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P2002 Sierra

SECTION B

M A I N T E N A N C E M A N U A L

pag.

B-23

Edition, April 22

, 2008

INSPECTION & SERVICING

REFERENCE MEASUREMENTS SUMMARY

TIGHTENING MOMENT FOR ATTACHMENT BOLTS AS A FUNCTION OF SHANK DIAMETER

BOLT Class of resistance 8.8

TIGHTENING MOMENT FOR

“UNI”

ATTACHMENT BOLTS

∅

4 = 3.1 Nm

∅

6 = 10.4 Nm

∅

8 = 24.6 Nm

Attention: bolts connecting propeller to support
flange albeit

∅

8 must be tightened to 18 Nm.

TIGHTENING MOMENT FOR

“AN”

ATTACHMENT BOLTS

MIN

MAX

∅

6.35 = 9 Nm

= 10 Nm

∅

7.94 = 11 Nm

= 16 Nm

∅

9.52 = 18 Nm

= 22 Nm

ONTROL CABLES TENSION

(

FOR AILERON AND RUDDER

)

VALUE

IRE PRESSURE

OSE

PSI

(1.0

BAR

)

AIN

PSI

(1.6

BAR

)

ONTROL SURFACES TRAVEL

Ailerons

Up 18°down 15°

2°

Stabilator

Up 15°down 4°

1°

Trim

2° 12°

1°

Rudder

RH 25° LH 25°

2°

Flap

0° -35°

2°

Summary of Contents for P2002 Sierra

Page 1: ...MAINTENANCE MANUAL Doc n 2002 61 1st Edition April 22th 2008 Revision 0 P2002 Sierra BUILD NUMBER BUILD YEAR REGISTRATION MARKINGS ...

Page 2: ...imal performance in absolute safety This manual consists of 6 sections a table of contents at the beginning of each section will allow you to reach quickly any selection Information contained herein is based on available data at time of publication possible variations shall be presented in servicing bulletins This manual describes correct servicing of parts manufactured by TECNAM and in subordinat...

Page 3: ...iii C 3 iv C 4 C 5 C 6 C 7 A A 1 22th April 2003 C 8 A 2 C 9 A 3 C 10 A 4 C 11 A 5 C 12 A 6 C 13 C 14 C 15 C 16 B B 1 22th April 2003 C 17 B 2 C 18 B 3 C 19 B 4 C 20 B 5 C 21 B 6 C 22 B 7 B 8 B 9 B 10 B 11 B 12 B 13 D D 1 22th April 2003 B 14 D 2 B 15 D 3 B 16 D 4 B 17 D 5 B 18 B 19 B 20 B 21 B 22 B 23 ii ...

Page 4: ...Sezione Pagina Data Sezione Pagina Data E E 1 22th April 2003 F F 1 22th April 2003 E 2 F 2 E 3 F 3 E 4 F 4 E 5 F 5 E 6 F 6 E 7 F 7 E 8 E 9 E 10 E 11 iii ...

Page 5: ...INDEX OF SECTIONS General Section A Inspection servicing Section B Airframe Section C Powerplant Section D Systems Section E Electrical systems Section F iv ...

Page 6: ...TE NA NCE MA NUA L SECTION A GENERAL pag A 1 SECTION A GENERAL TABLE OF CONTENTS 1 DESCRIPTION GENERAL CHARACTERISTICS 2 PRIMARY DIMENSIONS 3 ENGINE 4 PROPELLER 4 FUEL 5 OIL SYSTEM 5 COOLING 5 MAXIMUM WEIGHTS 6 STANDARD WEIGHT 6 SPECIFIC LOADINGS 6 ...

Page 7: ...GENERAL CHARACTERISTICS The P2002 Sierra is a twin seat single engine low wing metal structure mono plane with tricycle landing gear and steerable nose gear Figure A 1 shows a Three View drawing of the aircraft while the following table re port main technical features and dimensions FIGURE A 1 GENERAL VIEWS ...

Page 8: ...Taper ratio 0 6 Dihedral 5 FUSELAGE Length overall 6 61 m Width overall 1 11 m Height overall 2 43 m EMPENNAGE Stabilator span 2 90 m Vertical tail span 1 10 m LANDING GEAR Wheel track 1 85 m Wheel base 1 62 m Main wheel tyres Air Trac 5 00 5 Nose gear tyre Sava 4 00 6 CONTROL SURFACE TRAVEL RANGE Ailerons up 25 down 19 2 Stabilator up 15 down 3 1 Trim 2 9 1 Rudder Lh 30 Rh 30 2 Flap 0 40 1 ...

