Bailey Moyes 912 Dragonfly Maintenance Manual
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Bailey Moyes 912 Dragonfly Maintenance Manual

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Instructions for Printing & Binding
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Begin printing on Page 1 (the Cover) and print both sides of paper.
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Thank you for your interest in our products!
Be Safe & Have Fun!! Ed Pitman
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Summary of Contents for Bailey Moyes 912 Dragonfly

  • Page 1 Delete This Page before printing!! To Keep Page Orientation Correct Instructions for Printing & Binding This page gets wasted, to maintain orientation of pages throughout the manual when viewing online, To allow viewing 2 Pages Up. Begin printing on Page 1 (the Cover) and print both sides of paper. Page orientation is important.

  • Page 2: Copyright Ed Pitman, Rhett Radford , Bobby Bailey & Bill Moyes

    Publication Number DF-MM-912 rev 2 05/11/2014 dd/mm/yyyy Maintenance Manual 912 Dragonfly & Kit Assembly Manual 912 Dragonfly This Manual only applies to SLSA Dragonfly Aircraft and ELSA Dragonfly Kits Manufactured by Pitman Air, in the United States of America. Copyright Ed Pitman, Rhett Radford, Bobby Bailey & Bill Moyes 2014...
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  • Page 6 Record of Manual Revisions Note* A current version of this manual is always available on the internet at: http://www.pitmanair.com/dragonfly or www.safety-directives.org dd/mm/yyyy Revision Number & Date Purpose Paragraph Page numbers Rev.0 Original 04/04/2013 Rev 1 Safety Directives ¾” Axle Bolts DF- 34 &...

  • Page 7: Table Of Contents

    Table of Contents 1.1 GENERAL ..............................11 1.1.1 Equipment list, ...............................11 1.1.2 Sources to purchase parts, ............................11 1.1.3 List of disposable replacement parts ......................11 1.1.3.1 Engine Parts, ..............................11 1.1.3.2 Airframe and Systems ...........................12 1.1.4 Engine specifications, 912ULS & 912 UL ........................12 Performance 912 ULS ..............................
  • Page 8 Section 6 Pilot Seat................................33 Section 7 Fwd Wheel Throttle & Manual Brake .......................35 Section 8 Tail Wheel ................................37 Section 9 Vertical Stabilizer .............................39 Section 10 Rudder ................................41 Section 11 Horiz. Stabilizer & Elev. Frame ........................43 Section 12 Horiz. Stabilizer & Elev. Sails ..........................45 Section 13 Controls .................................47 Section 14 Aileron ................................49 Section 15 Aileron Sails ..............................51...
  • Page 9 USER’S MANUAL ............................100 GRAND RAPIDS TECHNOLOGIES INCORPORATED ................100 1. READ THIS FIRST! ..........................105 2. AN OVERVIEW OF INSTALLATION & SETUP ................. 105 3. USING THE ENGINE INFORMATION SYSTEM ................105 3.1 The Basics of the Engine Information System Operation ..................106 3.2Before Each Flight..............................
  • Page 10 7.15 User Definable Combination Pages ........................124 7.15.1 1D1, 1P1, … GD9, GP9 ..........................124 7.15.2 Table of User-Definable Page Entries......................125 7.16 Example Worksheet for setting up your custom pages..................128 BAR GRAPHS USE THE FIRST 8 CHARACTER POSITIONS. ( SHOWN AS SET AT PITMAN AIR ) ............................
  • Page 11 APPENDIX G – BAILEY RELEASE AND TOW SYSTEM ............... 177 1. General Information ..............................177 1.1 Introduction ................................177 1.2 Warnings, Cautions and Notes Explained: ......................... 177 1.3 Description of Bailey Release and Tow System ......................177 1.4 Perspective Views and Photos ........................... 177 FIGURE 1 (Bailey Release &...

  • Page 12: General

    1.1 General 1.1.1 Equipment list, Rotax 912 DCDI Engine w/E Gearbox 4:1 ratio Propeller EIS 2000- 1ea.-M2STD-01, 1ea.-OPT-IntAlt, 2ea.-EGT-CF-01, 2ea.-CHT-14-01, 1ea.-FT-1827-02, 1ea.- CAB-A-02 1.1.2 Sources to purchase parts, Note: The use of Used, Overhauled or Reconditioned Parts or Components is Strictly Prohibited unless otherwise authorized in this manual or a Letter of Authorization (LOA) is obtained from Pitman Air.

  • Page 13: Airframe And Systems

    1.1.3.2 Airframe and Systems (All Parts can be purchased direct from Pitman Air, alternate suppliers listed below) A: Clear Return Fuel Lines, # 2100686 Ether Based Superthane Only, NOT Ester Based NewAge® Industries, Inc., 145 James Way, Southampton, PA 18966-3817 Phone: 800-506-3924 or 215-526-2300 Fax: 800-837-1856 or 215-526-2190 E-mail: psales@newageindustries.com...

  • Page 14: Performance 912 Ul

    Performance 912 UL Maximum Power 81HP / 59.6KW @ 5800 RPM (5 minutes) Maximum Power 79HP / 58.9KW @ 5500 RPM (sustained) Maximum Torque 75.9ft-lb / 103NM @ 4800 RPM Combustion Chambers Bore 3.13" / 79.5mm Stroke 2.40" / 61.0mm Displacement 73.91cu.in.

  • Page 15: Weight And Balance Information

    1.1.5 Weight and balance information, 1.1.5.1 Weight and Balance Chart 1.1.5.2 Operating weights and loading (occupants, baggage, fuel, ballast) The CG must never be further FORWARD than 75.67 inches from the Datum nor further AFT than 80.78 inches from the Datum The aircraft must never be flown solo from the back seat.
  • Page 16 The Mean Aerodynamic Chord (MAC) is calculated by adding the wing and flaperon area and divide by span. AREA 183.10 ft sq 5.37ft / 64.50in MEAN SPAN 34.08ft 1. DATUM Cockpit front cross tube 0.00 2. Pilots Pelvis position Pilot 35.0in 3.
  • Page 17 1.1.5.3.3 CG WITH MAX FUEL & 100 KG / 221 lb. PILOT FOR MAX FORWARD CG (example) Weight Moment Aircraft 515lb 95.9in 49388.5in lb Fuel 33lb 60.0iin 1989.0in lb Pilot 221lb 35.0in 7735.0in lb 769lb 59112.5in lb MOMENT 59112.5 76.85in MASS As a percentage of MAC 76.85 –...

