United Technologies Pratt and Whitney PT6A-60 Series Training Manual

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PREFACE

PT6A-60 SERIES

TRAINING MANUAL

November 2007

Pratt & Whitney Canada

STUDENT: ________________________________

INSTRUCTOR:_____________________________

PREFACE I

PT6A-60 SERIES

TRAINING USE ONLY

P&WC Proprietary - Disclosure and use subject to the restrictions on page 2 of preface

Table of Contents

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Summary of Contents for United Technologies Pratt and Whitney PT6A-60 Series

Page 1 PREFACE PT6A-60 SERIES TRAINING MANUAL November 2007 Pratt & Whitney Canada © 1999-2007 Pratt & Whitney Canada, Inc. STUDENT: ________________________________ INSTRUCTOR:_____________________________ PREFACE I PT6A-60 SERIES TRAINING USE ONLY P&WC Proprietary - Disclosure and use subject to the restrictions on page 2 of preface...
Page 2: Preface Ii
DISCLOSURE WARNING - PROPRIETARY RIGHTS NOTICE This document is the property of Pratt & Whitney Canada Corp. “(P&WC)”. You may not possess, use copy or disclose this document or any information in it, for any purpose, including without limitation to design, manufacture or repair parts, or obtain FAA or any other government approval to do so, without P&WC’s express written permission.
Page 3: Pratt & Whitney Canada
PRATT & WHITNEY CANADA The Customer Training Centre, Pratt and Whitney Canada, Longueuil, Quebec, Canada issued this document. This document is to be used for Training Use Only. The data contained herein does not replace or supersede the information contained in the appropriate airframe or engine maintenance manuals or other official publications. For information concerning this manual, contact the P&WC Customer Training Department, by : Tel: 1-450-468-7774, Fax: 1-450-468-7824, or Email: customer.training@pwc.ca...
Page 4 BLANK PAGE PREFACE IV PT6A-60 SERIES TRAINING USE ONLY P&WC Proprietary - Disclosure and use subject to the restrictions on page 2 of preface...
Page 5: Table Of Contents
TABLE OF CONTENT PREFACE ............I COMPRESSOR INLET CASE ......2.6-2.7 DISCLOSURE............II COMPRESSOR ........... 2.8-2.9 PRATT & WHITNEY CANADA......III-IV COMPRESSOR WASH ........2.10-2.11 TABLE OF CONTENT.......... V-VIII COMPRESSOR BLEED VALVE ......2.12-2.15 PRE-SWIRL SYSTEM ......... 2.16-2.19 INTRODUCTION ..........IX BLEED VALVE CLOSING POINT ......
Page 6: Table Of Content
TABLE OF CONTENT (CONT’D) CHAPTER 4 - GEARBOXES....... 4.1 CHAPTER 8 - IGNITION SYSTEM....8.1 REDUCTION GEARBOX ........4.2-4.3 IGNITION SYSTEM ......... 8.2-8.3 STANDARD ROTATION REDUCTION GEARBOX4.4 PT6A-66 REVERSE ROTATION GEARBOX ..4.5 CHAPTER 9 - PERFORMANCE ..... 9.1-9.2 ACCESSORY GEARBOX ........4.6-4.7 ENGINE PERFORMANCE CHECK (TYPICAL)9.3 PIN LOCK ARRANGEMENT .......
Page 7 TABLE OF CONTENT (CONT’D) FLOW DIVIDER WITH PURGE VALVE ....10.22-10.23 HOT SECTION TOOLS........12.8-12.9 SIMPLEX FUEL NOZZLES.......10.24-10.25 CT TIP CLEARANCE MEASUREMENT..12.10 DUPLEX FUEL NOZZLES........10.26-10.27 HOT SECTION INSPECTION (CONT’D)..12.12 FUEL CONTROL UNIT MANUAL OVERRIDE .10.28 CT BLADE SULPHIDATION ......12.13 FCU MANUAL OVERRIDE .......10.29 HOT SECTION INSPECTION (CONT’D)..
Page 8 BLANK PAGE TABLE OF CONTENT VIII PT6A-60 SERIES TRAINING USE ONLY P&WC Proprietary - Disclosure and use subject to the restrictions on page 2 of preface...
Page 9: Introduction
INTRODUCTION INTRODUCTION INTRODUCTION IX PT6A-60 SERIES TRAINING USE ONLY P&WC Proprietary - Disclosure and use subject to the restrictions on page 2 of preface...
Page 10: Scope
SCOPE This training guide contains information pertaining to the description, operation, maintenance and troubleshooting of the PT6A-52 /60A / 60AG / 61 / 64 / 65AG / 65AR / 65B / 65R / 66 / 66A / 66B / 66D / 67 / 67A / 67AF / 67AG / 67AF / 67AR / 67B / 67D / 67F / 67P /67R engines.
Page 11: Abbreviations
ABBREVIATIONS Agricultural Palt Pressure Altitude Accessory Gearbox Pamb Ambient Air Pressure Airframe Maintenance Manual Primary Blade Angle Bleed Off Valve Power Lever Angle Counterclockwise Pounds Per Hour Clockwise Pounds Per Square Inch Constant Speed Unit (Prop Governor) PSIA Pounds Per Square Inch Absolute Compressor Turbine PSID Pounds Per Square Inch Differential...
Page 12: Engines Covered In This Manual
ENGINES COVERED IN THIS MANUAL Weight Certification Engine Model Aircraft (Lbs) Date PT6A-52 April 2007 Blackhawk B200GT PT6A-60A 1050 May 1983 Beech KA 300/350 PT6A-60AG 1050 May 1995 Air Tractor AT-602, Ayres PT6A-61 March 1983 Piper Cheyenne IIIA PT6A-64 April 1990 Socata TBM 700 PT6A-65B 1100...
Page 13: Pt6 General Notes
PT6 GENERAL NOTES Initial Design ........... 1958 First Production Engine (PT6A-6, 550 SHP)... 1963 Engines Delivered........... 42338* Hours Accumulated......... 316 000 000* Certified Aircraft Applications......128 Different Operators ......... 6724 Different Countries .......... 171 * Numbers Current as of December 2006 The Birth Of Pratt &...
Page 14: Major Engine Differences
MAJOR ENGINE DIFFERENCES The PT6A Engines Covered In This Manual Are Divided equipped and connected) In 4 Groups: Group 3: PT6A-67, A-67A, A-67R, A-67AF, A-64, and - PT6A-52, 60A, 60AG, 61 A-66/A/B/D - PT6A-65B, A-65R, A-65AR, A-65AG The A-67 engines differ from the A-65 in the following - PT6A-67, A-67A, A-67AF, A-64, A-66/A/B/D manner: - PT6A-67AG, A-67B, A-67D, A-67F and A-67P...
Page 15 MAJOR ENGINE DIFFERENCES (CONTINUED) Group 3: (continued) Group 4: PT6A-67AG, A-67B, A-67D, A-67F and A-67P. The engines from this group include the following design PT6A-66/B: Mechanically similar to A-67 with reduction modifications for increase power ratings: gearbox capable of standard or reverse rotation (A-61 derivative, 2000 rpm).
Page 16: P&Wc Publications
P&WC PUBLICATIONS Pratt and Whitney Canada publish various documents and Training Manuals manuals to support all the engines in service. This is a brief description of the documents: Training guides are published by the Customer Training Centre to assist the instructors in class. Illustrated Parts Catalog (IPC) Publication Price List Contain all part numbers and parts history information...
Page 17: Publication Standards
PUBLICATION STANDARDS General: The engine manuals are published following the ATA 100 revision 15 The engine Maintenance Manual basic chapters and The engine illustrated parts catalogue (IPC) basic sections are: chapters and sections are: FRONT MATTER (TEMPORARY REVISION, SERVICE 61 - 20 PROPELLER GOVERNING BULLETIN LIST) 72 - 00 ENGINE (SHIPPING) INTRODUCTION (TOOLS, CONSUMABLES)
Page 18 PUBLICATION STANDARDS (CON’T) Page blocks: The page block numbers of each chapter are used to separate the subjects within the manual for ease of reference. The standard page blocks are as follows: CHAPTER APPLICABILITY Pages 61-20 70-00 71-00 72-00 All others Description and Operation 1 to 99 Fault isolation...
Page 19: Service Bulletin Compliance Codes
SERVICE BULLETIN COMPLIANCE CODES Category 1 Do before the next flight. Category 2 Do the first time the aircraft is at a line station or maintenance base that can do the procedure. Category 3 Do before xxx hours or xxx cycles. This Category may be expanded as required, to specify a minimum and/or a maximum and/or repetitive interval/inspection.
Page 20 BLANK PAGE INTRODUCTION XX PT6A-60 SERIES TRAINING USE ONLY P&WC Proprietary - Disclosure and use subject to the restrictions on page 2 of preface...
Page 21: Chapter 1 - Engine Overview
ENGINE OVERVIEW ENGINE OVERVIEW ENGINE OVERVIEW 1.1 PT6A-60 SERIES TRAINING USE ONLY P&WC Proprietary - Disclosure and use subject to the restrictions on page 2 of preface...
Page 22: Pt6A-61 Right Front View
PT6A-61 RIGHT FRONT VIEW ENGINE OVERVIEW 1.2 PT6A-60 SERIES TRAINING USE ONLY P&WC Proprietary - Disclosure and use subject to the restrictions on page 2 of preface...
Page 23: Pt6A-64 Left Front View
PT6A-64 LEFT FRONT VIEW ENGINE OVERVIEW 1.3 PT6A-60 SERIES TRAINING USE ONLY P&WC Proprietary - Disclosure and use subject to the restrictions on page 2 of preface...
Page 24: Pt6A-60 Right Front View
PT6A-60 RIGHT FRONT VIEW ENGINE OVERVIEW 1.4 PT6A-60 SERIES TRAINING USE ONLY P&WC Proprietary - Disclosure and use subject to the restrictions on page 2 of preface...
Page 25: Pt6A-67 Left View
PT6A-67 LEFT VIEW ENGINE OVERVIEW 1.5 PT6A-60 SERIES TRAINING USE ONLY P&WC Proprietary - Disclosure and use subject to the restrictions on page 2 of preface...
Page 26: Major Assemblies And Flanges
MAJOR ASSEMBLIES AND FLANGES (POWER SECTION MODULE) EXHAUST DUCT POWER TURBINE HOUSING POWER TURBINE SHAFT HOUSING REDUCTION GEARBOX BUS BAR 2ND STAGE POWER TURBINE POWER SECTION 1ST STAGE 2ND STAGE VANE RING VANE RING 1ST STAGE POWER TURBINE ENGINE OVERVIEW 1.6 PT6A-60 SERIES TRAINING USE ONLY P&WC Proprietary - Disclosure and use subject to the restrictions on page 2 of preface...
Page 27 MAJOR ASSEMBLIES & FLANGES (GAS GENERATOR MODULE) DIAPHRAGM COMPRESSOR INLET ASSEMBLY CASE ACCESSORY GAS GENERATOR GEARBOX CASE COVER COMPRESSOR COMPRESSOR COMBUSTION TURBINE TURBINE CHAMBER GAS GENERATOR SECTION VANE RING ENGINE OVERVIEW 1.7 PT6A-60 SERIES TRAINING USE ONLY P&WC Proprietary - Disclosure and use subject to the restrictions on page 2 of preface...
Page 28: Features
FEATURES Modules: Reduction Gearbox: - Gas Generator - 2 stage planetary reduction - Power Section - Built-in hydro-mechanical torque measurement sys- tem. Main Components: - Reduce the power turbine speed to a speed suitable for propeller operation. Accessory Gearbox: - Driven by the compressor Engine Control System: - Provide drives for engine and aircraft accessories - Variable speed propeller...
Page 29 NOTES ENGINE OVERVIEW 1.9 PT6A-60 SERIES TRAINING USE ONLY P&WC Proprietary - Disclosure and use subject to the restrictions on page 2 of preface...
Page 30: General Turboprop Operation
GENERAL TURBOPROP OPERATION The PT6 is a lightweight turbine engine driving a propeller The hot expanding gases accelerate through the compres- via a two-stage reduction gearbox. Two major rotating sor turbine vane ring and cause the compressor turbine to assemblies compose the heart of the engine. The first is rotate (which rotates the compressor (approx.
Page 31: Turboprop Engine
TURBOPROP ENGINE COMPRESSOR TURBINE 2 ND STAGE 1 ST STAGE ACCESSORY POWER REDUCTION REDUCTION GEARBOX TURBINES COMPRESSOR GEAR GEAR PROPELLER SHAFT ENGINE OVERVIEW 1.11 PT6A-60 SERIES TRAINING USE ONLY P&WC Proprietary - Disclosure and use subject to the restrictions on page 2 of preface...
Page 32: Main Engine Bearings
MAIN ENGINE BEARINGS Function: Operation: - The ball bearings withstand the following thrusts: To support major rotating assemblies and minimize friction. - No. 1 bearing: Compressor thrust (rearward) - No. 4 bearing: Power turbine thrust (forward) Ball Bearings: - No. 6 bearing: Propeller thrust (forward) - Bearing nos.
Page 33: Bearings
BEARINGS A-60 A-65 A-67 A-52 A-61 A-64 A-66 ENGINE OVERVIEW 1.13 PT6A-60 SERIES TRAINING USE ONLY P&WC Proprietary - Disclosure and use subject to the restrictions on page 2 of preface...
