(a)  P7 Overhead Circuit Breaker Panel
 1) 7A9 NAV RADIO MKR VOR L

 S 864-008
 (5)  Do this task to supply electrical power: "Manual Control" (AMM 24-22-00/201).
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A 747-400 MAINTENANCE MANUAL
 (6)  S 714-009Do the BITE test on the VOR/MKR receiver: (a) Push and release either one of the two TEST switches on the front panel of the LCD screen and look for this sequence: 1) The TEST IN PROGRESS display is shown on the LCD screen. 2) The test continues for approximately 5 seconds. 3) The TEST COMPLETE NO FAILURES display is shown at the end of the test cycle.
 (7)  S 864-017If electrical power is not necessary, do this task to remove electrical power : "Manual Control" (AMM 24-22-00/201).##

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747-400 MAINTENANCE MANUAL
 RADIO ALTIMETER - DESCRIPTION AND OPERATION
___________________________________________
 1.  General (Fig. 1)_______
 A.  The radio altimeter (RA) system supplies vertical position data for use by the pilots for runway approach, landing, and takeoff. The RA system provides measurement of absolute altitude (height above terrain) from 2500 feet to touchdown. Altitude data is routed to user systems on 429 digital data buses.
 B.  AIRPLANES WITH TCAS; The radio altimeter system supplies radio altitude data to the traffic alert and collision avoidance system (TCAS) for setting sensitivity levels and calculating intruder advisories.
 C.  Three complete systems are installed. Each system consists of a receiver/transmitter (R/T), and one transmit and one receive antenna. Altitude data is displayed on the captain's and first officer's front instrument panels primary flight display (PFD) (Fig. 1).
 D.  Each receiver/transmitter provides a continous digital altitude output signal via a 429 digital bus to all three EFIS/EICAS interface units (EIU) in the pilots' integrated display system (IDS). The EIUs convert the digital signal into digital data displayed as a numerical value on the captain's and first officer's primary flight displays.
 E.  An adjustable decision height (DH) radio altitude alert operates with the radio altitude system and is independently selectable from 0 to 999 feet on the captain's and first officer's EFIS control panels. The DH altitude selection is compared and processed in the EIUs with the existing radio altitude value output from the radio altitude receiver/transmitters. When the airplane descends to the selected DH altitude, a flashing DH alert is displayed on the applicable primary flight display.
 F.  Refer to Fig. 2 for signal interfaces between the radio altimeter system and the EFIS, EICAS, and integrated display systems.
 2.  Component Detail (Fig. 1)________________
 A.  Receiver/Transmitter(R/T)
 (1)  
The left, center and right R/T units are installed in the main electronic equipment center in rack E9.

 (2)  
The R/T unit transmits then receives the reflected RF signal to compute height above the terrain. It outputs the computed altitude on two ARINC 429 digital data busses to the user systems on the airplane.

 (a)  The TEST switch initiates a self-test which first checks the status lights for burnout, then performs a self-test which checks the R/T and the antennas associated with the R/T.
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A
747-400
MAINTENANCE MANUAL

CIRCUIT BREAKER PANEL NO. 1 (P7)
CIRCUIT BREAKER PANEL NO. 2 (P7)
PILOTS' PANEL (P10)
　
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