Bailey Moyes 912 Dragonfly Скачать руководство пользователя | Manualshive

Страница: 116 / 191

background image

Page

115

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.

NOTE :

The length of wire on the EGT & CHT probes, or the extension wire may be shortened as

desired for your installation.

5.3

Verify the Wiring – A Quick Check

Take a moment now to review all wiring connections you have made to the EIS. Double check the
following wiring:

a) power
b) ground
c) tachometer connections
d) Verify that the same ground wire is not used as both a ground to the engine for the EIS, and as a
ground for the ignition kill switches. Verify that these separate ground leads do not connect to the
engine in such a way that they could be become disconnected from the engine, but remain connected
together. Do not use the same connection to the engine for these ground leads.

Finally, install the connector backshell using the supplied hardware. Secure the wiring, using cable
clamps to the aircraft structure so that no strain is transmitted to the connector. Plug the connectors
into the EIS and secure them to the instrument with the screws included with the back shell.

6.

Check-Out

6.1

Initial Application of Power to the Instrument

Apply power to the system Verify that the LCD display becomes active. The instrument will be on
display page 0. If this operation is not observed, immediately turn off power to the EIS and recheck all
wiring---especially power, ground, 4.8V excitation output and 12V fuel flow power output.

At this point, you may wish to completely configure the instrument for your installation. Refer the
section “Configuring the EIS for your Installation”.

6.2

Tachometer Initial Test

Turn on the EIS. The tachometer will display 0 when the engine is not operating. Refer to the
“Configuration Set Pages” section, and set the TachP/R according to the type of engine you have.
Turn off the EIS. Start the engine; turn on the EIS and verify that the tachometer reading is active and
appears reasonable.

6.2.1

Testing Tachometer Inputs

Two inputs are provided for the tachometer sensing. The EIS will use tachometer input 1 when a
tachometer signal is sensed. If tachometer input #1 is not providing any RPM indication, the EIS will
use the tachometer input #2. Each input must be tested to make sure it is functioning. This test is
accomplished by turning off tachometer input #1 (such as by turning off the magneto), and observing
is tachometer input #2 provides an accurate and stable tachometer reading. Repeat this by turning off
the tachometer input #2 and verifying the tachometer input #1 is accurate and stable.

«
...
114
115
116
117
118
...
»

Содержание 912 Dragonfly

Страница 1: ...at the same time Print on 20 Lb Min Premium Paper or better Printing both sides of paper I prefer Spiral Bound with Clear Front Cover and Heavy Black Back Cover This allows the manual to be opened and folded back leaving the desired page exposed and lays flat when opened to expose 2 pages while doing Inspections or Maintenance I generally get them printed at Staples or Office Depot where it costs ...

Страница 2: ... 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 ...

Страница 3: ...Page 2 ...

Страница 4: ...Page 3 ...

Страница 5: ...Page 4 ...

Страница 6: ... Rev 1 31 05 2014 Safety Directives Axle Bolts DF 1402 Horz Stab Bolt DF 1401 34 38 Rev 2 05 11 2014 Update Table of Contents All All Serial Number Information PA or PAK ____ ____ ____ ____ ____ ____ Pitman Air or Pitman Air Kit Engine Production Number Example PA 912 126 This Manual only applies to SLSA Dragonfly Aircraft and ELSA Dragonfly Kits Manufactured by Pitman Air in the United States of ...

Страница 7: ...ir of the aircraft and it s components 18 1 2 INSPECTIONS ANNUAL AND OR 100 HOUR INSPECTIONS 18 1 2 1 Checklist for Annual 100 hour Inspections 18 1 3 STRUCTURES 21 1 3 1 Wings see Sections 14 through 20 21 1 3 2 Empennage see Sections 1 2 4 8 through 13 21 23 21 1 3 3 Landing gear see Sections 2 7 8 and Appendix B 21 1 3 4 Structural Control Surfaces see Sections 9 through 21 21 1 3 5 Fabric Cove...

Страница 8: ... 85 3 2 LSA Repairman Inspection LSRI see 4 1 5 1 6 1 and Appendix D of this manual 85 3 3 LSA Repairman Maintenance LSRM see 4 1 5 1 6 1 85 3 4 A P see 4 1 5 1 6 1 85 3 5 Task Specific see 4 1 5 1 6 1 and Appendix D of this manual 85 3 5 1 Rotax Engines and Gearboxes 85 3 6 Multiple descriptors 85 4 LINE MAINTENANCE REPAIRS AND ALTERATIONS 85 4 1 Authorization to Perform 85 4 2 Typical Tasks Cons...

Страница 9: ... Inputs Labels and Scaling 117 7 1 1 Aux1 Aux2 Aux3 Aux4 Aux5 Aux6 117 7 1 2 Dual TIT Option and Aux5 Aux6 117 7 1 3 Auxiliary Scale Factors and Offsets 1SF 1OFF 2SF 2OFF 117 7 1 4 Configuring an Auxiliary Input for a Fluid Temperature Sensor 117 7 1 5 Auxiliary Forward Reverse Sensing Selection 118 7 1 6 Auxiliary Decimal Integer Selection D I 118 7 1 7 Transfer function 119 7 2 Units Fahrenheit ...

Страница 10: ...eral 146 APPENDIX E1 KIEVPROP INSTALLATION 148 1 Disassemble prop hub 148 2 Inspect each blade 148 3 Install shoulder bolts 148 4 On Rotax 912 applications 149 SECURING ASSEMBLED PROP TO ENGINE 149 5 Secure finger tight the propeller 149 6 With all bolts slightly tightened 149 8 Fit the aluminum end of the protractor 149 9 For Pusher aircraft 150 10 When all blade angles have been set 150 11 A sta...

Страница 11: ...ions 184 4 4 Operational Tests 184 5 Signals and Communications for Tow Operations 185 FIGURE 3 Common Signals 186 6 Safety Bulletins 188 7 Operational and Service Difficulty Reporting 188 SAFETY OF FLIGHT SERVICE DIFFICULTY REPORT FORM 189 SAFETY OF FLIGHT SERVICE DIFFICULTY REPORT FORM 190 Note The Contents and Structure of this manual are mandated by ASTM Standard F2483 05 FAA Regulations requi...

Страница 12: ...nsors Grand Rapids Technologies Inc 3133 Madison Ave Wyoming MI 49548 1211 PH 616 245 7700 FAX 616 245 7707 http www grtavionics com Engine and Gearbox Lockwood Aviation Supply Inc 1 Lockwood Lane Sebring FL 33870 Phone 863 655 5100 Fax 863 655 6225 http www lockwood aviation com Bolts Nuts Wire Misc Hardware Tools etc NOTE Be sure to ask for Documentation when ordering parts keep with permanent r...

Страница 13: ...ts Rotax requirements from any Marine or Auto Parts Supplier E Tires See Aircraft Spruce Above Any quality tires commonly used on General Aviation Aircraft NO Not for Highway Use Tractor or Cart Tires Note Maximum Pressure 29 PSI because of rims never exceed 32 psi F Airframe Structural Components and Parts including Fabric Coverings These parts must be OEM Pitman Air parts to insure proper qualit...

