(e)
Set flaps to each position shown in Table I. For each flap setting; rotate vane slowly up from no-shake position until control shaker shakes control column. Check that shaker actuates within tolerance specified in Table I.
(5) Test landing gear relay.
(a)
Place sensor vane in a position that actuates control column shaker, then lock vane in this position using portable calibrator.
WARNING: WHEN HANDLING SENSOR VANE DURING THIS TEST, ENSURE VANE IS COLD. VANE COULD CAUSE BURNS.
(b)
Open AURAL WARN circuit breaker on panel P6.
(c)
Place stall warning module switch to NORMAL position. Check that control column shaker stops shaking and stall warning module OFF light illuminates.
(d)
Depress and hold GRD SENSING TEST switch on landing gear electrical module located in electrical/electronic equipment compartment. Check that control column shaker shakes and stal1 warning module OFF light extinguishes.
(e)
Release GRD SENSING TEST switch. Check that control column shaker stops shaking and stall warning module OFF light illuminates.
(f)
Depress and hold AIR SENSING TEST switch on landing gear electrical module located in electrical/electronic equipment compartment. Check that control column shaker shakes and stall warning module OFF light extinguishes.
(g)
Release AIR SENSING TEST switch. Check that control column shaker stops shaking and stall warning module OFF light illuminates.
(h)
Place stall warning module switch to HTR OFF position.
(i)
Remove portable calibrator from angle of airflow sensor.
(j)
Place stall warning module switch to NORMAL position. Check that stall warning module OFF light remains illuminated.
(k)
Close AURAL WARN circuit breaker on P6.
D. Remove external power, if no longer required.
502
Oct 20/85 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 27-32-0 Page 505
ANGLE OF AIRFLOW SENSOR - REMOVAL/INSTALLATION
1. Equipment and Materials
A. Adhesive - BMS 5-95 (Ref 20-30-11)
2. Remove Angle of Airflow Sensor (Fig. 401)
A. Open stall warning, circuit breakers on P18.
B. Remove eight mounting screws surrounding sensor.
CAUTION: DO NOT APPLY ANY FORCE TO SENSOR VANE.
C. Remove sidewall panel alongside captain's position.
D. Disconnect electrical connector.
E. Lightly rock sensor body to break adhesion, then remove sensor.
CAUTION: EXERCISE CARE TO AVOID DAMAGING VANE DURING REMOVAL.
3. Install Angle of Airflow Sensor (Fig. 401)
A. Carefully insert sensor vane through fairing from inside.
NOTE: Conrac and Rosemount angle of airflow sensors are physically and functionally interchangeable.
B. Locate sensor with gasket and filler ring, and install eight mounting screws. Check that drain hole in body skin is aligned with drain hole in gasket and filler ring (drain hole Conrac only).
C. Check that face of sensor is flush with outside fuselage skin within + 0.02 inch. To obtain required flushness, delaminate or replace filler ring. If new filler ring is installed, bond to inside face of skin doubler.
D. Reconnect electrical connector.
E. Refit sidewall panel.
F. Close circuit breakers opened for sensor removal (Ref par. 2.A.).
G. Check that sensor drain hole is not plugged by dirt or due to incorrect installation of gasket and/or filler ring (drain hole Conrac only).
H. Carry out system performance test (Ref 27-32-0, A/T).
501
Jun 20/85 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 27-32-11 Page 401
Angle of Airflow Sensor Installation 501
27-32-11 Figure 401 Feb 20/85
Page 402
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
ANGLE OF AIRFLOW SENSOR - INSPECTION/CHECK
1. Check Angle-Of-Airflow Sensor (Fig. 601)
NOTE: Any vane which shows signs of heater plug migration, deteriorated index hole, bent vane shaft, or other deformation must not be reworked. Any repairs of sensor must not be done without consulting the vendor overhaul manual.
A. Check vane for heater plug migration evidenced by heater plugs not flush with surface plane.
B. Replace sensor showing evidence of heater plug migration.
(1)
Check vane for deformation, nicks, and pitting of leading edge, generally heavier on inboard portion of vane.
NOTE: Some erosion of vane leading edge is to be expected after a few thousand flight hours and will not adversely affect sensor performance. 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 飞行操纵 FLIGHT CONTROLS 2(134)
