Aquila ATO1, Maintenance Manual

Page 1: ...MM AT01 1020 100 This document is protected by copyright All associated rights in particular those of translation reprinting reproductionbyphotomechanicalorsimilarmeansandstoringindataprocessingfacilitiesinwholeorpartarereserved AQUILA Aviation by Excellence AG Phon 49 33 731 7070 Flugplatz Fax 49 33 731 707 11 14959 Schönhagen e mail info aquila aero com ...

Page 2: ...MAINTENANCE MANUAL AQUILA AT01 Aviation by Excellence AG ...

Page 3: ...stem Description 27 10 00 Aileron Control System Maintenance Practices 27 20 00 Rudder Control System Description 27 20 00 Rudder Control System Maintenance Practices 27 30 00 Elevator Control System Description 27 30 00 Elevator Control System Maintenance Practices 27 31 00 Elevator Trim Control System Description 27 31 00 Elevator Trim Control System Maintenance Practices 27 50 00 Flap Control S...

Page 4: ...ance Practices 34 20 00 Attitude and Direction Maintenance Practices 34 40 00 Independent Position Determining Maintenance Practices 34 50 00 Dependent Position Determining Maintenance Practices 51 STRUCTURES 51 00 00 Structures General 51 10 00 Fiberglass Laminate Structures Maintenance Practices 51 20 00 Repair of Fiberglass Laminate Components 52 DOORS 52 00 00 Doors General 52 10 00 Canopy Mai...

Page 5: ...f Vendor Technical Publications No Manual No Part No Manual Title Vendor 1 Doc No AFM AT01 1010 100 E Revision A 01 or a later Revision Airplane Flight Manual AQUILA T E GmbH 2 ROTAX Part No 899372 Rev 02 March 01 2003 or a later Revision ROTAX Engine Type 912 Series Maintenance Manual ROTAX Aircraft Engines 3 ROTAX Part No 899429 Rev 03 01 2005 or a later Revision IPC for ROTAX Engines Type 912 S...

Page 6: ...MAINTENANCE MANUAL AQUILA AT01 Aviation by Excellence AG INTRODUCTION Page 02 Introduction 30 04 08 Table 01 List of Vendor Technical Publications Cont ...

Page 7: ...the chapter number and the title B The Page Numbering System 1 The page numbering system consists three element numbers separated by dashes The first element of the division identify a system e g 27 Flight Controls a chapter The following element designate a subsystem in the system e g 27 30 Elevator a section If system consists of several subsystems further sections are added e g 27 31 Elevator T...

Page 8: ... if it appears necessary a unit or device to treat in greater detail 5 All maintenance data given in the MM is separated into specific types of information That facilitates work with the manual For this purpose page number blocks are reserved depending on type of information Page 1 99 Description and Operation Page 101 199 Troubleshooting Page 201 299 Maintenance Practices Page 301 399 Servicing P...

Page 9: ...nding chapter number here In the table of contents of the respective chapter one then finds closer information about the arrangement of material Using the Maintenance Manual Meter Common Meter Plus PSI Desired Value VDC Unit under test Pin 2 blk Pin 4 red 0 4 95 to 5 0 3010016 17 18 Pin 2 blk Pin 1 wht 0 1 70 to 2 10 3010016 17 18 Pin 2 bik Pin 3 grn 0 1 70 to 2 10 3010016 17 18 Pin 3 grn Pin 1 wh...

Page 10: ...licable for all aircraft at the bottoms left hand corner a effectivity block appears The effectivity identification placed in this block may be a six digit numeric indicator Ref to 2 a or an effectivity statement Refer to Figure 01 All information appearing on that page applies only to the aircraft noted in the effectivity block Pages with no effectivity block may be followed by pages which have e...

Page 11: ...serted are listed in sequence and assigned with the respective action In the record of revisions in front of the MM the accomplished revision is to be documented as required b Temporary revisions come as single pages Incorporate them as noted in the effectivity page delivered with the revision With appearance of the corresponding regular revision of the MM they lose its effectivity and will be rem...

Page 12: ...MAINTENANCE MANUAL AQUILA AT01 Aviation by Excellence AG Introduction ...

Page 13: ...s and Markings 12 Servicing AIRFRAME SYSTEMS 20 Standard Practices Airframe 21 Ventilation and Heating 08 07 02 23 Communications 24 Electrical Power 25 Equipment and Furnishings 26 04 05 27 Flight Controls 01 03 02 28 Fuel 01 03 02 31 Indicating Recording Systems 32 Landing Gear 15 03 02 33 Lights 18 05 02 34 Navigation STRUCTURES 51 Structures 22 03 02 53 Fuselage 14 05 02 55 Stabilizers 14 05 0...

Page 14: ... 26 11 01 78 Exhaust 07 11 01 79 Oil 07 11 01 80 Starting 05 11 01 91 Charts and Wiring Diagrams The date refers to the issue revision date of the respective chapter 26 04 05 26 04 05 26 04 05 30 04 08 LIST OF EFFECTIVE CHAPTERS Chapter Title Date List of Chapters 30 04 08 The technical content of this document is approved under the authority of DOA No EASA 21J 025 Date Signature Office of Airwort...

Page 15: ...MAINTENANCE MANUAL AQUILA AT01 Aviation by Excellence AG CHAPTER 5 TIME LIMITS MAINTENANCE CHECKS ...

Page 16: ...MAINTENANCE MANUAL AQUILA AT01 Aviation by Excellence AG ...

Page 17: ...0 1 SCHEDULED MAINTENANCE CHECKS 05 20 00 1 General 05 20 00 1 Inspection Time Intervals Chart AQUILA AT01 05 20 00 1 DAILY INSPECTIONS 05 30 00 1 General 05 30 00 1 Preflight Inspection 05 30 00 1 After Flights 05 30 00 1 UNSCHEDULED MAINTENANCE CHECKS 05 50 00 1 General 05 50 00 1 Special Inspections 05 50 00 1 Title Subject Page COMPONENT TIME LIMITS 05 00 01 1 General 05 00 01 1 Component Time...

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Page 19: ... chapter B Section 05 00 01 Component Time Limits This section contains the time limits of all service life limited components and parts and recommended time between overhaul TBO for components C Section 05 20 00 Scheduled Maintenance Checks This section contains information about recommended scheduled maintenance and inspections The recommended maintenance and Inspection Program for the systems a...

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Page 21: ...ecorded in the aircraft logbook 2 A Under specific circumstances the replacement or overhaul of components may be required before attaining the time limits as listed below B Replacement time limits 25 Restraint Assy 12 years no Pilot Co Pilot 32 Rubber Elements 5 years no of the Elastomer Spring Package at the Nose Gear 32 Flexible Hoses 10 years no of the Aircraft Brake System 71 Engine Shock 150...

Page 22: ...ever comes first 71 ROTAX Mechanical 5 years no Fuel Pump 71 ROTAX Flexible Fuel 5 years no Lines 71 ROTAX Rubber Parts 5 years no of Carburetors 71 Rubber Hoses of 5 years no Engine Cooling Note 1 Refer to manufacturers instructions for battery replacement time limits Note 2 Refer to latest issue of the mt propeller Service Bulletin No 1 and to the mt propeller E 124 Operation and Installation Ma...

Page 23: ...e inspections It is not to be utilized as the primary checklist for inspection of the aircraft B Under specific circumstances maintenance intervals can become shorter if the aircraft is operating under conditions which differ from normal environmental conditions 2 A The maintenance and checks listed in the following chart are to be practiced in the specified periods and are to be documented in a r...

Page 24: ...0 RPM duration depending on ambient temperature until oil temperature reaches 50 C Rudder Pedal Brakes and Parking Brake Check for proper 32 40 00 operation Propeller Governor Set 1700 RPM and note the manifold MT E 124 pressure then reduce engine speed by moving the propeller control for200 RPM Note the RPM drop and manifold pressure Increase RPM to 1700 RPM Repeat three times RPM drop _______RPM...

