TRAINING NOTES ARRIEL 1 Turbine Engine

Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) ARRIEL 1 Training Notes 1st line maintenance course This document is intended to assist a TURBOMECA-qualified instructor in teaching basic information related to the operation and maintenance of the ARRIEL 1 turboshaft engines. It is a training aid and should only be used to support the training course to which it refers, and only by a person attending such training. It must not be used in any other circumstances. It will not be updated and should not be relied upon for the maintenance or repair of ARRIEL 1 engines. Only the current approved TURBOMECA maintenance technical publications should be used for such purposes. The acquisition of this document does not constitute proof of official formal training. Only completion of a course delivered by a TURBOMECA-qualified instructor can lead to the issuance of a TURBOMECA-recognised training certificate stating, when applicable, a successful result. Turbomeca Training - December 2013 This document is the property of TURBOMECA and it may not be copied without the express written authority of TURBOMECA. Turbomeca Training is a registered Trademark. For training purposes only © Copyright - Turbomeca Training Edition: May 2014 0.1 FOREWORD Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) FOREWORD ARRIEL 1 Training Notes 1st line maintenance course 0 - Foreword 1 - Introduction 2 - Power plant 3 - Engine 4 - Oil system 5 - Air system 6 - Fuel system 8 - Measurement and indicating systems 9 - Starting system 10 - Electrical system 11 - Engine installation 12 - Troubleshooting 13 - Checking of knowledge 7 - Control system For training purposes only © Copyright - Turbomeca Training Edition: May 2014 0.2 SUMMARY Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) SUMMARY Training Notes 1st line maintenance course ARRIEL 1 0 - FOREWORD - Foreword........................................... Summary........................................... Table of contents............................... List of abbreviations.......................... Conversion table............................... 3 - ENGINE 0.1 0.2 0.3 0.7 0.11 - 1 - INTRODUCTION - General information.......................... 1.2 - Training programme ......................... 1.4 - 1.5 2 - POWER PLANT - Power plant....................................... - Principle of adaptation to the helicopter.......................................... - Main characteristics.......................... - Design and development ................. - Maintenance .................................... For training purposes only © Copyright - Turbomeca Training 2.2 2.8 2.10 2.14 2.18 - 2.29 Edition: May 2014 Engine - Presentation....................... Axial compressor.............................. Centrifugal compressor..................... Combustion chamber........................ Gas generator turbine....................... Power turbine.................................... Exhaust system................................. Reduction gearbox............................ Transmission shaft and accessory gearbox............................................. - Engine - Operation ........................... - Engine - 1st line maintenance .......... 3.2 3.6 3.8 3.10 3.12 3.14 3.16 3.18 3.20 3.32 3.34 - 3.39 0.3 TABLE OF CONTENTS Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) TABLE OF CONTENTS Training Notes 1st line maintenance course ARRIEL 1 TABLE OF CONTENTS 4 - OIL SYSTEM - Oil system - Presentation ................. - Oil tank - Oil cooler - Oil pressure transmitter ........................................ - Oil pumps ......................................... - Oil filter ............................................. - Oil filter pre-blockage indicator ........ - Low oil pressure switch .................... - Electrical magnetic plugs ................. - Mechanical magnetic plugs .............. - Strainers ........................................... - Centrifugal breather ......................... - Oil system - Operation ..................... - External oil pipes ............................. - Oil system - 1st line maintenance .... For training purposes only © Copyright - Turbomeca Training 5 - AIR SYSTEM 4.2 4.6 4.8 4.10 4.14 4.16 4.18 4.20 4.22 4.24 4.26 4.28 4.30 - 4.35 - Air system - Presentation ................. Internal air system ............................ Air tappings....................................... Compressor bleed valve................... External air pipes.............................. Air system - 1st line maintenance .... 6 - FUEL SYSTEM Edition: May 2014 - Fuel system - Presentation .............. - Fuel Control Unit............................... - Pressurising, stop purge and overspeed valves ............................. - Start valves assembly....................... - Start injectors.................................... - Main injection system........................ - Combustion chamber drain valve..... - Fuel system - Operation ................... - External fuel pipes ........................... - Fuel system - 1st line maintenance . 5.2 5.4 5.6 5.8 5.16 5.18 - 5.19 6.2 6.8 6.18 6.20 6.22 6.24 6.26 6.28 6.32 6.34 - 6.37 0.4 TABLE OF CONTENTS Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) (CONTINUED) Training Notes 1st line maintenance course ARRIEL 1 (CONTINUED) 7 - CONTROL SYSTEM - Control system - Presentation........... 7.2 - Control system - Operation .............. 7.6 - Control system - 1st line maintenance .................................... 7.30 - 7.31 8 - MEASUREMENT AND INDICATING SYSTEMS - Measurement and indicating systems - Presentation..................... - Speed measurement and indicating system............................................... - T4 measurement and indicating system............................................... - Torque measurement and indicating system............................................... - Miscellaneous indications................. - Measurement and indicating systems - 1st line maintenance ........ For training purposes only © Copyright - Turbomeca Training 9 - STARTING SYSTEM - Starting system - Presentation.......... Starter-generator............................... Ignition system.................................. Starting system - Operation ............. Starting system - 1st line maintenance .................................... 10 - ELECTRICAL SYSTEM - Electrical system - Presentation........ - Power turbine overspeed detection system............................................... - Electrical harnesses.......................... - Electrical system - 1st line maintenance .................................... 8.2 8.4 8.10 8.14 8.18 9.2 9.6 9.8 9.10 9.14 - 9.15 10.2 10.4 10.16 10.18 - 10.19 8.22 - 8.23 Edition: May 2014 0.5 TABLE OF CONTENTS Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) TABLE OF CONTENTS Training Notes 1st line maintenance course ARRIEL 1 TABLE OF CONTENTS 11 - ENGINE INSTALLATION - Engine compartment......................... Engine mounting and lifting............... Air intake and exhaust systems........ Engine/airframe system interfaces.... Drains - Purges - Air vents................ Power drive....................................... Fire protection................................... Engine installation - 1st line maintenance .................................... OBSERVATIONS .......................... LAST PAGE 11.2 11.4 11.6 11.8 11.16 11.18 11.20 These Training Notes are designed to meet the requirements of training and, to a certain extent, take into consideration ATA 104 recommendations and the requirements of the various authorities concerned. This document includes 329 pages. 11.22 - 11.25 12 - TROUBLESHOOTING - General............................................. 12.2 - Troubleshooting................................ 12.4 - Conclusion ....................................... 12.10 - 12.11 13 - CHECKING OF KNOWLEDGE - Introduction....................................... Questionnaire 1 ................................ Questionnaire 2 ................................ Questionnaire 3 ................................ Questionnaire 4................................. For training purposes only © Copyright - Turbomeca Training 13.2 13.3 13.6 13.12 13.15 - 13.28 Edition: May 2014 0.6 TABLE OF CONTENTS Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) (CONTINUED) Training Notes 1st line maintenance course ARRIEL 1 The abbreviations / symbols shown below may be used during training: A/C................. AC.................. ACMS............. ACW............... AEO................ AFCS.............. AMC................ AMCU............. AMM............... APM................ APU................ ARMS............. ATA................. BITE............... C1................... C2................... CAD................ CAN................ CDS................ CFT................. CPDS............. cSt.................. CVD................ CW.................. CWP............... daN................. Aircraft Alternating Current Automatic Control Monitoring System Anticlockwise All Engines Operating Automatic Flight Control System Aircraft Management Computer Auxiliary Mode Control Unit Aircraft Maintenance Manual Auto-Pilot Module Auxiliary Power Unit Automatic Recording Monitoring System Air Transport Association Built-In Test Equipment Gas generator operating cycles Power turbine operating cycles Caution Advisory Display Controller Area Network Cockpit Display System Frequency-to-Voltage Converter Central Panel Display System Centistokes Bleed valve control Clockwise Central Warning Panel Decanewtons For training purposes only © Copyright - Turbomeca Training DAU................ Data Acquisition Unit DC.................. Direct Current DCU................ Digital Control Unit DDR................ DECU Digital Read-out DECU............. Digital Engine Control Unit EBCAU........... Engine Back-up Control Auxiliary Unit ECL................. Engine Control Lever ECP................ Engine Control Panel ECU................ Electronic Control Unit EDR................ Engine Data Recorder EDU................ Electronic Display Unit EECU............. Engine Electronic Control Unit EGT................ Exhaust Gas Temperature EICAS............. Engine Instrumentation and Crew Advisory System EID................. Electronic Instrument Display EPC................ Engine Power Check F..................... Frequency FADEC........... Full Authority Digital Engine Control FAU................ Fault Annunciator Unit FCU................ Fuel Control Unit FLI.................. First Limit Indicator FM.................. Flight Manual FND................ Flight and Navigation Display FOD................ Foreign Object Damage ft..................... Feet Edition: May 2014 0.7 LIST OF ABBREVIATIONS Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) LIST OF ABBREVIATIONS Training Notes 1st line maintenance course ARRIEL 1 LIST OF ABBREVIATIONS FVC................ FWD............... g..................... G..................... GOV............... HE.................. HF................... HFC................ HIP/SARM...... HP................... HP................... HUMS............. Hz................... IAS.................. ICAO............... ICP.................. ICR................. IETP................ IFDS............... IGV................. IIDS................ ILS.................. IPC................. IPS.................. ISA.................. Frequency-to-Voltage Converter Forward Grams Mass airflow Governor High Energy Human Factor Hourly Fuel Consumption Hovering at Increased Power/Search And Rescue Mission Horsepower High Pressure Health and Usage Monitoring System Hertz Indicated AirSpeed International Civil Aviation Organisation Intermediate Contingency Power Intermediate Contingency Rating Interactive Electronic Technical Publication Integrated Flight Display System Inlet Guide Vanes Integrated Instrument Display System Integrated Logistics Support Illustrated Parts Catalogue Inlet Particle Separator International Standard Atmosphere For training purposes only © Copyright - Turbomeca Training KE................... kg/s................. kHz................. kPa................. kW.................. l/h.................... lb..................... LH................... LP................... LPG................ LRU................ LUH................ LVDT............... mA.................. Max................. MCL................ MCP................ MCP................ MCQ............... MCR............... MFD................ MGB............... MHz................ Min.................. MPAI............... MTCP............. Edition: May 2014 Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) (CONTINUED) Kinetic Energy Kilograms per second Kilohertz Kilopascals Kilowatts Litres per hour Pounds Left-Hand Low Pressure Collective pitch/control system link Line Replaceable Unit Light Utility Helicopter Linear Variable-Differential Transducer Milliamperes Maximum Manual Control Lever Maximum Continuous Power Maximum Contingency Power Multiple-Choice Questionnaire Maximum Contingency Rating Multi-Function Display Main gearbox Megahertz Minimum Multi-Purpose Air Intake Maintenance Test Control Panel 0.8 LIST OF ABBREVIATIONS Training Notes 1st line maintenance course ARRIEL 1 (CONTINUED) MTOP............. mV.................. N..................... N1 / NG.......... N2 / NTL / NFT / NPT...... NGV................ NMD............... NPS................ NPS................ NR.................. O/S................. OAT................ OEI................. OEICT............. OEIH............... OEIL............... OVSP.............. P..................... PFD................ PLA................. PPNG............. PSI.................. PSIA............... PSID............... PSIG............... Maximum Take-Off Power Millivolts Rotation speed Gas generator rotation speed Power turbine rotation speed Nozzle Guide Vane Navigation and Mission Display Power output shaft rotation speed Neutral Position Switch Rotor rotation speed Overspeed Outside Air Temperature One Engine Inoperative One Engine Inoperative - Continuous One Engine Inoperative - High One Engine Inoperative - Low Overspeed Pressure Primary Flight Display Power Lever Assembly NG piston position Pounds per Square Inch Pounds per Square Inch Absolute Pounds per Square Inch Differential Pounds per Square Inch Gauge For training purposes only © Copyright - Turbomeca Training PSU................ PT................... RDAU............. RH.................. rpm................. RVDT.............. SB................... SCR................ SFC................ shp.................. SI.................... SL................... SMM............... SMS................ SRU................ t...................... T..................... T/O.................. TBO................ TET................. TGT................ TOT................ TRQ................ TU................... US G............... V..................... Edition: May 2014 Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) LIST OF ABBREVIATIONS Power Supply Unit Power Turbine Remote Data Acquisition Unit Right-Hand Revolutions per minute Rotary Variable-Differential Transducer Service Bulletin Super Contingency Rating Specific Fuel Consumption Shaft horsepower International system of units Service Letter Safety Management Manual Safety Management System Shop Replaceable Unit Time Temperature Take-Off Time Between Overhauls Turbine Entry Temperature Turbine Gas Temperature Turbine Outlet Temperature Torque Technical Update US Gallons Volts 0.9 LIST OF ABBREVIATIONS Training Notes 1st line maintenance course ARRIEL 1 LIST OF ABBREVIATIONS VA................... VAC................ VDC................ VEMD............. VHIU............... Vin.................. VMD................ VMS................ Vout................ VSV................ W.................... WF.................. XBV................ XCP................ XF................... XMV................ XPA................. XTL................. XV................... Z..................... Zd................... Zp................... Volt-Amperes Volts, Alternating Current Volts, Direct Current Vehicle and Engine Multi-function Display Vehicle Helicopter Intermediate Unit Input voltage Vehicle Management Display Vehicle Monitoring System Output voltage Variable Stator Vanes Power Fuel flow Bleed valve position signal Collective pitch position signal Fuel metering valve position signal Metering valve position signal Pedal position signal Pedal position signal / N2 trim position signal Variable vane position signal Altitude Density altitude Pressure altitude For training purposes only © Copyright - Turbomeca Training °C................... °F.................... K..................... ±...................... Ω..................... ∆..................... ∆P................... ω..................... *...................... Edition: May 2014 Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) (CONTINUED) Degrees Celsius Degrees Fahrenheit Kelvins Plus or minus (tolerance permitted) Ohms Difference (delta) Pressure difference Angular velocity Datum (e.g. N1* = N1 datum) 0.10 LIST OF ABBREVIATIONS Training Notes 1st line maintenance course ARRIEL 1 UNIT International System British or American Systems Length 1 mm 1m Volume 1 dm3 = 1 litre Mass 1 kg = 2.2 lb Power 1 kW = 1.34 HP Temperature °C K Pressure 1 kPa = 0.01 bar = 0.145 PSI Flow (air, oil, fuel) 1 kg/s = 2.2 lb/s Specific Fuel Consumption 1 g/kW.h For training purposes only © Copyright - Turbomeca Training Edition: May 2014 = 0.039 inches = 3 ft 3 inches = 39 inches = 0.26 US gallons = (°F-32).5/9 = [(°F-32).5/9] + 273 = 0.00164 lb/HP.h 0.11 CONVERSION TABLE Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) CONVERSION TABLE Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) ARRIEL 1 Training Notes 1st line maintenance course Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) 1 - INTRODUCTION - General information .............................................................................. 1.2 - Training programme ............................................................................. 1.4 - 1.5 For training purposes only © Copyright - Turbomeca Training Edition: May 2014 1.1 INTRODUCTION ARRIEL 1 Training Notes 1st line maintenance course GENERAL INFORMATION TURBOMECA Training Adequate training is essential for obvious safety reasons, but also to reduce additional maintenance costs incurred by unjustified removals and excessive downtime. In accordance with TURBOMECA support's proximity policy, TURBOMECA Training has developed a worldwide training network: it has an official office or Training Center for each continent. "Greater knowledge leads to greater efficiency". TURBOMECA Training courses can therefore be conducted worldwide: Objectives of training - In the TURBOMECA France reference Training Center The main objective is the acquisition of the knowledge required for the tasks to be achieved (know and know how). Further information is also communicated to widen the skill and the experience of the trainee. - In other TURBOMECA subsidiaries, e.g. TURBOMECA AUSTRALASIA or TURBOMECA ASIA PACIFIC (Singapore) - In TURBOMECA approved Training Centers - Performance based training according to task analysis, with classroom sessions, student involvement, practical work and trouble shooting techniques - Advanced training aids: training notes, multimedia courseware (or Computer Aided Presentation) and demonstration training engine - Instructors trained on the product and in training methods, and qualified by TURBOMECA For training purposes only © Copyright - Turbomeca Training - In the TURBOMECA do Brasil reference Training Center - In delegated Training Centers Training approach - Courses are taught in English and French. - In the TURBOMECA USA reference Training Center - Directly on the customer's site. The training courses are conducted by an instructor detached from TURBOMECA or by a TURBOMECA qualified and accredited instructor. TURBOMECA training contact The focal point for all your TURBOMECA Training needs is the "TURBOMECA Operator On-Line Support" (TOOLS) web site: www.turbomeca-support.com Edition: May 2014 1.2 INTRODUCTION Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) "The power of knowledge" Training Notes 1st line maintenance course ARRIEL 1 TRAINING OBJECTIVES Adequate training is essential for obvious safety reasons, but also to reduce additional maintenance costs incurred by unjustified removals and excessive downtime. TRAINING APPROACH "Greater knowledge leads to greater efficiency". North America Area TM USA RTC Europe Africa Middle East Area The focal point for all your TURBOMECA Training needs: www.turbomeca-support.com TM F RTC Corporate TURBOMECA Training TAP RTC TM B RTC South America Area GENERAL INFORMATION For training purposes only © Copyright - Turbomeca Training Edition: May 2014 Asia Pacific Australasia Area RTC ................. Reference Training Centre TM ................... TURBOMECA TM F ................ TURBOMECA France TM USA........... TURBOMECA USA TM B................ TURBOMECA do Brasil TAP ................. TURBOMECA Asia Pacific 1.3 INTRODUCTION Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) TRAINING: "The power of knowledge" ARRIEL 1 Training Notes 1st line maintenance course The training programme is established to meet the training requirements and takes into consideration ATA 104 recommendations and the requirements of the various authorities concerned. Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) TRAINING PROGRAMME It should be noted that the "classroom sessions" alternate with periods devoted to demonstrations, practical exercises and visits. For training purposes only © Copyright - Turbomeca Training Edition: May 2014 1.4 INTRODUCTION Training Notes 1st line maintenance course ARRIEL 1 TRAINING COURSE 1st LINE MAINTENANCE COURSE DURATION 2 DAYS At the end of this course, the trainee will be able to identify the engine components, describe and explain the operation of the engine and its systems, and carry out maintenance procedures (engine installed in the airframe) and troubleshooting. 5 DAYS At the end of this course, the trainee will be able to identify the engine components, carry out certain maintenance procedures (engine removed from the airframe), i.e. the removal/installation of 2nd LINE MAINTENANCE modules and Shop Replaceable Units. PROGRAMME: The programme mainly includes practical work. It can be carried out j u s t after the COURSE 1st line maintenance course. 3 DAYS At the end of this course, the trainee will be able to carry out the intramodular maintenance procedures (deep maintenance). 3rd LINE MAINTENANCE COURSE FROM 3 DAYS TO 3 WEEKS PROGRAMME: This course consists entirely of practical work and the trainees must have certain qualifications. The course documentation consists of the Maintenance Manual and Maintenance Technical Instructions. The qualification awarded at the end of this course is time-limited and will be renewed under certain conditions. At the end of this course, the trainee will have a greater understanding of the engine and its systems. REFRESHER NOTE: This course is recommended for technicians who have already attended the 1st line maintenance course and who have since acquired about one year's experience on the type of engine concerned. 2 DAYS At the end of this course, the trainee will be able to better identify and correct operating problems. TROUBLESHOOTING FUEL AND CONTROL SYSTEMS ENGINE DOCUMENTATION NOTE: This course is recommended for technicians who have already attended the 1st line maintenance course and who have since acquired about one year's experience on the type of engine concerned. At the end of this course, the trainee will have an in-depth understanding of the engine fuel and control systems. NOTE: This course is recommended for technicians who have already attended the 1st line maintenance course and who have since acquired about one year's experience on the type of engine concerned. At the end of this course, the trainee will be able to understand and use the engine documentation. NOTE: A basic knowledge of engines is recommended. 2 DAYS 2 DAYS 2 DAYS TRAINING REQUIREMENTS / ATA 104 RECOMMENDATIONS / REQUIREMENTS OF THE VARIOUS AUTHORITIES CONCERNED TRAINING PROGRAMME For training purposes only © Copyright - Turbomeca Training Edition: May 2014 1.5 INTRODUCTION Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) FAMILIARISATION OBJECTIVE At the end of this course, the trainee will be able to describe the engine, explain its principle of operation and identify the main components of the engine and its systems. Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) ARRIEL 1 Training Notes 1st line maintenance course Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) 2 - POWER PLANT - Power plant ............................................................................................ 2.2 - Principle of adaptation to the helicopter ............................................ 2.8 - Main characteristics ............................................................................. 2.10 - Design and development ..................................................................... 2.14 - Maintenance .......................................................................................... 2.18 - 2.29 ALWAYS REFER TO THE MAINTENANCE MANUAL For training purposes only © Copyright - Turbomeca Training Edition: May 2014 2.1 POWER PLANT ARRIEL 1 Training Notes 1st line maintenance course POWER PLANT Function Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) GENERAL The power plant provides power by transforming the energy contained in the air and fuel into shaft power. Main characteristics - Type: free-turbine turboshaft engine with forward power drive via an external shaft - Design: modular - Max. Take-Off Power (MTOP) (engine installed): from 480 to 560 kW (650 to 760 shp): according to version - Specific Fuel Consumption: according to version - Output shaft speed: 6000 rpm (at 100% N2) (except 1S1) - Approximate dimensions and mass of engine (may vary according to version): • Length: 1166 mm (45.5 inches) • Width: 465.5 mm (18.2 inches) • Height: 609 mm (23.8 inches) • Dry mass: 126 kg (277 lb). For training purposes only © Copyright - Turbomeca Training Edition: May 2014 2.2 POWER PLANT Training Notes 1st line maintenance course GAS AIR POWER FUEL 6000 rpm at 100% N2 (except 1S1) POWER PLANT Type: Free turbine turboshaft engine with forward power drive via an external shaft Max. Take-Off Power (MTOP) (engine installed): From 480 to 560 kW (650 to 760 shp) according to version Design: Modular Specific fuel consumption: According to version Dry mass: 126 kg (277 lb) GENERAL POWER PLANT For training purposes only © Copyright - Turbomeca Training Edition: May 2014 2.3 POWER PLANT Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) ARRIEL 1 ARRIEL 1 Training Notes 1st line maintenance course POWER PLANT This section presents the main functional components of the engine. Gas generator Transmission shaft - External shaft housed in a protection tube which connects the reduction gearbox to the accessory gearbox. Accessory gearbox - Single-stage axial compressor - Gearbox containing the accessory drive train (driven by the gas generator) and the main power drive. - Single-stage centrifugal compressor - Annular combustion chamber with centrifugal fuel injection - Two-stage axial turbine. Power turbine - Single-stage axial turbine. Exhaust pipe - Elliptical, axial exhaust pipe. Reduction gearbox - Reduction gearbox comprising three stages of helical gears. For training purposes only © Copyright - Turbomeca Training Edition: May 2014 2.4 POWER PLANT Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) DESCRIPTION Training Notes 1st line maintenance course ARRIEL 1 Axial compressor Centrifugal compressor POWER TURBINE Combustion chamber EXHAUST PIPE Turbine Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) GAS GENERATOR ACCESSORY GEARBOX Accessory drive train Main power drive TRANSMISSION SHAFT REDUCTION GEARBOX DESCRIPTION POWER PLANT For training purposes only © Copyright - Turbomeca Training Edition: May 2014 2.5 POWER PLANT ARRIEL 1 Training Notes 1st line maintenance course OPERATION Power turbine This section presents the parameters and the adaptation of the gas generator and power turbine. Component adaptation The operation of the power turbine is defined by the balance between the power received from the gas generator in the form of kinetic energy and the torque applied on the shaft, i.e. the N2 rotation speed and the torque (TRQ). In terms of its operation, the engine can be divided into two functional assemblies: Operation - The gas generator, which provides kinetic energy - The power turbine, which transforms this kinetic energy into mechanical power on a shaft. The two assemblies have different rotation speeds. Operation is represented by the graph which shows the power (W), the rotation speeds (N1 and N2) and the max. torque limit (TRQ) imposed by the mechanical transmission: - The torque (TRQ) is a function of the N2 rotation speed - The power (W) is equal to the torque (TRQ) multiplied by the angular velocity (ω) Gas generator The operation of the gas generator is defined by: - At constant N2 speed, the power is only a function of the torque - The air mass flow (G) (airflow which enters the engine) - The air pressure and air temperature at the centrifugal compressor outlet (P2 and T2) - The engine parameters can be represented as a function of a reference parameter, e.g. N1. - The fuel flow (WF) (rate at which fuel is injected into the combustion chamber) - The gas temperature at the gas generator turbine inlet (TET) - The gas generator rotation speed (N1) - The Kinetic Energy (KE) supplied to the power turbine. For training purposes only © Copyright - Turbomeca Training Edition: May 2014 2.6 POWER PLANT Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) POWER PLANT Training Notes 1st line maintenance course ARRIEL 1 N1 (rotation speed) G (air mass flow) P2, T2 (compressor outlet pressure and temperature) POWER TURBINE TRQ (shaft torque) KE (Kinetic Energy) N2 (constant rotation speed) W (shaft power) TET (Turbine Entry Temperature) WF (fuel flow) W ENGINE PARAMETERS TRQ Q) . ax to rq ue R (T M Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) GAS GENERATOR N1 isospeeds G W = TRQ . ω ω = 2. .N 60 P0 W C HF T TE / P2 SFC N2 Power (W) and speeds N1, N2 N2 Torque (TRQ) as a function of N2 N1 P2/P0: Compression ratio HFC: Hourly Fuel Consumption SFC : Specific Fuel Consumption OPERATION POWER PLANT For training purposes only © Copyright - Turbomeca Training Edition: May 2014 2.7 POWER PLANT ARRIEL 1 Training Notes 1st line maintenance course Installation requirements Power transmission The main functional requirements of the installation are: The mechanical power supplied by the engine is used to drive the helicopter rotors through a mechanical transmission. - Constant rotor rotation speed (NR) in all operating conditions This power is absorbed by: - Max. torque (TRQ) limit (usually imposed by the aircraft transmission) - The main rotor (approx. 82%) - The tail rotor (approx. 10%) - Complete engine protection (N1 and N2 speeds, TET, compressor surge (∆WF/∆t), …) - The main gearbox (approx. 8%). - Good load sharing in twin-engine configuration. Twin-engine configuration Adaptation to requirements In twin-engine configuration, the engines are installed to the rear of the main gearbox. To obtain a constant power turbine rotation speed (N2), the power supplied by the engine is automatically adapted to the demand. The power turbines of the two engines are mechanically connected to the main gearbox, which drives the rotors (main rotor and tail rotor). For training purposes only © Copyright - Turbomeca Training This adaptation is regulated by the control system, which meters the fuel flow injected into the combustion chamber so as to deliver the required power (variation of the gas generator rotation speed (N1)), while keeping the engine within its operational limits. Edition: May 2014 2.8 POWER PLANT Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) PRINCIPLE OF ADAPTATION TO THE HELICOPTER Training Notes 1st line maintenance course ARRIEL 1 MAIN ROTOR ENGINE 2 ENGINE 100% TAIL ROTOR ENGINE 1 MAIN GEARBOX 8% TAIL ROTOR 10% MAIN GEARBOX POWER TRANSMISSION TWIN-ENGINE CONFIGURATION N2 W - Power NR ∆W N1, N2, TET, ∆WF/∆t ENGINE ∆N2 ∆N2 Max. torque (TRQ) limit ∆t ADAPTATION TO REQUIREMENTS INSTALLATION REQUIREMENTS PRINCIPLE OF ADAPTATION TO THE HELICOPTER For training purposes only © Copyright - Turbomeca Training time Edition: May 2014 2.9 POWER PLANT Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) MAIN ROTOR 82% ARRIEL 1 Training Notes 1st line maintenance course MAIN CHARACTERISTICS The engine ratings correspond to given conditions of helicopter operation. The ratings are generally defined under determined conditions of speed and atmosphere (altitude and temperature). Note 1: In single-engine configuration, only the MTOP and Max. Continuous Power ratings are authorised. The engine can operate in the following ratings: Note 2: Use of the OEI ratings: Use of these ratings requires certain maintenance procedures to be carried out. - AEO (All Engines Operating) ratings: • Max. Take-Off Power (MTOP): max. rating which can be used during take-off. This rating has a limited duration (5 min. continuous) • Max. Continuous Power: rating which can be used without time limitation (this does not imply that it is used permanently) Note 3: The power values indicated correspond to the following configuration: engine installed, max. torque in the corresponding rating, ISA conditions at sea level. - OEI (One Engine Inoperative) ratings: • Max. Contingency Power (MCP): rating which can be used in the event of one engine failure during take-off or landing. This rating is limited to a period of continuous operation of 2 min. 30 sec. • Intermediate Contingency Power (ICP): rating which can be used in the event of one engine failure in flight. This rating is limited to 30 min. or unlimited (according to versions). For training purposes only © Copyright - Turbomeca Training Edition: May 2014 2.10 POWER PLANT Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) ENGINE RATINGS Training Notes 1st line maintenance course Always refer to the Maintenance Manual for the OEI ratings’ permitted cumulative times N1 MCP MAX. 2 min. 30 sec. MTOP (5 min.) ICP Max. Continuous 30 min. or unlimited Power AEO RATINGS OEI RATINGS Note: The power values indicated correspond to the following configuration: engine installed, max. torque in the corresponding rating, ISA conditions at sea level. ENGINE RATINGS MAIN CHARACTERISTICS For training purposes only © Copyright - Turbomeca Training Edition: May 2014 2.11 POWER PLANT Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) ARRIEL 1 ARRIEL 1 Training Notes 1st line maintenance course MAIN CHARACTERISTICS The engine is designed to operate within a given climatic envelope. Note 1: The flight, starting and relight envelopes may also be affected by the types of oil and fuel used and/or by special procedures. This envelope differs according to the engine operating phase: Flight envelope Note 2: The engine also operates within various other limits: rotation speeds, temperatures, pressures, etc. The flight envelope is the range within which the engine is certified to be operated in "normal engine running" configuration. It is defined in terms of atmospheric temperature (T0) and pressure altitude (Zp). Note 3: Refer to the Flight Manual for the official values of the flight, starting and relight envelopes. Starting and relight envelope The starting and relight envelope is the range within which the engine is certified to be started and relit (restarted). Like the flight envelope, it is defined in terms of atmospheric temperature (T0) and pressure altitude (Zp). For training purposes only © Copyright - Turbomeca Training Edition: May 2014 2.12 POWER PLANT Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) ENGINE OPERATING ENVELOPE ARRIEL 1 Training Notes 1st line maintenance course REFER TO THE FLIGHT MANUAL FOR FURTHER DETAILS 6100 m (20000 ft) Flight envelope 4500 m (14750 ft) Starting and relight envelope ATMOSPHERIC TEMPERATURE T0 0 -500 m (-1650 ft) -55°C (-67°F) +50°C (+122°F) FLIGHT, STARTING AND RELIGHT ENVELOPES Note: The flight, starting and relight envelopes may also be affected by the types of oil and fuel used and/or by special procedures. ENGINE OPERATING ENVELOPE MAIN CHARACTERISTICS For training purposes only © Copyright - Turbomeca Training Edition: May 2014 2.13 POWER PLANT Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) PRESSURE ALTITUDE Zp ARRIEL 1 Training Notes 1st line maintenance course DESIGN AND DEVELOPMENT Development steps Design principles - Certification in 1977 by the French Authorities The engine is designed to meet the aircraft propulsion requirements and particularly for the new generation of helicopters. - The first production engine was delivered in January 1978 The engine design is based on: - An optimised thermodynamic cycle which gives high performance - Simple and reliable components giving a good supportability, and a good maintainability to reduce the costs. - ARRIEL engines will be in service for many years to come. Engine designation - Example: ARRIEL 1A2. ARRIEL - According to TURBOMECA tradition, engines are named after lakes in the Pyrenees mountains. - 1: Type Engine development The ARRIEL engine is based on research and experience of other engines: - A: Variant - 2: Version. - First generation engines: ASTAZOU, ARTOUSTE and TURMO. For training purposes only © Copyright - Turbomeca Training Edition: May 2014 2.14 POWER PLANT Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) GENERAL Training Notes 1st line maintenance course ARRIEL 1 Optimised thermodynamic cycle ARRIEL 1 640 - 700 shp Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) ENGINE DESIGN Simple, reliable components ASTAZOU 500 - 1000 shp Simple, reliable components High performance ARTOUSTE 400 - 850 shp Cost reduction TURMO 1500 - 1600 shp ENGINE DEVELOPMENT DESIGN PRINCIPLES Lake ARRIEL 2011 10000th Arriel (1 and 2) 1978 First production 1977 Certification Example: ARRIEL: ARRIEL 1A2 Name of a lake in the Pyrenees mountains 1: Type A: Variant 2: Version ENGINE DESIGNATION time STAGES OF DEVELOPMENT GENERAL DESIGN AND DEVELOPMENT For training purposes only © Copyright - Turbomeca Training Edition: May 2014 2.15 POWER PLANT ARRIEL 1 Training Notes 1st line maintenance course DESIGN AND DEVELOPMENT APPLICATIONS Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) The ARRIEL 1 engines currently power the following helicopters: - Squirrel and Dolphin (EUROCOPTER), - A 109 K2 (Agusta), - S 76 (Sikorsky), - BK 117 (EUROCOPTER). Maintenance concept The main aspects of the maintenance concept are: - Effective modularity - Good accessibility - Reduced removal and installation times - "On-condition" monitoring - Long TBO, right from initial introduction into service - Low cost of ownership: • Low production costs • Durability (defined and proven TBO and life limits) • High reliability • Low fuel consumption. For training purposes only © Copyright - Turbomeca Training Edition: May 2014 2.16 POWER PLANT Training Notes 1st line maintenance course SQUIRREL (EUROCOPTER) Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) ARRIEL 1 REGA A 109 K2 (AGUSTA) DOLPHIN (EUROCOPTER) I-RAIE BK 117 (EUROCOPTER) MAINTENANCE CONCEPT - Effective modularity - Good accessibility - Reduced removal and installation times - "On-condition" monitoring - Long TBO, right from initial introduction into service - Low cost of ownership: • Low production costs • Durability (defined and proven TBO and life limits) • High reliability • Low fuel consumption. S 76 (SIKORSKY) APPLICATIONS DESIGN AND DEVELOPMENT For training purposes only © Copyright - Turbomeca Training Edition: May 2014 2.17 POWER PLANT ARRIEL 1 Training Notes 1st line maintenance course MAINTENANCE LEVELS Other aspects of maintenance Maintenance tasks are divided into 4 levels or "lines": Refer to the pages that follow. 1st line maintenance: on-line engine maintenance. Note 1: LRU - Line Replaceable Unit SRU - Shop Replaceable Unit. - Scheduled and preventive maintenance • Checks and inspections • Removals due to completed TBO or life limits - Corrective maintenance • Failure detection • Replacement of LRUs • Checks. 2nd line maintenance: workshop engine maintenance. - Corrective maintenance: removal and installation of modules and SRUs. Note 2: The maintenance levels are determined by the operator taking into account material difficulties, the personnel and logistical considerations. As far as the engine manufacturer is concerned, the so-called routine maintenance procedures (1st and 2nd line) are defined and described in the Maintenance Manual. Deep maintenance (3rd line) and overhaul (4th line) are described in other documents and are subject to specific licence agreements. 3rd line maintenance: deep maintenance which involves module repairs. - Corrective maintenance: replacement of parts. 