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The PA-42-720 is powered by two Pratt & Whitney of Canada PT6A-61 turboprop engines. The engines are rated at 720 horsepower, at 2000 rpm each. The engines are free turbine type, with two independentturbine sections; one drives the compressorand accessory gear train section; the other drives the propeller shaft through a reduction gearbox.
The engines are completely enclosed by upper and lower cowling sectionsof cantilever construction. Accessto the accessory section is gained through eitherof two doors built into the top rear section of the cowl. Both doors are secured by two tension latches. The oil quantity dip stick is located inside the left access door.
An air inlet duct for starter generator cooling is located on the lower left section of both cowls. The
outlet duct is located on the top of the left accessory sectionaccess door.
The bleed air intercooler inlet duct is located on the lower outboard side of each cowl. The outlet duct is located on the outboard side of the nacelle above the wing leading edge.
An air inlet ice deflector door and oil cooler door are integral partsof the bottom nacelle assembly.
An access door to the enginewash ring is located on the outboard side of each nacelle just aft and
belowengineexhaust stub. The wash ringpermitsfield cleaning the engine.
The engine lubricatingsystemis a pressure type with the main oil pump located in the oil tank which is an integral part of the compressor inletcase. This system provideslubrication for all areas of the engine, pressure for the torque meter, and propeller pitch control.
For complete, detailedmaintenanceinformation,refer to Pratt & Whitney PT6A-61Maintenance ManualP/N 3034342. Enginetrend monitoring informationcan be attained from the latest Pratt & WhitneyAircraft Gas Turbine Operation Information Letter 23.
Informationor runup procedures canbe found in the PA-42-720 Pilot's Operating Handbook.
B. Fault Isolation
Referto Chart 1 and consult all available sourcesfor informationwhich may assist in diagnosing problems.
NOTE:  For additional information on troubleshooting the engine, refer to Pratt & Whitney PT6A-61 MaintenanceManual, P/N 3034342.
EFFECTIVITY:
040-999  71-00-00 PAGE

71-00-00 Jan 10/90

PIPERAIRCRAFT
PA-42-720(AdvancedTrainer)
MAINTENANCEMANUAL

B. Fault Isolation(continued)
CHART 1 FAULT ISOLATION (ENGINE) (Sheet 1 of 3)
Fault
Cause

Enginefailsto start. Nofuelsupplytoengine.
Airinfuelsystem.
Openignitioncircuit.
Defectiveenginedriven
fuelpump.
Defectivefuelcontrol
unit.
Defectivestartingflow
control.
Restrictedfuel
nozzles.
Enginedoesnotidleproperly. Idlespeedsettingincorrect.
Leakor restrictionin
FCUpneumaticsystem.
Remedy
Checkfor cleanfuel supply
at firewallshutoffvalve.
Performmotoringrun.
Checkwiringandconnections
Checkfor flowfrom pump
while motoringengine. If
noflow,replacepump.
Checkforflow from FCU outlettubeto startingflow controlwhile motoring engine.If no flow,remove FCU,checkbypassvalveby applying5 psi max.to bypass returnportandcheckfor air leakagefrom FCUinlet. If leakageisfound, replace fuel controlunitand fuel pump.If no leakage,replace only FCU.
Disconnectprimarytube
andcheckfor evidenceof flow whilemotoringengine with startcontrolleverin
runposition.If noflow, replacestartingflow control.
Cleanandchecknozzles. (Referto EngineMain-tenanceManual.)
Adjustidlespeedandminimu flow as required.
Checkall pneumatictubes andconnectionsfor leakage.
EFFECTIVITY: 040-999

Jan
Jan 10/90
71-0000
71-00-00
PIPER AIRCRAFT
PA-42-720 (Advanced Trainer)
MAINTENANCE MANUAL

B. Fault Isolation (continued)
CHART 1 FAULT ISOLATION (ENGINE) (Sheet 2 of 3)
Fault

Enginedoesnot accelerateproperly.
Enginedoes not decelerate.
Enginedoes not developfull power.
Excessivevibration.
Cause
Leak or restrictionin
fuel control pneumatic
system.
P3filterplugged.
Defectivefuel control
unit.
Power control linkage
adjustedincorrectly.
Defectivefuel control
unit.
Faulty engine instru-
mentation.
Controllinkageadjusted
incorrectly.
Propellergovernorpneumatic
sectionadjustedincorrectly.

Leak or restrictionin fuel

controlpneumaticsystem.
Enginepowersettingsnot
adjustedcorrectly.

Defective fuel control unit.
Restrictedfuel nozzles.

Propellerout of balance.

Compressoror compressor
turbinedisc out of balance.

Remedy
Check all connectionsfor
leakage. Check for dirt in P3
meteringorifice. (Referto
　
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