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weight and performance calculations for the Lockheed L1011-500 Tristar
Air Portugal L1011-500 CS-TEF taking off from Lisbon apt., 1988
Lockheed L1011-500 Tristar
role : wide-body airliner
importance : ****
first flight : 16 October 1978 operational : May 1979 (British Airways)
country : United States of America
production : 47 aircraft at Burbank
general information :
After the -200, Lockheed studied an extended version, designated the -300. But there was too little interest in it and this version was never built. There was interest in a long-distance version. Two tanks were installed in the centre section which gave an additional 24500 litres of fuel capacity. The fuselage was shortened by 4.10 [m] and the wingspan increased by 2.74 []. This version was given the designation L1011-500. It was given an active operating system in combination with an FMS. This system keeps the aircraft at the most favourable cruising speed, which results in significant fuel savings. The -250 is a version with the length of the -200 but with the fuel content of the -500. The RAF has taken 6 ex-British airways and 3 ex-Pan Am Tristars into service as tanker/transport aircraft. In 1984 the 250th and last Tristar rolled off the production line. Despite the fact that it was a good aircraft, according to many better than the DC-10 and certainly safer, it never became a great sales success. It was Lockheed's last airliner. In September 1993, 214 Tristars were still flying for 25 airlines.
The L1011-500 does not have the underfloor galleys anymore, all galleys are on the main deck.
primary users : British Airways (6), Delta, Pan Am (12), Air Lanka, Aeroperu, BWIA,
Air Canada, LTU (Germany), TAP/Air Portugal
Accommodation:
flight crew : 3 cabin crew : 8
flight crew consist of pilot, co-pilot and flight engineer
passengers : seating for 248 in two class : 26 business class and 222 economy
deluxe class seats ( 33 -in pitch) exit limit : 330 passengers, high density seating
for 317 passengers
engine : 3 Rolls Royce RB211-524B turbofan engines of 222.4 [KN] (50.000 [lbf])
dimensions :
wingspan : 50.09 [m], length overall: 50.04 [m], length of fuselage : 50.04 [m]
height : 16.87 [m] wing area : 329.0 [m^2] fuselage exterior width : 5.97 [m]
weights :
operating empty weight : 109300 [kg] max. structural payload : 44015 [kg]
Zero Fuel weight (ZFW) : 153315 [kg] max. landing weight (MLW) : 166920 [kg]
max.take-off weight : 224980 [kg] weight fuel : 96159 [kg] (122495 [litres])
performance :
Never-exceed speed : 0.95 [Mach] (1035 [km/hr]) at 9150 [m]
critical Mach speed : 0.88 [Mach]
max. cruising speed : 973 [km/hr] (Mach 0.91 ) at 10670 [m] (33 [%] power)
economic cruising speed : 899 [km/hr] (Mach 0.84 ) at 10670 [m]
service ceiling : 12800 [m]
range with max fuel and Max.TOW : 10371 [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 : Lockheed
average thickness/chord ratio : 10.0 [%], 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 : 10.46 [m]
wing chord at tip : 3.12 [m]
British Airways L1011-500 with factory registration N48354, later it flew with BA under registration G-BFCA c/n 193V-1157
taper ratio : 0.298 [ ]
mean wing chord : 6.57 [m]
calculated average wing chord tapered wing with rounded tips: 6.70 [m]
wing aspect ratio : 7.63 []
Oswald factor (e): 0.670 []
seize (span*length*height) : 42285 [m^3]
calculation : *2* (fuel consumption)
oil consumption : 6.0 [kg/hr]