Page 25: ...an X 6 Aircraft Interior Clean and vacuum X 7 Prepare aircraft for visual checks as X follows Remove Engine Cowling Remove Landing Gear Fairings Remove Cabin Carpets and Floorboards Remove Glareshield Remove Baggage Compartment Floorboard Remove Access Panel of the Baggage Compartment Bulkhead Remove Access Panel 210AB 06 30 00 8 Make a record of all malfunctions and abnormalities X No Pre Inspect...

Page 26: ...R 12 00 00 X filter element for metal particles Sec 5 3 Findings_____________________ 4 Visual inspection of the magnetic plug for accumulation X of chips 5 Check compression by differential pressure method R 12 00 00 200 h Test pressure 6 bar appr 6000 hpa 87 psi Sec 2 5 Pressure drop max 25 cyl 1 2 3 4 Pressure drop _____ _____ _____ _____ 6 Cooling Air Ducts Engine Baffling and Cylinder Cooling...

Page 27: ...ning from heat R 12 00 00 X porosity secure connections and attachments Sec 2 2 Verify routing for kinks or restricted elbows Steel fuel lines if applicable additionally check for cracks and for scuffing marks 16 Fuel Selector Shut OFF Valve Check for security of X attachment Check that the valve engages noticeable into the positions LEFT RIGHT and OFF 17 Filter Element of Electrical Fuel Pump ins...

Page 28: ... torque 25 60 Nm in free rotation Friction torque as measured _________Nm 30 Propeller Gear Box Inspect overload clutch R 05 50 00 600 h Sec 2 2 SB 912 033 latest Rev 31 Propeller Gear Box Inspect repair or overhaul in accordance R 12 00 00 800 h with the ROTAX instructions for continued airworthiness Sec 7 2 TSN Detailed inspection of affected gear box components 32 Magnetic Plug Inspect for accu...

Page 29: ...f travel 39 Air Filter Inspect and clean Renew if necessary Clean air R 12 00 00 X filter housing Check the drain hole at the bottom of housing sec 2 4 for obstructions or blockage 40 Other Engine External Accessories Inspect screws and nuts X of all other external engine parts and accessories for tight fit Inspect safety wiring if applicable replace as necessary 41 Engine Mounts manufactured by R...

Page 30: ...condition and security of attachment 6 Seats Verify security of attachment of the seat assy to X aircraft structure Check operation of seat adjustment mechanism and seat stops Inspect gas spring struts for oil leakage or other damage 7 Seats Remove seats Clean and lubricate seat rails as 25 10 00 Ann required Visually examine that portion of the engine controls lines and cables located in the cent...

Page 31: ...ol sticks the X brackets and the control rods for distortion cracks chafing corrosion and security Examine all bearings for condition and security fit Verify all safety means to be intact Check travel of control surfaces if the control stick is in the full forward neutral aft and full left neutral right positions Verify no binding or jumpy movement of the control sticks through their full range of...

Page 32: ...and excessive play 5 Aileron Hinges Check play allowed X Axial 1 00 mm 0 04 in Radial 0 30 mm 0 01 in 18 Hydraulic Brake Fluid Renew 2 years 19 Fuel Lines Check for leakage and security X 20 Wing Main Bolts Inspect for proper fit condition and 57 10 00 X correct safetying 21 Wing Main Bolts Remove for visual inspection and 57 10 00 Ann lubrication 22 Engine and Propeller Controls Check for proper ...

Page 33: ...s and ailerons as well as at the outboard end of the ailerons is at least 2 mm 0 08 in 10 Pitot Static System Check pitot tube for security of X attachment condition and obstructions Check pitot and static pressure lines for correct installation water and proper routing 11 Stall Warning System Check for condition and proper X operation 12 For serial numbers from AT01 100 to AT01 126 57 10 00 Ann B...

Page 34: ...rtical stabilizer Check for any damage for correct installation and function and for security and wear Inspect rudder hinge brackets rudder yoke and control cable thimble eyes for security conditions and wear Lubricate control cable thimble eyes as required 6 Rudder Rigging Set rudder pedals in neutral position 27 20 00 X Verify the rudder and the nose landing gear are also in neutral position Set...

Page 35: ...ricate 12 22 00 X 9 Wheel Brakes Clean Check freedom of movement of the 32 40 00 X pistons and pressure plates Inspect brake disks and brake linings for condition and wear Replace brake disk if worn below 3 8 mm 0 15 in Replace brake linings when worn to 3 0 mm 0 12 in Inspect brake fluid carrying lines at the main landing gear for condition leakage and security of attachment Page 13 05 20 00 Main...

Page 36: ...ontrols Check full range of motion X without any obstruction or excessive friction to travel Check throttle and propeller control levers friction lock 6 Airworthiness Directives Verify all airworthiness directives X complied with Service Letters Service Bulletins and Service Information Verify all Aquila t E GmbH and Suppliers service letters service bulletins and service information complied with...

Page 37: ...light Manual Section 4 A completely accomplished pre flight check is very essential for safety of flights since many accidents are to be traced back to an inadequate carrying out of this check 3 A These checks are to be practiced after the last flight of the day Most of it are visual inspections B The checks should contain all points of the pre flight check 1 Supplementary measures a Filling fuel ...

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Page 39: ...d Landing After an excessively hard landing or other unusual loads of the landing gear a thorough inspection of the affected components and their attachment is required Even if no obvious defects are detectable a visual inspection must be carried out Perform the following 1 Prepare aircraft for visual checks as follows a Remove engine cowling refer to 71 10 00 b Remove landing gear fairings c Insi...

Page 40: ...l of the defects before the aircraft is put into operation again 1 Disconnect battery refer to 24 30 00 2 Remove engine cowling refer to 72 10 00 3 Examine engine cowling Check for signs of fire damage 4 Examine electrical cables for damaged insulation 5 Examine fuel lines for damage of the fire protection sleeves 6 Check oil lines for damage of the fire protection sleeves 7 Check air filter eleme...

Page 41: ...MAINTENANCE MANUAL AQUILA AT01 Aviation by Excellence AG CHAPTER 10 PARKING MOORING STORAGE AND RETURN TO SERVICE ...

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Page 43: ...0 10 00 201 Parking 10 10 00 201 STORAGE 10 11 00 201 Storage with a Duration up to 30 Days 10 11 00 201 Storage with a Duration up to 90 Days 10 11 00 201 MOORING 10 20 00 201 General 10 20 00 201 Tools Equipment and Material 10 20 00 201 Mooring 10 20 00 201 RETURN TO SERVICE 10 30 00 201 Return to Service After a Storage up to 30 Days 10 30 00 201 Return to Service After a Storage up to 90 Days...

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Page 45: ... and Return to Service General This section gives a survey via content and purpose of the chapter B Section 10 10 00 Parking This section contains information as the airplane is to be parked C Section 10 11 00 Storage The section provides instructions for proper storage of the aircraft D Section 10 20 00 Mooring This section contains procedure supplementary information and required equipment for a...

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Page 47: ...rocedure should be applied 1 Taxi or tow aircraft into parking position Refer to Chapter 9 2 Head the aircraft into the wind if possible 3 If flaps down retract flaps 4 Set parking brake 4 Chock main gear wheels 5 If necessary install any rudder lock 6 Install the pitot head cover 7 Close and lock canopy When parking the aircraft in adverse weather conditions such as gusty or strong winds it is re...

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Page 49: ...E IGNITION SWITCH IS IN THE OFF POSITION AND THE THROTTLE IS CLOSED DO NOT ROTATE THE PROPELLER CLOCKWISE 4 After every seven days during storage rotate the propeller by hand After rotating the engine six revolutions stop the propeller 60 to 120 from its former position 5 If at the end of 30 days the aircraft will not be removed from storage the engine should be started and run in a safe area The ...

Page 50: ...umidity high temperatures etc possibly ventilate aircraft several times during storage 8 Landing gear wheels and tires a Landing gear It is recommended to jack up the aircraft to relieve load of the landing gear b Wheels Rotate wheels at least once a week 3 4 revolutions to avoid brake disc corrosion c Tire Clean any oil or grease from tires and treat with a tire protective The aircraft cannot be ...

