1_ HDG V/S selection
 The conventional tendency bars are displayed (pitch and roll
 FD bars).
 The yaw FD bar only appears in the RUNWAY mode (takeoff) and
 during the ALIGN and ROLL OUT phases (landing).
 2_ TRK FPA selection
 The flight path director symbols are displayed together with
 the flight path vector.
 The display of the yaw FD orders remains unchanged. The pitch
 and roll orders are provided when these two images are
 superimposed.
 The FMGCs generate all these data which are then transmitted
 to the DMCs. The DMCs convert them into images and messages on
 the display unit.

 C. Interface with DMCs and Automatic Changeover (Ref. Fig. 014) Each DMC receives:
 -a bus from each FMGC on which are routed: . FD orders, . AP/FD engagements, . AP/FD modes,

 AP/FD Information on the PFDs Figure 013
 1EFF : 1 1R 1CES  ALL  1 11 1 22-10-00 Page 38 Aug 01/05

 Interface Between FMGCs and PFDs
 Figure 014

 1EFF : ALL 1 22-10-00Page 39/40 1 1 Aug 01/05 1 1 1CES
1 the landing capabilities

 -
a wired discrete per FMGC giving the engagement status of the FDs

 -
a bit on a discrete label of the FCU corresponding to the action on the

 FD pushbutton switch associated with the PFD. A logic inside the acquisition module selects the FMGC bus(es) required to display the FD orders and the FMA messages (Ref. Para. C. and D.). In normal operation:
 -
the DMC 1 transmits data to CAPT PFD (PFD1)

 -
the DMC 2 transmits data to F/O PFD (PFD2). Each DMC is linked to its associated PFD by two connections (a normal one and an alternate one). The alternate connection is used for different types of changeover. In the event of a DMC failure, the DMC3 in standby can replace the faulty DMC after action on the EIS DMC selector switch on the SWITCHING panel 8VU (CAPT 3 position upon failure of the DMC1 ; F/03 position upon failure of the DMC2). In the event of a PFD failure, the data are transferred automatically from the PFD to the ND (data on the PFD have priority). This transfer can be made manually in two ways :

 -
by turning the PFD potentiometer to OFF (on the panels 301VU and 500VU)

 -
by action on the PFD/ND XFR pushbutton switch (on same panels).

 D. Selection of FMGC Bus for the FD Orders Each DMC makes a selection depending on the side on which it is installed and on the validity of each FD, according to:
 -engagement wired discretes
 -status matrices (SSM) of the labels 140, 141 and 143 on which the FD
 orders are routed.
 So the DMC1 (2) selects the FMGC1 (2) bus if the FD1 (2) is valid.
 The PFD1 (2) displays:

 -FD1 (2) message on the FMA or 1FD2 if energy management is activated.
 -FD orders from the FMGC1 (2).
 If an FD1 (2) validity loss is detected by the DMC1 (2) through:

 -loss of the FD1 (2) ENG condition
 -non refresh of FMGC1 (2) labels
 -status matrix of FMGC1 (2) labels coded at F/W status the DMC1 (2) will select the data from the FMGC2 (1) automatically and will display:
 -FD2 (1) message or 2FD2(1FD1) if energy management is activated.
 -FD orders from the FMGC2 (1).
 E. FD Order Removal All the FD orders can be cleared by the DMC by:
 -action on corresponding FD pushbutton switch on the FCU, or
 -validity loss of both FDs.
 The DMC clears a given FD order when the associated label is NCD.

 1EFF : ALL 1 22-10-00Page 41 1 1 Aug 01/05 1 1 1CES 1

 F. Selection of FMGC Bus for Display of AP/FD Modes and Landing Capabilities This selection depends on the engagement of the AP/FD systems.
 (1)
 FD only engaged Each DMC utilizes the bus selected for the FD orders as per the logic described in Para. C.

 (2)
 Only one AP engaged
 Each DMC utilizes the FMGC bus which corresponds to this AP.
 Each PFD displays:

 -AP1 or AP2 message depending on the AP engaged
 -
the modes corresponding to this AP

 -
the landing capabilities from the FMGC corresponding to the AP engaged.

 (3)
 Both APs engaged
 Each DMC is associated with the corresponding FMGC.
 The CAPT (F/O) PFD (PFD1 (2)) displays:

 -AP1 + 2 message
 -
the modes corresponding to AP1 (2)

 -
the landing capabilities from the FMGC1 (2).

 1EFF : ALL 1 22-10-00Page 42 1 1 Aug 01/05 1 1 1CES 1
　
中國航空網 www.k6050.com
航空翻譯 www.aviation.cn
本文鏈接地址：A320飛機維護手冊 AMM AUTO FLIGHT 自動飛行1(35)