-------------------------------------------------------------------------------| PARAMETER LIST PARAMETER CHARACTERISTICS (NUMERIC) | -------------------------------------------------------------------------------|EQ.SYS.LAB.SDI|PARAMETER | WORD RANGE |UNIT|SIG |BITS|XMSN|CODE|ALPHA|SOURCE | | |DEFINITION| OPER RANGE | |BIT | |INTV| |CODE |ORIGIN | | |(*=REMARK)| RESOLUTION | | | | | | |BUS No.| | |(X=NOTE) | ACCURACY | | | | | | |ATA REF| | | | | | | | | | |CONV | -------------------------------------------------------------------------------| 260 | DATE | 1 Day |MON:| 6 | | 1s |BCD | | | | | |YEAR| | | | | | |--------------|----------|------------|----|----|----|----|----|-------------| | | GPS | | | | | | | | | 273 | SENSOR | N/A |N/A |N/A | | 1s |DISC| | | | STATUS | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-------------| | 343 | DEST | 16 |NM | 11 | |0.5s|BNR | | | | HIL | 0.0078 | | | | | | | |--------------|----------|------------|----|----|----|----|----|-------------| | | ALT | | | | | | | | | 347 | WAYPNT | 16 |NM | 11 | |0.5s|BNR | | | | HIL | 0.0078 | | | | | | | |--------------|----------|------------|----|----|----|----|----|-------------| | 354 | GPSSU | N/A |N/A |N/A | | |ISO | | | | IDENT | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-------------| | 356 | MAINT | N/A |N/A |N/A | | |ISO | | | | DATA | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-------------| | | EQUIP-| | | | | | | | | 377 | MENT | N/A |N/A |N/A | | 1s |BCD | | | | ID | | | | | | | | -------------------------------------------------------------------------------
6. Component Description
_____________________
R **ON A/C 051-099,
R A. MMR
R (1) External description
R (Ref. Fig. 004)
R The face of the MMR is fitted with a handle, two attaching parts, a
R TEST pushbutton switch and three LEDs. The LRU STATUS LED has two
R colors (red/green).
R The three LEDs have the following name, color and function:

 1EFF : ALL 1 34-36-00Page 13 1 1 Config-2 May 01/05 1 1 1CES 1R MMR - External Description R Figure 004

R 1EFF : 051-099, 1 34-36-00Page 14 1 1 Config-2 May 01/05 1 1 1CES 1

R  - LRU STATUS (red) indicates that an internal fault is detected 
R  during the front panel self-test sequence 
R  - LRU STATUS (green) indicates that no internal fault is detected 
R  during the front panel self-test sequence 
R  - CONTROL FAIL (red) indicates that no control input is available 
R  during the test sequence. 
R  - ANT FAIL (red) indicates that a failed antenna is detected during 
R  the test sequence. 
R  The back of the MMR is equipped with one ARINC 600 size one 
R  connector, which includes three plugs: 
R  - Top Plug (TP): connection with the GPS antenna 
R  - Middle Plug (MP): service interconnection 
R  - Bottom Plug (BP): connection with the power supply circuit, and the 
R  LOC and G/S coaxial interconnections. 
R  (2) Internal description 
R  (Ref. Fig. 005) 
R  The MMR consists of four parts: 
R  - the power supply unit 
R  - the ILS receiver 
R  - the GPS receiver 
R  - the system processor unit. 
R  The primary function of the MMR is to receive and process ILS and GPS 
R  signals. The ILS receiver and the GPS receiver make up two of the 
R  subassemblies. The ILS signals, including both localizer and 
R  glideslope, are used to determine flight path deviations during 
R  precision approach and landing, and are supplied to the aircraft 
R  flight control and instrument systems. These deviations are based on 
R  radio frequency signals that the unit receives from a ground-based 
R  instrument landing system. 
R  The GPS receiver simultaneously tracks signals from up to twelve GPS 
R  satellites. The signals are processed to generate a three-dimensional 
R  position and a precise time. The receiver generates an estimate of 
R  the positional accuracy provided. An integrity alert is activated if 
R  an unannounced satellite malfunction is detected. The receiver has 
R  the capability of excluding satellites that are malfunctioning. 
R  The system processor card has the functions that follow: 
R  - output position and deviation data to other aircraft systems, 
R  - receive ILS frequency selections, 
　
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