Home

P92 Eaglet LSA maintenance manual

Contents

1. 12 2 6 1 List of Disposable Replacement PartS nnne rediera aa E EEan sene risas assess seran ana 12 2 6 2 Standard NN 13 Inspection and Servicing i sic cscisccdscciecccedcisccesccdeccesdcdaccessciescecdciedcesssrssessuvasssrsivasserssvissssasvassevssvassdassvassersevseverssvasseseess 14 3 1 Ground Handling T 14 3 2 Parking and o ur EE 14 3 3 ll 14 3 4 LOVOUIN A 15 3 4 1 Control surface settings iieri iter ru aka E eri cia MR EEC adan de Ve eva eu E AS 15 3 4 2 Trimstab adjUsttment rra eodeni rena eve iaa EN DES EX YX REDE TT EXE UT EY FEY EYE ENR RV Tue ex 15 3 4 3 Aircraft alignment NO 16 3 4 4 Br pn M ia 16 3 5 Jv M Pia 17 3 6 Determination Of acm kj ARA 17 3 6 1 ME ia PRE dra a ar aranan 18 3 7 Corrosion PFOVENEION liana iaia 19 3 8 Service DINO CHIVES P 19 3 9 SOIVICIO E 20 Revision Date 12 14 2007 Revision Number 1 01 Doc N 27 13 200 00 gr r COSTRUZIONI AERONAUTICHE P92 Eaglet E er TECNAM Line Maintenance Manual 3 9 1 BET AEE O 20 3 9
2. 2 P92 Eaglet m COSTRUZIONI AERONAUTICHE KELET TECNAM Line Maintenance Manual LINE MAINTENANCE MANUAL US LSA P92 Eaglet Manufacturer COSTRUZIONI AERONAUTICHE TECNAM S r l Type Certificate ASTM SLSA Serial number Build year Registration This manual contains information to be furnished to the pilot as required by the FAA in addition to further information supplied by the manufacturer The aircraft is to be operated and maintained in compliance with information and limitations contained herein All sections follow the ASTM guidelines as finalized 14 December 2007 1 Revision Date 12 14 2007 Revision Number 1 01 Doc N 27 13 200 00 P92 Eaglet 232 COSTRUZIONI AERONAUTICHE EABLET TECNAM Line Maintenance Manual Record of Revisions Any revisions to the present Manual except actual weighing data must be recorded in the following table New or amended text in the revised pages will be indicated by a black vertical line in the left hand margin Revision No and date will be shown on the left hand side of the amended page Log of Revisions Approved By 12 14 2007 02 02 2009 2 3 5 27 Revision n 1 2 February 2009 2 Revision Date 12 14 2007 Revision Number 1 01 Doc N 27 13 200 00 P92 Eaglet 232 COSTRUZIONI AERONAUTICHE EABLET TECNAM Line Maintenance Manual List of Valid Pages 12 14 2007 12 14 2007 56 12 142007 12 14 2007 ps
3. COSTRUZIONI AERONAUTICHE P92 Eaglet TECNAM Line Maintenance Manual _ Felt Figure 4 17 Removal of cup bearing 4 9 Nose gear The nose gear fig 4 18 is attached to the engine mount with two hinges 1 and is equipped with a Sava 4 00 6 type tire Steering motion is transmitted from the pedals through two steering tubes that are attached to the nose gear strut by means of two brackets 2 welded to the strut Gear fork is made up of light alloy plates 4 amp 5 and a spacer 6 it hinges on the strut leg and is braced by a rubber disc shock absorber 3 Figure 4 18 Nose gear assembly 42 Revision Date 12 14 2007 Revision Number 1 01 Doc N 27 13 200 00 COSTRUZIONI AERONAUTICHE P92 Eaglet Lr TECNAM Line Maintenance Manual 4 10 Removal of nose gear fairing and wheel To remove the nose gear fairings proceed as follows e To remove front portions of fairing 5 amp 6 loosen the screws 2 and 3 Remove the two fairings 6 and 5 To remove the rear upper fairing 4 loosen the screws 1 Unscrew nuts 7 and remove washer from wheel axle Unscrew bolt 8 in gear lever housing e Remove the rear fairing 9 Reverse procedure to reinstall Avoid damage to fiberglass fairing by not tightening screws excessively 4 11 To remove nose wheel proceed as follows Remove the fairings 5 6 and 9 Loosen bolts 10 11 and 13 Detach the two wheel forks 12 from each other
4. In case of failure of one or more utility load is automatically interrupted by circuit protection Proceed as follows e Exclude all loads relative to burnt breakers e Closecircuit by substituting the burnt breakers e Restore one by one all loads relative to the burnt breakers until circuit protection shuts down again NOTE This new interruption will indicate faulty utility 58 Revision Date 12 14 2007 Revision Number 1 01 Doc N 27 13 200 00 e P92 Eaglet 232 COSTRUZIONI AERONAUTICHE EABLET TECNAM Line Maintenance Manual SECTION 8 MARKING amp PLACARDS 8 Markings and Placards 8 1 Magnetic compass compensation table To compensate the deviation errors of the magnetic compass the following correction table is located just below the compass For IN 30 160 E 120 150 Steer Steer DATE RADIO ON AIRPATH 8 2 Engine throttle Two throttle control knobs are located on the instrument panel One positioned centrally while the other is on the upper left hand side The following placard 7x20mm is located near each one of them THROTTLE 8 3 Engine throttle friction A throttle friction lock is located on the instrument panel to keep the desired throttle setting The following placard 23x11 upper 21x11 lower is positioned near the friction lock knob 8 4 Cabin heat The cabin heat control knob is l
5. 38 Revision Date 12 14 2007 Revision Number 1 01 Doc N 27 13 200 00 COSTRUZIONI AERONAUTICHE P92 Eaglet er TECNAM Line Maintenance Manual Figure 4 13 Brake circuit To remove the leaf spring struts proceed as follows Remove cabin seats by sliding them forward Hoist aircraft onto supports Disconnect brake fluid line unscrewing the upper link of the external line tract near fuselage bottom Place temporary caps on lines to prevent spillage Loosen bolts part 5 fig 4 12 of the aluminum clamp part 4 fig 4 12 that secure spring leaf to edge of main girder Remove bolt connection between inboard end of spring leaf part 6 fig 4 12 and main girder Remove gear strut by pulling outward from fuselage Reinstall using reverse procedure It is however necessary to eliminate any trapped air once the circuit is closed and fluid in reservoir is at normal level bleed air through dedicated valve For best results use external pump to push fluid through valves allowing trapped air to escape through open reservoir If braking action appears degraded check and eventually replace main gear brake pads Refer to Periodic Inspection Chart in Section B for any service operation to main gear 39 Revision Date 12 14 2007 Revision Number 1 01 Doc N 27 13 200 00 COSTRUZIONI AERONAUTICHE P92 Ea let TECNAM 9 bo Line Maintenance Manual 4 8 1 Main Gear Removal of main gear wheel see fig 4
6. TECNAM Line Maintenance Manual PROPELLER SPACER WITH BUSH COVER DISK ENGINE PROP FLANGE WASHER SPINNER BULKHEAD Figure 5 3 Propeller installation 5 3 6 Periodic inspection Refer to specific subsection in Periodic Inspection Schedule of Section 3 For further information refer to the Owner s Manual and to all the pertinent documents issued by GT 48 Revision Date 12 14 2007 Revision Number 1 01 Doc N 27 13 200 00 P92 Eaglet m COSTRUZIONI AERONAUTICHE EABLET TECNAM Line Maintenance Manual SECTION 6 SYSTEMS 6 Systems 6 1 Fuel System The system is equipped with two aluminum fuel tanks 1 integrated within the wing leading edge and accessible for inspection through dedicated covers 6 Capacity of individual tank is 45 liters 11 8 gal and total usable fuel is 86 8 liters 22 9 gal total On the upper external are fuel caps 2 bay 3 for float 4 chamber and fuel tank bleed 5 Metal cover plate 6 may be removed for inspection of tank interior that assembly riveted and puttied with dope gasoline resistant Return line discharged flange 7 of fuel system on the left fuel tank rear wall placed Diaphragm mechanical pump 13 engine connected stoking provide by means flexible pipelines come to the fuel tank and across cabin vertical rods easily accessible after disassembled plastic structural On the same cabin vertical rods are circuit on off valve 9 one for each fuel
7. xd 3 11 Inspection 3 11 1 INTRODUCTION TECNAM considers the inspection schedule outlined below compulsory for the safe operation of the airframe and of the systems over an extended period of time Described servicing requirements pertain to operation in non extreme climatic conditions For the Rotax 912 ULS S engine unless otherwise stated in the present manual it is compulsory to adhere to maintenance requirements as reported in the Engine s Operator s Manual p n 899 370 For the GT propeller refer to manufacturer s maintenance manual Airframe and systems inspection schedule is as follows e Inspections for airworthiness before first flight of day as specified in Flight Manual e Periodic inspections at 100 hours e Special inspections added to normal periodic inspections e Singular inspection when aircraft has been exposed to conditions that may have damaged one or more of its components e If aircraft is rarely used a 100 hour inspection must be performed yearly e Replacement of parts subject to usage limitations are specified in par 3 14 Inspections and checks unless specifically indicated apply to the following e Structures in general Condition of panel covers ribs frames stringers etc absence of cracks deformation rivet slackening corrosion and any other apparent sign of damage e Moving parts Lubrication security of attachment safetying of bolts absence of excessive play proper adjustment proper tra
8. 49 Revision Date 12 14 2007 Revision Number 1 01 Doc N 27 13 200 00 COSTRUZIONI AERONAUTICHE P92 Eaglet XE er TECNAM Line Maintenance Manual Figure 6 2 Gascolator 50 Revision Date 12 14 2007 Revision Number 1 01 Doc N 27 13 200 00 COSTRUZIONI AERONAUTICHE TECNAM 6 2 Instrumentation P92 Eaglet Line Maintenance Manual VT HF RADIO Hours c RH Fue LH Fue BANK INDICATUR IGNITION A MASTER SWITCH AVIONIC MASTER GENERATOR Gyro compassTHROTTLE FR Land ligh BREAKERS n Clock Fuel pressure PARKING BRAKE Figure 6 5 Instrument panel typical The aluminum instrument panel see Fig 6 5 is sub divided in three distinct areas The left area holds flight instruments The right area holds engine gauges The central area can hold Nav Com instruments if installed The lower portion of the instrument panel holds e Master switch Landing and Strobe light Flap switch Ci
