-T1251 c/n 74393302016 at sunset
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weight and performance calculations for the Ilyushin Il-96-300
Cubana operated a few Il-96’s, coming in here is CU-T1251 c/n 74393302016 at sunset
Ilyushin Il-96-300
role : wide-body airliner
importance : **
first flight : 28 September 1988 (SSSR-96000 at Khodinka) operational : July 1993
country : Russia
ICAO aircraft type designator : IL96
production : 33 aircraft
general information :
More advanced successor to the Il-86. With FBW and more fuel-efficient turbofans.
Designed for 12.000 cycles and 60.000 hrs.
primary users : Aeroflot, Cubana
Accommodation:
flight crew : 3 cabin crew : 10
flight crew consist of pilot, co-pilot and flight engineer*
*cockpit has been designed for two man flight crew but an extra seat has been maintained
for a flight engineer
passengers : seating for 263 in two class : 62 business class and 201 coach class seats
( 34 -in pitch) high density seating for 300 passengers
engine : 4 Aviadvigatel PS-90A turbofan engines of 156.9 [KN] (35272 [lbf])
dimensions :
wingspan : 60.12 [m], length overall: 55.35 [m], length of fuselage : 51.15 [m]
height : 17.55 [m] wing area gross : 391.6 [m^2] fuselage exterior width : 6.08 [m]
weights :
operating empty weight : 117000 [kg] max. structural payload : 40000 [kg]
Zero Fuel weight (ZFW) : 157000 [kg] max. landing weight (MLW) : 174950 [kg]
max. take-off weight : 250000 [kg] weight usable fuel : 119807 [kg] (152620 [litres])
performance :
Max. operating Mach number (Mmo) : 0.89 [Mach] (950 [km/hr]) at 10670 [m]
critical Mach speed : 0.83 [Mach]
max. cruising speed : 900 [km/hr] (Mach 0.85 ) at 10670 [m] (37 [%] power)
economic cruising speed : 871 [km/hr] (Mach 0.82 ) at 10670 [m]
service ceiling : 13100 [m]
range with max fuel and MTOW : 10000 [km] (ATA domestic fuel reserves - 820.0 [km]
alternate)
description :
cantilever low-wing monoplane with retractable landing gear with nose wheel
engines attached with pylons to the wing, main landing gear attached to the wings, fuel
tanks in the wings and fuselage
Wings : tapered multi-cellular fail safe wing with aluminium alloy stressed skin with
Fowler-type double slotted trailing edge flaps on inner wing and single-slotted flap on
outer wing with full-span slotted LE flaps (slats) ,with spoilers and with winglets
airfoil : Ilyushin average thickness/chord ratio : 10.0 [%], sweep angle 3/4 chord: 30.0 [°]
incidence : 3.00 [°], dihedral : 7.0 [°]
Fuselage : Pressurized conventional semi-monocoque fail safe structure of circular cross-
section built mainly of high-strength aluminium alloy
Il-96-300 prototype CCCP-96000 at Sheremetyevo airport, September 1990. The aircraft visited the Paris Air Salon in 1989, and still wears the Salon registration nr. 386
calculation : *1* (dimensions)
measured wing chord at root: 11.56 [m]
measured wing chord at tip : 3.16 [m]
taper ratio : 0.273 [ ]
mean wing chord : 6.51 [m]
wing aspect ratio : 9.23 []
Oswald factor (e): 0.700 []
seize (span*length*height) : 58400 [m^3]
calculation : *2* (fuel consumption)
oil consumption : 22.0 [kg/hr]
fuel consumption (econ. cruise speed) : 9644.3 [kg/hr] (12285.8 [litre/hr]) at 26 [%] power
distance flown for 1 kg fuel : 0.09 [km/kg] at 10670 [m] height, sfc : 59.5 [kg/KN/h]
total fuel capacity : 152620 [litre] (119807 [kg])
calculation : *3* (weight)
weight engine(s) dry : 11700.0 [kg] = 18.64 [kg/KN]
weight 377.9 litre oil tank : 32.12 [kg]
oil tank filled with 4.0 litre oil : 3.5 [kg]
oil in engine 7.7 litre oil : 6.9 [kg]
weight all fuel lines and pumps containing 126 litres fuel : 288.8 [kg]
weight engine cowling : 1631.8 [kg]
weight thrust reversers : 941.4 [kg]
total weight propulsion system : 14605 [kg](5.8 [%])
***************************************************************
Accommodation cabin facilities:
