(b)  
Operate NAV test switch on NAV-1 panel. Verify that NAV test indications occur.

(c)  
Place A/P ENGAGE A switch to CMD, press APP button on mode control panel. Verify that APP light on MCP illuminates and flight mode annunciators indicate G/S arm. Operate radio altimeter-1 test switch and NAV test switch. Verify that no tests occur.

(d)  
Set G/S deviation signal to zero with G/S superflag valid. Verify that flight mode annunciators show G/S engaged (green).

(e)  
Operate radio altimeter-1 test switch and NAV test switch on NAV-1 panel. Verify that no tests occur.

(f)  
Pull on Captain's column to override CWS detent. Verify that CWS PITCH annunciations appear, G/S engaged annunciations are removed and APP button light on MCP extinguishes. Disengage autopilot.

(g)  
Repeat (a) thru (f) with channel B autopilot, No. 2 radio altimeter, NAV test switch on NAV-2 panel and F/O's column.

(h)  
Select A F/D switch to ON. With LOC tuned, push APP on MCP. Verify that G/S ARM is annunciated on CAPT FMA.

(i)  
Position NAV transfer SWITCH on BOTH ON 2. Verify that G/S ARM is still
annunciated on CAPT FMA. Position transfers switch back to NORMAL.

(j)  
Select B F/D switch to ON. Verify that G/S ARM is annunciated on BOTH FMA's.

(k)  
Position NAV transfer switch to BOTH ON 2. Verify that CAPT FMA does not annunciate G/S ARM. Position transfer switch back to NORMAL.

(l)  
Position NAV transfer switch to BOTH ON 1. Verify that F/O FMA does not
annunciate G/S ARM. Position transfer switch back to NORMAL.

(m)  
Select A F/D to OFF. Position NAV transfer switch to BOTH ON 1. Verify that F/O FMA still annunciates G/S ARM. Position transfer switch back to NORMAL. Select B F/D to OFF.

(17)
Dual Channel Approach Mode Test

(a)  
Manually trim stabilizer to 3 units.

(b)  
Set flaps at 5 units and Alpha vanes at zero (level with waterline).

(c)  
Set radio altimeters to 1800 ft. Place Altitude Select to 2000 ft.

(d)  
With ILS frequency selected, apply one dot FLY-UP glide slope signal. Place A/P ENGAGE A switch to CMD. Push APP button. Check that APP pushbutton illuminates. Set LOC signal to zero deviation.

(e)  
Select both F/D switches to ON. Verify that A F/D master light is illuminated.

(f)  
Place A/P ENGAGE B switch to CMD. Verify that A/P annunciators show SINGLE CH. Check that A F/D master light is illuminated. Open landing gear lights circuit breaker.

(g)  
Center glide slope deviation. Verify that mode annunciators indicate G/S engaged.

(h)  
Reduce radio altitude to 1400 feet. Check that FLARE arm annunciator appears after about 30-second delay and SINGLE CH annunciator is removed.

NOTE:  Confidence testing starts after glide slope engage. Failure to complete confidence testing results in disengagement of dual channels. Successful completion of confidence testing (approximately one half minute) results in appearance of FLARE arm annunciation.

(i)  
Place VG transfer switch (P5) to CAPT ON AUX. Check that both autopilot channels disengage.

(j)  
Repeat steps (c) thru (h). Place VG transfer switch to NORMAL. Check that both autopilot channels disengage.

(k)  
Repeat steps (c) thru (h).

(l)  
Repeat steps (i) and (j) with VG transfer switch selected to F/O on AUX, then back to normal.

(m)
Repeat steps (c) thru (h).

(n)  
Slowly reduce radio altitude signals to zero feet. Open LRRA No. 1 circuit breaker. Verify minimum of 1.5 second delay before A/P disengages. Close circuit breaker.

(o)  
Repeat steps (c) thru (h). Reduce radio altitude to zero feet. Open LRRA No. 2 circuit breaker. Verify minimum of 1.5 second delay before A/P disengages. Close circuit breaker.

(p)  
Repeat steps (c) thru (h). Reduce radio altitude to zero feet. Open LRRA No. 1 and 2 circuit breakers. Check that both A/P channels disengage immediately. Close both circuit breakers. Select radio altitude signals to 1400 feet.

(q)  
Verify that speed brake handle is not armed, then open AUTO SPEED BRAKE circuit breaker.

WARNING:  INADVERTENT SPOILER ACTIVATION CAN CAUSE SERIOUS INJURY. VERIFY THAT AUTO SPEED BRAKE SYSTEM IS DISARMED PRIOR TO APPLICATION OF WHEEL ROTATION SIGNALS TO ANTISKID SYSTEM.

(r)  
Connect antiskid test box (F80129) to antiskid unit. Place test box master switch to OFF, select 70 knots on speed control and select outboard wheels of left landing gears.

(s)  
Repeat steps (c) thru (h). Wait until FLARE arm is annunciated.

(t)  
Close autopilot 3 phase stabilizer trim circuit breaker. Decrease radio altimeter toward field elevation. At approximately 3 seconds after passing 400 ft altitude, check that stabilizer trims in a nose up direction. At approximately 42 ft altitude, check that annunciation changes from FLARE armed to engaged.
　
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