9. Serial Number Date of Inspection Total Time Airframe Engine Description of the un airworthy items found Owner of Aircraft Or write to Tecnam Aircraft 1350 Churchill Way Marietta GA 30062 2 6 Source to Purchase Parts Spare parts can be ordered from Tecnam Aircraft Inc at www tecnamaircraft com Tecnam www tecnam com or from your local dealer 2 6 1 List of Disposable Replacement Parts Air filten tet Rotax PN 825551 Fuel filter Facet filter Aircraft Spruce PN 479729 AAA Rotax PN 924420 Nose wheel tire Sava 4 00 6 type tire and tube or may be replaced with a similar size aircraft tire or tube Main gear tire Air Trac 5 00 5 type tire and tube or may be replaced with a similar size aircraft tire or tube Ollio See Rotax manual Coolant See Rotax manual 12 Revision Date 12 14 2007 Revision Number 1 01 Doc N 27 13 200 00 COSTRUZIONI AERONAUTICHE P92 Eaglet Ber S TECNAM Line Maintenance Manual 2 6 2 Standard Equipment Flight Instruments Airspeed Indicator Altimeter Vertical Speed Indicator Compass Engine instruments Tachometer Oil Pressure Fuel Pressure Oil Temperature Cylinder Head Temperature Hour Meter Left and Right Fuel Quantity Volt Meter Warning Lights and Indicators Trim Indicator Flap Indicator Generator Warning Light Controls Dual Stick Flight Controls Rudder Pe
10. Using the center valve 7 hot air from heat exchanger may be deviated towards carburetors A round knob located to center left of instrument panel controls this valve The heating system does not require particular servicing except for periodic check of heat exchanger and of intercept valve whose faulty closure may cause unwanted heat to enter cabin Figure 6 9 Carburetor heat and cabin heat systems 55 Revision Date 12 14 2007 Revision Number 1 01 Doc N 27 13 200 00 Z3 COSTRUZIONI AERONAUTICHE P92 Eaglet A er TECNAM Line Maintenance Manual 6 5 Brake System The reservoir 4 is directly connected to the brake master cylinders 3 as shown in the figure 6 10 Two flexible hoses connect the master cylinders on the co pilot s brake pedals to the master cylinders on the pilot s brake pedals The parking brake valve 6 is mounted on the floor of the fuselage below the seats and it s activated by lever 2 Figure 6 10 Brake System 6 5 1 Draining and replacing brake fluid To replace the brake fluid Service one side first then other A Remove reservoir cap B Unscrew line nipple 6 from disk caliper C Using a manually operated pump add brake fluid MIL 5606 until level reaches bottom of reservoir reattach line to caliper avoiding fluid spill Repeat operations A B C for other side Top fluid level to 3 4 and close cap To drain the brake system D Pull brake lever 5 to pressurize circuit E
11. wood composite 2 3 3 Fuel Fuel grade Min RON 95 Auto Fuel AKI 91 Premium USA AVGAS 100LL Fuel tanks 2 integrated wing tanks Capacity of each wing tank 45 liters 11 9 gal Total capacity 90 liters 23 8 gal Total usable fuel 86 8 liters 22 9 gal 2 3 4 Oil System Oil system Forced with external oil reservoir Oil See Rotax operator s manual Oil Capacity Max 3 0 liters 3 2 qt min 2 0 liters 2 1 qt 2 3 5 Cooling Cooling system Mixed air and liquid pressurized closed circuit system Coolant See Rotax operator s manual Doc N 27 13 200 00 11 Revision Date 12 14 2007 Revision Number 1 01 e P92 Eaglet 232 COSTRUZIONI AERONAUTICHE EABLET TECNAM Line Maintenance Manual 2 4 Weights 2 41 Maximum Weights Maximum take off weight 600 kg 1320 Ibs Maximum landing weight 600 kg 1320 Ibs Maximum baggage weight 20kg 44 lbs 2 4 2 Standard Weights Empty weight 325 kg 715 Ib Maximum payload weight 275 kg 605 Ib 2 4 8 Specific Loadings Wing Loading 50 kg m 10 23 Ib fC Power Loading 6 1 kg hp 13 5 Ib hp NOTE Standard weights are estimates based on standard equipment 2 5 Instructions for Reporting Possible Safety of Flight Concerns Email to Tecnam G bellsouth net the following information e Aircraft Make Model Serial Number Engine Make Model
12. 16a and 17 Removal of a single wheel is carried out as follows e Hoist aircraft onto supports e Release parking brake e Remove fairing 1 by releasing bolt 2 and the three Phillips screws 3 that hold fairing to plate e Remove bolt 4 and cup 5 e Remove wheel lock nut 6 e Unscrew 4 brake disc assembly bolts See Figure 4 14 and Figure 4 15 8 e Carefully remove wheel assembly with both hands Disc bolts Figure 4 14 Figure 4 15 Removal of main gear wheel Main Gear 4 8 2 Removal of cup bearing from main gear wheel 40 Revision Date 12 14 2007 Revision Number 1 01 Doc N 27 13 200 00 COSTRUZIONI AERONAUTICHE P92 Eaglet A er TECNAM Line Maintenance Manual Figure 4 16 Marc Ingegno Wheel Assembly Removal of cup bearing from main gear wheel see fig 4 17 Removal of a wheel bearing becomes necessary when excessive friction occurs during wheel motion Procedure is as follows e Using an appropriate tool remove Seeger type snap ring e Remove the two ring grease seals and the felt grease seal e Remove the cup bearing e Clean the bearings accurately using appropriate solvent and wipe wheel rim side Grease using FIAT ZETA2 Reverse procedure to re install Insert ring grease and felt grease seals by sliding them perpendicular to hole without forcing them 41 Revision Date 12 14 2007 Revision Number 1 01 Doc N 27 13 200 00 PIZ LR er
13. 2 AS COC tati iaia 20 3 10 Lubrication every 100 hours or annuallY iii 20 31051 Lubrication Points aria 20 3 102 A O 23 3 11 Tego A ELS 23 3 11 1 INTRODUCTION 23 3 12 Condition Inspection 100 hour annual iii 24 3 124 Inspectiom RNA 24 EN ALME JTETET CR EIE 24 3 123 Ca bin and cockpit srotUip s nm R aalaiia lkakakasda X M 24 3 12 4 Engine and nacelle group 24 3 125 ILANGING BEAL SKOUP LL OoO 24 3 12 06 Wing and center section assemblY iii 24 3 12 7 ARS la a PAIR CORTINE RIT a 25 3 12 8 Propeller group imet et reine estie AAA i ii 25 EN E MEME NO 25 3 12 10 Optional equipment deesse ia ARAN FE Ere venta aaa ra 25 3 12 11 A 25 3 13 Torgue Conversion Tables manakah iL Riolo in Aa eaey iaiaaeaia S redan BM 26 3 14 LIMITATIONS TO AIRWORTHINESS iii 27 ip4eguce 28 4 1 INEFOGUCTION PR R 28 4 2 pn 28 4 2 1 Installing and reinstalling the Wing iii 29 4 3 Flap CONTO
14. 8508 inch pounds Newton meters 0 1020 kilogram meter Revision Date 12 14 2007 Revision Number 1 01 Doc N 27 13 200 00 P92 Eaglet 232 COSTRUZIONI AERONAUTICHE EABLET TECNAM Line Maintenance Manual 3 14 LIMITATIONS TO AIRWORTHINESS 1000 hr or T0 yr Shock absorber rubber discs 92 8 200 1 QTY 7 1200 hr or 10 yrs Oil system flexible hose assy TECNAM pn s 21 11 910 001 5 yrs 21 11 910 002 21 11 910 003 Fuel system flexible hose TECNAM pn s 21 11 311 1 2 yrs 21 11 311 2 21 11 340 1 21 11 324 1 21 11 330 Liquid cooling system flexible 92 11 105 1 92 11 105 2 2 yrs hose 92 11 105 3 92 11 105 4 Revision n 1 2 February 2009 27 Revision Date 12 14 2007 Revision Number 1 01 Doc N 27 13 200 00 74 COSTRUZIONI AERONAUTICHE P92 Eaglet er TECNAM Line Maintenance Manual SECTION 4 AIRFRAME 4 AIRFRAME 4 1 Introduction The airframe consists of the following main groups as shown in figure 4 1 1 Wings 2 Fuselage 3 Empennage 4 Landing gear 5 Powerplant B Figure 4 1 Main groups 4 2 Wing Each wing is connected to the fuselage by means of two pin attachments and a single strut brace per side Wings are made up of a central light alloy torsion box a light alloy leading edge is attached to the front spar 1 while flap 2 and aileron 3 are attached to rear fake spar through two hinges each The torsion box as shown in figure 4 2 and with r
15. 9 d 3 M gt P 8 D 6 El 2 Je 14 NS FT NEC L ST 6 V NX V 1 2 N Figure 4 4 Aileron control To remove aileron disconnect one end of push pull rod and remove pins from hinges Reverse above procedure to reinstall aileron insuring that with stick vertical the aileron s trailing edge is aligned with wings trailing edge Through access panels located on wing s bottom check that the bell crank lever is in neutral position i e the inside arm at right angle with spar axis To remove half wings release pins 4 that secure short bar 3 to main rods 5 The steel cable system is designed to insure proper cable tension without the need to check whenever the half wings are removed It is however recommended that periodic checks be carried out and proper tension applied by acting on the two turnbuckles 8 located behind the cabin s aft panel Also check periodically that pulleys rotate freely and tolerance for entire linkage is within standards ref Section B If control stick should feel unusually hard reduce cable tension as this may be the primary cause for malfunction also check that pulleys and other parts of the link system positioned under seats are properly greased If control stiffness persists check integrity of bell cranks and pulleys and insure that cable has not come off pulleys Alignment of moving surfaces with wing must be done using outboard trailing edge as reference Further lateral correctio
16. Loosen small escape valve 7 allowing fluid spurt F Close small valve and release brake lever Repeat operations D E and F until fluid comes out clean and no longer in spurts proving absence of air bubbles e Top off reservoir with needed amount of brake fluid 56 Revision Date 12 14 2007 Revision Number 1 01 Doc N 27 13 200 00 COSTRUZIONI AERONAUTICHE P92 Eaglet A er TECNAM Line Maintenance Manual e Close reservoir and repeat operation for other brake e Hydraulic fluid may also be replaced using gravity after disconnecting the circuit This method is however more laborious and less reliable 6 5 2 Replacing brake pads When thickness of lining is less than 2 4 mm brake pads should be replaced using the following procedure and the fig 6 11 Make sure parking brake is released Remove fairings to expedite operation Loosen bolts 2 from the caliper 1 Remove brake pads 3 Replace brake pads Reassemble Figure 6 11 Brake Assemblies 57 Revision Date 12 14 2007 Revision Number 1 01 Doc N 27 13 200 00 P92 Eaglet m COSTRUZIONI AERONAUTICHE EABLET TECNAM Line Maintenance Manual SECTION 7 ELECTRICAL SYSTEM 7 Electrical system Electrical energy is supplied by a 12 volt direct current system Energy is supplied by an engine driven generator and by a buffer battery The 18 Ah capacity battery is located in a distinct compartment on the right side of th
