B. Pitot-Static Test Set - ERA 82305
C. VOR/LOC/GS Signal Generator - Collins, 972Q-4; Tel Inst Corp, T30B/B; Inst Flt Research, NAV 401L; Cossor, CRM555A
D. Tilt table (for vertical gyro) - Boeing Part Number 2TSJ60B00002
(1)
VG Extension Cable (for Bendix VG) - Boeing Tool Number F80138-1
(2)
VG Extension Cable (for Sperry VG) - Boeing Tool Number F80139-1
(3)
Tilt Table Adaptor (for Sperry VG) - Boeing Tool Number F70194-1
Feb 20/85 22-31-01 Page 501
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
E. 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)
F. EPR Test Set - Howell, H315; Smith Industries 3204KTQ-1
NOTE: EPR Test Set comes with one set of hoses and fittings. A second set of hoses and fittings are required to simulate EPR for both engines simultaneously.
G. N1 Tach Simulator:
(1)
Quantum Dynamics, CA-11-FS
plus N1 Simulator Adapter Cable - F80228-1
(2)
Alternate N1 Tach Simulator: Hewlett Packard HP201C (signal generator capable of 10 volts RMS output minimum, 26 volts RMS maximum)
3. Prepare for Test
A. Mount vertical gyro on tilt tables to measure pitch displacement. Connect gyros to system using vertical gyro extension cable. Level tilt table unless required otherwise.
B. Set switch on the No. 1 stall warning computer in the HEATER OFF position and open AC breaker on stall warning systems.
NOTE: This removes heater power from the left side angle-of-airflow (Alpha) vane so that the vane can be handled without danger of burns.
C. Verify that all circuit breakers are closed for following systems:
(1)
Autothrottle (A/T) system
(2)
Automatic Flight Control System (AFCS)
(3)
Attitude reference system (VG and ADI)
(4)
Performance Data Computer (PDC) system
(5)
Engine Pressure Ratio (EPR) indication
(6)
Distance Measuring Equipment (DME)
(7)
Digital Air Data Computer (DADC) system
(8)
Mach-Airspeed Indicators
(9)
Flap Position Indicator
D. Verify that following systems are on and that no flags are in view:
(1)
Attitude Reference
(2)
DADC No. 1
(3)
PDC
(4)
Autopilot/Flight Director
NOTE: If autopilot is not engaged, verify that at least one F/D switch is on.
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22-31-01 Page 502 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. Feb 20/85
E. Connect pitot-static test set to air data computer pitot and static sources as required to perform these tests.
CAUTION: OPEN FLAP LOAD RELIEF CIRCUIT BREAKER (P6-2) TO PREVENT PERSONNEL INJURY OR EQUIPMENT DAMAGE RESULTING FROM PITOT-STATIC INDUCED FLAP MOVEMENT. ATTACH DO-NOT-CLOSE IDENTIFIER.
NOTE: Maintain ambient pressures unless required otherwise.
Unless otherwise noted, pressures are provided to the Captain's airspeed indicator
and air data computer No. 1.
F. Position VOR/LOC/GS signal generator per manufacturer recommendations with the test set antenna at right angles to the airplane centerline.
NOTE: When no localizer or VOR signal is required, receivers should be detuned from any local station.
G. Align airspeed reference bugs with airspeed pointers (on Mach/Airspeed indicator) unless required otherwise.
H. Position left hand angle-of-airflow sensor vane in a trailing edge up position (with respect to the body water line) of 2.0 +1.0 degrees.
WARNING: HOT ALPHA VANES CAN CAUSE SEVERE BURNS. BE SURE VANE IS COOL BEFORE TOUCHING.
I. Perform inlet pressure line leakage test on both engines (Ref 77-11-0, adjustment/test). Verify that EPR systems passes leakage test.
J. Connect EPR test set to both engines simultaneously.
K. Connect radio altitude signal generator.
NOTE: Set radio altimeter at zero unless otherwise indicated.
L. Set VERTICAL GYRO switch (on overhead panel) to NORMAL position unless otherwise directed.
M. Verify that the Landing Gear Downlocks are installed. If the Landing Gear Doors are down, verify that the red door lock handles are in view below the lower surface of the wing.
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