Страница 14: ...tion Chambers Bore 3 13 79 5mm Stroke 2 40 61 0mm Displacement 73 91cu in 1211 2cm Compression ratio 9 0 1 Weight Engine with carburetors 121 2lbs 55 0Kg Exhaust System 8 8lbs 4 0Kg Air Filter 0 7lbs 0 3Kg Liquid Radiator 2 2lbs 1 0Kg Oil Radiator 1 1lbs 0 5Kg Regulator Rectifier 0 2lbs 0 1Kg Installed Weight 134 2lbs 60 9Kg Weight power ratio 1 66lbs HP 1 0Kg KW ...

Страница 15: ...to the aircraft specific figures recorded in section 1 1 5 3 4 912 The empty weight CG should be approximately 96 25 in from the Datum or 56 2 of the MAC 1 1 5 3 Center of gravity CG range and determination The weight and position of the Center of Gravity CG of the empty aircraft must be established to conduct load sheet calculations The aircraft must be weighed and measured in a fixed position an...

Страница 16: ... 31752in lb Total Weight 515 5lb Total Moments 49420in lb CG from Datum Moment 49420in lb 95 90in Mass 515 5lb The Leading Edge of the wing is 60 0in aft of Datum The empty weight CG position from the Leading Edge is then 95 90in 60in 35 9in As a percentage of MAC 35 9 0 556 55 6 64 5 1 1 5 3 1 MAX AFT CG WITH 133lb PILOT AND 11lb FUEL example Weight Arm Moment Aircraft 515lb 95 9in 49388 5in lb F...

Страница 17: ... AND CG POSITION NOTE Retrieve these numbers from your POH Pilot Operating Handbook Dragonfly Serial No Weight at tail wheel lb Weight at right main wheel lb Weight at left main wheel lb Empty weight with standard equipment lb Maximum take off weight 1080 lb Maximum load lb Empty weight CG position inch CG position MAC MAC Date Inspector 1 1 5 3 5 Load Sheet EMPTY WEIGHT CALCULATIONS WEIGH T lb MO...

Страница 18: ...own Tightening Instructions because of its location and function reference the appropriate Section in this manual or Illustrated Parts Kit Assembly Manual for the instructions on each fastener Bolt Tightening Lubricate Terms Defined Note Observation is required to ensure that no tubes or parts are deformed or crushed Loose In place but waiting for tightening after section is totally assembled Snug...

Страница 19: ...Appendix A in the back of this manual in the beginning of the POH Pilot Operating Handbook behind the Table of Contents 1 1 11 Standard Tools needed for the maintenance and repair of the aircraft and it s components Wrenches sockets Allen wrenches in both SAE and Metric are needed Hammers Safety Wire Pliers needle nose and square pliers screw drivers in both straight and Phillips chisels punches f...

Страница 20: ...nd Fittings for uncleanliness signs of corrosion excess wear and loose equipment that might foul the controls or systems Seats and safety belts for poor condition and apparent defects Windows and windshields for deterioration and breakage Instruments for poor condition mounting marking and where practicable improper operation Flight and engine controls for improper installation and improper operat...

Страница 21: ... where applicable the following components of the propeller group Propeller assembly for cracks nicks binds and oil leakage Bolts for improper torqueing and lack of safe tying I Each person performing an annual or 100 hour inspection shall inspect where applicable the following components of the radio group Radio and electronic equipment for improper installation and insecure mounting Wiring and c...

Страница 22: ...punctures at less than 60 the sails should be replaced If the sails are replaced A complete inspection of the frame and all members should be done for cracks loose fasteners or deterioration Special attention should be given around compression members Any members or parts not in good condition should be replaced before recovering Do not re cover a problem or weak area without fixing it 1 3 Engine ...

Страница 23: ...teration which may affect the Structural and or Aerodynamic Qualities of the aircraft and or its Systems must be thoroughly tested before authorization can be given Additional fees may apply depending upon the extent of testing required NOTE Request for LOA can be made by submitting detailed request for Change or Alteration including Drawings Pictures Diagrams etc which make clear the intended alt...

Страница 24: ...y 100 hrs or Annual DFP 005 5 100 hr Eye bolt AN42 4A through boom tube Flat end of eye bolt is at right angle with boom tube when tight Tight DFT 201 6 Replacement Insructions release cable Using old cable to pull new cable through tape the new release cable to the old cable and pull through Bring the aft end of the release through the 1 2 hole to align with the release boom DFQ 010 1 Recommended...

Страница 25: ...Page 24 Drawing 1 ...

Страница 26: ...ft end Slide plastic sleeve through bulkhead Screw pan head 10 x 3 4 cable clamp 1 4 tube plug 875 x 75 x 25 DFP 007 DFT 431 DFQ 009 DFT 512 8 LLP500 100 hr Place spacer 1 tube spacer 875 875 inside main boom supp tube You may squeeze the tube slightly with pliers to facilitate Be sure to wrap tube to prevent marring and use just enough pressure to avoid deforming tube Bolt AN4 16A 1 4 washer chan...

Страница 27: ...Page 26 Drawing 2 ...

Страница 28: ...ed above Max Wear defined 1 1 8 1 3 Type of maintenance Inspection Line Replacement Heavy when it involves replacement of structural components 4 Certification needed to accomplish the task Line LSRI Inspection or above Heavy LSRM Maintenance or above see 3 Level of Certification in this manual 5 Detailed instructions and diagrams as needed to perform the task listed above and adjacent page Every ...

Страница 29: ...Page 28 Drawing 3 ...

Страница 30: ... aluminium root tube saddle mid root supp aluminium root supp mid 1 4 washer AN4 full nut Very tight DFK 012 6 Bolt AN4 23A 1 4 washer flap adjuster assembly spacer stand off 375 root supp aft spacer stand off 375 flap adjuster assembly 1 4 washer AN4 half nut Tight DFG 008 7 Drill 5 32 hole in bottom centre of saddle mid root supp 1 125 stopping short of bolt through saddle screw pan head 10 x 3 ...

Страница 31: ...Page 30 Drawing 4 ...

Страница 32: ...oot tube saddle 1 upper cockpit tube starboard spacer 1 tube spacer 875 875 upper cockpit tube starboard 1 4 washer AN4 full nut Very tight DFC 005 DFC 004 8 Slide spacer 1 tube spacer 875 875 into upper cockpit tube port and starboard Bolt AN4 16A 1 4 washer channel brkt 1 upper cockpit tube spacer 1 tube spacer 875 875 upper cockpit tube channel brkt 1 1 4 washer AN4 half nut Very tight Tighten ...

Страница 33: ...Page 32 Drawing 5 ...

Страница 34: ... fwd hole Remove bolt 6 pin fwd hole and drill aft hole Repeat for left side through side cockpit port Put seat tube upper through seat Slide side cockpit port and side cockpit starboard into seat tube upper and align holes Take tank strap and using a tapered punch or similar tool work through strap spreading threads until a 1 4 bolt will pass through two inches from buckle Bolt AN4 31A 1 4 washer...

Страница 35: ...Page 34 Drawing 6 ...

Страница 36: ... 9 Remove one nut from brake cable Slide cable into brake cable anchor brkt Replace nut and adjust when assembly is complete 10 Nut 5 16 x 18 TPI brake arm brake assembly Very tight 11 Slide spacer brake plate 20mm x 3mm x 1 4 and wheel onto axle nut 5 8 UNF locknut Tight DFB 009 DFT 021 12 Bolt AN3 21A 3 16 washer cockpit tube lower left brake cable Tight 13 Bolt AN3 26 3 16 washer throttle lever...

