737 AMM 飞机维护手册 AUTO FLIGHT 自动飞行 1(95)

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Display  Library/Sub 
No.  Test No.  Nominal  LL  UL  Description  Notes 
2.49  11.2.3  0.230  0.0  0.46  APP INTEG  81  Pitch equalization 
2.50  input to integrator. 
(Continued) 
11.2.4  -0.295  -0.40  -0.19  VOR/LOC  23  Roll equalization 
BEAM INTEG  input to integrator. 
11.2.5  H0000  LCL CMD  810-6,  Bias checks 
3=0  equalization path. 
A delay of 28 sec. 
After the second 
paddle is raised is 
allowed for any 
FCC offsets to 
equalize out tests 
check α command 
signal path with 
A/P disengaged. 3 
sec. Delay allows 
extraneous signals 
to decay. 

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Jun 20/83  BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.  22-11-01 Page 171 

Display  Library/Sub 
No.  Test No.  Nominal  LL  UL  Description  Notes 
2.49  11.2.6  3.08  2.31  3.85  Alpha CMD  10E  Bias circuitry. 
2.50 
(Continued) 
11.2.7  -1.34  -1.74  -0.94  Alpha CMD  10E  Flap input to the α 
Command. 
11.2.8  -.149  -1.94  -1.04  Alpha CMD  10E  Checks 0.5° flap 
detector and 
switch. 
11.2.9  6.10  4.27  7.92  Alpha CMD  10E  Checks input to 
the α command. 
11.2.10  9.99  9.99  9.99  APP CMD  80  G/A SPD CMD 
can’t get through 
the least nose up 
detector α biases 
provide the 
command. Checks 
G/A altitude 
reference. 

512 
22-11-01 Page 172  BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.  Jun 20/83 

Display  Library/Sub 
No.  Test No.  Nominal  LL  UL  Description  Notes 
2.49  11.2.11  4.72  3.54  5.90  APP VPF  82  Checks G/A 
2.50  altitude reference 
(Continued) 
11.2.12  -3.55  -4.44  -2.66  Alpha CMD  10E  Checks comp path 
to the α μ 
command 
11.2.13  -0.551  -.072  -0.25  VOR/LOC  23  Checks roll 
BEAM INTEG  attitude input to 
the integrator in 
G/A 
11.2.14  1.938  1.45  1.42  APP VPF  82  Pitch attitude input 
to the G/A 
command 
11.2.15  -5.19  -6.49  -3.89  APP/SPD  10F  CAS input to the 
CMD  approach/speed 
command 
11.2.16  -5.048  -6.31  -3.79  Alpha CMD  10E  CAS input to the α 
command via μ 
comp path 
11.2.17  -0.49  -0.32  -0.66  APP INTEG  81  Y input to the 
integrator 
11.2.18  H 0000  BITFLG-2  Result of the 
foreign channel 
test 

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Jun 20/83  BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.  22-11-01 Page 173 

MODE  FUNCTION  POSSIBLE CAUSE 
GS ENGAGE  START ALPHA/FLAPS  CONFIDENCE TEST 
GS ENG+10 SEC  ALPHA/FLAPS TEST COMP.  ALPHA VANE FLAP POS XMTR 
GS ENG+10 SEC  2ND PITCH CH STARTS TO COME ON LINE. 
GS ENG+12.4 SEC  2ND UP PITCH CHANNEL DETENT PRESSURE SWITCH 
GS ENG+12.4 SEC  START P CONF TEST (PCT) 
GS ENG+12.6 SEC  FCC 
GS ENG+12.6 SEC  START P MONITOR CONF.  TESTS (PMCT 
GS ENG+16 SEC  PMCT COMPLETE  FCC 
GS ENG+17.9 SEC  BYPASS RELAYS ENERG  FCC 
APPROACH ON COURSE (AOC)  2ND ROLL CHANNEL STARTS TO COME ON LINE. 
AOC+2.4 SEC  2ND UP ROLL CHANNEL DETENT PWR SWITCH 
AOC+2.4  START ROLL CONF. TEST OF LATERAL ACCEL 
AOC+2.6  .  LATERAL ACCEL 
AOC+23 SEC  START ROLL MONITOR CONF TEST (RMCT 
AOC+27 SEC  FCC 
AOC+29 SEC  FLARE ARM ANN ILLUMINATES SINGLE CH ANN EXTINGUISHED. 

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