CP-2500
Installation Manual
Page 2-2
Installation
0040-17251-01
March 15, 2018
Revision D
•
Tighten all screws to snug (i.e. only such torque that can be applied by hand) unless specific
torque instructions are given.
•
After installation, refer to the Installation Checkout section for ground testing procedures.
2.
Electrical equipment chassis and shield/ground terminations must be electrically bonded to the
aircraft's main structure (metallic aircraft) or instrument panel (composite aircraft). Compliance of
the electrical bonding should be verified by inspection using a calibrated milliohm meter or an
equivalent OEM procedure.
•
The electrical bond should achieve direct current (DC) resistance less than or equal to 2.5 m
to
structure local to where the equipment is mounted for metallic aircraft or tube and fabric aircraft.
•
The electrical bond should achieve direct current (DC) resistance less than or equal to 5.0 m
to
the instrument panel for composite aircraft.
2.3.1 Location
The CP-2500 should be mounted in the instrument panel slightly below and in close proximity with the
pilot's normal line of view, with the controls within easy reach. In selecting a location, consider the
following:
1.
The CP-2500 should be accessible for inspection, maintenance, or removal and free from instrument
panel structural flexure and excessive vibration or heat.
2.
Compare the space requirements of the CP-2500 with the installation area being considered.
•
The CP-2500 with part numbers 9080-17250-01 & -02 mount in a 2 ¼ inch standard round
instrument hole. Refer to Figure 2-1. Outline dimensions are located in Figure 2-2.
•
The CP-2500 with part number 9080-17250-12 mounts in a 3 1/8 inch standard round
instrument hole. Refer to Figure 2-1. Outline dimensions are located in Figure 2-3.
9080-17250-01 & -02
9080-17250-12
Figure 2-1: Panel Cutout Dimensions