17. Remove wheel axle Remove the wheel 13 Figure 4 19 Removal of nose gear fairing 43 Revision Date 12 14 2007 Revision Number 1 01 Doc N 27 13 200 00 r COSTRUZIONI AERONAUTICHE P92 Eaglet TECNAM Line Maintenance Manual 4 12 Tire inflation pressure Nose tire 15 psi 1 0 bar Main tire 23 psi 1 6 bar er CHECKLIST TO CARRY OUT AFTER INSTALLATION CI rare stem toner pol ig e art Gsm s Riom sde tatwa romina 4 Front ohi side ving arechnen bok 245m s Fear ront sie in tchmentbok 265 s vppertok gni se sressny s esse ating mmm s Frontside wing ataciment bor REGNI 40 Fear ett sde wra atachimen ot 246 No vopervot etisge sm easnm 42 Ransasnapanaonmembartoanm 43 torse tap atachmen bok Goan 48 Fight de aero contol atsenmentbot GN Fis Lets leon conte atacment ok Nm 46 Riom sde soto serio busing 10 Lets sabio nerion busting 19 Letsce nemistaiorataciment bok OA Nm 20 sabio take spratachmenisceve __ Um Tabeomecionbushig SSCS 22 Tam connor ros anecon i Um Rahtaleronconuolbargreass E Um letaleronsonnolbargrease y 25 Fiori wira terine atene E Fa tng tere ateme U UE E as Fiort wing navigation toht wiring corneto 28 kot wna navigator tant wing comeston Doc N 27 13 200 00 D a a a a 44 Revision Date 12 14 2007 Revision Numb
18. improper operation por 3 12 10 Optional equipment Check all optional equipment for proper operation 3 12 11 ELT Remove and inspect the installed for proper operation of the G switch and calendar date currency of the batteries installed in accordance with FAA Advisory Circular 91 44 current revision 25 Revision Date 12 14 2007 Revision Number 1 01 Doc N 27 13 200 00 COSTRUZIONI AERONAUTICHE P92 Eaglet TECNAM Line Maintenance Manual Eker SUMMARY OF REFERENCE VALUES Torque settings for connection bolts are a function of their thread shank diameter Bolt resistance category 8 8 3 1 Nm 27 In Lb 10 4 Nm 92 In Lb 24 6 Nm 217 In Lb 50 0 Nm 442 In Lb Warning propeller attachment bolts must be fastened to 18 Nm 159 In Lb value even though they have an 8 diameter Control cable tension for both aileron and rudder Value 20 dN 2 dN 45 4 Tire pressure Nose 1 0 bar 15 PSI Main 1 6 bar 23 PSI 3 13 Torque Conversion Table Multiply By To obtain foot pounds 1 3558 Newton meters foot pounds 0 1383 kilogram meters foot pounds 12 0 inch pounds inch pounds 0 0115 kilogram meters inch pounds 0 1130 Newton meters inch pounds 0 0833 foot pounds kilogram meters 7 233 foot pounds kilogram meters 86 7964 inch pounds kilogram meters 9 8067 Newton meters Newton meters 0 7376 foot pounds Newton meters 8
19. tank easily accessible to the pilot Circuit link with union tee in correspondence of the firewall and then to drainage bowl 10 located left upper side in the engine bay visible through an upper cowling port Downstream respect to the gascolator is located a fuel filter 11 and then the mechanical pump 13 Mechanical pump feeds the fuel manifold 14 its left branch feeds the left carburetor and in derivation by a tee with restrictor the fuel pressure gauge 14 The rear branch of the X manifold 14 is connected to the fuel return line 17 In case of mechanical pump failure electrical pump feed is available Return tube 17 engage in pipe fitting 18 located on the fire wall and then by means a thin transparent tube return at the LH fuel tank Disassembled half wing is necessary disconnect return tube by means pipe fitting 19 For release of pipe fittings little tube push in direction to the base knurled flange For coupling to the tube insert in your seat Periodically check the fuel tank vent 5 to ensure that their openings are unobstructed repeat inspection more frequently if operating in dusty conditions It is recommended for inspection purposes to use a small rubber tube to blow through the vent clearing possible obstructions Drain gascolator daily see Fig 6 2 using the spring tap 2 Unscrew ring nut 1 for disconnect bowl and accede at wire mesh filter 4 use particular care not to damage seal 3 and spring 1
20. 12 14 2007 Od 214 2007 31 12 14 2007 fs 12 14 2007 32 12142007 TE 00 0 33 12142007 __ 0 34 12142007 E 00 0 35 12 14 2007 o Revision n 1 2 February 2009 3 Revision Date 12 14 2007 Revision Number 1 01 Doc N 27 13 200 00 COSTRUZIONI AERONAUTICHE P92 Eaglet ler TECNAM Line Maintenance Manual Table of Contents it ror NER O 8 1 1 Auth rizatiOhs Lidia isa iaia lhi 8 Descriptions amp General Characteristics o aaa aaa aaa Ee SE nae Ee SERV ariana nerina ina 9 2 1 Certification BASIS sadar kkj k i 9 2 2 Descriptive Bloom PEE 10 2 2 1 PUTING es dissed UIDERI EET EE r O 10 AA e WANG M H 10 2212 IET TH PERO 10 A A ti ere A ioe Cena Ra eodd aea AAA Sa d ER era paga aad ae e N gae a Pede kaka E rd ka h a 10 2 2 1 4 o TITO TT LT DTI 10 2 3 uum 11 2 3 1 Saulis m HEC NEP M vcr EE 11 2 3 2 Propeller 11 2 3 3 OE E asas lo Gesner 11 2 3 4 Oil SVStEM NS 11 2 3 5 HoT N sas costs OR 11 2 4 WI Endara ica et 12 2 4 1 Maximum Weights ince snudd HR raa eh E ds air 12 2 4 2 Standard Weights 1 4u PP 12 2 4 3 Specific HOACINGS EE TEE NO 12 2 5 Instructions for Reporting Possible Safety of Flight Concerns isses seen enne nnn nnns nnn 12 2 6 Source to PULCNASE POPES caidos
21. 2 61 BAZ Usable fuel 61 8 13 Fuel selector Valve ali iii cain 62 8 14 BO0gdaje cCOmpartmehlssassnasbssobonsosobhilnssluensisuesokiouli a 62 8 15 7 ol AA iaia 62 8 16 MEO oda a 63 Revision Date 12 14 2007 Revision Number 1 01 Doc N 27 13 200 00 P92 Eaglet PU EN EMG E EE TECNAM Line Maintenance Manual 8 17 Cooling system overflow tank ecd la a va f Aa ai liane eno aba aja H kaa Fee Ve 3p Ea tad Saa Ha la a diede 63 8 18 Brake Oll reservoir aaa 63 8 19 Tire VE NN 64 8 20 Aircraft longitudinal leveling reference pointS iii 64 8 21 J dentification plate iri arera isa 64 8 22 Externalemergency open COOK air 64 E IE h Ll 0 erene RN O NIN 64 8 24 Limitation Placards savia dd E A k j rj 65 T Revision Date 12 14 2007 Revision Number 1 01 Doc N 27 13 200 00 P92 Eaglet m COSTRUZIONI AERONAUTICHE EABLET TECNAM Line Maintenance Manual 1 Introduction Before servicing the aircraft we recommend careful reading of this manual the flight manual the propeller manual and the engine s service manual A thorough knowledge of the aircraft of its qualities and of its limitations will allow you to operate with greater safety The P92 Eaglet is an uncomplicated and sturdy machine whose features include simple servicing and superior flying qualities This manual describes time and modes for correct ser
22. 3 Empennage Stabilator span 2 900 m 9 57 Stabilator area 1 972 m 21 2 ft Stabilator cord 0 680 m 26 Vertical tail span 1 230 m 3 97 Vertical Stabilizer area 0 720 m 2 36 sq ft Rudder area 0 350 m 1 48 sq ft 2 2 1 4 Landing Gear Wheel track 1 800 m 5 97 Wheel base 1 600 m 5 27 Main gear tire Air Trac 5 00 5 Wheel brakes Marc Ingegno Nose gear tire Sava 4 00 6 Doc N 27 13 200 00 Revision Date 12 14 2007 Revision Number 1 01 X COSTRUZIONI AERONAUTICHE TECNAM 2 3 Systems P92 Eaglet Line Maintenance Manual P92 KELET 2 3 1 Engine Manufacturer Bombardier Rotax GmbH Model 912 ULS or 912 S2 optional Certification basis ASTM F2239 or FAR 33 Austrian T C No TW 9 ACG dated 27th November 1998 Type 4 cylinder horizontally opposed twins with overall displacement of 1352 c c mixed cooling water cooled heads and air cooled cylinders twin carburetors integrated reduction gear with torque damper Maximum rating 98 6hp 73 5kW 5800 rpm min 2388 rpm min prop Gear reduction ratio 2 4286 1 Max oil consumption Max 0 1 liters hour 2 3 2 Propeller Manufacturer GT Tonini Model GT 2 173 VRR FW101 SRTC Number of blades 2 Diameter 1730 mm 68 no reduction permitted Type Fixed pitch
23. 6 20 1836 20 1836 20 1880 20 Inches 184 4 184 4 164 4 164 4 72 3 72 3 74 16 Revision Date 12 14 2007 Revision Number 1 01 Doc N 27 13 200 00 COSTRUZIONI AERONAUTICHE P92 Eaglet TECNAM Line Maintenance Manual P92 KELET 3 5 Weighing USE GUIDELINES AS FOLLOWS 1 Carry out weighing procedure inside hangar 2 Remove any objects inadvertently left on board aircraft excessive dirt grease moisture etc 3 Make sure that all required items of equipment that is included in the empty weight is onboard 4 Align nose wheel 5 Drain all fuel in level flight attitude 6 Oil hydraulic fluids and coolants are at operating levels 7 Move seats to most forward position 8 Flaps retracted 0 9 Control surfaces in neutral position 10 Position scales min capacity 200 kg 440 lbs under each tire 11 Record weights of individual scales 12 Level the aircraft 13 Record weights of individual scales 14 Calculate empty weight 3 6 Determination of CG 1 NBA Drop a plumb bob tangent to the wing s leading edge in the un tapered section of the wing at about one meter 40 from the root trace a reference mark on floor Repeat operation on other half wing Connect the two reference marks with a taut line Measure distances between reference line and landing gear wheel axles Recorded data allows determination of C G location and aircraft s moment see following
24. 7 from support 6 release control shaft 4 from aft bell crank assembly 3 then release horn assembly 2 from brackets 6 33 Revision Date 12 14 2007 Revision Number 1 01 Doc N 27 13 200 00 COSTRUZIONI AERONAUTICHE P92 Eaglet er TECNAM Line Maintenance Manual 00 Figure 4 7 Stabilator control 4 5 1 Stabilator balance If it becomes necessary to verify stabilator balance repairs etc proceed as follows Remove the tail fairing and open the inspection hatch located on the bottom of the tail cone the one closest to tail end Disconnect the moving surface from its control rod To avoid interference with the free rotation of the tail plane temporarily secure control rod to the stabilator support assembly Disconnect the trim tab control rod Secure trim tab to stabilator to avoid any relative movement Use adhesive tape to avoid any influence on balance Check for excessive friction or lock ups in the moving parts The stabilator is balanced when the application of an 800 grams 28 21 ounces weight at point 1 in figure above brings stabilator to horizontal position If the stabilator should result trailing edge heavy it is necessary to add a few small weights to the leading edge near the root A slight imbalance towards the leading edge is acceptable as it is deemed conservative with respect to stability 4 6 Vertical Tail The vertical