Page 34: Stations
STATIONS 1 - AIR INTAKE 2 - COMPRESSOR INLET 2.5 - COMPRESSOR INTERSTAGE 3 - COMPRESSOR DISCHARGE PRESSURE 4 - COMPRESSOR TURBINE INLET 5 - INTERTURBINE 6 - TURBINE EXHAUST 7 - EXHAUST OUTLET ENGINE OVERVIEW 1.14 PT6A-60 SERIES TRAINING USE ONLY P&WC Proprietary - Disclosure and use subject to the restrictions on page 2 of preface...
Page 35 STATIONS PRESS TEMP PSIA 1100 1000 P2.5 NOTE: PRESSURES AND TEMPERATURES LISTED TEMPERATURE ARE TAKEN AT TAKEOFF POWER, STANDARD PRESSURE DAY FOR A PT6A-65 ENGINE ENGINE OVERVIEW 1.15 PT6A-60 SERIES TRAINING USE ONLY P&WC Proprietary - Disclosure and use subject to the restrictions on page 2 of preface...
Page 36: Engine External Components
ENGINE EXTERNAL COMPONENTS Reversing Cable T5 Harness T1 Trim Resistor (Trim Stick) Decal Patents Designation Cam Box (Reversing) Oil Return From Airframe Cooler Overboard Breather Discharge Oil Dipstick - (Electrical A-67B) Starter/Generator Pad Fuel Control Unit Oil To Airframe Cooler Fuel Pump Oil To Fuel Heater Oil Pressure Tapping...
Page 37 EXTERNAL COMPONENTS ENGINE OVERVIEW 1.17 PT6A-60 SERIES TRAINING USE ONLY P&WC Proprietary - Disclosure and use subject to the restrictions on page 2 of preface...
Page 38 ENGINE EXTERNAL COMPONENTS Inlet Screen P2.5 Cabin Bleed Fireseal - Front Fuel Nozzle Adapter Py Air Line Data Plate - Power Section Propeller Governor (CSU) Propeller Shaft Propeller Overspeed Governor Pad Torque Oil Pressure Port Chip Detector Igniter Plug Engine Mount Pad P3 Cabin Bleed Port Oil Scavenge Tubes Ignition Cables...
Page 39 EXTERNAL COMPONENTS ENGINE OVERVIEW 1.19 PT6A-60 SERIES TRAINING USE ONLY P&WC Proprietary - Disclosure and use subject to the restrictions on page 2 of preface...
Page 40 BLANK PAGE ENGINE OVERVIEW 1.20 PT6A-60 SERIES TRAINING USE ONLY P&WC Proprietary - Disclosure and use subject to the restrictions on page 2 of preface...
Page 41: Chapter 2 - Compressor Section
COMPRESSOR SECTION COMPRESSOR SECTION COMPRESSOR SECTION 2.1 PT6A-60 SERIES TRAINING USE ONLY P&WC Proprietary - Disclosure and use subject to the restrictions on page 2 of preface...
Page 42 COMPRESSOR SECTION Function: Compressor Air Is Used For The Following: - Supplies the required mass of air at the right pressure - Sustain combustion in order to produce the energy to the combustion chamber and all the supporting sys- required to drive the compressor and the power sec- tems tion (propeller) - Transmits the rotational energy from the compressor...
Page 43: Compressor Section
COMPRESSOR SECTION BLEED VALVE INLET CASE COMPRESSOR GAS GENERATOR COMPRESSOR SECTION 2.3 PT6A-60 SERIES TRAINING USE ONLY P&WC Proprietary - Disclosure and use subject to the restrictions on page 2 of preface...
Page 44: Inertial Separator (Airframe)
INERTIAL SEPARATOR (AIRFRAME) Function: Protects the engine from ingesting foreign objects such as When carrying-out a performance check, always assure stones, ice, sand, snow, rain, etc. that the inertial separator doors are in the CLOSED posi- tion. Inertial separator doors left in the open position will cause an increase in Ng, ITT and Wf which could be Operation: interpreted as a deteriorated compressor.
Page 45: Inertial Separator (Typical)
INERTIAL SEPARATOR (TYPICAL) BYPASS (ICING) POSITION NORMAL POSITION COMPRESSOR SECTION 2.5 PT6A-60 SERIES TRAINING USE ONLY P&WC Proprietary - Disclosure and use subject to the restrictions on page 2 of preface...
Page 46: Compressor Inlet Case
COMPRESSOR INLET CASE Function: Maintenance: - Directs air into the compressor - Inspect inlet screen for damage and cleanliness. Wire - Support no. 1 bearing mesh damage is not acceptable - Forms the oil tank - Inspect inlet screen rubber sealing rims for damage - Piccolo holes in hollow struts generate pre-swirl - Inspect inlet case for cracks in the strut area - Sight glass on left side of case allows for quick oil level...
Page 47 INLET CASE OIL TANK VENT AND PRESSURIZING VALVE OIL RETURN FROM COOLER PICOLLO HOLES OIL TO AGB OIL FILTER HOUSING INLET SCREEN LOCATION AIR INLET OIL FROM THERMOSTATIC AND BYPASS VALVE OIL LEVEL SIGHT GLASS OIL TANK DRAIN NO.1 BEARING SCAVENGE NO.2 BEARING OIL TANK...
Page 48: Compressor
COMPRESSOR Function: Compression Ratios: - Provides the combustion chamber with the correct air- flow at the required pressure 52, 60A,61 - The number 1 bearing supports the rear end of the 64, 65, 66, 67 12.1 compressor - The flexible housing transforms compressor vibrations Operation: Construction: Axial stage accelerates the air, which is then decelerated...
Page 49 COMPRESSOR AXIAL BLEED VALVE STAGES NO. 2 BRG. PICCOLO CENTRIFUGAL HOLES IMPELLER NO. 1 BRG. NO. 1 BRG. FLEXIBLE HOUSING INLET CASE GENERATOR CASE COMPRESSOR SECTION 2.9 PT6A-60 SERIES TRAINING USE ONLY P&WC Proprietary - Disclosure and use subject to the restrictions on page 2 of preface...
Page 50: Compressor Wash
COMPRESSOR WASH Function: - Remove salt and dirt deposits from the compressor After Wash Procedure: gas path - Reconnect P3 line to the FCU - Promote parts life and reduce potential overhaul costs Special Procedure: - If isopropyl alcohol or kerosene was used in the Type Of Washes: cleaning solution perform a dry motoring run before - Desalination wash...
Page 51 COMPRESSOR WASH COMPRESSOR WASH RING CLEANING SHUTOFF SHUTOFF SOLUTION VALVE VALVE PRESS. PRESS. GAGE GAGE REGULATED SPRAY SPRAY RING AIR PRESSURE RING WATER REGULATED AIR PRESSURE WATER DESALINATION SYSTEM PERFORMANCE RECOVERY SYSTEM COMPRESSOR SECTION 2.11 PT6A-60 SERIES TRAINING USE ONLY P&WC Proprietary - Disclosure and use subject to the restrictions on page 2 of preface...
Page 52: Compressor Bleed Valve
COMPRESSOR BLEED VALVE (64/65/66/67) Function: Px pressure depends on the restriction at the outlet of the cavity where it is drawn. This restriction is controlled by the Prevents compressor stall at low Ng. inside diameter of the compressor turbine stator air seal (baffle).
Page 53 COMPRESSOR BLEED VALVE (64/65/66/67) SEAL RING RETAINING RING DETAIL BLEED VALVE COVER GUIDE PIN PISTON BLEED SEAL RING VALVE VALVE SEAT HOUSING CLASSIFIED RETAINING RING VALVE SEAT SEAL RING PX (P3) PISTON P2.5 COMPRESSOR SECTION 2.13 PT6A-60 SERIES TRAINING USE ONLY P&WC Proprietary - Disclosure and use subject to the restrictions on page 2 of preface...
Page 54 COMPRESSOR BLEED VALVE (52/60/61) Function: As Ng increases, P3 rises faster than P2.5, thus increasing the pressure acting on the piston to gradually close it. The Prevents compressor stall at low Ng speed (Ng) at which the valve closes is a function of the Pri- mary and Convergent Divergent orifice sizes.
Page 55 BLEED VALVE (52/60/61) CONTROL PRESSURE (Px) AMBIENT PRESSURE (Pa) COVER FINAL ROLLING DIAPHRAGM ORIFICE GUIDE PIN SHAFT PISTON PRIMARY ORIFICE DISCHARGE PISTON DAMPER TO ATMOSPHERE DELIVERY (SPRING LOADED) PASSAGE PISTON SEAT SLEEVE P2.5 P2.5 CLOSED POSITION OPEN POSITION COMPRESSOR SECTION 2.15 PT6A-60 SERIES TRAINING USE ONLY P&WC Proprietary - Disclosure and use subject to the restrictions on page 2 of preface...
Page 56: Pre-Swirl System
PRE-SWIRL SYSTEM Function: Operation: - Change the relative angle of attack of the air entering the compressor When the bleed valve opens, P2.5 air flows to the plenum - Improve surge margin at low compressor speed chamber and to the inlet case hollow struts. The piccolo holes located on the inlet case struts produce P2.5 air jets Description: that cause swirling of the incoming air before it enters the...
Page 57 PRE-SWIRL SYSTEM (PICCOLO HOLES) INLET SCREEN INLET AIR P 2.5 INTERSTAGE PICCOLO HOLES NO. 1 BEARING COMPRESSOR SECTION 2.17 PT6A-60 SERIES TRAINING USE ONLY P&WC Proprietary - Disclosure and use subject to the restrictions on page 2 of preface...
Page 58 NOTES COMPRESSOR SECTION 2.18 PT6A-60 SERIES TRAINING USE ONLY P&WC Proprietary - Disclosure and use subject to the restrictions on page 2 of preface...
Page 59 PRE-SWIRL SYSTEM (52/60/61) (SLOTTED STRUTS) CASE HOLLOW STRUT TANGENTIAL FLOW (JET FLAP) INLET SCREEN SWING CHECK VALVE AIR INLET A65’s P 2.5 INTER-STAGE AIR COMPRESSOR BLEED VALVE BLEED AIR CASE ASSEMBLY P 2.5 P 2.5 FIRST - STAGE COMPRESSOR BLADE P 2.5 NO.
Page 60: Bleed Valve Closing Point
BLEED VALVE CLOSING POINT (65/67) Function: Note: If closing point does not fall within the tolerance band, the To verify at what Ng speed the bleed valve closes. following adjustments can be made. - Install higher class seat to raise Ng closing point Description: - Install lower class seat to lower Ng closing point - Replace bleed valve if piston does not move freely...
Page 61 BLEED VALVE CLOSING POINT CHECK 37.5 95.1 NOTE: OPERATING ABOVE THE BAND IS ACCEPTABLE. RUBBER TUBE 85.55 NOTE: OPERATING BELOW THE BAND IS NOT RECOMMENDED, AS THIS 84.25 MAY RESULT IN ENGINE STALL / SURGE DURING ACCELERATION / DECELERATION. −20 −10 −30 OUTSIDE AIR TEMPERATURE ( C)
Page 62 BLEED VALVE CLOSING POINT (52/60A/61) Description: Closing Point Too HIGH (Ng) ->Install Larger Orifice: A different closing point test is required for these BOV’s because these engines are ‘flat rated’ so they can make If plotted point is above acceptable range with more power at higher altitudes and temperatures.
Page 63 BLEED VALVE CLOSING POINT CHECK (52/60/61) CABIN BLEED AIR TRANSFER TUBE BOSS DIGITAL PRESSURE GAGE COMPRESSOR SECTION 2.23 PT6A-60 SERIES TRAINING USE ONLY P&WC Proprietary - Disclosure and use subject to the restrictions on page 2 of preface...
Page 64: Gas Generator Case
GAS GENERATOR CASE Function: Operation: Houses and supports various engine components such as The gas generator case houses the components necessary #2 brg, compressor assembly, engine mounts, diffuser for the compression of air and combustion of the fuel/air pipes. mixture. The gas generator case contains P3 air pressure. The diffuser pipes change the high velocity (2000ft/sec) low Tubes for oil pressure and scavenge to the number 2 bear- pressure into low velocity (200ft/sec) and high pressure.
Page 65: Gas Generator Case / Diffuser
GAS GENERATOR CASE / DIFFUSER AIR PRESSURE TUBE DIFFUSER PIPE TO BLEED VALVE FLANGE "C" NO. 2 BEARING. PRESSURE OIL TUBE P3 PRESSURE TUBE NO. 2 BEARING TO FUEL CONTROL SCAVENGE OIL TUBE STRAIGHTENING VANE COMPRESSOR SECTION 2.25 PT6A-60 SERIES TRAINING USE ONLY P&WC Proprietary - Disclosure and use subject to the restrictions on page 2 of preface...
Page 66: Cold Section Troubleshooting
COLD SECTION TROUBLESHOOTING Problem Symptoms At Constant Power Action Required Restricted inlet screen Clean and/or remove obstruction Dirty compressor Perform compressor wash /revise schedule Damaged compressor blades Blend blades as per Engine Maintenance Manual. Return to an approved overhaul facility if damage is beyond limit.
Page 67: Chapter 3 - Combustion & Turbine
COMBUSTION & TURBINE COMBUSTION & TURBINE COMBUSTION & TURBINE 3.1 PT6A-60 SERIES TRAINING USE ONLY P&WC Proprietary - Disclosure and use subject to the restrictions on page 2 of preface...