typical 2-class cabin layout for 263 passengers : economy : pitch : 87.0 [cm] 34.2 [-in]
( 3+3+3) seating in 31.2 rows
weight passenger seats : 1454.9 [kg]
weight cabin crew seats : 50.0 [kg]
weight flight crew seats : 63.0 [kg]
weight 2 jump seats in the cockpit :14.0 [kg]
high density seating passengers : 300 [pax] at mainly 9 -abreast seating in 34.5 rows, pitch
86.8 [cm] 34.2 [-in]
pax density, normal seating : 0.86 [m2/pax], high density seating : 0.76 [m2/pax]
passenger cabin luxurious spaced for good service, enough space for galleys and toilets even
at HD seating
weight 8 lavatories : 239.8 [kg]
weight 8 galleys : 710.1 [kg]
Interior of Kras Air Il-96-300 RA-96017
weight overhead stowage for hand luggage : 92.0 [kg]
weight 3 wardrobe closets : 26.3 [kg]
weight 10 video screens : 183.1 [kg]
weight 64 windows (41 x 28 cm) made of acrylic glass : 175.9 [kg]
weight 6 (1.83 x 1.07 [m]) Type A main entry doors : 403.4 [kg]
weight 3 (main door size : 1.82 x 1.78 [m]) freight doors (belly) : 315.3 [kg]*
total belly baggage/cargo hold volume : 118.4 [m3]
underfloor belly hold can accommodate : 16 ABK-1.5 containers, netto volume : 84.5 [m3]
and : 15.0 [m3] bulk cargo
cabin volume (usable), excluding flight deck : 468 [m3]
passenger compartment volume : 350 [m3]
passenger cabin max width : 5.70 [m] cabin length : 40.48 [m] max cabin height : 2.61 [m]
floor area : 227.0 [m2]
weight cabin facilities : 4087.8 [kg]
safety facilities:
evacuation time with 300 passengers : 51 [sec]
weight 12 hand fire extinguisher : 37 [kg]
weight cockpit voice recorder (CVR) and flight data recorder (FDR): 20.0 [kg]
weight oxygen masks & oxygen generators (deploy cabin alt.>4267m): 171.0 [kg]
weight emergency flare installation : 10 [kg]
weight 6 emergency evacuation slides : 363.4 [kg]
weight safety equipment & facilities : 602 [kg]
fuselage construction:
fuselage aluminium frame : 24139 [kg]
floor loading (payload/m2): 176 [kg/m2]
weight rear pressure bulkhead : 507.7 [kg]
fuselage covering ( 808.4 [m2] duraluminium 3.35 [mm]) : 7234.5 [kg]
weight floor beams : 3650.3 [kg]
weight cabin furbishing : 3647.3 [kg]
weight cabin floor : 3526.5 [kg]
weight (sound proof) isolation : 677.2 [kg] TO-noise level : 99.2 [EPNdB]
weight 47867 [litre] main central fuel tanks empty : 957.3 [kg]
weight empty 1022 [litre] potable water tanks : 90.5 [kg]
weight empty waste tank : 30.1 [kg]
weight fuselage structure : 44460.3 [kg]
Avionics:
weight VHF radio and Selcal : 9.0 [kg]
weight flight and service attendants intercom : 5.0 [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]
weight Triplex flight control and FMS, with head-up-display : 15 [kg]
weight CAT IIIa auto-landing system : 10.0 [kg]
weight EFIS (4 Rockwell Collins CRT screens ADI/PFD+HSI/ND displays) : 20 [kg]
weight engine monitoring system ECAM : 30 [kg]
weight reserve ADI, ASI, alti-meter, compass, engine temp. and rpm indicators : 15 [kg]
weight avionics : 165.0 [kg]
Systems:
Air-conditioning and pressurization system maintains sea level conditions up to 7350 [m]
and gives equivalent of 2100 [m] at 13000 [m]. pressure differential : 0.63 [bar] (kg/cm2)
pressurized fuselage volume : 894 [m3] cabin air refreshment time : 3.5 [min]
weight air-conditioning and pressurization system : 439 [kg]
weight APU / engine starter : 78.5 [kg]
weight lighting : 86.8 [kg]
weight four independent 207 bar hydraulic systems : 197.5 [kg]
weight three engine-driven 90kVA 400 Hertz electricity generators : 65.8 [kg]
weight integrated drive generator (IDG) : 25 [kg]
weight ram air turbine for emergency electric power : 5.0 [kg]
weight three 24V 25Ah nickel-cadmium batteries : 37.0 [kg]
weight controls : 23.3 [kg]
weight systems : 952.9 [kg]
total weight fuselage : 50268 [kg](20.1 [%])
***************************************************************
total weight aluminium ribs (1823 ribs) : 8289 [kg]
weight engine mounts : 314 [kg]