  • Page 18: Installed Optional Equipment List

    1.1.5.4 Installed optional equipment list affecting weight and balance or a reference as to where this information can be found. NOTE— ( Retrieve and/or Update this information in your POH ( Pilot Operating Handbook ) Also. Item Location Moment Weight 1.1.6 Tire inflation pressures , 15 to 25 PSI NOTE: (NEVER EXCEED 32 PSI)

  • Page 19: Lubricate"Defined

    1.1.8.1 Wear Tolerances of Cable, Bolt or Fastener and Hole Elongation. Bolts and Fastener Wear: Maximum 10% Example: ¼” 0.25 * 0.9 = 0.225’ as the thinnest part of bolt or ¼” fastener. Hole Elongation: Maximum of 15% Example: ¼” 0.25 * 1.15 = 0.2875 Maximum in longest direction of hole. Example for feeler gauge while bolt is in hole: ¼”...
  • Page 20 Items (5) and (6) contain things that may require special attention during the Inspection. Note: Each “Section” 1 through 30 of the Maintenance Instructions must be consulted to identify areas of Special Interest or “Life Limited Parts” (LLP) to identify if part needs special attention or replacement. See 2.2 of this manual.
  • Page 21  Accessories - for apparent defects in security of mounting.  All systems - for improper installation, poor general condition, defects, and insecure attachment.  Cowling or Fairings- for cracks, and defects. Continued next page (e) Each person performing an Annual or 100-hour Inspection shall inspect (where applicable) the following components of the landing gear group: ...

  • Page 22: Structures

    1.3 Structures Sections 1 through 29 and Appendix’s of this Manual 1.3.1 Wings see Sections 14 through 20 1.3.2 Empennage see Sections 1, 2, 4, 8 through 13, 21, & 23 1.3.3 Landing gear, see Sections 2, 7, 8, and Appendix B 1.3.4 Structural Control Surfaces, see Sections 9 through 21.

  • Page 23: Repairs And Alterations—Defined

    2 Inspection, Repair, and Alterations— 2.1 Repairs and Alterations—defined 2.1.1 Repairs— Repairs are to be done in accordance with Manufacturer’s Instructions for SLSA Aircraft and/or FAA AC 43.13-1B and AC 43.13- 2B for ELSA 2.1.2 Alterations— NOTE—No Alterations may be made to SLSA Aircraft without an LOA ( Letter of Authorization ) from the manufacturer.

  • Page 24: Section 1 Boom Tube

    Section 1 Pitman Air Maintenance & Inspection BOOM TUBE Assemble the internal and external parts in the following manner. Take care that each bolt that passes through the 5” boom or fuselage tube also passes through an internal tube or sleeve, so that the boom tube will not be squeezed out of round when bolts are tensioned.
  • Page 25 Drawing 1 Page 24...

  • Page 26: Section 2 Bulkhead

    Section 2 Dragonfly 582/912 Maintenance & Inspection BULKHEAD STEP INSTRUCTIONS for Assembly, for Disassembly reverse the order! PART NO. STAGE CERT. Install (see item 17 of Section 13) (LLP1000) bolt control pivot assembly DFW 012 LLP1000 into bulkhead DFI 001 as shown.
  • Page 27 Drawing 2 Page 26...

  • Page 28: Section 3 Root Tube

    Section 3 Dragonfly 912 Maintenance & Inspection ROOT TUBE STEP INSTRUCTIONS for Assembly, for Disassembly reverse the order! PART NO. STAGE CERT. Bolt AN4-27A, 1/4" washer, engine supp brkt DFO-048 912 only root tube 912, DFI 016 1/4" washer, AN4 full nut. Very tight. N/A 912 Bolt AN4-27A, 1/4”...
  • Page 29 Drawing 3 Page 28...

  • Page 30: Section 4 Fuselage

    Section 4 Dragonfly 912 Maintenance & Inspection FUSELAGE STEP INSTRUCTIONS for Assembly, for Disassembly reverse the order! PART NO. STAGE CERT. Bolt AN4-27A, 1/4" washer, root supp aft brkt lower, push rod guide aft root, DFP 013 Engine Mount Rotax 912, DFW 042 push rod guide aft root, root supp aft brkt lower, 1/4"...
  • Page 31 Drawing 4 Page 30...

  • Page 32: Section 5 Fwd Cockpit

    Section 5 Dragonfly 582/912 Maintenance & Inspection FWD COCKPIT STEP INSTRUCTIONS for Assembly, for Disassembly reverse the order! PART NO. STAGE CERT. Slide spacer 1” tube spacer .875” DFG 004 into cockpit tube fwd. DFC 018 Eye bolt AN43 – 15A, DFT 203 spacer stand off .375”, DFG 008...
  • Page 33 Drawing 5 Page 32...

  • Page 34: Section 6 Pilot Seat

    Section 6 Dragonfly 582/912 Maintenance & Inspection PILOT SEAT STEP INSTRUCTIONS for Assembly, for Disassembly reverse the order! PART NO. STAGE CERT. Slide seat tube lower fwd DFC 020 through seat-cushion. DFR 014 100 hr Bolt AN4-21A, 1/4" washer, cockpit tube lower, seat tube lower fwd. Tight. Slide seat tube fwd DFC 019...
  • Page 35 Drawing 6 Page 34...

  • Page 36: Section 7 Fwd Wheel Throttle & Manual Brake

    Section 7 Dragonfly 582/912 Maintenance & Inspection FWD WHEEL, THROTTLE & BRAKE Note: Hydraulic Brakes see Appendix B STEP PART NO. STAGE for Assembly, for Disassembly reverse the order! INSTRUCTIONS CERT. Wheel halves are not symmetrical. Take front wheel rim 8020 DFI 012 and using a 5/16"...
  • Page 37 Note: for Hydraulic Brakes see Appendix B Drawing 7 Page 36...

  • Page 38: Section 8 Tail Wheel

    Section 8 Dragonfly 582/912 Maintenance & Inspection TAIL WHEEL STEP for Assembly, for Disassembly reverse the order! PART NO. STAGE INSTRUCTIONS Wrap mylar shim around vert stab aft. DFA 006 Trim to fit snugly in main boom. Align holes, blind nut should be on fwd. side of tube. AN4 half nut, 1/4" washer, bolt vert stab aft 1/4”...
  • Page 39 Drawing 8 Page 38...

  • Page 40: Section 9 Vertical Stabilizer

    Section 9 Dragonfly 582/912 Maintenance & Inspection VERTICAL STABILIZER STEP INSTRUCTIONS for Assembly, for Disassembly reverse the order! PART NO. STAGE CERT. Wrap mylar shim around vert stab fwd DFC 003 and slide into boom tube. Align holes. AN4 half nut, 1/4" washer, Bolt vert stab fwd 1/4”...
  • Page 41 Drawing 9 Page 40...

  • Page 42: Section 10 Rudder

    Section 10 Dragonfly 582/912 Maintenance & Inspection RUDDER STEP for Assembly, for Disassembly reverse the order! PART NO. STAGE INSTRUCTIONS CERT. Slide rudder conn sleeve DFD 006 inside rudder fwd. DFC 009 Insert bolt AN3-13A temporarily screw into AN3 blind nut. Using 1/8" drill bit, drill rudder fwd and rudder conn sleeve through blind nut.
  • Page 43 Drawing 10 Page 42...