Страница 37: ...Page 36 Note for Hydraulic Brakes see Appendix B Drawing 7 ...

Страница 38: ...olt AN3 5A release arm release cable release arm AN3 half nut Very tight DFQ 011 11 Bolt AN4 26A 1 4 washer tail plate tail plate mount block tail plate 1 4 washer AN4 half nut Loose DFK 009 12 Bolt AN4 26A 1 4 washer tail plate saddle 1 75 vert stab aft saddle 1 75 tail plate 1 4 washer AN4 half nut Loose If you have trouble aligning holes loosen bolt 1 Sect 1 insert bolt 12 and re tighten bolt 1...

Страница 39: ...Page 38 Drawing 8 ...

Страница 40: ... the sail stop assembly of vert stab here and continue to next Section DFC 015 DFT 005 7 Burn holes in fabric for bolts 7 8 9 11 Bolt AN3 26A 3 16 washer horiz stab brkt spacer 1 x 25 x 125 saddle 1 75 vert stab aft saddle 1 75 spacer 1 x 25 x 125 horiz stab brkt 3 16 washer AN3 half nut Tight DFI 008 DFP 028 DFP 032 8 Bolt AN4 25AS 3 16 washer horiz stab brkt modified tube conn vert stab fwd sadd...

Страница 41: ...Page 40 Drawing 9 ...

Страница 42: ...ll rivet tight but do not pop This rivet keeps from flipping over during installation Slide rudder comp strut upper into fabric through half moon cut out in sail Put end of rudder comp strut over 1 2 tube insert from step 2 Holding rudder up to light sideways grasp rudder comp strut through fabric and work the other end over the 1 2 tube Push fwd end of comp strut into place through half moon cut ...

Страница 43: ...Page 42 Drawing 10 ...

Страница 44: ...nium 3 16 x 5 8 1 2 tube insert angled horiz stab fwd Set rivet Do not pop DFT 413 DFP 017 10 Pop rivet aluminium 3 16 x 5 8 1 2 tube insert horiz stab aft Set rivet do not pop DFP 017 DFB 006 11 Pop rivet aluminium 3 16 x 5 8 horiz stab tension tube horiz stab aft Pop the rivet Put first rivet in centre hole and pop Go to one end of tube centre horiz stab tension tube using hole in end of horiz s...

Страница 45: ...Page 44 Drawing 11 ...

Страница 46: ...ction 11 Tighten bolts 4 and 5 Snug but free Stop now if you intend to paint DFT 412 DFF 010 DFF 009 DFF 008 6 After Paint Bolt AN3 17A 3 16 washer horiz stab brkt horiz stab aft saddle 1 horiz stab brkt 3 16 washer AN3 half nut Tight 7 Bolt AN3 17A 3 16 washer horiz stab brkt horiz stab fwd saddle 1 spacer 1 x 25 x 125 horiz stab brkt 3 16 washer AN3 half nut Tight DFP 028 8 Bolt AN3 7A 3 16 wash...

Страница 47: ...Page 46 Drawings 12A 12B ...

Страница 48: ... LLP1500 3 16 washer push rod horn elevator push rod fwd push rod horn AN3 castle nut cotter pin Snug but free 17 LLP1000 Bolt control pivot assembly LLP1000 grease 3 16 washers as necessary joystick torsion tube 3 16 washer AN3 castle nut cotter pin Snug but free DFW 012 18 Bolt AN3 14 joystick hinge 3 16 washers as necessary seat tube fwd 3 16 washer AN3 castle nut cotter pin Snug but free 19 LL...

Страница 49: ...Page 48 Drawing 13 ...

Страница 50: ...be inserts are oversized they may be shaved to fit with a razor knife Lubricate and push inboard end of aileron trailing edge into aileron main spar 7 Screw CS 10 x 3 4 aileron trailing edge aileron splice 3 x 10 8mm tube aileron trailing edge aileron frame conn block Tight DFT 506 DFG 006 Put aileron leading edge over aileron splice shorter bend in leading edge is outboard Lubricate and insert 1 ...

Страница 51: ...Page 50 Drawing 14 ...

Страница 52: ...Go to tip of aileron and work out wrinkles Rotate tie wraps so that connection is to outboard so you do not run out of space while tightening Pull tie wraps tight Work out wrinkles rotate tie wraps tighten Repeat until gap closes to 1 To close gap cover roll fabric down side to side until right side out if gap cover stops when it reaches outboard fabric trim outboard fabric at leading and trailing...

Страница 53: ...Page 52 Drawing 15 ...

Страница 54: ... washer wing comp strut saddle channel brkt wing comp strut wing comp strut saddle channel brkt 1 4 washer AN4 half nut Tight 18 Bolt AN4 30A 1 4 washer wing comp strut saddle channel brkt wing comp strut wing comp strut saddle channel brkt 1 4 washer AN4 half nut Loose 19 Bolt AN4 30A 1 4 washer strut plate A wing spar trailing edge strut plate B 1 4 washer AN4 full nut Tight Check to be sure win...

Страница 55: ...Page 54 Drawing 16 ...

Страница 56: ...in Insert batten end aft in aft end of batten Continue pushing until batten just exits fwd end of pocket Remove batten end upper fwd and replace with batten end fwd Push aluminium piece over leading edge spar Push batten down until it stops Do not pop into place yet Repeat process moving inboard third batten from tip is the most difficult to access Use needle nosed pliers to remove tip and insert ...

Страница 57: ...Page 56 Drawing 17 ...

Страница 58: ...inboard fabric just above leading edge spar Slide wing tension bar upper into place Bend forward part of wing tension bar lower to match lower batten Slide into fwd cut out in lower sail Put fwd end into pocket and slide fwd Hold aileron up to light Locate and burn holes through patches over hinge points Burn small hole first to make sure hinge point is centred finished hole should be approx 3 4 s...

Страница 59: ...Page 58 Drawing 18 ...

Страница 60: ...to Root Tube Set Level to Zero on Root Tube Measure angle of Aileron at inboard part of outer frame where it is not affected by fabric angles Adjust using Ball Joint Rod Ends on Aileron Linkages both top and bottom this occasionally requires shortening the treads on Ball End Joints by as much as and tighten jamb nuts Note Be sure to hold stick centred during this process DFG 002 1 Recommended Spec...

Страница 61: ...Page 60 Drawing 19 ...

Страница 62: ... washer AN4 high temp nut Loose 12 Bolt AN4 22A 1 4 washer strut plate A strut block strut plate B 1 4 washer AN4 high temp nut Tighten bolts 8 12 Very tight 13 Slide jury strut oversleeve aft over jury strut aft Slide through jury strut conn aft Bolt AN3 10A 3 16 washer jury strut aft threaded insert 1 2 x 10 32 jury strut aft 3 16 washer AN3 half nut Very tight DFP 039 DFE 001 DFO 040 14 Bolt AN...

Страница 63: ...Page 62 Drawing 20 ...