Page 9: ...erall displacement of 1352 c c mixed cooling water cooled heads and air cooled cylinders twin carbu retors integrated reduction gear with torque dam per Maximum rating 73 5 kW 98 6 hp 5800 giri min max 5 min 69 0 kW 92 5 hp 5500 giri min continuous PROPELLER Manufacturer F lli Tonini Giancarlo Felice S n c Model GT 2 173 VRR SRTC FW101 Number of blades 2 Diameter 1730 mm Type Fixed pitch wood ...

Page 10: ... in engine cowling Capacity of each wing tank 50 L Total capacity 100 L Oil System Oil system type Forced with external oil reservoir Oil Lubricant specifications and grade are reported into the Rotax Operator s Manual and in its related documents Oil Capacity max 3 0 litres min 2 0 litres COOLING Cooling system Mixed air and liquid pressurized closed circuit system Coolant Coolant type and specif...

Page 11: ...rra MA I NTE NA NCE MA NUA L SECTION A GENERAL pag A 6 MAXIMUM WEIGHTS Maximum Takeoff weight 450 kg Maximum Landing weight 450 kg STANDARD WEIGHT Standard empty weight 289 kg SPECIFIC LOADINGS Wing loading 39 kg m2 Power loading 4 6 kg hp ...

Page 12: ...ONTROL SETTINGS 5 5 1 STABILATOR SETTING 5 5 2 TRIM TAB ADJUSTMENT 5 6 AIRCRAFT ALIGNMENTS 6 6 1 DATUM 7 6 2 NOMINAL DISTANCES 7 7 WEIGHING AND DETERMINATION OF VERTICAL CG 8 8 CORROSION PREVENTION 10 9 SERVICE BULLETINS 11 10 SERVICING 12 11 LUBRICATION 14 11 1 INTRODUCTION 14 11 2 LUBRICATION POINTS SEE FIG B 6 B 7 14 12 INSPECTION 17 13 INSPECTION 18 13 1 INTRODUCTION 18 13 2 PERIODIC INSPECTIO...

Page 13: ...r chock the wheels if chocks are available In severe weather and high wind conditions aircraft tie down is recom mended Tie ropes should be secured to the wing tie down fittings located under each wing 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 possi ble weathervaning...

Page 14: ...IGURE B 1 REAR LIFTING POINT In case of it would be necessary to lift the nose gear we suggest you to remove the engine s cowling and then acting on the engine s mount lift the aeroplane As general rule apply force to aircraft structure only on main struc tural elements such as frames ribs or spars WARNING ...

Page 15: ...inal levelling act as follows Slide off one of the two seat to get the access to the two seat track s supporting trusses Place longitudinally a spirit or water level over the two supporting trusses using if necessary a straight piece of wood as indicated into figure B 2 Adjust the aircraft s tilt through shims placed under wheels or by regulating tire pressure 4 2 TRANSVERSAL LEVELLING With one se...

Page 16: ...ILATOR SETTING 5 2 TRIM TAB ADJUSTMENT The following procedure lists the operation to be carried out to adjust the trim tab excursion Set the stabilator in its zero position and lock it in this position Turn the Master switch ON Trim to maximum pitch up Adjust thread of hinged control rod until tab is deflected down wards 9 use a protractor or measure downward displacement of trailing edge 9 is ap...

Page 17: ...P2002 Sierra SECTION B MA I NTE NA NCE MA NUA L pag B 6 2st Edition April 22th 2008 INSPECTION SERVICING 6 AIRCRAFT ALIGNMENTS FIGURE B 4 ALIGNMENTS C A A B C C D D B A D C C ...

Page 18: ...the access it is necessary to remove the engine s upper cowling C C On the stabilator upper surface is the rivet shared be tween the composite tip and the tubular spar rivet lines D D On the fin s skin is the upper aft rivet It shared between the upper rib and the rear spar rivet lines 6 2 NOMINAL DISTANCES The aim of the alignment control is mainly to compare the measures taken on both sides and ...

