22-24-00
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757 MAINTENANCE MANUAL
 (b)  
6L16, PITOT HEAT AUX L

 (c)  
6L21, PITOT HEAT R AUX

 (d)  
6L22, PITOT HEAD F/O MAIN

 (e)  
6L23, R AOA HEAT

 (f)  
6L24, TAT PROBE HEAT

 S 865-018
 (7)  Make sure these circuit breakers on the overhead circuit breaker panel, P11, are closed:
 (a)  
11C6, CSEU 1L AC or FLT CONT ELEC 1L AC

 (b)  
11C7, CSEU 1L DC or FLT CONT ELEC 1L DC

 (c)  
11C8, CSEU 2L AC or FLT CONT ELEC 2L AC

 (d)  
11C9, CSEU 2L DC or FLT CONT ELEC 2L DC

 (e)  
11C12, STAB TRIM SHUTOFF LEFT

 (f)  
11C13, STAB TRIM SHUTOFF RIGHT

 (g)  
11C14, FSEU-2 PWR or FLAP SLAT ELEC UNIT 2 POWER

 (h)  
11C15, FSEU-2 CONT or FLAP SLAT ELEC UNIT 2 CONT

 (i)  
11C16, FSEU-2 SENSOR or FLAP SLAT ELEC UNIT 2 SENSOR

 (j)  
11C30, LANDING GEAR POS SYS 1

 (k)  
11F19, STAB POS MOD CENTER

 (l)  
11G12, FSEU-1 PWR or FLAP SLAT ELEC UNIT 1 POWER

 (m)  
11G13, FSEU-1 CONT or FLAP SLAT ELEC UNIT 1 CONT

 (n)  
11G14, FSEU-1 SENSOR or FLAP SLAT ELEC UNIT 1 SENSOR

 (o)  
11G15, STAB POS MOD LEFT

 (p)  
11G17, CSEU 1R AC or FLT CONT ELEC 1R AC

 (q)  
11G18, CSEU 1R DC or FLT CONT ELEC 1R DC

 (r)  
11G21, FSEU-3 PWR or FLAP SLAT ELEC UNIT 3 POWER

 (s)  
11G22, FSEU-3 CONT, or
 FLAP SLAT ELEC UNIT 3 CONT, or
 FSAM CONTROL

 (t)  
11G23, FSEU-3 SENSOR, or
 FLAP SLAT ELEC UNIT 3 SENSOR, or
 FSAM SENSOR

 (u)  
11G24, STAB POS MOD RIGHT

 (v)  
11G27, CSEU 2R AC or FLT CONT ELEC 2R AC

 (w)  
11G28, CSEU 2R DC or FLT CONT ELEC 2R DC

 (x)  
11H10, STAB TRIM LEFT POS IND

 (y)  
11H11 or 11C05, STAB TRIM CONT LEFT

 (z)
11H19, STAB TRIM POS IND RIGHT (aa) 11H20, STAB TRIM CONT RIGHT (ab) AIRPLANES WITH ALTERNATE STAB TRIM SWITCHES ON THE CONTROL

 STAND;
 11B19, STAB TRIM ALT
 (ac) 11P28, R IND LTS 1
 (ad) 11S19, AIR/GND SYS 2

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BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A
757
MAINTENANCE MANUAL

 S 865-019
 (8)  Pressurize the Captain's and the F/O's pitot system (Ref 34-11-00).
 NOTE: This will be referred to during the test as the air data
____
 computer (ADC) airspeed.

 S 865-020
 (9)  Pressurize the captain's and the first officer's static system (Ref 34-11-00).
 NOTE: This is referred to during the test as the pressure altitude.
____
 S 865-021
 (10) Pressurize the Auxiliary No. 1 and the No. 2 pitot system (Ref 34-11-00).
 NOTE: This is referred to during the test as the elevator feel
____
 computer (EFC) airspeed.

 S 985-022
 (11)
 Set the ADC airspeed to 200 |5 knots.

 S 985-023

 (12)
 Set the EFC airspeed to 224 |20 knots.

 NOTE: This value will not change during the test.
____
 S 985-024
 (13) Set the ADC and EFC pressure altitude to 30,000 |1000 feet.
 NOTE: This value will not change during the test.
____
 S 865-003
 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 A PERSON OR DAMAGE TO EQUIPMENT CAN OCCUR WHEN HYDRAULIC POWER IS SUPPLIED.
 (14) Pressurize the right and the center hydraulic systems (Ref 29-11-00).
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