(f)
Thrust levers: mid-position
(g)
Landing gear handle: OFF
(h)
On AFCS control panel:
1) F/D switch ON
2) A/P OFF
3) SPEED switch OFF
4) A/T switch to ARM
(3)
Select CLB on PDC CDU.
NOTE: Do not engage PDC.
(4)
On AFCS control panel, set SPEED switch to OFF and select an altitude of 24,000 feet.
(5)
Press PDC button on AFCS control panel to ON and verify that thrust levers advance.
(6)
On flight mode annunciator panels, verify that:
(a)
A/P annunciates PDC SPD
(b)
A/T annunciates EPR
(c)
PDC annunciates CLB
(7)
Verify that CLB EPR Limit displayed on the PDC CDU is approximately 2.0.
(8)
Set the EPR input above the CLB EPR limit. Verify that thrust levers retard.
CAUTION: DO NOT EXCEED 42 INCHES OF MERCURY ABSOLUTE ON INLET PRESSURE LINE, OR 80 INCHES OF MERCURY ABSOLUTE ON EXHAUST PRESSURE LINE WHILE LINES ARE CONNECTED TO TRANSMITTER. MAXIMUM PRESSURE DIFFERENTIAL SHALL NOT EXCEED 51 INCHES OF MERCURY DURING THESE TESTS TO PREVENT PERMANENT DAMAGE TO THE TRANSMITTER.
(9)
Set the EPR input to 1.0. Verify that throttle levers advance.
(10)
Disengage autothrottle and reset the A/T disengage lights.
5B8
Oct 20/84 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 22-31-01 Page 515
G. Sensor Inputs Test
(1)
Establish the following initial conditions:
(a)
Angle-of-airflow sensor: 5 degrees trailing edge up
(b)
Radio altitude: 2500 feet
(c)
Both EPR: 1.5
(2)
Verify the following initial conditions (same as last test)
(a)
Simulated airspeed: 325 knots
(b)
Simulated altitude: 20,000 feet
(c)
Flap position: 0 degrees
(d)
LANDING GEAR-LIGHTS circuit breaker: open
(e)
Thrust levers: mid-position
(f)
Landing gear handle: OFF
(3)
Select CRZ on PDC CDU.
(4)
On AFCS control panel:
(a)
Set F/D switches to OFF
(b)
Verify A/P is OFF
(c)
Select 20,000 feet altitude
(d)
Verify SPEED switch is OFF
(e)
Set A/T switch to ARM
(5)
Set both F/D switches to ON. Verify that IAS/MACH window on the AFCS control panel indicates 325 knots. Check that SPEED is annunciated on the A/T section of the flight mode annunciators.
(6)
Rotate the left angle-of-airflow sensor vane trailing edge up to 7.5 degrees. Verify that the FAST/SLOW indicator on the ADI indicates SLOW and that the thrust levers advance.
(7)
Return the angle-of-airflow sensor vane to 2 degrees trailing edge up and the thrust levers to mid-position. Verify that SPEED is still annunciated on the A/T section of the flight mode annunciator.
(8)
Disengage the autothrottle and reset the warning lights. Tilt the vertical gyro in left roll to approximately 45 degrees at the rate of approximately 10 degrees per second. Check that the FAST/SLOW indicators move slightly toward SLOW while the gyro is rolling.
(9)
Level the vertical gyro and wait for the FAST/SLOW needle to center.
(10)
Repeat steps (8) and (9) for a right roll.
(11)
Tilt the vertical gyro to a 10-degree pitch up attitude. Verify that both FAST/SLOW pointers initially move toward SLOW and then slowly return to center.
(12)
Tilt the vertical gyro to a 10-degree pitch down attitude. Check that both FAST/SLOW pointers initially move toward FAST and then slowly return to center.
(13)
Engage the autothrottle in SPEED mode. Set thrust levers to mid-position, lower the flaps to 2 degrees and check that the thrust levers drive all the way aft and both FAST/SLOW pointers move toward FAST.
(14)
Level the vertical gyro.
(15)
Set flaps to 0 degrees.
(16)
Return the thrust levers to mid-position.
(17)
Set VERTICAL GYRO switch to CAPT ON AUX and repeat steps (9) thru (16) using the auxiliary VG instead of VG No. 1.
(18)
Set VERTICAL GYRO transfer switch to NORMAL.
(19)
Disengage the autothrottle and reset the A/T warning lights.
(20)
Continue with N1 tach signal test.
NOTE: The error signals slowly wash out so that the FAST/SLOW needle slowly returns to center.
5B8
22-31-01 Page 516 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. Oct 20/84
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本文鏈接地址：737 AMM 飛機(jī)維護(hù)手冊(cè) AUTO FLIGHT 自動(dòng)飛行 2(97)