Page 19: ...s to most forward position h Flaps retracted 0 i Control surfaces in neutral position j Position scales min capacity 200 kg under each tire LEVELLING a Level the aircraft see par 4 Levelling WEIGHING a Record weights of individual scales b Calculate empty weight DETERMINATION OF CG a Drop a plumb bob tangent to the wing s leading edge as indicated into fig ure B 5 Trace a reference mark on floor b...

Page 20: ...d from rib n 7 4 2 1 3 6 5 7 W2 A W1 B 100 D D D 1370 W1 W2 Reference line WEIGHT AND CG DETERMINATION TABLE Kg metres Fwd wheel weight W1 Distance from bob to Lh wheel AL Lh main WL Rh wheel AR Rh main WR Average distance AL AR 2 A W2 WL WR Distance from bob to nose wheel B Empty weight We W1 W2 D W A W B We 2 1 ________meters C G position as wing chord D D 1 37 100 FIGURE B 5 WEIGHT BALANCE ...

Page 21: ... 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 par ticl...

Page 22: ...002 Sierra SECTION B MA I NTE NA NCE MA NUA L pag B 11 2st Edition April 22th 2008 INSPECTION SERVICING 9 SERVICE BULLETINS NO DESCRIPTION CL N C VALIDITY O Optional P Prescribed R Recommended F Voluntary ...

Page 23: ...Fuel tank vents Check vents for obstruction see sect E Fuel sys tem 7 Battery Check electrolyte level 8 Fuel filter Remove and clean the fuel filter built in the electric pump 9 Engine oil Replace oil and filter see ROTAX 912ULS Maintenance Manual initially after the first 25 hours 10 Brake fluid Check level of brake fluid in the master cylinder lo cated below the left seat Add fluid as needed usi...

Page 24: ... 2st Edition April 22th 2008 INSPECTION SERVICING 13 Airspeed system drain Slide off the left seat disconnect the hose fit tings and let drain the system 14 Tyres Check condition and maintain proper tyre pressure FIGURE B 6 INSPECTION POINTS A s n e e d e d ...

Page 25: ... e g ESSO BEACON 325 11 2 LUBRICATION POINTS SEE FIG B 7 B 8 1 2 Rudder hinges 3 4 Rudder control cable terminals 5 Stabilator control rod terminals 6 7 Stabilator support bearings 8 9 Trim tab hinges 10 Tab control push rod terminals 11 Stabilator pass through rod 12 Stabilator control rod inside cabin 13 14 Aileron hinges 15 Differential ailerons hinges 16 Aileron control pushrods 17 Aileron con...

Page 26: ...P2002 Sierra SECTION B MA I NTE NA NCE MA NUA L pag B 15 2st Edition April 22th 2008 INSPECTION SERVICING FIGURE B 7 LUBRICATION POINTS ...

Page 27: ...P2002 Sierra SECTION B MA I NTE NA NCE MA NUA L pag B 16 2st Edition April 22th 2008 INSPECTION SERVICING FIGURE B 8 LUBRICATION EVERY 100 HOURS ...

Page 28: ...ss to stabilator torque tube and attachments to control lever attachment of vertical stabilizer aft spar rudder bellcrank trim actuator and pushrods 4 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 actua tor Remove the seats to get the access to the ai...

Page 29: ...anual B Periodic inspections at every 100 hours C Special inspections added to normal periodic D Singular inspection when aircraft has been exposed to fortuitous events that may have damaged one or more of its components If aircraft is rarely used inspection at 100 hours must be performed yearly Replacement of parts subject to usage limitations are specified in par 14 2 Inspections and checks unle...

Page 30: ...ning to the aircraft group or system It is suitable to use TECNAM prepared inspection checklists 13 3 SERVICING REQUIREMENTS NATURE OF INSPECTION INSPECTION INTERVALS HRS 100 Special ENGINE COMPARTMENT 1 Remove cowling and check for fuel oil and coolant leaks clean engine compartment 2 Visually inspect electric pump connections 3 Visually inspect engine mount and silent blocks attachments 4 Visual...

Page 31: ...ical connections 600 6 Check torque tube levers and attachments for flaps control 7 Check resin control lever for trim actuator 600 8 Check trim control levers and pushrods for integrity and play 9 Check rudder pedals for integrity and play 10 Check control stick group for integrity and play 11 General check for proper tension level for control cables 600 MOVING SURFACES 1 Visually inspect integri...

