737-300 400 500 AMM 飞机维护手册 自动飞行 AUTOFLIGHT 1(108)

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A
737-300/400/500MAINTENANCE MANUAL
 (c)  The DME Self-Test A and NAV Self-Test A signals are BITE stimulation signals generated by the FCC during BITE tests involving these LRUs. The DME signal causes the DME Interrogator to go into the self-test mode. The NAV signal cause the VHF NAV receiver to perform the UP/LT test.
 (5)  Command outputs signals are provided for A/P and F/D.
 (a)  The roll transfer valve command signal to the aileron actuator provides aileron movement in response to mode output requirements.
 L. Roll Signal Switching (Fig. 27)
 (1)  Attitude Transfer Logic
 (a)  
Flight control computer A receives roll information from both IRU-1 and IRU-2. Autopilot A uses roll attitude and roll attitude rate from IRU-2, any other roll information required will be supplied by IRU-1. The flight director uses all on side information from IRU-1, unless switched.

 (b)  
Attitude and EFIS relays are used to determine which should be used in the roll control laws for both A/P and F/D. A ground indicates the normal source is to be used.

 (c)  
LCL IRS XFER input signal indicates to the A FCC to use IRU-2 information only.

 (d)  
FGN IRS XFER input signal indicates to the A FCC to use IRU-1 information only.

 (e)  
Compass XFER input signal functions the same as attitude transfer signals.

 

R378 ATT XFER RELAY 2 (E1-2)
Roll Signal SwitchingFigure 27
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A
737-300/400/500MAINTENANCE MANUAL
 (f)  EFIS switching relay logic is used to ensure the attitude information used by FCC is from the same source which is displayed on the EADIs.
 M. Roll Channel Digital Interface (Fig. 28)
 (1)  
The digital interface diagram illustrates the various LRU's which provide inputs to and receive outputs from the FCC. These signals are in ARINC 429 format and include validity, sign, address, and data information.

 (2)  
Inertial Reference Unit (IRU) Inputs

 (a)  
The IRU's provide inputs which are FCC internally selected for use. These are magnetic heading, magnetic track angle, roll angle, roll rate, and lateral acceleration. The magnetic heading input is used in the HDG HOLD, HDG SEL and TAKEOFF modes of operation. The magnetic track angle is used in VOR, LOC, and G/A modes. The roll angle is used in all modes of operation and provides an additional input during localizer operation to generate the lag roll signal. The roll rate signal is also used in all modes in the common/inner loop area as a damping signal input. The lateral acceleration is used as a complimenting command during approach.

 (b)  
With the compass and attitude relays in normal the FCCs select the on-side IRU for F/D computations but only the on-side heading and track angle for A/P. The A/P portion uses the off-side roll attitude signals. This helps reduce the possibility of a dual axis hardover because the pitch attitude signals used are from the on-side IRU.

 

 (3)  
Digital Air Data Computer (DADC) Inputs

 (a)  The DADC provides computed airspeed which is used to provide gain control of amplifiers in the HDG SEL and TAKEOFF modes and also in the common/inner loop signal chain. The altitude input is used in determining over station sensor logic conditions in the VOR mode.

 (4)  
DFCS Mode Control Panel (MCP) Inputs

 (a)  The inputs from the MCP are selected course, selected heading, and discretes. The selected course is used as one of the prime guidance signals in the VOR and LOC modes of operation. The selected heading input is used in the HDG SEL and TAKEOFF mode (if wings level option is not selected). The discrete inputs provide the FCC with mode selection information.
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 22-11-01
 ú ú 08 Page 75 ú Nov 12/01
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A737-300/400/500MAINTENANCE MANUAL
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