4th line maintenance: overhaul and repair in a specialist workshop. - Scheduled maintenance performed at the end of the TBO or to replace parts which have reached their life limit. - Corrective maintenance. For training purposes only © Copyright - Turbomeca Training Edition: May 2014 2.18 POWER PLANT Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) MAINTENANCE Training Notes 1st line maintenance course MAINTENANCE LEVELS 1ST LINE MAINTENANCE - Scheduled or preventive maintenance - Corrective maintenance (LRUs) 2ND LINE MAINTENANCE - Corrective maintenance (modules, SRUs) Maintenance Manual (Operator or Service Centre or Maintenance Centre) 3RD LINE MAINTENANCE - Deep maintenance - Corrective maintenance (parts) 4TH LINE MAINTENANCE - Scheduled maintenance (overhaul, repair in a specialist workshop) - Corrective maintenance Maintenance Technical Instructions (Operator or Maintenance Centre) Overhaul Manual (Repair Centre) MAINTENANCE LEVELS MAINTENANCE For training purposes only © Copyright - Turbomeca Training Edition: May 2014 2.19 POWER PLANT Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) ARRIEL 1 ARRIEL 1 Training Notes 1st line maintenance course MAINTENANCE LIFE LIMITATIONS TBOs (Times Between Overhauls) are defined for the engine, the modules and certain accessories. These TBOs, which are determined on the basis of tests and experience, are subject to an extension programme. Counting of hours and cycles The counting of hours relates to flight hours and is performed either manually or automatically. TBOs are expressed in flight hours. Life limits Certain components (mainly rotating parts such as compressors, turbines, etc.) have a life limit which requires them to be scrapped when the limit is reached. Life limits are expressed in operating cycles (C1 or C2 cycles). Calendar limits A calendar limit is the time (expressed in years) after which an engine, module or accessory subject to a calendar limit has to be returned to the factory or an approved repair centre. The calendar limit begins when the engine, module or accessory concerned first enters into service after installation on the airframe (following manufacture, overhaul or repair). If an engine, module or accessory is put into storage, the calendar limit continues to run. A cycle is a clearly defined operating sequence. Cycles are counted either manually or automatically. The method for counting cycles and the various limits are described in chapter 05 of the Maintenance Manual. A counting-check procedure (comparison between automatic counting and manual counting) is carried out as part of periodic maintenance. A quick intermediate check can be carried out by comparing the two engines' counters for a given period of operation. On-condition monitoring Some components have no TBO, life limit or calendar limit. They are generally considered to be "on-condition" components. Use-limited parts These parts have a maximum usage time defined in hours and/or cycles and include parts such as bearings, casings and shafts. For training purposes only © Copyright - Turbomeca Training Edition: May 2014 2.20 POWER PLANT Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) TBOs Their limits are greater than the normal engine TBO, thus permitting them to be used over two or more TBOs, which reduces overhaul costs for the customer. These parts and their corresponding limits are listed in the engine log book and in chapter 05 of the Maintenance Manual. ARRIEL 1 - Engine - Modules - Accessories COUNTING OF HOURS AND CYCLES - Manual counting - Automatic counting - Counting-check procedure ON-CONDITION MONITORING Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) TBOs Training Notes 1st line maintenance course Some components have no TBO, life limit or calendar limit. They are generally considered to be "on-condition" components LIFE LIMITS USE-LIMITED PARTS Cycles for: - Compressors - Turbines - Etc. Maximum usage time: - Defined in hours and/or cycles - Greater than the normal engine TBO Can be used over two or more TBOs, which reduces overhaul costs CALENDAR LIMITS Time limits (since manufacture, overhaul or repair): - Engine - Modules - Accessories N1 and N2 cycle displays according to variant Cycle counter according to variant LIFE LIMITATIONS MAINTENANCE For training purposes only © Copyright - Turbomeca Training Edition: May 2014 2.21 POWER PLANT ARRIEL 1 Training Notes 1st line maintenance course MAINTENANCE Preventive maintenance is a programme of scheduled inspections aimed at preventing failures from occurring. They are defined in chapter 05 of the Maintenance Manual. It includes two inspection types. - Borescopic inspection: this permits inspection of internal parts which are otherwise not accessible without disassembly - Lubrication oil check: various methods are used to check for the contamination of the oil (magnetic plugs, strainers, sampling). Samples of oil are taken at regular intervals and the samples are analysed to measure the contamination, determine which component is failing and anticipate potential failures (analysis by magnetic-particle inspection, ferrography, spectrometric oil analysis) Servicing inspections (except 1E2) - Examples of inspections/checks carried out Inspection "after the last flight of the day" Inspection "before the first flight of the day" "Pre-flight" inspections "Post-flight" inspections. Servicing inspections (1E2) - Vibration level check: the vibration level of the rotating assemblies gives an indication of the engine's condition - Inspection before the first flight of the day - Inspection between two flights - Inspection after 15 flight hours or 7 days. - Power check: this is carried out by the pilot (refer to the Flight Manual) Periodic inspections - These procedures can be "blocked" (at fixed intervals for all the procedures) or staggered (each procedure is distributed over a period of time to reduce the turnaround time while still respecting the intervals) - Visits are scheduled as a function of flight hours (e.g.: every 500 hours) or calendar (e.g.: 2 years) - Special inspections (particular inspections et inspections according to airworthiness). - Visual inspections: direct visual inspections can also be carried out for "on-condition" monitoring. CORRECTIVE MAINTENANCE The aim of corrective maintenance is to put the engine back into normal service as soon as possible. Corrective maintenance includes all procedures which must be carried out when required (in the event of a failure, anomaly, etc.) and which are defined in chapter 71 of the Maintenance Manual. If an engine, module or accessory is put into storage, this calendar period is suspended. For training purposes only © Copyright - Turbomeca Training Edition: May 2014 2.22 POWER PLANT Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) PREVENTIVE MAINTENANCE Training Notes 1st line maintenance course ARRIEL 1 PREVENTIVE MAINTENANCE Servicing inspections / Scheduled inspections EXAMPLE OF MAIN INSPECTION POINTS - Visual checks Inspection of filters Inspection of magnetic plugs Oil sampling (for analysis) Oil level (and replenishment if required) Compressor cleaning (depending on operating conditions) - Ground run test - ... CORRECTIVE MAINTENANCE (refer to MM, chapter 71) To put the engine back into normal service as soon as possible LUBRICATION OIL CHECK VIBRATION LEVEL CHECK BORESCOPIC INSPECTION DIRECT VISUAL INSPECTIONS EXAMPLE OF MAIN TASKS - Troubleshooting Run-down time check Functional and condition checks Removal and installation Adjustments Miscellaneous procedures (cleaning, storage ...) Repairs (or replacements) Particular instructions FLI GH TM AN UA L POWER CHECK PREVENTIVE AND CORRECTIVE MAINTENANCE MAINTENANCE For training purposes only © Copyright - Turbomeca Training Edition: May 2014 2.23 POWER PLANT Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) (refer to MM, chapter 05) ARRIEL 1 Training Notes 1st line maintenance course TECHNICAL PUBLICATIONS - PRESENTATION Identification documents This section describes engine technical documentation used in 1st and 2nd line maintenance. - Maintenance Spare Parts Catalogue: contains the designations and references of the spare parts that may be required for maintenance on a particular engine variant Maintenance documents - Maintenance Manual: describes the engine, its systems and all the maintenance procedures. The "standard practices" used in 1st and 2nd line maintenance are described in chapter 70. They include for example tightening torques, thread inserts, electrical connectors, locking of assemblies, etc. - Service Bulletins: approved by the Authorities and issued to inform operators of a modification or instruction which affects operational aspects - Service Letters: sent to inform operators of certain measures relating to engine operation - Modification Index: lists all the modifications relating to a particular engine variant - Troubleshooting Book: forms the last volume (chapter 71-00-06) of the Maintenance Manual. It includes: • A list of failures observed during use • A list of failures observed during maintenance • A list of failure codes and their interpretation • A list of troubleshooting tasks. For training purposes only © Copyright - Turbomeca Training - Maintenance Tools Catalogue: contains the designations and references of the tools that may be required for maintenance on a particular engine variant. Operation documents - Engine Log Book: records and provides information on the engine status - Flight Manual: is the pilot’s basic reference document and specifies the limitations, the normal and emergency procedures, and the performance data. It is subject to approval by the Airworthiness Authorities. Electronic documentation - IETP (Interactive Electronic Technical Publication): this is an electronic version of the maintenance documentation - TOOLS: this is a website-based service which provides updates of technical publications such as Service Bulletins, Service Letters, Maintenance Manuals, etc. Each time an update is issued, subscribers to the service are immediately notified and sent a copy of the update by e-mail. Edition: May 2014 2.24 POWER PLANT Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) MAINTENANCE Training Notes 1st line maintenance course ARRIEL 1 IDENTIFICATION ARRIEL ARRIEL ARRIEL ARRIEL ARRIEL ARRIEL ARRIEL MAINTENANCE MANUAL MAINTENANCE MANUAL SERVICE BULLETINS SERVICE LETTERS MODIFICATION INDEX MAINTENANCE SPARE PARTS CATALOGUE MAINTENANCE TOOLS CATALOGUE 1 1 1 1 1 1 TYPICAL BREAKDOWN OF A MAINTENANCE MANUAL ARRIEL 1 MAINTENANCE MANUAL CHAP DESIGNATION 00 05 Introduction Time Limits / Maintenance Checks Servicing Fire Protection Standard Practices Power Plant Engine - Turbine Engine Fuel and Control Ignition Air Engine Controls Engine Indicating Exhaust Oil Starting Accessory Gearboxes 12 26 70 71 72 73 74 75 76 77 78 79 80 83 CHAP. 71-00-06 TROUBLESHOOTING Failures observed during use Failures observed during maintenance Troubleshooting tasks 1 OPERATION ENGINE LOG BOOK (compiled according to the "ATA 100" standard) FLI GH TM AN UA L ELECTRONIC MAINTENANCE TECHNICAL PUBLICATION TECHNICAL PUBLICATIONS - PRESENTATION MAINTENANCE For training purposes only © Copyright - Turbomeca Training Edition: May 2014 2.25 POWER PLANT Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) MAINTENANCE ARRIEL 1 Training Notes 1st line maintenance course MAINTENANCE Three types of advisory notice are used in the technical publications: - WARNING Examples WARNING: do not breathe oil vapours. Do not leave oil in contact with the skin. CAUTION: if the flush is being carried out because of metal particles in the oil system, change the filter and clean the tank thoroughly. - CAUTION - NOTE. NOTE: take the oil sample before carrying out any replenishment. Interpretation WARNING: warns the reader of the possibility of physical harm (e.g. injury, intoxication, electrocution). CAUTION: warns the reader of the possibility of damaging the engine or tooling. NOTE: gives the reader advice on how best to carry out a task. For training purposes only © Copyright - Turbomeca Training Edition: May 2014 2.26 POWER PLANT Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) TECHNICAL PUBLICATIONS - ADVISORY NOTICES Training Notes 1st line maintenance course WARNING (possibility of physical harm) CAUTION (possibility of damage) NOTE (advice) Examples: Examples: Examples: - Toxicity of engine oil and vapours Toxicity of cleaning products Toxicity of extinguishing products Eye protection Fire risk Electrical discharge from ignition units: - electrocution - risks involved with use in an inflammable atmosphere - …… - Cleaning of titanium parts Scrapping of O-ring seals Use of the correct cleaning products Engine cooling Engine cleaning after using extinguishing product Protection of orifices during disassembly Fragility of borescopes Torque-tightening …… - Spectrometric oil analysis Cycle counting Installation of O-ring seals Engine storage Isolation measures Procedural changes before or after modifications - …… TECHNICAL PUBLICATIONS - ADVISORY NOTICES MAINTENANCE For training purposes only © Copyright - Turbomeca Training Edition: May 2014 2.27 POWER PLANT Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) ARRIEL 1 ARRIEL 1 Training Notes 1st line maintenance course MAINTENANCE The International Civil Aviation Organisation (ICAO) requires that States establish a safety programme to achieve an acceptable level of safety in aviation operations. Therefore, States shall in turn require that individual operators, maintenance organisations, ATS providers and certified aerodrome operators implement a Safety Management System (SMS) that is approved by the State concerned. The ICAO provides a Safety Management Manual (SMM) which explains the implementation of an SMS (see below for details). HUMAN FACTORS The European Aviation Safety Agency (EASA) requires that aviation maintenance personnel receive training on Human Factors (HF). Such personnel must therefore have initial HF training, followed by regular refresher training. The ICAO SHEL(L) model below is a conceptual model representing the different components involved in human factors, and is intended as a basic aid to understanding HF: For training purposes only © Copyright - Turbomeca Training Software - The rules, procedures, written documents, etc., which are part of standard procedures Hardware - Tools, equipment, workshops, hangars Environment - The situation in which the SHEL(L) system must function, the social and economic climate as well as the natural environment Liveware - Human beings (engineers, technicians, aircrew, managers and administrative personnel) The edges of the blocks representing these components are not simple and straight because each component has to be adapted to the others. When considering HF, all the interfaces have to be taken into account: - Liveware - Software - Liveware - Hardware - Liveware - Environment - Liveware - Liveware Depending on the persons concerned, EASA Part 145 recommends 1 to 3 days' initial training on HF, and further training every 2 years. Edition: May 2014 2.28 POWER PLANT Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) SAFETY MANAGEMENT Training Notes 1st line maintenance course SOFTWARE Safety Management Manual (SMM) HARDWARE LIVEWARE LIVEWARE Safety Management System (SMS) ENVIRONMENT SAFETY OF AVIATION OPERATIONS Software Hardware Environment Liveware SAFETY MANAGEMENT HUMAN FACTORS SAFETY MANAGEMENT - HUMAN FACTORS MAINTENANCE For training purposes only © Copyright - Turbomeca Training Edition: May 2014 2.29 POWER PLANT Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) ARRIEL 1 Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) ARRIEL 1 Training Notes 1st line maintenance course Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) 3 - ENGINE - Engine - Presentation ........................................................................... 3.2 - Axial compressor .................................................................................. 3.6 - Centrifugal compressor ....................................................................... 3.8 - Combustion chamber ........................................................................... 3.10 - Gas generator turbine .......................................................................... 3.12 - Power turbine ........................................................................................ 3.14 - Exhaust system ..................................................................................... 3.16 - Reduction gearbox ............................................................................... 3.18 - Transmission shaft and accessory gearbox ...................................... 3.20 - Engine - Operation ................................................................................ 3.32 - Engine - 1st line maintenance ............................................................. 3.34 - 3.39 For training purposes only © Copyright - Turbomeca Training Edition: May 2014 3.1 ENGINE ARRIEL 1 Training Notes 1st line maintenance course ENGINE - PRESENTATION Main components Function The engine transforms the energy contained in the fuel and air into mechanical power on a shaft. Main characteristics - Type: free-turbine turboshaft engine with forward power drive via an external shaft - Gas generator • Axial compressor • Centrifugal compressor • Combustion chamber • Gas generator turbine Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) GENERAL - Power turbine - Exhaust pipe - Gas generator: • Speed: 52000 rpm (at 100% N1) • Direction of rotation: anti-clockwise (ACW) - Reduction gearbox - Power turbine: • Speed: 41600 rpm (at 100% N2) • Direction of rotation: anti-clockwise (ACW) - Accessory gearbox. - Transmission shaft - Output shaft: • Speed: 6000 rpm (at 100% N2) • Direction of rotation: clockwise (CW). Note: Direction of rotation given viewed from the rear. For training purposes only © Copyright - Turbomeca Training Edition: May 2014 3.2 ENGINE Training Notes 1st line maintenance course ARRIEL 1 Axial compressor Centrifugal compressor Combustion chamber Gas generator turbine POWER TURBINE EXHAUST PIPE Type : Free-turbine turboshaft engine with forward power drive via an external shaft Gas generator: 52000 rpm (at 100% N1); ACW Power turbine: 41600 rpm (at 100% N2); CW Output shaft: 6000 rpm (at 100% N2); CW ACCESSORY GEARBOX TRANSMISSION SHAFT REDUCTION GEARBOX GENERAL ENGINE - PRESENTATION For training purposes only © Copyright - Turbomeca Training Edition: May 2014 3.3 ENGINE Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) GAS GENERATOR ARRIEL 1 Training Notes 1st line maintenance course ENGINE - PRESENTATION Note 1: A module is a sub-assembly which can be replaced in a workshop (2nd line maintenance) without complex tooling or adaptation work. Modular design The engine is made up of 5 modules: Each module has its own identification plate. The overall engine identification plate is fitted on the righthand side of the module M01 protection tube. - Module M01: Transmission shaft and accessory gearbox - Module M02: Axial compressor - Module M03: Gas generator HP section Note 2: A number of accessories are linked to each module. - Module M04: Power turbine In these Training Notes, the accessories are dealt with in the chapters corresponding to the main systems concerned. - Module M05: Reduction gearbox. For training purposes only © Copyright - Turbomeca Training Edition: May 2014 3.4 ENGINE Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) DESCRIPTION Training Notes 1st line maintenance course MODULE M02 Axial compressor MODULE M03 Gas generator HP section MODULE M04 Power turbine MODULE M05 Reduction gearbox MODULES IDENTIFICATION PLATES MODULE M01 Transmission shaft and accessory gearbox External identification plate ENGINE IDENTIFICATION PLATE DESCRIPTION ENGINE - PRESENTATION For training purposes only © Copyright - Turbomeca Training Edition: May 2014 3.5 ENGINE Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) ARRIEL 1 ARRIEL 1 Training Notes 1st line maintenance course AXIAL COMPRESSOR Function - Stationary components: • Diffuser • Casing. The axial compressor ensures a first stage of compression to supercharge the centrifugal compressor. Functional description Position The axial compressor ensures a first stage of compression in order to supercharge the centrifugal compressor. - At the front of the engine (the axial compressor assembly forms the module M02). Compressor airflow Main characteristics - Type: axial supercharging compressor - Airflow: 2.5 kg/sec (5.5 lb/sec.) The ambient air, admitted through the air intake duct and guided by the inlet cone, flows between the blades of the axial compressor wheel. The air is discharged rearwards with an increased axial velocity. - Wheel made of titanium, cut from the solid. The air then flows through the vanes of the diffuser. Due to the divergent passage, the air velocity decreases and the pressure increases. Main components The flow is straightened by the stator vanes before being admitted, through an annular duct, to the centrifugal compressor. - Rotating components: • Air inlet cone • Axial wheel • Shaft • Bearing • Accessory drive shaft Note: In order to avoid compressor surge, a valve discharges overboard a certain amount of air in certain operating conditions. - Rotation speed: N1; ACW For training purposes only © Copyright - Turbomeca Training Edition: May 2014 3.6 ENGINE Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) PRESENTATION Training Notes 1st line maintenance course Type: Axial supercharging compressor Airflow: 2.5 kg/s (5.5 lb/sec.) P1': AIR DISCHARGED THROUGH THE COMPRESSOR BLEED VALVE Rotation speed: N1; ACW WHEEL DIFFUSER Wheel made of titanium, cut from the solid SHAFT COMPRESSION AND STRAIGHTENING OF THE AIR ACCELERATION OF THE AIR ADMISSION OF AMBIENT AIR AIR INLET CONE BEARING CASING ACCESSORY DRIVE SHAFT SUPERCHARGING OF THE CENTRIFUGAL COMPRESSOR PRESENTATION AXIAL COMPRESSOR For training purposes only © Copyright - Turbomeca Training Edition: May 2014 3.7 ENGINE Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) ARRIEL 1 ARRIEL 1 Training Notes 1st line maintenance course CENTRIFUGAL COMPRESSOR Function - Stationary components: • Diffusers • Casings. The compressor supplies the compressed air required for combustion. Functional description Supercharged by the axial compressor, it ensures the second stage of compression. The centrifugal compressor ensures the main stage of compression. Position Compressor airflow - At the front of the module M03. The air supplied by the axial compressor flows between the blades of the centrifugal compressor. The air pressure increases due to the divergent passage between the blades and the air velocity increases due to the centrifugal flow. Main characteristics - Type: centrifugal, high efficiency - Airflow: 2.5 kg/s (5.5 lb/sec.) - Compression ratio: 5.4/1 (global: 8.2/1) - Rotation speed: N1; ACW - Wheel made of titanium, cut from the solid. The air leaves the tips of the blades at very high velocity and then flows through the 1st stage diffuser vanes where the velocity is decreased and the pressure is increased. The air then passes through an elbow and the flow becomes axial. In the 2nd stage diffuser, the velocity is again decreased and the pressure increased. The air is then admitted into the combustion chamber. Main components - Rotating components: • Wheel • Shaft • Bearing For training purposes only © Copyright - Turbomeca Training Edition: May 2014 3.8 ENGINE Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) PRESENTATION Training Notes 1st line maintenance course ARRIEL 1 Airflow: 2.5 kg/s (5.5 lb/sec.) DIFFUSERS CASINGS BEARING Compression ratio: 5.4/1 (global: 8.2/1) Rotation speed: N1; ACW Wheel made of titanium, cut from the solid SUPERCHARGING BY THE AXIAL COMPRESSOR COMPRESSION OF THE AIR IN THE DIFFUSER STAGES AIR ADMITTED INTO THE COMBUSTION CHAMBER ACCELERATION AND COMPRESSION OF THE AIR CENTRIFUGAL WHEEL PRESENTATION CENTRIFUGAL COMPRESSOR For training purposes only © Copyright - Turbomeca Training Edition: May 2014 3.9 ENGINE Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) Type: Centrifugal, high efficiency ARRIEL 1 Training Notes 1st line maintenance course PRESENTATION Combustion chamber flow Function In the combustion chamber, the compressed air is divided into two flows: a primary air flow mixed with the fuel for combustion and a secondary air flow (or dilution air flow) for cooling of the gas. The combustion chamber forms an enclosure in which the air/ fuel mixture is burnt. Position - Central section of the gas generator. A second part flows through the hollow vanes of the turbine nozzle guide vane (cooling of the vanes) and through the orifices of the rear swirl plate. Main characteristics - Type: annular with centrifugal fuel injection The primary air is mixed with the fuel sprayed by the injection wheel. The combustion occurs between the two swirl plates. The flame temperature reaches approx. 2500°C (4532°F). - Made of special alloy Main components - Secondary air: the secondary air (or dilution air) flows through the orifices of the mixer unit and the dilution tubes. It is calibrated to obtain flame stability, cooling of the gas, and distribution of temperature on the turbine. - Outer part: • Front swirl plate • Mixer unit - Gas: The gas produced by the combustion is directed into the turbine nozzle guide vane. - Inner part: • Rear swirl plate • Shroud - Drain: a combustion chamber drain valve, fitted on a flange on the bottom of the turbine casing drains overboard any residual fuel. - Fuel injection system - Turbine casing Operating parameters - Combustion chamber drain valve. Functional description The combustion chamber forms an enclosure in which the fuel/ air mixture is burnt. For training purposes only © Copyright - Turbomeca Training - Primary air: one part flows through the orifices of the front swirl plate. The fuel/air ratio for combustion (primary air) is approximately 1/15; the total fuel/air ratio is approximately 1/45. The pressure drop in the combustion chamber is approximately 4%. Edition: May 2014 3.10 ENGINE Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) COMBUSTION CHAMBER Training Notes 1st line maintenance course Type: Annular with centrifugal fuel injection Primary air (combustion) Secondary air (dilution + cooling) Made of special alloy OUTER PART Front swirl plate Mixer unit Gases INNER PART Rear swirl plate COMPRESSED AIR Shroud FUEL INJECTION SYSTEM Combustion chamber drain valve Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) ARRIEL 1 TURBINE CASING FUEL INJECTION GAS FLOW TO THE TURBINE COMBUSTION (2500°C / 4532°F) PRESENTATION COMBUSTION CHAMBER For training purposes only © Copyright - Turbomeca Training Edition: May 2014 3.11 ENGINE ARRIEL 1 Training Notes 1st line maintenance course PRESENTATION Functional description Function The gas generator turbine transforms the kinetic energy contained in the burnt gases into mechanical power to drive the compressors and accessories. The turbine extracts sufficient energy from the gas flow to drive the compressors and the accessories. Position The operation is characterised by the first phase of expansion. Turbine gas flow - At the rear of the gas generator. The gas first flows through the nozzle guide vanes. The gas velocity increases due to the convergent passage. Main characteristics The flow on the blades results in aerodynamic forces whose resultant causes the rotation of the wheel. - Type: axial, two stages - Rotation speed: N1; ACW - Turbine inlet temperature: approx. 1100°C (2012°F) according to engine version The gas, still containing energy, is directed to the power turbine. - Made of special alloy. Main components - Rotating components: • Wheels • Shafts • Bearing - Stationary components: • Nozzle guide vanes • Containment shield • Casing. For training purposes only © Copyright - Turbomeca Training Edition: May 2014 3.12 ENGINE Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) GAS GENERATOR TURBINE Training Notes 1st line maintenance course ARRIEL 1 Rotation Rotation speed: N1; ACW NOZZLE GUIDE VANES WHEELS Turbine inlet temperature: Approx. 1100°C (2012°F) according to engine version Made of special alloy BEARING NOZZLE GUIDE VANES (convergent passage) Nozzle guide vane Turbine wheel GAS TO THE POWER TURBINE GAS FROM THE COMBUSTION CHAMBER COMPRESSOR DRIVE axial, two stages CONTAINMENT SHIELD CASING SHAFTS ROTATION PRESENTATION GAS GENERATOR TURBINE For training purposes only © Copyright - Turbomeca Training Edition: May 2014 3.13 ENGINE Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) Type: Axial, two stages ARRIEL 1 Training Notes 1st line maintenance course PRESENTATION Functional description Function The power turbine transforms the gas energy into mechanical power to drive the reduction gearbox. The turbine extracts the energy from the gas to drive the power shaft through the reduction gearbox. The operation is characterised by the second phase of expansion. Position Turbine flow - Between the gas generator and the reduction gearbox. The gases supplied by the gas generator flow through the nozzle guide vane. In the nozzle guide vane, the gas velocity increases due to the convergent passage. It forms the module M04. Main characteristics - Type: axial, single stage - Rotation speed: N2; CW The gases are directed onto the turbine wheel and the resultant of the aerodynamic forces on the blades causes the wheel to rotate. The gases are then discharged overboard through the exhaust pipe. - Made of special alloy Main components - Rotating components: • Wheel • Shaft • Bearings - Stationary components: • Nozzle guide vane • Containment shield • Casing. For training purposes only © Copyright - Turbomeca Training Edition: May 2014 3.14 ENGINE Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) POWER TURBINE Training Notes 1st line maintenance course ARRIEL 1 Rotation speed: N2; CW NOZZLE GUIDE VANE WHEEL BEARINGS Made of special alloy ROTATION OF THE POWER TURBINE WHEEL Rotation Nozzle guide vane Turbine wheel REDUCTION GEARBOX DRIVE (CW) GAS FROM THE GAS GENERATOR TURBINE EXPANSION IN THE NOZZLE GUIDE VANE CONTAINMENT SHIELD POWER TURBINE CASING SHAFT DISCHARGE OF GASES OVERBOARD PRESENTATION POWER TURBINE For training purposes only © Copyright - Turbomeca Training Edition: May 2014 3.15 ENGINE Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) Type: Axial, single stage ARRIEL 1 Training Notes 1st line maintenance course Function Functional description The exhaust system continues the expansion phase and expels the gas overboard. The exhaust pipe, which has an elliptical outlet, is made from stainless steel. It is bolted to the rear flange of the power turbine casing with the containment shield. Position A heat shield is fitted between the exhaust pipe and the reduction gearbox to protect the gearbox from the exhaust heat. - Behind the power turbine, around the reduction gear. The exhaust pipe has a drain at the bottom. Main characteristics Functionally it should be noted that the exhaust gas still contains a certain amount of energy which produces a small residual thrust. - Type: elliptical - Non-modular assembly - Gas temperature: 600°C (1080°F) - Made of stainless steel. Main components - Exhaust pipe - Heat shield. Note: The exhaust pipe is considered to be an SRU. (Shop Replaceable Unit) For training purposes only © Copyright - Turbomeca Training Edition: May 2014 3.16 ENGINE Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) EXHAUST SYSTEM Training Notes 1st line maintenance course ARRIEL 1 EXHAUST PIPE EXHAUST PIPE Non-modular assembly HEAT SHIELD Gas temperature: 600°C (1080°F) Reduction gearbox Made of stainless steel HEAT SHIELD EXHAUST GAS HEAT SHIELD EXHAUST PIPE REDUCTION GEARBOX EXHAUST SYSTEM For training purposes only © Copyright - Turbomeca Training Edition: May 2014 GAS FROM THE POWER TURBINE 3.17 ENGINE Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) Type: Elliptical ARRIEL 1 Training Notes 1st line maintenance course REDUCTION GEARBOX Functional description - The reduction gear provides a forward output drive at a reduced speed Function The reduction gearbox provides a reduced speed output and transmits the drive forwards. - The drive gear is directly driven by the power turbine shaft (muff coupling drive). It transmits the movement to the intermediate gear Position - The intermediate gear drives the output gear which provides the power drive. - At the rear of the engine - It forms the module M05. Main characteristics - Type: 3 stages, helical gears - Drive gear speed: N2 - Output gear speed: 6000 rpm (except 1S1); CW. - Gears made of steel Main components - Drive gear - Intermediate gear - Fork shaped plates - Output gear - Casings - Hydraulic torquemeter. For training purposes only © Copyright - Turbomeca Training Edition: May 2014 3.18 ENGINE Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) PRESENTATION Training Notes 1st line maintenance course 2 FORK SHAPED PLATES MUFF COUPLING DRIVE GEAR INTERMEDIATE GEAR INTERMEDIATE GEAR N2 DRIVE GEAR HYDRAULIC TORQUEMETER Type: 3 stages, helical gears 100% N2, CW OUTPUT GEAR Drive gear speed: N2 OUTPUT GEAR Output gear speed: 6000 rpm (except 1S1) Gears made of steel CASINGS PRESENTATION REDUCTION GEARBOX For training purposes only © Copyright - Turbomeca Training Edition: May 2014 3.19 ENGINE Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) ARRIEL 1 ARRIEL 1 Training Notes 1st line maintenance course TRANSMISSION SHAFT AND ACCESSORY GEARBOX Driven accessories - Starter-generator Function - Breather The shaft transmits the power to the helicopter via the power off-take at the front of the engine. - N2 tachometer generator The accessory gearbox provides the drive for the engine accessories. - Oil pump Position Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) GENERAL - N1 governor - N2 tachometer generator - N2 governor. - Shaft beneath the engine - Accessory gearbox at the front of the engine - This assembly forms the module M01. Main characteristics - Type of gears: • spur gear • bevel gear. Main components - Accessory drive shaft - Accessory drive train - Casings. For training purposes only © Copyright - Turbomeca Training Edition: May 2014 3.20 ENGINE Training Notes 1st line maintenance course ACCESSORY DRIVE SHAFT (N1) Type of gears: Spur gear Bevel gear FRONT CASING STARTER-GENERATOR DRIVE GEAR BREATHER GEAR ACCESSORY DRIVE SHAFT REAR CASING ACCESSORY DRIVE TRAIN N1 TACHOMETER GENERATOR N1 GOVERNOR AND OIL PUMP TRANSMISSION SHAFT GEAR POWER OFF-TAKE N2 GOVERNOR AND N2 TACHOMETER GENERATOR ACCESSORY DRIVE GEAR (N2) TRANSMISSION SHAFT GENERAL TRANSMISSION SHAFT AND ACCESSORY GEARBOX For training purposes only © Copyright - Turbomeca Training Edition: May 2014 3.21 ENGINE Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) ARRIEL 1 ARRIEL 1 Training Notes 1st line maintenance course TRANSMISSION SHAFT - TWIN-ENGINE CONFIGURATION Function Description The shaft transmits the power to the power off-take and accessory gearbox. The shaft is located in a protection tube bolted to the reduction gearbox at the rear and to the accessory gearbox at the front. - Lower part of the engine. The front of the shaft is supported by a ball bearing in the accessory gearbox front casing. The triangular flange which forms the power off-take is splined onto the front of the transmission shaft and is secured by a nut. Sealing of the oil which lubricates the bearing is ensured by a magnetic carbon seal. Main characteristics Three oil tubes are located between the shaft and the protection tube. The shaft transmits the power to the front power off-take. Position Hollow steel shaft. The rear of the shaft is splined into the hub of the output gear of the reduction gear. Main components - Transmission shaft - Protection tube - Accessory drive gear - Power off-take. For training purposes only © Copyright - Turbomeca Training Edition: May 2014 3.22 ENGINE Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) TRANSMISSION SHAFT AND ACCESSORY GEARBOX Training Notes 1st line maintenance course SHAFT POWER OFF-TAKE (triangular flange) Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) ARRIEL 1 OUTPUT GEAR ACCESSORY DRIVE GEAR MAGNETIC CARBON SEAL OIL TUBE PROTECTION TUBE FRONT PART REAR PART TRANSMISSION SHAFT - TWIN-ENGINE CONFIGURATION TRANSMISSION SHAFT AND ACCESSORY GEARBOX For training purposes only © Copyright - Turbomeca Training Edition: May 2014 3.23 ENGINE Training Notes 1st line maintenance course TRANSMISSION SHAFT AND ACCESSORY GEARBOX Three oil pipes are located within the protection tube. TRANSMISSION SHAFT - SINGLE ENGINE CONFIGURATION A free wheel is mounted on the triangular flange to drive the power drive shaft which drives the main gearbox and the tail rotor. Function The shaft transmits the power to the front and to the rear of the engine. Position: Lubrication of the free wheel and its bearing is by the oil contained in the free wheel housing, or by the oil system of the engine, according to the version. The rear of the transmission shaft is splined into the hub of the output gear of the reduction gear. The rear of the tail rotor drive shaft is supported by a ball bearing in the hub of the output gear. A magnetic carbon seal is fitted in the rear cover of the gearbox. - Lower part of the engine. Main characteristics Note: In single-engine configuration the free wheel and transmission shaft front magnetic carbon seal can be replaced in 1st line maintenance. - Hollow steel shaft with coaxial drive shaft. Description The shaft transmits the power to the power drive shaft. The transmission shaft is located in a protection tube bolted to the reduction gearbox at the rear and to the accessory gearbox at the front. The front of the transmission shaft is supported by a ball bearing in the accessory gearbox front casing. A triangular flange is splined onto the front of the transmission shaft. Sealing of the oil which lubricates the bearing is ensured by a magnetic carbon seal. For training purposes only © Copyright - Turbomeca Training Edition: May 2014 3.24 ENGINE Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) ARRIEL 1 Training Notes 1st line maintenance course SEAL TRIANGULAR FLANGE TAIL ROTOR DRIVE SHAFT ACCESSORY DRIVE GEAR POWER DRIVE SHAFT FREE WHEEL MAGNETIC CARBON SEAL MAGNETIC CARBON SEAL OIL TUBE FRONT PART REAR PART TRANSMISSION SHAFT - SINGLE ENGINE CONFIGURATION TRANSMISSION SHAFT AND ACCESSORY GEARBOX For training purposes only © Copyright - Turbomeca Training Edition: May 2014 3.25 ENGINE Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) ARRIEL 1 ARRIEL 1 Training Notes 1st line maintenance course TRANSMISSION SHAFT AND ACCESSORY GEARBOX Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) ACCESSORY GEARBOX - DESCRIPTION (1) The accessory gearbox has four drives on the front face: • starter-generator (equipped with a magnetic carbon seal on each side) • fuel control unit N1 • fuel control unit N2 • power and mounting bolts on the upper part for attachment of the M02. It has 3 power drives on the rear face: • oil pump • N1 tachometer generator • N2 tachometer generator and the protection tube mounting flange, and the accessory drive shaft passage on the upper part. For training purposes only © Copyright - Turbomeca Training Edition: May 2014 3.26 ENGINE Training Notes 1st line maintenance course MOUNTING BOLTS MAGNETIC CARBON SEALS ACCESSORY DRIVE SHAFT PASSAGE (N1) N1 TACHOMETER GENERATOR FUEL CONTROL UNIT N1 DRIVE OIL PUMP STARTERGENERATOR DRIVE FUEL CONTROL UNIT N2 DRIVE POWER DRIVE PROTECTION TUBE MOUNTING FLANGE N2 TACHOMETER GENERATOR FRONT VIEW REAR VIEW ACCESSORY GEARBOX - DESCRIPTION (1) TRANSMISSION SHAFT AND ACCESSORY GEARBOX For training purposes only © Copyright - Turbomeca Training Edition: May 2014 3.27 ENGINE Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) ARRIEL 1 ARRIEL 1 Training Notes 1st line maintenance course TRANSMISSION SHAFT AND ACCESSORY GEARBOX Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) ACCESSORY GEARBOX - DESCRIPTION (2) The transmission shaft and the accessory box assembly constitutes the module M01 located at the engine lower part. The accessory gearbox includes a train of gears housed in a gearbox formed by two half casings made of light alloy. The gearbox is installed at the bottom of the axial compressor by means of four bolts. The starter-generator gear forms the engine breather. The fuel control unit N1 gear drives the oil pump at the rear. The fuel control unit N2 gear is driven by the gear on the transmission shaft. The module identification plate is fitted on the front face of the gearbox. Note: The engine front support casing is bolted onto the front face of the accessory gearbox (according to version). For training purposes only © Copyright - Turbomeca Training Edition: May 2014 3.28 ENGINE Training Notes 1st line maintenance course ARRIEL 1 REAR CASING DRIVE SHAFT (N1) N1 TACHOMETER GENERATOR TRANSMISSION SHAFT GEAR (N2) Starter-generator mounting flange N1 TACHOMETER GENERATOR N1 FUEL CONTROL UNIT AND OIL PUMP DRIVE N1 FUEL CONTROL UNIT AND OIL PUMP DRIVE OIL PUMPS Identification plate N2 FUEL CONTROL UNIT AND N2 TACHOMETER GENERATOR FRONT CASING N2 FUEL CONTROL UNIT N2 TACHOMETER GENERATOR ACCESSORY GEARBOX - DESCRIPTION (2) TRANSMISSION SHAFT AND ACCESSORY GEARBOX For training purposes only © Copyright - Turbomeca Training Edition: May 2014 3.29 ENGINE Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) STARTERGENERATOR / BREATHER GEAR ARRIEL 1 Training Notes 1st line maintenance course TRANSMISSION SHAFT AND ACCESSORY GEARBOX The operation is considered during engine starting and in normal running. The gas generator drives the accessory gear train through the bevel gear located on the axial compressor shaft. The following accessories are driven: Operation during engine starting During starting, the starter motor drives the accessory gearbox and thus the gas generator rotating assembly. The compressors supply air to the combustion chamber and the starting sequence continues. At self-sustaining speed the electrical supply to the starter motor is cut. The starter motor is then mechanically driven by the engine and operates as a generator to provide DC current to the aircraft electrical system. For training purposes only © Copyright - Turbomeca Training Normal running - Starter-generator - FCU: N1 and N2 - Oil pumps - Tachometer generator: N1 and N2. Edition: May 2014 3.30 ENGINE Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) ACCESSORY GEARBOX - OPERATION Training Notes 1st line maintenance course FWD STARTER MOTOR FWD DRIVE SHAFT DIRECT CURRENT GENERATOR DURING ENGINE STARTING Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) ARRIEL 1 DRIVE SHAFT NORMAL RUNNING (N1 ≥ self-sustaining speed) ACCESSORY GEARBOX - OPERATION TRANSMISSION SHAFT AND ACCESSORY GEARBOX For training purposes only © Copyright - Turbomeca Training Edition: May 2014 3.31 ENGINE ARRIEL 1 Training Notes 1st line maintenance course Engine operation can be broken down into the following phases: compression, combustion, expansion and power transmission. Expansion Compression During this phase, the pressure and temperature of the gases drop, whilst their velocity increases. The ambient air is compressed by a supercharging axial compressor and a centrifugal compressor. The gases expand through the gas generator turbine, which extracts the energy required to drive the compressors and accessories. This phase is essentially characterised by the airflow (approx. 