Page 51: ...as in section 10 10 00 Parking described manner 2 Immobilize the ailerons and elevator by looping the seat belt around the control stick and pulling it tight 3 Chock the main gear wheels fore and aft 4 Screw tie down ring into the adapter at the underside of each wing red marked 5 Secure tie down ropes to the wing tie down rings and to the lower fin Secure at approximately 45 degree angles to the ...

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Page 53: ... s Manuel for installed engine model b After removing spark plugs rotate propeller several revolutions counterclockwise Then reinstall spark plugs c Check oil level and grade 3 Fuel System a Check fuel filter and clean it if necessary b Check fuel tanks and lines for water and sediment Drain fuel into clear cup and check for water and sediment Drain until water or sediment is gone 4 Electrical Sys...

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Page 55: ...MAINTENANCE MANUAL AQUILA AT01 Aviation by Excellence AG CHAPTER 11 PLACARDS AND MARKINGS ...

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Page 57: ...scription 11 00 00 1 EXTERIOR PLACARDS AND MARKINGS 11 20 00 201 General 11 20 00 201 Tools Equipment and Material 11 20 00 201 Removal Installation 11 20 00 201 Maintenance Care 11 20 00 204 INTERIOR PLACARDS AND MARKINGS 11 30 00 201 General 11 30 00 201 Tools Equipment and Material 11 30 00 201 Removal Installation 11 30 00 201 Title Subject Page Placards and Markings 30 04 08 ...

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Page 59: ...ral This section provides a general overview of content and purpose of the chapter The structure is explained B Section 11 20 00 Exterior Placards and Markings This section gives maintenance and care instructions to exterior placards graphics markings etc and contains information about required equipment and material C Section 11 30 00 Interior placards and Markings This section gives maintenance ...

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Page 61: ...ll downward on graphic Remove graphic 3 Remove all traces of old adhesive by using a cloth with isopropyl alcohol as required B Install self adhesive Graphics 1 Clean aircraft surface carefully Remove all old adhesive traces using isopropyl alcohol 2 Remove paperliner from backside of graphic to expose adhesive 3 Position top edge of graphic precisely 4 Work uniformly downward and apply graphic to...

Page 62: ...ail A Detail Placards and Markings KRAFTSTOFF ABLASS FUEL DRAIN EN 228 SUPER EN 228 SUPER plus AVGAS 100 LL AUSFLIEGBAR 54 8 Liter EN 228 SUPER EN 228 SUPER plus AVGAS 100 LL USABLE FUEL 54 8 Liters 14 5 U S GAL VERZURRPUNKT TIE DOWN E A K K A O B B C C C B D F G H F G D J I L M N M N 30 04 08 O P P P P Note Placards illustrated not in scale O ...

Page 63: ...ngs 2 5 bar 36 PSI 2 0 bar 30 PSI roteMarkierung der Aufbockpunkte Red Jack Point Markings Erdungspunkt Auspuffendrohr Electric Ground Exhaust Port HAUBE GEÖFFNET CANOPY UNLOCKED HAUBE VERRIEGELT CANOPY LOCKED Rot Red Gelb Grün Farbmarkierungen für die Position der Landeklappe Colored Flap Position Markings Yellow Green ELT HIER EINGEBAUT ELT INSTALLED HERE 30 04 08 Jack Point Aufbockpunkt Note Pl...

Page 64: ...xcellence AG 11 20 00 Page 204 Placards and Markings 30 04 08 NICHT BETRETEN NICHT SCHIEBEN NO STEP or PUSH NO PUSH M Detail N Detail O Detail P Detail Exterior Placards and Markings Figure 201 Sheet 3 of 3 Note Placards illustrated not in scale ...

Page 65: ... Externe Stromversorgung 12 V DC GROUND POWER 12 VDC A B WINTER KIT SHOULD BE INSTALLED BELOW 5 C 41 F WINTER KIT MUST BE REMOVED ABOVE 15 C 59 F KÜHLERABDECKUNG UNTERHALB 5 C 41 F INSTALLIEREN KÜHLERABDECKUNG OBERHALB 15 C 59 F ENTFERNEN Aircraft equipped with an external power system and or winterization kit 30 04 08 EFFECTIVITY Note Placards illustrated not in scale ...

Page 66: ...allow fuel to spill on graphics If fuel spills on graphics wipe off by a cloth and rinse with water thoroughly 5 Do not eliminate snow and ice on surfaces using peaked and sharp edged instruments 6 If a high pressure washer is used keep nozzle at least 0 5 m approx 1 6 ft from edge of graphic 11 20 00 Page 206 Placards and Markings 30 04 08 ...

Page 67: ...ommercially Available 3 A Remove Self adhesive Placards 1 Heat up placard a little by using a heat gun approx 40 50 C 2 Carefully separate a corner of the placard and then pull parallel to surface to remove it 3 Remove all traces of old adhesive by using a cloth with isopropyl alcohol as required B Install Self adhesive Placards 1 Remove protective film from backside of placard to expose adhesive ...

Page 68: ...kings Figure 201 Sheet 1 of 7 Placards and Markings 30 04 08 A B B1 D1 F1 C D E J1 L L1 Y K K1 M G N O F E1 A1 H H W T R V R Q Z Q U X S H1 H H J P 3x I1 C1 G1 On the right side wall of the center pedestal adjacent to the adjusting knob N1 M1 I Position of this placard can vary on the instrument panel ...

Page 69: ...or Trimmotor Com NAV Wende Kraftstoff Lüfter Stall Advisory Warning Lights Intercom OAT CHT Charge Light Turn Fuel Reserved Indicator Level Encoder Instru Elev Trim ments 2 System Attidude Flap Control Gyro System Directional Starter Gyro Relay GPS Battery Flap Actuator Transponder Alternator Trim Actuator Com NAV Instru ments 3 12V DC Receptacle Stall Advisory Warning Lights Intercom OAT CHT Char...

Page 70: ...tor Warning Light Kurskreisel Directional Gyro 12V Steck dose 12V DC Receptacle Starter relais Starter relay Wende zeiger Turn Coordin Kraftstoff vorrat Fuel Gauge Lüfter Avionik Cooler Avionics Höhen kodierer Blind Encoder Instru mente 1 Instru ments 1 Trimm steuerung Trim Control Instru mente 2 Instru ments 2 Klappen anzeige Flap Control Künstl Horizont Attitude Gyro GPS GPS Batterie Battery Kla...

Page 71: ...tail RAUCHEN VERBOTEN NO SMOKING C Detail D Detail E Detail F Detail G Detail CHOKE ZIEHEN EIN CHOKE PULL ON VERGASERVORW ZIEHEN EIN CARB HEAT PULL ON HEIZUNG ZIEHEN EIN CABIN HEAT PULL ON ÖLTEMPERATUR ZYLINDERKOPFTEMP OIL TEMP CYL HEAD TEMP VOLLGAS OPEN LEERLAUF IDLE START Max RPM HIGH RPM Min RPM REISE LOW RPM TRIMM ANZEIGE TRIM CONTROL Kopflastig NOSE DOWN Start T O Schwanzlastig Voltmeter Volt...

Page 72: ...Liter M Detail N Detail O Detail Q R P Detail Detail Detail Detail Detail S Detail Detail Detail Interior Placards and Markings Figure 201 Sheet 5 of 7 11 30 00 Page 205 HAUBE GEÖFFNET CANOPY OPEN HAUBE VERRIEGELT CANOPY CLOSED KOPFLASTIG NOSE DOWN SCHWANZLASTIG NOSE UP TRIMM SCHALTER TRIM SWITCH ÖLDRUCK PARKING BRAKE PULL SET COPILOT PILOT COPILOT PILOT KOPFHÖHRER HEADPHONES Note Placards illustr...

Page 73: ...SECURELY ANCHORE DOWN ACHTUNG Kein Flugmotorenöl einfüllen Siehe Flughandbuch CAUTION DO NOT use aviation grade oil Refer to POH ELT REMOTE CONTROL Zur Aktivierung den Hauptschalter des ELT auf ARMED stellen ELT REMOTE CONTROL To activate switch transmitter to ARMED Das Flugzeug ist für den Betrieb unter VFR Tag ohne Vereisungsbedingungen zugelassen Alle Kunstflugmanöver einschließlich beabsichtig...

