Aviation Partners Boeing 757-200 MAINTENANCE MANUAL SUPPLEMENT  Part II
1 and 12  14.7 + 1.5o (averaged) 
2 and 11  14.7 + 1.5o (averaged) 
3 and 10  14.7 + 1.5o (averaged) 
5 and 8  9.8 + 1.4o (averaged) 
6 and 7  7.5 + 1.0o (averaged) 

NOTE: Review the measured panel positions in step 16 above. If the spoiler panel positions are out of tolerance then adjust the Autostow rod (757-3921). See 27-62-01, Figure 402, page 406.
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Retracting the rod by one FULL turn of the rod end clockwise will retract the spoiler panels 1,2,3,10,11 and 12 by a further 0.36o and panels 5, 6, 7 and 8 a further 0.24o.

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The deflection of panels 1,2,3,10,11 and 12 should add up to 88.2o +9o when the SPEEDBRAKE handle is in the 50% position.

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The deflection of panels 5,6,7,8 must add up to 34.6o + 4.8o when the SPEEDBRAKE handle is in the 50% position.

.  The deflection of all panels totaled together must add up to 122.8 o +13.8o when the SPEEDBRAKE handle is in the 50% position. 17) If adjustment is required, paragraphs 13 through 17 shall be repeated. 18) Use an air data test set to simulate 300 KCAS on the right air data computer (R-ADC). 19) Cycle the SPEEDBRAKE handle to the DN position then to full UP position and back to the
DN and locked position. Verify that the handle forces are normal. 20) Verify the following:
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All SAC module lights are extinguished

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amber AUTO SPEED BRAKE EICAS message is extinguished

. amber AUTO SPDBRK message on overhead panel is extinguished 21) Temporarily disconnect power from Switches S452 & S453 to prevent injury during
subsequent wire removal.  Do this by opening Circuit Breaker C1023 on the P11-1 Panel (Grid location G11) and attaching a DO-NOT-CLOSE tag. a) Refer to Boeing AMM 32-32-18-004 when removing jumper wires. b) Depressurize the left, right, and centre hydraulic systems. Refer AMM 29-11-00 c) Remove jumper wires previously installed per Step i2 in D3208 Pins 2 & 3; and D3192
Pins 2 & 3.
d) Reinstall connectors D3192 and D3208.
e) Reestablish power to Switches S452 & S453 by closing circuit breaker C1023.
f) Pressurize the left, right, and centre hydraulic systems. Refer AMM 29-11-00.

22) Use an air data test set to simulate 150 KCAS on the right air data computer (R-ADC).
23) Select FLAPS 1.
24) Place the airplane in the GROUND mode.  The AUTOSTOW fault light may illuminate

temporarily while the gear is being de-slugged to simulate the GROUND mode. 25) Use an air data test set to simulate 70 KCAS on the right air data computer (R-ADC).Verify the following:
Aviation Partners Boeing
757-200 MAINTENANCE MANUAL SUPPLEMENT  Part II
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All SAC module lights are extinguished

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amber AUTO SPEED BRAKE EICAS message is extinguished
　
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