Tecnam P2002 JF Maintenance Manual Download | Manualshive

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SUPPLEMENT SG-1

CHAPTER 34 - NAVIGATION

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SYSTEM STATUS PAGE (CONFIGURATION MODE)

The System Status Page displays system LRU information. Enter system configuration
mode by applying power to GDU 620 while holding the ENT key. The System Status
Page is displayed on the left display while the system is operating in configuration
mode.

The devices online status indicators are as follows:

•

Green: the LRU status is OK

•

Red: the LRU status is FAIL

•

Black: the LRU status is TIMEOUT

Replace any LRU which indicates “FAIL” status.

System Status Configuration Page

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Summary of Contents for P2002 JF

Page 1: ...eronautiche TECNAM srl Via Maiorise CAPUA CE Italy Tel 39 0 823 62 01 34 WEB www tecnam com The technical content of this document is approved under the authority of DOA Ref EASA 21J 335 THIS PUBLICATION IS PROPERTY OF COSTRUZIONI AERONAUTICHE TECNAM s r l IT IS NOT TO BE REPRODUCED IN WHOLE OR IN PART WITHOUT WRITTEN PERMISSION ...

Page 2: ...2nd Edition Rev 0 INTENTIONALLY LEFT BLANK ...

Page 3: ...the change When technical changes cause expansion or deletion of text which results in un changed text appearing on a different page a revision bar will be placed in the right hand margin adjacent to the page number of all affected pages providing no other revision bar appears on the page These pages will be updated to the current regular revision date When a new issue of the Maintenance Manual is...

Page 4: ...Page 2 2nd Edition Rev 0 RECORD OF REVISIONS Record of revisions Rev Revised chapter page Description of Revision Reference ...

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Page 7: ...2nd Edition Rev 0 Chapter 01 Introduction ...

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Page 9: ...1 LOEP 1 2nd Edition Rev 0 2 2nd Edition Rev 0 01 TOC 1 2nd Edition Rev 0 2 2nd Edition Rev 0 01 10 1 2nd Edition Rev 0 01 20 1 2nd Edition Rev 0 2 2nd Edition Rev 0 3 2nd Edition Rev 0 01 30 1 2nd Edition Rev 0 2 2nd Edition Rev 0 01 40 1 2nd Edition Rev 0 2 2nd Edition Rev 0 3 2nd Edition Rev 0 4 2nd Edition Rev 0 ...

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Page 11: ...Page 1 2nd Edition Rev 0 01 TOC CHAPTER 01 TABLE OF CONTENTS 01 10 FOREWORD 1 01 20 MANUAL BREAKDOWN AND ORGANIZATION 1 01 30 ABBREVIATIONS 1 01 40 OCCURRENCE REPORTING INSTRUCTIONS 1 ...

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Page 13: ... ATA of America Additional information can be found in these documents Components Maintenance and Operating Manuals for vendor equipment Propeller Hoffmann Propellers AMM Handbook N E 0110 74 Additionally Rotax Aircraft Engines publishes the following manuals for engine maintenance Maintenance Manual Line and Heavy Maintenance for ROTAX Engine Type 912 series Operators Manual for ROTAX Engine Type...

Page 14: ...07 Jacking 08 Leveling and Weighing 09 Towing and Taxiing 10 Parking Mooring Storage and Return to Service 11 Placards and Markings 12 Servicing 20 Standard Practices Airframe GROUP B 21 Heating and ventilation 23 Communications 24 Electrical system 25 Equipment and furnishings 26 Fire protection 27 Flights controls 28 Fuel system 29 Hydraulic system 30 Ice protection 31 Indicating system 32 Landi...

Page 15: ...ription and Operation Page Block 101 pages 101 thru 199 Troubleshooting Page Block 201 pages 201 thru 299 Maintenance Practices A List of Effective Pages LOEP is provided at the beginning of each chapter It shows the latest date of issue revision of each page Each chapter is provided with a page entitled Table of Contents TOC which lists the contents of the chapter allowing the user to locate need...

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Page 17: ... Breaker C F Crossfeed CAB Cabin CMM Component Maintenance Manual CMND Command COM Communication CPLT Copilot CTRL Control CW Control Wheel DN Down EMER Emergency ENG Engine FS Fuselage Station FWD Forward GEN Generator GND Ground GS Glide Slope HDG Heading HI High HTR Heater HYD Hydraulic IGN Ignition INB Inboard INSP Inspection LH Left hand LDG Landing LG Landing gear LOEP List of Effective Page...

Page 18: ...r MLG Main Landing Gear NAV Navigation NLG Nose Landing Gear OAT Outside Air Temperature OPR Operator OPT Option OUTB Outboard OVSP Overspeed OVV Overvoltage PAXS Passengers PLT Pilot PNL Panel POS Position TOC Table of Contents WOF Whichever Occurs First ...

Page 19: ...ue or significant service difficulty upon discovery by means of the official Occurrence Report Form herein reported You can download the Occurrence Report in digital format from the following link http www tecnam com Documents Support Occurrence_Report pdf Below are reported the general information to get in contact with Tecnam Office of Airworthiness Tecnam Office of Airworthiness Postal address ...

Page 20: ...Page 2 2nd Edition Rev 0 01 40 OCCURRENCE REPORTING INSTRUCTIONS ...

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Page 23: ...2nd Edition Rev 0 Chapter 02 Conversion charts ...

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Page 25: ...tion Page Edition Revision 02 LOEP 1 2nd Edition Rev 0 2 2nd Edition Rev 0 02 TOC 1 2nd Edition Rev 0 2 2nd Edition Rev 0 02 10 1 2nd Edition Rev 0 2 2nd Edition Rev 0 02 20 1 2nd Edition Rev 0 2 2nd Edition Rev 0 3 2nd Edition Rev 0 4 2nd Edition Rev 0 ...

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Page 27: ...n Rev 0 02 TOC CHAPTER 02 TABLE OF CONTENTS 02 10 CONVERSION FACTORS 1 02 20 CONVERSION TABLES 1 Liters US gallon conversion table 1 Inch Pound Newton Meter conversion table 2 Foot Pound Newton Meter conversion table 3 ...

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Page 29: ...Y YIELDS FORCE Kilograms kg 2 205 Pounds lbs Pounds lbs 0 4536 Kilograms kg MULTIPLYING BY YIELDS SPEED Meters per second m s 196 86 Feet per minute ft min Feet per minute ft min 0 00508 Meters per second m s Knots kts 1 853 Kilometers hour km h Kilometers hour km h 0 5396 Knots kts MULTIPLYING BY YIELDS PRESSURE Atmosphere atm 14 7 Pounds sq in psi Pounds sq in psi 0 068 Atmosphere atm ...

Page 30: ...rs cm Inches in 25 40 Millimeters mm Millimeters mm 0 0393 Inches in MULTIPLYING BY YIELDS VOLUME Liters l 0 2642 U S Gallons US Gal U S Gallons US Gal 3 785 Liters l MULTIPLYING BY YIELDS AREA Square meters m2 10 76 Square feet sq ft Square feet sq ft 0 0929 Square meters m2 MULTIPLYING BY YIELDS TORQUE Foot pound ft lb 1 355 Newton meter Nm Newton meter Nm 0 738 Foot pound ft lb Inch pound in lb...

Page 31: ...0 3 11 4 20 5 3 4 15 1 25 6 6 6 22 7 30 7 9 8 30 3 35 9 2 10 37 9 40 10 6 12 45 4 45 11 9 14 53 0 50 13 2 16 60 6 60 15 9 18 68 1 70 18 5 20 75 7 80 21 1 22 83 3 90 23 8 24 90 9 100 26 4 26 98 4 110 29 1 28 106 0 120 31 7 30 113 6 130 34 3 32 121 1 140 37 7 34 128 7 150 39 6 36 136 3 160 42 3 38 143 8 170 44 9 40 151 4 180 47 6 45 170 3 190 50 2 50 189 3 200 52 8 55 208 2 ...

Page 32: ...VERSION TABLES INCH POUND NEWTON METER CONVERSION TABLE Find the Nm value in correspondence of the horizontal axis then move vertically to reach the diagonal line and move horizontally across to the vertical axis giving the in lb value ...

Page 33: ...VERSION TABLES FOOT POUND NEWTON METER CONVERSION TABLE Find the Nm value in correspondence of the horizontal axis then move vertically to reach the diagonal line and move horizontally across to the vertical axis giving the ft lb value ...

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Page 35: ...2nd Edition Rev 0 Chapter 03 Airplane general description ...

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Page 37: ... 03 00 1 2nd Edition Rev 0 2 2nd Edition Rev 0 3 2nd Edition Rev 0 4 2nd Edition Rev 0 5 2nd Edition Rev 0 6 2nd Edition Rev 0 7 2nd Edition Rev 0 8 2nd Edition Rev 0 9 2nd Edition Rev 0 10 2nd Edition Rev 0 11 2nd Edition Rev 0 12 2nd Edition Rev 0 13 2nd Edition Rev 0 14 2nd Edition Rev 0 15 2nd Edition Rev 0 16 2nd Edition Rev 0 17 2nd Edition Rev 0 18 2nd Edition Rev 0 ...

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Page 39: ...0 AIRPLANE GENERAL DESCRIPTION 1 Wing 2 Fuselage 3 Empennages 4 Flight Controls 6 Engine and Propeller 8 Landing Gear 9 Brake System 10 Fuel System 12 Electrical System 13 Pitot and Static System 14 Ventilation Cabin Heat and Windshield Defrost 15 General Features 16 ...

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Page 41: ...03 00 AIRPLANE GENERAL DESCRIPTION 03 00 AIRPLANE GENERAL DESCRIPTION The P2002 JF is a twin seat single engine low wing metal structure monoplane with fixed tricycle landing gear and steerable nose gear Figure 1 General Views ...

Page 42: ...al spar to which front and rear ribs are jointed Wrapped around aluminum stressed skin panels cover all the structures FUEL TANK FRONT SPAR LEADING EDGE FLAP AILERON REAR SPAR Figure 2 Wing structure The ailerons control is actuated manually through the control stick The ailerons are balanced by balance masses The ailerons are hinged at two places on the rear spar of each wing Flaps provide the re...

Page 43: ...ed around by stressed stretched panels Nose cone is made of composite material Tail fairing is made of composite material Cabin and baggage compartment floor is a warping of beams and keelsons supporting the seats guides baggage and other components Seats access occur by a sliding canopy In tail cone two spar frames support the horizontal and vertical empennages attachments Figure 3 Fuselage ...

Page 44: ...a twin spar with aluminum alloy stressed skin Rudder providing directional control of the airplane is made up of aluminium alloy The rudder is connected to the vertical tail at two hinges REAR SPAR TIP RUDDER TIP FRONT SPAR FWD ATCH REAR ATCHs RIBs RUDDER RIBs RUDDER SPAR Figure 4 Vertical empennage structure FWD ATACHMENT REAR ATACHMENT ...

Page 45: ... DESCRIPTION The horizontal empennage is an all moving type stabilator its structure consists of a twin spar to which six ribs are joined and it is covered by stressed aluminum alloy skin The trim tab completes the assy Figure 5 Stabilator structure ...

Page 46: ... left on the instrument panel A trim disconnect toggle switch is provided Aileron control is of mixed type with push rods and cables a cable control circuit is confined within the cabin and it is connected to a pair of push pull rod systems positioned in each main wing which control ailerons differentially Stick controls the ailerons its motion is transferred to the ailerons through a cable loop u...

Page 47: ...dition Rev 0 03 00 AIRPLANE GENERAL DESCRIPTION Rudder is operated through a cable system The rudder has a trim tab adjustable on the ground allows aircraft directional trimming Figure 7 Flight control system Flaps ...

Page 48: ...ers horizontally opposed with 1352 c c of overall displacement liquid cooled cylinder heads ram air cooled cylinders carburetor integrated reduction gear box with torsional shock absorber and overload clutch Propeller is made by Hoffmann Propeller It is fitted with two wood composite blades and aluminum hub Figure 8 Engine mount and propeller ...

Page 49: ...CRIPTION Landing Gear Main landing gear is provided by leaf springs fixed by plates to the central main bean of aircraft fuselage Nose landing gear has a non retractile leg with a rubber disc dumper Figure 9 Nose landing gear Figure 10 Main landing gear ...

Page 50: ...it shut off valve 2 is positioned between seats With circuit shut off pulling emergency brake lever activates parking brake function Braking is simultaneous on both wheels via a T shaped joint 6 Control lever 1 activates master cylinder 3 that features built in brake fluid reservoir 4 The brake system is equipped with a non return valve 5 which insures that braking action is always effective even ...

Page 51: ... brake circuit as shown in the Figure 11 Optional Control lever 1 activates pump 3 that features built in brake fluid reservoir 4 check valve 5 secure brake function when activated unintentionally parking brake Figure 11 Hydraulic differential brake circuit Optional C C C C FWD ...

Page 52: ...ks fuel from the selected tank Fuel valve is located on cabin central tunnel it allows to switch LH and RH tank An electric fuel pump supplies the engine in case of engine driven pump failure On instrument panel there are other instruments The fuel pressure indicator and fuel quantity indicators FUEL TANK ENGINE COMPARTEMENT FUEL SELECTOR ELECTRICAL PUMP GEAR PUMP ELECRIC FUEL PRESSURE SENDER Figu...

Page 53: ...iven generator The battery of lead acid type featuring 12 V 18 Ah in 1h acts as a pad and supplies the energy for engine starting The 20 Amp generators are set up on the left side of engines The nominal output voltage is 14 2 14 8 V dc a regulator is installed separately An external power socket allows to start engine using electric power taken from an external source Figure 13 Electrical system t...

Page 54: ...Page 14 2nd Edition Rev 0 03 00 AIRPLANE GENERAL DESCRIPTION Pitot and Static System The aircraft has a single pitot tube located on the bottom side of LH wing Figure 14 Pitot system scheme ...

Page 55: ... by engine exhaust gases and then it is routed to the heating system hoses The cabin heat defrost control knobs are positioned on the lower side of the LH instrument panel when knobs are fully pulled cabin receives maximum hot air There is a switch on the instrument panel that allows to change heating defrost If heating mode is activated the hot air flows out from a pipe located in the lower part ...

Page 56: ...ding 50 kg m2 Aspect ratio 6 4 Taper ratio 0 6 Dihedral 5 Fuselage Length overall 6 61 m Width overall 1 11 m Height overall 2 43 m Empennage Stabilator span 2 90 m Vertical tail span 1 10 m Landing Gear Wheel track 1 85 m Wheel base 1 62 m Main wheel tyres Air Trac 5 00 5 Main Gear Wheel Brakes Cleveland 199 102 Nose gear tyre Air Trac 5 00 Control surface travel Ailerons Up 20 2 down 15 2 Stabil...

Page 57: ...d pitch wood Fuel Fuel grade EN 228 Super Super Plus min RON 95 AKI 91 AVGAS 100LL ASTM D910 Fuel tanks 2 wing tanks integrated within the wing s leading edge with fuel strainer located in engine cowling Capacity of each wing tank 50 Liters Total capacity 100 Liters Usable fuel 99 Liters 49 5 liters each tank Oil System Oil system type Forced with external oil reservoir Oil Lubricant specification...

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Page 59: ...2nd Edition Rev 0 Chapter 04 Airworthiness limitations The Airworthiness Limitations Section is EASA approved and variations must also be approved ...

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Page 61: ...d Edition Rev 0 04 LOEP CHAPTER 04 LOEP Section Page Edition Revision 04 LOEP 1 2nd Edition Rev 0 2 2nd Edition Rev 0 04 TOC 1 2nd Edition Rev 0 04 00 1 2nd Edition Rev 0 2 2nd Edition Rev 0 3 2nd Edition Rev 0 ...

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Page 63: ...Page 1 2nd Edition Rev 0 04 TOC CHAPTER 04 TABLE OF CONTENTS 04 00 AIRWORTHINESS LIMITATIONS 1 Introduction 1 Airworthiness Limitation Table 2 ...

Page 64: ...ement time life limited structural items and the inspection intervals and procedures necessary to maintain the airworthiness conditions required for Type Certification as a result of the certification process The items requiring inspection retiring are presented by description of inspection or item to be overhauled retired what action is required and the frequency of such action The flight time re...

Page 65: ...se flexible line 22 9 120 1 22 9 122 1 22 9 124 000 22 9 130 000 22 9 132 000 Life limit 2 yrs If applied MOD2002 36 Fuel hose change 22 9 155 1 2pz 22 9 124 000 22 9 130 000 22 9 132 000 79 Oil system flexible hose 22 11 910 001 22 11 910 002 22 11 910 003 22 11 910 4 Life limit 5 yrs If applied MOD2002 33 Thermostaic oil valve 22 11 210 004 22 11 210 010 22 11 210 008 22 11 210 009 22 11 910 002...

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Page 67: ...2nd Edition Rev 0 Chapter 05 Time Limits and Maintenance schedule ...

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Page 69: ...ition Rev 0 05 10 1 2nd Edition Rev 0 2 2nd Edition Rev 0 05 20 1 2nd Edition Rev 0 2 2nd Edition Rev 0 3 2nd Edition Rev 0 4 2nd Edition Rev 0 5 2nd Edition Rev 0 6 2nd Edition Rev 0 7 2nd Edition Rev 0 8 2nd Edition Rev 0 9 2nd Edition Rev 0 10 2nd Edition Rev 0 11 2nd Edition Rev 0 12 2nd Edition Rev 0 13 2nd Edition Rev 0 14 2nd Edition Rev 0 15 2nd Edition Rev 0 16 2nd Edition Rev 0 17 2nd Ed...

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Page 71: ...2nd Edition Rev 0 05 00 LOEP Page 3 Section Page Edition Revision 05 60 4 2nd Edition Rev 0 5 2nd Edition Rev 0 6 2nd Edition Rev 0 7 2nd Edition Rev 0 8 2nd Edition Rev 0 9 2nd Edition Rev 0 ...

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Page 73: ...CORROSION PREVENTION 1 05 50 SPECIAL SCHEDULED MAINTENANCE 1 1 Operation in Highly Dusty or Industrial Pollution Environment 1 2 Operation in High Salt or High Humidity Environments 2 3 Operation in Extreme Cold Environment 5 4 Operation on Soft or Unusual Terrain 5 05 60 UNSCHEDULED MAINTENANCE 1 1 Lightning strike 1 2 Engine over speed over temp loss of oil or sudden stoppage 2 3 Severe turbulen...

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Page 75: ...t specified intervals and Special Scheduled Unscheduled Inspections The flight time recorded in the airplane log book is the time that is applicable for the time limits WARNING For vendor equipment installed in Tecnam aircraft make sure to consult applicable maintenance instructions in terms of time lim its addressed on vendor publications Inobservance of this rec ommendation may affect the aircra...

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Page 77: ...Or BHC 105 408 Life limit 1000 hrs 4 years WOF 25 ELT Battery Pack 452 6499 Life limit Refer to CMM 570 1600 latest issue 32 Brake fluid Life limit 800 hrs 3 years WOF 61 Propeller Model HO17GHM A 174 177 C Overhaul Refer to Propeller CMM Last issue 72 Engine Model 912 S2 Overhaul Refer to Rotax En gine Maintenance Manual 75 Coolant hose flexible line 92 11 105 02 Rev B Life limit 5 years 92 11 10...

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Page 79: ... tasks are grouped in function of ATA 100 code The first column shows the ATA code which the item belongs to the second col umn shows the system name the third column shows the maintenance task and the last columns shows the task frequency required namely Column A if a X is indicated in this column the task must be performed at each A inspection Column B if a X is indicated in this column the task...

Page 80: ...ation and tension FLUID LINES and HOSES for leaks cracks dents kinks chafing proper radius corrosion obstructions and deterioration METAL PARTS for security of attachment cracks metal distortion broken spotwelds and riveting corrosion and any other apparent damage WIRING for security chafing burning defective insulation loose or broken terminals heat deterioration BOLTS for correct torque safetyin...

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Page 82: ... on related Component Maintenance Manuals CMM Inobservance of this recommendation may affect the aircraft airworthiness A list of applicable CMMs is herein reported Doc No Description 570 1600 Description operation installation and maintenance manual ME406 ELT Last issue 08038F rev 05 ELT Kannad Installation and Operation Manual 190 00357 05 GNS 500W SERIES MAINTENANCE MANUAL GPS 500W and GNS 530W...

Page 83: ...06 Engine Cowling Check the integrity of ablative cowl ing coating internal side of engine cowlings Repaint if necessary X 11 Markings and Placards Inspect internal placards check for their readability and wear X 11 Markings and Placards Inspect external placards and ID board check for readability and wear X 21 Heating and ventilation Cabin heat valve check for cracks and security of installation ...

Page 84: ...s for damage and se curity of installation X 23 Communications Check electrical bonding to the a c X 24 Electrical system Check for proper battery installation Inspect battery cables and housing Check vent and drain lines free of ob structions X 24 Electrical system Remove the battery and perform ca pacity test Re install battery if air worthy X 24 Electrical system Inspect External Power Receptac...

Page 85: ... Inspect safety belts at tachments X 25 Equipment and furnishings Inspect the first aid kit check for ex piration date of the single parts if necessary replace the items X 25 Equipment and furnishings Inspect cargo net and the floor at tachment points for condition X 25 Equipment and furnishings ELT refer to applicable CMM See Chapter 05 20 Para 3 X 26 Fire protection Inspect portable fire extingu...

Page 86: ...ed X 28 Fuel System Inspect fuel tanks and lines for leaks and condition X 28 Fuel System Inspect fuel tank vents free from ob struction X 28 Fuel System Inspect fuel selector valve for leaks general condition and security of in stallation Check fuel tank sump drain valves for conditions and operation X 28 Fuel System Inspect operation of fuel selector valve control knob Check for re stricted move...

Page 87: ... damage or any other condition that can cause stress concentrations and eventual failure X 32 Landing gear Inspect gear fairings for cracks de formation proper rigging and gen eral condition X 32 Landing gear Inspect the NLG for movement con dition and relative steering system X 32 Landing gear Check shock for general condition and state of rubber disks X 32 Landing gear Inspect tires for cuts wor...

Page 88: ...d security of installation Inspect parking brake handle check for restricted movement interference or unusual play X 32 Landing gear Inspect rudder pedals for operation and condition X 32 Landing gear Check toe brakes for operation and master cylinders hoses for leaks X 32 Landing gear Disassemble and inspect the brake as semblies and examine the parts lin ing disc and plates for wear cracks warpa...

Page 89: ...eck static ports for condition and operation Ex amine Pitot static system water trap drain if required X 34 Navigation Check calibration of airspeed indica tor and altimeter Perform leak test 24 months 34 Navigation Inspect magnetic compass for condi tion operation and security of instal lation X 34 Navigation Perform Magnetic compass compen sation procedure 24 months 52 Doors Inspect the canopy f...

Page 90: ...X 55 Stabilator and Rudder Inspect stabilator and tab for surface damage or irregularities skin cracks distortion dents and corrosion struc tural defects loose or missing rivets hinges and bearings damage and ex cessive wear free to move X 55 Stabilator and Rudder Inspect stabilator attachments and at tach bracket for corrosion rust and security Check control surface stops for looseness effectiven...

Page 91: ...ion X 57 Wings Inspect ailerons control rods electri cal wires and attaching parts for secu rity routing chafing deterioration wear and correct installation X 57 Wings Inspect ailerons for surface damage or irregularities skin cracks distor tion dents corrosion structural de fects loose or missing rivets hinge damage excessive wear Check bal ance mass mounting for security of installation X 57 Win...

Page 92: ...er lockwire X 61 Propeller Check the propeller for surface dam age skin cracks distortion dents Check the bolts torque values X 71 Power Plant Engine mounts isolators check for integrity X 71 Power Plant Check integrity of engine firewall Check for cracks distortion or wrin kles X 71 Power Plant Visually inspect engine mount struc ture for bent cracked or buckled tubes and engine mount isolators a...

Page 93: ... fluid flow or cause a leakage All lines must be inspected to ensure that they are properly supported and are not rubbing against a structure Fit tings should be checked for signs of improper installation over torqueing excessive tension or other conditions which may lead to a failure Inspect engine parameters sensors for general condition and security of installation X 75 Coolant system Check coo...

Page 94: ...0 hr 79 Oil system Check oil circuit there should be no indication of leakages X 79 Oil system Disassembly check and rinse the oil tank X 79 Oil system Visually inspect oil radiator and thermostatic valve for condition and security of installation X 79 Oil system Visually inspect oil tank and tank vent line for condition and security of installation X 79 Oil system Check thermostatic valve for cor...

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Page 97: ...d Use recommended lubricants Where general purpose lubricating oil is specified but unavailable clean engine oil may be used as satisfactory substitute Check the components to be lubricated for evidence of excessive wear and replace them as necessary Remove all excess lubricants from components in order to prevent the collection of dirt and sand in abrasive quantities capable of causing excessive ...

Page 98: ...ation e g ESSO Beacon 325 MIL G 25013E Grease bearings lubrication e g AEROSHELL Grease No 15 Universal Airframe Grease AEROSHELL Grease No 33 Grease bearings lubrication AEROSHELL Grease No 5 MIL PRF 23827C Multi purpose aerosol grease e g ZIP CHEM D 5907NS Aerosol 3M aerosol white grease 8875 Lithium Lube Cleveland wheel bearing approved grease MOBIL Aviation Grease SHC 100 ...

Page 99: ...ubricate then apply a protective coat of grease Lubrication points wipe all lubrication points clean of old grease oil dirt etc before lubricating Aerosol Grease approved aerosol grease applying is allowed for all lubrication points unless otherwise indicated WARNING Item no Lubrication points Frequency 1 Rudder upper bushing 100 Hrs 2 Rudder lower bushing 100 Hrs 3 Teflon road stop LH 100 Hrs 4 T...

Page 100: ... 100 Hrs 27 Control column attachments 100 Hrs 28 Control column attachments 100 Hrs 29 Control axis to column attach ments 100 Hrs 30 Ailerons pulleys RH 100 Hrs 31 Ailerons pulleys LH 100 Hrs 32 NLG Lower attachment 100 Hrs 33 Shock absorber attachments 100 Hrs 34 NLG Upper attachments 100 Hrs 35 Steering attachments 100 Hrs 36 Pedals attachments 100 Hrs 37 Upper brake pump attachments if instal...

Page 101: ...2nd Edition Rev 0 Page 5 05 30 LUBRICATION Figure 1 Inspection points ...

Page 102: ...2nd Edition Rev 0 Page 6 05 30 LUBRICATION Figure 2 Inspection points details ...

Page 103: ...2nd Edition Rev 0 Page 7 05 30 LUBRICATION Figure 3 Rudder upper bushing Figure 4 Rudder lower bushing and teflon road stop ...

Page 104: ...2nd Edition Rev 0 Page 8 05 30 LUBRICATION Figure 5 Stabilator rod end Figure 6 Stabilator supports ...

Page 105: ...2nd Edition Rev 0 Page 9 05 30 LUBRICATION Figure 7 Stabilator supports ...

Page 106: ...2nd Edition Rev 0 Page 10 05 30 LUBRICATION Figure 8 Aircraft moving surfaces hinges Figure 9 Flaps lower bushing ...

Page 107: ...2nd Edition Rev 0 Page 11 05 30 LUBRICATION Figure 10 Stabilator rod loops Figure 11 Stabilator rod end ...

Page 108: ...2nd Edition Rev 0 Page 12 05 30 LUBRICATION Figure 12 Aileron rod ends and rotation bushing Figure 13 Aileron rod loop ...

Page 109: ...2nd Edition Rev 0 Page 13 05 30 LUBRICATION Figure 14 Flap rod end Figure 15 Flap rod attachments RH ...

Page 110: ...2nd Edition Rev 0 Page 14 05 30 LUBRICATION Figure 16 Flaps rod attachment LH and Flaps actuator attachments ...

Page 111: ...2nd Edition Rev 0 Page 15 05 30 LUBRICATION Figure 17 Pedals and rudder cables attachments Figure 18 Steering attachments ...

Page 112: ...2nd Edition Rev 0 Page 16 05 30 LUBRICATION Figure 19 Brake attachments If Applicable Figure 20 Control column ...

Page 113: ...2nd Edition Rev 0 Page 17 05 30 LUBRICATION Figure 21 Shock absorber attachments Figure 22 NLG Attachment and steering attachments ...

Page 114: ...2nd Edition Rev 0 Page 18 05 30 LUBRICATION Figure 23 Pedals attachments If Applicable Figure 24 Brakes pump attachments If Applicable ...

Page 115: ...2nd Edition Rev 0 Page 19 05 30 LUBRICATION Figure 25 Connection pedal rudder Figure 26 Steering control road ...

Page 116: ...2nd Edition Rev 0 Page 20 05 30 LUBRICATION Figure 27 Parking brake lever If Applicable A B Figure 28 Main gear wing bearings ...

Page 117: ...2nd Edition Rev 0 Page 21 05 30 LUBRICATION Figure 29 Nose gear wing bearings 42 ...

Page 118: ...omponents main gear steel spring requires particular care b For aluminum parts treatment consists in mechanically removing as much as pos sible corrosion by products applying corrosion inhibitor and replacing original finish Steel wool emery or steel brushes unless stainless steel along with other highly abra sive material should not be used since steel or emery particles become embedded in the so...

Page 119: ...nd RH wing attachment plates Vertical and horizontal stabilizers an hing es All metric bearings and terminals Engine compartment Not on exhaust components Corrosion prevention Table Note use the ACF 50 in closed hangar and make sure that the product is always under the temperature limits indicated on the technical data sheets Note remove all traces of salt water and salt water residue by thoroughl...

Page 120: ...al A log book entry should be made upon completion of any inspec tions 1 Operation in Highly Dusty or Industrial Pollution Environ ment ITEM INSPECTION INSPECTION INTERVAL Engine air filter Clean and inspect Daily Engine oil cooler and coolant radiator Clean and inspect 25 hours Pitot Static system Check for obstruction 100 hours or as required NLG shock absorbers Clean Before each flight Landing ...

Page 121: ...mpartment for elec trolyte spillage and condition of pro tective paint Inspect area around bat tery vent for corrosion 100 hours or 1 year WOF Landing gear Inspect landing gear components for damage to exterior finish coating and corrosion Particular attention should be given to exposed surfaces and at taching hardware ribs and lower skin surfaces 100 hours or 1 year WOF Control cables Inspect con...

Page 122: ...salt water residue by thoroughly washing the aircraft with fresh water 2 Apply anticorrosion product ACF 50 every 12 months on the areas indicated in the following table Area Component Fuselage wing attachments stabilator attach ments Landing gear Gear attachment bolts nuts and pins Wing section and hinges LH and RH wing Vertical and horizontal stabilizers an hinges All metric bearings and termina...

Page 123: ...tarted Keep the ignition wires tires and other rubber parts free of the mixture 6 Where maximum corrosion protection is desired on stationary parts use exterior surface corrosion preventive compound Specification MIL C 16173 grade I 7 When the aircraft operates near salt water and off coral beaches the corro sion can be very rapid Except for friction and bearing surfaces apply a protective coating...

Page 124: ... Operation on Soft or Unusual Terrain ITEM INSPECTION INSPECTION INTERVAL Landing Gear Inspect for cracks attachment damages cleanliness and lubrica tion 100 hours Wheels Inspect for crack damage bear ings for damage corrosion and lubrication 100 hours Tires Inspect for cuts wear inflation and deterioration Daily Brakes Inspect for damage foreign mate rial cracks and overheating Daily Flaps lower ...

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Page 126: ...anu al Each occurrence before further flight Electrical and avionics sys tem Inspect and check harness connec tion and equipment for high volt age damage burns and insulation degradation Replace or overhaul as required Consult with avionics vendor s for inspections and op erational checks Bench test alter nator and voltage regulator s Each occurrence before further flight All exterior surfaces ski...

Page 127: ...raft in a normal level attitude Make a preliminary inspection checking alignment and out of track condition of engine wings tail landing gear and doors Follow Tecnam P2002 JF and Rotax Maintenance Manuals for procedures If there any question regarding repairs or procedures contact your Tecnam dis tributor s service advisor DSA Inspect the following items closely to determine the extent of damage I...

Page 128: ...parwebs fuel tanks for damage and leaks Each occurrence before further flight Engine and propeller Engine mounts for distortions and damage to elastomeric parts Propel ler for evidence of ground strike i e hard or overweight landing Each occurrence before further flight Fuselage Canopy alignment windows and at tachment for overstress cracks or damage Stringers bulkheads keel beams for buckling cra...

Page 129: ...ms wiring radios should be disas sembled as necessary and the contaminants completely removed Nevertheless these guidelines are general in nature and should be applied or var ied to fit the individual aircraft according to water level exposure time and other variables Only those areas that might not be obvious to the mechanics are ad dressed Make all repairs and or adjustments in accordance with t...

Page 130: ...io of eight parts detergent to 20 parts of alcohol Add the deter gent alcohol mixture to 72 parts of tap water and mix thoroughly For use add one part of the preceding concen trate to nine parts of tap water warm water if available and mix thorough ly If the above specified deter gent alcohol materials are not availa ble use water emulsion cleaning compound MIL C 43616 Add one part compound to nin...

Page 131: ...lace porous materials exposed to wa ter immersion unless surfaces are ade quately sealed to prevent penetration by water Virtually all solvents and phenolic type cleaning agents are det rimental to acrylics and will either sof ten the plastic or cause crazing Re move instruments and radios and ap plicable cables and plumbing and re pair and inspect as necessary If immersed each occur rence before ...

Page 132: ...of engine after reinstalla tion If immersed each occur rence before further flight Propeller and propeller governor Inspect and repair as necessary in an authorized propeller repair center If immersed each occur rence before further flight Electrical systems Replace all circuit breakers and switches Replace all solenoids relays and master contactors Replace bat tery Disassemble all connectors clea...

Page 133: ...occur rence before further flight Heating and ventilating system Clean and inspect all distribution ducts and valves Inspect and check system control cables Replace corroded or binding cables If immersed each occur rence before further flight Avionics systems Instruments avionics antennas etc must be returned to the equipment manufacturer for inspection if im mersed If immersed each occur rence be...

Page 134: ...2nd Edition Rev 0 Page 9 05 60 UNSCHEDULED MAINTENACE INTENTIONALLY LEFT BLANK ...

Page 135: ...2nd Edition Rev 0 Chapter 06 Dimensions and inspection caps ...

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Page 137: ...vision 06 LOEP 1 2nd Edition Rev 0 2 2nd Edition Rev 0 06 TOC 1 2nd Edition Rev 0 06 00 1 2nd Edition Rev 0 2 2nd Edition Rev 0 3 2nd Edition Rev 0 4 2nd Edition Rev 0 06 10 1 2nd Edition Rev 0 2 2nd Edition Rev 0 3 2nd Edition Rev 0 4 2nd Edition Rev 0 5 2nd Edition Rev 0 ...

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Page 139: ...Page 1 2nd Edition Rev 0 O6 TOC CHAPTER 06 TABLE OF CONTENTS 06 00 DIMENSIONS AND AREAS 1 General Dimensions 1 Control Surfaces Travel Limits 3 06 10 INSPECTION CAPS 1 ...

Page 140: ... 06 00 DIMENSIONS AND AREAS This chapter gives the airplane major dimensions and areas The International System is used in any case Chapter 02 provides unit conversion charts General Dimensions Following figure addresses the airplane general dimensions ...

Page 141: ...ratio 6 4 Taper ratio 0 6 Dihedral 5 Fuselage Length overall 6 61 m 21 7 ft Width overall 1 11 m 3 6 ft Height overall 2 43 m 10 0 ft Empennage Stabilator span 2 90 m 9 5 ft Vertical tail span 1 10 m 3 5 ft Main Landing gear Wheel track 1 85 m 6 1 ft Wheel base 1 62 m 5 3 ft Main wheel tyres type 5 00 5 Nose gear Nose gear tyre type 4 00 6 type 5 00 5 ...

Page 142: ... 00 DIMENSIONS AND AREAS Cabin dimensions Figure 1 Cabin dimensions Control Surfaces Travel Limits Ailerons Up 20 2 down 15 2 Stabilator Up 3 1 down 15 1 Trim Up 2 1 down 9 1 Rudder LH 30 2 RH 30 2 Flap Up 0 1 T O 15 1 FULL 40 2 ...

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Page 144: ...cess All access plates and panels are secured by either metal fasteners or screws and are identified as follows 1 The suffix is the zone location namely C cabin CF cabin floor E engine nacelle F fuselage W wing L light 2 The second suffix consists of a number The access and inspection caps for the airplane are shown in the following Figures ...

Page 145: ...Page 2 2nd Edition Rev 0 O6 10 INSPECTION CAPS Figure 2 Inspection caps ...

Page 146: ...dder control cable 2 F8 Instrument panel 2 LH and RH F9 Battery and its connections 1 F10 Stabilator torque tube its attachments and control rod vertical tail rear spar rudder bellcrank trim actuator and its connecting rods 1 F22 Tail cone structure 1 C11 Parking brake valve lever brake configuration rudder control cables 1 C12 Instrument panel and radio equipment 1 C15 Tail cone structure tail co...

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Page 149: ...2nd Edition Rev 0 Chapter 07 Jacking ...

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Page 151: ...CHAPTER 07 LOEP Section Page Edition Revision 07 LOEP 1 2nd Edition Rev 0 2 2nd Edition Rev 0 07 TOC 1 2nd Edition Rev 0 2 2nd Edition Rev 0 07 00 200 2nd Edition Rev 0 201 2nd Edition Rev 0 202 2nd Edition Rev 0 203 2nd Edition Rev 0 ...

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Page 153: ...Page 1 2nd Edition Rev 0 O7 TOC CHAPTER 07 TABLE OF CONTENTS 07 00 JACKING MAINTENANCE PRACTICES 200 General 200 Jacking the aircraft 200 Removing airplane from jacks 202 ...

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Page 155: ...m cylinder fastened to the outer keelsons Below of it could be placed either a hydraulic jack or a lifting rod The lifting point is realized with a 11mm hole which could be used to fit a lifting rod safety pivot Figure 1 Lifting point Jacking the aircraft Tools Item Quantity Part Number Notes Jacks 2 Commercial check for suitable max load Jack adapters 2 Commercial Ø11 mm Nose trestle 1 Commercial...

Page 156: ... the nose wheel off the ground for at least 7 cm about 3 in 4 Place jacks with related adapters at MLG jacking points locations refer to Figure 2 In order to prevent unintended a c unbalancing during jacks operation it is advisable a third person is next to the a c tail 5 Simultaneously operate jacks to prevent excessive side loads on a c structure and jacks until wheels are clear of ground for ab...

Page 157: ...arking brake is engaged 2 Remove tail trestle installed during the jacking procedure In order to prevent unintended a c unbalancing during jacks operation it is advisable a third person is next to the a c tail 3 Lower MLG jacks until airplane rests on MLG and jacks can be removed 4 Remove jacks and trestle ...

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Page 159: ...2nd Edition Rev 0 Chapter 08 Leveling and Weighing ...

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Page 161: ...8 LOEP 1 2nd Edition Rev 0 2 2nd Edition Rev 0 08 TOC 1 2nd Edition Rev 0 2 2nd Edition Rev 0 08 10 200 2nd Edition Rev 0 201 2nd Edition Rev 0 202 2nd Edition Rev 0 08 20 200 2nd Edition Rev 0 201 2nd Edition Rev 0 202 2nd Edition Rev 0 203 2nd Edition Rev 0 204 2nd Edition Rev 0 ...

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Page 163: ...Page 1 2nd Edition Rev 0 O8 TOC CHAPTER 08 TABLE OF CONTENTS 08 10 LEVELING 200 General 200 Longitudinal leveling 201 Transversal Levelling 202 08 20 WEIGHING 200 General 200 Procedure 201 ...

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Page 165: ...pter 07 for jacking procedures during the weighing procedure while the wheels are on the scales or while the wheels are on the ground during other operations Leveling on wheels can be performed deflating the tires Tools Item Quantity Part Number Notes Spirit level 1 Commercial Be careful when you deflates the tires do not deflate them to a point where damage to the tire sidewalls could arise ...

Page 166: ... Slide off one of the two seat to get the access to the two seat track s supporting trusses Place longitudinally a spirit or water level over the two supporting trusses using if necessary a straight piece of wood as indicated into figure 1 Adjust the aircraft s tilt by regulating tire pressure Figure 1 Longitudinal leveling ...

Page 167: ...Page 202 2nd Edition Rev 0 O8 10 LEVELING Transversal Levelling With one seat removed place a level along the forward seat track s supporting truss Level the aircraft by deflating the main gear tyres ...

Page 168: ...ight figures make sure baggage compartment is empty All weighing operations must be conducted in a closed hangar and taking care that no air currents pass over the airplane during weighing otherwise inaccurate readings could result If necessary wash the airplane to remove accumulations of mud dirt etc Tools Item Quantity Part Number Notes Scales 3 Commercial Ramps 3 Commercial Spirit level 1 Comme...

Page 169: ...oolants at operating levels 7 Move seats to most forward position 8 Flaps retracted 0 9 Control surfaces in neutral position 10 Position scales min capacity 200 kg under each tire 11 Level the aircraft 12 Record weights of individual scales 13 Calculate empty weight 14 Drop a plumb bob tangent to the wing s leading edge Trace a reference mark on floor 15 Repeat operation on other wing 16 Connect t...