Page 74: ...mp Avionics Nav Lights ACL Landing Lights Instrument Light Cabin Light Reise Start Landung Lade kontrolle Reservee Kraftstoff druck ALTERNATOR CONTROL Reserve FUEL PRESSURE CRUISE T O Landing Note Placards illustrated not in scale ACHTUNG Automobilbremsflüssigkeit verwenden Siehe Flughandbuch Keine CAUTION DO NOT use automotive brake fluid Refer to POH Reibverstellung Leistung Propeller Friction L...

Page 75: ...MAINTENANCE MANUAL AQUILA AT01 Aviation by Excellence AG CHAPTER 23 COMMUNICATIONS ...

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Page 77: ...0 00 201 Garmin 430 530 VHF COM Antenna Removal Installation 23 10 00 201 Garmin 430 530 SPEECH COMMUNICATION DESCRIPTION 23 10 00 1 Garmin SL30 40 Introduction 23 10 00 1 Garmin SL30 40 Description and Operation 23 10 00 1 Garmin SL30 40 SPEECH COMMUNICATION MAINTENANCE PRACTICES 23 10 00 201 Garmin SL30 40 General 23 10 00 201 Garmin SL30 40 NAV COM Transceiver Removal Installation 23 10 00 201 ...

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Page 79: ...e AVIONICS switch The radio and the intercom system are protected by the circuit breakers labeled NAV COM and Intercom B Optional to the Bendix King equipment in combination with the PM 501 Intercom system the following NAV COM equipment and Audio Panel combinations may be installed 1 GARMIN GNS 430 VHF COMMUNICATIONS TRANSCEIVER VOR ILS RECEIVER GPS RECEIVER in combination with a GARMIN GMA 340 A...

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Page 81: ...z Display Backlighted Liquid crystal Display LCD Voltage Supply 14V 2 A Fig 1 shows the NAV COM radio front view with short explanations B VHF Speech Communication Part the of the NAV COM Radio Description 1 For controlling and indicating the left frontside of the NAV COM radio is used An active and a standby frequency can be adjusted The left COM frequency window displays the active COM frequency...

Page 82: ...w NAV Information Window NAV Frequency Window COMM Frequency Transfer Button Standby COMM Frequency Display COMM Volume Pull Test Knob This knob also turns power ON OFF to the unit COMM Frequency Selection Knobs OBS T X TO FR FLAG PULL 25K PULL 25K PULL TEST PULL IDENT OFF COMM NAV KX 125 TSO MODE BENDIX KING S B Y S B Y Communications 30 04 08 ...

Page 83: ... Turn wrench counterclockwise until locking paw releases unit from mounting tray 3 Grasp NAV COM and carefully pull aft out of mounting tray B Install NAV COM 1 Ensure that all required plugs at the back of the mounting tray are properly reconnected 2 Carefully slide NAV COM forward into the mounting tray 3 On face of NAV COM insert a 3 32 hex wrench into the mounting hole see Fig 01 and engage he...

Page 84: ...MAINTENANCE MANUAL AQUILA AT01 Aviation by Excellence AG COM Antenna Installation Figure 201 23 10 00 Page 202 Communications ...

Page 85: ...r to the GARMIN GNS 530 Pilot s Guide and Reference P N 190 00181 00 latest revision respectively C GNS 430 Specifications 1 Physical Unit Size W D H 159 mm 6 25 in 279 mm 11 00 in 67 mm 2 65 in Unit Weight 3 0 kg 6 6 lbs installed 2 Power Input 13 8 27 5 Volts DC 3 Environmental Temperature 20 C to 55 C operating range Humidity 95 non condensing Altitude 457 m 1 500 ft to 15 240 m 50 000 ft 4 VHF...

Page 86: ...n Description 1 The GNS 430 530 speech communications portion consists of a digitally tuned integrated VHF communications COM transceiver The transceiver receives all narrow and wide band VHF communications transmissions within a frequency range of 118 000 MHz to 136 975 MHz in 25 0 kHz steps 760 channels or for use in Europe in 8 33 kHz steps 2280 channels The tuning controls are located at the l...

Page 87: ... enable disable the ident tone 3 The large left knob 4 is used to tune the megahertz MHz value of the standby frequency for the COM transceiver or the VLOC receiver whichever is currently selected by the tuning cursor 4 The small left knob 5 is used to tune the kilohertz kHz value of the standby frequency for the COM transceiver or the VLOC receiver whichever is currently selected by the tuning cu...

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Page 89: ...em respectively 2 Note For aircraft that are equipped with an external VHF NAV COM antenna only A Remove Antenna 1 Ensure battery and main avionics switches are in OFF position 2 Open baggage compartment door and remove access inspection plate 211 KC Refer to 25 21 00 3 Disconnect coax connector from antenna 4 Supporting antenna remove 3 nuts securing antenna to fuselage 5 Remove mounting plate 6 ...

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Page 91: ...5 in Unit Weight SL30 1 02 kg 2 25 lbs unit only SL40 0 9 kg 2 lbs 2 Power Input 10 to 40 VDC 3 Environmental Temperature 20 C to 55 C operating range 4 Display SL30 32 character high intensity alphanumeric LED display SL40 16 character high intensity alphanumeric LED display 5 VHF COM Channels 760 25 kHz spacing Frequency Range 118 000 MHz to 136 975 MHz Transmit Power 8 watts carrier power 2 A F...

Page 92: ...t Photocell Active Frequency To From Indication Graphic CDI Bearing Transmit Annunciator Function Annunciators Power Volume Squelch COMM Radio To From OBS Select Enter Small Inner Knob Large Outer Knob System Settings Select Mode Select Standby Frequency Standby Symbol TX 119 80 s121 50 SL40 PULL SQUELCH VOL OFF EC MON RCL MEM Frequency Flip Flop Frequency Monitor Photocell Active Frequency Standb...

Page 93: ...er The VHF NAV COM dipole antenna is laminated on the inner shell of the vertical stabiliser and can not be removed and replaced A second VHF NAV COM antenna the same as installed on S N below AT01 164 may be installed on the bottom of the fuselage in case the aircraft is equipped with a second NAV COM transceiver Communications 23 10 00 Page 03 30 04 08 EFFECTIVITY Aircraft equipped with Garmin S...

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Page 95: ... unit from mounting tray 3 Grasp NAV COM and carefully pull aft out of mounting tray 4 Disconnect all plug connectors and cables Mark the removed cables as required B Install NAV COM Transceiver 1 Ensure that all required plug connectors and cables at the back of the mounting tray are properly connected 2 Carefully slide NAV COM forward into the mounting tray 3 On the face of NAV COM insert a 3 32...

Page 96: ...ide of fuselage install mounting plate 3 Secure antenna base to fuselage using screws nuts and washers Reinstall ground wire 4 Reconnect coaxial connector and secure 5 Install access inspection plate 211 KC Refer to 25 21 00 23 10 00 Page 202 EFFECTIVITY Aircraft equipped with Garmin SL30 SL40 Transceiver Communications 30 04 08 ...

Page 97: ... the flight crew headphones and speakers and the output of the flight crew microphones into the communication transmitters B The intercom system consists primarily of the PM 501 audio control unit located on the instrument panel above the NAV COM transceiver the pilot and co pilot audio jacks mounted on the middle console near the seat backs and the Push To Talk PTT switches located on the control...

Page 98: ...ft hand side to mounting bracket 5 Supporting audio control unit by a hand loosen and remove two screws on front panel fixing the control unit to instrument panel 6 Remove audio control unit B Install Audio Control Unit 1 Install audio control unit to the instrument panel and secure using two screws 2 Secure audio control unit on the left hand side to the mounting bracket using two nuts Make sure ...

Page 99: ...c Selector switch is turned to the OFF position C For a complete description of the GMA 340 Audio Panel refer to the GARMIN GMA 340 Audio Panel Pilot s Guide P N 190 00149 10 Rev A or higher D Refer to Garmin GMA 340 Audio Panel Installation Manual P N 190 00149 01 Rev K or later for additional maintenance information on the GMA 340 2 A Remove Garmin GMA 340 Audio Control Unit 1 Ensure battery and...