weight 4 wing fuel tanks empty for total 104753 [litre] fuel : 1571 [kg]
weight 610 [litre] vent surge tanks : 73 [kg]
weight wing covering (painted aluminium 3.84 [mm]) : 8123 [kg]
total weight aluminium spars (multi-cellular wing structure) : 10645 [kg]
weight wings : 27056 [kg]
weight wing/square meter : 69.09 [kg]
weight thermal leading-edge anti-icing : 66.1 [kg]
weight high & low speed ailerons (22.75 [m2]) : 630.1 [kg]
weight fin (38.08 [m2]) : 1318.4 [kg]
weight rudder (23.27 [m2]) : 773.3 [kg]
weight tailplane (stabilizer) (78.77 [m2]): 2999.8 [kg]
weight elevators (17.96 [m2]): 335.76 [kg]
weight flight control hydraulic servo actuators: 97.3 [kg]
weight trailing-edge double + single slotted flaps (28.87 [m2]) : 852.8 [kg]
weight track-mounted light alloy construction leading edge slats (37.46 [m2]) : 693.5 [kg]
weight spoilers made of CFRP (13.9 [m2]) : 210.9 [kg]
weight winglets : 200 [kg]
total weight wing construction : 37192 [kg] (31.8 [%])
*******************************************************************
tire pressure main wheels : 11.65 [Bar] (nitrogen), ply rating : 23 PR
tire speed limit : 364 [km/hr]
total tyre footprint : 1.27 [m2]
Runway LCN at MTOW (0.76m radius of rigidity) : 51 [ ]
Aircraft Classification Number (ACN), MTOW on rigid runway and medium subgrade
strength (B) : 29 [ ] Can also operate from unpaved runways subgrade B
wheel pressure : 18333.3 [kg]
wheel track : 10.40 [m] wheelbase : 20.07 [m]
weight 12 main wheels (1300 [mm] by 477 [mm]) : 1587.8 [kg]
weight 2 nose wheels : 132.3 [kg]
weight hydraulic disc wheel-brakes : 157.0 [kg]
weight Duplex anti-skid units : 12.6 [kg]
weight oleo-pneumatic shock absorbers : 209.3 [kg]
weight wheel hydraulic operated retraction system : 2197.5 [kg]
weight undercarriage struts (six-wheel bogies) with axle 6581.3 [kg]
total weight landing gear : 10877.9 [kg] (4.4 [%]
*******************************************************************
Aeroflot Il-96-300 RA-96008
********************************************************************
calculated empty weight : 112942 [kg](45.2 [%])
weight oil for 13.3 hours flying : 327.4 [kg]
unusable fuel in engine and tanks 933.3 litre fuel : 732.6 [kg]
weight lifejackets : 118.4 [kg]
weight 5 life rafts : 164.4 [kg]
weight catering : 657.5 [kg]
weight water : 904.7 [kg]
weight crew : 1053 [kg]
weight crew luggage, nav. chards, flight doc., miscell. items : 100 [kg]
operational weight empty : 117000 [kg] (46.8 [%])
********************************************************************
Kras Air Il-96-300
weight 263 passengers : 20251 [kg]
weight luggage : 4208 [kg]
weight cargo : 15541 [kg] (cargo + luggage/m3 belly : 158 [kg/m3])
zero fuel weight (ZFW): 157000 [kg](62.8 [%])
weight fuel for landing (1.9 hours flying) : 17950 [kg]
max. landing weight (MLW): 174950 [kg](70.0 [%])
max. fuel weight : 236807 [kg] (94.7 [%])
payload with max fuel : 142 passengers + luggage 13193 [kg]
published maximum take-off weight : 250000 [kg] (100.0 [%])
calculation : * 4 * (engine power)
power loading (Take-off) : 398 [kg/KN]
power loading (Take-off) 1 PUF: 531 [kg/KN]
max. total take-off power : 627.6 [KN]
calculation : *5* (loads)
manoeuvre load : 1.1 [g] at 9000 [m]
limit load : 2.5 [g] ultimate load : 3.8 [g] load factor : 1.1 [g]
design flight time : 5.00 [hours]
design cycles : 13230 sorties, design hours : 66150 [hours]
max. wing loading (MTOW & flaps retracted) : 638 [kg/m2]
wing stress (2 g) during operation : 154 [N/kg] at 2g emergency manoeuvre
calculation : *6* (angles of attack)
angle of attack zero lift : -1.70 ["]
max. angle of attack (stalling angle, clean) : 12.49 ["]
max. angle of attack (full flaps) : 16.44 ["]
angle of attack at economic cruise speed : 3.15 ["]
calculation : *7* (lift & drag ratios)
lift coefficient at angle of attack 0° : 0.15 [ ]
lift coefficient at max. speed : 0.40 [ ]
