Home

P92-JS - DigiSky

1. OFF E 1 FRICTION o B T H T E A 1 2 HEAT THROTTLE Figure 9 3A Central throttle control system with Carb Heat control lever Date Issue 3 rev 1 25 February 2015 FRICTIDN MT 4 40 D I THROTTLE Figure 9 3B Central throttle control system 9 22 P92 JS FLIGHT MANUAL EC M SUPPLEMENT N 5 NEW ANALOGICAL INSTRUMENTS PANEL 5 INTRODUCTION This section contains supplementary information for safe and efficient operation of the aircraft if equipped with the new analogical instruments panel 5 22 GENERAL No variations 5 3 LIMITATIONS No variations 5 4 EMERGENCY PROCEDURES No variations 5 5 NORMAL OPERATION No variations 5 6 PERFORMANCE No variations 5 7 WEIGHT AND BALANCE No variations Date Issue rev 1 25 May 2010 9 23 P92 JS lt lt TECNAM FLIGHT MANUAL SECTION 9 5 8 SYSTEMS The new analogical instruments panel is designed with a modular concept to improve the instruments visibility The new instruments panel is divided into three main parts The left part with the flight instruments central part with the avionic instruments and the right part with the engine instruments The following picture shown the new analogical instru
2. FIG 4 1 B Remove protection cap and check pitot mounted on left strut is unobstructed do not blow inside vents place protection cap inside aircraft Date Issue 3 25 May 2010 4 4 P92 JS COSTRUZSON AERONAJTICHE SECTION 4 TECNAM FLIGHT MANUAL NORMAL PROCEDURES C Left side leading edge and wing skin visual inspection D Left aileron visual inspection E Left flap and hinges visual inspection F Left main landing gear check inflation 14 psi 1 0 bar tire condition alignment fuselage skin condition G Horizontal tail and tab visual inspection H Vertical tail and rudder visual inspection I Right side main landing gear check inflation 14 psi 1 0 bar tire condition alignment fuselage skin condition L Right flap and hinges visual inspection M Right aileron visual inspection N Right leading edge and wing skin visual inspection O Check freedom of movement of stall detector microswitch on right side leading edge activate Master switch and check cabin acoustic warning signal is operative deactivate Master switch P Right side fuel filler cap check visually for desired fuel level and secure Right side tank vent check for obstructions Q Right side static port check for obstructions do not blow inside vents read note R Nose wheel strut and tire check inflation 11 psi 0 8 bar tire condition and condition of rubber shock absorber discs S Propeller and spi
3. 21 45 21 4 6 WEIGHT 004414 2502 0 02 21 CLERC PONI 22 NEW ANALOGICAL INSTRUMENTS 23 5S 23 C 23 23 54 5 290 0040 23 55 NORBMALOPERATION rias 23 56 PERFORMANCE cntntnecunnnt mira tmimitimintnimea taki 23 5 7 WEIGHT AND 23 ICONE STEN CNET 24 6 CHINESE AIRCRAFT FLIGHT MANUAL SUPPLEMENT 25 1 Placard am Chinese oir 26 Date Issue 3 25 2010 9 2 1 This P92 JS COSTRUZIONI AERONAUTICHE SECTION 9 TECNAM FLIGHT MANUAL SUPPLEMENTS SUPPLEMENT N 1 GARMIN GNS 430 GPS VHF COMM NAV INTRODUCTION section contains supplementary information for safe and efficient operation of the aircraft if equipped with a Garmin GNS 430 system 1 2 1 GENERAL The GPS GNS 430 Global Positioning System is an integrated system that contains a GPS navigation system in addition to a VHF COMM radiotransceiver and a VOR ILS receiver The system includes an antenna for GPS a receiver for GPS a VOR LOC antenna a VOR ILS receiver a VHF
