3.  Remove Torque Limiter Switch (Fig. 401)
NOTE:  The torque limiter switch can be removed without disturbing the throttle cable rigging installation.
A.  Locate the torque limiter switch located on top of the torque switch mechanism assembly (Fig. 401).
B.  Disconnect the torque limiter switch pigtail from the adjacent terminal block.
C.  Using a short slot screwdriver, remove the two screws that attach the torque limiter switch to the top of the torque switch mechanism assembly.
4.  Install Torque Limiter Switch (Fig. 401)
A.  Set torque limiter switch in position on top of torque switch mechanism assembly and attach using a short slot screwdriver.
B.  Connect torque limiter switch pigtail to adjacent terminal block (T328 or T329) (the brown lead to terminal 2 and the black lead to terminal 1).
5B8 
Jan 20/83  BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.  22-31-91 Page 403 

AUTO THROTTLE COMPUTER - REMOVAL/INSTALLATION
EFFECTIVITY
AS N730AS, N740AS, N742AS SA ZS-SIA and on CJ B2509 and B-2510
1.  General
A.  The auto throttle (A/T) computer is retained in the electronic rack with a pair of shelf-mounted swivel bolts.
2.  Remove Computer
A.  Open auto throttle circuit breakers on P18 load control center.
B.  Release computer by loosening swivel bolts and operate extractor to release unit.
C.  Remove computer.
3.  Install Computer
A.  Place computer in rack and mate into electrical connector per 20-10-111 R/I.
B.  Close all auto throttle circuit breakers.
4.  Test Computer
A.  An installation test of the auto throttle computer is provided by BITE. BITE can be performed via the PDC CDU or from the front panel of the auto throttle computer.
B.  Prepare for BITE by providing electrical power to auto throttle system, PDC attitude reference, LRRA and air data system.
C.  Verify that airplane is in normal on-ground condition with flaps full up, airspeed is at 0 knots, radio altitude is at 0 (normal on-ground display) and thrust levers are at idle stop position.
D.  If BITE is performed via PDC CDU, provide PDC initial data for outside-air-temperature, destination elevation, zero fuel weight and reserve fuel weight.
E.  Perform computer BITE test.
(1)  
If BITE is performed via PDC CDU, select A/T test page 4-X.

(2)  
If BITE is performed via auto throttle computer, press test switch on A/T computer once to enter test.

(3)  
Verify that A/T disengage lights illuminate steady red.

(4)  
Engage A/T system and press ENGAGE switch on PDC CDU or operate TEST switch on A/T computer. Wait for test to operate and check for P (pass) or F (fail) indication on PDC CDU or A-A-A (pass) or A-F-( ) (fail) on A/T computer at completion of test. Disengage A/T if system did not automatically disengage.

NOTE:  BITE A checks A/T computer, for remaining BITE refer to 22-31-01 adjustment test.

(5)  
Terminate BITE by paging away on PDC CDU or by advancing one thrust lever forward when A/T computer is not conducting test or processing test results.

(6)  
Restore airplane to normal and remove electrical power if no longer required.

Jan 20/83 22-31-101 Page 401
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.