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4.4 Horizontal Tail

P92 Echo Super

Maintenance Manual

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.
The stabilator structure (see fig.4-5) is made-up of an aluminum tubular spar (1) to which a series of ribs (2) and an
aluminum leading edge (3) are riveted. Dacron heat-shrink wrap-around material covers structure.
A trim tab (4) provides stick force adjustment and longitudinal compensation through an electric actuator co ntrolled 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.

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Figure 4-5 Stabilator

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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-pull 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 bellcrank (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 bellcrank assembly (5).
All significant transmission elements such as bellcranks, pushrods, supports and hinges can be easily accessed and
inspected.

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Revision Date: 10-29-2007
Revision Number: 3.01

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Содержание P92 Echo Super

Страница 1: ......

Страница 2: ...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 Revision No Date released Chapters Approved By 1 0 03 30 2005 All Tecnam 2 0 12 30 2006 All Tecnam 2 01 04 11 2007 1 Tecnam 2 02 06 13 2007 2 Tecnam 2 03 08 12 2007 3 Tecnam 3 00 10 29 2007 All Tecnam 3 01 02 02 2009 3 Tecnam NOTE Extensiv...

Страница 3: ...7 47 10 29 2007 13 10 29 2007 48 10 29 2007 14 10 29 2007 49 10 29 2007 15 10 29 2007 50 10 29 2007 16 10 29 2007 51 10 29 2007 17 10 29 2007 52 10 29 2007 18 10 29 2007 53 10 29 2007 19 10 29 2007 54 10 29 2007 20 10 29 2007 55 10 29 2007 21 10 29 2007 56 10 29 2007 22 10 29 2007 57 10 29 2007 23 10 29 2007 58 10 29 2007 24 10 29 2007 59 10 29 2007 25 10 29 2007 60 10 29 2007 26 02 02 2009 61 10 ...

Страница 4: ... 5 4 6 33 4 4 01 3 4 7 3 2A 4 B C 3 0 A2 B 7 D E 1 FA2 7 A 9 9 FA2 7 4 6 G G 8 9 2 0 C D 4 3 E28 B F GH2 32 3 IH B 1 42 0 J 42 F 4 2 F H 8 2A I 26 2 J3 K 63 G A A2 H A 9 9 5L1 6 A 120 5 0 K L M LH B 0 F N B L O 2PL Q R 4N B S292H B 4 7 C A 3 21 G 2 AA 2 7 4 7 M NA J 9O12A A 7 4 7 4 G A 3 A B 4 7 7 I A1 B C A2 B B J J 72 2 3 1K J 4 H FA 9 C M J3 P 1 F 292 6 6 2 9 42 7 24 92 6 2 9 4 B ...

Страница 5: ... 2 GA 22 J3 4 4 P 5 6 22 J3 7 4 U 6 33 16 7 4 K 9 16 7 4 6A 3 L1 6 A 7 4 58M 7 O W 2 1 92 O GH2 0C SDXDO ODYZ OY DEAYEOMDZ 0J A B 0 7 Q 2A 33 9 2A 33 AF V U 0 IH 8 4 H 0 H2 4 H M H O H 7 7 A J 3 A J 3 G 44 C 2 4 H O H J I 2H B2 J S L B K2 6 7 P D 7 7 P K W 3 G16NJ VF 3 7 6 Z 2B2 E2 9 H 3 2B2 3 B L Q 22H O 2 92 2 Q 22H 8 422L 3 HH Q O 2 3H 8 2 2 A0 265 B B C V3 7H B 5 D 0 A1 2 7P 5 Revision Date 10...

Страница 6: ...9 63 G J T 31 9 BP H B K 63 G J T 6 92 BU F60 56 1C1 0D G 9 H5 I 1 5 65 5 1 B U D A G G 6 22 G 6 2 A A J3 H U T J T W 3W H U 4 5 AF AA3 H U 7 5 AF AA3 GA H U B C J F A H U H C J1 A F A H U P M 2V AGF H U U 012 2 H4 U 03 62 H4 U A D 2A A A H4 U CF T H4 U A 3 FA H7 U 4 S2 J3 1 3 H7 U 7 G 6 A A H7 U B 01 3 A T2 HB U H 3 A T 2 W HB U P C 3 2 2A W 3 V A T HH U U T 3 2 W HH U M 6 221 2 HH U Q9 A G A 63 ...

