(a)
AC Ammeter - Amp ranges 0-25 with a short circuit selector switch. The switch contacts should be the make-before-break type to prevent arcing during mode selection. The meter scales shall permit accurate reading to the nearest 0.10 amp on the 0-25 scale.
(b)
Cable Assembly, Hydraulic Leak Check - F80135-10 (Fig. 606).
(c)
Hydraulic service cart - variable flow pump capable of 0 to 3000 psi
(d)
Flowmeter - should have capability to measure flows of 50 to 20,000 cc/min with a remote readout of sufficient length to be located in the control cabin
(e)
Digital multimeter - Simpson Model 461
(f)
Amp-Clamp Adapter - Model 153 (used with digital multimeter)
(g)
Landing gear downlocks (Ref 32-00-01)
(3)
Prepare for Check
(a)
Connect external power and adjust voltage to 114-116 volts as 400 ±5 Hz.
NOTE: Do not conduct any other electrical operation on aircraft during this test.
(b)
Install landing gear downlocks (Ref 32-00-01), and establish communication between ground and crew compartment.
(c)
If ammeter method is used, install ammeter in series with one phase of standby pump. 1) Disconnect pump electrical connector. 2) Connect one end of test harness to pump connector. 3) Connect other end of harness to wiring disconnected from the pump.
CAUTION: CHECK THAT THE AMMETER IS IN THE SHORT CIRCUIT POSITION UNTIL THE SYSTEM HAS STABILIZED. SWITCH AMMETER INTO CIRCUIT ONLY AT TIME OF TAKING A READING. THE STARTING CURRENT FOR THE MOTOR PUMP IS APPROXIMATELY 100 AMPS. THIS WILL DESTROY THE AMMETER IF THE AMMETER IS IN CIRCUIT.
(d)
If flowmeter is used, install flowmeter in standby pump pressure line.
(e)
Position alternate flap switch to ARM.
(f)
Check that systems A and B hydraulic systems are off.
(g)
Operate standby system through several cycles to bring fluid to operating
temperature.
500
Feb 20/84 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 29-00 Page 623
F85966
Ammeter Wiring Harness 500
29-00 Figure 606 May 20/82
Page 624
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
(h)
Check standby module for sound and hot spots. If a hissing noise is present and module return line is hot, replace pressure relief valve before performing test.
(i)
If Amp-clamp and multimeter are used, perform following: 1) Gain access to standby system pump circuit breaker C847 in P6-11 or C848 in P6-12 as applicable. 2) Select relay and place amp-clamp adapter around any one of the three wires
connected to the load side of the circuit breaker. 3) Connect leads between multimeter and amp-clamp adapter. 4) Provide electrical power to airplane.
CAUTION: CARE SHOULD BE TAKEN TO ENSURE THAT AMP-CLAMP DOES NOT COME IN CONTACT WITH CIRCUIT BREAKER TERMINALS WHICH CAN CAUSE DAMAGE TO EQUIPMENT.
NOTE: If a ground cart is used for electrical power, it is essential that the voltage be maintained within 114 to 116 volts ac at 400 +5 Hz. No other electrical operation is permitted during this test.
(4) Perform Internal Leakage Check
(a) After preparation for check has been completed, accomplish the following steps and follow instruction given in Fig. 607 to determine component internal leakage. 1) Pressurize the B hydraulic system via the electric motor pump. 2) Position B system flight control switch to ON. 3) Position ALTERNATE FLAP switch to ARM. Allow system to stabilize and take
basic reference reading, enter as step 1 in Fig. 607. 4) Position A system flight control switch to STDBY RUD. Allow flow to stabilize
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