Page 32: ...structure 600 5 Check attachment between vertical stabilizer and tail beam 600 6 Check integrity and fastening of stabilizer support assy 600 7 Check integrity and general condition of transparent surfaces and canopy 8 Check canopy rails and ball bearings for smooth movements 9 Check electric circuit wiring and antennae attachments from in side of tailcone 600 10 Visually check the Wing Carry Thro...

Page 33: ...n and state of rubber disks 6 Inspect wheel for condition and fastening 7 Remove wheel clean and grease wheel bearings 600 c 8 Remove nose gear assy for general safety check and inspection 1200 9 Check integrity of fairing and fairing attachments L INSTRUMENT PANEL 1 General inspection of operation of flight and engine instruments 2 Check acoustic stall warning if installed 3 Check compass alignme...

Page 34: ...CHMENT BOLTS 4 3 1 Nm 6 10 4 Nm 8 24 6 Nm Attention bolts connecting propeller to support flange albeit 8 must be tightened to 18 Nm TIGHTENING MOMENT FOR AN ATTACHMENT BOLTS MIN MAX 6 35 9 Nm 10 Nm 7 94 11 Nm 16 Nm 9 52 18 Nm 22 Nm CONTROL CABLES TENSION FOR AILERON AND RUDDER VALUE 20 dN 2 dN TIRE PRESSURE NOSE 15 PSI 1 0 BAR MAIN 23 PSI 1 6 BAR CONTROL SURFACES TRAVEL Ailerons Up 18 down 15 2 S...

Page 35: ...IGGING OF WING 3 2 1 FLAP CONTROL SEE FIG C 4 5 2 2 AILERON CONTROL SEE FIG C 5 5 3 HORIZONTAL TAIL 7 3 1 STABILATOR BALANCE 10 4 VERTICAL TAIL 10 5 FUSELAGE 12 6 LANDING GEAR 15 6 1 REMOVAL OF THE MAIN LANDING GEAR WHEEL SEE FIG C15 17 6 2 REMOVAL OF THE MLG WHEEL ROLLER BERINGS SEE FIG C16 19 6 3 NOSE LANDING GEAR 20 6 4 NLG WHEEL REMOVAL SEE FIG C 18 21 ...

Page 36: ... edge 2 is attached to the front spar 5 while flap 3 and aileron 4 are at tached to rear fake spar 6 through two hinges each The torsion box as shown in figure C 2 and with reference to numbers in paren thesis consists of a main spar 5 and a fake spar 6 that make up its front and rear vertical walls A series of ribs 7 and wrap around panels complete the structure Front and aft spars are complete w...

Page 37: ... wing s leading edge is an integrated aluminium fuel tank with individual filler cap Fuel tanks vent through tubes exhausting in the wing tip trailing edge 2 RIGGING AND DE RIGGING OF WING A Drain fuel tank using drain tank and closing opposite side tank fuel circuit B Remove the wing s composite root leading edge C Remove all of the wing to fuselage fairings D Remove the fuel tank outlet inspecti...

Page 38: ...luggage compartment floor to get the access to the aileron control circuit I Disconnect aileron control see fig C 5 by removing pins 4 that connect the small bar 3 to the pushrods 5 J While supporting the wing release at first the rear spar pin and then the two main spar s pins K Replace pins in their original location and cap fuel lines Reverse above procedure for reinstallation paying close atte...

Page 39: ...wo push pull rods controlling flap movement feature an adjustable linkage just before the roller bearings allowing trailing edge alignment FIGURE C 4 FLAP CONTROL 2 2 AILERON CONTROL SEE FIG C 5 Aileron control system uses push pull rods and bellcranks inside wing and steel cables and pulleys inside fuselage Layout of flight control system inside cabin includes two pairs of pulleys which transmit ...

Page 40: ... s trailing edge Through access panels located on wing s bottom check that the bellcrank lever is in neutral position i e the inside arm at right angle with spar axis To remove a wing 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 wings are removed It is however recommended that periodic...

Page 41: ...side may be carried out adjusting trim tab located on left aileron trailing edge 3 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 fuse lage at the desired pitch setting The stabilator structure see fig C 6 is made up by an aluminium spar 1 to which a series of ribs 2 ar...