Page 170: ...erence line Model P2002 JF S N ________ Weighing no _________ Date _________ Datum leading edge vertical Kg metres Fwd wheel weight W1 Distance from bob to Lh wheel AL Lh main WL Rh wheel AR Rh main WR Average distance AL AR 2 A W2 WL WR Distance from bob to nose wheel B Empty weight We W1 W2 D W A W B We 2 1 ________meters C G position as wing chord D D 1 37 100 Figure 2 CG and moment computation...

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Page 173: ...2nd Edition Rev 0 Chapter 09 Towing and Taxiing ...

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Page 175: ... CHAPTER 09 LOEP Section Page Edition Revision 09 LOEP 1 2nd Edition Rev 0 2 2nd Edition Rev 0 09 TOC 1 2nd Edition Rev 0 2 2nd Edition Rev 0 09 10 1 2nd Edition Rev 0 2 2nd Edition Rev 0 09 20 1 2nd Edition Rev 0 2 2nd Edition Rev 0 ...

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Page 177: ...Page 1 2nd Edition Rev 0 09 TOC CHAPTER 09 TABLE OF CONTENTS 09 10 TOWING 200 MAINTENANCE PRACTICES 200 09 20 TAXIING 200 MAINTENANCE PRACTICES 200 ...

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Page 179: ...ips CAUTION CAUTION CAUTION Tools Item Quantity Part Number Notes Tow bar 1 Commercial Procedure 1 Attach the tow bar to the nose wheel 2 Remove if employed wheel chocks and mooring cables if installed 3 Release parking brake 4 Tow the aircraft making smooth starts and stops 6 When towing operation is completed turn nose wheel to center engage parking brakes 7 Install wheel chocks and if required ...

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Page 181: ...start roll 5 Taxi forward a few feet and apply brakes to determine their effectiveness 6 Taxi with propellers controls in full forward position 7 While taxiing make slight turns to ascertain the effectiveness of steering 8 Observe wing clearances when taxiing near buildings or other stationary objects If possible station a guide outside the aircraft to observe 9 When taxiing on uneven ground look ...

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Page 183: ...2nd Edition Rev 0 Chapter 10 Parking Mooring Storage and Return to Service ...

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Page 185: ...TER 10 LOEP Section Page Edition Revision LOEP 1 2nd Edition Rev 0 2 2nd Edition Rev 0 TOC 1 2nd Edition Rev 0 10 10 200 2nd Edition Rev 0 10 20 200 2nd Edition Rev 0 10 30 200 2nd Edition Rev 0 201 2nd Edition Rev 0 202 2nd Edition Rev 0 ...

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Page 187: ...tion Rev 0 10 TOC CHAPTER 10 TABLE OF CONTENTS 10 10 PARKING 200 General 200 Procedure 200 10 20 MOORING 200 Procedure 200 10 30 STORAGE AND RETURN TO SERVICE 200 General 200 Storage 200 Restoration from storage 201 ...

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Page 189: ...t Procedure 1 Position airplane on levelled surface headed into the prevailing wind if practical 2 Engage parking brake In case of long time parking or overnight parking it is recommended to moor the a c as shown on Para 10 20 CAUTION Do not engage the parking brakes at low ambient temperature when an accumulation of moisture may cause the brakes to freeze or when they become hot from severe use I...

Page 190: ... Assure that flaps are retracted 4 Electrically ground airplane by connecting ground cable to the engine muffle 5 Close and lock canopy 6 Secure tie down cables to the wings and tail cone tie down rings at approximately 45 degree with respect to the ground Mooring is strongly recommended when the wind is more than 10knots and the a c is completely refueled Do not engage the parking brakes at low a...

Page 191: ...Page 201 2nd Edition Rev 0 10 20 MOORING Figure 1 Mooring scheme ...

Page 192: ...head it into the prevailing wind 2 Center nose wheel 3 Apply wheels chocks 4 Remove the battery see Chapter 12 battery removal procedure 5 Drain the fuel from the fuel tanks see Chapter 12 fuel tanks drainage procedure 6 Deactivate ELT 7 Ensure flaps are retracted 8 Electrically ground airplane by connecting ground cable to the engine muffle 9 Ensure that all inspection caps are closed and secured...

Page 193: ...procedure 2 Check the wheels pressure 3 Check oil and cooling system 4 Reactivate ELT 5 Remove chocks from wheels 6 Engine refer to Rotax Operator s Manual P N 899372 Engine Back to Operation Instructions 7 Propeller refer to Hoffman propeller Operation and Installation Manual Storage instructions 8 Make an engine start test see AFM engine start procedure ...

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Page 195: ...2nd Edition Rev 0 Chapter 11 Markings and Placards ...

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Page 197: ... 1 2nd Edition Rev 0 11 00 1 2nd Edition Rev 0 11 10 200 2nd Edition Rev 0 201 2nd Edition Rev 0 11 20 200 2nd Edition Rev 0 201 2nd Edition Rev 0 11 30 200 2nd Edition Rev 0 201 2nd Edition Rev 0 202 2nd Edition Rev 0 203 2nd Edition Rev 0 204 2nd Edition Rev 0 205 2nd Edition Rev 0 206 2nd Edition Rev 0 207 2nd Edition Rev 0 ...

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Page 199: ...00 Paint Features 201 Ornament Removal 201 Ornament Installation 201 11 20 EXTERNAL PLACARDS 200 MAINTENANCE PRACTICES 200 Placard Removal 200 Placard Installation 200 11 30 INTERNAL PLACARDS 200 Self Adhesive Placard Removal 200 Self Adhesive Placard Installation 200 Stiff Riveted Placard Removal 201 Stiff Riveted Placard Installation 201 ...

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Page 201: ...e fuselage on the left side The placard identifies the airplane manufacturer airplane type and serial number its identification marks and EASA Type Certificate number This Chapter reports the location of these placards and markings as below described Exterior colour External placards Internal placards Self adhesive placards are used for all the placards except for the aircraft identification plate...

Page 202: ...or colour scheme is reported below Figure 1 Airplane typical exterior colouring Item Q ty Lh Rh Description 1 1 Ornament Lh customer option 2 1 1 P2002 Logo 3 1 1 P2002 Logo 4 1 Tecnam logo 5 1 1 Tail cone registration mark Lh 6 1 LG Fairing ornament customer option Application of colours other than those approved by Tecnam may cause excessive temperatures and consequent degradation of structural ...

Page 203: ...sol paint Ornament Removal Tools Item Quantity Part Number Notes Solvent a r Commercial type Procedure Detach the ornament from the airplane using a hot air blower to soften the adhesive and lifting one corner taking care not to damage any adjacent component or paintwork Then clean the surface with the solvent and a lint free cloth Ornament Installation Tools Item Quantity Part Number Notes Solven...

Page 204: ...Page 202 2nd Edition Rev 0 11 20 EXTERIOR COLOR MAINTENANCE PRACTICES Remove the protective covering from the adhesive side of the ornament and position the ornament pressing firmly to the surface ...

Page 205: ...h the solvent and a lint free cloth Placard Installation Tools Item Quantity Part Number Notes Solvent a r Commercial type Felt pad 1 Commercial type Procedure Clean the surface with a cloth made moist with the solvent and wipe carefully with a clean lint free cloth Remove the bottom protective covering from the adhesive side of the placard and position the placard pressing to the surface If an up...

Page 206: ... cap marking 2 1 1 Canopy lock marking 3 1 1 Wing no step zone marking 4 1 Zero stabilator marking 5 1 1 Tecnam Logo 6 1 1 Tecnam Logo 7 1 External power marking 8 1 Battery marking 9 1 1 MLG tires pressure marking 10 1 NLG tire pressure marking 11 1 1 P2002 logo 12 1 1 Tail cone aircraft marking 13 1 1 Aircraft ornaments 14 1 Under wing aircraft marking ...

Page 207: ...m Quantity Part Number Notes Solvent a r Commercial type Procedure Detach the placard from the airplane using a hot air blower to soften the adhesive taking care not to damage any adjacent component or paintwork Then clean the surface with the solvent and a lint free cloth Self Adhesive Placard Installation Tools Item Quantity Part Number Notes Solvent a r Commercial type Procedure Clean the surfa...

Page 208: ...e The rivets must be removed utilizing a 3 25 mm drill bit with an appropriate drill stop carefully drill the rivet head with light pressure heavy pressure can cause deformation of the substructure Stiff Riveted Placard Installation Tools Item Quantity Part Number Notes Riveter 1 Commercial type Rivet a r AVDEL Avex 01663 00410 Procedure Place in position the placard and fix the required rivets in...

Page 209: ...Page 202 2nd Edition Rev 0 11 30 INTERNAL PLACARDS MAINTENANCE PRACTICES Figure 4 Instrument panel analogic system ...

Page 210: ...ption 1 Breaker panel 2 Master generator ON OFF 3 Op Limitations 4 Aircraft logo 5 No smoking 6 Fuel Tank serigraph 7 Annunciator panel serigraph 8 Maneuvering speed 9 Trim Switch 10 First aid kit Em Hammer Fire ext 11 Throttle 12 Choke Push 13 Cabin Heat 14 Carburetor Heat 15 Trim Led ...

Page 211: ...v 0 11 30 INTERNAL PLACARDS MAINTENANCE PRACTICES Figure 5 Internal placards Item Description 1 Canopy lock 2 Fuel selector command 3 Parking brake 4 Level point ind 5 Tie down max press 6 Emergency hammer 7 Fire extinguisher ...

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Page 215: ...2nd Edition Rev 0 Chapter 12 Servicing ...

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Page 217: ...01 2nd Edition Rev 0 202 2nd Edition Rev 0 203 2nd Edition Rev 0 204 2nd Edition Rev 0 12 30 200 2nd Edition Rev 0 201 2nd Edition Rev 0 12 30 200 2nd Edition Rev 0 201 2nd Edition Rev 0 202 2nd Edition Rev 0 203 2nd Edition Rev 0 12 50 200 2nd Edition Rev 0 201 2nd Edition Rev 0 12 60 200 2nd Edition Rev 0 201 2nd Edition Rev 0 12 70 200 2nd Edition Rev 0 201 2nd Edition Rev 0 12 80 200 2nd Editi...

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Page 219: ... Oil Level Checking and Filling Procedure 201 Oil Change Procedure 203 Oil Tank Cleaning 204 12 30 COOLANT SYSTEM Servicing practices 200 Coolant System Level Check 200 12 40 SEATS Handling and cleaning instructions 200 General 200 Seats Removal and Installation Procedure 201 Seats Cleaning Instructions 202 12 50 AIRPLANE CLEANING INSTRUCTIONS 200 General 200 External Surfaces Cleaning Procedure 2...

Page 220: ...0 Removal Procedure 200 Installation Procedure 200 12 70 WHEELS SERVICING PRACTICES 200 General 200 12 80 BRAKE SYSTEM SERVICING PRACTICES 200 BRAKE TOE SYSTEM 200 General 200 Brake Oil level check procedure 200 TOE BRAKE SYSTEM optional 201 General 201 Oil level check procedure 202 ...

Page 221: ...led information on the engines will be found in the engine Maintenance Manual For inspection caps location make reference to Chapter 06 10 The Chapter 12 includes the following procedures 12 10 Fuel system servicing practices 12 20 Oil system servicing practices 12 30 Coolant system servicing practices 12 40 Seats handling and cleaning instructions 12 50 Airplane cleaning instructions 12 60 Batter...

Page 222: ...ntact of fuel with the skin can cause disease During refueling apply grounding and make sure that a fire extinguisher is available in the area Master switch has to be turned OFF Do not refuel with passengers on board Use only clean fuel servicing equipment Prolonged use of Aviation Fuel Avgas 100LL results in greater wear of valve seats and greater combustion deposits inside cylinders due to highe...

Page 223: ...Page 201 2nd Edition Rev 0 12 10 FUEL SYSTEM SERVICING PRACTICES Pictures below show the fuel filler cap and fuel sump drain valve location Figure 1 Drain Valve RH Shown LH Opp and Filler caps ...

Page 224: ...t the procedure for the other tank 11 Remove aircraft s ground Fuel Contamination Check Procedure 1 Apply aircraft s ground 2 Place a glass container under the drain valve 3 Open the drain valve 4 Fill the glass container and close the drain valve 5 Check fuel sample a must be clear and clean b there should be no water inside c there should be no deposits inside Fuel System Drainage Procedure 1 Ap...

Page 225: ...he selection of suitable lubricant refer to the additional information provided by Rotax Operators Manual P N 899371 Operating media Section last issue Make certain that fluids and fluid containers are protected from contamination of any kind If there is any doubt regarding the cleanliness of the fluid do not use it Containers for fluid must never be left open to air longer than necessary Allow th...

Page 226: ...rom the engine to the oil tank the process is complete when air flows back to the oil tank perceived by a gurgling 4 Soak the dipstick in the oil tank 5 Read the oil level refer to Figure 2 the level must be between the two marks 6 If necessary replenish oil At the selection of suitable lubricants refer to the additional information provided by Rotax Operators Manual P N 899371 last issue 7 Fit di...

Page 227: ...Page 202 2nd Edition Rev 0 12 20 OIL SYSTEM SERVICING PRACTICES Figure 3 Oil tank location ...

Page 228: ...then apply oil level checking procedure to record oil consumption 5 Remove safety wire and oil drain plug refer to Figures 4 And 5 and apply Oil change procedure addressed on Rotax Engine Maintenance Manual P N 899735 disposing used oil as per environmental regulations 6 Install oil drain plug with safety wire 7 Re install upper and lower engine cowling Remove and replace engine oil filter at each...

Page 229: ... tank Oil Tank Cleaning In event of heavy oil contamination apply the following procedure 1 Engage parking brake master switch OFF disconnect battery 2 Remove upper and lower engine cowling 3 Refer to Rotax Engine Maintenance Manual P N 899735 last issue for detailed instructions for oil tank cleaning 4 Reinstall upper and lower engine cowling ...

Page 230: ...formation provided by Rotax Operators Manual P N 899371 Operating media Section last issue Coolant System Level Check Do not remove the expansion tank radiator cap when the engine is hot escape of boiling coolant can cause injury to persons Procedure 1 Wait for the engine to cool down 2 Open engine cowling 3 Refer to Figures 6 and 7 for coolant tank location 4 Visual inspect of expansion tank leve...

Page 231: ...Page 201 2nd Edition Rev 0 12 20 COOLANT SYSTEM SERVICING PRACTICES Figure 6 Coolant expansion tank Figure 7 Coolant overflow bottle ...

Page 232: ...parallel tracks attached to the compartment floor structure which allow the seat to move forward or rearward Each seat consists of the following main components 1 Primary Structure Assembly consisting of the sitting and backrest assemblies 2 Horizontal Position Adjustment System allowing for the horizontal position adjustment The device consists of a lever located in the lower side of the structur...

Page 233: ...edure 1 Remove seats locking device unscrew and remove refer to Figure 9 2 Pull seat lever then slide seat all forward refer to Figure 10 3 Pull Up seat and remove it from his location 4 Apply procedure for both seats 5 To reinstall seats reverse these steps Figure 9 Seats locking device Figure 10 Seats remove procedure ...

Page 234: ...plicable CMM Polycarbonate Components Cleaning Tools Item Quantity Part Number Notes Standard cleaning products A R Commercial Procedure Perform polycarbonate components cleaning procedure using commercial products NEVER USE ABRASIVE OR HIGHLY ALKALINE CLEANER POLYCARBONATE LIFE WILL BE SERIOUSLY REDUCED AND CRACKING WILL OCCUR IF CLEANED WITH STRONG SOLVENTS Polyurethane Components Cleaning Tools...

Page 235: ...R IF CLEANED WITH STRONG SOLVENTS Leather Dress Cover Cleaning LEATHER DRESS COVER SHOULD BE CLEANED USING EXCLUSIVELY THE METHOD OF TREATMENT SWOWN IN THE TABLE BELOW OTHER CLEANING PRODUCTS COULD REMOVE THE SUPERFICIAL TREATMENTS CAUSING A LOSS OF PERFORMANCE IN TERM OF FLAME AND FUNGAL GROWTH RESISTANCE Procedure and tools To perform dress cover cleaning procedure refers to following table ...

Page 236: ...operating It is important that the airplane be kept in a clean condition and repeated cleaning should be accomplished as often as necessary The necessity for cleaning is indicated whenever there is any appreciable amount of soil accumulation by the presence of salt deposits or other contaminants by evidence of paint surface deterioration and by the presence of excessive oil or exhaust deposits or ...

Page 237: ...uch static vents it is recommended that openings and vents be plugged as a precaution Install protective caps if practical Windows Cleaning Procedure 1 Remove with water dirt mud etc from external surfaces 2 Wash with warm soapy water or with an aircraft plastic cleaner employ a soft cloth or sponge using a straight rubbing motion Do not harshly rub surfaces 3 Remove oil and grease with a alcohol ...

Page 238: ...ide information for battery removal installation When installing or removing a battery take special care to ensure that no sparks are created by tools and that the terminals are not shorted out by tools or loose jewellery Removal Procedure 1 Master switch OFF 2 Open fuselage inspection cap F9 3 Pull out the battery until both terminals are accessible 4 Disconnect the negative cable from the batter...

Page 239: ...Page 201 2nd Edition Rev 0 12 60 BATTERY SERVICING PRACTICES Figure 11 Anti vibration PAD ...

Page 240: ...flight check for damages cuts wear etc As safety general rule when servicing aircraft tires personnel should stand either in the front or rear of the wheel and avoid approaching from either side of the tire Procedure 1 Unscrew the valve dust cap 2 Connect a pressure gauge 3 Read the pressure If required adjust the pressure MLG and NLG wheels 2 2 bar 32psi 4 Fit the valve dust cap ...

Page 241: ...OSHELL Fluid 41 The brake system operation with low oil level could affect the brakes performances and could cause permanent damage Make certain that hydraulic fluids and fluid containers are protected from contamination of any kind Dirt particles may cause hydraulic units to become inoperative cause seal damage etc If there is any question regarding the cleanliness of the fluid do not use it Cont...

Page 242: ...e brake system is 400ml order of magnitude Fluid is drawn from the reservoir by the brake cylinders to maintain the fluid volume required for maximum braking efficiency The oil level check procedure is addressed below refer to Chapter 32 for bleeding and filling brake system procedures APPROVED HYDRAULIC FLUID SPECIFICATION MIL H 5606 e g AEROSHELL Fluid 41 ...

Page 243: ...come inoperative cause seal damage etc If there is any question regarding the cleanliness of the fluid do not use it Containers for hydraulic fluid must never be left open to air longer than necessary Oil level check procedure 1 Remove the baggage compartment panel Rear seats baggage compartment refer to Figure 13 2 Check oil reservoir for oil level must be between the two marks 3 If necessary rem...

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Page 247: ...2nd Edition Rev 0 Chapter 20 Standard practices Airframe ...

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Page 249: ...0 20 30 200 2nd Edition Rev 0 201 2nd Edition Rev 0 202 2nd Edition Rev 0 203 2nd Edition Rev 0 20 40 200 2nd Edition Rev 0 201 2nd Edition Rev 0 202 2nd Edition Rev 0 203 2nd Edition Rev 0 204 2nd Edition Rev 0 205 2nd Edition Rev 0 206 2nd Edition Rev 0 207 2nd Edition Rev 0 208 2nd Edition Rev 0 209 2nd Edition Rev 0 210 2nd Edition Rev 0 211 2nd Edition Rev 0 212 2nd Edition Rev 0 213 2nd Edit...

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Page 251: ...NTENANCE PRACTICES 200 20 30 CONTROL CABLES 200 MAINTENANCE PRACTICES 200 Inspection Technique 200 Cable damage 200 External wear patterns 202 Internal cable wear 202 Cable fittings 203 Pulleys 204 Pulley wear patterns 204 20 40 SAFETYING MAINTENANCE PRACTICES 200 General 200 Installation of Safety Wiring 201 Securing With Cotter Pins 208 Turnebuckles 209 Double wrap method 212 Single wrap method ...

Page 252: ...eads are clean and dry unless otherwise specified Run the nut down to near contact with the washer or bearing surface and check the friction drag torque required to turn the nut Whenever possible apply the torque to the nut and not the bolt This will reduce rotation of the bolt in the hole and reduce wear Add the friction drag torque to the desired torque This is referred to as final torque which ...

Page 253: ...Page 201 2nd Edition Rev 0 20 10 TORQUE DATA MAINTENANCE PRACTICES Figure 1 Torque wrench with various adapters ...

Page 254: ... the Maintenance Manual procedures Torque values are expressed in Nm conversion factors and tables are reported on Chapter 02 AN Threads Thread Torque Value 10 32 AN3 series 3 Nm 1 4 28 AN4 series 10 Nm 5 16 24 AN5 series 16 Nm 3 8 24 AN6 series 22 Nm 7 16 20 AN7 series 57 Nm 1 2 20 AN8 series 78 Nm 9 16 18 AN9 series 113 Nm 5 8 18 AN10 series 147 Nm ISO Metric Threads Thread Torque Value M4 Serie...

Page 255: ...20 CABLES TENSION MAINTENANCE PRACTICES Following table addresses the control cables tension values Tension values are expressed in decanewton conversion factors are reported on Chapter 02 Control line Tension Rudder control cables 44 4 lbs Ailerons control cables 44 4 lbs ...

Page 256: ... for the cables which pass through fairleads and around pulleys To inspect each section which passes over a pulley or through a fairlead remove cable for broken wires by passing a cloth along length of cable This will clean the cable for a visual inspection and detect broken wires if the cloth snags on cable When snags are found closely examine cable to determine full extent of damage The absence ...

Page 257: ...Page 201 2nd Edition Rev 0 20 20 CONTROL CABLE MAINTENANCE PRACTICES Figure 1 Control cable inspection technique ...

Page 258: ...s depicted in in the figure below Internal cable wear As wear is taking place on the exterior surface of a cable the same condition is taking place internally particularly in the section of the cable which pass over pulleys and quadrants This condition shown in Figure 3 is not easily detected unless the strands of cable are separated Wear of this type is a result of the relative motion between inn...

Page 259: ... to corrosion and pitting on cable terminals turnbuckles and cable fittings Any corrosion or pitting found requires replacement of the corroded fitting and or cable 100 hours special inspection for aircraft 15 years old or older using a 10X magnifier visually inspect the entire surface of each cable terminal turnbuckle or other cable fitting for corrosion or cracking Inspect under safety wire or c...

Page 260: ...a new bearing surface for the cable Maintain pulleys alignment to prevent the cable from riding on flanges and chafing against guards covers or adjacent structure Check all pulley brackets and guards for damage alignment and security Pulley wear patterns Various cable system malfunctions may be detected by analyzing pulley conditions These include such discrepancies as too much tension misalignmen...

Page 261: ...ic data for other types of safety locking are described in the individual maintenance practices Three basic methods are used in safetying safety wire cotter pins and self locking nuts Wire either soft brass or steel is often used on control cable turnbuckles and engine accessory attaching bolts Cotter pins are used on any point where a turning or actuating movement takes place Self locking nuts ar...

Page 262: ... two methods of safety wiring the double twist method that is most commonly used and the single wire method used on screws bolts and or nuts in a closely spaced or closed geometrical pattern such as a triangle square rectangle or circle The single wire method may also be used on parts in electrical systems and in places that are difficult to reach See figures below Figure 5 Safety wiring securing ...

Page 263: ...ts of less than 2 inches When using the single wire method the largest size wire that the hole will accommodate should be used Copper wire 020 inch diameter aluminium wire 031 inch diameter or other similar wire called for in specific technical orders should be used as seals on equipment such as first aid kits portable fire extinguishers or emergency valves A secure seal indicates that the compone...

Page 264: ... other When there are two or more units it is desirable that the holes in the units be aligned to each other Never Overtorque or loosen to obtain proper alignment of the holes It should be possible to align the wiring holes when the bolts are torqued within the specified limits However if it is impossible to obtain a proper alignment of the holes without undertorquing or overtorquing try another b...

Page 265: ... SAFETYING MAINTENANCE PRACTICES Figure 7 Securing caps drain cocks valves Although there are several safety wiring techniques used to secure aircraft hardware practically all are derived from the basic examples shown in figures below ...

Page 266: ...Page 205 2nd Edition Rev 0 02 40 SAFETYING MAINTENANCE PRACTICES Figure 8 Safety wiring procedures 1 3 ...

Page 267: ...Page 206 2nd Edition Rev 0 02 40 SAFETYING MAINTENANCE PRACTICES Figure 9 Safety wiring procedures 2 3 ...

Page 268: ...Page 207 2nd Edition Rev 0 02 40 SAFETYING MAINTENANCE PRACTICES Figure 10 Safety wiring procedures 3 3 ...

Page 269: ...tter pin hole and or the slots in the nut Cotter pins must not be reused on aircraft In using the method of cotter pin safetying as shown in Figures below ensure the prong bent over the bolt is seated firmly against the bolt shank and does not exceed bolt diameter Also when the prong is bent over the nut ensure the bent prong is down and firmly flat against the nut and does not contact the surface...

Page 270: ... safety wire Before securing turnbuckles threaded terminals should be screwed into the turnbuckle barrel until no more than three threads of either terminal are outside the barrel After that the turnbuckle has been adjusted for proper cable tension All lock wire used in the safetying of turnbuckles should be carbon steel corrosion resistant steel nickel chromium iron alloy inconel nickel copper al...

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Page 272: ...Edition Rev 0 02 40 SAFETYING MAINTENANCE PRACTICES More than a satisfactory method for turnbuckle safetying can be adopted hereinafter are reports the common ones Figure 13 Safetying turnbuckles acceptable methods ...

Page 273: ...in opposite directions through the hole in the turnbuckle eyes or between the jaws of the turnbuckle fork as applicable laying one wire along the barrel and wrapping the other at least four times around the shank of the turnbuckle and binding the laid wires in place before cutting the wrapped wire off Wrap the remaining length of safety wire at least four turns around the shank and cut it off Repe...

Page 274: ...middle of the barrel so that the third crossing of wire ends is in the hole again spiral the two wire ends in opposite directions around the remaining half of the turnbuckle crossing them twice Then pass one wire end through the cable eye or fork or through the hole in the swaged terminals in the manner previously described Wrap both wire ends around the shank for at least four turns each cutting ...

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Page 277: ...2nd Edition Rev 0 Chapter 21 Heating and ventilation ...

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Page 279: ...v 0 2 2nd Edition Rev 0 3 2nd Edition Rev 0 4 2nd Edition Rev 0 5 2nd Edition Rev 0 100 2nd Edition Rev 0 200 2nd Edition Rev 0 201 2nd Edition Rev 0 202 2nd Edition Rev 0 203 2nd Edition Rev 0 204 2nd Edition Rev 0 205 2nd Edition Rev 0 206 2nd Edition Rev 0 21 20 1 2nd Edition Rev 0 2 2nd Edition Rev 0 100 2nd Edition Rev 0 200 2nd Edition Rev 0 201 2nd Edition Rev 0 ...

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Page 281: ...TING 100 MAINTENANCE PRACTICES 200 1 CABIN HEATING AND DEFROST SYSTEM OPERATIONAL TEST 201 2 CABIN HEAT AND DEFROST VALVES CONTROL CABLE RIGGING 201 3 HOT AIR VALVES REPLACEMENT 202 4 HOT AIR VALVES CONTROL CABLE REPLACEMENT 204 21 20 VENTILATION 1 DESCRIPTION AND OPERATION 1 TROUBLESHOOTING 1010 MAINTENANCE PRACTICES 200 ...

Page 282: ...0 21 10 CABIN HEATING DESCRIPTION AND OPERATION 21 10 CABIN HEATING DESCRIPTION AND OPERATION The cabin heating system conveys the hot air drawn from the engine heat exchanger as shown in figure below Figure 1 Hot air system ...

Page 283: ...d between the heat exchanger item 2 located on engine muffler Heated air is directed toward two ways 1 Carburetor heat item 4 through the air box item 3 2 Defrost Cabin heat through an hot air valve item 5 Figure 4 that open or close the air flow to windshield defrost item 6 and to cabin heat item 7 Both systems are operable from the instruments panel carburettor heat command lever Figure 2 is loc...

Page 284: ...Page 3 2nd Edition Rev 0 21 10 CABIN HEATING DESCRIPTION AND OPERATION Figure 2 Carb Heat command lever Figure 3 Cabin Heat Defrost command knob ...

Page 285: ...Page 4 2nd Edition Rev 0 21 10 CABIN HEATING DESCRIPTION AND OPERATION Figure 4 Cabin heat valve Figure 5 Hot air valve ...

Page 286: ...Page 5 2nd Edition Rev 0 21 10 CABIN HEATING DESCRIPTION AND OPERATION Figure 6 Cold air access to carburettors ...

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Page 288: ...t the cabin heating system ATA 21 10 Troubleshooting Trouble Likely cause Action required Cabin heat loss of hot air flow Control cable disconnected Check control cable rigging Hot air valves seized Repair replace valve Hot air hoses disconnected Inspect hoses routing Defrost does not work Defrost valve seized broken Repair replace valve Control cable disconnected Check control cable rigging ...

Page 289: ...CES This Chapter contains the following maintenance tasks description Cabin heating and defrost system operational test Cabin heat valves control cable rigging Hot air valves replacement Hot air valves control cable replacement Heating and defrost system are managed by the same equipment ...

Page 290: ...Figure 3 5 Verify the hot air flow from air diffusers 6 PUSH cabin heat knob verify no air flows 2 CABIN HEAT AND DEFROST VALVES CONTROL CABLE RIGGING This operation must be done for LH and RH hot air valves Step no Task description Additional info References 1 Remove upper and lower engine cowling 2 Make sure that the hot air knob are in closed position Refer to Figure 7 3 Attach Bowden cable to ...

Page 291: ...pper and lower engine cowling 2 Unscrew cabin heat valve control cable and remove Bowden and sheat from Bowden stop on valve Refer to Figure 11 3 Remove hot conduit from valve Refer to Figure 14 4 Unscrew the bolt that attach valve to firewall Refer to Figure 15 5 Remove hot valve 6 Reverse these step to install a new one then apply hot cabin heat rigging procedure Figure 7 Hot air valve Figure 8 ...

Page 292: ... Edition Rev 0 21 10 CABIN HEATING MAINTENANCE PRACTICE Figure 9 Hot air knob in off position Figure 10 Hot air valve in close position Figure 11 Hot air knob in on position Figure 12 Hot air valve in open position ...

Page 293: ...and lower engine cowling 2 Unscrew cabin heat valve control cable Refer to Figure 11 3 Pull out cabin heat knob from its housing Refer to Figure 12 4 Unscrew cabin heat lever head Refer to Figure 13 5 Remove Bowden if necessary and replace Refer to Figure 13 6 Reinstall cabin heat control knob to its location Refer to Figure 12 7 Apply cabin heat control valve rigging procedure ...

Page 294: ...Page 205 2nd Edition Rev 0 21 10 CABIN HEATING MAINTENANCE PRACTICE Figure 13 Hot air valve command cable fitting Figure 14 Hot air knob housing Figure 15 Hot air knob assy ...

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Page 296: ... air diffusers located to left and right side of instruments panel 4 5 1 6 2 3 Figure 16 Ventilation system The external cold air is caught by the Naca intake access point item no 1 Figure 16 and can be used for internal ventilation if the diffusers are open The cold air diffuser can be opened by pressing on his push point as indicated in the followings pictures ...

Page 297: ...Page 2 2nd Edition Rev 0 21 20 VENTILATION DESCRIPTION AND OPERATION Figure 17 Pushing point Figure 18 Diffuser in open position Figure 19 Naca intake access point ...

Page 298: ...ollowing troubleshooting steps are provided to augment specific system information found in this manual about the ventilation system ATA 21 20 Troubleshooting Trouble Likely cause Action required LH or RH cabin ventilation loss of air flow Air hoses disconnected Inspect hoses routing ...

Page 299: ...tion Additional info References 1 Remove serflex clamp and disconnect air hose from the rear of diffuser You can easily access the hose from the bottom of the instrument panel 2 Unthread diffuser from its seat Strongly push diffuser inward from its rear 3 Replace diffuser if necessary 4 Place the new overhauled unit into seat Note tongues on diffuser s outer surface push diffuser until you hear cl...

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Page 301: ...2nd Edition Rev 0 Chapter 23 Communications ...

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Page 303: ...d Edition Rev 0 4 2nd Edition Rev 0 5 2nd Edition Rev 0 6 2nd Edition Rev 0 7 2nd Edition Rev 0 8 2nd Edition Rev 0 9 2nd Edition Rev 0 100 2nd Edition Rev 0 101 2nd Edition Rev 0 200 2nd Edition Rev 0 201 2nd Edition Rev 0 202 2nd Edition Rev 0 203 2nd Edition Rev 0 204 2nd Edition Rev 0 205 2nd Edition Rev 0 206 2nd Edition Rev 0 207 2nd Edition Rev 0 208 2nd Edition Rev 0 209 2nd Edition Rev 0 ...

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Page 305: ... COMM 2 4 Garmin Apollo SL30 SL40 4 Antennas 7 TROUBLESHOOTING 100 MAINTENANCE PRACTICES 200 1 GNS 430W 530W unit removal installation 201 2 GNS 430W 530W periodic maintenance 202 3 GMA 340 unit removal installation 203 4 GMA 340 periodic maintenance 204 5 SL30 SL40 unit removal installation 205 6 SL30 SL 40 periodic maintenance 206 7 COMM antenna removal installation 207 ...

Page 306: ...vigations functions Position and velocity determination using signals transmitted by Global Positioning System GPS Satellites Display of the stored navigation and map database for use by the pilot flight crew Area navigation functions using the determined position velocity and stored navigation data Approach navigation functions including WAAS precision approaches and the associated database Inter...

Page 307: ... audio Morse code identifier output Remote DME channeling The unit features a 240 by 128 pixel color LCD and two removable data cards one with a Jeppesen database to be inserted in the left card slot and the second being a terrain database to be inserted in the right card slot Garmin GNS 530W Garmin GNS 530W provides the same functions but with a greater screen dimension Figure 2 GNS 530W front pa...

Page 308: ... Comm microphone and audios to simplify cockpit workload MASQ processing reduces ambient noise from the avionics inputs Comm transmit indication is also provided Speaker selection is available to monitor the aircraft radios Figure 3 GMA340 front panel Each microphone input 4 sockets are available for all airplane occupants pilots and passengers has a dedicated VOX circuit to ensure that only the a...

Page 309: ...n optional COMM 2 Garmin Apollo SL30 SL40 The optional COMM NAV 2 equipment is the Garmin Apollo SL30 which includes a 760 channel VHF Comm transceiver and 200 channel VOR LOC GS navigation Figure 5a SL30 front panel The Garmin SL 40 VHF COM is only COM Radio equipment Figure 5b SL40 front panel ...

Page 310: ...r function listens to standby while monitoring active Emergency channel menu Squelch test function Stuck Mic time out 12 watt audio amplifier Includes two place VOX intercom The NAV radio features are the following 200 channel Nav with solid state DSP technology VOR Localizer and Glideslope receivers Built in VOR Localizer converter Fequency range VOR 108 00 117 95 MHz Localizer 108 00 111 95 MHz ...

Page 311: ...s From radial of the standby channel Back course annunciator output LOC enable annunciator output Internal RF diplexor Active and standby flip flop frequencies DME tuning and data display SL30 SL40 is installed on the central instruments panel area within easy view and reach of the pilot by means of a mounting frame for ease of installation connections and service of the unit Figure 7 Control Desc...

Page 312: ...cy Monitor Function Voice Monitor Function Voice Activated Intercom Dedicate Emergency Channel Selector Upgradeable to Include GPS Option Upgradeable to Include GPS Option Squelch Test Function Stuck Mic Time Out 35 seconds Antennas Item P n Description 1 CI 138C Antenna VOR fig 7 2 CI 291 11 17991 Antenna COMM 1 3 GA 35 Antenna GPS it s located under instrument panel cover fig 6 4 CI105 Antenna T...

Page 313: ...Page 8 2nd Edition Rev 0 23 10 COMM 1 AND 2 DESCRIPTION AND OPERATION Figure 8 Antennas ...

Page 314: ...Page 9 2nd Edition Rev 0 23 10 COMM 1 AND 2 DESCRIPTION AND OPERATION Figure 6 Antenna GPS Figure 7 Antenna VOR Figure 9 Antennas ADF Marker Beacon Transponder Marker Beacon ...

Page 315: ...re power is connected to the main connector Check circuit breakers and avionics switch The unit does not transmit Antenna disconnected Check antenna connection Antenna wiring defective Test wiring PTT switch failure Replace PTT switch PTT circuit defective Test PTT switch wiring MIC failure Replace MIC MIC circuit defective Test MIC switch wiring Unit defective Replace overhaul unit Following tabl...

Page 316: ...ing The SL30 does not transmit The TxKey input is not being pulled low Checks the TxKey mic key input pulled low for transmit A weather channel is selected Select a different frequency the unit will not transmit on a weather channel The input voltage is too low Check input supply voltage 9 volts DC required Antenna disconnected Check antenna connection Antenna wiring defective Test wiring PTT swit...

Page 317: ...is Chapter contains the following maintenance tasks description GNS 430W 530W unit removal installation GNS 430W 530W periodic maintenance GMA 340 unit removal installation GMA 340 periodic maintenance SL30 SL40 unit removal installation SL30 SL40 maintenance COMM antenna removal installation ...

Page 318: ...it that all screws are secure and in place 2 Verify that the display face is clean 3 Verify that external surfaces have no dents scratches etc 4 Inspect for broken or bent pins on external connectors 5 Inspect wires and cables for breaks in insulation or tears 5 Slide the unit into the rack straight in until it stops about 1 inch short of the final positison It may be necessary to insert the hex d...

Page 319: ...he display Battery Replacement The 430W unit includes an internal battery that will last 5 to 8 years The battery is used for internal time clock and GPS system information Regular planned replacement is not necessary The 430W unit will display a Low Battery and Unit Needs Service message when replacement is required Once the low battery message is displayed the battery should be replaced within 1...

Page 320: ...erify that external surfaces have no dents scratches etc Inspect for broken or bent pins on external connectors Inspect wires and cables for breaks in insulation or tears 6 Plug electrical connectors 7 Position the cam lock fully unscrewed turned counter clockwise 8 Slide the unit into the rack until jack screw makes contact with the receptacle located in the back plate 9 Turn clockwise and carefu...

Page 321: ...Page 204 2nd Edition Rev 0 23 10 COMM 1 and 2 MANTEINANCE PRACTICE 4 GMA 340 periodic maintenance The GMA 340 unit is designed to not require any regular general maintenance ...

Page 322: ...t the end of the cam lock travel or the unit may be damaged 4 With the cam lock fully disengaged pull the unit straight out holding onto the sides of the bezel It is not recommended that you pull the unit out by the rotary knobs 5 Unplug the connectors 6 Put in position the new overhauled unit plugging the electrical connectors Verify that the display face is clean Verify that external surfaces ha...

Page 323: ...rtighten The back of the bezel must be flush to the mounting tube If the cam lock is hard to turn or the unit does not seat fully the unit is probably binding and the mounting tube should be checked 11 Perform functional check See CMM post installation check out 6 SL30 SL 40 periodic maintenance The SL30 unit is designed to not require any regular general maintenance Cleaning the front panel The f...

Page 324: ... skin surface is not painted in correspondence of the fixing bolts Remove any interior paint in the area where the fixing nuts and washers are placed to assure a good ground 8 Put in position the new repaired antenna with the cork gasket 9 Tighten fixing nuts with washers as per standard values See standard torque values as addressed on Chapter 20 10 Connect antenna cable Refer to fig 8 11 Perform...

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Page 327: ...2nd Edition Rev 0 Chapter 24 Electrical system ...

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Page 329: ...tion Rev 0 200 2nd Edition Rev 0 201 2nd Edition Rev 0 202 2nd Edition Rev 0 203 2nd Edition Rev 0 204 2nd Edition Rev 0 205 2nd Edition Rev 0 206 2nd Edition Rev 0 207 2nd Edition Rev 0 208 2nd Edition Rev 0 209 2nd Edition Rev 0 24 20 1 2nd Edition Rev 0 2 2nd Edition Rev 0 100 2nd Edition Rev 0 200 2nd Edition Rev 0 201 2nd Edition Rev 0 202 2nd Edition Rev 0 203 2nd Edition Rev 0 204 2nd Editi...

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Page 331: ... 1 MAINTENANCE PRACTICES GENERAL RULES 201 2 GENERATOR REMOVAL AND INSTALLATION 202 3 BATTERY REMOVAL AND INSTALLATION 202 4 BATTERY SERVICING 202 5 BATTERY CAPACITY TEST 206 6 VOLT METER AMMETER REPLACEMENT 207 24 20 POWER DISTRIBUTION 1 DESCRIPTION AND OPERATION 1 TROUBLESHOOTING 100 MAINTENANCE PRACTICES 200 1 MASTER SWITCH RELAYS REPLACEMENT 201 2 STARTER RELAY REPLACEMENT 203 3 GENERATOR REGU...

Page 332: ...the 40 Amps generator is installed the 20 Amps one will be disabled Secondary DC power is provided by a battery GILL G25 which provides the energy necessary for feeding the essential electrical loads in the event of a generator failure For ground maintenance and or starting an external power socket is provided 12V electrical power socket IS installed on the instrument panel Electrical power is dis...

