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Rotation
-
125
􀁮
-28
􀁯􀁰
127
EFFECTIVITY
Aircraft 45-002 & Subsequent
modified by SB 45-72-1
Limitations
1-16 FM-126
FAA Approved 5-19-2004
ENGINE TRANSIENT SPEED LIMITS
N1 LIMITS
N2 LIMITS
􀁮 Reduce applicable N1 or N2 below limit.
􀁯 Reduce applicable N1 or N2 below limit. Record maximum N1 or N2, and time
above limit in engine log book. Refer to Honeywell Engine Light Maintenance Manual
for control check and performance calibration.
􀁰 Reduce applicable N1 or N2 below limit. Record maximum N1 or N2, and time
above limit in engine log book. Refer to Honeywell Engine Light Maintenance Manual
for overspeed inspection.
􀁱 N2 may operate for 5 minutes in APR.
NOTE: On aircraft 45-002 & subsequent modified by 45-72-1, there may be a momentary
N1 red EI illumination which is allowable.
Figure 1-5
100
101
102
103
0
TIME ~ SECONDS
N 1 PERCENT (PHYSICAL)
10
100.5
F45-011400-000-01
2 3
1
Limitations
FM-126 1-17.4
FAA Approved 5-19-2004
ENGINE TEMPERATURE LIMITS (ITT) (Cont)
STARTING
􀁮 Abort start. Record maximum ITT and time in excess of 991°C in engine log book.
Determine cause and correct prior to next start.
􀁯 Abort start. Record maximum ITT and time in excess of 991°C in engine log book.
Refer to Honeywell Engine Light Maintenance Manual for static takeoff power check.
􀁰 Abort start. Record maximum ITT and time in excess of 991°C in engine log book.
Refer to Honeywell Engine Light Maintenance Manual for hot section inspection.
Figure 1-6.4
EFFECTIVITY
Aircraft 45-002 & Subsequent
modified by SB 45-72-1
0 10
F45-011500-000-02
970
TIME-SECONDS
980
990
1000
1010
INTERSTAGE TURBINE TEMPERATURE (ITT) ~ °C
1020
1030
1040
1013°C
991°C
1 2
3
Limitations
1-18.4 FM-126
FAA Approved 5-19-2004
ENGINE TEMPERATURE LIMITS (ITT) (Cont)
EXCEPT STARTING
􀁮 Record APR cycle in engine log book per Honeywell Engine Light Maintenance Manual.
􀁯 Reduce thrust below limit. Record maximum ITT and time in excess of limit in engine
log book. Refer to Honeywell Engine Light Maintenance Manual.
􀁰 Reduce thrust below limit. Record maximum ITT and time in excess of limit in engine
log book. Refer to Honeywell Engine Light Maintenance Manual for hot section
inspection.
􀁱 Reduce thrust below limit. Record maximum ITT and time in excess of limit in engine
log book. Refer to Honeywell Engine Light Maintenance Manual for hot section
inspection.
Figure 1-7.4
EFFECTIVITY
Aircraft 45-002 & Subsequent
modified by SB 45-72-1
Limitations
FM-126 1-19
FAA Approved 5-19-2004
Change 1
FUEL LIMITS
FUEL LOAD/BALANCE
Do not takeoff or land with wing fuel imbalance greater than 200
pounds (91 kg).
On aircraft 45-002 thru 45-258 and 45-260 not modifed by SB 45-28-8:
During flight, wing fuel balance must be maintained within 500
pounds (227 kg) flaps up or 200 lb (91 kg) with flaps greater than 3°.
On aircraft 45-259, 45-261 thru 45-2000 and prior aircraft modified by
SB 45-28-8:
During flight, wing fuel balance must be maintained within 200
pounds (91 kg).
APPROVED FUELS
The mixing of fuel types is allowed.
JP-5, JP-8, Jet A and Jet A-1 fuels are approved. Refer to Addendum I —
FUEL SERVICING for a listing of approved fuels.
FUEL ADDITIVES
ANTI-ICING ADDITIVE
On aircraft 45-002 thru 45-064 not modified by SB 45-11-1:
Anti-icing additive conforming to MIL-I-27686 or MIL-I-85470 is a
requirement.
The aircraft may be single-point pressure refueled with approved premixed
fuels.
The following products have been approved for blending MIL-I-27686
additive during refueling (gravity fill method only):
- Hi-Flo Prist 20 fluid ounce aerosol blender.
- Quell 20 fluid ounce aerosol blender.
- D-Ice 20 fluid ounce aerosol blender.
The following products have been approved for blending MIL-I-85470
additive during refueling (gravity fill method only):
- Hi-Flash Prist 20 fluid ounce aerosol blender.
- D-Ice Flash 190, 20 fluid ounce aerosol blender.
Limitations
1-20 FM-126
FAA Approved 5-19-2004
ANTI-ICING ADDITIVE (Cont)
The anti-icing additive concentrations by volume are as follows:
Use not less than 20 fluid ounces (1 can) of MIL-I-27686 per 260 gallons
　
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