Page 42: ...tor connection to facilitate insertion and gently tapping parts into position being careful not to deform outward ribs The stabilator control system is push pull type see fig C 7 and is controlled from the cabin via the control sticks Control is transmitted through a push pull rod 1 linked to a bellcrank 2 and a shaft 3 that runs through the tail cone supported at midsection by a bracket 4 and con...

Page 43: ... Longitudinal trim control is available in two versions in dependence with the aircraft configuration One of them consists in a rocker switch located on the cen tral tunnel between the two seats The second configuration has two switches on the top of each stick handle For this configuration it is possible to select the left or the right controls for operation For both configuration it is available...

Page 44: ... 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 con servative with respect to stability 4 VERTICAL TAIL The vertical tail consists of an all metal light alloy structure fig C 9 Vertical stabilizer tip is made of two pieces one fixed to the fin and the other as a part of the rudder The...

Page 45: ...ntrol system layout fig C 10 is a steel cable driven and circuit terminates on rudder pedals and then on the nose wheel steering lever Rudder pedals 1 are attached to two pushrods 3 that 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 ef fective realignment of the r...

Page 46: ...the cabin s bottom section Forward truss structure drawing fig C 11 shows location of attachment points for wing s main spar 1 wing s rear spar 2 tail cone 4 main landing gear 5 engine mount 3 flap torque tube 7 stabilator bellcrank 6 throttle support 8 and pulley support for cable driven aileron control Seat supports and safety har ness attachment points are also shown The aft part of the fuselag...

Page 47: ...2st Edition April 22th 2008 P2002 Sierra MA I NTE NA NCE MA NUA L SECTION C AIRFRAME pag C 13 FIGURE C 11 CABIN TRUSS FIGURE C 12 TAIL CONE ...

Page 48: ...p and two at each side Seats are made out of metal tubing framework with fabric covered foam pad ding The two seats can be independently adjusted by sliding backward and for ward 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 finish...

Page 49: ...l spring leaf to the edge of the outer keel son 2 via a light alloy tie 6 while a single bolt 8 and nut secures the inboard end of the leaf spring to inner keelson 3 FIGURE C 13 MAIN LANDING GEAR Wheels are cantilevered on gear struts and feature hydraulically actuated disc brakes see fig s C 14 C 15 controlled by a lever 1 located on cabin tunnel between seats Main gear wheels mount Air Trac type...

Page 50: ...tally be closed FIGURE C 14 BRAKES CIRCUIT To remove each leaf spring strut proceed as follows A Remove the luggage compartment floor B Hoist aircraft onto supports C Disconnect each spring leaf brake fluid line unscrewing the upper links from the Tee connection 6 Placing temporarily caps on lines to prevent spillage D Loosen the two external bolts and unfasten the aluminum tie part 6 fig C 13 tha...

Page 51: ... 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 6 1 REMOVAL OF THE MAIN LANDING GEAR WHEEL SEE FIG C15 Removal of a single wheel is carried out as follows A Hoist aircraft onto supports see Sect B B Release...

Page 52: ...2st Edition April 22th 2008 P2002 Sierra MA I NTE NA NCE MA NUA L SECTION C AIRFRAME pag C 18 FIGURE C 15 REMOVAL OF THE MLG WHEEL ...

Page 53: ...necessary when excessive friction occurs during wheel motion Procedure is as follows A Pull out the wheel 1 from the axle 3 by unscrewing the nut 2 B Remove bushing 4 and the plates 5 C Remove the roller bearing 6 Clean the bearings accurately using appropriate solvent and wipe wheel rim side Grease using FIAT ZETA2 FIGURE C 16 REMOVAL OF THE MLG WHEEL ROLLER BEARINGS 6 3 5 1 4 5 6 2 ...

Page 54: ...nges 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 5 and a spacer 6 it hinges on the strut leg and is braced by a rubber disc shock absorber 3 FIGURE C 17 NOSE LANDING GEAR LEG ...

Page 55: ...s 6 and 5 C To remove the rear upper fairing 4 loosen the screws 1 D Unscrew nuts 7 and remove washer from wheel axle E Unscrew bolt 8 in gear lever housing F Remove the rear fairing 9 Reverse procedure to reinstall Avoid to damage the fiberglass fairing by not tightening screws excessively To remove nose wheel proceed as follows A Remove the fairings 5 6 and 9 B Loosen bolts 10 11 and 13 C Detach...

