Display Library/Sub
No. Test No. Nominal LL UL Description Notes
2.40 17 VG Interface
17.1 0.0 -1.0 1.0 Roll Att 28
Sin
17.2 -6.76 -8.0 -5.0 Roll Att 27
Cos
17.3 0.0 -1.0 1.0 Pitch Att 45
Sin
17.4 -6.76 -8.0 -5.0 Pitch Att 46
Cos
17.5 2.91 1.0 5.0 Roll Att 28
Sin
17.6 2.91 1.0 5.0 Pitch Att 45
Sin
17.7 0.0 -1.0 1.0 FGN Roll 28
Att Sin
17.8 -6.76 -8.0 -5.0 FGN Roll 27
Att Cos
17.9 0.0 -1.0 1.0 FGN Pitch 45
Attn Sin
17.10 -6.76 -8.0 -5.0 FGN Pitch 46
Att Cos
17.11 2.91 1.0 5.0 FGN Roll 28
Att Sin
17.12 2.91 1.0 5.0 FGN Pitch 45
Att Sin
2.41 18 Compass Interface
18.1 3.01 1.0 4.0 HDG Sin 10 Compass
18.2 3.01 1.0 4.0 HDG Cos 11
22-11-01 Jun 20/83
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BITE TEST RESULTS TABLE
Display Library/Sub
No. Test No. Nomin LL UL Description Notes
al
2.40 18.3 3.01 1.0 4.0 PSC Sin 12
(Continued 18.4 3.01 1.0 4.0 PSC Cos 13
)
18.5 3.01 1.0 4.0 PSH Sin 14 Compass/MCP
18.6 3.01 1.0 4.0 PSH Cos 15
18.7 0.25 0.167 0.333 Heading 12/13 Compass
angle 4.5’ System inputs
track heading.
18.8 -0.25 -0.167 -0.333 Course angle 14/15
18.9 0.25 0.167 0.333 Heading
select angle
2.42 33 Alpha Vane
33.1 -2.012 -2.7 -1.3 Alpha Buff 102 Failure effect
Land and G/A
2.43 21 Extended
Memory Test
21.1 H 0000 Test is only in Tests of ROM
ground and RAM
functional memories
2.44 8 DME
8.1 H H0001 HFFFF H0000 = fail Activity of DME
XXXX signal
8.2 H 0141 DME Valid
and 0.0 miles
2.45 L NAV
(-112 FCC)
(-114 FCC)
(-214 FCC)
(-314 FCC)
Feb 20/89 22-11-01
Page 161
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
BITE TEST RESULTS TABLE BITE TEST RESULTS TABLE BITE TEST RESULTS TABLE BITE TEST RESULTS TABLE BITE TEST RESULTS TABLE
Display Library/Sub
No. Test No. Nominal LL UL Description Notes
2.45 27 Elevator Control
(-111 FCC) 27.1 -4.34 -5.03 -3.65 Actr Posn 4E a) Failure
(-113 FCC) effects all
2.46 pitch AP
(-112 FCC) modes.
(-114 FCC) Failures
(-214 FCC) cause a
(-314 FCC) transient at
GS Eng.
Checks servo
loop electronic.
27.2 0.6128 1.431 0.756 10F a) Failure
effects all
pitch AP
modes.
Failure
cause a
transient at
GS Eng.
Elevator position
input to
approach sync
loop.
2.45 27.3 -2.86 -3.73 -1.90 Elev. 4D a) Failure
2.46 effects all
(Continued) pitch AP
modes.
Failures
cause a
transient at
GS Eng.
Elevator position
feedback.
512
22-11-01 Page 162 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. Feb 20/89
Display Library/Sub
No. Test No. Nominal LL UL Description Notes
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