AW139 Pilot Recurrent Ground Course (PRT) Training Manual PDF
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Leonardo S.P.A. - Training Academy “A. Marchetti”
2018
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Summary
This document is a training manual for the AW139 helicopter pilot recurrent ground course (PRT). It covers various aircraft systems and performance, along with malfunction procedures. The manual aims to prepare trainees for simulator sessions and emphasizes the importance of referring to official technical publications.
Full Transcript
TRAINING PUBLICATION PMC-39-A0126-PR001-00 AW139 PILOT RECURRENT GROUND COURSE (PRT) TRAINING MANUAL 39-PR001-TP FOR TRAINING PURPOSE ONLY Issue No.005 2018-03-06 Page: 1 TRAINING PUBLICATION...
TRAINING PUBLICATION PMC-39-A0126-PR001-00 AW139 PILOT RECURRENT GROUND COURSE (PRT) TRAINING MANUAL 39-PR001-TP FOR TRAINING PURPOSE ONLY Issue No.005 2018-03-06 Page: 1 TRAINING PUBLICATION PMC-39-A0126-PR001-00 THIS TRAINING PUBLICATION IS ISSUED TO TRAINEES OF LEONARDO S.P.A. - TRAINING ACADEMY “A.MARCHETTI” (LEONARDO) FOR TRAINING PURPOSE ONLY. THE INFORMATION CONTAINED IN THIS TRAINING PUBLICATION IS NOT INTENDED TO SUBSTITUTE OR REPLACE ANY RELEVANT TECHNICAL PUBLICATION/ORDER/INSTRUCTION ISSUED BY ANY COMPETENT DESIGN AUTHORITY IN RELATION TO THE SUBJECT MATTER HEREIN AND THE TRAINEES SHALL ALWAYS REFER TO THESE OFFICIAL DOCUMENTS WHILE PERFORMING ACTIVITIES ON THE HELICOPTER. THE INFORMATION HEREIN IS UPDATED AT THE DATE OF RELEASE OF THIS TRAINING PUBLICATION AND LEONARDO DOES NOT TAKE ANY COMMITMENT TO UPDATE THE SAME UNLESS LEONARDO DETERMINES AT ITS SOLE DISCRETION TO RELEASE AN UPDATE OF THIS DOCUMENT. MOREOVER LEONARDO REPRESENTS THAT NO FURTHER DOCUMENT WILL BE PROVIDED TO THE TRAINEE IN ADDITION TO THE TRAINING PUBLICATION HEREIN. INFORMATION AND DRAWINGS CONTAINED IN THIS TRAINING PUBLICATION ARE CONFIDENTIAL AND PROPERTY OF LEONARDO, TRAINEE SHALL USE SUCH INFORMATION FOR THE TRAINING PURPOSE ONLY AND KEEP THE INFORMATION HEREIN CONFIDENTIAL AND NOT MAKE AVAILABLE OR OTHERWISE DISCLOSE SUCH INFORMATION TO ANY THIRD PARTY WITHOUT THE PRIOR WRITTEN CONSENT OF LEONARDO, ANY UNAUTHORISED USE DISCLOSURE REPRODUCTION IN WHOLE OR IN PART OF THE INFORMATION CONTAINED IN THIS TRAINING PUBLICATION IS FORBIDDEN AND PROSECUTED IN ACCORDANCE WITH THE APPLICABLE LAW. 39-PR001-TP FOR TRAINING PURPOSE ONLY Issue No.005 2018-03-06 Page: 2 TRAINING PUBLICATION PMC-39-A0126-PR001-00 TABLE OF CONTENTS The listed chapters are included in issue 005, dated 2018-03-06 of this publication. N = New chapter, C = Changed data module, D = Deleted chapter. The publication consists of 296 pages total, as below specified. CHAPTER TITLE CHAPTER CODE ISSUE DATE N. OF PAGES APPLICABLE TO 00 – HELICOPTER - GENERAL Technical Publications 39-A-00-40-00-00A-048A-T C 2018-03-06 10 PR 22 – AUTO FLIGHT Autopilot 39-A-22-00-00-00A-048A-T C 2018-03-06 26 PR 23 - COMMUNICATIONS General 39-A-23-00-00-00A-048A-T C 2018-03-06 22 PR 24 – ELECTRICAL POWER General 39-A-24-00-00-00A-048A-T C 2018-03-06 30 PR Electrical – Service lost 39-A-24-11-00-00A-048A-T C 2018-03-06 8 PR 26 – FIRE PROTECTION General 39-A-26-00-00-00A-048A-T C 2018-03-06 10 PR 28 – FUEL General 39-A-28-00-00-00A-048A-T C 2018-03-06 18 PR 39-PR001-TOC FOR TRAINING PURPOSE ONLY 2018-03-06 Page: 1 TRAINING PUBLICATION PMC-39-A0126-PR001-00 CHAPTER TITLE CHAPTER CODE ISSUE DATE N. OF PAGES APPLICABLE TO 29 – HYDRAULIC POWER General 39-A-29-00-00-00A-048A-T C 2018-03-06 24 PR 32 – LANDING GEAR General 39-A-32-00-00-00A-048A-T C 2018-03-06 14 PR 34 – NAVIGATION General 39-A-34-00-00-00A-048A-T C 2018-03-06 46 PR 46 – SYSTEM INTEGRATION AND DISPLAY General 39-A-46-00-00-00A-048A-T C 2018-03-06 14 PR 63 – MAIN ROTOR DRIVE General 39-A-63-00-00-00A-048A-T C 2018-03-06 16 PR 71 – POWER PLANT General 39-A-71-00-00-00A-048A-T C 2018-03-06 28 PR 39-PR001-TOC FOR TRAINING PURPOSE ONLY 2018-03-06 Page: 2 TRAINING PUBLICATION PMC-39-A0126-PR001-00 PURPOSE OF THE COURSE The purpose of this course is to provide an opportunity for the class to review aircraft systems and performance and to discuss malfunction procedures. The course is not intended to review the procedures you perform each day but to focus on abnormal conditions and prepare you for your simulator sessions. In that regard, you are expected to refer to the procedures in the QRH (or company ECL) whenever a malfunction is displayed on the screen. Your personal field experience is an important part of the course. You are encouraged to share pertinent operational events as they directly relate to the subjects presented. It is not possible to comprehensively cover all the subjects listed in the course menu in a two-day class. The flow of the classroom subjects is dependent on your input and your preferences. The instructor may ask for your preferences after certain base subjects are covered. 39-PR001-TOC FOR TRAINING PURPOSE ONLY 2018-03-06 Page: 3 TRAINING PUBLICATION PMC-39-A0126-PR001-00 PAGE INTENTIONALLY LEFT BLANK 39-PR001-TOC FOR TRAINING PURPOSE ONLY 2018-03-06 Page: 4 TRAINING PUBLICATION PMC-39-A0126-PR001-00 LIST OF ABBREVIATIONS A AP Autopilot AB Agusta Bell APM Aircraft Personality Module AC Alternating Current APP Approach A/C Aircraft APPR Approach ACCB Air Conditioning Control Box ARINC Aeronautical Radio Inc. ACT Actuator ASCB-D Avionics Standard Communication Bus ver.D ADC Ampére Direct Current ATC Air Traffic Control ADI Attitude Director Indicator ATT Attitude ADF Automatic Direction Finder AUD Audio ADM Air Data Module AUTO Automatic ADS Air Data System AUX Auxiliary ADV Advance AW AgustaWestland AEO All Engine Operative AWG Aural Warning Generator AFCS Automatic Flight Control System AGB Accessory Gear Box B AGL Above Ground Level BAG Baggage Ah Ampere hour BATT Battery AHRS Attitude And Heading Reference System BC Back Course AHRU Attitude Heading Reference Unit BFO Beat Frequency Oscillator AIOP Actuator Input/Output Processor (Module) BIT Built In Test ALT Altitude BKUP Backup ALTA Altitude Acquire BL Buttock Line ALTN Alternate BLT Belt ALT SEL Altitude Select BOD Bottom Of Descent ALVL Autolevel BOW Basic Operating Weight AM Amplitude Modulation BRG Bearing AMSL Above Mean Sea Level BRK Breaker AMLCD Active Matrix Liquid Crystal Display BRT Bright ; Brightness AMP Ampére BTL Bottle ANT Antenna 39-PR001-LoA FOR TRAINING PURPOSE ONLY 2018-03-06 Page: 1 TRAINING PUBLICATION PMC-39-A0126-PR001-00 C CPLT Copilot C Collective CPL Coupled °C Celsius / Centigrade(degrees) CRS Course CAB Cabin CRZ Cruise CAN Control Area Network (bus) CSIO Custom Input/Output (MAU Module) CAPTS Captions CSL Console CAS Crew Alerting System CT Current Transformer CAS Calibrated Airspeed CTO Continued Take-Off CAT Category CVR Cockpit Voice Recorder CB Circuit Breaker CW Clock-Wise C/B Circuit Breaker CWS Central Warning System CCD Cursor Control Device CCW Counter Clock-Wise D CFUR Critical Failure (ECC) DC Direct Current CG Center of Gravity DC Display Controller CHM Chime DC Down Counter CHRG Charge DCL Deceleration CIO Control Input/Output (MAU Module) DCM Detachable Configuration Module CKPT Cockpit DCU Data Collection Unit CLPR Caliper DEL Delete CLR Clear DEOS Digital Engine Operating System (MAU) CLTV Collective DET Detector CMC Central Maintenance Computer DETR Detector CMC-RT Central Maintenance Computer Remote Terminal DF Directional Finder CMS Central Maintenance System DG Directional Gyro COLL Collective DGR Degraded COLL Collision DH Decision Height COM Communication DICP Display Instrument Control Panel (Display Controller) COMM Communication (sameas DC) COND Conditioning DIM Dimmer / Dimmed / Dimming CONTR Control DIR Direct/ Direct to CP Control Panel 39-PR001-LoA FOR TRAINING PURPOSE ONLY 2018-03-06 Page: 2 TRAINING PUBLICATION PMC-39-A0126-PR001-00 DME Distance Measuring Equipment EXTG Extinguish / Extinguisher DMG Digital Map Generator DN Down F DOP Dilution