Lockheed L1011-1 FDE v1
Copyright 2000 by Sam Chin
All Rights Reserved
MTOW: 430,000 lbs
MLW: 358,000 lbs
ZFW: 291,500 lbs
STALL: 108/148
VMO/MMO: 350kias/M0.90
CRUISE: M.80 (econ) to 520ktas
Vref: 145 at MLW (48% total fuel)
V1/Vr/V2: 160/165/172 at MTOW
RANGE: 2,870 with full capacity/cargo (this air file is full capacity)
FAA Specifications
I - Model L-1011-385-1 (Transport Category Aircraft), Approved April 14, 1972
-22C Engine
Static thrust at sea level
Takeoff (5 min.) 41,030 lbs. (flat rated to ISA 1 + 3.8ø C)
Maximum continuous 36,900 lbs. (flat rated to ISA + 10ø C)
-22B Engine
Static thrust at sea level
Takeoff (5 min.) 41,030 lbs. (flat rated to ISA + 13.9ø C)
42,670 lbs. (flat rated to ISA + 8.4ø C)2
Maximum continuous 40,140 lbs. (flat rated to ISA + 9.0ø C to 25,000 ft. and
ISA + 13ø C above 25,000 ft.)
40,140 lbs. (flat rated to ISA + 8.4ø C to 5600 ft.
Thereafter, thrust reduces linearly to be
same as the -22B at ISA + 13.9ø C and 10,000 ft.)
N 1 (%) N 2 (%) N 3 (%) N 1 (%) N 2 (%) N 3 (%)
Takeoff(5min) 99.0 99.5 99.5 99.5 101.5 95.0
Max continuous 97.5 98.8 94.3 101.0 101.5 93.7
Ground idle 24 25
Maximum turbine temperature (measured at low pressure NGV 6 :
-22C Engine Only -22B Engine Only
Takeoff (5 min.) 1328ø F (720ø C) 1342ø F (728ø C)
Maximum continuous 1292ø F (700ø C) 1292ø F (700ø C)
Starting 1022ø F (550ø C) 1022ø F (550ø C)
Reverse thrust (30 sec.) 1265ø F (685ø C) 1265ø F (685ø C)5
Max for acceleration (2 min.) 1337ø F (725ø C) 1360ø F (738ø C)
V fe Load Relieving System Operative
Flap Angle Selected, in Degrees Knots IAS/mach No.
4ø 250K M = 0.6
10ø 230K M = 0.5
14ø 215K M = 0.5
18ø 210K M = 0.5
22ø 205K M = 0.5
27ø 200K M = 0.5
33ø 170K M = 0.4
42ø 164K M = 0.4
V LO (landing gear)
Retraction 230k not to exceed (M = 0.85)
Extension 300k not to exceed (M = 0.85)
V L3 (landing gear extended) 300k not to exceed (M = 0.85)
VMO/MMO IAS
At Sea Level 350K
At 10,000 feet 375K
At 26,200 feet 375K (M = 0.9)
At 42,000 feet 264K (M = 0.9)
At 43,000 feet 256K (M = 0.9)
