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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 12) Use an air data test set to simulate and maintain 300 KCAS on the right air data computer (R-
ADC).
13) Place the SPEEDBRAKE handle to the full UP position
14) Use an air data test set to simulate and maintain 340 KCAS on the right air data computer (R-
ADC). Verify the following:
.  
SPEEDBRAKE handle does not move.

.  
all three lights on the SAC module are extinguished

.  
amber AUTO SPEEDBRAKE EICAS message is extinguished

. amber AUTO SPDBRK message on overhead panel is extinguished 15) Use an air data test set to simulate and maintain 300 KCAS on the right air data computer (R-
ADC). 16) Input 222,000 lbs (100,697 kg) in the FMC.
Aviation Partners Boeing
757-200 MAINTENANCE MANUAL SUPPLEMENT  Part II
NOTE:

Values in (x) represent x1000kg. Typed values below are arbitrary, but will work for all aircraft. Any summation of FUEL weight value from 0-123, with ZFW value from 100-220 to give 222 GR WT is acceptable]
a.
When the MENU page is displayed on either CDU, press LSK 1L (FMC) on that CDU.

b.
PRESS, the INIT/REF button on CDU-1.

c.
 PRESS, LSK 6L (INDEX) on CDU-1.

d.
PRESS, 3L (PERF) on CDU-1.

e.
  TYPE, 42 (19.1) on CDU-1

f.
PRESS, LSK 2L (FUEL) on CDU-1

g.
　
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