of Precision FAA Federal Aviation Administration DR Dead Reckoning FAF Final Approach Fix DSCWD Discrete Worth (EEC) FCOC Fuel Cooled Oil Cooler DTK Desired Trak F/C Flight Control DU Display Unit FCP Fuel Control Panel FCU Fuel Computer Unit E FCS Flight Control System EAPS Engine Air Particle Separator FCU Fuel Control Unit EASA European Aviation Safety Agency FD Flight Director ECL Engine Control Lever FDR Flight Data Recorder ECP Engine Control Panel FF Fuel Flow ECS Environmental Control System FH Flight Hours ECU Engine Control Unit FL Flight Level EDS Electronic Display System FL Fuel EEC Electronic Engine Control FLIR Forward Looking Infra Red EGPWS Enhanced Ground Proximity Warning System FLT Flight ELEC Electric / Electrical FLT DIR Flight Director ELT Emergency Locator System FMCW Frequency Modulated Continuous Wave EMERG Emergency FMM Fuel Management Module EMS Emergency Medical Service FMS Flight Management System ENAC Ente Nazionale Aviazione Civile FMV Fuel Management Valve ENBL Enable / Enabled FOD Foreign Object Damage ENG Engine FOG Fiber Optic Gyro EPU Estimated Position Uncertainty FOM Figure of Merit ESS Essential FPL Flight Plan ET Elapsed Time FTR Force Trim Release ETA Estimated Time of Arrival FWD Forward ETE Estimated Time En-route EXT External 39-PR001-LoA FOR TRAINING PURPOSE ONLY 2018-03-06 Page: 3 TRAINING PUBLICATION PMC-39-A0126-PR001-00 G H-V Height - Velocity GA GoAround HVR Hover GC Guidance Controller HYD Hydraulic GCU Generation Control Unit GEN General I GEN Generator IAF Initial Approach Fix GOV Governor (Engine) IAS Indicated Air Speed GND Ground ICS Intercommunication System GPS Global Positioning System ID Ident / Identifier GR Gear IETP Interactive Electronic Technical Publication GS Glide Slope IFR Instrument Flight Rules GS Ground Speed IGB Intermediate Gearbox GSE Ground Support Equipment IGE In Ground Effect GW Gross Weight IGN Ignition IHBT Inhibit H ILS Instrument Landing System HCB Heating Control Box INPH Interphone Hd Density Altitude IR Infra Red HDG Heading ISA International Standard Atmosphere HDPH Head Phone ITT Inter-Turbine Temperature HDST Headset HF High Frequency J HIL Horizontal Integrity Limit (GPS) JAA Joint Aviation Authority HOV Hover JAR Joint Airworthiness Regulations Hp Pressure Altitude HP High Pressure K HP Horse Power KIAS Knots Indicated Air Speed HPA hecto Pascal (hPa) KPH Kilograms per Hour HIS Horizontal Situation Indicator KTS Knots HT Height HTR Heater HUMS Health and Usage Monitoring System 39-PR001-LoA FOR TRAINING PURPOSE ONLY 2018-03-06 Page: 4 TRAINING PUBLICATION PMC-39-A0126-PR001-00 L M L Left MAG MAGnetic LAN Local Area Network MAN Manual LAT Lateral MAP Missed Approach Point LCD Liquid Crystal Display MAU Modular Avionics Unit LD Load MAX Maximum LDG Landing MB Marker Beacon LDG GR Landing Gear MCDU Multifunction Control Display Unit LED Light Emitting Diode MCL Master Caution Light LG Landing Gear MCP Maximum Continuous Power LGCL Landing Gear Control Lever MDA Minimum Descent Altitude LGCP Landing Gear Control Panel MEM Memory LGCV Landing Gear Control Valve MFD Multi-Function Display LH Left Hand MGB Main Gear Box LIM Limiter / Limiting MIC Microphone LLD Low Level Detection MIN Minimum LLDM Low Level Detection Mode MISC Miscellaneous LLS Lightning Sensor System MKR BCN Marker Beacon LOC Localizer MLG Main Landing Gear LONG Longitude MMEL Master Minimum Equipment List LONG Longitudinal MOT Mark On Target LNAV Lateral Navigation MPFDR Multipurpose Flight Data Recorder LP Low Pressure MPOG Minimum Pitch On Ground LRM Line Replaceable Module MR Main Rotor LRU Line Replaceable Unit MRA Main Rotor Actuator LSK Line Select Key MRC Modular Radio Cabinet LSS Lightning Sensor System MRDS Main Rotor Drive System LT Left MSG Message LT Light LT Local Time LVDT Linear Variable Differential Transducer 39-PR001-LoA FOR TRAINING PURPOSE ONLY 2018-03-06 Page: 5 TRAINING PUBLICATION PMC-39-A0126-PR001-00 MSTR Master P MTBF Mean Time Between Failures P Pitch MTTR Maintenance Time to Replace PA Passenger Address MWL Master Warning Light PA Pubblic Address MWS Monitor Warning System PAX Passengers PCM Power Control Module PDP Power Distribution Panel N PERF Performance NAV Navigation PFD Primary Flight Display NCFUR Non-Critical Failure (EEC) PI Power Index N-ESS Non Essential PLT Pilot Nf or NF Engine free turbine speed PMA Permanent Magnent Alternator Ng or NG Engine gas generator speed POSN Position NIC Network Interface Controller P/N Part Number NIM Network Interface Module PPH Pounds per Hour NLG Nose Landing Gear PRAIM Predictive RAIM NM Nautical Mile PREV Previous NORM Normal PRI Primary NO SMK No Smoking PROG Progress Nr or NR Rotor speed PRV Preview; Pressure Relief Valve NVG Night Vision Goggle PSU Passenger Service Unit NVM Non Volatile Memory PTT Press to Talk PTT Press to Transmit O PWR Power OAT Outside Air Temperature OC Over Current Q OEI One Engine Inoperative QRH Quick Reference Handbook OGE Out of Ground Effect OS Over Station OVHD Overhead OVHT Overheat OVTQ Overtorque 39-PR001-LoA FOR TRAINING PURPOSE ONLY 2018-03-06 Page: 6 TRAINING PUBLICATION PMC-39-A0126-PR001-00 R RT Right RTD Resistance Temperature Device R Right / Roll RTN Return RA Rectract Actuator RTO Rejected Take-Off RAD Radio RTR Rotor RAD ALT Radio Altitude / Radio Altimeter RAIM Receiver Autonomus Performance RB Rotor Brake S RBA Rotor Brake Assembly SA Shortening Actuator RBAA Rotor Brake Actuation Assembly SAR Search and Rescue RBCL Rotor Brake Control Lever SAS Stability Augmentation System RBCM Rotor Brake Control Module SATCOM Satellite Communication RBPI Rotor Brake Pressure Indicator SCMS Software Configuration Management Module RBRB Rotor Brake Relays Box SEAT BLT Seat Belt RCP Reversion Control Panel SEL Select RCRD Record SELCAL Selective Call RDR Radar SHP Shaft Horse Power REC Received SHT DN Shut Down REC Record SID Standard Instrument Departure REL Release SL Sea Level RETR Retract / Retraction S/N Serial Number RFM Rotorcraft Flight Manual SOV Shut Off Valve RH Right Hand SP Space RHT Radar Altitude Hold SPD Speed RIC Remote Instrument Controller SPKR Speaker RICP Remote Instrument Control Panel (same as RIC) SQ Squelch RNAV Area Navigation STA Station (line) RNP Required Navigatio Performance STAR Standard Terminal Arrival Route ROC Rate of Climb STBY Stand-By RPM Revolution Per Minute ST/SP Start / Stop RSB Radio System Bus SW Stopwatch RST Reset SYS System 39-PR001-LoA FOR TRAINING PURPOSE ONLY 2018-03-06 Page: 7 TRAINING PUBLICATION PMC-39-A0126-PR001-00 T UTIL SOW Utility Shut-Off Valve TA Traffic Advisory / Terrain Awareness UV Ultra-Violet TAD Terrain / Obstacle Awareness Display TAS True Air Speed V TAWS Terrain Awareness and Warning System VAPP VOR Approach TBD To Be Defined / To Be Determined VCE Voice TBO Time Between Overhaul VLO Maximum landing gear operating speed TCAS Traffic Alert and Collision Avoidance System VLE Maximum landing gear extended speed TCV Temperature Control Valve VNE Never Exceed speed TEMP Temporary VDR VHF Data Radio TERR Terrain VEL Velocity TGB Tail Gear Box VENT Ventilation TNG Training VFR Visual Flight Rules TO Take-Off VGP Vertical Glide Path T/O Take-Off VHF Very High Frequency TOC Table of Contents; Top Of Climb VIDL VOR/ILS Data Link TOD Top Of Descent VIL Vertical Integrity Limit (GPS) TOP Take Off Power VIP Very Important Person TQ Engine Torque V/L VOR/LOC TR Tail Rotor VNAV Vertical Navigation TRA Tail Rotor Actuator VOL Volume TRANS Transmission VOR VHF Omnidirectional Range TRDS Tail Rotor Drive System VOX Voice Operated Switch / Voice Operated Circuit TRSOV Tail Rotor Shut-Off Valve VPATH Vertical Flight Path TU Transition Up Vs versus VS Vertical Speed U VTA Vertical Track Alert UCPL Uncoupled V/UHF VHF and UHF UHF Ultra High Frequency ULB Underwater Locator Beacon UNLK Unlock UTIL Utility 39-PR001-LoA FOR TRAINING PURPOSE ONLY 2018-03-06 Page: 8 TRAINING PUBLICATION PMC-39-A0126-PR001-00 