  • Page 44: Section 11 Horiz. Stabilizer & Elev. Frame

    Section 11 Dragonfly 582/912 Maintenance & Inspection HORIZONTAL STABILIZER & ELEVATOR FRAME STEP INSTRUCTIONS for Assembly, for Disassembly reverse the order! PART NO. STAGE CERT. Bolt AN3-13A, 3/16” washer, horiz stab comp strut inboard, DFC 016 threaded insert 7/16” x 10/32, DFO 037 horiz stab comp strut inboard, AN3 half nut.
  • Page 45 Drawing 11 Page 44...

  • Page 46: Section 12 Horiz. Stabilizer & Elev. Sails

    Section 12 Dragonfly 582/912 Maintenance & Inspection HORIZONTAL STABILIZER & ELEVATOR SAILS STEP PART NO. STAGE CERT. for Assembly, for Disassembly reverse the order! INSTRUCTIONS Slide spacer aileron hinge 1.125” DFG 002 in end of horiz stab aft. Bolt AN3-15A, hinge brkt, horiz stab aft, spacer aileron hinge 1.125”, horiz stab aft, tube conn saddle end 1”, threaded insert 7/16”...
  • Page 47 Drawings 12A & 12B Page 46...

  • Page 48: Section 13 Controls

    Section 13 Dragonfly 582/912 Maintenance & Inspection CONTROLS STEP INSTRUCTIONS for Assembly, for Disassembly reverse the order! PART NO. STAGE Bolt AN3-16, 3/16” washer, eyebolt, 3/16” washer, push rod follow block, DFP 004 3/16” washer, eyebolt, 3/16” washer, AN3 castle nut, cotter pin. Snug but free. Lubricate. Rod end 1/4”.
  • Page 49 Drawing 13 Page 48...

  • Page 50: Section 14 Aileron

    Section 14 Dragonfly 582/912 Maintenance & Inspection AILERON PART NO. STAGE CERT. STEP INSTRUCTIONS for Assembly, for Disassembly reverse the order! Bolt AN3-7, hinge brkt, grease, hinge point, DFK 007 grease, hinge brkt, 3/16” washer, AN3 castle nut, cotter pin. Snug but free. (Hinge brkt may need to be spread slightly so hinge point turns freely).
  • Page 51 Drawing 14 Page 50...

  • Page 52: Section 15 Aileron Sails

    Section 15 Dragonfly 582/912 Maintenance & Inspection AILERON SAILS PART NO. STAGE CERT. STEP INSTRUCTIONS for Assembly, for Disassembly reverse the order! Sprinkle generous amounts of baby powder into fabric aileron port DFR 003 and on aileron frame. Pull sail onto frame until just snug. (Patches are sewn on top side of sail).
  • Page 53 Drawing 15 Page 52...

  • Page 54: Section 16 Wing

    Section 16 Dragonfly 582/912 Maintenance & Inspection WING STEP INSTRUCTIONS for Assembly, for Disassembly reverse the order! PART NO. STAGE Bolt AN4-26A, 1/4” washer, wing spar leading edge DFA 002 (turn rivet heads to inside), wing tip insert, DFP 008 wing tip, DFC 008 wing tip insert, wing spar leading edge, 1/4”...
  • Page 55 Drawing 16 Page 54...

  • Page 56: Section 17 Wing Battens & Sails

    Section 17 Dragonfly 582/912 Maintenance & Inspection WING BATTENS AND SAILS STEP for Assembly, for Disassembly reverse the order! PART NO. STAGE CERT. INSTRUCTIONS Remove tape holding trailing edge in place. Unfold sail wing port DFR 001 and sail wing starboard DFR 002 and lay leading edge mylar flat on ground.
  • Page 57 Drawing 17 Page 56...

  • Page 58: Section 18 Wing Sail Access Holes And Sealing

    Section 18 Dragonfly 582/912 Maintenance & Inspection WING SAIL ACCESS HOLES & SEALING PART NO. STAGE CERT. STEP INSTRUCTIONS for Assembly, for Disassembly reverse the order! Using a hot knife, burn a slot against outboard sides of bent strut plates until they push through fabric.
  • Page 59 Drawing 18 Page 58...

  • Page 60: Section 19 Aileron Support Tubes & Mounting

    Section 19 Dragonfly 912 Maintenance & Inspection AILERON SUPPORT TUBES & MOUNTING PART NO. STAGE CERT. STEP INSTRUCTIONS for Assembly, for Disassembly reverse the order! Bolt AN4-30A, 1/4” washer, strut plate A, DFL 004 wing spar leading edge, strut plate B, DFL 005 1/4”...
  • Page 61 Drawing 19 Page 60...

  • Page 62: Section 20 Struts & Wing Connection

    Section 20 Dragonfly 582/912 Maintenance & Inspection STRUTS & WING CONNECTION STEP INSTRUCTIONS for Assembly, for Disassembly reverse the order! PART NO. STAGE Push spacer strut 1” into strut aft using a length of tubing or wood approx. six feet long. Cut a notch in one end of pusher tube for spacer to fit in so you may twist tube as you work.
  • Page 63 Drawing 20 Page 62...

  • Page 64: Section 21 Cable Bracing

    Section 21 Dragonfly 912 Maintenance & Inspection CABLE BRACING STEP INSTRUCTIONS PART NO. STAGE CERT. for Assembly, for Disassembly reverse the order! mirror mount brkt DFL 011 over cockpit tube lower port. Slide mirror tube 3/4” tube DFD 007 through mirror mount brkt and spacer mirror brkt DFD 008 with approx 1/8”...
  • Page 65 Drawing 21 Page 64...

  • Page 66: Section 22 Aft Seat

    Section 22 Dragonfly 582/912 Maintenance & Inspection AFT SEAT STEP INSTRUCTIONS PART NO. STAGE CERT. for Assembly, for Disassembly reverse the order! Align seat brkt aft DFO 045 to back hole. Drill 3/16” hole, pop rivet stainless steel 3/16” x 1/4”, DFT 402 seat brkt aft, seat main frame aft.
  • Page 67 Drawing 22 Page 66...

  • Page 68: Section 23 Aft Seat & Controls

    Section 23 Dragonfly 582/912 Maintenance & Inspection AFT SEAT & CONTROLS STEP INSTRUCTIONS PART NO. STAGE CERT. for Assembly, for Disassembly reverse the order! seat belt aft DFR 011 into shackle large 1/4” x 1 1/4”. DFT 602 Bolt AN4-23A, aft root supp brkt upper, shackle large 1/4” x 1 1/4”, seat supp aft, shackle large 1/4”...
  • Page 69 Drawing 23 Page 68...

  • Page 70: Section 24 912 Engine Mounting

    Section 24 Dragonfly 912 Maintenance & Inspection 912 ENGINE MOUNT These instructions are for installation of a two-stroke engine onto the engine support brackets as shown on Section STEP INSTRUCTIONS PART NO. STAGE CERT. for Assembly, for Disassembly reverse the order! Bolt AN4-10A, 8 each Engine Mount Housing, 2 each DFK 014...
  • Page 71 Drawing 24 Page 70...

