(f)
Press HDG SEL button and repeat steps (e) except rotate control wheel to the right.
(g)
Set Radio Altitude to zero.
(h)
Place A/P ENGAGE A switch to CWS. With VG level, slew compass No. 1 to 20 degrees in increasing heading. Observe that control wheels remain centered.
NOTE: If autopilot disengages during compass slewing, re-engage and continue test.
(i)
Increase Radio Altitude to 1600 feet and repeat step (h). Observe that control wheels slowly turn to right. Reset Radio Altitude to zero.
(j)
Place A/P ENGAGE A switch to CMD and repeat step (h). Observe that control wheels slowly turn to right.
(k)
Disengage autopilot.
(l)
Repeat steps (a) thru (k) using A/P ENGAGE B switch and AFCS computer B.
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D. Return Airplane to Normal
(1)
Upon completion of all tests, remove the following equipment and materials from the airplane.
(a)
VOR/LOC/GS and DME signal generators
(b)
Radio altimeter test set
(c)
Portable pressure test equipment
(d)
Tilt tables
(e)
Vertical gyro extension cables
(f)
Protractors and adapters
(g)
Torque tools and adapters
(h)
Spring scale
(i)
Steel measuring tape
(j)
DC volt-ohmmeter
(k)
Radio altimeter signal simulators
(l)
Test point breakout boxes
(2)
Install vertical gyros and radio altimeters and verify following systems are normal (Ref Chapter 34).
(a)
Attitude Reference
(b)
Radio Altimeter
(3)
Close autopilot stabilizer trim 3-phase circuit breaker and place CUTOUT switch to NORMAL.
(4)
Remove electrical and hydraulic power if no longer required.
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3. Autopilot/Flight Director Autoland Test
A. The AP/FD autoland test is performed using system BITE. The test checks all mode switching and signals used during the LAND mode.
B. Prepare for BITE test.
(1)
Check that all control surface areas are cleared of obstructions and personnel.
(2)
Provide electrical and hydraulic power. Verify that BAT switch is positioned to ON.
(3)
When prompted by BITE instructions, position hydraulic system A and B switches to ON and close FLT CONT SYS circuit breaker.
WARNING: MAKE SURE ALL PERSONNEL AND OBSTRUCTIONS ARE CLEAR OF ELEVATOR, AILERON, RUDDER AND TAB SURFACES. SURFACES MAY MOVE ABRUPTLY WHEN HYDRAULIC POWER IS APPLIED.
(4)
Ensure that all autopilot, autothrottle, performance data computer system, flight instrument, VHF navigation system, low range radio altimeter, marker beacon and air data computer system circuit breakers are closed.
(5)
Ensure following systems are operation (Ref Chapter 34).
(a)
Attitude reference system
(b)
Compass system
(c)
VOR/ILS navigation system
(d)
Low range radio altimeter system
(e)
Air data computer system
(f)
Performance Data Computer (PDC) system
(6)
Perform AP/FD BITE
(a)
Switch PDC CDU mode control switch to STBY. Press RCL, then press PAGE
forward until the following is displayed:
A/P TEST 5-X
TEST
SYMPTOM/PIREP
TEST DESIRED
ENG = Y, ENT = NO
(b)
Verify that A/P warning light are illuminated steady. Course and Heading displays on the MCP indicate their originally selected values. Verify air data instruments and radio altimeters are indicating normal airplane-on-ground display.
(c)
Advance system to Ground Functional Test by pressing ENT (no) after SYMPTOM/PIREP TEST DESIRED message. Verify that GROUND FUNCTIONAL TEST DESIRED message is displayed.
(d)
Press ENT (no) to step display to VERIFICATION.
(e)
Press ENG (yes) to step display to LRU INTERFACE.
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