Page 100: ...e GMA 340 test button 10 checks the internal LED annunciators and marker beacon LED s 12 Press TEST to confirm operation of the LED s c Cover the photocell 11 with a finger and observe that the LED annunciators dim automatically d Check the front panel backlighting and dimming function Each annunciation is illuminated Inspection Check COM1 MIC COM1 SENS TEST COM2 MIC COM2 NAV1 DME COM3 MIC COM 1 2...

Page 101: ...oper operation of volume and squelch controls 1 2 8 and 9 e Press the PA button 5 Verify that microphone audio is heard over the speaker 5 Aircraft Receivers a Select the audio source corresponding to each installed avionics unit and check for audio over the headsets b Check for pilot copilot audio isolation when pressing the COM 1 2 button 3 c Press the SPKR button 4 and verify that any selected ...

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Page 103: ...MAINTENANCE MANUAL AQUILA AT01 Aviation by Excellence AG CHAPTER 31 INDICATING RECORDING SYSTEMS ...

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Page 105: ...MAINTENANCE PRACTICES 31 10 00 201 General 31 10 00 201 Glare Shield Removal Installation 31 10 00 201 Instrument Panel Removal Installation 31 10 00 201 RECORDERS MAINTENANCE PRACTICES 31 30 00 201 General 31 30 00 201 KAPI Unit Removal Installation 31 30 00 202 KAPI GPS GSM Antenna Removal Installation 31 30 00 202 KAPI Airspeed Sensor Removal Installation 31 30 00 203 KAPI G Sensor Removal Inst...

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Page 107: ...contains the avionics equipment The Bendix King NAV COM transceiver is arranged over the transponder A group of instruments for verifying operating conditions of the engine and systems is on the right side of the avionics column located These gauges indicate the fuel level in each tank cylinder head temperature oil temperature oil pressure as well as amperes and volts of the electrical system In f...

Page 108: ...cator 26 Course Deviation Indicator CDI optional Hour Meter 27 Multifunctional Display optional 28 Voltmeter 29 Oil Temperature Indicator 30 Circuit Breaker Panel 31 12 14 VDC Receptacle 32 Fresh Air Ventilator 33 34 Electrical Fuel Pump Switch 35 36 37 Anti Collision Light Switch 38 Landing Light Switch 39 Instrument Light Switch 40 Cabin Light Switch 41 Flap Control Switch Ind 42 Ammeter 43 Oil ...

Page 109: ...age and instrument panel using screws 2 I A Remove Instrument Panel 1 Disconnect battery Refer to 24 30 00 2 Remove glare shield as described above It is recommended label wires hoses and plugs which must be disconnected for the correct reinstallation of the instrument panel Refer to 91 00 00 for wiring diagrams Refer to 34 10 00 system schematic for proper connecting components of the Pitot stati...

Page 110: ...d below C Instrument Panel Inspection Check 1 Perform pitot system leakage test Refer to 34 10 00 2 Perform static system leakage test Refer to 34 10 00 3 Install glare shield as described above pt 2 4 Connect battery Refer to 24 30 00 5 Perform function test for all instruments and systems to assure proper operation A flight test is recommended after instrument panel installation to ensure a prop...

Page 111: ...tionally installed together with the KAPI system airspeed and g sensor Furthermore the KAPI system processes data derived from GPS signals that are received with an external GPS antenna which is a combined GPS receiving and GSM transmitting antenna for the data transfer to the ground station The GPS GSM antenna is mounted on a support bracket attached to the LH side support plate of the Instrument...

Page 112: ...02 Indicating Recording EFFECTIVITY Aircraft equipped with KAPI Data Logger System KAPI Components Installation Figure 201 B C D Instrument Panel Forward Side KAPI Unit Speed Sensor G Sensor GPS Antenna Cable Ties Adhesive Tape A B Detail A Detail D Detail C Detail 30 04 08 ...

Page 113: ...ry and avionics master switches are in off position 2 Gain access to the interior of the instrument panel by dismounting the Instrument Panel Cover Remove all 10 attachment screws on top 4 screws and on both sides of the Instrument Panel Cover 3 on each side 3 Disconnect the antenna cable from the KAPI unit and remove the attachment cable ties of its laying 4 Mark the installation position and rem...

Page 114: ... The correct installation position of the sensor is vital for a correct data acquisition 2 Fixate the KAPI Airspeed Sensor in its installation position by installing the attachment screws washers and nuts of its attachment 3 Remove the plugs caps from the sensor port and the pitot pressure line Re connect the pitot pressure line to the respective sensor port Make sure that the pressure line is pro...

Page 115: ...on position of the sensor is vital for a correct data acquisition 2 Fixate the KAPI G Sensor on its installation bracket by installing the attachment screws washers and nuts of its attachment 3 Connect the required plug connector at the sensor Make sure that the plug is properly connected 4 Re install the Instrument Panel Cover 5 Perform a functional check of the KAPI system 31 30 00 Page 205 Indi...

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Page 117: ...MAINTENANCE MANUAL AQUILA AT01 Aviation by Excellence AG CHAPTER 34 NAVIGATION ...

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Page 119: ...ion 34 11 00 1 STALL WARNING SYSTEM MAINTENANCE PRACTICES 34 11 00 201 General 34 11 00 201 Transmitter Removal Installation 34 11 00 201 Adjustment 34 11 00 201 ATTITUDE AND DIRECTION MAINTENANCE PRACTICES 34 20 00 201 General 34 20 00 201 Magnetic Compass Removal Installation 34 20 00 201 Turn Coordinator Removal Installation 34 20 00 201 Attitude Indicator Removal Installation 34 20 00 201 Dire...

Page 120: ...MAP AHRS Sensor Removal Installation 34 40 00 205 FLYMAP Inspection Check 34 40 00 206 FLYMAP FLARM COLLISION WARNING SYSTEM MAINTENANCE PRACTICES 34 41 00 201 FLARM General 34 41 00 201 FLARM FLARM Unit Removal Installation 34 41 00 202 FLARM GPS Antenna Removal Installation 34 41 00 202 FLARM FLARM Radio Antenna Removal Installation 34 41 00 203 FLARM FLARM Display Unit Removal Installation 34 4...

Page 121: ...a forces to supply data to determine aircraft attitude and heading That includes a Attitude Indicator b Directional Gyro c Turn Coordinator d Magnetic Compass 2 Devices which sense environmental conditions and use the data to influence navigation That includes a Air Speed Indicator b Altimeter c Vertical Speed Indicator d Stall Warning System 3 Devices which provide information to determine positi...

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Page 123: ... A Pitot Static Tube and Lines The Pitot and static pressures are picked up by the Pitot static tube installed on the underside of the left wing and carried through lines inside the wing and fuselage to the gauges on the instrument panel Both the pitot and the static pressure lines have filter elements to prevent foreign matters such as dust or water from entering the flight instruments The filter...

Page 124: ...ot Static System Schematic Figure 1 Static Pressure Pitot Pressure Pitot Static Tube Filter Air Speed Indicator Airspeed Sensor KAPI Data Logger optional AHRS Sensor FLYMAP Multifunctional Display optional Altimeter Vertical Speed Indicator Navigation Compensation Tank 30 04 08 ...

Page 125: ...S 2 Required in Quantity Equipment Parts No Manufacturer 5 B 1 Sphygmo commercially manometer Pres available sure Bulb with Check Valve 5 B 1 Surgical Hose commercially available 3 A Remove Pitot Static Tube 1 Remove screws securing pitot static tube to wing skin 2 Identify and disconnect pitot static lines and electrical connector at pitot tube 3 Remove pitot static tube from aircraft B Install P...

Page 126: ... 2 Insert a T in a static pressure line 3 Squeeze sphygmomanometer bulb and close check valve to establish a vacuum inside bulb 4 Connect sphygmomanometer to the static pressure line 5 Slowly open air bulb check valve until altimeter indicates a 1000 foot increase in altitude then close check valve to trap suction in system 6 While increasing suction and altimeter indicating 1000 feet ensure that ...