  • Page 72: Section 25 912 Exhaust & Muffler Installation

    Section 25 Dragonfly 912 Maintenance & Inspection 912 EXHAUST & MUFFLER INSTALLATION STEP INSTRUCTIONS PART NO. STAGE CERT. for Assembly, for Disassembly reverse the order! Lubricate Muffler and exhaust pipe Ball Joints with thin film of High Temp Copper Anti-Seize or current Rotax recommended product. Oriented as shown in Drawing 25, place pipes into sockets of muffler, move to one side and place one exhaust spring, move it the opposite way stretching spring to place opposite spring, Repeat until all 4 pipes are on...
  • Page 73 Drawing 25 Page 72...

  • Page 74: Section 26 582 Radiator Installation

    Section 26 Dragonfly 912 Maintenance & Inspection 912 RADIATOR INSTALLATION PART NO. STAGE CERT. STEP INSTRUCTIONS for Assembly, for Disassembly reverse the order! Install Radiator Tangs DFO 050 Screw two rubber Rotax mounts & Stainless brackets, radiator mounts & DFQ 026 & DFQ 027 Rubber Buffer Rotax 25x20xM6 4 each Rotax # 260 657 into engine housing, With 6mm x 20mm 1 pitch and washer.
  • Page 75 Drawing 26 Page 74...

  • Page 76: Section 27 912 Fuel System

    Section 27 Dragonfly 912 Maintenance & Inspection 912 FUEL SYSTEM STEP INSTRUCTIONS PART NO. STAGE CERT. for Assembly, for Disassembly reverse the order! Drill 3/32” hole through cap of fuel tank DFP 051 or ventilation. Insert Fuel Strainer into Gates # 27348 Fuel Line 5/16” I.D. G# 27348 making sure it is installed with the arrow pointing upwards, fasten with hose clamp 1/4”.
  • Page 77 Drawing 27 Page 76...

  • Page 78: Section 28 Electrical System

    Section 28 Dragonfly 582/912 Maintenance & Inspection ELECTRICAL SYSTEM PART NO. STAGE CERT. STEP INSTRUCTIONS for Assembly, for Disassembly reverse the order! Mount the battery bracket, DFL 023 on the root tube. Install rubber cushion pad in bottom of battery bracket. Fit battery into position and use a wing strap to buckle the battery into position.
  • Page 79 Drawing 28a Wiring1.jpg Page 78...
  • Page 80 Drawing 28b Wiring2.jpg Page 79...
  • Page 81 Drawing 28c elecLights.jpg Page 80...

  • Page 82: Section 29 Parachute & Elt Mounting

    Section 29 Dragonfly 582/912 Maintenance & Inspection PARACHUTE & ELT MOUNTING PART NO. STAGE CERT. STEP INSTRUCTIONS for Assembly, for Disassembly reverse the order! Set Second Chantz 1100 lb. Parachute on root tube, mark holes Loose. Slide parachute mount assembly onto top of root tube as shown ( 1” space between Parachute and Gap Seal.) and Mark holes both sides.
  • Page 83 Drawing 29 Page 82...

  • Page 84: Section 30 Trim Tabs Setup

    Section 30 Dragonfly 912 Maintenance & Inspection TRIM TAB SET-UP PART NO. STAGE CERT. STEP INSTRUCTIONS for Assembly, for Disassembly reverse the order! AN42B-14A 2 each hold Elevator Trim Tab to Elevator. With Cable Bracket Hose Clamp loose (shown in Drawing 30 Item #3) Align Horizontal Stabilizer, Elevator and Trim Tab, using straight board as shown in Drawing 30 item #1 Upper portions should align at 4 points.
  • Page 85 Drawing 30 Page 84...

  • Page 86: Level Of Certification

    3 Level of Certification— 3.1 Owner— Items that can be expected to be completed by a responsible owner who holds a pilot certificate but who has not received any specific authorized training. i.e. May do certain Preventative Maintenance on SLSA as defined in Appendix D of this manual. NOTE:—FAA regulations authorize SLSA aircraft owners who hold at least a sport pilot certificate to perform maintenance as outlined in 14 CFR Part 43.

  • Page 87: Heavy Maintenance, Repairs, And Alterations

    4.2.4.4 Starters/generators/alternators, (may require additional Rotax ratings) 4.2.4.5 Exhaust manifolds/mufflers, (may require additional Rotax ratings) 4.2.4.6 Wheel and brake assemblies, 4.2.4.7 Propellers, (may require additional ratings, see manufacturers manual) 4.2.4.8 Sparkplugs, ignition wires, and electronic ignition models/components limited to the use of mechanical connections, (may require additional Rotax ratings) 4.2.4.9 Hoses and lines, (may require additional Rotax ratings) 4.2.4.10 Sailcloth covering, ( may be heavy Maintenance depending on area )

  • Page 88: Major Repairs And Alterations

    6.3 Typical components that are overhauled include: 6.3.1 Engines, Must be performed by Rotax Authorized Service Centre, refer to Rotax Manuals and website: www.flyrotax.com for specific information. 6.3.2 Carburettors/fuel injection systems, refer to Rotax Manuals and website: www.flyrotax.com for specific information. 6.3.3 Starters/alternators/generators, refer to Rotax Manuals and website: www.flyrotax.com for specific information.

  • Page 89: Terminology

    9.2.4 The level of certification needed to accomplish the task, for example, A&P, Repairman Inspection, etc.. 9.2.5 Detailed instructions and diagrams as needed to perform the task, and 9.2.6 Method to test/inspect to verify the task was accomplished properly. Service Directives are considered as mandatory tasks in order to maintain a condition of safe operation and compliance with the applicable original ASTM design specification.
  • Page 90 Major Repair, Alteration, or Maintenance —any repair, alteration, or maintenance for which instructions to complete the task excluded from the maintenance manual(s) supplied to the consumer are considered major. Manufacturer —any entity engaged in the production of an LSA or component used on an LSA. Minor Repair, Alteration, or Maintenance —any repair, alteration, or maintenance for which instructions provided for in the maintenance manual(s) supplied to the consumer of the product are considered minor.

  • Page 91: Appendix A -- Safety Of Flight Reporting Form & Comment Form

    Appendix A -- Safety of Flight Reporting Form & Comment Form (make copies of this page as needed) Safety of Flight & Service Difficulty Report Form Mail to: Pitman Air, 1840 Airport Blvd., Red Bluff, CA 96080 and/or Online at: www.pitmanair.com/dragonfly/ Item of Service Check One...

  • Page 92: Appendix B Brakes Manual For Bx1320 & Bx1000

    Appendix B Brakes Manual for BX1320 & BX1000 Appendix B Page 1 Page 91...
  • Page 93 Appendix B Page 2 Page 92...
  • Page 94 Appendix B Page 3 Page 93...

