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Engine Sync..............................................................................................OFF
Fuel Load............................................Wings balanced within 200 pounds
❶ Both fuel computers must be ON and operative except for ferry flight as
permitted by applicable regulations.
❷ Required only if system is to be used.
❸ Airplane may dispatch with two symbol generators provided separate
symbol generators are selected for pilot’s and copilot’s displays.
• Trim Systems • Stall Warning System
• Standby Attitude Gyro • 3 Symbol Generators ❸
• Both ADC Systems • Both EADI’s and EHSI’s
• Rudder Boost ❷ • Both AHS Systems
Change 21
Learjet 31A AFM Limitations
FM-121 1-11
FAA Approved 7-25-91
OPERATIONAL LIMITS/REQUIREMENTS (Cont)
FLIGHT LOAD ACCELERATION LIMITS
These acceleration values limit the bank angle in a level coordinated
turn to 70° (flaps up) and 60° (flaps down). In addition, pullups and
pushovers must be limited to these values.
• Flaps Up .................................................................. +3.0 g to -1.0 g
• Flaps Down .............................................................. +2.0 g to 0.0 g
DEMONSTRATED CROSSWIND
Refer to METEOROLOGICAL DEFINITIONS in Section V —
PERFORMANCE.
MANEUVERS
No aerobatic maneuvers, including spins, are approved.
Intentional stalls are prohibited above 18,000 feet with flaps and/or
landing gear extended.
SEAT BELTS AND SHOULDER HARNESSES
Seat belts and shoulder harnesses must be worn during takeoff and
landing.
Limitations Learjet 31A AFM
1-12 FM-121
FAA Approved 7-25-91
AMBIENT TEMPERATURE LIMITS
Figure 1-4
-60 -40 -20 0 20 40 60
STATIC AIR TEMPERATURE, SAT ~ °C
10
PRESSURE ALTITUDE ~ 1000 FT
-80
20
30
40
50
NOTE: Operation for altitude
and temperature within the
shaded area is within allowable
limits.
Learjet 31A AFM Limitations
FM-121 1-13
FAA Approved 7-25-91
Change 25
SYSTEM LIMITS
AIR DATA SYSTEM
Both air data systems must be operative and the onside system selected
(ADC 1 for pilot’s side and ADC 2 for copilot’s side) for takeoff.
All flags on airspeed/Machmeters and altitude/vertical speed indicators
must be retracted for takeoff.
To assure proper air data system operation the BEFORE STARTING
ENGINES air data system check must be accomplished in accordance
with Section II of this manual.
Reduced Vertical Separation Minimums (RVSM) (Aircraft 31-213,
31-222 & Subsequent and prior aircraft modified by SB 31-34-11) — This aircraft
has been shown to meet the airworthiness requirements for operation
in Reduced Vertical Separation Minimum (RVSM) airspace
between 29,000 and 41,000 feet inclusive. This does not constitute an
operational approval.
ATTITUDE HEADING REFERENCE SYSTEM
The onside attitude heading system must be selected (i.e., AHS 1 for pilot’s
side and AHS 2 for copilot’s side) for takeoff.
AUTOPILOT/FLIGHT DIRECTOR
The Bendix/King KFC 3100 Pilot’s Guide (No. 006-08486-0000) must be
immediately available to the flight crew.
The autopilot/flight director system is approved for category I ILS approaches.
When using autopilot, the pilot or copilot must be in their respective
seat with their seat belt fastened.
Autopilot pitch and roll axes must not be used for takeoff and landing.
The minimum altitude for use of the autopilot is:
• Approach Configuration ............................................ 200 feet AGL
• Enroute Configuration ............................................. 1000 feet AGL
CABIN PRESSURIZATION
Do not takeoff or land with the cabin pressurized.
Maximum Differential Pressure ......................................................10.0 PSI
Limitations Learjet 31A AFM
1-14 FM-121
FAA Approved 7-25-91
Change 21
SYSTEMS LIMITS (Cont)
ELECTRONIC FLIGHT INSTRUMENT SYSTEM (EFIS)
The Bendix/King EFS 50 Electronic Flight Instrument System Pilot’s
Guide (No. 006-08485-0000) must be immediately available to the flight
crew. The pilot’s guide must be of a revision level compatible with the
level of software installed.
Airplane performance and operation must not be predicated on the use
of the multifunction display as the source of required performance and
operational data.
Whenever a symbol generator (SG) or EFIS control panel is removed
and replaced, the reversionary modes must be verified prior to flight.
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