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Page 334: ...erator 2 External generator Main features maximum power output W 250 5800rpm nominal voltage V 14 0 3 current limit A 28 maximum current output A 20 operational temperature range C 25 90 The generator is provided with an external solid state electronic full wave rectifier regulator The current vs rpm chart is shown below Figure 1 Generator Features ...

Page 335: ...ry installed on VFR DAY configuration is a lead type one FIAMM BATTERY PRODUCTS 12V 19Ah in 20 hours The battery is located in the tail cone right side wing fuselage rear attachments zone in a dedicated box easily accessible through the inspection cap F9 the box is vented and drained thorough two hoses in order to avoid likely toxic gasses or fluid accumulate in the aircraft and damage the adjacen...

Page 336: ...r When DC external power is connected the external power relay automatically allows to feed directly the battery bus Before external power is connected Master Switch must be turned OFF after connection of external DC source Master Switch can be turned in the ON position in order to recharge the battery Voltmeter and Ammeter The electrical system is equipped with a voltmeter located on the instrume...

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Page 338: ...it Check wiring Regulator fails Replace regulator Switch fails Replace switch External power off line External socket not well connected Insert correctly external power socket External power relay fails Replace relay Battery has low capacity Battery is at end of life Replace battery Battery will not come up to full charge Charging rate is insufficient Check and correct settings for appropriate bat...

Page 339: ... and battery box caused by overfilling high charge rates Could cause battery to bridge across the terminals discharging battery in the process Remove battery from aircraft clean and neutralize the exterior of the battery and inside battery box with a solution of sodium bicarbonate baking soda Wash with clean water and dry thoroughly Recharge battery before placing in service Possible excessive use...

Page 340: ...ICE MAINTENANCE PRACTICES This Chapter contains the following maintenance tasks description Maintenance practices general rules Generator removal and installation Battery removal and installation Battery servicing Battery capacity test Volt meter Amp meter replacement ...

Page 341: ...tected from damage during maintenance cap them with dust covers 7 If needed renew wire markings they have to be clearly identified Inspection and or checking of the electrical system and components shall be conducted in accordance with inspection intervals addressed on Chapter 05 and when a closed area is opened for other maintenance purposes Following inspections are applicable 1 Check electrical...

Page 342: ...e reference to the instructions addressed on Rotax Installation Manual part no 899735 last issue and Heavy Maintenance Manual part no 899603 last issue 3 BATTERY REMOVAL AND INSTALLATION Make reference to Chapter 12 60 4 BATTERY SERVICING Before performing battery servicing operation apply following instructions ...

Page 343: ...or higher the battery is proper charged and ready to install on aircraft 3 If the voltage is lower than 10 60 in one of the following situations Dry charge new battery 10 12 hours after having filled up with acid Battery already in use which as remained inactive for long time For battery recharge refer to step 4 Of these table 4 For constant voltage charging procedure Constant voltage range 14 40 ...

Page 344: ...ntainer as the electrolyte flow may be interrupted and stop flowing 3b Refer to ITEM 3a 4 Air bubbles will come up from one or more of the right hand three filler ports as well as one or more of the left hand ones Make sure air bubbles are coming up as state din step 3 above Leave the container in this state for 20 minutes or longer Refer to ITEM 4a 5 if no air bubbles are coming up from any of th...

Page 345: ...NCE PRACTICE Step no Battery capacity test Task description Additional info References the same level as the cover of the battery The fill up procedure is now complete never remove the strip of caps nor add any water or electrolyte Figure 5 Battery activation ...

Page 346: ...s Record the discharge time 5 The battery is considered airworthy if it meets 80 of the one hour capacity rating 48 minutes to the cut off voltage 6 If the battery fails to meet the minimum run time recharge using the constant current method until the specific gravity reading stabilizes over three consecutive readings Allow the battery to stand on open circuit for one hour Refer to Par 4 Battery s...

Page 347: ...minum panel Hold firmly the instrument by hand during removal 4 Clear the voltmeter AmMeter of the instrument panel 5 Place into position the new overhauled unit in correspondence of the instrument panel cut out 6 Install the attaching screws which fix the ins volt ammeter to the aluminum panel Hold firmly the instrument by hand during installation Do not over tighten screws to avoid instrument ca...

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Page 350: ...e installed it provides the power distribution to avionics and is energized from the battery bus On the instrument panel LH lower area pilot side see Figure below there are three switches each one featuring ON and OFF positions The MASTER SWITCH allows for connecting through the battery relay the battery to its own distribution bus GENERATOR switch controls the field signal to the generator settin...

Page 351: ...s is connected to the battery through a relay controlled by the Master Switch There is a 50 Amps breaker between the battery and the battery bus All systems are connected to battery bus Avionic BUS The avionic BUS furnish power to the following systems 1 GMA 340 2 GNS 430w 3 GI 106 A 4 GTX 328 ...

Page 352: ...Troubleshooting Trouble Likely cause Action required Avionic bus not supplied Avionics switch fail Replace switch Avionics relay fail Replace relay Wiring short circuit Check wiring Generator not supplied with generator switch ON Switch fail Replace switch Breaker 1 Breaker pulled out 2 Breaker jumped out 3 Breaker fail 1 Push breaker 2 Check the electrical wires for short circuit 3 Replace breake...

Page 353: ...0 POWER DISTRIBUTION MAINTENACE PRACTICE MAINTENANCE PRACTICES This Chapter contains the following maintenance tasks description Master switch external power relay replacement Starter relay replacement Generator regulator replacement ...

Page 354: ... 06 10 4 Remove relay electrical wires 4 items extracting sheathings Refer to figure below Record wires positioning 5 Unscrew bracket screws and remove the relay 6 Put in place new relay 7 Fix the bracket screws 8 Connect relay electrical wires relocating sheathings Make reference to the recorded wires positioning 9 Perform functional test For Master Switch relay Set Master Switch ON Verify positi...

Page 355: ...Page 202 2nd Edition Rev 0 24 20 POWER DISTRIBUTION MAINTENACE PRACTICE Figure 7 Master switch external power relay Make sure that no foreign objects tools are left inside during replacement ...

Page 356: ...ernal power is provided 3 Pull out battery breaker 4 Open engine cowling upper and lower panel 5 Remove relay electrical wires 3 items extracting sheathings Refer to figure below Record wires positioning 6 Unscrew bracket screws and remove the relay 7 Put in place new relay 8 Fix the bracket screws 9 Connect relay electrical wires relocating sheathings Make reference to the recorded wires position...

Page 357: ...Page 204 2nd Edition Rev 0 24 20 POWER DISTRIBUTION MAINTENACE PRACTICE Figure 8 Starter relay Make sure that no foreign objects tools are left inside during replacement ...

Page 358: ...F 2 Make sure that no external power is provided 3 Open engine cowling upper and lower panel 4 Remove regulator electrical wires and connector Refer to figure below Record wires positioning 5 Unscrew bracket screws and remove the regulator 6 Put in place new regulator 7 Fix the bracket screws 8 Connect the electrical wires and connector Make reference to the recorded wires positioning 9 Perform fu...

Page 359: ...Page 206 2nd Edition Rev 0 24 20 POWER DISTRIBUTION MAINTENACE PRACTICE Figure 9 Generator regulator ...

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Page 361: ...2nd Edition Rev 0 Chapter 25 Equipment and furnishing ...

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Page 363: ... 200 2nd Edition Rev 0 201 2nd Edition Rev 0 202 2nd Edition Rev 0 203 2nd Edition Rev 0 204 2nd Edition Rev 0 205 2nd Edition Rev 0 206 2nd Edition Rev 0 207 2nd Edition Rev 0 208 2nd Edition Rev 0 25 20 1 2nd Edition Rev 0 2 2nd Edition Rev 0 200 2nd Edition Rev 0 201 2nd Edition Rev 0 202 2nd Edition Rev 0 25 30 1 2nd Edition Rev 0 2 2nd Edition Rev 0 200 2nd Edition Rev 0 201 2nd Edition Rev 0...

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Page 365: ...NANCE PRACTICES 200 1 CABIN PANELS REMOVAL INSTALLATION 201 25 20 SAFETY BELTS 1 DESCRIPTION AND OPERATION 1 MAINTENANCE PRACTICES 200 1 SAFETY BELT REMOVAL PROCEDURE 200 2 SAFETY BELT CLEALING PROCEDURE 202 25 30 EMERGENCY LOCATOR TRANSMITTER ELT 1 MAINTENANCE PRACTICES 200 1 ELT REMOVAL PROCEDURE 200 2 ELT INSTALLATION PROCEDURE 200 25 40 FIRST AID KIT 200 ...

Page 366: ...and interiors described in this chapter are those items related to comfort and safety of the crew This chapter is structures as follows 25 10 Cabin interiors 25 20 Safety belts 25 30 Emergency Locator Transmitter ELT 25 40 First aid kit Seats removal instructions and cleaning practices are reported on Chapter 12 40 ...

Page 367: ...e seat to move forward or rearward The cabin has accommodation for dual flight controls instruments electrical and electronic control panels conveniently located for crew accessibility Each seat consists of the following main components 1 Primary Structure Assembly consisting of the sitting and backrest assemblies 2 Horizontal Position Adjustment System allowing for the horizontal position adjustm...

Page 368: ... DESCRIPTION AND OPERATION For seats remove installation procedure refer to Chapter 12 40 The baggage compartment is located behind the seats in its upper side horizontal rear panel is located the ELT in its lower side is located the first aid kit ...

Page 369: ...Page 200 2nd Edition Rev 0 25 10 CABIN INTERIORS MAINTENANCE PRACTICES MAINTENANCE PRACTICES This Chapter contains the following maintenance tasks description Cabin panels removal installation ...

Page 370: ...lot side left cove r PAN EL LH3 rear pilot side left cove r PAN EL RH1 fwd co pi lot side right cove r PAN EL RH2 cente r co pi lot side right cove r PAN EL RH1 rear co pi lot side right cove r PAN EL BC3 uppe r bagg age comp artem ent cove r PAN EL BC2 fronta l lowe r side bagg age comp artem ent cove r PAN EL BC1 fronta l uppe r side bagg age comp artem ent cove r Type A Type A Type B Type B Typ...

Page 371: ...S Panel IP1 Step Task description Refer to 1 Unscrew and remove from panel compass 2 Unscrew the RH two upper screws and the two LH upper screws of IP01 panel 3 Unscrew the LH and the RH frontal lower screws 4 Pull out IP1 panel 5 For reassembly panel reverse these steps ...

Page 372: ...to 1 Apply IP1 panel removal procedure Tab 1 2 Slide off IP2 panel from its location Panel LH1 Step Task description Refer to 1 Lift move or remove fitted carpet in correspondence of panel lower side 2 Remove panel pins A A type 3 Pull out LH1 panel from its location 4 For reassembly panel reverse these steps ...

Page 373: ... Step Task description Refer to 1 Apply Panel LH1 removal procedure Tab 3 2 Remove panel pins and screws A A type on right and upper side B type on left side 3 Pull out LH2 panel from its location carefully sliding canopy can damage panel 4 For reassembly panel reverse these steps ...

Page 374: ...4 2 Unscrew panel fittings Type B 3 Pull out LH3 panel from its location 4 For reassembly panel reverse these steps Panel RH1 RH2 RH3 Step Task description Refer to 1 For RH1 removal procedure apply same task of LH1 panel Tab 3 2 For RH2 removal procedure apply same task of LH2 panel Tab 4 3 For RH3 removal procedure apply same task of LH3 panel Tab 5 ...

Page 375: ...ge 206 2nd Edition Rev 0 25 10 CABIN INTERIORS MAINTENANCE PRACTICES Panel BC1 Step Task description Refer to 1 Unscrew panel from canopy type B 2 Pull out panel 3 For reassembly panel reverse these steps ...

Page 376: ...nel BC2 Step Task description Refer to 1 Apply LH3 RH3 panel removal procedure Tab 5 6 2 Unscrew upper frontal and lower panel fitting type B 3 4 Unscrew upper secure belts attachments and remove it 5 Remove panel from its location 6 For reassembly panel reverse these steps ...

Page 377: ...E PRACTICES Panel BC3 Step Task description Refer to 1 Apply BC2 panel removal procedure Tab 8 2 Remove Bc3 panel stops at the right and left of it 3 Unscrew frontal panel attachments 4 Pull out panel from its location 5 For reassembly panel reverse these steps ...

Page 378: ... AND OPERATION Herein after is shown safety belt system for P2002 JF aircraft Each seat is fitted with a safety belt featuring four attaching points Figure 3 Safety belts scheme Figure 4 Safety belt lower attachment SAFETY BELT LOWER ATTACHMENT LH SHOWN RH OPPOSITE SAFETY BELT LOWER ATTACHMENT CENTRAL ...

Page 379: ...Page 2 2nd Edition Rev 0 25 20 SAFETY BELTS DESCRIPTION AND OPERATION Figure 5 Safety belt upper attachment Figure 6 Safety belts SAFETY BELT UPPER ATTACHMENT ...

Page 380: ...procedure Safety belt cleaning procedure 1 SAFETY BELT REMOVAL PROCEDURE Secure belt removal procedure Step Task description Refer to 1 For a suitable work area apply remove seats Chapter 12 2 Unscrew and remove upper safety belts attachments LH RH Fig 5 3 Unscrew and remove lower safety belts attachments LH RH Fig 4 4 Pull out safety belts from its location 5 For reassembly safety belts reverse t...

Page 381: ...sive chafe marks wear fusing The webbing must be replaced in these cases frayed webbing stands for the broken filaments from either the longitudinal yarns or the transverse ones Web edge cut or torn Broken filaments which obscure the identity of any yarn viewed from a distance of 8 inches Frayed zone more than 10 of the webbing width and 8 inches in length Webbing with more than 15 broken yarns in...

Page 382: ...s the system itself to last longer and prevents corrosion of the metal parts The webbing can be cleaned with fresh water and a mild soap machine washing not allowed using a sponge or a soft brush Do not use water or soap on metal parts these can be protected by pieces of cloth during webbing cleaning The metal fittings are cleaned with a cloth moistened with isopropyl alcohol ...

Page 383: ...Hz lasting until battery power is gone This 121 5 MHz signal is mainly used to pinpoint the beacon during search and rescue operations In addition for the first 24 hours of operation a 406 MHz signal is transmitting at 50 second intervals This transmission lasts 440 ms and contains identification data programmed into the beacon and is received by COSPAS SARSAT satellites The transmitted data is re...

Page 384: ...Page 2 2nd Edition Rev 0 25 30 ELT DESCRIPTION AND OPERATION Figure 8 ELT Location Fig 9 Antenna ELT ...

Page 385: ...h OFF 2 Disconnect D SUB connector from ELT unscrewing pivots Refer to Fig 10 3 Disconnect BNC connector unscrewing ring nut and pulling it out Refer to Fig 10 4 Pull velcro strap 5 Remove ELT 2 ELT INSTALLATION PROCEDURE ELT installation procedure 1 Put ELT on support tray 2 Lock with velcro strap 3 Insert D SUB connector and screw pivots Refer to Fig 9 4 Insert BNC connector and screw ring nut R...

Page 386: ...Page 201 2nd Edition Rev 0 25 30 ELT MAINTENANCE PRACTICES Figure 10 ELT ...

Page 387: ...table lists the kit s content DESCRIPTION QTY Roll of adhesive Band Aid cm 3 x m 5 1 Medicated Band Aids cm 6 x 2 8 Ammonia salts solution ml 100 Gauze cm 10 x m 5 1 Gauze cm 5 x m 5 1 Pomade for burn treatment gr 100 Eye drops gr 30 Sterilized Cotton gr 30 Cloth triangle measuring 100 cm per side 1 Skin disinfectant ml 100 Scissors 1 Tweezers 1 Figure 9 First Aid Kit ...

Page 388: ...Page 1 2nd Edition Rev 0 25 30 FIRT AID KIT INTENTIONALLY LEFT BLANK ...

Page 389: ...2nd Edition Rev 0 Chapter 26 Fire protection ...

Page 390: ...2nd Edition Rev 0 INTENTIONALLY LEFT BLANK ...

Page 391: ... 0 26 LOEP CHAPTER 02 LOEP Section Page Edition Revision 26 LOEP 1 2nd Edition Rev 0 2 2nd Edition Rev 0 26 TOC 1 2nd Edition Rev 0 26 00 1 2nd Edition Rev 0 200 2nd Edition Rev 0 201 2nd Edition Rev 0 202 2nd Edition Rev 0 ...

Page 392: ...Page 2 2nd Edition Rev 0 26 LOEP INTENTIONALLY LEFT BLANK ...

Page 393: ...Page 1 2nd Edition Rev 0 26 TOC CHAPTER 26 TABLE OF CONTENTS 26 00 FIRE PROTECTION GENERAL 1 MAINTENANCE PRACTICES 200 1 FIRE EXTINGUISHER CHECK 201 ...

Page 394: ...age 1 2nd Edition Rev 0 26 00 FIRE PROTECTION GENERAL 26 00 FIRE PROTECTION GENERAL The fire protection equipment consists of a fire extinguisher located on the cabin floor under the baggage compartment ...

Page 395: ...Page 200 2nd Edition Rev 0 26 00 FIRE PROTECTION MAINTENACE AND PRACTICES MAINTENANCE PRACTICES This Chapter contains the following maintenance tasks description Fire extinguisher check ...

Page 396: ...e extinguisher from bracket Refer to Figure 1 or 2 according your configuration 2 Check fire extinguisher weigh and follow service instruction as written on the bottle if necessary replace Refer to related CMM 3 Check security of installation and effortlessness of removal 4 Reinstall the fire extinguisher on the support Figure 1 Fire extinguisher Figure 2 Fire extinguisher ...

Page 397: ...Page 202 2nd Edition Rev 0 26 00 FIRE PROTECTION MAINTENACE AND PRACTICES INTENTIONALLY LEFT BLANK ...

Page 398: ...Page 203 2nd Edition Rev 0 26 00 FIRE PROTECTION MAINTENACE AND PRACTICES INTENTIONALLY LEFT BLANK ...

Page 399: ...2nd Edition Rev 0 Chapter 27 Flight controls ...

Page 400: ...2nd Edition Rev 0 INTENTIONALLY LEFT BLANK ...

Page 401: ...on Rev 0 203 2nd Edition Rev 0 204 2nd Edition Rev 0 205 2nd Edition Rev 0 206 2nd Edition Rev 0 207 2nd Edition Rev 0 208 2nd Edition Rev 0 209 2nd Edition Rev 0 27 30 1 2nd Edition Rev 0 2 2nd Edition Rev 0 100 2nd Edition Rev 0 200 2nd Edition Rev 0 201 2nd Edition Rev 0 202 2nd Edition Rev 0 203 2nd Edition Rev 0 204 2nd Edition Rev 0 205 2nd Edition Rev 0 27 40 1 2nd Edition Rev 0 200 2nd Edi...

Page 402: ...ion Rev 0 27 LOEP 27 50 1 2nd Edition Rev 0 2 2nd Edition Rev 0 200 2nd Edition Rev 0 201 2nd Edition Rev 0 202 2nd Edition Rev 0 203 2nd Edition Rev 0 204 2nd Edition Rev 0 205 2nd Edition Rev 0 206 2nd Edition Rev 0 ...

Page 403: ...EMENT 202 3 CONTROL AXIS REMOVAL INSTALLATION 203 4 CONTROL COLUMN REMOVAL INSTALLATION 205 27 30 FLAPS 1 DESCRIPTION AND OPERATION 1 TROUBLESHOOTING 100 MAINTENANCE PRACTICES 200 1 FLAP ACTUATOR REPLACEMENT 201 2 FLAP POSITION TRANSMITTER REPLACEMENT 203 27 40 STABILATOR AND TRIM 1 DESCRIPTION AND OPERATION 1 MAINTENANCE PRACTICES 200 1 STABILATOR SETTING 201 2 STABILATOR TRIM TAB CONTROL CABLE R...

Page 404: ...Page 2 2nd Edition Rev 0 27 TOC 27 50 RUDDER 207 DESCRIPTION AND OPERATION 207 MAINTENANCE PRACTICES 200 1 RUDDER CONTROL CABLE REPLACEMENT 201 ...

Page 405: ...t is controlled in flight by the use of the three standards primary control surfaces stabilator rudder and ailerons Control devices are of conventional type a double system of control axis and pedal is provided The wing flaps are electrically operated and can be positioned in any locations up to 40 Figure 1 Flight controls ...

Page 406: ...Page 2 2nd Edition Rev 0 27 10 FLIGHT CONTROLOS GENERAL Figure 2 Flight Controls 1 STICK CONTROL GROUP 4 RUDDER CONTROL 2 AILERON CONTROL 5 STABILATOR CONTROL 3 FLAP CONTROL 6 TRIM CONTROL ...

Page 407: ...leys which transmit movement from the two control sticks 1 linked in parallel by a rod 2 to a small bar 3 located under the baggage compartment floor in correspondence with main pushrods 5 issuing from the wings Main rods 5 are connected to the small bar 3 using two pins 4 The two main rods 5 are routed through the ribs and are attached at opposite end to a bell crank 6 and a push pull rod 7 The p...

Page 408: ...Page 2 2nd Edition Rev 0 27 20 AILERONS DESCRIPTION AND OPERATION Figure 3 Aileron control system ...

Page 409: ...Page 3 2nd Edition Rev 0 27 20 AILERONS DESCRIPTION AND OPERATION A 2 A 3 A4 A 1 Figure 4 Aileron Control System ...

Page 410: ...IN WASHER LARGE D 6 8 BOLT HEX HEAD 9 JUNCTION 10 AILERON CONTROL ROD 11 JOINT 12 WASHER D 6 13 STOP NUT M5 14 WASHER D 5 15 BUSHING 16 BOLT HEX HEAD M5 L 55 CR 8 8 A2 PUSH PULL ROD 17 TUBE 18 AILERON CONTROL ROD TERMINAL 19 POP RIVET 4 00 A3 ASSY AILERON CABLES ATTACHING ROD AFT 20 JOINT 21 AFT AILERON CABLE 22 WASHER D 6 23 STOP NUT M6 24 BOLT HEX HEAD M6 L 35 CR 8 8 25 AILERON CABLE ATTACHING R...

Page 411: ... This Chapter contains the following maintenance tasks description First bellcrank replacement Connecting rod replacement Control axis removal Control axis installation Control column removal Control column installation Ailerons removal installation procedures are reported on Chapter 57 ...

Page 412: ...rear of bolt Remove bell crank Refer to Figure 6 5 Replace bellcrank if required 6 Connect bellcrank to support apply torque as per defined value Refer to Figure 4 items A1 7 Connect upper control rod to bellcrank apply torque as per defined value Refer to Figure 4 items A1 See Chapter 20 8 Connect lower control rod to bellcrank apply torque as per defined value Refer to Figure 4 items A1 See Chap...

Page 413: ...A1 and to fig 5 4 Disconnect control rods from aileron unscrewing nuts pull out control rod Refer to Figure 4 items A1 and to fig 5 5 Replace control rod if required 6 Connect control rod to bellcrank apply torque according the torque value See Chapter 20 Torque values 7 Connect control rod to aileron reinstall aileron bellcrank inspection cap cap 1 See Chapter 06 8 Check ailerons travel limits UP...

Page 414: ...o References 1 Remove seat s See Chapter 12 41 2 Unscrew and remove floor panel under seats Refer to Figure 7 3 With a wrench unscrew the control axis fixing bolt Refer toFigure 8 4 Replace if necessary control axis Torque according the torque value See Chapter 20 Torque values 5 Reinstall floor panel and seats See Chapter 12 41 Figure 7 6 Perform the final inspection ...

Page 415: ...Page 204 2nd Edition Rev 0 27 20 AILERONS MAINTENANCE PRACTICES Figure 7 Floor panel Figure 8 Control axis fixing bolt ...

Page 416: ... link lh rh item B remove coppiglia Refer to Figures 9 and 10 6 Unscrew and remove the aileron command cable lh rh item C Refer to Figure 11 7 Unscrew and remove stabilator rod attachments item D Refer to Figure 12 8 Unscrew and remove control column cabin truss attachments lh rh item E Refer to Figure 13 9 Pull out control column and replace if necessary 10 Reinstall control column reversing thes...

Page 417: ...Page 206 2nd Edition Rev 0 27 20 AILERONS MAINTENANCE PRACTICES Figure 9 Control column item A Upper link ...

Page 418: ...Page 207 2nd Edition Rev 0 27 20 AILERONS MAINTENANCE PRACTICES Figure 10 Control column Control axis exploded view C C A A B B D E E ...

Page 419: ...Page 208 2nd Edition Rev 0 27 20 AILERONS MAINTENANCE PRACTICES Figure 11 Control column Item B lower link Figure 12 Aileron command cable Item C ...

Page 420: ...Page 209 2nd Edition Rev 0 27 20 AILERONS MAINTENANCE PRACTICES Figure 13 Stabilator control rod item D Figure 14 Control column cabin truss attachments item E ...

Page 421: ...Page 210 2nd Edition Rev 0 27 20 AILERONS MAINTENANCE PRACTICES INTENTIONALLY LEFT BLANK ...

Page 422: ...r and is located on the instrument panel Shunt must be activated until desired position is reached and read on instrument 0 TO 15 or FULL 40 During flap retraction shunt supplies the actuator until flaps are completely retracted Flap control system is push pull type The torque tube 1 is hinged to the cabin truss and connects the two moving surfaces by two levers 2 An electric linear actuator 4 gov...

Page 423: ...on Rev 0 27 30 FLAPS DESCRIPTION AND OPERATION Figure 15b Flap control 1 2 3 4 4 5 1 Flaps torque tube 2 Torque tube Cabin truss attachments 3 Flaps actuator 4 Command rod Flaps attachments 5 Flaps position transmitter ...

Page 424: ...Page 3 2nd Edition Rev 0 27 30 FLAPS DESCRIPTION AND OPERATION INTENTIONALLY LEFT BLANK ...

Page 425: ... 27 30 TROUBLESHOOTING Trouble Likely cause Action required Flaps do not operate Flaps switch failure Replace switch Actuator failure Replace actuator Circuit breaker fails open Circuit breaker replacement Flaps indication fails Position transmitter fails Check transmitter wiring and mechanical connection replace transmitter if needed Position indicator fails Check wiring replace indicator if need...

Page 426: ...S MAINTENANCE PRACTICE MAINTENANCE PRACTICES This Chapter contains the following maintenance tasks description Flap actuator replacement Flap position transmitter replacement Flaps removal installation procedures are reported on Chapter 57 ...

Page 427: ...res 16 and 17 5 Disconnect flap actuator from flap torque tube lever and from FWD attachment unscrew bolt Refer to Figures 15 16 and 17 6 Remove actuator and replace if needed 7 Join FWD flap actuator attachment and flap actuator rod end to flap torque tube lever Refer to Figures 15 16 and 17 8 Connect actuator connector and apply fasteners Refer to Figure 17 9 Close C4 inspection cap 10 Insert fl...

Page 428: ...Stop nut D 6 32 UNI 5737 8x40 Bolt hex head M8 L 40 cr 8 8 34 22 5 172 1 Lower liner actuator link 35 UNI 7473 8 Stop nut M8 36 UNI 6592 8 Washer D 8 37 6812607 Flap actuator 38 UNI 7473 6 Stop nut M6 39 UNI 6592 6 Washer D 6 40 UN I5737 6 35 Bolt hex head M6 L 35 cr 8 8 41 22 5 174 1 Upper liner actuator link 42 UNI 5737 6 45 Bolt 6x45 43 22 6 368 1 Thickness ...

Page 429: ...tion on flap torque tube and loosen serflex 7 Remove ground wire from transmitter plate then remove transmitter and replace it if needed Refer to Figures 18 and 19 9 Position flap transmitter as recorded during removal 10 Position ground wire between serflex and transmitter plate tighten serflex screw to lock Connect transmitter lever Refer to Figures 18 and 19 NOTE REPLACE ALWAYS THE SELF LOCKING...

Page 430: ... MAINTENANCE PRACTICE Figure 18 Flap position transmitter 1 Torque tube 22 5 152 000 25 Flap pos transmitter 22 5 178 000 26 Serflex 25 40 27 Bolt UNI 5737 4 20 28 Transmitter lever 24 5 208 2 29 Washer UNI 6592 4 30 Nut DIN985 4 31 Ground ...

Page 431: ...Page 205 2nd Edition Rev 0 27 30 FLAPS MAINTENANCE PRACTICE 1 28 25 26 27 29 30 Figure 19 Flap position transmitter ...

Page 432: ...PERATION 27 40 STABILATOR AND TRIM DESCRIPTION AND OPERATION The stabilator is operated by the longitudinal movement of the control column fig 20 item A which allows the control push pull assy two rods connected to the bell crank fig 20 item B to operate the stabilator ...

Page 433: ...dependent from stabilator one it s possible to control stabilator trim tab even if stabilator fails Stabilator trim is acted electrical with a switch located on the control stick The trim control is irreversible thanks its mechanic actuator see fig 21 item A screw jack type loss of trim control line does not lead to an uncontrolled trim surface movement A B ...

Page 434: ...Page 3 2nd Edition Rev 0 27 40 STABILATOR AND TRIM DESCRIPTION AND OPERATION Figure 21 Trim tab command A ...

Page 435: ... 0 27 50 RUDDER DESCRIPTION AND OPERATION MAINTENANCE PRACTICES This Chapter contains the following maintenance tasks description Stabilator setting Stabilator trim tab control cable replacement Stabilator trim tab adjustment ...

Page 436: ...SETTING In order to find the stabilator s zero the aeroplane must be previously longitudinally leveled Place a shim 19mm thick over the stabilator s rear spar and place the level over the shim and the stabilator s tubular spar then level the stabilator Figure 22 Stabilator setting ...

Page 437: ...il cone fairing Item 14 cotter pin Item 19 and 10 pin and washer Items 20 bolts Unscrewing bolts from actuator support plate Items 10 11 washers and nuts Item 6 actuator Pull out actuator from it s housing Refer to Figure 22 Figure 23 Figure 24 Figure 25 Figure 26 5 Reinstall all actuator fitting and tail cone fairing Refer to Figures 22 23 and 26 6 Connect the trim actuator electrical wiring to t...

Page 438: ... OPERATION Figure 22 Tail cone fairing Figure 23 Trim actuator assy 5 22 5 138 1 Connecting rod 6 T2 10A Actuator 10 UNI 6592 4 Washer 11 UNI 7473 4 Stop nut 14 MS24665 153 Cotter pin 19 MS20392 2C19 Clevis pin 20 UNI 5737 4 16 Bolt hex head M4 L 16 cr 8 8 ...

Page 439: ...Page 204 2nd Edition Rev 0 27 50 RUDDER DESCRIPTION AND OPERATION Figure 24 Trim tab actuator Figure 25 Cotter pin ...

Page 440: ...Page 205 2nd Edition Rev 0 27 50 RUDDER DESCRIPTION AND OPERATION Figure 26 Actuator fixing bolts ...

Page 441: ...iption Additional info References 1 Set the stabilator in its zero position and lock it in this position 2 Turn the Master switch ON 3 Trim to maximum pitch up 4 Adjust thread of hinged control rod until tab is deflected downwards 9 use a protractor or measure downward displacement of trailing edge 9 is approximately 16mm 5 Tighten lock nut for adjustment thread and fasten connecting pin of contro...

Page 442: ...re connected to torque elements which have link arms for the attachment of the rudder cables routing aft under the floor boards through pulleys to the rudder pulleys Two position rods are attached to the rudder pedal torque tube arms and to the fuselage bellcrank to complete the rudder control system The nose gear steering rod is attached to the left rudder pedal torque tube and to the nose gear s...

Page 443: ...Page 208 2nd Edition Rev 0 27 50 RUDDER DESCRIPTION AND OPERATION Figure 27 Rudder and steering control system ...

Page 444: ...Page 200 2nd Edition Rev 0 27 50 RUDDER MAINTENANCE PRACTICES MAINTENANCE PRACTICES This Chapter contains the following maintenance tasks description Rudder control cable replacement ...

Page 445: ... item B Refer to Figures 27 item B 29 31 THESE STEPS ARE APPLICABLE TO LH AND RH RUDDER CABLE 8 Remove and replace if required rudder cables 9 In 8a 8b inspection cap join LH and RH control cable to pedals tighten according standard value lubricate with grease Refer to Figures 27 item A 28 See chapter 12 and 20 10 Drive cable trough pulley rear panel BC2 Refer to figs 30 31 11 Join cable to termin...

Page 446: ...Page 202 2nd Edition Rev 0 27 50 RUDDER MAINTENANCE PRACTICES Figure 28 Rudder cables pedals attachments ...

Page 447: ...Page 203 2nd Edition Rev 0 27 50 RUDDER MAINTENANCE PRACTICES Figure 29 Redder cables attachments LH shown RH opposite Figure 30 Rudder cables pulleys C ...

Page 448: ...CES Figure 31 rudder control cable joints No Description 1 Carbon steel cable Front 2 Carbon steel cable Rear 3 Turnbuckles 4 Turnbuckles element RH 5 Turnbuckles element LH 6 Crimping ring 7 Support for cable fixing plate on rudder 8 Cable terminal on pedals ...

Page 449: ...Page 205 2nd Edition Rev 0 27 50 RUDDER MAINTENANCE PRACTICES INTENTIONALLY LEFT BLANK ...

Page 450: ...Page 206 2nd Edition Rev 0 27 50 RUDDER MAINTENANCE PRACTICES INTENTIONALLY LEFT BLANK ...

Page 451: ...2nd Edition Rev 0 Chapter 28 Fuel system ...

Page 452: ...2nd Edition Rev 0 INTENTIONALLY LEFT BLANK ...

Page 453: ...dition Rev 0 5 2nd Edition Rev 0 6 2nd Edition Rev 0 100 2nd Edition Rev 0 200 2nd Edition Rev 0 201 2nd Edition Rev 0 202 2nd Edition Rev 0 203 2nd Edition Rev 0 204 2nd Edition Rev 0 205 2nd Edition Rev 0 206 2nd Edition Rev 0 207 2nd Edition Rev 0 208 2nd Edition Rev 0 209 2nd Edition Rev 0 210 2nd Edition Rev 0 211 2nd Edition Rev 0 212 2nd Edition Rev 0 213 2nd Edition Rev 0 214 2nd Edition R...

Page 454: ...Page 2 2nd Edition Rev 0 28 LOEP INTENTIONALLY LEFT BLANK ...

Page 455: ...FUEL QUANTITY INDICATION TEST 201 2 ELECTRIC FUEL PUMP TEST 202 3 FUEL QUANTITY SENDER REPLACEMENT 204 4 ELECTRIC FUEL PUMP REPLACEMENT 206 5 FUEL QUANTITY INDICATOR REPLACEMENT 208 6 FUEL PRESSURE INDICATOR REPLACEMENT 209 7 GASCOLATOR CLEANING 210 8 FUEL VENT INSPECTION 210 9 FUEL TANK INSPECTION AND CLEANING 211 10 ELECTRIC FUEL PUMP FILTER CLEANING 212 ...

Page 456: ...Page 2 2nd Edition Rev 0 28 TOC INTENTIONALLY LEFT BLANK ...

Page 457: ...mechanical pump which is part of the engine and also through an electric pump that supplies adequate engine feed in case of main pump failure Only a part of the fuel flow entering the engine driven mechanical pump is delivered to the combustion chambers The return flow is conveyed in the left fuel tank through the return line Fuel System is constituted by the following main equipment installed Fue...

Page 458: ...in s floor near the firewall Fuel level indicators for each tank are located on instrument panel each fuel tank is equipped with individual sensor floats 3 Fuel feed is through an engine driven mechanical pump 8 and through an emergency electric pump 7 Electric pump is equipped with a thin mesh filter 7a that can be accessed for inspection via the closer cap 7b An electric fuel pressure sender 12 ...

Page 459: ...TION AND OPERATION 8 6 5 12 7 11 9 2a 7b 7a 7 1 3 10 4 2b Figure 2 Fuel system Fuel outlet is located at the lowest point of the inboard sidewall of each fuel tank fig 2 2a and is equipped with a standard mesh filter fig 3 Figure 3 Standard mesh filter ...

Page 460: ...RATION Tank vent connection fig 4 1 is located at the highest point of the inboard sidewall of each fuel tank in order to expel the excessive vapors through a tube located at the each wing tips fig 4 2 Figure 4 1 Tank vent connection Figure 4 2 Fuel tank vent hose ...

Page 461: ...Page 5 2nd Edition Rev 0 28 10 FUEL SYSTEM DESCRIPTION AND OPERATION Fig 4 3 Fuel tank vent inner view ...

Page 462: ...e valve Gascolator valve leakage Valve damaged Replace valve Visual evidence of leaking fuel Hose leaking loose connection or fuel system component leaking Visually check fuel system components replace items if needed Fuel quantity indicator gives incorrect indication Indicator or fuel sender fails Test system replace indicator or fuel sender if needed Fuel continues to flow with fuel selector val...

Page 463: ...ndication test Electric fuel pump test Fuel quantity sender replacement Electric fuel pump replacement Fuel quantity indicator replacement Fuel pressure indicator replacement Fuel selector valve replacement Fuel tank check valve replacement Gascolator cleaning Fuel vent inspection Fuel filter cleaning Fuel tank inspection and cleaning Electric fuel pump filter cleaning ...

Page 464: ...r Switch ON 6 Check correspondence between empty tank and fuel quantity indicator See Figure 4a 7 Fill with 25 lt and check for indicator position 1 2 See Figure 4b 8 Fill with 50 lt and check for indicator position 1 See Figure 4c Repeat procedure for both fuel tank In case of test failure missing correspondence between fuel q ty and indications investigate the cause if due to fuel q ty sender or...

Page 465: ...ON or the green light on the annunciator panel goes on and Fuel pressure indicator pointer gives a feedback Check for green arc 2 2 to 5 8 psi Refer to Figures 5 6 and 7 5 Set fuel pump switch and Master switch to OFF 6 Ensure that advisory green light on annunciator panel goes OFF and Fuel pressure indicator pointer does not give a feedback In case of test failure investigate the cause whenever f...

Page 466: ...Page 203 2nd Edition Rev 0 28 10 FUEL SYSTEM MAINTENANCE PRACTICE Figure 4 fuel pump light Figure 5 Fuel pressure indicator ...

Page 467: ...er 12 4 Unscrew fuel q ty sender cap from wing upper chamber in correspondence of fuel tank cap 21 See Chapter 6 5 Unscrew along fuel q ty sender flange and disconnect ground connector Refer to Figures 8 and 9 6 Remove fuel sender and replace if needed 7 Reconnect ground connector to fuel sender Refer to Figures 9 8 Screw fuel sender on its housing and reapply cap cap 21 See Chapter 6 and Figure 8...

Page 468: ...Page 205 2nd Edition Rev 0 28 10 FUEL SYSTEM MAINTENANCE PRACTICE Figure 6 Fuel sender inspection cap Figure 7 Fuel qty sender ...

Page 469: ...Open engine cowling 4 Unscrew electrical fuel pump support Refer to Figure 10 5 Remove electrical connection single splice Crop the two plastic serflex Remove the fireproof shield Disconnect splice Refer to Figure 11 6 Remove the electrical fuel pump and replace if necessary 7 Reverse these steps for electrical fuel pump installation 8 Perform a fuel pump test for check proper fuel pump operation ...

Page 470: ...Page 207 2nd Edition Rev 0 28 10 FUEL SYSTEM MAINTENANCE PRACTICE Figure 8 Electrical fuel pump support Figure 9 Fuel pump splice location ...

Page 471: ...ly the instrument by hand during removal 4 Clear the instrument of the instrument panel 5 Place into position the new overhauled unit in correspondence of the instrument panel cut out 6 Install the attaching screws which fix the instrument to the aluminum panel Hold firmly the instrument by hand during installation Do not over tighten screws to avoid instrument case damage 7 Install Fuel q ty indi...

Page 472: ...he aluminum panel Hold firmly the instrument by hand during removal 4 Clear the instrument of the instrument panel 5 Place into position the new overhauled unit in correspondence of the instrument panel cut out 6 Install the attaching screws which fix the instrument to the aluminum panel Hold firmly the instrument by hand during installation Do not over tighten screws to avoid instrument case dama...

Page 473: ...fety wire Refer to Figures 12 and 13 8 FUEL VENT INSPECTION Step Task description Additional note 1 Engage parking brake 2 Drain fuel tank according to Fuel system draining procedure Refer to Chapter 12 4 Remove the Tank vent inspection cover 23 Refer to Chapter 6 3 Disconnect the tube vent of the tank Refer to Figures 4 3 4 Take an air pistol or suitable means 5 Put air pistol outflow in correspo...

Page 474: ...e corrosion signs of leaks and security of attachment 7 Restore mastic layer along edges and attachment points if needed PR 1776 B2 Let mastic dry as long as required 8 Spray fuel approved fuel into tank 9 Open fuel drain valve and let drain fuel used for washing Use suitable containers to gather draining fuel Repeat Step 6 and 7 several times as required 10 Close drain valve 11 Remove all mastic ...

Page 475: ...ctric fuel pump so to gather eventual fuel leakages 4 Remove safety wire Refer to Figure 16 5 Unscrew wheel electric fuel pump lower cover Refer to Figure 16 6 Remove gasket then filter 7 Clean filter by suitable means removing all impurities 8 Place filter into the pump then apply gasket 9 Screw electric fuel pump lower cover Refer to Figure 16 10 Fasten lower cover by safety wire Refer to Figure...