  • Page 95: Double Caliper Parts

    on ¾” Axle One Caliper up and One Aft of axle. Double Caliper Parts Elbow changes to DFN 003 ¾ & Bolts go up one size through elbow and axle Appendix B Page 4 Page 94...
  • Page 96 Appendix B Page 5 Page 95...
  • Page 97 Appendix B Page 6 Page 96...
  • Page 98 Appendix B Page 7 Page 97...
  • Page 99 Every 100 hours or Annual Inspection Loosen Set Screw ½ turn and insure there is no significant play in Woodruff Key, then re tighten. Inspect to insure 3 Allen Screws that disc floats on are tight, that there are no leaks, no significant scoring of disc and that fibre pads both sides of disc are at least 3/32”...
  • Page 100 Since these are disc brakes there is no need for a shuttle valve. When the brake piston starts to move it covers the reservoir return hole, then starts to add pressure to the system. If the piston does not return to the full back position, it will not open the reservoir return port.

  • Page 101: Model 4000/6000

    Appendix C EIS 4000 912/914 Model 4000/6000 ENGINE INFORMATION SYSTEM User’s Manual Grand Rapids Technologies Incorporated 3133 Madison Ave SE Grand Rapids, MI 49548 (616) 245-7700 Fax (616) 245-7707 Rev L Applicable to Software Versions 7.5 and above. Software Version_____________ Serial Number________________ Model Number _______________ Options ____________________...
  • Page 102 1. READ THIS FIRST! ..........................105 2. AN OVERVIEW OF INSTALLATION & SETUP ................. 105 3. USING THE ENGINE INFORMATION SYSTEM ................105 3.1 The Basics of the Engine Information System Operation ..................106 3.2 Before Each Flight ..............................106 4.
  • Page 103 7.15.2 Table of User-Definable Page Entries. 7.16 Example Worksheet for setting up your custom pages..................128 7.17 Worksheet for Planning User-Definable Pages ...................... 129 8. DISABLING PAGES ..........................131 9. ENGINE ANALYSIS FUNCTIONS ......................131 9.1 The EGT Tracking Function ............................131 9.2 Leaning Functions ..............................
  • Page 104 Figure 1a - Description of Display Pages Page 103...
  • Page 105 Figure 1b. Description of Display Pages Page 104...

  • Page 106: Read This First

    Congratulations on your purchase of Grand Rapids Technologies' Engine Information System (EIS). We are pleased that you have chosen our product to meet your aircraft instrumentation needs. You will find this system will enhance your flying pleasure while increasing your level of safety. 1.

  • Page 107: The Basics Of The Engine Information System Operation

    3.1 The Basics of the Engine Information System Operation Power to EIS when starting the engine. It is good practice to turn on the EIS before starting the engine, and verify a low oil pressure warning is generated. This verifies the oil pressure sensor is able to sense zero pressure correctly.

  • Page 108: Set Pages - Setting Engine Limits And Other User Entries

    All engine limits are stored with a checksum. If the instrument determines a user setting has been lost, it will generate a “Check Entries” message at power-up. If you see this message, carefully review all user settings. At power-up, the EIS will automatically select the page you have set as your favorite in the “DISPLAY”...

  • Page 109: Set Page Table Of Limits. [Brackets Denote Dragonfly Factory Settings] N/U = Not Used

    4.1 Set Page Table of Limits. [Brackets denote Dragonfly Factory Settings] N/U = not used Setting Recommended Setting Cont Contrast - Adjusts screen for maximum readability based on 2 or 3 viewing angle and instrument temperature. *See end of table [ 2 or 3 ] for more information about this setting.
  • Page 110 used as a warning that the engine RPM is dropping too low on the landing rollout which could result in engine stall. Min Fuel Minimum Fuel Quantity – Generates a warning when the fuel Set to at least enough useable fuel N/U [ 0 ] flow function’s fuel quantity drops below this limit.

  • Page 111: Installation

    Max EGT-Inc Maximum Increase in EGT from the Lean Point. This alarm Set limit based on experience. A N/U [ 0 ] is active while lean point is active. This alarm will often small value will allow sensitive generate a false alarm when the load on the engine detection increases, significantly reduced during descent.

  • Page 112: Wiring

    The instrument should be secured using the mounting holes in the faceplate. Figure 4 provides the physical dimensions of the instrument and a full-size mounting template. If the mounting template is used, its dimensions should be verified, as paper may expand and contract with humidity. NOTE: No special consideration must be given regarding protection from vibration.

  • Page 113: Outside Air Temperature Sensor

    3) Do not use the same ground lead for the instrument, and the ignition kill switch(es). Be sure these separate ground leads do not connect to the engine in such a way that they could become disconnected from the engine, but remain connected together. 4) The remainder of the signals are now connected.

  • Page 114: External Alarm Output

    5.2.6 External Alarm Output This output is used to control the external warning light included. The output is an OPEN/GROUND type output. This means that when this output is off (the alarm is not active), this line is equivalent to an OPEN circuit.

  • Page 115: Carburetor Temperature Probe

    4) Position the hole around the manifold so that the probe does not interfere with the cowl, and takes into consideration practical needs related to maintenance (does not interfere with the access to the oil filter, etc.), inspections, or probe mounting. Insert the probe into the exhaust manifold and secure it by tightening the clamp firmly.

  • Page 116: Verify The Wiring - A Quick Check

    Crimp the mating connectors onto the extension wire. Plug the color-coded leads onto the matching color extension wires. Secure the probe leads with suitable wire clamps to prevent them from chaffing against the engine or airframe. Heat shrink tubing can be used to protect the leads from abrasion, and insulate the electrical connections to the probe.

  • Page 117: Testing Tachometer Accuracy

    If desired, a combination page can be programmed to display the tachometer reading being sensed by the tachometer input #2. This is accomplished by selecting "N2" to be displayed on a combination page. N2 will always show the RPM calculated from tachometer input #2. The normal "Tach" display will show EITHER tachometer input #1 if it is available, OR tachometer input #2 if it is available.

  • Page 118: Setting Up Your Auxiliary Inputs - Labels And Scaling

    The settings shown on the “Configuration Set” pages are as follows. The order has been altered by grouping everything related to the auxiliary inputs at the beginning, with the remainder of the settings, in order, following the auxiliary section. 7.1 Setting up your Auxiliary Inputs – Labels and Scaling You may prefer to wire certain auxiliary functions to particular auxiliary inputs so that they show up together on the labeled page.

  • Page 119: Auxiliary Forward/Reverse Sensing Selection (+/-)

    The auxiliary inputs can be configured to provide accurate readings when connected to a fluid temperature sensor by setting the auxiliary scale factor to a special code of 0. This tells the instrument that the auxiliary input has been wired to a fluid temperature sensor (of the type the instrument has been factor set for, such as type V, or type S as shown on the label on the rear cover).

  • Page 120: Transfer Function

    7.1.7 Transfer function The transfer function mathematically defines the relationship between the auxiliary input voltage, and the numeric data displayed on the instrument. This function is of no use to most users, but is provided here for those interested in creating custom applications for the auxiliary inputs. AuxDisplay = (AuxVoltage * AuxScaleFactor / 2.5) + AuxOffset Where the AuxDisplay is the value shown on the screen, AuxVoltage is 0-5 Volts, the AuxScaleFactor is the number entered into the 1SF, 2SF, 3SF or 4SF entry.

