Honeywell International Inc. RTA-50D Manuale Utente
MAINTENANCE MANUAL
965-1696
C.
Interwiring and Cable Fabrication (Subtask 23-20-59-000-007-A01)
(1)
General
(a)
Figure 2001 is the complete aircraft interwiring diagram for a single RTA-50D VDR system
and associated components. This diagram requires complete study before the installer
begins installation of the aircraft wiring.
and associated components. This diagram requires complete study before the installer
begins installation of the aircraft wiring.
(b)
When two or more systems are being installed in the aircraft, the interconnecting wiring
as well as all other installation instructions must be duplicated.
as well as all other installation instructions must be duplicated.
(c)
Cabling must be fabricated by the installer. Wires connected to parallel pins must be
approximately the same length so that the best distribution of current can be effected.
Honeywell recommends that all wires including the spares must be included in the
fabricated harness. However, if full ARINC wiring is not desired, the installer must
make sure that the minimum wiring requirements for the features and functions are
incorporated. Refer to Figure 2001.
approximately the same length so that the best distribution of current can be effected.
Honeywell recommends that all wires including the spares must be included in the
fabricated harness. However, if full ARINC wiring is not desired, the installer must
make sure that the minimum wiring requirements for the features and functions are
incorporated. Refer to Figure 2001.
NOTE:
To allow for inspection or repair of the connector or the wiring to the connector,
sufficient lead length must be provided. This will let the rear connector
assembly to be pulled forward several inches when the mounting hardware
for the rear connector assembly is removed. A bend must be made in the
harness near the connector to let water condensation drip off at the bend
and not collect at the connector.
sufficient lead length must be provided. This will let the rear connector
assembly to be pulled forward several inches when the mounting hardware
for the rear connector assembly is removed. A bend must be made in the
harness near the connector to let water condensation drip off at the bend
and not collect at the connector.
(d)
When the cables are installed in the aircraft, they must be supported firmly enough to
prevent movement and must be carefully protected against chafing. Additional protection
must also be provided in all locations where the cables can be subject to abuse. In
wire bundles, the cabling must not be tied tightly together as this tends to increase the
possibility of noise pick-up and similar interference. When routing cables through the
airframe, try to avoid running cables or wire close to power sources (400-Hz generator,
etc.). If unavoidable, the cables must cross high-level lines at a right angle or high-quality
shielded conductors must be used.
prevent movement and must be carefully protected against chafing. Additional protection
must also be provided in all locations where the cables can be subject to abuse. In
wire bundles, the cabling must not be tied tightly together as this tends to increase the
possibility of noise pick-up and similar interference. When routing cables through the
airframe, try to avoid running cables or wire close to power sources (400-Hz generator,
etc.). If unavoidable, the cables must cross high-level lines at a right angle or high-quality
shielded conductors must be used.
(e)
If a cable must pass through a bulkhead between pressurized and unpressurized zones,
this passage must conform to the aircraft manufacturer’s specifications.
this passage must conform to the aircraft manufacturer’s specifications.
(f)
The assembler must be knowledgeable of any system variations unique to the installation
and must completely understand the complexities associated with handling related
problems of line lengths, capacitance, and of susceptibility to interference.
and must completely understand the complexities associated with handling related
problems of line lengths, capacitance, and of susceptibility to interference.
(g)
The following determinants are the responsibility of the installation agency for fabrication
of the wiring harness. Refer to Table 2001.
of the wiring harness. Refer to Table 2001.
Table 2001. RTA-50D VDR Communications Transceiver Connector Determinants
Pin No.
Type
Signal Name
Function
MPA1
Input
MIC audio input (high)
Microphone audio input. Part of the standard four wire
microphone interwiring as described in Attachment
6 of ARINC 716-10. Required for ARINC 716 VHF
communication only.
microphone interwiring as described in Attachment
6 of ARINC 716-10. Required for ARINC 716 VHF
communication only.
MPB1
Input
MIC audio input (low)
Microphone audio input. Part of the standard four wire
microphone interwiring as described in Attachment
6 of ARINC 716-10. Required for ARINC 716 VHF
communication only.
microphone interwiring as described in Attachment
6 of ARINC 716-10. Required for ARINC 716 VHF
communication only.
EFFECTIVITY
ALL
23-20-59
Page 2003
1 Mar 2011
© Honeywell International Inc. Do not copy without express permission of Honeywell.