25. Seat supports and safety harness attachment points are also shown 36 Revision Date 12 14 2007 Revision Number 1 01 Doc N 27 13 200 00 P92 KELET P92 Eaglet Line Maintenance Manual COSTRUZIONI AERONAUTICHE TECNAM Figure 4 10 Cabin truss Engine mount is constructed of steel tubing and is secured to cabin truss via a four point attachment Bolts travel through bushings welded on mount pass through the firewall and exit through other bushings welded to cabin truss Nose gear support assembly is attached to engine mount Figure 4 11 Tail cone 37 Cabin access is through two doors constructed of light alloy square tubing A synthetic material door panel shaped for better comfort is riveted to doorframes Both doors feature spring lock door handles with inside safety latch Revision Date 12 14 2007 Revision Number 1 01 Doc N 27 13 200 00 P92 Eaglet m COSTRUZIONI AERONAUTICHE EABLET TECNAM Line Maintenance Manual Seats are made out of metal tubing framework with fabric covered foam padding The two seats can be independently adjusted by sliding backward and forward along rails fixed to cabin truss structure Seat release levers are located just below seat cushions Cabin floor is constructed of light alloy and features matting Entire fuselage wing and other exposed surfaces are finished with a highly resistant weatherproofing synthetic coating Wash using
26. Sii Rk GS r ade 30 4 4 ACTON eigo PRE O 30 4 5 Horizontal Tail rm 31 4 5 1 Stabilator balance NO 34 4 6 Vertical Tallaksen eee 34 4 7 DIL 36 4 8 Hol DActol T MM 38 4 8 1 IMAI GO ai TERR PEE 40 4 8 2 Removal of cup bearing from main gear wheel eene nennen nennen nnns 40 4 9 NOS GQ pop RP 42 4 10 Removal of nose gear fairing and wheel aaaaaiviiinaaannnnnnnnannnnnnnnnnnnnnnnnnnnnnnnnnnnnnnnnnnnnnnnnnnnnnnnnnnnnnnnnnnnnnnannnnnnaann 43 4 11 To remove nose wheel proceed as follows axaaaiiinnaannnsnnnnnnnnnnnnsnnnnnnnnnnnnnnnnnnnnnnnnnnnnnnnnnnnnnnnnnnnnnannnnnnnnnannnaannaaai 43 412 Tireinflation TA A v eer PEE skinke aa 44 PoWerplahtusduslk salsera eee 45 5 1 CO O O 45 Revision Date 12 14 2007 Revision Number 1 01 Doc N 27 13 200 00 gr r COSTRUZIONI AERONAUTICHE P92 Eaglet ES er TECNAM Line Maintenance Manual 5 2 Engine Main FOC EUROS yi adaa f a tegere peser napa Saeco ana iii kka Baa Dala ata SEE 46 5 3 General Servicing Procedures vedeweaacersccvsasusateaseayied ani 47 5 3 1 ldle spe d synchronizatioNa sunnd sasnis uaddastsklask sdad aaskss un tulrisuadgisiibunkdi sslk rssnakad u 47 5 3 2 Ordinary SERVICING akak gR R 47 5 3 3 A O 47 5 3 4 Prope
27. amp cloth Apply protective finish the same day in which treatment begins 3 8 Service Directives 19 Revision Date 12 14 2007 Revision Number 1 01 Doc N 27 13 200 00 COSTRUZIONI AERONAUTICHE TECNAM 3 9 Servicing For scheduled servicing on engine refer to manufacturer s Operator s manual 3 9 1 3 9 2 3 10 Lubrication every 100 hours or annually Daily P92 Eaglet Line Maintenance Manual Pitot and static ports Check for obstructions Oil Check oil level Coolant Check coolant level Fuel strainer Check and drain Gascolator for water or sediment Fuel tank vents Check vents for obstruction As needed Tires Check condition and maintain proper tire pressure P92 KESET Periodic lubrication of moving parts insures proper operation and extends parts life considerably Lubrication type points and intervals are indicated below Avoid excessive lubrication as this may cause external surfaces of hinges and bearing to collect dirt and dust 3 10 1 If part is not lubricated using a grease gun grease part by hand removing excess To grease main gear wheel bearings first remove thrust bearings from wheel hubs then clean surface using solvent apply grease and re assemble Use grease type MIL G 3278 or equivalent i e Mobil grease 27 Synthetic aviation grease Lubrication Points 1 2 Rudder hinges Rudder control cable terminals Stabilator control
28. and other foreign matter To avoid damage to finish do not use polishing detergents Original or equivalent corrosion prevention must be re applied after any alteration or repair If any trace of corrosion is detected it should be removed as soon as possible and part should be immediately treated to prevent further corrosion a For steel parts with the exception of highly stressed components or stainless steel it is possible to use abrasives power brushes steel brushes if operated manually and steel wool Removing corrosion by products from highly stressed steel components main gear steel spring requires particular care b For aluminum parts treatment consists in mechanically removing as much as possible corrosion by products applying corrosion inhibitor and replacing original finish Steel wool emery or steel brushes unless stainless steel along with other highly abrasive material should not be used since steel or emery particles become embedded in the softer material causing corrosion After cleaning surface corrosion parts must be treated with an anti corrosion finish prepared as follows 4 liter solution containing 10 chromic acid with 20 drops of battery electrolyte Accurate brushing with a sturdy fiber brush will rid most of the corrosion and insure that the anti corrosion agent will penetrate completely in the cracks Leave the chromic acid solution on the part for at least five minutes and then remove excess with water or a d
29. che Tecnam Model P92 Eaglet Serial number 123 8 22External emergency open door On each door is a placard 60x40mm for the external emergency open door left and right side IN CASE OF EMERGENCY IN CASE OF EMERGENCY GASP HANDLE AND GASP HANDLE AND PULL WITH FORCE HERE A PULL WITH FORCE HERE 8 23 No smoking On the pilot s panel a placard will state the following 27x7mm 64 Revision Date 12 14 2007 Revision Number 1 01 Doc N 27 13 200 00 e P92 Eaglet 232 COSTRUZIONI AERONAUTICHE EABLET TECNAM Line Maintenance Manual NO SMOKING 8 24 Limitation Placards Next to the airspeed indicator is the following placard 6x52mm Maneuvering speed Va 93 KIAS On the pilot s panel a placard will state the following NO INTENTIONAL SPINS Located on the instrument panel is the following placard This aircraft was manufactured in accordance with Light Sport aircraft airworthiness standards and does not conform to standard category airworthiness requirements On near each door is a placard 530x50mm that says Light Sport Light Sport 65 Revision Date 12 14 2007 Revision Number 1 01 Doc N 27 13 200 00 P92 Eaglet 232 COSTRUZIONI AERONAUTICHE EABLET TECNAM Line Maintenance Manual Feedback Form Send your comments to In the USA Tecnam Aircraft Inc 1350 Churchill Way Marietta GA 30062 www tecnamaircraft com T
30. chnical data Maximum power rating 73 5 kW RPM max power 5800 rpm Cruise power rating 69 0 kW 5500 rpm Bore 84 mm Stroke 61 mm Displacement 1352 cm3 Compression ratio 10 5 1 Firing order 1 4 2 3 Direction of rotation of prop shaft clockwise pilot s view Max temp Cylinder heads 135 C Fuel See Flight Manual Sect 2 Limitations Reduction ratio 1 2 4286 EXPANSION TANK VACUM PUMP er PROPELLER GEAR PROPELLER FLANGE _ VACUM VALVE I B ELECTRIC FUEL PUMP E n GASCOLATOR D p a OIL FILTER AIR VALVE OIL COOLER P SILENT BLOCK RADIATOR RAM AIR INTAKE CABIN HEAT VALVE ENGINE MOUNT EXHAUST STACK Figure 5 2 Engine installation 46 Revision Date 12 14 2007 Revision Number 1 01 Doc N 27 13 200 00 P92 Eaglet 157 COSTRUZIONI AERONAUTICHE EABLET TECNAM Line Maintenance Manual 5 3 General Servicing Procedures 5 3 1 Idle speed synchronization With the exception of idle speed synchronization no other carburetor adjustments are required Fuel mixture is controlled and set by the manufacturer and requires no further adjustment 5 3 2 Ordinary servicing Refer to the Engine Operator s Manual furnished by the engine s manufacturer p n 899370 Issue 0 of 1 7 1998 and later versions for all se
31. ck absorbing devices for damage Check linkages trusses and members for undue or excessive wear fatigue and distortion Check hydraulic lines for leakage Check electrical system for change and improper operation of switches Check wheels for cracks defects and condition of bearings Check tires for wear and cuts Check brakes for improper adjustment SOR o rs 3 12 6 Wing and center section assembly Check for 1 Poor general condition 24 Revision Date 12 14 2007 Revision Number 1 01 Doc N 27 13 200 00 arare COSTRUZIONI AERONAUTICHE P92 Eaglet KLAR er TECNAM Line Maintenance Manual 2 Fabric or skin deterioration 3 Distortion 4 Evidence of failure 5 Insecurity of attachment 3 12 7 Empennage assembly Inspect all components and systems for General condition Fabric or skin deterioration Distortion Evidence of failure Insecure attachment Improper component installation Improper component operation ID AO 3 12 8 Propeller group Check propeller assembly for 1 Cracks 2 Nicks 3 Binds 4 Bolts for improper torque and lack of safetying 3 12 9 Radio group Check radio and electronic equipment for improper installation and insecure mounting Check wiring and conduits for improper routing insecure mounting and obvious defects Check bonding and shielding for improper installation and poor condition Check antenna including trailing antenna for poor condition insecure mounting and
32. d 3 whose position is adjusted via an electric linear actuator 4 governed by a switch on dashboard Jack stop are adjustable by adjustable pallet placed on the slide 4 Two push pull rods 6 are connected to the ends of the torque tube see fig C 3 1 allowing quick inspection owing to favorable location between wing and fuselage The two push pull rods controlling flap movement feature an extendible linkage just before the roller bearings allowing trailing edge line up Figure 4 3 Flap control 4 4 Aileron control Aileron control system uses push pull rods and bell cranks inside wing and steel cables and pulleys inside fuselage 30 Revision Date 12 14 2007 Revision Number 1 01 Doc N 27 13 200 00 Z3 COSTRUZIONI AERONAUTICHE P92 Eaglet A er TECNAM Line Maintenance Manual Layout of flight control system inside cabin includes three pairs of pulleys which transmit movement from the two control sticks 1 linked in parallel by a rod 2 to a small bar 3 located in cabin overhead in correspondence with main pushrods issuing from half wings Main rods are connected to the small bar using two pins 4 The two main rods 5 are routed through the ribs and are attached at opposite end to a bell crank 6 and a push pull rod 7 The push pull rod then crosses the wing s fake spar to transmit motion Linkage length is adjustable 6 3 a Y A ops K 5 E _ i e S A 5 N j SK Ze 7 x i