Page 127: ...in a static pressure line 15 Attach hose to T and slowly apply positive pressure until altimeter indicates a 500 foot decrease in altitude Maintain this altimeter indication while checking for leaks 16 Coat line with a solution of mild soap and water watching for bubbles to locate leaks 17 Tighten leaking connections Repair or replace defective components 18 Reconnect airspeed vertical speed indic...

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Page 129: ...ading edge of the left wing and a warning buzzer behind the instrument panel Both are connected by electrical wires B As the aircraft approaches a stall the low pressure on the upper surface of the wings moves forward around the leading edge of the wings As a result a micro plate at the transmitter is deflected upwards A mechanical contact is made thereby sending an electrical signal to the warnin...

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Page 131: ...ing from wing 4 Label and disconnect electrical connectors B Install Transmitter 1 Connect electrical connectors 2 Place transmitter into position and secure with two screws to wing structure 3 Install transmitter covering 3 A The stall warning system is so adjusted the system will come into action approx 10 15 km h 6 8 kts before aircraft stalls If the values are not achieved loosen the two screw...

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Page 133: ...eld refer to Chapter 31 Section Instrument Panel Maintenance 3 Disconnect electrical connector from turn coordinator 4 Remove screws securing turn coordinator to instrument panel 5 Remove turn coordinator from aircraft B Install Turn Coordinator 1 Place turn coordinator to instrument panel and secure using screws 2 Reconnect electrical connector to turn coordinator 3 Install glare shield refer to ...

Page 134: ... CRUISE RPM FOR MORE THAN 3 MIN e Run engine and set throttle at cruise position When performing maintenance practices on the magnetic compass use a non magnetic or plastic screwdriver 2 Remove screws securing access plate to compass housing to reveal adjustment screws 3 Set adjustment screws of compensator on zero Zero position is indicated when dot of screw is aligned with dot on compass frame 4...

Page 135: ...tion on the GNS 430 System or to Garmin 500 Series Installation Manual P N 190 00181 02 latest Revision for the GNS 530 System respectively 2 A Remove GNS 430 530 Unit 1 Ensure battery and avionics master switches are in off position 2 Insert a 3 32 hex wrench into the access hole at the bottom of the unit face Refer to 23 10 00 Figure 01 and engage hex bolt 3 Turn wrench counterclockwise until th...

Page 136: ...antenna from aircraft B Install GPS Antenna 1 Position gasket and antenna from outside and backing plate from inside to fuselage 2 Install washers and nuts securing antenna to fuselage Simultaneously connect ground cable to backing plate 3 Seal the antenna and gasket to fuselage using a good quality electrical sealant 4 Connect antenna cable 5 Close baggage compartment door and install access insp...

Page 137: ...oval procedures of equipment and functional tests Refer to Honeywell Installation Manual BENDIX KING KMD 150 Multifunction Display GPS Manual No 006 10607 0000 Rev 0 November 1999 or later for additional maintenance information on the system Refer to KMD 150 Pilot s Guide and Reference Manual No 006 18220 0000 Rev 2 October 2002 or later and AQUILA AT01 AFM for detailed description and operation i...

Page 138: ...reconnected WHEN MOUNTING THE UNIT DO NOT PRESS ON DISPLAY WINDOW AS DAMAGE MAY RESULT BE SURE NOT TO OVER TIGHTEN THE UNIT INTO THE RACK THE APPLICATION OF HEX WRENCH TORQUE EXCEEDING 15 IN LBS CAN DAMAGE THE LOCKING MECHANISM WHILE SLIDING IN THE UNIT ENSURE THAT THE FLOATING BNC CONNECTOR IS POINTING STRAIGHT OUT OF THE BACK OF THE RACK TWISTING THE BNC CABLE TO THE LEFT RIGHT OR UP DOWN CAN CA...

Page 139: ... WASTE IN THE EVENT OF BATTERY LEAKAGE AVOID CONTACT WITH CORROSIVE ELECTROLYTE CONTAINED IN BATTERY A A lithium battery is located within the KMD 150 It is recommended that this battery be replaced after ten years 5 A After Installation test system as follows 1 Ensure that the correct PCMCIA card is installed in the slot provided below the display 2 Place battery and avionics master switches in O...

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Page 141: ...n warnings with other aircrafts if the necessary subsystems are installed The FLYMAP Multifunctional Display System is approved for VFR operation only and is not intended to be used as the primary source for flight parameters and navigation data For more information refer to the Operator s Manual of the FLYMAP L The FLYMAP L is installed in a mounting frame located in the avionics rack in the mids...

Page 142: ...40 00 Page 202 EFFECTIVITY Aircraft equipped with FLYMAP L Multifunctional Display Navigation Instrument Panel Forward Side A Note Surrounding components and parts omitted for clarity Unit Attachment Screws FLYMAP L Unit Installation Figure 201 A Detail 30 04 08 ...

Page 143: ...YMAP attachment at the backside of the unit 5 Carefully pull out the unit from the rack B Install FLYMAP L Unit WHEN MOUNTING THE UNIT DO NOT PRESS ON THE DISPLAY WINDOW AS DAMAGE MAY RESULT 1 Insert the unit carefully in the rack until it is in its final installation position 2 Install both Philips head screws at the backside of the unit to fix the FLYMAP to its installation bracket 3 Connect all...

Page 144: ...4 40 00 Page 204 EFFECTIVITY Aircraft equipped with FLYMAP L Multifunctional Display Navigation Instrument Panel Forward Side FLYMAP GPS Antenna AHRS Sensor Installation Figure 202 A Detail B Detail Cable Ties Adhesive Tape A B GPS Antenna AHRS Sensor 30 04 08 ...

Page 145: ...t screws on top 4 screws and on both sides of the Instrument Panel Cover 3 on each side 3 Disconnect the pitot and static pressure lines from the fwd end of the sensor PLUG OR CAP THE SENSOR PORTS AS WELL AS THE END OF THE PRESSURE LINES IMMEDIATELY AFTER THEIR DISCONNECTION TO PREVENT THE ENTRY OF DIRT OR FOREIGN OBJECTS INTO THE SENSOR AND THE PRESSURE SYSTEM 4 Disconnect the plug connector from...

Page 146: ...he pitot and static pressure system in accordance with section 5 of chapter 34 10 00 6 Re install the Instrument Panel Cover 7 Perform a functional check of the FLYMAP 5 A Besides of a functional test a flight test is recommended after the installation of the FLYMAP unit or the AHRS sensor to ensure the proper function of the system Inspection Check Navigation 30 04 08 ...

Page 147: ...M determines the risk of dangerous proximity to one or more aircraft or obstacles the unit gives the pilot warning of the greatest danger at that moment The warning is given by a whistle sound beep and bright light emitting diodes LED The display also gives indication of the threat level plus the horizontal and vertical bearing to the threat The GPS and collision information received from other ai...

Page 148: ...AG 34 41 00 Page 202 Aircraft equipped with FLARM Collision Warning System Navigation EFFECTIVITY FLARM Components Installation Figure 201 Instrument Panel Forward Side B A Detail B Detail Cable Ties Adhesive Tape A Radio Antenna GPS Antenna Unit 30 04 08 ...

Page 149: ...ectors and cables Mark the removed cables as required and the installation position of the unit 4 Remove both attachment screws of the FLARM unit inside the instrument panel While removing the attachment screw secure the FLARM unit by hand to prevent it from falling down 5 Carefully remove the unit B Install FLARM Unit 1 Hold the unit correctly aligned at its installation position and install both...

Page 150: ...e antenna cable from the FLARM unit and remove the attachments of its laying 4 Mark the installation position and remove the cable ties of the antenna attachment 5 Carefully take the antenna out of the instrument panel interior B Install FLARM Radio antenna 1 Install the rubber protection sleeve on the antenna if applicable 2 Install the antenna in its installation holders on the backside of the i...