4. T 7 2 2 cE 7 2 3 EMERGENCY PROCEDURES 0 00 0 9 2 4 NORMAL 6 6 0600 9 2 5 5 11 2 6 WEIGHT amp 0 14 seld suncg 14 2 7 O Y O TE O 15 DIFFERENTIAL BRAKE SYSTEM 18 3 5 18 3 1 GENERA 18 3 2 LIMITATIONS 18 3 3 EMERGENCY PROCEDURES 0000 18 P92 JS COSTRUZIONI AERONAUTICHE SEC TI ON 9 TECNAM FLIGHT MANUAL SUPLEMENTY 3 4 18 48 522 tici tle eui 18 3 6 WEIGHT AND 18 suns cM LU 19 CENTRAL THROTTLE CONTROL SYSTEM cens 21 TINTS SUC 21 4 1 GENERAL MM 21 Zo 21 43 EMERGENCY PROCEDURES ssssssssesesssesssssesssssesssseesssssessssnsneteneneeaes 21 44 NORMAL
5. Bowden cable The towing hook is a TOST 85 approved type Type Certificate No 30 230 1 Hook TOST E85 Date Issue 3 rev 1 25 February 2015 9 16 P92 JS TECNAM FLIGHT MANUAL 22 For further information please refer to the hook s Operating Manual for tow releases On the left door a rear view mirror is positioned to let the pilot to see the banner during towing MIRROR Date Issue 3 rev 1 25 February 2015 9 17 P92 JS FLIGHT MANUAL EC M SUPPLEMENT N 3 DIFFERENTIAL BRAKE SYSTEM 3 INTRODUCTION This section contains supplementary information for safe and efficient operation of the aircraft if equipped with the differential brake system 31 GENERAL No variations 3 2 LIMITATIONS No variations 33 EMERGENCY PROCEDURES No variations 3 4 NORMAL OPERATION No variations 3 5 PERFORMANCE No variations 3 6 WEIGHT AND BALANCE No variations Date Issue 3 rev 1 25 February 2015 9 18 P92 JS QTECNAM FLIGHT MANUAL SECTION 9 3 7 SYSTEMS Figure 9 2 shows the brake system schematic diagram The left and right wheel brakes are independent systems The system has a reservoir 4 visible from a little window on the baggage compartment The reservoir is directly connected to the brake master cylinders 3 Two flexible hoses connect the master cylinders on the co pilot s brake pedals to the master cylinders on the pilot
6. 200 a 150 1 T O WEIGHT gt 10 0 00 550 500 150 400 5 OAT C WEIGHT Kg OBSTACLE HEIGHT m Fig 5 4 TAKEOFF PERFORMANCE Date Issue 3 25 May 2010 5 7 P92 JS COSTRUZIONI AERONAJTICHE X FLIGHT MANUAL ORAN CLIMB RATE IN TAKEOFF CONFIGURATION Approved data CONDITIONS 550 kg 600 kg MTOW MTOW 159 159 Engine full throttle full throttle 56 KIAS 58 KIAS Climb rate in demonstrated ISA s l conditions is 850 ft min at maximum takeoff weight of 550 kg and 750ft min at maximum takeoff weight of 600 kg Date Issue 3 25 May 2010 5 8 P92 JS DOSTRUZIOM AERONAJTICHE SECTION 5 TECNAM FLIGHT MANUAL PERFORMANCE CLIMB PERFORMANCE CLIMB RATE IN CLEAN CONFIGURATION CONDITIONS Flaps 0 Engine full throttle Vy 70KIAS for 550kg MTOW Vy 73KIAS for 600kg MTOW R C residual 100 ft min 14000 12000 8000 10000 a Y lt 6000 x w 4 8000 o O 4000 p Q 4 6000 2000 4000 0 2000 0 2000 20 400 600 800 1000 1200 1400 20 10 0 10 20 30 RATE OF CLIMB ft m TEMPERATURE deg C Example Given O A T 17 C Pressure altitude 5600