fuel consumption (econ. cruise speed) : 8048.3 [kg/hr] (10252.6 [litre/hr]) at 31 [%] power
distance flown for 1 kg fuel : 0.11 [km/kg] at 10670 [m] height, sfc : 38.3 [kg/KN/h]
total fuel capacity : 122495 [litre] (96159 [kg])
calculation : *3* (weight)
weight engine(s) dry : 15075.0 [kg] = 22.59 [kg/KN]
weight 109.9 litre oil tank : 9.34 [kg]
oil tank filled with 4.2 litre oil : 3.8 [kg]
oil in engine 8.2 litre oil : 7.3 [kg]
fuel in engine 36.4 litre fuel : 26.69 [kg]
weight fuel lines : 205.5 [kg]
weight engine cowling : 1734.7 [kg]
British Airways L1011-500 G-BFCA
weight thrust reversers : 1000.8 [kg]
total weight propulsion system : 18063 [kg](8.0 [%])
***************************************************************
Accommodation cabin facilities:
typical 2-class cabin layout for 248 passengers : economy : pitch : 83.8 [cm] 33.0 [-in]
( 2+5+2 ) seating in 28.4 rows
weight passenger seats : 1396.0 [kg]
weight cabin crew seats : 40.0 [kg]
weight flight crew seats : 63.0 [kg]
weight 2 jumpseats in the cockpit :14.0 [kg]
high density seating passengers : 317 [pax] at mainly 10 -abreast seating in 36.1 rows,
pitch 83.8 [cm] 33.0 [-in]
pax density, normal seating : 0.78 [m2/pax], high density seating : 0.61 [m2/pax]
weight 7 lavatories : 195.7 [kg]
weight 3 galleys : 308.0 [kg]
weight overhead stowage for hand luggage : 86.8 [kg]
weight 2 wardrobe closets : 24.8 [kg]
weight 6 movie screens : 124.4 [kg]
weight 59 windows (47x38cm) : 52.9 [kg]
weight 6 (1.93 x 1.07 [m]) main entry doors : 357.6 [kg]
weight 3 (main door size : 1.75 x 1.78 [m]) freight doors (belly) : 254.1 [kg]*
total belly baggage/cargo hold volume : 118.5 [m3]
underfloor belly hold can accommodate : 19 LD3 containers
and : 14.2 [m3] bulk cargo
cabin volume (usable), excluding flight deck : 407 [m3]
passenger compartment volume : 265 [m3]
passenger cabin max width : 5.77 [m] cabin length : 37.31 [m] max cabin
height : 2.41 [m]
floor area : 192.7 [m2]
weight cabin facilities : 2917.3 [kg]
safety facilities:
evacuation time with 317 passengers : 51 [sec]
weight 12 hand fire extinguisher : 35 [kg]
weight cockpit voice recorder (CVR) and flight data recorder (FDR): 20.0 [kg]
weight oxygen masks & oxygen generators : 161.2 [kg]
weight emergency flare installation : 10 [kg]
weight 6 emergency evacuation slides : 336.5 [kg]
weight safety equipment & facilities : 563 [kg]
fuselage construction:
fuselage aluminium frame : 18583 [kg]
floor loading (payload/m2): 228 [kg/m2]
weight rear pressure bulkhead : 437.1 [kg]
fuselage covering ( 740.4 [m2] duraluminium 2.81 [mm]) : 5539.3 [kg]
weight floor beams : 4344.3 [kg]
weight cabin furbishing : 2897.6 [kg]
weight cabin floor : 2724.6 [kg]
weight (sound proof) isolation : 542.0 [kg]
weight 17504 [litre] main central fuel tanks empty : 980.2 [kg]
weight 14845 [litre] additional central fuel tank (ACT) empty : 831.3 [kg]
weight empty 258 [litre] potable water tank : 22.8 [kg]
weight empty waste tank : 27.8 [kg]
weight engine mount in tail : 111 [kg]
weight fuselage structure : 37041.4 [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]
Cockpit of Luzair L1011-500 CS-TMP c/n 193H-1248
weight VOR/ILS,RMI,DME,radio altimeter, ASI, time clock : 20.0 [kg]
weight Integrated Flight System / auto-pilot : 23.0 [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 : 9 [kg]
weight reserve ADI, ASI, alti-meter, compass, engine temp.and rpm indicators : 15 [kg]
weight avionics : 129.0 [kg]
