NEITHER A/P IN CMD, LOC ENGAGED,
GS ENGAGE AND LRRA LESS THAN 800 FEET
Pitch Bar Bias TableFigure 22
A737-300/400/500MAINTENANCE MANUAL
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A
737-300/400/500MAINTENANCE MANUAL
(i)
Event 9 - The mode control is set for a lower altitude, however, the FMC command is V/S climb.
(j)
Event 10 - The FMC target V/S is not valid.
(k)
Event 11 - If A/P GA mode is engaged and if failure causes the F/D GA not be initiated, the bars are biased out of view.
(l)
Event 12 - Flare mode is not used in conjunction with the F/D and the bars are biased out of view.
(m)
Event 13 - IRU transfer (Attitude or EFIS to Both on 2) from the normal position without either A/P in CMD and both F/D on.
(n)
Event 14 - Local AC bus transfer without either A/P in CMD and both FD on.
(o)
Event 15 - VHF NAV transfer from the normal position without either A/P in CMD and both F/D on.
(p)
Event 16 - Selected IRU pitch angle not valid.
(q)
Event 17 - Selected IRU roll angle not valid.
(r)
Event 18 - Selected IRU pitch attitude rate not valid.
(s)
Event 19 - Selected IRU vertical acceleration not valid.
(t)
Event 20 - Selected IRU longitudinal acceleration not valid.
(u)
Event 21 - Selected IRU vertical speed not valid.
(v)
Event 22 - ADC static pressure not valid.
(w)
Event 23 - ADC TAS not valid.
(x)
Event 24 - ADC Baro uncorrected altitude not valid.
(y)
Event 25 - ADC Baro corrected altitude not valid.
(z)
Event 26 - ADC CAS not valid.
(aa) Event 27 - ADC mach not valid.
(ab) Event 28 - A loss of the 115 volts power.
(ac) Event 29 - The VHF navigation system is in autotune.
(ad) Event 30 - F/D comparator 3° difference for more than 3 seconds
between captain and first officer's F/D commands.
H. Deviation Monitor (Fig. 23) (Used only if ILS DEV option enabled)
(1)
The deviation monitor provides a flashing warning when the airplane is off the glide path while making an ILS approach. LOC and GS deviation warning is provided by changing the LOC and GS scales from white to yellow and the pointers blink at four hertz rate. Also the stem of the rising runway blinks. The system is armed for warnings below 1500 feet. The GS warning is inhibited below 100 feet provided the warning is not on when passing through 100 feet.
(2)
The deviation warnings are checked three seconds after passing through 1500 feet provided an A/P is in CMD and in the APP mode. The warnings are on for 2 seconds as FCC A is tested, off for 2 seconds and on for 2 seconds as B is tested.
(3)
If the LOC deviation is greater than 20 mV for 7 seconds, the LOC deviation warning is turned on. If the GS deviation is greater than 75 mV for 7 seconds, the GS deviation warning is turned on. A LRRA logic circuit inhibits the GS deviation when less than 100 feet providing the GS deviation warning was not present when passing through 100 feet.
I. Roll Axis Flight Control Operation (Fig. 24)
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M924 A FLIGHT CONTROL COMPUTER A
Deviation Monitor Schematic
Figure 23
A 737-300/400/500MAINTENANCE MANUAL
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本文链接地址：737-300 400 500 AMM 飞机维护手册 自动飞行 AUTOFLIGHT 1(104)
