Honeywell MK VI - Manual (Page 52)

Honeywell
MK VI MK VIII EGPWS Installation Design Guide
Proprietary notice on title page applies
CAGE CODE: 97896 SCALE: NONE SIZE: A DWG NO: 060-4314-150 REV: SHEET 52
3.2.2 Chassis Gr ound
Chassis ground provides a redundant metal connection and should not be used as a normal current carrying
conductor. Chassis ground should be connected as follows:
Pin Signal
J1-42, J1-53 GND
Pins J1-42 and J1-53 are both connected to chassis ground internally. It is not necessary to tie them both to
ground in the aircraft wiring. Pin J1-53 was made available to provide a convenient way to supply a ground to
external equipment. If the OAT probe is not present, nothing needs to be tied to J1-53.
3.2.3 GPS Anten na
A GPS antenna connector is available on the front of the MK VI EGPWS 965-1190-0XX and MK VIII EGPWS
965-1220-0XX. See Appendix E paragraphs 3.2.2 and 4.2.9 for connector details. The J1 connector backshell
supplied with classic MK VI GPWS installation kits can interfere with the GPS antenna connector for this reason
a new J1 backshell is supplied with MK VI-VIII installation kits.
3.2.4 Analog and Digital Inputs
The analog and digital inputs to the MK VI/VIII EGPWS are defined as the Categories are selected. Instructions
for documenting these interfaces are provided with the Category selection instructions.
3.2.5 Discrete Inp uts
The discrete inputs are defined in Appendix E Section 6.6. Additional information for some discretes is provided
within the Category in which they are used.
3.2.6 Serial Outp uts
The EGPWC provides for ARINC 453 and ARINC 429 serial outputs.
Terrain display data is output on two ARINC 453 channels when the Terrain Awareness display function is
enabled.
Low speed ARINC 429 output buses are provided by the EGPWC are described in Appendix E Section 7. The
ARINC 429 output data includes:
1. Internal data (data output for test purposes only such as internal logic booleans, Geometric Altitude, and
Terrain Clearance information).
2. Alert/Warning status (Voice and Lamp activity can be provided to display systems and flight recorders).
3. Internal mode status.
4. Terrain display messages for TAD cockpit integration.
Note: During EGPWS Self Test, the SSM of each output label is set to the Functional Test status code.