(e) The internal leakage check is divided into four separate procedures. 1) Procedure 1 (par. C.(4)) determines total systems A and B internal leakage and the need for further testing. 2) Procedure 2 (par. C.(5)) provides an initial brief check to determine basic and null leakage of major flight control systems. 3) Procedure 3 (par. C.(6)) provides an entire leakage check procedure. Portions of the check may be accomplished as required. 4) Procedure 4 (par. C.(7)) provides a method of locating and checking the condition of a single component without disturbing other components or subsystems. 5) Procedure 5 (par. C.(8) and C.(9)) provides a method of checking the leakage rate of SP-177 autopilot aileron and elevator actuators. Either procedure may be used. 6) Standby Hydraulic System Internal Leakage Check. This procedure does a leak check in the Standby Hydraulic System.
7) Airplanes with the Enhanced Rudder Control System (RSEP) (POST-SB 27-1252); Procedure 6 provides an internal leak check for the Rudder Power Control Unit (PCU). You use this procedure to find the internal leakage of the Rudder Power Control Unit.
F86261
Ammeter Wiring Harness 597
29-00 Figure 602 May 01/03
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(2)
Equipment and Materials
(a)
AC Ammeter – Amp ranges 0-25 and 0-50 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 and 0.20 amp on the 0-50 scale
(b)
Cable Assembly, Hydraulic Leak Check – F80135-1 (Fig. 602).
(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 - Model 8024B, John Fluke Mfg. Co. Inc., Redmond, WA
(f)
Amp-Clamp Adapter -AC Current, Model 80i-600, John Fluke Mfg. Co. Inc., Redmond, WA (used with digital multimeter)
(g)
Landing gear downlocks (Ref 32-00-01)
(h)
Mechanic's stethoscope, GA 111D, Snap-on-Tools Corp., Kenosha, WI
(i)
Test Set - SP177/SP300 Autopilot Elevator/Rudder/Aileron & Spoiler -P/N F80217-101
(3)
Prepare for Check
(a)
Install landing gear downlocks in main and nose gear (Ref 32-00-01). Check that main gear is blocked and that block and tow bar are removed from nose gear. Establish communications between ground and control cabin if ammeter or flowmeter method is used.
(b)
Ammeter Method 1) Disconnect airplane wiring from No. 1 or 2 system B pump at the pump
connector. 2) Connect one end of the test harness to the B pump connector. 3) Connect the other end of the harness to the airplane wiring disconnected from
the pump.
4) Place the ammeter in short circuit position.
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 180 AMPS. THIS WILL DESTROY THE AMMETER IF THE AMMETER IS IN CIRCUIT.
(c)
Flowmeter Method 1) Connect hydraulic service cart to ground service module. 2) Connect flowmeter remote readout to service cart and place remote indicator in
control cabin.
3) Start hydraulic service cart.
(d)
Amp-clamp and Multimeter method 1) Gain access to system B pump relays located in P6-4 panel. R23 relay is for No. 1 pump. R24 relay is for No. 2 pump. 2) Select relay and place amp-clamp adapter around any one of three wires
protruding forward from relay.
3) Connect leads between multimeter and amp-clamp adapter.
502 May 01/03 29-00
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BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
(e)
Provide electrical power (Ref 24-22-00 MP). 1) Place battery switch to ON.
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. 中國航空網 www.k6050.com 航空翻譯 www.aviation.cn 本文鏈接地址：737 AMM 飛機維護手冊 液壓 HYDRAULIC POWER(9)