Page 68: Hot Section
HOT SECTION Description: Produce and extract energy from the hot expanding gases to drive the compressor turbine, compressor and AGB accessories. At the same time, drive the power turbines / propeller to provide thrust for the aircraft. Components: - Combustion chamber - Compressor turbine vane ring - Compressor turbine - Power turbine housing...
Page 69: Hot Section Area
HOT SECTION AREA POWER TURBINE POWER POWER STATOR HOUSING TURBINE TURBINES EXHAUST VANE RINGS CASE NO. 2 BRG COMBUSTION COVER CHAMBER COMPRESSOR FLANGE TURBINE VANE RING SHROUD LOCK SHROUD SEGMENTS SEALING PLATE SEGMENT RING COMPRESSOR HOUSING TURBINE SMALL EXIT NO. 2 BRG DUCT C.T.
Page 70: Combustion Chamber Liner & Small Exit Duct
COMBUSTION CHAMBER LINER & SMALL EXIT DUCT Function: The combustion chamber forms an envelope that turns the gas 180°. This configuration permits location of the tur- Provide an area for the combustion of fuel/air mixture and bines closer to the compressor and within the combustion form an envelope that changes the direction of the gas flow chamber area, thus making the engine shorter and lighter.
Page 71 COMBUSTION CHAMBER AND SMALL EXIT DUCT FUEL NOZZLE COOLING RINGS ADAPTER BOSSES LOUVERED COOLING RING OUTER LINER OUTER LINER INNER LINER INNER LINER SMALL SPARK EXIT IGNITER BOSS SMALL EXIT DUCT DUCT COOLING RING COMBUSTION & TURBINE 3.5 PT6A-60 SERIES TRAINING USE ONLY P&WC Proprietary - Disclosure and use subject to the restrictions on page 2 of preface...
Page 72: Compressor Turbine Vane Ring
COMPRESSOR TURBINE VANE RING Vane Ring: Operation: - Directs and accelerates gases to the compressor tur- bine at the optimum angle and speed. The compressor turbine vane ring receives hot gases from - Convergent vanes change static pressure into velocity the combustion chamber.
Page 73 COMPRESSOR TURBINE VANE RING (52/60/61) COMPRESSIBLE SEALS INTERSTAGE (SB13168) SEAL RINGS SMALL P3 AIR EXIT DUCT OUTER VANE LINER RING CLEARANCE SHROUD HOUSING P3 AIR LOCK PLATE SHROUD SEGMENT NO.2 BEARING COVER COMPRESSOR TURBINE POST-SB 13181 PRE-SB 13181 COMBUSTION & TURBINE 3.7 PT6A-60 SERIES TRAINING USE ONLY P&WC Proprietary - Disclosure and use subject to the restrictions on page 2 of preface...
Page 74: Compressor Turbine
COMPRESSOR TURBINE VANE RING (64, 66, 67A, AG, AF, R) SHROUD HOUSING INTERSTAGE SEALING RINGS SMALL P3 AIR EXIT DUCT CLEARANCE VANE RING P3 AIR SHROUD SEGMENTS COMPRESSOR TURBINE LOCK PLATE COMBUSTION & TURBINE 3.8 PT6A-60 SERIES TRAINING USE ONLY P&WC Proprietary - Disclosure and use subject to the restrictions on page 2 of preface...
Page 75 COMPRESSOR TURBINE VANE RING (66B, 66D, 67B, 67D, 67F and 67P) COMPRESSIBLE SEALS INTERSTAGE SMALL SEALING RINGS P3 AIR EXIT DUCT P3 AIR CLEARANCE VANE RING SEAL RING P3 AIR P3 AIR COMPRESSOR TURBINE P3 AIR LOCK PLATE NO.2 BEARING COVER COMBUSTION &...
Page 76 COMPRESSOR TURBINE Function: At maximum speed, the compressor rotor turns at approxi- mately 39,000 rpm (104%), with each blade pulling on the Extract energy from the hot gases to turn the compressor disk with a force of approximately one ton (2000 lbs.). rotor unit.
Page 77 COMPRESSOR TURBINE MASTER SPLINE DETAIL WEIGHT CUP WASHER RETAINING BOLT COMBUSTION & TURBINE 3.11 PT6A-60 SERIES TRAINING USE ONLY P&WC Proprietary - Disclosure and use subject to the restrictions on page 2 of preface...
Page 78: Compressor Turbine Trim Balancing
COMPRESSOR TURBINE TRIM BALANCING (64, 66, 67) Function: Example: A residual unbalance remains once the CT is mated with 1st weight -- B 05 L -- the compressor assembly. Adding TRIM weights minimizes vibration and maintains original compressor rotor balance Denotes trim weight class (A,B, C, D, E and G) during field replacement of the compressor turbine.
Page 79: Compressor Turbine
COMPRESSOR TURBINE TRIM BALANCE WEIGHTS #1 ALIGNED WITH 1 2 3 C/T DISK REAR FACE PLANE A PLANE B MASTER SPLINE REAR FRONT FACE FACE C/T DISK FRONT FACE LIGHT MANUFACTURED HEADS OFFSET ON INSIDE OF RIM, BOTH FACES HEAVY OFFSET DATA PLATE PERFORMANCE REFERENCE DATA...
Page 80: Alternate Trim Weights
ALTERNATE TRIM WEIGHTS (64/66/67) Function: Starting from hole no. 4 counter clockwise and from hole no. 7 clockwise (the weights are installed at holes no. 39 Allows the trim balancing to perform even when the trim and 40 on one side and holes no. 11 and 12 in the other). weights location as per the data plate is occupied by detail Alternatively, 2 class # 1 weights can be installed 6 holes balancing weights.
Page 81 ALTERNATE TRIM WEIGHTS NOTE: WHEN A NEW DETAIL WEIGHT OCCUPIES A TRIM WEIGHT ORIGINAL LOCATION TRIM WEIGHT TABLE (REF. DATA PLATE), ALTERNATIVE TRIM WEIGHTS MUST BE USED IN PAIRS ONE EACH SIDE OF AND EQUIDISTANT FROM ORIGINAL TRIM WEIGHT LOCATION TRIM WEIGHT CLASS CLASS CLASS...
Page 82: Power Turbine Vane Rings
POWER TURBINE VANE RINGS Function: Operation: - Direct gases to the first and second stage power tur- bines at the optimum speed and angle Gases leaving the compressor turbine are accelerated - Change static pressure into velocity through the first and second stage vane rings while causing their respective power turbines to rotate.
Page 83 POWER TURBINE VANE RINGS P.T. VANE RING T5 PROBE FIRST STAGE SLOT F L O A I R P.T. VANE RING SECOND STAGE COMBUSTION & TURBINE 3.17 PT6A-60 SERIES TRAINING USE ONLY P&WC Proprietary - Disclosure and use subject to the restrictions on page 2 of preface...
Page 84: Power Turbines
POWER TURBINES Function: Operation: Extract energy from the gases to drive the propeller through The two power turbines extract the energy necessary to the reduction gearbox. drive the propeller. The rotational energy extracted by the power turbine is Description: transmitted to the power turbine shaft through splines on - Turbine disks are machined from nickel alloy the second stage turbine hub.
Page 85 POWER TURBINES FIRST STAGE POWER TURBINE SHROUDED BLADES AIR SEAL SECOND STAGE POWER TURBINE COMBUSTION & TURBINE 3.19 PT6A-60 SERIES TRAINING USE ONLY P&WC Proprietary - Disclosure and use subject to the restrictions on page 2 of preface...
Page 86: Turbine Wash
TURBINE WASH Function: Sulphidation: Remove salt deposits from the turbine section of the engine Sulphidation is a common name for a type of hot corrosion to minimize sulphidation of the turbine blades. which can affect turbine area components. Sulphidation occurs at engine operating temperatures when Method: sodium and sulphur are present.
Page 87 TURBINE WASH SHUTOFF VALVE CLEAN OR DEMINERALIZED WATER PRESSURE GAGE REGULATED AIR / NITROGEN PRESSURE COMBUSTION & TURBINE 3.21 PT6A-60 SERIES TRAINING USE ONLY P&WC Proprietary - Disclosure and use subject to the restrictions on page 2 of preface...
Page 88: Exhaust Duct & Pt Shaft Housing
EXHAUST DUCT & PT SHAFT HOUSING Exhaust Duct: - Direct the exhaust gases to ambient atmosphere with minimum flow restriction - Welded assembly of heat resistant Nickel alloy sheet metal - On the A-67R/A-65AR, the exhaust duct is rotated 30° to suit the airframe installation (Shorts) Power Turbine Stator Housing: - Support the power turbine vane rings, the T5 harness...
Page 89 EXHAUST DUCT & PT SHAFT HOUSING POWER NO. 3 BEARING TURBINE PT SHAFT SHAFT HOUSING POWER TURBINES POWER TURBINE STATOR HOUSING PT SHAFT HOUSING FLANGE "B" POWER TURBINE INSULATION NO. 4 VANE RINGS REAR BLANKET BEARING CASE EXHAUST DUCT COMBUSTION & TURBINE 3.23 PT6A-60 SERIES TRAINING USE ONLY P&WC Proprietary - Disclosure and use subject to the restrictions on page 2 of preface...
Page 90 SEALING OF THE HOT SECTION AREA (52/60/61/64/65/66/67, A, AF, R) Function: Gas sealing in the hot section area is a very important factor affecting hot section life. This section describes the major sealing surfaces in the hot section and their purposes. Sealing Description Function...
Page 91: Hot Section Sealing
HOT SECTION SEALING COMBUSTION & TURBINE 3.25 PT6A-60 SERIES TRAINING USE ONLY P&WC Proprietary - Disclosure and use subject to the restrictions on page 2 of preface...
Page 92 SEALING OF THE HOT SECTION AREA (67AG, 67B, D, F, P, T, 66B, 66D) Function: Gas sealing in the hot section area is a very important factor affecting hot section life. This section highlight sealing sur- faces in the hot section and their functions. Sealing Description Function...
Page 93 HOT SECTION SEALING COMBUSTION & TURBINE 3.27 PT6A-60 SERIES TRAINING USE ONLY P&WC Proprietary - Disclosure and use subject to the restrictions on page 2 of preface...
Page 94: Hot Section Troubleshooting
HOT SECTION TROUBLESHOOTING Problem Symptoms At Constant Power Action Required Seal ring leak Same Reposition or replace seal ring. Verify seal ring groove and replace shroud housing if damaged. Gas leakage at junction between Same Lap sealing faces. Send parts to an small exit duct and vane ring approved shop if required to restore the sealing faces.
Page 95: Chapter 4 - Gearboxes
GEARBOXES GEARBOXES REDUCTION GEARBOX 4.1 PT6A-60 SERIES TRAINING USE ONLY P&WC Proprietary - Disclosure and use subject to the restrictions on page 2 of preface...
Page 96: Reduction Gearbox
REDUCTION GEARBOX Function: The second stage reduction system is similar to the first stage but uses five planet gears instead of three. The sec- Reduce the power turbine speed to a speed suitable for pro- ond stage gear carrier drives the propeller shaft via splines. peller operation.
Page 97 REDUCTION GEARBOX REAR HOUSING 1ST STAGE 2ND STAGE FRONT HOUSING REDUCTION GEARBOX 4.3 PT6A-60 SERIES TRAINING USE ONLY P&WC Proprietary - Disclosure and use subject to the restrictions on page 2 of preface...
Page 98: Standard Rotation Reduction Gearbox4.4
STANDARD ROTATION REDUCTION GEARBOX SECOND STAGE SECOND STAGE PLANET GEAR FIRST STAGE RING GEAR RING GEAR ACC. DRIVES(3) FIRST STAGE PLANET GEAR FIRST STAGE SUN GEAR SECOND STAGE SUN GEAR REDUCTION GEARBOX 4.4 PT6A-60 SERIES TRAINING USE ONLY P&WC Proprietary - Disclosure and use subject to the restrictions on page 2 of preface...
Page 99: Pt6A-66 Reverse Rotation Gearbox
PT6A-66 REVERSE ROTATION GEARBOX REDUCTION GEARBOX 4.5 PT6A-60 SERIES TRAINING USE ONLY P&WC Proprietary - Disclosure and use subject to the restrictions on page 2 of preface...
Page 100: Accessory Gearbox
ACCESSORY GEARBOX Function: Construction: - Two light alloy casings (diaphragm and rear hsg.) sup- Provides drive pads for engine and airframe accessories port the drive gears. such as: - The casings are bolted together and then to the inlet - Fuel pump and fuel control unit case.
Page 101 ACCESSORY GEARBOX FUEL PUMP & FCU GEAR CENTRIFUGAL BREATHER & STARTER GENERATORS GEARS 6250 11000 7650 4200 OPTIONAL ACCESSORY DRIVES PRE-SB14112 MAIN OIL PRESSURE PUMP, OIL SCAVENGE PUMP & 12000 TACHO-GENERATOR EXTERNAL OIL SCAVENGE & POST-SB14112 3800 OPTIONAL DRIVE REDUCTION GEARBOX 4.7 PT6A-60 SERIES TRAINING USE ONLY P&WC Proprietary - Disclosure and use subject to the restrictions on page 2 of preface...
Page 102: Pin Lock Arrangement
