.  
amber AUTO SPDBRK message on overhead panel illuminates and remains illuminated

.  
the SPEEDBRAKE handle retracts to the 50% detent

6)  Move SPEEDBRAKE handle slowly to the full UP position. Record the SPEEDBRAKE handle forces.
7)  The SPEEDBRAKE handle forces shall increase approximately 20 pounds above the normal forces at the 50% (40 Degrees) handle position and remain constant up to approximately the 60 degrees handle position then increase to 27 pounds for a further 2 degrees i.e. 62 degrees handle position then reduce to zero force above normal and continue at zero force above normal to the full up position. i.e. 78 degrees.
8)  The SPEEDBRAKE handle will remain in the UP position when the handle is released.
9)  Move the SPEEDBRAKE handle to the DOWN position.
10) Press and hold the RIGGING test button on the SAC module for one second. Verify the following occur:
.  
the AUTOSTOW actuator will extend

.  
the TEST IN PROGRESS light on the SAC module extinguishes

.  
amber AUTO SPEED BRAKE EICAS message remains extinguished

.  
amber AUTO SPDBRK message on overhead panel extinguishes

11) Move SPEEDBRAKE handle slowly to the full UP position and back to the DOWN position.  Verify that the forces are normal.
Aviation Partners Boeing
757-200 MAINTENANCE MANUAL SUPPLEMENT  Part II
12) Verify the following:
.
amber AUTO SPEED BRAKE EICAS message is extinguished

.
amber AUTO SPDBRK message on overhead panel is extinguished

. all lights on the SAC module are extinguished 13) Return the airplane to normal configuration.
Aviation Partners Boeing
757-200 MAINTENANCE MANUAL SUPPLEMENT  Part II
27-62-00-000-506
6.  AUTOSTOW System and Airplane System Interface Check
A. General:
1)  This test is a complete system test. It ensures that all system interfaces are functioning and the correct SAC pin programs for the specific airplane have been grounded.
B.  Tool and Equipment Requirements
1) Slugs for landing gear proximity switches
2) Air data test set (simulate air data to the right air data  computer (R-ADC)D.
3) Wire: BMS13-60, Type 2, Class 1, 20 gauge. Approx 24” (can be non-continuous)

C. Procedure
1) Make sure the airplane is in this configuration:

a)  Electrical power is on (AMM 24-22-00/201). Note: If external power is used, supply external power per AMM 24-22-00/201, S862-
036. Failure to supply power per this procedure will cause the “Autostow Fault” light to illuminate on the SAC module.
b)  Hydraulic power is on (AMM 29-11-00/201).
WARNING: Keep persons and equipment away from all control surfaces when hydraulic power is supplied.  Ailerons, elevators, rudder, flaps, slats, spoilers and stabilizer are fully powered surfaces.  Injury to persons or damage to equipment can occur when hydraulic power is supplied.
　
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