Aviation Partners Boeing
757-200 MAINTENANCE MANUAL SUPPLEMENT  Part II
f.
PRESS, LSK 2L (FUEL) on CDU-1

g.
  TYPE, 180 (81.6) on CDU-1

h.
   PRESS, LSK 3L (ZFW) on CDU-1

i.
 Verify that (GR WT) line 1L is 222.0 [222,000lbs].

7)  Verify that there are not any fault lights on the SAC module. See task 27-62-00-000-502, step 17 to clear faults if necessary.  (Determine the reason for the fault light(s) if the fault light(s) do not clear).
8)  Use an air data test set to simulate 150 KCAS on the right air data computer (R-ADC).
9)  a) Place the airplane in the AIR mode.  See the maintenance manual for instructions to place the airplane in AIR mode (AMM 32-09-02-042-001). The AUTOSTOW fault light may illuminate temporarily while the gear is being slugged to simulate the AIR mode.
b)  Temporarily remove power from Left & Right Gear Tilt Pressure Switches S452 &
S453 (ref: WDM 27-62-11) to prevent injury during subsequent wire installations. 
Do this by opening Circuit Breaker C1023 on the P11-1 Panel (Grid location G11)
and attaching a DO-NOT-CLOSE tag.

i.  Refer to Boeing AMM 32-32-18-004 when installing jumper wires.
ii.  Depressurize the left, right, and centre hydraulic systems. Refer AMM 29-11-00
iii.  At the main landing gear stabilizing link, disconnect wire connectors D3192 and D3208 from switches S452 and S453, respectively.
iv.  
Install jumper wire from Connector D3208 Pin 2 to Pin 3.  Wire to be made from BMS13-60, Type 2, Class 1, 20 gauge and installed per SWPM (D6-54446).

v.  
Install jumper wire from Connector D3192 Pin 2 to Pin 3.  Wire to be made from BMS13-60, Type 2, Class 1, 20 gauge and installed per SWPM (D6-54446).

vi.  Reestablish power by closing circuit breaker C1023.
vii. Pressurize the left, right, and centre hydraulic systems. Refer AMM 29-11-00. 10) Use an air data test set to simulate 200 KCAS on the right air data computer (R-ADC). 11) Select FLAPS UP
The AUTOSTOW actuator located below the center control stand in the flight deck will cycle

(extent and retract).
NOTE: The above step checks that the “In-flight” system test and ensures that AUTOSTOW
system will detect a heavy weight airplane.

12) Wait several seconds, then place SPEEDBRAKE handle to the full UP position.
13) Use an air data test set to simulate and maintain 340 KCAS on the right air data computer (R-ADC). The SPEEDBRAKE handle moves to the 50% mark on the light plate at approximately
330 KCAS).
14) Do not manually move the SPEEDBRAKE handle.
15) Shake out the lateral controls system by rotating control wheel up to a maximum of +10.0
degrees (1.5 units of wheel) and systematically reducing amplitude to zero. 16) Measure the spoiler panels.  If the following panel angles are with in the noted ranges then the total allowed panel deflection equal to 122.8+13.8o (see NOTE below) will be satisfied.  Use these results to calculate the total deflection as described in the note below.
　
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