PIN LOCK ARRANGEMENT COMPRESSOR HUB A.G.B. COUPLING SHAFT INSERT SEAL RING SPRING SLEEVE REDUCTION GEARBOX 4.8 PT6A-60 SERIES TRAINING USE ONLY P&WC Proprietary - Disclosure and use subject to the restrictions on page 2 of preface...
Page 103: Accessory Gearbox
ACCESSORY GEARBOX BALL-LOCK ARRANGEMENT PRE SB13161 FLANGED ROLLER ACCESSORY GEARBOX HOUSING BEARING ACCESSORY GEARBOX DIAPHRAGM BALL LOCK REAR HUB COMPRESSOR ASSEMBLY PLUG OIL TRANSFER TUBE GEARBOX INPUT DRIVESHAFT INLET CASE PRESSURE PUMP REDUCTION GEARBOX 4.9 PT6A-60 SERIES TRAINING USE ONLY P&WC Proprietary - Disclosure and use subject to the restrictions on page 2 of preface...
Page 104 NOTES REDUCTION GEARBOX 4.10 PT6A-60 SERIES TRAINING USE ONLY P&WC Proprietary - Disclosure and use subject to the restrictions on page 2 of preface...
Page 105: Chapter 5 - Oil System
OIL SYSTEM OIL SYSTEM OIL SYSTEM 5.1 PT6A-60 SERIES TRAINING USE ONLY P&WC Proprietary - Disclosure and use subject to the restrictions on page 2 of preface...
Page 106 OIL SYSTEM Function: Oil System Flushing: - Supplies filtered oil to the engine in order to cool, lubri- - Flush oil system if new type of oil is to be used cate and clean various components - Refer to Engine Maintenance Manual for flushing pro- - Provides oil to the propeller governor to allow propeller cedure pitch and speed control.
Page 107 OIL SYSTEM (BOTTOM VIEW) OIL TO AIRFRAME OIL PRESSURE LINE COOLER OIL OUT TO COOLER RGB & PROPELLER NO. 2 BEARING NO. 3 & 4 BEARING SCAVENGE PRESSURE OIL SYSTEM 5.3 PT6A-60 SERIES TRAINING USE ONLY P&WC Proprietary - Disclosure and use subject to the restrictions on page 2 of preface...
Page 108 OIL SYSTEM Pressure System: The accessory gearbox receives oil from the No. 1, 2, 3 and 4 bearings scavenge systems. From there, the oil is routed Oil is drawn from the oil tank through a gear type pump and to the fuel heater by the AGB scavenge pump. is delivered to the oil filter and Pressure Regulating Valve.
Page 109 OIL SYSTEM (REAR) OIL IN FROM AIRFRAME COOLER THERMOSTATIC BYPASS & CHECK VALVE CENTRIFUGAL TO OIL BREATHER AIRFRAME COOLER MAIN OIL FILTER PRESSURE TRANSMITTER TEMP. BULB SCAVENGE OIL TANK DRAIN OIL SUPPLY TO PROPELLER & REDUCTION OIL SYSTEM 5.5 PT6A-60 SERIES TRAINING USE ONLY P&WC Proprietary - Disclosure and use subject to the restrictions on page 2 of preface...
Page 110 OIL SYSTEM (CONT’D) No. 3 and 4 bearing area scavenge into the accessory gearbox via a scavenge tube mounted on the left-hand side of the engine. Oil is scavenged by one of the externally mounted pumps located at the rear of the accessory gearbox.
Page 111 OIL SYSTEM (FRONT) TORQUE PRESS. TRANSDUCER PROPELLER GOVERNOR OIL SUPPLY TO PROPELLER TORQUEMETER OIL SUPPLY SCAVENGE OIL TO PROPELLER AND REDUCTION OIL SYSTEM 5.7 PT6A-60 SERIES TRAINING USE ONLY P&WC Proprietary - Disclosure and use subject to the restrictions on page 2 of preface...
Page 112: Oil Pressure Regulation & Filtration
OIL PRESSURE REGULATION & FILTRATION Oil Pump: Filter: - Gear type - 15 micron filter with 40 micron internal screen. - Inlet screen protects the pump - Clean electro-sonically only (post SB 13412 and 14392 are not cleanable). - Inspect every 100 hours. Pressure Regulating Valve: - Discard at 1000 hours - Maintains engine oil pressure within specified limits...
Page 113 OIL PRESSURE REGULATION & FILTRATION PRESSURE REGULATING VALVE COLD OIL PRESSURE RELIEF VALVE BLEED ORIFICE FILTER SECONDARY BYPASS FILTER VALVE INLET CASE OIL PUMP `O`RING CHECK FILTER VALVE HOUSING OIL PUMP GEARS BY PASS OIL PRESSURE OIL TO PRESSURE INLET FILTERED PRESSURE OIL SYSTEM SCREEN...
Page 114: Thermostatic Bypass & Check Valve
THERMOSTATIC BYPASS & CHECK VALVE Function: The check valve opens when the oil pressure coming from the fuel heater is higher than the pressure of the scavenge Bring oil to normal operating temperature faster during first oil from the reduction gearbox by 5 psi. This allows the oil few minutes of engine operation.
Page 115 THERMOSTATIC BYPASS & CHECK VALVE RETURN FROM COOLER EXPANSIVE THERMOSTATIC MATERIAL ELEMENT OIL OUT TO TANK TANK RETURN BYPASS SPRING VALVE FROM SCAVENGE FUEL RELIEF SPRING CHECK OIL OUT TO THERMOSTATIC FUEL IN FUEL HEATER VALVE AIR FRAME COOLER BYPASS SCAVENGE OIL OUT TO COOLER AIR &...
Page 116: Oil System Troubleshooting
OIL SYSTEM TROUBLESHOOTING Symptoms Possible Cause And Fix High Oil Pressure Check indicating system Adjust/verify pressure regulating valve. Low Oil Pressure Clean/replace oil filter Check indicating system Cracked oil pump housing Adjust pressure regulating valve Oil Pressure Fluctuation Check oil level Check indicating system Check oil tank pressurizing valve Replace/Clean pressure regulating valve...
Page 117 OIL SYSTEM TROUBLESHOOTING (CONT’D)) Symptoms Possible Cause And Fix Excessive Oil Discharged From Oil level kept too high. Overboard Breather Verify oil filter check valve (static transfer, blown out during start). Check O-rings between oil filter housing and inlet case (static transfer) Verify/replace centrifugal breather carbon seal in accessory gearbox.
Page 118 NOTES OIL SYSTEM 5.14 PT6A-60 SERIES TRAINING USE ONLY P&WC Proprietary - Disclosure and use subject to the restrictions on page 2 of preface...
Page 119: Chapter 6 - Secondary Air System
SECONDARY AIR SYSTEM SECONDARY AIR SYSTEM ENGINE INDICATING 6.1 PT6A-60 SERIES TRAINING USE ONLY P&WC Proprietary - Disclosure and use subject to the restrictions on page 2 of preface...
Page 120 SECONDARY AIR SYSTEM General: The secondary air system consists of all the compressor air that is not used to sustain combustion or for airframe use. Of all the air entering the engine the combustion process uses only 25%, 65% cools the combustion gases, the air- frame uses 5% and the secondary air system uses the remaining 5%.
Page 121 SECONDARY AIR SYSTEM P2.5 P2.5 ENGINE INDICATING 6.3 PT6A-60 SERIES TRAINING USE ONLY P&WC Proprietary - Disclosure and use subject to the restrictions on page 2 of preface...
Page 122: Accessory Gearbox Breather
ACCESSORY GEARBOX BREATHER Function: The relatively oil free breather air flows through the center of the impeller and out to the atmosphere via a cored pas- Separates oil particles from air in the accessory gearbox sage in the accessory gearbox diaphragm. before discharging overboard.
Page 123 ACCESSORY GEARBOX BREATHER STARTER / GENERATOR GEAR CARRIER CARBON SEAL BREATHER IMPELLER CARBON SEAL BREATHER IMPELLER CARRIER CARBON SEAL AIR / OIL MIX ENGINE INDICATING 6.5 PT6A-60 SERIES TRAINING USE ONLY P&WC Proprietary - Disclosure and use subject to the restrictions on page 2 of preface...
Page 124: Oil Tank Pressurizing Valve
OIL TANK PRESSURIZING VALVE Function: The oil tank pressurizing valve maintains air pressure in the tank 5 to 7 psi above the accessory gearbox pressure. This Reduces oil pressure fluctuation and oil consumption at positive pressure applied on the oil reduces pressure fluctu- high altitude.
Page 125 OIL TANK PRESSURIZING VALVE PRESSURIZING VALVE HOUSING SEAT INLET CASE AGB DIAPHRAGM PISTON AIR / OIL MIX ENGINE INDICATING 6.7 PT6A-60 SERIES TRAINING USE ONLY P&WC Proprietary - Disclosure and use subject to the restrictions on page 2 of preface...
Page 126: Turbine Cooling And Airbleed System
TURBINE COOLING AND AIRBLEED SYSTEM Description: Internal passages in the engine distribute P3 air to provide cooling to the combustion chamber turbine and vane rings. After cooling, the air is evacuated in the gas path. Using the same distribution passages, P2.5 and P3 air are provided to the no.
Page 127 TURBINE COOLING AND AIRBLEED SYSTEM P2.5 ENGINE INDICATING 6.9 PT6A-60 SERIES TRAINING USE ONLY P&WC Proprietary - Disclosure and use subject to the restrictions on page 2 of preface...
Page 128: Bearing Compartment Sealing
BEARING COMPARTMENT SEALING Function: Possible Cause For Oil Loss Through Labyrinth Seals: - Lack of air flow through labyrinth seal (Not probable) Prevents oil from leaking outside the bearing cavities. - Wear on the knife's edges due to rotor unbalance or bearing distress Description: - Oil coking in the grooves between the knife's edges...
Page 129 BEARING COMPARTMENT SEALING P2.5 NO.3 BEARING NO.2 BEARING NO.1 BEARING ENGINE INDICATING 6.11 PT6A-60 SERIES TRAINING USE ONLY P&WC Proprietary - Disclosure and use subject to the restrictions on page 2 of preface...
Page 130 NOTES ENGINE INDICATING 6.12 PT6A-60 SERIES TRAINING USE ONLY P&WC Proprietary - Disclosure and use subject to the restrictions on page 2 of preface...
Page 131: Chapter 7 - Engine Indicating System
ENGINE INDICATING SYSTEM ENGINE INDICATING SYSTEM ENGINE INDICATING SYSTEM 7.1 PT6A-60 SERIES TRAINING USE ONLY P&WC Proprietary - Disclosure and use subject to the restrictions on page 2 of preface...
Page 132 ENGINE INDICATING SYSTEM Function: - Provide the pilot with indications concerning the engine parameters during flight - Provide the required data for engine condition trend monitoring and performance Engine Indicating Systems: - Ng / Np Tachometer-Generators (Pulse pick-up probes on the PC12) - Oil temp/ Oil pressure indication - Chip detector Indicating Systems Built Into Engines:...
Page 133 ENGINE INDICATING SYSTEM COMPRESSOR SPEED OIL TEMPERATURE (C˚) TORQUE PROPELLER SPEED NG (%) AND PRESSURE (PSIG) (C˚) (FT-LBS) Np (RPM) START PROP RPM TORQUE 6 5 4 FTLB ˚c x 100 X 100 x100 X 100 x 10 20 15 Np TACHO GENERATOR Ng TACHO...
Page 134: Inter-Turbine Temperature (T5)
INTER-TURBINE TEMPERATURE (T5) Function: Provides an indication of the Inter-Turbine Temperature (ITT), between the compressor turbine and the first stage power turbine vane ring (station 5). Description: - 10 individual thermocouples (chromel-alumel) - 1 positive bus bar (chromel-small terminal) - 1 negative bus bar (alumel-large terminal) - 1 trim probe - 1 T5 wiring harness Note:...
Page 135: Temperature Indicating System (T5)
TEMPERATURE INDICATING SYSTEM (T5) WIRING HARNESS THERMOCOUPLE TRIM PROBE PRE-SB 13038 (A-60/61/65) TERMINAL BLOCK BUS-BAR ALUMEL LEAD CHROMEL LEAD INDIVIDUAL THERMOCOUPLE JUNCTION THERMOCOUPLE ENGINE INDICATING SYSTEM 7.5 PT6A-60 SERIES TRAINING USE ONLY P&WC Proprietary - Disclosure and use subject to the restrictions on page 2 of preface...
Page 136: Temperature Indicating System (Itt)
TEMPERATURE INDICATING SYSTEM (ITT) Operation: Maintenance: - Check system loop resistance (continuity) As temperature increases, an increasing voltage is gener- - Check resistance of individual probe ated at the chromel/alumel junction of each thermocouple. - Check insulation resistance (harness, probe and trim probe) Uneven heat distribution within the gas path causes individ- - Check probes for heat response...
Page 137: T5 System Schematic
T5 SYSTEM SCHEMATIC ALUMEL CHROMEL VARIABLE SEALED RESISTANCE BUS BARS & (PRE SB 13338 & THERMOCOUPLES SB 14299) TRIM PROBE ENGINE INDICATING SYSTEM 7.7 PT6A-60 SERIES TRAINING USE ONLY P&WC Proprietary - Disclosure and use subject to the restrictions on page 2 of preface...
Page 138: Torque System