Page 476: ...Page 213 2nd Edition Rev 0 28 10 FUEL SYSTEM MAINTENANCE PRACTICE Figure 11 Gascolator exploded view A C B Figure 12 Fuel tank assy INSPECTION CAPS filter drainage tank gasket ...

Page 477: ...Page 214 2nd Edition Rev 0 28 10 FUEL SYSTEM MAINTENANCE PRACTICE A C B Figure 13 Fuel system ...

Page 478: ...Page 215 2nd Edition Rev 0 28 10 FUEL SYSTEM MAINTENANCE PRACTICE Figure 14 Electrical fuel pump ...

Page 479: ...Page 216 2nd Edition Rev 0 28 10 FUEL SYSTEM MAINTENANCE PRACTICE INTENTIONALLY LEFT BLANK ...

Page 480: ...Page 200 2nd Edition Rev 0 28 10 FUEL SYSTEM MAINTENANCE PRACTICE INTENTIONALLY LEFT BLANK ...

Page 481: ...2nd Edition Rev 0 Chapter 30 Ice protection ...

Page 482: ...2nd Edition Rev 0 INTENTIONALLY LEFT BLANK ...

Page 483: ...Page 1 2nd Edition Rev 0 02 LOEP CHAPTER 30 LOEP Section Page Edition Revision 30 LOEP 1 2nd Edition Rev 0 2 2nd Edition Rev 0 30 TOC 1 2nd Edition Rev 0 30 10 1 2nd Edition Rev 0 ...

Page 484: ...Page 2 2nd Edition Rev 0 02 LOEP INTENTIONALLY LEFT BLANK ...

Page 485: ...Page 1 2nd Edition Rev 0 02 TOC CHAPTER 30 TABLE OF CONTENTS 30 00 ICE PROTECTION GENERAL 100 ...

Page 486: ...CE PROTECTION GENERAL Tecnam P2002 JF features only an ice protection device consisting in the LH Pitot heating system whose indications are reported on the annunciator panel Pitot system is described on Chapter 34 10 Annunciator panel is described on Chapter 31 10 ...

Page 487: ...2nd Edition Rev 0 Chapter 31 Indicating system ...

Page 488: ...2nd Edition Rev 0 INTENTIONALLY LEFT BLANK ...

Page 489: ...ition Rev 0 31 10 1 2nd Edition Rev 0 2 2nd Edition Rev 0 3 2nd Edition Rev 0 4 2nd Edition Rev 0 5 2nd Edition Rev 0 200 2nd Edition Rev 0 201 2nd Edition Rev 0 202 2nd Edition Rev 0 203 2nd Edition Rev 0 204 2nd Edition Rev 0 205 2nd Edition Rev 0 206 2nd Edition Rev 0 207 2nd Edition Rev 0 208 2nd Edition Rev 0 209 2nd Edition Rev 0 ...

Page 490: ... 10 INDICATING SYSTEM 1 DESCRIPTION AND OPERATION 1 MAINTENANCE PRACTICES 200 1 SCREWED INDICATORS REPLACEMENT 201 2 CLAMPED INDICATORS REPLACEMENT 203 3 ANNUNCIATOR WARNING PANEL REPLACEMENT 205 4 OIL PRESSURE SENSOR REPLACEMENT Errore Il segnalibro non è definito ...

Page 491: ...Page 3 2nd Edition Rev 0 31 TOC INTENSIONALLY LEFT BLANK ...

Page 492: ...t of the indicators with their own reference ATA Chapter where it is addressed The instrument panel is divided into five parts refer to Fig 1 The left side includes the flight instruments Fig 1 panel A the right side Fig 1 panel B includes the control instruments the central panel Fig 1 panel C includes the communication instruments The two lower panels Fig 1 panel D and panel E include switches F...

Page 493: ...7 8 Figure 2 Instrument panel left side Typical layout Item Description Reference chapter 1 Turn coordinator 34 2 Directional gyro indicator 34 3 Vertical speed indicator 34 4 Altimeter indicator 34 5 Artificial Horizon 34 6 Airspeed indicator 34 7 ADF indicator 34 8 VOR ILS Indicator 34 ...

Page 494: ...Figure 3 Instrument panel right side Typical layout Item Description Reference chapter 1 Chronometer 31 2 Voltmeter 24 3 Ammeter 24 4 ELT 31 5 Hour meter 31 6 Fuel q ty indicator 24 7 Oil pressure indicator 31 8 Oil temp indicator 31 9 Fuel pressure indicator 24 10 CHT 31 11 RPM 31 12 Flap indicator 31 ...

Page 495: ...ION AND OPERATION 1 2 4 3b 3a Figure 4 Instrumental panel central panel typical layout Item Description Reference chapter 1 GTX 328 Audio Panel 23 2 SL 30 Comm Nav 23 34 3a Alternator warning light 31 3b Annunciator panel exclusive for VFR Night 4 Compass 31 ...

Page 496: ...or panel For clearance the color of the lights is here reported Light Red warning Green advisory ALT X FUEL PUMP X PITOT HEAT X Annunciator panel see fig 2 consisting of three lights namely ALT caution light it indicates that the alternator is OFF or not working properly PITOT HEAT advisory light it indicates that Pitot heating system is ON FUEL PUMP advisory light it indicates that the electrical...

Page 497: ...ACTICES MAINTENANCE PRACTICES This Chapter contains the following maintenance tasks description Screwed indicators replacement Clamped indicators replacement Alternator warning light replacement Other sensors are part of the engine refer to Engine Maintenance Manual ...

Page 498: ...ATORS REPLACEMENT The following procedure applies to those indicators fixed to the instrument panel by means of four screws drawing a square around the indicator itself see figure below for reference Figure 6 Examples of screwed indicators Figure 7 Examples of screwed indicators rear view ...

Page 499: ...nts panel upper cover 4 Remove all instrument hoses and connections 5 Unscrew the attaching screws which fix the instrument to the aluminum panel Hold firmly the instrument by hand during removal 6 Clear the instrument of the instrument panel 7 Place into position the new overhauled unit in correspondence of the instrument panel cut out 8 Install the attaching screws which fix the instrument to th...

Page 500: ...RS REPLACEMENT The following procedure applies to those indicators fixed to the instrument panel by means of stirrups screwed themselves to the rear of the indicator See figures below for reference Figure 8 Example of clamped indicators Figure 9 Example of clamped indicator rear view Stirrup ...

Page 501: ...which fix the instrument to the stirrup s Hold firmly the instrument by hand during removal 7 Clear the instrument of the instrument panel 8 Place into position the new overhauled unit in correspondence of the instrument panel cut out 9 Install the attaching nuts which fix the instrument to the stirrup s Hold firmly the instrument by hand during installation Do not over tighten nuts to avoid instr...

Page 502: ...he annunciator panel by hand during removal Refer to Figure 10 6 Unscrew the attaching screws which fix the lights to the annunciator panel Refer to Figure 11 7 Clear the light housing of the annunciator panel 8 Apply a slight pressure by suitable means on both the light cover sides in order to make the cover plugs release Refer to Figure 12 9 Replace light 10 Install the light cover Make sure tha...

Page 503: ...Page 206 2nd Edition Rev 0 31 10 INDICATING SYSTEM MAINTENACE PRACTICES Figure 10 Unscrewing attaching screws Figure 11 Unscrewing attaching screws Figure 12 Unscrewing attaching screws ...

Page 504: ...Page 207 2nd Edition Rev 0 31 10 INDICATING SYSTEM MAINTENACE PRACTICES INTENTIONALLY LEFT BLANK ...

Page 505: ...Page 208 2nd Edition Rev 0 31 10 INDICATING SYSTEM MAINTENACE PRACTICES INTENTIONALLY LEFT BLANK ...

Page 506: ...2nd Edition Rev 0 Chapter 32 Landing gear ...

Page 507: ...2nd Edition Rev 0 INTENTIONALLY LEFT BLANK ...

Page 508: ...ev 0 203 2nd Edition Rev 0 204 2nd Edition Rev 0 205 2nd Edition Rev 0 206 2nd Edition Rev 0 207 2nd Edition Rev 0 208 2nd Edition Rev 0 209 2nd Edition Rev 0 210 2nd Edition Rev 0 211 2nd Edition Rev 0 212 2nd Edition Rev 0 213 2nd Edition Rev 0 214 2nd Edition Rev 0 215 2nd Edition Rev 0 216 2nd Edition Rev 0 217 2nd Edition Rev 0 218 2nd Edition Rev 0 219 2nd Edition Rev 0 220 2nd Edition Rev 0...

Page 509: ...Rev 0 101 2nd Edition Rev 0 102 2nd Edition Rev 0 200 2nd Edition Rev 0 201 2nd Edition Rev 0 202 2nd Edition Rev 0 33 30 1 2nd Edition Rev 0 100 2nd Edition Rev 0 200 2nd Edition Rev 0 201 2nd Edition Rev 0 202 2nd Edition Rev 0 203 2nd Edition Rev 0 204 2nd Edition Rev 0 205 2nd Edition Rev 0 206 2nd Edition Rev 0 ...

Page 510: ...SPECTION 208 4 MAIN WHEEL REMOVAL 210 5 MAIN WHEEL INSTALLATION 212 6 MAIN WHEEL DISASSEMBLY 216 7 MAIN WHEEL REASSEMBLY 217 8 MAIN WHEEL TYRE REMOVAL 218 9 MAIN WHEEL TYRE INSTALLATION 219 10 BRAKE ASSEMBLY REMOVAL 221 11 BRAKE ASSEMBLY INSTALLATION 222 12 BRAKE LINING REPLACEMENT 224 32 20 BRAKE SYSTEM 1 DESCRIPTION AND OPERATION 1 Lever Brake System 1 Toe Brake System 2 TROUBLESHOOTING 100 MAIN...

Page 511: ... GEAR 1 DESCRIPTION AND OPERATION 1 MAINTENANCE PRACTICES 200 1 REMOVAL OF NOSE GEAR FAIRING 201 2 INSTALLATION OF NOSE GEAR FAIRINGS 201 3 REMOVAL OF NOSE WHEEL 202 4 ON AIRCRAFT NOSE WHEEL INSPETION 202 5 NOSE WHEEL DISASSEMBLY 203 6 NOSE WHEEL REASSEMBLY 204 7 NLG DAMPER ON AIRCRAFT MAINTENANCE 205 ...

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Page 513: ...with nose wheel steering This Chapter contains instructions for the maintenance of P2002JF landing gear system and it addresses also the brake system descriptions with related maintenance practices The landing gear can divided in two parts MLG mean landing gear 1 NLG nose landing gear 2 1 Figure 1 Airplane MLG and NLG ...

Page 514: ... to fuselage for elastic cushioning of landing loads Each spring leaf 1 is connected to the fuselage via two keelsons 2 3 Two leather spacers 4 5 are inserted between each spring leaf and the keelsons Two bolts 7 and nuts secure the individual spring leaf to the edge of the outer keelson 2 via a light alloy tie 6 while a single bolt 8 and nut secures the inboard end of the leaf spring to inner kee...

Page 515: ...ne condition Replace wheel or wheel half Use of sharp objects to break tire bead Replace wheel or wheel half Landing with flat tire or abnormally hard landing Replace wheel or wheel half Landing in crabbing position in crosswind causing excessive side force Replace wheel or wheel half Normal fatigue failure when used beyond expected wheel life Replace wheel or wheel half Damaged bearing cone Misal...

Page 516: ...Page 101 2nd Edition Rev 0 32 10 MLG and BRAKES TROUBLESHOOTING INTENTIONALLY LEFT BLANK ...

Page 517: ...tion MLG removal MLG installation On aircraft main wheels inspections Main wheel removal Main wheel installation Main wheel disassembly Main wheel reassembly Main wheel tyre removal Main wheel tyre installation Brake assembly removal Brake assembly installation Brake lining replacement Information hereinafter addressed applies to both LH and RH MLG leg ...

Page 518: ...s until the wheels are clear of the ground Refer to Figure 2 Refer to Chapter 06 00 WARNING INSURE AIRCRAFT IS SECURE AND STABLE BEFORE BEGINNING ANY WORK WORKING UNDER AN IMPROPERLY STABILIZED AIRCRAFT COULD CAUSE INJURY OR DEATH 3 Remove following cover LWR CENTRAL WING TO FUSELAGE FAIRING CAP n 6 Refer to IPC Refer to Figure 3 Refer to Chapter 06 00 4 Remove flexible brake fluid line from the w...

Page 519: ...se the leg in the bay then align the holes 4 Insert the bolt aligning the holes with respect to those of the leg Refer to Figure 5 5 Fit the nuts the washers and the bolts Tighten the nut as per standard torque value Fit the leather spacers Errore L origine riferimento non è stata trovata 6 Fit the wheel if removed See instructions within this Chapter 7 Fit brake flexible line on the wheel Refer t...

Page 520: ...ion Rev 0 32 10 MLG and BRAKES MAINTENANCE PRACTICES MLG Fuselage bolts torque values AN365 524A torque 15 1 Nm 132 lib in 4 MLG external bolts AN365 624A torque 25 3 2 Nm 221 lib in 2 MLG internal bolt Figure 3 Jacking ...

Page 521: ...Page 204 2nd Edition Rev 0 32 10 MLG and BRAKES MAINTENANCE PRACTICES Figure 4 Cover Figure 5 Brake fluid line removal ...

Page 522: ...Page 205 2nd Edition Rev 0 32 10 MLG and BRAKES MAINTENANCE PRACTICES Figure 6 Nuts Removal Installation ...

Page 523: ...Page 206 2nd Edition Rev 0 32 10 MLG and BRAKES MAINTENANCE PRACTICES Figure 7 Fit brake flexible line Figure 8 Fit brake flexible ...

Page 524: ...Page 207 2nd Edition Rev 0 32 10 MLG and BRAKES MAINTENANCE PRACTICES INTENTIONALLY LEFT BLANK ...

Page 525: ...are cool 6 Inspect the brake disc for rust excessive grooves large cracks or other visible damage 7 Visually inspect the brake cylinder for corrosion cracks or other visible damage Check inlet fitting bosses and anchor bolt lugs for cracks 8 Check back plate attachment bolts to insure they are properly torqued and have not worked loose Gaps between the back plate and cylinder would be evidence of ...

Page 526: ...Page 209 2nd Edition Rev 0 32 10 MLG and BRAKES MAINTENANCE PRACTICES INTENTIONALLY LEFT BLANK ...

Page 527: ...aft on the jacks Refer to Chapter 07 00 WARNING INSURE AIRCRAFT IS SECURE AND STABLE BEFORE BEGINNING ANY WORK WORKING UNDER AN IMPROPERLY STABILIZED AIRCRAFT COULD CAUSE INJURY OR DEATH 3 Release parking brake 4 Remove the fairing Refer to Figure 8 5 Remove brake assembly back plate tie bolts 1 and washers and remove back plate Refer to Figure 9 6 Remove bolt 3 and nut 4 Remove wheel axle ring 1 ...

Page 528: ...Page 211 2nd Edition Rev 0 32 10 MLG and BRAKES MAINTENANCE PRACTICES Figure 9 Main wheel scheme ...

Page 529: ...arking brake is released 3 Install the wheel on the axle 4 Fit wheel axle ring 1 and axle ring nut 2 Tighten the ring nut loosen and then tighten it once again make sure wheel can be turned by hand with a slight friction and without noise Apply slippage mark Fit bolt 3 and nut 4 Refer to Figure 10 Refer to Figure 11A B 5 Fit brake back plate fit bolts 1 and washers Tighten bolts at torque value of...

Page 530: ...Page 213 2nd Edition Rev 0 32 10 MLG and BRAKES MAINTENANCE PRACTICES Figure 10 Cover Installation Removal Figure 11 Brake system P N 30 9 ...

Page 531: ...Page 214 2nd Edition Rev 0 32 10 MLG and BRAKES MAINTENANCE PRACTICES Figure 12 MLG Wheel Figure 13A Bolt Installation Removal ...

Page 532: ...Page 215 2nd Edition Rev 0 32 10 MLG and BRAKES MAINTENANCE PRACTICES Figure 13B Bolt Removal Installation ...

Page 533: ... wheel halves to note relationship to each other for reassembly Refer to Figure 12 6 Remove inner tube from the tyre 7 Remove bearing cone 4 seals 2 3 and snap ring 1 The bearing cup 4 should not be removed unless replacement is necessary due to scratches nicks pitting corrosion or evidence of overheating Refer to Figure 12 CAUTION Refer to CMM Parker Cleveland P N AWBCMM0001 7 last issue for more...

Page 534: ...hrough brake disc and wheel halves take into account the recorded halves relationship Inspect bolts and washers 6 prior to assembly bolt heads are to be on brake disc side of wheel Torque nuts to value specified on wheel nameplate Refer to Figure 12 Observe the torque required to turn the nut free running torque This value must be added to the value stated on the casting nameplate to obtain a true...

Page 535: ...ger be heard escaping from the tyre 3 Separate tyre beads from wheel halves using a bead breaker or by applying pressure in even increments around the entire sidewall of the tyre as close to the tyre beads as possible 4 Remove nuts 5 washers 6 and bolts 7 holding wheel halves and brake disc together Refer to Figure 12 5 Separate inner wheel half 10 outer wheel half 8 brake disc 11 and remove hubs ...

Page 536: ...re 12 3 Install bolts 7 through brake disc and wheel halves Inspect bolts and washers 6 prior to assembly bolt heads are to be on brake disc side of wheel Torque nuts to value specified on wheel nameplate Refer to Figure 12 Observe the torque required to turn the nut free running torque This value must be added to the value stated on the casting nameplate to obtain a true torque value 4 Inflate ty...

Page 537: ...Page 220 2nd Edition Rev 0 32 10 MLG and BRAKES MAINTENANCE PRACTICES Figure 14A MLG wheel assembly P N 40 77A ...

Page 538: ...N Insure parking brake is off and wheels are chocked 1 Release parking brake 2 Remove flexible brake fluid line from the wheel Refer to Figure 4 3 Remove brake assembly back plate tie bolts 1 and washers 2 and remove back plate Refer to Figure 13 4 Carefully slide brake cylinder 3 out of torque plate Refer to Figure 13 5 If torque plate 1 removal is required remove wheel tyre per wheel removal ins...

Page 539: ... 14A B 2 If wheel has been removed install wheel prior to installing brake cylinder assembly See instructions within this Chapter 3 Remove brake assembly back plate tie bolts 1 and washers 2 Refer to Figure 13 4 Install cylinder 3 in torque plate by sliding do not force anchor bolts into torque plate bushings Refer to Figure 13 A dry film lubricant should be applied to anchor bolts and torque plat...

Page 540: ...tion Task description Additional info References 6 Uncap and attach hydraulic line to cylinder inlet fitting 7 Bleed the brake system Apply procedure described within Chapter 32 20 8 Test brake system During taxiing operate brakes for efficiency check additionally pedals should feel firm and not spongy ...

Page 541: ...nchor bolts Refer to Figure 3 3 Inspect the caliper for corrosion bent anchor bolts cracks around bolts cracks around anchor bolt lugs and inlet fittings and other visible damage Inspect the torque plate assemblies for corrosion around anchor bolt bushings and excessive wear in bushings 4 The organic brake lining is identified by its semi hard composition and rivets 5 used to attach the lining to ...

Page 542: ...sing draw flattening or straightening techniques Refer to Figure 13 7 Align new factory authorized replacement lining 7 segments on pressure plate back plates and install rivets of corresponding part number using appropriate riveting tools 8 Check to be sure lining is tight and movement free with no distortion of parts 9 Slide pressure plate 4 with new lining over anchor bolts Refer to Figure 13 1...

Page 543: ...Page 226 2nd Edition Rev 0 32 10 MLG and BRAKES MAINTENANCE PRACTICES Figure 15A Torque plate installation removal Figure 14B 2 Torque plate installation removal Figure 15B Torque plate ...

Page 544: ...Page 227 2nd Edition Rev 0 32 10 MLG and BRAKES MAINTENANCE PRACTICES INTENTIONALLY LEFT BLANK ...

Page 545: ...System LEVER BRAKE SYSTEM The brake system consists of a brake fluid reservoir 1 a master cylinder 2 and two disc brakes assemblies 3 an intercept valve activates parking brake 4 Braking action is through a lever 5 located on cabin tunnel between seats The brake system is equipped with a non return valve 6 which insures that braking action is always effective even if parking brake circuit should a...

Page 546: ...ected to an inlet fitting on the caliper The caliper operation description is given on Chapter 32 10 A parking brake valve mounted in correspondence of the cabin floor and operated by a knob on the cockpit central pedestal intercepts the hydraulic lines once pressurized by toe brakes to hold the brake assemblies linings tightened round the main wheels brake discs Brakes can be operated from either...

Page 547: ...Page 3 2nd Edition Rev 0 32 20 BRAKE SYSTEM DESCRIPTION AND OPERATION Figure 37 Rudder pedals and brake master cylinders pilot and co pilot side ...

Page 548: ...Page 4 2nd Edition Rev 0 32 20 BRAKE SYSTEM DESCRIPTION AND OPERATION C PARKING BRAKE CLEVELAND BRAKE SYSTEM OIL TANK RESERVOIR BRAKES PUMPS Figure 18 Toe brake system scheme ...

Page 549: ...essive brake deflection Torque bolts to proper value Excess bolt torque has caused back plate to crush cylinder evidenced by depressions around bolt holes Replace cylinders Improper adjustment of master cylinder rod length restricting the development of maximum stroke Check cylinder rod for free movement up to maximum compression Brake drag Piston cocked in cylinder resulting in overheating brake ...

Page 550: ...air replace Restriction in hydraulic line Isolate and remove restriction Lining not firmly seated flush against pressure back plate Debur rivet hole on surface adjacent to lining Rapid disc and lining wear Dragging brakes Refer to Brake drag troubleshooting section Improper conditioning of brake linings See on aircraft inspection section for lining conditioning checking procedure Excessive rusting...

Page 551: ...sufficient hydraulic brake pressure troubleshooting section Organic brake lining carburized overheated Replace lining Pressure plate contacting torque plate assembly Check for correct torque plate wheel installation New Lining installed with old disc Lining not seated in wear track creating partial contact with disc Replace excessively worn disc Parking brake won t hold Valve failure Replace valve...

Page 552: ...e 200 2nd Edition Rev 0 32 20 BRAKE SYSTEM MAINTENANCE PRACTICES MAINTENANCE PRACTICES This Chapter contains the following maintenance tasks Brake fluid replacing Brake fluid draining Brake pads replacing ...

Page 553: ...oiding fluid spill 4 Top off brake fluid to of maximum level 5 Screw line nipple to disk caliper 6 Put reservoir cap 2 BRAKE FLUID DRAINING Procedure both sides Step no Task description Additional info References 1 Pull brake lever to pressurize circuit 2 Loosen small escape valve allowing fluid spurt 3 Close small valve and release brake lever 4 Repeat operations 1 2 And 3 Until fluid comes out c...

Page 554: ...g brake is released 2 Remove fairings to expedite operation 3 Loosen bolts 1 from the caliper 2 4 Slide caliper 2 along the guides 3 being careful not to bend brake fluid line 5 Remove the backplate 4 and the pressure plate 5 6 Remove and replace linings 6 by drilling out the rivets 7 Replace new linings with brand 6 and fasten them with new rivets 7 8 Reassemble all previously removed parts and p...

Page 555: ...th two hinges 1 and is equipped with a 4 00 6 type tire Steering motion is transmitted from the pedals through two steering tubes that are attached to the nose gear strut by means of two brackets 2 welded to the strut Gear fork is made up of light alloy plates 4 5 and a spacer 6 it hinges on the strut leg and is braced by a rubber disc shock absorber 3 Figure 20 Nose landing gear ...

Page 556: ...29 troubleshooting section Use of sharp objects to break tyre bead Replace wheel or wheel half Landing with flat tyre or abnormally hard landing Replace wheel or wheel half Normal fatigue failure when used beyond expected wheel life Replace wheel or wheel half Damaged bearing cone Misalignment of bearings Replace bearing cone being sure it is properly seated in bearing bore Axle nut improperly tor...

Page 557: ...ANCE PRACTICES This Chapter contains the following maintenance tasks description Removal of nose gear fairings Installation of nose gear fairings Removal of nose wheel On aircraft nose wheel inspection Nose wheel disassembly Nose wheel reassembly NLG damper on aircraft maintenance ...

Page 558: ...gure 21 3 Remove the rear upper fairings 4 loosen the screws 1 Refer to Figure 21 4 Unscrew nuts 7 and remove washer from wheel axle Refer to Figure 21 5 Unscrew bolt 8 in gear lever housing Refer to Figure 21 6 Remove the rear fairing Refer to Figure 21 2 INSTALLATION OF NOSE GEAR FAIRINGS Proceed the previous procedure in a reverse way to reinstall An over tightening can cause the damage of scre...

Page 559: ...ON Perform on aircraft inspection as follows 1 Visually inspect the wheels for corrosion cracks or other visible damage 2 Check wheel nuts to be sure they are properly installed and have not worked loose Bolt threads should be flush to 1 1 2 threads extending beyond the nut 3 Visually inspect tyres for cuts flat spots and tread or sidewall damage 4 Check inflation pressure Proper inflation will pr...

Page 560: ...ED AIRCRAFT COULD CAUSE INJURY OR DEATH 2 Lift aircraft on the jacks Refer to Chapter 07 0 Jacking Procedure As alternative engage parking chock main wheels press down the stabilator front spar adjacent to the fuselage to raise the nose wheel then place the nose trestle in correspondence of the first fuselage bulkhead 3 Remove bolt 8 nut 7 and washers 6 Refer to Figure 21 1 Remove caps 5 Refer to ...

Page 561: ... Figure 22 3 install bolts 5 through wheel halves Inspect bolts and washers 6 prior to assembly nuts are to be on valve side of wheel Torque nuts to value specified on wheel nameplate Refer to Figure 22 4 If removed carefully fit bearing cup 2 Fit bearing cone 129 seals 8 and 10 and snap rings 9 into each wheel half Refer to Figure 22 5 Inflate tyre to correct rated inflation pressure Deflate tyre...

Page 562: ...LD CAUSE INJURY OR DEATH 2 Remove nose gear fairings 3 Lift the airplane on jacks until the wheels are clear of the ground Refer to Chapter 07 0 Jacking Procedure As alternative engage parking chock main wheels press down the stabilator front spar adjacent to the fuselage to raise the nose wheel then place the nose trestle in correspondence of the first fuselage bulkhead 4 Remove upper and lower p...

Page 563: ...Page 206 2nd Edition Rev 0 32 40 NOSE LANDING GEAR MAINTENANCE PRACTICES Figure 23 Nose landing gear dumper ...

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Page 566: ...2nd Edition Rev 0 Chapter 33 Lights ...

Page 567: ...2nd Edition Rev 0 INTENTIONALLY LEFT BLANK ...

Page 568: ...ion Rev 0 33 10 1 2nd Edition Rev 0 2 2nd Edition Rev 0 3 2nd Edition Rev 0 100 2nd Edition Rev 0 200 2nd Edition Rev 0 201 2nd Edition Rev 0 202 2nd Edition Rev 0 33 20 1 2nd Edition Rev 0 2 2nd Edition Rev 0 3 2nd Edition Rev 0 100 2nd Edition Rev 0 200 2nd Edition Rev 0 201 2nd Edition Rev 0 202 2nd Edition Rev 0 203 2nd Edition Rev 0 ...

Page 569: ...Page 2 2nd Edition Rev 0 33 LOEP INTENTIONALLY LEFT BLANK ...

Page 570: ...S 200 1 MAINTENANCE PRACTICES GENERAL RULES 201 2 LED LIGHT REPLACEMENT 201 3 ANNUNCIATOR PANEL LIGHTS REPLACEMENT 202 33 20 EXTERNAL LIGHTS 1 DESCRIPTION AND OPERATION 1 TROUBLESHOOTING 100 MAINTENANCE PRACTICES 200 1 TAXI AND LANDING LIGHT REPLACEMENT 201 2 WINGTIP NAV AND STROBE LIGHTS ASSY REPLACEMENT 201 3 STROBE LIGHTS CONTROL UNIT REPLACEMENT 202 ...

Page 571: ... additional equipment VFR NIGHT INTERNAL ADDITIONAL EQUIPMENT Instruments lights A couple of instrument lights LED type is connected to the main bus trough a circuit breaker and installed in correspondence of fixed part of canopy one for each side Fitted with flexible struts they can be adapted to illuminate the instruments panel as pilot needs Figure 1 Couple of instruments lights A dimmer device...

Page 572: ...e the dome light installed on the cabin ceiling and directly connected to the battery trough a circuit breaker provides the pilot with an additional mean to illuminate the cabin and instruments panel Figure 2 Dome light Torch An emergency torch 3 AAA batteries needed is provided in the cabin pocket Figure 3 Torch ...

Page 573: ...e alternator is OFF or not working properly PITOT HEAT advisory light it indicates that Pitot heating system is ON FUEL PUMP advisory light it indicates that the electrical fuel pump is ON The VFR night day switch allows for regulating annunciator panel brightness depending on light conditions it is located next to the annunciator panel itself and it permits two brightness set ups day and night Fi...

Page 574: ...ing repair replace defective wiring Refer to chapter 92 Cockpit lights do not operate Cockpit lights are defective Instrument breaker is pulled out Wiring is faulty Replace cockpit lights Insert instrument breaker Perform a continuity test of wiring repair replace defective wiring Refer to chapter 92 Dome light does not operate Dome light is defective Dome light breaker is pulled out Wiring is fau...

Page 575: ...INTERNAL LIGHTS MAINTENANCE PRACTICE MAINTENANCE PRACTICES This Chapter contains the following maintenance tasks description Maintenance practices general rules Led light replacement Annunciator panel replacement Dome light replacement ...

Page 576: ...ire markings they have to be clearly identified Inspection and or checking of the electrical system and components shall be conducted in accordance with inspection intervals addressed on Chapter 05 and when a closed area is opened for other maintenance purposes Following inspections are applicable 1 Check electrical wiring for chafing and cuts 2 Check wire clamps and supports for security of insta...

Page 577: ...ht 5 Put in position a new light Engage the connector and test the light before fixing with mastic 6 Fix the light with a new binding of mastic 7 Engage the electrical connector 8 Install the over head panel 9 Perform a functional test 4 LED LIGHT REPLACEMENT Step no Task description Additional info References 1 Make sure Master Switches are turned off 2 Disassemble the dome light box 3 Unscrew th...

Page 578: ... aircraft flight direction identification Navigation lights are installed on the wing tips and on top of vertical stabilizer All navigation lights are controlled by a single switch located on instrument panel and are protected by a circuit breaker A green light is located on right wing tip a red light on left wing tip and a white lamp is on vertical stabilizer Refer to chap 92 for electric schemat...

Page 579: ...edge Landing light switch is located on instrument panel Light is protected by a 10 A circuit breaker Figure 7 Landing light Strobe lights They provide aircraft identification to prevent collision The strobe light is installed on top of the vertical stabilizer Strobe light is activated by a switch and is protected by a breaker Switch and breaker are positioned on the instrument panel The signal re...

Page 580: ...panel RH lower side The strobe lights mode switch instead allows for selecting two operational modes NORM all strobe lights are ON EMER only the strobe light on the vertical fin ON The switch allows for reducing electrical loads in event of electrical system failures Figure 9 Switches Landing lights Landing lights is located under the engine nacelle instead of the left wing leading edge in order t...

Page 581: ...Page 4 2nd Edition Rev 0 33 20 EXTERNAL LIGHTS DESCRIPTION AND OPERATION INTENTIONALLY LEFT BLANK ...

Page 582: ...obe lights do not operate Defective strobe light Strobe light switch is faulty Wiring defective Strobe lights breaker is pulled out Strobe light control unit fails Replace wingtip strobe light assy Replace switch Perform a continuity test of wiring repair replace defective wiring Red chap 92 Insert strobe breaker Replace strobe light control unit ...

Page 583: ...NAL LIGHTS MAINTENANCE PRACTICE MAINTENANCE PRACTICES This Chapter contains the following maintenance tasks description Taxi and landing light replacement Wingtip NAV and strobe lights assy replacement Strobe Lights Control Unit replacement ...

Page 584: ...tating the light path as required 11 Close inspection cap 2 WINGTIP NAV AND STROBE LIGHTS ASSY REPLACEMENT Step no Task description Additional info References 1 Make sure Master Switches are turned off Ref Figure 11 2 Unscrew the retaining screw 11 Remove retainer 10 and lenses 9 and 6 with the gasket 5 Ref Figure 11 3 Remove the three screws which fix the base plate to the wingtip Record bonding ...

Page 585: ...ction caps See chap 06 4 Remove connectors from control unit and record correct position for each one Ref Figure 11 5 Uninstall control unit from fuselage unscrewing the screws Ref Figure 11 6 Remove control unit 7 Replace control unit with new one if needed 8 Screw CU on fuselage use screws and groover washers Ref Figure 11 9 Connect connectors as recorded during removal Ref Figure 11 10 Close in...

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Page 587: ...Page 204 2nd Edition Rev 0 33 20 EXTERNAL LIGHTS MAINTENANCE PRACTICE INTENTIONALLY LEFT BLANK ...

Page 588: ...2nd Edition Rev 0 Chapter 34 Navigation ...

Page 589: ...2nd Edition Rev 0 INTENTIONALLY LEFT BLANK ...

Page 590: ...205 2nd Edition Rev 0 206 2nd Edition Rev 0 207 2nd Edition Rev 0 208 2nd Edition Rev 0 34 20 1 2nd Edition Rev 0 200 2nd Edition Rev 0 201 2nd Edition Rev 0 202 2nd Edition Rev 0 203 2nd Edition Rev 0 204 2nd Edition Rev 0 205 2nd Edition Rev 0 206 2nd Edition Rev 0 207 2nd Edition Rev 0 34 30 1 2nd Edition Rev 0 2 2nd Edition Rev 0 3 2nd Edition Rev 0 4 2nd Edition Rev 0 5 2nd Edition Rev 0 6 2n...

Page 591: ...ion Rev 0 205 2nd Edition Rev 0 206 2nd Edition Rev 0 207 2nd Edition Rev 0 208 2nd Edition Rev 0 209 2nd Edition Rev 0 210 2nd Edition Rev 0 211 2nd Edition Rev 0 212 2nd Edition Rev 0 213 2nd Edition Rev 0 214 2nd Edition Rev 0 215 2nd Edition Rev 0 ...

Page 592: ...PASS COMPENSTATION REPLACEMENT 202 3 ATTITUDE INDICATOR REPLACEMENT 204 4 DIRECTIONAL GYRO REPLACEMENT 205 34 30 POSITION DETERMINING 1 Description and operation 1 Troubleshooting 100 Maintenance practices 200 1 GNS 430W 530W UNIT REMOVAL INSTALLATION 201 2 GNS 430W PERIODIC MAINTENANCE 202 3 GNS 530W PERIODIC MAINTENANCE 203 4 SL30 UNIT REMOVAL INSTALLATION 204 5 SL30 PERIODIC MAINTENANCE 206 6 G...

Page 593: ...dicator The Pitot line is connected to GDC 74A unit and to the standby airspeed indicator The VFR Night configuration presents HEAT Pitot in case of ice formation on Pitot Alternate static port that is an alternative air inlet for the static system It is located in the cabin on the instrument panel LH side Refer to Figure 2 Number Item 1 Pitot 2 Static and total pressure drainage point 3 Standby a...

Page 594: ...Page 2 2nd Edition Rev 0 34 10 PITOT STATIC SYSTEM DESCRIPTION AND OPERATION Figure 1 Pitot static system ...

Page 595: ... mounted on the leading edge of the RH wing As the aircraft approaches a stall the sensor activates the acoustic alarm system made up of a cabin installed horn In case of removal or replacement of the stall sensor it is recommended to reinstall it so as to be effective in detecting stall condition from 1 to 3 kts before the stall speed indicated in the Flight Manual Never lacquer the stall warning...

Page 596: ...d indication incorrect Indicator fails Replace indicator Water not drained Drain the static system System leakage Perform system leak test Vertical speed Pointer doesn t set on zero Aging of diaphragm Replace indicator Altimeter indication incorrect Indicator fails Replace indicator Water not drained Drain the static system System leakage Perform system leak test High altimeter reading Static pres...

Page 597: ...OT STATIC SYSTEM MAINTENANCE PRACTICES MAINTENANCE PRACTICES This Chapter contains the following maintenance tasks description Instruments replacement Pitot Static System Leak test Pitot Static System drainage Pitot Static System cleaning ...

Page 598: ...w the attaching screws which fix the instrument to the aluminum panel Hold firmly the instrument by hand during removal 4 Clear the instrument of the instrument panel 5 Place into position the new overhauled unit in correspondence of the instrument panel cut out 6 Install the attaching screws which fix the instrument to the aluminum panel Hold firmly the instrument by hand during installation Do n...

Page 599: ...tests are listed follow them in order to avoid Air Data Instruments damages Pressure applied during tests and its rate of change must not exceed limits imposed by instruments manufacturers After testing do not forget to restore the whole system to its operating configuration Tools Item Quantity Part Number Notes Pitot static tester 1 ADTS500 by DRUCK or equivalent equipemnt Pitot tube adaptor 1 Co...

Page 600: ... Slowly apply pressure to Pitot tube until tester s display indicates an airspeed of 40 kts Wait for pressure to get steady Remember that pressure rate of increase must not exceed airspeed indicator s limits 4 Compare the speed indicated by Pitot tester with the one indicated by airplane s speed indicator Check that allowable tolerances listed in Table 1 are not exceeded in a 1 min pressure applic...

Page 601: ...leakage Refer to Figure 2 4 Slowly apply vacuum to static ports until tester s display indicates an altitude of 1000 ft Wait for pressure to get steady Remember that pressure s rate of change must not exceed altimeter s limits 5 Compare the altitude indicated by static tester with the one indicated by airplane s altimeter Check that allowable tolerances listed in Table 2 are not exceeded in a 1 mi...

Page 602: ... with a parallel path with a dedicated filter which allows catching the moisture present in the air in order not to affect the instruments The following steps describe the procedure to check for dirt and replace if necessary the mentioned filter water trap Procedure Step no Task description Additional info References 1 Engage parking brake 2 Remove pilot seat 3 Identify water trap Refer to Figure ...

Page 603: ...ir compressor provided with oil separator 1 Commercial Procedure Step no Task description Additional info References 1 Engage parking brake 2 Set ELECTRIC MASTER switch and PITOT HEAT switch OFF If installed 3 Pull out PITOT HEAT breaker LH breaker panel 4 Remove the instruments panel upper cover 5 Remove rubber tubes from the rear of each of the instruments connected to Pitot system and static sy...

Page 604: ...2nd Edition Rev 0 34 10 PITOT STATIC SYSTEM MAINTENANCE PRACTICES Step no Task description Additional info References 10 Perform a static leak test See 34 10 pag 204 11 Install the instruments panel upper cover ...

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Page 606: ...w A compass correction card is provided Heading information is provided by directional gyro indicator An attitude indicator informs the pilot of the orientation of the aircraft relative to earth It indicates pitch fore and aft tilt and bank side to side tilt The turn and bank indicator shows the rate of turn and the coordination slip or skid of the turn The rate of turn is indicated from a rate gy...

Page 607: ...E AND HEATING MAINTENANCE PRACTICE MAINTENANCE PRACTICES This Chapter contains the following maintenance tasks description Magnetic compass replacement Magnetic compass compensation Attitude indicator replacement Directional gyro replacement ...

Page 608: ...rocedure Step no Magnetic compass replacement Task description Additional info References 1 Remove the nuts that retain the magnetic compass to the windshield strut 2 Clear the compass of its seat 3 Put into position the new overhauled compass 4 Fix the two attaching nuts 5 Perform the compensation procedure ...

Page 609: ...magnetization of the airframe itself This is often evidenced by excessive uncompensated compass error more than 30 35 degrees Center windshield post becoming magnetized can lead to compensation problems Degaussing the airframe component will solve this problem In flight compensation will achieve the best results Operators should consider removing any jewelry while compensating compasses Such thing...

Page 610: ... dot on the compensator frame Use a brass or other non ferrous material screwdriver when making compensator adjustments 3 Head aircraft on magnetic North heading Adjust N S adjustment screw until compass reads exactly North 4 Head aircraft on magnetic East heading Adjust E W adjustment screw until compass reads exactly East 5 Head aircraft on magnetic South heading Note the resulting South error A...

Page 611: ...y hand during removal 5 Clear of the instrument of the instrument panel 6 Place into position the new overhauled unit in correspondence of the instrument panel cut out 7 Install the attaching screws which fix the instrument to the aluminum panel Hold firmly the instrument by hand during installation Do not over tighten screws to avoid instrument case damage 8 Connect instrument electrical wires om...

Page 612: ... AND HEATING MAINTENANCE PRACTICE Step no Task description Additional info References 13 Ensure that gyro warning flag is out of view Attitude indicator is fed 14 Check for attitude indicator alignment use Pull to Cage knob to erect gyroscope ...

Page 613: ...tion the new overhauled unit in correspondence of the instrument panel cut out 7 Install the attaching screws which fix the instrument to the aluminum panel Hold firmly the instrument by hand during installation Do not over tighten screws to avoid instrument case damage 8 Connect instrument electrical wires at the rear of the instrument Be sure that the electrical cables don t have radius of curva...

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Page 615: ...and map database for use by the pilot flight crew Area navigation functions using the determined position velocity and stored navigation data Approach navigation functions including WAAS precision approaches and the associated database Interfacing with other flight instruments such as autopilot CDI HIS including OBS indicators The VOR ILS localizer receiver tuning from 108 00 to 117 95 MHz in 50 k...

