User's Manual Part 1

CAS / Part No. 9000000

SYSTEM DESCRIPTION AND INSTALLATION MANUAL

34-43-20

15 Feb 2003

Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.

2--8

Figure 2--3. Typical Single Terrain Hazard Display Annunciator Switch Panel

I. Transponder Provisions

This paragraph contains the mechanical installation data for the ACSS Mode S Data Link

Transponder, Part No. 7517800--XXYYY and ACSS Diversity Mode S Transponder, Part

No. 7510700--850. It also contains provisions for installing the ATC transponder

antennas.

(1) Mode S Data Link Transponder Provisions

Mechanical installation data for the ACSS Mode S Data Link Transponder, Part No.

7517800--XXYYY is shown in Figure 2--8. The transponder can be mounted in any

convenient location in the aircraft; however, it should be mounted within 30 feet of the

antennas unless low loss coaxial cable is used to maintain a worst case loss of 3dB

per ARINC 718. Top and bottom antenna coaxial run length differences can be

compensated for by use of the antenna delay program pins on the transponder. The

unit can utilize external cooling air in accordance with ARINC 600 or ARINC 404 or

operate in convection--cooled environments. The transponder is mounted in an

ARINC 600 4--MCU tray assembly.

(2) Diversity Mode S Transponder Provisions

Mechanical installation data for the ACSS RCZ -- 852 Diversity Mode S Transponder,

Part No. 7510700--850 is shown in Figure 2-- 9. The transponder can be mounted in

any convenient location in the aircraft that allows the unit to be upright during normal

flight. The exact location should allow the cabling between the unit, control panel,

and antennas to be as short as possible. The location of the mounting tray (part of

installation kit, Part No. 7510707--968) should allow adequate space for installation

of the transponder, provide reasonable accessibility for servicing, and allow space on

top, sides, and rear of unit for adequate ventilation. The location must also p rovide a

solid mechanical mount to prevent vibration amplification. The mounting tray should

be electrically bonded to the aircraft frame by a low resistance path of less than 2.5

milliOhms.