Страница 64: ...t AN4 26A cable wing tail lower tail plate tail plate cable wing tail lower AN4 high temp nut Tight 7 Bolt AN3 20A cable wing tail upper vert stab aft tow pylon vert stab aft cable wing tail upper AN3 high temp nut Tight DFA 008 8 Bolt AN3 16A 3 16 washer tow pylon tang hg bent AN3 half nut Tight DFO 034 1 Recommended Special Tools None 2 The parts needed to perform the task Replace worn damaged p...

Страница 65: ...Page 64 Drawing 21 ...

Страница 66: ...p brkt DFK 004 6 Bolt AN3 16A 3 16 washer aft seat supp brkt saddle 1 seat main frame lower aft 3 16 washer AN3 half nut DFP 031 7 Burn hole for seat supp aft Bolt AN4 31A 1 4 washer seat frame lower aft seat supp aft 1 4 washer AN4 half nut Loose DFB 005 8 Burn top hole for seat supp aft Bolt AN3 23A 3 16 washer seat main frame upper aft seat supp aft 3 16 washer AN3 half nut 9 Knob throttle thre...

Страница 67: ...Page 66 Drawing 22 ...

Страница 68: ...addle 1 push rod aft saddle 1 joystick plate aft 3 16 washer AN3 castle nut cotter pin DFC 017 7 Bolt AN3 20 3 16 washer joystick plate aft push rod follow block joystick plate aft 3 16 washer AN3 castle nut cotter pin 8 Bolt AN3 14 3 16 washer mid push rod conn push rod aft mid push rod conn 3 16 washer AN3 castle nut cotter pin 9 Connect throttle cable aft DFQ 007 1 Recommended Special Tools Non...

Страница 69: ...Page 68 Drawing 23 ...

Страница 70: ...osition Install by fitting 4 bolts AN7 43A AN970 7 washers on each side of Rubber Engine Mount 912 Note Rubber Engine Mounts are directional Install as shown in diagram Radiator supp brkt 912 2 each on lower bolts washer on top 2 AN7 full nut DFS 009 DFO 026 DFO 027 1 Recommended Special Tools None 2 The parts needed to perform the task Replace worn damaged parts as needed listed above Max Wear de...

Страница 71: ...Page 70 Drawing 24 ...

Страница 72: ... Ball Joints and Muffler for Cracks Wear Security and Defects 1 Recommended Special Tools None 2 The parts needed to perform the task Replace worn damaged parts as needed listed above Max Wear defined 1 1 8 1 3 Type of maintenance Inspection Line Replacement Heavy when it involves replacement of structural components refer to Rotax Manual for guidance on Engine Engine Components 4 Certification ne...

Страница 73: ...Page 72 Drawing 25 ...

Страница 74: ...ead 12 7mm H10108 cut ti fit as shown DFL 021 7 Mount Overflow Bottle R 922 327 w Bracket 4 6mm screws MMC92925A102 4 washers behind Bracket Cut 1 4 steam hose and fit from Bottle to radiator tank fasten each end with hose clamp 1 4 DFO 051 8 Fit radiator cap 9 Insure all directions in Drawing 26 have been accomplished 10 Complete step 4 on Section 24 11 Complete step 8 on Section 25 1 Recommended...

Страница 75: ...Page 74 Drawing 26 ...

Страница 76: ...ted at engine fasten all w hose clamps Add Return Line of Superthane Tubing from fuel bypass on top of engine back along Fuel Supply line back to Fuel Tank Cap EASOV 120S P60504 PA 5 16CV Lockwood NAPA 1 Recommended Special Tools None 2 The parts needed to perform the task Replace worn damaged parts as needed listed above Max Wear defined 1 1 8 1 3 Type of maintenance Inspection Line Replacement H...

Страница 77: ...Page 76 Drawing 27 ...

Страница 78: ...nders to Engine Connectors Drawing 28b 12 Connect EIS to Engine Connectors Drawing 28b 1 Recommended Special Tools None 2 The parts needed to perform the task Replace worn damaged parts as needed listed above Max Wear defined 1 1 8 1 3 Type of maintenance Inspection Line replacement of fuses etc Replacement Heavy when it involves replacement of structural components all Electrical Components and W...

Страница 79: ...Page 78 Wiring1 jpg Drawing 28a ...

Страница 80: ...Page 79 Wiring2 jpg Drawing 28b ...

Страница 81: ...Page 80 elecLights jpg Drawing 28c ...

Страница 82: ... manufacturer s instructions ELT Mount located on the front top of Left Wing Inboard Compression Strut NOTE ELT must be inspected every 12 calendar months in accordance with FAR 91 207 d Battery Replacement Regulations require ELT batteries to be replaced after one hour of operation or after 50 percent of the battery s useful life The one hour usage requirement is cumulative if the ELT is used two...

Страница 83: ...Page 82 Drawing 29 ...

Страница 84: ...craft 1 Recommended Special Tools None 2 The parts needed to perform the task Replace worn damaged parts as needed listed above Max Wear defined 1 1 8 1 3 Type of maintenance Inspection Line Replacement Heavy when it involves replacement of structural components Parachute Components 4 Certification needed to accomplish the task Line LSRI Inspection or above Heavy LSRM Maintenance or above see 3 Le...

Страница 85: ...Page 84 Drawing 30 ...

Страница 86: ...dust dirt while inside the engine and methods not commonly found in aircraft engines As well as features in their gearboxes which are unique to Rotax General aircraft engine experience may not be sufficient to correctly maintain or service these engines and related components Therefore We agree with Rotax That the technician must have the appropriate Rotax training experience and certificates to w...

Страница 87: ... be performed is generally considered the minimum level of certification to perform heavy maintenance of LSA 5 2 Typical Tasks Considered as Heavy Maintenance for SLSA s Include 5 2 1 Removal and replacement of components for which instructions are provided in the maintenance manual or service directive instructions such as 5 2 1 1 Complete engine removal and reinstallation in support of an engine...

Страница 88: ...ition for safe operation 7 4 The manufacturer or other entity that performs the evaluation shall provide information LOA to the owner of the aircraft for the documentation of the alteration in the aircraft s records 8 Task Specific Training 8 1 A manufacturer of a product may require type specific training in order to accomplish a task in either the maintenance manual or in an authorization for a ...

Страница 89: ...ns or alterations not considered heavy maintenance that is approved by the manufacturer and is specified in the manufacturer s Maintenance Manual LLP Life Limited Part Life Limited Parts are parts known to have a limited amount of use before replacement is required LSA Light Sport Aircraft aircraft designed in accordance with ASTM standards under the jurisdiction of Committee F37 Light Sport Aircr...

Страница 90: ...oduced by that manufacturer Qualified Person A person with the proper Certification Training and Experience in that specific task to perform the task correctly Repair Facility facility specifically authorized by the aircraft or component manufacturer to repair the product originally produced by that manufacturer Structural Component Any part or group of parts which are critical to the structure by...

Страница 91: ...m of Concern Safety of Flight Service Difficulty Reporting Party Contact Information Name Address City ST Zip Code Day Phone FAX email address Check Appropriate Owner Operator LSRI LSRM A P Other Explain Aircraft Specific Information Aircraft Information Engine Information Make Make Model Model Serial Number Serial Number N Number Gearbox Ratio Date of Mfg Propeller Mfg Propeller Serial Date of Pr...

Страница 92: ...Page 91 Appendix B Brakes Manual for BX1320 BX1000 Appendix B Page 1 ...

