(3)
INS to PMS Data.
EFFECTIVITY
AIRPLANES WITH DELCO INS CONFIG 1 02 A Page 61 Apr 25/8734-41-00
(a)
The INS transmits INS inertial present position, displayed present position, true heading, N-S velocity, E-W velocity, sum of the INS present FROM and TO waypoints, an INS status word and a program part number word to the PMS. This INS data to the PMS is by a six wire clock-sync-data transmission. An INS data warn discrete is also connected to the PMS. The INS also provides a vertical acceleration signal to the PMS. This signal to the PMS is by a two wire connection.
(b)
INS present position latitude and longitude is transmitted to the PMS in two forms - inertial position and displayed position. The inertial position is used by the PMS during the ALIGN mode to verify proper ramp coordinates. The inertial and displayed positions can be used in the NAV mode to verify proper position transmission and PMS/INS mix computations.
(c)
True heading, north/south and east/west velocity is used by the PMS if reliable ground based DME information is not available to determine present position. This data is transmitted as NO COMPUTED DATA until the NAV mode is entered.
(d)
The INS determines a waypoint sum based on the FROM/TO waypoints being flown by the INS when under PMS waypoint control. The sum is used by the PMS to verify that the value of the FROM/TO legs transmitted by the PMS and used by the INS are correct. The PMS will not transmit further flight plan information unless this sum is correct.
(e)
The INS program part number is transmitted to the PMS for display on the PMS CDU.
(f)
The INS status word (from the INS, to the PMS) includes information that indicates: INS mode (ALIGN or NAV), INS alignment status, INS identification (INS-1, -2, or -3), PMS lockout, true or magnetic heading, INS - HSI test (as commanded by PMS), and a HSI warn (in response to PMS command).
E. INS Instrument Switching
(1)
The transfer switching for INS navigation data is shown in Fig. 15. The navigation display signals normally are applied from INS 1 to the captain's HSI and from INS 2 to the first officer's HSI. Selection of an alternate INS may be made by operating the INS transfer switch, which positions the associated ledex relay. The VOR-ILS/INS switch determines whether radio navigation data or INS navigation data will be displayed.
(2)
On ATLAS ALL EXCEPT AT 701-750, the INS pitch and roll attitude signals drive the attitude display sphere in the ADI. A flag signal is provided to the ADI's in case of loss or failure of attitude reference signals (Fig. 16). The attitude signals are normally routed from INS 1 to the captain's ADI and from INS 2 to the first officer's ADI. INS 3 is selected as an alternate source for either ADI by operating the ATT/COMP STAB transfer switch which positions the appropriate transfer relay.
EFFECTIVITY
AIRPLANES WITH DELCO INS CONFIG 1 02 A Page 62 Apr 25/8734-41-00
On AT 701-750, the INS pitch and roll attitude signals drive the attitude display sphere in the ADI. A flag signal is provided to the ADI's in case of loss or failure of attitude reference signals (Fig. 16). The attitude signals are normally routed from INS 1 to the captain's ADI and from INS 2 to the first officer's ADI. INS 3 is selected as an alternate source for either ADI by operating the ATTITUDE transfer switch which positions the appropriate transfer relay.
(3) On ATLAS ALL EXCEPT AT 701-750, platform heading signals from the INS are used by the magnetic heading reference system (MHRS) for compass stabilization. Refer to 34-21-00. Platform heading is normally applied from INS 1 to MHRS compass coupler 1 and from INS 2 to MHRS compass coupler 2. (Fig. 16). INS 3 is selected as an alternate source for either compass coupler by operating the ATT/COMP STAB transfer switch which positions the appropriate transfer relay. On AT 701-750, platform heading signals from the INS are used by the magnetic heading reference system (MHRS) for compass stabilization. Refer to 34-21-00. Platform heading is normally applied from INS 1 to MHRS compass coupler 1 and from INS 2 to MHRS compass coupler 2 (Fig. 16). INS 3 is selected as an alternate source for either compass coupler by operating the ATTITUDE transfer switch which positions the appropriate transfer relay.
15. INS Power Interface (Fig. 17 and 18)
___________________ On LH 081; AF 151-199; MD 501-599; GN 601-699; VM 751-799, power for the INS system is derived from the standby, essential, and No. 2 flight instrument buses. Control is through the electronic circuit breaker panel P7, the overhead circuit breaker panel P126 and the main power circuit breaker panel P6. On AT 701-750; LH 011-030, 051-070, 082-099; AZ 221-299, power for the INS system is derived from the standby bus, the fail-op bus and from the essential and No. 2 flight instrument buses. Control is through the electronic circuit breaker panel (P7), the overhead circuit breaker panel (P126) and the main power circuit breaker panel (P6).
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本文鏈接地址：747飛機維護手冊AMM CHAPTER 34 - NAVIGATION 第34章導航2(100)
