-RF section which filters and mixes the RF signal.
 -ASIC GNSS which processes the signals from the RF section.
 -Processor section which performs position, velocity, time (PVT) and integrity calculation with data received from ASIC GNSS. It also provides satellite information to I/O section.
 -I/O section which consists of ARINC 429 drivers and receivers and discrete I/O logic. It provides PVT, integrity and satellite information with aircraft systems. ARINC 429 inputs/outputs are processed by a specially designed ASIC (GLUCOMA).

 (e)
 Power supply module (POWER SUPPLY) The power supply module generates, from 115VAC/400HZ single phase, four regulated power supplies required for operation of the modules and boards (+12VDC, +5VDC, +15VDC, -15VDC). This module protects the secondary power supply voltages against short-circuits and spikes, makes primary power supply micro-interrupts transparent and isolates the equipment from the primary power supply.

R 1EFF : 001-049, 101-149, 151-199, 201-299, 1 34-36-00Page 22 1301-399, 401-499, 1Config-2 Aug 01/05 1 1 1CES 1

 (f) High Intensity Radiated Field interconnect module (HIRF) The HIRF module provides with connection of the different internal modules and connection with the aircraft environment. It protects the MMR against electromagnetic interference, lightning indirect effects and has two filters for the 115VAC/400Hz input power.

R **ON A/C ALL
 B. GPS Antenna (Ref. Fig. 006) Two L-Band antennas are mounted on the top of the fuselage, at the centerline, to receive signals from the GPS satellites. The GPS antenna is an active antenna with an integrated preamplifier and filter. It receives GPS signals at 1575.42 MHz and matches to a 50 ohms coaxial cable at the input to the MMR. The antenna has a right-hand circular polarized and omnidirectional radiation pattern. The power supply of the preamplifier is provided by the MMR through the coaxial cable.
 NOTE : The antenna connectors have a hole to install a lockwire and
____
 safety the coaxial cable.

 C. Localizer Antenna (Ref. Fig. 007) The localizer antenna is an airborne antenna used to receive LOC signals in the 108-112MHz range. It is a folded half-loop type driven by capacitive coupling. The antenna has two independent RF connectors used to feed two independent ILS receivers. Connector separation is provided by a hybrid junction in the antenna.
 D. Glide Slope Antenna (Ref. Fig. 007) The glide slope antenna is an airborne antenna used to receive GLIDE signals in the 329-335MHz range. It is a folded half-loop type driven by capacitive coupling. The antenna has two independent RF connectors used to feed two independent ILS receivers. Connector separation is provided by a hybrid junction in the antenna.
 1EFF : ALL 1 34-36-00Page 23 1 1 Config-2 May 01/05 1 1 1CES 1

 GPS Active - Antenna Figure 006
 1EFF : 1 1R 1CES  ALL  1 11 1 Page 2434-36-00 Config-2 May 01/05

 ILS - Antennas Figure 007
 1EFF : 1 1R 1CES  ALL  1 11 1 Page 2534-36-00 Config-2 May 01/05

 7. Operation
_________
 A. ILS Operation
 (1)
 Normal operation (Ref. Fig. 008) Each MMR is connected to one Radio Management Panel (RMP). The MMR 1 is connected to the RMP 1 (the MMR 2 to the RMP 2). The MMR 1 receives management bus from the FMGC 1 through the RMP 1 (the MMR 2 from the FMGC 2 through the RMP 2). In normal operation, the FMGC 1(2) tunes the MMR 1(2) either automatically or manually by means of the MCDU. In this case the RMP 1(2) operates as a relay which sends the frequency information from the FMGC 1(2) to the receiver 1(2). Via a second port, the MMR 1(2) receives a second management bus (ILS FREQ + RWY HDG) directly from the FMGC 2(1). The receiver selects one of the two input ports according to the FREQ/FUNCT DATA SOURCE SEL discrete signal, which is received from the FMGC 1(2) through the RMP 1(2).

 (2)
 Operation in case of failure With failure of one FMGC, the second FMGC automatically controls the two MMRs, the off side directly, the on side through its RMP. With failure of the RMP 1(2) or two RMPs, the RMP concerned is transparent to data and discrete from FMGC.

 (3)
 Manual operation In manual operation (at any time, or with failure of two FMGCs) the RMP 1 can control the MMR 1 after ON NAV mode selection. Same possibility for the RMP 2 (MMR 2). (Ref. Fig. 009) In this mode the RMP 1 can control the MMR 2 through the RMP 2 after ON NAV mode selection on the RMP 2. Same possibility for RMP 2 through RMP 1. After any frequency selection it is always necessary to select the associated course.

 (4)
 Reconfiguration switching In normal utilization, the ILS 1 data are shown on the CAPT PFD and the F/O ND; the ILS 2 data on the F/O PFD and the CAPT ND. The DMC 1 supplies data to the CAPT PFD and ND; the DMC 2 to the F/O PFD and ND. With failure of the DMC 1(2) it is possible to switch over to the DMC 3 with the EIS DMC selector switch located on the panel 8VU on the center pedestal.
　
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