(6) Remove all tools, equipment and unwanted materials from the work area.
WARNING:
MAKE SURE THAT ALL PERSONS IN THE AREA OF THE
AIRCRAFT ARE TOLD BEFORE THE ELECTRICAL SYSTEM IS
ENERGIZED. IF YOU DO NOT DO THIS, YOU CAN CAUSE
INJURIES TO PERSONS OR DAMAGE TO EQUIPMENT.
(7) Apply electrical power to aircraft.
(8) Push and hold the PRESS TO TEST push button on the PROP RPM indicator.
Check that the analog pointer aligns with the unlit blue dot at 1050 and the digital
display shows 1050.
(9) Release the PRESS TO TEST push button on the PROP RPM indicator. Check that
the analog pointer and digital display show 0.
(10) On the overhead console, rotate the ENGINE PANEL lighting selector from OFF to
BRT. Check that the PROP RPM indicator back lighting varies from off to bright.
(11) Do an engine start (refer to Chapter 71−00−00).
(12) Check for correct operation of the propeller (PROP RPM) indicator.
(13) For aircraft with the Beta Lockout System (CR873CH00011), do the Functional Test
of the Overspeed Protection System and Power Lever Micro Switch (6141−S3 and
S4) Calibration Check (Refer to AMM 76−10−16).
(14) Shut down the engine (refer to Chapter 71−00−00).
2.
Adjustment/Test
Equipment and Materials:
Signal Generator HP204C or equivalent
A.
Propeller RPM (NP) Indicating System − Calibration Check
(1) With dc power on, press test pushbutton on indicator. Check pointer moves
opposite blue dot at 1050 RPM and equivalent digital reading. Check that on
release of pushbutton indicator returns to original setting.
(2) Open and clip the following circuit breakers:
(a)
ENG 1 NP IND (G5) on 28 V dc left circuit breaker panel. (Engine No. 1).
(b)
ENG 2 NP IND (G5) on 28 V dc right circuit breaker panel. (Engine No. 2).
(c)
FDAU (G2) and FDR STAT (H2) on left 28 V dc essential bus circuit breaker
panel and FDR (A9) on Avionics circuit breaker panel.
(3) Disconnect electrical connector 6142−P6 at engine speed sensor (magnetic
pick−up) on top of reduction gearbox on engine No. 1 (when testing engine No. 1
system) or 6142−P6 at similar location on engine No. 2 (refer to Figure 202).
Disconnect electrical connector 9811−P104 located at station X210 on left side of
cabin, on relay panel behind avionics rack.
(4) Carry out continuity, resistance and insulation test of speed sensor (magnetic
pick−up) of engine system under test (refer to Engine Maintenance Manual).
(5) Connect signal generator across pins 3 and 4 of connector 6142−P6 of engine
indicating system being tested.
(6) Close circuit breaker in (2) (a) or (b) for applicable engine.
(7) Adjust signal generator output from 0 to 3500 Hz with output voltage between 0.5 V
(peak to peak) minimum and 5.0 V (peak to peak) maximum. Check output
D
SERIES 100
AIRCRAFT MAINTENANCE MANUAL
MASTER
EFFECTIVITY: See Pageblock 61−44−00 page 201
61−44−00
Page 202
Jun 20/2005