(18)
Push the key for INIT/REF (CDU key) to get out of BITE.
(19)
Do the procedure to put the airplane back to its usual condition.
S 866-043
S 846-044
TASK 29-00-00-796-045
5. System Internal Leak Check (Procedure 2).
__________________________
A. General
(1) Use this procedure to find the internal leakage of the systems that use hydraulic power.
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(2)
You must find the changes in the flow of hydraulic fluid (during different conditions of operation) to find the internal leakage rate for each part. There are three procedures to measure the flow: the ammeter procedure, the flowmeter procedure, and the amp-clamp and multimeter procedure.
(a)
To use the ammeter procedure, you connect an ammeter in series with one phase of the motor on the electric motor-driven pump (EMDP). To find the flow you measure the current subtract the applicable system basic current, and use Figure 603 to change it to a flow.
(b)
To use the flowmeter procedure, you install a flowmeter on a hydraulic service cart and read the flow from it.
(c)
To use the amp-clamp and multimeter procedure, you put the amp-clamp adapter around one of the wires connected to a relay for the EMDP. You then read the current on the multimeter (that is connected to the amp-clamp adapter) subtract the applicable system basic current, and use Figure 603 to get the flow. One person can do this procedure from the Control Cabin.
(3)
When you read the ammeter, make a record of the value to the nearest
0.1 ampere. Use Figure 603 to change current to flow.
(4)
When you read the flowmeter, make a record of the value to the nearest 100 cc/minute.
B. References
(1) AMM 29-15-00/201, Hydraulic Systems A, B, and Standby
C. Access
(1) Location Zones
101/102 Control Cabin
216/217 Main Wheel Wells
D. Procedure
S 846-046
(1)
Do the Prepare for an Internal Leak Check procedure.
S 866-047
(2)
Close the No. 1 through No. 6 isolation valves (in the tail
compartment) (Fig. 604).
S 866-050
(3)
If you use the ammeter procedure, set the ammeter to its highest range.
S 866-051
(4)
Remove hydraulic power from system A (if it is on) (AMM
29-15-00/201).
(5)
Make sure the pressure in system B is a minimum of 2800 psi.
S 216-052
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MAINTENANCE MANUAL
ISOLATION VALVES IN THE TAIL COMPARTMENT ASEE 7 ISOLATION VALVES FOR THE LANDING GEAR LOCKING BAR HYDRAULIC LINE (EXAMPLE)
SEE B 6 NO. 6
ISOLATION VALVE LANDING GEAR ISOLATION VALVE FOR THE LEFT MAIN LANDING GEAR FOR THE RIGHT MAIN ISOLATION VALVE (SHOWN OPEN) 5 4 NO. 5 NO. 4
3 NO. 3
2 NO. 2
1 NO. 1
FWD
(LANDING GEAR) ISOLATION VALVE A 7 (TAIL COMPARTMENT) ISOLATION VALVE B
6 7 5 4 3 2 1 NOT ON ALL AIRPLANES RIGHT ELEVATOR PCU AND ELEVATOR AUTO-PILOT ACTUATOR (SYSTEM B) RUDDER PCU/YAW DAMPER (SYSTEM B) FEEL ACTUATOR (SYSTEM B) LEFT ELEVATOR PCU AND ELEVATOR AUTO-PILOT ACTUATOR (SYSTEM A) RUDDER PCU/YAW DAMPER (SYSTEM A) FEEL ACTUATOR (SYSTEM A)
Isolation Valves Figure 604
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