TORQUE SYSTEM Function: Maintenance: Provide an accurate indication of the torque applied to the Check/calibrate the airframe torque transducer and gage propeller. (ref. to airframe maintenance manual). Description: Troubleshooting: - Hydro-mechanical system - Floating first stage ring gear with helical splines Problem Area Symptom - Piston...
Page 139 TORQUE SYSTEM ELECTRIC TORQUE PRESSURE TORQUE TRANSDUCER SIGNAL (AIRFRAME) FIRST STAGE PLANET GEAR REDUCTION GEARBOX TORQUE STATIC PRESSURE METER 1ST STAGE OIL BLEED RING GEAR RING GEAR ORIFICE MOVEMENT TORQUE OIL PRESSURE CONTROL VALVE ENGINE OIL PRESSURE TORQUE PISTON CYLINDER METERING ORIFICE LOW POWER HIGH POWER...
Page 140: Chip Detector
CHIP DETECTOR Function: Maintenance: - Inspect chip detector at interval specified by aircraft Provides an indication of metal particle contamination of the maintenance manual engine oil system. - Functionally test chip detector - 100hrs -> Check Continuity - 600hrs/12Mo. -> Function Check Description: - Two magnetic poles...
Page 141 CHIP DETECTOR VALVE VALVE HOUSING VALVE CLOSED MAGNETIC POLES VALVE OPEN SELF CLOSING CHIP DETECTOR (A-52, A60, A61, A65 & LOCKWIRE CERTAIN A67 MODELS ONLY) SECURING LUG PREFORMED PACKING NON SELF CLOSING CHIP DETECTOR INSULATION (A64, A66 & CERTAIN A67 MODELS) MAGNETIC CHIP DETECTOR...
Page 142 NOTES ENGINE INDICATING SYSTEM 7.12 PT6A-60 SERIES TRAINING USE ONLY P&WC Proprietary - Disclosure and use subject to the restrictions on page 2 of preface...
Page 143: Chapter 8 - Ignition System
IGNITION SYSTEM IGNITION SYSTEM IGNITION SYSTEM 8.1 PT6A-60 SERIES TRAINING USE ONLY P&WC Proprietary - Disclosure and use subject to the restrictions on page 2 of preface...
Page 144 IGNITION SYSTEM Function: Exciter Box Specifications: Input voltage............ 9-30 VDC Provide the spark to ignite the fuel/air mixture. Input current ............ 3.5 amp Operating Altitude ........... 0-50000 feet Description: Spark rate 10 VDC ........1 spark/sec - Airframe mounted ignition exciter 30 VDC ..........
Page 145: Ignition System
IGNITION SYSTEM IGNITERS POWER TURBINE COMBUSTION CHAMBER STATOR HOUSING LINER GASKET SPARK IGNITER IGNITION CABLES 0.300 IN. MAX. IGNITION EXCITER 0.015 IN. ACCEPTABLE WORN OUT IGNITER WEAR IGNITION SYSTEM 8.3 PT6A-60 SERIES TRAINING USE ONLY P&WC Proprietary - Disclosure and use subject to the restrictions on page 2 of preface...
Page 146 NOTES IGNITION SYSTEM 8.4 PT6A-60 SERIES TRAINING USE ONLY P&WC Proprietary - Disclosure and use subject to the restrictions on page 2 of preface...
Page 147: Chapter 9 - Performance
PERFORMANCE PERFORMANCE PERFORMANCE 9.1 PT6A-60 SERIES TRAINING USE ONLY P&WC Proprietary - Disclosure and use subject to the restrictions on page 2 of preface...
Page 148 PERFORMANCE CHECK Function: Permits verification of engine condition over a wide range of - From appropriate curves (Airframe M/M), determine: ambient temperatures without exceeding torque or T5 lim- Target Torque. its. Fuel Flow Performance Check Should Be Performed: - Determine parameter limits using tolerance from the - After engine installation.
Page 149: Engine Performance Check (Typical)9.3
ENGINE PERFORMANCE CHECK (TYPICAL) PERFORMANCE 9.3 PT6A-60 SERIES TRAINING USE ONLY P&WC Proprietary - Disclosure and use subject to the restrictions on page 2 of preface...
Page 150: Performance Check (Shorts Install)9.4-9.6
PERFORMANCE CHECK (SHORTS INSTALL) General: Static Maximum Take Off Power Check: Shorts installations use two types of performance checks. A Static MTOP check is required upon replacement of an 1. Static Reduced Power Check.(Static RTOP) engine after the Static Reduced Torque Check has been 2.
Page 151 PERFORMANCE CHECK (SHORTS INSTALL) PERFORMANCE 9.5 PT6A-60 SERIES TRAINING USE ONLY P&WC Proprietary - Disclosure and use subject to the restrictions on page 2 of preface...
Page 152 PERFORMANCE CHECK (SHORTS INSTALL) PERFORMANCE 9.6 PT6A-60 SERIES TRAINING USE ONLY P&WC Proprietary - Disclosure and use subject to the restrictions on page 2 of preface...
Page 153 ENGINE CONDITION TREND MONITORING (WEBECTM) Function: Data Acquisition: - Maintenance tool The accuracy of the WebECTM process depends on the - Allows user to monitor the engine performance quality of the data entered into a computer system. Cruise - Permits early detection of engine deterioration condition is the only flight configuration where engine reac- - Helps determine trouble area tion can be predicted.
Page 154: Webectm
WEBECTM (CON’T) Plotting: Guidelines for interpretation of trend: Following computation, DELTA Ng, DELTA ITT, and DELTA Wf should be plotted on a continuous sheet. Flight log Net change of 10 to 15°C ITT: number may be used as the abscissa, although the trend Early sign of deterioration, that should be investigated when could also be recorded as a function of date or, preferably, convenient.
Page 155: Ectm Sample Plot
ECTM SAMPLE PLOT COMPRESSOR WASH TIME PERIOD PERFORMANCE 9.9 PT6A-60 SERIES TRAINING USE ONLY P&WC Proprietary - Disclosure and use subject to the restrictions on page 2 of preface...
Page 156: Tbo & Hsi Interval
TBO AND HSI INTERVAL • SB 13003 for PT6A-65 • SB 13303 for PT6A-52/60/61 Engine H.S.I. • SB 13203 for PT6A-60AG, A-65AG • SB 14003 for PT6A-67R, 67D PT6A-52/60/61 3600 1800 • SB 14303 for PT6A-67AF, F PT6A-65 6000 1200 /2000 •...
Page 157: Operating Limits
OPERATING LIMITS* Description: Operating limits define the upper and lower boundaries for all engine parameters observed in the cockpit during nor- mal operation for each specific engine model. Excursion beyond these limits may accelerate engine wear and possibly lead to component malfunction. For current operating limits, refer to applicable aircraft pilot operating handbook.
Page 158 OPERATING LIMITS PT6A-52 Power Setting Torque Max ITT Oil Pressure Oil Temp. lb-ft psig °C °C Take-off/Max Cont 2230 72.95 39000 2000 90 to 135 0 to 110 Max Climb 2230 72.95 39000 2000 90 to 135 0 to 110 Max.
Page 159 OPERATING LIMITS PT6A-61 Power Setting Torque Max ITT Oil Pressure Oil Temp. lb-ft psig °C °C Take-off/Max Cont. 2230 72.95 39000 2000 90 - 135 0 – 110 Max. Cruise 2230 72.95 39000 2000 90 - 135 10 – 104 Normal Cruise 2230 72.95...
Page 160 OPERATING LIMITS PT6A-65B Power Setting Torque Max ITT Oil Pressure Oil Temp. @ OAT lb-ft °C °C Take-off 1100 3625 43.34 39,000 1700 90 to 135 0 to 110 Maximum Continuous 1100 3625 43.34 39,000 1700 90 to 135 0 to 110 Maximum Climb 1000 3625...
Page 161 OPERATING LIMITS PT6A-65AG Power Setting Torque Max ITT Oil Pressure Oil Temp. lb-ft °C °C Take-off 1300 4017 48.03 39,000 1700/100% 90 to 135 0 to 110 Maximum Continuous 1220 3825 45.74 39,000 1700 90 to 135 0 to 110 Maximum Cruise/ 3625 43.34...
Page 162 OPERATING LIMITS PT6A-67A Power Setting Torque Max ITT Oil Pressure Oil Temp. lb-ft °C °C Take-off 1200 3708 44.34 39,000 1700/100% 90 to 135 10 to 110 Max Cont 1200 3708 44.34 39,000 1700 90 to 135 10 to 110 Max.
Page 163 OPERATING LIMITS PT6A-67B Power Setting Torque Max ITT Oil Pressure Oil Temp. lb-ft psig °C psig °C Take-off 1200 3708 44.34 39000 1700/100% 90 to 135 10 to 110 Maximum Continuous 1200 3708 44.34 39000 1700 90 to 135 10 to 110 Maximum Cruise/ 1000 3090...
Page 164 OPERATING LIMITS PT6A-67P Power Setting Torque Max ITT Oil Pressure Oil Temp. lb-ft psig °C psig °C Take-off 1200 3708 44.34 39000 1700/100% 90 to 135 10 to 110 Maximum Continuous 1200 3708 44.34 39000 1700/100% 90 to 135 10 to 105 Maximum Climb/ 1200 3708...
Page 165: Rotor Components - Service Life
ROTOR COMPONENTS - SERVICE LIFE Description: Flight Count Factor: Certain rotating components are subject to low-cycle This is an index of severity. An indication of how much a fatigue due to cyclic operation of the engine. Additionally, component is affected during the engine operation. This is other factors such as high frequency fatigue and metallurgi- a multiplier and will change for a given component if cal changes related to time rather than flight cycles are con-...
Page 166: Overtorque Chart (Typical)
OVERTORQUE CHART (TYPICAL) 3000 OUTPUT TORQUEMETER TORQUE PRESSURE (FT-LBS) (PSI) RECORD IN LOG BOOK NO ACTION REQUIRED TIME (MINUTES) PERFORMANCE 9.20 PT6A-60 SERIES TRAINING USE ONLY P&WC Proprietary - Disclosure and use subject to the restrictions on page 2 of preface...
Page 167: Overtemperature Chart (Typical)
OVERTEMPERATURE CHART (TYPICAL) 2000 INTER TURBINE TEMPERATURE ( C° ) NO ACTION REQUIRED * ITT RED LINE TIME (SECONDS) A = DETERMINE & CORRECT CAUSE OF OVERTEMPERATURE - START OVERTEMP, INSPECT P.T. BLADES THROUGH EXHAUST - RECORD IN LOG BOOK B = PERFORM HOT SECTION INSPECTION C = SHIP ENGINE TO AN OVERHAUL FACILITY * ITT RED LINE = MAXIMUM TAKE OFF ITT...
Page 168: Engine Troubleshooting
ENGINE TROUBLESHOOTING Effective engine troubleshooting infers monitoring engine Troubleshooting of problems related to internal engine com- parameters on a regular basis, using performance check ponents is generally divided in 2 areas: and engine condition trend monitoring. - Compressor section - Hot section. Effective troubleshooting can be divided into four steps: The compressor section refers to all the components of the 1.
Page 169: Performance Troubleshooting
PERFORMANCE TROUBLESHOOTING Introduction: Systematic Approach: - The following information is a guide only. - Preferred approach - Refer to the appropriate aircraft or engine mainte- - Gathering of all applicable information nance manual as necessary. - Analysis of engine symptoms - Determination of most probable cause - Corrective actions Troubleshooting:...
Page 170 PERFORMANCE TROUBLESHOOTING (CONT’D) The Basics: tance limits on compressor FOD. The extended limits are - Understand the problem approximately double the previous ones but are acceptable - Simultaneous review of ECTM* and recent past history providing that engine performance remains acceptable. - Pilot reports, and maintenance logs Therefore, if the FOD is towards the high side of the A review of the ECTM plots for the past three to six months...
Page 171 PERFORMANCE TROUBLESHOOTING (CONT’D) Instrument Calibration: From the previous example, the importance of instrument - How long since last calibration. calibration can not be overemphasized. - Accurate calibrations are worth the effort. - OAT, PA, and IAS are used in normalization process and thereby affect ECTM accuracy .
Page 172 PERFORMANCE TROUBLESHOOTING (CONT’D) Eliminate Cabin Bleed Leaks (Cont'd): Trim Determination: - Trim on/off runs to determine if trim compensation is Compare the results of the two runs. If the parameters of correct. the run with the bleeds blanked appear lower, you have a - Not a "dial as required system"...
Page 173 PERFORMANCE TROUBLESHOOTING (CONT’D) Borescope Inspection: Engines are assembled; performance tested and trimmed - Borescope engine to confirm hot section distress. with a particular set of CT and first stage PT vane classes. - Does what you see with the borescope agree with the It is important to know what these classes were as a refer- ECTM plots.
Page 174 NOTES PERFORMANCE 9.28 PT6A-60 SERIES TRAINING USE ONLY P&WC Proprietary - Disclosure and use subject to the restrictions on page 2 of preface...