Страница 7: ... for correct servicing procedures Scrupulously following instructions will insure that your P92 Echo Super 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 1 will allow you to reach any selection quickly Information contained herein is based on available data at time of publication possible v...

Страница 8: ...ore 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 Maintenance Manual contains the following sections 1 Introduction 2 General 3 Inspection and Servicing 4 Airframe 5 Powerplant 6 Systems 7 Markings and Placards 2 1 Certification...

Страница 9: ...505 m 4 937 Aileron chord 0 385 m 1 263 2 2 1 2 Fuselage Overall length 6 4 m 21 Overall width 1 1 m 43 Overall height 2 5 m 8 2 2 2 1 3 Empennage Stabilator span 2 900 m 9 5 Stabilator area 1 972 m2 21 2 ft2 Stabilator cord 0 680 m 26 Vertical tail span 1 230 m 3 9 Vertical Stabilizer area 0 720 m2 2 36 sq ft Rudder area 0 350 m2 1 48 sq ft 2 2 1 4 Landing Gear Wheel track 1 800 m 5 9 Wheel base ...

Страница 10: ...sumption 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 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 35 liters 9 2 gal optional 45 liters 11 9 gal Total capacity 70 liters 1...

Страница 11: ... tecnam co nz the following information Aircraft Make Model Serial Number Engine Make Model Serial Number Date of Inspection Total Time Airframe Engine Description of the un airworthy items found Owner of Aircraft 2 6 Source to Purchase Parts Spare parts can be ordered from Tecnam Australasia Ltd info tecnam co nz or from your local dealer 2 6 1 List of Disposable Replacement Parts Air filter Rota...

Страница 12: ...aps 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 Fa...

Страница 13: ...raft 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 aircr...

Страница 14: ...low AILERONS starting from tip line up Up 20 Down 15 2 STABILATOR Up 16 Down 3 1 TRIM Stab at 0 see fig below 2 12 1 RUDDER RH 25 LH 25 1 FLAPS max travel 0 38 1 CONTROL CABLE TENSION for all 20 daN 45 2 daN 4 REFERENCE MARK FIGURE 3 1 STABILATOR ADJUSTMENT 3 4 2 Trim tab adjustment Travel adjustment of trim tab on stabilator should be carried out as follows Move stabilator to neutral 0 degrees an...

Страница 15: ... B SPINNER BACK PLATE UPPER POINT A A LAST RIVET ON THE LOWER SIDE OF THE REAR WING SPAR C C FIRST RIVET BETWEEN THE TUBULAR SPAR AND THE OUTERMOST RIB UPPER REAR RIVET ON ALUMINIUM SKIN i e The rivet in common between the fin s rear spar and the upper rib G C C F F Main Wheels Axle Line A B 4690 20 184 6 A C 4140 20 163 A C 4140 20 163 C G 1800 20 70 87 C G 1800 20 70 87 F F 1880 20 74 ...

Страница 16: ...rward 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 Drop a plumb bob tangent to the wing s leading edge in the un tapered section of the wing at about one meter 40...

Страница 17: ...e 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 Kg Fwd wheel weight W1 Main wheel left WL Main wheel ...

Страница 18: ...omponents main gear steel spring requires particular care b For aluminum parts treatment consists in mechanically removing as much as possible corrosion byproducts 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 softe...

Страница 19: ...rease 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 3 10 1 Lubrication Points 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 co...

Страница 20: ...P92 Echo Super Maintenance Manual Figure 3 3 Lubrication points Figure 3 4 Every 50 hours 20 Revision Date 10 29 2007 Revision Number 3 01 ...

Страница 21: ...P92 Echo Super Maintenance Manual Figure 3 5 Every 100 hours 21 Revision Date 10 29 2007 Revision Number 3 01 ...

Страница 22: ...ler hub 3 11Inspection 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 main...

Страница 23: ...xcessive 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 lo...

