(bi) Open No. 1 landing gear isolation valve. Record difference between steps (bh) and (bi) as leakage for left main gear and lock. Check that flow does not exceed 300 cc/min.
(bj) Open No. 2 landing gear isolation valve. Record difference between steps (bi) and (bj) as leakage for right main gear and lock. Check that flow does not exceed 300 cc/min.
(bk) Switch No. 1 thrust reverser to OVERRIDE. Record difference between steps (bj) and (bk) as leakage at No. 1 thrust reverser in stowed position. Check that flow does not exceed 300 cc/min.
(bl) Switch No. 2 thrust reverser to OVERRIDE. Record difference between steps (bk) and (bl) as leakage at No. 2 thrust reverser in stowed position. Check that flow does not exceed 300 cc/min.
(7) Check Internal Leakage (Procedure 4)
NOTE: The following procedure provides a method of locating and checking the condition of a single component without disturbing other components or subsystem.
(a)
Prepare for check per par. C.(3).
(b)
If ammeter is used, set for highest range and record amp readings to nearest 0.1 amp. If S.P.E.C. voltmeter is used, record readings to nearest 1.0 millivolt.
(c)
If flowmeter is used, record reading to nearest 100 cc/min.
(d)
Determine suspected system and component. See Fig. 605 to locate steps within procedure 3 to perform unique test of component and determine its condition.
(e)
Determine if additional testing is required. If not, restore airplane to normal per par. C.(10).
(8) Check Internal Leakage SP-177 Autopilot Actuators using F80217-101 Test Set (Procedure 5).
NOTE: Two autopilot actuator internal leakage test procedures are provided in the following paragraphs. Section C(8) utilizes the F80217-103 Test Set and section C(9) utilizes the AFCS BITE. Either of these two procedures may be used to test the internal leakage of the autopilot actuators.
(a)
Prepare for check per par. C.(3).
(b)
If ammeter is used, set for highest range and record amp readings to nearest 0.1 amp.
(c)
Test autopilot B aileron actuator. 1) Open AUTOPILOT circuit breakers (P6 and P18). 2) Remove connector D1691 from B aileron autopilot actuator. 3) Install J2 lead to test set and B aileron autopilot actuator connector. 4) Connect power cable of test set to D152 electronic equipment rack service
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outlet. Make certain test set POWER switch is OFF.
5) Establish a basic flow rate with system B flight controls switched ON and isolation valves 4, 5 and 6 closed. Record this flow as base for autopilot B aileron actuator leakage.
6) Set test set switches:
a) SOLENOID EXCITATION [PISTON and ENGAGE] B - ON (2)
b) CURRENT SELECT switch - B T-VALVE
c) SOLENOIDS selector switch - B NORMAL
d) SOLENOID ON/OFF switch - ON
e) ACTUATOR SELECT switch - B only
f) POWER switch - ON
CAUTION: PERSONNEL AND EQUIPMENT MUST BE CLEARED FROM SURFACE MOVEMENT AREA PRIOR TO APPLYING POWER TO PREVENT EQUIPMENT DAMAGE OR PERSONNEL INJURY.
7) Adjust B ONLY ACTUATOR SELECT POSITION CONTROL until ailerons are neutral. Allow flow to stabilize and take reading. 8) Difference between flow rate step (c)5) and (c)7) is leakage for autopilot B
aileron actuator. Maximum permissible 2000 cc/min. 9) Place POWER switch on test set - OFF. 10) Place SOLENOID EXCITATION [PISTON/ENGAGE] switches (2) - OFF. 11) Remove J2 cable from autopilot B aileron actuator. 12) Install connector D1691 to autopilot B aileron actuator. 13) Close AUTOPILOT circuit breakers (P6 and P18).
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