CESSNA SECTION 7
MODEL
208B (675 SHP) AIRPLANE AND SYSTEMS DESCRIPTION
ENGINE
(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%
Ng 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.
NOTE
The knob on the emergency power lever has cross-
hatching. The crosshatching is visible when the lever is in
MAX position. Also, the emergency power lever is
annunciated on the annunciator panel whenever it is
unstowed from the NORMAL position. These precautions
are intended to preclude starting of the engine with the
emergency power lever inadvertently placed in any position
other than NORMAL.
(Continued Next Page)
U.S. 7-49
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