Page 616: ...o the Garmin GI 106A VOR LOC GS GPS indicator see figure below Figure 1 Garmin GI 106A VOR LOC GS indicator GI 106A displays following information Rectilinear needle movements Integral GPS NAV and VLOC mode lights Integral resolver for VOR GPS OBS feedback VOR LOC GPS needle TO FROM arrow NAV warning flag Glideslope needle ...

Page 617: ...rse approach Automatic display of station ID by decoding Morse code Interfaces to most CDI w resolver HSI and autopilot systems VOR receiver displays To or From radial of the active channel VOR monitor displays From radial of the standby channel Back course annunciator output LOC enable annunciator output Internal RF diplexor Active and standby flip flop frequencies DME tuning and data display The...

Page 618: ...antenna The GPS receiver is embodied within the GNS 430W 530W it provides precise position velocity and time measurements for enroute terminal and non precision approaches The position velocity and time determinations are computed by the receiver based on satellite signals provided by the Global Positioning System GPS satellite constellation ...

Page 619: ...osition and number of pulses transmitted Mode C replies include framing pulses and encoded altitude Mode S interrogations are selective The Mode S transponders can respond to a single directed interrogation from the ground station or another aircraft Ground stations interrogate Mode S Transponders individually using a 24 bit ICAO Mode S address which is unique to the particular aircraft In additio...

Page 620: ...Page 6 2nd Edition Rev 0 34 20 POSITION DETERMINING DESCRIPTION AND OPERATION NAV equipment antennas Following figure shows the NAV equipment antennas location ...

Page 621: ...ed to the applicable unit and based on the fault messages displayed ATA 34 30 GNS 430W 530W Troubleshooting Trouble Likely cause Action required The unit does not power on The unit is not getting power to the main connector Make sure power is connected to the main connector Check circuit breakers and avionics switch The unit does not receive signals Antenna disconnected Check antenna connection An...

Page 622: ...ions Mix NAV Audio With Com The sidetone level is too low or too high Wrong type of headsets or level needs adjustment Check the Sidetone Level Adjustment Intercom failure Control input not connected The intercom select input must be pulled to ground to turn on the intercom function Active frequency signal present Change the active frequency The active frequency has priority No voice activation or...

Page 623: ... 330 Troubleshooting Trouble Likely cause Action required The unit does not power on The unit is not getting power Check power connections breakers and avionics switch Faulty electrical wiring Check wiring Main board fuse failure Unit repair required fuse replacement No transponder reply Low output power Check antenna connections replace antenna if needed Antenna disconnected Panel lighting failur...

Page 624: ...ce tasks description GNS 430W 530W unit removal installation GNS 430W periodic maintenance GNS 530W periodic maintenance SL30 unit removal installation SL30 periodic maintenance GPS antenna removal installation Transponder removal installation Transponder periodic maintenance Transponder antenna removal installation VHF NAV antenna replacement ...

Page 625: ...ectors Verify on the unit that all screws are secure and in place 2 Verify that the display face is clean 3 Verify that external surfaces have no dents scratches etc 4 Inspect for broken or bent pins on external connectors 5 Inspect wires and cables for breaks in insulation or tears 5 Slide the unit into the rack straight in until it stops about 1 inch short of the final position It may be necessa...

Page 626: ...e 430W unit includes an internal battery that will last 5 to 8 years The battery is used for internal time clock and GPS system information Regular planned replacement is not necessary The 430W unit will display a Low Battery and Unit Needs Service message when replacement is required Once the low battery message is displayed the battery should be replaced within 1 to 2 months If the battery is no...

Page 627: ...urs The backlight lamp may dim and the display may not perform as well in direct sunlight conditions over time The user must determine by observation when the display brightness is not suitable for use Contact Garmin when the backlight lamp requires service Battery Replacement The unit has an internal battery used for the real time clock and GPS system information that will last approximately 5 8 ...

Page 628: ... at the end of the cam lock travel or the unit may be damaged 4 With the cam lock fully disengaged pull the unit straight out holding onto the sides of the bezel It is not recommended that you pull the unit out by the rotary knobs 5 Unplug the connectors 6 Put in position the new overhauled unit plugging the electrical connectors Verify that the display face is clean Verify that external surfaces ...

Page 629: ...s it easy to exceed the allowable torque on the cam lock resulting in damage to the unit The unit will be pulled into the frame securing the unit and the connectors Do NOT overtighten The back of the bezel must be flush to the mounting tube If the cam lock is hard to turn or the unit does not seat fully the unit is probably binding and the mounting tube should be checked 11 Perform functional chec...

Page 630: ...The SL30 unit is designed to not require any regular general maintenance Cleaning the font panel The front bezel keypad and display can be cleaned with a soft cotton cloth dampened with clean water DO NOT use any chemical cleaning agents Care should be taken to avoid scratching the surface of the display ...

Page 631: ...Page 207 2nd Edition Rev 0 34 20 POSITION DETERMINING MAINTENANCE PRACTICES INTENTIONALLY LEFT BLANK ...

Page 632: ...ng bolts Remove any interior paint in the area where the fixing nuts and washers are placed to assure a good ground 7 Place antenna over mounting holes using the fours screw holes to align the antenna Insert the four screws Make sure that GPS antenna is fitted with the O ring Secure the O ring in the O ring groove on the underside of the antenna See Figure 2 8 Tighten nuts with washers apply torqu...

Page 633: ...Page 209 2nd Edition Rev 0 34 20 POSITION DETERMINING MAINTENANCE PRACTICES Figure 2 GPS Antenna ...

Page 634: ...ed unit plugging the connectors Verify on the unit that all screws are secure and in place 2 Verify that the display face is clean 3 Verify that external surfaces have no dents scratches etc 4 Inspect for broken or bent pins on external connectors 5 Inspect wires and cables for breaks in insulation or tears 5 Slide the unit into the rack straight in until it stops about 1 inch short of the final p...

Page 635: ...Page 211 2nd Edition Rev 0 34 20 POSITION DETERMINING MAINTENANCE PRACTICES 8 TRANSPONDER PERIODIC MAINTENANCE No scheduled servicing tasks are required on the GTX 328 330 unit ...

Page 636: ...f the fuselage skin 6 Make sure that the internal skin surface is not painted in correspondence of the fixing bolts Remove any interior paint in the area where the fixing nuts and washers are placed to assure a good ground 7 Put in position the new repaired antenna 8 Tighten fixing nuts with washers as per standard values to secure the antenna See standard torque values as addressed on Chapter 20 ...

Page 637: ...Page 213 2nd Edition Rev 0 34 20 POSITION DETERMINING MAINTENANCE PRACTICES INTENTIONALLY LEFT BLANK ...

Page 638: ...s loosen hex screw 8 Unscrew completely radiators from antenna 9 Unscrew and pull ring nut to remove connector from antenna 10 Remove antenna from cover 11 Unscrew bolts to uninstall antenna from its support 12 Replace antenna if needed 13 Install antenna on support UNI5737 4x25 bolt 2x UNI6592 4 washer 4x UNI7473 4 self locking nut 2x NOTE REPLACE ALWAYS THE SELF LOCKING NUTS WITH NEW ONES 14 Ins...

Page 639: ...POSITION DETERMINING MAINTENANCE PRACTICES Step no Task description Additional info References 20 Apply mastic in correspondence of radiators holes and cove rear holes use sealant Type 2 21 Paint See Chapter 11 for color specification ...

Page 640: ...Page 216 2nd Edition Rev 0 34 20 POSITION DETERMINING MAINTENANCE PRACTICES INTENTIONALLY LEFT BLANK ...

Page 641: ...2nd Edition Rev 0 Chapter 51 Standard Practices Structures ...

Page 642: ...2nd Edition Rev 0 INTENTIONALLY LEFT BLANK ...

Page 643: ... Rev 0 6 2nd Edition Rev 0 51 10 1 2nd Edition Rev 0 2 2nd Edition Rev 0 3 2nd Edition Rev 0 51 20 1 2nd Edition Rev 0 2 2nd Edition Rev 0 3 2nd Edition Rev 0 4 2nd Edition Rev 0 5 2nd Edition Rev 0 200 2nd Edition Rev 0 201 2nd Edition Rev 0 202 2nd Edition Rev 0 203 2nd Edition Rev 0 204 2nd Edition Rev 0 51 30 1 2nd Edition Rev 0 2 2nd Edition Rev 0 3 2nd Edition Rev 0 4 2nd Edition Rev 0 5 2nd...

Page 644: ...Page 2 2nd Edition Rev 0 51 TOC Section Page Edition Revision 51 40 1 2nd Edition Rev 0 2 2nd Edition Rev 0 ...

Page 645: ...00 STRUCTURE GENERAL 1 51 10 STRUCTURE CLASSIFICATION 1 51 20 DAMAGE CLASSIFICATION AND REPAIRS 1 MAINTENANCE PRACTICES 200 1 WINDSHIELD AND CANOPY REPAIR 201 2 COMPOSITE STRUCTURAL COMPONENTS CRACKS STOPPING 204 51 30 CONSUMABLE MATERIALS 1 51 40 ALIGNMENT CHECK 1 ...

Page 646: ...are constructed with a central spar to which front and rear ribs are jointed Wrapped around aluminum stressed skin panels cover all the structures Steel alloy attachments connect left and right wing to each other The ailerons control is actuated manually through the control wheels or automatically through the autopilot system if installed The ailerons are balanced by balance masses The ailerons ar...

Page 647: ...els Nose cone and tail fairings are of composite material Cabin and baggage compartment floor is a warping of beams and keelsons supporting the seats guides baggage and other components Seats access occur by a sliding canopy In tail cone two spar frames support the horizontal and vertical empennages attachments MLG ATTACHMENT WING ATTACHMENT CANOPY BAGGAGE COMPARTEMENT INTERNAL STRUCTURE TAIL CONE...

Page 648: ...up of a twin spar with aluminum alloy stressed skin Rudder providing directional control of the airplane is made up of aluminium alloy The rudder is connected to the vertical tail at two hinge points REAR SPAR TIP RUDDER TIP FRONT SPAR FWD ATCH REAR ATCHs RIBs RUDDER RIBs RUDDER SPAR Figure 3 Vertical empennage structure ...

Page 649: ... all moving type stabilator its structure consists of a twin spar to which front and rear ribs are joined and it is covered by stressed aluminum alloy skin The trim tab completes the assy TRIM TAB RIB s REAR SPAR LEADING EDGE FRONT SPAR FRONT RIB TIP Figure 4 Stabilator structure ...

Page 650: ...ontally opposed with 1352 c c of overall displacement liquid cooled cylinder heads ram air cooled cylinders carburetor integrated reduction gear box with torsional shock absorber and overload clutch Propellers are made by Hoffmann propeller They are fitted with two wood composite blades and aluminum hub Figure 5 Engine mount and propeller ...

Page 651: ...RE GENERAL LANDING GEAR Main landing gear is provided by spring steel directly fix by plates to the central main bean of aircraft fuselage Nose landing gear have a fix leg with a dumper Figure 6 Nose landing gear Figure 7 Main landing gear ...

Page 652: ... Primary structure structural components or assemblies which are necessary to sustain design ultimate flight and ground loads or which provide essential support necessary to maintain airplane safe operation Secondary structure structural components which conveys loads paths from their point of application to the primary structure Tertiary structure structural components which does not contribute t...

Page 653: ... X VERTICAL FIN FUSELAGE FAIRING X NAV VOR ANTENNA FAIRING X WINDSHIELD AND CANOPY X FLOOR PANELS X FLOOR BEAMS X WINGS X WINGS SKIN X WINGS INSPECTION CAPS X INTEGRATED FUEL TANKS X FLAPS X AILERONS X ENGINE MOUNT X LEADING EDGE OUTBOARD X LEADING EDGE INBOARD X STABILATOR X STABILATOR SKIN X STABILATOR LEADING EDGE X STABILATOR TRIM TAB X STABILATOR TIP X VERTICAL FIN X VERTICAL FIN TIP X VERTIC...

Page 654: ...inspection is widely used for detecting and examining aircraft surface cracks which are particularly important because of their relationship to structural failures As general rule Clean the areas or surface of the parts to be inspected Remove any contaminates that might hinder the discovery of existing surface indications Do not remove the protective finish from the part or area prior to inspectio...

Page 655: ...est response therefore only qualified personnel should perform this test Examine castings and machined parts for cracks if necessary use a non destructive test method Check rivets for security cracked or flaking paint is usually a sign of rivet disturbance Care must be applied to the secondary damages likely to occur when a shock is sustained or when weakening of the structure allows for fatigue i...

Page 656: ...ructure and application No crack should be regarded as negligible until the damage limits for the affected structure have been determined True crack length determination will generally require some form of Non Destructive Testing such as Eddy Current or Fluorescent penetrants Holes punctures penetrations or cutouts that breach the complete thickness of the material and is fully surrounded by undam...

Page 657: ...erial should not be used since steel or emery particles become embedded in the softer material causing corrosion After cleaning surface corrosion parts must be treated with an anti corrosion finish prepared as follows 4 liter solution containing 10 cromic acid with 20 drops of battery electrolyte Accurate brushing with a sturdy fiber brush will rid of most of the corrosion and insure that the anti...

Page 658: ...turer Secondary and tertiary structural components Damage to secondary and tertiary metal structure must be referred to the manufacturer Damage on secondary and tertiary structural composite components may be corrected by a simple corrective action procedure such as stop drilling cracks but consideration should be given to the economic viability of repair or replacement of the components If the da...

Page 659: ...AMAGE CLASSIFICATION AND REPAIRS MAINTENANCE PRACTICES MAINTENANCE PRACTICES This Chapter contains the following maintenance tasks description Windshield and canopy Secondary and tertiary composite structural components cracks stopping ...

Page 660: ...not the equal of a new section either optically or structurally At the first sign of crack development drill a small hole with a 1 8 inch drill at the extreme ends of the cracks as shown in figure below This allows to localize the cracks and to prevent further splitting by distributing the strain over a large area If the cracks are small less than 1 inch stopping them with drilled holes will usual...

Page 661: ... of the crack or hole Bevel the edges as shown in figure below If the section to be repaired is curved shape the patch to the same contour by heating it in an oil bath at a temperature of 248 to 302 F or it may be heated on a hot plate until soft Boiling water should not be used for heating Coat the patch evenly with plastic solvent adhesive and immediately place it over the hole Maintain a unifor...

Page 662: ...patch slightly thicker than the material being repaired and similarly bevel its edges Install patches in accordance with figure below Heat the plug until soft and press it into the hole without cement and allow to cool to make a perfect fit Remove the plug coat the edges with adhesive and then reinsert in the hole Maintain a firm light pressure until the cement has set Sand or file the edges level...

Page 663: ... holes will usually suffice until replacement can be made At the first sign of crack development drill a small hole with a 1 8 inch drill at the extreme ends of the cracks as shown in figure below This allows to localize the cracks and to prevent further splitting by distributing the strain over a large area Apply sealant type 2 see Chapter 51 30 if required to prevent moisture from entering the m...

Page 664: ...ces of other Chapters are given reference numbers which correspond to the reference item numbers assigned to the consumable materials within this Section Certain consumable materials if used incorrectly can be dangerous When they are used always obey to all the manufacturer s safety precautions given in the safety card either supplied by the material manufacturer or written on the container Some p...

Page 665: ...uct down the internal threads to the bottom of the hole Assemble and tighten as required For Sealing Applications apply a 360 bead of product to the leading threads of the male fitting leaving the first thread free Force the material into the threads to thouroughly fill the voids For bigger threads and voids adjust product amount accordingly and apply a 360 bead of product on the female threads al...

Page 666: ...ading threads of the male fitting leaving the first thread free Force the material into the threads to thoroughly fill the voids For bigger threads and voids adjust product amount accordingly and apply a 360 bead of product on the female threads also Disassembly Remove with standard hand tools In rare instances where hand tools do not work because of excessive engagement length apply localized hea...

Page 667: ...ct can be removed with a combination of soaking in a Loctite solvent and mechanical abrasion such as a wire brush Sealant Type 1 Sikaflex 221 multi purpose one component adhesive sealant Surface preparation Surfaces must be clean dry and free from all traces of grease oil and dust Application cartridge Cut off the tip of the nozzle to suit joint width and apply the sealant into the joint with a su...

Page 668: ... with time Limitations Avoid application below 40 F 5 C and above 105 F 40 C Do not apply on frozen or wet surfaces or through standing water Do not apply over silicones or in the presence of curing silicones Contact with alcohol or alcohol containing solvents will prevent cure Deliberate misuse by inhalation of vapors may be harmful or fatal Sealant Type 2 JLF TOTALSEAL 34 One component polyureth...

Page 669: ...der the effect of air humidity the film forms very quickly once the product has been applied After one day the mastic is already hard to a thickness of 3 mm The product provides an anti vibration effect it is elastic can be polished and has no corrosive effects Processing temperature 5 C to 35 C Cleaner Solvents like MEK for uncured material as well as for cleaning and degreasing bonding area Do n...

Page 670: ...temperatures below 40 F 5 C or above 105 F 40 C Overpainting Not allowed Adhesive Tesa Professional Spray Glue Permanent p n 60021 or 60020 Application Shake can well before use and remove any dried on glue from the nozze For new applications test suitability by gluing a sample The parts to be bonded must be dry and free from dust and grease Cleaning with tesa INDUS TRY CLEANER 60040 recommended A...

Page 671: ...s the external line B On the top of engine reducer To verify it is necessary to remove the upper sie of engine nacelle C C On stabilator back it is the rivet in common between the nailing line of the tip and the nailing line of tubular spar skin C C On stabilator back it is the rivet in common between the nailing line of external rib and the rear spar D D On the rudder it is the rivet in the upper...

Page 672: ...Page 2 2nd Edition Rev 0 51 40 ALIGNMENT CHECK GENERAL C C A A A B B C C C C D D D Figure 8 Alignment ...

Page 673: ...Page 3 2nd Edition Rev 0 51 40 ALIGNMENT CHECK GENERAL INTENTIONALLY LEFT BLANK ...

Page 674: ...2nd Edition Rev 0 Chapter 52 Canopy ...

Page 675: ...2nd Edition Rev 0 INTENTIONALLY LEFT BLANK ...

Page 676: ...dition Rev 0 202 2nd Edition Rev 0 203 2nd Edition Rev 0 52 10 1 2nd Edition Rev 0 2 2nd Edition Rev 0 3 2nd Edition Rev 0 200 2nd Edition Rev 0 201 2nd Edition Rev 0 52 20 1 2nd Edition Rev 0 2 2nd Edition Rev 0 200 2nd Edition Rev 0 201 2nd Edition Rev 0 202 2nd Edition Rev 0 203 2nd Edition Rev 0 204 2nd Edition Rev 0 205 2nd Edition Rev 0 206 2nd Edition Rev 0 207 2nd Edition Rev 0 208 2nd Edi...

Page 677: ...Page 2 2nd Edition Rev 0 52 LOEP INTENTIONALLY LEFT BLANK ...

Page 678: ... 1 CANOPY HANDLE SUPPORT INSTALLATION 201 2 CANOPY REPAIR 203 52 10 DOOR SAFETY LOCK GENERAL 1 MAINTENANCE PRACTICES 200 1 EMERGENCY LOCK REPAIR 201 52 20 CANOPY REMOVAL INSTALLATION 1 MAINTENANCE PRACTICES 200 1 CANOPY REMOVAL INSTALLATION PROCEDURE 2 BEARING TRACK REMOVAL INSTALLATION PROCEDURE ...

Page 679: ...e it allows the opening and closing of cockpit It is made of Plexiglas and resins It can be closed through three lockers two on the side of canopy and one on the top Canopy presents two side windows in the side and is linked to the windshield It can be handle from both sides Figure 1 Canopy and windshield structure Figure 2 Canopy ...

Page 680: ...Page 2 2nd Edition Rev 0 52 00 CANOPY GENERAL Figure 3 Windshield and canopy ...

Page 681: ...Page 200 2nd Edition Rev 0 52 00 CANOPY MAINTENANCE PRACTICE MAINTENANCE PRACTICES This Chapter contains the following maintenance tasks description Canopy handle support installation Canopy repair ...

Page 682: ...ke on ON 4 Remove RH and LH canopy handle and screw from the canopy Refer to Figure 4 5 Copy the holes from the canopy on the support 6 Apply Sicaflex 221 under the support surface 7 Install the RH Canopy handle support P N 22 4 333 2 Refer to Figures 5 and 6 8 Operate the same instructions for the other side 9 Reinstall RH and LH canopy handle and screw 10 Check the correctly functioning of the c...

Page 683: ...Page 202 2nd Edition Rev 0 52 00 CANOPY MAINTENANCE PRACTICE Figure 6 Canopy handle support Figure 7 Canopy handle support ...

Page 684: ...NOPY REPAIR Procedure Step no Task description Additional info References 1 Park the aircraft in a closed hangar 2 Remove the ignition key and the negative terminal of the battery 3 Remove the strip of sealant mastic and the rivets 4 Clean the affected area and paint ...

Page 685: ...Page 1 2nd Edition Rev 0 52 10 DOOR SAFETY LOCK GENERAL 52 10 CANOPY SAFETY LOCK GENERAL On the canopy there are three safety lock two on the lateral sides and one on the top Figure 8 Safety locks ...

Page 686: ...Page 2 2nd Edition Rev 0 52 10 DOOR SAFETY LOCK GENERAL Figure 9 Lateral safety lock Figure 10 Upper safety lock external ...

Page 687: ...Page 3 2nd Edition Rev 0 52 10 DOOR SAFETY LOCK GENERAL Figure 11 Upper safety lock internal ...

Page 688: ...Page 200 2nd Edition Rev 0 52 10 DOOR SAFETY LOCK MAINTENANCE PRACTICE MAINTENANCE PRACTICES This Chapter contains the following maintenance tasks description Emergency lock repair ...

Page 689: ...rocedure Step no Task description Additional info References 1 Unscrew screws in the lower part of emergency lock Refer to Figure 12 2 Put off the pin that link the internal and external part 3 Replace 4 Reassemble the emergency lock 5 Perform final check lock unlock the canopy Figure 12 Safety lock ...

Page 690: ...d Edition Rev 0 52 20 CANOPY REMOVAL INSTALLATION GENERAL 52 20 CANOPY REMOVAL INSTALLATION GENERAL Refer to the following instructions to replace the canopy and any bearing track Figure 13 Canopy typical layout ...

Page 691: ...Page 2 2nd Edition Rev 0 52 20 CANOPY REMOVAL INSTALLATION GENERAL INTENTIONALLY LEFT BLANK ...

Page 692: ... 52 20 CANOPY REMOVAL INSTALLATION MAINTENANCE PRACTICES MAINTENANCE PRACTICES This Chapter contains the following maintenance tasks description Canopy removal installation procedure Bearing track removal installation procedure ...

Page 693: ...to Fig 14 2 Push the LH and RH Emergency Locks out of the housing Refer to Fig 15 3 Remove the screws Refer to Fig 16 4 Loosen the nut behind the canopy key lock Refer to Fig 17 5 Extract the canopy from the guide rail lifting up the canopy Refer to Fig 18 6 To install the canopy reverse mentioned steps described in this table 7 Make sure that the emergency locks are in place and the canopy slides...

Page 694: ...Page 202 2nd Edition Rev 0 52 20 CANOPY REMOVAL INSTALLATION MAINTENANCE PRACTICES Figure 14 Locking pin Figure 15 Emergency locks removal ...

Page 695: ...Page 203 2nd Edition Rev 0 52 20 CANOPY REMOVAL INSTALLATION MAINTENANCE PRACTICES Figure 16 Screws removal Figure 17 Canopy key lock ...

Page 696: ...Page 204 2nd Edition Rev 0 52 20 CANOPY REMOVAL INSTALLATION MAINTENANCE PRACTICES Figure 18 Canopy lifting direction ...

Page 697: ...Page 205 2nd Edition Rev 0 52 20 CANOPY REMOVAL INSTALLATION MAINTENANCE PRACTICES INTENTIONALLY LEFT BLANK ...

Page 698: ...e the screws from the travel stop Refer to Fig 19 2 Remove the guide rail moving it backward Refer to Fig 20 3 In order to remove the bearing track unscrew the allen screws and bolts Refer to Fig 21 4 Replace the bearings bolts and self locking nuts Refer to Fig 22 5 To install the guide rail on the fuselage reverse mentioned steps 6 Make sure that there is not play between bearings and guide rail...

Page 699: ...Page 207 2nd Edition Rev 0 52 20 CANOPY REMOVAL INSTALLATION MAINTENANCE PRACTICES Figure 19 Travel stop Figure 20 Allen screws and bolts ...

Page 700: ...Page 208 2nd Edition Rev 0 52 20 CANOPY REMOVAL INSTALLATION MAINTENANCE PRACTICES Figure 21 Bearings ...

Page 701: ...Page 209 2nd Edition Rev 0 52 20 CANOPY REMOVAL INSTALLATION MAINTENANCE PRACTICES INTENTIONALLY LEFT BLANK ...

Page 702: ...2nd Edition Rev 0 Chapter 53 Fuselage ...

Page 703: ...2nd Edition Rev 0 INTENTIONALLY LEFT BLANK ...

Page 704: ...ion Page Edition Revision 53 LOEP 1 2nd Edition Rev 0 2 2nd Edition Rev 0 53 TOC 1 2nd Edition Rev 0 53 10 1 2nd Edition Rev 0 2 2nd Edition Rev 0 3 2nd Edition Rev 0 200 2nd Edition Rev 0 201 2nd Edition Rev 0 202 2nd Edition Rev 0 202 2nd Edition Rev 0 ...

Page 705: ...Page 2 2nd Edition Rev 0 53 LOEP INTENTIONALLY LEFT BLANK ...

Page 706: ...Page 1 2nd Edition Rev 0 53 TOC CHAPTER 52 TOC 53 10 FUSELAGE 1 DESCRIPTION AND OPERATION 1 MAINTENANCE PRACTICES 200 1 TAIL FAIRING REPLACEMENT 201 ...

Page 707: ...g s main spar 1 wing s rear spar 2 tail cone 4 main landing gear 5 engine mount 3 flap torque tube 7 stabilator bellcrank 6 throttle support 8 and pulley support for cable driven aileron control Seat supports and safety harness attachment points are also shown The aft part of the fuselage is constructed with an aluminum alloy semi monocoque structure Attachments to cabin truss is at the forward fi...

Page 708: ...ccess is through a sliding canopy made of composite material The canopy is fastened via three lock levers one at the top and two at each side Seats are made out of metal tubing framework with fabric covered foam padding The two seats can be independently adjusted by sliding backward and forward along rails fixed to cabin truss structure Seat release levers are located just below seat cushions Cabi...

Page 709: ...3 2nd Edition Rev 0 53 10 FUSELAGE DESCRIPTION AND OPERATION f Figure 3 Fuselage longitudinal stations The longitudinal Datum reference is the forward side of the engine s propeller flange without the spacer ...

Page 710: ...Page 200 2nd Edition Rev 0 53 10 FUSELAGE MAINTENANCE PRACTICES MAINTENANCE PRACTICES This Chapter contains the following maintenance tasks description Tail fairing replacement ...

Page 711: ... 4 Unscrew the two screws of the rear side of stabilator Refer to Figure 5 5 Remove the pins on both stabilator side Refer to Figure 6 6 Unfasten the two side of the stabilator Refer to Figure 5 7 Check the tail fairing and replace if necessary removing the eight crews Refer to Figure 7 8 Put the stabilator paying attention to the torque tube Refer to figure 7 9 Proceed to assemble the stabilator ...

Page 712: ...Page 202 2nd Edition Rev 0 53 10 FUSELAGE MAINTENANCE PRACTICES Figure 5 Rear side of stabilator Figure 6 Stabilator pin ...

Page 713: ...Page 203 2nd Edition Rev 0 53 10 FUSELAGE MAINTENANCE PRACTICES Figure 7 Tail fairing and torque tube Torque tube ...

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Page 715: ...Page 205 2nd Edition Rev 0 53 10 FUSELAGE MAINTENANCE PRACTICES INTENTIONALLY LEFT BLANK ...

Page 716: ...2nd Edition Rev 0 Chapter 55 Stabilator and Rudder ...

Page 717: ...2nd Edition Rev 0 INTENTIONALLY LEFT BLANK ...

Page 718: ...0 55 10 1 2nd Edition Rev 0 2 2nd Edition Rev 0 3 2nd Edition Rev 0 4 2nd Edition Rev 0 200 2nd Edition Rev 0 201 2nd Edition Rev 0 202 2nd Edition Rev 0 203 2nd Edition Rev 0 204 2nd Edition Rev 0 205 2nd Edition Rev 0 55 20 1 2nd Edition Rev 0 2 2nd Edition Rev 0 200 2nd Edition Rev 0 201 2nd Edition Rev 0 202 2nd Edition Rev 0 203 2nd Edition Rev 0 ...

Page 719: ...Page 2 2nd Edition Rev 0 55 LOEP INTENTIONALLY LEFT BLANK ...

Page 720: ...AND OPERATION 1 MAINTENANCE PRACTICES 200 1 STABILATOR REMOVAL INSTALLATION 201 2 TRIM TAB REMOVAL INSTALLATION 203 3 STABILATOR BALANCE MASS CHECK 200 55 20 RUDDER 1 DESCRIPTION AND OPERATION 1 MAINTENANCE PRACTICES 200 1 RUDDER REMOVAL INSTALLATION 201 2 CABLE TENSION CHECK 203 ...

Page 721: ...selage at the desired pitch setting The stabilator structure is made up by an aluminum spar to which a series of ribs are riveted It is covered by aluminum panels A trim tab provides stick force adjustment and longitudinal compensation through an electric actuator controlled by pilot Tab is split in two parts interconnected at the support brackets and attached to the stabilator through four extern...

Page 722: ...h as bellcranks pushrods supports and hinges can be easily accessed and inspected The aft bellcrank assembly consists of a steel tube 1 with welded horn assembly 2 attachment for stabilator control shaft 3 and balanced weight bellcrank 4 Counterweight is located at the end of a prong bolted to the torque tube and entering tail cone through the tail frame cut out Figure 2 Stabilator control Longitu...

Page 723: ... Rev 0 55 10 STABILATOR DESCRIPTION AND OPERATION 5 connected to supports and horn assembly 7 Actuator s motion is transmitted to an adjustable push pull rod 8 through a bellcrank 9 Figure 3 Torque tube and trim control ...

Page 724: ...Page 4 2nd Edition Rev 0 55 10 STABILATOR DESCRIPTION AND OPERATION INTENTIONALLY LEFT BLANK ...

Page 725: ...Page 5 2nd Edition Rev 0 55 10 STABILATOR DESCRIPTION AND OPERATION INTENTIONALLY LEFT BLANK ...

Page 726: ...ATOR DESCRIPTION AND OPERATION MAINTENANCE PRACTICES This Chapter contains the following maintenance tasks description Stabilator removal installation Stabilator trim tab removal installation Stabilator balance mass check Stabilator balance ...

Page 727: ... Remove the pins on both stabilator upper side and remove the two grains on stabilator bottom side Refer to Figure 6 6 Unfasten the two plane of the stabilator Refer to Figure 5 7 Check and if necessary repair or replace the stabilator Reverse procedure for reinstallation setting the torque value according to AMM ATA20 and applying a small amount of grease around the torque tube inside the stabila...

Page 728: ...Page 202 2nd Edition Rev 0 55 10 STABILATOR DESCRIPTION AND OPERATION Figure 5 Rear side of stabilator Figure 6 Stabilator pin ...

Page 729: ...ab rod Refer to Figure 4 4 Rotate the trim tab surface upward and remove the pins that link the trim tab and the stabilator Refer to Figure 8 5 Remove the trim tab and check it If necessary repair or replace Refe to figure 9 Reverse procedure for reinstallation setting the torque value according to AMM ATA20 and applying a small amount of grease on the hinges and trim tab connections Then check th...

Page 730: ...screw the bolts which fix the torque tube to stabilator mounting plates and remove the torque tube Fif 9 item 2 Reverse procedure for reinstallation setting the torque value according to AMM ATA20 and applying a small amount of grease on connections Figure 9 Stabilator torque tube assy NOTE During the 100 hours inspection of the integrity and bearing cap play of the stabilator attachments followin...

Page 731: ...void interference with the free rotation of the tailplane temporarily secure control rod to the stabilator support assy 3 Disconnect trim tab control rod 4 Disconnect trim tab to tabulator to avoid any relative movement Use adhesive tape to avoid any influence on balance 5 Secure trim tab to stabilatot to avoid any relative movement Use adhesive tape to avoid any influence on balance 6 Check for e...

Page 732: ... rudder The rudder composite tip can accommodate navigation and strobe lights The vertical stabilizer consists of a twin spar with wrap around stressed skin paneling An attachment plate 1 secures the vertical stabilizer s front spar to the penultimate tailcone frame while the rear spar is extended to attach directly into the last tailcone ordinate 2 The rudder consists of an aluminum alloy torque ...

Page 733: ...11 Rudder mass balancing 10 is placed on the rudder upper rib s horn To inspect this part it is necessary to remove the composite tip Control system layout is a steel cable driven and circuit terminates on rudder pedals and then on the nose steering lever Figure 11 Rudder and steering control Rudder pedals 1 are attached to two pushrods 3 that transmit steering motion to the nose gear leg through ...

Page 734: ...Page 200 2nd Edition Rev 0 55 20 RUDDER MAINTENANCE PRACTICES MAINTENANCE PRACTICES This Chapter contains the following maintenance tasks description Rudder removal installation Cable tension check ...

Page 735: ...ures in this chapter 3 Disconnect the control cables form Rubber bellcrank Refer to Figure 12 4 Remove the rudder tip fairing removing the rivets from LH and RH side Refer to Figure 13 5 Loose and remove the upper bolt Refer to Figure 14 6 Remove the rudder upward Reverse procedure for reinstallation setting the torque value according to AMM ATA20 and applying a small amount of grease on the hinge...

Page 736: ...Page 202 2nd Edition Rev 0 55 20 RUDDER MAINTENANCE PRACTICES Figure 13 Rudder fairing Figure 14 Rudder upper bolt ...

Page 737: ...ension must be checked periodically and adjusted to proper value using the turnbuckles Tension 20 daN 2 Pulley 5 condition and their smooth operation must also be checked To access levers and rudder pedals support remove cabin s central tunnel for speedier operation remove seats from railings ...

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Page 739: ...2nd Edition Rev 0 Chapter 56 Windows ...

Page 740: ...2nd Edition Rev 0 INTENTIONALLY LEFT BLANK ...

Page 741: ...tion Rev 0 2 2nd Edition Rev 0 56 TOC 1 2nd Edition Rev 0 56 10 1 2nd Edition Rev 0 2 2nd Edition Rev 0 3 2nd Edition Rev 0 4 2nd Edition Rev 0 200 2nd Edition Rev 0 201 2nd Edition Rev 0 202 2nd Edition Rev 0 203 2nd Edition Rev 0 204 2nd Edition Rev 0 205 2nd Edition Rev 0 206 2nd Edition Rev 0 ...

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Page 743: ...2nd Edition Rev 0 56 TOC CHAPTER 56 TABLE OF CONTENTS 56 10 WINDOWS 1 DESCRIPTION AND OPERATION 1 MAINTENANCE PRACTICES 200 1 WINDSHIELD REPLACEMENT 201 2 SIDE WINDOWS REPLACEMENT 200 3 CANOPY REPLACEMENT 200 ...

Page 744: ...lity is guaranteed by two side windows one on each side by a wide windshield that allows pilot and copilot an overall visual for every flight maneuver and by the two windows located on the canopy Windows are made of splinterless plexiglass GS 233 Windshield defrosting is accomplished by heating system make reference to Chapter 21 ...

Page 745: ...Page 2 2nd Edition Rev 0 56 10 WINDOWS DESCRIPTION AND OPERATION A Figure 1 fuselage and windows ...

Page 746: ...de windows made of acrylic plastics when damaged they are usually replaced unless the damage is minor and a repair would not be in the line of vision Repairs usually require a great deal of labor Replacement parts are readily available so replacement is normally more economical than repair ...

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Page 748: ...dition Rev 0 56 10 WINDOWS MAINTENANCE AND PRACTICES MAINTENANCE PRACTICES This Chapter contains the following maintenance tasks description Windshield replacement Side windows replacement Canopy windows replacement ...

Page 749: ...erences 1 Engage aircraft parking brake 2 Sand along windshield strips to remove painting so to locate rivets position 3 Remove rivets and mastic along the strips and record their position Refer to Figure 2 4 Remove strips and be careful to avoid deformations in that case strip replacement is required Refer to Figure 2 5 Remove windshield 6 Remove mastic all along the edges of windshield frame by ...

Page 750: ...e edges for windshield border painting by means of scotch tape Make reference to the windshield removed Apply adhesive masking tape 12 Sand windshield within adhesive masking tape edges and paint Black paint is required Apply paint on lower inner windshield surface 13 Apply a layer of mastic type 1 multi purpose sealant along the edges of windshield seat See Chapter 51 for mastic specifications 14...

Page 751: ...Page 203 2nd Edition Rev 0 56 10 WINDOWS MAINTENANCE AND PRACTICES Figure 2 Windshield ...

Page 752: ...o 3 3 Remove rivets and mastic along the edges by using cutter or suitable means 4 Remove windows 5 Fit new window to frame and mark window edges according with frame ones Use a permanent marker or suitable means 6 Trim windows frame as marked 7 Trace edges for window border painting by means of scotch tape Border painting must have a 10 mm width 8 Sand within scotch tape edges and paint Black pai...

Page 753: ...Page 201 2nd Edition Rev 0 56 10 WINDOWS MAINTENANCE AND PRACTICES Figure 3 Side window ...

Page 754: ...Figure 4 3 Remove rivets and mastic along the edges by using cutter or suitable means 4 Remove windows 5 Fit new window to frame and mark window edges according with frame ones Use a permanent marker or suitable means 6 Trim windows frame as marked 7 Trace edges for window border painting by means of scotch tape Border painting must have a 10 mm width 8 Sand within scotch tape edges and paint Blac...

Page 755: ...Page 201 2nd Edition Rev 0 56 10 WINDOWS MAINTENANCE AND PRACTICES Figure 3 Canopy window ...

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Page 758: ...Chapter 57 Wings ...

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Page 762: ...IONS CHAPTER 57 TABLE OF CONTENTS 57 10 WINGS 1 DESCRIPTION AND OPERATION 2 MAINTENANCE PRACTICES 200 1 WING REMOVAL 201 2 WING INSTALLATION 204 3 FLAPS REMOVAL 206 4 FLAPS INSTALLATION 207 5 AILERON REMOVAL 208 6 AILERON INSTALLATION 209 7 WING INSPECTION 211 ...

Page 763: ... a rear spar 6 that make up its front and rear vertical walls a series of ribs 7 and wrap around panels complete the structure Front and aft spars are complete with wing to fuselage attachment fittings 8 An integral fuel tank is a part of the wing s leading edge It feature two inspection panels at its root and tip side On the upper side of each tank there are the filler cap and the fuel level sens...

Page 764: ... ribs are joined Aluminum skin panels wrap around the flap structure Wing tips are moulded epoxy resin fibreglass reinforced At the inboard end of the wing s leading edge is an integrated aluminum fuel tank with individual filler cap Wing station 0 STA 0 is the intersection between the chord s plane and the a c plane of symmetry The transversal dihedral angle between the chord plane and the a c ho...

Page 765: ...Page 4 2nd Edition Rev 0 57 10 WINGS DESCRIPTION AND OPERATIONS Figure 2 Wing stations ...

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Page 767: ...GS MAINTENANCE PRACTICE MAINTENANCE PRACTICES This Chapter contains the following maintenance tasks description Wing removal Wing installation Wing flaps removal Wing flaps installation Aileron removal Aileron installation Wing inspection ...

Page 768: ...ge 5 Remove all wing fuselage fairings 6 Remove the fuel tank outlet inspection panel Unfasten and remove the fuel hose from the tank s outlet Place temporary a cap on line to prevent spillage Only for the left wing dis connect also the fuel return line 7 For the right wing disconnect stall warning system wires 8 Disconnect the fuel quantity sensor wiring and the position lights wiring 9 Disconnec...

Page 769: ...k description Additional info References 12 Remove wing fuselage pins Refer to Figure 5 13 While supporting the wing release at first the rear spar pin and then the two main spar s pins 14 Provide to replace pins and cap fuel lines in their original location Figure 3 Flaps ...

Page 770: ...Page 203 2nd Edition Rev 0 57 10 WINGS MAINTENANCE PRACTICE Figure 4 Aileron Figure 5 Wing fuselage pins ...

Page 771: ...2 Examine the main bolt assemblies Look espe cially for corrosion and deformation Replace bolts if required Procedure Step no Task description Additional info References 1 Set the Master Switch OFF and ground the aicraft 2 Apply jacking procedure See chapter 7 of this manu al 3 Install aileron on the wing 4 Install flap on the wing 5 Put the wing in position Refer to Figure 5 6 Install wing fusela...

Page 772: ...g sys tem wires 12 Install the fuel tank outlet inspection panel Fasten and install the fuel hose from the tank s outlet Only for the left wing connect also the fuel return line 13 Install all wing fuselage fairings 14 Install the wing s composite root leading edge NOTE On the wing to fuselage main fittings there is a gap of about 1mm between the wing s main spar lugs and the carrythrough This gap...