Page 56: ...Edition April 22th 2008 P2002 Sierra MA I NTE NA NCE MA NUA L SECTION C AIRFRAME pag C 22 FIGURE C 18 NLG WHEEL REMOVAL SUMMARY OF TIRE INFLATION PRESSURE Nose tire 15 psi 1 0 bar Main tires 23 psi 1 6 bar ...

Page 57: ... pag D 1 SECTION D POWERPLANT TABLE OF CONTENTS 1 POWERPLANT 2 1 1 COWLING 2 1 2 ENGINE MAIN FEATURES 3 2 GENERAL SERVICING PROCEDURES 4 2 1 IDLE SPEED SYNCHRONIZATION 4 2 2 ORDINARY SERVICING 4 3 PROPELLER 4 3 1 PROPELLER REMOVAL 4 3 2 PROPELLER INSTALLATION 4 3 3 PERIODIC INSPECTION 5 ...

Page 58: ... 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 D 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 FIGURE D 1 ENGINE S COWLING Cam ...

Page 59: ...p drive is via reduction gear with integrated shock absorber and overload protection Electric starter integrated AC generator and mechanical fuel pump are stan dard Technical 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 cw ...

Page 60: ...ecial lacquer coating 3 1 PROPELLER REMOVAL To remove propeller use the following procedure A Remove screws holding spinner dome to spinner bulkhead B Remove safetying C 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 3 2 PROPELLE...

Page 61: ...before takeoff let the engine run for a few minutes and after turning it off carry out further inspection tightness overall state etc FIGURE D 3 PROPELLER INSTALLATION 3 3 PERIODIC INSPECTION Refer to specific subsection in Periodic Inspection Schedule of Section B For further information refer to Owner Manual furnished by the manufacturer ...

Page 62: ... E 1 SECTION E SYSTEMS TABLE OF CONTENTS 1 FUEL SYSTEM 2 2 INSTRUMENTS 5 2 1 ENGINE INSTRUMENTATION 6 3 PITOT AND STATIC SYSTEM 7 4 EXHAUST MANIFOLDS 8 5 CARBURETTORS HEAT AND CABIN HEAT SYSTEMS 8 6 BRAKE SYSTEM 10 6 1 DRAINING AND REPLACING BRAKE FLUID 10 6 2 BRAKES LINING REPLACEMENT 11 ...

Page 63: ...h a cabin installed shutoff valve 5 A strainer cup with a drainage valve 6 Gascolator is located on the engine side of the fire wall Fuel level indicators for each tank are located on instrument panel each fuel tank is equipped with individual sensor floats 3 Fuel feed is through an engine driven mechanical pump 8 and through an electric pump 7 Electric pump is equipped with a thin mesh filter 7a ...

Page 64: ...ecessary to remove the hose 4 after releas ing nut 3 FIGURE E 2 TANK OUTLET AND FILTER Potential fuel tank leaks can be readily detected by the visible fuel traces Re pairs can eventually be made only if cracks are small and using specific glue type 1422 B2 DMS 2082 after emptying tank and thoroughly and repeatedly rinsing the area with water Periodically check fuel tank vents to ensure that their...

Page 65: ...2st Edition April 22th 2008 P2002 Sierra MA I NTE NA NCE MA NUA L SECTION E SYSTEMS pag E 4 The figure E 3 shows a schematic of the fuel system FIGURE E 3 FUEL SYSTEM LAYOUT ...

Page 66: ... protection fuses throttle knobs Individual instruments may be accessed for removal by releasing 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 1 Do not over tighten b...

Page 67: ...An electric oil temperature indicator is installed The sensor is located on the oil pump tube and is marked with TO on the pump flange FIGURE E 5 PRESSURE AND OIL TEMP SENSORS An oil pressure instrument is installed Sensor is located on oil tube Cylinder head temperature sensors are located on cylinders 2 or 3 and are linked with relative instrumentation ...

Page 68: ...eriodic Inspection Table found in Section B 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 3 and static ports 6 clearing possible obstructions FIGURE E 6 PITOT AND STATIC SYSTEM For safety reasons and to ensure correct airspeed readings it is im...

