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Conditions in Section V.
MINIMUM FLIGHT CREW
The minimum flight crew shall consist of pilot and copilot.
Limitation
1 2 FM 132
FAA Approved 9-24-2004
Change 2
WEIGHT AND C.G. LIMITS
MAXIMUM RAMP WEIGHT
- Aircraft not modified by SB 40-11-01 ......................... 20,600 Pounds
9344 kg
- Aircraft modified by SB 40-11-01 ................................ 21,250 Pounds
9639 kg
MAXIMUM CERTIFIED TAKEOFF WEIGHT
- Aircraft not modified by SB 40-11-01 ......................... 20,350 Pounds
9231 kg
- Aircraft modified by SB 40-11-01 ................................ 21,000 Pounds
9525 kg
MINIMUM FLIGHT WEIGHT.................................................. 13,500 Pounds
6124 kg
MAXIMUM ZERO FUEL WEIGHT ......................................... 16,000 Pounds
7258 kg
All weights in excess of Maximum Zero Fuel Weight
must consist of fuel.
MAXIMUM ALLOWABLE TAKEOFF WEIGHT
The takeoff weight is limited by the most restrictive of the following
requirements:
- Maximum Certified Takeoff Weight.
- Maximum Takeoff Weight (Climb or Brake Energy Limited) for
altitude and temperature as determined from the applicable figure
entitled TAKEOFF WEIGHT LIMITS, Section V.
- Maximum Takeoff Weight for the runway and ambient conditions
as determined from the applicable figure entitled TAKEOFF
DISTANCE, Section V.
NOTE
Limitation
FM 132
FAA Approved 9-24-2004
Change 2
WEIGHT AND C.G. LIMITS (Cont)
MAXIMUM CERTIFIED LANDING WEIGHT........................19,200 Pounds
8709 kg
MAXIMUM ALLOWABLE LANDING WEIGHT
The landing weight is limited by the most restrictive of the following
requirements:
- Maximum Certified Landing Weight.
Perform Hard or Overweight Landing Inspection
(Chapter 5, Learjet 40 Maintenance Manual) if Maximum
Certified Landing Weight is exceeded.
- Maximum Landing Weight for the runway and ambient conditions
as determined from the applicable figure entitled
ACTUAL LANDING DISTANCE, Section V.
- Maximum Landing Weight (Approach Climb or Brake Energy
Limited) for altitude and temperature as determined from the
applicable figure entitled LANDING WEIGHT LIMITS,
Section V.
Perform High Energy Stop Inspection (Chapter 5,
Learjet 40 Maintenance Manual) if the maximum
brake energy weight for landing is exceeded during
a landing or rejected takeoff.
CENTER-OF-GRAVITY
The center-of-gravity of the airplane for all flight conditions must be
maintained within the applicable figure entitled CENTER-OFGRAVITY
ENVELOPE, this section.
NOTE
NOTE
1-2A
Limitations
FM-132 1-3.1
FAA Approved 9-24-2004
CENTER-OF-GRAVITY ENVELOPE
Figure 1-1.1
EFFECTIVITY
Aircraft 45-2001 & Subsequent
modified by SB 40-11-1
CENTER-OF-GRAVITY - % MAC
0 5 10 15 20 25 30
WEIGHT x 100 - KILOGRAMS
60
65
70
75
80
85
90
95
100
WEIGHT x 1000 - POUNDS
13
14
15
16
17
18
19
20
21
22
23
Max Takeoff Weight
21,000 lb (9525 kg)
Max Zero Fuel Weight
16,000 lb (7258 kg)
Min Flight Weight
13,500 lb (6124 kg)
MaxRampWeight
21,250 lb (9639 kg)
28.0% MAC
F.S. 438.19 in.
11,130 mm
27.1% MAC
F.S. 437.41 in.
11,110 mm
19.6% MAC
F.S. 430.86 in.
10,944 mm
14% MAC
F.S. 425.98 in.
10,820 mm
7% MAC
F.S. 419.88 in.
10,665 mm
23.5% MAC
F.S. 434.27 in.
11,030 mm
20.2.% MAC
F.S. 431.35 in.
10,956 mm
45-1554
Max Landing Weight
19,200 lb (8709 kg)
Limitations
1-4.1 FM-132
FAA Approved 9-24-2004
AIRSPEED/MACH LIMITS
PRIMARY PITOT-STATIC SYSTEM
Figure 1-2.1
EFFECTIVITY
Aircraft 45-2001 & Subsequent
modified by SB 40-11-1
MMO with Mach Trim Inoperative &
Autopilot Disengaged
MMO Limit
VA 21,000 Lb/9525 kg
VA 19,200 Lb/8709 kg
VA 17,000 Lb/7711 kg
VA 14,000 Lb/6350 kg
Mach Trim Inoperative
& Autopilot Disengaged
VMO Limit
45-1400
MMO with Autopilot Disengaged
MMO with Autopilot Engaged
Autopilot Engaged
Autopilot Disengaged
Limitation
FM 132 1 5
FAA Approved 9-24-2004
Change 2
AIRSPEED/MACH LIMITS
MAXIMUM OPERATING SPEED VMO/MMO
VMO/MMO shall not be deliberately exceeded in any regime of flight
(climb, cruise, or descent) unless a higher speed is authorized for flight
test.
Primary Display
　
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