Страница 93: ...Page 92 Appendix B Page 2 ...

Страница 94: ...Page 93 Appendix B Page 3 ...

Страница 95: ...Page 94 Double Caliper Parts on Axle One Caliper up and One Aft of axle Elbow changes to DFN 003 Bolts go up one size through elbow and axle Appendix B Page 4 ...

Страница 96: ...Page 95 Appendix B Page 5 ...

Страница 97: ...Page 96 Appendix B Page 6 ...

Страница 98: ...Page 97 Appendix B Page 7 ...

Страница 99: ...ds both sides of disc are at least 3 32 thick The Allen Set Screw is tight WARNING When brakes are set up for front and rear there is a chance the rear cylinder will turn into a check valve if the rear brake is not all the way back out This can happen if dirt gets under the snap ring that holds the piston in or if the person in the rear seat applies a little pressure with enough motion for the cup...

Страница 100: ...head of the piston and cannot come back the other way because of the Cup Seal shape Also the piston retainer snap ring is punched out so it has a rounded side and a square side The rounded side has to face the piston so that the square side is holding the piston from coming out We have had the piston pop out of the rear master cylinder because the rounded side was trying to hold the piston in when...

Страница 101: ...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 ____________________ ...

Страница 102: ...Aux5 Aux6 117 7 1 2 Dual TIT Option and Aux5 Aux6 117 7 1 3 Auxiliary Scale Factors and Offsets 1SF 1OFF 2SF 2OFF 117 7 1 4 Configuring an Auxiliary Input for a Fluid Temperature Sensor 117 7 1 5 Auxiliary Forward Reverse Sensing Selection 118 7 1 6 Auxiliary Decimal Integer Selection D I 118 7 1 7 Transfer function 119 7 2 Units Fahrenheit Celsius and Gallons Liters 119 7 3 FC1 FC2 Fuel Flow Acti...

Страница 103: ...32 9 2 1 Leaning with the Bar Graph 132 9 2 2 Digital Leaning Page 132 9 2 3 Special leaning functions 133 9 2 4 First Cylinder to Peak FRST2PK 133 9 2 5 EGPk First Cylinder to Peak Leaning Status 133 9 3 Shock Cooling Detection 133 10 DETAILED DESCRIPTION OF OTHER FUNCTIONS 134 10 1 Flight Timer 13410 2 Unit Temperature 134 10 3 H2O Water Temperature Function 134 11 UPDATING THE EIS SOFTWARE 135 ...

Страница 104: ...Page 103 Figure 1a Description of Display Pages ...

Страница 105: ...Page 104 Figure 1b Description of Display Pages ...

Страница 106: ...t must be connected through the auxiliary inputs The auxiliary inputs may be used for other functions also but these are the most common uses The only significant consideration concerns the position of the auxiliary input functions on the labeled pages Referring to figure 1b you will note that auxiliary 1 2 3 appear on page 12 and auxiliary 4 appears on the next page You may prefer to see two or t...

Страница 107: ...t is flashing the instrument will ignore the other buttons Acknowledging an alarm returns the instrument to the page it was previously on and allows it to alert you to the next problem After acknowledging an alarm the warning light will remain continuously on as long as any out of limit condition exists The warning light will go out when everything is within limits An alarm that goes away and then...

Страница 108: ... are retained when the instrument is turned off No electrical connection to the instrument or battery is required to maintain these settings Since all limits can be entered easily by the pilot at any time it is practical to set engine limits lower than those indicated by the engine manufacturer but slightly higher than encountered in normal operation In this way a change in normal engine operation...

Страница 109: ... changing fuel tank selection Max Flow N U 0 Maximum Fuel Flow Generates a warning when the fuel flow rate of fuel burn exceeds this limit Useful for detecting badly leaking fuel lines loose connections to fuel injectors etc Very useful safety feature for all engines but especially fuel injected engines Be sure to use it Set about 10 20 above max fuel flow rate at full takeoff power Applicable onl...

Страница 110: ...never instrument is on while engine is not running Set to 12 4 volts or less to avoid alarm when engine not running but still gives alarm shortly after battery discharging has begun Max Carb N U 0 Carb temp warning is generated when the carb temp falls between the Max Carb and Min Carb Limit 40 60 deg F Min Carb N U 0 See Max Carb 0 20 deg F Max EGT 1480 F Maximum EGT Not all engines have publishe...

Страница 111: ...for engine troubleshooting problems Also useful as an engine not warmed up yet reminder Set limit based on experience or to zero if not used Display 1 Define which page number is your favorite The instrument will select this page at power up or when leaving the set pages after all alarms if any are acknowledged This page is also selected by double clicking the Display button See figure 2 for page ...

Страница 112: ... the remainder of the electrical system if possible These separate ground wires should attach to different places on the case of the engine so that both sets of grounds could not disconnect from the engine while remaining connected to each other This provides additional protection for the instrument although its internal protection is usually more than adequate but more importantly protects other ...

Страница 113: ...sor Start by installing the sensor in the engine according to the recommendations of the engine manufacturer After installation route the wires through engine compartment making certain the wire is supported so that it will not be chaffed A connector or terminal strip may be used between the aircraft wiring and the sensor to enhance maintainability if desired Single wire type sensors those which h...

Страница 114: ... 6 0 Volts 5 2 8 Cylinder Head Temperature Probe Installation Ring terminal type CHT probes are installed by removing the spark plug placing the sensor under it and re installing the plug into the engine Orient the sensor so that as much clearance as possible is provided between its leads and the engine structure Bayonet type CHT probes for Lycoming and Continental engines are retained by a bayone...

Страница 115: ... may cause erratic EGT readings 5 2 10 Carburetor Temperature Probe The carburetor temperature probe is mounted in the carburetor such that it senses the air temperature in the venturi See the sheet that accompanies this probe for further details about its mounting 5 2 11 EGT CHT Extension Wire All models of the EIS correct the EGT and CHT inputs the thermocouple inputs for the ambient temperature...

Страница 116: ...ument with the screws included with the back shell 6 Check Out 6 1 Initial Application of Power to the Instrument Apply power to the system Verify that the LCD display becomes active The instrument will be on display page 0 If this operation is not observed immediately turn off power to the EIS and recheck all wiring especially power ground 4 8V excitation output and 12V fuel flow power output At ...

Страница 117: ... an inaccurate tachometer could result in less than full power being available and this could be very dangerous 6 3 Other Checks CAUTION Verify that no leaks are observed around the coolant temperature sensor if so equipped as well as the oil pressure and temperature sensors Loss of engine oil or coolant will severely damage your engine and will result in sudden stoppage The remainder of the funct...

Страница 118: ...on Use 3 character labels for auxiliary inputs configured as integer since the combination screen will allocate 3 spaces on the screen for auxiliary inputs configured as integers Auxiliary inputs configured as decimal numbers will be allocated 4 spaces making it practical to use 3 or 4 character labels 7 1 2 Dual TIT Option and Aux5 Aux6 Instruments that have the dual TIT option can be identified ...

Страница 119: ...put will be sensed forward increasing voltage increasing value or reverse increasing voltage decreasing value The sheet included with the auxiliary input sensor will tell you if forward or reverse is required In most cases forward sensing is used This page displays all 6 forward reverse selections on one page Use the left and center buttons to select the combination that fits your needs The signs ...