Page 151: ...h acetone B Install FLARM Display Unit 1 Remove the protective film of the double sided adhesive tape on the backside of the FLARM Display Unit and install it on the instrument panel in its correct installation position 2 Connect the plug connector at the backside of the display unit Make sure that the plug is properly connected 3 Re install the Instrument Panel Cover 4 Perform a functional check ...

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Page 153: ...der is a radio transmitter and receiver which operates on radar frequencies Receiving ground radar interrogations at 1030 MHz it returns a coded response of pulses to groundbased radar on a frequency of 1090 MHz The KT 76A C unit is mounted in the instrument panel in the avionics column The transponder antenna is installed on the bottom of the cabin below the co pilot s seat Refer to KT 76C INSTAL...

Page 154: ...a from falling away from the aircraft 3 From outside the aircraft disconnect antenna cable at connector and remove antenna from aircraft B Install Transponder Antenna 1 From outside the aircraft connect antenna cable to the transponder antenna 2 From inside the fuselage insert antenna studs through mounting holes and position the backing plate 3 Install washers and nuts securing transponder antenn...

Page 155: ... Installation Manual P N 190 00140 02 Revision G or later for additional maintenance information on the GNS 430 System or to Garmin 500 Series Installation Manual P N 190 00181 02 latest revision for GNS 530 system respectively C Garmin SL30 COM NAV Transceiver The SL30 is a combination of a VHF communications transceiver and a VHF navigation receiver which includes VOR Localizer and Glideslope re...

Page 156: ... cabin below the co pilot s seat For additional maintenance information on the GTX 330 Mode S Transponder refer to GTX 330 Installation Manual P N 190 00207 02 latest revision F Garmin GTX 328 Mode S Transponder The GTX 328 transponder is a radio transmitter and receiver that operates on radar frequencies receiving ground radar or TCAS interrogations at 1030 MHz and transmitting a coded response o...

Page 157: ...o the access hole at the bottom of the unit face and engage hex bolt 3 Turn wrench clockwise until the unit is secured in the rack 3 A Remove Transponder Antenna 1 Remove access inspection plate 211 BB Refer to 25 21 00 gaining access to the transponder antenna 2 Remove nuts and washers securing transponder antenna to fuselage NOTE The connected antenna cable prevents the antenna from falling away...

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Page 159: ...MAINTENANCE MANUAL AQUILA AT01 Aviation by Excellence AG CHAPTER 52 DOORS ...

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Page 161: ...NERAL 52 00 00 1 Introduction 52 00 00 1 General Description 52 00 00 1 CANOPY MAINTENANCE PRACTICES 52 10 00 201 Description and Operation 52 10 00 201 Canopy Removal Installation 52 10 00 201 Canopy Latching Mechanism 52 10 00 201 Adjustment Canopy Latching Mechanism 52 10 00 201 Title Subject Page Doors 30 04 08 ...

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Page 163: ...ether The window has two direct vision panels that can be opened in flight The canopy moves up and forward to open A latching mechanism holds the canopy closed by two latching pins The canopy is locked from the outside with a key lock B The baggage door is located on the left side of the fuselage just aft of the wing It is made of composite materials The door allows easy access to the baggage comp...

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Page 165: ...usly by push pull cable that goes inside the canopy frame Roll pins hold the latch in fully latched position 2 A Remove the Canopy 1 Open the canopy 2 While supporting the canopy by helpers remove four hex bolts securing canopy to the hinge frame and lift the canopy clear of aircraft B Install the Canopy 1 Lift canopy into position on the aircraft 2 Install washers and hex bolts securing the canop...

Page 166: ...MAINTENANCE MANUAL AQUILA AT01 Aviation by Excellence AG 52 10 00 Page 202 A B C A Detail Canopy Latching Mechanism Figure 201 Doors 30 04 08 ...

Page 167: ...cellence AG 52 10 00 Page 203 B Detail C Detail Canopy Latching Mechanism Assembly Figure 202 Latching Pin Receiver Inner Handle Outer Handle Canopy Lock Roll Pin Push Pull Road Spacer Spacer Locking Pin Shaft Actuation Lever Spacer Doors 30 04 08 ...

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Page 169: ...MAINTENANCE MANUAL AQUILA AT01 Aviation by Excellence AG CHAPTER 91 CHARTS AND WIRING DIAGRAMS ...

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Page 171: ...iring Diagram 91 00 01 7 Fuselage Wiring Diagram 91 00 01 9 Wings Wiring Diagram 91 00 01 11 Avionics Wiring Diagram Modification 1 Instrument Panel KX125 GNS 430 GTX 327 GMA 340 91 00 01 13 Avionics Wiring Diagram Modification 1 Fuselage 91 00 01 15 Avionics Wiring Diagram Modification 2 KX125 GNS 430 GTX 330 GMA 340 91 00 01 17 Avionics Wiring Diagram Modification 3 KX 125 GNS530 GTX 330 GMA 340...

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Page 173: ...ef Fig 4 5 Fuselage Ref Fig 4 6 Wings Ref Fig 6 B The wiring diagrams listed below define the wiring of optional equipment which may be installed in the aircraft 1 Avionics Wiring Diagram Modification 1 Instrument Panel KX125 GNS 430 GTX 327 GMA 340 Ref Fig 7 2 Avionics Wiring Diagram Modification 1 Fuselage Ref Fig 8 3 Avionics Wiring Diagram Modification 2 KX125 GNS 430 GTX 330 GMA 340 Ref Fig 9...

Page 174: ...R VERSION RCA AND MIDCONTINENT 4300 INCL LIGHTING VERSION RCA W O LIGHTING ELT SWITCH ELT CONNECTOR ELT BUZZER FLAP CONTROL CRUISE T O LDG TRIM POSITION INDICATOR FUSELAGE CONNECTOR 5 FUSELAGE CONNECTOR 3 FUSELAGE CONNECTOR 2 FUSELAGE CONNECTOR 1 INSTR LIGHT ALTERNATOR MAIN SWITCH FUEL PRESSURE TERMINAL BLOCK GROUND TERMINALS FIREWALL FEED THROUGH 30 04 08 ...

Page 175: ...e 01 2 91 00 01 Page 02 Charts and Diagrams FIREWALL FEED THROUGH TRIM POSITION INDICATOR FLAP CONTROL IF OPTION WITH MODE S TRANSPONDER IS INSTALLED AND FOR ENGINE CONNECTOR PRESSURE SWITCH CLOCK OPERATION HOUR METER BUZZER RECEPTACLE NOT INSTALLED IF HOUR METER 2840 186 WINTER IS USED 30 04 08 ...

Page 176: ...MAINTENANCE MANUAL AQUILA AT01 Aviation by Excellence AG COM NAV and Intercom Wiring Diagram Instrument Panel Figure 02 1 91 00 01 Page 03 Charts and Diagrams 30 04 08 ...

Page 177: ...MAINTENANCE MANUAL AQUILA AT01 Aviation by Excellence AG COM NAV and Intercom Wiring Diagram Instrument Panel Figure 02 2 91 00 01 Page 04 Charts and Diagrams 30 04 08 ...

Page 178: ...MAINTENANCE MANUAL AQUILA AT01 Aviation by Excellence AG COM NAV and Intercom Wiring Diagram Fuselage Figure 03 1 91 00 01 Page 05 Charts and Diagrams 30 04 08 ...

Page 179: ...MAINTENANCE MANUAL AQUILA AT01 Aviation by Excellence AG COM NAV and Intercom Wiring Diagram Fuselage Figure 03 2 91 00 01 Page 06 Charts and Diagrams 30 04 08 ...

Page 180: ...T01 Aviation by Excellence AG Engine Wiring Diagram Figure 04 1 91 00 01 Page 07 Charts and Diagrams FIREWALL FEED THRU ENGINE CONNECTOR FUEL PRESS FUSE CLOCK MASTER RELAY STARTER RELAY EXTERNAL POWER RECEPTACLE BATTERY 30 04 08 ...

Page 181: ...UAL AQUILA AT01 Aviation by Excellence AG Engine Wiring Diagram Figure 04 2 91 00 01 Page 08 Charts and Diagrams FUEL PRESS FUEL PUMP LANDING LIGHT OIL PRESS IGNITION BOX A IGNITION BOX B OIL TEMP RPM TRANSD 30 04 08 ...

