2-23. POWER LEVERS.
Moving the power levers into
reverse range without the engines
running may result in damage to
the reverse linkage mechanism.
Two power levers are located on the control
pedestal (fig. 2-8). These levers regulate power in the
reverse, idle, and forward range, and operate so that
forward movement increases engine power. Power
control is accomplished through adjustment of the N1
speed governor in the fuel control unit. Power is
increased when N1 RPM is increased. The power levers
also control propeller reverse pitch. Distinct movement
(pulling up and then aft on the power lever) by the pilot is
required for reverse thrust. Placarding beside the lever
travel slots reads POWER. Upper lever travel range is
designated INCR (increase), supplemented by an arrow
pointing forward. Lower travel range is marked IDLE,
LIFT and REVERSE. A placard below the lever slots
reads: CAUTION REVERSE ONLY WITH ENGINES
2-24. CONDITION LEVERS.
Two condition levers are located on the control
pedestal (fig. 2-8). Each lever starts and stops the fuel
supply, and controls the idle speed for its engine. The
levers have three placarded positions: FUEL CUTOFF,
LO IDLE, and HIGH IDLE. In the FUEL CUTOFF
position, the condition lever controls the cutoff function of
its engine-mounted fuel control unit. From LO IDLE to
HIGH IDLE, they control the governors of the fuel control
units to establish minimum fuel flow levels. LO IDLE
position sets the fuel flow rate to attain 52 to 55% (at sea
level) minimum N1 and HIGH IDLE position sets the rate
to attain 70% minimum N1.The power lever for the
corresponding engine can select N1 from the respective
idle setting to maximum power. An increase in low idle
N1 will be experienced at high field elevation.
2-25. FRICTION LOCK KNOBS.
Four friction lock knobs (fig. 2-8) are located on the
control pedestal to adjust friction drag. One knob is below
the propeller levers, one below the condition levers, and
two under the power levers. When a knob is rotated
movement of the affected lever as set by the pilot.
Counterclockwise rotation of a knob will decrease friction
drag thus permitting free and easy lever movement. Two
FRICTION LOCK placards are located on the pedestal
adjacent to the knobs.
2-26. ENGINE FIRE DETECTION SYSTEM.
Description. A flame surveillance system is
installed on each engine to detect external engine fire and
provide alarm to the pilot. Both nacelles are monitored,
each having a control amplifier and three detectors.
Electrical wiring connects all sensors and control
amplifiers to DC power and to the cockpit visual alarm
units. In each nacelle, one detector monitors the forward
nacelle, a second monitors the upper accessory area, and
a third the lower accessory area. Fire emits an infrared
radiation that will be sensed by the detector which
monitors the area of origin. Radiation exposure activates
the relay circuit of a control amplifier which causes signal
power to be sent to cockpit warning systems. An
activated surveillance system will return to the standby
state after the fire is out. The system includes a
functional test switch and has circuit protection through
the FIRE DETR circuit breaker. Warning of internal
nacelle fire is provided as follows: the red MASTER
accompanied by the illumination of a red warning light in
the appropriate fire control T-handle placarded No.1 FIRE
PULL or No.2 FIRE PULL (fig. 2-30). Fire detector
circuits are protected by a single 5-ampere circuit breaker,
placarded FIRE DETR, located on the overhead circuit
breaker panel (fig. 2-27).
b. Fire Detection System Test Switch. One rotary switch
placarded FIRE PROTECTION TEST on the copilot's
subpanel is provided to test the engine fire detection
system. Before checkout, battery power must be on and
the FIRE DETR circuit breaker must be in. Switch
position DETR 1, checks the area forward of the air intake
of each nacelle, including circuits to the cockpit alarm and
indication devices. Switch position DETR 2, checks the
circuits for the upper accessory compartment of each
nacelle. Switch position DETR 3, checks the circuits for
the lower accessory compartment of each nacelle. Each
indications previously described.
c. Erroneous Fire Detection System Indications. During
ground test of the engine fire detection system, an
erroneous indication of system fault may be encountered
if an engine cowling is not closed properly, or if the