Страница 120: ... limits entered for all temperature data are not changed by this option Be sure to enter temperature limits in same units as you have chosen for display 7 3 FC1 FC2 Fuel Flow Activation Codes For instruments that include the fuel flow option these entries have no use For instruments originally ordered without the fuel flow option these codes are used to activate the fuel flow function without the ...

Страница 121: ... sensed If tachometer input 1 is not providing any RPM indication the EIS will use tachometer input 2 Each tachometer input has a corresponding TachP R setting allowing them to be independently configured This allows the use of two dissimilar tachometer inputs such as a magneto and an electronic ignition input The settings are identified as Tach1P R and Tach2P R corresponding to each of the inputs...

Страница 122: ...ly 1 2 as many pulses will be generated as there are poles in the lighting coil For 3 phase electrical systems 1 3 as many pulses as there are poles in the lighting coil For CDI equipped Rotax Engines 12 magnets are used generating 6 pulses per revolution of the engine For non CDI type Rotax engines 2 pulses per revolution is generated Jabiru 4 cylinder engines generate 5 pulses revolution and Jab...

Страница 123: ...chometer is above the TIM RPM entry It will reset to zero after 6553 5 hours 7 11 Tim RPM Hourmeter Flight Timer RPM Threshold This entry controls the RPM that will activate the Hourmeter and Flight Timer While the engine RPM displayed by the EIS is less than the entry on this page the hourmeter and flight timer will not advance Setting this entry slightly above the power setting used for taxi wil...

Страница 124: ...e of this function may best illustrate how to us it I have found from experience that based on my flying habits my RPM does not go below 1900 until I am in beginning my descent in the pattern for landing I have also noted that while in the pattern even when making large power changes my RPM does not go above 2400 although it always goes above 2400 during takeoff I set my TachLo entry to 1900 and m...

Страница 125: ...est set to the airplane Be sure the pitot connection is secure as damage to the airspeed pressure sensor could occur if the pitot connection from the air data test set becomes disconnected during this calibration 3 Set the air data test set altitude to an altitude near the airplane s ceiling Use the AltSF adjustment to correct the displayed altitude so that it matches the altitude selected on the ...

Страница 126: ...t settings for these pages 7 15 2 Table of User Definable Page Entries Data to be Displayed Name used to select this data on the Configuration Set Page Number Of Spaces Required Notes Nothing displayed Off 0 This entry is skipped and nothing is printed to the screen Set unused entries to Off EGT1 EG1 4 EGT2 EG2 4 EGT3 EG3 4 EGT4 EG4 4 EGT5 EG5 4 EGT6 EG6 4 CHT1 CH1 3 CHT2 CH2 3 CHT3 CH3 3 CHT4 CH4...

Страница 127: ...d seconds Flight Timer Minutes Mn 2 Flight Timer Seconds Sc 2 Fuel Flow Function s Endurance Hours EH 2 Use a to separate hours and minutes Fuel Flow Function s Endurance Minutes EM 2 Cylinder number with highest CHT C 1 This is not the temperature but which cylinder has the hottest CHT such as cylinder 2 Cylinder number with highest EGT E 1 Cylinder number with highest EGT Outside Air Temperature...

Страница 128: ...mbering 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 ...

Страница 129: ...e altitude and airspeed are displayed as shown Oil Temperature Oil Pressure Tachometer 1 2 2 5 3 0 4 0 5 6 7 8 9 10 11 1 12 8 13 0 14 15 4 16 5 17 1 18 0 19 5 20 0 21 0 22 23 24 25 26 27 28 29 30 1 31 2 32 5 Altitude Airspeed 2 Once satisfied with the layout create a list of the entries Use the table above to determine the identifier used by the instrument for each of the items Fill out the list 1...

Страница 130: ...ch 1D7 VS 1P1 1 1P7 24 1D2 OT 1D8 CHH 1P2 6 1P8 30 1D3 1D9 off 1P3 9 1P9 0 1D4 EGH 1D10 off 1P4 13 1P10 0 1D5 Alt 1D11 off 1P5 17 1P11 0 1D6 1D12 off 1P6 23 1P12 0 1 T 2 A 3 C 4 H 5 6 V 7 O 8 L 9 T 10 11 E 12 G 13 H 14 15 16 E 17 O 18 T 19 20 21 O 22 P 23 24 25 26 27 28 C 29 H 30 H 31 32 C Combo Page 2 2D1 Tach 2D7 2P1 1 2P7 20 2D2 Volt 2D8 OP 2P2 6 2P8 21 2D3 EGH 2D9 CHH 2P3 11 2P9 28 2D4 2D10 2P...

Страница 131: ...0 H 21 22 O 23 T 24 25 26 O 27 P 28 29 V 30 O 31 L 32 T 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 GD1 Hr GP1 12 GD2 GP2 14 GD3 Mn GP3 15 GD4 Tach GP4 17 GD5 OT GP5 22 GD6 GP6 25 GD7 OP GP7 26 GD8 Volt GP8 29 GD9 off GP9 0 ...

Страница 132: ...is function was sensitive enough to detect a single spark plug just beginning to foul or a valve intermittently sticking or a minute intake manifold leak or a host of any other problems which could not possibly be detected by the human senses Imagine the confidence you will feel as you set out over forests mountains or a body of water knowing that your engine has been subject to this scrutiny This...

Страница 133: ...ts highest EGT the cylinder s EGT is displayed b When a cylinder s EGT is more than the amount specified on the PEAK setting below the highest EGT a negative value will be displayed showing how far this cylinder s EGT is below its highest c The highest EGT for a cylinder is continually updated That is whenever an EGT goes above the internally stored value for the highest EGT it is updated D Select...

Страница 134: ...rst Cylinder to Peak FRST2PK This function indicates which cylinder peaked first during leaning This function will display 0 after selecting RESET from the SAVE LEAN POINT page It will remain as 0 until a cylinder has peaked fallen by more than the PEAK setting from its highest EGT Once the first cylinder has peaked this function will show which cylinder was the first to peak It will not change un...

Страница 135: ...ose using water cooled engines It may also be useful for measuring other temperatures in the range of 80 300 degrees F such as under cowl temperatures especially for composite airplanes 11 Use with Precision Airmotive Eagle Engine Controller The EIS is compatible with the Precision Airmotive Eagle engine controller The following notes apply for installations with this system Fuel Flow No flow sens...

Страница 136: ...starter or if it is turned on before the engine is started in airplanes without batteries or when power or ground connections are loose 14 Troubleshooting Common Problems Instrument does not turn on Warning light is on steady Either the instrument is not receiving power or the 12V or 4 8V output from the instrument is shorted to ground A simple test is to make a cable with only power and ground wi...

Страница 137: ... date of purchase This warranty includes parts and labor The instrument includes a lifetime warranty for any manufacturing defects Grand Rapids Technologies expressly reserves the right to repair or replace a defective unit with new or reconditioned parts or equipment of the same or similar design This warranty is void if damage to the instrument is caused by incorrect connection of the tachometer...

Страница 138: ...Page 137 Appendix C EIS 4000 912 914 ...

Страница 139: ...Page 138 Appendix C EIS 4000 912 914 ...

Страница 140: ...Page 139 Appendix C EIS 4000 912 914 ...