W WHL Wheel WL Water Line WOW Weight-On-Wheels WT Weight WTR Winch-man Trim WX Weather WXR Weather Radar X XFD Crossfeed XFEED Crossfeed XMIT Transmit XMSN Transmission XPDR Trasponder Y Y Yaw Z Z Zulu (time) 39-PR001-LoA FOR TRAINING PURPOSE ONLY 2018-03-06 Page: 9 TRAINING PUBLICATION PMC-39-A0126-PR001-00 PAGE INTENTIONALLY LEFT BLANK 39-PR001-LoA FOR TRAINING PURPOSE ONLY 2018-03-06 Page: 10 TRAINING PUBLICATION PMC-39-A0126-PR001-00 CHAPTER 00 HELICOPTER - GENERAL 39-A-00-40-00-00A-048A-T FOR TRAINING PURPOSE ONLY 2018-03-06 Page: 1 TRAINING PUBLICATION PMC-39-A0126-PR001-00 PAGE INTENTIONALLY LEFT BLANK 39-A-00-40-00-00A-048A-T FOR TRAINING PURPOSE ONLY 2018-03-06 Page: 2 TRAINING PUBLICATION PMC-39-A0126-PR001-00 SECTION 40 – TECHNICAL PUBLICATION AIRCRAFT PUBLICATIONS 39-A-00-40-00-00A-048A-T FOR TRAINING PURPOSE ONLY 2018-03-06 Page: 1 TRAINING PUBLICATION PMC-39-A0126-PR001-00 IETP — INTERACTIVE ELECTRONIC TECHNICAL PUBLICATION 39-A-00-40-00-00A-048A-T FOR TRAINING PURPOSE ONLY 2018-03-06 Page: 2 TRAINING PUBLICATION PMC-39-A0126-PR001-00 MASTER MINIMUM EQUIPMENT LIST (MMEL) 39-A-00-40-00-00A-048A-T FOR TRAINING PURPOSE ONLY 2018-03-06 Page: 3 TRAINING PUBLICATION PMC-39-A0126-PR001-00 RFM – ROTORCRAFT FLIGHT MANUAL 39-A-00-40-00-00A-048A-T FOR TRAINING PURPOSE ONLY 2018-03-06 Page: 4 TRAINING PUBLICATION PMC-39-A0126-PR001-00 RFM - APPROVAL 39-A-00-40-00-00A-048A-T FOR TRAINING PURPOSE ONLY 2018-03-06 Page: 5 TRAINING PUBLICATION PMC-39-A0126-PR001-00 RFM – TERMINOLOGY 39-A-00-40-00-00A-048A-T FOR TRAINING PURPOSE ONLY 2018-03-06 Page: 6 TRAINING PUBLICATION PMC-39-A0126-PR001-00 SECTION 3 PROCEDURES - LANDING GUIDANCE 39-A-00-40-00-00A-048A-T FOR TRAINING PURPOSE ONLY 2018-03-06 Page: 7 TRAINING PUBLICATION PMC-39-A0126-PR001-00 QRH – QUICK REFERENCE HANDBOOK 39-A-00-40-00-00A-048A-T FOR TRAINING PURPOSE ONLY 2018-03-06 Page: 8 TRAINING PUBLICATION PMC-39-A0126-PR001-00 CHAPTER 22 AUTO FLIGHT 39-A-22-00-00-00A-048A-T FOR TRAINING PURPOSE ONLY 2018-03-06 Page: 1 TRAINING PUBLICATION PMC-39-A0126-PR001-00 PAGE INTENTIONALLY LEFT BLANK 39-A-22-00-00-00A-048A-T FOR TRAINING PURPOSE ONLY 2018-03-06 Page: 2 TRAINING PUBLICATION PMC-39-A0126-PR001-00 SECTION 00 – GENERAL AUTOMATIC FLIGHT CONTROL SYSTEM (AFCS) – GENERAL The AW139 Automatic Flight Control System (AFCS) is part of the PRIMUS EPIC® Integrated Avionics System. The AFCS is a system fully duplicated for redundancy and consists of: Autopilot No.1 (AP1) Autopilot No.2 (AP2) Flight Director No.1 (FD1) Flight Director No.2 (FD2) The Flight Director is an optional equipment that is available in three configurations with increasing capabilities: 4-AXIS BASIC FLIGHT DIRECTOR: When coupled to the Autopilot it provides automatic flight path control around the three axis of the aircraft plus collective control. (Auto Hover mode not available). Refer: RFM Supplement 40 or 70 4-AXIS ENHANCED FLIGHT DIRECTOR: Same as the 4-Axis Basic FD plus Auto Hover/Velocity Hold Mode. Refer: RFM Supplement 34 or 67 4-AXIS ENHANCED FLIGHT DIRECTOR WITH SAR MODES: Same as 4-Axis Enhanced FD plus the following SAR modes: Transition Down (TD), Transition Up (TU), Winch-man Trim (WTR), Mark-On-Target (MOT). Refer: RFM Supplement 69 The AFCS is an Active-Active system because both Autopilots operate on the flight controls at the same time. The No.1 and No.2 AP and FD systems normally operate together. Each AP and FD is capable of providing full functionality in case of failure of the paired system. The AFCS is designed to be fail-safe because autopilot malfunctions are demonstrated to be safely recoverable by the pilot flying the helicopter manually. The pilot can override the AFCS at any time by manually operating the flight controls. The system gives the pilot full authority over flight controls regardless of whether the autopilot is engaged or disengaged. The dual AFCS uses: two AFCS computers (part of MAU1 and MAU2) two independent sets of sensors (AHRS, ADS, RAD ALT, VOR/ILS, FMS) three sets of dual Linear (series) Actuators (Pitch, Roll, Yaw) four single rotary Trim (parallel) Actuators (Pitch, Roll, Yaw and Collective) 39-A-22-00-00-00A-048A-T FOR TRAINING PURPOSE ONLY 2018-03-06 Page: 1 TRAINING PUBLICATION PMC-39-A0126-PR001-00 PURPOSE, ARCHITECTURE AND MAIN COMPONENTS 39-A-22-00-00-00A-048A-T FOR TRAINING PURPOSE ONLY 2018-03-06 Page: 2 TRAINING PUBLICATION PMC-39-A0126-PR001-00 MAU1 AND MAU2 – AFCS MODULES 39-A-22-00-00-00A-048A-T FOR TRAINING PURPOSE ONLY 2018-03-06 Page: 3 TRAINING PUBLICATION PMC-39-A0126-PR001-00 TRIM ACTUATORS 39-A-22-00-00-00A-048A-T FOR TRAINING PURPOSE ONLY 2018-03-06 Page: 4 TRAINING PUBLICATION PMC-39-A0126-PR001-00 TRIM ACTUATORS AND FORCE TRIM 39-A-22-00-00-00A-048A-T FOR TRAINING PURPOSE ONLY 2018-03-06 Page: 5 TRAINING PUBLICATION PMC-39-A0126-PR001-00 PITCH AND ROLL DUAL LINEAR ACTUATORS 39-A-22-00-00-00A-048A-T FOR TRAINING PURPOSE ONLY 2018-03-06 Page: 6 TRAINING PUBLICATION PMC-39-A0126-PR001-00 YAW DUAL LINEAR ACTUATOR 39-A-22-00-00-00A-048A-T FOR TRAINING PURPOSE ONLY 2018-03-06 Page: 7 TRAINING PUBLICATION PMC-39-A0126-PR001-00 AUTOPILOT – FUNCTIONAL DIAGRAM 39-A-22-00-00-00A-048A-T FOR TRAINING PURPOSE ONLY 2018-03-06 Page: 8 TRAINING PUBLICATION PMC-39-A0126-PR001-00 YAW AXIS CONTROL FUNCTIONS 39-A-22-00-00-00A-048A-T FOR TRAINING PURPOSE ONLY 2018-03-06 Page: 9 TRAINING PUBLICATION PMC-39-A0126-PR001-00 FLIGHT DIRECTOR – FUNCTIONAL BLOCK DIAGRAM 39-A-22-00-00-00A-048A-T FOR TRAINING PURPOSE ONLY 2018-03-06 Page: 10 TRAINING PUBLICATION PMC-39-A0126-PR001-00 FLIGHT DIRECTOR INDICATIONS 39-A-22-00-00-00A-048A-T FOR TRAINING PURPOSE ONLY 2018-03-06 Page: 11 TRAINING PUBLICATION PMC-39-A0126-PR001-00 COLLECTIVE CUE AND PI LIMITING 39-A-22-00-00-00A-048A-T FOR TRAINING PURPOSE ONLY 2018-03-06 Page: 12 TRAINING PUBLICATION PMC-39-A0126-PR001-00 APP MODE – VGP 39-A-22-00-00-00A-048A-T FOR TRAINING PURPOSE ONLY 2018-03-06 Page: 13 TRAINING PUBLICATION PMC-39-A0126-PR001-00 APP MODE – VGP PATTERN 39-A-22-00-00-00A-048A-T FOR TRAINING PURPOSE ONLY 2018-03-06 Page: 14 TRAINING PUBLICATION PMC-39-A0126-PR001-00 APP MODE – VGP PATTERN 39-A-22-00-00-00A-048A-T FOR TRAINING PURPOSE ONLY 2018-03-06 Page: 15 TRAINING PUBLICATION PMC-39-A0126-PR001-00 ILS – DCL MODE 39-A-22-00-00-00A-048A-T FOR TRAINING PURPOSE ONLY 2018-03-06 Page: 16 TRAINING PUBLICATION PMC-39-A0126-PR001-00 GA MODE 39-A-22-00-00-00A-048A-T FOR TRAINING PURPOSE ONLY 2018-03-06 Page: 17 TRAINING PUBLICATION PMC-39-A0126-PR001-00 HOV MODE (HOVER/VELOCITY HOLD) 39-A-22-00-00-00A-048A-T FOR TRAINING PURPOSE ONLY 2018-03-06 Page: 18 TRAINING PUBLICATION PMC-39-A0126-PR001-00 HOV MODE OPERATION 39-A-22-00-00-00A-048A-T FOR TRAINING PURPOSE ONLY 2018-03-06 Page: 19 TRAINING PUBLICATION PMC-39-A0126-PR001-00 HOV MODE – VEL FAIL 39-A-22-00-00-00A-048A-T FOR TRAINING PURPOSE ONLY 2018-03-06 Page: 20 TRAINING PUBLICATION PMC-39-A0126-PR001-00 FD AURAL MESSAGES 39-A-22-00-00-00A-048A-T FOR TRAINING PURPOSE ONLY 2018-03-06 Page: 21 TRAINING PUBLICATION PMC-39-A0126-PR001-00 FLIGHT DIRECTOR INDICATIONS (PRIMUS EPIC® PHASE 5, 6 & 7 ONLY) 39-A-22-00-00-00A-048A-T FOR TRAINING PURPOSE ONLY 2018-03-06 Page: 22 TRAINING PUBLICATION PMC-39-A0126-PR001-00 SAFETY FLY-UP FUNCTIONALY EG: VS MODE (PRIMUS EPIC® PHASE 5, 6 & 7 ONLY) 39-A-22-00-00-00A-048A-T FOR TRAINING PURPOSE ONLY 2018-03-06 Page: 23 TRAINING PUBLICATION PMC-39-A0126-PR001-00 PRIMUS EPIC® SOFTWARE PHASE 7 ONLY – SPECIFIC FUNCTIONS “LPV APPROACH CAPABILITY” 39-A-22-00-00-00A-048A-T FOR TRAINING PURPOSE ONLY 2018-03-06 Page: 24 TRAINING PUBLICATION PMC-39-A0126-PR001-00 CHAPTER 23 COMMUNICATIONS 39-A-23-00-00-00A-048A-T FOR TRAINING PURPOSE ONLY 2018-03-06 Page: 1 TRAINING PUBLICATION PMC-39-A0126-PR001-00 PAGE INTENTIONALLY LEFT BLANK 39-A-23-00-00-00A-048A-T FOR TRAINING PURPOSE ONLY 2018-03-06 Page: 2 TRAINING PUBLICATION PMC-39-A0126-PR001-00 SECTION 00 – GENERAL BACKUP ICS MODE Each audio panel has a backup mode that can