NOTE: This step engages the A OR B A/P's for the aileron and elevator.
1) Turn the control switch on the Control Display Unit (CDU) to the STBY
position. 2) Press RCL and - key on CDU. 3) Press PAGE key on CDU until the CDU displays A/P TEST . . . .
SYMPTOM/PIREP TEST DESIRED. 4) Press ENT keys on CDU and the CDU will change message to GROUND FUNCT. 5) Press ENT key on CDU and the CDU will change the message to VERIFICATION. 6) Press ENGAGE key on CDU and the CDU will change the message to LRU INTERFACE. 7) Press ENT key on CDU and the CDU will change the message to LAND VERIFY. 8) Press ENT key on CDU and the CDU will change the message to RIGGING. 9) Press ENGAGE key on CDU and the CDU will change the message to CHAN A ONLY. 10) Press ENT key on CDU and the CDU will change the message to CHAN B ONLY. 11) Press ENT key on CDU and the CDU will change the message to CHAN A & B. 12) Press ENGAGE key on CDU and the CDU will change the message to
OPEN AURAL WARNING C/B. 13) Make sure both F/D (Flight Direct) switches are OFF. 14) Open AURAL WARNING C/B and press ENGAGE key on CDU and the
CDU will change the message to OPEN STAB TRIM C/B. 15) Open STAB TRIM C/B and press ENGAGE key on CDU and the CDU will change the message to VERIFY THAT SURFACES ARE CLEAR.
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16) Make sure control surfaces are clear and press ENGAGE and the CDU will change the message to PRESSURIZE BOTH HYDRAULIC SYSTEMS.
17) Make sure hydraulic system B is pressurized and press ENGAGE key on CDU and the CDU will change the message to ELEC PUMPS ON, PARK BRAKE ON, GRD INTCT OPEN.
18) Ignore ELEC PUMPS ON, PARK BRAKE SET, GRD INTCT OPEN message and press ENGAGE key on CDU and the CDU will change the message to ELEV TEST DESIRED.
19) Press ENT key on CDU and the CDU will change the message to AILERON TEST DESIRED.
20) Press ENGAGE key on CDU and the CDU will change the message to REF TO MM FOR AIL RIGGING.
21) Ignore REF TO MM FOR AIL RIGGING message, press ENGAGE key on CDU and the CDU will change the message to SET A/P A ENGAGE TO CMD.
22) Ignore SET A/P A ENGAGE TO CMD and ENGAGE A/P B TO CMD.
(g)
Record difference between steps (c) and (g) as total system B leakage. Check that total flow does not exceed 14,500 cc/min.
(h)
Disengage A/P B.
(i)
Position system B spoilers and flight controls to OFF. Record flow for system B basic reference.
(j)
Open ground interconnect valve and position alternate flap switch to OFF.
(k)
Position flap lever to 25 units and allow flaps to stabilize.
(l)
Switch system A spoilers to ON. With control wheel centered, position speed brake handle mid way between armed and flight detent.
(m)
Position system A flight controls switch to ON.
(n)
Engage A/P A to CMD.
(o)
Place landing gear handle in down position.
(p)
Record difference between readings in steps (i) and (p) as total system A flow. Check that flow does not exceed 22,000 cc/min.
(q)
Press PAGE key on CDU to exit BITE.
NOTE: This step disengages the autopilot actuators.
(r)
Determine from flow readings if procedure 2, 3 or 4 should be performed. If not, restore airplane to normal per par. C.(10).
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A/P No. ____________ Pump Mfr. __________ Ser. No. ____________ Date _______________ Pump Used: No. 1 or No. 2 Recorded Amps Amp Change Flow (cc/min) (Fig. 604) Max Flow Limit (cc/min)
1. System B basic reference [Step 1.C.(4)(c)] a. Total system B leakage [Step 1.C.(4)(g)] b. Establish new system B reference [Step 1.C.(4)(i)] c. Total system A leakage [Step 1.C.(4)(p)] __________ ____________________ __________ a-1 c-b 0 0 14,500 22,000
Internal Leakage Test Data Sheet -Procedure 1 512
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(5) Check Internal Leakage (Procedure 2)
NOTE: The following procedure provides an initial brief check to determine basic and null leakage of major flight control systems.
(a)
Prepare for check per par. C.(3).
(b)
If ammeter is used, set for highest range.
(c)
With system B pump on, record reading for system B basic reference.
NOTE: When ammeter is being used, record amp reading for each step to the nearest 0.1 amp. When flowmeter is being used, record reading for each step to the nearest 100 cc/min. 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(11)
