(m)
Difference in control wheel rotation angles between steps (k) and (l) should not exceed 3 degrees.
5C1
Oct 20/87 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 22-11-01 Page 513
5C1
22-11-01 Page 514 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. Oct 20/87
NOTE: Unsymmetrical stop indicates limiter cam is not properly centered by detent spring.
(14)
Check Angle of Airflow (ALPHA) sensor.
(a)
Set the flaps to 15 units.
(b)
Select 10,000 feet altitude on MCP.
(c)
Verify that heater power is removed from ALPHA vanes.
WARNING: HOT ALPHA VANES CAN CAUSE SEVERE BURNS. BE SURE VANE IS COOL BEFORE TOUCHING.
(d)
Mount angle-of-airflow sensor calibration tool to left side ALPHA vane.
(e)
Adjust left ALPHA vane to faired condition (vane parallel with airplane axis). Check that voltage at A FCC J6-86 is +4.1 +1.5 vdc.
(f)
Place A/P ENGAGE A switch to CMD and select V/S mode. Slowly rotate left side ALPHA vane trailing edge up until α
flag appears on MCP. Check that reading on tool is 0 +1.5 degrees.
NOTE: Rosemount (sweep-back wing) angle-of-airflow sensors have a correction factor stamped on trailing edge of vane. Positive (+) offset (CCW) and negative (-) offset (CW) must be added to vane tool reading.
(g)
Disengage autopilot. Return vane to level.
(h)
Repeat steps (c) thru (g) using right vane, checking voltage on B FCC and using A/P ENGAGE B switch.
(i)
Raise flaps.
(15)
Check Flap position sensors (Airplanes with CONRAX [straight wing] stall warning vane)
(a)
Lower trailing edge flaps to 5 units. Set both ALPHA vanes to level (airplane waterline). Check that voltage at both A and B FCC J6-91 is -6.2 士2 VDC.
(b)
Place A/P ENGAGE A switch to CMD and select ALT HOLD mode. Simulate flight mode. Place A/T switch on MCP to ARM.
(c)
Slowly increase pitot airspeed input (1 knot/sec) until VF flag appears on MCP. Observe that VF flag appears at 218 士5 knots as displayed in MCP IAS/MACH window and A/T annunciation on FMA's show SPEED. Slowly reduce airspeed input. Observe that VF flag disappears at 1 to 7 knots below the pull in value. Disengage A/P and A/T. Reduce airspeed to 150 knots.
(d)
Set flaps to 15 units. Repeat step (b) and (c). Observe that VF flag appears at 188 士5 knots and disappears at 1 to 7 knots below the pull in value.
(e)
Set flaps to 25 units. Repeat step (b) and (c). Observe that VF flag appears at 183 士5 knots and disappears at 1 to 7 knots below the pull in value.
(f)
Set flaps to 40 units. Repeat step (b) and (c). Observe that VF flag appears at 163 士5 knots and disappears at 1 to 7 knots below the pull in value.
(g)
Repeat steps (c) thru (f) for channel B autopilot.
(h)
Restore airplane to ground mode and return airspeed to 200 knots.
505
Jun 20/88 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 22-11-01 Page 515
(15A) Check flap position sensor (Airplanes with ROSEMOUNT [sweep wing] stall warning vane)
(a)
Lower trailing edge flaps to 5 units. Set both ALPHA vanes to level (airplane waterline). Check that voltage at both A and B FCC J6-91 is -6.2 士2 vdc.
(b)
Place A/P ENGAGE A switch to CMD and select V/S mode. Simulate flight mode. Place A/T switch on MCP to ARM. Verify A/T annunciator shows ARM.
(c)
Push SPEED pushbutton, verify that A/T annunciator shows ARM.
(d)
Slowly increase pitot airspeed input (1 knot/sec) until VF flag appears on MCP. Observe that VF flag appears between 215 and 225 knots as displayed in MCP IAS/MACH window.
(e)
Disengage A/P and A/T. Reduce airspeed to 150 knots.
(f)
Set flaps to 15 units. Repeat steps (b) thru (d). Observe that VF flag appears between 188 and 195 knots.
(g)
Set flaps at 25 units. Repeat steps (b) thru (d). Observe that VF flag appears between 183 and 190 knots.
(h)
Set flaps at 40 units. Repeat steps (b) thru (d). Observe that VF flag appears between 160 and 170 knots.
(i)
Repeat steps (d) thru (h) for channel B autopilot.
(j)
Restore airplane to ground mode and return airspeed to 200 knots.
(16)
Test Radio Altimeter, NAV Test Inhibit and CWS Option
(a)
Simulate 1 dot fly-up glideslope, centered localizer on NAV-1. Press radio altimeter No. 1 test switch. Verify that captain's radio altimeter's altitude indication changes.
中国航空网 www.aero.cn
航空翻译 www.aviation.cn
本文链接地址：737 AMM 飞机维护手册 AUTO FLIGHT 自动飞行 1(103)