  • Page 121: Flocalr (Return Fuel Flow Calibration)

    7.5 FloCalR (Return Fuel Flow Calibration) This entry adjusts the scaling of the return fuel flow sensor. It is not used unless your fuel system requires monitoring the outgoing and return fuel, using two fuel flow sensors. If only one flow sensor is used, this setting is ignored, and will not affect the fuel flow calculation.

  • Page 122: Tach Connections To Lighting Coils (Jabiru, Rotax, And Others)

    An external switch may also be used to manually select which ignition system provides the tachometer source. Since magneto problems can often be detected early on by erratic tachometer readings, an external switch allows the pilot to choose which magneto is to be monitored, allowing him to choose a different mag on each flight, and thus providing some monitoring of the health of each magneto.

  • Page 123: Tachsen

    7.7 TachSen Each tachometer input includes a sensitivity adjustment, identified as Tach1Sen and Tach2Sen on the configuration set pages. The "L" (low) sensitivity setting is best for most tachometer connections as it provides the greatest amount of filtering and tolerance of noise on the tachometer signal from the engine.

  • Page 124: Rpm Range Limit

    b) The tachometer must exceed the TachHi setting, and then go below the TachLo entry. This will generate an tachometer warning (the red warning light will flash, the page will change to the labeled page that includes tachometer, and the tachometer will flash). Acknowledging this alarm (by pressing the "Ack"...

  • Page 125: Altsf, 1 (10K), 2 (20K), 3 (30K), 4 (40K) Altimeter Adjustments (Sw Version 5.8 And Above)

    To calibrate the altimeter so that the barometric pressure it registers is correct, the follow procedure should be followed. This procedure must be performed with a new instrument, and should be re- checked on an annual basis. a) Turn on the instrument and allow 5 minutes or more for its internal temperatures to stabilize. b) Using the Altimeter Set page, set the altimeter so that the barometric pressure display matches the current altimeter setting.

  • Page 126: Table Of User-Definable

    Note: The items set up for the graphical leaning pages (that is, the pages with the bar graphs), apply to both of the bar graph pages. Three or four letter identifiers are used to define the data that can be displayed, and a numeric entry describes the position on the screen where this data appears.
  • Page 127 TACH Tach Highest CHT Factory Use Only CHT Rate Highest EGT EGT Span Highest EGT Change EGPk Leaning info (EGT or delta from peak EGT) for first cylinder to peak. (FRST2PK indicates which cylinder was first to peak.) FRST2PK Cylinder number of first to peak while leaning.
  • Page 128 The following illustration shows the numbering of positions on the display screen for the user-defined pages. Note how the 32 character positions are numbered from 1-32 starting in the upper left corner. 1 2 3 4 5 6 7 8 9 10 11 12 13 14 15 16 17 18 19 20 21 22 23 24 25 26 27 28 29 30 31 32 Page 127...

  • Page 129: Example Worksheet For Setting Up Your Custom

    7.16 Example Worksheet for setting up your custom pages. The easiest way to create your custom pages is to plan them on page, and then translate you plan into the entries that you will make in the instrument. To illustrate this, lets create a simple page. 1.

  • Page 130: Worksheet For Planning User-Definable

    7.17 Worksheet for Planning User-Definable Pages ( Shown as set at Pitman Air ) Note: > denotes field going further spaces 12 13 > > 22 23 26 27 28 29 30 > > Combo Page #1 1D1 = Tach 1D7 = VS 1P1 = 1 1P7 = 24...

  • Page 131: Bar Graphs Use The First 8 Character Positions

    Bar Graphs use the first 8 character positions. ( Shown as set at Pitman Air ) 10 11 12 21 22 28 29 > Graphical (Leaning) Pages Note: Don’t assign any items to position 1-8, as this space is reserved for the bar graphs. The setup for this page applies to both bar graph pages.

  • Page 132: Disabling Pages ( Pitman Air Disables Pages 0, 4, 6, 7, 9, 11, 12, 13, 14, & 15 )

    8. Disabling Pages ( Pitman Air disables Pages 0, 4, 6, 7, 9, 11, 12, 13, 14, & 15 ) Up to 10 display pages may be disabled so that they do not appear when pressing the "Next" and "Previous" buttons. Disabling pages can make it easier to get to the pages that you find the most useful.

  • Page 133: Leaning Functions

    The tracking function may also be activated during climb or descent if desired. This is especially useful when troubleshooting an intermittent problem. (It may be necessary to re-activate it during this phase of the flight to account for the change in exhaust gas temperatures resulting from the new power setting.) 9.2 Leaning Functions (Not used with Rotax Engines) For those with engines having adjustable mixture controls, the leaning functions are probably what attracted you to the EIS, and you will not be disappointed.

  • Page 134: Special Leaning Functions

    cylinders which were leaned past peak with first increase, and then decrease. The key to making it simple, it to ignore all but the first to peak (the first to go negative). Use this cylinder to adjust mixture to your desired setting (such as 50 degrees rich of peak). Note that the leaning page is typically most meaningful while leaning, and for several minutes after leaning.

  • Page 135: Detailed Description Of Other Functions

    10. Detailed Description of Other Functions 10.1 Flight Timer At power-up of the EIS, the flight timer shows the length of the previous flight in hours and minutes. This makes it easy to recall the last flight time if power is turned off to the instrument before the time is noted.

  • Page 136: Updating The Eis Software

    12. Updating the EIS Software EIS Model 4000 instruments with software version 70 or greater (as shown in the software version number on the label, or as might be displayed on the screen at power-up) include field re- programmable memory that allows the instrument to have software updates loaded into it via its serial port.

  • Page 137: Warranty

    ground. If the EIS show a high temperature, the connection to the instrument is good. If it does not change, check the wire between the instrument, and the oil or coolant temperature sensor, especially the crimp on the quick-disconnect that plugs onto the coolant temperature sensor. Tach Reading is zero when one This is normal, as the tach signal is generated by one of the mags.
  • Page 138 Appendix C EIS 4000 912/914 Page 137...
  • Page 139 Appendix C EIS 4000 912/914 Page 138...
  • Page 140 Appendix C EIS 4000 912/914 Page 139...
  • Page 141 Appendix C EIS 4000 912/914 End Appendix C Page 140...

  • Page 142: Appendix D: Items Permitted Under The Privileges Of Preventive Maintenance

    Appendix D: Items Permitted Under the Privileges of Preventive Maintenance Taken from an article for your help in determining if you are qualified! Special Note: Please read carefully the following 32 items that are permitted under the privileges of preventive maintenance and the short brief that follows.
  • Page 143 Use a magnet to extract ferrous particles, and save them for later examinations. Filter the remaining solvent through a coffee filter, and examine the remains. You should ask your A&P mechanic for advice on what you see the first couple of times.
  • Page 144 14. Replacing safety belts. You are allowed to replace your seat belts and shoulder harnesses with approved belts for your make and model airplane. If you elect to change the belts it is strongly suggested that you follow the service manual instructions for installation. If the manual calls for two washers and a spacer, use them.
  • Page 145 24. Replacing and servicing batteries. When replacing your airplane’s battery, use only an approved battery for your make and model airplane. You are also permitted to add water (distilled water) and charge your battery. If you need to clean the battery, terminals, or battery box area, baking soda works about the best.