Page 182: ...lage Wiring Diagram Figure 05 1 FUSELAGE CONNECTOR 5 CABIN LIGHT ASSEMBLY TRIM CONTROL SWITCH ASSEMBLY FLAPS WING FUEL TANK CABLE HARNESS DW AT01 8220 021 EXTERIOR LIGHTING WING TRIM CONTROL FUSELAGE CONNECTOR 3 FUSELAGE CONNECTOR 2 FUSELAGE CONNECTOR 1 1 1 3 1a 1b 6055C20 6055AS20 6055AK20 30 04 08 ...

Page 183: ... 10 Charts and Diagrams Fuselage Wiring Diagram Figure 05 2 CABLE HARNESS FLAPS DW AT01 8220 021 TRIM CONTROL RED RED BLACK GREEN YELLOW BROWN BLUE TRIM ACTUATOR ASSEMBLY FLAP ACTUATOR ASSEMBLY POSITION TRANSDUCER ASSEMBLY CABLE HARNESS TRIM CONTROL AT01 8220 022 30 04 08 ...

Page 184: ...01 Aviation by Excellence AG 91 00 01 Page 11 Charts and Diagrams Wings Wiring Diagram Figure 06 1 WING FUEL TANK LEFT WING TRANSDUCER STALL WARNING SYSTEM RED RED BLACK BLACK WHITE YELLOW FUEL LEVEL SENSOR LH WING TIP LH 30 04 08 ...

Page 185: ...ANUAL AQUILA AT01 Aviation by Excellence AG 91 00 01 Page 12 Charts and Diagrams Wings Wiring Diagram Figure 06 2 EXT LIGHT WING RIGHT WING RED RED BLACK BLACK WHITE YELLOW FUEL LEVEL SENSOR RH WING TIP RH 30 04 08 ...

Page 186: ...ication 1 Instrument Panel Figure 07 1 91 00 01 Page 13 Charts and Diagrams WH GR WH GR WH YE GR PI GR BR BR GR YE BR YE WH BR PI GR GR RE RE BL BL BL VI GROUND TERMINAL BLOCK B INSTR LIGHT GROUND TERMINAL GROUND TERMINAL A2 FAN CD PLAYER POWER SUPPLY COOLING FAN GROUND TERMINAL 30 04 08 ...

Page 187: ... L PILOT PHONES R CO PILOT PHONES L LIGHT 14V HI LIGHT 14V HI GRD SPEAKER SPEAKER RETURN MUSIC 1 RETURN MUSIC 1 RIGHT MUSIC 1 LEFT GRD NAV 1 AUDIO NAV 2 RETURN NAV 1 RETURN COM 1 RETURN COM 2 RETURN COM 2 PHONES COM 1 PHONES COM 2 MIC COM 1 MIC COM 1 PTT COM 2 PTT PILOT MIC CO PILOT MIC PILOT PTT CO PILOT PTT PILOT MIC RETURN CO PILOT MIC RETURN CABIN SPEAKER FUSELAGE CONNECTOR 4 1 PILOT FUSELAGE ...

Page 188: ... 8742Ebsh22s 8741Ebsh22s 8741Cc22s 1 8741Bc22s 1 8742Bsh22s 2 8742Bsh22s 1 8741Bsh22s 1 8742Csh22s 1 8742Cc22s 1 8742Cb22s 1 8742Cd22s 2 8742Ce22s 2 8742Ca22s 1 8742Cf22s 2 8741Cb22s 1 8741Ca22s 1 8741Csh22s 1 8742Csh22s 2 8741Ba22s 1 8741Bb22s 1 8742Ba22s 1 8742Bf22s 2 8742Be22s 2 8742Bd22s 2 8742Bb22s 1 8742Bc22s 1 8741Bsh22s 2 8741Cd22s 2 8741Ce22s 2 8741Cf22s 2 8741Csh22s 2 8741Eb22s 8742Eb22s...

Page 189: ...MAINTENANCE MANUAL AQUILA AT01 Aviation by Excellence AG 91 00 01 Page 16 Charts and Diagrams Intentionally left blank 30 04 08 ...

Page 190: ...cellence AG 91 00 01 Page 17 Charts and Diagrams Avionics Wiring Diagram Modification 2 Figure 09 1 GROUND TERMINAL GROUND TERMINAL GROUND TERMINAL BLOCK B INSTR LIGHT GROUND TERMINAL A2 FAN CD PLAYER POWER SUPPLY COOLING FAN GTX 330 328 30 04 08 ...

Page 191: ...1 MIC COM 1 PTT COM 2 PTT PILOT MIC PILOT PTT PILOT MIC RETURN LIGHT 14V LO CO PILOT PHONES RET PILOT PHONES RET CO PILOT PHONES R PILOT PHONES L PILOT PHONES R CO PILOT PHONES L LIGHT 14V HI LIGHT 14V HI GRD SPEAKER SPEAKER RETURN MUSIC 1 RETURN MUSIC 1 RIGHT MUSIC 1 LEFT GRD CO PILOT MIC CO PILOT PTT CO PILOT MIC RETURN FUSELAGE CONNECTOR 4 1 PILOT FUSELAGE CONNECTOR 4 2 CO PILOT 4 3 HEAD SET CO...

Page 192: ...cellence AG 91 00 01 Page 19 Charts and Diagrams Avionics Wiring Diagram Modification 3 Figure 10 1 GROUND TERMINAL GROUND TERMINAL GROUND TERMINAL BLOCK B INSTR LIGHT GROUND TERMINAL A2 FAN CD PLAYER POWER SUPPLY COOLING FAN GTX 330 328 30 04 08 ...

Page 193: ...C COM 1 PTT COM 2 PTT PILOT MIC PILOT PTT PILOT MIC RETURN LIGHT 14V LO CO PILOT PHONES RET PILOT PHONES RET CO PILOT PHONES R PILOT PHONES L PILOT PHONES R CO PILOT PHONES L LIGHT 14V HI LIGHT 14V HI GRD SPEAKER SPEAKER RETURN MUSIC 1 RETURN MUSIC 1 RIGHT MUSIC 1 LEFT GRD CO PILOT MIC CO PILOT PTT CO PILOT MIC RETURN CABIN SPEAKER FUSELAGE CONNECTOR 4 1 PILOT FUSELAGE CONNECTOR 4 2 CO PILOT 4 3 H...

Page 194: ...MAINTENANCE MANUAL AQUILA AT01 Aviation by Excellence AG 91 00 01 Page 21 Charts and Diagrams Avionics Wiring Diagram Modification 4 Figure 11 1 Lighting GTX 330 328 30 04 08 ...

Page 195: ...MAINTENANCE MANUAL AQUILA AT01 Aviation by Excellence AG 91 00 01 Page 22 Charts and Diagrams Avionics Wiring Diagram Modification 4 Figure 11 2 30 04 08 ...

Page 196: ...y Excellence AG 91 00 01 Page 23 Charts and Diagrams Avionics Wiring Diagram Modification 5 Figure 12 1 GROUND TERMINAL P4 Lighting GROUND TERMINAL P2 GROUND TERMINAL P1 GROUND TERMINAL BLOCK B4 INSTR LIGHT GND GND GND GND GTX 330 328 30 04 08 ...

Page 197: ...m Modification 5 Figure 12 2 GPS ANTENNA GPS ANTENNA COM ANTENNA GPS ANTENNA GPS ANTENNA OPTIONAL TO FLYMAP L PITOT PRESSURE STATIC PRESSURE POSITION SENSOR GND GND OPTIONAL EXTERNAL DISPLAY 9 PIN SUB D RECEPTACLE OPTIONAL INTERFACE TO FLYMAP 500 mA FUSE BROWN BLUE ORANGE BROWN WHITE ORANGE WHITE GREEN WHITE 30 04 08 ...

Page 198: ...MAINTENANCE MANUAL AQUILA AT01 Aviation by Excellence AG Charts and Diagrams ...