Pan Am L1011-500 N509PA Clipper Golden Eagle c/n 193Y-1188
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 [bars] (kg/cm2)
pressurized fuselage volume : 557 [m3]
weight air-conditioning and pressurization system : 318 [kg]
weight APU / engine starter: 111.2 [kg]
weight lighting : 81.8 [kg]
weight four independent 207 bar hydraulic systems : 178.7 [kg]
weight engine-driven 40kVA electricity generators : 62.0 [kg]
weight three 24V 25Ah nickel-cadmium batteries : 35.6 [kg]
weight controls : 21.7 [kg]
weight systems : 809.3 [kg]
total weight fuselage : 41460 [kg](18.4 [%])
***************************************************************
average Take-off weight : 179874 [kg](80.0 [%])
total weight aluminium ribs (1574 ribs) : 7219 [kg]
weight engine mounts : 222 [kg]
weight 6 wing fuel tanks empty for total 90146 [litre] fuel : 5048 [kg]
weight wing covering (painted aluminium 3.73 [mm]) : 6623 [kg]
total weight aluminium spars (multi-cellular wing structure) : 9389 [kg]
weight wings : 23231 [kg]
weight wing/square meter : 70.61 [kg]
weight thermal leading-edge anti-icing : 55.1 [kg]
weight high& low speed ailerons (14.88 [m2]) : 526.3 [kg]
weight fin (51.11 [m2]) : 1808.2 [kg]
weight rudder (11.87 [m2]) : 403.3 [kg]
weight tailplane (stabilizer) (94.83 [m2]): 3690.5 [kg]
weight elevators (24.18 [m2]): 461.98 [kg]
weight flight control hydraulic servo actuators: 70.5 [kg]
weight trailing-edge double slotted flaps (49.74 [m2]) : 1497.9 [kg]
weight leading edge slats made of aluminium alloy honeycomb (33.42 [m2]) : 632.7 [kg]
weight spoilers (19.9 [m2]) : 344.2 [kg]
total weight wing construction : 37992 [kg] (34.8 [%])
*******************************************************************
tire pressure main wheels : 12.41 [Bar] (nitrogen), ply rating : 23 PR
tire speed limit : 389 [km/hr]
total tyre footprint : 1.16 [m2]
Runway LCN at MTOW (0.76m radius of rigidity) : 50 [ ]
Aircraft Classification Number (ACN), MTOW on rigid runway and medium subgrade strength (B) : 74 [ ]
Can only operate from paved runways subgrade A
L1011-500 BWIA 9Y-TGJ at Zurich-Kloten apt., September 1993.
wheel pressure : 24747.8 [kg]
weight 8 Dunlop main wheels (1270 [mm] by 508 [mm]) : 1423.2 [kg]
weight 2 nose wheels : 177.9 [kg]
weight hydraulic disc wheel-brakes : 153.3 [kg]
weight Duplex anti-skid units : 9.0 [kg]
weight oleo-pneumatic shock absorbers : 204.4 [kg]
weight wheel hydraulic operated retraction system : 2016.4 [kg]
weight undercarriage struts (four-wheel bogies) with axle 5997.0 [kg]
total weight landing gear : 9981.2 [kg] (4.4 [%]
*******************************************************************
********************************************************************
calculated empty weight : 107497 [kg](47.8 [%])
weight oil for 12.8 hours flying : 86.1 [kg]
weight lifejackets : 111.6 [kg]
weight 4 life rafts : 155.0 [kg]
weight catering : 285.2 [kg]
weight water : 228.2 [kg]
weight crew : 891 [kg]
weight crew lugage,nav.chards,flight doc.,miscell.items : 46 [kg]
operational weight empty : 109300 [kg] (48.6 [%])
********************************************************************
weight 248 passengers : 19096 [kg]
weight luggage : 3968 [kg]
weight cargo : 20951 [kg] (cargo+luggage/m3 belly : 202 [kg/m3])
zero fuel weight (ZFW): 153315 [kg](68.1 [%])
weight fuel for landing (1.7 hours flying) : 13605 [kg]
max. landing weight (MLW): 166920 [kg](74.2 [%])
max. fuel weight : 205459 [kg] (91.3 [%])
payload with max fuel : 210 passengers+luggage 19521 [kg]