be selected via the BKUP pop-up control knob when one of the Audio Panels fails. The backup mode connects the pilot headset directly to the onside VHF COMM (Backup analog radio audio line) and cross-side audio panel ICS for intercommunication (Backup analog interphone line). In case the Audio Panel failure depends on the loss of input power (ICS PLT or ICS CPLT circuit breaker tripped), power to operate the Audio Panel in Backup mode comes from the cross-side Audio Panel. In Backup mode, switching between inter-communication and radio transmission is performed by an external relay controlled by the Radio PTT button. In Backup mode, the BKUP pop-up control knob on the Audio Panel controls both the ICS and COM audio volumes. In this case the ICS and COM audio volumes cannot be adjusted separately. BACKUP RADIO TUNING In case the normal radio tuning is not available (eg. NIM failure, MAU failure) a BKUP RADIO page is available in the MCDU to permit limited control of the on-side main radios only. A dedicated backup radio tuning line (ARINC 429 digital bus) between each MCDU and the on-side MRC allows each pilot only to tune the on-side VHF COM and VHF NAV radios and to control the on-side transponder. DME Hold function is not available in backup mode, The DME will automatically be retuned to the VHF NAV paired frequency. MAU FAILURE: The BKUP RADIO page is automatically selected on the on-side MCDU Normal tuning using the CCD and the PFD is still available via the cross-side MAU. FAILURE INDICATIONS Any of the components of the radio system that are not supplying valid data to the MCDU or PFD are shown in amber and frequencies are replaced with amber dashes. NIM FAILURE: Failure of a NIM does not trigger any message in the CAS window. It can only be recognized by the simultaneous loss of all the associated radios indicated by amber labels and amber dashes replacing frequencies. The on-side pilot only can control the radios in the affected MRC by selecting the MCDU to BACKUP RADIO page. The affected VHF COM radio can be used for transmission by the on-side pilot only if the Audio Panel is set to BKUP. 39-A-23-00-00-00A-048A-T FOR TRAINING PURPOSE ONLY 2018-03-06 Page: 1 TRAINING PUBLICATION PMC-39-A0126-PR001-00 PURPOSE AND MAIN COMPONENTS 39-A-23-00-00-00A-048A-T FOR TRAINING PURPOSE ONLY 2018-03-06 Page: 2 TRAINING PUBLICATION PMC-39-A0126-PR001-00 MODULAR RADIO CABINET (MRC) 39-A-23-00-00-00A-048A-T FOR TRAINING PURPOSE ONLY 2018-03-06 Page: 3 TRAINING PUBLICATION PMC-39-A0126-PR001-00 MRC1 AND MRC2 STANDARD CONFIGURATION 39-A-23-00-00-00A-048A-T FOR TRAINING PURPOSE ONLY 2018-03-06 Page: 4 TRAINING PUBLICATION PMC-39-A0126-PR001-00 ANTENNAS LOCATION 39-A-23-00-00-00A-048A-T FOR TRAINING PURPOSE ONLY 2018-03-06 Page: 5 TRAINING PUBLICATION PMC-39-A0126-PR001-00 COMMUNICATION SYSTEM – MAIN COMPONENTS 39-A-23-00-00-00A-048A-T FOR TRAINING PURPOSE ONLY 2018-03-06 Page: 6 TRAINING PUBLICATION PMC-39-A0126-PR001-00 COMMUNICATION SYSTEM – ALL COMPONENTS 39-A-23-00-00-00A-048A-T FOR TRAINING PURPOSE ONLY 2018-03-06 Page: 7 TRAINING PUBLICATION PMC-39-A0126-PR001-00 COMMUNICATION SYSTEM – ALL COMPONENTS + BACKUP LINE 39-A-23-00-00-00A-048A-T FOR TRAINING PURPOSE ONLY 2018-03-06 Page: 8 TRAINING PUBLICATION PMC-39-A0126-PR001-00 NORMAL RADIO OPERATION 39-A-23-00-00-00A-048A-T FOR TRAINING PURPOSE ONLY 2018-03-06 Page: 9 TRAINING PUBLICATION PMC-39-A0126-PR001-00 RADIO OPERATION – COM 1 FAILURE 39-A-23-00-00-00A-048A-T FOR TRAINING PURPOSE ONLY 2018-03-06 Page: 10 TRAINING PUBLICATION PMC-39-A0126-PR001-00 RADIO OPERATION – MAU 1 FAILURE 39-A-23-00-00-00A-048A-T FOR TRAINING PURPOSE ONLY 2018-03-06 Page: 11 TRAINING PUBLICATION PMC-39-A0126-PR001-00 RADIO OPERATION – MAU 2 FAILURE 39-A-23-00-00-00A-048A-T FOR TRAINING PURPOSE ONLY 2018-03-06 Page: 12 TRAINING PUBLICATION PMC-39-A0126-PR001-00 Copilot side Pilot side MAU 1 failure: MAU 2 failure: RADIO OPERATION – MAU 1 AND MAU 2 FAILURE 39-A-23-00-00-00A-048A-T FOR TRAINING PURPOSE ONLY 2018-03-06 Page: 13 TRAINING PUBLICATION PMC-39-A0126-PR001-00 RADIO OPERATION – AUDIO PANEL FAILURE 39-A-23-00-00-00A-048A-T FOR TRAINING PURPOSE ONLY 2018-03-06 Page: 14 TRAINING PUBLICATION PMC-39-A0126-PR001-00 RADIO OPERATION – NIM 1 FAILURE 39-A-23-00-00-00A-048A-T FOR TRAINING PURPOSE ONLY 2018-03-06 Page: 15 TRAINING PUBLICATION PMC-39-A0126-PR001-00 RADIO OPERATION – NIM 2 FAILURE 39-A-23-00-00-00A-048A-T FOR TRAINING PURPOSE ONLY 2018-03-06 Page: 16 TRAINING PUBLICATION PMC-39-A0126-PR001-00 Copilot side Pilot side NIM 1 failure: NIM 2 failure: RADIO OPERATION – NIM 1 AND NIM 2 FAILURE 39-A-23-00-00-00A-048A-T FOR TRAINING PURPOSE ONLY 2018-03-06 Page: 17 TRAINING PUBLICATION PMC-39-A0126-PR001-00 MCDU – MANUAL BACKUP MODE ON THE COPILOT SIDE 39-A-23-00-00-00A-048A-T FOR TRAINING PURPOSE ONLY 2018-03-06 Page: 18 TRAINING PUBLICATION PMC-39-A0126-PR001-00 MCDU – MANUAL BACKUP MODE ON THE PILOT SIDE 39-A-23-00-00-00A-048A-T FOR TRAINING PURPOSE ONLY 2018-03-06 Page: 19 TRAINING PUBLICATION PMC-39-A0126-PR001-00 CAS MESSAGES 39-A-23-00-00-00A-048A-T FOR TRAINING PURPOSE ONLY 2018-03-06 Page: 20 TRAINING PUBLICATION PMC-39-A0126-PR001-00 CHAPTER 24 ELECTRICAL POWER 39-A-24-00-00-00A-048A-T FOR TRAINING PURPOSE ONLY 2018-03-06 Page: 1 TRAINING PUBLICATION PMC-39-A0126-PR001-00 PAGE INTENTIONALLY LEFT BLANK 39-A-24-00-00-00A-048A-T FOR TRAINING PURPOSE ONLY 2018-03-06 Page: 2 TRAINING PUBLICATION PMC-39-A0126-PR001-00 SECTION 00 – GENERAL ELECTRICAL POWER – GENERAL The electrical power system is a 28 VDC system that: Generates and distributes DC electrical power Stores electrical energy into batteries for: In-flight emergency operations, and Autonomous engine starting and ground operations Distributes DC electrical power provided by an external power source on the ground ELECTRICAL POWER – GENERAL ARRANGEMENT The system consists of two similar subsystems, no.1 (LH) and no.2 (RH), each consisting of: A Starter-Generator and the relevant Generator Control Unit (GCU) A Battery (Main on LH; Auxiliary on RH) A set of bus bars ranked – from the most important – as: Essential bus........................................................... (ESS) Main bus.................................................................. (MAIN) Non-Essential bus.................................................... (NON ESS) A Battery Bus – directly powered by the Auxiliary Battery supplies power to the on-board recorders (FDR/CVR and CMC) for proper shut-down when power is removed from the Essential busses. ESS BUS 1 and ESS BUS 2 are interconnected via a circuit breaker and protected by diodes so that they cannot supply power to any other bus bar. MAIN BUS 1 and MAIN BUS 2 are normally isolated; a BUS TIE contactor permits interconnection to allow transfer of power from one side to the other in case of generator failure or when generators are not operating. External power – when available – is connected to MAIN BUS 1; however, external power is distributed to all bus bars. The Auxiliary Battery is only capable of providing electrical power to the Essential Bus. Diodes prevent power from being directed anywhere else. 39-A-24-00-00-00A-048A-T FOR TRAINING PURPOSE ONLY 2018-03-06 Page: 1 TRAINING PUBLICATION PMC-39-A0126-PR001-00 PURPOSE, AND MAJOR COMPONENTS 39-A-24-00-00-00A-048A-T FOR TRAINING PURPOSE ONLY 2018-03-06 Page: 2 TRAINING PUBLICATION PMC-39-A0126-PR001-00 DC POWER – GENERAL ARRANGEMENT 39-A-24-00-00-00A-048A-T FOR TRAINING PURPOSE ONLY 2018-03-06 Page: 3 TRAINING PUBLICATION PMC-39-A0126-PR001-00 REAR AVIONICS BAYS – LH AVIONICS RACK 39-A-24-00-00-00A-048A-T FOR TRAINING PURPOSE ONLY 2018-03-06 Page: 4 TRAINING PUBLICATION PMC-39-A0126-PR001-00 AUXILIARY BATTERY - PLACARD 39-A-24-00-00-00A-048A-T FOR TRAINING PURPOSE ONLY 2018-03-06 Page: 5 TRAINING PUBLICATION PMC-39-A0126-PR001-00 CABIN ROOF 39-A-24-00-00-00A-048A-T FOR TRAINING PURPOSE ONLY 2018-03-06 Page: 6 TRAINING PUBLICATION PMC-39-A0126-PR001-00 