lift coefficient at max. angle of attack (clean): 1.25 [ ]
max. lift coefficient full flaps : 1.97 [ ]
drag coefficient at max. speed : 0.0427 [ ]
drag coefficient at econ. cruise speed : 0.0373 [ ]
induced drag coefficient at econ. cruise speed : 0.0091 [ ]
drag coefficient (zero lift) : 0.0282 [ ]
lift/drag ratio at econ. speed : 9.42 [ ]
calculation : *8* (speeds
take-off decision speed (V1) : 257 [km/u] (139 [kt])
take-off rotation speed (VR) : 281 [km/u] (152 [kt])
minimum unstick speed (Vmu) at TO angle 12.0 ° : 287 [km/u] (155 [kt])
lift-off speed (VLOF) : 315 [km/u] (170 [kt]) at pitch angle : 10.0 [°]
take-off safety speed (V2) : 318 [km/u] (172 [kt])
flap retraction speed (V3) at 500m (OW loaded : 240356 [kg]): 343 [km/u] (185 [kt])
steady initial climb speed (V4) : 344 [km/u] (186 [kt])
climb speed (to FL150 with 63 [%] power) : 529 [km/hr] (285 [kt])
max. endurance speed (Vbe): 668 [km/u] min. fuel/hr : 8273 [kg/hr] at height : 10973 [m]
max. range speed (Vbr): 862 [km/u] (0.82 [mach]) min. fuel consumption : 10.50 [kg/km] at
cruise height : 11582 [m]
max. cruising speed : 900 [km/hr] (486 [kt]) at 10670 [m] (power:28 [%])
max. operational speed (Mmo) : 950 [km/hr] (Mach 0.89 ) at 10670 [m] (power:34 [%])
airflow at cruise speed per engine : 269.0 [kg/s]
speed of thrust jet : 1495 [km/hr]
initial descent speed 10000 - 7315 [m]: Mach 0.72
descent speed 7315 - 3048 [m]: 537 [km/u] (290 [kt]) 
approach speed 3048 - 500 [m] (clean): 463 [km/u] (250 [kt])
minimum control speed (MCS) Vmca (clean): 306 [km/u] (165 [kt])
stalling speed clean at 500 [m] height at Max.Landing Weight : 174950 [kg]): 278 [km/u]
(150 [kt])
final approach speed (landing speed) at sea-level with full flaps VREF (max. landing weight):
265 [km/u] (143 [kt])
ICAO Aircraft Approach Category (APC) : D
stalling speed at sea-level with full flaps VSO (max. landing weight): 204 [km/u] (110 [kt]
rate of climb at sea-level ROC (loaded, 63 % power) : 883 [m/min]
rate of climb at sea-level ROC (loaded, 75 % power) : 1210 [m/min]
rate of climb at 1000 [m] with 1 engine out (PUF/MTOW, 100 % power on remaining
engines) : 980 [m/min]
can not stay on height 1000 [m] with 2 engines out, immediate emergency landing needed
rate of descent from FL240 to FL100 (7315m > 3048m): 914 [m/min] (2999 [ft/min])
rate of descent during approach with landing gear extended, with use of spoilers: 457
[m/min] (8 [m/s])
calculation : *9* (regarding various performances)
low wheel pressure, can also take off from unpaved runways
take-off distance at sea-level gravel/packed earth field : 3064 [m]
ICAO Aerodrome Reference Code : 4E
Brake kinetic energy capacity : 2654 [KW]
FAR TO balanced runway length (TOFL) requirement at TOW 250000 [kg] standard day
at SL (distance to 10.7m height x 1.15): 2936 [m]
+++ FAA certification landing distance : +++
landing weight : 174950 [kg], TE flap setting : 30 [°]
runway condition : dry , landing over 50ft (15m) at threshold at sea-level
without use of thrust reversers
FAA approved landing field length : 1984 [m] (6510 [ft])
landing distance (C.A.R.) from 15 [m] at SL, wet runway: 2278 [m] (7473 [ft])
max. lift/drag ratio : 13.41 [ ]
climb to 5000 [m] with max payload : 5.24 [min]
climb to 10000 [m] with max payload : 16.13 [min]
descent time from 10000 [m] to 250 [m] : 24.33 [min]
ceiling limited by max. pressure differential 17025 [m]
theoretical ceiling fully loaded (mtow- 60 min.fuel: 240356 [kg] ) : 15600 [m]
calculation *10* (action radius & endurance)
range with max. payload: 8111 [km] with 40000.0 [kg] max. useful load (77.6 [%] fuel)*
range with high density pax: 9313 [km] with 300 passengers (87.7 [%] fuel)*
range with typical two-class pax: 9661 [km] with 263 passengers (90.6 [%] fuel)*
IL-96M RA-96000 prototype, this version is stretched with 10m, and has PW2337 engines. Range with 312 passengers is 10400 km. But politics blocked further development.