2.5 kg/s; 5.5 lb/s), the increase in temperature and the compression ratio (approx. 8.2). There is a further phase of expansion through the power turbine, which extracts most of the remaining energy to drive the output shaft. Combustion After the power turbine, the gases are discharged overboard through the exhaust pipe, giving a slight forward residual thrust. The compressed air is admitted into the combustion chamber, mixed with the fuel and burnt in a continuous process. Power transmission The air is divided into two flows: The power is transmitted forwards by a reduction gearbox and an external transmission shaft. - A primary flow for combustion - A secondary flow for dilution and cooling of the gases. This phase is essentially characterised by an increase in temperature (flame temperature approx. 2500°C; 4532°F) and a drop in pressure of about 4%. For training purposes only © Copyright - Turbomeca Training Note: The engine reference stations are: 0 - Ambient air 1 - Axial compressor inlet 1' - Axial compressor outlet 2 - Centrifugal compressor outlet 3 - Gas generator turbine inlet 4 - Gas generator turbine outlet 5 - Power turbine outlet. Edition: May 2014 3.32 ENGINE Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) ENGINE - OPERATION Training Notes 1st line maintenance course Primary air (combustion) Secondary air (dilution + cooling) Gases Residual thrust EXHAUST AIRFLOW 2.5 kg/s (5.5 lb/s) Fuel 0 1 2 1' 2500 (4532) 3 1125 (2057) 880 (1616) 820 (118.9) 101.3 P kPa (14.7) (PSI) T°C (°F) V 15 (59) Air intake ADMISSION 160 (23.2) 800 (116) POWER TRANSMISSION 5 4 600 (1080) 300 (43.5) 320 (608) 108 (15.7) 65 (149) Values given for information at a given reference rating under ISA conditions Compressors Combustion chamber COMPRESSION COMBUSTION Turbines Exhaust EXPANSION ENGINE - OPERATION For training purposes only © Copyright - Turbomeca Training (power transmitted forwards by a reduction gearbox and an external transmission shaft) Edition: May 2014 3.33 ENGINE Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) ARRIEL 1 ARRIEL 1 Training Notes 1st line maintenance course ENGINE - 1ST LINE MAINTENANCE PREVENTIVE MAINTENANCE (1) Scheduled inspections List of maintenance tasks to be carried out: - Inspection before the first flight of the day - Turn-around inspection - Inspection after the last flight of the day - Inspection after 15 flight hours or 7 days Operations to be performed to comply with Airworthiness objectives are listed in the table of mandatory maintenance tasks. Manufacturer-required maintenance tasks The manufacturer considers that the manufacturer-required maintenance tasks must be carried out at the scheduled inspection frequency. Failure to do so may cause occurrences liable to affect the engine operating safety. - Inspection at 30 flight hours Optional maintenance tasks - Inspection at 50 flight hours Optional maintenance tasks are recommended by the manufacturer as a means of improving reliability, increasing operational availability and reducing operating costs. - Inspection at 100 flight hours - Inspection at 150 flight hours - Inspection at 200 flight hours - Inspection at 300 flight hours - Inspection at 400 flight hours - Inspection at 500 flight hours - Inspection at 600 flight hours - Inspection at 750 flight hours - Inspection at 1,000 flight hours - Inspection at 1,200 flight hours Note 1: Before carrying out any maintenance tasks, remember to refer to the latest Service Bulletins and Service Letters. Note 2: The maintenance tasks shown below concern the ARRIEL 1D1 variant by way of example and may differ for other ARRIEL 1 variants. Always refer to the Maintenance Manual of the variant concerned. - Inspection at 1,500 flight hours - Inspection at 3,000 flight hours - Inspection at 3,600 flight hours For training purposes only © Copyright - Turbomeca Training Edition: May 2014 3.34 ENGINE Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) Refer to the Maintenance Manual (chapter 05). Mandatory maintenance tasks Training Notes 1st line maintenance course ARRIEL 1 PREVENTIVE MAINTENANCE (scheduled inspections) INSPECTION AFTER THE LAST FLIGHT OF THE DAY MANDATORY Pre TU197 or pre TU202: - Make sure that there are no abnormal noises during gas generator rundown Note: during engine shut-down or after a ventilation for a maximum of 5 seconds - Manually check that the HP gas generator rotates freely (no abnormal noises) and visually check that the engine is in good condition Note: when T4 is below 150°C INSPECTION AT 50 FLIGHT HOURS MANUFACTURER-REQUIRED Check the axial compressor blades (significant impacts, blade distortion) Chap. 72 INSPECTION AT 100 FLIGHT HOURS MANUFACTURER-REQUIRED Pre TU215 or Pre TU254 or Pre TU255, Pre TU259: - Inspection and check of the Module 04 Free turbine Chap. 72 INSPECTION AT 150 FLIGHT HOURS INSPECTION AFTER 15 FLIGHT HOURS OR 7 DAYS MANUFACTURER-REQUIRED Inspection of the axial compressor wheel (impacts on the leading edge), free rotation of the rotating assembly, absence of abnormal noises (rub) MANUFACTURER-REQUIRED Check the axial compressor blades (significant impacts, blade distortion) OPTIONAL Pre TU244: - Inspection and check of the combustion chamber INSPECTION AT 30 FLIGHT HOURS MANUFACTURER-REQUIRED Pre TU347: - Visual inspection of the free turbine blades Chap. 72 Chap. 72 Chap. 72 Before carrying out any maintenance tasks, remember to refer to the latest Service Bulletins and Service Letters. PREVENTIVE MAINTENANCE (1) ENGINE - 1ST LINE MAINTENANCE For training purposes only © Copyright - Turbomeca Training Edition: May 2014 3.35 ENGINE Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) (refer to MM, chapter 05) ARRIEL 1 Training Notes 1st line maintenance course ENGINE - 1ST LINE MAINTENANCE PREVENTIVE MAINTENANCE (2) Scheduled inspections List of maintenance tasks to be carried out: - Inspection before the first flight of the day - Turn-around inspection - Inspection after the last flight of the day - Inspection after 15 flight hours or 7 days Operations to be performed to comply with Airworthiness objectives are listed in the table of mandatory maintenance tasks. Manufacturer-required maintenance tasks The manufacturer considers that the manufacturer-required maintenance tasks must be carried out at the scheduled inspection frequency. Failure to do so may cause occurrences liable to affect the engine operating safety. - Inspection at 30 flight hours Optional maintenance tasks - Inspection at 50 flight hours Optional maintenance tasks are recommended by the manufacturer as a means of improving reliability, increasing operational availability and reducing operating costs. - Inspection at 100 flight hours - Inspection at 150 flight hours - Inspection at 200 flight hours - Inspection at 300 flight hours - Inspection at 400 flight hours - Inspection at 500 flight hours - Inspection at 600 flight hours - Inspection at 750 flight hours - Inspection at 1,000 flight hours Note 1: Before carrying out any maintenance tasks, remember to refer to the latest Service Bulletins and Service Letters. Note 2: The maintenance tasks shown below concern the ARRIEL 1D1 variant by way of example and may differ for other ARRIEL 1 variants. Always refer to the Maintenance Manual of the variant concerned. - Inspection at 1,200 flight hours - Inspection at 1,500 flight hours - Inspection at 3,000 flight hours - Inspection at 3,600 flight hours For training purposes only © Copyright - Turbomeca Training Edition: May 2014 3.36 ENGINE Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) Refer to the Maintenance Manual (chapter 05). Mandatory maintenance tasks Training Notes 1st line maintenance course ARRIEL 1 PREVENTIVE MAINTENANCE (scheduled inspections) INSPECTION AT 300 FLIGHT HOURS MANUFACTURER-REQUIRED Pre TU244: - Inspection and check of the combustion chamber Post TU215 or Post TU254 or Post TU255, Post TU259: - Inspection and check of the Module 04 Free turbine OPTIONAL - Inspection and check of the heat shield (free from cracks, correct attachment) - Inspection and check of the exhaust pipe assembly (free from cracks, correct attachment) INSPECTION AT 400 FLIGHT HOURS Chap. 72 Chap. 72 Chap. 72 Chap. 72 MANDATORY - Vibration check at the engine rear part Chap. 71 Note: Operation in a dusty atmosphere MANUFACTURER-REQUIRED - Do a check of the rotating components of the axial compressor Chap. 72 Note: Engines which operate in erosive atmosphere as per SB No. A292 72 0230 Note: If blade wear is incorrect, do a check for anomalies on the stationary parts of axial compressor INSPECTION AT 500 FLIGHT HOURS MANUFACTURER-REQUIRED Borescope inspection of 1st stage turbine blades of gas generator Post TU244: - Inspection and check of the combustion chamber Chap. 72 Chap. 72 Before carrying out any maintenance tasks, remember to refer to the latest Service Bulletins and Service Letters. PREVENTIVE MAINTENANCE (2) ENGINE - 1ST LINE MAINTENANCE For training purposes only © Copyright - Turbomeca Training Edition: May 2014 3.37 ENGINE Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) (refer to MM, chapter 05) ARRIEL 1 Training Notes 1st line maintenance course ENGINE - 1ST LINE MAINTENANCE PREVENTIVE MAINTENANCE (3) Scheduled inspections List of maintenance tasks to be carried out: - Inspection before the first flight of the day - Turn-around inspection - Inspection after the last flight of the day - Inspection after 15 flight hours or 7 days Operations to be performed to comply with Airworthiness objectives are listed in the table of mandatory maintenance tasks. Manufacturer-required maintenance tasks The manufacturer considers that the manufacturer-required maintenance tasks must be carried out at the scheduled inspection frequency. Failure to do so may cause occurrences liable to affect the engine operating safety. - Inspection at 30 flight hours Optional maintenance tasks - Inspection at 50 flight hours Optional maintenance tasks are recommended by the manufacturer as a means of improving reliability, increasing operational availability and reducing operating costs. - Inspection at 100 flight hours - Inspection at 150 flight hours - Inspection at 200 flight hours - Inspection at 300 flight hours - Inspection at 400 flight hours - Inspection at 500 flight hours - Inspection at 600 flight hours - Inspection at 750 flight hours - Inspection at 1,000 flight hours Note 1: Before carrying out any maintenance tasks, remember to refer to the latest Service Bulletins and Service Letters. Note 2: The maintenance tasks shown below concern the ARRIEL 1D1 variant by way of example and may differ for other ARRIEL 1 variants. Always refer to the Maintenance Manual of the variant concerned. - Inspection at 1,200 flight hours - Inspection at 1,500 flight hours - Inspection at 3,000 flight hours - Inspection at 3,600 flight hours For training purposes only © Copyright - Turbomeca Training Edition: May 2014 3.38 ENGINE Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) Refer to the Maintenance Manual (chapter 05). Mandatory maintenance tasks Training Notes 1st line maintenance course ARRIEL 1 PREVENTIVE MAINTENANCE (scheduled inspections) INSPECTION AT 3,000 FLIGHT HOURS INSPECTION AT 750 FLIGHT HOURS MANUFACTURER-REQUIRED Do a check of the rotating components of the axial compressor Chap. 72 Note: Non-erosive atmosphere Note: If blade wear is incorrect, do a check for anomalies on the stationary parts of axial compressor Do a vibration check at rear point Chap. 71 Note: Non-dusty atmosphere Inspection and check of the heat shield (free from cracks, correct attachment) Chap. 72 Inspection and check of the exhaust pipe assembly (free from cracks, correct attachment) Chap. 72 INSPECTION AT 1,000 FLIGHT HOURS MANUFACTURER-REQUIRED Check casing condition (no leakage on the various mating faces) MANUFACTURER-REQUIRED Pre TU275: - Intermediate inspection of Module 02 Note: Module 02 must be removed Chap. 72 INSPECTION AT 3,600 FLIGHT HOURS MANUFACTURER-REQUIRED Post TU275: - Intermediate inspection of Module 02 Chap. 72 Note: Module 02 must be removed Post TU215 or Post TU255, Post TU259: - Intermediate inspection of Module 04 Chap. 72 Note: Module 04 must be removed Replacement of the free turbine front bearing Chap. 72 Note: The engine must be removed Inspection and check of Module 01 Chap. 72 Note: Module 01 must be removed Note: The embodiment of these tasks must be mentioned on the Module 01's log card INSPECTION AT 1,200 FLIGHT HOURS MANUFACTURER-REQUIRED Examine the coupling sleeve Chap. 72 Note: Only perform if the engine is not followed by spectrometric oil analysis every 100 hours Note: Module 05 must be removed Before carrying out any maintenance tasks, remember to refer to the latest Service Bulletins and Service Letters. PREVENTIVE MAINTENANCE (3) ENGINE - 1ST LINE MAINTENANCE For training purposes only © Copyright - Turbomeca Training Edition: May 2014 3.39 ENGINE Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) (refer to MM, chapter 05) Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) ARRIEL 1 Training Notes 1st line maintenance course Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) 4 - OIL SYSTEM - Oil system - Presentation ..................................................................... 4.2 - Oil tank - Oil cooler - Oil pressure transmitter ................................... 4.6 - Oil pumps .............................................................................................. 4.8 - Oil filter .................................................................................................. 4.10 - Oil filter pre-blockage indicator ........................................................... 4.14 - Low oil pressure switch ....................................................................... 4.16 - Electrical magnetic plugs ..................................................................... 4.18 - Mechanical magnetic plugs ................................................................. 4.20 - Strainers ................................................................................................ 4.22 - Centrifugal breather .............................................................................. 4.24 - Oil system - Operation .......................................................................... 4.26 - External oil pipes ................................................................................. 4.28 - Oil system - 1st line maintenance ....................................................... 4.30 - 4.35 For training purposes only © Copyright - Turbomeca Training Edition: May 2014 4.1 OIL SYSTEM ARRIEL 1 Training Notes 1st line maintenance course OIL SYSTEM - PRESENTATION Lubrication requirements Function Lubrication is required for the following components: The oil system lubricates and cools the engine. - Gas generator front bearings • Axial compressor bearing • Centrifugal compressor bearing Position All the system components are located on the engine, except the oil tank and cooler. - Gas generator rear bearing Main characteristics - Reduction gearbox bearings and gears - Type: variable pressure, full flow, dry sump, synthetic oil - Accessory gearbox bearings and gears. - Max. oil temperature: 115°C (239°F) - Power turbine bearings Sealing - Min. oil pressure: 90 or 130 kPa (13 or 18.85 PSIG) according to version The 3 gas generator bearings and the power turbine front bearing are sealed by pressurised labyrinth seals with abradable coatings. - Max. oil pressure: 800 kPa (116 PSIG) - Max. oil consumption: 0.3 l/h or 0.15 l/h according to version. Note: For oil specification tables and precautions, refer to Maintenance Manual chapter 71. For training purposes only © Copyright - Turbomeca Training Edition: May 2014 4.2 OIL SYSTEM Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) GENERAL Training Notes 1st line maintenance course ARRIEL 1 GAS GENERATOR REAR BEARING FRONT BEARINGS Engine lubrication POWER TURBINE FRONT BEARING REAR BEARINGS Engine cooling Type: Variable pressure, full flow, dry sump, synthetic oil Max. oil temperature: 115°C (239°F) Min. oil pressure: 90 or 130 kPa (13 or 18.85 PSIG) according to version Max. oil pressure: 800 kPa (116 PSIG) Max. oil consumption: 0.3 l/h or 0.15 l/h according to version BEARINGS GEARS BEARINGS ACCESSORY GEARBOX GEARS REDUCTION GEARBOX Sealing: The 3 gas generator bearings and the power turbine front bearing are sealed by pressurised labyrinth seals with abradable coatings. GENERAL OIL SYSTEM - PRESENTATION For training purposes only © Copyright - Turbomeca Training Edition: May 2014 4.3 OIL SYSTEM Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) OIL SYSTEM ARRIEL 1 Training Notes 1st line maintenance course OIL SYSTEM - PRESENTATION The system contains all the components necessary for engine lubrication. Oil tank The tank contains the volume of oil required to lubricate the engine. It is supplied by the aircraft manufacturer. Oil pumps The pump unit contains one pressure pump and three scavenge pumps. The gear type pumps are driven by the accessory gearbox. The pressure pump is equipped with a pressure-relief valve and, on some versions, a check valve. Oil filter The filter retains any particles which may be present in the oil. It is provided with a by-pass valve and a pre-blockage indicator. A check valve is fitted downstream of the scavenge pumps, on the general oil return line to the oil tank. Oil cooler The oil cooler cools the oil. It is supplied by the aircraft manufacturer. Centrifugal breather The centrifugal breather separates the oil from the air/oil mist and vents the system. Indicating devices - Oil temperature probe (supplied by the aircraft manufacturer) - Pre-blockage indicator Strainers The strainers protect the scavenge pumps from debris in the system. - Low oil pressure switch - Pressure transmitter - Magnetic plugs Magnetic plugs Mechanical magnetic plugs are fitted upstream of the scavenge pumps. An electrical magnetic plug is fitted at the general scavenge outlet, another one at the rear bearing of the gas generator scavenge. For training purposes only © Copyright - Turbomeca Training Check valve (general oil return line to oil tank) - Electrical magnetic plugs. Edition: May 2014 4.4 OIL SYSTEM Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) DESCRIPTION Training Notes 1st line maintenance course ARRIEL 1 Low oil pressure switch ENGINE Oil temperature probe Check valve (some versions) Pressurerelief valve TANK Check valve Electrical magnetic plug CENTRIFUGAL BREATHER Pre-blockage indicator By-pass valve COOLER Scavenge pumps Pressure transmitter Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) AIRFRAME Pressure pump FILTER Magnetic plug Electrical magnetic plug Magnetic plug STRAINERS OIL PUMPS DESCRIPTION OIL SYSTEM - PRESENTATION For training purposes only © Copyright - Turbomeca Training Edition: May 2014 4.5 OIL SYSTEM ARRIEL 1 Training Notes 1st line maintenance course Main characteristics Oil tank - Type: air-oil cooler - Differential and thermostatic by-pass valve Function The tank contains the oil required for engine lubrication. Oil pressure transmitter Position Function - On the aircraft: it is installed with the oil cooler above the plenum chamber, between the main gearbox and the front firewall. The transmitter provides a signal of oil pressure to the instrument panel. Main components Position - In the system: in the supply system, downstream of the filter - Filler cap, level indicator, drain plug (with magnetic plug), temperature probe and unions (supply, return and vent). - On the engine: screwed into the filter base. Oil cooler - Output signal: voltage proportional to the oil pressure. Main characteristics Function The oil cooler cools the oil after it has passed through the engine. Position - In the system: between the scavenge pumps and the tank - On the aircraft: it is installed on the oil tank above the plenum chamber between the main gearbox and the front firewall. For training purposes only © Copyright - Turbomeca Training Note 1: All these components are supplied by the aircraft manufacturer. Refer to the aircraft manufacturer documentation. Note 2: On the 1E2 version only, the oil pressure transmitter is supplied by TURBOMECA. Edition: May 2014 4.6 OIL SYSTEM Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) OIL TANK - OIL COOLER - OIL PRESSURE TRANSMITTER Training Notes 1st line maintenance course All these components are supplied by the aircraft manufacturer. Refer to the aircraft manufacturer documentation. AIRFRAME OIL PRESSURE TRANSMITTER Electrical signal to the cockpit Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) ARRIEL 1 ENGINE OIL TANK OIL COOLER OIL TANK - OIL COOLER - OIL PRESSURE TRANSMITTER For training purposes only © Copyright - Turbomeca Training Edition: May 2014 4.7 OIL SYSTEM ARRIEL 1 Training Notes 1st line maintenance course OIL PUMPS - The pump casing provided with inlet and outlet orifices Function - The pressure-relief valve - The check valve (according to version). Position - On the engine: the pump pack is mounted on the rear face of the accessory gearbox. Main characteristics - Type: gear - Pressure pump outlet pressure: approx. 300 kPa (43.5 PSI) (variable pressure system) - Pressure-relief valve setting: 800 kPa (116 PSI) Description The oil pump unit is mounted on the rear left face of the accessory gearbox and is driven at a speed proportional to N1. - 4 gear type pumps: • Pressure pump • Gas generator rear bearing scavenge pump • Reduction gearbox scavenge pump • Accessory gearbox scavenge pump For training purposes only © Copyright - Turbomeca Training The pressure pump draws the oil from the tank and pumps it to the filter. The scavenge pumps draw the oil from the casings and pump it to the cooler. Pressure-relief valve operation If the oil pressure exceeds the valve setting the valve opens and allows the oil to return to the pump inlet. - Check valve: according to version. It consists of: Operation In normal operation the valve is closed and only opens in exceptional circumstances, e.g. starting with very low temperature. Pressure pump outlet check valve operation When the oil pressure is very low, e.g. engine stopped or at the beginning of start, the valve is closed in order to prevent flow between the oil pressure pump and the oil system. Edition: May 2014 4.8 OIL SYSTEM Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) The pumps ensure oil circulation. Training Notes 1st line maintenance course Check valve (according to version) Pressurerelief valve From oil tank PUMP UNIT Type: Gear Oil filter Pressure pump outlet pressure: Approx. 300 kPa (43.5 PSI) (variable pressure system) To lubrication To oil cooler From engine Pressure-relief valve setting: 800 kPa (116 PSI) Check valve: According to version Normal running condition (valve closed) Overpressure (valve open) PRESSURE-RELIEF VALVE OPERATION Scavenge pumps Pressure pump OIL PUMPS DRIVE SHAFT Normal running condition (valve open) Engine stopped and initial phase of starting (valve closed) PUMP BODY PRESSURE PUMP OUTLET CHECK VALVE OPERATION OIL PUMPS For training purposes only © Copyright - Turbomeca Training Edition: May 2014 4.9 OIL SYSTEM Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) ARRIEL 1 ARRIEL 1 Training Notes 1st line maintenance course OIL FILTER Main components Function - Filter base The filter retains particles that may be in the oil. - Pre-blockage indicator (pre-blockage pressure switch on 1E version) Position - Cover - In the system: downstream of the pressure pump - By-pass valve. - On the engine: on the left rear face of the accessory gearbox. Main characteristics - Type: metal cartridge - Filtering ability: 30 microns - Mechanical pre-blockage indicator: ∆P 150 kPa (21.7 PSID) - By-pass valve setting: ∆P 200 kPa (29 PSID). For training purposes only © Copyright - Turbomeca Training Edition: May 2014 4.10 OIL SYSTEM Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) GENERAL ARRIEL 1 Training Notes 1st line maintenance course FILTER BASE PRE-BLOCKAGE INDICATOR (pre-blockage pressure switch on 1E version) BY-PASS VALVE Type: Metal cartridge Filtering ability: 30 microns Mechanical pre-blockage indicator: ∆P 150 kPa (21.7 PSID) Pressurerelief valve Check valve (according to version) Pre-blockage indicator To lubrication From oil tank By-pass valve setting: ∆P 200 kPa (29 PSID) By-pass valve FILTER GENERAL OIL FILTER For training purposes only © Copyright - Turbomeca Training Edition: May 2014 4.11 OIL SYSTEM Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) COVER ARRIEL 1 Training Notes 1st line maintenance course OIL FILTER Operation Description Normal condition (filtering) The main components of the filtering unit are the following: The oil supplied by the pressure pump passes through the filter from outside to inside. The filtered oil then passes to the engine for lubrication. - Filter base - Filter cover Pre-blockage - Metal cartridge (filtering element) If the filter begins to become blocked the pressure difference across the filter increases. At a given difference, a red mechanical indicator pops out. The oil continues to flow through the filter. - By-pass valve (fitted inside the filter base) - Drain valve. The filter base incorporates mounting points for the following: - Pre-blockage indicator Blockage If the pressure difference exceeds the by-pass valve setting, the by-pass valve opens and unfiltered oil passes to the system. - Low oil pressure switch - Oil pressure transmitter. For training purposes only © Copyright - Turbomeca Training Edition: May 2014 4.12 OIL SYSTEM Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) DESCRIPTION - OPERATION Training Notes 1st line maintenance course ARRIEL 1 FILTER COVER FILTERING ELEMENT LOW OIL PRESSURE SWITCH PRE-BLOCKAGE INDICATOR OIL PRESSURE TRANSMITTER BY-PASS VALVE NORMAL CONDITION OPERATION OF THE MECHANICAL PRE-BLOCKAGE INDICATOR PRE-BLOCKAGE BY-PASS VALVE DRAIN VALVE FILTER BASE PRE-BLOCKAGE INDICATOR BLOCKAGE OPERATION OF THE BY-PASS VALVE DESCRIPTION - OPERATION OIL FILTER For training purposes only © Copyright - Turbomeca Training Edition: May 2014 4.13 OIL SYSTEM Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) OIL FILTER (filtering 30 microns) ARRIEL 1 Training Notes 1st line maintenance course OIL FILTER PRE-BLOCKAGE INDICATOR Operation The indicator indicates the onset of filter blockage. Normal operation Position Filter downstream pressure plus spring pressure is greater than upstream pressure. The two pistons are held together by magnetic force. The indicator is not visible. On the left face of the filter housing. Main characteristics - Pre-blockage Type: differential Setting: ∆P 150 kPa (21.7 PSID) Indication: red indicator Manual rearming. Filter upstream pressure exceeds downstream plus spring pressure and the ∆P piston displaces. This breaks the magnetic hold and the indicator piston is pushed out by its spring. The indicator is visible. Description The bi-metallic thermal lock ensures that the indicator is not triggered by a low oil temperature (locked below 50°C (122°F)). The pre-blockage indicator comprises the following parts: - Indicator body including: • Filter upstream pressure inlet • Filter downstream pressure inlet - Red indicator piston - ∆P piston - Transparent cover - Thermal lock - O-ring seals ensure the filter pre-blockage indicator sealing. For training purposes only © Copyright - Turbomeca Training It is re-armed by removing the cover and pushing in the indicator. Note: In the 1E version, the filter pre-blockage indicator is replaced by a filter pre-blockage pressure switch. Edition: May 2014 4.14 OIL SYSTEM Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) Function Training Notes 1st line maintenance course ARRIEL 1 INDICATOR BODY < 50°C (122°F) > 50°C (122°F) Thermal lock operation Downstream pressure Type: Differential RED INDICATOR Setting: ∆P 150 kPa (21.7 PSID) Upstream pressure NORMAL OPERATION Indication: Red indicator Manual re-arming Pressurerelief valve From oil tank Check valve (according to version) PRE-BLOCKAGE INDICATOR Red indicator out Downstream pressure To lubrication Upstream pressure PRE-BLOCKAGE OIL FILTER PRE-BLOCKAGE INDICATOR For training purposes only © Copyright - Turbomeca Training Edition: May 2014 4.15 OIL SYSTEM Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) TRANSPARENT COVER ARRIEL 1 Training Notes 1st line maintenance course LOW OIL PRESSURE SWITCH The low oil pressure switch detects low oil system pressure and provides cockpit indication. Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) Function Position - In the system: downstream of the filter - On the engine: fitted on the filter base. Main characteristics - Type: diaphragm pressure switch - Setting: 90 or 130 kPa (13 or 18.9 PSI) (according to version) - Indication: light on instrument panel. Functional description The pressure switch microswitch is open during normal engine operation. If the oil pressure reduces to less than the low oil pressure switch setting, the diaphragm moves down. This causes the electrical contact to close, completing the circuit of the low oil pressure warning light. An O-ring seal ensures the sealing between the pressure switch and the filter base. For training purposes only © Copyright - Turbomeca Training Edition: May 2014 4.16 OIL SYSTEM Training Notes 1st line maintenance course ARRIEL 1 ELECTRICAL CONTACT ELECTRICAL CONNECTOR Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) LOW OIL PRESSURE SWITCH From filter (pressure pump) WARNING LIGHT (instrument panel) +28 VDC PLUNGER DIAPHRAGM From filter Type: Diaphragm pressure switch Setting: 90 or 130 kPa (13 or 18.9 PSI) according to version Indication: Light on instrument panel To lubrication LOW OIL PRESSURE SWITCH For training purposes only © Copyright - Turbomeca Training Edition: May 2014 4.17 OIL SYSTEM ARRIEL 1 Training Notes 1st line maintenance course ELECTRICAL MAGNETIC PLUGS The electrical magnetic plugs provide a cockpit indication of metal particles in the oil system. Position A resistor is connected across the gap. The plugs are connected, via the engine electrical harness, to the aircraft instrument panel with an optional test system. The plugs are fitted into a housing which is provided with a self-sealing valve. The scavenge oil flows across the magnetic probe. - In the system: • one downstream of the scavenge pumps • one upstream of the rear bearing scavenge pump - On the engine: • one near the pump assembly (scavenge pumps) • one on the left side of the accessory gearbox (rear bearing). Note: The oil system also has two mechanical magnetic plugs located on the lower part of the accessory gearbox and on the lower part of the reduction gearbox. Operation The magnetic probe attracts magnetic particles present in the oil. If it attracts sufficient particles to form a bridge across the gap, this will complete the electrical circuit between the two magnetic parts and thus illuminate an indicator on the instrument panel. Main characteristics - Type: • Magnetic with electrical indication • Self-sealing housing. The resistor is fitted to allow the installation of a test circuit. Description Note: Refer to aircraft documents for further details. The electrical magnetic plugs comprise a magnetic probe which has two parts which are electrically insulated from one another and have a small gap between them. For training purposes only © Copyright - Turbomeca Training Edition: May 2014 4.18 OIL SYSTEM Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) Function Training Notes 1st line maintenance course Type: Electrical magnetic plug Housing: Self-sealing Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) ARRIEL 1 ELECTRICAL CONNECTOR PLUG BODY Strainer To oil cooler From engine GAP ELECTRICAL MAGNETIC PLUG Scavenge pumps Firewall AIRCRAFT Resistor HOUSING ENGINE GAP + SELF-SEALING VALVE INDICATOR ELECTRICAL MAGNETIC PLUG ELECTRICAL MAGNETIC PLUGS For training purposes only © Copyright - Turbomeca Training Edition: May 2014 4.19 OIL SYSTEM ARRIEL 1 Training Notes 1st line maintenance course Function Main components The mechanical magnetic plugs retain magnetic particles contained in the oil to provide a rapid and frequent check of the internal condition of the engine. - Self sealing housing: • Housing • O-ring seal • Valve • Spring Position In the system: Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) MECHANICAL MAGNETIC PLUGS - Magnetic plug: • Magnet • O-ring seal(s) • Locating pins or notches. - One on the reduction gearbox scavenge return - One on the accessory gearbox scavenge return. On the engine: - One at the bottom of the reduction gearbox - One at the bottom of the accessory gearbox. They are mounted on the left or the right side according to the position of the engine in the helicopter. Main characteristics - Type: • Single magnetic pole • Self-sealing housing For training purposes only © Copyright - Turbomeca Training Edition: May 2014 4.20 OIL SYSTEM ARRIEL 1 Training Notes 1st line maintenance course LOCATING PINS O-RING SEALS O-RING SEAL HOUSING AFTER TU 308A BEFORE TU 308A MAGNET Type: Single magnetic pole Self-sealing housing NORMAL POSITION SPRING MAGNET To scavenge pumps MECHANICAL MAGNETIC PLUGS LOCATING PIN REMOVED POSITION MECHANICAL MAGNETIC PLUGS For training purposes only © Copyright - Turbomeca Training O-RING SEALS Edition: May 2014 4.21 OIL SYSTEM Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) VALVE ARRIEL 1 Training Notes 1st line maintenance course Function Main components The strainers protect the scavenge pumps against large particles which might be in the oil. - Strainer body Position - Mounting flange - In the system: they are fitted in each scavenge line upstream of the scavenge pump - O-ring seal. - On the engine: • Two strainers are located on the accessory gearbox casing (reduction gearbox and accessory gearbox scavenge) • One strainer is located on the oil pump assembly (gas generator rear bearing scavenge) Functional description - Wide-mesh filter A strainer is a wide-mesh filter which retains any large particles which may be present in the oil in order to protect the scavenge pumps. Main characteristics - Type: wide-mesh filter. Note: The rear bearing strainer is fitted in the electrical magnetic plug housing (post TU 208). For training purposes only © Copyright - Turbomeca Training Edition: May 2014 4.22 OIL SYSTEM Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) STRAINERS Training Notes 1st line maintenance course ARRIEL 1 Type: Wide-mesh filter Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) Gas generator rear bearing strainer GAS GENERATOR REAR BEARING STRAINER (POST TU 208) Accessory gearbox strainer Reduction gearbox strainer ACCESSORY GEARBOX AND REDUCTION GEARBOX STRAINERS STRAINER To oil cooler From engine GAS GENERATOR REAR BEARING STRAINER (PRE TU 208) To scavenge pumps STRAINERS STRAINERS For training purposes only © Copyright - Turbomeca Training Edition: May 2014 4.23 OIL SYSTEM ARRIEL 1 Training Notes 1st line maintenance course Function Operation The centrifugal breather separates the oil from the air/oil mist created by the oil system. The centrifugal breather is driven by the intermediate gear of the accessory drive. Position When the engine is running, the air/oil mist passes through the breather. It is formed by the starter-generator drive gear in the accessory gearbox. - Centrifugal force throws the oil droplets out into the gearbox where they fall to the bottom of the casing Main characteristics - The de-oiled air passes out through the shaft, via a gearbox passage, into an external pipe which discharges into the exhaust. - Type: centrifugal - De-oiled air: through the rear of the hollow shaft. Description The centrifugal breather is formed by the starter-generator drive gear. This gear is formed in one piece with a hollow shaft and has holes which provide a passage between the gearbox and the air vent. The gear is supported by two ball bearings and has a magnetic carbon seal at each end. Only the front magnetic carbon seal can be replaced in 1st line maintenance. The breather air outlet is at the rear end of the shaft, where the air passes into the gearbox outlet. For training purposes only © Copyright - Turbomeca Training Edition: May 2014 4.24 OIL SYSTEM Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) CENTRIFUGAL BREATHER Training Notes 1st line maintenance course Type: Centrifugal De-oiled air: Through the rear of the hollow shaft Oil droplets (expelled by centrifugal force) AIR/OIL MIST - from accessory gearbox - from gas generator bearings - from power turbine bearings - from reduction gearbox MAGNETIC CARBON SEAL STARTERGENERATOR DRIVE GEAR AIR VENT DE-OILED AIR De-oiled air (to air vent) Air/Oil mist STARTERGENERATOR DRIVE BREATHER HOLES OIL DROPLETS CENTRIFUGAL BREATHER For training purposes only © Copyright - Turbomeca Training MAGNETIC CARBON SEAL Edition: May 2014 4.25 OIL SYSTEM Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) ARRIEL 1 ARRIEL 1 Training Notes 1st line maintenance course OIL SYSTEM - OPERATION Supply The pressure pump draws the oil from the tank and supplies the system. A pressure-relief valve limits the maximum pressure by returning oil to the pressure pump inlet above a certain pressure. The oil is then delivered through a check valve, the oil filter and a calibrated orifice to the parts of the engine which require lubrication: - Gas generator front bearings Scavenge After lubrication, the oil falls by gravity to the bottom of the sumps. The oil is then immediately drawn away by the scavenge pumps and returned to the tank through the oil cooler (dry sump system). Strainers protect the scavenge pumps against any particles which may be in the oil. A check valve, located downstream of the scavenge pumps, prevents any oil flow from the oil tank to the engine when the pressure is very low (engine stopped). - Gas generator rear bearing Magnetic plugs attract and retain any magnetic particles which may be in the oil. - Power turbine bearings Breathing - Reduction gearbox The air/oil mist which results from lubrication is returned to the accessory gearbox, where the oil is separated from the air by a centrifugal breather, which vents overboard. - Accessory gearbox and torquemeter (supply upstream of the calibrated orifice). The oil is sprayed by jets onto the parts to be lubricated. The gas generator rear bearing has a direct air vent. Indication The system provides the following indications: pressure, temperature, low pressure, electrical magnetic plug and filter pre-blockage. For training purposes only © Copyright - Turbomeca Training Edition: May 2014 4.26 OIL SYSTEM Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) The main functions of the oil system are: supply, scavenge, breathing and indication. Training Notes 1st line maintenance course AIRFRAME ENGINE SUCTION SUPPLY PRESSURISATION SCAVENGE BREATHING AIR VENT OIL SYSTEM - OPERATION For training purposes only © Copyright - Turbomeca Training Edition: May 2014 Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) ARRIEL 1 4.27 OIL SYSTEM ARRIEL 1 Training Notes 1st line maintenance course EXTERNAL OIL PIPES Breathing pipe The external oil pipes carry the oil to and from the various components of the oil system and the parts of the engine that require lubrication (bearings). - Oil tank breathing pipe (supplied by the aircraft manufacturer) - Breathing T-union - Oil system breathing pipe (to exhaust pipe). Main characteristics - Type of pipes: rigid, stainless steel Air vent pipes - Type of unions: standard (connecting flange with bolts). - Gas generator rear bearing air vent pipe (overboard). Description The external oil pipes can be divided into 4 categories: Supply pipes - Oil inlet pipe (from oil tank to pressure pump; supplied by the aircraft manufacturer) - Gas generator front bearings supply pipe - Low oil pressure switch and oil pressure transmitter supply pipe - Gas generator rear bearing supply pipe. Scavenge pipes - Gas generator rear bearing scavenge pipe - Oil outlet pipe (from scavenge pumps to oil cooler; supplied by the aircraft manufacturer). For training purposes only © Copyright - Turbomeca Training Edition: May 2014 4.28 OIL SYSTEM Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) Function Training Notes 1st line maintenance course Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) ARRIEL 1 LOW OIL PRESSURE SWITCH AND OIL PRESSURE TRANSMITTER SUPPLY PIPE GAS GENERATOR FRONT BEARINGS SUPPLY PIPE GAS GENERATOR REAR BEARINGS SUPPLY PIPE GAS GENERATOR REAR BEARING AIR VENT PIPE OIL SUPPLY PIPE GAS GENERATOR REAR BEARING SCAVENGE PIPE Type of pipes: Rigid, stainless steel EXTERNAL OIL PIPES For training purposes only © Copyright - Turbomeca Training Edition: May 2014 4.29 OIL SYSTEM ARRIEL 1 Training Notes 1st line maintenance course OIL SYSTEM - 1ST LINE MAINTENANCE PREVENTIVE MAINTENANCE (1) Scheduled inspections List of maintenance tasks to be carried out: - Inspection before the first flight of the day - Turn-around inspection - Inspection after the last flight of the day - Inspection after 15 flight hours or 7 days Operations to be performed to comply with Airworthiness objectives are listed in the table of mandatory maintenance tasks. Manufacturer-required maintenance tasks The manufacturer considers that the manufacturer-required maintenance tasks must be carried out at the scheduled inspection frequency. Failure to do so may cause occurrences liable to affect the engine operating safety. - Inspection at 30 flight hours Optional maintenance tasks - Inspection at 50 flight hours Optional maintenance tasks are recommended by the manufacturer as a means of improving reliability, increasing operational availability and reducing operating costs. - Inspection at 100 flight hours - Inspection at 150 flight hours - Inspection at 200 flight hours - Inspection at 300 flight hours - Inspection at 400 flight hours - Inspection at 500 flight hours - Inspection at 600 flight hours - Inspection at 750 flight hours - Inspection at 1,000 flight hours - Inspection at 1,200 flight hours Note 1: Before carrying out any maintenance tasks, remember to refer to the latest Service Bulletins and Service Letters. Note 2: The maintenance tasks shown below concern the ARRIEL 1D1 variant by way of example and may differ for other ARRIEL 1 variants. Always refer to the Maintenance Manual of the variant concerned. - Inspection at 1,500 flight hours - Inspection at 3,000 flight hours - Inspection at 3,600 flight hours For training purposes only © Copyright - Turbomeca Training Edition: May 2014 4.30 OIL SYSTEM Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) Refer to the Maintenance Manual (chapter 05). Mandatory maintenance tasks Training Notes 1st line maintenance course ARRIEL 1 PREVENTIVE MAINTENANCE (scheduled inspections) INSPECTION AT 30 FLIGHT HOURS TURN-AROUND INSPECTION MANDATORY Inspection of oil level in tank and top up if required Aircraft documentation INSPECTION AFTER THE LAST FLIGHT OF THE DAY MANUFACTURER-REQUIRED Inspection of oil level in tank and top up if required Aircraft documentation MANUFACTURER-REQUIRED - Inspection and cleaning of the mechanical magnetic plug of accessory gearbox Post TU232: - Inspection and cleaning of the mechanical magnetic plug of reduction gear Chap. 72 Chap. 72 INSPECTION AT 100 FLIGHT HOURS INSPECTION AFTER 15 FLIGHT HOURS OR 7 DAYS MANUFACTURER-REQUIRED Pre TU232: - Inspection and cleaning of the mechanical magnetic plug of reduction gear Visually check that there are no leaks on the rear bearing oil ducts Check the visual blockage indicator of the oil filter Before carrying out any maintenance tasks, remember to refer to the latest Service Bulletins and Service Letters. Chap. 72 Chap. 72 MANUFACTURER-REQUIRED S.O.A. inspection Chap. 71 Note: When Module 02 or Module 04 have been operated for more than 3,000 hours after the manufacturing or the last general overhaul Pre TU274, Pre TU281, Pre TU283, Pre TU284: - Inspection of the rear bearing (for clogging) Chap. 72 Pre TU208: - Inspection and cleaning of the strainer of the oil return pipe of the rear bearing Chap. 72 Post TU208: - Inspection and cleaning of the strainer of the oil return pipe of the rear bearing Chap. 79 PREVENTIVE MAINTENANCE (1) OIL SYSTEM - 1ST LINE MAINTENANCE For training purposes only © Copyright - Turbomeca Training Edition: May 2014 4.31 OIL SYSTEM Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) (refer to MM, chapter 05) ARRIEL 1 Training Notes 1st line maintenance course OIL SYSTEM - 1ST LINE MAINTENANCE PREVENTIVE MAINTENANCE (2) Scheduled inspections List of maintenance tasks to be carried out: - Inspection before the first flight of the day - Turn-around inspection - Inspection after the last flight of the day - Inspection after 15 flight hours or 7 days Operations to be performed to comply with Airworthiness objectives are listed in the table of mandatory maintenance tasks. Manufacturer-required maintenance tasks The manufacturer considers that the manufacturer-required maintenance tasks must be carried out at the scheduled inspection frequency. Failure to do so may cause occurrences liable to affect the engine operating safety. - Inspection at 30 flight hours Optional maintenance tasks - Inspection at 50 flight hours Optional maintenance tasks are recommended by the manufacturer as a means of improving reliability, increasing operational availability and reducing operating costs. - Inspection at 100 flight hours - Inspection at 150 flight hours - Inspection at 200 flight hours - Inspection at 300 flight hours - Inspection at 400 flight hours - Inspection at 500 flight hours - Inspection at 600 flight hours - Inspection at 750 flight hours - Inspection at 1,000 flight hours Note 1: Before carrying out any maintenance tasks, remember to refer to the latest Service Bulletins and Service Letters. Note 2: The maintenance tasks shown below concern the ARRIEL 1D1 variant by way of example and may differ for other ARRIEL 1 variants. Always refer to the Maintenance Manual of the variant concerned. - Inspection at 1,200 flight hours - Inspection at 1,500 flight hours - Inspection at 3,000 flight hours - Inspection at 3,600 flight hours For training purposes only © Copyright - Turbomeca Training Edition: May 2014 4.32 OIL SYSTEM Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) Refer to the Maintenance Manual (chapter 05). Mandatory maintenance tasks Training Notes 1st line maintenance course ARRIEL 1 PREVENTIVE MAINTENANCE (scheduled inspections) INSPECTION AT 150 FLIGHT HOURS INSPECTION AT 300 FLIGHT HOURS MANUFACTURER-REQUIRED Inspection of the filtering element Chap. 72 OPTIONAL S.O.A. inspection Chap. 71 Note: When Module 02 or Module 04 have been not operated for more than 3,000 hours after the manufacturing or the last general overhaul MANUFACTURER-REQUIRED Inspection and cleaning of the electrical magnetic plugs at oil outlet Chap. 79 Post TU208: - Inspection and cleaning of the electrical magnetic plugs at gas generator rear bearing oil return Chap. 79 Inspection and check of the low oil pressure switch Chap. 79 Inspection and check of the oil pump Chap. 79 Oil draining Chap. 79 Note: Use of ROYCO 560, ASTO 560 and ETO 2380 type oils INSPECTION AT 200 FLIGHT HOURS MANUFACTURER-REQUIRED Post TU274, Post TU281, Post TU283, Post TU284: - Inspection of the rear bearing (for clogging) Before carrying out any maintenance tasks, remember to refer to the latest Service Bulletins and Service Letters. Chap. 72 INSPECTION AT 750 FLIGHT HOURS MANUFACTURER-REQUIRED Oil draining Note: No use of ROYCO 560, ASTO 560 and ETO 2380 type oils Make sure the three hollow struts for the passage of the rear-bearing oil-tubes are serviceable Chap. 79 Chap. 72 PREVENTIVE MAINTENANCE (2) OIL SYSTEM - 1ST LINE MAINTENANCE For training purposes only © Copyright - Turbomeca Training Edition: May 2014 4.33 OIL SYSTEM Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) (refer to MM, chapter 05) ARRIEL 1 Training Notes 1st line maintenance course OIL SYSTEM - 1ST LINE MAINTENANCE PREVENTIVE MAINTENANCE (3) Scheduled inspections List of maintenance tasks to be carried out: - Inspection before the first flight of the day - Turn-around inspection - Inspection after the last flight of the day - Inspection after 15 flight hours or 7 days Operations to be performed to comply with Airworthiness objectives are listed in the table of mandatory maintenance tasks. Manufacturer-required maintenance tasks The manufacturer considers that the manufacturer-required maintenance tasks must be carried out at the scheduled inspection frequency. Failure to do so may cause occurrences liable to affect the engine operating safety. - Inspection at 30 flight hours Optional maintenance tasks - Inspection at 50 flight hours Optional maintenance tasks are recommended by the manufacturer as a means of improving reliability, increasing operational availability and reducing operating costs. - Inspection at 100 flight hours - Inspection at 150 flight hours - Inspection at 200 flight hours - Inspection at 300 flight hours - Inspection at 400 flight hours - Inspection at 500 flight hours - Inspection at 600 flight hours - Inspection at 750 flight hours - Inspection at 1,000 flight hours - Inspection at 1,200 flight hours Note 1: Before carrying out any maintenance tasks, remember to refer to the latest Service Bulletins and Service Letters. Note 2: The maintenance tasks shown below concern the ARRIEL 1D1 variant by way of example and may differ for other ARRIEL 1 variants. Always refer to the Maintenance Manual of the variant concerned. - Inspection at 1,500 flight hours - Inspection at 3,000 flight hours - Inspection at 3,600 flight hours For training purposes only © Copyright - Turbomeca Training Edition: May 2014 4.34 OIL SYSTEM Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) Refer to the Maintenance Manual (chapter 05). Mandatory maintenance tasks Training Notes 1st line maintenance course ARRIEL 1 PREVENTIVE MAINTENANCE (scheduled inspections) INSPECTION AT 1,000 FLIGHT HOURS MANUFACTURER-REQUIRED Pre TU274, Pre TU281, Pre TU283, Pre TU284: - Cleaning of the rear bearing Post TU274, Post TU281, Post TU283, Post TU284: - Remove, cleaning and installation of the oil scavenge tube of the rear bearing Chap. 72 Chap. 72 Before carrying out any maintenance tasks, remember to refer to the latest Service Bulletins and Service Letters. PREVENTIVE MAINTENANCE (3) OIL SYSTEM - 1ST LINE MAINTENANCE For training purposes only © Copyright - Turbomeca Training Edition: May 2014 4.35 OIL SYSTEM Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) (refer to MM, chapter 05) Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) ARRIEL 1 Training Notes 1st line maintenance course Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) 5 - AIR SYSTEM - Air system - Presentation .................................................................... 5.2 - Internal air system ................................................................................ 5.4 - Air tappings ........................................................................................... 5.6 - Compressor bleed valve ...................................................................... 5.8 - External air pipes .................................................................................. 5.16 - Air system - 1st line maintenance ....................................................... 5.18 - 5.19 For training purposes only © Copyright - Turbomeca Training Edition: May 2014 5.1 AIR SYSTEM ARRIEL 1 Training Notes 1st line maintenance course AIR SYSTEM - PRESENTATION The air system includes: Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) Function - An internal air system which: • Pressurises the labyrinth seals • Cools certain internal engine parts • Balances the forces on the rotating assemblies - Air tappings which are used to: • Ventilate the start injectors • Supply air to control compressor bleed valve operation • Supply the aircraft air system • Supply air to the FCU metering unit - The compressor bleed valve. For training purposes only © Copyright - Turbomeca Training Edition: May 2014 5.2 AIR SYSTEM Training Notes 1st line maintenance course AIR TAPPINGS - Ventilate the start injectors - Supply air to control compressor bleed valve operation - Supply the aircraft air system - Supply air to the FCU metering unit INTERNAL AIR SYSTEM - Pressurises the labyrinth seals - Cools certain internal engine parts - Balances the forces on the rotating assemblies COMPRESSOR BLEED VALVE AIR SYSTEM - PRESENTATION For training purposes only © Copyright - Turbomeca Training Edition: May 2014 5.3 AIR SYSTEM Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) ARRIEL 1 ARRIEL 1 Training Notes 1st line maintenance course INTERNAL AIR SYSTEM Gas generator HP section The internal air system pressurises the labyrinth seals, cools certain internal engine parts, and balances the forces on the rotating assemblies. Position All the components making up the system are internal parts of the engine, except for the power turbine labyrinth seal pressurisation pipe, which is an external pipe. Main characteristics - Type: pressurised air tappings with a calibrated flow Air tapped from the centrifugal compressor is used to pressurise the labyrinth seal on the shaft. The air from the centrifugal compressor outlet flows through the hollow nozzle guide vanes (1st stage) and through holes in the shroud. It is used to: - Cool the nozzle guide vane and the front face of the gas generator turbine - Cool the front and rear faces of the gas generator turbines (discharging into the gas flow) - Pressurise the labyrinth seals of the gas generator rear bearing (small flow into the bearing housing) and the injection wheel. - Airflow: approx. 2% of the total engine flow. The centrifugal compressor casing is fitted with air tapping points. This air is called clean air as it is out of the main air flow stream. Note: The internal air system is also referred to as the secondary air system. Power turbine section Functional description The internal air system can be divided into 3 sections: Front section Air tapped from the centrifugal compressor inlet is used to pressurise the front bearing labyrinths. There is a very small flow of air into the bearing chamber. Air tapped from the same point is discharged through the compressor bleed valve, mounted on the compressor casing (see compressor bleed valve). For training purposes only © Copyright - Turbomeca Training Air tapped from the combustion chamber (P2 air) is taken by an external pipe to the reduction gearbox casing (except on post TU356 1E2 and 1S versions: the air is tapped from the compressor bleed valve control air tapping union). It then passes through internal passages to pressurise the labyrinth seal on the power turbine shaft and to cool the rear face of the power turbine. A circulation of P0 air, induced by venturi effect, cools the gas generator rear bearing chamber, and then flows through the power turbine nozzle guide vanes, cooling them and then joins the gas flow. Edition: May 2014 5.4 AIR SYSTEM Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) Function Training Notes 1st line maintenance course ARRIEL 1 Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) Post TU 356 1E2 and 1S versions P0 FRONT SECTION INTERNAL AIR SYSTEM GAS GENERATOR HP SECTION (post TU 360) Post TU 356 1E2 and 1S versions - Internal passages - External pipe External pipe for the power turbine labyrinth seal pressurisation Type: Pressurised air tappings with a calibrated flow Airflow: Approx. 2% of the total engine flow P0 (atmospheric pressure) P1' (centrifugal compressor inlet pressure) P2 (centrifugal compressor outlet pressure) POWER TURBINE SECTION INTERNAL AIR SYSTEM For training purposes only © Copyright - Turbomeca Training Edition: May 2014 5.5 AIR SYSTEM ARRIEL 1 Training Notes 1st line maintenance course Function Aircraft services Air tappings are used for: Compressor delivery air is tapped off for use in various aircraft systems. - Fuel control The engine has two air tapping unions (used for the aircraft services) on the centrifugal compressor casing. - Start injector ventilation - Aircraft services Note: The use of this bleed is restricted during take-off. - Bleed valve operation - Air intake anti-icing. Bleed valve operation Fuel control Compressor delivery air is tapped to operate the compressor bleed valve. P2 air is used for the acceleration control unit (for all versions) and the deceleration (in some versions 1C, 1D, 1K, 1E, 1S,...). Air intake anti-icing The system includes a pressure tapping and a pipe between the tapping union and the FCU. Start injector ventilation 1S: P2 air is used for air intake anti-icing. The system includes an air tapping point, a pipeline which passes forward through the front firewall, an electro-valve, a pressure switch and the double skinned air intake duct. Compressor delivery air is used to ventilate the start injectors to avoid blockage by the carbonisation of unburnt fuel. The system comprises a tapping union and a pipe connected to the start electro-valve. For training purposes only © Copyright - Turbomeca Training Edition: May 2014 5.6 AIR SYSTEM Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) AIR TAPPINGS Training Notes 1st line maintenance course ACCELERATION CONTROL UNIT Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) ARRIEL 1 DECELERATION CONTROL UNIT AIRCRAFT SERVICES 1S: AIR INTAKE ANTI-ICING P0 P0 P2 SIGNAL FOR THE FUEL CONTROL P2 BLEED VALVE OPERATION AIR TAPPINGS For training purposes only © Copyright - Turbomeca Training Edition: May 2014 START INJECTOR VENTILATION 5.7 AIR SYSTEM ARRIEL 1 Training Notes 1st line maintenance course COMPRESSOR BLEED VALVE Principle Function The compressor bleed valve prevents compressor surge at low N1 speed. Position The valve prevents compressor surge by bleeding off a certain quantity of air tapped from the axial compressor outlet. When the valve is open, the discharge of air causes the air flow through the axial compressor to increase thus moving the working line away from the surge line. - In the system: between the axial and centrifugal compressors - On the engine: at the top of the counter-casing. Main characteristics - Type: pneumatic or electro-pneumatic (according to version) - Control: • by P2/P0 pressure ratio (pneumatic type) • as a function of N1 (electro-pneumatic type). Note: The air can be discharged under the cowling in order to improve cooling of the engine compartment. For training purposes only © Copyright - Turbomeca Training Edition: May 2014 5.8 AIR SYSTEM Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) GENERAL Training Notes 1st line maintenance course Type: Pneumatic or electro-pneumatic (according to version) Control: - P2/P0 pressure ratio (pneumatic type) - As a function of N1 (electro-pneumatic type) P1': AIR DISCHARGED THROUGH THE COMPRESSOR BLEED VALVE P2/P0 PRESSURE RATIO COMPRESSION AND STRAIGHTENING OF THE AIR Surge line Working line (valve closed) ADMISSION OF AMBIENT AIR Working line (valve open) AIRFLOW G GENERAL COMPRESSOR BLEED VALVE For training purposes only © Copyright - Turbomeca Training Edition: May 2014 5.9 AIR SYSTEM Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) ARRIEL 1 ARRIEL 1 Training Notes 1st line maintenance course COMPRESSOR BLEED VALVE Operation Description Closing This compressor bleed valve includes 3 main parts: the tachometer box, the control electro-valve and the bleed valve. When the N1 reaches 96% the tachometer box closes the electrical contact which actuates the control electro-valve to the open position. P2 pressure pushes the piston which closes the bleed valve. Tachometer box It operates a relay controlled by a speed signal from the N1 tachometer transmitter. Control electro-valve It admits P2 air to close the valve when it is electrically supplied. Opening When the N1 decreases below 94%, the tachometer box opens the electrical contact and the spring moves the electro-valve to the closed position. The spring pushes the piston which opens the bleed valve. Bleed valve It includes a spring loaded piston subjected to P2 pressure. The piston operates the valve. For training purposes only © Copyright - Turbomeca Training Edition: May 2014 5.10 AIR SYSTEM Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) ELECTRO-PNEUMATIC TYPE Training Notes 1st line maintenance course TACHOMETER BOX BLEED VALVE Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) ARRIEL 1 P2 + P1' N1 96% P2 AIR SUPPLY 94% GRILL ON P1' AIR DISCHARGE CONTROL ELECTRO-VALVE ELECTRO-PNEUMATIC TYPE COMPRESSOR BLEED VALVE For training purposes only © Copyright - Turbomeca Training Edition: May 2014 5.11 AIR SYSTEM ARRIEL 1 Training Notes 1st line maintenance course COMPRESSOR BLEED VALVE The compressor bleed valve includes 3 main parts: the detection capsule, the intermediate stage and the bleed valve. Operation Closing Detection capsule When the gas generator rotation speed N1 increases, the compression ratio P2/P0 increases and beyond a certain value: It is subjected to P2/P0 pressure ratio and controls the air leak downstream of the calibrated orifice B. - The pressure becomes sufficient to distort the detection capsule which closes the leak It is fitted with a filter at the inlet. - The pressure downstream of the calibrated orifice B increases Intermediate stage - The diaphragm of the intermediate stage closes the leak It includes a diaphragm which is subjected to the pressure downstream of B. The diaphragm controls the leak which determines the pressure downstream of the calibrated orifice A. - The pressure downstream of the calibrated orifice A increases - The piston moves down under P2 pressure and the valve closes and stops the P1' air discharge. Bleed valve Opening It includes a spring loaded piston subjected to a downstream pressure. The piston opens or closes the P1' air passage. The P2/P0 ratio is not sufficient to distort the capsule and there are air leaks downstream of the calibrated orifices. The piston is not actuated and the valve is open. It also includes a microswitch, operated by the piston, which provides indication of the bleed valve position. For training purposes only © Copyright - Turbomeca Training A certain amount of air, tapped from the centrifugal compressor inlet, is discharged overboard. Edition: May 2014 5.12 AIR SYSTEM Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) PNEUMATIC TYPE Training Notes 1st line maintenance course BLEED VALVE INTERMEDIATE STAGE DETECTION CAPSULE FILTER P2 A INTERMEDIATE STAGE B DETECTION CAPSULE FILTER P0 P1' P1' MICROSWITCH INDICATOR BLEED VALVE PNEUMATIC TYPE COMPRESSOR BLEED VALVE For training purposes only © Copyright - Turbomeca Training Edition: May 2014 5.13 AIR SYSTEM Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) ARRIEL 1 ARRIEL 1 Training Notes 1st line maintenance course COMPRESSOR BLEED VALVE Operation Description Closing The compressor bleed valve includes 3 main parts: the detection capsule, the intermediate stage and the bleed valve. When the gas generator rotation speed N1 increases, the compression ratio P2/P0 increases and beyond a certain value: Detection capsule - The pressure becomes sufficient to deform the detection capsule which closes the leak It is subjected to P2/P0 pressure ratio and controls the air leak downstream of the calibrated orifice B. - The pressure downstream of the calibrated orifice B increases It is fitted with a filter at the inlet. - The diaphragm of the intermediate stage closes the leak Intermediate stage - The pressure downstream of the calibrated orifice A increases It includes a diaphragm which is subjected to the pressure downstream of B. The diaphragm controls the leak which determines the pressure downstream of the calibrated orifice A. - The piston moves down under P2 pressure and rotates the butterfly valve through the rack and pinion mechanism. The valve closes and stops the air discharge. Bleed valve Opening It includes a spring loaded piston subjected to pressure downstream of orifice A. The piston actuates the butterfly valve by means of a rack and pinion mechanism. The P2/P0 ratio is not sufficient to distort the capsule and there are air leaks downstream of the calibrated orifices. The piston is not actuated and the butterfly valve is open. It also includes a microswitch, operated by the piston, which gives the position of the bleed valve by means of a light ("on" valve "open"). A certain amount of air, tapped from the centrifugal compressor inlet, is discharged overboard. For training purposes only © Copyright - Turbomeca Training Edition: May 2014 5.14 AIR SYSTEM Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) PNEUMATIC BUTTERFLY TYPE Training Notes 1st line maintenance course ARRIEL 1 P2 AIR BUTTERFLY VALVE A FILTER B FILTER PISTON P0 AIR P2 air MICROSWITCH DETECTION CAPSULE INTERMEDIATE STAGE P1’ P1’ BUTTERFLY VALVE PINION RACK PNEUMATIC BUTTERFLY TYPE COMPRESSOR BLEED VALVE For training purposes only © Copyright - Turbomeca Training Edition: May 2014 5.15 AIR SYSTEM Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) MICROSWITCH ARRIEL 1 Training Notes 1st line maintenance course EXTERNAL AIR PIPES The external air pipes carry air to and from the various components of the air system. Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) Function Main characteristics - Type of pipes: rigid, stainless steel - Type of unions: QUINSON unions. Description The external air pipes connect the air tappings to the following components: - Compressor bleed valve - FCU metering unit - Start valves assembly - Power turbine labyrinth seal. For training purposes only © Copyright - Turbomeca Training Edition: May 2014 5.16 AIR SYSTEM Training Notes 1st line maintenance course TO COMPRESSOR BLEED VALVE TO FCU METERING UNIT TO POWER TURBINE LABYRINTH SEAL (except 1E2-1S) TO POWER TURBINE LABYRINTH SEAL (1E2-1S) TO START VALVES ASSEMBLY Type of pipes: Rigid, stainless steel Type of unions: QUINSON unions EXTERNAL AIR PIPES For training purposes only © Copyright - Turbomeca Training Edition: May 2014 5.17 AIR SYSTEM Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) ARRIEL 1 ARRIEL 1 Training Notes 1st line maintenance course AIR SYSTEM - 1ST LINE MAINTENANCE PREVENTIVE MAINTENANCE Scheduled inspections List of maintenance tasks to be carried out: - Inspection before the first flight of the day - Turn-around inspection - Inspection after the last flight of the day - Inspection after 15 flight hours or 7 days Operations to be performed to comply with Airworthiness objectives are listed in the table of mandatory maintenance tasks. Manufacturer-required maintenance tasks The manufacturer considers that the manufacturer-required maintenance tasks must be carried out at the scheduled inspection frequency. Failure to do so may cause occurrences liable to affect the engine operating safety. - Inspection at 30 flight hours Optional maintenance tasks - Inspection at 50 flight hours Optional maintenance tasks are recommended by the manufacturer as a means of improving reliability, increasing operational availability and reducing operating costs. - Inspection at 100 flight hours - Inspection at 150 flight hours - Inspection at 200 flight hours - Inspection at 300 flight hours - Inspection at 400 flight hours - Inspection at 500 flight hours - Inspection at 600 flight hours - Inspection at 750 flight hours - Inspection at 1,000 flight hours - Inspection at 1,200 flight hours Note 1: Before carrying out any maintenance tasks, remember to refer to the latest Service Bulletins and Service Letters. Note 2: The maintenance tasks shown below concern the ARRIEL 1D1 variant by way of example and may differ for other ARRIEL 1 variants. Always refer to the Maintenance Manual of the variant concerned. - Inspection at 1,500 flight hours - Inspection at 3,000 flight hours - Inspection at 3,600 flight hours For training purposes only © Copyright - Turbomeca Training Edition: May 2014 5.18 AIR SYSTEM Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) Refer to the Maintenance Manual (chapter 05). Mandatory maintenance tasks Training Notes 1st line maintenance course ARRIEL 1 PREVENTIVE MAINTENANCE (scheduled inspections) INSPECTION AT 150 FLIGHT HOURS MANUFACTURER-REQUIRED Pre TU231: - Inspection and cleaning of P2 union/Free Turbine Test of the opening and closing thresholds of the bleed valve INSPECTION AT 1,000 FLIGHT HOURS MANUFACTURER-REQUIRED Inspection of the bleed valve filter Chap. 75 Chap. 75 Chap. 75 INSPECTION AT 300 FLIGHT HOURS MANUFACTURER-REQUIRED Inspection and check of the turbine casing drain valve assy Inspection of the bleed valve Chap. 72 Chap. 75 INSPECTION AT 600 FLIGHT HOURS MANUFACTURER-REQUIRED Post TU231: - Inspection and cleaning of P2 union/Free Turbine Chap. 75 Before carrying out any maintenance tasks, remember to refer to the latest Service Bulletins and Service Letters. PREVENTIVE MAINTENANCE AIR SYSTEM - 1ST LINE MAINTENANCE For training purposes only © Copyright - Turbomeca Training Edition: May 2014 5.19 AIR SYSTEM Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) (refer to MM, chapter 05) Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) ARRIEL 1 Training Notes 1st line maintenance course Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) 6 - FUEL SYSTEM - Fuel system - Presentation .................................................................. 6.2 - Fuel Control Unit ................................................................................... 6.8 - Pressurising, stop purge and overspeed valves ............................... 6.18 - Start valves assembly .......................................................................... 6.20 - Start injectors ........................................................................................ 6.22 - Main injection system ........................................................................... 6.24 - Combustion chamber drain valve ....................................................... 6.26 - Fuel system - Operation ....................................................................... 6.28 - External fuel pipes ................................................................................ 6.32 - Fuel system - 1st line maintenance ..................................................... 6.34 - 6.37 For training purposes only © Copyright - Turbomeca Training Edition: May 2014 6.1 FUEL SYSTEM ARRIEL 1 Training Notes 1st line maintenance course FUEL SYSTEM - PRESENTATION Main components Function The fuel system supplies, distributes, controls, meters and injects the fuel. - Fuel Control Unit • Fuel pump • Fuel filter • Metering unit Position - Pressurising, stop purge and overspeed valves All the system components are located on the engine, except for the tachometer box (twin-engine configuration). - Start valves assembly Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) GENERAL - Fuel injection system. Main characteristics - Supply by the airframe system and the engine pump - Centrifugal main injection and start injection by injectors - Manual control - Fuel control: hydromechanical controlling and metering device. Note: For tables indicating the types of fuel which can be used and the corresponding US, UK, NATO and French specifications, refer to Maintenance Manual chapter 71. For training purposes only © Copyright - Turbomeca Training Edition: May 2014 6.2 FUEL SYSTEM Training Notes 1st line maintenance course ARRIEL 1 DISTRIBUTION FUEL SUPPLY CONTROL Supply: By the airframe system and the engine pump INJECTION Centrifugal main injection and start injection by injectors METERING Manual control TACHOMETER BOX (according to version) START VALVES ASSEMBLY METERING UNIT P2 MANUAL CONTROL TANK Booster pump (according to version) Airframe Fuel control: Hydromechanical controlling and metering device PRESSURISING, STOP PURGE AND OVERSPEED VALVES FUEL FILTER FUEL INJECTION SYSTEM FUEL PUMP N1 FUEL CONTROL UNIT Engine GENERAL FUEL SYSTEM - PRESENTATION For training purposes only © Copyright - Turbomeca Training Edition: May 2014 6.3 FUEL SYSTEM Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) SUPPLY ARRIEL 1 Training Notes 1st line maintenance course LOW PRESSURE FUEL SYSTEM (1E, 1S) Functional description Function The ejector is supplied with fuel from the HP pump via the astatic valve which opens at a given pressure. The ejector ensures a supply of fuel to the HP pump inlet. This system is designed for aircraft without a booster pump and assures the supply to the HP pump. Position All the components are fitted on a bracket on the underside of the protection tube. A connection between the two engines permits priming of one engine by the other. Priming can also be carried out using a hand pump. Main components - LP filter (with a by-pass valve, a pre-blockage indicator or pre-blockage pressure switch according to version) - Min. pressure switch - Pressure transmitter (optional) - Manual valve - Ejector - Astatic valve - Pre-blockage indicator - Jet. For training purposes only © Copyright - Turbomeca Training Edition: May 2014 6.4 FUEL SYSTEM Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) FUEL SYSTEM - PRESENTATION Training Notes 1st line maintenance course ARRIEL 1 ASTATIC VALVE PRE-BLOCKAGE INDICATOR (pre-blockage pressure switch in 1E version) PRESSURE TRANSMITTER (optional) To HP pump (FCU) MIN PRESSURE SWITCH LP FILTER HP pump pressure (FCU) Priming supply to other engine (1S version) EJECTOR FILTER Fuel suction from tank MANUAL VALVE HP pump pressure (FCU) To HP pump (FCU) Fuel suction from tank EJECTOR ASTATIC VALVE MANUAL VALVE MIN PRESSURE SWITCH BY-PASS VALVE To LP filter Fuel suction from tank JET EJECTOR LOW PRESSURE FUEL SYSTEM (1E, 1S) FUEL SYSTEM - PRESENTATION For training purposes only © Copyright - Turbomeca Training Edition: May 2014 6.5 FUEL SYSTEM Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) BY-PASS VALVE ARRIEL 1 Training Notes 1st line maintenance course FUEL SYSTEM - PRESENTATION Valves Fuel pump - Non-return valve Gear type pump, mechanically driven by the accessory gearbox and fitted with a pressure-relief valve. - Pressurising valve Filter - Start electro-valve The filter has a pre-blockage indicator (according to version) and a by-pass valve. - Start purge valve Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) DESCRIPTION - Stop purge valve - Overspeed electro-valve. Main and manual valves The main and manual valves are controlled by the control lever which acts at the same time on the acceleration control unit cam. Injection system - Start injectors (x 2) - Centrifugal injection wheel. Metering unit The hydromechanical controller acts on the metering needle (see next chapter). For training purposes only © Copyright - Turbomeca Training Edition: May 2014 6.6 FUEL SYSTEM ARRIEL 1 Pre-blockage indicator START ELECTRO-VALVE Pressure-relief valve FILTER Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) FUEL PUMP Training Notes 1st line maintenance course START INJECTORS Filter by-pass valve START PURGE VALVE MANUAL VALVE MAIN VALVE CONTROL LEVER Cam METERING UNIT STOP PURGE VALVE NON-RETURN VALVE PRESSURISING VALVE INJECTION WHEEL OVERSPEED ELECTRO-VALVE DESCRIPTION FUEL SYSTEM - PRESENTATION For training purposes only © Copyright - Turbomeca Training Edition: May 2014 6.7 FUEL SYSTEM ARRIEL 1 Training Notes 1st line maintenance course FUEL CONTROL UNIT Main components Function - Fuel pump The Fuel Control Unit (FCU) ensures fuel supply and fuel flow metering. - Filter (position according to version) Position Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) GENERAL - Pre-blockage indicator (1E, 1K, 1S versions only) - On the left front face of the accessory gearbox. - Manual control • Valves and cam • Anticipator Main characteristics - Metering unit. - Type: hydro-mechanical - Mounting: clamp - Replaceable components: • Filter • Pre-blockage indicator (according to version). For training purposes only © Copyright - Turbomeca Training Edition: May 2014 6.8 FUEL SYSTEM ARRIEL 1 Training Notes 1st line maintenance course Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) VALVE SHAFT CAM PRE-BLOCKAGE INDICATOR (1E, 1K, 1S versions only) Type: Hydro-mechanical Mounting: Clamp Replacable components: • Filter • Pre-blockage indicator (according to version) ANTICIPATOR FILTER (position according to version) GENERAL FUEL CONTROL UNIT For training purposes only © Copyright - Turbomeca Training Edition: May 2014 6.9 FUEL SYSTEM ARRIEL 1 Training Notes 1st line maintenance course FUEL PUMP Pressure-reducing valve Function This is a diaphragm valve which provides a constant pressure output of approx. 400 kPa (58 PSI) for the hydraulic supply of the hydromechanical governor. The pump assembly supplies fuel under determined conditions of pressure and flow. Main characteristics Operation Fuel pump - Type: spur gears - Rotation speed: proportional to N1 speed. The pump receives fuel from the aircraft LP system. The fuel is drawn in by the pump, it passes between the gears and the casing and is forced out under pressure. Description Pressure-relief valve - Pressure-relief valve setting: 3300 kPa (478.5 PSI) The assembly comprises the pressure pump and the pressurerelief valve. Fuel pump If the pump outlet pressure exceeds a given value, the pressure relief valve will open and allow fuel to return to the pump inlet thus limiting the maximum pressure in the system. It is a spur-gear pump which has a drive gear and a driven gear, the drive gear being driven by the accessory drive via the pump drive shaft which is a quill shaft. The shaft is sealed by two lip seals, with a drain between them which prevent fuel from entering the accessory gearbox. Pressure-reducing valve The pump is supplied with fuel from the aircraft system. When pump outlet pressure increases the diaphragm moves up, reducing the valve opening and thus maintaining a constant downstream pressure. Pressure-relief valve It is a conical valve held closed by a spring during normal operation. For training purposes only © Copyright - Turbomeca Training The diaphragm is subjected to fuel pressure on one side opposed by spring pressure on the other side. The position of the diaphragm determines the position of the valve. Edition: May 2014 6.10 FUEL SYSTEM Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) FUEL CONTROL UNIT Training Notes 1st line maintenance course ARRIEL 1 Type: Spur gears PUMP Pressure-relief valve setting: 3300 kPa (478.5 PSI) Rotation speed: Proportional to N1 speed DRIVEN GEAR PRESSURE-RELIEF VALVE SEALS PUMP CIRCLIP PRESSURERELIEF VALVE DOUBLE SEALING RING PRESSUREREDUCING VALVE DRIVE GEAR DRAIN FUEL PUMP (BEFORE TU 367) SHAFT SPACER SEALING RING FUEL PUMP (AFTER TU 367) FUEL PUMP FUEL CONTROL UNIT For training purposes only © Copyright - Turbomeca Training Edition: May 2014 6.11 FUEL SYSTEM Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) PRESSURERELIEF VALVE ARRIEL 1 Training Notes 1st line maintenance course FUEL CONTROL UNIT - 1E, 1K and 1S: The visual pre-blockage indicator. Function The filter retains any particles that may be in the fuel in order to protect the metering unit components. Position This is a differential visual indicator. It includes a red indicator which pops out in a transparent cover when the pressure difference across the filtering element exceeds a given value. Two O-ring seals which ensure the sealing between the indicator and the FCU body and between the upstream pressure inlet and the downstream pressure inlet. Operation - In the system: between the pump and the metering unit Normal operation - On the engine: lower part of FCU. The fuel from the pump enters the fuel filter and flows through the filtering element (from outside to inside). Main characteristics - Type: metal cartridge The filtering element retains particles larger than 20 microns. The fuel then flows to the metering unit. - Filtering ability: 20 microns Pre-blockage - By-pass valve setting: ∆P 200 kPa (39 PSID) When the filter becomes dirty, the pressure difference across the filtering element increases. - Visual pre-blockage indicator setting: ∆P 150 kPa (21.75 PSID). If the pressure difference becomes higher than the visual preblockage indicator setting, the red visual indicator pops out. Description Note: The visual pre-blockage indicator can be reset by removing the cover and pushing in the indicator. The assembly comprises: Blockage - The filtering element: O-ring seals ensure the sealing between the cartridge and the filter housing When the pressure difference across the filtering element exceeds the by-pass valve setting, the by-pass valve opens and causes the fuel flow to by-pass the filter. - The by-pass valve For training purposes only © Copyright - Turbomeca Training Edition: May 2014 6.12 FUEL SYSTEM Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) FUEL FILTER - VISUAL PRE-BLOCKAGE INDICATOR (1E, 1K, 1S) Training Notes 1st line maintenance course ARRIEL 1 CUP FILTERING CARTRIDGE FILTER BASE FUEL FILTER PRE-BLOKAGE INDICATOR FUEL FILTER BY-PASS VALVE BY-PASS VALVE RED INDICATOR NORMAL OPERATION FILTER BLOCKAGE ONSET FILTER VISUAL PRE-BLOCKAGE INDICATOR Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) PIN INDICATOR OPERATION (THE RED VISUAL INDICATOR APPEARS) TRANSPARENT COVER Type: Metal cartridge PRE-BLOCKAGE Filtering ability: 20 microns Upstream pressure FILTER BLOCKAGE OPENING OF BY-PASS VALVE By-pass valve setting: ∆P 200 kPa (39 PSID) Visual pre-blockage indicator setting: ∆P 150 kPa (21.75 PSID) Downstream pressure 1E, 1K AND 1S: VISUAL PRE-BLOCKAGE INDICATOR BLOCKAGE FUEL FILTER - VISUAL PRE-BLOCKAGE INDICATOR (1E, 1K, 1S) FUEL CONTROL UNIT For training purposes only © Copyright - Turbomeca Training Edition: May 2014 6.13 FUEL SYSTEM ARRIEL 1 Training Notes 1st line maintenance course FUEL CONTROL UNIT Operation Function Stop position A mechanical control linked to the fuel control unit permits starting control, acceleration to nominal speed and stopping. It can also be used as a manual fuel flow control in the event of automatic control failure. The collective pitch lever inputs signals to the anticipator during flight. Start and acceleration range - position b : progressive opening of the main valve; the cam frees the metering needle above a certain angle. Note: There is a start pre-selection position at 20° for the 1E2 version. Position - Interface on the left side of the FCU. Flight position Description - position c : the main valve is fully open. The manual control includes the following devices: "Manual control +" range - The main valve which permits acceleration control during the start phase and the use of the "manual control -" range - The manual valve which is used for the "manual control +" range - The acceleration control cam which controls the position of the metering needle for starting. For training purposes only © Copyright - Turbomeca Training - position a : the two valves are closed, the cam maintains the metering needle closed. - position d : progressive opening of the manual valve, the main valve remaining open. "Manual control -" range In case of automatic control failure supplying too much fuel to the engine, the control lever can be placed in the start and acceleration range b to reduce the fuel flow. Edition: May 2014 6.14 FUEL SYSTEM Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) MANUAL CONTROL Training Notes 1st line maintenance course ARRIEL 1 0 to 5° STOP POSITION CAM CONTROL LEVER CONTROL LEVER CAM MANUAL VALVE c b 1E2: 20° ACCELERATION CONTROL CAM 5° 52° 45° 90 27° IDLE POSITION CONTROL LEVER 52° FLIGHT POSITION 62° ° a METERING UNIT Fully closed Fully closed Fully closed by the cam Partially open Fully closed Partially opened by the cam Partially open Fully closed Partially opened by the cam Fully open Fully closed Controlled by the automatic control sytem through the working piston Fully open Partially open Fuel flow controlled manually through the manual valve 1E2: 20° START POSITION ANTICIPATOR MAIN VALVE MANUAL VALVE d Flight position P2 Note: In the acceleration phase from 27° to 52°, the main valve is progressively opened manually (the cam does not actuate the needle above approx. 