(c)
Make sure the POWER switch on the test set is OFF.
(d)
Connect the power cable of the test set to the service outlet of the D152 electronic equipment rack (if it is not connected).
(e)
Open the No. 3 isolation valve (in the tail compartment).
(f)
Read the amperage or the flow value (for hydraulic system A) and write it here:
Amperage _______________(subtract system A basic current first)
Flow _______________ cc/minute (Value 7)
(g)
Make a mark to show the position of the trailing edge of the right elevator.
(h)
Put the switches on the test set in these positions: 1) A SOLENOID EXCITATION PISTON switch -ON 2) A SOLENOID EXCITATION ENGAGE switch -ON 3) CURRENT SELECT switch -A T-VALVE 4) SOLENOIDS selector switch -A NORMAL 5) SOLENOID ON/OFF switch -ON 6) ACTUATOR SELECT switch -A ONLY
WARNING: MAKE SURE THAT PERSONS AND EQUIPMENT ARE CLEAR OF ALL
_______ CONTROL SURFACES. THE CONTROL SURFACES CAN MOVE WHEN YOU SUPPLY POWER TO THE TEST SET. THIS CAN CAUSE INJURY TO PERSONS AND DAMAGE TO EQUIPMENT.
(i)
Put the POWER switch (on the test set) in the ON position.
(j)
Adjust the A ONLY ACTUATOR SELECT POSITION CONTROL until the trailing edge of the right elevator is less than 1/2 inch from the mark you made.
(k)
After the flow becomes stable, read the amperage or the flow value and write it here:
Amperage _______________(subtract system A basic current first)
Flow _______________ cc/minute (Value 8)
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BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A
737-300/400/500MAINTENANCE MANUAL
(l)
Subtract the Value 7 flow from the Value 8 flow. The difference must be less than 2000 cc/minute.
(m)
Put the POWER switch (on the test set) in the OFF position.
(n)
Put the B SOLENOID EXCITATION PISTON and the B SOLENOID EXITATION ENGAGE switches in the OFF position.
(o)
Disconnect the J1 lead from the elevator autopilot actuator.
(p)
Connect the D1681 connector to the elevator autopilot actuator.
S 866-144
(12) Remove the DO-NOT-CLOSE tags and close these circuit breakers:
(a)
P6-2
1) AFCS B SNSR EXC AC
2) AFCS B FCC DC
3) AFCS B ENGAGE INTLK
4) AFCS WARN LIGHT
5) AFDS MCP CRS 2 DC
6) AFCS MACH TRIM B AC
7) AFCS MACH TRIM B DC
(b)
P18-1 1) AFCS A SNSR EXC AC 2) AFCS A FCC DC 3) AFCS A ENGAGE INTLK 4) AFCS WARN LIGHT 5) ALL EXCEPT AIRPLANES WITH -914FCC;
AFDS Ail Force Liimiter 6) AFDS MCP DC 7) AFCS MACH TRIM A AC 8) AFCS MACH TRIM A DC
S 846-145
(13) Do the procedure to put the airplane back to its usual condition.
TASK 29-00-00-796-146
8. Internal Leak Check for the Autopilot Actuators (Procedure 4B)._______________________________________________
A. General
(1) There are two internal leak check procedures for the autopilot actuators (Procedures 4A and 4B). This procedure (4B) uses the the built-in-test equipment in the Digital Flight Control System (DFCS BITE) to engage the autopilot actuators. Procedure 4A uses the F80217-103 Test Set to engage the autopilot actuators. If you do one of the procedures, it is not necessary to do the other.
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