  • Page 146: Advisory Circular 43-12A

    Advisory Circular 43-12a Preventive Maintenance Subject: Preventive Maintenance Date: 10/28/83 AC No: 43-12A Initiated by: AWS-340 1. PURPOSE. This advisory circular (AC) provides information concerning preventive maintenance, who may perform it, the standards of performance applicable to it, authority for approving aircraft for return to service, and the applicable recording requirements.

  • Page 147: Far 43.13 Performance Rules (General)

    2. FAR 43.13 requires the use of the tools, equipment, and test apparatus necessary to assure completion of the work in accordance with accepted industry practices. This means that the proper tools and test apparatus must be used. Normally these are listed as part of any FAA-approved manufacturer’s maintenance literature. 3.
  • Page 148 (a) Each person performing maintenance, alteration, or preventive maintenance on an aircraft, engine, propeller, or appliance shall use the methods, techniques, and practices prescribed in the current manufacturer's maintenance manual or Instructions for Continued Airworthiness prepared by its manufacturer, or other methods, techniques, and practices acceptable to the Administrator, except as noted in §43.16.

  • Page 149: Appendix E1 Kievprop Installation

    Appendix E1 KievProp Installation KievProp INSTALLATION INSTRUCTIONS www.kievpropamerica.com For engine type with ROTAX 912 series 75mm Bolt Pattern 8 lb. 1 oz. w/o 6 mounting bolts CG datum Point 132” 1. Disassemble prop hub, noting orientation of prop hub halves. The stamped number on each Hub half must remain adjacent to each other during re- assembly! 2.

  • Page 150: On Rotax 912 Applications

    4. On Rotax 912 applications, the hub does not require the insert to bolt directly onto the prop flange. However, if you are installing a KievProp Spacer, you will need to install the supplied insert into the prop hub. IMPORTANT! On Pusher configurations with the propeller installed, make sure that there is at least 3.75”...

  • Page 151: For Pusher Aircraft

    PUSHER TRACTOR 9. For Pusher aircraft, place the notched end of the protractor against the trailing edge of each prop blade. For Tractor applications, the notched end should be on the Leading edge of each blade. Rotate the blade until it sits flat against the leading and trailing edge of the protractor. IMPORTANT: Ensure that the ears on the protractor are flush against the hub when the setting the blade angle.

  • Page 152: A Static Check Of Rpm's

    11. A static check of rpm’s must be performed before flight. Refer to engine manual for specific instructions. With engine off, make sure your throttle has full travel and the carburetors are adjusted properly and open fully. NOTE: DO NOT FLY UNTIL YOU HAVE CHECKED AND RECHECKED YOUR PROPELLER FOR PROPER MOUNTING AND PERFORMED A STATIC CHECK OF R.P.M.’s.
  • Page 153 MOUNTING BOLTS (DRILLED MOUNTING BOLTS (UNDRILLED SHANK): AN5-36 SHANK): AN5-36A THICK WASHERS: AN960-516 THICK WASHERS: AN960-516 CASTLE NUTS: AN310-5 JAM NUT: MS21045-5 Appendix E1 Page 5 End of Appendix E1 Page 152...

  • Page 154: Appendix E2 Powerfin Installation

    Appendix E2 Powerfin Installation Powerfin Type F 72” 3 Blade pitch to 5250 rpm static INSTALLATION INSTRUCTIONS 9.7 lbs. w/o 6 mounting bolts @ CG datum Point 132” Appendix E2 Powerfin Prop Page 1 Page 153...
  • Page 155 Appendix E2 Powerfin Prop Page 2 Page 154...
  • Page 156 Appendix E2 Powerfin Prop Page 3 Page 155...
  • Page 157 Appendix E2 Powerfin Prop Page 4 Page 156...
  • Page 158 Appendix E2 Powerfin Prop Page 5 Page 157...
  • Page 159 Appendix E2 Powerfin Prop Page 6 Page 158...
  • Page 160 Appendix E2 Powerfin Prop Page 7 Page 159...
  • Page 161 Appendix E2 Powerfin Prop Page 8 Page 160...
  • Page 162 Appendix E2 Powerfin Prop Page 9 Page 161...
  • Page 163 Appendix E2 Powerfin Prop Page 10 Page 162...
  • Page 164 Appendix E2 Powerfin Prop Page 11 End of Appendix E2 Page 163...

  • Page 165: Appendix F Ameri-King Ak-451 & Ak-450

    Appendix F Ameri-King AK-451 & AK-450 GENERAL INFORMATION SCOPE This contains most information necessary for the installation, test and operation of the model AK-451, Emergency Locator Transmitter, manufactured by Ameri-King Corporation, California, U.S.A. For more detailed information refer to appropriate manuals on Ameri- King website. http://www.ameri-king.com/ Important Note: In the event your aircraft is equipped with an AK-450: Apply these differences: 1) Batteries are 6 D Cell Alkaline batteries...

  • Page 166: Application And Equipment Limitation

    The ELT (AF)(AP) has an automatic activation G-Switch. It is activated automatically upon a crash or manually operated. If for any reason, a fixed mounting is not required, the ELT (AF)(AP) can be used as a Portable Device, due to it ‘s manual operated hand use Portability.

  • Page 167: General Specifications (Standard Conditions)

    • GENERAL SPECIFICATIONS (STANDARD CONDITIONS): • TRANSMITTER: Operating Frequencies: 406.028 MHz ± 0.001 MHz (not on AK-450) 121.500 MHz ± 0.005 % 243.000 MHz ± 0.005 % Short term stability ≤ 2 x 10 /100ms 9 /min Medium slope -1 to +1x10 ≤...
  • Page 168 Figure 1: Mounting Tray for ELT- (AF)(AP). P/N 450 013 Figure 2: Holder for ELT- (AF)(AP) P/N 450 014 Figure 3: Mounting Tray with Velcro Holder and Portable Antenna for Appendix F Page 4 Page 167...

  • Page 169: Mechanical Installation

    ELT- (AF)(AP) Figure 4: Battery Pack Replacement for ELT Main Unit (Actual View) Figure 5: Battery Cell Replacement for ELT Main Unit (Actual View) (AK-450 has 6 D Cell Alkaline Batteries) MECHANICAL INSTALLATION The ELT is designed with the installer in mind. All accessories, which are required for complete ELT system installation, are provided, including Mounting Tray, Velcro Holder, Coaxial Cable Assembly and Wiring Cable Assembly.

  • Page 170: Quick Operation Check

    Installations must be made by qualified personnel in accordance with FAA regulations. Duplicating a previous installation may not be acceptable. Refer to the Department of Transportation Regional ACO for detailed information. Please refer to FAA AC 43.13 for guideline. QUICK OPERATION CHECK Note: Refer to Appendix A.1 for Quick Operation Check in sequence order.
  • Page 171 ELT Self Test: (does not apply to AK-450) Place the main switch position from “OFF” to “ARM.” The buzzer sounds, and the 2 ELT Green “ON” lights (Red Light for AK-450) shall illuminate for 4 seconds, then extinguish. After 25 seconds, a 406 MHz test signal is transmitted.