Страница 24: ...Bolts for improper torque and lack of safetying 3 12 9 Radio group 1 Check radio and electronic equipment for improper installation and insecure mounting 2 Check wiring and conduits for improper routing insecure mounting and obvious defects 3 Check bonding and shielding for improper installation and poor condition 4 Check antenna including trailing antenna for poor condition insecure mounting and ...

Страница 25: ...lage fitting bolts NAS 1308 28 100 Nm 73 Ft Lb 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 13Torque 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 ...

Страница 26: ...or 10 yrs 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 21 11 910 002 21 11 910 003 5 yrs Fuel system flexible hose TECNAM pn s 21 11 311 1 21 11 311 2 21 11 340 1 21 11 324 1 21 11 330 2 yrs Liquid cooling system flexible hose 92 11 105 1 92 11 105 2 92 11 105 3 92 11 105 4 2 yrs Revision n 1 2nd February 2009 ...

Страница 27: ... 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 reference to numbers in parenthesis consists of a main spar 4 and a fake spar 5 ...

Страница 28: ...immediately below the tanks 4 1 1 Installing and reinstalling the wing Procedure for removal of wing and strut is as follows 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...

Страница 29: ...se position is adjusted via an electric linear actuator 4 governed by a switch on instrument panel Two push pull rods 6 are connected to the ends of the torque tube 1 and are located in the area between wing and fuselage thus facilitating inspection The two push pull rods controlling flap movement feature an adjustable linkage just before the roller bearings allowing trailing edge alignment Figure...

Страница 30: ... s bottom check that the bellcrank 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 app...

Страница 31: ...lator 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 be...

Страница 32: ...ntering 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 bellcrank 9 To remove the stabilator torque tube disconne...

Страница 33: ... 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 5 V...

Страница 34: ...removable for overhang To remove rudder after removing tail fairing disconnect cables from bellcrank unfasten lower support flange from stabilizer and uncouple rudder with downward motion 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 trans...

Страница 35: ...P92 Echo Super Maintenance Manual Figure 4 9 Rudder control 35 Revision Date 10 29 2007 Revision Number 3 01 ...

Страница 36: ... 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 bellcrank 7 throttle support 8 and pulley support for cable driven aileron control 9 Seat supports and safety harness attachment points are also shown Fi...

Страница 37: ...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 only water mild detergent and chamois All parts in Perspex material must ne...

Страница 38: ... 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...

Страница 39: ...lt 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 trapp...

Страница 40: ...nto supports Release parking brake Remove fairing 1 by releasing bolt 2 and the three Phillips screws 3 that hold fairing to plate Remove bolt 4 and cup 5 Remove wheel lock nut 6 Unscrew 4 brake disc assembly bolts See Figure 4 14 and Figure 4 15 8 Carefully remove wheel assembly with both hands Disc bolts Figure 4 14 40 Revision Date 10 29 2007 Revision Number 3 01 ...

Страница 41: ... TECNAM P92 Echo Super Maintenance Manual v 3 Figure 4 15 Removal of main gear wheel 41 Rev1s1on Date 10 29 2007 Revision Number 3 01 ...

Страница 42: ...tion Procedure is as follows Using an appropriate tool remove Seeger type snap ring Remove the two ring grease seals and the felt grease seal Remove the cup bearing 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...

Страница 43: ...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 4 9 Removal of nosegear fairing and wheel To remove the nose gear fairings proceed as follows To remove front portions of fairing 5 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 nut...

Страница 44: ...he two wheel forks 12 from each other Remove wheel axle Remove the wheel 13 4 10To remove nose wheel proceed as follows Remove the fairings 5 6 and 9 Loosen bolts 10 11 and 13 Figure 4 19 Removal of nosegear fairing 4 11Tire inflation pressure Nose tire 15 psi 1 0 bar Main tire 23 psi 1 6 bar ...

Страница 45: ...de flap attachment bolt 10 4 Nm 13 Left side flap attachment bolt 10 4 Nm 14 Right side aileron control attachment bolt 6 Nm 15 Left side aileron control attachment bolt 6 Nm 16 Right side stabilator insertion bushing 17 Right side hemi stabilator attachment bolt 10 4 Nm 18 Left side stabilator insertion bushing 19 Left side hemi stabilator attachment bolt 10 4 Nm 20 Stabilator fake spar attachmen...

