(b)  
Turn mode selector to AUTO APP and set ALTITUDE HOLD switch to ON. Check that VOR/LOC annunciator is amber and that ALT HOLD and HDG SEL annunciations are green.

(c)  
Rotate heading knob and then return it to airplane heading. Check that V-bars respond to heading knob for roll command, that VOR/LOC annunciation remains amber, and that ALT HOLD and HDG SEL annunciations remain green.

(d)  
Slowly reduce localizer deviation signal until APD changes to indicate green VOR/LOC and amber GS. Check that APD changes when deviation bar reaches 2 ±0.5 dots; that V-bars indicate fly-left command that ALT HOLD annunciation remains green, and that HDG SEL annunciator is off.

(e)  
Reduce localizer signals to zero deviation. Check that V-bars stabilize within 2 minutes to zero roll command with 0 ±3 degree of VG-1 tilt.

(f)  
Close RADIO ALTM circuit breaker. Using radio altimeter test set, apply a greater than 1500-foot altitude which can be read on radio altimeter indicator. Slowly reduce glide slope deviation signal until APD GS annunciation changes from amber to green. Check that APD changes when glide slope deviation is 0 ±5 dot, that V-bars indicate fly-down command but stabilize to zero command in 45 seconds with 0 ±3 degree of VG-1 tilt, that ALT HOLD switch returns to OFF position, that APD ALT HOLD annunciator is off, and that VOR/LOC annunciation remains green.

(g)  
Apply a 1 dot fly down glide slope signal. Check that V-bar command indicates 6 ±2 degrees pitch down.

(h)  
Apply a 1 dot fly up glide slope signal. Check that V-bar command indicates 6 ±2 degrees pitch up.

(i)  
Apply fly-up glide slope signal to give 7-degrees of V-bar command. Reduce radio altitude to 1400 feet. Check that V-bar command reduces to 3 ±1 degrees pitchup over a period of 120 ±12 seconds.

(j)  
Apply a glide slope signal to give 6 degrees pitchup command. Reduce radio altitude to 150 feet. Check that V-bar command reduces to 3 ±1 degrees pitchup over a period of 7.5 ±2 seconds.

(k)  
Set mode selector switch to HDG. Set radio altitude to 2000 feet. Check that APD HDG SEL annunciation is green.

(l)  
Set mode selector to AUTO APP position. Check that APD GS annunciation changes from green to amber.

(m)  
Reduce glide slope deviation to zero. Check that APD VOR/LOC and GS annunciations are green.

(n)  
Apply fly-up glide slope signal to give 7-degree pitchup command. Open radio altimeter circuit breaker. Check that V-bar command reduces to 3 ±1 degrees over a period of 120 ±12 seconds, and that APD VOR/LOC and GS annunciations remain green.

(o)  
Apply a glide slope signal to give 6 degrees pitchup command. Set marker beacon sensitivity to LOW. Apply a middle marker signal for 3 seconds. Check that V-bar command reduces to 3 ±1 degrees in 7.5 ±2 seconds, and that APD VOR/LOC and GS annunciations remain green.

(p)  
Close RADIO ALTM circuit breaker.

(2)  
F/O's Side:

5C8 
34-26-0 Page 508  BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.  Jan 20/83 

(a)  Repeat step (1) using F/O's components and VG-2 instead of VG-1
F.  Manual Glide Slope (MAN GS) Mode Test
(1) 
 Captain's Side:

(a)  
For captain's instruments, place mode selector in HDG. Apply 2-dot fly-down and fly-right glide slope and localizer signals. Set mode selector to MAN GS position. Check that APD VOR/LOC and GS annunciations are green and that V-bars indicate pitch down and fly-right command.

(b)  
Reduce glide slope deviation to zero. Wait 2 minutes. Tilt VG-1 in right roll until V-bars indicate zero roll command. Check that VG tilt is 15 ±3 degrees right roll.

(c)  
Level VG-1. Set localizer deviation to zero. Set FLT DIR mode selector to AUTO APP. Apply glide slope signal to give 7-degree pitch up command.

(d)  
Place mode selector in MAN GS position. Check that V-bar command reduces to  3 ±1 degrees in 120 ±12 seconds and that APD VOR/LOC and GS annunciations remain green.

(e)  
Apply a glide slope signal to give 6 degrees pitch up command. Set marker beacon sensitivity to LOW. Press test switch on front of marker beacon receiver for greater than 3 seconds. Check that V-bar command reduces to 3 ±1 degrees in 7.5 ±2 seconds and that APD VOR/LOC and GS annunciations remain green.

(2)  
F/O's Side:

(a)  Repeat step (1) for F/O's components.
G.  Go-Around Mode Test
(1) 
 Captain's Side:
　
中國航空網 www.k6050.com
航空翻譯 www.aviation.cn
本文鏈接地址：737 AMM 飛機維護手冊 導航 NAVIGATION 1(101)