35°) 62° to 90° MANUAL "+" RANGE MANUAL CONTROL FUEL CONTROL UNIT For training purposes only © Copyright - Turbomeca Training Edition: May 2014 6.15 FUEL SYSTEM Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) VALVE SHAFT MAIN VALVE ARRIEL 1 Training Notes 1st line maintenance course FUEL CONTROL UNIT Main components Function - Constant ∆P valve This constantly meters of the fuel injected into the combustion chamber. - Metering needle. Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) METERING UNIT Position - In the system: downstream of the pump - On the engine: in the FCU. Main characteristics - Profiled needle which moves in a calibrated orifice. - The metering needle is controlled by the control system. For training purposes only © Copyright - Turbomeca Training Edition: May 2014 6.16 FUEL SYSTEM Training Notes 1st line maintenance course CONSTANT ∆P VALVE Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) ARRIEL 1 Profiled needle which moves in a calibrated orifice The metering needle is controlled by the control system METERING NEEDLE (controlled by the control system) METERING UNIT FUEL CONTROL UNIT For training purposes only © Copyright - Turbomeca Training Edition: May 2014 6.17 FUEL SYSTEM ARRIEL 1 Training Notes 1st line maintenance course Engine running Function The pressurising valve ensures that priority of fuel flow is given to the start injectors during starting. The stop purge valve controls the fuel supply to the injection wheel: - Fuel supply during starting and in operation - Fuel shut-off and draining of the injection wheel during shutdown. It is associated with an electro-valve for a rapid engine shutdown in the event of power turbine overspeed (only on twinengine aircraft). Position - Lower left side of the combustion chamber casing. Main characteristics Pressurising valve setting: 180 kPa (26.1 PSI). Main components As soon as the fuel pressure is sufficient to open the pressurising valve, the pressure is admitted under the diaphragm which causes the closing of the purge valve and the opening of the fuel supply valve. The fuel flows to the injection wheel and is sprayed into the combustion chamber. During shut-down The normal stop selection (closing of the main valve by the control lever) results in a decrease of injection pressure. The pressurising valve closes, the pressure decreases below the diaphragm which causes the supply valve to close (as the direct pump pressure increases) and the purge valve to open: draining of fuel to prevent blockage of the distributor by carbonization of the remaining fuel. The fuel is returned to the tank (post TU 262). When the engine is completely stopped, the purge valve closes under the force of its spring (see detail). Overspeed shut-down (twin-engine configuration) Engine shut-down can also be commanded by the electro-valve which, when opened, causes the pressure to decrease below the diaphragm and the valve to move down (shut-down in case of power turbine overspeed; only in twin-engine configuration). - Pressurising valve - Stop purge valve (dual valve) - Overspeed electro-valve. For training purposes only © Copyright - Turbomeca Training Edition: May 2014 6.18 FUEL SYSTEM Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) PRESSURISING, STOP PURGE AND OVERSPEED VALVES Training Notes 1st line maintenance course STOP PURGE VALVE Pressurising valve setting: 180 kPa (26.10 PSI) Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) ARRIEL 1 PRESSURISING VALVE OVERSPEED ELECTRO-VALVE (only on twin-engine version) Pump direct pressure To the tank (post TU 262) ENGINE RUNNING DURING SHUT-DOWN PRESSURISING, STOP PURGE AND OVERSPEED VALVES For training purposes only © Copyright - Turbomeca Training Edition: May 2014 6.19 FUEL SYSTEM ARRIEL 1 Training Notes 1st line maintenance course Function Operation The start valves assembly ensures the fuel distribution to the two injectors during engine starting and their purge at the end of start. Purge before start Position Upper part of the combustion chamber casing. Fuel injection Main characteristics - Re-injection prohibit pressure switch setting: approx. 52% N1 - Start purge valve setting: • opening at 5 kPa (0.725 PSI) When starting is selected, the fuel pump pressure increases rapidly and closes the purge valve, the electro-valve is energised open and the fuel supplied by the engine pump flows to the 2 injectors which spray it into the combustion chamber. The fuel is then ignited by the sparks of the igniter plugs. Ventilation of the start injectors • closing at 120 kPa (17.4 PSI). Description - Start electro-valve - P2 ball valve - Re-injection prohibit pressure switch - Start purge valve (with cover and a support drain, according to versions). For training purposes only © Copyright - Turbomeca Training During the initial phase of starting, the fuel supplied from the aircraft system flows into the FCU, through the non-return valve to the start purge valve which opens and returns the fuel to the tank. The purpose of this phase is to expel any air which may be in the system. At the end of starting, the supply to the electro-valve is cut and the valve closes. The air under compressor pressure P2 (which has increased in the meantime) lifts the ball of the valve and flows to ventilate the injectors. This ventilation continues as long as the engine operates to prevent blockage of the injectors by carbonization of the remaining fuel. The P2 pressure actuates the pressure switch to prevent any re-injection which could cause a flame-out by suddenly reducing fuel flow to the injection wheel. Edition: May 2014 6.20 FUEL SYSTEM Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) START VALVES ASSEMBLY Training Notes 1st line maintenance course ARRIEL 1 P2 BALL VALVE START ELECTRO-VALVE AND RE-INJECTION PROHIBIT PRESSURE SWITCH COVER FUEL OUTLET TO INJECTORS P2 FUEL INLET Pump pressure PURGE BEFORE START FUEL INJECTION Pump pressure VENTILATION OF THE START INJECTORS START VALVES ASSEMBLY For training purposes only © Copyright - Turbomeca Training Edition: May 2014 PURGE TO TANK PUMP PRESSURE Re-injection prohibit pressure switch setting: Approx. 52% N1 Start purge valve setting: • opening at 5 kPa (0.725 PSI) • closing at 120 kPa (17.4 PSI) 6.21 FUEL SYSTEM Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) START PURGE VALVE (with drain, according to versions) ARRIEL 1 Training Notes 1st line maintenance course Function Operation The two start injectors spray fuel into the combustion chamber during engine starting. Starting Position The fuel is atomised and is ignited by the sparks from the igniter plugs. The flame thus produced, ignites the fuel sprayed by the centrifugal injection wheel. - On the upper part of the turbine casing at 2 o'clock and 10 o'clock - They penetrate into the mixer unit. During starting the injectors are supplied with fuel. Normal running When the engine reaches self sustaining speed (approx. 45% N1) the fuel supply to the injectors is shut off. Main characteristics P2 air is then blown through the injectors to avoid carbonisation of the residual fuel. - Type: simple injector - Quantity: 2 It should be noted that ventilation is continuous during engine running. - Ventilation: by P2 airflow. Description The injectors are mounted on the upper part of the turbine casing. They penetrate into the combustion chamber through holes in the mixer unit. They are secured by bolts onto bosses with seals and spacers to prevent leaks and adjust the depth of penetration into the combustion chamber. For training purposes only © Copyright - Turbomeca Training Edition: May 2014 6.22 FUEL SYSTEM Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) START INJECTORS Training Notes 1st line maintenance course ARRIEL 1 Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) Type: Simple injector START INJECTOR SUPPLY Quantity: 2 Ventilation: By P2 airflow START INJECTOR SPACERS AND SEALS SHROUD NUT Fuel inlet START INJECTOR IGNITER PLUG STARTING START INJECTOR VENTILATION FILTER MANIFOLD P2 JET Airflow direction NORMAL RUNNING START INJECTORS For training purposes only © Copyright - Turbomeca Training Edition: May 2014 6.23 FUEL SYSTEM ARRIEL 1 Training Notes 1st line maintenance course MAIN INJECTION SYSTEM Centrifugal injection assembly The injection system sprays fuel into the combustion chamber to give stable and efficient combustion. Position - On the engine: inside the combustion chamber. The injection wheel is mounted between the centrifugal compressor and the turbine shaft. The distributor is bolted to the diffuser backplate. Operation The fuel is delivered to the distributor by the internal supply pipe. Main characteristics It passes through the distributor's axial holes into the chamber in the injection wheel. - Type: centrifugal injection As the centrifugal injection wheel is rotating at high speed (N1) the fuel is centrifuged out through the radial holes and is sprayed between the two swirl plates. - Radial fuel supply. Description Combustion chamber fuel inlet union Fitted at the lower right front face of the compressor casing, it has a plug to test the sealing of the union. Internal supply pipe This pipe connects the inlet union to the fuel distributor. It is fitted between the front swirl plate and the diffuser back-plate. For training purposes only © Copyright - Turbomeca Training This assembly consists of a stationary distributor and a wheel. The distributor, fitted onto the diffuser back-plate, is drilled with axial holes which deliver the fuel to the wheel. The injection wheel, mounted by curvic-couplings between the compressor and the turbine shaft, is drilled with radial holes which form the fuel spraying jets. Sealing between the distributor and the wheel is achieved by pressurised labyrinth seals. It should be noted that the injection pressure is supplied by the centrifugal force and therefore the fuel system does not require very high pressures. The centrifugal injection wheel fuel chamber is sealed by pressurised labyrinth seals. There is a small air flow into the fuel chamber. During shut-down, the fuel remaining in the system is purged via the stop purge valve. Edition: May 2014 6.24 FUEL SYSTEM Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) Function Training Notes 1st line maintenance course COMBUSTION CHAMBER FUEL INLET UNION Type: Centrifugal injection FUEL SPRAYING INTO THE COMBUSTION CHAMBER CENTRIFUGAL INJECTION WHEEL Radial fuel supply DISTRIBUTOR INTERNAL SUPPLY PIPE DISTRIBUTOR CENTRIFUGAL INJECTION WHEEL (with spraying jets) COMBUSTION CHAMBER FUEL INLET UNION Fuel inlet COMBUSTION CHAMBER FUEL INLET UNION SUPPLY PIPE LEAK CHECK PLUG MAIN INJECTION SYSTEM For training purposes only © Copyright - Turbomeca Training Edition: May 2014 6.25 FUEL SYSTEM Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) ARRIEL 1 ARRIEL 1 Training Notes 1st line maintenance course Function Operation The valve drains overboard any unburnt fuel remaining in the combustion chamber. The valve has two positions: open and closed. Position - On the engine: screwed into the turbine casing lower part. Open position When the engine is not running and at the beginning of start, the valve is held open by the action of the tension spring. - Type: half-ball valve Any unburnt fuel in the combustion chamber will drain through the valve overboard to the drain system. This ensures that no fuel accumulates in the combustion chamber which could cause starting problems (e.g. overtemperature). - Setting: closing obtained at about 40% N1. Closed position Description As the engine starts the combustion chamber pressure increases. This pressure is felt on the upper surface of the half ball which moves down to close the drain. Main characteristics The drain valve includes the following components: - A threaded part to fix the valve on the combustion chamber The valve closes during the initial phase of starting for a speed of about 40% N1. - A half-ball valve mounted on a tension spring - An outlet union which connects to the drain system - A circlip which retains the valve in the body. For training purposes only © Copyright - Turbomeca Training Edition: May 2014 6.26 FUEL SYSTEM Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) COMBUSTION CHAMBER DRAIN VALVE Training Notes 1st line maintenance course ARRIEL 1 Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) Setting: Closing obtained at about approx. 40% N1 Unburnt fuel P2 air pressure CIRCLIP SPRING THREADED PART COMBUSTION CHAMBER DRAIN VALVE HALF-BALL VALVE OUTLET UNION To drain system "OPEN" position COMBUSTION CHAMBER DRAIN VALVE For training purposes only © Copyright - Turbomeca Training Edition: May 2014 "CLOSED" position 6.27 FUEL SYSTEM Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) Type: Half-ball valve ARRIEL 1 Training Notes 1st line maintenance course PRE-START - FUEL SYSTEM AIR PURGE STARTING Starting Pre-start When engine start is selected, the start accessories are electrically supplied. - The pump is not operating and there is no pressure in the system - The main and manual valves are closed - The constant ∆P valve is closed - The metering needle is closed by the acceleration control cam - The following valves are closed: • non-return valve • pressurising valve • start purge valve The constant ∆P valve operates and returns the excess fuel to the pump inlet. The fuel flow is controlled by the movement of the control lever. At 45% N1, the start accessories are de-energised by releasing the start button and the start injectors are ventilated by P2 air pressure. At 52% N1, P2 pressure opens the reinjection prohibit pressure switch to avoid an accidental fuel re-injection, which could cause engine flame-out. - The stop purge valve is in its injection position - The start electro-valve is closed. Fuel system air purge During the initial phase of starting, the fuel supplied from the airframe system flows into the FCU, through the non-return valve and to the start purge valve which opens and returns the fuel to the tank. The purpose of this phase is to expel any air which may be in the system. For training purposes only © Copyright - Turbomeca Training The pump is driven and supplies the start injectors, due to the priority given by the pressurising valve, then the centrifugal injection wheel. The control lever is moved to the flight position, progressively opening the main valve to accelerate the engine until the hydromechanical control takes over. Edition: May 2014 6.28 FUEL SYSTEM Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) FUEL SYSTEM - OPERATION Training Notes 1st line maintenance course P2 P2 STARTING 45% < N1 < 52% P2 FUEL SYSTEM AIR PURGE STARTING N1 < 45% STARTING N1 > 52% PRE-START - FUEL SYSTEM AIR PURGE - STARTING FUEL SYSTEM - OPERATION For training purposes only © Copyright - Turbomeca Training Edition: May 2014 6.29 FUEL SYSTEM Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) ARRIEL 1 ARRIEL 1 Training Notes 1st line maintenance course FUEL SYSTEM - OPERATION Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) NORMAL RUNNING - MANUAL CONTROL - ENGINE SHUT-DOWN Normal running The required fuel flow is metered by the metering needle. The metering needle position is determined by the hydromechanical control system. The fuel pump always supplies more fuel than the engine requires. The excess fuel returns to the pump inlet through the constant ∆P valve. The start injectors are continuously ventilated by P2 air circulation. Manual control The manual control is used for starting and stopping the engine. It can also be used in case of a control system failure. Engine shut-down The lever is pulled fully rearward, closing the main valve which cuts the fuel flow to the engine, causing it to run down and stop. For training purposes only © Copyright - Turbomeca Training Edition: May 2014 6.30 FUEL SYSTEM Training Notes 1st line maintenance course P2 P2 - P2 + Flight position NORMAL RUNNING P2 MANUAL CONTROL ENGINE SHUT-DOWN When the engine is completely stopped, the dual valve closes the drain under action of the spring NORMAL RUNNING - MANUAL CONTROL - ENGINE SHUT-DOWN FUEL SYSTEM - OPERATION For training purposes only © Copyright - Turbomeca Training Edition: May 2014 6.31 FUEL SYSTEM Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) ARRIEL 1 ARRIEL 1 Training Notes 1st line maintenance course EXTERNAL FUEL PIPES The external fuel pipes carry the fuel to and from the various components of the fuel system. Note: The routing of the pipes may be different according to version. Main characteristics - Type of pipes: rigid, stainless steel - Type of unions: standard (connecting flange with bolts). Description The external fuel pipes connect the various components as follows: - Fuel pump → Stop purge valve - FCU → Pressurising valve - Pressurising valve → Start electro-valve - Start electro-valve → Start injectors (2 pipes) - Start purge valve → Stop purge valve - Start purge valve → Fuel tank - Stop purge valve → Combustion chamber fuel inlet union - Pre TU262: Stop purge valve → Drain - Post TU262: Stop purge valve → Fuel tank. For training purposes only © Copyright - Turbomeca Training Edition: May 2014 6.32 FUEL SYSTEM Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) Function Training Notes 1st line maintenance course ARRIEL 1 START ELECTRO-VALVE / LEFT START INJECTOR PRESSURISING VALVE / START ELECTRO-VALVE P2 Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) START PURGE VALVE / STOP PURGE VALVE P2 FUEL PUMP / STOP PURGE VALVE START ELECTRO-VALVE / RIGHT START INJECTOR FCU / PRESSURISING VALVE STOP PURGE VALVE / COMBUSTION CHAMBER FUEL INLET UNION START PURGE VALVE / FUEL TANK STOP PURGE VALVE / FUEL TANK (post TU262) STOP PURGE VALVE / DRAIN (pre TU262) EXTERNAL FUEL PIPES For training purposes only © Copyright - Turbomeca Training Edition: May 2014 6.33 FUEL SYSTEM ARRIEL 1 Training Notes 1st line maintenance course FUEL SYSTEM - 1ST LINE MAINTENANCE PREVENTIVE MAINTENANCE (1) Scheduled inspections List of maintenance tasks to be carried out: - Inspection before the first flight of the day - Turn-around inspection - Inspection after the last flight of the day - Inspection after 15 flight hours or 7 days Operations to be performed to comply with Airworthiness objectives are listed in the table of mandatory maintenance tasks. Manufacturer-required maintenance tasks The manufacturer considers that the manufacturer-required maintenance tasks must be carried out at the scheduled inspection frequency. Failure to do so may cause occurrences liable to affect the engine operating safety. - Inspection at 30 flight hours Optional maintenance tasks - Inspection at 50 flight hours Optional maintenance tasks are recommended by the manufacturer as a means of improving reliability, increasing operational availability and reducing operating costs. - Inspection at 100 flight hours - Inspection at 150 flight hours - Inspection at 200 flight hours - Inspection at 300 flight hours - Inspection at 400 flight hours - Inspection at 500 flight hours - Inspection at 600 flight hours - Inspection at 750 flight hours - Inspection at 1,000 flight hours - Inspection at 1,200 flight hours Note 1: Before carrying out any maintenance tasks, remember to refer to the latest Service Bulletins and Service Letters. Note 2: The maintenance tasks shown below concern the ARRIEL 1D1 variant by way of example and may differ for other ARRIEL 1 variants. Always refer to the Maintenance Manual of the variant concerned. - Inspection at 1,500 flight hours - Inspection at 3,000 flight hours - Inspection at 3,600 flight hours For training purposes only © Copyright - Turbomeca Training Edition: May 2014 6.34 FUEL SYSTEM Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) Refer to the Maintenance Manual (chapter 05). Mandatory maintenance tasks Training Notes 1st line maintenance course ARRIEL 1 PREVENTIVE MAINTENANCE (scheduled inspections) INSPECTION AT 100 FLIGHT HOURS MANUFACTURER-REQUIRED - Leak test of the deceleration control unit Note: During a ground run INSPECTION AT 300 FLIGHT HOURS Chap. 73 INSPECTION AT 200 FLIGHT HOURS MANUFACTURER-REQUIRED Pre TU183: - Do a check of the FCU characteristics Chap. 73 Note: This check is to be carried out systematically in case of NR drift. The anticipator adjustment is prohibited if this check has not been carried pout. MANUFACTURER-REQUIRED Inspection of the start injectors Inspection and check of the ignition solenoid valve Inspection and check of the starting drain valve assy Inspection and check of the drain valve of the injection manifold Inspection and check of the pressurizing valve Inspection and check of the Fuel Control Unit Check of the FCU controls travel and of the immobilization of pins Note: Engine installed on helicopter Inspection and check of the starting drain valve for leaks (manual valve) Note: During a ground run Inspection and check of the re-injection prohibit switch of the ignition solenoid valve (engine running) Note: During a ground run Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) (refer to MM, chapter 05) Chap. 72 Chap. 73 Chap. 73 Chap. 73 Chap. 73 Chap. 73 Chap. 73 Chap. 73 Before carrying out any maintenance tasks, remember to refer to the latest Service Bulletins and Service Letters. PREVENTIVE MAINTENANCE (1) FUEL SYSTEM - 1ST LINE MAINTENANCE For training purposes only © Copyright - Turbomeca Training Edition: May 2014 6.35 FUEL SYSTEM ARRIEL 1 Training Notes 1st line maintenance course FUEL SYSTEM - 1ST LINE MAINTENANCE PREVENTIVE MAINTENANCE (2) Scheduled inspections List of maintenance tasks to be carried out: - Inspection before the first flight of the day - Turn-around inspection - Inspection after the last flight of the day - Inspection after 15 flight hours or 7 days Operations to be performed to comply with Airworthiness objectives are listed in the table of mandatory maintenance tasks. Manufacturer-required maintenance tasks The manufacturer considers that the manufacturer-required maintenance tasks must be carried out at the scheduled inspection frequency. Failure to do so may cause occurrences liable to affect the engine operating safety. - Inspection at 30 flight hours Optional maintenance tasks - Inspection at 50 flight hours Optional maintenance tasks are recommended by the manufacturer as a means of improving reliability, increasing operational availability and reducing operating costs. - Inspection at 100 flight hours - Inspection at 150 flight hours - Inspection at 200 flight hours - Inspection at 300 flight hours - Inspection at 400 flight hours - Inspection at 500 flight hours - Inspection at 600 flight hours - Inspection at 750 flight hours - Inspection at 1,000 flight hours Note 1: Before carrying out any maintenance tasks, remember to refer to the latest Service Bulletins and Service Letters. Note 2: The maintenance tasks shown below concern the ARRIEL 1D1 variant by way of example and may differ for other ARRIEL 1 variants. Always refer to the Maintenance Manual of the variant concerned. - Inspection at 1,200 flight hours - Inspection at 1,500 flight hours - Inspection at 3,000 flight hours - Inspection at 3,600 flight hours For training purposes only © Copyright - Turbomeca Training Edition: May 2014 6.36 FUEL SYSTEM Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) Refer to the Maintenance Manual (chapter 05). Mandatory maintenance tasks Training Notes 1st line maintenance course ARRIEL 1 PREVENTIVE MAINTENANCE (scheduled inspections) INSPECTION AT 500 FLIGHT HOURS MANUFACTURER-REQUIRED Post TU183: - Do a check of the FCU characteristics Chap. 72 Note: This check is to be carried out systematically in case of NR drift. The anticipator adjustment is prohibited if this check has not been carried out INSPECTION AT 750 FLIGHT HOURS MANUFACTURER-REQUIRED - Permeability check of the injection manifold Chap. 72 Before carrying out any maintenance tasks, remember to refer to the latest Service Bulletins and Service Letters. PREVENTIVE MAINTENANCE (2) FUEL SYSTEM - 1ST LINE MAINTENANCE For training purposes only © Copyright - Turbomeca Training Edition: May 2014 6.37 FUEL SYSTEM Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) (refer to MM, chapter 05) Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) ARRIEL 1 Training Notes 1st line maintenance course Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) 7 - CONTROL SYSTEM - Control system - Presentation ............................................................ 7.2 - Control system - Operation .................................................................. 7.6 - Control system - 1st line maintenance ............................................... 7.30 - 7.31 For training purposes only © Copyright - Turbomeca Training Edition: May 2014 7.1 CONTROL SYSTEM ARRIEL 1 Training Notes 1st line maintenance course CONTROL SYSTEM - PRESENTATION Main components Function - Fuel Control Unit (FCU) The control system is designed to adapt the engine to the aircraft's power requirements, whilst remaining within defined limits. - Engine (engine and engine systems) The main functions are: - Manual control - Airframe (various systems: control, monitoring and indication) - Tachometer box (according to version). - Speed control - Various limits - Acceleration control - Overspeed detection. Main characteristics - Hydromechanical control - Manual control. For training purposes only © Copyright - Turbomeca Training Edition: May 2014 7.2 CONTROL SYSTEM Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) GENERAL Training Notes 1st line maintenance course ARRIEL 1 Hydromechanical control Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) MAIN CHARACTERISTICS Manual control AIRFRAME (various systems) TEST MAIN FUNCTIONS - Manual control FUEL CONTROL UNIT TACHOMETER BOX (according to version) - Speed control - Various limits - Acceleration control - Overspeed detection ENGINE (engine and engine systems) GENERAL CONTROL SYSTEM - PRESENTATION For training purposes only © Copyright - Turbomeca Training Edition: May 2014 7.3 CONTROL SYSTEM ARRIEL 1 Training Notes 1st line maintenance course CONTROL SYSTEM - PRESENTATION The complete system includes airframe components, engine components and the FCU. Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) DESCRIPTION Airframe components - Control components (control lever and anticipator) - Monitoring components (indications, warning lights, etc.) Engine components - Hydromechanical components: • Stop purge valve • Start purge valve • Start electro-valve • Pressurising valve • Start injectors • Main injection system - FCU components: • Power turbine speed governor • Gas generator speed governor • Acceleration control unit • Metering unit • Deceleration control unit. For training purposes only © Copyright - Turbomeca Training Edition: May 2014 7.4 CONTROL SYSTEM Training Notes 1st line maintenance course ARRIEL 1 START ELECTRO-VALVE START INJECTORS POWER TURBINE SPEED GOVERNOR START PURGE VALVE CONTROL LEVER GAS GENERATOR SPEED GOVERNOR STOP PURGE VALVE ACCELERATION CONTROL UNIT METERING UNIT DECELERATION CONTROL UNIT PRESSURISING VALVE INJECTION WHEEL DESCRIPTION CONTROL SYSTEM - PRESENTATION For training purposes only © Copyright - Turbomeca Training Edition: May 2014 7.5 CONTROL SYSTEM Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) ANTICIPATOR ARRIEL 1 Training Notes 1st line maintenance course CONTROL SYSTEM - OPERATION Adaptation to requirements Installation configuration The gas generator supplies power to the power turbine which is connected to the helicopter main rotor. Installation requirements - Aircraft rotor speed (NR) almost constant in all operating conditions (because of the rotor efficiency) whatever the load applied - Max. torque limitation (imposed by the mechanical transmission and the helicopter main gearbox) - Power turbine rotation speed (N2) within given limits (in fact almost constant, as it is connected to the rotor) The control system ensures the engine adaptation to the requirements by metering the fuel flow WF sprayed into the combustion chamber. Thus, the gas generator adapts automatically to the requirements (N1 demand) to maintain constant power turbine rotation speed N2 whilst keeping all the other parameters within determined limits. This adaptation is illustrated by: - The diagram W/N2 which illustrates the power W, the max. torque TRQ and the rotation speeds N1 and N2 - The diagram N1/N2 which illustrates the N1/N2 relationship. - Limitation of the gas generator rotation speed N1: • Max. N1 (maximum engine power) • Min. N1 (to avoid critical speeds) - Load sharing (equal sharing of loads between the 2 engines) - Protection against surge, flame-out, overtemperature… For training purposes only © Copyright - Turbomeca Training Edition: May 2014 7.6 CONTROL SYSTEM Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) CONTROL Training Notes 1st line maintenance course ARRIEL 1 NR N2 Q W Ma TRQ qu or t x. Max. N1 R eT Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) N1 W N1 isospeeds TET Min. N1 WF Control system N2 POWER W / N1, N2 N1 REQUIREMENTS Max. - NR - N2 - Max. torque TRQ - N1 - W eng 1 = W eng 2 - Protections Nominal N2 Operating range Min. INSTALLATION CONFIGURATION AND REQUIREMENTS N1 / N2 N2 ADAPTATION TO REQUIREMENTS CONTROL CONTROL SYSTEM - OPERATION For training purposes only © Copyright - Turbomeca Training Edition: May 2014 7.7 CONTROL SYSTEM ARRIEL 1 Training Notes 1st line maintenance course CONTROL SYSTEM - OPERATION Compensation Static droop Each governor (N2 and N1) uses the principle of the centrifugal governor (a system invented by James Watt), in which a control spring is set in opposition to a flyweight. The spring attempts to open the metering valve and is opposed by the centrifugal force generated by the flyweight. At a stabilised rating, the system is in equilibrium: the force exerted by the spring is equal to the centrifugal force (Fs = Fc). There is therefore a given fuel flow and a nominal rating. In a transient rating, e.g. when the engine rpm decreases (due to the increase in the resisting torque), the centrifugal force decreases. The force exerted by the spring therefore becomes the greater of the two and opens the metering valve. This increases the engine rpm until the equilibrium is re-established (Fs = Fc). Although the equilibrium has been re-established, the spring is now less compressed than at the previous engine rpm. It therefore exerts less force, which leads to a slight reduction in the nominal engine rpm. In this type of control system, the N1 speed is made to be inversely proportional to the N2. The relationship between N1 and N2 illustrates this proportionality and the variation in N2 is referred to as "static droop". As the largest load variations are caused by changes in collective pitch, a link between the collective pitch lever and the governor allows the system to compensate for the static droop. In addition, the detection phase is brought forward (hence the name "anticipator") to reduce the response time. To do this, a cam is added to compress the spring so that it exerts the same force in all collective pitch positions. The diagram shows the apparent static-droop line for different collective pitch positions (anticipator effect): In the diagram: θ1 = fine pitch, θ2 = medium pitch, θ3 = coarse pitch. In operation, points 1, 2 and 3 are obtained and the static droop is therefore compensated for, i.e. the power turbine speed and therefore the rotor speed are almost constant in all operating conditions. In transient ratings, the power turbine speed varies, but the governor acts to bring it very quickly back to its nominal value, to within the value of the static droop. Note: The static droop is slightly overcompensated. Although the "static droop" ensures the stability of the system, it is not acceptable because the helicopter rotor requires one constant rotation speed. For training purposes only © Copyright - Turbomeca Training Edition: May 2014 7.8 CONTROL SYSTEM Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) STATIC DROOP - COMPENSATION Training Notes 1st line maintenance course L1 L2 WF/N1 L1 L1 WF/N1 3 2 θ3 1 θ2 θ1 Static droop N2 N2 STATIC DROOP - COMPENSATION CONTROL SYSTEM - OPERATION For training purposes only © Copyright - Turbomeca Training Edition: May 2014 7.9 CONTROL SYSTEM Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) ARRIEL 1 ARRIEL 1 Training Notes 1st line maintenance course CONTROL SYSTEM - OPERATION The system meters the fuel flow in order to match the engine power to the requirements thus keeping power turbine rotation speed constant. The control components are contained in the hydromechanical unit mounted on the front face of the accessory gearbox. Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) PRINCIPLE OF THE CONTROL LOOP Operation of the control loop The power turbine governor compares the actual speed N2 with a speed datum which varies with the collective pitch. It determines a speed datum (N1*) which is a function of the difference measured. The gas generator governor compares the datum speed (N1*) and the actual speed (N1) and meters the fuel to maintain the datum speed, thus matching the gas generator to the conditions. The acceleration control unit limits the transient fuel flow (WF) variations in relation to P2 pressure so as to prevent compressor surge while permitting quick response times. For training purposes only © Copyright - Turbomeca Training Edition: May 2014 7.10 CONTROL SYSTEM Training Notes 1st line maintenance course ARRIEL 1 POWER TURBINE GAS GENERATOR LOAD TRQ (e.g. collective pitch) t N2 t MAIN GEARBOX N2 SPEED (Transient variation and quick return to nominal speed) P2 WF ACCELERATION CONTROL UNIT COLLECTIVE PITCH CONTROL θ t + FUEL FLOW WF (Variation controlled by the governor) N1 GAS GENERATOR SPEED GOVERNOR WF N1 N1* + N2 POWER TURBINE SPEED GOVERNOR + t N1 SPEED (Increase or decrease to match the load variations) N2* VARIATION OF THE MAIN PARAMETERS IN TIME PRINCIPLE OF THE CONTROL LOOP CONTROL SYSTEM - OPERATION For training purposes only © Copyright - Turbomeca Training Edition: May 2014 7.11 CONTROL SYSTEM Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) TRQ ARRIEL 1 Training Notes 1st line maintenance course POWER TURBINE GOVERNOR GAS GENERATOR GOVERNOR This proportional type governor determines a datum signal according to the anticipator signal and the actual speed. This integral type governor controls the datum speed demanded by the power turbine governor. It achieves this control by metering the fuel flow. In stabilized conditions, the flyweight centrifugal force balances the datum spring force. The lever is in a fixed position in front of the potentiometric jet. The reduced pressure flows to the low pressure and a modulated pressure is established in the chamber. The amplifier piston (subjected to a reference pressure on one side and to the modulated pressure on the other side) determines the N1 datum transmitted to the gas generator governor by a lever and a plunger. Transient conditions, the anticipator modifies the spring force while the centrifugal force changes. The lever pivots and moves in front of the potentiometric jet thus altering the leak and therefore changing the modulated pressure. The amplifier piston then moves and, by means of the lever and plunger, sets a new datum on the gas generator governor. The gas generator adapts itself to the new condition until the balance is regained. In stabilized conditions, the flyweight centrifugal force balances the force of the datum spring. The lever is in a fixed position and the valve determines a given modulated pressure. The working piston controls a given position of the metering needle which meters the fuel flow to obtain the required rotation speed. The system is "in balance". In transient conditions, we have seen that the power turbine governor determines a new datum which upsets the balance. The lever moves, the leak varies and consequently the modulated pressure. The working piston moves the metering needle until the new N1 datum is obtained. The gas generator speed increases or decreases, thus regulating engine output power to match the load and obtain a constant power turbine speed. Thermal compensator The thermal compensator moves the potentiometric jet as a function of the fuel temperature, which slightly modifies the modulated pressure, thus maintaining the max. N1 speed constant. For training purposes only © Copyright - Turbomeca Training Edition: May 2014 7.12 CONTROL SYSTEM Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) CONTROL SYSTEM - OPERATION Training Notes 1st line maintenance course ARRIEL 1 N2 DATUM SPRING Modulated pressure N2 (approx. 280 kPa) Modulated pressure N1 (approx. 300 kPa) AMPLIFIER PISTON LEVER POTENTIOMETRIC JET Reduced pressure (approx. 400 kPa) N1 SPEED DETECTOR (flyweight) MAX N1 STOP LEVER MIN N1 STOP DAMPING DEVICE N1 DATUM PLUNGER N1 DATUM SPRING THERMAL COMPENSATOR POTENTIOMETRIC JET WORKING PISTON METERING NEEDLE POWER TURBINE GOVERNOR AND GAS GENERATOR GOVERNOR CONTROL SYSTEM - OPERATION For training purposes only © Copyright - Turbomeca Training Edition: May 2014 7.13 CONTROL SYSTEM Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) ANTICIPATOR Low pressure (approx. 