Eagle ICA-D212-725, Instructions Manual

Page: 665 / 729

ICA-D212-725 (96)
Page 54 of 90
CHAPTER 96 – ELECTRICAL SYSTEM (96-00-00)

COPYRIGHT

2007 BY DART AEROSPACE LTD.

THIS DOCUMENT IS PRIVATE AND CONFIDENTIAL AND IS SUPPLIED ON THE EXPRESS CONDITION THAT IT IS NOT TO BE USED FOR ANY PURPOSE OR COPIED OR COMMUNICATED TO ANY
OTHER PERSON WITHOUT WRITTEN PERMISSION FROM DART AEROSPACE LTD.
Revision:
4
Date: 11.06.01
2312G or TT1000A
NOTE
Tolerances stated do not include
test equipment tolerances.
96.6.13B.1 Supply electrical power to
helicopter.
96.6.13B.2 Disconnect connector containing
engine harness chromel/alumel wiring from the RH
aft firewall disconnect.
96.6.13B.3 Connect turbine temperature test
set to the connector on the RH aft firewall from
where the engine side harness was disconnected.
Adjust tester for an input of 675

C and verify the
analog indication reads within 5

C of this
temperature and the digital indication reads within
2

C of this temperature.
96.6.13B.4 Check insulation resistance of
engine thermocouple harness with tester.
Resistance to ground from either chromel or
alumel terminal (pins A and B) shall be not less
than 25,000 ohms. Reference Honeywell
Maintenance Manual, T5313B and T5317 Series,
Section 77-20-01, Paragraphs 3-A-5 and 3-F-1-a.
96.6.13B.5 Measure
loop resistance between
chromel and alumel terminals (pins A and B) of the
engine thermocouple harness. Resistance shall
be between 1.6

and 1.8

when measured at
18

C to 24

C. Reference Honeywell Maintenance
Manual, T5313B and T5317 Series, Section 77-
20-01, Paragraph 3-D.
96.6.14 Hydraulic Oil Temperature
Indicators
The hydraulic oil temperature indicator system
consists of 2 identical systems, No.1 and No.2
hydraulic temp bulbs, and hydraulic indicators.
Hydraulic temperature bulbs control indicators
which display in degrees Celsius. The indicator is
a dual hydraulic temperature/pressure indicator.
96.6.15 Operational Check – Hydraulic
Temperature Indicators
96.6.15.1
No.1 hydraulic system.
96.6.15.1.1 Apply electrical power to helicopter
electrical system.
96.6.15.1.2 Verify
No.1 HYD OIL temperature
indicator reads approximately ambient
temperature with engine cold.
96.6.15.2
No.2 hydraulic system.
96.6.15.2.1 Verify
No.2 HYD OIL temperature
indicator reads approximately ambient
temperature with engine cold.
96.6.15.2.2
Turn electric power off.
96.6.16 Attitude Indicator
The attitude indicator is a self-contained unit which
displays aircraft attitude, pitch and roll. The
indicator also as a backup battery which can
supply power to the indicator for up to one hour
should aircraft power be lost to the indicator. The
indicator also has a PULL TO CAGE knob located
in the lower right corner of the unit and a STBY
PWR light and test switch used to test the battery
and indicator. Rotating the PULL TO CAGE knob
will move the aircraft icon up or down.
96.6.17 Operational Check – Attitude
Indicator
96.6.17.1
Apply electrical power to helicopter
electrical system.
96.6.17.2
Close ATT IND PILOT circuit
breaker. Verify that gyro begins to spin up. Pull
the PULL TO CAGE knob and verify indicator
erects to correct attitude. Warning flag should be
out of view in less than 3 minutes.
96.6.17.3
Once warning flag is out of view,
accomplish the following:
96.6.17.3.1 Open ATT IND PILOT circuit
breaker. Verify the warning flag appears, and that
the gyro begins to spin down.
96.6.17.3.2 Close ATT IND PILOT circuit
breaker.
96.6.17.4
Turn electric power off.