33. dals Dual Throttles Throttle Friction Control Engine Choke Electric Flaps Hydraulic Disc Brakes with Parking Brake Left and Right Fuel Selector Valves Direct Nose Wheel Steering Interior Adjustable Pilot and Copilot Seats Acoustic Cabin Soundproofing Adjustable Cabin Air Ventilators Steel Roll Cage Cabin Heat and Windshield Defrost 12V Power Outlet Metal Instrument Panel Exterior All Aluminum structure Landing Light Strobe Light Fixed Landing Gear Nose Gear Strut Fairing Nose and Main Wheel Fairings Powerplant and Accessories Rotax 912 ULS Engine 100 hp Composite Covered Wood Propeller with Spinner 12Volt 18 Ah Battery internal 18 Amp AC generator Engine Driven Fuel Pump Electric Aux Fuel Pump Electric Starter Engine Exhaust Muffler Gascolator with Quick Drain Integral Wing Fuel Tanks All Electric Circuits Fuse Protected 13 Revision Date 12 14 2007 Revision Number 1 01 Doc N 27 13 200 00 P92 Eaglet ree COSTRUZIONI AERONAUTICHE EABLET TECNAM Line Maintenance Manual SECTION 3 INSPECTION amp SERVICING 3 Inspection and Servicing 3 1 Ground Handling Move the aircraft on the ground by pushing on the wing struts close to wing attachments or by pulling on the propeller blades close to hub It is preferable to use a tow bar A tow bar can be attached to fittings provided on nose gear fork Aircraft can be steered using the rudder or for
34. e above shown 8 8 Flaps The flap control switch is located on the lower portion of the instrument panel The following placards 15x10mm the upper 6x15mm the lower are just next to it DOWI 8 9 Generator Master Starter On the lower part of the instrument panel are located in order The starter marked with a placard 60 Revision Date 12 14 2007 Revision Number 1 01 Doc N 27 13 200 00 P92 Eaglet 232 COSTRUZIONI AERONAUTICHE EABLET TECNAM Line Maintenance Manual For the generator and master switches F gt T 20 A sae ASK 8 10 Choke Located above the choke lever AVI P N FURA Push 8 11 Generator light A generator warning light is located on the upper right side of the instrument panel and it is marked with the following label ALT 8 12Usable fuel Located next to the two fuel level gauges are the two placards indicating the usable fuel for each tank 18x13mm Left Tank Right Tank Usable Fuel Usable Fuel 61 Revision Date 12 14 2007 11 5 gallons 11 5 gallons Revision Number L 01 Doc N 27 13 200 00 COSTRUZIONI AERONAUTICHE P92 Eaglet C TECNAM Line Maintenance Manual P92 KESET Note For extended tanks the usable fuel per side is 45 liters or 11 9 gallons 8 13 Fuel
35. e tail cone The compartment is suitably drained and vented and access is through a small hatch secured by a screw Every 50 hours or more often during summer add distilled water to keep electrolyte at correct level Battery elements must be completely submerged Before installing battery accurately clean support removing any trace of electrolyte and insure that drain tube is free from obstructions Use sodium bicarbonate solution for cleaning purposes Make sure battery terminals are in proper condition and apply Vaseline Insure Master switch is OFF before connecting cables Also insure that no sulfuric acid comes into contact with the aircraft s structure In case this should occur rinse accurately using soap and water Generator is permanent magnet type DC conversion is via an electronic regulator with integrated rectifier Generator servicing and repair must be carried out by specialized personnel Circuit protection is through breakers located on right lower side of dashboard The drawing below shows position and capacity of breakers used 10 as 5s 3 2 5 2 5 Y 75 10 Fuel pump Instr 1 Instr 2 Trim Flap Strobe Nav Light Landing AL NN TSN fy SN 7 CN 7 7 SN 7 SN 10 i 3 3 ie oe ae i 2 2 1 7 5 ff 10 3 SS N AA NS A MS 74 NM Z S My N LP N TDR ENC AUDIO PH AVIONIC AUX GEN SOCKET 12V Com Nav dd INTERCOM MASTER Figure 7 1 Breakers Typical panel
36. ecnam O bellsouth net 770 309 4155 Italian Address COSTRUZIONI AERONAUTICHE TECNAM s r l www tecnam com Casoria industrial plant Capua industrial plant la Traversa via G Pascoli n 1 Via Maiorise 80026 Casoria NA ITALY 81043 Capua CE ITALY 39 081 7583210 39 081 7584528 39 0823 620134 39 0823 622899 66 Revision Date 12 14 2007 Revision Number 1 01 Doc N 27 13 200 00
37. eference to numbers in parenthesis consists of a main spar 4 and a fake spar 5 that makes up its front and rear vertical walls a series of ribs 6 and wrap around panels complete the structure 28 Revision Date 12 14 2007 Revision Number 1 01 Doc N 27 13 200 00 Z3 COSTRUZIONI AERONAUTICHE P92 Eaglet A er TECNAM Line Maintenance Manual Front and aft spars are complete with wing to fuselage attachment fittings 7 Wing to strut attachment fittings are located approximately in the middle of main spars 8 Aileron uses piano hinges type MS 20001 4 for direct attachment of aileron spar to wing spar Flap hinges are external to wing torsion box and feature SKF GE10E type ball bearings In the following figure as shown the position of aileron plumb mass balancing 12 Figure 4 2 Wing structure The aileron is constructed of an aluminum spar to which a formed sheet metal leading edge and metal ribs are attached Dacron synthetic material wrap around aileron structure Flaps are constructed of a center spar to which front and rear ribs are joined aluminum skin panels wrap around flap structure Wing tips are molded epoxy resin fiberglass reinforced At the inboard end of half wing s leading edge is an integrated aluminum fuel tank with individual filler cap Fuel tanks vent through light alloy tubes in the area immediately below the tanks 4 2 1 Installing and reinstalling the wing Procedure for removal of win
38. em overflow tank Located on the overflow tank cap is the placard indicating the solution proportion between the antifreeze additive and the water 80 antifreeze 20 distilled water 8 18 Brake oil reservoir On the cap of the brake s oil tank is a placard indicating the type of oil that must be used SPECIFY YDRAULIC OIL MIL H5606 On the rear of the passenger seat is a placard indicating the brake oil check 40x15mm 63 Revision Date 12 14 2007 Revision Number 1 01 Doc N 27 13 200 00 e P92 Eaglet 232 COSTRUZIONI AERONAUTICHE EABLET TECNAM Line Maintenance Manual 8 19Tire pressures On each steel spring leaf is a placard indicating the main tires inflating pressure 18x6mm 23 psi On the nose gear is located the following placard indicating the nose tire inflating pressure 18x6mm 15 psi 8 20 Aircraft longitudinal leveling reference points Between the two seats on the forward and aft seat s supporting trusses are the following placards 15x20mm indicating the leveling reference point LEVEL HERE See Maintenace Manual for the procedure 8 21 Identification plate The following placard is located on the pilot side of the empennage forward of the stabilator and made of stainless steel Builder Costruzioni Aeronauti
39. er 1 01 P92 Eaglet m COSTRUZIONI AERONAUTICHE EABLET TECNAM Line Maintenance Manual SECTION 5 POWERPLANT 5 Powerplant 5 1 Cowling The engine cowling is available in two versions either classic or gull wing type The cowling is made up of two parts the upper part consists of a fiberglass nose and light alloy panels while the bottom part is partially made of fiberglass and aluminum Cowling top is easily removed by releasing four latches two on each side Removal of lower portion is just as easy by quick release of two side pins and two latches located on bottom See fig 5 1 If any cracks are detected immediately drill stop holes at crack ends Air circulation is provided by front openings in nose section and by an outflow area on the underside by the firewall Aluminium Aluminium Figure 5 1 Engine cowling 45 Revision Date 12 14 2007 Revision Number 1 01 Doc N 27 13 200 00 COSTRUZIONI AERONAUTICHE TECNAM 5 2 Engine Main Features P92 Eaglet Line Maintenance Manual P92 KESET The installed engine is a BOMBARDIER ROTAX type 912 S2 horizontally opposed four cylinder one central camshaft with pushrods and OHV Other features include liquid cooled cylinder heads and ram air cooled cylinders Prop drive is via reduction gear with integrated shock absorber and overload protection Electric starter integrated AC generator and mechanical fuel pump are standard Te
40. g and strut is as follows e Drain fuel tank using drain tank and closing opposite side tank fuel circuit Remove panel inside cabin to access and disconnect fuel line For the right wing disconnect stall warning system wires Disconnect position lights wiring if present Disconnect flap control see fig 4 3 by removing roller bearings 7 that link push pull rods 6 to flap control plate e Disconnect aileron control see fig 4 4 by removing pins 4 that connect the small bar 3 to the pushrods 5 e While supporting the wing s end not from wingtip release strut s upper pin then release lower pin and remove strut e While supporting the half wing from below the root area release the two wing to fuselage attachment pins To expedite release of aft pin keep flap lifted then remove wing e Replace pins in their original location and cap fuel lines 29 Revision Date 12 14 2007 Revision Number 1 01 Doc N 27 13 200 00 P92 Eaglet m COSTRUZIONI AERONAUTICHE EABLET TECNAM Line Maintenance Manual e Reverse above procedure for reinstallation paying close attention to tighten strut s bolts to recommended value M8 bolt torque 24 6 Nm 218 inch pounds 4 3 Flap control Flap control system is push rod type The torque tube 1 connects the two moving surfaces and hinges to supports 2 rigidly attached to fuselage structure Link is secured by bolt nut and cotter pin Rotation is transmitted through a push ro
