4) Verify valve No. 6 is open. a) With B flight control switch ON, move control column full travel and check that column force is approximately 25 pounds.
NOTE: If valve is closed, column force will be approximately 60 pounds. This can be verified by positioning B flight control switch to OFF and comparing forces.
5) Verify valve No. 5 is open. a) With B flight control switch ON, move rudder pedals full travel and check that pedal force is approximately 60 pounds.
NOTE: If valve is closed, pedal force will be approximately 160 pounds. This can be verified by positioning B flight control switch to OFF and comparing forces.
6) Verify valve No. 1 is open. a) Position A flight control switch to ON and check that FEEL DIFF PRESS light goes out. 7) Verify valve No. 3 is open. a) With B flight control switch OFF and A flight control switch ON, repeat step 4) a). 8) Verify valve No. 2 is open. a) With B flight control switch OFF and A flight control switch ON, repeat step 5)a).
(c)
Remove hydraulic power (Ref 29-12-0, Hydraulic System B - Maintenance Practices).
(d)
Open any hydraulic isolation shutoff valve found closed during test. Install locking bar over open valves and secure with bolt and nut.
(e)
Open landing gear shutoff valves. Install guard bracket to secure valves in open position.
(f)
Close standby pump NORMAL (No. 1 GEN BUS) and ALTERNATE (No. 2 GEN BUS) circuit breakers on the P6 panel.
(g)
Position alternate arm switch to off.
(h)
Position flight control switches A and B and spoiler switches on.
(i)
Remove electrical power from airplane.
500
29-00 Page 622 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. Jun 20/85
502 Internal Leakage Test Data Sheet
Aug 01/94 (Sheet 1) 29-00
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BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
502 Internal Leakage Test Data Sheet
Aug 01/94 (Sheet 2) 29-00
Page 622B
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
502 Internal Leakage Test Data Sheet
Aug 01/94 (Sheet 3) 29-00
Page 622C
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
502 Internal Leakage Test Data Sheet
Oct 20/85 (Sheet 4) 29-00
Page 622D
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
A/P No. ____________ Pump Mfr. __________ Ser. No. ____________ Date _______________ Recorded Amp Flow (cc/min) (Fig. 604) Max Flow Limit (cc/min)
Pump Used: No. 1 or No. 2 Amps Change Cumulative Increment
as. Establish new basic reference [Step 1.C.(6)(bh)] _________ _______ ________ _____
at. Left main gear and lock leakage [Step 1.C.(6)(bi)] _________ _______ ________ at-as ____ 300
au. Right main gear and lock leakage [Step 1.C.(6)(bj)] _________ _______ ________ au-at ____ 300
av. No. 1 thrust reverser stowed leakage [Step 1.C.(6)(bk)] _________ _______ ________ av-au ___ 300
aw. No. 2 thrust reverser stowed leakage [Step 1.C.(6)(bl)] _________ _______ ________ aw-av ___ 300
500 Internal Leakage Test Data Sheet
Aug 01/94 (Sheet 5) 29-00
Page 622E
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
D. Standby Hydraulic System Internal Leakage Check
(1) General
(a)
The following procedure provides instructions for performing an internal leakage check of the standby hydraulic system to determine the condition of the system based on the degree of internal leakage. By comparing measured leakage to recommended in-service leakage limits, a determination of the system condition can be made.
(b)
Leakage flows are determined by measuring changes in the flow rates during different operating conditions while hydraulic power is applied. Three methods for measuring the flow rates are available: the ammeter method, the flowmeter method and the amp-clamp and multimeter method. 1) The ammeter method uses an ammeter connected in series with one phase of
the standby pump. The leakage rates are determined by measuring the current and current changes of the pump. These current changes are then related to an amperage versus flow rate chart (Fig. 608).
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