7. MANUAL SYSTEMS LH FUEL QUANTITY INDICATUR RH FUEL QUANTITY INDICATUR LH FUEL QUANTITY SENSUR ELECTRICAL LINE ELECTRICAL LINE RH FUEL QUANTITY SENS R FUEL VENT YEE VENT 1 RH FUEL TANK RH FUEL TANK SHUT UFF VALVE FUEL PRESSUR INDICATUR gc FUEL VENT LH FUEL TANK LH FUEL TANK SHUT 9FF VALVE ELECTRICAL LINE o FIREWALL 4 MESH FILTER TANK DRAIN ELECTRIC FUEL PUMP FUEL PRESSURE SENDER FILTER MECHANICAL FUEL PUMP LH CARBURAT R T RH CARBURATOR FUEL PRESSURE SENDER RETURN LINE Fig 7 3 FUEL SYSTEM SCHEMATIC Date Issue 3 25 May 2010 7 7 P92 JS TECNAM FLIGHT MANUAL 570 ELECTRICAL SYSTEM The aircraft s electrical system consists of a 12 Volt DC circuit controlled by the Generator Switch located on the instrument panel Electricity is provided by an alternator and by a buffer battery placed in the fuselage tail section Generator light is located on the right side of the instrument panel WARNING If the ignition key is in the position L R or BOTH an accidental movement of the propeller may start the engine with possible danger for bystanders STARTER gt AG FUEL PUMP IGNITION SYSTEM ENCLOSURE IGNITION AND STARTER Pd STARTER RELAY e TRIM e Se L3L EXTERNAL POWER 4A LANDING LIGHT RECEPTACLE AMMETER amp amp D B _
8. E18 f Antenna ELT ELT 21 2 230 19 Fire extinguisher Fire fighting Enterprises 2 20 2 16 Ltd 51015 3 Fire extinguisher HALON H3G 1301 Altitude Encoder AK30 Ge 1 100 Date Issue 3rev1 25 February 2015 6 13 TECNAM MANUAL LEFT INTENTIONALLY BLANK Date Issue 3rev1 25 February 2015 P92 JS SECTION 6 WEIGHT amp BALANCE P92 JS SECTION 7 AIRCRAFT amp SYSTEMS DESCRIPTION TABLE OF CONTENTS INTRODUCTION 2 AIRFRAME E ins Mid 2 FLIGHT CONTROLS 3 INSTRUMENT Debe E Ee co 4 SEATS AND SAFETY HARNESS ceciren deee ener nne nennen ener 5 eg e 5 COMPARTMENT venini peer NH Eee eee e db dev 5 POWERPLANT vi 6 FUEL SYSTEM net vum ele dec Ele S rera Doe a eR Ever i eb uds 6 ELECTRICAL SYSTEM hr eer t ee vei epe ie e c eb edet 8 PITOT AND STATIC PRESSURE 5 5 5 10 M 11 8 000 2 11 PLACARDS OUTSIDE 22 2 0 9 60 6 tente 15 Date Issu
9. Date Issue 3 25 May 2010 7 4 P92 JS COSTRUZIONI AERONAUTICHE S E 7 MANUAL SYSTEMS THROTTLE FRICTION LOCK It is possible to adjust the engine s throttle friction lock by appropriately tightening the friction lock disk located on the instrument panel near the center throttle control SEATS AND SAFETY HARNESS Aircraft features three point fitting safety belts with waist and diagonal straps adjustable via a sliding metal buckle Seats are built with light alloy tube structure and synthetic material cushioning A lever located on the right lower side of each seat allows for seat adjustment according to pilot size DOORS Aircraft doors feature external and internal door handles with door lock provided externally on left side door An internal safety latch mechanism is positioned in proximity of door s upper edge and must be used before flight to secure door Mechanism rotates to engage doorframe to cabin tubular framework BAGGAGE COMPARTMENT The baggage compartment is located behind the pilots seats Baggage shall be uniformly distributed on utility shelf and its weight shall not exceed 20kg Tie down baggage using adjustable tie down net WARNING Before loading baggage check aircraft s weight and CG location see section 6 Date Issue 3 25 May 2010 7 5 P92 JS COSTRUZIONI AERONAUTICHE SECTION 7 lt lt TECNAM FLIGHT MANUAL Systems POWERPLANT ENGINE ROTAX 91252 4 stroke