Page 175: Chapter 10 - Fuel System
FUEL SYSTEM FUEL SYSTEM FUEL SYSTEM 10.1 PT6A-60 SERIES TRAINING USE ONLY P&WC Proprietary - Disclosure and use subject to the restrictions on page 2 of preface...
Page 176: Power Management
POWER MANAGEMENT - 3 lever control system Propeller Lever: - 2 levers on PT6A-66 and A-67B/P - Connected to the propeller speed control lever on the top of the propeller governor (CSU). Power Lever: - Controls the propeller speed in the governing mode. - Controls the compressor speed in forward as well as - Allows feathering of the propeller.
Page 177 POWER MANAGEMENT MIN. POWER TAXI POWER RANGE RANGE REVERSE MIN. RPM MAX. POWER BETA MAX. RPM FEATHER POWER PROPELLER LEVER LEVER CAM ASSY PROPELLER GOVERNOR LOW IDLE SHUT-OFF HIGH IDLE FUEL CONDITION LEVER FUEL SYSTEM 10.3 PT6A-60 SERIES TRAINING USE ONLY P&WC Proprietary - Disclosure and use subject to the restrictions on page 2 of preface...
Page 178: Fuel System
FUEL SYSTEM Function: Alternate/Emergency Fuels: Provides the engine with clean fuel at the required pressure Minimize use of AVGAS. AVGAS may contribute to acceler- and flow to permit control of engine power. ate hot section deteriorations. Run AVGAS a maximum of 150 hrs between overhauls.
Page 179 FUEL SYSTEM CONDITION LEVER BYPASS POWER PORT LEVER Py AIR TO CSU FUEL MANIFOLD ADAPTER FUEL OUT FUEL PUMP DRAIN VALVES P3 IN FUEL IN FUEL CONTROL UNIT FUEL CONTROL UNIT(FCU) FLOW DIVIDER VIEW A FUEL DELIVERY TUBE P3 AIR FUEL HEATER TO FCU FUEL FROM...
Page 180 FUEL SYSTEM Description: Fuel from the aircraft tank is sent to the fuel heater via one or more airframe boost pumps. From the fuel heater, fuel is directed to the fuel pump. The fuel pump sends the fuel to the fuel control unit (FCU) which determines the quantity of fuel required by the engine to produce the power requested through the power lever and according to the ambient con- ditions.
Page 181: Fuel System Schematic
FUEL SYSTEM SCHEMATIC FUEL HEATER FUEL CONTROL UNIT FUEL PUMP UNIT FUEL METERING INPUTS INLET FILTER OIL OUT OIL IN PUMP (SELF RELIEVING) OUTLET FILTER BYPASS FUEL LEVER BYPASS PRESSURE P3 AIR REGULATING VALVE FUEL TANK FLOW METER FUEL DISTRIBUTION (AIR FRAME) BOOST PUMP PRIMARY...
Page 182: Fuel Heater
FUEL HEATER Function: Maintenance: - Heat the fuel to prevent ice crystal formation - Replace unit if defective. - Heat the FCU housing to prevent condensation from - Repair the coating on fuel heater as per engine Main- freezing in the bellows assembly tenance Manual.
Page 183 FUEL HEATER FUEL OUTLET INLET SLIDE VALVE PUSH ROD RETURN SPRING THERMAL ELEMENT FUEL OUT OUTLET OIL IN OIL OUT FUEL INLET FUEL IN FUEL PASSAGE OIL PASSAGE FUEL SYSTEM 10.9 PT6A-60 SERIES TRAINING USE ONLY P&WC Proprietary - Disclosure and use subject to the restrictions on page 2 of preface...
Page 184: Fuel Pump
FUEL PUMP Function: Outlet Filter Bypass Valve: - Bypass fuel if filter gets restricted Provide clean fuel under pressure to the fuel control unit. - Set to open at 15-25 psid Description: - Single stage Bypass Pressure Regulating Valve: - Gear type pump - Maintains bypass pressure above a minimum to mini- - Brass bushings loaded against pump gears mize fuel leakage at the brass bushing...
Page 185 FUEL PUMP HIGH PRESSURE FUEL TO FCU OUTLET FILTER BYPASS FILTER VALVE CARBON SEAL CARBON SEAL BRASS BUSHINGS COUPLING TO FCU BYPASS ACCESSORY RETURN GEARBOX FUEL INLET PRESSURE INLET FILTER BYPASS FUEL (SELF RELIEVING) PUMP DELIVERY PRESSURE BYPASS PRESSURE REGULATING VALVE LOW PRESSURE FUEL FROM FUEL HEATER FUEL SYSTEM 10.11...
Page 186: Fuel Control Unit (Main Flow)
FUEL CONTROL UNIT (MAIN FLOW) Function: Minimum Flow: - Provides minimum fuel to start engine and prevents Deliver the required amount of fuel at the required pressure flame out during rapid deceleration - Factory set at ≈90 pph to the fuel nozzles. Pressure Relief Valve: Pump Unloading Valve: - Prevents system over pressurization...
Page 187 FUEL CONTROL UNIT (MAIN FLOW) HIGH TO FUEL PRESSURE PUMP RELIEF VALVE BYPASS PUMP UNLOADING VALVE P1 PUMP DELIVERY PRESSURE P2 METERED FUEL PRESSURE P0 BYPASS FUEL PRESSURE MINIMUM FLOW Py MODIFIED Px FROM FUEL PUMP BYPASS VALVE TO FUEL DISTRIBUTION SYSTEM FUEL...
Page 188 FUEL CONTROL UNIT (METERING) Function: Fuel Valve And Bellows Section: Determines fuel flow to the engine in response to the follow- The Fuel Valve rotates and moves up and down to deter- ing inputs: mine the amount of fuel going to the engine by varying the - Power Lever Position (PLA) opening between the inner rotating valve and the static - Compressor discharge pressure (P3)
Page 189: Fuel Metering Section
FUEL METERING SECTION P1 FROM PUMP POWER LEVER FUEL VALVE FOLLOWER FUEL VALVE BLEED TO Po COMPRESSOR 3D CAM FOLLOWERS SPEED METERED FUEL OUTLET P1 PUMP DELIVERY SYSTEM P2 METERED FUEL PRESSURE DRAIN Pt FUEL SERVO PRESSURE FLYWEIGHT COMPRESSOR Po BYPASS FUEL GOVERNOR PRESSURE Py GOVERNING AIR PRESSURE...
Page 190: Metering Section (3D Cam)
METERING SECTION (3D CAM) INCREASE NG 3D CAM FOLLOWER POWER LEVER FUEL VALVE FOLLOWER FOLLOWER SPRING DECREASE NG 3D CAM FLY WEIGHT PT BLEED FUEL VALVE TO Po A- DECEL NG GOVERNOR B- STEADY STATE C- ACCEL D- INTERMEDIARY P3 SENSOR BELLOWS FUEL SYSTEM 10.16 PT6A-60 SERIES...
Page 191: Fuel Control System
FUEL CONTROL SYSTEM FUEL CONTROL UNIT (FCU) FUEL PUMP FUEL METERING MAIN FLOW FUEL INLET (FROM FUEL FUEL CONDITION HEATER) LEVER AND PUMP HIGH HIGH IDLE UNLOADING VALVE PRESSURE RELIEF VALVE PUMP FUEL VALVE POWER FOLLOWER LEVER MINIMUM FLOW BYPASS 3D CAM FUEL VALVE...
Page 192: Compressor Delivery Air Lines
COMPRESSOR DELEVERY AIR LINES Function: To provide clean P3 air to the FCU. Description: Compressor discharge air (P3), derived from the diffuser section of the gas generator case, is routed to the metering section of the FCU through external lines and a fine-screen filter.
Page 193: P3 Air Filter Element
P3 AIR FILTER ELEMENT P3 AIR FILTER ELEMENT (POST−SB 13175 (PRE−SB 13175 & POST-SB 14054) & PRE-SB 14054) FUEL SYSTEM 10.19 PT6A-60 SERIES TRAINING USE ONLY P&WC Proprietary - Disclosure and use subject to the restrictions on page 2 of preface...
Page 194: Flow Divider With Dump Valve
FLOW DIVIDER WITH DUMP VALVE Function: Operation: Provides a means to separate the starting flow (primary) When the condition lever is moved to the "fuel on" position, from the normal engine running flow (Pri & Sec). Allows the fuel enters the flow divider and pushes against the primary fuel flow to be ported to a collector can during the shutdown and secondary valve and spring.
Page 195 FLOW DIVIDER AND DUMP VALVE FLOW DIVIDER AND DUMP VA LVE FUEL NOZZLE COMBUSTION CHAMBER OUTER LINER ASSEMBLY FUEL NOZZLE SHEATH SECONDARY PRIMARY MANIFOLD PORT MANIFOLD PORT PRIMARY GAS GENERATOR CASE FUEL MANIFOLD SECONDARY FUEL DUMP FUEL MANIFOLD (To collector can) INLET ADAPTER FUEL FLOW DIVIDER P2 FUEL IN...
Page 196: Flow Divider With Purge Valve
FLOW DIVIDER WITH PURGE VALVE (SB 13074, 14065) Operation: Function: When the fuel lever is moved to the "fuel on" position, fuel enters the flow divider and pushes against the primary and Provides a means to separate the starting flow (primary) secondary valves.
Page 197 FLOW DIVIDER AND PURGE VALVE FUEL NOZZLE COMBUSTION CHAMBER OUTER LINER ASSEMBLY FUEL NOZZLE SHEATH PRIMARY SECONDARY MANIFOLD PORT MANIFOLD PORT PRIMARY GAS GENERATOR CASE FUEL MANIFOLD P3 AIR SECONDARY P2 FUEL IN FUEL MANIFOLD INLET ADAPTER FUEL FLOW DIVIDER PRIMARY FLOW POSITION SECONDARY VALVE CHECK VALVE...
Page 198 SIMPLEX FUEL NOZZLES (A52/60/61, A64, A65) Function: Maintenance: - Clean or replace nozzles every 400 hours Deliver and atomize metered fuel into the combustion - New operator clean every 200 hours chamber. - Alternate cleaning method, in situ cleaning every 200 hours to extend intervals between removals - Leak test if nozzles tips are removed Construction:...
Page 199: Simplex Fuel Nozzles
SIMPLEX FUEL NOZZLES PRIMARY FUEL MANIFOLD ADAPTER FUEL MANIFOLD ADAPTER WORKING WORKING TRANSFER TUBE PRESSURE PRESSURE (SECONDARY) 9 PSI 17 PSID FUEL MANIFOLD ADAPTER TRANSFER TUBE TRANSFER TUBE (PRIMARY) (SECONDARY) FUEL NOZLE SHEATH PRIMARY FUEL MANIFOLD SECONDARY FUEL MANIFOD TRANSFER TUBE (PRIMARY) FUEL SYSTEM 10.25 PT6A-60 SERIES...
Page 200 DUPLEX FUEL NOZZLES (A67B/D/F/P AND POST SB FOR OTHERS) Function: Maintenance: - Clean or replace nozzles every 400 hours. Deliver and atomize metered fuel into the combustion - New operator should clean every 200 hours. chamber. - Alternate cleaning method, in situ cleaning every 200 hours to extend intervals between removals.
Page 201: Duplex Fuel Nozzles
DUPLEX FUEL NOZZLES FUEL MANIFOLD ADAPTER WORKING TRANSFER TUBE PRESSURE (SECONDARY) 9 PSI + FUEL MANIFOLD ADAPTER TRANSFER TUBE (PRIMARY) TRANSFER TUBE FUEL NOZLE (SECONDARY) SHEATH PRIMARY FUEL MANIFOLD SECONDARY FUEL MANIFOD TRANSFER TUBE (PRIMARY) FUEL SYSTEM 10.27 PT6A-60 SERIES TRAINING USE ONLY P&WC Proprietary - Disclosure and use subject to the restrictions on page 2 of preface...
Page 202: Fuel Control Unit Manual Override .10.28
FUEL CONTROL UNIT MANUAL OVERRIDE Function: The P1 to Pz pressure differential will move the fuel valve down to increase fuel flow. Allows the pilot to manually control the FCU fuel valve in the event of a pneumatic (P3, Py) system malfunction. A return spring below the P2 valve ensures the valve fol- lows the bellows movement during normal operation.
Page 203: Fcu Manual Override
FCU MANUAL OVERRIDE MANUAL OVERRIDE LEVER RATE PISTON MANUAL OVERIDE ORIFICE P3 AIR SPRING P1 PUMP DELIVERY SYSTEM P2 METERED FUEL PRESSURE Pz FUEL INTERMEDIATE PRESSURE Po BYPASS FUEL Py GOVERNING AIR PRESSURE P3 COMPRESSOR DISCHARGE PRESSURE FUEL SYSTEM 10.29 PT6A-60 SERIES TRAINING USE ONLY P&WC Proprietary - Disclosure and use subject to the restrictions on page 2 of preface...
Page 204 POWER RECOVERY SYSTEM (PT6-A65R/AR AND 67R ONLY) Function: On twin engine aircraft’s, provides manual or automatic power increase on one engine in the event of a severe power loss from the opposite engine. Description: A solenoid valve activated by a low torque reading on the failed engine allows P3 air to push on a piston located at the back of the FCU.
Page 205: Power Recovery System
POWER RECOVERY SYSTEM P1 FROM PUMP FOLLOWER FUEL VALVE FOLLOWER POWER LEVER 3D CAM P2 TO FUEL NOZZLES FUEL VALVE VALVE SEAT BLEED TO ATMOSPHERE SOLENOID VALVE NG GOVERNOR Py TO (AIRFRAME) PROPELLER GOVERNOR DRAIN P3 FILTER P1 PUMP DELIVERY SYSTEM P2 METERED FUEL PRESSURE P3 SENSOR BELLOWS...
Page 206: Overtorque Limiter
OVERTORQUE LIMITER Function: A solenoid (deleted by SB 14185) valve is used on the A- 67B and A-67AF to disable the torque limiter when not A back-up unit which prevents engine overtorques. The pilot required. The solenoid valve closes when de-powered. It is always responsible for operating the engine within limits.