DC POWER – SIMPLIFIED DIAGRAM 39-A-24-00-00-00A-048A-T FOR TRAINING PURPOSE ONLY 2018-03-06 Page: 7 TRAINING PUBLICATION PMC-39-A0126-PR001-00 DC POWER – SIMPLIFIED DIAGRAM 39-A-24-00-00-00A-048A-T FOR TRAINING PURPOSE ONLY 2018-03-06 Page: 8 TRAINING PUBLICATION PMC-39-A0126-PR001-00 DC POWER – SIMPLIFIED DIAGRAM 39-A-24-00-00-00A-048A-T FOR TRAINING PURPOSE ONLY 2018-03-06 Page: 9 TRAINING PUBLICATION PMC-39-A0126-PR001-00 DC POWER – SIMPLIFIED DIAGRAM 39-A-24-00-00-00A-048A-T FOR TRAINING PURPOSE ONLY 2018-03-06 Page: 10 TRAINING PUBLICATION PMC-39-A0126-PR001-00 DC POWER – SIMPLIFIED DIAGRAM 39-A-24-00-00-00A-048A-T FOR TRAINING PURPOSE ONLY 2018-03-06 Page: 11 TRAINING PUBLICATION PMC-39-A0126-PR001-00 DC POWER – SIMPLIFIED DIAGRAM 39-A-24-00-00-00A-048A-T FOR TRAINING PURPOSE ONLY 2018-03-06 Page: 12 TRAINING PUBLICATION PMC-39-A0126-PR001-00 DC POWER – SIMPLIFIED DIAGRAM 39-A-24-00-00-00A-048A-T FOR TRAINING PURPOSE ONLY 2018-03-06 Page: 13 TRAINING PUBLICATION PMC-39-A0126-PR001-00 DC POWER – SIMPLIFIED DIAGRAM 39-A-24-00-00-00A-048A-T FOR TRAINING PURPOSE ONLY 2018-03-06 Page: 14 TRAINING PUBLICATION PMC-39-A0126-PR001-00 DC POWER – SIMPLIFIED DIAGRAM (E1) 39-A-24-00-00-00A-048A-T FOR TRAINING PURPOSE ONLY 2018-03-06 Page: 15 TRAINING PUBLICATION PMC-39-A0126-PR001-00 DC POWER – SIMPLIFIED DIAGRAM 39-A-24-00-00-00A-048A-T FOR TRAINING PURPOSE ONLY 2018-03-06 Page: 16 TRAINING PUBLICATION PMC-39-A0126-PR001-00 DC POWER – SIMPLIFIED DIAGRAM 39-A-24-00-00-00A-048A-T FOR TRAINING PURPOSE ONLY 2018-03-06 Page: 17 TRAINING PUBLICATION PMC-39-A0126-PR001-00 DC POWER – SIMPLIFIED DIAGRAM 39-A-24-00-00-00A-048A-T FOR TRAINING PURPOSE ONLY 2018-03-06 Page: 18 TRAINING PUBLICATION PMC-39-A0126-PR001-00 DC POWER – SIMPLIFIED DIAGRAM 39-A-24-00-00-00A-048A-T FOR TRAINING PURPOSE ONLY 2018-03-06 Page: 19 TRAINING PUBLICATION PMC-39-A0126-PR001-00 DC POWER – SIMPLIFIED SCHEMATIC DIAGRAM (M1) 39-A-24-00-00-00A-048A-T FOR TRAINING PURPOSE ONLY 2018-03-06 Page: 20 TRAINING PUBLICATION PMC-39-A0126-PR001-00 SINGLE DC GEN FAILURE 39-A-24-00-00-00A-048A-T FOR TRAINING PURPOSE ONLY 2018-03-06 Page: 21 TRAINING PUBLICATION PMC-39-A0126-PR001-00 DC BUS FAILURE (OVERCURRENT) - BUS 1 OC LEVEL 1 39-A-24-00-00-00A-048A-T FOR TRAINING PURPOSE ONLY 2018-03-06 Page: 22 TRAINING PUBLICATION PMC-39-A0126-PR001-00 DC BUS FAILURE (SHORT CIRCUIT) - BUS 1 OC LEVEL 2 39-A-24-00-00-00A-048A-T FOR TRAINING PURPOSE ONLY 2018-03-06 Page: 23 TRAINING PUBLICATION PMC-39-A0126-PR001-00 DUAL DC GEN FAILURE – MAIN BATT ON 39-A-24-00-00-00A-048A-T FOR TRAINING PURPOSE ONLY 2018-03-06 Page: 24 TRAINING PUBLICATION PMC-39-A0126-PR001-00 DUAL DC GEN FAILURE – MAIN BATT OFF 39-A-24-00-00-00A-048A-T FOR TRAINING PURPOSE ONLY 2018-03-06 Page: 25 TRAINING PUBLICATION PMC-39-A0126-PR001-00 CAS WARNING MESSAGE 39-A-24-00-00-00A-048A-T FOR TRAINING PURPOSE ONLY 2018-03-06 Page: 26 TRAINING PUBLICATION PMC-39-A0126-PR001-00 CAS CAUTION MESSAGES 39-A-24-00-00-00A-048A-T FOR TRAINING PURPOSE ONLY 2018-03-06 Page: 27 TRAINING PUBLICATION PMC-39-A0126-PR001-00 CAS CAUTION MESSAGES (PRIMUS EPIC® PHASE 5, 6 & 7 ONLY) 39-A-24-00-00-00A-048A-T FOR TRAINING PURPOSE ONLY 2018-03-06 Page: 28 TRAINING PUBLICATION PMC-39-A0126-PR001-00 SECTION 11 – SERVICE LOST DC POWER – SIMPLIFIED DIAGRAM 39-A-24-11-00-00A-048A-T FOR TRAINING PURPOSE ONLY 2018-03-06 Page: 1 TRAINING PUBLICATION PMC-39-A0126-PR001-00 Refer to the QRH to identify services lost when Main Bus 2 is no longer powered as a result of a short circuit or dual generator failure. LOSS OF MAIN BUS 2 39-A-24-11-00-00A-048A-T FOR TRAINING PURPOSE ONLY 2018-03-06 Page: 2 TRAINING PUBLICATION PMC-39-A0126-PR001-00 Cockpit indications when Main Bus 2 is no longer powered as a result of a short circuit or dual generator failure. LOSS OF MAIN BUS 2 39-A-24-11-00-00A-048A-T FOR TRAINING PURPOSE ONLY 2018-03-06 Page: 3 TRAINING PUBLICATION PMC-39-A0126-PR001-00 Cockpit functions affected when Main Bus 2 is no longer powered as a result of a short circuit or dual generator failure. LOSS OF MAIN BUS 2 39-A-24-11-00-00A-048A-T FOR TRAINING PURPOSE ONLY 2018-03-06 Page: 4 TRAINING PUBLICATION PMC-39-A0126-PR001-00 Refer to the QRH to identify services lost when both Main Bus 1 and Main Bus 2 are no longer powered following a dual generator failure and after turning the BATT MAIN OFF LOSS OF MAIN BUS 1 AND 2 39-A-24-11-00-00A-048A-T FOR TRAINING PURPOSE ONLY 2018-03-06 Page: 5 TRAINING PUBLICATION PMC-39-A0126-PR001-00 Cockpit indications when both Main Bus 1 and Main Bus 2 are no longer powered as a result of a short circuit or dual generator failure. LOSS OF MAIN BUS 1 AND 2 39-A-24-11-00-00A-048A-T FOR TRAINING PURPOSE ONLY 2018-03-06 Page: 6 TRAINING PUBLICATION PMC-39-A0126-PR001-00 Cockpit functions affected when both Main Bus 1 and Main Bus 2 are no longer powered as a result of a short circuit or dual generator failure. LOSS OF MAIN BUS 1 AND 2 39-A-24-11-00-00A-048A-T FOR TRAINING PURPOSE ONLY 2018-03-06 Page: 7 TRAINING PUBLICATION PMC-39-A0126-PR001-00 Cockpit functions affected when both Main Bus 1 and Main Bus 2 are no longer powered as a result of a short circuit or dual generator failure and the completion of the extended endurance procedure. LOSS OF MAIN BUS 1 AND 2 39-A-24-11-00-00A-048A-T FOR TRAINING PURPOSE ONLY 2018-03-06 Page: 8 TRAINING PUBLICATION PMC-39-A0126-PR001-00 CHAPTER 26 FIRE PROTECTION 39-A-26-00-00-00A-048A-T FOR TRAINING PURPOSE ONLY 2018-03-06 Page: 1 TRAINING PUBLICATION PMC-39-A0126-PR001-00 PAGE INTENTIONALLY LEFT BLANK 39-A-26-00-00-00A-048A-T FOR TRAINING PURPOSE ONLY 2018-03-06 Page: 2 TRAINING PUBLICATION PMC-39-A0126-PR001-00 SECTION 00 – GENERAL FIRE DETECTION – PRINCIPLE OF OPERATION The firewire element takes into account two types of high temperature conditions: The first type is a general overheat condition. In this case if the temperature around the firewire element increases over a preset limit. As a consequence the sensor acts in accordance with the law of gases: if the volume of the firewire element is held constant, its pressure will increase as temperature increases. The helium gas in the tube exerts a pressure which closes the high pressure switch that generates the ENG FIRE message. The second type is a fire condition at a short section of the firewire sensor element. In this case the core material releases a large volume of hydrogen gas so that the internal pressure of the firewire element increases very quickly and the gas in the tube exerts a pressure which closes the high pressure switch that generates the ENG FIRE message. After the situation is corrected, the material reabsorbs the hydrogen and the system returns to a stand-by mode. In case of leakage of the helium gas from the firewire element, the pressure will decrease and operates the low pressure switch which generates the FIRE DET message. FIRE EXTINGUISHING – PRINCIPLE OF OPERATION Refer to AW139 Rotor Flight Manual (RFM) for emergency procedures to be applied in case of fire (on the Ground or in Flight). NOTE: The command to extinguish fire is done via the FIRE switch on the FIRE EXTG panel which, after being pressed, illuminates the amber segment ARM. The extinction of the fire does not cause the automatic re-opening of the fuel shut-off valve which was automatically closed when the FIRE switch was activated. In case the first shot fails to extinguish the fire, a second shot is available by moving the switch to the second bottle indication. 