(h)
By hand, movepropellerbladesto feathered position.Check that all adjustment screwsare in contactwith guide collar.
(i)
Refer to Figure 514. Install dome nut. Tighten to a torque of 120 foot-pounds. () Startengine.Cycle propeller into and out of feather.
(k)
Check1900 rpm torque setting. (Refer to step (d) under Engine Running Adjustments.)
(I)
Shut down engine. Check for oil leaks.
(m)Notingreferencemarks,install spinner.
(n) Performin flight feather check.
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PIPERAIRCRAFT
PA-42-720(Advanced Trainer)
MAINTENANCEMANUAL
H. FeatherStop Adjustment (continued)
2. ExternalFeather Stop Adjustment (continued)
SECTION A-A
A-2626-() Screw Guide Collar
Piston
SupportRing
LinkArms Cylinder
NOTE: Use length of A -2626 -() screw as required to maintain a minimum of 1/2 inch of screw engagedin piston.
ElasticNuts-Adjusting
ExternalFeatherStop Adjustment Figure 514
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PIPER AIRCRAFT
PA-42-720 (Advanced Trainer)
MAINTENANCE MANUAL
CHAPTER 77
LIST OF EFFECTIVE PAGES
CHAPTER CHAPTER
SECTION PAGE DATE SECTION PAGE DATE
77-EFFECTIVITY 1 Feb 1/98
77-CONTENTS 1 Jan 10/90
77-00-00 1 Jan 10/90
77-10-00 1 Jan 10/90
77-10-00 2 Jan 10/90
77-10-00 3 Jan 10/90
77-20-00 1 Jan 10/90
77-20-00 2 Jan 10/90
77-20-00 3 Jan 10/90
77-20-00 4 Jan 10/90
77-20-00 5 Feb 1/98
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77-30-00 1 Jan 10/90
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Feb 1/98
PIPERAIRCRAFT
PA-42-720(AdvancedTrainer)
MAINTENANCEMANUAL
CHAPTER77-ENGINEINDICATING
TABLE OF CONTENTS
SUBJECT CHAPTER PAGE
77-00-00 EngineIndicating 1 General 1 77-10-00 Power 1 TorquePressureIndicatingSystem 1 Calibration 1 Tachometer-Generators(PropellerandGas Generator) 3 Removalof Generator 3 Installationof Generator 3 77-20-00 Temperature 1 InterTurbineTemperatureSensingSystem 1 Descriptionand Operation 1 ResistanceCheck of Engine InterTurbineTemperatureSystem 1 CalibrationCheck of ITT Gauge andWiring 2 77-30-00 Analyzers 1 EngineConditionTrendMonitoringSystem 1 General 1
EFFECTIVITY: 040-999
CONTENTS
Jan10/90
PIPERAIRCRAFT
PA-42-720(AdvancedTrainer)
MAINTENANCEMANUAL
EngineIndicating
A. General
Thischapterdescribeshowto remove,calibrate,andinstallsystemcomponentsthatindicateengine operatingconditions.
EFFECTIVITY:
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PIPER AIRCRAFT
PA-42-720(Advanced Trainer)
MAINTENANCEMANUAL
A. Power
1. TorquePressure Indicating System
The torque pressure system consists of a pressure transmitter mounted at the reduction gearbox case and a torquemeter mounted in the instrument panel. The torque pressure value is obtained from the pressure transmitter, which monitors pressure differential between two outlets on top of reduction gearbox case.
(a) Calibration (Refer to Figure 501.)
(1.) Remove torque pressure line from the torque transmitter.
CAUTION: BE SURE THE SERIAL NUMBER (SN) ON TEST GAUGE CALIBRATION CARDCORRESPONDSTO SN ON TEST GAUGE.
(2.) Using appropriate AN fittings and pressure line, connect a Barfield pressure tester to torque transmitter.
(a.) Check that test gauge has been calibrated. (b.) Check that test gauge is capable of using engine oil to provide and monitor static pressures of 0.0 to 80.0 psi.
(3.) Turn aircraft master switch on.
(4.) Loosen fittings and point valve knob toward line.
(5.) Turn handle clockwise until air is bled from line (evident when oil is observed dripping from
fitting.) Tightenfitting. (6.) Turn valve knob toward reservoir; turn handle counterclockwise. (7.) Turn valve knob toward line. Turn handle clockwise until test gauge reads 65.42 psi.
Adjust cockpit torque gauge to read 2000 foot-pounds. (8.) Turn tester handle counterclockwise until test gauge reads 13.08 psi. Adjust cockpit torque gauge to read 400 foot-pounds.
NOTE: Test gauge pressure of 65.42 psi corresponds to 2000 foot-pounds of engine torque; 13.08 psig corresponds to 400 foot-pounds of engine torque.
NOTE: During test, minimize friction error by gently tapping test gauge and cockpit torque gauge.
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