5-9. STARTER LIMITATIONS.
The starters in this aircraft are limited to an
operating time of 40 seconds on, then 60 seconds off,
for two starter operations. After two starter operations,
the starter shall be operated for 40 seconds on, then
30 minutes off.
5-10. AUTOPILOT LIMITATIONS.
a. A pilot must be seated at the controls with the
seat belt fastened when the autopilot is in operation.
b. Operation of the autopilot and yaw damper is
prohibited during takeoff and landing and below
200 feet above terrain. Maximum speed for autopilot
operation is 260 knots/0.52 Mach.
c. During coupled ILS approach, do not operate
the propellers in the 1750 to 1850 RPM range.
5-11. FUEL SYSTEM LIMITS.
Aviation gasoline (AVGAS) contains a form
of lead that has an accumulative adverse
effect on gas turbine engines. The lowest
octane AVGAS available (less lead content)
should be used. If any AVGAS is used, the
total operating time shall be entered on DA
a. Operating Limits. Operation with FUEL
PRESS light on is limited to 10 hours. Log FUEL
PRESS light on time on DA Form 240813-1. One
standby boost pump may be inoperative for takeoff.
Crossfeed fuel will not be available from the side with
the inoperative standby boost pump. Operation on
aviation gasoline is time limited to 150 hours between
engine overhaul and altitude limited to 20,000 feet with
one standby boost pump inoperative. Crossfeed
capability is required for climb when using aviation
gasoline above 20,000 feet.
b. Fuel Management. Fuel shall not be added
to auxiliary tanks unless the corresponding main tank
is full. Maximum allowable fuel imbalance is
1000 pounds. Do not take off if fuel quantity gages
indicate in yellow arc, less than 265 pounds of fuel in
each main tank. Crossfeed only during single engine
c. Fuel System AntiIcing. Icing inhibitor
conforming to MIL127686 (PRIST) shall be added to
commercial fuel not containing an icing inhibitor during
temperatures. The additive provides antiicing
protection and functions as a biocide to kill
microbiological growth in aircraft fuel systems.
Failure to comply with Paragraph 511d(1)
could result in the collapse of the tanks. If
the 1500 feet per minute rate of descent is
exceeded, the air may not flow through the
surge tank and tank vent lines fast enough
to keep the tank air pressure and cabin air
emergency dictates a greater rate of
descent, loosening or removing the tank
caps will allow the two air pressures to
equalize but could allow fuel fumes to
escape into the cabin.
(1) The cabin air pressure RATE OF
DESCENT MUST NOT EXCEED 1500 FEET PER
MINUTE when the extended range fuel tanks are
installed in the cabin and the caps are on.
(2) Maximum takeoff weight must not exceed
14,500 pounds (130% of normal max weight), VNE
must not exceed 216 knots, VMO must not exceed
0.43 Mach, and the aft CG must not exceed
(3) Maximum quantity of fuel carried in the
ferry fuel tanks must not exceed 240 U.S. gallons total.
(4) The use of autopilot for flight operations
greater than 12,500 pounds is prohibited.
(5) Weather conditions with moderate to
severe turbulence should be avoided.
(6) When a landing over 12,500 pounds has
been made or the aircraft has encountered moderate
to severe turbulence while over 12,500 pounds, the
aircraft must be inspected for damage. Inspections
performed and the findings must be entered in the
Airframe Log Book. The pilot in command is
responsible, before the next flight, for determining that
the aircraft is in an airworthy condition.
5-12. LANDING GEAR CYCLING AND BRAKE
a. Hydraulic Landing Gear D2 T . While
conducting training operations, the landing gear cyclic
rate shall not exceed five complete (extension and
retraction) cycles equally spaced in 20 minutes,
without allowing a 10 to 15 minute interval between the