39-A-26-00-00-00A-048A-T FOR TRAINING PURPOSE ONLY 2018-03-06 Page: 1 TRAINING PUBLICATION PMC-39-A0126-PR001-00 FIRE DETECTION - FIREWIRE 39-A-26-00-00-00A-048A-T FOR TRAINING PURPOSE ONLY 2018-03-06 Page: 2 TRAINING PUBLICATION PMC-39-A0126-PR001-00 FIRE DETECTION - RESPONDER 39-A-26-00-00-00A-048A-T FOR TRAINING PURPOSE ONLY 2018-03-06 Page: 3 TRAINING PUBLICATION PMC-39-A0126-PR001-00 LOCATION OF MAJOR COMPONENTS – FIRE EXTINGUISHER 39-A-26-00-00-00A-048A-T FOR TRAINING PURPOSE ONLY 2018-03-06 Page: 4 TRAINING PUBLICATION PMC-39-A0126-PR001-00 FIRE EXTINGUISHING - DISCHARGE INDICATOR 39-A-26-00-00-00A-048A-T FOR TRAINING PURPOSE ONLY 2018-03-06 Page: 5 TRAINING PUBLICATION PMC-39-A0126-PR001-00 ENGINE FIRE WARNING CONTROLS AND INDICATIONS 39-A-26-00-00-00A-048A-T FOR TRAINING PURPOSE ONLY 2018-03-06 Page: 6 TRAINING PUBLICATION PMC-39-A0126-PR001-00 SCHEMATIC DIAGRAM - FIRE EXTINGUISHER 39-A-26-00-00-00A-048A-T FOR TRAINING PURPOSE ONLY 2018-03-06 Page: 7 TRAINING PUBLICATION PMC-39-A0126-PR001-00 BAGGAGE SMOKE DETECTOR AND INDICATIONS 39-A-26-00-00-00A-048A-T FOR TRAINING PURPOSE ONLY 2018-03-06 Page: 8 TRAINING PUBLICATION PMC-39-A0126-PR001-00 CHAPTER 28 FUEL 39-A-28-00-00-00A-048A-T FOR TRAINING PURPOSE ONLY 2018-03-06 Page: 1 TRAINING PUBLICATION PMC-39-A0126-PR001-00 PAGE INTENTIONALLY LEFT BLANK 39-A-28-00-00-00A-048A-T FOR TRAINING PURPOSE ONLY 2018-03-06 Page: 2 TRAINING PUBLICATION PMC-39-A0126-PR001-00 SECTION 00 – GENERAL FUEL – GENERAL The fuel system consists of the following sub-systems: fuel storage fuel distribution fuel indicating FUEL STORAGE – GENERAL DESCRIPTION The storage system is composed of two tanks connected together through a flange located on the lower side of the tanks. Both tanks are gravity refilled through a filler cap located on top of the tank 2 (optional left hand gravity filler cap and optional pressure (closed circuit) refuelling are also available). A sump plate with a fuel drain valve and a water drain valve is installed at the bottom of each tank. To ensure an equal level of pressure between the tanks and the existing ambient pressure, each tank is provided at the top with a venting pipeline routed to the opposite side. A flame arrestor in each venting pipeline prevents flashback to the tanks in the event of fire hazards. FUEL STORAGE – MAIN COMPONENTS TANKS The fuel tanks are bladder-type and are attached to the airframe by two types of restraints: velcro pads and nylon chord. The two tanks are interconnected by an open flange that permits free flow: this ensures automatic fuel balancing between LH and RH tanks, when the fuel level is above the flange (about 228 kg per tank). Consequently, each tank retains a maximum of about 228 kg that cannot be transferred to the other tank: this permits a suitable amount of fuel to be saved in case of rupture of one of the tanks. In case of a crash, the main landing gear collapses upward, away from the fuel tank: in this case, foam supports in the lower side of each tank help to maintain the tank in the right position. SUMP PLATES The sump plates are located at the bottom of each tank and are provided with: a fuel booster pump a secondary fuel quantity probe with a low level sensor a fuel drain valve a water drain valve FUEL DRAIN VALVES AND WATER DRAIN VALVES The water drain valves can be operated electrically with a switch located in the main landing gear sponson to sump fuel for normal check operations. 39-A-28-00-00-00A-048A-T FOR TRAINING PURPOSE ONLY 2018-03-06 Page: 1 TRAINING PUBLICATION PMC-39-A0126-PR001-00 FUEL STORAGE 39-A-28-00-00-00A-048A-T FOR TRAINING PURPOSE ONLY 2018-03-06 Page: 2 TRAINING PUBLICATION PMC-39-A0126-PR001-00 FUEL STORAGE – MAIN AND AUXILIARY TANKS 39-A-28-00-00-00A-048A-T FOR TRAINING PURPOSE ONLY 2018-03-06 Page: 3 TRAINING PUBLICATION PMC-39-A0126-PR001-00 FUEL STORAGE – MAIN AND AUXILIARY TANKS 39-A-28-00-00-00A-048A-T FOR TRAINING PURPOSE ONLY 2018-03-06 Page: 4 TRAINING PUBLICATION PMC-39-A0126-PR001-00 FUEL DISTRIBUTING – MAIN COMPONENTS 39-A-28-00-00-00A-048A-T FOR TRAINING PURPOSE ONLY 2018-03-06 Page: 5 TRAINING PUBLICATION PMC-39-A0126-PR001-00 FUEL INDICATING 39-A-28-00-00-00A-048A-T FOR TRAINING PURPOSE ONLY 2018-03-06 Page: 6 TRAINING PUBLICATION PMC-39-A0126-PR001-00 SCHEMATIC DIAGRAM 39-A-28-00-00-00A-048A-T FOR TRAINING PURPOSE ONLY 2018-03-06 Page: 7 TRAINING PUBLICATION PMC-39-A0126-PR001-00 FUEL PUMP FAIL 39-A-28-00-00-00A-048A-T FOR TRAINING PURPOSE ONLY 2018-03-06 Page: 8 TRAINING PUBLICATION PMC-39-A0126-PR001-00 FUEL PUMP OFF – CROSSFEED CLOSED – #2 IN SUCTION MODE 39-A-28-00-00-00A-048A-T FOR TRAINING PURPOSE ONLY 2018-03-06 Page: 9 TRAINING PUBLICATION PMC-39-A0126-PR001-00 CAUTIONS 39-A-28-00-00-00A-048A-T FOR TRAINING PURPOSE ONLY 2018-03-06 Page: 10 TRAINING PUBLICATION PMC-39-A0126-PR001-00 FUEL QUANTITY INDICATION FAILURES 39-A-28-00-00-00A-048A-T FOR TRAINING PURPOSE ONLY 2018-03-06 Page: 11 TRAINING PUBLICATION PMC-39-A0126-PR001-00 FUEL QUANTITY INDICATION FAILURES 39-A-28-00-00-00A-048A-T FOR TRAINING PURPOSE ONLY 2018-03-06 Page: 12 TRAINING PUBLICATION PMC-39-A0126-PR001-00 FUEL QUANTITY INDICATION FAILURES 39-A-28-00-00-00A-048A-T FOR TRAINING PURPOSE ONLY 2018-03-06 Page: 13 TRAINING PUBLICATION PMC-39-A0126-PR001-00 SECONDARY PROBE AND LOW LEVEL SENSOR 39-A-28-00-00-00A-048A-T FOR TRAINING PURPOSE ONLY 2018-03-06 Page: 14 TRAINING PUBLICATION PMC-39-A0126-PR001-00 CAUTIONS AND ADVISORY MESSAGES 39-A-28-00-00-00A-048A-T FOR TRAINING PURPOSE ONLY 2018-03-06 Page: 15 TRAINING PUBLICATION PMC-39-A0126-PR001-00 PAGE INTENTIONALLY LEFT BLANK 39-A-28-00-00-00A-048A-T FOR TRAINING PURPOSE ONLY 2018-03-06 Page: 16 TRAINING PUBLICATION PMC-39-A0126-PR001-00 CHAPTER 29 HYDRAULIC POWER 39-A-29-00-00-00A-048A-T FOR TRAINING PURPOSE ONLY 2018-03-06 Page: 1 TRAINING PUBLICATION PMC-39-A0126-PR001-00 PAGE INTENTIONALLY LEFT BLANK 39-A-29-00-00-00A-048A-T FOR TRAINING PURPOSE ONLY 2018-03-06 Page: 2 TRAINING PUBLICATION PMC-39-A0126-PR001-00 SECTION 00 – GENERAL HYDRAULIC POWER – GENERAL The purpose of the hydraulic power system is to supply the hydraulic power necessary to operate: the flight control circuit (main rotor and tail rotor servo-actuators) the utility circuit (landing gear extension and retraction system) The hydraulic power system is constituted by two independent circuits, the system n°.1 and the system n°.2, that supply hydraulic fluid at a nominal pressure of 207 bar (3000 psi). Both systems supply hydraulic power to the flight controls. System n°.1 is used to operate the landing gear only in emergency situations. System n°.2 is used to operate the landing gear in normal conditions and is provided with a Tail Rotor Shut-Off Valve (TRSOV) to prevent a possible fluid leakage. System n°.1 includes an electrical pump which can supply hydraulic fluid at reduced pressure for pre-flight check on ground only. The HYD control panel shows over temperature and/or over pressure of the hydraulic system and allows operating on the system itself. 39-A-29-00-00-00A-048A-T FOR TRAINING PURPOSE ONLY 2018-03-06 Page: 1 TRAINING PUBLICATION PMC-39-A0126-PR001-00 HYDRAULIC POWER – GENERAL LAYOUT 39-A-29-00-00-00A-048A-T FOR TRAINING PURPOSE ONLY 2018-03-06 Page: 2 TRAINING PUBLICATION PMC-39-A0126-PR001-00 POWER CONTROL MODULE 39-A-29-00-00-00A-048A-T FOR TRAINING PURPOSE ONLY 2018-03-06 Page: 3 TRAINING PUBLICATION PMC-39-A0126-PR001-00 PCM #2 SCHEMATIC 39-A-29-00-00-00A-048A-T FOR TRAINING PURPOSE ONLY 2018-03-06 Page: 4 TRAINING PUBLICATION PMC-39-A0126-PR001-00 HYDRAULIC SYNOPTIC SYMBOLOGY 39-A-29-00-00-00A-048A-T FOR TRAINING PURPOSE ONLY 2018-03-06 Page: 5 TRAINING PUBLICATION PMC-39-A0126-PR001-00 HYDRAULIC SYNOPTIC - NORMAL OPERATION 39-A-29-00-00-00A-048A-T FOR TRAINING PURPOSE ONLY 2018-03-06 Page: 6 TRAINING PUBLICATION PMC-39-A0126-PR001-00 SENSORS AND CAUTIONS 39-A-29-00-00-00A-048A-T FOR TRAINING PURPOSE ONLY 2018-03-06 Page: 7 TRAINING PUBLICATION PMC-39-A0126-PR001-00 PRE-FLIGHT CHECK OPEARTIONS – ELECTRICAL PUMP ON 39-A-29-00-00-00A-048A-T FOR TRAINING PURPOSE ONLY 2018-03-06 Page: 8 TRAINING PUBLICATION PMC-39-A0126-PR001-00 FAILURE OF HYDRAULIC PUMP 2 39-A-29-00-00-00A-048A-T FOR TRAINING PURPOSE ONLY 2018-03-06 Page: 9 TRAINING PUBLICATION PMC-39-A0126-PR001-00 FAILURE OF HYDRAULIC PUMP 1 39-A-29-00-00-00A-048A-T FOR TRAINING PURPOSE ONLY 2018-03-06 Page: 10 TRAINING PUBLICATION PMC-39-A0126-PR001-00 HYDRAULIC 