10. 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 Each main wheel has a brake disc 7 Figure 9 2 Differential brake system Date Issue 3 rev 1 25 February 2015 9 19 P92 JS X TECNAM FLIGHT MANUAL 22 The following placard is located on the central pedestal Figure 9 3 Parking brake placard Date Issue 3 rev 1 25 February 2015 9 20 P92 JS FLIGHT MANUAL EC M SUPPLEMENT N 4 CENTRAL THROTTLE CONTROL SYSTEM 4 INTRODUCTION This section contains supplementary information for safe and efficient operation of the aircraft if equipped with the central throttle control system 4 1 GENERAL No variations 4 2 LIMITATIONS No variations 4 3 EMERGENCY PROCEDURES No variations 4 4 NORMAL OPERATION No variations 4 5 PERFORMANCE No variations 4 6 WEIGHT AND BALANCE No variations Date Issue 3 rev 1 25 February 2015 9 21 P92 JS FLIGHT MANUAL EMEN 4 7 SYSTEMS SUPPLEMENTS The figures 9 3A and 9 3B show the central throttle control system when the Carb Heat lever installed and only with central throttle lever The engine throttle lever is located on the left site and the choke lever is located on the right site The levers friction for both configurations is located on the lateral right site of the central throttle control system
11. see table below Max Power Max RPM Time max kW hp RPM prop eng 73 5 98 6 2388 5800 69 92 5 2265 5500 NOTE The static rpm range at full throttle carburetors heat Off is 2100 100 prop rpm TEMPERATURES Max cylinder heads 135 Cooling liquid monitored at cylinder heads 135 Oil 130 Min 50 OIL PRESSURE Min 0 8 bar Max 5 bar Date Issue 3 25 May 2010 2 4 P92 JS TECNAM FLIGHT MANUAL DANS WARNING ENGINE START OPER TEMP OAT Min 25 C OAT Max 50 C Admissible pressure for cold start is 7 bar maximum for short periods FUEL PRESSURE Min 2 2 psi Max 5 8 psi VISCOSITY Use viscosity grade oil as specified in the following table Klima 7Mehrbereichs le climatic x conditions multi grade oils tropisch tropical gemaBigt temperate SAE 20W 40 SAE 5W 40 o 5 x lt arktisch arctic WARNING Date Issue 3 25 May 2010 2 5 COSTRUZIONI AERONAUTICHE P92 JS TECNAM FLIGHT MANUAL SECTION 2 LIMITATIONS Use of Aviation Grade Oil with or without additives is not permitted COOLANT Mixture 80 concentrated antifreeze e g BASF Glysantin Anticorrosion or equivalent with anticorrosion additive and 2096 demineralized water PROPELLER MANUFACTURER HOFFMANN Propeller MODEL HO17GHM 174 177C or HO17GHM A 174 177C PROPELLER TYPE Wood twin blade fixed pitch DIAMETER 17
12. horizontally opposed 4 cylinder mixed air and water cooled twin electronic ignition forced lubrication Maximum rating 98 6hp 73 5Kw 5800 rpm min 2388 rpm min prop Gear reduction ratio 2 4286 1 For further information see Engine Operating Manual Engine control instruments are located on right side of instrument panel PROPELLER wood twin blade HOFFMAN type HO17GHM 174 177C or HO17GHM A 174 177C for further information see Service Manual for P92 JS and Propeller Service Manual FUEL SYSTEM The system is equipped with two aluminum fuel tanks integrated within the wing leading edge and accessible for inspection through dedicated covers Capacity of individual tank is 351t 4511 optional and total usable fuel is 66 81t 86 8 10 Each fuel tank is equipped with a cabin installed shutoff valve A strainer cup with a drainage valve Gascolator is located on the engine side of the firewall Fuel level indicators for each tank are located on instrument panel Fuel feed is through an engine driven mechanical pump and through an electric pump for emergencies normally ON for takeoff that supplies adequate engine feed in case of main pump failure fuel lines located in the engine compartment are protected with fireproof braiding to avoid possible fire Figure 7 3 illustrates the schematic of the fuel system Date Issue 3 25 May 2010 7 6 P92 JS COSTRUZIONI AERONAUTICHE SECTION 7 TECNAM
