Use of aviation gasoline is time-
limited to 150 hours of operation
during any Time-Between-Overhaul
(TBO) period. It may be used in any
quantity with primary or alternate
Whenever limiting temperatures, listed in the
Engine Operating Limitations chart (table 5-1), are
exceeded and cannot be controlled by retarding the
power levers, the engine will be shut down and a landing
made as soon as possible.
During engine starting the temperatures and
time limits listed in the Engine Operating Limitations
chart (table 5-1) must be observed. When these limits
are exceeded, the incident will be entered as an engine
discrepancy in the appropriate maintenance forms. It is
particularly important to record the amount and duration
of over temperature.
Whenever the prescribed engine overspeed limit
or engine RPM operating limit is exceeded, the incident
must be reported as an engine discrepancy in the
appropriate maintenance forms. It is particularly
important to record the maximum percent of RPM
registered by the tachometer, and the duration of
Continued engine operation above 810C will
reduce engine life.
The following definitions describe the engine power
permissible, limited to periods of five minutes duration.
continuous power is the highest power rating not limited
by time. Use of this rating is intended for emergency
situations at the discretion of the pilot.
5-16. GENERATOR LIMITS.
Maximum generator load is limited for flight and
variable during ground operations. Observe the limits
shown in table 5-2 during ground operation.
Table 5-2. Generator Load Limits
MINIMUM GAS GENERATOR RPM - N
0 to 95%
95 to 100%
Section IV. LOADING LIMITS
5-17. CENTER OF GRAVITY LIMITATIONS.
computation of the center of gravity are contained in
Chapter 6. The center of gravity range will remain within
limits, providing the aircraft loading is accomplished
according to instructions in Chapter 6.
5-18. WEIGHT LIMITATIONS.
The ability to experience loss of
engine power and successfully stop,
continue the takeoff, or climb, before
or after gear retraction is not assured
for all conditions. Thorough mission
planning must be accomplished prior
to takeoff by analysis of maximum
takeoff weight permitted by takeoff
one engine inoperative climb at lift
gradient, and climb performance.
This data will describe performance
Max. Ramp Weight - 16,620 lbs