published maximum take-off weight : 224980 [kg] (100.0 [%])
calculation : * 4 * (engine power)
power loading (Take-off) : 337 [kg/KN]
power loading (Take-off) 1 PUF: 506 [kg/KN]
max. total take-off power : 667.2 [KN]
calculation : *5* (loads)
manoeuvre load : 1.5 [g] at 9000 [m]
Royal Jordanian L1011-500 JY-AGE c/n 293A-1238 at Schiphol, July 1993
limit load : 2.5 [g] ultimate load : 3.8 [g] load factor : 1.0 [g]
design flight time : 2.30 [hours]
design cycles : 13880 sorties, design hours : 31924 [hours]
max. wing loading (MTOW & flaps retracted) : 684 [kg/m2]
wing stress (2 g) during operation : 165 [N/kg] at 2g emergency manoeuvre
calculation : *6* (angles of attack)
angle of attack zero lift : -2.01 ["]
max. angle of attack (stalling angle, clean) : 14.66 ["]
max. angle of attack (full flaps) : 18.86 ["]
angle of attack at max. speed : 1.64 ["]
calculation : *7* (lift & drag ratios
lift coefficient at angle of attack 0° : 0.17 [ ]
lift coefficient at max. speed : 0.31 [ ]
lift coefficient at max. angle of attack (clean): 1.41 [ ]
max. lift coefficient full flaps : 2.08 [ ]
drag coefficient at max. speed : 0.0566 [ ]
drag coefficient at econ. cruise speed : 0.0539 [ ]
induced drag coefficient at econ. cruise speed : 0.0124 [ ]
drag coefficient (zero lift) : 0.0416 [ ]
lift/drag ratio at econ. speed : 5.46 [ ]
calculation : *8* (speeds
take-off decision speed (V1) : 262 [km/u] (142 [kt])
lift-off speed (VLOF) : 289 [km/u] (156 [kt])
take-off safety speed (V2) : 305 [km/u] (165 [kt])
steady initial climb speed (V4) : 331 [km/u] (179 [kt])
flap retraction speed (V3) at 500m (OW loaded : 216932 [kg]): 335 [km/u] (181 [kt])
Luzair L1011-500 CS-TMP
climb speed (to FL150 with 60 [%] power) : 488 [km/hr] (264 [kt])
max. endurance speed (Vbe): 490 [km/u] min. fuel/hr : 6767 [kg/hr] at height : 5486 [m]
max. range speed (Vbr): 908 [km/u] (0.86 [mach]) min. fuel consumption : 8.60 [kg/km] at cruise height : 11278 [m]
max. cruising speed : 973 [km/hr] (525 [kt]) at 10670 [m] (power:38 [%])
max. operational speed (Mmo) : 1035 [km/hr] (Mach 0.95 ) at 9150 [m] (power:52 [%])
airflow at cruise speed per engine : 386.4 [kg/s]
speed of thrust jet : 1761 [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): 322 [km/u] (174 [kt])
final approach speed (landing speed) at sea-level with full flaps VREF (max. landing weight): 267 [km/u] (144 [kt])
ICAO Aircraft Approach Category (APC) : D
stalling speed at sea-level with full flaps VSO (max. landing weight): 206 [km/u]
rate of climb at sea-level ROC (loaded, 60 % power) : 780 [m/min]
rate of climb at sea-level ROC (loaded, 75% power) : 1224 [m/min]
rate of climb at 1000 [m] with 1 engine out (PUF/MTOW, 100 % power on remaining engines) : 1878 [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)
high wheel pressure, can only take off from paved runways
take-off distance at sea-level concrete runway : 2516 [m]
ICAO Aerodrome Reference Code : 4D
take-off distance at sea-level over 15 [m] height : 2672 [m]
FAR TO runway length requirement at MTOW, standard day at SL (ASDA): 2974 [m]
landing run (MLW) : 978 [m]
landing distance (C.A.R.) from 15 [m] at SL, dry runway : 1952 [m]
landing distance (C.A.R.) from 15 [m] at SL, wet runway : 2252 [m]
Yes Air L1011-500 CS-TMX with crew
FAR landing runway length requirements at SL : 1956 [m]
max. lift/drag ratio : 9.83 [ ]
climb to 5000 [m] with max payload : 5.93 [min]
