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Honeywell
MK XXII EGPWS Installation Manual
CAGE CODE: 97896 SCALE: NONE SIZE: A DWG NO: 060-4314-225 REV: C
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SECTION II - INSTALLATION
2.1 Introduction
This section contains suggestions and factors to consider before installing the Enhanced Ground Proximity
Warning System. Close adherence to these suggestions will assure satisfactory performance from the
equipment.
NOTE
The conditions and tests performed on this article are minimum performance
standards. It is the responsibility of those desiring to install this article either on or
within a specific type or class of aircraft to determine that the aircraft installation
conditions are within these performance standards. The article may be installed only if
further evaluation by the applicant documents an acceptable installation and is
approved by the Administrator.
2.2 Unpacking and Inspec ting the Equipment
Exercise extreme caution when unpacking equipment. Perform a visual inspection of the unit for evidence
of damage incurred during shipment. If a damage claim must be filed then save the shipping container and
all packing materials to substantiate your claim. The claim should be filed as soon as possible. The
shipping container and all packing materials should be retained in the event that storage or reshipment of
the equipment is necessary.
2.3 Equipment Installation
2.3.1 General
The following paragraphs contain information pertaining to the installation of the MK XXII EGPWS,
including instructions concerning the location and mounting of the equipment. The equipment should be
installed in the aircraft in a manner consistent with acceptable workmanship and engineering practices,
and in accordance with the instructions set forth in this publication. To ensure the system has been
properly and safely installed in the aircraft, the installer should make a thorough visual inspection and
conduct an overall operational check of the system, on the ground, prior to flight.
CAUTION
AFTER INSTALLATION OF THE CABLING AND BEFORE INSTALLATION OF THE
EQUIPMENT, A CHECK SHOULD BE MADE WITH THE AIRCRAFT PRIMARY POWER
SUPPLIED TO THE MOUNTING CONNECTOR, TO ENSURE THAT POWER IS
APPLIED ONLY TO THE PINS SPECIFIED IN THE INTERWIRING DIAGRAMS IN
SECTION III.