41. g gear support beam do not place support against lower aluminum panel as doing so would deform and damage the panel Prevent possible tip over of the aircraft by placing a suitable stand to rear of aircraft WARNING As a general rule apply force to aircraft structure only on main structural elements such as frames ribs or spars 14 Revision Date 12 14 2007 Revision Number 1 01 Doc N 27 13 200 00 P92 Eaglet 157 COSTRUZIONI AERONAUTICHE EABLET TECNAM Line Maintenance Manual 3 4 Leveling Occasional leveling of aircraft may be necessary to insure proper wing incidence and or dihedral or for exact CG location The aircraft is level when the cabin floor and in a transversal direction the landing gear bulkhead are horizontal Level the aircraft using a simple spirit or water level and adjust the aircraft s tilt through shims placed under wheels or by regulating tire pressure 3 4 1 Control surface settings Adjustment of control surfaces must not exceed travel limits reported in table below The zero reference mark for stabilator 1s on left side of aircraft see figure below AILERONS starting from tip line up Up 18 STABILATOR Up 15 TRIM Stab at 0 see fig below RUDDER LH 25 FLAPS max travel ps FS CONTROL CABLE TENSION for all 20daN 454 2daN 4 In order to find the stabilator s zero the aeroplane must be previously longitudinally levelled Place a s
42. him 19mm thick over the stabilator s rear spar and place the level over the shim and the stabilator s tubular spar see figure B 3 then level the stabilator FIGURE 3 1 STABILATOR ADJUSTMENT 3 4 2 Trim tab adjustment Travel adjustment of trim tab on stabilator should be carried out as follows e Move stabilator to neutral 0 degrees and lock in position this is accomplished by aligning the leading edge of the stabilator with the reference rivet located on the left side of tail cone e Turn Master Switch ON e Trim to maximum pitch up e Adjust thread of hinged control rod until tab is deflected downwards 12 use a protractor or measure downward displacement of trailing edge 12 is approximately 24mm 945 e Trim to maximum pitch down e Tighten lock nut for adjustment thread and fasten connecting pin of control rod to trim tab 15 Revision Date 12 14 2007 Revision Number 1 01 Doc N 27 13 200 00 P92 Eaglet Line Maintenance Manual COSTRUZIONI AERONAUTICHE X TECNAM 3 4 3 Aircraft alignment P92 KESET lt PANNELLO VENTRALE LATO TIP R 1 F U il V 7 J LL 4B LL U Figure 3 2 Alignments 3 44 Datum Distances in mm 4684 20 4684 20 4176 20 417
43. ining A amp P or an FAA Repair Station may perform heavy maintenance repairs and alterations Overhaul Authorization to perform Only the manufacturer of a LSA or the component to be overhauled on a LSA may perform or authorize to be performed the overhaul of a LSA component A separate overhaul manual in addition to the manufacturer s line maintenance manual is required to perform the overhaul of a LSA or LSA component Note The installation of any item not installed by the factory requires an authorization letter prior to installation This applies to any optional items whether listed in the manual or not Contact Tecnam Aircraft at Tecnam bellsouth net or 770 309 4155 For additional information or explanations contact In the USA Tecnam Aircraft Inc 770 309 4155 www tecnamaircraft com Tecnam bellsouth net Tools Needed Most of the aircraft uses metric hardware A standard set of metric wrenches is required to work on this aircraft The necessary tools to work on the engine are listed in the maintenance manuals provided by Rotax 8 Revision Date 12 14 2007 Revision Number 1 01 Doc N 27 13 200 00 COSTRUZIONI AERONAUTICHE P92 Eaglet TECNAM Line Maintenance Manual SECTION 2 GENERAL PIZ KELET 2 Descriptions amp General Characteristics The P92 Eaglet is an all metal high wing two place single engine airplane equipped with tricycle landing gear It is an ASTM com
44. l type see fig 4 6 and is controlled from the cabin via the control sticks Control is transmitted through a push pull rod 1 linked to a bell crank 2 and a shaft 3 that runs through the tail cone supported at midsection by a bracket 4 and connected with the stabilator torque tube through the aft bell crank assembly 5 All significant transmission elements such as bell cranks pushrods supports and hinges can be easily accessed and inspected 32 Revision Date 12 14 2007 Revision Number 1 01 Doc N 27 13 200 00 P92 Eaglet m COSTRUZIONI AERONAUTICHE EABLET TECNAM Line Maintenance Manual Figure 4 6 Stabilator control If unusual tolerance is found along transmission replace parts displaying excessive wear The aft bell crank assembly see fig 4 7 consists of a steel tube 1 with welded horn assembly 2 attachment for stabilator control shaft 3 and balanced weight bell crank 4 Counterweight is located at the end of a prong bolted to the torque tube and entering tail cone through the tail frame cutout Longitudinal trim is controlled through two switches on the stick handle and is monitored via an indicator located on instrument panel Control activates the linear actuator 5 connected to supports 6 and horn assembly 7 Actuator s motion is transmitted to an adjustable push pull rod 8 through a bell crank 9 To remove the stabilator torque tube disconnect electric actuator frame assembly
45. ller removal EE NN NE cR RENE 47 5 3 5 Propeller installationi nici ate 47 5 3 6 Periodic INSpECtio Morrenia SE DL ERE 48 O OO 49 6 1 Fuel S StelM sana aka r r 49 6 2 INSTEUMENTAION aaah 51 6 2 1 Engine instrumentation AO 52 6 3 Pitot and Statie System siii di RA portae heb uta aaa CREER SR NE A dende Laa Ia S Re eq al INA 53 6 4 Exhaust Manifolds iaei ieren a eoa er FRE Po ao aaa 54 6 4 1 A E NE RR eee 54 6 4 2 Carb retor MO Abs ava RRR k iaa 55 6 5 BAKE SVSTOMT A AEEA TE A A EEE A E E id dani 56 6 5 1 Draining and replacing brake fluid La 56 6 5 2 Replacing brake pads eee oer nee iskja aaa vi Bankar A ne 57 Electrical SEM A EEEE aE EARNE SERERA 58 MEE AAA 59 8 1 Magnetic compass compensation table iinaaaaavsisnnanannnnnsnnnnnnnnnnnnnnnnnnnnnnnnnnnnnnnnnnnnnnnnnnnnnnnnnnnnnnnnnnnnnnnnnnnnnnannnani 59 8 2 Engine throttle it d vai cade E ERE d eo FERRE eR EE E RS TRE k it Reed i aiar 59 8 3 Engine throttle friction eH 59 8 4 GODIN Nea akse 59 8 5 Garb retor heat usant am ere r EEE 59 8 6 elus MEE 60 8 7 hber Ml MG 60 8 8 hrec M i aid 60 8 9 Generator Master Starter iiv sak d aa ideale cine equa Po Pene bis Fere ts dua Qon Rode 60 LEITET 61 CIENEECHITJeuldiriteeE 7
46. n be modified via adjustable ball and socket connections Cable tension must be checked periodically and adjusted to proper value using the turnbuckles 4 Tension 20 daN 2 Pulley condition 5 and their smooth operation must also be checked To access levers and rudder pedals support remove cabin s central tunnel for speedier operation remove seats from railings 35 Revision Date 12 14 2007 Revision Number 1 01 Doc N 27 13 200 00 VT COSTRUZIONI AERONAUTICHE P92 Ea let E ar TECNAM Line Maintenance Manual Figure 4 9 Rudder control 4 7 Fuselage The front part of the fuselage is made up of a mixed structure a truss structure with special steel members for cabin survival cell fig 4 10 and a light alloy semi monocoque structure for the cabin s bottom section The aft part of the fuselage fig 4 11 is constructed of an aluminum alloy semi monocoque structure Attachment to cabin truss 1s at the forward fittings of four stringers that run the aft fuselage length 1 Two flanges are located at the aft end of the tail section to support the horizontal tail assembly 2 and the vertical tail forward and aft spars Forward truss structure drawing fig 4 10 shows location of attachment points for half wing 1 aft section 2 brace strut 3 main landing gear 4 engine mount 5 flap torque tube 6 stabilator bell crank 7 throttle support 8 and pulley support for cable driven aileron control 9
47. n wing underside access to aileron differential bellcrank main spar and torque box inspection of wing to strut attachment 2 Upper strut fairing inspection of strut to wing attachment Lower strut fairing inspection of strut to fuselage attachment 4 Tailcone underside portholes access to stabilator control rod pass through battery relay front attachment of vertical stabilizer inspection of aft structure and of cables for rudder control Battery porthole access to battery not normally installed 6 Tailcone end fairing access to stabilator torque tube and attachments to control lever attachment of vertical stabilizer aft spar rudder bellcrank trim actuator and pushrods 7 Aft cabin bulkhead and baggage compartment floor inspection of aft fuselage section and attachments inspection of stabilator control system and of cable pulleys for rudder control access to flap actuator access to aileron control cable turnbuckles 8 Forward cabin side panels access to half wing s forward attachment access to fuel line tank outflow 9 Cabin ceiling panel access to bellcrank joining cabin cable circuit to wing pushrods for aileron control 10 Instrument panel cover access to instrumentation and radio 11 Engine cowling access to engine and related systems access to main components of electrical system access to nose gear strut and steering assembly mechanism 12 Propeller spinner access to propeller hub
48. ns aircraft leans to one side may be carried out adjusting trim tab located on left aileron trailing edge 4 5 Horizontal Tail The horizontal tail is an all moving type that is the stabilizer and elevator form a single uniform plane called stabilator that rotates about an axis normal to fuselage at the desired pitch setting 31 Revision Date 12 14 2007 Revision Number 1 01 Doc N 27 13 200 00 COSTRUZIONI AERONAUTICHE P92 Eaglet LR r TECNAM Line Maintenance Manual The stabilator structure see fig C 7 is made up by an aluminium spar 1 to which a series of ribs 2 are riveted It is covered by aluminium panels 3 A trim tab 4 provides stick force adjustment and longitudinal compensation through an electric actuator controlled by pilot Tab is split in two parts interconnected at the support brackets 5 and attached to the stabilator through four external hinges 6 that allow for immediate inspection FIGURE 4 5 STABILATOR To remove the stabilator disconnect the two halves of the tab from each other and from the control rod remove pins 7 and then remove half planes To avoid cover damage during operation handle parts by their rigid components Reverse procedure for reinstallation applying a small amount of grease to the inside of the torque tube 1 to facilitate insertion and gently tapping parts into position being careful not to deform outward ribs The stabilator control system is push pul