climb to 10000 [m] with max payload : 18.25 [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: 216932 [kg] ) : 16500 [m]
calculation *10* (action radius & endurance)
range with max. payload: 7750 [km] with 44015.0 [kg] max. useful load (74.5 [%] fuel)*
range with high density pax: 9503 [km] with 317 passengers (89.6 [%] fuel)*
range with typical two-class pax: 10298 [km] with 248 passengers (96.3 [%] fuel)*
range with max.fuel : 10741 [km] with 11 crew and 210 passengers and 100.0 [%] fuel*
ferry range : 11312 [km] with 3 crew and zero payload (100.0 [%] fuel)*
max range theoretically with additional fuel tanks total 148842 [litre] fuel : 13400 [km]*
* calculated ranges without fuel reserves
Available Seat Kilometres (ASK) : 2785116 [paskm]
useful load with range 1000km : 44015 [kg]
useful load with range 1000km : 317 passengers
production (theor.max load): 42827 [tonkm/hour]
production (useful load): 42827 [tonkm/hour]
production (passengers): 271670 [paskm/hour]
oil and fuel consumption per tonkm : 0.188 [kg]
Pan Am L1011-500 N511PA “Clipper Black Hawk”
calculation *11* (operating cost)
fuel cost per hour (10253 [litre]):6151 [eur] (26 [pax-km/litre fuel])
fuel cost per seat 1000km flight (279 [pax] 2-class seating): 22.64 [eur/1000PK]
oil cost per hour: 25 [eur]
crew cost per hour : 1500 [eur]
list price 2023 : 285 [mln USD]
average flying hours in 1 year : 2625 [hours] technical life : 12 [year]
real average service life : 16 [years]
economic hours (average real flown hours) : 34125 [hours]
financing interest per flying hour : 2532 [EUR]
write off per flying hour : 7191 [EUR]
time between engine failure : 17225 [hr]
can continue fly on 2 engines, low risk for emergency landing for PUF
workhours per day : 9.54 [hr]
no fatalities during service life > 100%% safe
average flight hours till crash : 1.60 [mln hr] (611 service years)
safe flight hours till fatality : 1603875 [hr] (611.0 service years)
reservation pax liability/flying hour : 0.08 [SDR*] (0.10 [eur])
insurance cost per hour : 196 [eur]
Air Lanka L1011-500 4R-ULB c/n 293F-1236 ferrying an extra engine.
engine maintenance cost per hour : 767.5 [eur]
wing maintenance cost per hour : 314.7 [eur]
fuselage maintenance cost per hour : 279.93 [eur]
tire life (time till worn out) : 99 [cycles]
maintenance cost per hour (excluding engines): 3524 [eur]
DOC in 1980 4.5 USD/km at M 0.83 > 3940 USD/hr
direct operating cost per hour: 21887 [eur]
DOC per seat 1000km flight (279 [pax] 2-class seating): 80.56 [eur/1000PK]
DOC per seat 1000km flight (high density seating): 70.95 [eur/1000PK]
DOC per kg cargo for a 1000km flight : 0.51 [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 : 4.81 [eur/pax]
airport landing fee / passenger : 4.81 [eur/pax]
retour ticket price 1000km trip : 245.53 [eur/pax]
price retour ticket Schiphol-Barcelona : 289.84 [eur/pax]
accidents with fatalities > no fatal accidents happened with a L1011-500
Literature :
Articles: L-1011-500 TriStar technical profile | TriStar500.net (aviation-is.better-than.tv)
Lockheed L-1011 TriStar - Wikipedia Yes Air L1011 Tristar (worldairroutes.com)
https://contentzone.eurocontrol.int/aircraftperformance/default.aspx ?
Lockheed L-1011 TriStar - Wikipedia
Jane’s all the world aircraft 1979-80 page 373,374
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/
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(c) B van der Zalm 18 November 2023 contact : info.aircraftinvestigation@gmail.com ac jetpax 2020.py python 3.7.4