13. 06 o D a o 06 1 8 gt 0 S ES 0 BN o T 5 k 2 o n 223 LU 5 ary ri BUSES o 2 S S S S s eo FR 8 ive Moment empty Kg m Date Issue 3rev1 25 February 2015 6 6 P92 JS COSTRUZIONI AERONAUTICHE S ECTION 6 SSS FLIGHT MANUAL WEIGHI amp BALANCE 600 580 560 540 520 Y 500 5 C G TRAVEL 480 mi A 460 440 420 400 1 71 1 72 1 73 1 74 1 75 1 76 1 77 1 78 1 727 1 768 METERS AFT OF DATUM Fig 6 2 C G RANGE CHART Date Issue 3rev1 25 February 2015 6 7 COSTRUZIONI AERONAUTICHE TECNAM Date Issue 3rev1 25 February 2015 P92 JS SECTION 6 WEIGHT amp BALANCE FLIGHT MANUAL Distance in meters from Propeller support flange Fuel 1 66m Ir A Y Pilot mean value 1 76 C b d 1 Baggage 2 21m Fig 6 3 LOAD POSITION WITH RESPECT TO DATUM 6 8 P92 JS COSTRUZIONI AERONAUTICHE SECTION 6 LOADING Baggage compartment i
14. 92 1 Noise Certification Basis JAR 36 Sub C Issue 23 May 1997 ICAO Annex 16 Chap 10 issue 1993 WARNINGS CAUTIONS NOTES The following definitions apply to warnings cautions and notes used in the Flight Manual A Means that non observation of WARNING corresponding procedure leads to immediate or important degradation of the flight safety Means that the non observation of the corresponding procedure leads to a minor or to a more or less long term degradation of the flight safety Draws the attention to any special item not directly NOTE LONE related to safety but which is important or unusual zn Date Issue 3 25 May2010 1 2 COSTRUZIONI AERONAUTICHE P92 JS THREE VIEW DRAWING NOTE e Dimensions shown refer to aircraft weight of 550kg and 600 kg and normal operating tire pressure e Propeller ground clearance 320mm e Propeller ground clearance with deflated front tire and nosewheel shock absorber compressed by 102mm e Minimum ground steering radius 5 5m Date Issue 3 25 May2010 1 3 P92 JS SECTION 1 DESCRIPTIVE DATA WING For 550 kg For 600 kg MTOW MTOW Wing span 8 7m 8 7m Wing chord 14 1 4 Wing surface 12 m 12 m Wing loading 45 8 kg m 50 0 kg m Aspect ratio 6 31 6 31 Taper ratio 1 0 1 0 Dihedral 1 5 1 59 FUSELAGE Overall length 6 400 m 6 400 m Overall width 1 100 m 1 100 m Overall heig
15. Issue 1993 and results are shown in the following table 550 kg MTOW 600 kg MTOW Noise Level db 63 6 Date Issue 3 25 May 2010 65 0 5 14 P92 JS COSTRUZIONI AERONAUTICHE S C SECTION 6 WEIGHT amp BALANCE EQUIPMENT LIST TABLE OF CONTENTS INTRODUCTION 2 AIRCRAFT WEIGHING 2 WEIGHING REPORT MEREDITH Amd 3 WEIGHT AND BALANCE 5 LOADING T 9 EQUIPMENT EISE en 9 Date Issue 3rev1 25 February 2015 6 1 P92 JS COSTRUZIONI AERONAUTICHE SECTION 6 X TECNAM __ MANUAL _ INTRODUCTION This section describes the procedure for establishing the basic empty weight and moment of the aircraft Loading procedure information is also provided AIRCRAFT WEIGHING PROCEDURES PREPARATION a Carry out weighing procedure inside closed hangar b Remove from cabin any objects left unintentionally a Insure on board presence of Flight manual airnavigation certificate navigation charts etc Align nose wheel Drain fuel via specific drain valve Oil hydraulic fluid and coolant to operating levels Move sliding seats to most forward position Raise flaps to fully retracted position 0 Place control surfaces in neutral position Place scales min capacity 150 kg under each wheel orm Egg
