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TRIM SYSTEMS
To assure proper trim systems operation, the BEFORE STARTING
ENGINES trim systems checks in Section II of this manual must be
successfully completed before each flight.
The complete TRIM SYSTEMS OPERATIONAL CHECK in Section II of
this manual shall be successfully completed a minimum of once every
10 hours of airplane flight operation.
Failure to conduct a pitch trim preflight check prior
to each flight increases the probability of an undetected
system failure. An additional single failure in the
trim system could result in a trim runaway.
VHF COMM/VHF NAV
The use of VHF COMM frequency 119.00 MHz is prohibited whenever
a VHF NAV frequency of 116.00 MHz is in use.
If the above combination of frequencies is used, keying
the COMM causes the NAV to flag.
WINDSHIELD ALCOHOL ANTI-ICE
Methyl alcohol (Methanol) per Federal Specification O-M-232, Grade
A, is required.
The alcohol reservoir shall be refilled after each use.
WARNING
NOTE
Change 12
Limitations Learjet 31A AFM
1-18 FM-121
FAA Approved 7-25-91
Change 28
POWERPLANT LIMITS
ENGINE TYPE
Honeywell TFE731-2-3B turbofan propulsion engine, part number:
3073610-x -3 (with fuel heaters)
-1 (without fuel heaters)
ENGINE SPEED
❶ If overspeed limit is exceeded, contact nearest Honeywell Field
Service Propulsion Engine Representative prior to engine removal
for overspeed inspection.
❷ If limit is exceeded, reduce thrust to within limits and make necessary
fuel control adjustment prior to next flight.
❸ Thrust settings above performance chart values may exceed engine
rated thrust.
ENGINE OPERATING TEMPERATURES
Refer to TURBINE TEMPERATURE LIMITS (Figure 1-5 and Figure 1-6).
AIRSTART ENVELOPE
Refer to AIRSTART ENVELOPE (Figure 4-1) in Section IV.
CONDITION LIMIT
OVERSPEED ❶ 105% N1 or N2
TRANSIENT ❷
5 SECONDS
1 MINUTE
103-105% N1 or N2
100-103% N1 or N2
TAKEOFF ❸
Refer to TAKEOFF THRUST (N1) charts in
Section V.
MAXIMUM ❸
CONTINUOUS
Refer to MAXIMUM CONTINUOUS
THRUST (N1) tables in Section V.
{
Change 28
Learjet 31A AFM Limitations
FM-121 1-18A
FAA Approved 7-25-91
Change 28
Change 28
TURBINE TEMPERATURE LIMITS (ITT)
STARTING
Figure 1-5
TIME-SECONDS F31-011500-000-01
INTERSTAGE TURBINE TEMPERATURE (ITT) ~ °C
850
930
860
870
880
890
900
910
920
0 5 10
3 4
1 2
1 Abort start. Record maximum ITT and time in excess of 860°C in engine log
book. Determine cause and correct prior to next start.
2 Abort start. Record maximum ITT and time in excess of 860°C in engine log
book. Refer to Honeywell Engine Light Maintenance Manual for static takeoff
power check.
3 Abort start. Record maximum ITT and time in excess of 880°C in engine log
book. Refer to Honeywell Engine Light Maintenance Manual for static takeoff
power check.
4 Abort start. Record maximum ITT temperature and time in excess of 880°C
in engine log book. Refer to Honeywell Engine Light Maintenance Manual for
hot section inspection before further engine operation.
Learjet 31A AFM Limitations
FM-121 1-19
FAA Approved 7-25-91
Change 28
TURBINE TEMPERATURE LIMITS (ITT)
EXCEPT STARTING
Figure 1-6
F31-011500-000-02
0 10 5
TIME-SECONDS TIME-MINUTES
INTERSTAGE TURBINE TEMPERATURE (ITT) ~ °C
810
820
830
840
850
860
870
890
1
800
900
880
2
832°C
1 Takeoff Transient Limit. Reduce thrust setting to within limits and make electronic
computer N1 adjustment before next flight. Record maximum ITT and
time in excess of limit in engine log book. Observe takeoff ITT limit.
2 Record maximum ITT and time in excess of limit in engine log book. Refer to
Honeywell Engine Light Maintenance Manual for hot section inspection.
Maximum continuous limit is 832°C. For greatest
engine life it is recommended that, under normal
conditions, engine thrust be reduced to an ITT of
795°C or less after 30 minutes of maximum continuous
operation.
NOTE
Change 28
Limitations Learjet 31A AFM
1-20 FM-121
FAA Approved 7-25-91
OIL LIMITS
OIL TEMPERATURE LIMITS
Sea Level to 30,000 feet ................................................................... 127°C
Above 30,000 feet ............................................................................ 140°C
　
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