100 kPa) N2 SPEED DETECTOR (flyweight) ARRIEL 1 Training Notes 1st line maintenance course ACCELERATION CONTROL UNIT DECELERATION CONTROL UNIT It limits fuel flow increase in transient conditions, in order to prevent compressor surge during acceleration. In some versions, a deceleration control unit (or min flow limiter) is included in the metering unit to prevent flame-out during deceleration. In stabilized conditions, there is a gap between the fork and the metering needle. The position of the metering needle is determined by the working piston. In load increase transient conditions, the governor "responds" and the working piston moves rapidly. Under the action of its spring, the metering needle opens until it stops against the fork. This displacement represents what is called "instant flow increase" initiating the acceleration. Then the subsequent increase in P2 pressure causes the deformation of the capsule which permits further opening of the metering needle until it comes into contact with the working piston. For training purposes only © Copyright - Turbomeca Training In load decrease transient conditions, the closing of the metering needle is limited by a mechanical stop. This mechanical stop is controlled by a diaphragm subjected to P2 pressure. The stop withdraws as the P2 pressure decreases in order to prevent engine flame-out during rapid deceleration. Edition: May 2014 7.14 CONTROL SYSTEM Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) CONTROL SYSTEM - OPERATION Training Notes 1st line maintenance course ARRIEL 1 Max. flow for a determined P2 pressure (lever mechanism position) Max. X WF Max. flow stop of the acceleration control unit Min. flow curve as a function of P2 pressure "X" instant flow increase = distance between the metering valve position and fork position Min. flow stop of the acceleration control unit Min. P2 ACCELERATION CURVE (Fuel flow WF as a function of compressor pressure P2) WORKING PISTON GAP (x) CAM FUEL METERING NEEDLE WORKING PISTON DECELERATION CONTROL UNIT CAM x P0 ACCELERATION CAPSULE ACCELERATION CAPSULE LEVER MECHANISM DIAGRAM OF THE MECHANISM P2 DECELERATION CURVE (WF as a function of P2) P0 P2 BAROSTATIC DEVICE P2 METERING NEEDLE LEVER MECHANISM ACCELERATION CONTROL UNIT AND DECELERATION CONTROL UNIT CONTROL SYSTEM - OPERATION For training purposes only © Copyright - Turbomeca Training Edition: May 2014 7.15 CONTROL SYSTEM Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) WF ARRIEL 1 Training Notes 1st line maintenance course CONTROL SYSTEM - OPERATION Operation Metering valve The metering valve consists of a profiled needle which moves in a calibrated orifice. Graph of fuel flow (WF) as a function of metering valve position (S): each position corresponds to a fuel flow and each displacement ∆S corresponds to a proportional flow variation ∆WF. The fuel under pump pressure flows through the passage determined by the needle sliding in the orifice. Constant ∆P valve To obtain a fuel flow solely dependent on the metering valve position, the constant ∆P valve keeps a constant pressure difference across the metering valve. It consists of a diaphragm subjected to pressure variation. Any variation of pressure difference (∆P) is detected by this valve, which returns more or less fuel to the pump inlet. In fact, the pump always supplies more fuel than the engine requires, and the excess fuel is returned to the pump inlet by this valve. The ∆P transient variations are due to the pump pressure variations, to the downstream pressure variations and of course to the displacement of the metering valve. For example: when the metering valve opens, the pressure difference decreases, the ∆P valve diaphragm senses this and moves to close the return. More fuel is admitted to the engine, the upstream pressure increases and the nominal ∆P is regained. For training purposes only © Copyright - Turbomeca Training Edition: May 2014 7.16 CONTROL SYSTEM Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) METERING UNIT Training Notes 1st line maintenance course ARRIEL 1 CONSTANT ∆P VALVE FUEL RETURN WF P2 P0 ∆WF S ∆S WF AS A FUNCTION OF METERING VALVE POSITIONS (S) METERING VALVE FUEL OUTLET (WF) METERING UNIT CONTROL SYSTEM - OPERATION For training purposes only © Copyright - Turbomeca Training Edition: May 2014 7.17 CONTROL SYSTEM Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) FUEL INLET ARRIEL 1 Training Notes 1st line maintenance course CONTROL SYSTEM - OPERATION Min. governed speed Limits of gas generator speeds The gas generator rotation speed varies (to adapt the engine to changing conditions) between two extreme limits represented by adjustable mechanical stops. Max. speed It is automatically limited by an adjustable mechanical stop which represents the max operating rating. MTOP-Max. Take-Off Power in the case of a single engine (in fact, this rating is given at a value slightly lower than the mechanical stop and the engine must be operated not to overcome it). MCP -Max. Contingency Power in the case of engine failure during take-off or landing of a twin engine helicopter (OEI 2 min. 30 sec.) The effect of fuel temperature on the speed (variation of fuel viscosity changing the balance point of the hydromechanical governor) is compensated by the capsule in order to obtain speed invariability (especially max. N1). A slight max. N1 variation is however introduced but within given limits. For training purposes only © Copyright - Turbomeca Training It is limited by an adjustable mechanical stop to avoid low speeds corresponding to critical ratings. In operation, this limit is practically never reached because, even at zero torque, the power to drive the compressor requires a higher speed. Therefore, the stop is only a safety measure and it is only adjusted on the FCU test rig. Limits of fuel flow Fuel flow variation in transient conditions is limited by the acceleration control unit to obtain an optimum acceleration without compressor surge. The acceleration rate determines the response time. The slope of acceleration is only adjustable on the test rig. The min. fuel flow (limit to prevent flame-out) is limited by a mechanical stop on the metering needle. In some versions, this stop is variable with P2 pressure; it is also called the deceleration control unit. The max. fuel flow is determined by the full opening of the metering needle for a given pressure difference ∆P. It is a factory adjustment which represents a sort of power limitation. In manual control (emergency control), the max. fuel flow is limited at a lower value to avoid exceeding of the limits. Edition: May 2014 7.18 CONTROL SYSTEM Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) LIMITS Training Notes 1st line maintenance course ARRIEL 1 N1 N1 max. as a function of fuel temperature N1 limit to ensure power WF Metering unit max. WF Manual control max. WF (emergency) Temperature N1 LIMITS Metering unit min. WF (with deceleration control unit) Metering unit min. WF (without deceleration control unit) P2 FUEL FLOW LIMITS (WF) LIMITS CONTROL SYSTEM - OPERATION For training purposes only © Copyright - Turbomeca Training Edition: May 2014 7.19 CONTROL SYSTEM Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) N1 thermal limit ARRIEL 1 Training Notes 1st line maintenance course CONTROL SYSTEM - OPERATION Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) TORQUE LIMITATION AND POWER TURBINE OVERSPEED DETECTION SYSTEM Torque limitation A max. torque limit is required by the mechanical transmission. The control system does not ensure a torque limit and the operating instructions should be observed to prevent any overtorque. The flight manual indicates the torque limits: also see chapter "indication" of this manual for details of the torque measuring system. Power turbine overspeed detection system This detection system is not included in the control unit but is often mentioned among the functions of the engine control system. The overspeed detection system is designed mainly to take into account the case of shaft failure resulting in a very sudden acceleration which cannot be contained by the speed governor. The system includes a speed detector, a tachometer box, the overspeed electro-valve and the stop purge valve. The system is currently only used on twin-engine versions. For training purposes only © Copyright - Turbomeca Training Edition: May 2014 7.20 CONTROL SYSTEM Training Notes 1st line maintenance course STOP PURGE VALVE WF TACHOMETER BOX Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) ARRIEL 1 N2 DETECTOR TRQ TEST TORQUE INDICATOR OVERSPEED ELECTRO-VALVE TORQUE LIMITATION - POWER TURBINE OVERSPEED DETECTION SYSTEM CONTROL SYSTEM - OPERATION For training purposes only © Copyright - Turbomeca Training Edition: May 2014 7.21 CONTROL SYSTEM ARRIEL 1 Training Notes 1st line maintenance course CONTROL SYSTEM - OPERATION As regards the operation, the control system performance determines some flight characteristics. The following can be distinguished: - The response time It is the transient speed variation occurring during a load variation. The amplitude of this variation can be observed on the rotor speed indicator; it is related to the other characteristics. Static variation of power turbine speed - The static and dynamic power turbine speed variations It can be defined as the speed variation at different ratings. This static variation (a static droop which is slightly overcompensated) can be checked by noting NR speed at different operating points (eg: ground fine pitch and cruise pitch). With the increase of power, the NR increases slightly within given limits. - The max. speed of the gas generator. Response time It can be defined as the time required to regain power turbine nominal speed in transient conditions. The response time is closely associated to the rate of acceleration of the gas generator. A check of the response time can be made by recording parameters during a load application. It is less than 4 seconds between N1 min. and max. in standard conditions. For training purposes only © Copyright - Turbomeca Training Dynamic variation of power turbine speed Max. available speed of the gas generator It is the max. speed that can be obtained from the gas generator (take-off on single engine and max. contingency on twin engine). This rating can be checked on a load application, noting the max speed obtained when the rotor speed starts decreasing. Edition: May 2014 7.22 CONTROL SYSTEM Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) CONTROL SYSTEM PERFORMANCE Training Notes 1st line maintenance course N2 N1 Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) ARRIEL 1 Max. 100% < 4 sec. 90 time 80 70 < 4 sec. Min. 100% RESPONSE TIME AND DYNAMIC VARIATION OF THE POWER TURBINE SPEED N2 N2 STATIC VARIATION OF N2 POWER TURBINE SPEED CONTROL SYSTEM PERFORMANCE CONTROL SYSTEM - OPERATION For training purposes only © Copyright - Turbomeca Training Edition: May 2014 7.23 CONTROL SYSTEM ARRIEL 1 Training Notes 1st line maintenance course CONTROL SYSTEM - OPERATION Principle of load sharing Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) TWIN-ENGINE CONFIGURATION In normal conditions, the helicopter rotor is driven by the two power turbines and therefore: NR = k.N2 eng 1 = k.N2 eng 2 The speed signals received by the two power turbine governors being identical (as well as the signals from the collective pitch), they determine identical datum signals sent to the two gas generator governors which meter fuel flow to keep them constant. As the power is closely related to the N1 speed and as the efficiency does not vary much from one power turbine to another, a fairly good load sharing is obtained. Operation on one engine In this case, the engine remaining in operation supplies the power while the other one is disconnected by the free wheel. The limit of the operative engine is represented by the max. contingency rating automatically limited by the fuel control unit. This rating, determined for engine failure during take-off or landing, has a limited duration: 2 min. 30 sec. For training purposes only © Copyright - Turbomeca Training Edition: May 2014 7.24 CONTROL SYSTEM Training Notes 1st line maintenance course MAIN GEARBOX NR = k.N2 eng1 = k.N2 eng2 COLLECTIVE PITCH FREE WHEEL REDUCTION GEARBOX N NR N2 (1 and 2) TRQ TRQ1 and TRQ2 POWER TURBINE GAS GENERATOR N2 T4 Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) ARRIEL 1 T4 N1 Max. POWER TURBINE GOVERNOR WF N1 N1 TRIM N2* N1* GAS GENERATOR GOVERNOR TWIN-ENGINE CONFIGURATION CONTROL SYSTEM - OPERATION For training purposes only © Copyright - Turbomeca Training Edition: May 2014 7.25 CONTROL SYSTEM ARRIEL 1 Training Notes 1st line maintenance course CONTROL SYSTEM - OPERATION Evolution of parameters Effects of a load increase θ - Collective pitch Sudden increase from min. to max. almost instantly t=0 - "Start" = Collective pitch movement θ - The pitch increases W1 > W - The resisting torque becomes higher than the drive torque N2 - The power turbine rotation speed decreases G - The N2 governor detects the 2 signals, and sends a datum increase to the N1 governor: the N1 governor increases the fuel flow WF WF - Instantaneous flow step P2 - The compressor discharge pressure increases AC - The acceleration control unit enables the acceleration to continue Combustion N1 N2 - Power turbine speed Transient decrease and rapid return to nominal speed after a slight overshoot, and a slight overcompensation of the static droop N1 - Gas generator speed Speed increase and stabilisation after a slight overshoot t - Time in seconds - The flow WF increases in the combustion chamber - increases, the output power W increases, the N2 speed stops decreasing and returns to its nominal value when the equilibrium between torques W1 = W is achieved. t < 4 sec. - End of transient For training purposes only © Copyright - Turbomeca Training Edition: May 2014 7.26 CONTROL SYSTEM Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) CONTROL SYSTEM LOOP - LOAD INCREASE Training Notes 1st line maintenance course ARRIEL 1 Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) NR t=0 t t<4 W=W N2 1 W >W N2 1 3 1 N2 2 G N2 W WF N1 P2 N1 t 2 3 1 t 1 3 AC 2 Combustion 2 3 WF 1 Effects of a load increase N1 N2 Evolution of parameters during a load increase CONTROL SYSTEM LOOP - LOAD INCREASE CONTROL SYSTEM - OPERATION For training purposes only © Copyright - Turbomeca Training Edition: May 2014 7.27 CONTROL SYSTEM ARRIEL 1 Training Notes 1st line maintenance course CONTROL SYSTEM - OPERATION Evolution of parameters Effects of a load decrease θ - Collective pitch Rapid decrease of pitch t=0 - "Start" = Collective pitch movement θ - The pitch decreases W1 < W - The resisting torque becomes lower than the drive torque N2 - The power turbine rotation speed increases N1 - Gas generator speed Speed decrease and stabilisation G - The governor detects the N2 increase and decreases the fuel flow WF t WF - Instantaneous deceleration flow P2 - The compressor discharge pressure decreases DC - The deceleration control unit limits the min. fuel flow (if needs be) Combustion N1 N2 - Power turbine speed Transient increase and return to nominal speed (within the static droop) - Time in seconds - The flow WF decreases in the combustion chamber - decreases, the output power W decreases, the N2 speed returns to its nominal value. t < 4 sec. - End of transient For training purposes only © Copyright - Turbomeca Training Edition: May 2014 7.28 CONTROL SYSTEM Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) CONTROL SYSTEM LOOP - LOAD DECREASE Training Notes 1st line maintenance course ARRIEL 1 t=0 t<4 t N2 1 W <W N2 1 W =W Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) NR 2 1 3 N2 t N2 N1 G W WF N1 P2 1 3 2 1 DC t 3 1 2 Combustion WF N1 3 N2 2 Effects of a load decrease Evolution of parameters during a load decrease CONTROL SYSTEM LOOP - LOAD DECREASE CONTROL SYSTEM - OPERATION For training purposes only © Copyright - Turbomeca Training Edition: May 2014 7.29 CONTROL SYSTEM ARRIEL 1 CONTROL SYSTEM - 1ST LINE MAINTENANCE Mandatory maintenance tasks Refer to the Maintenance Manual (chapter 05). Operations to be performed to comply with Airworthiness objectives are listed in the table of mandatory maintenance tasks. Scheduled inspections Manufacturer-required maintenance tasks List of maintenance tasks to be carried out: - Inspection before the first flight of the day - Turn-around inspection - Inspection after the last flight of the day The manufacturer considers that the manufacturer-required maintenance tasks must be carried out at the scheduled inspection frequency. Failure to do so may cause occurrences liable to affect the engine operating safety. - Inspection after 15 flight hours or 7 days Optional maintenance tasks - Inspection at 30 flight hours Optional maintenance tasks are recommended by the manufacturer as a means of improving reliability, increasing operational availability and reducing operating costs. - Inspection at 50 flight hours - Inspection at 100 flight hours - Inspection at 150 flight hours - Inspection at 200 flight hours - Inspection at 300 flight hours - Inspection at 400 flight hours - Inspection at 500 flight hours - Inspection at 600 flight hours - Inspection at 750 flight hours Note 1: Before carrying out any maintenance tasks, remember to refer to the latest Service Bulletins and Service Letters. Note 2: The maintenance tasks shown below concern the ARRIEL 1D1 variant by way of example and may differ for other ARRIEL 1 variants. Always refer to the Maintenance Manual of the variant concerned. - Inspection at 1,000 flight hours - Inspection at 1,200 flight hours - Inspection at 1,500 flight hours - Inspection at 3,000 flight hours - Inspection at 3,600 flight hours For training purposes only © Copyright - Turbomeca Training Edition: May 2014 7.30 CONTROL SYSTEM Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) PREVENTIVE MAINTENANCE Training Notes 1st line maintenance course Training Notes 1st line maintenance course ARRIEL 1 PREVENTIVE MAINTENANCE (scheduled inspections) INSPECTION AFTER THE LAST FLIGHT OF THE DAY MANDATORY Post TU207: - Carry out a consistency check Chap. 05 Note: engines equipped with a tachometer box with cycle counting aid Record in the engine log book the cumulated number of C1 and C2 cycles consumed since the last recording Chap. 05 INSPECTION AT 100 FLIGHT HOURS MANUFACTURER-REQUIRED Engine health inspection Note: In flight Aircraft documentation Before carrying out any maintenance tasks, remember to refer to the latest Service Bulletins and Service Letters. PREVENTIVE MAINTENANCE CONTROL SYSTEM - 1ST LINE MAINTENANCE For training purposes only © Copyright - Turbomeca Training Edition: May 2014 7.31 CONTROL SYSTEM Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) (refer to MM, chapter 05) Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) Training Notes 1st line maintenance course 8 - MEASUREMENT AND INDICATING SYSTEMS Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) ARRIEL 1 - Measurement and indicating systems - Presentation ....................... 8.2 - Speed measurement and indicating system ..................................... 8.4 - T4 measurement and indicating system ............................................. 8.10 - Torque measurement and indicating system ..................................... 8.14 - Miscellaneous indications ................................................................... 8.18 - Measurement and indicating systems - 1st line maintenance ......... 8.22 - 8.23 For training purposes only © Copyright - Turbomeca Training Edition: May 2014 8.1 MEASUREMENT AND INDICATING SYSTEMS ARRIEL 1 Training Notes 1st line maintenance course Different measurement and indicating systems Functions The measurement and indicating systems perform the following functions: - Check that the engine is operating within its defined limits - Detect and signal failures or abnormal changes in parameters - Check certain operating phases. - N2 (power turbine rotation speed) - T4 (gas generator turbine outlet temperature) - Engine torque - Oil pressure and temperature Note: A distinction is made between control parameters (N1 and torque) and monitoring parameters (N2, TET, oil pressure and oil temperature). For training purposes only © Copyright - Turbomeca Training - N1 (gas generator rotation speed) - Miscellaneous (indicator lights and monitoring devices). Edition: May 2014 8.2 MEASUREMENT AND INDICATING SYSTEMS Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) MEASUREMENT AND INDICATING SYSTEMS - PRESENTATION Training Notes 1st line maintenance course ARRIEL 1 - Check that the engine is operating within its defined limits - Detect and signal failures or abnormal changes in parameters T4 GAS TEMPERATURE - Check certain operating phases Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) FUNCTIONS MISCELLANEOUS (indicator lights and monitoring devices) OIL PRESSURE AND TEMPERATURE VITESSE N1 EXCEPT 1E, 1S: N2 SPEED ENGINE TORQUE 1E, 1S: N2 SPEED MEASUREMENT AND INDICATING SYSTEMS - PRESENTATION For training purposes only © Copyright - Turbomeca Training Edition: May 2014 8.3 MEASUREMENT AND INDICATING SYSTEMS ARRIEL 1 Training Notes 1st line maintenance course PRESENTATION Operation Function N1 is an operating parameter as it reflects the engine power and serves to determine the limit ratings. This system measures the rotation speeds of the gas generator (N1) and the power turbine (N2). The N2 signal is used for the N2 indication (associated with the NR indication). Main characteristics - Type: • tachometer transmitter • phonic wheel (according to version) - Transmitter signals: frequency proportional to the rotation speed. Main components - N1 speed transmitter - N2 speed transmitter (optional) - Electrical harnesses for connection to the indicators. Description One or two tachometer generators (N2 optional) linked to one or two indicators. For training purposes only © Copyright - Turbomeca Training Edition: May 2014 8.4 MEASUREMENT AND INDICATING SYSTEMS Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) SPEED MEASUREMENT AND INDICATING SYSTEM Training Notes 1st line maintenance course ARRIEL 1 N1 SPEED SENSOR ELECTRICAL CONNECTOR PHONIC WHEEL (starter-generator drive shaft) N1 SPEED SENSOR N2 SPEED SENSOR REAR OF THE INTERMEDIATE GEAR OF THE REDUCTION GEARBOX N2 INDICATOR ACCESSORY GEARBOX REAR FACE ELECTRICAL CONNECTOR N2 SPEED SENSOR PRESENTATION SPEED MEASUREMENT AND INDICATING SYSTEM For training purposes only © Copyright - Turbomeca Training Edition: May 2014 8.5 MEASUREMENT AND INDICATING SYSTEMS Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) N1 INDICATOR ARRIEL 1 Training Notes 1st line maintenance course Description N1 AND N2 TACHOMETER TRANSMITTERS (EXCEPT 1E, 1S) The assembly consists of: Function The system measures the gas generator rotation speed (N1) and the power turbine rotation speed (N2). Position - A tachometer-generator whose rotor is a mechanically driven permanent magnet. It delivers a 3-phase AC voltage electrical signal whose frequency is proportional to the speed - An asynchronous motor which receives the signal from the transmitter and displays the speed on a graduated dial. General operation - On the rear face of the accessory gearbox: • N1 on the right-hand side • N2 on the left-hand side (according to version). The N1 signal is a control parameter because it reflects the power being supplied and determines the operating "limit ratings". The N2 signal is an indicating parameter (associated with the rotor rotation speed indication (NR)). Main characteristics N1/N2 operation - Type: • Tachometer-transmitter • 3-phase permanent magnet generator The rotation of the permanent magnet in front of the three windings induces an AC voltage. - Transmitter signals: frequency proportional to the rotation speed The frequency of this AC voltage is proportional to the rotation speed. - Quantity: 2 identical N1/N2 transmitters (interchangeable). For training purposes only © Copyright - Turbomeca Training Edition: May 2014 8.6 MEASUREMENT AND INDICATING SYSTEMS Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) SPEED MEASUREMENT AND INDICATING SYSTEM Training Notes 1st line maintenance course ARRIEL 1 BODY Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) Type: - Tachometer-transmitter - 3-phase permanent magnet generator Transmitter signals: Frequency proportional to the rotation speed Quantity: 2 identical N1/N2 transmitters (interchangeable) ELECTRICAL PLUG STATOR INDICATOR N1 AND N2 TACHOMETER TRANSMITTERS (EXCEPT 1E, 1S) SPEED MEASUREMENT AND INDICATING SYSTEM For training purposes only © Copyright - Turbomeca Training Edition: May 2014 8.7 MEASUREMENT AND INDICATING SYSTEMS ARRIEL 1 Training Notes 1st line maintenance course SPEED MEASUREMENT AND INDICATING SYSTEM Description The system consists of a toothed wheel, called a phonic wheel, rotating in front of an electro-magnetic pick-up which is connected to an indicator. Function The system measures the gas generator rotation speed (N1) and the power turbine rotation speed (N2). Position - N1 sensor: on the starter-generator drive shaft - N2 sensor: at the intermediate gear of the reduction gearbox casing. Main characteristics Operation The passage of the teeth in front of the electro-magnetic sensor induces an alternating current in the sensor windings. This current has a frequency proportional to the speed and the number of teeth: F= nd x N 60 (nd = Number of teeth; N = rotation speed in rpm; F = frequency) - Type: electro-magnetic The signal from the sensor is transmitted to the cockpit indicator which transforms it into an indication which may be analog, digital or both. - Quantity: 2 (interchangeable) - N1 phonic wheel: • Quantity: 1 • On the starter-generator drive shaft - N2 phonic wheel: • Quantity: 1 • On the rear of the intermediate gear of the reduction gearbox. For training purposes only © Copyright - Turbomeca Training Edition: May 2014 8.8 MEASUREMENT AND INDICATING SYSTEMS Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) N1 AND N2 SPEED SENSORS (1E, 1S) Training Notes 1st line maintenance course ARRIEL 1 Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) TO THE INDICATOR PHONIC WHEEL SPEED SENSOR N1 SPEED SENSOR ELECTRICAL CONNECTOR REAR CASING OF THE INTERMEDIATE GEAR F= nd x N 60 PHONIC WHEEL (starter-generator drive shaft) N2 SPEED SENSOR INDICATOR ELECTRICAL CONNECTOR ELECTRO-MAGNETIC SENSOR PHONIC WHEEL N1 AND N2 SPEED SENSORS (1E, 1S) SPEED MEASUREMENT AND INDICATING SYSTEM For training purposes only © Copyright - Turbomeca Training Edition: May 2014 8.9 MEASUREMENT AND INDICATING SYSTEMS ARRIEL 1 Training Notes 1st line maintenance course PRESENTATION Functional description Function The gas temperature (T4) is an operating parameter, particularly during engine starting. This system measures and indicates the T4 temperature, i.e. the gas temperature at the gas generator turbine outlet. As it would be difficult to measure the turbine inlet temperature, the gas generator outlet temperature is measured. Position All versions (except 1E-1S): The system includes thermocouple probes which are connected to an indicator by means of a harness. - All the system components are located on the engine, except for the T4 indicator. Main characteristics - Type: thermocouple probes - Indication: degrees Celsius. 1E-1S: The thermocouple junction box provides a connection between the thermocouple probes and the indicator. The system produces a voltage proportional to the temperature of a junction of two dissimilar metals. The voltage produced is measured by a galvanometer indicator which is graduated in degrees Celsius. Main components - Thermocouple probes (x 3) - Indicator - 1E-1S: Thermocouple junction box. For training purposes only © Copyright - Turbomeca Training Edition: May 2014 8.10 MEASUREMENT AND INDICATING SYSTEMS Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) T4 MEASUREMENT AND INDICATING SYSTEM Training Notes 1st line maintenance course ARRIEL 1 Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) THERMOCOUPLE PROBES GAS GENERATOR TURBINE 1E/1S 1E-1S: THERMOCOUPLE JUNCTION BOX 1E/1S 1E-1S: THERMOCOUPLE JUNCTION BOX THERMOCOUPLE PROBES Except 1E/1S T° Type: Thermocouple probes Indication: Degrees Celsius T4 TEMPERATURE INDICATION PRESENTATION T4 MEASUREMENT AND INDICATING SYSTEM For training purposes only © Copyright - Turbomeca Training Edition: May 2014 8.11 MEASUREMENT AND INDICATING SYSTEMS ARRIEL 1 Training Notes 1st line maintenance course T4 MEASUREMENT AND INDICATING SYSTEM Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) SYSTEM COMPONENTS Thermocouple probes Function The thermocouple probes measure the gas temperature (T4) at the gas generator outlet. Position - Around the rear part of the combustion chamber casing. Function The thermocouple junction box forms the interface between the thermocouples and the indicator. Position Main characteristics - On a bracket at the upper part of the power turbine. - Type: Chromel - Alumel thermocouple Main characteristics - Quantity: 3 - Type: box with connectors. - Connection: in parallel. Functional description Functional description The 3 thermocouple probes are identical. They are positioned to give a homogeneous measurement. Each probe contains a hot junction (Chromel - Alumel wires soldered together). The probes are connected in parallel either to the aircraft indicator directly or through an amplifier providing analog and digital outputs. For training purposes only © Copyright - Turbomeca Training Thermocouple junction box (1E-1S) The thermocouple junction box contains connection system of Chromel - Alumel wires and provides a connection between the thermocouple probes and the aircraft indicator. It includes the connectors of the thermocouple probes (x 3) and of the indicator. Edition: May 2014 8.12 MEASUREMENT AND INDICATING SYSTEMS Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) A thermocouple probe produces an electromotive force which is proportional to the temperature difference between the hot and the cold junction. The electromotive force is delivered to the T4 indicator (galvanometer graduated in degrees Celsius). The reading obtained is an average temperature. Training Notes 1st line maintenance course ARRIEL 1 1E-1S: THERMOCOUPLE JUNCTION BOX 1E/1S Type: Chromel - Alumel thermocouple Type: Box with connectors Quantity: 3 Connection: In parallel Indicator connector Thermocouple connector Mounting nut 1E/1S Cable 1E-1S: THERMOCOUPLE JUNCTION BOX THERMOCOUPLE PROBE Chromel Thermocouple connectors Cold junction INDICATOR Hot junction Alumel SYSTEM COMPONENTS T4 MEASUREMENT AND INDICATING SYSTEM For training purposes only © Copyright - Turbomeca Training Edition: May 2014 8.13 MEASUREMENT AND INDICATING SYSTEMS Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) THERMOCOUPLE PROBES ARRIEL 1 Training Notes 1st line maintenance course TORQUE MEASUREMENT AND INDICATING SYSTEM Operation General operation Function This system measures and indicates the engine torque at the reduction gearbox intermediate gear. Position - All the system components are located on the engine, except for the torque indicator. The reaction torque is transformed into an axial force on the reduction gearbox intermediate gear. The force is transmitted to a piston which determines an oil flow modulating a pressure representative of the torque. The pressure is transformed into electrical current supplied to the indicator by a transmitter. Torquemeter operation - Type: hydraulic torquemeter The torque on the output shaft is transmitted to the reduction gearbox. The intermediate gear, which has helical teeth, transmits the axial force to the piston, via the stop bearing. Description The movement of the intermediate gear/piston assembly varies the oil flow between the piston and the tube base. Main characteristics The torquemeter piston is fitted in the intermediate gear of the reduction gearbox on a stop bearing. This pressure variation is felt by the torque transmitter. The head of the piston fits into a cavity in the reduction gearbox front casing. An oil tube passes through the hollow shaft of the piston and forms a passage between the piston and the tube base. Oil from the torquemeter system can pass through this passage. For training purposes only © Copyright - Turbomeca Training Edition: May 2014 8.14 MEASUREMENT AND INDICATING SYSTEMS Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) PRESENTATION Training Notes 1st line maintenance course ARRIEL 1 REDUCTION GEARBOX CASING TORQUEMETER PISTON Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) Type: Hydraulic torquemeter STOP BEARING INTERMEDIATE GEAR OIL FLOW VARIATION INDICATOR TRANSMITTER LIMITED FLOW LUBRICATION TUBE OIL INLET (pressure modulated by the piston) PRESENTATION TORQUE MEASUREMENT AND INDICATING SYSTEM For training purposes only © Copyright - Turbomeca Training Edition: May 2014 8.15 MEASUREMENT AND INDICATING SYSTEMS ARRIEL 1 Training Notes 1st line maintenance course TORQUE MEASUREMENT AND INDICATING SYSTEM Note: The torque transmitter or the indicator (according to version) is adjusted and matched to the reduction gearbox. Function The transmitter transforms the hydraulic signal (modulated pressure from the piston) into an electrical signal and transmits it to the indicator. Position - Rear face of the accessory gearbox. Main characteristics - Type: inductive or resistive (according to version). Description The system includes: - A calibrated orifice - A transmitter - A pressure tapping point. For training purposes only © Copyright - Turbomeca Training Edition: May 2014 8.16 MEASUREMENT AND INDICATING SYSTEMS Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) TORQUE TRANSMITTER Training Notes 1st line maintenance course PUMP PRESSURE RESTRICTOR TORQUEMETER PISTON MODULATED PRESSURE INDICATOR Type: Inductive or resistive (according to version) TRANSMITTER PRESSURE TAPPING Note: The torque transmitter or the indicator (according to version) is adjusted and matched to the reduction gearbox. TORQUE TRANSMITTER TORQUE MEASUREMENT AND INDICATING SYSTEM For training purposes only © Copyright - Turbomeca Training Edition: May 2014 8.17 MEASUREMENT AND INDICATING SYSTEMS Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) ARRIEL 1 ARRIEL 1 Training Notes 1st line maintenance course MISCELLANEOUS INDICATIONS There are several indicators and instruments which give information about the engine operation. These pages summarize the various lights which have already been dealt with in other chapters. Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) GENERAL Position - Engine - On the cockpit instrument panel. Main characteristics - Indicator lights directly connected to engine sensors - Indications provided by the aircraft - Electrical measurement circuit directly connected to indicators. Main components - Sensors and engine accessories (refer to corresponding chapters for more information) Lights directly connected to the engine sensors - Low oil pressure - Bleed valve position - Magnetic particles. For training purposes only © Copyright - Turbomeca Training Edition: May 2014 8.18 MEASUREMENT AND INDICATING SYSTEMS Training Notes 1st line maintenance course + 28 V Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) ARRIEL 1 Low oil pressure Bleed valve position Circuit breaker Magnetic particles ENGINE INDICATING: • Fuel • Oil • Air • Power • Overspeed • Fire AIRFRAME GENERAL MISCELLANEOUS INDICATIONS For training purposes only © Copyright - Turbomeca Training Edition: May 2014 8.19 MEASUREMENT AND INDICATING SYSTEMS ARRIEL 1 Training Notes 1st line maintenance course MISCELLANEOUS INDICATIONS Operation Function The cycle counter automatically carries out the calculations stated in the maintenance manual. Main components The input signal is the N1 speed supplied by a pick-up or by the tachometer generator. With this information, the system converts the engine actual operating cycles into "reference cycles" and displays the result. For the power turbine, the relationship is: 1 cycle = 1 start. - Tachometer box with failure indicator It is then possible to calculate the number of cycles of life limited parts. - Display unit with N1 and N2 cycle displays The electronic box corresponding to an engine variant can perform some (or all) of the following functions: - Electrical connectors. Note: In the 1E and 1S versions, the same box ensures the two functions of N2 overspeed detection and cycle counter. - Count engine operating cycles - Control electro-pneumatic compressor bleed valve - Detect any power turbine overspeed - Monitor the power turbine. For training purposes only © Copyright - Turbomeca Training Edition: May 2014 8.20 MEASUREMENT AND INDICATING SYSTEMS Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) CYCLE COUNTER Training Notes 1st line maintenance course FAILURE INDICATOR Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) ARRIEL 1 DISPLAY UNIT N1 AND N2 CYCLE DISPLAYS N1, N2 AND 24 V INPUT Note: In the 1E and 1S versions, the same box ensures the two functions of N2 overspeed detection and cycle counter. CYCLE COUNTER MISCELLANEOUS INDICATIONS For training purposes only © Copyright - Turbomeca Training Edition: May 2014 8.21 MEASUREMENT AND INDICATING SYSTEMS ARRIEL 1 MEASUREMENT AND INDICATING SYSTEMS - 1ST LINE MAINTENANCE Mandatory maintenance tasks Refer to the Maintenance Manual (chapter 05). Operations to be performed to comply with Airworthiness objectives are listed in the table of mandatory maintenance tasks. Scheduled inspections Manufacturer-required maintenance tasks List of maintenance tasks to be carried out: - Inspection before the first flight of the day - Turn-around inspection - Inspection after the last flight of the day The manufacturer considers that the manufacturer-required maintenance tasks must be carried out at the scheduled inspection frequency. Failure to do so may cause occurrences liable to affect the engine operating safety. - Inspection after 15 flight hours or 7 days Optional maintenance tasks - Inspection at 30 flight hours Optional maintenance tasks are recommended by the manufacturer as a means of improving reliability, increasing operational availability and reducing operating costs. - Inspection at 50 flight hours - Inspection at 100 flight hours - Inspection at 150 flight hours - Inspection at 200 flight hours - Inspection at 300 flight hours - Inspection at 400 flight hours - Inspection at 500 flight hours - Inspection at 600 flight hours - Inspection at 750 flight hours - Inspection at 1,000 flight hours Note 1: Before carrying out any maintenance tasks, remember to refer to the latest Service Bulletins and Service Letters. Note 2: The maintenance tasks shown below concern the ARRIEL 1D1 variant by way of example and may differ for other ARRIEL 1 variants. Always refer to the Maintenance Manual of the variant concerned. - Inspection at 1,200 flight hours - Inspection at 1,500 flight hours - Inspection at 3,000 flight hours - Inspection at 3,600 flight hours For training purposes only © Copyright - Turbomeca Training Edition: May 2014 8.22 MEASUREMENT AND INDICATING SYSTEMS Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) PREVENTIVE MAINTENANCE Training Notes 1st line maintenance course Training Notes 1st line maintenance course ARRIEL 1 PREVENTIVE MAINTENANCE (scheduled inspections) INSPECTION AT 300 FLIGHT HOURS MANUFACTURER-REQUIRED Inspection and check of torquemeter transmitter Chap. 72 Inspection and check of the tachometer transmitter N1 (NG) Chap. 77 Inspection and check of the pyrometric harness attachment (tightness of thermocouples) Chap. 77 Note: Pyrometric harness installed INSPECTION AT 750 FLIGHT HOURS MANUFACTURER-REQUIRED Inspection and check of the pyrometric harness (test) Chap. 77 INSPECTION AT 1,000 FLIGHT HOURS MANDATORY Post TU207: - Check for correct operation of the "cycle counting" function for the tachometer box Chap. 77 Note: Engines equipped with a tachometer box with cycle counting aid Before carrying out any maintenance tasks, remember to refer to the latest Service Bulletins and Service Letters. PREVENTIVE MAINTENANCE MEASUREMENT AND INDICATING SYSTEMS - 1ST LINE MAINTENANCE For training purposes only © Copyright - Turbomeca Training Edition: May 2014 8.23 MEASUREMENT AND INDICATING SYSTEMS Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) (refer to MM, chapter 05) Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) ARRIEL 1 Training Notes 1st line maintenance course Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) 9 - STARTING SYSTEM - Starting system - Presentation ........................................................... 9.2 - Starter-generator ................................................................................... 9.6 - Ignition system ...................................................................................... 9.8 - Starting system - Operation ................................................................. 9.10 - Starting system - 1st line maintenance .............................................. 9.14 - 9.15 For training purposes only © Copyright - Turbomeca Training Edition: May 2014 9.1 STARTING SYSTEM ARRIEL 1 Training Notes 1st line maintenance course STARTING SYSTEM - PRESENTATION Main components Function - Starter-generator (cranking) The starting system is used to start the engine (on the ground and in flight) and crank the engine. It includes the following functions: cranking, fuel supply and ignition. - Ignition units and igniter plugs Position All the starting accessories are located on the engine. Indicating and control components are supplied by the aircraft manufacturer. Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) GENERAL - Fuel system (supply, metering and delivery) - Indicating and control components: • Electrical system • Instruments. Main characteristics - Starting envelope: according to version - Start duration: between 25 and 30 sec. - Max. crank time: 15 sec. - Stabilisation time before shut-down: 60 sec. - Run-down time: > 30 sec. from 30 to 0% N1. For training purposes only © Copyright - Turbomeca Training Edition: May 2014 9.2 STARTING SYSTEM ARRIEL 1 Starting envelope: According to version IGNITION UNITS IGNITER PLUGS Start duration: Between 25 and 30 sec. Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) STARTER-GENERATOR Training Notes 1st line maintenance course Max. crank time: 15 sec. Stabilisation time before shut-down: 60 sec. CRANKING Run-down time: > 30 sec. from 30 to 0% N1 FUEL SUPPLY AND DISTRIBUTION IGNITION START CONTROL AND INDICATING GENERAL STARTING SYSTEM - PRESENTATION For training purposes only © Copyright - Turbomeca Training Edition: May 2014 9.3 STARTING SYSTEM ARRIEL 1 Training Notes 1st line maintenance course STARTING SYSTEM - PRESENTATION The igniter plugs are installed close to the start injectors and are connected to the ignition units by two cables. Starter The starter is electrically supplied with direct current from the batteries through the aircraft electrical system. Fuel system The fuel system supplies fuel to the start and main injectors. During starting, the starter drives the gas generator rotating assembly through the accessory drive train. Control and indicating system At the end of starting, the electrical supply to the starter is cut. The control system includes: The starter is installed on the front face of the gearbox casing. - The cockpit components (circuit-breaker, crank and start push-buttons, the manual control lever) Ignition unit - The power supply (28 V battery) The ignition units are of high energy type. They transform the direct current voltage provided by the aircraft system into high energy voltage required for the igniter plug operation. The ignition units are located at the right side of the axial compressor casing. - The accessory relay (to electrically supply the starting accessories) - The starter contactor - The overspeed box (twin engine only). Igniter plugs The engine has two igniter plugs which ignite the air fuel mixture sprayed by the start injectors. For training purposes only © Copyright - Turbomeca Training Edition: May 2014 9.4 STARTING SYSTEM Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) DESCRIPTION Training Notes 1st line maintenance course ARRIEL 1 STARTERGENERATOR CIRCUIT BREAKER CRANK PUSH-BUTTON START PUSH-BUTTON Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) STARTER CONTACTOR START ELECTRO-VALVE ACCESSORY RELAY OVERSPEED BOX IGNITION UNITS DESCRIPTION STARTING SYSTEM - PRESENTATION For training purposes only © Copyright - Turbomeca Training Edition: May 2014 9.5 STARTING SYSTEM ARRIEL 1 Training Notes 1st line maintenance course Function - Direct current supply to the aircraft system from the startergenerator when the starting phase is completed. The starter cranks the gas generator rotating assembly during starting and cranking. At the end of starting (when the rotation speed is sufficient), the starter operates as a Direct Current generator. Operation Position - On the front face of the accessory gearbox. It is secured by a clamp. Main characteristics - Supplied by the aircraft manufacturer Engine cranking When "START" is selected, the starter contactor closes and connects the aircraft DC busbar to the starter. The starter then cranks the rotating assembly through the accessory drive train. The torque on the starter shaft is inversely proportional to the gas generator speed and will be higher when the atmospheric temperature is low. - Type: starter-generator - Supply: VDC through heavy-duty cables (32 V max.) - The starter-generator The N1 increases up to self-sustaining speed (45%) at which point the torque becomes negative. The supply to the starter is cut by the opening of the starter contactor. - The mounting flange Electrical generation Main components - The supply terminals. Interfaces - Starter electrical supply from the + 28 VDC supply busbar through the starter contactor At the end of the start cycle the starter is no longer electrically supplied and it is driven by the gas generator through the accessory drive train. Thus it acts as an electrical generator and supplies current to the aircraft circuit. - Drive of the gas generator rotating assembly through the accessory drive train For training purposes only © Copyright - Turbomeca Training Edition: May 2014 9.6 STARTING SYSTEM Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) STARTER-GENERATOR ARRIEL 1 Training Notes 1st line maintenance course DRIVE SHAFT STARTERGENERATOR START TORQUE TORQUE WITH A LOWER ATMOSPHERIC TEMPERATURE Supplied by the aircraft manufacturer Type: Starter-generator Electrical supply: VDC through heavyduty cables (32 V max.) 45% 0 SELF-SUSTAINING SPEED STARTER STARTER-GENERATOR For training purposes only © Copyright - Turbomeca Training N1 Edition: May 2014 GENERATOR 9.7 STARTING SYSTEM Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) TERMINALS ARRIEL 1 Training Notes 1st line maintenance course Function Main components This system ignites the fuel that is sprayed into the combustion chamber by the start injectors. - 2 ignition units (identical, high energy) Position - 2 igniter plugs (surface-discharge type, incorporating a central electrode insulated from the body, and a semi-conductor at the tip). With the exception of the electrical supply circuit, all the ignition system components are located on the engine: - Ignition units: mounted on a support, on the front right-hand side of the engine - 2 ignition cables (identical, triple-braided, high energy) Functional description - Ignition cables: between the ignition units and the igniter plugs The ignition units are supplied with the DC voltage from the aircraft mains electrical system, and transform it into a highenergy voltage. - Igniter plugs: beside the start injectors, on either side of the turbine casing. This high-energy voltage (approximately 2 kV) is then delivered to the igniter plugs through the ignition cables. Main characteristics The high-energy voltage produced by the ignition units is supplied to the central electrode of the igniter plugs. It discharges between the semi-conductor and the plug body causing powerful sparks. - Type: High Energy (HE) - Supply voltage: 28 VDC For training purposes only © Copyright - Turbomeca Training These sparks ignite the fuel that is sprayed into the combustion chamber by the start injectors. Edition: May 2014 9.8 STARTING SYSTEM Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) IGNITION SYSTEM Training Notes 1st line maintenance course ARRIEL 1 Electrical connector (connection with the ignition unit) Seals and spacers Electrical connector (to the ignition unit) Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) Electrical connector (to the igniter plug) Body (-) Spark Central electrode (+) IGNITION CABLE Identification plate IGNITER PLUG Insulator Semiconductor START INJECTORS IGNITER PLUG Mounting flanges Type: High Energy (HE) IGNITION UNITS Supply voltage: 28 VDC IGNITION SYSTEM For training purposes only © Copyright - Turbomeca Training Edition: May 2014 COMBUSTION CHAMBER 9.9 STARTING SYSTEM ARRIEL 1 Training Notes 1st line maintenance course Starting cycle Crank cycle The starting cycle is characterised by the evolution of the engine parameters, especially the rotation speed and the gas temperature. Cranking consists of driving the rotating assembly without supplying fuel or energising the ignition system ("dry" crank). It is used to cool the engine or for maintenance procedures. The main phases of the starting cycle are: The main phases of the crank cycle are: - Start selection - Selection of crank - Self-sustaining speed (de-energisation of the starter and ignition units) - Driving of the rotating assembly - End of start (stabilisation at min. power). Shut-down cycle - End of cranking and run-down. Note: Cranking time is limited to a maximum of 15 seconds to avoid overheating of the starter. The main phases of the shut-down cycle are: - Stabilisation at idle speed - Stop selection - Run-down and stop. For training purposes only © Copyright - Turbomeca Training Edition: May 2014 9.10 STARTING SYSTEM Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) STARTING SYSTEM - OPERATION (1) Training Notes 1st line maintenance course ARRIEL 1 N1 + Stop selection Stabilisation at idle speed Starting accessories ACCESSORY RELAY Run-down CRANK SELECTION + STARTER CONTACTOR Startergenerator T4 N1 N2 100% N1 Dry crank cancel Run-down N1 idle Self-sustaining speed Approx. 