(t)
Push the ACTUATED indicator to change it to black.
(u)
Push the TEST 2 button on the E-11 shelf. 1) Make sure the ACTUATED indicator changes to white.
(v)
Push the ACTUATED indicator to change it to black.
S 844-059
(3)
Put the airplane in its initial condition.
(a)
Remove pressure from hydraulic system A and B, if it is not necessary (AMM 29-15-00/201).
(b)
Remove electrical power, if it is not necessary (AMM 24-22-00/201).
P. Test for the M1190 Circuit Card (Engine Speed Detector)_______________________________
S 844-060
(1)
Prepare for the test:
(a)
Make sure the ground locks are installed on all the gear (AMM 32-00-01/201).
(b)
Supply electrical power (AMM 24-22-00/201).
(c)
Supply hydraulic power to systems A and B (AMM 29-15-00/201).
(d)
Open these circuit breakers on the P6 panel:
1) ENG #1, N2 TACH IND
2) LDG SYS XFR VALVE - SECONDARY CONTROL
(e)
Open the left fan cowl panel on Engine #1 (AMM 71-11-02/201).
(f)
Disconnect electrical connector D552 from the N2 sensor (AMM 77-12-00/501 for location).
(g)
Connect the applicable cable from the test box to the D552 connector.
(h)
Connect a function generator to the mating receptacle on the test box.
(i)
Close the ENG #1, N2 TACH IND circuit breaker on the P6 panel.
(j)
Supply a 467.5 Hz signal 3.0 |0.5v ac signal as measured on the DVM terminal on the test box.
NOTE: The voltage on the voltmeter will vary with the
____ frequency selected. Keep the input voltage to the test box at 3 volts so the system parameters stay constant.
1) Make sure the N2 LED display shows 25 |0.1% N2. 2) Make sure the pointer shows 25 |0.5% N2.
(k)
Open the LDG GEAR SYS XFR VALVE - PRIMARY CONTROL circuit breaker on the P6 panel.
(l)
Close the LDG GEAR SYS XFR VALVE - SECONDARY CONTROL circuit breaker on the P6 panel.
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32-09-20
ALL ú ú 02 Page 418 ú Jul 12/00
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A
737-300/400/500MAINTENANCE MANUAL
(m) Move the landing gear lever to the OFF position.
S 724-061
(2)
Do a test of the M1190 circuit card:
(a)
Adjust the function generator until the N2 tach for engine no. 1 shows 60%.
(b)
Push and hold the GROUND SENSING test switch on the E-11 shelf.
1) Make sure the ACTUATED indicator on the E-11 shelf stays black.
(c)
Decrease the frequency on the function generator until the N2 tach for engine no. 1 shows 40%. 1) Make sure the ACTUATED indicator on the E-11 shelf changes
to white.
(d)
Release the GROUND SENSING test switch on the E-11 shelf.
(e)
Push the ACTUATED indicator to change it to black.
(f)
Close the LDG GEAR SYS XFR VALVE - PRIMARY CONTROL circuit breaker on the P6 panel.
(g)
Open the LDG GEAR SYS XFR VALVE - SECONDARY CONTROL circuit breaker on the P6 panel.
(h)
Push and hold the GROUND SENSING test switch on the E-11 shelf. 1) Make sure the ACTUATED indicator changes to white.
(i)
Release the GROUND SENSING test switch.
(j)
Push the ACTUATED indicator to change it to black.
S 844-062
(3)
Put the airplane in its initial condition.
(a)
Remove the test equipment: 1) Close the LDG GEAR SYS XFR VALVE - SECONDARY CONTROL circuit breaker on the P6 panel. 2) Open the ENG #1, N2 TACH IND circuit breaker on the P6 panel. 3) Disconnect the test cable from the N2 sensor connector, D552 and connect D552 to the N2 sensor.
4) Close the ENG #1, N2 TACH IND circuit breaker on the P6 panel.
(b)
Close the left fan cowl panel on Engine #1 (AMM 71-11-02/201).
(c)
Remove pressure from hydraulic system A and B, if it is not necessary (AMM 29-15-00/201).
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