2 – FLUID LEVEL = 50% 39-A-29-00-00-00A-048A-T FOR TRAINING PURPOSE ONLY 2018-03-06 Page: 11 TRAINING PUBLICATION PMC-39-A0126-PR001-00 HYDRAULIC 2 – FLUID LEVEL = 28% 39-A-29-00-00-00A-048A-T FOR TRAINING PURPOSE ONLY 2018-03-06 Page: 12 TRAINING PUBLICATION PMC-39-A0126-PR001-00 HYDRAULIC 2 – FLUID LEVEL = 22% (MIN.) 39-A-29-00-00-00A-048A-T FOR TRAINING PURPOSE ONLY 2018-03-06 Page: 13 TRAINING PUBLICATION PMC-39-A0126-PR001-00 HYDRAULIC 1 – FLUID LEVEL = 50% 39-A-29-00-00-00A-048A-T FOR TRAINING PURPOSE ONLY 2018-03-06 Page: 14 TRAINING PUBLICATION PMC-39-A0126-PR001-00 HYDRAULIC 1 – FLUID LEVEL = 28% 39-A-29-00-00-00A-048A-T FOR TRAINING PURPOSE ONLY 2018-03-06 Page: 15 TRAINING PUBLICATION PMC-39-A0126-PR001-00 HYDRAULIC 1 – FLUID LEVEL = 22% (MIN.) 39-A-29-00-00-00A-048A-T FOR TRAINING PURPOSE ONLY 2018-03-06 Page: 16 TRAINING PUBLICATION PMC-39-A0126-PR001-00 HIGH HYDRAULIC TEMP 39-A-29-00-00-00A-048A-T FOR TRAINING PURPOSE ONLY 2018-03-06 Page: 17 TRAINING PUBLICATION PMC-39-A0126-PR001-00 HIGH 1 HYDRAULIC TEMP WITH 2 SERVO 39-A-29-00-00-00A-048A-T FOR TRAINING PURPOSE ONLY 2018-03-06 Page: 18 TRAINING PUBLICATION PMC-39-A0126-PR001-00 SERVO ACTUATOR 39-A-29-00-00-00A-048A-T FOR TRAINING PURPOSE ONLY 2018-03-06 Page: 19 TRAINING PUBLICATION PMC-39-A0126-PR001-00 SERVO ACTUATOR OPERATION 39-A-29-00-00-00A-048A-T FOR TRAINING PURPOSE ONLY 2018-03-06 Page: 20 TRAINING PUBLICATION PMC-39-A0126-PR001-00 CONTROL SPOON VALVE JAM 39-A-29-00-00-00A-048A-T FOR TRAINING PURPOSE ONLY 2018-03-06 Page: 21 TRAINING PUBLICATION PMC-39-A0126-PR001-00 PAGE INTENTIONALLY LEFT BLANK 39-A-29-00-00-00A-048A-T FOR TRAINING PURPOSE ONLY 2018-03-06 Page: 22 TRAINING PUBLICATION PMC-39-A0126-PR001-00 CHAPTER 32 LANDING GEAR 39-A-32-00-00-00A-048A-T FOR TRAINING PURPOSE ONLY 2018-03-06 Page: 1 TRAINING PUBLICATION PMC-39-A0126-PR001-00 PAGE INTENTIONALLY LEFT BLANK 39-A-32-00-00-00A-048A-T FOR TRAINING PURPOSE ONLY 2018-03-06 Page: 2 TRAINING PUBLICATION PMC-39-A0126-PR001-00 SECTION 00 – GENERAL LANDING GEAR – GENERAL The landing gear is a “fore and aft” retractable tricycle type. It: supports the helicopter on the ground giving the correct ground clearance; gives shock absorption and rebound control during landing, taxiing and maneuvers on the ground; decelerates and stops the helicopter after landing and during taxiing; allows to park the helicopter. The landing gear includes: the Main Landing Gear (MLG) located on the left and on the right side of the fuselage under the sponsons; the Nose Landing Gear (NLG) located under the cockpit; the extension / retraction system of the MLG and NLG; the braking system; the automatic centering and lock system (or steering system) located on the NLG. The landing gear is operated by the pilot to perform: normal retraction and extension by means of the Landing Gear Control Lever (LGCL); emergency extension by means of the EMER DOWN pushbutton. 39-A-32-00-00-00A-048A-T FOR TRAINING PURPOSE ONLY 2018-03-06 Page: 1 TRAINING PUBLICATION PMC-39-A0126-PR001-00 MLG AND NLG GENERAL ARRANGEMENT 39-A-32-00-00-00A-048A-T FOR TRAINING PURPOSE ONLY 2018-03-06 Page: 2 TRAINING PUBLICATION PMC-39-A0126-PR001-00 MAIN LANDING GEAR 39-A-32-00-00-00A-048A-T FOR TRAINING PURPOSE ONLY 2018-03-06 Page: 3 TRAINING PUBLICATION PMC-39-A0126-PR001-00 LANDING GEAR RETRACTED 39-A-32-00-00-00A-048A-T FOR TRAINING PURPOSE ONLY 2018-03-06 Page: 4 TRAINING PUBLICATION PMC-39-A0126-PR001-00 LANDING GEAR DOWN AND LOCKED 39-A-32-00-00-00A-048A-T FOR TRAINING PURPOSE ONLY 2018-03-06 Page: 5 TRAINING PUBLICATION PMC-39-A0126-PR001-00 LOSS OF ELECTRICAL POWER WITH LG UP 39-A-32-00-00-00A-048A-T FOR TRAINING PURPOSE ONLY 2018-03-06 Page: 6 TRAINING PUBLICATION PMC-39-A0126-PR001-00 EMERGENCY EXTENSION 39-A-32-00-00-00A-048A-T FOR TRAINING PURPOSE ONLY 2018-03-06 Page: 7 TRAINING PUBLICATION PMC-39-A0126-PR001-00 NLG AUTO CENTERLOCK 39-A-32-00-00-00A-048A-T FOR TRAINING PURPOSE ONLY 2018-03-06 Page: 8 TRAINING PUBLICATION PMC-39-A0126-PR001-00 BRAKE SYSTEM SCHEMATIC 39-A-32-00-00-00A-048A-T FOR TRAINING PURPOSE ONLY 2018-03-06 Page: 9 TRAINING PUBLICATION PMC-39-A0126-PR001-00 CAS CAUTION MESSAGES 39-A-32-00-00-00A-048A-T FOR TRAINING PURPOSE ONLY 2018-03-06 Page: 10 TRAINING PUBLICATION PMC-39-A0126-PR001-00 CAS ADVISORY MESSAGES 39-A-32-00-00-00A-048A-T FOR TRAINING PURPOSE ONLY 2018-03-06 Page: 11 TRAINING PUBLICATION PMC-39-A0126-PR001-00 PRIMUS EPIC ® SOFTWARE PHASE 7 ONLY – SPECIFIC FUNCTIONS “AURAL WARNING MESSAGES” 39-A-32-00-00-00A-048A-T FOR TRAINING PURPOSE ONLY 2018-03-06 Page: 12 TRAINING PUBLICATION PMC-39-A0126-PR001-00 CHAPTER 34 NAVIGATION 39-A-34-00-00-00A-048A-T FOR TRAINING PURPOSE ONLY 2018-03-06 Page: 1 TRAINING PUBLICATION PMC-39-A0126-PR001-00 PAGE INTENTIONALLY LEFT BLANK 39-A-34-00-00-00A-048A-T FOR TRAINING PURPOSE ONLY 2018-03-06 Page: 2 TRAINING PUBLICATION PMC-39-A0126-PR001-00 SECTION 00 – GENERAL AIR DATA SYSTEM (ADS) – GENERAL AIR DATA SYSTEM (ADS) – MAIN COMPONENTS The two Air Data Systems (ADS 1 and ADS 2) provide: two Pitot-Static Probes Barometric Altitude (BARO) two Air Data Modules (ADM 1 and ADM 2) Indicated Airspeed (IAS) two OAT Probes Vertical Speed (VS) two Alternate Static Sources Outside Air Temperature (OAT) Each Pitot-Static Probe includes: Air data are also used by: one total pressure port AFCS two static pressure ports AHRS an electrical heater to prevent ice formation FMS A drain hole for draining any condensed water inside the probe. Weather Radar (if installed) TCAS (if installed) Air Data Module (ADM) Each ADM is a solid state transducer that converts dynamic and static pressure values into digital signals used by the MAU to generate air data such as calibrated airspeed, altitude, vertical speed and OAT. The Air Data Modules are installed in the nose compartment on the cockpit bulkhead. Outside Air Temperature (OAT) Probes The two outside air temperature probes sense the temperature of the external air and are installed in the bottom forward fuselage. Alternate Static Sources The two alternate static sources are static ports located in the overhead panel: one on the LH sidewall (co-pilot) which is part of ADS 1 and the other on the RH sidewall (pilot) which is part of ADS 2. Each port is integral with a lever-type selector valve. The control is protected by a red guard to prevent inadvertent actuation. ATTITUDE AND HEADING REFERENCE SYSTEM (AHRS) The attitude and heading reference system (AHRS) installed in the AW139 interfaces to PRIMUS EPIC using ARINC 429. It is an attitude and direction sensing system that generates attitude and heading data used by the displays, the automatic flight control system (AFCS), the WX radar, and other systems of the helicopter. The helicopter is equipped with two AHRS. Each one is an all attitude, inertial sensor system using fiber optic gyros (FOGs) and micro-mechanical accelerometers to compute the attitude, heading and flight dynamic information of the helicopter. The FOGs and accelerometers are mechanically fixed or strapped down to the principle helicopter axes where it measures rates of change in pitch, roll, and yaw. A digital computer combines the rate of change data from the sensors to find and continuously update the pitch, roll, and heading. Attitude and Heading Reference Unit (AHRU) -- The AHRU is the main electronic assembly of the AHRS. It contains the inertial sensor assembly, which includes FOGs and micro-mechanical accelerometers. 