Page 69: ... HEAT AND CABIN HEAT SYSTEMS The heating system see Fig E 6 exhaust vents are 1 Hot air vent located near the rudder pedals 1 2 De frost vents located in proximity of the windshield 2 The heating system is made of A heat exchanger 3 a hot air shut off valve 4 and by the above mentioned exhaust outlet The shut off valve is controlled by a knob located on the instrument panel Carburettors are fed by...

Page 70: ... NA NCE MA NUA L SECTION E SYSTEMS pag E 9 to avoid any kind of exhausted gas intrusion from the muffler into the heating system Inspection should also recommended to the cabin hot air shut off valve FIGURE E 8 CARBURETTOR HEAT AND CABIN HEAT SYSTEMS ...

Page 71: ...located between seats and when closed with lever pulled keeps circuit under pressure and aircraft s parking brake on FIGURE E 9 BRAKING SYSTEM 6 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 UNIVIS J43 until level reaches bottom of re...

Page 72: ...n for other brake Hydraulic fluid may also be replaced using gravity after disconnecting the circuit This method is however more laborious and less reliable 6 2 BRAKES LINING REPLACEMENT When the thickness of lining is less then 2 4mm brake pads should be replaced using the following procedure referring to the fig E 10 A Make sure that the parking brake is released B Remove fairings to expedite op...

Page 73: ...ICAL SYSTEM TABLE OF CONTENTS 1 GENERAL 2 2 BATTERY 4 2 1 BATTERY REMOVAL 4 2 2 BATTERY CHECK 4 2 3 BATTERY INSTALLATION 4 3 GENERATOR 5 4 REGULATOR RECTIFIER 5 5 EXTERIOR LIGHTING 6 6 1 POSITION LIGHTS OPTIONAL 6 6 2 LANDING LIGHT OPTIONAL 6 6 3 STROBE LIGHT OPTIONAL 6 6 STALL WARNING SYSTEM OPTIONAL 6 7 FLAP SYSTEM 7 ...

Page 74: ... 12 Volt DC circuit An 18 Ah lead battery provides the energy necessary to start the engine and acts as an emergency stand by supply of electrical power for electrical components in case of generator malfunction A single phase generator connected to a regulator rectifier supplies DC power to the bus bars and to recharge the battery FIGURE F 1 WIRING DIAGRAM ...

Page 75: ...gure F 1 The following table lists a legend of electrical components POS DESCRIZIONE 1 Battery 2 Fuse 3 Ammeter 4 Master switch 5 Ignition systems 6 Master relay 7 Starter 8 Regulator rectifier 9 Generator 10 Ignition switches 11 Flap switch 12 Flap s actuator 13 Voltmeter 14 Trim tab switch 15 Trim tab actuator 16 Trim tab position indicator 17 Strobe light switch 18 Strobe light power supply 19 ...

Page 76: ...e 2 2 BATTERY CHECK Battery check should be performed every 100 hours or more frequently if operating in warm climates A Unscrew battery caps B Use a densimeter to check the electrolyte and compare value with the fol lowing table Densimeter reading Charge 1 280 100 1 250 75 1 220 50 1 190 25 1 160 Dead battery An acceptable value should be between 1 250 and 1 280 If densimeter read ing is below ac...

Page 77: ...ies alternate current to a regulator rectifier Servicing or repair of the generator must be carried out only by authorized personnel 4 REGULATOR RECTIFIER A regulator rectifier type DUCATI 965 345 is installed on the firewall with in the engine compartment To remove it proceed as follows A Master switch OFF B Disconnect wires from terminals of component to be removed C Unscrew and release componen...

Page 78: ... is protected by a 10 A circuit fuse 6 3 STROBE LIGHT OPTIONAL The strobe light is installed on top of the vertical stabilizer Strobe light is activated by a switch and is protected by a fuse Switch and breaker are positioned on the instrument panel The signal reaches a strobe light trigger circuit box positioned in the tailcone just behind the baggage compartment and from here reaches the light 6...

Page 79: ...ion Mi croswitches positioned within the actuator automatically interrupt current flow when flaps reach all out or all in positions A bowden type cable issuing from the flap actuator controls flap position in dicator located on the right side of the instrument panel Flap extension shunt is supplied by the primary bus bar through a breaker and is located on the instrument panel Shunt must be activa...

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