737 Operations Manual
Fire and Overheat System Test with an Inoperative Loop
To determine the specific inoperative loop:
OVHT DET switches .......................................................................A
Test switch ......................................................................OVHT/FIRE If the FAULT light remains extinguished and both ENG
OVERHEAT lights and engine fire warning switches illuminate,
loop A is good.
If the FAULT light illuminates and one of the ENG OVERHEAT
lights and corresponding engine fire warning switch remain
extinguished, there is a fault in loop A of the detection system of
that engine.
OVHT DET switches .......................................................................B
Test switch ......................................................................OVHT/FIRE If the FAULT light remains extinguished and both ENG
OVERHEAT lights and engine fire warning switches illuminate,
loop B is good.
If the FAULT light illuminates and one of the ENG OVERHEAT
lights and corresponding engine fire warning switch remain
extinguished, there is a fault in loop B of the detection system of
that engine.
OVHT DET switches .......................................................As required Select the good loop for each engine (NORMAL if both loops tested good).
Test switch ......................................................................OVHT/FIRE If the test is successful, leave the fire panel in this configuration for flight.
Supplementary Procedures -Fire Protection 737 Operations Manual
Intentionally
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Copyright . The Boeing Company. See title page for details.
SP.8.2 December 1, 2000
737 Operations Manual
Flight Controls Check
This is a check of normal flight control functions and is not a complete check of the flight control system. Two people are required; both on interphone.
FLIGHT DECK ACTION GROUND RESPONSE
Electrical power (APU or external) – On bus
System A and B electric hydraulic pump switches – OFF
Control wheel – Left “LEFT AILERON UP, TAB DOWN; RIGHT AILERON DOWN, TAB UP”
Control wheel – Right “LEFT AILERON DOWN, TAB UP; RIGHT AILERON UP, TAB DOWN”
Control wheel – Neutral
Control column – Forward “ELEVATOR DOWN, TABS UP”
Control column – Aft “ELEVATOR UP, TABS DOWN”
Control column – Neutral
Request hydraulic clearance “CLEAR FOR HYDRAULIC PRESSURE, WING AND CONTROL AREAS CLEAR”
System A and B electric hydraulic pump switches – ON Verify System A & B pressure indicators and brake pressure indicator read 2800 psi minimum
Parking brake – Set
Copyright . The Boeing Company. See title page for details.
June 4, 2004 SP.9.1
Supplementary Procedures -Flight Controls 737 Operations Manual
FLIGHT DECK ACTION GROUND RESPONSE
Rudder trim – Turn left Verify left rudder pedals move forward
Rudder trim – Turn right Verify right rudder pedals move forward
Rudder trim – Zero, pedals centered
Aileron trim – Turn left Verify control wheel turns to left
Aileron trim – Turn right Verify control wheel turns to right
Aileron trim – Zero, control wheels centered
Nose gear steering wheel – Hold “LEFT AILERON UP, TAB
Control wheel – Left DOWN; LEFT FLIGHT
Control column – Forward SPOILERS UP; RIGHT AILERON DOWN, TAB UP;
Rudder pedal – Left RUDDER LEFT; ELEVATORS DOWN, TABS UP”
Nose gear steering wheel – Hold Control wheel – Right Control column – Aft Rudder pedal – Right “LEFT AILERON DOWN, TAB UP; RIGHT FLIGHT SPOILERS UP; RIGHT AILERON UP, TAB DOWN; RUDDER RIGHT; ELEVATORS UP, TABS DOWN”
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