ELEVATOR CENTERING SPRING-INSPECTION CHECK
EFFECTIVITY
SA ZS-SIA and on SD ST-AIB and on WA N235WA-N241WA GJ B-2509 and B-2510
1. General (Fig. 601)
A. The elevator centering springs are mounted on the aft bulkhead station 1156 (Ref Chapter 27, Elevator 2nd Tab Control System).
B. Equipment and Materials
(1) Ladder on stand for access to tail cone access door.
C. Elevator Centering Spring Inspection
(1)
Remove tail cone access door 3802K.
(2)
Visually inspect elevator centering springs located above elevator fuel actuator. Check that springs are not broken or damaged. If defect is found refer to 27-31-151 for replacement.
(3)
Install tail cone access door 3802R.
May 15/81 22-11-371 Page 601
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
H19380
Elevator Centering Spring Location 580
22-11-371 Figure 601 Feb 15/81
Page 602
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
ANGLE OF AIRFLOW SENSOR - ADJUSTMENT/TEST
EFFECTIVITY
WA N235WA thru N259WA GJ B-2509 and B-2510
1. General
A. The left angle of airflow sensor (ALPHA) is part of the No. 1 stall warning system (Ref 27-32-11). The sensor also provides signals to the auto throttle system and system A AP/FD. The right angle of airflow sensor is part of No. 2 stall warning system (when installed) and provides signals to system B AP/FD. The following tests assure proper operation of autopilot synchro input of either angle of airflow sensor to AP/FD.
2. Equipment and Materials
A. Portable pressure test equipment to simulate 0 to 200 knots airspeed
B. Angle-of-airflow sensor calibrator
(1)
F72786-181 (Preferred) (Use with either Conrac or Rosemont Sensor)
(2)
F72786-101 (Conrac Sensor)
(a) F72786-183 (To modify F72786-101 for use on Rosemont Sensor)
C. DC Voltohmmeter - Simpson Model 260
3. Prepare for Test
A. Provide electrical power. Ensure that circuit breakers on P6 and P18 circuit breaker panels are closed.
B. Verify that heater power is removed from ALPHA sensors.
WARNING: HOT ALPHA VANES CAN CAUSE SEVERE BURNS. BE SURE VANE IS COOL BEFORE TOUCHING.
C. Mount angle-of-airflow calibration tool to applicable ALPHA sensor.
D. Connect pitot static pressure test equipment to air data computer pitot and static sources as required. Maintain ambient static pressure and pitot pressure to produce 200 士5 knots indicated airspeed (KIAS).
CAUTION: INSTRUMENT DAMAGE MAY RESULT IF PRESSURE TEST EQUIPMENT IS NOT CONNECTED PROPERLY. REFER TO CHAPTER 34, AIR DATA INSTRUMENTS, FOR DETAILED INSTRUCTIONS.
4. Test Angle-of-Airflow Sensor
A. Turn on B-hydraulic pressure and place GRD HYDRAULIC INTERconnect switch to OPEN. Verify parking brake is set.
B. Set flaps to 15 units.
C. Set altitude on mode control panel to 10,000 feet.
D. Adjust applicable ALPHA vane to faired condition (vane parallel with airplane axis for left sensor), 14 degrees as indicated on calibration tool; for right sensor, 346 degrees as indicated on calibration tool.
Oct 20/86 22-11-381 Page 501
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
E.
Connect voltmeter to applicable FCC test connector J6-86 and airframe ground. Check that voltage is +4.1 士1.5 VDC.
F.
Position applicable A/P ENGAGE switch to CMD; select V/S mode.
G.
Slowly rotate applicable ALPHA vane trailing edge up until (alpha) flag appears in MCP. Check that ALPHA vane is 0 士1.5 degrees.
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