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from the airplane to the ground. The radio altitude shows in the
flight compartment on the display units (DU). The radio altitude
is computed with the receiver transmitter unit by comparing the
transmitted signal to the received signal. The R/T unit transmits
a radio signal then receives the reflected RF signal back from
the ground to determine the altitude of the aircraft. The R/T
sends computed altitude data out on two ARINC 429 data buses
to user systems on the aircraft.
The flight crew and other airplane systems use the altitude data
during low altitude flight, approach, and landing.
The system has a range of -12 to 2500 feet.
An adjustable radio minimums alert operates with the radio
altitude system and is independently selectable from 0 to 999
feet on the captains and first officers EFIS control panels. The
radio minimums altitude selection is compared and processed
in the display electronics units (DEUs) with the existing radio
altitude value output from the radio altitude R/T. When the
airplane descends to the selected radio minimums altitude a
flashing radio minimums alert is displayed on the applicable
DU.
Abbreviations and Acronyms
* ADI - attitude direction indication
* AID - aircraft installed delay
* altm - altimeter
* ant - antenna
* approx - approximately
* ARINC - Aeronautical Radio, Inc.
* BITE - built-in test equipment
* CAPT - captain
* CDS - common display system
* conn - connector
* CP - control panel
* CW - continuous wave
* DEU - display electronics unit
* DH - decision height
* DME - distance measuring equipment
* DU - display unit
* EFIS - electronic flight instrument system
* F - frequency
* FCC - flight control computer
* FDAU - flight data acquisition unit
* FM - frequency modulation
* F/O - first officer
* freq - frequency
* fwd - forward
* gnd - ground
* GPWC - ground proximity warning computer
* ILS - instrument landing system
* LCD - liquid crystal display
* LED - light emitting diode
* LRU - line replaceable unit
* maint - maintenance
* MDA - minimum descent altitude
* mins - minimums
RADIO ALTIMETER SYSTEM - INTRODUCTION
EFFECTIVITY
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* PFD - primary flight display
* P/N - part number
* RA - radio altimeter
* RA - radio altitude
* rec - receiver
* RF - radio frequency
* rst - reset
* R/T - receiver transmitter
* S/W - software
* sys - system
* T - time
* TCAS - traffic alert and collision avoidance system
* VCO - voltage controlled oscillator
* WXR - weather radar
* xmit - transmit
RADIO ALTIMETER SYSTEM - INTRODUCTION
EFFECTIVITY
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BOEING PROPRIETARY - Copyright#- Unpublished Work - See title page for details.
737-600/700/800/900 AIRCRAFT MAINTENANCE MANUAL
34-33-00-001
RADIO ALTIMETER SYSTEM - INTRODUCTION
RADIO ALTIMETER SYSTEM - INTRODUCTION
EFFECTIVITY
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737-600/700/800/900 AIRCRAFT MAINTENANCE MANUAL
34-33-00-001
General
The radio altimeter system has two receiver/transmitters (R/
Ts). Each R/T has a transmit and a receive antenna. The radio
altimeter R/T makes a frequency modulated continuous wave
RF signal that is sent to the ground and reflected back to the
airplane. The time that it takes for the signal to travel from the
transmit circuit of the R/T to the receive circuit of the R/T is
changed into absolute altitude. The number one system altitude
shows on the captain display and the number two system
shows on the first officer display.
The altitude data and signal validity is sent on two ARINC 429
data buses.
ARINC 429 data bus 1 sends data to these components:
* Flight control computers (FCC)
* Autothrottle computer.
ARINC 429 data bus 2 sends data to these components:
* Ground proximity warning computer (GPWC)
* Traffic alert and collision avoidance system (TCAS)
computer
* Flight data acquisition unit (FDAU)
* Weather Radar (WXR)
* Common display system (CDS) display electronic units
(DEU).
The receiver/transmitters get discrete inputs from the proximity
switch electronics unit (PSEU) used to count flight legs for fault
　
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