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a visual inspection may not detect very small levels of contamination; therefore,
a tactile (hand on surface) check of the wing leading edge and adjacent
wing upper surface is required when the ambient temperature is less
than 10°C (50°F).
Limitations
FM-126 1-1
FAA Approved 5-19-2004
GENERAL
TYPE OF OPERATION
This airplane is certificated in accordance with FAR 25 in the transport
category and is eligible for the following kinds of operations when the
appropriate instruments and equipment required by the airworthiness
and operating requirements are installed and approved and are in operable
condition.
This airplane is approved for:
- VFR (Visual)
- IFR (Instrument)
- Day
- Night
- Icing
Icing conditions exist when outside air temperature (OAT) on the
ground and for takeoff is 10°C (50°F) or below, or the static air temperature
(SAT) in flight is 10°C (50°F) to -40°C (-40°F), and visible moisture
in any form is present (such as clouds, fog with visibility of one mile or
less, rain, snow, sleet, or ice crystals).
Icing conditions also exist when the OAT on the ground and for takeoff
is 10°C (50°F) or below when operating on ramps, taxiways, or runways
where surface snow, ice, standing water, or slush may be ingested
by the engines, or freeze on engines, nacelles, or engine sensor probes.
This airplane is not certificated for ditching under FAR 25.801.
PERFORMANCE CONFIGURATION
The airplane configuration must be as presented under Standard Performance
Conditions in Section V.
MINIMUM FLIGHT CREW
The minimum flight crew shall consist of pilot and copilot.
WEIGHT AND C.G. LIMITS
On aircraft 45-002 & subsequent not modified by SB 45-11-4:
MAXIMUM RAMP WEIGHT..................................................20,750 Pounds
9412 kg
MAXIMUM CERTIFIED TAKEOFF WEIGHT.........................20,500 Pounds
9299 kg
On aircraft 45-002 & subsequent modified by SB 45-11-4:
MAXIMUM RAMP WEIGHT..................................................21,750 Pounds
9865 kg
MAXIMUM CERTIFIED TAKEOFF WEIGHT.........................21,500 Pounds
9752 kg
Limitations
1-2 FM-126
FAA Approved 5-19-2004
WEIGHT AND C.G. LIMITS (Cont)
MINIMUM FLIGHT WEIGHT.................................................. 14,000 Pounds
6350 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.
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 45 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 45 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
NOTE
Limitations
FM-126 1-3.3
FAA Approved 5-19-2004
CENTER-OF-GRAVITY ENVELOPE
Figure 1-1.3
EFFECTIVITY
Aircraft 45-002 & Subsequent
modified by SB 45-11-4
60
65
70
75
80
85
90
95 21
20
19
18
17
16
15
14
5 10 15 20 25 30
WEIGHT x 1000 — POUNDS
WEIGHT x 100 — KILOGRAMS
0
25.0% MAC
F.S. 435.57 in.
　
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