Page 773: ...on Additional info References 1 Fully extend the flaps and remove bolt washer and nut from the control rod end Refer to Figure 6 2 Support the Flap and disconnect the flap hinges by removing nuts washer and hinge bolts 3 Pull the flap straight back off the wing Figure 6 Wing flap attachments and mass balance ...

Page 774: ... bracket 4 Operate the flap several times to ascertain it operates freely 5 Align flap trailing edge with aileron to 0 trailing edge with usable means This position is 0 position for wing flaps 6 Check flaps travel limits UP 0 Down 40 7 Check correspondence between flaps posi tion flap position transmitter and flaps po sition indicator flaps fully retracted 0 2 and transmit ter lever to the rear e...

Page 775: ...description Additional info References 1 Disconnect the aileron control rod by removing nut washer and bolt Refer to Figure 7 2 Loosen the mass balance 3 Support the aileron and disconnect the inboard and outboard aileron hinges by removing nuts washers and hinge bolts Figure 7 Wing aileron attachments ...

Page 776: ...he wing and in stall bolts washers and nuts at the hinges 2 Connect mass balance 3 Connect aileron control rod to the ailer on with bolt washer and nut 4 Check aileron control cables tension See chapter 20 5 Align aileron trailing edge with wing tip trailing edge with usable means This position is 0 posi tion for ailerons 6 Check ailerons travel limits UP 20 and Down 15 2 ...

Page 777: ...Page 210 2nd Edition Rev 0 57 10 WINGS MAINTENANCE PRACTICE Figure 8 RH Aileron ...

Page 778: ...on or rivets loosening No cracks defor mation and rivet loos ing are allowed Refer to Figures 9 and 10 3 Check for FWD AFT spar lack of cracks corrosions and deformations 4 Examine that wing and fuselage FWD AFT attachment points are free from damages corrosion or defor mations No deformation permit ted No corrosion permitted 5 Examine the main bolt assemblies Look especially for corrosion and def...

Page 779: ...Page 212 2nd Edition Rev 0 57 10 WINGS MAINTENANCE PRACTICE Figure 9 Wing upper surface Figure 10 Wing lower surface ...

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Page 782: ...2nd Edition Rev 0 Chapter 61 Propeller ...

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Page 784: ...ion 61 LOEP 1 2nd Edition Rev 0 2 2nd Edition Rev 0 61 TOC 1 2nd Edition Rev 0 2 2nd Edition Rev 0 61 10 1 2nd Edition Rev 0 2 2nd Edition Rev 0 100 2nd Edition Rev 0 200 2nd Edition Rev 0 201 2nd Edition Rev 0 202 2nd Edition Rev 0 203 2nd Edition Rev 0 204 2nd Edition Rev 0 ...

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Page 786: ...age 1 2nd Edition Rev 0 61 TOC CHAPTER 61 TABLE OF CONTENTS 56 10 PROPELLER 1 DESCRIPTION AND OPERATION 1 TROUBLESHOOTING 1 MAINTENANCE PRACTICES 200 1 PROPELLER REMOVAL 201 2 PROPELLER INSTALLATION 203 ...

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Page 788: ...Hoffmann Propeller and is all wood with composite reinforced leading edge and blade protective finished with special lacquer coating The following tables report propeller s main technical features Manufacturer Hoffmann propeller GmbH Model HO17GHM A 174 177C Number of blades 2 Diameter 1740 mm Type Fixed pitch Material Wood Figure 1 Propeller ...

Page 789: ...Page 2 2nd Edition Rev 0 61 10 PROPELLER DESCRIPTION AND OPERATION INTENTIONALLY LEFT BLANK ...

Page 790: ...Page 100 2nd Edition Rev 0 61 10 PROPELLER TROUBLESHOOTING TROUBLESHOOTING Make reference to the Owner s Manual No E0110 74 and to all the pertinent documents issued by Hoffman ...

Page 791: ...Page 200 2nd Edition Rev 0 61 10 PROPELLER MAINTENACE PRACTICES MAINTENANCE PRACTICES This Chapter contains the following maintenance tasks description Propeller removal Propeller installation ...

Page 792: ...ng unscrewing along the edges 5 Remove the spinner Refer to Figure 2 6 Remove screws holding spinner dome to spinner bulkhead 7 Remove safeting 8 Remove bolts that secure propeller to the hub Refer to Figure 3 NOTE REPLACE ALWAYS THE SELF LOCKING NUTS WITH NEW ONES 9 Pull slowly propeller off from its position NOTA After removal do not lay propeller down on its tip but always lay flat and away fro...

Page 793: ...Page 202 2nd Edition Rev 0 61 10 PROPELLER MAINTENACE PRACTICES Figure 2 Ogive Figure 3 Hub propeller screws ...

Page 794: ...ler flange with solvent of gasoline Both surfaces must be dry and clean Remove all surface defects Remove the shipping plugs and protective wrap if any 5 Check bolts for cracks rust propeller thread and cleanliness 6 Check spinner bulkhead for craks or deformations 7 Install spinner spacer and propeller Refer to Figure 4 8 Insert washers and fasten locknuts Bolt torque is 17NM 9 Safety all bolts 1...

Page 795: ...Page 204 2nd Edition Rev 0 61 10 PROPELLER MAINTENACE PRACTICES Figure 4 Propeller installation ...

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Page 798: ...Chapter 71 Power plant ...

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Page 802: ...WLING INSTALLATION 1 71 20 ENGINE MOUNT 1 DESCRIPTION AND OPERATION 1 MAINTENANCE PRACTICES 200 1 ENGINE MOUNT REMOVAL 201 2 ENGINE MOUNT INSTALLATION 202 71 30 AIR INTAKES 1 DESCRIPTION AND OPERATION 1 MAINTENANCE PRACTICES 200 1 AIR FILTER CLEANING AND REPLACEMENT 201 71 40 ENGINE DRAINAGE 1 DESCRIPTION AND OPERATION 1 MAINTENANCE PRACTICES 200 1 DRAINAGE HOSES REPLACEMENT 201 ...

Page 803: ...sists of a fiberglass nose and light alloy panels while the bottom part is partially made of fiberglass and aluminum Cowling top is easily removed by releasing four latches two on each side Removal of lower portion is just as easy by quick release of two side pins and two latches located on bottom Air circulation is provided by front openings in nose section and by an outflow area on the underside...

Page 804: ...on Rev 0 71 10 ENGINE COWLINGS DESCRIPTION AND OPERATION Ram air intake NACA Hinges Pin Cam Lock Alluminium FG Alluminium Oil radiator air intake Water radiator air intake Cabin heat air intake Figure 1 Engine cowling ...

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Page 806: ...Page 200 2nd Edition Rev 0 71 10 ENGINE COWLINGS MAINTENACE PRACTICES MAINTENANCE PRACTICES Engine cowling removal Engine cowling installation ...

Page 807: ... removal Task description Additional info References 1 Engage parking brake 2 Loosen the screws inside the engine cowling Refer to Figure 2 3 Remove the upper cowling 4 Remove the lateral pins of the lower cowling and loosen the screws in the down side Refer to Figure 3 5 Remove the lower cowling Figure 2 Upper engine cowling screws ...

Page 808: ...Page 201 2nd Edition Rev 0 71 10 ENGINE COWLINGS DESCRIPTION AND OPERATION Figure 3 Lower engine mount pins and screws ...

Page 809: ...ine cowling removal Task description Additional info References 1 Engage parking brake 2 Install both upper engine cowlings Refer to Figure 4 3 Install the lower engine cowling using pins and screws Refer to Figure 3 4 Install the upper engine cowling using screws Refer to Figure 2 5 Figure 4 Engine cowling inspection cap ...

Page 810: ... 71 20 ENGINE MOUNT DESCRIPTION AND OPERATION Tubular steel makes engine mount this truss has welded joints The engine mounting frame is provided with four mounting pads at firewall Bolts through the pads attach the engine mount to the engine nacelle Figure 5 Engine Assy ...

Page 811: ... mount to engine attachment 2 Engine mount to engine attachment 3 Engine mount to fire proof wing attachments 4 Engine mount to fire proof wing attachments 5 Engine mount to fire proof wing attachments 6 Engine mount to fire proof wing attachments Figure 6 Shock mount attachments ...

Page 812: ...Page 200 2nd Edition Rev 0 71 20 ENGINE MOUNT MAINTENANCE PROCESSES MAINTENANCE PRACTICES This Chapter contains the following maintenance tasks description Engine mount removal Engine mount installation ...

Page 813: ...rences 1 Engage parking brake 2 Remove engine cowlings See Chapter 54 3 Remove engine Refer to Chapter 72 Engine removal 4 Unscrew upper engine mount attachments Refer to Figure 4 5 Unscrew lower engine mount attachments Refer to Figure 4 6 Hold firmly engine mount MAY REQUIRE 2 OR MORE OPERATORS TO COMPLETE THIS PROCEDURE 7 Remove engine mount attachments ...

Page 814: ...ed No corrosion permitted No cracks permitted 2 Examine the main bolt assemblies Look espe cially for corrosion and deformation Replace bolts if required Hereinafter they are addressed instruction to install the engine assembly Installation Procedure Step no Engine mount installation Task description Additional info References 1 Engage parking brake 2 Align engine mount attachment holes with fire ...

Page 815: ...installation Task description Additional info References 5 Lower attachments Bolt AN4 25 2x Washer AN960 416 L 4x Self locking nut MS21042 4 2x Refer to Figure 4 NOTE REPLACE ALWAYS THE SELF LOCKING NUTS WITH NEW ONES 6 Apply a torque value of 10 N m Figure 7 Engine mount attachment points ...

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Page 817: ...carburetors both hot and cold air flow are conveyed to air box Cold air flow reaches air box through front air inlet Hot air flow instead comes from heat exchanger It is pos sible to mix cold and hot air flow acting on air box valve through the carburetor Air Inlet Air Inlet To Carburettor To Carburettor Figure 8 Carburetor heating system Air box heat exchanger valve Air filter ...

Page 818: ... 2 2nd Edition Rev 0 71 30 AIR INTAKES DESCRIPTION AND OPERATION When Carb Heat knob is on OFF position only cold air flow is sent to air box Moving knob backward allows a progressive hot air flow increases ...

Page 819: ...AIR INTAKES MAINTENANCE PRACTICES MAINTENANCE PRACTICES This Chapter contains the following maintenance tasks description Air filter cleaning and replacement The carburetor hating controls rigging procedures are addressed on Chapter 72 ...

Page 820: ...Refer to the procedure n 1 in this chapter 3 Unscrew the screws from air inlet Refer to Figure 9 4 Remove air inlet 5 Remove filter Refer to Figure 10 6 Clean filter with air gun or suitable means 7 Replace filter if needed 8 Insert filter into seat 9 Apply air inlet and screw to lock it 10 Install engine cowlings Refer to procedure n 2 in this chapter 11 Perform final check make sure that no exte...

Page 821: ...Page 202 2nd Edition Rev 0 71 30 AIR INTAKES MAINTENANCE PRACTICES Figure 9 Air inlet Figure 10 Air filter ...

Page 822: ...ION Engine drainage system provides three different drainage lines one per carbure tor Carburetor drainage line gathers fuel leakages in a drip tray then fuel is con veyed within hoses which passing through firewall ejects the overflow external ly Figure 11 Engine drainage air box carburetor drip tray FWD AFT oil tank ...

Page 823: ...ENGINE DRAINAGE DESCRIPTION AND OPERATION Air box drain system allows the expulsion of fluid derived from condensation drainage hoses follows the same path of carburetor drains one Oil tank drainage provides for oil overflow ejecting ...

Page 824: ...Page 200 2nd Edition Rev 0 71 40 ENGINE DRAINAGE MAINTENANCE PRACTICES MAINTENANCE PRACTICES This Chapter contains the following maintenance tasks description Drainage hoses replacement ...

Page 825: ...x on air box 5 Loosen serflex on hoses under RH and LH drip trays 6 Loosen serflex on oil tank 7 Remove fasteners and clamps and record hoses placement 8 Replace hoses if needed 9 Screw serflex on hoses under RH and LH drip trays and on air box 10 Place hoses as recorded during removal 11 Apply clamps and fasteners 12 Install engine cowlings Refer to this chapter 71 20 13 Perform a final check mak...

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Page 828: ...Chapter 75 Liquid cooling system ...

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Page 832: ...Il segnalibro non è definito DESCRIPTION AND OPERATION Errore Il segnalibro non è definito Standard Configuration 1 Optiona Configuration 3 TROUBLESHOOTING 100 MAINTENANCE PRACTICES Errore Il segnalibro non è definito 1 THERMOSTATIC VALVE REPLACEMENT Errore Il segnalibro non è definito 2 RADIATOR REPLACEMENT Errore Il segnalibro non è definito ...

Page 833: ...essure cap 3 fitted with pres sure relief valve and return valve At temperature rise and expansion of the coolant the pressure relief valve opens and the coolant flows via a hose at atmospheric pressure to the transparent overflow bottle 4 When cooling down the coolant is sucked back into the cooling circuit The system is fitted with an overflow bottle where surplus coolant is collected and re tur...

Page 834: ...Page 3 2nd Edition Rev 0 75 10 LIQUID COOLING SYSTEM DESCRIPTION AND OPERATION Optional Configuration Figure 2 Scheme of liquid cooling system with thermostatic valve ...

Page 835: ...o thermal sensors allows an automatic adjust ment of temperature by controlling coolant flow to radiator and keeping it at tempera tures between 50 C and 135 C green arch on CHT indicator Figure 3 CHT indicator Thermostatic valve s functioning is described below Coolant temperature below 90 C The scheme in figure 4 shows coolant flow at T 90 C The coolant in the overflow bot tle is sucked in the c...

Page 836: ...C and 100 C Coolant circulation in this case is described by figure 5 Figure 5 Coolant flow at 90 C T 100 C As in the previous case coolant is forced by pressure generated by the pump but in this case as effect of thermal expansion first sensor set to 90 C is pushed down In this configuration part of the coolant is driven through the radiator ...

Page 837: ...ND OPERATION Coolant temperature above 100 C Figure 6 describes coolant flow when temperature is above 100 C Figure 6 Coolant flow at T 100 C Now both the thermal sensors of the thermostatic valve are pushed down and all the coolant flow is forced through the radiator ...

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Page 839: ...ubleshooting Trouble Likely cause Action required CHT stay high Thermostatic valve stuck closed Replace overhaul thermo static valve Leakage of coolant Check coolant system line to locate leakage point Repair where needed and restore coolant level If leakage is located on radia tor replace it CHT stays low Thermostatic valve stuck opened Replace overhaul thermo static valve ...

Page 840: ...RACTICES MAINTENANCE PRACTICES This Chapter contains the following maintenance tasks description Thermostatic valve replacement Radiator replacement Refer to Engine Maintenance Manual for further maintenance practices e g ex pansion tank and overflow bottle maintenance ...

Page 841: ...NCE ON THE THERMOSTATIC VALVE 1 Engage parking brake 2 Set electric MASTER switch OFF 3 Remove engine cowlings 4 Unscrew Serflex and remove all hoses connected to the valve Note connections Refer to Figure 7 5 Attach the new overhauled unit to the support by valve bolts Restore the same configura tion noted at step 4 6 Restore proper connections to the valve as noted at step 4 7 Install engine cow...

Page 842: ...nscrew serflex and remove hoses connected to the radiator Note connections Refer to Figure 8 5 Unscrew bolts that fix the radiator to its support Hold firmly the radiator by hand during removal Refer to Figure 9 6 Clear the radiator of support replace it if needed 7 Place into position the new overhauled unit Align radiator s lower holes with support s ones 8 Fix the unit to the support by bolts H...

Page 843: ...Page 203 2nd Edition Rev 0 75 10 LIQUID COOLING SYSTEM MAINTENANCE PRACTICES Figure 8 Radiator hoses Figure 9 Radiator engine mounting bolts ...

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Page 846: ...2nd Edition Rev 0 Chapter 78 Exhaust ...

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Page 848: ... Rev 0 TOC 1 2nd Edition Rev 0 78 10 1 2nd Edition Rev 0 2 2nd Edition Rev 0 200 2nd Edition Rev 0 201 2nd Edition Rev 0 202 2nd Edition Rev 0 203 2nd Edition Rev 0 204 2nd Edition Rev 0 205 2nd Edition Rev 0 206 2nd Edition Rev 0 207 2nd Edition Rev 0 208 2nd Edition Rev 0 209 2nd Edition Rev 0 210 2nd Edition Rev 0 ...

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Page 850: ...1 2nd Edition Rev 0 78 TOC CHAPTER 78 TABLE OF CONTENTS 56 10 EXHAUST 1 DESCRIPTION AND OPERATION 1 MAINTENANCE PRACTICES 200 1 EXHAUST REMOVAL 201 2 EXHAUST INSTALLATION 202 3 HEAT EXCHANGER INSPECTION 207 ...

Page 851: ...The muffler also works as a heat exchanger 3 for carb and cabin heat The exhaust system must always be checked for possible cracks ref Periodic Inspection Table on chapter 5 Close attention must be given to the heat exchanger system which should be totally disassembled for inspection as cracks would allow noxious fumes to be mixed with carb and cabin air heat Figure 1 Exhaust system ...

Page 852: ...ing 7 Heat exchanger 8 Exhaust ring 9 Exhaust ring The system above described is independent from cabin and carburetor heating systems see respectively Chapter 21 and 71 Nevertheless through the heat exchanger joined to muffler and riveted on exhaust rings ram air is warmed and conveyed to cabin heat and defrost system and carburetors Figure 2 Muffler and heat exchanger ...

Page 853: ...200 2nd Edition Rev 0 78 10 EXHAUST MAINTENACE PRACTICES MAINTENANCE PRACTICES This Chapter contains the following maintenance tasks description Exhaust Removal Exhaust Installation Heat Exchanger inspection ...

Page 854: ...aster Switch is turned OFF 3 Remove engine upper and lower cowling panel See Chapter 54 CAUTION ENSURE THAT ENGINE IS COOL BEFORE STARTING ANY OPERATION 4 Loosen serflex and remove air system hoses from heat exchanger Refer to Figure 3 5 Remove spring from exhaust manifold Refer to Figure 3 6 Unscrew nut to disconnect exhaust manifold Refer to Figure 3A 7 Remove muffler ...

Page 855: ...nt A R TYPE3 High temperature sealant Pre installation Procedure Step no Task description Additional info References 1 Examine that exhaust manifold are free from corrosion or deformations No deformation permitted No corrosion permitted 2 Examine the main bolt assemblies Look especially for corrosion and deformation Replace bolts if required Refer to Figure 3A ...

Page 856: ...X 912S Installation Manual Refer to Figure 3 3 Apply copper lubricant between exhaust manifold and muffler Refer to Figures 3B and 3C 4 Install spring on exhaust manifold Refer to Figure 3C 5 Apply sealant into the springs Figure 2A Sista SL509 High Heat Acetic Silicon or equivalent 6 Apply air system hoses on heat exchanger and tighten screwing serflex Refer to Figure 4 7 Install engine upper and...

Page 857: ...Page 204 2nd Edition Rev 0 78 10 EXHAUST MAINTENACE PRACTICES Figure 3 Heat exchanger Figure 3A Detail C B A nut ...

Page 858: ...Page 205 2nd Edition Rev 0 78 10 EXHAUST MAINTENACE PRACTICES Figure 3B Detail Figure 3C Detail copper lubricant copper lubricant ...

Page 859: ...Page 206 2nd Edition Rev 0 78 10 EXHAUST MAINTENACE PRACTICES Figure 4 Air system hoses heat exchanger ...

Page 860: ...sition Refer to Figure 5 5 Open heat exchanger along longitudinal edges and remove it from muffler Refer to Figure 6 6 Remove all mastic traces Refer to Figure 5 7 Inspect heat exchanger to locate corrosions cracks and deformations No corrosion cracks or deformation allowed 8 Apply a mastic layer on muffler rings and in correspondence of rivet line Use type 3 sealant See Chapter 51 Refer to Figure...

Page 861: ...Page 208 2nd Edition Rev 0 78 10 EXHAUST MAINTENACE PRACTICES Figure 5 Muffler with heat exchanger Figure 6 Heat exchanger removed rivet line longitudinal edges mastic muffler ...

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Page 864: ...Chapter 79 Oil system ...

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Page 868: ...TABLE OF CONTENTS 79 10 OIL SYSTEM 1 DESCRIPTION AND OPERATION 1 MAINTENANCE PRACTICES 200 1 OIL TANK CLEANING 201 2 OIL TANK REPLACEMENT 201 3 THERMOSTATIC VALVE REPLACEMENT 202 4 OIL COOLER REPLACEMENT 204 5 OIL PRESSURE SENSOR REPLACEMENT 208 ...

Page 869: ...m are Oil filter Oil radiator Oil reservoir Thermostatic valve Oil drain valves Oil vent valves Oil filler Oil quantity measurement device stick type Anyway the complete oil system of the A C is composed of the following addi tional parts for each engine Oil temperature sensor Oil pressure sensor The above mentioned oil parameters are monitored by means of analogical transducers located on the ins...

Page 870: ...C Once came to the pump oil is transferred to the engine lubrication circuit and then to the cartridge filtering element integrated in the engine The oil is then conveyed in the oil reservoir Rotax part 1 2 4 3 5 6 7 Condizione fredda T 90 C Figure 1 Rotax 912S oil circuit schematic oil temperature below 90 C Oil temperature 90 C to 100 C As above described the oil circulates for effect of the pum...

Page 871: ...o 100 C Oil temperature greater than 100 C The schematic reported in Figure 3 shows oil circulation when the oil tempera ture reaches and overcomes a value of 100 C In this case because of the opera tion of the second thermal sensor the oil as a whole is conveyed toward the ra diator 1 2 4 3 5 6 7 Condizione intermedia 90 C T 100 C ...

Page 872: ...esigned for full flow oil system in order to filter the contaminants from the circulated oil before it passes through the bearing surfaces Figure 4 Rotax 912S filter cartridge section The oil flow is forced in the filter by the oil pump by means of external holes it passes through the filtering element and it is conveyed into the circuit by means of the central hole 1 2 4 3 5 6 7 Condizione calda ...

Page 873: ...e 5 2nd Edition Rev 0 79 10 OIL SYSTEM DESCRIPTION AND OPERATION Radiator The oil radiator is installed on the front end of the engine cowling and it is con nected on the engine mount Figure 5 Oil radiator ...

Page 874: ...racket structure allow for air ventilation see figure below Figure 6 Oil tank ventilation flow The reservoir gathers also the oil coming from the breather hose and it is fitted with a dipstick see figure below item 11 An hose immediately located beneath the filler cap allows for oil relief discharged in a safe zone in the cowling far from exhausts and other heat sources ...

Page 875: ...Page 7 2nd Edition Rev 0 79 10 OIL SYSTEM DESCRIPTION AND OPERATION Figure 7 Oil tank ...

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Page 877: ...ANCE PRACTICES This Chapter contains the following maintenance tasks description Oil tank cleaning Oil tank replacement Thermostatic valve replacement Oil cooler replacement Make reference to Engine Maintenance Manual for maintenance practices spe cifically related to the engine ...

Page 878: ...gage parking brake 2 Set electric MASTER switch OFF 3 Open the RH pilot view engine cowling 4 Unscrew and remove all hoses from the top of the tank Refer to 6 7 5 Slightly unscrew and release the support tie that fix the tank to the support Refer to 6 6 Clear oil tank of its housing by moving it upward replacement of the tank 7 Place into position the new overhauled unit 8 Secure back the tank to ...

Page 879: ...LVE 1 Engage parking brake 2 Set electric MASTER switch OFF 3 Remove engine cowlings 4 Remove the screws that fix metallic cover to the hose 5 Unscrew and remove all hoses connected to the valve Note connections 6 Remove the screws that fix thermostatic valve sup port to the hose Hold firmly the valve by hand during removal 7 Unscrew and disconnect valve from support re place it if needed Remove s...

Page 880: ...y screws to the wall 12 Apply engine cowling 4 OIL COOLER REPLACEMENT Procedure Step no Task description Additional info References CAUTION ENSURE THAT ENGINE IS OFF AND COOL BEFORE OPERATING MAINTENANCE ON THE OIL COOLER 1 Engage parking brake 2 Set electric MASTER switch OFF 3 Remove engine cowlings 4 Remove the bolts that fix hoses to the oil cooler Remove safety wire The same bolts also attach...

Page 881: ...port replace it if needed Hold firmly the cooler by hand during removal 7 Place into position the new overhauled unit Align cooler s holes with support s ones Ref Figure 8 8 Place into position hoses and screw them and cool er to support Hold firmly the cooler by hand during installation Restore connections re moved at step 5 9 Install engine cowlings ...

Page 882: ...EM MAINTENANCE AND PRACTICES 2nd Edition Rev 0 Page 205 Figure 8 Oil system schematic Support tie Support Oil tank Thermostatic valve Protection cover Protection cover Oil cooler Radiators to engine mount attachment ...

Page 883: ...79 10 OIL SYSTEM MAINTENANCE AND PRACTICES 2nd Edition Rev 0 Page 206 Figure 9 Thermostatic valve ...

Page 884: ...79 10 OIL SYSTEM MAINTENANCE AND PRACTICES 2nd Edition Rev 0 Page 207 Figure 10 Radiators assembly Oil cooler ...

Page 885: ...d locker A R Commercial Procedure Step Task description Additional note 1 Engage parking brake 2 Set electric MASTER switch OFF 3 Disconnect oil pressure indicator connector You can easily ac cess it from the top engine Refer to Figure 13 4 Detect the sensor You can find it be hind the oil cooling radiator Refer to Figure 14 5 Unscrew sensor form the T joint Refer to Figure 14 6 Remove the sensor ...

Page 886: ...79 10 OIL SYSTEM MAINTENANCE AND PRACTICES 2nd Edition Rev 0 Page 209 Figure 13 Oil pressure Indicator connector Figure 14 Oil pressure sensor sensor joint ...

Page 887: ...79 10 OIL SYSTEM MAINTENANCE AND PRACTICES 2nd Edition Rev 0 Page 210 INTENTIONALLY LEFT BLANK ...

Page 888: ...Chapter 80 Starting ...

Page 889: ...INTENTIONALLY LEFT BLANK ...

Page 890: ...EP CHAPTER 80 LOEP Section Page Edition Revision LOEP 1 2nd Edition Rev 0 TOC 1 2nd Edition Rev 0 80 10 1 2nd Edition Rev 0 2 2nd Edition Rev 0 100 2nd Edition Rev 0 200 2nd Edition Rev 0 201 2nd Edition Rev 0 202 2nd Edition Rev 0 ...

Page 891: ...Page 2 2nd Edition Rev 0 80 LOEP INTENTIONALLY LEFT BLANK ...

Page 892: ...Page 1 2nd Edition Rev 0 80 TOC CHAPTER 80 TABLE OF CONTENTS 80 10 STARTING 1 Description and operation 1 Troubleshooting 100 Maintenance practices 200 1 Starter relay replacement 201 ...

Page 893: ...starter and a relay located in the engine con nected to the firewall The starter button is activated by the key The key rotation energizes the starter relay closing the relay contacts to connect the external power supply or aircraft battery to the connection of the starter Figure 1 Starting system The wiring diagram is reported on Chapter 92 ...

Page 894: ...Page 2 2nd Edition Rev 0 80 10 STARTING DESCRIPTION AND OPERATION INTENTIONALLY LEFT BLANK ...

Page 895: ...about the starting system For starter system in the Rotax Operators Manual possible problems are listed At the same time a brief description of the necessary remedial action is given ATA 80 10 Troubleshooting Trouble Likely cause Action required Starter does not work Engine starter fails Refet to Rotax Operators Manual Starter relay fails Replace relay Starter relay circuit fails Check wiring ...

Page 896: ...TARTING DESCRIPTION AND OPERATION MAINTENANCE PRACTICES This Chapter contains the following maintenance tasks description Starter relay replacement For maintenance tasks related to the starter make reference to Rotax Mainte nance Manual ...

Page 897: ...WITCH is set to OFF 2 Make sure that no external power is provided 3 Remove the engine cowling 4 Disconnect the electrical wires from the relay 5 Remove the nut and washer fixing the relay to the firewall Refer to Figure 2 6 Install on the panel the new relay 7 Install the washer and nut fixing the relay 8 Connect the electrical wires on the relay 9 Reinstall the engine cowling 10 Test switch for ...

Page 898: ...Page 202 2nd Edition Rev 0 80 10 STARTING DESCRIPTION AND OPERATION Figure 2 Starter relay ...

Page 899: ...Page 203 2nd Edition Rev 0 80 10 STARTING DESCRIPTION AND OPERATION INTENTIONALLY LEFT BLANK ...

Page 900: ...2nd Edition Rev 0 AMM SUPPLEMENTS LIST Page 1 Tecnam P2002JF AMM Supplements List ...

Page 901: ...ange MOD2002 127 Variable Pitch Propeller Supplement S2 For airplanes embodying the Design Change MOD2002 141 Rudder and Throttle Additional Controls Supplement SG3 For airplanes embodying the Design Change MOD2002 041 Garmin G500 Installation Supplement S4 P2002JF post shipment assembly procedure ...

Page 902: ...Tecnam P2002 JF AMM Supplement S 4 2nd Edition Rev 0 29 09 2015 P2002 JF post shipment assembly procedure ...

Page 903: ... Edition Rev 0 2 2nd Edition Rev 0 3 2nd Edition Rev 0 ROR 1 2nd Edition Rev 0 2 2nd Edition Rev 0 TOC 1 2nd Edition Rev 0 2 2nd Edition Rev 0 Introduction 1 2nd Edition Rev 0 2 2nd Edition Rev 0 Chapter 12 1 2nd Edition Rev 0 2 2nd Edition Rev 0 200 2nd Edition Rev 0 201 2nd Edition Rev 0 202 2nd Edition Rev 0 203 2nd Edition Rev 0 204 2nd Edition Rev 0 205 2nd Edition Rev 0 Chapter 55 1 2nd Edit...

Page 904: ...0 204 2nd Edition Rev 0 205 2nd Edition Rev 0 206 2nd Edition Rev 0 207 2nd Edition Rev 0 208 2nd Edition Rev 0 209 2nd Edition Rev 0 210 2nd Edition Rev 0 211 2nd Edition Rev 0 Chapter 72 1 2nd Edition Rev 0 2 2nd Edition Rev 0 200 2nd Edition Rev 0 201 2nd Edition Rev 0 202 2nd Edition Rev 0 203 2nd Edition Rev 0 204 2nd Edition Rev 0 205 2nd Edition Rev 0 206 2nd Edition Rev 0 207 2nd Edition R...

Page 905: ...Page 3 SUPPLEMENT S4 RECORD OF REVISIONS 2nd Edition Rev0 INTENTIONALLY LEFT BLANK ...

Page 906: ...basic publication 2 for the second one etc Should be necessary to completely reissue a publication for contents and format changes the Edition code will change to the next number 2 for the second edi tion 3 for the third edition etc Additions deletions and revisions to existing text will be identified by a revision bar black line in the left hand margin of the page adjacent to the change When tech...

Page 907: ...Page 2 SUPPLEMENT S4 RECORD OF REVISIONS 2nd Edition Rev0 Record of Revisions Rev Revised page Description of Revision Tecnam Approval EASA Approval Or Under DOA Privileges DO OoA HDO ...

Page 908: ...ON È DEFINITO 1 Maintenance Practices 200 1 Stabilator pre installation procedure 201 2 Stabilator installation 201 CHAPTER 57 WINGS 1 Maintenance Practices 200 1 Wing pre installation procedure 201 2 Wing installation 201 3 Aileron control assembling 204 4 Flaps control assembling 206 5 Control cable and hoses pre installation procedure 207 6 Control cable and hoses installation 207 CHAPTER 72 EN...

Page 909: ...Page 2 SUPPLEMENT S4 TABLE OF CONTENTS 2nd Edition Rev0 INTENTIONALLY LEFT BLANK ...

Page 910: ... some part in the supplements for engine check and the instruction for the installation and fastening of electrical wire in the wing compartment Herein are reported the ATA Chapters impacted by procedure in subject For the correct reassembly the suggested installation sequence is the following 1 The wing fuselage coupling refer to chapter 57 in this document 2 Flaps and Ailerons control assembly r...

Page 911: ...Page 2 SUPPLEMENT S4 INTRODUCTION 2nd Edition Rev0 INTENTIONALLY LEFT BLANK ...

Page 912: ...Page 1 SUPPLEMENT S4 SERVICING 2nd Edition Rev 0 Chapter 12 Servicing ...

Page 913: ...Page 2 SUPPLEMENT S4 SERVICING 2nd Edition Rev 0 INTENTIONALLY LEFT BLANK ...

Page 914: ...MENT S4 SERVICING POST SHIPMENT ASSEMBLY INSTRUCTION 2nd Edition Rev 0 MAINTENANCE PRACTICES This Chapter contains the following maintenance tasks description Seats removal Seats installation Battery cable connection ...

Page 915: ...ing device Refer to Figure 12 1 4 Pull seat lever then slide seat all forward Refer to Figure 12 2 5 Pull up seat and remove it from his location 6 Apply the same procedure for the other seat 2 SEATS INSTALLATION Procedure Step no Seats installation Task description Additional info References 1 Engage parking brake 2 Make sure that Master switch is set to off 3 Put seat in his location 4 Pull seat...

Page 916: ...ke sure that Master switch is set to OFF 3 Open inspection cap F9 Refer basic manual ATA 06 WARNING When installing a battery take special care to ensure that no sparks are created by tools and that the terminals are not shorted out by tools 4 Remove the protective tape 5 Connect the negative cable if not installed 6 Connect the positive cable to the battery Refer to Figure 12 3 7 Make sure that f...

Page 917: ...Page 203 SUPPLEMENT S4 SERVICING POST SHIPMENT ASSEMBLY INSTRUCTION 2nd Edition Rev 0 Figure 12 1 Seats locking device Figure 12 2 Seats remove procedure ...

Page 918: ...Page 204 SUPPLEMENT S4 SERVICING POST SHIPMENT ASSEMBLY INSTRUCTION 2nd Edition Rev 0 Figure 12 3 Battery cables connection ...

Page 919: ...Page 205 SUPPLEMENT S4 SERVICING POST SHIPMENT ASSEMBLY INSTRUCTION 2nd Edition Rev 0 INTENTIONALLY LEFT BLANK ...

Page 920: ...Page 1 SUPPLEMENT S4 STABILATOR AND RUDDER 2nd Edition Rev 0 Chapter 55 Stabilator and Rudder ...

Page 921: ...Page 2 SUPPLEMENT S4 STABILATOR AND RUDDER 2nd Edition Rev 0 INTENTIONALLY LEFT BLANK ...

Page 922: ...LATOR AND RUDDER POST SHIPMENT ASSEMBLY INSTRUCTION 2nd Edition Rev 0 MAINTENANCE PRACTICES This Chapter contains the following maintenance tasks description Stabilator pre installation procedure Stabilator installation procedure ...

Page 923: ...allation Task description Additional info References 1 Engage parking brake 2 Make sure that Master switch is set to OFF 3 Put the right half stabilator on the torque tube 4 Screw the RH stabilator attachment Spacer washer bolt nut Refer to basic manual ATA 20 for correct torque value Refer to Figures 55 1 and 55 4 5 Put the left stabilator on torque tube and screw the LH stabilator attachment Ref...

Page 924: ...Page 202 SUPPLEMENT S4 STABILATOR AND RUDDER POST SHIPMENT ASSEMBLY INSTRUCTION 2nd Edition Rev 0 Figure 55 1 Stabilator attachment Figure 55 2 Stabilator rear side screws ...

Page 925: ...Page 203 SUPPLEMENT S4 STABILATOR AND RUDDER POST SHIPMENT ASSEMBLY INSTRUCTION 2nd Edition Rev 0 Figure 55 3 Stabilator trim tab connection 7 Figure 55 4 Stabilator assembling ...

Page 926: ...Page 204 SUPPLEMENT S4 STABILATOR AND RUDDER POST SHIPMENT ASSEMBLY INSTRUCTION 2nd Edition Rev 0 INTENTIONALLY LEFT BLANK ...

Page 927: ...Page 205 SUPPLEMENT S4 STABILATOR AND RUDDER POST SHIPMENT ASSEMBLY INSTRUCTION 2nd Edition Rev 0 INTENTIONALLY LEFT BLANK ...

Page 928: ...Page 1 SUPPLEMENT S4 WINGS POST SHIPMENT ASSEMBLY INSTRUCTION 2nd Edition Rev0 Chapter 57 Wings ...

Page 929: ...Page 2 SUPPLEMENT S4 WINGS POST SHIPMENT ASSEMBLY INSTRUCTION 2nd Edition Rev0 INTENTIONALLY LEFT BLANK ...

Page 930: ...MAINTENANCE PRACTICES This Chapter contains the following maintenance tasks description Wing pre installation procedure Wing installation Ailerons control assembly Flaps control assembly Control cable and hoses pre installation procedure Control cable and hoses installation procedure ...

Page 931: ...te procedure for wings installation WARNING For this operation are required minimum 3 persons 1 person in correspondence of the front spare attachment 1 person in correspondence of the rear spare attachment and 1 person in correspondence of the tip for wing suspension NOTE On the wing to fuselage main fittings there is a gap of about 1mm between the wing s main spar lugs and the carrythrough This ...

Page 932: ...ge 2 Connect the LH wing on fuselage and place the bolts in their original location Use 2xbolts 1xshim 4 alu minium washers 2x nuts Refer to Figures 57 1 and 57 2 3 Connect the RH wing on fuselage and place the bolts in their original location Use 2xbolts 1xshim 4 alu minium washers 2x nuts Refer to Figure 57 1 and 57 2 Torque value front bolts NAS 1308 28D 100 Nm Torque value rear bolts M8 24 6 N...

Page 933: ...Page 203 SUPPLEMENT S4 WINGS POST SHIPMENT ASSEMBLY INSTRUCTION 2nd Edition Rev 0 Figure 57 2 External wing attachment ...

Page 934: ...l info References 1 Remove seats 2 Remove cabin floor panels Refer to Figure 57 3 3 Connect ailerons control applying bolts 4 Use 2xbolts 2xspacers 2xaluminum washers and 2xnuts Refer to Figure 57 4 and 57 5 4 Connect the small bar 3 to the pushrods 5 Refer to Figure 57 4 and 57 5 WARNING Report a slippage marks at the end of installation Figure 57 3 Floor cabin panels ...

Page 935: ...Page 205 SUPPLEMENT S4 WINGS POST SHIPMENT ASSEMBLY INSTRUCTION 2nd Edition Rev 0 Figure 57 4 Ailerons control assembling Figure 57 5 Ailerons control command lever connection ...

Page 936: ...assembly Task description Additional info References 1 Connect flaps control applying roller bearings 6 that link push pull rod 5 to flap control plate Use 2xbolts 2xaluminum washers 2xnuts Refer to Figure 57 6 2 Repeat for other side WARNING Report a slippage marks at the end of installation Figure 57 6 Flaps control assembling ...

Page 937: ...k description Additional info References 1 Engage parking brake 2 Make sure that Master switch is set to OFF 3 Remove the protective cap and connect the fuel system hoses LH and RH side Refer to Figures 57 7 and 57 8 4 Connect the fuel quantity sensors TELEVEL wiring and the position lights wiring LH and RH side Pay attention aligns the connectors with the same placards Refer to Figures 57 7 and 5...

Page 938: ...oses of wing as marked before Connect the Pitot Heat connector only if VFR Night package is installed Refer to Figure 57 7 8 Connect stall warning device connector on RH wing Refer to Figure 57 8 9 Install fairings between the wings and fuse lage 10 Install the wing s composite root leading edge 11 Install all cabin floor panels and all baggage compartment panels Refer to Figure 57 3 12 Install th...

Page 939: ...Page 209 SUPPLEMENT S4 WINGS POST SHIPMENT ASSEMBLY INSTRUCTION 2nd Edition Rev 0 Figure 57 7 LH wing cable and hoses Figure 57 8 RH wing cable and hoses ...

Page 940: ...Page 210 SUPPLEMENT S4 WINGS POST SHIPMENT ASSEMBLY INSTRUCTION 2nd Edition Rev 0 INTENTIONALLY LEFT BLANK ...

Page 941: ...Page 211 SUPPLEMENT S4 WINGS POST SHIPMENT ASSEMBLY INSTRUCTION 2nd Edition Rev 0 INTENTIONALLY LEFT BLANK ...

Page 942: ...Page 1 SUPPLEMENT S4 ENGINE 2nd Edition Rev 0 Chapter 72 Engine ...

Page 943: ...Page 2 SUPPLEMENT S4 ENGINE 2nd Edition Rev 0 INTENTIONALLY LEFT BLANK ...

Page 944: ...200 SUPPLEMENT S4 ENGINE POST SHIPMENT ASSEMBLY INSTRUCTION 2nd Edition Rev 0 MAINTENANCE PRACTICES This Chapter contains the following maintenance tasks description Engine check Powerplant controls rigging ...

Page 945: ...Page 201 SUPPLEMENT S4 ENGINE POST SHIPMENT ASSEMBLY INSTRUCTION 2nd Edition Rev 0 1 ENGINE CHECK Refer to Rotax maintenance manual 912 Series part number 899735 ...