49. ocated on central tunnel panel area just The cabin s heat control is marked with this placard 20x11mm CABIN HEAT Pull on 8 5 Carburetor heat The carburetors heat control knob is located on the instrument panel central area near the central engine s throttle In correspondence of it is located the following placard 20x11mm 59 Revision Date 12 14 2007 Revision Number 1 01 Doc N 27 13 200 00 P92 Eaglet 238 COSTRUZIONI AERONAUTICHE EABLET TECNAM Line Maintenance Manual CARB HEAT Pull on 8 6 Trim switch The trim shunt control is located on the upper left area of the instrument panel alternatively allocating trim control to either Rh or Lh control stick The following placard 25x14mm is positioned just above of it TRIM SWITC LH RH 8 7 Breakers Breakers are located on the lower right side of the instrument panel and each fuse is individually marked as follows from left to right gt Fuel PUMP 7 5A INSTR 1 7 54 INSTR2 5A TRIM 3A FLAP 7 54 NAV L 7 54 Land L 104 AUX GEN STROBE 7 54 COM NAV 10A GPS 5A TDR 3A ENC 24 AUDIO 24 COM 2 104 STALL 1A AVIONIC MAST 3A BATT 25A Depending on the specific equipment installed on the a c the type and position of the breakers could vary from th
50. only water mild detergent and chamois All parts in Perspex material must never be dusted dry but washed with lukewarm soapy water In any case never use on this kind of surface products such as gasoline alcohol or any kind of solvent 4 8 Landing Gear The main landing gear see fig 4 12 consists of two special steel spring leaf struts 1 positioned crossways to fuselage for elastic cushioning of landing loads The two steel spring leaf struts are attached to the fuselage underside via the main girder Two rawhide liners 2 3 are inserted between each spring leaf and the girder Two bolts 5 and nuts secure the individual spring leaf to the edge of the girder via a light alloy clamp 4 while a single bolt 6 and nut secures the inboard end of the leaf spring to the girder Figure 4 12 Main landing gear Wheels are cantilevered on gear struts and feature hydraulically actuated disc brakes see fig 4 13 controlled by a lever 1 located on cabin tunnel between seats Main gear wheels mount Air Trac type 5 00 5 tires inflated at 23 psi 1 6 bar Hydraulic circuit shut off valve 2 is positioned between seats With circuit shut off pulling emergency brake lever activates parking brake function Differential brake circuit as shown in the Figure 4 13 Control lever 1 activates pump 3 that features built in brake fluid reservoir 4 check valve 5 secure brake function when activated unintentionally parking brake
51. or static ports as this causes immediate damage to the airspeed indicator 53 Revision Date 12 14 2007 Revision Number 1 01 Doc N 27 13 200 00 P92 Eaglet 157 COSTRUZIONI AERONAUTICHE KELET TECNAM Line Maintenance Manual 6 4 Exhaust Manifolds With reference to figure 6 8 exhaust manifolds 1 are flanged to the engine and join the muffler separately 2 The muffler also works as a heat exchanger 3 for carburetor and cabin heat The exhaust system must always be checked for possible cracks ref Periodic Inspection Table Section B Close attention must be given to the heat exchanger system which should be totally disassembled for inspection as cracks would allow noxious fumes to be mixed with carburetor and cabin air heat Figure 6 8 Exhaust manifold 6 4 1 Cabin heat Cabin heat system consists of the following see Fig 6 9 e Hot air vent near rudder pedal bar 1 e De frost vents near windshield 2 e Heat exchanger 3 round knob located on lower left side of instrument panel controls cabin heat via the intercept valve located on lower part of firewall external to cabin 54 Revision Date 12 14 2007 Revision Number 1 01 Doc N 27 13 200 00 COSTRUZIONI AERONAUTICHE P92 Eaglet f er TECNAM Line Maintenance Manual 6 4 2 Carburetor heat The system is also designed to direct carburetor air intake from scoop 5 and manifold 6 located on top portion of firewall
52. pliant airplane designed to be flown by sport pilot rated pilots as well as higher rated pilots This aircraft is designed and built in Italy and as such was built using the metric system Therefore the primary numbers are in metric and the US conversion is in parenthesis for your information Figure 2 1 shows a Three View drawing of the aircraft while tables below report main technical features and dimensions The Line Maintenance Manual contains the following sections Introduction General Inspection and Servicing Airframe Powerplant Systems Markings and Placards ADAL ANS 2 1 Certification Basis This aircraft complies with ASTM standards and is certificated as a Special Light Sport Aircraft Figure 2 1 General Views Doc N 27 13 200 00 9 Revision Date 12 14 2007 Revision Number 1 01 COSTRUZIONI AERONAUTICHE TECNAM 2 2 Descriptive Data 2 2 1 Airframe P92 Eaglet Line Maintenance Manual PIZ KELET 2 2 1 1 Wing Wing span 8 7m 28 547 Wing area 12 m 129 sq ft Aspect ratio 6 31 Taper ratio 1 0 Wing chord 1 400 m 4 6 Flap span 1 970 m 6 463 Flap chord 0 390 m 15 35 Aileron span 1 505 m 4 937 Aileron chord 0 385 m 1 2637 2 2 1 2 Fuselage Overall length 6 5m 21 37 Overall width 1 143 m 457 Overall height 2 5m 8 2 2 2 4
53. r aza Figure 6 6 Pressure and oil temperature sensors 52 Revision Date 12 14 2007 Revision Number 1 01 Doc N 27 13 200 00 P92 Eaglet m COSTRUZIONI AERONAUTICHE EABLET TECNAM Line Maintenance Manual 6 3 Pitot and Static System Referring to figure 6 6 system consists of a pitot tube 1 mounted on left wing strut and two static ports 2 connected in parallel 3 and located on left and right side of fuselage just ahead of door frames Flexible plumbing connects pitot and static ports to pressure instruments Figure 6 7 PITOT AND STATIC SYSTEM Servicing the system is easy and is carried out in accordance with schedule listed in the Periodic Inspection Table found in the Inspection section of this manual Simply remove tubes from instruments and blow air in tube in port direction and never vice versa clearing possible obstructions and checking line condition Check visually and more frequently pitot tube on left strut 1 and static ports 2 clearing possible obstructions For safety reasons and to ensure correct airspeed readings it is important to check the pitot system for leaks adopting the following procedure Fasten a piece of rubber hose approximately 30 centimeters long to the pitot tube close off the opposite end of the hose and slowly roll it up until the airspeed indicator shows cruise speed Constant reading is an indication of no leak in system WARNING Avoid blowing air through pitot
54. rcuit protection breakers Throttle Cabin heat Carburetor heat knobs Dil pressur PIZ KELET e ount qty indic qty indic Individual instruments may be accessed for removal by releasing a screw located next to magnetic compass and sliding instrument panel protective cover along railings Before removing individual instruments use particular care in disconnecting wires hoses or other links as the case applies When installing instruments follow recommendations below e Do not over tighten bolts as plastic instrument casing may break 51 Revision Date 12 14 2007 Revision Number 1 01 Doc N 27 13 200 00 P92 Eaglet ree COSTRUZIONI AERONAUTICHE EABLET TECNAM Line Maintenance Manual e Insure hoses are free of any foreign matter and that no tight radius turns are present as this may choke hose or cause malfunction e Insure proper grounding and tightening of all electrical instruments Repair calibration or overhaul of instruments must be carried out only by specialized stations 6 2 1 Engine instrumentation e Electric tachometer e Hour meter e Electric oil temperature indicator The sensor is located on the oil pump tube and is marked with TO on the pump flange e Oil pressure gauge Sensor is located on oil tube Oil temperature gauge Coolant Cylinder temperature gauge Cylinder head temperature sensors are located on cylinders 2 or 3 Fuel Pressure Gauge OIL PRESS LADA d o m
55. rking and where practicable improper operation Check flight and engine controls for improper installation and improper operation Check battery for improper installation and improper charge Check all systems for improper installation poor general condition apparent and obvious defects and insecurity of attachment DIG R EE 3 12 4 Engine and nacelle group 1 Check engine section for visual evidence of excessive oil fuel or hydraulic leaks and sources of such leaks 2 Check studs and nuts for improper torque and obvious defects 3 Check engine compression If there is weak cylinder compression check for improper internal condition and improper internal tolerances 4 Check for metal particles or foreign matter on screens and sump drain plugs 5 Check engine mount for cracks looseness of mounting and looseness of engine to mount 6 Check flexible vibration dampeners for poor condition and deterioration 7 Check engine controls for defects improper travel and improper safetying 8 Check lines hoses and clamps for leaks improper condition and looseness 9 Check exhaust stacks for cracks defects and improper attachment 10 Check accessories for apparent defects in security of mounting 11 Check all systems for improper installation poor general condition defects and insecure attachment 12 Check cowling for cracks and defects 3 12 5 Landing gear group Check all units for poor condition and insecurity of attachment Check sho
56. rod terminals Stabilator support bearings Trim tab hinges Tab control push rod terminals Stabilator pass through rod Stabilator control rod inside cabin Aileron hinges Differential ailerons hinges Aileron control pushrods Aileron control rods pass trough Flaps control pushrods Flaps torque tube support Flap actuator terminals Rudder pedals support Rudder pushrods and cable terminals Brake lever support Control stick lever and support Aileron control pulleys Nose gear fork attachment hinge Shock absorber attachment hinge Nose gear strut attachment hinge Steering pushrod terminals Grease door hinges and adjustable seat rails when necessary Doc N 27 13 200 00 20 Revision Date 12 14 2007 Revision Number 1 01 COSTRUZIONI AERONAUTICHE P92 Eaglet Lr TECNAM Line Maintenance Manual Figure 3 3 Lubrication points 21 Revision Date 12 14 2007 Revision Number 1 01 Doc N 27 13 200 00 COSTRUZIONI AERONAUTICHE P92 Eaglet IES er TECNAM Line Maintenance Manual Lr Br FIGURE B 5 LUBRICATION EVERY 100 HOURS 22 Revision Date 12 14 2007 Revision Number 1 01 Doc N 27 13 200 00 P92 Eaglet m COSTRUZIONI AERONAUTICHE KELET TECNAM Line Maintenance Manual 3 10 2 Inspection panels Inspection points that are not in plain view may be accessed through inspection ports and or removal of panels or fairings as detailed below 1 Inspection Ports o