  • Page 172: Detailed Operation Check

    Detailed Operation Check: Main Switch ON/OFF/ARM Operation: In normal operation, the Main Switch, located on the ELT main unit, must be in the "ARM" position. In the event of a crash, an acceleration activated crash censor (G- switch) turns the ELT 'on' automatically when the ELT experiences a change in velocity (or deceleration) of 4.5 fps ±...

  • Page 173: System Integration Test: (Some Parts May Not Apply To Ak-450)

    Figure 6: ELT Front Panels-Main Unit and Remote Unit. System Integration Test: (some parts may not apply to AK-450) The test consists of turning the unit “ON” and then “resetting” it to verify that the Transmitter, Latch Circuit, Batteries, and associated equipment are operating properly. Regulations require that Transmitter tests only be done during the first 5 minutes of each hour and must not last for more than 3 Audio sweeps (1.5 seconds).
  • Page 174 3.1 Monitor 121.5 MHz using the Aircraft Com Receiver or Portable Hand Held Receiver. Turn the Squelch all the way up or ON. 3.2 Ensure that the main switch on the ELT is on “ARM” position. • Push the “ON” button on the Cockpit Remote Switch Unit. Verify that both the Green ON lights, located on the Main Unit and the Cockpit Remote Switch Unit, are flashing.

  • Page 175: Transmitter Funtional Test For Elt-(S) Only

    (tuning dial on any setting) is held about 6 inches from the activated ELT Antenna, the ELT Aural tone will be heard (see note below). The ELT must be reset by pressing either the RESET push button located on the ELT Main unit or the ELT Remote Unit.

  • Page 176: Periodic Maintenance (Instructions For Continued Airworthiness)

    6 PERIODIC MAINTENANCE (INSTRUCTIONS FOR CONTINUED AIRWORTHINESS): REFERENCES: FAR Part 91.207, Part 43 Appendix D (i). FAR Part 91.207 Paragraph (d) FAR Part 91.407 PURPOSE: To insure continued reliability of your ELT, it must be inspected for damage and wear which could be caused by age, exposed elements, vibrations, etc.
  • Page 177 Verification of Digital Message Note: This test is not mandatory per FAR 91.207(d) however Ameri-King strongly recommends that it be performed as part of periodic maintenance, at least every year. Verify the 406 MHz digital message using a Computer Test Set or equivalent, capable of receiving and decoding the message.

  • Page 178: Appendix G - Bailey Release And Tow System

    1. General Information 1.1 Introduction The Bailey Release and Tow System has been used and refined since 1990 on the Bailey Moyes Dragonfly for towing Hang Gliders, Ultralight Gliders and Light Sailplanes. This is more than a Release , it is a complete System.
  • Page 179 Quick Release and Safety Link Quick Change Pin and Retainer showing configuration of Safety Link. Slider Ring or Karabiner Page 178...
  • Page 180 Top Post Quick Change Line Retainer and Simple Knot. Simple Granny Knot with tail tucked in tube ahead of Knot E: Small Karabiner or Ring with Funnel Device for wind resistance and additional drag to make the untethered line fly higher behind the Tow Plane. It also protects the Ring attachment line. Rings or Karabiner are attached with line passed through loop and pulled snug.
  • Page 181 Single Point Glider Attachment picture shows Single Loop Doubled to give 4 strands of 130 lb. Safety Link connecting glider to towline. 2 Point Glider Attachment picture shows a Single Loop Safety Link of 130 lb. Solo or 200 lb. Tandem, attached by passing it through itself and attaching to Glider Release.

  • Page 182: Limitations

    Release Handle Release Pressure is easily measured with a Digital Postal Scale. Normally 5 lb. 4 oz. 4 to 9 lbs. of pressure are acceptable. More than 9 lbs. pressure indicates cable needs replacement or there is excessive resistance somewhere in the system. 2.

  • Page 183: Angles

    FIGURE 2 Knots used for Safety Links CAUTION: Any increase in Safety Link strength or change of configuration can cause structural damage and/or allow either or both aircraft to get into unsafe attitudes. Safety Links must be installed in the configurations outlined within! NOTE: Automotive GOOP can be applied over knots to help them last longer.

  • Page 184: Specifications

    2.6 Specifications 2.6.1 Tow Lines and Safety Links. Towlines and Bridle are made of Spectra 1000 or Dyneema (UHMwPE). 1100# to 2200# due to the dragging of the line during landing and taxi we use a more durable line. The small diameter and light weight of the towline, allows it to maintain alignment with less effect from wind &...

  • Page 185: Post-Flight

    3.3 Post-Flight 1) Conduct the Pre-Flight Inspection to see if maintenance is needed before next operation. 4. Maintenance and Service 4.1 General Proper Service and Maintenance of the Tow and Release System is critical to Safe Operations. Safety Links in prescribed configurations protect the airframe structure from excessive forces. 4.2 Installation Installation must be in accordance with the current Dragonfly Maintenance Manual.

  • Page 186: Signals And Communications For Tow Operations

    CAUTION: Proper materials and installation of Safety Links are required. 4.5 Corrosion, Wear and Breakage The components in the Bailey Release and Towing System are made of materials that resist corrosion. Any excessive Corrosion, Cracks, Breakage or Wear of parts or assemblies, requires replacement of bad parts or assemblies with factory supplied parts or assemblies.

  • Page 187: Figure 3 Common Signals

    By Memphis Soaring FIGURE 3 Common Signals Page 186...
  • Page 188 FIGURE 4 Common Arm and Hand Signals By Evergreen Soaring FIGURE 5 Common Aircraft Signals By Evergreen Soaring Page 187...

  • Page 189: Safety Bulletins

    7.2 Registration in Dragonfly and Bailey Release and Tow System Safety Information Network. Original Owners of the Bailey Moyes Dragonfly by Pitman Air are automatically included in the information network. Owners of SLSA are required to inform Pitman Air or the Continued Airworthiness Authority of any change of address or contact information within 30 days of such changes.

  • Page 190: Safety Of Flight & Service Difficulty Report Form

    Safety of Flight & Service Difficulty Report Form Mail to: Pitman Air, 1840 Airport Blvd., Red Bluff, CA 96080 OR Online at: www.pitmanair.com/dragonfly/ Check One Item of Concern Safety of Flight Service Difficulty Reporting Party Contact Information Name Address City Zip Code Day Phone # FAX #...

  • Page 191: Safety Of Flight & Service Difficulty Report Form

    Safety of Flight & Service Difficulty Report Form Mail to: Pitman Air, 1840 Airport Blvd., Red Bluff, CA 96080 OR Online at: www.pitmanair.com/dragonfly/ Item of Service Concern Safety of Flight Difficulty Check One Reporting Party Contact Information Name Address City Zip Code Day Phone # FAX #...

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