Page 946: ...tional info References 1 Engage parking brake 2 Open engine cowlings upper and lower See Chapter 54 of Basic MM AIR BOX CONTROL RIGGING 1 Connect airbox bowden cable to airbox control lever 2 Check carburetor heat control stroke Ensure that when Carb Heat knob is full forward Off position air box control lever is fully rightward Refer to Figure 77 1 Ensure that when Carb Heat knob is full backward...

Page 947: ...aring to adjust cable as needed Screw nut to lock position Connect bowden cable to con trol lever 4 Check carburetor heat control stroke CHOKE CONTROL RIGGING 1 Connect choke bowden cable to choke control lever 2 Check choke control stroke Ensure that when choke knob is fully upward choke control lever reaches the relative stop screw Refer to Figure 77 3 Ensure that when choke knob is fully downwa...

Page 948: ...rol stroke THROTTLE CONTROL RIGGING 1 Connect throttle bowden cable to throttle control lever 2 Check throttle control stroke Ensure that when throttle knob is fully forward throttle control lever is fully forward Refer to Figure 77 5 Ensure that when throttle knob is fully backward throttle control lever is fully backward Refer to Figure 77 6 3 Stroke adjusting move throttle control cable from th...

Page 949: ...Page 205 SUPPLEMENT S4 ENGINE POST SHIPMENT ASSEMBLY INSTRUCTION 2nd Edition Rev 0 Figure 72 1 Carb Heat OFF ...

Page 950: ...Page 206 SUPPLEMENT S4 ENGINE POST SHIPMENT ASSEMBLY INSTRUCTION 2nd Edition Rev 0 Figure 72 2 Carb Heat ON ...

Page 951: ...Page 207 SUPPLEMENT S4 ENGINE POST SHIPMENT ASSEMBLY INSTRUCTION 2nd Edition Rev 0 Figure 72 3 Choke OFF Figure 72 4 Choke ON ...

Page 952: ...Page 208 SUPPLEMENT S4 ENGINE POST SHIPMENT ASSEMBLY INSTRUCTION 2nd Edition Rev 0 Figure 72 5 Throttle maximum power Figure 72 6 Throttle minimum power ...

Page 953: ...Page 1 SUPPLEMENT S4 WIRING DIAGRAMS POST SHIPMENT ASSEMBLY INSTRUCTION 2nd Edition Rev 0 INTENTIONALLY LEFT BLANK ...

Page 954: ...Tecnam P2002 JF AMM Supplement S1 2nd Edition Rev 0 29 09 2015 For airplanes embodying the Design Change MOD2002 127 Variable Pitch Propeller ...

Page 955: ...INTENTIONALLY LEFT BLANK ...

Page 956: ...page 2nd Edition Rev 0 29 September 2015 Section Page Edition Revision LOEP 1and 2 2nd Edition Rev 0 ROR 3and 4 2nd Edition Rev 0 TOC 5and 6 2nd Edition Rev 0 Introduction 7and 8 2nd Edition Rev 0 ATA 3 1and 2 2nd Edition Rev 0 ATA 5 1and4 2nd Edition Rev 0 ATA 10 1and 2 2nd Edition Rev 0 ATA 11 1and 2 2nd Edition Rev 0 ATA 31 1and 2 2nd Edition Rev 0 ATA 61 1 thru 3 2nd Edition Rev 0 100 2nd Edit...

Page 957: ...2nd Edition Rev 0 SUPPLEMENT S1 LOEP Page 2 INTENTIONALLY LEFT BLANK ...

Page 958: ...asic publication 2 for the second one etc Should be necessary to completely reissue a publication for contents and format changes the Edition code will change to the next number 2 for the second edi tion 3 for the third edition etc Additions deletions and revisions to existing text will be identified by a revision bar black line in the left hand margin of the page adjacent to the change When techn...

Page 959: ...2nd Edition Rev 0 SUPPLEMENT S1 RECORD OF REVISIONS Page 4 Record of Revisions Rev Revised page Description of Revision Tecnam Approval EASA Approval Or Under DOA Privileges DO OoA HDO ...

Page 960: ...NGINE 1 PROPELLER 1 GOVERNOR 1 Chapter 5 Inspection Program 1 5 1 Additional Inspection Program 2 5 2 ENGINE and PROPELLER 2 5 3 Governor 2 Chapter 10 STORAGE and RETURN to SERVICE 1 Chapter 11 Marking and Placards 1 Chapter 31 Indicating System 1 Chapter 61 Propeller 1 Troubleshooting 100 Maintenance practices 200 1 Propeller removal 201 2 Propeller installation 202 3 Governor replacement 204 ...

Page 961: ...2nd Edition Rev 0 SUPPLEMENT S1 TABLE OF CONTENTS Page 6 INTENTIONALLY LEFT BLANK ...

Page 962: ...hich embody the Design Change 2002 127 Variable Pitch Propeller The Design Change introduces the installation of the same variable pitch propel ler used for P2002 JR version Herein are reported the sections impacted by the design change mentioned The information are to be considered replacing basic AMM ones ...

Page 963: ...2nd Edition Rev 0 SUPPLEMENT S1 INTRODUCTION Page 8 INTENTIONALLY LEFT BLANK ...

Page 964: ...mixed cooling water cooled heads and air cooled cylinders twin carburetors inte grated reduction gear with torque damper Maximum rating 73 5kW 98 5hp 5800rpm max 5 69 0kW 92 5hp 5500rpm cont PROPELLER Manufacturer Hoffmann Propeller Certification Basis Joint Airworthiness Requirements JAR P Propellers Change 7 inclusive Type Certificate No LBA TCDS 32 130 88 dated 20 08 2003 Model HOV352F1 C170FQ ...

Page 965: ...2nd Edition Rev 0 SUPPLEMENT S1 Chapter 3 Airplane General Description Page 2 INTENTIONALLY LEFT BLANK ...

Page 966: ...mation For the Rotax 912S3 engine unless otherwise stated in the present Manual it is compulsory to adhere to maintenance requirements as reported in the Mainte nance Manual Line Maintenance p n 899373 ed 1 rev 0 of 9 1 2007 and later versions furnished along with the present manual For the Hoffmann propeller please refer to its Operation and maintenance n E5400A For the Governor produced by Jihos...

Page 967: ...llers Propeller governor check for oil leakage at governor s surface and at mounting pad No oil leakage is per mitted X 61 Propellers Check for free movement of propeller control levers X 5 2 ENGINE AND PROPELLER All the limitations to airworthiness related to the engine ROTAX 912S or to the propeller Hoffmann HO V352F1 C170FQ 8 are defined into their Manuals and all of the issued Service Bulletin...

Page 968: ...2nd Edition Rev 0 SUPPLEMENT S1 Chapter 5 Inspection Program Page 3 INTENTIONALLY LEFT BLANK ...

Page 969: ...2nd Edition Rev 0 SUPPLEMENT S1 Chapter 5 Inspection Program Page 4 INTENTIONALLY LEFT BLANK ...

Page 970: ...D RETURN TO SERVICE Refer to Hoffmann Propeller Operation and Installation Manual last issue for propeller in spections and maintenance with related schedule Refer to Governor JIHOSTROJ P AB1 X Y Operation and Installation Manual last issue for governor inspections and maintenance with related schedule ...

Page 971: ...2nd Edition Rev 0 SUPPLEMENT S1 Chapter 10 STORAGE and RETURN to SERVICE Page 2 INTENTIONALLY LEFT BLANK ...

Page 972: ...on Rev 0 SUPPLEMENT S1 Chapter 11 Marking and Placards Page 1 CHAPTER 11 MARKING AND PLACARDS Engine s throttle and Propeller s Pitch The following placard is used when the throttle is installed on the pedestal ...

Page 973: ...2nd Edition Rev 0 SUPPLEMENT S1 Chapter 11 Marking and Placards Page 2 INTENTIONALLY LEFT BLANK ...

Page 974: ...ctrical Indicator listed below Attitude indicator Directional gyro indicator only on analogic instrument panel version The related vacuum indicator is consequently removed The propeller control line is realized with bowden cables The following figures show samples of analogic and digital instrument panels highlighting the propel ler control located on the central pedestal 10 11 12 13 14 17 18 21 2...

Page 975: ...d Edition Rev 0 SUPPLEMENT S1 Chapter 31 Indicating System Page 2 1 2 3 4 5 6 7 8 9 10 11 12 G500 P2002JF Digital instrument panel Propel ler Knob Manifold pressure indica tor Electric Attitude indica tor ...

Page 976: ...tective finished with special lacquer coating PROPELLER Manufacturer Hoffmann Propeller Certification Basis Joint Airworthiness Requirements JAR P Propellers Change 7 inclusive Type Certificate No LBA TCDS 32 130 88 dated 20 08 2003 Model HOV352F1 C170FQ 8 Number of blades 2 Diameter 1780 mm no reduction allowed Type Variable pitch wood GOVERNOR Manufacturer Jihostroj Model P 110 030 A Type Hydrau...

Page 977: ...2nd Edition Rev 0 SUPPLEMENT S1 Chapter 61 Propeller Page 2 HUB DESIGNATION example ...

Page 978: ...2nd Edition Rev 0 SUPPLEMENT S1 Chapter 61 Propeller Page 3 BLADE DESIGNATION example ...

Page 979: ...ffmann Propeller document on the basis of HOV352F1 C170FQ 8 propeller features see hub and blade designation rules For the Hoffmann propeller please refer to its Operation and maintenance n E5400A For the Governor produced by Jihostroja s please refer to its Operation and in stallation manual p n P ROV 514 01 ...

Page 980: ...dition Rev 0 SUPPLEMENT S1 Chapter 61 Propeller Page 200 MAINTENANCE PRACTICES This Chapter contains the following maintenance tasks description Propeller removal Propeller installation Governor Replacement ...

Page 981: ...out 4 Remove screws holding spinner dome to spinner bulkhead 5 Remove safety wires and stops on hex screw 6 Unscrew hex screws on pulley carriers Note Lose all the hex screws at same time supporting the propeller until its removal During the operation is suggested to use a container under the propel ler attach because the oil can go out 7 Pull slowly propeller off from its position 8 Position the ...

Page 982: ...l hub hole and in the fixing holes Remove all surface de fects Remove the shipping plugs and protective wrap if any 6 If necessary proceed to clean the propeller as well as the hub flange before the assembly us ing a gentle detergent and not abrasive deter gent Dry perfectly all the surfaces 7 Check if both O rings are installed in center ring install if required NOTE Lubricate O Ring using en gin...

Page 983: ...ll spinner on support plates observe mating marks 15 Perform a functional check a Adjust power lever for approx 1800 rpm Pull propeller lever back out until the rpm drops by 300 Push propeller lever full forward in and observe rpm in crease The time required for pitch change should be about the same in both direc tion rpm increase and decrease Cycle three times at least this procedure See engine s...

Page 984: ...crew bolt 6 Remove mounting nuts and washers Governor drive and en gine pad must be without impurities metal chips etc If it is necessary clean governor drive and engine pad by appropriate means 7 Pat on the governor to release it and then remove governor from engine pad 8 If necessary Perform preservation in ac cordance with section 8 0 of Governor op eration manual to prepare for long term stora...

Page 985: ...er bowden cable to gov ernor control lever 14 Install hydraulic connection to accumulator mount on governor fitting 15 Check correspondence between governor lever position and propeller knobs Ensure that when pro peller knob is full for ward governor control lever reaches the rela tive stop screw Ensure that when pro peller knob is in full rwar position governor control lever reaches the relative ...

Page 986: ...ointed to opposite direction and average two numbers As a general rule propeller should be 25 100 rpm below the red line limit during check 2 Pull back the propeller lever 3 to 5 times to remove the air in the system See engine starting and shut down procedure on AFM Keep parking brake engaged See Governor CMM Chapter Troubleshoot ing to check if the pro peller or governor limits the rpm 18 After ...

Page 987: ...2nd Edition Rev 0 SUPPLEMENT S1 Chapter 61 Propeller Page 207 INTENTIONALLY LEFT BLANK ...

Page 988: ...2nd Edition Rev 0 SUPPLEMENT S1 Chapter 61 Propeller Page 208 INTENTIONALLY LEFT BLANK ...

Page 989: ...Tecnam P2002 JF AMM Supplement S2 2nd Edition Rev 0 29 09 2015 For airplanes embodying the Design Change MOD2002 141 Rudder and Throttle Additional Controls ...

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Page 991: ... page 2nd Edition Rev 0 September 29 2015 Section Page Edition Revision LOEP 1 2 2nd Edition Rev 0 ROR 1 thru 4 2nd Edition Rev 0 TOC 1 2 2nd Edition Rev 0 Introduction 1 2 2nd Edition Rev 0 ATA 3 3 thru 8 2nd Edition Rev 0 ATA 5 9 10 2nd Edition Rev 0 ATA 6 11 12 2nd Edition Rev 0 ATA 11 13 14 2nd Edition Rev 0 ATA23 15 16 2nd Edition Rev 0 ATA 27 17 thru 22 2nd Edition Rev 0 ATA 53 23 24 2nd Edi...

Page 992: ...SUPPLEMENT S2 LOEP Page 2 2nd Edition Rev 0 INTENTIONALLY LEFT BLANK ...

Page 993: ... basic publication 2 for the second one etc Should be necessary to completely reissue a publication for contents and format changes the Edition code will change to the next number 2 for the second edition 3 for the third edition etc Additions deletions and revisions to existing text will be identified by a revision bar black line in the left hand margin of the page adjacent to the change When tech...

Page 994: ...SUPPLEMENT S2 RECORD OF REVISIONS Page 2 2nd Edition Rev 0 RECORD OF REVISIONS Rev Revised page Description of Revision Tecnam Approval EASA Approval or Under DOA Privileges DO OoA HDO 0 ...

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Page 996: ...SUPPLEMENT S2 RECORD OF REVISIONS Page 4 2nd Edition Rev 0 INTENTIONALLY LEFT BLANK ...

Page 997: ...RD OF REVISIONS 1 TABLE OF CONTENTS 1 INTRODUCTION 1 Chapter 3 Airplane General Description 3 Chapter 5 Inspection Program 9 Chapter 6 Inspection 11 Chapter 11 Marking and Placards 13 Chapter 23 Electric System 15 Chapter 27 Flight Control 17 Chapter 53 Fuselage 23 Chapter 55 Stabilator and Rudder 25 ...

Page 998: ...SUPPLEMENT S2 TABLE OF CONTENTS Page 2 2nd Edition Rev 0 INTENTIONALLY LEFT BLANK ...

Page 999: ...addition on the same hand control it is installed a guarded switch for the flap control This supplement to the Airplane Maintenance Manual has been prepared to provide maintenance personnel with instructions for installation removal and maintenance of the central hand control kit for disabled pilots Herein are reported the sections impacted by the design change mentioned above The information cont...

Page 1000: ...SUPPLEMENT S2 INTRODUCTION Page 2 2nd Edition Rev 0 INTENTIONALLY LEFT BLANK ...

Page 1001: ...ontrol An electric guarded flap switch is also installed on the top of the additional stick grip Moreover a lever installed on the left standard stick allows to operate the brake system without using the standard handle of basic airplane E The Change consists also of a permanent factory made installation of external handles on canopy and reinforcement of the right wing leading edge to ease access ...

Page 1002: ...SUPPLEMENT S2 Chapter 3 Airplane General Description Page 4 2nd Edition Rev 0 FIGURE 3 1 HAND CONTROL AND BRAKE LEVER FIGURE 3 2 INSTRUMENT PANEL ...

Page 1003: ...rip an additional pump has been installed on the standard left stick this pump is connected to the airplane brake system and is operated by a hand operated lever see Figure A 4 Pilot pushes lever to operate brakes The hydraulic connection between the standard pump and the additional lever is in series so that pulling one of the two handles activate the brakes The brake oil reservoir is connected w...

Page 1004: ...3 000 previously welded to the truss is installed the assy 22 5 410 000 which through the assy 22 5 435 001 control rod is connected to pedals Figure A 5 FIGURE 3 5 CONTROL COLUMN PEDALS CONNECTION In order to make the disassembling of the central hand control group easy the configuration features The brake pump is installed on the LH stick to avoid during the hand control disassembly also disconn...

Page 1005: ...Rev 0 FIGURE 3 6 CONTROL COLUMN MECHANICAL INTERFACE In the back of the cockpit panel a steel plate is welded on the cabin truss and allows the installation of the ball bearing joint via two anchor nuts and MS20004 bolts Figure A 8 FIGURE 3 7 REINFORCEMENT AND ROTARY JOINT ...

Page 1006: ...stalled outside of instrument panel on the steel plate two anchor nuts are installed and two MS20004 6 35mm diameter bolts are used to allow an easy and fast installation and removal FIGURE 3 8 The terminal part of the control handle p n 22 5 420 000 must be removed from the aircraft without removing the remaining parts when the kit is not to be installed don the aircraft ...

Page 1007: ... and drying them thoroughly to prevent the possible onset of corrosion INSPECTION ITEMS FLIGHT HOURS 50 100 Special 1 Check links brackets and terminals for defects and secure connection 2 Lubricate joint terminal and throttle bowden wire 3 Check electrical cables and connections After each removal installation of kit or 100 flight hours whichever occur first Normal care is required for rudder and...

Page 1008: ...SUPPLEMENT S2 Chapter 5 Inspection Program Page 10 2nd Edition Rev 0 INTENTIONALLY LEFT BLANK ...

Page 1009: ...ng edge is reinforced to enable its use as a support an internal reinforcement Figure C 1 is provided creating an anchor to the fuselage using two brackets to drop that follow the contour along across the board p n 22 1 950 1 2 Figure C 2 FIGURE 6 1 REINFORCEMENT ON THE RIGHT WING LEADING EDGE FIGURE 6 2 FUSELAGE REINFORCEMENT ...

Page 1010: ...SUPPLEMENT S2 Chapter 6 Inspection Page 12 2nd Edition Rev 0 INTENTIONALLY LEFT BLANK ...

Page 1011: ...d on the instrument panel It provides alternatively flap control to either knob on the instrument panel Std mode or hand control knob Hand Control mode The following placard is positioned just above of it FIGURE 11 1 FLAP SELECTOR PLACARD The flap control switch is located on the upper side of the hand control The following placard is just next to it ...

Page 1012: ...SUPPLEMENT S2 Chapter 11 Marking and Placards Page 14 2nd Edition Rev 0 INTENTIONALLY LEFT BLANK ...

Page 1013: ...ditional flap switch installed on the hand control grip Flap switch selector installed on the instrument panel Installation of the circuit selector is permanent and cannot be removed when other elements of the kit for disabled pilots are removed from the aircraft When the additional hand control kit is not installed the flap switch selector is always on std normal position in order to allow only t...

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Page 1015: ...4 Disconnect the flap connector and secure it to the central column 5 Pull out the hand control assembly from the cockpit 6 Install the cover plate on the instrument panel to hide the hole 7 Select the flap switch selector on STD position POST REMOVAL CHECKS 1 Move the rudder pedals and verify the following a Movement is free and smooth b The rudder control reaches its maximum travel in both direc...

Page 1016: ...interface p n 22 5 445 000 are installed properly and do not interfere with movement of the system rods 2 Verify that the two bolts securing the bearing on the cockpit panel are installed properly 3 Make sure that the flap connector switch is fastened 4 Verify the following a Movement is free and smooth b The rudder control reaches its maximum travel in both directions c The throttle control reach...

Page 1017: ...SUPPLEMENT S2 Chapter 27 Flight Control Page 19 2nd Edition Rev 0 FIGURE 27 1 CONNECTION JOINT CONTROL COLUMN HAND CONTROL FIGURE 27 2 INSTRUMENT PANEL ...

Page 1018: ...SUPPLEMENT S2 Chapter 27 Flight Control Page 20 2nd Edition Rev 0 INTENTIONALLY LEFT BLANK ...

Page 1019: ...he changes introduce an additional control switch on the grip Figure A 1 It operates in accordance with the following movement and actuation up for flap movement up and down for flap movement down The mode of operation STANDARD or HAND CONTROL is selected through a selector switch located on the instrument panel The electrical scheme is provided in Figure F 1 FIGURE 27 3 FLAP SYSTEM ELECTRIC SCHEM...

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Page 1021: ...r pedals and throttle additional control The assy 22 5 403 000 in the red box in the figure is welded into the truss standard which then assumes p n 22 2 100 005 Figure C 3 FIGURE 53 1 TRUSS REINFORCEMENT FOR ADDITIONAL CONTROLS The truss reinforcement is to be intended as permanent factory made installation and must not be removed when the kit is not installed on the aircraft ...

Page 1022: ...SUPPLEMENT S2 Chapter 53 Fuselage Page 24 2nd Edition Rev 0 INTENTIONALLY LEFT BLANK ...

Page 1023: ...ose left PULL for rudder and nose wheel to right A C nose right Throttle The additional central stick can rotate around its axis and allows the control of the engine power The stick is mechanically connected to the airplane engine control system then actuation of the central stick moves the throttle lever on the instrument panel left side and the friction knob operates on both standard and hand co...

Page 1024: ...SUPPLEMENT S2 Chapter 55 Stabilator and Rudder Page 26 2nd Edition Rev 0 FIGURE 55 1 RUDDER AND THROTTLE CONTROL ...

Page 1025: ...Tecnam P2002 JF AMM Supplement SG 3 2nd Edition Rev 0 29 09 2015 For airplanes embodying the Design Change MOD2002 041 Garmin G500 Installation ...

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Page 1027: ...tion Rev 0 2 2nd Edition Rev 0 3 2nd Edition Rev 0 4 2nd Edition Rev 0 5 2nd Edition Rev 0 6 2nd Edition Rev 0 7 2nd Edition Rev 0 8 2nd Edition Rev 0 ROR 1 2nd Edition Rev 0 2 2nd Edition Rev 0 3 2nd Edition Rev 0 4 2nd Edition Rev 0 TOC 1 2nd Edition Rev 0 2 2nd Edition Rev 0 Introduction 1 2nd Edition Rev 0 2 2nd Edition Rev 0 Chapter 04 1 2nd Edition Rev 0 2 2nd Edition Rev 0 Chapter 05 1 2nd ...

Page 1028: ... 0 11 2nd Edition Rev 0 12 2nd Edition Rev 0 13 2nd Edition Rev 0 14 2nd Edition Rev 0 100 2nd Edition Rev 0 101 2nd Edition Rev 0 102 2nd Edition Rev 0 103 2nd Edition Rev 0 104 2nd Edition Rev 0 105 2nd Edition Rev 0 106 2nd Edition Rev 0 107 2nd Edition Rev 0 108 2nd Edition Rev 0 109 2nd Edition Rev 0 110 2nd Edition Rev 0 111 2nd Edition Rev 0 200 2nd Edition Rev 0 201 2nd Edition Rev 0 202 2...

Page 1029: ... 2nd Edition Rev 0 4 2nd Edition Rev 0 200 2nd Edition Rev 0 201 2nd Edition Rev 0 202 2nd Edition Rev 0 203 2nd Edition Rev 0 Chapter 92 1 2nd Edition Rev 0 2 2nd Edition Rev 0 3 2nd Edition Rev 0 4 2nd Edition Rev 0 5 2nd Edition Rev 0 6 2nd Edition Rev 0 7 2nd Edition Rev 0 8 2nd Edition Rev 0 9 2nd Edition Rev 0 10 2nd Edition Rev 0 11 2nd Edition Rev 0 12 2nd Edition Rev 0 13 2nd Edition Rev ...

Page 1030: ...dition Rev 0 22 2nd Edition Rev 0 23 2nd Edition Rev 0 24 2nd Edition Rev 0 25 2nd Edition Rev 0 26 2nd Edition Rev 0 27 2nd Edition Rev 0 28 2nd Edition Rev 0 29 2nd Edition Rev 0 30 2nd Edition Rev 0 31 2nd Edition Rev 0 32 2nd Edition Rev 0 33 2nd Edition Rev 0 34 2nd Edition Rev 0 35 2nd Edition Rev 0 ...

Page 1031: ...e basic publication 2 for the second one etc Should be necessary to completely reissue a publication for contents and format changes the Edition code will change to the next number 2 for the second edi tion 3 for the third edition etc Additions deletions and revisions to existing text will be identified by a revision bar black line in the left hand margin of the page adjacent to the change When te...

Page 1032: ...2nd Edition Rev 0 SUPPLEMENT SG 3 RECORD OF REVISIONS Page 2 Record of Revisions Rev Revised page Description of Revision Tecnam Approval EASA Approval Or Under DOA Privileges DO OoA HDO ...

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Page 1035: ...M 1 Description and operation 1 Chapter 31 INDICATING SYSTEM 3 Description and operation 3 Troubleshooting 100 GDU 620 PFD MFD removal installation 201 GRS 77 AHRS removal installation 202 GMU 44 removal installation 203 GDC 74A ADC removal installation 204 Software upload 205 Chapter 34 NAVIGATION 3 Description and operation 3 Maintenance practices 200 1 Standby attitude indicator replacement and...

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Page 1037: ...ge mentioned above When the G500 suite is installed a 40A External Alternator must be installed to provide the necessary amount of current to the LRUs When this design change is applied a dedicated breaker panel is installed on the cockpit LH side Moreover the installation of GNS 430W or other equivalent external NAV GPS source is necessary in order to provide G500 suite with GPS and NAV infor mat...

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Page 1039: ...worthiness limitations The Airworthiness Limitations Section is EASA approved and variations must also be approved The Airworthiness Limitations Section is FAA approved and specifies maintenance required under 14 CFR Sections 43 16 and 91 403 unless an alternative program has been FAA approved ...

Page 1040: ... SUPPLEMENT SG 3 CHAPTER 04 AIRWORTHINESS LIMITATIONS Page 2 CHAPTER O4 AIRWORTHINESS LIMITATIONS No further Airworthiness Limitations are prescribed other than those reported on the basic Maintenance Manual Chapter 04 ...

Page 1041: ...2nd Edition Rev 0 SUPPLEMENT SG 3 CHAPTER 05 TIME LIMITS AND MAINTENANCE SCHEDULE Page 1 Chapter 05 Time Limits and Maintenance schedule ...

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Page 1043: ...ning to Part 43 Appendix E and F Pitot Static leak test as described in Part 91 411 maintenance of the GDC 74A is on condition of failure on ly 5 4 GDU 620 DISPLAY UNIT Maintenance of the GDU 620 is on condition of failure only For regulatory periodic func tional checks refer to approved aircraft maintenance manuals or manual supplements for ac tual aircraft maintenance requirements 5 5 GRS 77 ATT...

Page 1044: ...e GRS 77 remains a Garmin supported product Table herein reported shows the maintenance tasks performed at defined inter vals to retain the Garmin IFDS installation in a serviceable condition by system atic inspection and maintenance These tasks are additional with respect to those reported on Chapter 05 of the basic AMM The inspection program consists of individual inspections performed at the in...

Page 1045: ... compartment for general condition operation and security of installation X 31 Indicating system Inspect Garmin G500 GMU 44 in stalled under the vertical fin for general condition operation and security of installation X 31 Indicating system Inspect Garmin G500 GTP 59 in stalled on the RH lower side wing fuselage for general condition operation and security of installa tion X 31 Indicating system ...

Page 1046: ...2nd Edition Rev 0 SUPPLEMENT SG 3 CHAPTER 05 INSPECTION PROGRAM Page 6 INTENTIONALLY LEFT BLANK ...

Page 1047: ...2nd Edition Rev 0 SUPPLEMENT SG 3 CHAPTER 24 ELECTRICAL SYSTEM Page 1 Chapter 24 Electrical system ...

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Page 1049: ...cessive voltage caused by generator failures The alternative energy source is a lead type battery Gill Teledyne G25 12V 18 Ah in 1h which provides energy for the engine start up or when an alternator failure happens Emergency condition and is connected to the battery bus with a 50A protection breaker The battery is housed in a vented and drained dedicated box accessible through an inspection cap l...

Page 1050: ...ump Fuel Pump Operation Light Rpm Indicator Fuel Pressure Indicator Voltmeter Generator light Field Fuel Level Indicator LH Fuel Level Indicator RH Oil Pressure Indicator Strobe Light Landing Light Navigation Light Trim Actuator Trim Position Indicator Flap actuator Oil Temperature Indicator Cylinder Head Temperature Stall warning GDU 620 PFD MFD GRS 77 AHRS GDC 74A ADC Battery Bus GMA 340 GNS 430...

Page 1051: ...wo allow respectively to connect the battery through a relay to its distribution bus and to provide the field signal to the alternator The second one allows through a relay the power supply of the loads connected to the avionic bus The ignition switches RH and LH are activated through the ignition key which also allows the engine starting WARNING If ignition key is on L R or ON position a propelle...

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Page 1053: ...2nd Edition Rev 0 SUPPLEMENT SG 3 CHAPTER 31 INDICATIONG SYSTEM Page 1 Chapter 31 Indicating system ...

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Page 1055: ...FD and the Multifunction Dis play MFD The system is composed of several units also known as Line Replaceable Units LRUs LRUs have a modular design some ones are installed directly on the in strument panel some other ones are installed remotely in dedicated areas of the a c prescribed by G500 Installation manual Each LRU has a specific function or sub set of functions that contributes to the system...

Page 1056: ...perating mode the Primary Flight Display PFD presents graphical flight instrumentation attitude heading airspeed altitude vertical speed HSI replacing the traditional flight instrument cluster The Multi Function Display MFD displays a full color moving map with navi gation information as well as supplemental data The below schematic shows a block diagram of G500 suite describing the main system in...

Page 1057: ...y flight display PFD and the right side is the multi function display MFD For the GDU 620 RH the right side of the GDU is the primary flight display PFD and the left side is the multi function display MFD The PFD shows primary flight information The MFD shows navigation and flight plan in formation traffic weather and terrain An external configuration module is used so no configuration is required...

Page 1058: ...ces with both the GDC 74 air data computer and the GMU 44 magnetometer The GRS 77 also utilizes GPS signals sent from the GPS SBAS navigator Actual attitude and heading information is sent using ARINC 429 digital interface to the GDU 620 and op tional GAD 43 adapter GMU 44 The GMU 44 magnetometer senses magnetic field information Data is sent to the GRS 77 AHRS for processing to determine aircraft...

Page 1059: ...he GDC 74 is responsible for providing pressure altitude airspeed vertical speed and OAT information to the G500 system The GDC 74 provides data to the GDU 620 and GRS 77 using ARINC 429 digital interfaces The GDC 74 also communicates maintenance and configuration in formation to the GDU 620 using an RS 232 interface GTP59 It is the temperature probe which provides Outside Air Temperature OAT data...

Page 1060: ...n installed to provide the pilot with main flight informations also in the event of G500 failure These instruments are pneumatic and they don t need to be fed by the A C electric power The below table lists the manufacturer and P Ns for the stand by indicators Indicator type Manufacturer P N Airspeed indicator MID CONTINENT 25020 0179 Altimeter MID CONTINENT 15035 1102 ...

Page 1061: ...e shows the main components location inside the airplane Namely GDU 620 located on the instrument panel GRS 77 AHRS located on the rear of baggage compartment GMU 44 located under the vertical fin GDC 74 Air Data Computer located behind the firewall in the RH side GTP 59 located on the lower side of RH wing ...

Page 1062: ...2nd Edition Rev 0 SUPPLEMENT SG 3 CHAPTER 31 INDICATIONG SYSTEM Page 10 Garmin G500 LRUs location ...

Page 1063: ...e below figure shows a schematic of the Pitot static system with the connec tions to the instruments and Air Data Computer Static line is connected with the GDC 74A standby altimeter and standby air speed indicator The Pitot line is connected to GDC 74A unit and to the standby airspeed indicator ...

Page 1064: ...2nd Edition Rev 0 SUPPLEMENT SG 3 CHAPTER 31 INDICATIONG SYSTEM Page 12 Pitot static line scheme ...

Page 1065: ...on Rev 0 SUPPLEMENT SG 3 CHAPTER 31 INDICATIONG SYSTEM Page 13 Number Item 1 Pitot 2 Static and total pressure drainage point 3 Standby airspeed indicator 4 Standby altimeter 5 GDC74A ADC 6 Alternate static port ...

Page 1066: ... 0 SUPPLEMENT SG 3 CHAPTER 31 INDICATIONG SYSTEM Page 14 Instruments panel Following figure shows the typical instruments panel layout for airplanes fitted with Garmin G500 Garmin G500 Instruments panel typical layout ...

Page 1067: ...system to isolate a problem to a faulty LRU The following troubleshooting methods are included LRU Failure Annunciations Red X LRU Failure Indication on the System Status Page Normal Mode Data Path Indication on the System Status Page Configuration Mode ARINC 429 and RS 232 Port Configuration Pages Data Status Indications Fault Messages ...

Page 1068: ... removal of a unit or units to gain access to connectors Follow the guidance given in Section 4 for LRU replacement Refer to the OEM mainte nance documentation for instructions on removing any aircraft access panels LRU FAILURE ANNUNCIATIONS A red X through a display field indicates that a particular display field is not receiving valid data Figure below shows typical display fields and their asso...

Page 1069: ...connector is secure and proper wire harness strain relief is provided Ensure the GRS 77 is fastened down tight ly in its mounting rack and that the mount ing rack is not loose CAUTION do not loosen the mounting rack hardware to the airframe shelf or the aircraft will need to be re leveled and the PITCH ROLL OFF SET procedure performed Cycle GRS 77 power to restart initializa tion Ensure GPS has ac...

Page 1070: ...oving aircraft away from metal objects to determine if metal objects were the source of the interference Allow up to five minutes for the heading to reinitialize Perform a Magnetometer Interference Test to check for interference from onboard electrical system components e g NAV lights Pay par ticular attention to any new electrical devices that have been installed since the aircraft was new Correc...

Page 1071: ...ot turned on even in a monitoring state in the cabin Check PFD Alert Window for PFD MFD or GDC configuration software or failed data path error messages Correct any errors before pro ceeding Inspect GDC 74A pitot static ports and plumb ing for blockage Check GDC 74A configuration settings Reload if unsure they are correct If configuration settings are correct replace the GDC 74A configuration modu...

Page 1072: ...TUS PAGE NORMAL MODE The System Status Page normal mode can be used to help identify a faulty LRU The System Status Page displays information about device connectivity and system data bases Green checks indicate active LRUs red x s indicate failed LRUs Replace any LRU which indicates FAIL status System Status Page ...

Page 1073: ...ation mode by applying power to GDU 620 while holding the ENT key The System Status Page is displayed on the left display while the system is operating in configuration mode The devices online status indicators are as follows Green the LRU status is OK Red the LRU status is FAIL Black the LRU status is TIMEOUT Replace any LRU which indicates FAIL status System Status Configuration Page ...

Page 1074: ...2nd Edition Rev 0 SUPPLEMENT SG 3 CHAPTER 31 INDICATIONG SYSTEM Page 107 FAULT MESSAGES ALERT TEXT The system will display a number of alerts on the GDU 620 Alerts Page ...

Page 1075: ...that a cell phone or a device using cell phone technology is not turned on even in a monitoring state in the cabin Check GPS status If one or both GPS receivers cannot acquire a position lock troubleshoot GPS problems Replace the GRS 77 AHRS1 GPS AHRS 1 operating in exclusively in no GPS mode AHRS is not receiving any GPS information Ensure that at least one GPS has acquired a valid position If GD...

Page 1076: ...Close ADC C B GDC not receiving input from GTP 59 OAT probe Verify wiring is correct ARINC 429 connection from GDC 74A to GRS 77 is not working Verify wir ing is correct CNFG MODULE The configuration module is inoperative Verify wiring to configura tion module Replace configuration module DATA LOST Pilot stored data was lost Recheck data and settings FAN 1 FAIL Fan 1 has reported 0 RPM when it was...

Page 1077: ...quired MANIFEST GDU has received product data for an LRU that should have a manifest entry but is not in the manifest Ensure the manifest is properly configured Refer to Section for additional in formation The LRU software P N and version number in the man ifest does not match the values being reported by that LRU Update the LRU software to match the manifest refer to Section Update the manifest t...

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Page 1079: ...ONG SYSTEM Page 200 MAINTENANCE PRACTICES This Chapter contains the following maintenance tasks description GDU 620 PFD MFD removal installation GRS 77 AHRS removal installation GMU 44 removal installation GDC 74A ADC removal installation Software upload ...

Page 1080: ...ough out from the instrument panel to access the three rear connectors 3 Disconnect the rear connectors 4 Remove the GDU 620 Replacement 1 Visually inspect the connectors to ensure that there are no bent or damaged pins Repair any damage 2 Connect the rear connectors ensuring that each slide lock is secured on both sides 3 Set the GDU 620 into place 4 Install the six mounting screws into the bezel...

Page 1081: ...plate are removed the GRS 77 must be recalibrated See Section 5 6 in the G500 or the G600 Installation Manual Replacement 1 Place the GRS 77 on the mounting plate ensuring the orientation is correct 2 Fasten the unit to the plate using the Phillips thumbscrews Recommended torque is 22 25 inch pounds 3 Visually inspect the connectors to ensure there are no bent or damaged pins Repair any damage 4 C...

Page 1082: ... three screws that hold the GMU 44 to its mounting rack 3 Carefully lift the GMU 44 from the rack 4 Disconnect the wiring harness Replacement 1 Visually inspect the connectors to ensure there are no bent or damaged pins Repair any damage 2 Connect the wiring harness to the GMU 44 3 Lower the GMU 44 into the rack and secure the plate with the three Phillips screws ...

Page 1083: ...2 Loosen each thumbscrew on the hold down clamp and remove the clamp 3 Carefully remove the unit from its mount Replacement 1 Place the unit in the mounting tray 2 Position the locking clamp and fasten using the thumbscrews 3 Connect the Pitot static plumbing 4 Inspect the connector and pins for damage Repair any damage 5 Connect the connector to the unit ensuring that each slide lock is secured o...

Page 1084: ...rcraft systems and avionics G500 P2002 Software Loader Card applicable P N G500 P2002 Installer Unlock Card P N 010 00769 60 G500 P2002 Loader Card Software Configuration Drawing N 22 9 007 1 sheet 2 Garmin G500 Software System SW Upload procedure The system software upload procedure for G500 system must be performed load ing the software for each installed unit Before starting the SW upload proce...

Page 1085: ...ay remove power from the stand by instruments by pulling the circuit breakers 4 Master switch ON 5 GRS breaker push 6 GDC breaker push 7 While holding the ENT key on the GDU620 restore power by closing the GDU circuit breaker 8 When the words appear in the upper center of the PFD MFD release the ENT key 9 The system prompts the user to load the new software version contained on the loader card in ...

Page 1086: ...n shots including software file names versions and part numbers is subject to change and may not be up to date 11 New software is loaded to the GDU620 When complete the following message is shown Press any soft key to acknowledge the prompt The number of files updated may vary depending on the software version to be uploaded 12 The GDU620 software has now bee loaded to the LRU 13 The GDU620 starts...

Page 1087: ... Press ENT key to start the software upload 17 A progress bar showing the percentage of the upload process completed is shown 18 When the upload procedure is completed an Upload complete message will be shown When this message is shown press the ENT key to acknowledge the process completion 19 Repeat steps from 14 to 18 selecting GDC74 20 Repat steps from 14 to 18 selecting GMU44 ...

Page 1088: ...ect G500 software Loader card into the GDU620 top card slot 8 Make sure that GDU620 breaker is pulled Optionally the technician may remove power from the stand by instruments by pulling the circuit breakers 9 Master switch ON 10 GRS breaker push 11 GDC breaker push 12 While holding the ENT key on the GDU620 restore power by closing the GDU circuit breaker 13 When the words appear in the upper cent...

Page 1089: ...ce only All information depicted in screen shots including software file names versions and part numbers is subject to change and may not be up to date 16 New software is loaded to the GDU620 When complete the following message is shown Press any soft key to acknowledge the prompt This step is valid only if ENT key is pressed at previous step 17 The GDU620 starts in configuration mode 18 Go to the...

Page 1090: ...of the upload process completed is shown 22 When the upload procedure is completed an Upload complete message will be shown When this message is shown press the ENT key to acknowledge the process completion 23 Go to the MANIFEST CONFIGURATION page in the SYS page group The manifest will be empty on first use 1 Wait for the GRS 77 GMU 44 and GDC 74A to power up 2 Press the MANIFEST soft key to auto...

Page 1091: ...o Software load confirmation procedure Additional in fo References 1 Start the G500 system in NORMAL mode 2 Go to the AUX System Status page on MFD 3 Check for SW versions shown besides each LRU to be the same of the ones reported in the drawing mentioned above 4 Start the G500 system in CONFIGURATION mode ...

Page 1092: ...e 213 Step no Software load confirmation procedure Additional in fo References 5 Activate the cursor in the System Status page on the PFD 6 Highlight all installed LRUs 7 Verify that the software p n and version match the information found in the drawing reported above ...

Page 1093: ...46 35 Vx 61 61 Vy 66 66 Follow the below instructions to set up the airspeed markings Step no Airspeed Markings setup Additional info References 1 Master OFF 2 GDU breaker pull Optionally the technician may remove power from the stand by instruments by pulling the circuit breakers 3 GRS breaker pull 4 GDC breaker pull 5 Insert the correct Installer Unlock Card 010 00769 60 into the GDU620 bottom c...

Page 1094: ...l remain applied to the system If GDU620 software has to be installed press the ENT key to load new software Else press CLR key All G500 screen shots used in this document are intended to provide visual reference only All information depicted in screen shots including software file names versions and part numbers is subject to change and may not be up to date 13 The GDU620 starts in configuration ...