200°C (injection wheel supply) Selection STARTING CYCLE time Selection STARTING SYSTEM - OPERATION (1) For training purposes only © Copyright - Turbomeca Training time SHUT-DOWN CYCLE Edition: May 2014 (15 sec. max.) CRANK CYCLE time 9.11 STARTING SYSTEM Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) START SELECTION ARRIEL 1 Training Notes 1st line maintenance course Power supply of the helicopter "ON" Stop - Valves closed, metering needle closed by the cam. - After stabilisation pull the control lever to the "stop" position: the main valve closes. Note the run-down time. Booster pumps switched on Crank - Purge of the fuel system with a return to the tank. - Power supply switched on Starting - Press the crank push-button (max. 15 sec.): • power supply to the starter motor via the starter contactor. - The control lever is moved to the "start" position: • slight opening of the main valve - Pushing the start push button initiates the start by electrically supplying: • the starter • the start electro-valve (which opens) • the ignition system - At 45% of N1 (self-sustaining speed) it is necessary to release the start push button to cut the supply to the start relay and accessories. Note: During starting, it is necessary to control the acceleration of the engine, with the control lever, and to observe the N1 speed and T4 temperature. For training purposes only © Copyright - Turbomeca Training Edition: May 2014 9.12 STARTING SYSTEM Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) STARTING SYSTEM - OPERATION (2) ARRIEL 1 Training Notes 1st line maintenance course Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) STARTING SYSTEM - OPERATION (2) For training purposes only © Copyright - Turbomeca Training Edition: May 2014 9.13 STARTING SYSTEM ARRIEL 1 STARTING SYSTEM - 1ST LINE MAINTENANCE Mandatory maintenance tasks Refer to the Maintenance Manual (chapter 05). Operations to be performed to comply with Airworthiness objectives are listed in the table of mandatory maintenance tasks. Scheduled inspections Manufacturer-required maintenance tasks List of maintenance tasks to be carried out: - Inspection before the first flight of the day - Turn-around inspection - Inspection after the last flight of the day The manufacturer considers that the manufacturer-required maintenance tasks must be carried out at the scheduled inspection frequency. Failure to do so may cause occurrences liable to affect the engine operating safety. - Inspection after 15 flight hours or 7 days Optional maintenance tasks - Inspection at 30 flight hours Optional maintenance tasks are recommended by the manufacturer as a means of improving reliability, increasing operational availability and reducing operating costs. - Inspection at 50 flight hours - Inspection at 100 flight hours - Inspection at 150 flight hours - Inspection at 200 flight hours - Inspection at 300 flight hours - Inspection at 400 flight hours - Inspection at 500 flight hours - Inspection at 600 flight hours - Inspection at 750 flight hours Note 1: Before carrying out any maintenance tasks, remember to refer to the latest Service Bulletins and Service Letters. Note 2: The maintenance tasks shown below concern the ARRIEL 1D1 variant by way of example and may differ for other ARRIEL 1 variants. Always refer to the Maintenance Manual of the variant concerned. - Inspection at 1,000 flight hours - Inspection at 1,200 flight hours - Inspection at 1,500 flight hours - Inspection at 3,000 flight hours - Inspection at 3,600 flight hours For training purposes only © Copyright - Turbomeca Training Edition: May 2014 9.14 STARTING SYSTEM Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) PREVENTIVE MAINTENANCE Training Notes 1st line maintenance course Training Notes 1st line maintenance course ARRIEL 1 PREVENTIVE MAINTENANCE (scheduled inspections) INSPECTION AT 300 FLIGHT HOURS MANUFACTURER-REQUIRED Inspection and check of H.E. generators Inspection and check of the ignition cables Inspection of the ignition plugs Operational check of each starting system Note: During a ground run OPTIONAL Inspection and check (test) of the H.E. generators and H.E. igniters Chap. 74 Chap. 72 Chap. 72 Chap. 72 Chap. 72 Before carrying out any maintenance tasks, remember to refer to the latest Service Bulletins and Service Letters. PREVENTIVE MAINTENANCE STARTING SYSTEM - 1ST LINE MAINTENANCE For training purposes only © Copyright - Turbomeca Training Edition: May 2014 9.15 STARTING SYSTEM Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) (refer to MM, chapter 05) Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) ARRIEL 1 Training Notes 1st line maintenance course - Electrical system - Presentation .......................................................... 10.2 - Power turbine overspeed detection system ....................................... 10.4 - Electrical harnesses ............................................................................. 10.16 - Electrical system - 1st line maintenance ............................................ 10.18 - 10.19 For training purposes only © Copyright - Turbomeca Training Edition: May 2014 10.1 ELECTRICAL SYSTEM Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) 10 - ELECTRICAL SYSTEM ARRIEL 1 Training Notes 1st line maintenance course Function Main components The electrical system contributes to the engine control and indicating functions: - Electrical components of the engine (accessories and sensors) - Electrical controls - Control and indicating components (airframe) - Electrical harnesses. - Control system - Safety systems. Main characteristics - Direct current: 28 VDC from the airframe electrical system. For training purposes only © Copyright - Turbomeca Training Edition: May 2014 10.2 ELECTRICAL SYSTEM Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) ELECTRICAL SYSTEM - PRESENTATION Training Notes 1st line maintenance course Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) ARRIEL 1 CONTROL AND INDICATING COMPONENTS ELECTRICAL HARNESSES Direct current: 28 VDC from the airframe electrical system ACCESSORIES AND SENSORS ELECTRICAL SYSTEM - PRESENTATION For training purposes only © Copyright - Turbomeca Training Edition: May 2014 10.3 ELECTRICAL SYSTEM ARRIEL 1 Training Notes 1st line maintenance course POWER TURBINE OVERSPEED DETECTION SYSTEM Description The speed sensor is mounted facing two phonic wheels with a different number of teeth, mounted on the turbine shaft. It is connected to the tachometer box (in the aircraft). Function The safety system causes the immediate shut-down of the engine in the event of power turbine overspeed. The system (mainly designed to protect against shearing of the power shaft) requires a very quick response and high reliability. This detection system is only installed in twin-engine configurations. Position The tachometer box electrically supplies the overspeed electrovalve mounted on the stop purge valve. Operation In the event of an overspeed, when the tachometer box receives two frequency signals, it energises the overspeed electro-valve to move to drain position causing the engine shut-down. All the components are installed on the engine, except the tachometer box which is mounted on the aircraft. Main characteristics Overspeed setting: 120% N2 - Automatic test: • for each start • during periodic inspection. For training purposes only © Copyright - Turbomeca Training Edition: May 2014 10.4 ELECTRICAL SYSTEM Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) GENERAL Training Notes 1st line maintenance course ARRIEL 1 Automatic test: • for each start • during periodic inspection SPEED SENSOR PHONIC WHEELS TACHOMETER BOX OVERSPEED ELECTRO-VALVE This detection system is only installed in twin-engine configurations OVERSPEED ELECTRO-VALVE SPEED SENSOR TACHOMETER BOX GENERAL POWER TURBINE OVERSPEED DETECTION SYSTEM For training purposes only © Copyright - Turbomeca Training Edition: May 2014 10.5 ELECTRICAL SYSTEM Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) Overspeed setting: 120% N2 ARRIEL 1 Training Notes 1st line maintenance course POWER TURBINE OVERSPEED SENSOR Description Function The sensor is fitted facing the phonic wheels, it includes two electro-magnetic pick-ups. The power turbine overspeed sensor monitors N2 and transmits the signal to the tachometer box (twin-engine versions). The sensor is secured by a hollow bolt and is fitted with a locating pin to ensure the correct orientation. Position Operation Screwed into the bottom of module 4 casing. The passage of the teeth in front of the electro-magnetic sensor induces two alternating currents having a frequency proportional to the speed and to the number of teeth : Main characteristics - Double pick-up - Type: Electro-magnetic. nd x N F = 60 (nd = number of teeth, N = rotation speed in rpm, F = Frequency) As the phonic wheels don't have the same number of teeth, the double sensor gives two different frenquencies proportional to the speed. For training purposes only © Copyright - Turbomeca Training Edition: May 2014 10.6 ELECTRICAL SYSTEM Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) POWER TURBINE OVERSPEED DETECTION SYSTEM Training Notes 1st line maintenance course ARRIEL 1 TO THE TACHOMETER BOX Type: Electro-magnetic F = nd x N 60 SENSOR PHONIC WHEEL PHONIC WHEELS SENSOR LOCATING DOWEL HOLLOW BOLT TACHOMETER BOX ELECTRO-MAGNETIC PICK-UP PHONIC WHEEL POWER TURBINE OVERSPEED SENSOR POWER TURBINE OVERSPEED DETECTION SYSTEM For training purposes only © Copyright - Turbomeca Training Edition: May 2014 10.7 ELECTRICAL SYSTEM Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) Double pick-up ARRIEL 1 Training Notes 1st line maintenance course POWER TURBINE OVERSPEED DETECTION SYSTEM The tachometer box is mounted in the aircraft, it is connected to the overspeed sensor by an electrical harness. Function To supply the overspeed electro-valve in case of an overspeed detection and to control the operation of the bleed valve (according to version). Position Description It includes two frequency detectors, a V relay, a bistable relay S and S', a re-arming and a test push-button. A cross-monitoring system between the two overspeed boxes inhibits the overspeed detection system of the other engine in case of overspeed. - In the aircraft Main characteristics - Electronic box - Automatic test - Periodic test. For training purposes only © Copyright - Turbomeca Training Edition: May 2014 10.8 ELECTRICAL SYSTEM Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) TACHOMETER BOX - GENERAL - DESCRIPTION Training Notes 1st line maintenance course ARRIEL 1 TEST OSCILLATOR RE-ARMING PUSH-BUTTON ELECTRICAL CONNECTOR S 120% N2 120% N2 V OVERSPEED ELECTRO-VALVE TEST SELECTOR ENGINE SHUT-DOWN INHIBITION OF STARTING INHIBITION OF THE OTHER ENGINE SYSTEM 25% S' TEST RE-ARMING OVERSPEED CONNECTOR ELECTRICAL CONNECTOR FOR THE COMPRESSOR BLEED VALVE CONTROL 25% POSSIBLE INHIBITION OF THIS SYSTEM TACHOMETER BOX - GENERAL - DESCRIPTION POWER TURBINE OVERSPEED DETECTION SYSTEM For training purposes only © Copyright - Turbomeca Training Edition: May 2014 10.9 ELECTRICAL SYSTEM Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) TEST PUSH-BUTTON ARRIEL 1 Training Notes 1st line maintenance course POWER TURBINE OVERSPEED DETECTION SYSTEM Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) TACHOMETER BOX - OPERATION (1) Power on At power on, the sensors give the F1 and F2 frequencies to frequency detectors which supply the light through the mutual monitoring system (up 25% of N2). Re-arming is possible. Overspeed condition In the event of N2 overspeed (N2 approx. 120%), the two signals of N2 (F1 and F2) are supplied to the two frequency detectors which complete the circuit through relay V. Relay V closes its contacts: • supplying relay S • breaking the circuit of the other engine. The contacts of relay S • open the other engine's overspeed circuit • supply the overspeed solenoid • open the start circuit • open the overspeed light circuit. For training purposes only © Copyright - Turbomeca Training Edition: May 2014 10.10 ELECTRICAL SYSTEM Training Notes 1st line maintenance course ARRIEL 1 TEST POWER ON - The light turns on (up to 25% of N2) - Re-arming (if necessary) S N2 120% N2 V OVERSPEED - Supply of the mono-stable relay V - Supply of the bistable relay S - Supply of the overspeed electro-valve - Inhibition the other engine system - Inhibition of starting 120% OVERSPEED ELECTRO-VALVE ENGINE INHIBITION OF STARTING SHUT-DOWN INHIBITION OF THE OTHER ENGINE SYSTEM 25% S' RE-ARMING 25% POSSIBLE INHIBITION OF THIS SYSTEM POWER ON OVERSPEED TACHOMETER BOX - OPERATION (1) POWER TURBINE OVERSPEED DETECTION SYSTEM For training purposes only © Copyright - Turbomeca Training Edition: May 2014 10.11 ELECTRICAL SYSTEM Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) OSCILLATOR ARRIEL 1 Training Notes 1st line maintenance course POWER TURBINE OVERSPEED DETECTION SYSTEM Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) TACHOMETER BOX - OPERATION (2) Automatic monitoring (all versions except 1E and 1S) The condition of the pick-up signals is checked at each start with the light turning off above 25% N2. Periodic test Engine stopped, operation of the push-button simulates an overspeed: • the light goes off • the electro-valve is supplied • the start system is inhibited After this test, it is necessary to re-arm the system. Re-arming When the re-arm push-button is pressed the relay S' is supplied and the relay returns to the normal position. For training purposes only © Copyright - Turbomeca Training Edition: May 2014 10.12 ELECTRICAL SYSTEM Training Notes 1st line maintenance course ARRIEL 1 TEST OSCILLATOR - Supply of the oscillator 120% * - Oscillator inhibited for N2 > 25% AUTOMATIC MONITORING ALL VERSIONS EXCEPT 1E AND 1S: WHATEVER N1 S 120% N2 120% N2 V OVERSPEED ELECTRO-VALVE N2 (x) N2 (y) OK OK Light off OK 0 Light on 0 OK Light on 0 0 Light on ENGINE INHIBITION OF STARTING SHUT-DOWN INHIBITION OF THE OTHER ENGINE SYSTEM 25% S' RE-ARMING OVERSPEED MANUAL TEST 25% POSSIBLE INHIBITION OF THIS SYSTEM AUTOMATIC MONITORING TACHOMETER BOX - OPERATION (2) POWER TURBINE OVERSPEED DETECTION SYSTEM For training purposes only © Copyright - Turbomeca Training Edition: May 2014 10.13 ELECTRICAL SYSTEM Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) OVERSPEED MANUAL TEST ARRIEL 1 Training Notes 1st line maintenance course POWER TURBINE OVERSPEED DETECTION SYSTEM Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) TACHOMETER BOX - OPERATION (3) Automatic monitoring (1E, 1S versions) This protection does not exist on all boxes. - Above 25% N2 and below 82% N1: the loss of one N2 speed signal is indicated by the light staying "on". - Above 25% N2 and 82% N1: • the loss of one N2 speed signal is also indicated by the light staying "on" • the loss of two N2 speed signals causes the engine to be shut down by the overspeed system. - Above 25% N2. • the loss of the N1 speed signal or any defect of the detection stage is indicated by the flashing of the light. Note: In all cases of engine shut-down by overspeed, starting is not possible. For training purposes only © Copyright - Turbomeca Training Edition: May 2014 10.14 ELECTRICAL SYSTEM Training Notes 1st line maintenance course TEST AUTOMATIC MONITORING 1S, 1E VERSIONS: N1 < 82% N2 (x) N2 (y) OK OK Light off OK 0 Light on 0 OK Light on 0 0 Light on OSCILLATOR S N1 > 82% N2 (y) OK OK Light off OK 0 Light on 0 OK Light on 0 0 Pre TU 369: Engine shut-down Post TU 369: Light on N2 > 25% ENGINE SHUT-DOWN 120% N2 V INHIBITION OF STARTING INHIBITION OF THE OTHER ENGINE SYSTEM 25% S' RE-ARMING N1 0 N2 OVERSPEED ELECTRO-VALVE N2 (x) OK 120% 1S, 1E VERSION 25% Light on Light flashing 82% 1E, 1S VERSION MONITORING N1 POSSIBLE INHIBITION OF THIS SYSTEM TACHOMETER BOX - OPERATION (3) POWER TURBINE OVERSPEED DETECTION SYSTEM For training purposes only © Copyright - Turbomeca Training Edition: May 2014 10.15 ELECTRICAL SYSTEM Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) ARRIEL 1 ARRIEL 1 Training Notes 1st line maintenance course ELECTRICAL HARNESSES The electrical harnesses connect the engine's electrical components to the airframe. Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) Function Functional description All engine versions have a multi-pin plug for the engine/aircraft interface and a second electrical plug for the pyrometric system (except on ARRIEL 1S1: only one electrical plug for the two harnesses). On the twin-engine version : a harness for the N2 speed detection to stop the engine in case of overspeed. Note: The starter-generator cables must also be mentioned. For training purposes only © Copyright - Turbomeca Training Edition: May 2014 10.16 ELECTRICAL SYSTEM Training Notes 1st line maintenance course N2 SPEED DETECTION HARNESS FOR THE OVERSPEED SYSTEM (twin-engine version) PYROMETRIC HARNESS ACCESSORY HARNESS ARRIEL 1S1: only one connector ELECTRICAL HARNESSES For training purposes only © Copyright - Turbomeca Training Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) ARRIEL 1 Edition: May 2014 10.17 ELECTRICAL SYSTEM ARRIEL 1 ELECTRICAL SYSTEM - 1ST LINE MAINTENANCE Mandatory maintenance tasks Refer to the Maintenance Manual (chapter 05). Operations to be performed to comply with Airworthiness objectives are listed in the table of mandatory maintenance tasks. Scheduled inspections Manufacturer-required maintenance tasks List of maintenance tasks to be carried out: - Inspection before the first flight of the day - Turn-around inspection - Inspection after the last flight of the day The manufacturer considers that the manufacturer-required maintenance tasks must be carried out at the scheduled inspection frequency. Failure to do so may cause occurrences liable to affect the engine operating safety. - Inspection after 15 flight hours or 7 days Optional maintenance tasks - Inspection at 30 flight hours Optional maintenance tasks are recommended by the manufacturer as a means of improving reliability, increasing operational availability and reducing operating costs. - Inspection at 50 flight hours - Inspection at 100 flight hours - Inspection at 150 flight hours - Inspection at 200 flight hours - Inspection at 300 flight hours - Inspection at 400 flight hours - Inspection at 500 flight hours - Inspection at 600 flight hours - Inspection at 750 flight hours - Inspection at 1,000 flight hours Note 1: Before carrying out any maintenance tasks, remember to refer to the latest Service Bulletins and Service Letters. Note 2: The maintenance tasks shown below concern the ARRIEL 1D1 variant by way of example and may differ for other ARRIEL 1 variants. Always refer to the Maintenance Manual of the variant concerned. - Inspection at 1,200 flight hours - Inspection at 1,500 flight hours - Inspection at 3,000 flight hours - Inspection at 3,600 flight hours For training purposes only © Copyright - Turbomeca Training Edition: May 2014 10.18 ELECTRICAL SYSTEM Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) PREVENTIVE MAINTENANCE Training Notes 1st line maintenance course Training Notes 1st line maintenance course ARRIEL 1 PREVENTIVE MAINTENANCE (scheduled inspections) INSPECTION AT 300 FLIGHT HOURS MANUFACTURER-REQUIRED Inspection and check of control and monitoring harness (tightness and locking of connectors) Chap. 71 Before carrying out any maintenance tasks, remember to refer to the latest Service Bulletins and Service Letters. PREVENTIVE MAINTENANCE ELECTRICAL SYSTEM - 1ST LINE MAINTENANCE For training purposes only © Copyright - Turbomeca Training Edition: May 2014 10.19 ELECTRICAL SYSTEM Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) (refer to MM, chapter 05) Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) ARRIEL 1 Training Notes 1st line maintenance course - Engine compartment ............................................................................ 11.2 - Engine mounting and lifting ................................................................ 11.4 - Air intake and exhaust systems .......................................................... 11.6 - Engine/airframe system interfaces ..................................................... 11.8 - Drains - Purges - Air vents ................................................................... 11.16 - Power drive ............................................................................................ 11.18 - Fire protection ....................................................................................... 11.20 - Engine installation - 1st line maintenance ......................................... 11.22 - 11.25 For training purposes only © Copyright - Turbomeca Training Edition: May 2014 11.1 ENGINE INSTALLATION Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) 11 - ENGINE INSTALLATION ARRIEL 1 Training Notes 1st line maintenance course Function Description The engine compartment houses the engine and ensures its ventilation. A typical twin-engine installation includes the following components: Position - At the rear of the helicopter main gearbox. Main characteristics - Insulated compartments - Ventilation by air circulation. Main components - Firewalls - Cowlings - Support platform. - Two areas separated by a central firewall: • Right engine area • Left engine area - Three main firewalls: • Front firewall • Rear firewall • Central firewall. - The main engine mountings - Two main cowlings: • The air inlet cowling which permits access to the air intake • The engine cowling which permits access to the engine and to the exhaust system. The compartment ventilation is ensured by air circulation in order to maintain an acceptable temperature in the various areas. The ventilation can be increased by the compressor bleed valve air discharging into the engine compartment. For training purposes only © Copyright - Turbomeca Training Edition: May 2014 11.2 ENGINE INSTALLATION Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) ENGINE COMPARTMENT Training Notes 1st line maintenance course ARRIEL 1 ENGINE SUPPORT PLATFORM FRONT FIREWALL ENGINE MOUNTING MAIN GEARBOX EXAMPLE OF SINGLE-ENGINE INSTALLATION AIR INLET COWLING Edition: May 2014 REAR FIREWALL ENGINE COWLING EXAMPLE OF TWIN-ENGINE INSTALLATION ENGINE COMPARTMENT For training purposes only © Copyright - Turbomeca Training CENTRAL FIREWALL 11.3 ENGINE INSTALLATION Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) - Insulated compartments - Ventilation by air circulation ARRIEL 1 Training Notes 1st line maintenance course ENGINE MOUNTING ENGINE LIFTING Function Function The engine mountings attach the engine to the airframe. The 3 lifting rings are used to lift the engine. Description - Front mounting: at the front lower part of the accessory gearbox casing, - Rear mounting: at the front lower part of the reduction gearbox casing, or on the protection tube (according to version). Functional description The front and rear engine mountings differ according to the engine variant concerned. - All variants except E-K-S: • Front mounting - ring of bolts on the front support casing front flange • Rear mounting - a cradle under the protection tube, secured by two clamps - Variants E-K-S: • Front mounting - yoke bolted to the front face of the accessory gearbox, supported on two trunnion mounts, • Rear mounting - a rod connects to the bracket on the bottom of module M05. Description - 3 lifting rings: 2 at the front and 1 at the rear. Engine removal and installation Turbomeca supplies an engine lifting beam which attaches to the lifting rings on the engine. This allows the engine to be removed from and installed in the airframe. The removal/installation procedure is described in the Airframe Maintenance Manual. Engine removal and installation must only be carried out in accordance with this procedure and using the appropriate tooling. - Variant E: • Front mounting: 2 lateral supports fitted on the accessory gearbox For training purposes only © Copyright - Turbomeca Training Edition: May 2014 11.4 ENGINE INSTALLATION Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) ENGINE MOUNTING AND LIFTING Training Notes 1st line maintenance course ARRIEL 1 MOUNTING BY CLAMPS ON THE PROTECTION TUBE ENGINE LIFTING BEAM ALL VARIANTS EXCEPT E-K-S ALL VARIANTS EXCEPT E-K-S REAR LIFTING RING FRONT LIFTING RINGS MOUNTING BY TWO ATTACHMENT POINTS ON THE AIRFRAME VARIANTS E-K-S REAR MOUNTING VARIANT E ENGINE MOUNTING AND LIFTING For training purposes only © Copyright - Turbomeca Training Edition: May 2014 VARIANTS E-K-S 11.5 ENGINE INSTALLATION Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) MOUNTING BY THE FRONT SUPPORT CASING FRONT FLANGE ARRIEL 1 Training Notes 1st line maintenance course AIR INTAKE SYSTEM EXHAUST SYSTEM Function Function The air intake system directs the ambient air into the engine. The exhaust system discharges the exhaust gas overboard. Position Position - In front of the engine. - At the rear of the engine. Main characteristics Main characteristics - Type: static or dynamic, annular - Type: divergent - Airflow: 2.5 kg/sec. (5.5 lb/sec.). - Gas temperature: 600°C (1080°F). Main components Main components - Helicopter air intake - Exhaust pipe - Intake duct - Exhaust extension. - Anti-icing system. Functional description Functional description A circular flange on the compressor casing permits connection of the aircraft air intake duct. The admission of air can be made through a static or a dynamic intake which can be provided with protection devices (filters, anti-icing...). A pressurised seal can also be fitted to improve the connection sealing. Some versions are provided with a device for compressor washing. For training purposes only © Copyright - Turbomeca Training The exhaust expels the gases directly but it can be adapted to the aircraft by means of an extension. The engine compartment ventilation can be accelerated by venturi effect between the engine exhaust pipe and the aircraft duct. Edition: May 2014 11.6 ENGINE INSTALLATION Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) AIR INTAKE AND EXHAUST SYSTEMS Training Notes 1st line maintenance course AIR INTAKE SYSTEM Type: Static or dynamic, annular EXHAUST SYSTEM Type: Divergent Airflow: 2.5 kg/sec. (5.5 lb/sec.) Gas temperature: 600°C (1080°F) AIR DUCT ANTI-ICING SEAL EXHAUST PIPE FILTER VENTURI TO ACCELERATE COMPARTMENT VENTILATION UNION FOR COMPRESSOR WASHING AIR INTAKE AND EXHAUST SYSTEMS For training purposes only © Copyright - Turbomeca Training EXTENSION Edition: May 2014 11.7 ENGINE INSTALLATION Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) ARRIEL 1 ARRIEL 1 Training Notes 1st line maintenance course ENGINE/AIRFRAME SYSTEM INTERFACES For each engine, the oil system has 3 engine/airframe interfaces as follows: Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) OIL SYSTEM - Oil return line to the airframe oil cooler - Oil supply line to the oil pump pack - The vent line: from the oil tank to the accessory gearbox and to the exhaust. For training purposes only © Copyright - Turbomeca Training Edition: May 2014 11.8 ENGINE INSTALLATION Training Notes 1st line maintenance course ARRIEL 1 AIRFRAME BREATHING Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) OIL SUPPLY ENGINE OIL RETURN TO THE COOLER OIL SYSTEM ENGINE/AIRFRAME SYSTEM INTERFACES For training purposes only © Copyright - Turbomeca Training Edition: May 2014 11.9 ENGINE INSTALLATION ARRIEL 1 Training Notes 1st line maintenance course AIRFRAME LOW PRESSURE FUEL SYSTEM Functional description Function The interface comprises the union on the FCU and return to tank union. The aircraft system may include various devices: vent, level indication, filler neck, booster pump, pressure indicator, flowmeter. The booster pump will prime the engine system and prevent cavitation of the pump. The system supplies the engine with fuel under determined conditions of pressure, flow, temperature and filtering. Main characteristics - Filtering 10 microns. Main components - Fuel tank - Booster pump (except 1S) The filtering unit, normally fitted with a pre-blockage indicator and a by-pass valve is in the line before the shut-off valve which is used to isolate the engine compartment from the aircraft system. Note: In the 1E, 1S versions, the fuel inlet union is located on the LP fuel system, located under the engine. - Filter assembly - Fuel shut-off valve - Fuel inlet union - Return to tank union. For training purposes only © Copyright - Turbomeca Training Edition: May 2014 11.10 ENGINE INSTALLATION Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) ENGINE/AIRFRAME SYSTEM INTERFACES Training Notes 1st line maintenance course TO HP PUMP (FCU) FUEL INLET UNION FUEL SHUT-OFF VALVE RETURN TO TANK UNION FUEL SUCTION FROM TANK FILTER UNIT (filtering 10 microns) FUEL TANK 1E, 1S VERSIONS BOOSTER PUMP (except 1S) AIRFRAME LOW PRESSURE FUEL SYSTEM ENGINE/AIRFRAME SYSTEM INTERFACES For training purposes only © Copyright - Turbomeca Training Edition: May 2014 11.11 ENGINE INSTALLATION Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) ARRIEL 1 ARRIEL 1 Training Notes 1st line maintenance course ENGINE/AIRFRAME SYSTEM INTERFACES Functional description Function To allow the control of the fuel valves and of the anticipator. Position The engine control lever and the collective pitch lever are in the cockpit and are mechanically connected to the FCU. - Engine control lever (lever actuating 2 valves and a cam in the fuel control unit: see chapter "FUEL SYSTEM" and aircraft manuals for the mechanical linkage). - Anticipator control (linkage with the helicopter collective pitch: see operation of the anticipator in the chapter "CONTROL SYSTEM" and details of the mechanical connection in the aircraft manuals). Main components - Control lever - Collective pitch lever - Fuel control unit. For training purposes only © Copyright - Turbomeca Training Edition: May 2014 11.12 ENGINE INSTALLATION Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) MECHANICAL CONTROLS Training Notes 1st line maintenance course Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) ARRIEL 1 FUEL VALVE CONTROL CONTROL LEVER ANTICIPATOR CONTROL COLLECTIVE PITCH LEVER MECHANICAL CONTROLS ENGINE/AIRFRAME SYSTEM INTERFACES For training purposes only © Copyright - Turbomeca Training Edition: May 2014 11.13 ENGINE INSTALLATION ARRIEL 1 Training Notes 1st line maintenance course ENGINE/AIRFRAME SYSTEM INTERFACES Possible uses of the air Function - Cabin heating The system provides warm compressed air to the aircraft for the aircraft services. - Pressurised seal Position - Particle separator... One tapping boss on each side of the centrifugal compressor casing. Main components - Air intake anti-icing Note: Refer to aircraft manuals for detailed description of these systems. - Air tapping points (x 2). Functional description Aircraft pipes can be connected to the two tapping points to supply a given flow of P2 air. The flow is limited by restrictors but any air bleed affects engine performance. For training purposes only © Copyright - Turbomeca Training Edition: May 2014 11.14 ENGINE INSTALLATION Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) AIR SYSTEM Training Notes 1st line maintenance course ARRIEL 1 P2 TAPPING Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) P2 AIR SYSTEM ENGINE/AIRFRAME SYSTEM INTERFACES For training purposes only © Copyright - Turbomeca Training Edition: May 2014 11.15 ENGINE INSTALLATION ARRIEL 1 Training Notes 1st line maintenance course Function Description These devices drain and purge fluids from certain areas of the engine, and vent the oil system. Drains Main components The pipes from the output shaft seal drain, FCU drive drain and combustion chamber drain valve are connected to the drain collector, which is fitted on a bracket at the bottom of the accessory gearbox casing. The drain collector discharge pipe is a flexible pipe connected to the aircraft drain. The gas generator rear bearing oil supply drain pipe drains into the engine compartment. The 2 exhaust pipe drains join together to form one single pipe, which is connected to the aircraft drain. Drains Purges - The start purge valve pipe returns to the fuel tank. The stop purge valve pipe is connected to the drain collector (pre TU262) or returns to the fuel tank (post TU262). Position - Various pipes located on the engine Main characteristics - Stainless steel pipes Output shaft seal drain FCU drive drain Combustion chamber drain valve Gas generator rear bearing oil supply drain Exhaust pipe drains (x 2) Air vents The centrifugal breather outlet is connected to a T-union. The front of this T-union is connected to the oil tank air vent pipe, and the rear is connected to the oil system air vent pipe. These pipes vent into the flow of exhaust gases. The gas generator rear bearing air vent pipe vents into the flow of exhaust gases or into the engine compartment (according to version). Purges - Start purge valve - Stop purge valve Air vents - Oil tank air vent (supplied by the aircraft manufacturer) - Oil system air vent (supplied by the aircraft manufacturer) - Gas generator rear bearing air vent For training purposes only © Copyright - Turbomeca Training Edition: May 2014 11.16 ENGINE INSTALLATION Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) DRAINS - PURGES - AIR VENTS Training Notes 1st line maintenance course OIL TANK AIR VENT (supplied by the aircraft manufacturer) GAS GENERATOR REAR BEARING AIR VENT COMBUSTION CHAMBER DRAIN VALVE START PURGE VALVE From oil tank To fuel tank To exhaust/engine compartment GAS GENERATOR REAR BEARING OIL SUPPLY DRAIN STOP PURGE VALVE (pre TU262) EXHAUST PIPE DRAIN FCU DRIVE DRAIN STOP PURGE VALVE (post TU262) OUTPUT SHAFT SEAL DRAIN OUTPUT SHAFT DRAIN To fuel tank To engine compartment To airframe drain To airframe drain DRAINS - PURGES - AIR VENTS For training purposes only © Copyright - Turbomeca Training OIL SYSTEM AIR VENT (supplied by the aircraft manufacturer) Edition: May 2014 11.17 ENGINE INSTALLATION Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) ARRIEL 1 ARRIEL 1 Training Notes 1st line maintenance course Function Functional description The power drive transmits the engine power to the helicopter main gearbox through a drive shaft. The engine drive shaft consists of a steel tube, fitted with the following elements at each end: The link is made by a transmission shaft designed to absorb the engine torque and slight misalignements (supply by aircraft manufacturer or TURBOMECA according to version) - A triangular flange connected to the MGB input flange with a flexible coupling Position - A splined flange, connected to an adaptor flange which is connected to the engine drive shaft flange with a flector. The flexible couplings are installed between the flanges. They transmit torque, absorb shock and vibration and allow slight misalignment. - Between the engine and the helicopter main gearbox. Main characteristics - Shaft designed to absorb the engine torque and slight misalignments Note: In single-engine versions, the free wheel unit drives the main gearbox and the tail rotor shaft drive. - Rotation speed: 6000 rpm at 100%. Main components The main components are: • The engine drive shaft flange • The flector (engine end) • The adapting flange • The drive shaft • The flexible coupling (MGB end) • The main gearbox input flange. For training purposes only © Copyright - Turbomeca Training Edition: May 2014 11.18 ENGINE INSTALLATION Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) POWER DRIVE Training Notes 1st line maintenance course ARRIEL 1 ENGINE DRIVE-FLANGE DRIVE SHAFT 1S VERSION Shaft designed to absorb the engine torque and slight misalignments Rotation speed: 6000 rpm at 100% SPLINES ADAPTOR FLANGE (splined) FLEXIBLE COUPLING MAIN GEARBOX INPUT FLANGE 1E VERSION POWER DRIVE For training purposes only © Copyright - Turbomeca Training Edition: May 2014 11.19 ENGINE INSTALLATION Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) FLECTOR ARRIEL 1 Training Notes 1st line maintenance course FIRE PROTECTION Fire detectors Function The fire detection system detects overtemperature in the engine compartment and gives a cockpit indication. An extinguishing system is installed in the aircraft. Main characteristics - Supplied by the engine manufacturer (except 1S) • Bi-metallic detectors, The detection is ensured by non-sealed detectors with normally closed contact (all versions except 1E and 1S) or one sealed detector with normally open contact (1E) or by means of an aircraft mounted optical device (1S). Some detectors (all variants except 1A, 1B, 1E and 1S) have a resistor fitted in parallel, which allows you to differenciate between the different operating statuses (normal, overtemp or wiring anomaly). In the case of detectors with normally closed contact, the detectors are installed in series and have a setting which corresponds to the engine area of location ("cold" area or "hot" area) and thus they are not interchangeable. - Supplied by the aircraft manufacturer • Optical detectors (1S only) • Indicating system • Extinguishing system. Fire extinguishing system (only on twinengine aircraft) Description - Engine: six detectors (except: 1E: one detector, 1S: no detectors) and the harness (fire proof cables), - Airframe: two detectors (1E and 1S), extinguishing system and a test system. The fire extinguishing system is supplied by the aircraft manufacturer. It includes two extinguisher bottles and spraying jets which spray the extinguishing product, and can be triggered from the cockpit. Note: For more information on the fire extinguishing system, refer to the aircraft manufacturer's documentation. For training purposes only © Copyright - Turbomeca Training Edition: May 2014 11.20 ENGINE INSTALLATION Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) Fire detection system Training Notes 1st line maintenance course ARRIEL 1 + Alarm Area 1 (cold) Area 2 (hot) Supplied by the engine manufacturer (except 1S): • Bi-metallic detectors Detection Supplied by the aircraft manufacturer: • Optical detectors (1S only) • Indicating system • Extinguishing system logic + Test button EXTINGUISHING SYSTEM (bottle, manifold... ) (only on twin-engine helicopters) + Extinguishing button PRINCIPLE OF FIRE PROTECTION SYSTEM All versions except 1E and 1S (6 detectors) 1E 1E NON-SEALED DETECTOR (all versions except 1E and 1S) SEALED DETECTOR (1E and after TU 294) FIRE PROTECTION For training purposes only © Copyright - Turbomeca Training Edition: May 2014 1S 1E and 1S (2 detectors on aircraft) POSITION OF DETECTORS 11.21 ENGINE INSTALLATION Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) Airframe Engine ARRIEL 1 ENGINE INSTALLATION - 1ST LINE MAINTENANCE Mandatory maintenance tasks Refer to the Maintenance Manual (chapter 05). Operations to be performed to comply with Airworthiness objectives are listed in the table of mandatory maintenance tasks. Scheduled inspections Manufacturer-required maintenance tasks