range with max.fuel : 10820 [km] with 13 crew and 142 passengers and 100.0 [%] fuel*
ferry range (calculated): 11249 [km] with 3 crew and zero payload (100.0 [%] fuel)*
max range theoretically with additional fuel tanks total 172449 [litre] fuel : 12469 [km]*
* calculated ranges without fuel reserves
Available Seat Kilometres (ASK) : 2743827 [paskm]
useful load with range 1000km : 40000 [kg]
useful load with range 1000km : 300 passengers
production (theor.max load): 36000 [tonkm/hour]
production (useful load): 36000 [tonkm/hour]
production (passengers): 261877 [paskm/hour]
oil and fuel consumption per tonkm : 0.269 [kg]
calculation *11* (operating cost)
fuel cost per hour (12286 [litre]):7371 [eur] (21 [pax-km/litre fuel])
fuel cost per seat 1000km flight (291 [pax] 2-class seating): 28.15 [eur/1000PK]
oil cost per hour: 91 [eur]
crew cost per hour : 1800 [eur]
list price 2024 : 110 [mln USD]
average flying hours in 1 year : 2800 [hours] technical life : 24 [year]
real average service life : 20 [years]
depreciation - 20 [years] to 10% residual value
Aeroflot Il-96-300 RA-96008 c/n 74393201005
economic hours (expected total flying hours): 56000 [hours] is 0 [%] less then cor. design
hours 56000 [hours]
financing interest per flying hour : 887 [EUR]
write off per flying hour : 1638 [EUR]
time between engine failure : 6364 [hr]
can continue fly on 3 engines, low risk for emergency landing for PUF
workhours per day : 8.82 [hr]
no fatalities during service life > 100%% safe
average flight hours till crash : 2.07 [mln hr] (740 service years)
safe flight hours till fatality : 2072000 [hr] (740.0 service years)
reservation pax liability/flying hour : 0.06 [SDR*] (0.08 [eur])
insurance cost per hour : 245 [eur] insurance rate : 1.7 [%]
engine maintenance cost per hour : 1204.5 [eur]
wing maintenance cost per hour : 172.3 [eur]
fuselage maintenance cost per hour : 64.67 [eur]
tire life (time till worn out) : 79 [cycles]
maintenance cost per hour (excluding engines): 1970 [eur]
direct operating cost per hour: 15207 [eur], DOC per km : 17.46 [eur]
DOC per seat 1000km flight (291 [pax] 2-class seating): 58.07 [eur/1000PK]
DOC per seat 1000km flight (high density seating): 56.32 [eur/1000PK]
DOC per kg cargo for a 1000km flight : 0.42 [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 : 6.04 [eur/pax]
airport landing fee / passenger : 6.04 [eur/pax]
retour ticket price 1000km trip : 201.46 [eur/pax]
price retour ticket Schiphol-Barcelona : 233.40 [eur/pax]
RA-96010 on fire at Sheremetyevo Airport (SVO), Moscow, 3 June 2014. While parked a fire broke out in the cockpit. There were no casualties but the aircraft was destroyed by the fire.
accidents with fatalities > there have been no fatal accidents with an Ilyushin Il-96-300
Literature :
https://contentzone.eurocontrol.int/aircraftperformance/default.aspx ?
Air International page 203 Jane’s all the world aircraft 2000-2001 page 375,376
Jane’s all the world aircraft 1991-92 page 246,247
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 03 June 2024 contact : info.aircraftinvestigation@gmail.com ac jetpax 2020.py python 3.7.4
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