Page 1095: ...nd calibrating various G500 sub systems Troubleshooting diagnostics information can also be derived from this mode To start the system in Configuration mode Step no G500 Configuration mode Additional info References 1 Master OFF 2 GDU breaker pull 3 GRS breaker pull 4 GDC breaker pull 5 Insert the correct Installer Unlock Card 010 00769 60 into the GDU620 bottom card slot 6 Make sure that SW part ...

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Page 1097: ...2nd Edition Rev 0 SUPPLEMENT SG 3 CHAPTER 31 INDICATIONG SYSTEM Page 1 Chapter 34 Navigation ...

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Page 1099: ...2nd Edition Rev 0 SUPPLEMENT SG 3 CHAPTER 34 DESCRIPTION AND OPERATION Page 3 CHAPTER 34 NAVIGATION DESCRIPTION AND OPERATION General GNS 430W ...

Page 1100: ...2nd Edition Rev 0 SUPPLEMENT SG 3 CHAPTER 34 DESCRIPTION AND OPERATION Page 4 530W ...

Page 1101: ...ition Rev 0 SUPPLEMENT SG 3 CHAPTER 34 MAINTENANCE PRACTICES Page 200 MAINTENANCE PRACTICES This Chapter contains the following maintenance tasks description Standby attitude indicator replacement and testing ...

Page 1102: ...instrument panel cut out 6 Install the attaching screws which fix the instru ment to the aluminum panel Hold firmly the instrument by hand during installation Do not over tighten screws to avoid instrument case dam age 7 Connect instrument electrical wires at the rear of the instrument Be sure that the electrical ca bles don t have radius of cur vature too small the instru ments may not operate co...

Page 1103: ...tation aligning the symbolic airplane with the horizon and retighten the screw 11 C If caging is required caging should be accom plished when the aircraft is in a wings level nor mal cruise attitude as indicated by AHRS If the gyro is caged when the aircraft is not in this atti tude the resulting attitude presentation immedi ately after caging will be in error by the difference between true vertic...

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Page 1107: ...test and service the airplane electrical system when the engine starting battery is installed The information is given in the form of drawings reporting the Tecnam code number 22 9 0007 xxx D D stand for Digital version x digits represent the ATA chapter referenced within this Manual As far as the maintenance practices are concerned make reference to Chapter 92 of the basic AMM Each drawing herein...

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Page 1140: ...Tecnam P2002 JF AMM Supplement S2 1st Edition Rev 0 01 09 2012 P2002 JF post shipment reassembling procedure ...

Page 1141: ...Edition Rev 0 2 1st Edition Rev 0 3 1st Edition Rev 0 ROR 1 1st Edition Rev 0 2 1st Edition Rev 0 TOC 1 1st Edition Rev 0 2 1st Edition Rev 0 Introduction 1 1st Edition Rev 0 2 1st Edition Rev 0 Chapter 12 1 1st Edition Rev 0 2 1st Edition Rev 0 200 1st Edition Rev 0 201 1st Edition Rev 0 202 1st Edition Rev 0 203 1st Edition Rev 0 204 1st Edition Rev 0 205 1st Edition Rev 0 Chapter 55 1 1st Editi...

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Page 1144: ...basic publication 2 for the second one etc Should be necessary to completely reissue a publication for contents and format changes the Edition code will change to the next number 2 for the second edi tion 3 for the third edition etc Additions deletions and revisions to existing text will be identified by a revision bar black line in the left hand margin of the page adjacent to the change When tech...

Page 1145: ...Page 2 SUPPLEMENT S2 RECORD OF REVISIONS 1st Edition Rev0 Record of Revisions Rev Revised page Description of Revision Tecnam Approval EASA Approval Or Under DOA Privileges DO OoA HDO ...

Page 1146: ...NON È DEFINITO Maintenance Practices 200 1 Stabilator pre installation procedure 201 2 Stabilator installation 201 CHAPTER 57 WINGS 1 Maintenance Practices 200 1 Wing pre installation procedure 201 2 Wing installation 201 3 Aileron control assembling 204 4 Flaps control assembling 206 5 Control cable and hoses pre installation procedure 207 6 Control cable and hoses installation 207 CHAPTER 72 ENG...

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Page 1148: ... some part in the supplements for engine check and the instruction for the installation and fastening of electrical wire in the wing compartment Herein are reported the ATA Chapters impacted by procedure in subject For the correct reassembly the suggested installation sequence is the following 1 The wing fuselage coupling refer to chapter 57 in this document 2 Flaps and Ailerons control assembly r...

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Page 1150: ...Page 1 SUPPLEMENT S2 SERVICING 1st Edition Rev Chapter 12 Servicing ...

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Page 1152: ...MENT S2 SERVICING POST SHIPMENT REASSEMBLY INSTRUCTION 1st Edition Rev MAINTENANCE PRACTICES This Chapter contains the following maintenance tasks description Seats removal Seats installation Battery cable connection ...

Page 1153: ...ing device Refer to Figure 12 1 4 Pull seat lever then slide seat all forward Refer to Figure 12 2 5 Pull up seat and remove it from his location 6 Apply the same procedure for the other seat 2 SEATS INSTALLATION Procedure Step no Seats installation Task description Additional info References 1 Engage parking brake 2 Make sure that Master switch is set to off 3 Put seat in his location 4 Pull seat...

Page 1154: ...ake sure that Master switch is set to OFF 3 Open inspection cap F9 Refer basic manual ATA 06 WARNING When installing a battery take special care to ensure that no sparks are created by tools and that the terminals are not shorted out by tools 4 Remove the protective tape 5 Connect the negative cable if not installed 6 Connect the positive cable to the battery Refer to Figure 12 3 7 Make sure that ...

Page 1155: ...Page 203 SUPPLEMENT S2 SERVICING POST SHIPMENT REASSEMBLY INSTRUCTION 1st Edition Rev Figure 12 1 Seats locking device ...

Page 1156: ...Page 204 SUPPLEMENT S2 SERVICING POST SHIPMENT REASSEMBLY INSTRUCTION 1st Edition Rev Figure 12 2 Seats remove procedure Figure 12 3 Battery cables connection ...

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Page 1158: ...Page 1 SUPPLEMENT S2 STABILATOR AND RUDDER 1st Edition Rev Chapter 55 Stabilator and Rudder ...

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Page 1160: ...LATOR AND RUDDER POST SHIPMENT REASSEMBLY INSTRUCTION 1st Edition Rev MAINTENANCE PRACTICES This Chapter contains the following maintenance tasks description Stabilator pre installation procedure Stabilator installation procedure ...

Page 1161: ...stallation Task description Additional info References 1 Engage parking brake 2 Make sure that Master switch is set to OFF 3 Put right half stabilator on the torque tube 4 Screw the RH stabilator attachment Spacer washer bolt nut Refer to basic manual ATA 20 for correct torque value Refer to Figures 55 1 and 55 4 5 Put the left stabilator on torque tube and screw the LH stabilator attachment Refer...

Page 1162: ...Page 202 SUPPLEMENT S2 STABILATOR AND RUDDER POST SHIPMENT REASSEMBLY INSTRUCTION 1st Edition Rev Figure 55 1 Stabilator attachment Figure 55 2 Stabilator rear side screws ...

Page 1163: ...Page 203 SUPPLEMENT S2 STABILATOR AND RUDDER POST SHIPMENT REASSEMBLY INSTRUCTION 1st Edition Rev Figure 55 3 Stabilator trim tab connection 7 Figure 55 4 Stabilator assembling ...

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Page 1166: ...Page 1 SUPPLEMENT S2 WINGS 1st Edition Rev0 Chapter 57 Wings ...

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Page 1168: ...MAINTENANCE PRACTICES This Chapter contains the following maintenance tasks description Wing pre installation procedure Wing installation Ailerons control assembly Flaps control assembly Control cable and hoses pre installation procedure Control cable and hoses installation procedure ...

Page 1169: ...omplete procedure for wings installation WARNING For this operation are required minimum 3 persons 1 person in correspondence of the front spare attachment 1 person in correspondence of the rear spare attachment and 1 person in correspondence of the tip for wing suspension NOTE On the wing to fuselage main fittings there is a gap of about 1mm between the wing s main spar lugs and the carrythrough ...

Page 1170: ...uselage 2 Connect the LH wing on fuselage and place the bolts in their original location Use 2xbolts 1xshim 4 alu minium washers 2x nuts Refer to Figures 57 1 and 57 2 3 Connect the RH wing on fuselage and place the bolts in their original location Use 2xbolts 1xshim 4 alu minium washers 2x nuts Refer to Figure 57 1 and 57 2 Torque value front bolts NAS 1308 28D 100 Nm Torque value rear bolts M8 2...

Page 1171: ...Page 203 SUPPLEMENT S2 WINGS POST SHIPMENT REASSEMBLY INSTRUCTION 1st Edition Rev Figure 57 2 External wing attachment ...

Page 1172: ...l info References 1 Remove seats 2 Remove cabin floor panels Refer to Figure 57 3 3 Connect ailerons control applying bolts 4 Use 2xbolts 2xspacers 2xaluminum washers and 2xnuts Refer to Figure 57 4 and 57 5 4 Connect the small bar 3 to the pushrods 5 Refer to Figure 57 4 and 57 5 WARNING Report a slippage marks at the end of installation Figure 57 3 Floor cabin panels ...

Page 1173: ...Page 205 SUPPLEMENT S2 WINGS POST SHIPMENT REASSEMBLY INSTRUCTION 1st Edition Rev Figure 57 4 Ailerons control assembling Figure 57 5 Ailerons control command lever connection ...

Page 1174: ...assembly Task description Additional info References 1 Connect flaps control applying roller bearings 6 that link push pull rod 5 to flap control plate Use 2xbolts 2xaluminum washers 2xnuts Refer to Figure 57 6 2 Repeat for other side WARNING Report a slippage marks at the end of installation Figure 57 6 Flaps control assembling ...

Page 1175: ...k description Additional info References 1 Engage parking brake 2 Make sure that Master switch is set to OFF 3 Remove the protective cap and connect the fuel system hoses LH and RH side Refer to Figures 57 7 and 57 8 4 Connect the fuel quantity sensors TELEVEL wiring and the position lights wiring LH and RH side Pay attention aligns the connectors with the same placards Refer to Figures 57 7 and 5...

Page 1176: ...oses of wing as marked before Connect the Pitot Heat connector only if VFR Night package is installed Refer to Figure 57 7 8 Connect stall warning device connector on RH wing Refer to Figure 57 8 9 Install fairings between the wings and fuse lage 10 Install the wing s composite root leading edge 11 Install all cabin floor panels and all baggage compartment panels Refer to Figure 57 3 12 Install th...

Page 1177: ...Page 209 SUPPLEMENT S2 WINGS POST SHIPMENT REASSEMBLY INSTRUCTION 1st Edition Rev Figure 57 7 LH wing cable and hoses Figure 57 8 RH wing cable and hoses ...

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Page 1180: ...Page 1 SUPPLEMENT S2 ENGINE 1st Edition Rev Chapter 72 Engine ...

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Page 1182: ...200 SUPPLEMENT S2 ENGINE POST SHIPMENT REASSEMBLY INSTRUCTION 1st Edition Rev MAINTENANCE PRACTICES This Chapter contains the following maintenance tasks description Engine check Powerplant controls rigging ...

Page 1183: ...Page 201 SUPPLEMENT S2 ENGINE POST SHIPMENT REASSEMBLY INSTRUCTION 1st Edition Rev 1 ENGINE CHECK Refer to Rotax maintenance manual 912 Series part number 899735 ...

Page 1184: ...ional info References 1 Engage parking brake 2 Open engine cowlings upper and lower See Chapter 54 of Basic MM AIR BOX CONTROL RIGGING 1 Connect airbox bowden cable to airbox control lever 2 Check carburetor heat control stroke Ensure that when Carb Heat knob is full forward Off position air box control lever is fully rightward Refer to Figure 77 1 Ensure that when Carb Heat knob is full backward ...

Page 1185: ...ring to adjust cable as needed Screw nut to lock position Connect bowden cable to con trol lever 4 Check carburetor heat control stroke CHOKE CONTROL RIGGING 1 Connect choke bowden cable to choke control lever 2 Check choke control stroke Ensure that when choke knob is fully upward choke control lever reaches the relative stop screw Refer to Figure 77 3 Ensure that when choke knob is fully downwar...

Page 1186: ...ol stroke THROTTLE CONTROL RIGGING 1 Connect throttle bowden cable to throttle control lever 2 Check throttle control stroke Ensure that when throttle knob is fully forward throttle control lever is fully forward Refer to Figure 77 5 Ensure that when throttle knob is fully backward throttle control lever is fully backward Refer to Figure 77 6 3 Stroke adjusting move throttle control cable from thr...

Page 1187: ...Page 205 SUPPLEMENT S2 ENGINE POST SHIPMENT REASSEMBLY INSTRUCTION 1st Edition Rev Figure 72 1 Carb Heat OFF ...

Page 1188: ...Page 206 SUPPLEMENT S2 ENGINE POST SHIPMENT REASSEMBLY INSTRUCTION 1st Edition Rev Figure 72 2 Carb Heat ON ...

Page 1189: ...Page 207 SUPPLEMENT S2 ENGINE POST SHIPMENT REASSEMBLY INSTRUCTION 1st Edition Rev Figure 72 3 Choke OFF Figure 72 4 Choke ON ...

Page 1190: ...Page 208 SUPPLEMENT S2 ENGINE POST SHIPMENT REASSEMBLY INSTRUCTION 1st Edition Rev Figure 72 5 Throttle maximum power Figure 72 6 Throttle minimum power ...

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Page 1192: ...Tecnam 2002 JF AMM Supplement S 1 2nd Edition Rev 0 28 02 2011 For airplanes embodying the Design Change MOD2002 041 Garmin G500 Installation ...

Page 1193: ...INTENTIONALLY LEFT BLANK ...

Page 1194: ... Section Page Edition Revision LOEP 1 2nd Edition Rev 0 2 2nd Edition Rev 0 3 2nd Edition Rev 0 4 2nd Edition Rev 0 5 2nd Edition Rev 0 6 2nd Edition Rev 0 7 2nd Edition Rev 0 8 2nd Edition Rev 0 ROR 1 2nd Edition Rev 0 2 2nd Edition Rev 0 3 2nd Edition Rev 0 4 2nd Edition Rev 0 TOC 1 2nd Edition Rev 0 2 2nd Edition Rev 0 3 2nd Edition Rev 0 4 2nd Edition Rev 0 Introduction 1 2nd Edition Rev 0 2 2...

Page 1195: ... 6 2nd Edition Rev 0 7 2nd Edition Rev 0 8 2nd Edition Rev 0 Chapter 23 1 2nd Edition Rev 0 2 2nd Edition Rev 0 Chapter 24 1 2nd Edition Rev 0 2 2nd Edition Rev 0 3 2nd Edition Rev 0 4 2nd Edition Rev 0 5 2nd Edition Rev 0 6 2nd Edition Rev 0 7 2nd Edition Rev 0 100 2nd Edition Rev 0 200 2nd Edition Rev 0 201 2nd Edition Rev 0 Chapter 34 1 2nd Edition Rev 0 2 2nd Edition Rev 0 3 2nd Edition Rev 0 ...

Page 1196: ...17 2nd Edition Rev 0 18 2nd Edition Rev 0 19 2nd Edition Rev 0 20 2nd Edition Rev 0 21 2nd Edition Rev 0 22 2nd Edition Rev 0 23 2nd Edition Rev 0 24 2nd Edition Rev 0 100 2nd Edition Rev 0 101 2nd Edition Rev 0 200 2nd Edition Rev 0 201 2nd Edition Rev 0 202 2nd Edition Rev 0 203 2nd Edition Rev 0 204 2nd Edition Rev 0 205 2nd Edition Rev 0 206 2nd Edition Rev 0 207 2nd Edition Rev 0 208 2nd Edit...

Page 1197: ...0 221 2nd Edition Rev 0 222 2nd Edition Rev 0 223 2nd Edition Rev 0 224 2nd Edition Rev 0 225 2nd Edition Rev 0 226 2nd Edition Rev 0 227 2nd Edition Rev 0 228 2nd Edition Rev 0 229 2nd Edition Rev 0 230 2nd Edition Rev 0 231 2nd Edition Rev 0 232 2nd Edition Rev 0 233 2nd Edition Rev 0 234 2nd Edition Rev 0 235 2nd Edition Rev 0 236 2nd Edition Rev 0 237 2nd Edition Rev 0 238 2nd Edition Rev 0 23...

Page 1198: ...0 252 2nd Edition Rev 0 253 2nd Edition Rev 0 254 2nd Edition Rev 0 255 2nd Edition Rev 0 256 2nd Edition Rev 0 257 2nd Edition Rev 0 258 2nd Edition Rev 0 259 2nd Edition Rev 0 260 2nd Edition Rev 0 261 2nd Edition Rev 0 262 2nd Edition Rev 0 263 2nd Edition Rev 0 264 2nd Edition Rev 0 265 2nd Edition Rev 0 266 2nd Edition Rev 0 267 2nd Edition Rev 0 268 2nd Edition Rev 0 269 2nd Edition Rev 0 27...

Page 1199: ... Edition Rev 0 6 2nd Edition Rev 0 7 2nd Edition Rev 0 8 2nd Edition Rev 0 9 2nd Edition Rev 0 10 2nd Edition Rev 0 11 2nd Edition Rev 0 12 2nd Edition Rev 0 13 2nd Edition Rev 0 14 2nd Edition Rev 0 15 2nd Edition Rev 0 16 2nd Edition Rev 0 17 2nd Edition Rev 0 18 2nd Edition Rev 0 19 2nd Edition Rev 0 20 2nd Edition Rev 0 21 2nd Edition Rev 0 22 2nd Edition Rev 0 23 2nd Edition Rev 0 24 2nd Edit...

Page 1200: ...P Page 7 Section Page Edition Revision 28 2nd Edition Rev 0 29 2nd Edition Rev 0 30 2nd Edition Rev 0 31 2nd Edition Rev 0 Chapter 92 32 2nd Edition Rev 0 33 2nd Edition Rev 0 34 2nd Edition Rev 0 35 2nd Edition Rev 0 36 2nd Edition Rev 0 ...

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Page 1202: ...e basic publication 2 for the second one etc Should be necessary to completely reissue a publication for contents and format changes the Edition code will change to the next number 2 for the second edi tion 3 for the third edition etc Additions deletions and revisions to existing text will be identified by a revision bar black line in the left hand margin of the page adjacent to the change When te...

Page 1203: ...2nd Edition Rev 0 SUPPLEMENT SG 1 RECORD OF REVISIONS Page 2 Record of Revisions Rev Revised page Description of Revision Tecnam Approval EASA Approval Or Under DOA Privileges DO OoA HDO ...

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Page 1206: ... Errore Il segnalibro non è definito 5 GDU 1040 display removal installation testingErrore Il segnalibro non è definito 6 GMA 1347 removal installation testing Errore Il segnalibro non è definito 7 GIA 63W removal installation testing Errore Il segnalibro non è definito 8 GDC 74 removal installation Errore Il segnalibro non è definito 9 GDC 74 testing and leak test Errore Il segnalibro non è defin...

Page 1207: ...re Il segnalibro non è definito 13 1 ADF check out Errore Il segnalibro non è definito 13 2 DME check out Errore Il segnalibro non è definito 13 3 Final check list Errore Il segnalibro non è definito 16 Configuration mode Errore Il segnalibro non è definito Chapter 92 WIRING DIAGRAMS 108 ...

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Page 1210: ...ge mentioned above When the G500 suite is installed a 40A External Alternator must be installed to provide the necessary amount of current to the LRUs When this design change is applied a dedicated breaker panel is installed on the cockpit LH side Moreover the installation of GNS 430W or other equivalent external NAV GPS source is necessary in order to provide G500 suite with GPS and NAV infor mat...

Page 1211: ...2nd Edition Rev 0 SUPPLEMENT SG 1 INTRODUCTION Page 2 INTENTIONALLY LEFT BLANK ...

Page 1212: ...worthiness limitations The Airworthiness Limitations Section is EASA approved and variations must also be approved The Airworthiness Limitations Section is FAA approved and specifies maintenance required under 14 CFR Sections 43 16 and 91 403 unless an alternative program has been FAA approved ...

Page 1213: ... SUPPLEMENT SG 1 CHAPTER 04 AIRWORTHINESS LIMITATIONS Page 2 CHAPTER O4 AIRWORTHINESS LIMITATIONS No further Airworthiness Limitations are prescribed other than those reported on the basic Maintenance Manual Chapter 04 ...

Page 1214: ...2nd Edition Rev 0 SUPPLEMENT SG 1 CHAPTER 05 TIME LIMITS AND MAINTENANCE SCHEDULE Page 1 Chapter 05 Time Limits and Maintenance schedule ...

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Page 1216: ...ning to Part 43 Appendix E and F Pitot Static leak test as described in Part 91 411 maintenance of the GDC 74A is on condition of failure on ly 5 4 GDU 620 DISPLAY UNIT Maintenance of the GDU 620 is on condition of failure only For regulatory periodic func tional checks refer to approved aircraft maintenance manuals or manual supplements for ac tual aircraft maintenance requirements 5 5 GRS 77 ATT...

Page 1217: ...e GRS 77 remains a Garmin supported product Table herein reported shows the maintenance tasks performed at defined inter vals to retain the Garmin IFDS installation in a serviceable condition by system atic inspection and maintenance These tasks are additional with respect to those reported on Chapter 05 of the basic AMM The inspection program consists of individual inspections performed at the in...

Page 1218: ... compartment for general condition operation and security of installation X 31 Indicating system Inspect Garmin G500 GMU 44 in stalled under the vertical fin for general condition operation and security of installation X 31 Indicating system Inspect Garmin G500 GTP 59 in stalled on the RH lower side wing fuselage for general condition operation and security of installa tion X 31 Indicating system ...

Page 1219: ...2nd Edition Rev 0 SUPPLEMENT SG 1 CHAPTER 05 INSPECTION PROGRAM Page 6 INTENTIONALLY LEFT BLANK ...

Page 1220: ...2nd Edition Rev 0 SUPPLEMENT SG 1 CHAPTER 24 ELECTRICAL SYSTEM Page 1 Chapter 24 Electrical system ...

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Page 1222: ...excessive voltage caused by generator failures The alternative energy source is a lead type battery Gill Teledyne G25 12V 18 Ah in 1h which provides energy for the engine start up or when an alternator failure happens Emergency condition and is connected to the battery bus with a 50A protection breaker The battery is housed in a vented and drained dedicated box accessible through an inspection cap...

Page 1223: ... Pump Fuel Pump Operation Light Rpm Indicator Fuel Pressure Indicator Voltmeter Generator light Field Fuel Level Indicator LH Fuel Level Indicator RH Oil Pressure Indicator Strobe Light Landing Light Navigation Light Trim Actuator Trim Position Indicator Flap actuator Oil Temperature Indicator Cylinder Head Temperature Stall warning GDU 620 PFD MFD GRS 77 AHRS GDC 74A ADC Battery Bus GMA 340 GNS 4...

Page 1224: ... two allow respectively to connect the battery through a relay to its distribution bus and to provide the field signal to the alternator The second one allows through a relay the power supply of the loads connected to the avionic bus The ignition switches RH and LH are activated through the ignition key which also allows the engine starting WARNING If ignition key is on L R or ON position a propel...

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Page 1226: ...2nd Edition Rev 0 SUPPLEMENT SG 1 CHAPTER 24 TROUBLESHOOTING Page 100 TROUBLESHOOTING Refer to basic MM Chapter 24 ...

Page 1227: ...2nd Edition Rev 0 SUPPLEMENT SG 1 CHAPTER 24 MAINTENANCE PRACTICES Page 200 MAINTENANCE PRACTICES Refer to basic MM Chapter 24 ...

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Page 1229: ...2nd Edition Rev 0 SUPPLEMENT SG 1 CHAPTER 34 NAVIGATION Page 1 Chapter 31 Indicating system ...

Page 1230: ...2nd Edition Rev 0 SUPPLEMENT SG 1 CHAPTER 34 NAVIGATION Page 2 INTENTIONALLY LEFT BLANK ...

Page 1231: ...ay PFD and the Multifunction Dis play MFD The system is composed of several units also known as Line Replaceable Units LRUs LRUs have a modular design some ones are installed directly on the in strument panel some other ones are installed remotely in dedicated areas of the a c prescribed by G500 Installation manual Each LRU has a specific function or sub set of functions that contributes to the sy...

Page 1232: ...Flight Display PFD presents graphical flight instrumentation attitude heading airspeed altitude vertical speed HSI replacing the traditional flight instrument cluster The Multi Function Display MFD displays a full color moving map with navi gation information as well as supplemental data The below schematic shows a block diagram of G500 suite describing the main system interconnections Garmin G500...

Page 1233: ...he right side is the multi function display MFD For the GDU 620 RH the right side of the GDU is the primary flight display PFD and the left side is the multi function display MFD The PFD shows primary flight information The MFD shows navigation and flight plan in formation traffic weather and terrain An external configuration module is used so no configuration is required if the GDU 620 is replace...

Page 1234: ...with both the GDC 74 air data computer and the GMU 44 magnetometer The GRS 77 also utilizes GPS signals sent from the GPS SBAS navigator Actual attitude and heading information is sent using ARINC 429 digital interface to the GDU 620 and op tional GAD 43 adapter GMU 44 The GMU 44 magnetometer senses magnetic field information Data is sent to the GRS 77 AHRS for processing to determine aircraft mag...

Page 1235: ...DC 74 is responsible for providing pressure altitude airspeed vertical speed and OAT information to the G500 system The GDC 74 provides data to the GDU 620 and GRS 77 using ARINC 429 digital interfaces The GDC 74 also communicates maintenance and configuration in formation to the GDU 620 using an RS 232 interface GTP59 It is the temperature probe which provides Outside Air Temperature OAT data to ...

Page 1236: ...stalled to provide the pilot with main flight informations also in the event of G500 failure These instruments are pneumatic and they don t need to be fed by the A C electric power The below table lists the manufacturer and P Ns for the stand by indicators Indicator type Manufacturer P N Airspeed indicator MID CONTINENT 25020 0179 Altimeter MID CONTINENT 15035 1102 ...

Page 1237: ...2nd Edition Rev 0 SUPPLEMENT SG 1 CHAPTER 34 NAVIGATION Page 6 INTENTIONALLY LEFT BLANK ...

Page 1238: ...ows the main components location inside the airplane Namely GDU 620 located on the instrument panel GRS 77 AHRS located on the rear of baggage compartment GMU 44 located under the vertical fin GDC 74 Air Data Computer located behind the firewall in the RH side GTP 59 located on the lower side of RH wing ...

Page 1239: ...2nd Edition Rev 0 SUPPLEMENT SG 1 CHAPTER 34 NAVIGATION Page 8 Garmin G500 LRUs location ...

Page 1240: ...ow figure shows a schematic of the Pitot static system with the connec tions to the instruments and Air Data Computer Static line is connected with the GDC 74A standby altimeter and standby air speed indicator The Pitot line is connected to GDC 74A unit and to the standby airspeed indicator ...

Page 1241: ...2nd Edition Rev 0 SUPPLEMENT SG 1 CHAPTER 34 NAVIGATION Page 10 Pitot static line scheme ...

Page 1242: ...dition Rev 0 SUPPLEMENT SG 1 CHAPTER 34 NAVIGATION Page 11 Number Item 1 Pitot 2 Static and total pressure drainage point 3 Standby airspeed indicator 4 Standby altimeter 5 GDC74A ADC 6 Alternate static port ...

Page 1243: ... Rev 0 SUPPLEMENT SG 1 CHAPTER 34 NAVIGATION Page 12 Instruments panel Following figure shows the typical instruments panel layout for airplanes fitted with Garmin G500 Garmin G500 Instruments panel typical layout ...

Page 1244: ...m to isolate a problem to a faulty LRU The following troubleshooting methods are included LRU Failure Annunciations Red X LRU Failure Indication on the System Status Page Normal Mode Data Path Indication on the System Status Page Configuration Mode ARINC 429 and RS 232 Port Configuration Pages Data Status Indications Fault Messages ...

Page 1245: ...oval of a unit or units to gain access to connectors Follow the guidance given in Section 4 for LRU replacement Refer to the OEM mainte nance documentation for instructions on removing any aircraft access panels LRU FAILURE ANNUNCIATIONS A red X through a display field indicates that a particular display field is not receiving valid data Figure below shows typical display fields and their associat...

Page 1246: ...ctor is secure and proper wire harness strain relief is provided Ensure the GRS 77 is fastened down tight ly in its mounting rack and that the mount ing rack is not loose CAUTION do not loosen the mounting rack hardware to the airframe shelf or the aircraft will need to be re leveled and the PITCH ROLL OFF SET procedure performed Cycle GRS 77 power to restart initializa tion Ensure GPS has acquire...

Page 1247: ...g aircraft away from metal objects to determine if metal objects were the source of the interference Allow up to five minutes for the heading to reinitialize Perform a Magnetometer Interference Test to check for interference from onboard electrical system components e g NAV lights Pay par ticular attention to any new electrical devices that have been installed since the aircraft was new Correct an...

Page 1248: ... monitoring state in the cabin Check PFD Alert Window for PFD MFD or GDC configuration software or failed data path error messages Correct any errors before proceeding Inspect GDC 74A pitot static ports and plumbing for blockage Check GDC 74A configuration settings Reload if unsure they are correct If configuration settings are correct replace the GDC 74A configuration module If problem persists r...

Page 1249: ...PAGE NORMAL MODE The System Status Page normal mode can be used to help identify a faulty LRU The System Status Page displays information about device connectivity and system data bases Green checks indicate active LRUs red x s indicate failed LRUs Replace any LRU which indicates FAIL status System Status Page ...

Page 1250: ...n mode by applying power to GDU 620 while holding the ENT key The System Status Page is displayed on the left display while the system is operating in configuration mode The devices online status indicators are as follows Green the LRU status is OK Red the LRU status is FAIL Black the LRU status is TIMEOUT Replace any LRU which indicates FAIL status System Status Configuration Page ...

Page 1251: ...2nd Edition Rev 0 SUPPLEMENT SG 1 CHAPTER 34 NAVIGATION Page 20 FAULT MESSAGES ALERT TEXT The system will display a number of alerts on the GDU 620 Alerts Page ...

Page 1252: ...a cell phone or a device using cell phone technology is not turned on even in a monitoring state in the cabin Check GPS status If one or both GPS receivers cannot acquire a position lock troubleshoot GPS problems Replace the GRS 77 AHRS1 GPS AHRS 1 operating in exclusively in no GPS mode AHRS is not receiving any GPS information Ensure that at least one GPS has acquired a valid position If GDU 620...

Page 1253: ... not receiving input from GTP 59 OAT probe Verify wiring is correct ARINC 429 connection from GDC 74A to GRS 77 is not working Verify wir ing is correct CNFG MODULE The configuration module is inoperative Verify wiring to configura tion module Replace configuration module DATA LOST Pilot stored data was lost Recheck data and settings FAN 1 FAIL Fan 1 has reported 0 RPM when it was powered with a P...

Page 1254: ...U has received product data for an LRU that should have a manifest entry but is not in the manifest Ensure the manifest is properly configured Refer to Section for additional in formation The LRU software P N and version number in the man ifest does not match the values being reported by that LRU Update the LRU software to match the manifest refer to Section Update the manifest to match the LRU so...

Page 1255: ...IGATION Page 24 MAINTENANCE PRACTICES This Chapter contains the following maintenance tasks description GDU 620 PFD MFD removal installation GRS 77 AHRS removal installation GMU 44 removal installation GDC 74A ADC removal installation Software upload ...

Page 1256: ...h out from the instrument panel to access the three rear connectors 3 Disconnect the rear connectors 4 Remove the GDU 620 Replacement 1 Visually inspect the connectors to ensure that there are no bent or damaged pins Repair any damage 2 Connect the rear connectors ensuring that each slide lock is secured on both sides 3 Set the GDU 620 into place 4 Install the six mounting screws into the bezel ...

Page 1257: ...te are removed the GRS 77 must be recalibrated See Section 5 6 in the G500 or the G600 Installation Manual Replacement 1 Place the GRS 77 on the mounting plate ensuring the orientation is correct 2 Fasten the unit to the plate using the Phillips thumbscrews Recommended torque is 22 25 inch pounds 3 Visually inspect the connectors to ensure there are no bent or damaged pins Repair any damage 4 Conn...

Page 1258: ...ee screws that hold the GMU 44 to its mounting rack 3 Carefully lift the GMU 44 from the rack 4 Disconnect the wiring harness Replacement 1 Visually inspect the connectors to ensure there are no bent or damaged pins Repair any damage 2 Connect the wiring harness to the GMU 44 3 Lower the GMU 44 into the rack and secure the plate with the three Phillips screws ...

Page 1259: ...oosen each thumbscrew on the hold down clamp and remove the clamp 3 Carefully remove the unit from its mount Replacement 1 Place the unit in the mounting tray 2 Position the locking clamp and fasten using the thumbscrews 3 Connect the Pitot static plumbing 4 Inspect the connector and pins for damage Repair any damage 5 Connect the connector to the unit ensuring that each slide lock is secured on b...

Page 1260: ...aft systems and avionics G500 P2002 Software Loader Card applicable P N G500 P2002 Installer Unlock Card P N 010 00769 60 G500 P2002 Loader Card Software Configuration Drawing N 22 9 007 1 sheet 2 Garmin G500 Software System SW Upload procedure The system software upload procedure for G500 system must be performed load ing the software for each installed unit Before starting the SW upload procedur...

Page 1261: ...emove power from the stand by instruments by pulling the circuit breakers 4 Master switch ON 5 GRS breaker push 6 GDC breaker push 7 While holding the ENT key on the GDU620 restore power by closing the GDU circuit breaker 8 When the words appear in the upper center of the PFD MFD release the ENT key 9 The system prompts the user to load the new software version contained on the loader card in the ...

Page 1262: ...ts including software file names versions and part numbers is subject to change and may not be up to date 11 New software is loaded to the GDU620 When complete the following message is shown Press any soft key to acknowledge the prompt The number of files updated may vary depending on the software version to be uploaded 12 The GDU620 software has now bee loaded to the LRU 13 The GDU620 starts in c...

Page 1263: ...ss ENT key to start the software upload 17 A progress bar showing the percentage of the upload process completed is shown 18 When the upload procedure is completed an Upload complete message will be shown When this message is shown press the ENT key to acknowledge the process completion 19 Repeat steps from 14 to 18 selecting GDC74 20 Repat steps from 14 to 18 selecting GMU44 ...

Page 1264: ...rrect Installer Unlock Card 010 00769 60 into the GDU620 bottom card slot 6 Make sure that SW part number reported on the SD Loader Card is the correct one 7 Insert the correct G500 software Loader card into the GDU620 top card slot 8 Make sure that GDU620 breaker is pulled Optionally the technician may remove power from the stand by instruments by pulling the circuit breakers 9 Master switch ON 1...

Page 1265: ...date 15 Ensure that power will remain applied to the system If GDU620 software has to be installed press the ENT key to load new software Else press CLR key All G500 screen shots used in this document are intended to provide visual reference only All information depicted in screen shots including software file names versions and part numbers is subject to change and may not be up to date 16 New so...

Page 1266: ...he software upload 21 A progress bar showing the percentage of the upload process completed is shown 22 When the upload procedure is completed an Upload complete message will be shown When this message is shown press the ENT key to acknowledge the process completion 23 Go to the MANIFEST CONFIGURATION page in the SYS page group The manifest will be empty on first use 1 Wait for the GRS 77 GMU 44 a...

Page 1267: ...tep no Software load confirmation procedure Additional in fo References 1 Start the G500 system in NORMAL mode 2 Go to the AUX System Status page on MFD 3 Check for SW versions shown besides each LRU to be the same of the ones reported in the drawing mentioned above 4 Start the G500 system in CONFIGURATION mode ...

Page 1268: ... Step no Software load confirmation procedure Additional in fo References 5 Activate the cursor in the System Status page on the PFD 6 Highlight all installed LRUs 7 Verify that the software p n and version match the information found in the drawing reported above ...

Page 1269: ...5 Vx 61 61 Vy 66 66 Follow the below instructions to set up the airspeed markings Step no Airspeed Markings setup Additional info References 1 Master OFF 2 GDU breaker pull Optionally the technician may remove power from the stand by instruments by pulling the circuit breakers 3 GRS breaker pull 4 GDC breaker pull 5 Insert the correct Installer Unlock Card 010 00769 60 into the GDU620 bottom card ...

Page 1270: ...main applied to the system If GDU620 software has to be installed press the ENT key to load new software Else press CLR key All G500 screen shots used in this document are intended to provide visual reference only All information depicted in screen shots including software file names versions and part numbers is subject to change and may not be up to date 13 The GDU620 starts in configuration mode...

Page 1271: ...librating various G500 sub systems Troubleshooting diagnostics information can also be derived from this mode To start the system in Configuration mode Step no G500 Configuration mode Additional info References 1 Master OFF 2 GDU breaker pull 3 GRS breaker pull 4 GDC breaker pull 5 Insert the correct Installer Unlock Card 010 00769 60 into the GDU620 bottom card slot 6 Make sure that SW part numbe...

Page 1272: ...2nd Edition Rev 0 SUPPLEMENT SG 1 CHAPTER 34 NAVIGATION Page 41 INTENTIONALLY LEFT BLANK ...

Page 1273: ...2nd Edition Rev 0 SUPPLEMENT SG 1 CHAPTER 34 NAVIGATION Page 1 Chapter 34 Navigation ...

Page 1274: ...2nd Edition Rev 0 SUPPLEMENT SG 1 CHAPTER 34 NAVIGATION Page 2 INTENTIONALLY LEFT BLANK ...

Page 1275: ...2nd Edition Rev 0 SUPPLEMENT SG 1 CHAPTER 34 DESCRIPTION AND OPERATION Page 3 CHAPTER 34 NAVIGATION DESCRIPTION AND OPERATION General GNS 430W ...

Page 1276: ...2nd Edition Rev 0 SUPPLEMENT SG 1 CHAPTER 34 DESCRIPTION AND OPERATION Page 4 530W ...

Page 1277: ...2nd Edition Rev 0 SUPPLEMENT SG 1 CHAPTER 34 DESCRIPTION AND OPERATION Page 5 INTENTIONALLY LEFT BLANK ...

Page 1278: ...2nd Edition Rev 0 SUPPLEMENT SG 1 CHAPTER 34 TROUBLESHOOTING Page 100 TROUBLESHOOTING ...

Page 1279: ...ition Rev 0 SUPPLEMENT SG 1 CHAPTER 34 MAINTENANCE PRACTICES Page 101 MAINTENANCE PRACTICES This Chapter contains the following maintenance tasks description Standby attitude indicator replacement and testing ...

Page 1280: ...2nd Edition Rev 0 SUPPLEMENT SG 1 CHAPTER 34 MAINTENANCE PRACTICES Page 102 INTENTIONALLY LEFT BLANK ...

Page 1281: ...instrument panel cut out 6 Install the attaching screws which fix the instru ment to the aluminum panel Hold firmly the instrument by hand during installation Do not over tighten screws to avoid instrument case dam age 7 Connect instrument electrical wires at the rear of the instrument Be sure that the electrical ca bles don t have radius of cur vature too small the instru ments may not operate co...

Page 1282: ...tation aligning the symbolic airplane with the horizon and retighten the screw 11 C If caging is required caging should be accom plished when the aircraft is in a wings level nor mal cruise attitude as indicated by AHRS If the gyro is caged when the aircraft is not in this atti tude the resulting attitude presentation immedi ately after caging will be in error by the difference between true vertic...

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Page 1284: ...2nd Edition Rev 0 SUPPLEMENT SG 1 CHAPTER 92 WIRING DIAGRAMS Page 106 Chapter 92 Wiring diagrams ...

Page 1285: ...2nd Edition Rev 0 SUPPLEMENT SG 1 CHAPTER 92 WIRING DIAGRAMS Page 107 INTENTIONALLY LEFT BLANK ...

Page 1286: ...ne electrical system when the engine starting battery is installed The information is given in the form of drawings reporting the Tecnam code number 26 9 0007 xxx D D stand for Digital version x digits represent the ATA chapter referenced within this Manual Garmin G950 LRUs wiring diagram is reported in the drawing no 26 9 0007 092 As far as the maintenance practices are concerned make reference t...

Page 1287: ... DWG no Rev No Sheets 27 26 9 0007 027 D 0 1 25 26 9 0007 025 D 0 1 26 26 9 0007 026 D 0 1 27 26 9 0007 027 D 0 3 28 26 9 0007 028 D 0 2 30 26 9 0007 030 D 0 1 31 26 9 0007 031 D 0 4 32 26 9 0007 032 D 0 2 33 26 9 0007 032 D 0 4 74 26 9 0007 074 D 0 1 80 26 9 0007 080 D 0 1 92 G950 IFDS 26 9 0007 092 0 9 ...

Page 1288: ...2nd Edition Rev 0 SUPPLEMENT SG 1 CHAPTER 92 WIRING DIAGRAMS Page 110 INTENTIONALLY LEFT BLANK ...

Page 1289: ...2nd Edition Rev 0 SUPPLEMENT SG 1 CHAPTER 92 WIRING DIAGRAMS Page 111 INTENTIONALLY LEFT BLANK ...

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