Страница 46: ... 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 Aluminium FG Aluminium Aluminium FG Cam lock A...

Страница 47: ...er and overload protection Electric starter integrated AC generator and mechanical fuel pump are standard 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 clockwise pilot s view Max temp Cylinder heads 135 C Fuel See ...

Страница 48: ...r 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 2 5 Propeller installation To install propeller follow procedure below Insure that propeller is correctly aligned with hub before ti...

Страница 49: ...nce Manual 5 2 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 49 Revision Date 10 29 2007 Revision Number 3 01 ...

Страница 50: ...hen 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 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...

Страница 51: ...P92 Echo Super Maintenance Manual Figure 6 1 Fuel System Figure 6 2 Gascolator 51 Revision Date 10 29 2007 Revision Number 3 01 ...

Страница 52: ...sed 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 Do not over tighten bolts as plastic instrument casing may break Insure hoses are free of...

Страница 53: ... on the oil pump tube and is marked with TO on the pump flange 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 Figure 6 6 Pressure and oil temperature sensors 53 Revision Date 10 29 2007 Revision Number 3 01 ...

Страница 54: ... 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 hos...

Страница 55: ...llowing see Fig 6 9 Hot air vent near rudder pedal bar 1 De frost vents near windshield 2 Heat exchanger 3 A 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 6 4 2 Carburetor heat if installed The system is also designed to direct carburetor air intake from scoop 5 and manifold 6 located on top...

Страница 56: ...P92 Echo Super Maintenance Manual Figure 6 9 Carburetor heat and cabin heat systems 56 Revision Date 10 29 2007 Revision Number 3 01 ...

Страница 57: ...s circuit under pressure and aircraft s parking brake on A check valve is installed 5 that provides braking action even if the parking brake valve 2 is shut 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 MI...

Страница 58: ...brake fluid Close reservoir and repeat operation 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 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 fair...

Страница 59: ...rect 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 sulfuri...

Страница 60: ...P92 Echo Super Maintenance Manual Revision Date 10 29 2007 Revision Number 3 01 60 Figure 7 1 WIRING DIAGRAM TYPICAL ...

Страница 61: ...ted just below the compass For N 30 60 E 120 150 Steer For S 210 240 W 300 330 Steer DATE RADIO ON AIRPATH 8 1 2 Parking brake valve The following placard 55x42mm is located on the central tunnel behind the two seats next to the parking brake shutoff valve 8 1 3 Engine throttle Two throttle control knobs are located on the instrument panel One positioned centrally while the other is on the upper l...

Страница 62: ...nstrument panel central area just below the left throttle control The cabin s heat control is marked with this placard 20x11mm 8 1 6 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 8 1 7 Trim switch The trim shunt control is located on the upper cent...

Страница 63: ...ipment installed on the a c the type and position of the fuses could vary from the above shown 8 1 9 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 8 1 10 Generator Master Starter On the lower part of the instrument panel are located in order The starter marked with a placard 19x11m...

Страница 64: ... 13 Usable fuel Located next to the two fuel level gauges are the two placards indicating the usable fuel for each tank 18x13mm Note For extended tanks the usable fuel per side is 45 liters or 11 9 gallons 8 1 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 Left Tank Usable Fuel 11 5...

Страница 65: ...ler caps is located a placard 57x120mm indicating the type of fuel and the total tank s capacity Note For extended fuel tanks the capacity is 45 liters or 11 9 gallons 8 1 16 Oil tank reservoir On the oil tank reservoir are present two placards 30x12mm indicating the type and quantity of engine s oil stored into the reservoir ...

Страница 66: ...d indicating the type of oil that must be used 8 1 19 Tire pressures On each steel spring leaf is a placard indicating the main tires inflating pressure 18x6mm On the nose gear is located the following placard indicating the nose tire inflating pressure 18x6mm 8 1 20 Identification plate The following placard is located on the pilot side of the empennage forward of the stabilator and made of stain...

Страница 67: ... placard will state the following 27x7mm NO SMOKING Next to the airspeed indicator is the following placard 6x52mm Maneuvering speed VA 84 KIAS On the pilot s panel a placard will state the following NO INTENTIONAL SPINS 67 Revision Date 11 29 2007 Revision Number 3 01 ...

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