Страница 141: ...Page 140 Appendix C EIS 4000 912 914 End Appendix C ...

Страница 142: ...ing it down using a clean rag with some MIL H 5606 on it This will help to increase the life of the strut 4 Servicing landing gear wheel bearings such as cleaning and greasing Cleaning and greasing wheel bearings is an art There are several very important steps to follow when servicing the wheel bearings Cleaning This must be done thoroughly using a cleaner such as Varsol Inspection Now that the b...

Страница 143: ...g tail group surfaces excluding balanced control surfaces fairings cowlings landing gear cabin or cockpit interior when removal or disassembly of any primary structure or operating system is not required Refinishing decorative coating At first glance this sounds like a simple task but it becomes complicated very fast You should start by checking the service manual for recommended procedures and ma...

Страница 144: ...des a torque wrench Use the proper spark plugs for the engine Know the plug rotation sequence for the engine Many people use a simple process of rotating the plugs from top to bottom and then next in firing order 21 Replacing any hose connection except hydraulic connections Owners are allowed to replace any hose or hose connection except hydraulic connections which also includes broken lines You a...

Страница 145: ...facturer when installing anti misfueling devices on your airplane 29 Removing checking and replacing magnetic chip detectors Comply with the engine and airframe manufacturers recommendations when removing checking and replacing the magnetic chip detector 30 The inspection and maintenance tasks prescribed and specifically identified as preventive maintenance in a primary category aircraft type cert...

Страница 146: ...rt 43 Appendix A paragraph c contains the list of those functions determined by the FAA to meet this definition If a function does not appear in this list it is not preventive maintenance Further because of differences in aircraft a function may be preventive maintenance on one aircraft and not on another To provide for this paragraph c contains the limitation provided it does not involve complex ...

Страница 147: ...vely The certificate number is that number displayed on the certificate being exercised Affixing a signature to the entry which describes the work accomplished constitutes approval for return to service as required by Section 43 9 a 4 NOTE Since owners pilots are not authorized to approve work accomplished by others Section 43 9 a 3 is not applicable when preventive maintenance is performed by the...

Страница 148: ... a quality that the condition of the aircraft airframe aircraft engine propeller or appliance worked on will be at least equal to its original or properly altered condition with regard to aerodynamic function structural strength resistance to vibration and deterioration and other qualities affecting airworthiness c Special provisions for holders of air carrier operating certificates and operating ...

Страница 149: ...or glue residue from brass leading edges Install propeller blades into their positions between the hub halves Use caution to not drop or hit blade tips on the ground or hard surface The tips are the most fragile area of the prop NOTE There is a tiny hole in the tip that must remain open to expel any moisture or condensation trapped inside the blade If it is clogged open by pushing in a straight pi...

Страница 150: ...ill be necessary SECURING ASSEMBLED PROP TO ENGINE 5 Secure finger tight the propeller to the engine with the supplied 8 8 X 1 25mm bolts washers and nuts NOTE The supplied bolts are grade 8 8 metric and the nuts are metric Nyloc Some clients prefer using AN5 bolts and metal jam nuts or castellated nuts These are available from Aircraft Spruce Specialty Co or from us at an additional cost 6 With a...

Страница 151: ...or the other blades 10 When all blade angles have been set and using a calibrated torque wrench tighten the Nyloc nuts sequentially with 5 ft lb increments to 14 5 foot lb This will help to insure proper tracking Check the pitch of all blades again and once satisfied begin torquing the center mounting hardware sequentially opposing and with 5 ft lb increments to 14 5 lb A 13mm crows foot on the en...

Страница 152: ...n Never over torque or STRETCH prop bolts The standard prop bolt for this propeller is a Grade 8 8 X 1 25 metric and will fit the Rotax 75mm bolt pattern AN 5 prop bolts will fit the ROTAX 912 application use the same torque value NEVER OVER TORQUE or exceed established recommended usage of prop bolts Check for wear and deterioration of prop attachment hardware during maintenance and Annual Condit...

Страница 153: ...e 152 Appendix E1 Page 5 End of Appendix E1 MOUNTING BOLTS UNDRILLED SHANK AN5 36A THICK WASHERS AN960 516 JAM NUT MS21045 5 MOUNTING BOLTS DRILLED SHANK AN5 36 THICK WASHERS AN960 516 CASTLE NUTS AN310 5 ...

Страница 154: ...Page 153 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 ...

Страница 155: ...Page 154 Appendix E2 Powerfin Prop Page 2 ...

Страница 156: ...Page 155 Appendix E2 Powerfin Prop Page 3 ...

Страница 157: ...Page 156 Appendix E2 Powerfin Prop Page 4 ...

Страница 158: ...Page 157 Appendix E2 Powerfin Prop Page 5 ...

Страница 159: ...Page 158 Appendix E2 Powerfin Prop Page 6 ...

Страница 160: ...Page 159 Appendix E2 Powerfin Prop Page 7 ...

Страница 161: ...Page 160 Appendix E2 Powerfin Prop Page 8 ...

Страница 162: ...Page 161 Appendix E2 Powerfin Prop Page 9 ...

Страница 163: ...Page 162 Appendix E2 Powerfin Prop Page 10 ...

Страница 164: ...Page 163 Appendix E2 Powerfin Prop Page 11 End of Appendix E2 ...

Страница 165: ...ased equipment It is extremely reliable equipment designed to meet TSO C126 and TSO C91A requirements batteries operated and self contained The ELT Emergency Locator Transmitter is designed only for emergency use The model AK 451 may be used as one or more of the following ELT types Automatic Fixed ELT AF The ELT AF is designed to be permanently attached to the aircraft before and after a crash Au...

Страница 166: ...stallation of an ELT in an aeronautical product is carried out under a Supplemental Type Certificate STC This is a separate regulatory requirement and should therefore refer to Ameri King Document No ICA 451 for the Operations and Instructions for Continued Airworthiness ICA The conditions and tests required for TSO approval of this article are minimum performance standards It is the responsibilit...

Страница 167: ...r 406 028 MHz 3K20A3X for 121 5 MHz BATTERY REQUIREMENTS Transmitter Main Unit Battery Pack consists of 4 cells LiMnO2 or LiSO2 AK 450 has 6 cells D Size DURACELL AUTOMATIC CRASH ACTIVATION Velocity Change of 2 3 0 3 G 4 5 0 5 FPS per TSO C 126 DO 204A and ETSO 2C126 EUROCAE ED 62 requirement ANTENNA RADIATION CHARACTERISTICS Radiation on 121 5 243 0 MHz and 406 028 MHz Vertically polarized Omni d...

Страница 168: ...Page 167 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 ...

Страница 169: ...r Coaxial Cable Assembly and Wiring Cable Assembly Because of the critical nature of an ELT it is very important that the installation be performed according to the following instructions Installation of the ELT is somewhat unique as is the installation of any TSO C126 and TSO C91a ELT it requires experience in sheet metal work and avionics Only licensed technicians should install the ELT Many pro...

Страница 170: ... 5 MHz VHF radio No LED light illuminates No buzzer sound Detail Operation Check 1 Monitor 121 5 MHz using the Aircraft Communication Receiver or a Portable Hand Held Receiver Important The Squelch must be turned all the way UP Max to hear he sweep tone on most receivers 2 Place the Main Switch on the front of the ELT Main Unit in the ON position and verify that the Audio Sweep Tone can be heard o...

