SECTION 7 CESSNA
AIRPLANE AND SYSTEMS DESCRIPTION MODEL 208B 867 SHP
GARMIN G1000
U.S.
ENGINE CONTROLS (Continued)
EMERGENCY POWER LEVER
The EMERGENCY POWER lever is connected through linkage to the
manual override lever on the fuel control unit and governs fuel supply to
the engine should a pneumatic malfunction occur in the fuel control
unit. When the engine is operating, a failure of any pneumatic signal
input to the fuel control unit will result in the fuel flow decreasing to
minimum idle (about 48% N
g
at sea level and increasing with altitude).
The EMERGENCY POWER lever allows the pilot to restore power in
the event of such a failure. The EMERGENCY POWER lever has
NORMAL, IDLE, and MAX positions. The NORMAL position is used for
all normal engine operation when the fuel control unit is operating
normally and engine power is selected by the POWER lever. The range
from IDLE position to MAX governs engine power and is used when a
pneumatic malfunction has occurred in the fuel control unit and the
power lever is ineffective. A mechanical stop in the lever slot requires
that the EMERGENCY POWER lever be moved to the left to clear the
stop before it can be moved from the NORMAL (full aft) position to the
IDLE position.
• The knob on the EMERGENCY POWER lever has
crosshatching. The crosshatching is visible when the
lever is in MAX position.
• The EMERGENCY POWER lever is annunciated by a
red (OFF and STRT modes) or amber (RUN mode)
EMERG PWR LVR on the PFD.
• The red annunciation will illuminate whenever the
EMERGENCY POWER lever is unstowed from the
NORMAL position with the ITT indications in either of the
OFF or STRT modes. This precaution is intended to
preclude starting of the engine with the EMERGENCY
POWER lever inadvertently placed in any position other
than NORMAL.
• The amber annunciation will illuminate whenever the
EMERGENCY POWER lever is unstowed during normal
operations.
(Continued Next Page)
208BPHCUS-00
7-50
To Next Page
Loading...