57. rvicing operations furnished along with the present manual 5 3 3 Propeller The propeller is manufactured by GT Propeller and is all wood with composite reinforced leading edge and blade protective finished with special lacquer coating 5 3 4 Propeller removal To remove propeller use the following procedure 1 Remove screws holding spinner dome to spinner bulkhead 2 Remove safetying 3 Remove bolts that secure prop to hub After removal do not lay propeller down on its tip but always lay flat and away from sources of humidity heat or in any case away from areas subject to excessive temperature change 5 3 5 Propeller installation To install propeller follow procedure below Insure that propeller is correctly aligned with hub before tightening bolts Carefully clean hub area insuring no oil traces are present Check bolts for cracks rust proper thread and cleanliness Check spinner bulkhead for cracks or deformations Check spinner for cracks and deformations Install spinner spacer and prop Insert washers and fasten locknuts bolt torque 17 Nm Safety all bolts Install spinner Gos Oy Se akon After correct installation of propeller and before takeoff let the engine run for a few minutes and after turning it off carry out further inspection tightness overall state etc 47 Revision Date 12 14 2007 Revision Number 1 01 Doc N 27 13 200 00 P92 Eaglet ree COSTRUZIONI AERONAUTICHE EABLET
58. selector valve Fuel shutoff valves are located on cabin truss forward members RH valve shuts off fuel flow from RH fuel tank LH valve shuts off fuel flow from LH fuel tank When valve lever is aligned with truss member the valve is open if lever is rotated 90 with truss member the valve is closed 2 all ON puruELTANK OFF ON LHFUELTANK OFF SHUT OFF VALVE S D SHUT OFF VALVE 8 14 Baggage compartment A placard 30x50mm indicating the maximum weight and to fasten the baggage s retain harnesses is present visible into the baggage compartment TIE DOWN HARNESS MAX WEIGHT 20kg 44 lbs SPEC PRESS 2 5 kg dm 8 15 Fuel tanks Next to the fuel tank filler caps is located a placard 57x120mm indicating the type of fuel and the total tank s capacity 62 Revision Date 12 14 2007 Revision Number 1 01 Doc N 27 13 200 00 P92 Eaglet ree COSTRUZIONI AERONAUTICHE EABLET ES TECNAM Line Maintenance Manual AUTOMOTIVE FUEL ROZ MIN 95 OCT LEADED OR UNLEADED Note For extended fuel tanks the capacity is 45 liters or 11 9 gallons 8 16 Oil tank reservoir On the oil tank reservoir are present two placards 30x12mm indicating the type and quantity of engines oil stored into the reservoir OIL AUTOMOTIVE OIL SG CAPACITY 3 5 LT 8 17 Cooling syst
59. sharp turns by lowering the tail to raise the nosewheel off the ground In this case owing to the favorable CG location a gentle push on the tailcone just ahead of empennage surfaces is all that is needed Avoid dragging nosewheel sideways and do not attempt to counter any movement of the aircraft by handling it by its wing tips 3 2 Parking and Tie down s a general precaution for outdoor parking it is wise to position aircraft into the wind and to set the parking brakes or chock the wheels if chocks are available In severe weather and high wind conditions aircraft tie down is recommended Tie ropes should be secured to the wing tie down fittings located at the upper end of each wing strut Secure opposite end of ropes to ground anchors Nose gear fork may be used as fixing for forward tie down Aircraft control stick should be locked using safety belts to prevent possible wind damage to control surfaces 3 3 Jacking Given the light empty weight of the aircraft lifting one of the main wheels can be easily accomplished even without the use of hydraulic jacks Remove the aluminum panel located between the steel springs and while one person lifts one half wing by acting on the wing spar immediately before the wingtip another person will place a suitable stand with protective cover under the steel spring attachment If one of the steel springs needs to be removed the support stand must be positioned in the specific location along the landin
60. table 17 Revision Date 12 14 2007 Revision Number 1 01 Doc N 27 13 200 00 P92 Eaglet 232 COSTRUZIONI AERONAUTICHE EABLET TECNAM Line Maintenance Manual 3 6 1 Weight and CG Table Datum Horizontal Reference Plumb Line Sal LA een Note e 1463 mm 57 6 e A 524 mm 22 05 e B 1135 mm 41 8 Information Only Adapted from AC 43 13 1B CHG 1 C G D F L W C G Distance from datum to center of gravity of the airplane W The weight of the aircraft at the time of weighing D The horizontal distance measured from the datum to the main wheel weighing point L The horizontal distance measured from the main wheel weighting point to the nose wheel weighing point F Weight at nosewheel weighing point D 1965 mm L 1622 mm Meters Fwd wheel weight Main wheel left Main wheel right W2 WL WR Meters Arm meters D Moment Kg m D We Nor weigh Wet P Weight unusable fuel 2 6 1 9 4 2 1 660 65 35 3 2 274 47 liter 2 75 quarts TOTAL De Me We CG position as wing chord De De 1 4 100 Revision Date 12 14 2007 Revision Number 1 01 Doc N 27 13 200 00 e P92 Eaglet ree COSTRUZIONI AERONAUTICHE EABLET TECNAM Line Maintenance Manual 3 7 Corrosion Prevention It is important to keep the aircraft clean and to remove any collection of corrosive agents such as oil grease dregs
61. tail consists of an all metal light alloy structure fig 4 8 Vertical stabilizer tip is composite with cut outs for navigation and strobe light The vertical stabilizer consists of a twin spar with wrap around stressed skin paneling An attachment plate 1 secures the stabilizer s front spar to the penultimate tail cone frame while the rear spar is extended to attach directly onto the last tail cone ordinate 2 The rudder is equipped with two end run stops made of Teflon 11 34 Revision Date 12 14 2007 Revision Number 1 01 Doc N 27 13 200 00 COSTRUZIONI AERONAUTICHE P92 Eaglet TECNAM Line Maintenance Manual LA er FIGURE 4 8 FIN AND RUDDER Rudder mass balancing 10 is placed on the rudder upper rib s horn To inspect this part it is necessary to remove the composite tip To remove the rudder disconnect the control cables from the bellcrank loose and remove the upper bolt e g removing the composite rudder tip and remove moving upwards the rudder Control system layout fig 4 9 is steel cable driven and circuit terminates on nose wheel steering lever Rudder pedals 1 are attached to two pushrods 3 that terminate the control circuit 2 for the rudder and transmit steering motion to the nose gear leg through a lever This lever hinges on the engine mount and springs connected to the steering lever via two small plates allow for a more effective realignment of the rudder Length of pushrods ca
62. vel condition of attachments and hinges absence of corrosion deformation rivet slackening cleanliness e Fluid lines and hoses Absence of leaks cracks dents chafing proper radius deterioration e Bolts and attachments Proper tightening and safetying absence of cracks or nicks absence of corrosion and punctiform corrosion damage to thread wear and excessive play 23 Revision Date 12 14 2007 Revision Number 1 01 Doc N 27 13 200 00 2 P92 Eaglet m COSTRUZIONI AERONAUTICHE EABLET TECNAM Line Maintenance Manual 3 12Condition Inspection 100 hour annual 3 12 1 Inspection Panels Each person performing an annual or 100 hour inspection shall before that inspection e Remove or open all necessary inspection plates access doors fairing and cowling Clean the aircraft and aircraft engine after initial visual inspection for e Oil exhaust or other leaks 3 12 2 Fuselage group 1 Check fabric and skin for deterioration distortion other evidence of failure and defective or insecure attachment of fittings 2 Check systems and components for improper installation apparent defects and unsatisfactory operation 3 12 3 Cabin and cockpit group Check for cleanliness and for loose equipment that might foul the controls Check the seats and safety belts for condition and or any defects Check windows and windshields for deterioration and breakage Check instruments for poor condition mounting ma
63. vicing procedures Scrupulously following instructions will insure that your P92 Eaglet will accompany you dependably for a long time with optimal performance in absolute safety This manual consists of 8 sections a table of contents in section I will allow you to reach any selection quickly Information contained herein is based on available data at time of publication possible variations shall be presented in service directives This manual describes correct servicing of parts manufactured by TECNAM and in subordinate measure of the list of components purchased from external suppliers for more complete information on individual components it is necessary to refer to the component s manufacturer s manual 1 1 Authorizations Levels of Certifications Owner LSA Repairman Maintenance Airplane A amp P FAA Repair Station Task Specific Preventive Maintenance Authorization to perform The owner of a SLSA who holds at least a sport pilot certificate LSA Repairman Maintenance Airplane A amp P or an FAA Repair Station may perform preventive maintenance Aircraft owners see FAR part 43 Appendix A Subpart C Line Maintenance Repairs and Alterations Authorization to perform LSA Repairman Maintenance Airplane A amp P or an FAA Repair Station may perform line maintenance repairs and alterations Heavy Maintenance Repairs and Alterations Authorization to perform LSA Repairman Maintenance Airplane with task specific tra

Download Pdf Manuals

Related Search

Related Contents

CTFID - Bosch Security Systems  NX-240 NX-240V NX-340 NX-340U  Spektrum DX9 - Horizon Hobby  Seller User Manual - SA Crafters Market  医療事故情報収集等事業第 27 回報告書の公表について  Descarga Manual    Manuel d`atelier  TCX01 - Chauvin Arnoux  Samsung SEK-2000 User Manual  

Copyright © All rights reserved. Failed to retrieve file