List of maintenance tasks to be carried out: - Inspection before the first flight of the day - Turn-around inspection - Inspection after the last flight of the day The manufacturer considers that the manufacturer-required maintenance tasks must be carried out at the scheduled inspection frequency. Failure to do so may cause occurrences liable to affect the engine operating safety. - Inspection after 15 flight hours or 7 days Optional maintenance tasks - Inspection at 30 flight hours Optional maintenance tasks are recommended by the manufacturer as a means of improving reliability, increasing operational availability and reducing operating costs. - Inspection at 50 flight hours - Inspection at 100 flight hours - Inspection at 150 flight hours - Inspection at 200 flight hours - Inspection at 300 flight hours - Inspection at 400 flight hours - Inspection at 500 flight hours - Inspection at 600 flight hours - Inspection at 750 flight hours Note 1: Before carrying out any maintenance tasks, remember to refer to the latest Service Bulletins and Service Letters. Note 2: The maintenance tasks shown below concern the ARRIEL 1D1 variant by way of example and may differ for other ARRIEL 1 variants. Always refer to the Maintenance Manual of the variant concerned. - Inspection at 1,000 flight hours - Inspection at 1,200 flight hours - Inspection at 1,500 flight hours - Inspection at 3,000 flight hours - Inspection at 3,600 flight hours For training purposes only © Copyright - Turbomeca Training Edition: May 2014 11.22 ENGINE INSTALLATION Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) PREVENTIVE MAINTENANCE (1) Training Notes 1st line maintenance course Training Notes 1st line maintenance course ARRIEL 1 PREVENTIVE MAINTENANCE (scheduled inspections) INSPECTION BEFORE THE FIRST FLIGHT OF THE DAY MANDATORY Make sure the engine (that may have undergone repairs subsequent to the inspection after the last flight) is in good flight condition TURN-AROUND INSPECTION MANDATORY Remove the blanks and make sure that there are no foreign objects: examine near the air intakes and the exhaust zone INSPECTION AFTER THE LAST FLIGHT OF THE DAY MANUFACTURER-REQUIRED Make sure that there are no foreign objects: examine near the air intakes and the exhaust zone. Install the blanks Check cowling condition (articulation, locking) Before carrying out any maintenance tasks, remember to refer to the latest Service Bulletins and Service Letters. INSPECTION AFTER 15 FLIGHT HOURS OR 7 DAYS MANDATORY Carry out a run-up. After this run, proceed with an "after the last flight of the day" type inspection Chap. 71 Note: If the aircraft remains on the ground over a week MANUFACTURER-REQUIRED Inspection of the free wheel operation: with the rotor brake on, actuate by hand the blades of the free turbine, from inside the exhaust pipe. Seen from the rear, the free turbine must rotate counter-clockwise and be locked clockwise Examine the engine: tightness of mating surfaces and pipes, condition of the casing, the exhaust pipe and the exhaust pipe attachment Examine the engine: attachment of the accessories and pipes and make sure that pipes show no signs of wear caused by insufficient clearance between pipes and engine Condition and attachment of the engine: compulsory check of the front support Examine the engine: connection of the FCU controls Condition check of the electric equipment and harness attachments (locking of connectors) PREVENTIVE MAINTENANCE (1) ENGINE INSTALLATION - 1ST LINE MAINTENANCE For training purposes only © Copyright - Turbomeca Training Edition: May 2014 11.23 ENGINE INSTALLATION Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) (refer to MM, chapter 05) ARRIEL 1 ENGINE INSTALLATION - 1ST LINE MAINTENANCE Mandatory maintenance tasks Refer to the Maintenance Manual (chapter 05). Operations to be performed to comply with Airworthiness objectives are listed in the table of mandatory maintenance tasks. Scheduled inspections Manufacturer-required maintenance tasks List of maintenance tasks to be carried out: - Inspection before the first flight of the day - Turn-around inspection - Inspection after the last flight of the day The manufacturer considers that the manufacturer-required maintenance tasks must be carried out at the scheduled inspection frequency. Failure to do so may cause occurrences liable to affect the engine operating safety. - Inspection after 15 flight hours or 7 days Optional maintenance tasks - Inspection at 30 flight hours Optional maintenance tasks are recommended by the manufacturer as a means of improving reliability, increasing operational availability and reducing operating costs. - Inspection at 50 flight hours - Inspection at 100 flight hours - Inspection at 150 flight hours - Inspection at 200 flight hours - Inspection at 300 flight hours - Inspection at 400 flight hours - Inspection at 500 flight hours - Inspection at 600 flight hours - Inspection at 750 flight hours Note 1: Before carrying out any maintenance tasks, remember to refer to the latest Service Bulletins and Service Letters. Note 2: The maintenance tasks shown below concern the ARRIEL 1D1 variant by way of example and may differ for other ARRIEL 1 variants. Always refer to the Maintenance Manual of the variant concerned. - Inspection at 1,000 flight hours - Inspection at 1,200 flight hours - Inspection at 1,500 flight hours - Inspection at 3,000 flight hours - Inspection at 3,600 flight hours For training purposes only © Copyright - Turbomeca Training Edition: May 2014 11.24 ENGINE INSTALLATION Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) PREVENTIVE MAINTENANCE (2) Training Notes 1st line maintenance course Training Notes 1st line maintenance course ARRIEL 1 PREVENTIVE MAINTENANCE (scheduled inspections) INSPECTION AT 100 FLIGHT HOURS INSPECTION AT 600 FLIGHT HOURS MANUFACTURER-REQUIRED Inspect visually the two attachment clamps of engine (condition and locking) INSPECTION AT 150 FLIGHT HOURS OPTIONAL Clean the air duct when the engine comes for inspection Chap. 71 INSPECTION AT 300 FLIGHT HOURS MANUFACTURER-REQUIRED Inspection and check of the accessories (attachment, condition of the pipes, supports and unions, locking of connectors) Inspection and check of the pipes and supports MANUFACTURER-REQUIRED Inspection of the fire detection system (attachment, supports, locking of connectors) Chap. 26 Visual inspection of a fire detector Chap. 26 INSPECTION AT 1,500 FLIGHT HOURS MANUFACTURER-REQUIRED Inspection and check of the engine front support for cracks Chap. 72 Chap. 70 Before carrying out any maintenance tasks, remember to refer to the latest Service Bulletins and Service Letters. PREVENTIVE MAINTENANCE (2) ENGINE INSTALLATION - 1ST LINE MAINTENANCE For training purposes only © Copyright - Turbomeca Training Edition: May 2014 11.25 ENGINE INSTALLATION Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) (refer to MM, chapter 05) Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) ARRIEL 1 Training Notes 1st line maintenance course - General ................................................................................................... 12.2 - Troubleshooting .................................................................................... 12.4 - Conclusion ............................................................................................ 12.10 - 12.11 For training purposes only © Copyright - Turbomeca Training Edition: May 2014 12.1 TROUBLESHOOTING Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) 12 - TROUBLESHOOTING ARRIEL 1 Training Notes 1st line maintenance course Introduction Repair procedure Troubleshooting is a very important aspect of maintenance. The repair procedure should be guided by two main considerations: It allows the probable cause(s) of a failure to be identified. Efficient diagnosis reduces the extra maintenance costs due to unjustified removals and additional diagnosis time. In fact, even with a very high-reliability product, failure is inevitable and required actions should be taken efficiently. - Minimum downtime - Justified removal of components. The procedure to be applied depends on the case concerned but, in general, good knowledge of the product and methodical research allows a safe diagnosis and quick corrective action. Generally, the procedure includes the identification of the failure, its analysis, the isolation of the non-conforming component, and the choice of the repair to be applied. For training purposes only © Copyright - Turbomeca Training Edition: May 2014 12.2 TROUBLESHOOTING Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) GENERAL Training Notes 1st line maintenance course Inevitable Random Failure (single, double, dormant) Troubleshooting/ repair - Diagnosis - Remedy - Repair - Check MTTR (Mean Time To Repair) - Appropriate means and procedures - Training of personnel Symptoms (additional information, etc.) Do not neglect any components and take interactions into consideration. Analysis of the anomaly Isolation of the non-conforming component Or other means of detection Additional checks Total time required for troubleshooting / repair Substitution Remedy (adjustment, replacement, cleaning, repair) GENERAL For training purposes only © Copyright - Turbomeca Training Deduction Edition: May 2014 12.3 TROUBLESHOOTING Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) ARRIEL 1 Training Notes 1st line maintenance course REFER TO THE MAINTENANCE MANUAL Chapter 71-00-06 On selection of start, N1 increase, but no increase in T4 The ignition system operates (noise of HE components) Yes No Note: Refer to the test procedure in order to discriminate Possible start on 1 injector + 1 igniter plug if on the same side Note: Yes Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) ARRIEL 1 It is also possible to check the fuel flow through the combustion chamber drain valve. Fuel flow No STARTING ANOMALIES (1) TROUBLESHOOTING For training purposes only © Copyright - Turbomeca Training Edition: May 2014 12.4 TROUBLESHOOTING Training Notes 1st line maintenance course REFER TO THE MAINTENANCE MANUAL Chapter 71-00-06 T4 approx. 200°C Abnormal T4 rise T4 > 200°C but not sufficient Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) ARRIEL 1 T4 too high Increase due to the injectors, but the main system is not supplied Note: In all cases, check the electrical supply (battery voltage). STARTING ANOMALIES (2) TROUBLESHOOTING For training purposes only © Copyright - Turbomeca Training Edition: May 2014 12.5 TROUBLESHOOTING Training Notes 1st line maintenance course Crank selection (press and hold) REFER TO THE MAINTENANCE MANUAL Chapter 71-00-06 Note: 15 sec. max. to avoid starter overheat Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) ARRIEL 1 N1 indication No Yes The starter turns Yes No The gas generator is driven Yes Starting is possible No Yes "Normal" crank No ANOMALIES DURING CRANKING TROUBLESHOOTING For training purposes only © Copyright - Turbomeca Training Edition: May 2014 12.6 TROUBLESHOOTING Training Notes 1st line maintenance course REFER TO THE MAINTENANCE MANUAL Chapter 71-00-06 Abnormal oil pressure indication Low pressure Yes No pressure Low oil pressure light illuminated? Variation Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) ARRIEL 1 High pressure No LUBRICATION ANOMALIES TROUBLESHOOTING For training purposes only © Copyright - Turbomeca Training Edition: May 2014 12.7 TROUBLESHOOTING Training Notes 1st line maintenance course REFER TO THE MAINTENANCE MANUAL Chapter 71-00-06 Uncommanded shut-down Operation of the power turbine overspeed safety system Yes Yes Actual overspeed N2, N1, TRQ, T4, oil pressure decrease Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) ARRIEL 1 No No Doubt Note: Unlikely Note: In a twin engine configuration, the engine which remains in operation supplies the required power within its limits. ANOMALIES LEADING TO IN-FLIGHT SHUT-DOWN TROUBLESHOOTING For training purposes only © Copyright - Turbomeca Training Edition: May 2014 12.8 TROUBLESHOOTING Training Notes 1st line maintenance course REFER TO THE MAINTENANCE MANUAL Chapter 71-00-06 Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) ARRIEL 1 Abnormal gas generator rotation speed N1 Uncommanded acceleration Overspeed Uncommanded deceleration Incorrect response time Fluctuations Note: If one engine remains at a fixed speed, while the second engine operates normally, this indicates a major failure ("frozen" metering unit) MISCELLANEOUS CASES TROUBLESHOOTING For training purposes only © Copyright - Turbomeca Training Edition: May 2014 12.9 TROUBLESHOOTING ARRIEL 1 Training Notes 1st line maintenance course Despite the high reliability of the product, failures remain inevitable and happen at random. However, their rate and effects can be reduced if the “enemies” of the engine are taken into consideration. Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) CONCLUSION When a failure occurs, you have to be in a position to correct it. "Enemies" of the engine The traditional adverse conditions for this type of engine are: - Supply (oil, air, fuel, electricity): • Oil: not in conformity with spec., contamination • Air: sand, salt, pollution • Fuel: not in conformity with spec., contamination • Electricity: low voltage, connectors, interference - Operation (failure to comply with instructions and procedures, severe operating conditions) - Maintenance (failure to comply with inspection frequencies, various errors, poor logistics). For training purposes only © Copyright - Turbomeca Training Edition: May 2014 12.10 TROUBLESHOOTING Training Notes 1st line maintenance course FUEL ELECTRICITY - Not in conformity with specifications - Water in fuel - Sulphur + salt in the air = sulphidation - Low voltage during starting - Interference AIR OPERATION - Sand - Salt - Pollution - Failure to comply with instructions and procedures - Severe operating conditions OIL MAINTENANCE - Failure to comply with inspection frequencies - Various errors - Poor logistics - Not in conformity with specifications - Contamination CONCLUSION For training purposes only © Copyright - Turbomeca Training Edition: May 2014 12.11 TROUBLESHOOTING Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) ARRIEL 1 Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) ARRIEL 1 Training Notes 1st line maintenance course - Introduction ........................................................................................... 13.2 - Questionnaire 1 ..................................................................................... 13.3 - Questionnaire 2 ..................................................................................... 13.6 - Questionnaire 3 ..................................................................................... 13.12 - Questionnaire 4...................................................................................... 13.15 - 13.28 For training purposes only © Copyright - Turbomeca Training Edition: May 2014 13.1 CHECKING OF KNOWLEDGE Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) 13 - CHECKING OF KNOWLEDGE ARRIEL 1 Training Notes 1st line maintenance course Method Types of questionnaires Continuous checking helps to ensure the information is assimilated. It is more a method of work than a testing in the traditional sense. Several types of questionnaire can be used during a course: - Traditional written questionnaires - "Short answer" questionnaires Objectives of the questionnaires The questionnaires allow progressive assimilation and longterm retention of knowledge. The questionnaires are a subject for discussion (effects of group dynamics). They also allow trainees to consider important subjects several times from different points of view. - Multiple-Choice Questionnaires (MCQ) - Oral questionnaires - Learning Through Teaching (LTT): the trainee has to explain a given subject. Integration into the training programme Examination - First hour every day for revision of the subjects previously studied The final examination at the end of the course consists of three tests: written, oral and practical. A course certificate is given to each trainee. - After each chapter (or module) of the course - At the end of the training course. For training purposes only © Copyright - Turbomeca Training Edition: May 2014 13.2 CHECKING OF KNOWLEDGE Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) INTRODUCTION ARRIEL 1 Training Notes 1st line maintenance course This traditional questionnaire is established according to the same plan as the training notes in which the answers can be found. Power plant 1 - List the main functional components of the power plant. 2 - Explain the thermodynamic operation of the engine. 3 - State the following features (at take-off, in standard atmosphere): • Power on the shaft • Output shaft rotation speed • Mass of the engine with specific equipment. Engine 1 - List the main components of the gas generator. 2 - State the following characteristics: • Compression ratio • Turbine entry temperature • N2 speed at 100% • N1 speed at 100% 3 - Describe the power turbine assembly. 4 - Describe the fuel injection system. 5 - List the engine driven accessories. 6 - List the bearings which support the gas generator. 7 - Describe the system used for bearing sealing. 4 -Explain the principle of engine adaptation to helicopter power requirements. 5 - List the main operating ratings. 8 - Describe the modular construction of the engine. 6 - How do temperature and altitude affect the engine performance. 9 - Describe the engine air intake. 7 - List the main aspects of the maintenance concept. 8 - List the technical publications used for engine maintenance. 9 - Name the LRUs of the air system. 10 - List the manufacturing materials of the engine main components. 10 -Explain the attachment of each of the modules. For training purposes only © Copyright - Turbomeca Training Edition: May 2014 13.3 CHECKING OF KNOWLEDGE Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) QUESTIONNAIRE 1 ARRIEL 1 Training Notes 1st line maintenance course QUESTIONNAIRE 1 (continued) Oil system Control system 1 - List the main functions of the control system. 2 - Explain the general operation of the oil system. 2 - Explain the basic principle of the control system. 3 - Describe the oil filter assembly. 3 - Explain the operating principle of the speed control. 4 - State the location of strainers and magnetic plugs. Air system 4 - Describe the purpose and operation of the anticipator control. 1 - List the functions ensured by the internal air system (secondary system). 5 - Explain the operation of the acceleration controller. 2 - List the function of the various air tappings. 3 - Why are the start injectors ventilated? 4 - Explain the purpose and the operation of the compressor bleed valve. Fuel system 6 - What are the main sections of the FCU. 7 - Describe and explain the operation of the power turbine overspeed system. 8 - Describe the principle of load sharing in a twin engine configuration. 1 - What is the purpose of the Booster pump. Measurement and indicating systems 2 - Describe the fuel pump. 1 - Describe the power turbine speed indicating system. 3 - Describe the fuel metering unit. 2 - Explain the operating principle of the torquemeter system. 4 - What is the purpose of the constant ∆P valve. 3 - Describe the gas temperature indicating system. 5 - Explain the principle of fuel injection (main and starting injection). 6 - Explain the operation of the overspeed electro-valve and the stop valve. 7 - Describe the manual control system. For training purposes only © Copyright - Turbomeca Training Edition: May 2014 13.4 CHECKING OF KNOWLEDGE Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) 1 - Draw a simplified diagram of the oil system. ARRIEL 1 Training Notes 1st line maintenance course Starting system Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) QUESTIONNAIRE 1 (continued) 1 - Describe the cranking function of the engine. 2 - Describe the ignition system (ignition unit and igniter plugs). 3 - List the main phases of the starting cycle. 4 - Describe the starting control electrical system. Electrical system 1 - List the engine electrical accessories. 2 - List the sensors (state the type of signal produced). 3 - Describe the electrical harnesses and connectors. Engine installation 1 - Describe the attachment of the engine to the aircraft. 2 - Describe the engine power drive and the power transmission. 3 - List the various engine / aircraft interfaces. 4 - Describe the fire protection system of the engine. For training purposes only © Copyright - Turbomeca Training Edition: May 2014 13.5 CHECKING OF KNOWLEDGE Training Notes 1st line maintenance course ARRIEL 1 Questions QUESTIONNAIRE 2 Trainees can answer orally or in writing in the space provided. 10 - Flight envelope - Max. altitude? Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) The following questions require short, precise answers. Answers 11 - Flight envelope Max. temperature? Questions Answers 12 - Start envelope - Max. altitude? 1 - ARRIEL 1 power class? 13 - Engine air flow at 100% N1? 2 - Power turbine rotation speed at 100%? 14 - Overall compression ratio? 3 - Type of main fuel injection? 4 - Number of engine modules? 5 - Number of power turbine stages? 6 - Meaning of AEO? 15 - Max. turbine entry temperature? 16 - Gas generator rotation speed at 100% N1? 17 - Direction of rotation of the gas generator? 7 - Mass of the equipped engine? 18 - Direction of rotation of the power turbine? 8 - Power evolution when altitude increases? 19 - Manufacturing material for the axial compressor? 9 - Torque evolution function of N2 rotation speed? 20 - What type of bearing is the axial compressor bearing? For training purposes only © Copyright - Turbomeca Training Edition: May 2014 13.6 CHECKING OF KNOWLEDGE Training Notes 1st line maintenance course ARRIEL 1 QUESTIONNAIRE 2 (continued) 21 - How is the axial compressor mounted on the gas generator module? 22 - Axial compressor compression ratio? 23 - Manufacturing material for the centrifugal compressor wheel? Answers Questions Answers 30 - Type of gas generator rear bearing? 31 - Type of power turbine front bearing? 32 - To which module does the power turbine nozzle guide vane belong? 33 - Type of power turbine? 24 - Number of stages of the centrifugal compressor diffuser? 34 - Does the exhaust pipe belong to one module (yes or no)? 25 - Type of combustion chamber? 35 - Type of exhaust pipe attachment? 26 - Manufacturing material for the combustion chamber? 36 - Number of gears in the reduction gearbox? 27 - Type of main fuel injection? 37 - Rotation speed of the intermediate gear of the reduction gearbox? 28 - Pressure drop in the combustion chamber? 29 - Number of stages of the gas generator turbine? For training purposes only © Copyright - Turbomeca Training Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) Questions 38 - Number of driven accessories on the accessory gearbox? 39 - Manufacturing material for the accessory gearbox casing? Edition: May 2014 13.7 CHECKING OF KNOWLEDGE Training Notes 1st line maintenance course ARRIEL 1 QUESTIONNAIRE 2 (continued) Answers Questions Answers 40 - Is the oil pressure adjustable? 50 - Setting of the low oil pressure switch? 41 - Number of pumps in the oil pump pack? 51 - Max. oil temperature? Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) Questions 52 - Location of the centrifugal breather? 42 - Type of oil pumps? 43 - What is the setting of the check valve at the pressure pump outlet? 44 - Filtering ability of the oil filter? 45 - Setting of the oil filter by-pass valve? 53 - Air tapping for the pressurisation of the power turbine front bearing? 54 - Air pressure at the centrifugal compressor outlet? 55 - Temperature at the centrifugal compressor outlet? 46 - Which bearings are ball bearings? 56 - When does the start injector ventilation begin? 47 - Type of seal for the gas generator rear bearing sealing? 57 - Max. air tapping flow? 48 - Max. oil consumption? 49 - Type of oil pressure transmitter? For training purposes only © Copyright - Turbomeca Training 58 - Type of compressor bleed valve? 59 - Position of the bleed valve during starting? Edition: May 2014 13.8 CHECKING OF KNOWLEDGE Training Notes 1st line maintenance course ARRIEL 1 QUESTIONNAIRE 2 (continued) Answers Questions Answers 60 - What are the bleed valve control signals? 71 - How is the anticipator signal transmitted? 61 - Where is the bleed valve fitted? 72 - Setting of the fuel pressurising valve? 62 - Type of fuel filter? 73 - Fuel flow through the start injectors? 63 - Filtering ability of the fuel filter? 64 - Setting of the fuel filter by-pass valve? 65 - Type of fuel pump? 74 - Number of start injectors? 75 - Position of the combustion chamber drain valve when the engine is stopped? 66 - Position of the pump pressure relief valve in normal engine running? 76 - Type of fuel control system? 67 - Type of fuel metering device? 77 - Signals for the acceleration controller 68 - Position of the constant ∆P valve when the engine is stopped? 78 - Average response time of the control system 69 - Type of manual fuel flow control? 79 - Is the static droop compensated 70 - Type of valve for injector ventilation? 80 - Position of the main valve with lever in emergency plus For training purposes only © Copyright - Turbomeca Training Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) Questions Edition: May 2014 13.9 CHECKING OF KNOWLEDGE Training Notes 1st line maintenance course ARRIEL 1 QUESTIONNAIRE 2 (continued) 81 - Meaning of OEI? 82 - Type of N2 controller? 83 - Position of the manual valve with the lever in the emergency minus range? 84 - Closing threshold of the reinjection prohibition switch 85 - What keeps the metering needle closed when the control lever is closed? 86 - Position of the manual control lever in normal engine running? Answers Questions Answers 91 - Where is the oil pressure transmitter located? Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) Questions 92 - H o w a r e t h e t h e r m o c o u p l e s connected (parallel or series)? 93 - Location of the torquemeter? 94 - Type of torque transmitter? 95 - Type of signal output by the transmitter sensor? 96 - Is the torque transmitter associated with a particular module? 97 - Type of starter? 87 - Type of speed sensors? 98 - Type of ignition system? 88 - What is the average torque pressure at 100% torque ? 99 - Gas generator rotation speed at starter cut-off? 89 - How does the low oil pressure switch sense the pressure? 90 - Number of thermocouple probes? For training purposes only © Copyright - Turbomeca Training Edition: May 2014 13.10 CHECKING OF KNOWLEDGE Training Notes 1st line maintenance course ARRIEL 1 QUESTIONNAIRE 2 (continued) Answers Questions Answers 100 - Number of igniter plugs? 111 - Max. gas temperature during starting? 101 - Max. duration of a ventilation? 112 - Low oil pressure switch setting? 102 - Is the ignition cable integral with the igniter plug? 113 - Min. electrical supply voltage before starting? 103 - Number of electrical connectors? 114 - Meaning of LRU? 104 - Location of the tachometer box? 115 - Meaning of TBO? 105 - Type of seal on the power shaft? 116 - Is borescopic inspection of the combustion chamber possible? Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) Questions 106 - Type of connection engine/MGB? 107 - Number of engine drains? 117 - Is there an adjustment of the torquemeter? 108 - Engine operating envelope; min. and max. altitude pressure? 109 - Max. starting altitude? 110 - Power turbine max. overspeed? For training purposes only © Copyright - Turbomeca Training Edition: May 2014 13.11 CHECKING OF KNOWLEDGE ARRIEL 1 Training Notes 1st line maintenance course This type of questionnaire is used to revise certain important points in a relatively short time and to assess how much knowledge has been acquired. The answers to the questions can be found at the end of the questionnaire. 1 - The ARRIEL 1 engine is: a) a free turbine turboshaft engine b) a turbo-jet engine c) a fixed turbine turboshaft engine. 2 - Section of passage of the compressor diffusers: a) regular b) divergent c) convergent. 3 - Type of combustion chamber: a) annular with centrifugal injection b) annular, reverse flow c) annular, indirect flow. 4 - The power turbine nozzle guide vane belongs to : a) module M04 b) module M03 c) module M02 5 - Type of exhaust pipe attachment: a) bolts b) mounting pads c) clamp. For training purposes only © Copyright - Turbomeca Training 6 - How many bearings support the gas generator : a) 4 b) 2 c) 3 Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) QUESTIONNAIRE 3 7 - The engine includes: a) a hot section and a cold section b) 5 modules c) 4 modules. 8 - Type of oil system: a) dry sump b) constant pressure c) lubrication by splashing. 9 - Setting of the oil filter pre-blockage indicator : a) lower than the by-pass valve b) higher than the by-pass valve c) the same as the pump valve. 10 - The oil strainers are located: a) at the outlet of the pumps b) on the inlet of the scavenge pumps c) at the inlet of the lubricated components. 11 - Is there a max. oil temperature: a) yes, 60°C b) no c) yes, 115°C max. Edition: May 2014 13.12 CHECKING OF KNOWLEDGE ARRIEL 1 Training Notes 1st line maintenance course 12 - The air tapped at the centrifugal wheel outlet pressurises : a) some labyrinth seals b) the tank c) the pumps. 13 - Position of the bleed valve during flight? a) open b) closed c) depends on conditions. 14 - Ventilation of start injectors: a) does not exist b) is made with air from the compressor c) is made with atmospheric air pressure: 15 - The injection centrifugal wheel is drained: a) permanently b) to enable the ventilation cycle c) during engine shut-down. 16 - The max. speed of the gas generator is: a) limited by a mechanical stop b) limited by a hydraulic stop c) not limited by the Fuel Control Unit. For training purposes only © Copyright - Turbomeca Training 17 - The gap between the metering needle and the fork: a) represents the instant flow step b) varies with N1 c) provides a smoother acceleration. 18 - The fuel pump is: a) vane type b) centrifugal c) gear type. 19 - The fuel system pressurising valve: a) is electrically controlled b) operates when overpressure occurs c) gives priority to the start injectors. 20 - The starter is de-energised (except 1E version): a) automatically b) by air pressure c) manually. 21 - The thermocouples are wired: a) in series b) in parallel c) on the turbine casing. Edition: May 2014 13.13 CHECKING OF KNOWLEDGE Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) QUESTIONNAIRE 3 (continued) ARRIEL 1 Training Notes 1st line maintenance course 22 - The torque indicating system: a) is hydraulic b) is not used c) is of phase displacement type. 28 - HE ignition means: a) Hot Electrode b) High Energy c) High Emission. 23 - Number of thermocouple probes: a) 3 b) 4 c) 5. 29 - Borescopic inspection is used to check: a) the external parts condition b) the condition of internal parts which are not accessible without removal c) the reduction gearbox condition. 24 - Oil pump pressure relief valve setting? a) 300 kPa b) 600 kPa c) 800 kPa. 30 - The reliability of the engine is: a) good b) fairly good c) extremely good. 4-b 9-a 14 - b 19 - c 24 - c 29 - b 5-a 10 - b 15 - c 20 - c 25 - b 30 - abc? Answers For training purposes only © Copyright - Turbomeca Training 3-a 8-a 13 - c 18 - c 23 - a 28 - b 27 - Starting is possible with one igniter: a) yes b) no c) yes, in emergency. 2-b 7-b 12 - a 17 - a 22 - a 27 - a 26 - The starter is supplied via a: a) contactor b) micro switch c) transistor. 1-a 6-c 11 - c 16 - a 21 - b 26 - a 25 - Bleed valve position is transmitted by: a) a pressure switch b) a micro switch c) an RVDT. Edition: May 2014 13.14 CHECKING OF KNOWLEDGE Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) QUESTIONNAIRE 3 (continued) ARRIEL 1 Training Notes 1st line maintenance course This type of questionnaire is a sort of drill which is also used to test and perfect the knowledge acquired. 2 - Name the reference stations and place the numbers in the correct circles: 1 - Complete this table (with values): C G T1 T2 Max. Take-Off Power CC Compression ratio Engine air flow 0 1 2 WF 3 4 5 N2 speed at 100% N1 speed at 100% For training purposes only © Copyright - Turbomeca Training 0 - ..................................... 3 - .................................... 1 - ..................................... 4 - .................................... 2 - ..................................... 5 - .................................... Edition: May 2014 13.15 CHECKING OF KNOWLEDGE Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) QUESTIONNAIRE 4 Training Notes 1st line maintenance course ARRIEL 1 QUESTIONNAIRE 4 (continued) 1 2 3 6 5 4 1 - ......................................................... 2 - ............................................................. 3 - ....................................................... 4 - ......................................................... 5 - ............................................................. 6 - ...................................................... For training purposes only © Copyright - Turbomeca Training Edition: May 2014 13.16 CHECKING OF KNOWLEDGE Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) 3 - Engine - Complete the legend of the diagram below: Training Notes 1st line maintenance course ARRIEL 1 4 - Oil system - Complete the legend of the diagram below: AIRFRAME 4 ENGINE 2 1 5 3 6 1 - ......................................................... 2 - ............................................................. 3 - ....................................................... 4 - ......................................................... 5 - ............................................................. 6 - ...................................................... For training purposes only © Copyright - Turbomeca Training Edition: May 2014 13.17 CHECKING OF KNOWLEDGE Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) QUESTIONNAIRE 4 (continued) ARRIEL 1 Training Notes 1st line maintenance course QUESTIONNAIRE 4 (continued) P0 P1' Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) 5 - Air system - Tick the boxes as required to indicate which air pressure is used for each function: P2 Injector ventilation Acceleration control unit Bleed valve control pressure Injection wheel pressurisation Axial compressor bearing pressurisation Gas generator rear bearing cooling Power turbine bearing chamber labyrinth pressurisation Gas generator turbine disc cooling For training purposes only © Copyright - Turbomeca Training Edition: May 2014 13.18 CHECKING OF KNOWLEDGE Training Notes 1st line maintenance course ARRIEL 1 6 - Air system - Complete the legend of the compressor field diagram: Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) QUESTIONNAIRE 4 (continued) P2/P0 PRESSURE RATIO A B C AIRFLOW G A - ......................................................... For training purposes only © Copyright - Turbomeca Training B - ............................................................. Edition: May 2014 C - ....................................................... 13.19 CHECKING OF KNOWLEDGE Training Notes 1st line maintenance course ARRIEL 1 QUESTIONNAIRE 4 (continued) 1 2 3 Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) 7 - Fuel system - Complete the legend of the diagram below: 4 5 6 8 7 1 - ..................................... 2 - ..................................... 3 - ..................................... 4 - .............................. 5 - ..................................... 6 - ..................................... 7 - ..................................... 8 - .............................. For training purposes only © Copyright - Turbomeca Training Edition: May 2014 13.20 CHECKING OF KNOWLEDGE Training Notes 1st line maintenance course ARRIEL 1 QUESTIONNAIRE 4 (continued) Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) 8 - Fuel system - Complete the legend of the diagram below: 8 7 1 2 6 3 5 4 1 - ..................................... 2 - ..................................... 3 - ..................................... 4 - .............................. 5 - ..................................... 6 - ..................................... 7 - ..................................... 8 - .............................. For training purposes only © Copyright - Turbomeca Training Edition: May 2014 13.21 CHECKING OF KNOWLEDGE ARRIEL 1 Training Notes 1st line maintenance course QUESTIONNAIRE 4 (continued) Engine stopped Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) 9 - Fuel system - Indicate the position of the following components according to the operating conditions: Engine in stabilised flight Fuel pump.................................................................. Pump pressure relief valve......................................... Constant ∆P valve ..................................................... Metering needle ......................................................... Start electro-valve...................................................... Stop purge valve........................................................ Pressurising valve...................................................... Main valve.................................................................. Combustion chamber drain valve............................... For training purposes only © Copyright - Turbomeca Training Edition: May 2014 13.22 CHECKING OF KNOWLEDGE Training Notes 1st line maintenance course ARRIEL 1 10 - Control system - List the components: 1 2 6 P2 3 WF 5 + N1 4 N1* + N2 + N2* 1 - ......................................................... 2 - ............................................................. 3 - ....................................................... 4 - ......................................................... 5 - ............................................................. 6 - ...................................................... For training purposes only © Copyright - Turbomeca Training Edition: May 2014 13.23 CHECKING OF KNOWLEDGE Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) QUESTIONNAIRE 4 (continued) ARRIEL 1 Training Notes 1st line maintenance course QUESTIONNAIRE 4 (continued) Power turbine speed N2 time Load TRQ Fuel flow WF time time Gas generator speed N1 time For training purposes only © Copyright - Turbomeca Training Edition: May 2014 13.24 CHECKING OF KNOWLEDGE Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) 11 - Complete the following graphs during a load TRQ increase: Training Notes 1st line maintenance course ARRIEL 1 QUESTIONNAIRE 4 (continued) 4 Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) 12 - Drains/Purges/Air vents - Complete the legend of the diagram below: 3 5 6 7 8 1 2 1 - ..................................... 2 - ..................................... 3 - ..................................... 4 - .............................. 5 - ..................................... 6 - ..................................... 7 - ..................................... 8 - .............................. For training purposes only © Copyright - Turbomeca Training Edition: May 2014 13.25 CHECKING OF KNOWLEDGE ARRIEL 1 Training Notes 1st line maintenance course QUESTIONNAIRE 4 (continued) Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) 13 - Complete the following table : Number of lifting points? Type of fire detectors? Number of drain points? Air used for intake anti-icing? Max. air tapping flow for aircraft use? Loss of power due to aircraft tapping? For training purposes only © Copyright - Turbomeca Training Edition: May 2014 13.26 CHECKING OF KNOWLEDGE ARRIEL 1 Training Notes 1st line maintenance course 14 - Give a brief definition of the following documents: Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) QUESTIONNAIRE 4 (continued) Maintenance manual(s) Spare parts catalogue Tools catalogue Service bulletins Service letters Engine log book Flight manual For training purposes only © Copyright - Turbomeca Training Edition: May 2014 13.27 CHECKING OF KNOWLEDGE ARRIEL 1 Training Notes 1st line maintenance course QUESTIONNAIRE 4 (continued) Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) 15 - Troubleshooting - Indicate the probable cause(s) of the following failures. 1 - On start selection, N increases but not the gas temperature. 2 - On start selection, N and T4 increase but not sufficiently to obtain start. 3 - Surge of the compressor. 4 - Max. power not obtained. 5 - On stop selection, the engine does not completely shut-down. 6 - Incorrect speed of the helicopter rotor. 7 - Power turbine overspeed. 8 - Drop of oil pressure. 9 - Abnormal T4 temperature. 10 - N1 overspeed. For training purposes only © Copyright - Turbomeca Training Edition: May 2014 13.28 CHECKING OF KNOWLEDGE of these Training Notes and (maybe also) of the course but not the END of your training which must be continued, harmonising knowledge and experience. THANK YOU for your kind attention. Au revoir Goodbye Adiós Auf Wiedersehen Adeus Arrivederci Farvel To t z i e n s Adjö Näkemiin Antio Ma salaam Selamat jalan Adishatz Ikus Arte Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) END Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) Any remarks (appreciations, criticisms, suggestions...) should be forwarded to: TURBOMECA CENTRE D’INSTRUCTION 40220 TARNOS - FRANCE REMARKS CONCERNING THE TRAINING AIDS REMARKS CONCERNING THE TRAINING COURSE Name.......................................................................................................................... . Address..................................................................................................................... . Course........................................................ from.........................to.......................... . TURBOMECA Training Centre Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) REMARKS Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page) Training information only delivered during a Turbomeca Training course and not updated after the course (refer to the FOREWORD page)

TRAINING NOTES ARRIEL 1 Turbine Engine

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