Страница 171: ...ored in Memory at fault 3 flashes Battery voltage is low Useful Life Battery Voltage setting 4 flashes Vcc supplies for F3 F2 or F1 at fault 5 flashes F3 RF power level 33 dBm 406 028 MHz 7 flashes F1 F2 VHF RF power level 17 dBm 121 5 243 MHz 9 flashes PLL locked in F3 or F1 or F2 at fault Continuous flash no F3 F2 F1 RF output power ELT shuts down completely Note The self test mode that transmit...

Страница 172: ...d and the 2 Green ON lights shall illuminate for 4 seconds then extinguish This is to allow coding programming during the next 20 seconds window and self test for 1 second thereafter Note The ELT may be ID coding programming during the aforementioned 20 seconds window period If no programming happened the ELT will then enter the Self Test Mode for 1 second thereafter Self Test takes 25 sec Self te...

Страница 173: ...t 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 If you are at a location where there is an FAA Control Tower or other monitoring facility notify the facility before beginning the tests Never activate the ELT while airborne for any reason See Figure 18 for the ELT Fron...

Страница 174: ...e If the ELT is not accessible in flight you should land at the nearest suitable airport and set the Main Switch to the OFF position In either case the unit should be inspected by qualified facility as soon as possible The Aircraft may be operated with the ELT removed for inspection or repair subject to the conditions of FAR 91 207 In the event of an accident Push the ON button on the Cockpit Remo...

Страница 175: ... system is fully self tested 5 2 Transmitter Self Test Turn and hold the main switch from the OFF position to the SELF TEST position The Green ON light shall illuminate for 4 seconds then extinguish This is to allow coding programming during next 20 seconds window and self test for 1 second thereafter The ELT S may be coding programming during the aforementioned 20 seconds window period If no prog...

Страница 176: ...must be selected at ARM position at all times Activate the ELT using applied force The direction for mounting and force activation is indicated on the ELT The AK 451 AF AP ELT can be activated by using a rapid forward throwing motion coupled by a rapid reversing action Verify that the ELT has been activated by use of the Wattmeter the Airplane s VHF Radio Communications Receiver when tuned to 121 ...

Страница 177: ...Ameri King dealer for availability of the Computer Test Set or call Ameri King Follow instructions provided with the computer test set The AMERI KING AK 451 has a self test feature which is encoded such that it will be ignored by the SAR satellite system This 15 digit number is used to register the ELT with the appropriate 406 MHz ELT registration authority In the US the National Oceanic and Atmos...

Страница 178: ... Equipment PPE is required when working on the system components CAUTION Denote items pertaining to safety that may be easily overlooked and may need double checking NOTE Items of particular interest or must be Inspected during routine maintenance and inspection 1 3 Description of Bailey Release and Tow System The Bailey Tow and Release System has a release similar to the Schweizer Release but als...

Страница 179: ...Page 178 B Quick Release and Safety Link Quick Change Pin and Retainer showing configuration of Safety Link C Slider Ring or Karabiner ...

Страница 180: ...abiner 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 Refer to Pilot Operating Handbook for complete Towing Operation and Limitations ...

Страница 181: ...ty Link of 130 lb Solo or 200 lb Tandem attached by passing it through itself and attaching to Glider Release This provides 2 strands of Safety Link carrying the loads 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 with...

Страница 182: ...Manual 2 3 Loads Maximum gross vehicle weight to be towed 562 lbs 255 Kg Loads are limited by proper installation and used of Safety Links commonly referred to as Weak Links Safety Links are made from 130 lb or 200 lb Braided Dacron Fishing Line depending upon placement and loads The Single Loop is used to fasten the Towline to the Glider being towed Point E in Figure 1 Solo Glider TUF LINE BRAIDE...

Страница 183: ...be in the Cockpit and view of the Tow Pilot Glider towline assembly Safety Link breaking strength not to exceed 130 lbs and tied in the manner specified in the manuals and Banner towing is excluded by the Light Sport Rule AC 43 13 2B 807 NOTE Placard in Cockpit to indicate Release operation Emergency Release Squeeze Lever to Release Towline 2 4 Angles Angles tested in accordance with AC 43 13 2B 8...

Страница 184: ...fic TBO However every Annual or 100 Hour Inspection requires a thorough inspection to insure there are no problems with wear or operation of the Release and all components in the Tow Release and System There are Releases in operation that are more the 20 years old and are still in good working condition Some older units had a zinc plated steel spring that eventually corrodes But the newer Stainles...

Страница 185: ...e Cable Housing for cracks which would indicate deterioration of the cable housing 3 Insure that the Release Handle Pressure measured at the top of the handle does not exceed 8 lbs 4 Insure that the cable moves freely through the cable housing and returns to the normal position by release spring pressure only 5 Insure that the release L link has not developed a wear notch This notch can be smoothe...

Страница 186: ...t zero plasticity allowing all forces to get to the Safety Links rapidly NOTE Because of the durable size of the line it is important to insure Safety Links are properly installed CAUTION Loads are limited by proper installation and used of Safety Links commonly referred to as Weak Links Refer to FIGURE 2 for proper tying and configuration The Single Loop is used to fasten the Towline to the Glide...

Страница 187: ...Page 186 By Memphis Soaring FIGURE 3 Common Signals ...

Страница 188: ...Page 187 FIGURE 4 Common Arm and Hand Signals By Evergreen Soaring FIGURE 5 Common Aircraft Signals By Evergreen Soaring ...

Страница 189: ... as possible NOTE Experimental Dragonfly Aircraft that transitioned from Ultralights may take advantage of the Tow System Authorization or Waiver by maintaining their Aircraft and Tow System in accordance with the Maintenance and Service Instructions contained in the Dragonfly Maintenance Manual and Pilot Operating Handbook POH posted on the web at www pitmanair com dragonfly Any Changes Alteratio...

Страница 190: ...Name Address City ST Zip Code Day Phone FAX email address Check Appropriate Owner Operator LSRI LSRM A P Other Explain Aircraft Specific Information Aircraft Information Engine Information Make Make Model Model Serial Number Serial Number N Number Gearbox Ratio Date of Mfg Propeller Mfg Propeller Serial Date of Problem Discovery dd mm yyyy Description Comments Signature____________________________...

Страница 191: ...City ST Zip Code Day Phone FAX email address Check Appropriate Owner Operator LSRI LSRM A P Other Explain Aircraft Specific Information Aircraft Information Engine Information Make Make Model Model Serial Number Serial Number N Number Gearbox Ratio Date of Mfg Propeller Mfg Propeller Serial Date of Problem Discovery dd mm yyyy Description Comments Signature_________________________________________...

Отзывы:

Нет отзывов

Похожие инструкции для 912 Dragonfly

Бренд: SKY PARAGLIDERS Страницы: 36

Бренд: MAC PARA Страницы: 32

Бренд: SKY PARAGLIDERS Страницы: 62

Vector Canard Sport Citrus

Бренд: Premier Kites Страницы: 17

Бренд: Maxford USA Страницы: 13

Бренды по названию

0 1 2 3 4 5 6 7 8 9 A B C D E F G H I J K L M N O P Q R S T U V W X Y Z

Популярные бренды

Загрузить еще бренды