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C.  The autothrottle servomechanism is located in front of the electronics compartment and can be accessed directly without removing and airplane panels.
D.  This procedure only covers the removal/installation of the torque switch mechanism.
2.  Equipment and Materials
A.  Corrosion Preventive Compound - MIL-C-16173, Grade 2
B.  Torque wrench - 0 to 100 pound-inch capacity
C.  Cable Terminal Retainer - 69-72479-1
3.  Remove Torque Switch Mechanism
A.  Place thrust levers in idle position.
B.  Clamp applicable TA and TB cables and detach cables at turnbuckles forward and aft of torque switch mechanism.
NOTE: Tag cables to ensure correct replacement.
C.  Remove four mounting bolts (1, Fig. 401) and remove torque switch mechanism (2), actuator assembly (3) and potentiometer (4) from support (5).
D.  Remove cable guards (6).
E.  Rotate the quadrants of the torque switch mechanism as required until the cable terminals for grooves one and four are accessible.
F.  Unbend the ends of the cable terminal retainer’s (7) approximately 90 degrees to free cable terminals.
Oct 20/84 76-11-92 Page 401
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.

Torque Switch Mechanism Installation  5B8 
76-11-92  Figure 401  Feb 20/84 
Page 402 
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 

G.  Remove cable terminals from their terminal holes and remove cables from quadrants.
H.  Rotate the quadrants as required until the cable terminals for groove two and three are accessible.
I.  Unbend ends of cable terminal retainers (7) approximately 90 degrees to free cable terminals.
J.  Remove cable terminals from their terminal holes and remove cables from quadrants.
4.  Install Torque Switch Mechanism
A.  Rotate the quadrants of the torque switch mechanism (2) as required to gain access to the cable terminals holes.
B.  Install new cable terminal retainers (7) in cable terminal holes. Apply corrosion preventive compound to faying surfaces to hold retainers in place (Fig. 401).
C.  Insert cable terminals for grooves one and four. Rotate quadrants as required for access. Pull cable terminals into their terminal holes.
D.  Bend end of cable terminal retainers (7) approximately 90 degrees to trap cable terminals.
E.  Insert cable terminals for grooves two and three. Rotate quadrants as required for access. Pull cable terminals into their terminal holes.
F.  Bend end of cable terminal retainers (7) approximately 90 degrees to trap cable terminal.
G.  Install cable guards (6).
H.  Install torque switch mechanism (2), actuator assembly (3) and potentiometer (4) in support (5). Install four mounting bolts (1).
I.  Attach TA and TB cables at turnbuckles forward and aft of torque switch mechanism and remove cable clamps.
J.  Adjust and test engine control system (Ref 76-11-0, Adjustment/Test).
K.  Test integrated autothrottle system (Ref Chapter 22, Auto Flight).
5B8 
Feb 20/84  BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.  76-11-92 Page 403 

ENGINE FIRE EMERGENCY SHUTDOWN - DESCRIPTION AND OPERATION
1. General
A.  Emergency fire shutdown is initiated by receipt of a fire signal in the control cabin. The fire signal consists of a continuously sounding fire alarm bell, the lighting of the master fire warning lights on the captain's and first officer's light shield and the lighting of the applicable fire switch handle in the fire protection system module on the control stand aft electronic control panel. The alarm bell is silenced by depressing either of the master fire warning lights or the bell cutout switch on the control stand aft electronic control panel. A fire signal unlocks the corresponding fire switch handle, leaving it free to be pulled and rotated. Emergency fire shutdown consists of shutting off the engine and isolating it from the other systems.
B.  Emergency shutoff is accomplished by moving the thrust lever to idle and positioning the start lever to cutoff, which closes an outflow valve in the fuel control unit and closes the engine fuel shutoff valve.
C.  Pulling the fire switch handle will close the applicable engine bleed air, engine hydraulic shutoff valve and open the generator field circuit. Closure of the engine fuel valve will also occur by pulling the fire switch if positioning the start lever to cutoff has not been accomplished (Fig. 1).
D.  Counterclockwise rotation of the handle will discharge the left fire extinguisher bottle and clockwise rotation will discharge the right fire extinguisher bottle into the selected nacelle (Ref Chapter 26, Engine Fire Extinguishing System).
　
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