39-A-34-00-00-00A-048A-T FOR TRAINING PURPOSE ONLY 2018-03-06 Page: 1 TRAINING PUBLICATION PMC-39-A0126-PR001-00 ADS – PURPOSE AND MAIN COMPONENTS 39-A-34-00-00-00A-048A-T FOR TRAINING PURPOSE ONLY 2018-03-06 Page: 2 TRAINING PUBLICATION PMC-39-A0126-PR001-00 AIR DATA SYSTEM 39-A-34-00-00-00A-048A-T FOR TRAINING PURPOSE ONLY 2018-03-06 Page: 3 TRAINING PUBLICATION PMC-39-A0126-PR001-00 PITOT AND STATIC PRESSURE LINES - SCHEMATIC 39-A-34-00-00-00A-048A-T FOR TRAINING PURPOSE ONLY 2018-03-06 Page: 4 TRAINING PUBLICATION PMC-39-A0126-PR001-00 PITOT - STATIC SYSTEM – GENERAL LAYOUT 39-A-34-00-00-00A-048A-T FOR TRAINING PURPOSE ONLY 2018-03-06 Page: 5 TRAINING PUBLICATION PMC-39-A0126-PR001-00 AIRSPEED AND BARO ALTITUDE ANNUNCIATIONS 39-A-34-00-00-00A-048A-T FOR TRAINING PURPOSE ONLY 2018-03-06 Page: 6 TRAINING PUBLICATION PMC-39-A0126-PR001-00 AIR DATA SYSTEM FAILURE (ADS 2 EXAMPLE) 39-A-34-00-00-00A-048A-T FOR TRAINING PURPOSE ONLY 2018-03-06 Page: 7 TRAINING PUBLICATION PMC-39-A0126-PR001-00 AHRS – PURPOSE AND MAIN COMPONENTS 39-A-34-00-00-00A-048A-T FOR TRAINING PURPOSE ONLY 2018-03-06 Page: 8 TRAINING PUBLICATION PMC-39-A0126-PR001-00 AHRS – MISCOMPARE ANNUNCIATORS 39-A-34-00-00-00A-048A-T FOR TRAINING PURPOSE ONLY 2018-03-06 Page: 9 TRAINING PUBLICATION PMC-39-A0126-PR001-00 NAVIGATION SYSTEM – AHRS: CONTROL PANEL 39-A-34-00-00-00A-048A-T FOR TRAINING PURPOSE ONLY 2018-03-06 Page: 10 TRAINING PUBLICATION PMC-39-A0126-PR001-00 AHRS FAILURE (AHRS 2 EXAMPLE) 39-A-34-00-00-00A-048A-T FOR TRAINING PURPOSE ONLY 2018-03-06 Page: 11 TRAINING PUBLICATION PMC-39-A0126-PR001-00 NAVIGATION SYSTEM – HEADING ANNUNCIATORS 39-A-34-00-00-00A-048A-T FOR TRAINING PURPOSE ONLY 2018-03-06 Page: 12 TRAINING PUBLICATION PMC-39-A0126-PR001-00 ESIS 39-A-34-00-00-00A-048A-T FOR TRAINING PURPOSE ONLY 2018-03-06 Page: 13 TRAINING PUBLICATION PMC-39-A0126-PR001-00 STANDBY INDICATOR 39-A-34-00-00-00A-048A-T FOR TRAINING PURPOSE ONLY 2018-03-06 Page: 14 TRAINING PUBLICATION PMC-39-A0126-PR001-00 STANDBY INDICATOR 39-A-34-00-00-00A-048A-T FOR TRAINING PURPOSE ONLY 2018-03-06 Page: 15 TRAINING PUBLICATION PMC-39-A0126-PR001-00 STANDBY INDICATOR - SCHEMATIC 39-A-34-00-00-00A-048A-T FOR TRAINING PURPOSE ONLY 2018-03-06 Page: 16 TRAINING PUBLICATION PMC-39-A0126-PR001-00 FLIGHT MANAGEMENT SYSTEM (FMS) – GENERAL The function of the FMS is to give flight planning capability, navigation information and flight performance data. The FMS manages flight details from takeoff to touchdown. These details include Standard Instrument Departures (SID), Standard Terminal Arrival Routes (STAR), approaches and missed approaches. The FMS combines inputs of other aircraft systems (GPS, DME, VOR, AHRS, ADS) to output navigation, lateral and vertical commands and aircraft performance predictions. FMS uses GPS as long range sensor and DME/DME and VOR/DME as short range sensors. Primary functions of FMS are position computation and flight planning. The FMS Database is essential in order to easily retrieve navaids, airways, procedures, airports, other navigation data and store and retrieve waypoints and flight plans. Secondary functions of FMS are performance, including fuel management, time estimates for the flight, vertical navigation estimates, stored flight plans and other functions. Provided the FMS is receiving usable signals, it has been demonstrated capable of and has been shown to meet the accuracy specifications of: VFR/IFR en route domestic, terminal, and instrument approach (GPS, VOR, VOR-DME, TACAN, NDB, NDB-DME, RNAV) operation. Satellite navigation data is based upon use of only the NAVSTAR Global Positioning System (GPS). Refer to the Honeywell PRIMUS EPIC® PILOT’S GUIDE for a detailed description of the FMS. FMS DISPLAYS AND CONTROL – GENERAL Flight Management System displays and data are presented on the PFD (HSI), on the MFD (MAP and PLAN formats) and on the Multipurpose Control Display Unit (MCDU). The MCDU is the controller for the FMS. DC (Display Controller) is also used in conjunction with the FMS for the following functions: To select FMS as the Primary Navaid by using the LNAV pushbutton To display bearing to the FMS waypoint via the HSI bearing pointers by using the BRG ○ pushbutton for FMS1 and the BRG ◊ pushbutton for FMS2 To display the active flightplan on the ARC HSI by using the MAP pushbutton 39-A-34-00-00-00A-048A-T FOR TRAINING PURPOSE ONLY 2018-03-06 Page: 17 TRAINING PUBLICATION PMC-39-A0126-PR001-00 FMS CONFIGURATION 39-A-34-00-00-00A-048A-T FOR TRAINING PURPOSE ONLY 2018-03-06 Page: 18 TRAINING PUBLICATION PMC-39-A0126-PR001-00 FMS – RNP FUNDAMENTALS 39-A-34-00-00-00A-048A-T FOR TRAINING PURPOSE ONLY 2018-03-06 Page: 19 TRAINING PUBLICATION PMC-39-A0126-PR001-00 FMS – RNP FUNDAMENTALS 39-A-34-00-00-00A-048A-T FOR TRAINING PURPOSE ONLY 2018-03-06 Page: 20 TRAINING PUBLICATION PMC-39-A0126-PR001-00 FMS – POSITION COMPUTATION 39-A-34-00-00-00A-048A-T FOR TRAINING PURPOSE ONLY 2018-03-06 Page: 21 TRAINING PUBLICATION PMC-39-A0126-PR001-00 FMS – POSITION COMPUTATION 39-A-34-00-00-00A-048A-T FOR TRAINING PURPOSE ONLY 2018-03-06 Page: 22 TRAINING PUBLICATION PMC-39-A0126-PR001-00 GPS PURPOSE AND MAIN COMPONENTS 39-A-34-00-00-00A-048A-T FOR TRAINING PURPOSE ONLY 2018-03-06 Page: 23 TRAINING PUBLICATION PMC-39-A0126-PR001-00 ENHANCED GROUND PROXIMITY WARNING SYSTEM (EGPWS) – GENERAL The Honeywell MK XXII Helicopter EGPWS provides the pilot with following outputs: Terrain/Obstacle Awareness Display (TAD) Voice Alerts/Warnings/Callouts Visual Cautions/Warnings. This information is provided through two independent functions: 1. Ground Proximity Warning System (GPWS) 2. Terrain Awareness Display with “Look-Ahead” Alerting and Warning. The EGPWS (GPWS + TA) uses information from the GPS and other sources on the aircraft to calculate horizontal position and vertical altitude. In particular the system merges barometric pressure, Radio Altitude and a GPS derived altitude into a so-called “Geometric Altitude” to provide more accurate altitude information less susceptible to errors induced by pilot (altimeter settings), cold temperature or malfunctions in altimeters systems. GROUND PROXIMITY WARNING SYSTEM The ground proximity system is based primarily on the vertical separation of the helicopter with the terrain. It uses radio and barometric altitude to determine altitude rates/terrain closure rates to alert for insufficient terrain clearance. There are 6 modes: - Mode 1: Excessive Descent Rate - Mode 2: Excessive Terrain Closure Rate - Mode 3: Descent after take-off - Mode 4: Unsafe terrain clearance - Mode 5: Descent below Glideslope - Mode 6: Advisory Alerts for the following functions: Excessive bank angle Tail too low Altitude call-outs in autorotation TERRAIN AWARENESS FUNCTIONS The Terrain Awareness Display depicts the terrain in front of the aircraft as variable density dot patterns in green, yellow and red. When terrain awareness alerts are generated, the threatening terrain is painted solid yellow or red. The display includes numerical values of minimum and maximum elevation of the displayed terrain. 39-A-34-00-00-00A-048A-T FOR TRAINING PURPOSE ONLY 2018-03-06 Page: 24 TRAINING PUBLICATION PMC-39-A0126-PR001-00 39-A-34-00-00-00A-048A-T FOR TRAINING PURPOSE ONLY 2018-03-06 Page: 25 TRAINING PUBLICATION PMC-39-A0126-PR001-00 EGPWS – GPWS + Terraing Awareness (TA) GPWS FUNCTIONS The GPWS function is based primarily on the vertical separation of the aircraft with terrain. It uses altitude and altitude rates/terrain closure rates to alert the Crew of insufficient terrain clearance. The system operates by categorizing the potential areas of concern into six operating modes, not selectable by the operator: Mode 1: Excessive Descent Rate Mode 2: Excessive Terrain Closure Rate Mode 3: Descent after Take-Off Mode 4: Unsafe terrain clearance Mode 5: Descent Below Glideslope Mode 6: Advisory alerts for: - Excessive Bank Angle - Tail Too Low - Altitude call outs in Autorotation. 39-A-34-00-00-00A-048A-T FOR TRAINING PURPOSE ONLY 2018-03-06 Page: 26 TRAINING PUBLICATION PMC-39-A0126-PR001-00 TERRAIN AWARENESS (TA) FUNCTIONS The EGPWS computer uses following aircraft inputs: Radio Altitude Roll and Pitch Attitude Baro Altitude and Vertical Speed Ground Speed and track Localizer and Glide Slope Engine torque Airspeed and OAT GPS signal quality Gear position and Weight on Wheels, Magnetic Heading Display range …to determine the aircraft?