Page 207 OVERTORQUE LIMITER (A-64, 66A/B/D, 67AF, 67B/R/T) ADJUSTMENT SCREW FLAPPER Py AIR Py AIR VALVE FROM FCU FROM FCU ADJUSTMENT SCREW BELLOWS BIMETALLIC TORQUEMETER TORQUEMETER DISKS OIL PRESSURE OIL PRESSURE RESTRICTOR OVERTORQUE NORMAL POSITION POSITION FUEL SYSTEM 10.33 PT6A-60 SERIES TRAINING USE ONLY P&WC Proprietary - Disclosure and use subject to the restrictions on page 2 of preface...
Page 208: Fuel Control Unit Adjustment
FUEL CONTROL UNIT ADJUSTMENT Deadband - Adjust deadband first, by deadband adjustment screw. - Clockwise increases the deadband angle. - Always verify low idle after a deadband adjustment. Low Idle - Always adjust before high idle setting - Loosen FCU lever clamping screw - To increase Ng, loosen top screw, tighten lower one - To decrease Ng, loosen lower screw, tighten top screw - When adjusting Ng, turn screw in increments of 1/6 of a turn at a time...
Page 209 TYPICAL FUEL CONTROL UNIT ADJUSTMENTS FUEL CONDITION LEVER DEADBAND ADJUSTMENT IF THERE IS MAX Ng (FORWARD) STAGGER HIGH IDLE STOP FCU LEVER POWER LEVER CAM FOLLOWER ADJ. MAX Ng REV (HIGH IDLE) IF NO STAGGER HIGH IDLE CAM RESERVE POWER STOP SPEED RESET SERVO...
Page 210: Troubleshooting Summary
FUEL SYSTEM TROUBLESHOOTING SUMMARY Observed Problem Verification Engine Does Not Start / Hot - Ensure that minimum cranking speed is achievable Starts - Verify igniters for proper operation - Check for evidence of fuel flow to the flow divider while motoring the engine - Ensure primary and secondary fuel nozzles are in their respective position (N/A for engines equipped with duplex nozzles) - Replace flow divider...
Page 211: Chapter 11- Propeller System
PROPELLER SYSTEM PROPELLER SYSTEM PROPELLER SYSTEM 11.1 PT6A-60 SERIES TRAINING USE ONLY P&WC Proprietary - Disclosure and use subject to the restrictions on page 2 of preface...
Page 212 PROPELLER SYSTEM Function: Change the power produced by the engine into thrust in order to propel the aircraft through the air. Description: - Three to six bladed propellers - Made of Aluminium or Composite materials - Variable pitch, single acting type - Propeller governor (CSU) controls: Propeller Speed in governing mode.
Page 213 PROPELLER SYSTEM PROPELLER BLADE PROPELLER PITCH CHANGE GOVERNOR MECHANISM SPINNER PROPELLER SYSTEM 11.3 PT6A-60 SERIES TRAINING USE ONLY P&WC Proprietary - Disclosure and use subject to the restrictions on page 2 of preface...
Page 214: Pitch Change Mechanism
PITCH CHANGE MECHANISM Function: When oil pressure is decreased, the return spring and counter weights force the oil out of the servo piston and Allow varying the propeller blade angle in order to maintain change the blade pitch to a coarser position. a constant Np through various ambient conditions and power settings.
Page 215 PITCH CHANGE MECHANISM PROPELLER PROPELLER GOVERNOR (CSU) MOVES FORWARD FROM PBA TO REV SPIDER HUB SERVO PISTON (DOME) OIL TRANSFER SLEEVE FEATHERING SPRING BLADE ACTUATING LEVER PROPELLER SYSTEM 11.5 PT6A-60 SERIES TRAINING USE ONLY P&WC Proprietary - Disclosure and use subject to the restrictions on page 2 of preface...
Page 216: Propeller Governor Governing Mode
PROPELLER GOVERNOR GOVERNING MODE Description: Speeder Spring: - Opposes a mechanical force to the centrifugal force of Is the range of operation where engine power is sufficient to the flyweights maintain the selected propeller speed by varying the blade - Determines the propeller speed at which the flyweights angle (pitch).
Page 217 GOVERNING MODE NO MOVEMENT PROPELLER SPEED BETA CONTROL LEVER RESET POST VALVE GOVERNOR LEVER PRESSURE SPRING RELIEF SHUT-OFF VALVE (LOCK PITCH) SOLENOID VALVE RESET PT6A-67B/P NO MOVEMENT WITH FIXED PROPELLER SPEED MIN. GOV. ADJ. BETA VALVE PILOT VALVE CARBON ENGINE NO MOVEMENT CSU PUMP BLOCK...
Page 218: Propeller Governor
PROPELLER GOVERNOR BETA MODE (FORWARD OPERATION) Power Lever: Description: On the ground, movement of the power lever below the idle gate causes the reversing cam to actuate the beta valve, The beta mode corresponds to a range of operation where thus causing the blade angle to reduce the blade angle is between PBA (Primary Blade Angle) and reverse.
Page 219 BETA MODE (FORWARD OPERATION) NO MOVEMENT PROPELLER SPEED BETA CONTROL LEVER RESET POST VALVE GOVERNOR LEVER SPRING SHUT-OFF (LOCK PITCH) SOLENOID VALVE RESET MOVES IN RESPONSE TO BETA FEEDBACK RING MIN. GOV. ADJ. BETA VALVE PILOT VALVE CARBON ENGINE CSU PUMP BLOCK SUPPLY PRESSURE RETURN TO PUMP...
Page 220 PROPELLER GOVERNOR (CONT’D) Lockpitch Solenoid Valve: Prevents the propeller from going into reverse or below the primary blade angle in the event of a Beta system malfunc- tion in flight. The solenoid is energized by a switch (air- frame supplied) mechanically connected to the propeller slip-ring linkage via a second carbon block.
Page 221 BLANK PAGE PROPELLER SYSTEM 11.11 PT6A-60 SERIES TRAINING USE ONLY P&WC Proprietary - Disclosure and use subject to the restrictions on page 2 of preface...
Page 222: Propeller Governor
PROPELLER GOVERNOR BETA MODE (REVERSE OPERATION) As Np increases due to the increase in engine power, the governor flyweights begin to move outwards. Since the Function: reset lever is closer to the speeder spring cup, the cup con- tacts the reset lever before the flyweights would normally Allows the pilot to control the propeller with a negative blade reach the on-speed position (95% Np instead of 100%).
Page 223 BETA MODE (REVERSE OPERATION) REVERSING CAM PUSH-PULL CONTROL REARWARD MOVEMENT PROPELLER SPEED BETA VALVE LEVER CONTROL LEVER RESET POST GOVERNOR SPRING SHUT-OFF (LOCK PITCH) SOLENOID VALVE RESET REARWARD MOVEMENT UNDERSPEED BETA ECCENTRIC VALVE SCREW PILOT VALVE CARBON CSU PUMP BLOCK ENGINE SUPPLY PRESSURE RETURN TO PUMP...
Page 224: Propeller Feathering
PROPELLER FEATHERING Function: Maintenance: Minimise propeller drag by streamlining the blades in the Check feathering operation as per Airframe Maintenance event of an in-flight engine shutdown. Manual instruction. Adjustment: Description: Adj. Feather screw CW -> Increases the time to feather Bringing the propeller lever to the feather position causes Adj.
Page 225 PROPELLER FEATHERING FEATHERING VALVE SPEEDER SPRING ACTUATING LEVER GOVERNOR SPRING FEATHERING TO SUMP PLUNGER PILOT VALVE TO SUMP CARBON BLOCK GOVERNOR OIL PRESSURE BYPASS TO PUMP PROPELLER SERVO PRESSURE BETA ROD HYDRAULIC LOW PITCH ADJ. PROPELLER SYSTEM 11.15 PT6A-60 SERIES TRAINING USE ONLY P&WC Proprietary - Disclosure and use subject to the restrictions on page 2 of preface...
Page 226 NF GOVERNOR (OVERSPEED PROTECTION) Description: The movement of the reset lever around its pivot point opens the Py air passage. Py bleeds into the reduction The CSU contains a Py bleed orifice closed by a ‘flapper’ gearbox limiting the fuel supply to the engine. This will pre- valve and reset lever.
Page 227: Nf Governor
NF GOVERNOR RESET LEVER Py SEAL SPEEDER SPRING CUP FLYWEIGHTS AIR BLEED ORIFICE PIVOT TO SUMP Py AIR FROM FCU OIL TO RGB PROPELLER SERVO OIL PROPELLER SYSTEM 11.17 PT6A-60 SERIES TRAINING USE ONLY P&WC Proprietary - Disclosure and use subject to the restrictions on page 2 of preface...
Page 228: Propeller Overspeed Governor
PROPELLER OVERSPEED GOVERNOR (AIRFRAME OPTION) increase in blade pitch puts more load on the engine and slows down the propeller. Function: To test the unit, the speed reset solenoid is activated and Provides back up protection against propeller and power servo oil pressure pushes against the reset piston to cancel turbine over speeds (4% over max prop speed).
Page 229 PROPELLER OVERSPEED GOVERNOR (AIRFRAME) SPEED ADJUSTING RESET SPRING REDUCES SPRING TENSION = LOWER O/S SCREW RESET PISTON SPEEDER SPRING FLYWEIGHTS SPEED RESET SOLENOID SPEED RESET OIL ACTIVATION FEATHERING SOLENOID GOVERNOR VALVE SPLINE DRIVE FROM CSU PROPELLER SYSTEM 11.19 PT6A-60 SERIES TRAINING USE ONLY P&WC Proprietary - Disclosure and use subject to the restrictions on page 2 of preface...
Page 230 NOTES PROPELLER SYSTEM 11.20 PT6A-60 SERIES TRAINING USE ONLY P&WC Proprietary - Disclosure and use subject to the restrictions on page 2 of preface...
Page 231 PROPELLER OVERSPEED GOVERNOR PT6A-67B OIL OUT FROM FEATHERING VALVE Py TO FCU ISOLATING SOLENOID VALVE LIMITER PROPELLER OVERSPEED GOVERNOR (A-67B/P ONLY) PROPELLER SYSTEM 11.21 PT6A-60 SERIES TRAINING USE ONLY P&WC Proprietary - Disclosure and use subject to the restrictions on page 2 of preface...
Page 232: Propeller Governor Adjustments
PROPELLER GOVERNOR ADJUSTMENTS Maximum - Set propeller lever at maximum position in the cockpit Forward - Ensure that max Np stop is contacted Propeller - Adjust screw CCW to increase maximum Np, CW to decrease. Speed (Np) - One flat alter Np 2% (A-67R/AF/AG), 4% (A-67/67A) Maximum - Set propeller lever at maximum Np position Reverse...
Page 233 PROPELLER GOVERNOR ADJUSTMENT RESET ARM MAX. STOP A67B/P FEATHERING TIME DO NOT ADJUST ADJUSTMENT FRONT CLEVIS MAX PROP SPEED BETA LEVER (FORWARD) BETA VALVE CAM BOX UNDERSPEED ECCENTRIC SCREW (MAX REVERSE Np) CAP NUT INTERCONNECT ROD RIG FLUSH VALVE CLEVIS BETA VALVE PROPELLER SYSTEM 11.23 PT6A-60 SERIES...
Page 234: Primary Blade Angle (Pba) Check
PRIMARY BLADE ANGLE (PBA) CHECK Function: Troubleshooting: - Indicated torque lower than target = PBA too fine Provide equal flight idle torques for appropriate aircraft han- - Indicated torque higher than target = PBA too coarse dling. On twin engine applications the aircraft may yaw if PBA is not the same on both engines.
Page 235: Primary Blade Angle Chart
PRIMARY BLADE ANGLE CHART PRESSURE ALTITUDE IN FEET °C PROPELLER TORQUE IN FT-LBS PROPELLER SPEED 1500 RPM PROPELLER SYSTEM 11.25 PT6A-60 SERIES TRAINING USE ONLY P&WC Proprietary - Disclosure and use subject to the restrictions on page 2 of preface...
Page 236: Propeller System Troubleshooting11.26
PROPELLER SYSTEM TROUBLESHOOTING Observed Problem Action Required Np And Torque Fluctuations At High Max Np setting may be too high (interference with OSG) Power Overspeed governor test solenoid leaking. (interferes with prop.Governor) (No Ng Fluctuation) Np And Torque Fluctuation At Low Verify Beta ring is not distorted Power Inspect carbon block for excessive wear...
Page 237: Chapter 12 - Maintenance Practices.12.1
MAINTENANCE PRACTICES MAINTENANCE PRACTICES MAINTENANCE PRACTICES 12.1 PT6A-60 SERIES TRAINING USE ONLY P&WC Proprietary - Disclosure and use subject to the restrictions on page 2 of preface...
Page 238: Periodic Inspection
PERIODIC INSPECTION The following table is for reference only, refer to your Engine Maintenance Manual. FREQUENCY COMPONENTS Routine : coincides with daily or pre-flight airframe inspec- 25 hours Power Turbine Blades tion. 50 hours Stage PT Blades Minor : coincides with a typical airframe inspection. Engine Oil 100 hours Notes:...
Page 239 PERIODIC INSPECTION (CON’T) FREQUENCY COMPONENTS FREQUENCY COMPONENTS Minor Tubing, Wiring & Hoses 250 hours Power Turbine Blades (Oil/Fuel/P3/Py) Fuel Pump Inlet Screen 300 hours Ignition Exciter Oil Filter Ignition Cables Fuel Manifold Adapter & 400 or 600 hours Sparks Igniters Nozzle Assemblies Accessories Sundstrand Fuel Pump only...
