C.  Receiving and/or transmitting antennas required by navigation systems are located externally on the aircraft as shown in figure 1.
 D.  Navigation system information is displayed in analog and/or digital form on the flight instruments. (See figure 2). The flight instruments interface with several systems through the flight instrument switching network. Operation of these instruments is described separately under each related system as follows:
 (1)  
Attitude Director Indicator (ADI)

 (a)  
Inertial navigation system (Refer to 34-41-00, INS -Description and Operation; and 34-41-05, ADI -Adjustment/Test.)

 (b)  
VOR/ILS system (Ref 34-31-00, Description and Operation).

 (c)  
Low range radio altimeter system (Ref 34-33-00, Description and Operation).

 (d)  
Auto throttle system (Ref 22-31-00, Description and Operation).

 (e)  
Flight director system (Ref 34-26-00,Description and Operation)

 (f)  
Yaw damper system (Ref 22-16-00, Description and Operation).

 (2)  
Horizontal Situation Indicator (HSI)

 (a)  
Inertial navigation system (Ref 34-41-00, Description and Operation; and 34-41-06, Removal/Installation).

 (b)  
VOR/ILS system (Ref 34-31-00, Description and Operation).

 (c)  
Magnetic heading reference system (Ref 34-21-00, Description and Operation).

 (3)  
Radio Magnetic Indicator (RMI)

 (a)  
Magnetic heading reference system (Ref 34-21-00, Description an Operation; and 34-21-06, Removal/Installation).

 (b)  
VOR/ILS system (Ref 34-31-00, Description and Operation).

 (c)  
ADF system (Ref 34-57-00, Description and Operation).

 EFFECTIVITY
 AF ALL
 AT ALL

 GN ALL  CONFIG 2 MD ALL  01 Page 1 VM ALL  Oct 25/80

34-00-00
 (d)  Distance measuring equipment (Refer to 34-55-00, DME -Description and Operation.)
 (4)  
Air Data Pressure Instruments (Ref 34-13-00, Description and Operation; Adjustment/Test).

 (5)  
Optional analog, digital, and illuminated displays. (Refer to pertinent related system.)

 2.  Pitot-Static System (34-11-00)
___________________
 A.  The pitot-static system senses the dynamic (pitot) and ambient (static) air pressure external to the aircraft and supplies these two pressures to the indicators and control units determining the functions of vertical speed, airspeed, mach number, or altitude.
 3.  Central Air Data Computer System________________________________(34-12-00) Bendix 1903925
 A.  The central air data computer system provides computed air data to the airplane flight control, inertial navigation, air traffic control, ground proximity warning and air data instrumentation systems. The central air data computer outputs consist of electrical and electromechanical analogs of selected and computed functions of altitude, airspeed, mach number, and air temperature. These outputs are derived from dynamic (pitot) pressure, ambient (static) pressure, and total air temperature; all sensed external to the airplane.
 4.  Air Data Pressure Instruments (34-13-00)
_____________________________
 A.  The air data pressure instruments are a group of instruments displaying information relative to the atmosphere surrounding the airplane. This information includes functions of airspeed, barometric altitude, mach number, and air temperature and is determined by sampling the surrounding atmosphere.
 5.  Mach Airspeed Warning System (34-14-00) Lear Siegler B070710011
____________________________
 Aero Mechanism 6501

 A.  The mach airspeed warning system provides an aural warning (clacking) to the flight crew when the airplane exceeds its maximum mach airspeed operating limit.
 6.  Altitude Alert System (34-16-00) United Control 965-0184-011 (AF ALL EXCEPT
_____________________ 155-190, 194-199; AT ALL; AZ 231-233); United Control 965-0184-001 (GN ALL); Smith's Industries 70-200-04 (MD ALL); Smith's Industries 70-200-07 (AF 155-190, 194-199; AZ 231-233)
 A.  The altitude alert system provides the pilots with a visual and aural indication of the airplane proximity to a preselected altitude.
 7.  Magnetic Heading Reference System (34-21-00)
_________________________________
 A.  The magnetic heading reference system (MHRS) provides gyro stabilized magnetic heading information to the airplane flight instruments and other interfacing navigation systems.
 8.  Standby Attitude Reference System_________________________________(34-24-00) SFENA 705-7V9
　
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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1(12)