Page 240: Hot Section Inspection
HOT SECTION INSPECTION Purpose: HSI Frequency: - As per relevant SB To optimize engine performance, fuel economy, safety and - On condition (as per ECTM result) increase components life. The condition of the hot section parts has a direct effect on engine performance. Deteriora- Pre HSI Actions: tion of the hot section can be detected by using engine con- dition trend monitoring (ECTM) and / or by doing...
Page 241 NOTES MAINTENANCE PRACTICES 12.5 PT6A-60 SERIES TRAINING USE ONLY P&WC Proprietary - Disclosure and use subject to the restrictions on page 2 of preface...
Page 242: Borescope Inspection
BORESCOPE INSPECTION Description: Procedure: - Remove one fuel manifold adapter. The borescope inspection allows operators to visually - Insert the guide tube through the open port. inspect hot section components without disassembling the - Install the holding fixture to the engine "C" flange. engine.
Page 243: Guide Tube Orientation
GUIDE TUBE ORIENTATION FUEL MANIFOLD ADAPTER PORT RIGID GUIDE TUBE POINT OF ENTRY (REF.) FIBERSCOPE TIP VANE RING DISTAL POINT RELATION BETWEEN POINT OF ENTRY AND DISTAL TIP VIEW FROM EXHAUST DUCT TOWARD AIR INLET CASE MAINTENANCE PRACTICES 12.7 PT6A-60 SERIES TRAINING USE ONLY P&WC Proprietary - Disclosure and use subject to the restrictions on page 2 of preface...
Page 244: Hot Section Tools
HOT SECTION TOOLS 1. Power Section Sling (Without The Propeller Installed On The Engine) (PWC34673). 2. Compressor Turbine Holding Wrench (PWC30331). 3. Spacers (4) (PWC34478). 4. Spreader (PWC30335). 5. Compressor Turbine Puller (PWC30403). 6. Protector Sleeve (PWC30336). 7. Puller No. 2 Bearing Cover (PWC32823). 8.
Page 245 HOT SECTION TOOLS MAINTENANCE PRACTICES 12.9 PT6A-60 SERIES TRAINING USE ONLY P&WC Proprietary - Disclosure and use subject to the restrictions on page 2 of preface...
Page 246: Ct Tip Clearance Measurement
CT TIP CLEARANCE MEASUREMENT Procedure: - Measure tip clearance using a tapered or a wire feeler gage, loading the CT disk in the direction of the mea- surement. - The tip clearance limits for each individual model is listed in the Engine Maintenance Manual. - No need to rotate turbine while taking measurements.
Page 247 NOTES MAINTENANCE PRACTICES 12.11 PT6A-60 SERIES TRAINING USE ONLY P&WC Proprietary - Disclosure and use subject to the restrictions on page 2 of preface...
Page 248: Hot Section Inspection (Cont'd)
HOT SECTION INSPECTION (CONT’D) Inspection CT Vane: - Inspect vane ring for evidence of burning, cracking and Gas Generator Case: coating loss. - Inspect case for cracks, distortion, corrosion and evi- - Insure proper sliding fit (lugs to slots) with mating dence of overheating.
Page 249: Ct Blade Sulphidation
CT BLADE SULPHIDATION STAGE 1 - MILD SULPHIDATION STAGE 2 - OXIDE FAILURE EVIDENT SLIGHT ROUGHNESS OF SURFACE ROUGHNESS OF SURFACE IS MORE EVIDENT DUE TO SOME GROWTH AND BREAK DOWN AS BREAKDOWN OF THE OXIDE SCALE LAYER OF THE OXIDE LAYER. CONTINUES.
Page 250: Hot Section Inspection (Cont'd)
HOT SECTION INSPECTION (CONT’D) Inter-Stage Sealing Ring: Sealing surface restoration - Inspect sealing ring(s) for fretting wear on sealing diameter and face. Purpose: - Fit ring on sealing diameter for full contact. To achieve best sealing of P3 in the gas generator case area and keep leakage to a minimum.
Page 251 HOT SECTION INSPECTION (CONT’D) Fitting Of Hot Section Parts Step 2: Purpose: Install the shroud housing on a bench with the slots upper- - To achieve best fitting of the hot section parts for mini- most. Install the vane ring lugs inside the shroud housing mizing side play which can result in CT tip rub.
Page 252 HOT SECTION INSPECTION (CONT’D) Shroud Segment Grinding Preparations: - Mask vane ring, #2 bearing and gas generator area To achieve optimum Compressor Turbine tip clearance all carefully. around the shroud. - Install the 4 rubber spacers with equal tension between the large and small exit ducts. - Install the grinder adapter on compressor stub shaft.
Page 253 HOT SECTION INSPECTION (CONT’D) Calculate Actual Tip Clearance Before Grinding As Fol- lows: (the numbers used are for examples only) - Dimension stamped on side of - gauge (master).= 4.282" - Dial gage reading.= -0.009" (plus or minus sign is important) - CT largest diameter / 2 (8.532 / 2).= 4.266"...
Page 254 HOT SECTION INSPECTION (CONT’D) Fuel Nozzle Functional Check: Pressure Test: Pressure test for leakage between nozzle tip and adapter at Ensures the engine combustion chamber receives properly 500 PSIG fluid pressure or 200 PSIG air pressure, no leak- atomized fuel. age allowed.
Page 255 HOT SECTION INSPECTION (CONT’D) T5 System Functional Check: Heat Response Test: (T5 Probe Functional Check) T5 system inspection should be performed during hot sec- This check is done to verify proper functioning of T5 probes. tion inspection with the engine split at flange "C" or when- Ensures T5 probes respond to heat.
Page 256 NOTES MAINTENANCE PRACTICES 12.20 PT6A-60 SERIES TRAINING USE ONLY P&WC Proprietary - Disclosure and use subject to the restrictions on page 2 of preface...
Page 257: Chapter 13 - Rigging
RIGGING RIGGING RIGGING 13 PT6A-60 SERIES TRAINING USE ONLY...
Page 258: Basic Engine Rigging
BASIC ENGINE RIGGING Purpose: Provide the operator with a basic approach to engine rig- COCKPIT ging. This section defines the logical sequence that should LEVERS be followed when rigging the engine. It also describes the post run-up adjustments necessary to get an ideal cockpit lever to engine response relationship.
Page 259: Rear Linkage Rigging
REAR LINKAGE RIGGING One of the first steps prior to rigging the fuel control unit on Note: the PT6 is to carefully rig the cambox position. Once this is A “rig pin" hole located on the cambox may be used to facil- done, the fuel control unit and the reversing cable can be itate the track point rigging.
Page 260: Woodward Fuel Control Rigging
WOODWARD FUEL CONTROL RIGGING 1. Disconnect the FCU interconnecting rod and set it's length to 1/8 inch shorter than specified in the airframe maintenance manual (the rod length will be rectified later on). 2. With the rod disconnected position the fuel lever to con- tact the idle stop without going into the deadband.
Page 261: Rear Linkage (Woodward)
REAR LINKAGE (WOODWARD) REVERSING CAM IDLE REVERSING CABLE IDLE FORWARD REVERSE CAMBOX INPUT CAM FOLLOWER PIN LEVER FCU CONNECTING ROD MAX FORWARD NG STOP FCU ARM CAM BOX DEAD-BAND ADJUSTMENT AIRFRAME POWER LEVER CABLE HIGH IDLE ROLLER HIGH IDLE CAM MAX REVERSE NG STOP RIGGING 13...
Page 262: Front Linkage Rigging
FRONT LINKAGE RIGGING Telescopic Interconnect Rod: Rigid Interconnect Rod: 1. Disconnect the reverse cable at the cambox. 1. Disconnect the reverse cable at the cambox. 2. Move the Power Lever in the cockpit between Flight Idle 2. Move the cockpit power lever between idle and maximum and Max Power setting to verify free movement.
Page 263: Front Linkage
FRONT LINKAGE RESET ARM MAX. STOP FEATHERING TIME DO NOT ADJUST ADJUSTMENT FRONT CLEVIS BETA LEVER MAX PROP SPEED (FORWARD) BETA VALVE CAM BOX PNEUMATIC MINIMUM ADJUSTMENT (MAX REVERSE Np) CAP NUT INTERCONNECT ROD (GAP AS PER RIG FLUSH AIRFRAME M.M.) VALVE CLEVIS BETA VALVE...
Page 264: Fuel Condition Lever
FUEL CONDITION LEVER - Disconnect control cable from the fuel idle reset/cut- Propeller Lever: off lever - Move the cockpit propeller lever fully forward. Ensure - Insert rigging pin through the idle reset/cut-off lever that speed select lever contacts maximum Np stop - Place cockpit fuel condition lever to ground idle and screw.
Page 265: Fuel & Propeller Lever Rigging
FUEL & PROPELLER LEVER RIGGING FEATHER STOP RESET ARM MAX. STOP SCREW DO NOT ADJUST MAX. SPEED ADJ. HIGH IDLE STOP CUT-OFF (ONLY IF STOP STAGGER EXISTS) WOODWARD RIGGING 13 PT6A-60 SERIES TRAINING USE ONLY...
Page 266: Post Run Up Adjustments
POST RUN UP ADJUSTMENTS Prior to running the engine ensure that: - The FCU maximum Ng stop is contacted when the cockpit power lever is advanced to the maximum position. - The cut-off stop is contacted when the condition lever is at the cut-off position. - The speed select lever on the CSU makes firm contact with the maximum speed stop.
Page 267 POST RUN UP ADJUSTMENTS (CONT’D) Symptom - Verify position of the beta valve is identical on the two engines when the cockpit power lever is advanced halfway between idle and maximum power. Primary Blade Angle Check; Different - Adjust beta valve position using the reversing cable clevis end (small Torque On The Two Engines adjustment) or adjust beta nuts if airframe maintenance manual permits (big adjustment)
Page 268: Twin Engine Rigging Troubleshooting
TWIN ENGINE RIGGING TROUBLESHOOTING Condition 1 Ideal Condition. Condition 5 Reverse Pick-Up Point Are Split - Adjust deadband screw on the right hand engine May vary from airframe to airframe. The Airframe Mainte- (CCW) to reduce the band. This will change the dead- nance manual provides a description of the required set- band in forward as well.
Page 269: Post Run-Up Adjustments (Twin Engine)
POST RUN-UP ADJUSTMENTS (TWIN ENGINE) IDLE DETENT IDLE DETENT REVERSE LEGEND TQ : CRUISE TORQUE PU : NG PICK -UP POINT Z T : ZERO THRUST POSITION BVT:BETA VALVE TRACKING RIGGING 13 PT6A-60 SERIES TRAINING USE ONLY...
Page 270 TRAINING MATERIAL CHANGE REQUEST Date: ________________________________ Company Name and Address: ____________________________________________________________________________ Your Name: __________________________________ Job Title:_________________________________________ Training Aid Title:_______________________________________________________________________________________ Reference Page(s): _____________________________________________________________________________________ Recommended Change(s) and Reason(s) for Change(s):_______________________________________________________ _____________________________________________________________________________________________________ _____________________________________________________________________________________________________ ____________________________________________________________________________________________________ TMCR ID Number (P&WC Office Use Only): _________________________________________________________________ Send To: Note: If you would like to be contacted regarding the Pratt &...

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United Technologies Pratt and Whitney PT6A-60 Series Training Manual

Chapter 1 - Engine Overview

Chapter 2 - Compressor Section

Chapter 3 - Combustion & Turbine

Chapter 4 - Gearboxes

Chapter 5 - Oil System

Chapter 6 - Secondary Air System

Chapter 7 - Engine Indicating System

Chapter 8 - Ignition System

Chapter 9 - Performance

Chapter 10 - Fuel System

Chapter 11- Propeller System

Chapter 12 - Maintenance Practices.12.1

Chapter 13 - Rigging

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Summary of Contents for United Technologies Pratt and Whitney PT6A-60 Series