16. LEVELING a Level the aircraft using the cabin floor as datum b Center bubble on level by deflating nose tire WEIGHING a Record weight shown on each scale b Repeat weighing procedure three times c Calculate empty weight DETERMINATION OF C G LOCATION a Drop a plumb bob tangent to the leading edge in non tapered area of one half wing approximately one meter from wing root and trace reference mark on the floor Repeat operation for other half wing Stretch a taught line between the two marks Measure the distance between the reference line and main wheel axis Using recorded data it is possible to determine the aircraft s C G location and moment see following table papp Date Issue 3rev1 25 February 2015 6 2 P92 JS COSTRUZIONI AERONAUTICHE SECTION 6 _ MANUAL weenrasaiance _ WEIGHING REPORT Model P92 JS S N Weighingn Date Datum Propeller support flange w o spacer Equipment list date MAC 1400 mm 1405 D DATUM Horizontal Plumb Line Bon distance fom ose wheel B Maximum takeoff weight Wr 550kg Empty weight Maximum payload Wr We 1 Including unusable fuel 2 3 kg Date Issue 3rev1 25 February 2015 6 3 P92 JS aram COSTRUZIONI AERONAUTICHE S ECTION 6 TECNAM MANUAL WEIGHT amp BALANCE WEIGHING REPORT Model P92 JS S N Weighing n Dat
17. May 2010 9 12 P92 JS COSTRUZIONI AERONAUTICHE 5 TI 9 FLIGHT MANUAL SUPPLEMENTS TAKE OFF RUN AND DISTANCE TOWING A BANNER OF NOT MORE THAN 90 m CONDITIONS Flap 15 Runway dry compact grass runway Take off weight 550 kg Runway slope 0 Engine throttle Full Wind zero 2 surface 90 Peso Press DISTANCE DISTANCE DISTANCE GRND DISTANCE A m Alt Pom 15 n 15 m ja 15m 15m m kg ft 2 104 196 431 275 114 214 470 300 124 272 234 513 328 jo 136 297 256 561 358 786 2 surface 70 209 90 Peso Press GRND DISTANGE GRAD Laictance DISTANCE Alt in anos nos i an OBS kg ft 2 470 81 178 Ed 88 194 167 512 96 212 182 399 559 7 105 231 199 436 611 783 For towing banners whose surface is less than 90 the maximum allowed take off weight reaches 550kg Date Issue 3 25 May 2010 9 13 P92 JS lt lt TECNAM FLIGHT MANUAL SECTION 9 RATE OF CLIMB CONDITIONS 0 Engine throttle Full Vy 53 KIAS OATS 35 Airfield pressure altitude lt 3000 ft Banner s surface 140 m Take off weight 460 kg The rate of climb is higher than 2 m s CONDITIONS Flap 0 Engine throttle Full Vy 53 KIAS lt 35 Airfield pressure
18. SYSTEMS 15 psi 0 STABI The following aircraft identification placard is located on tailcone TECNAM S R L 92 JS S N CERT N A 412 On the right side of the tail cone next to the battery case access door is present the BATTERY INSIDE following placard 69x17mm Date Issue 3 rev 1 25 February 2015 7 16 P92 JS COSTRUZIONI AERONAUTICHE S E C TI N 7 On the right side of the tail cone on the power receptacle s door is present the following placard 135x25mm EXTERNAL POWER RECEPTACLE 12 Volt DC On both the main landing gear fairings the following placard 120x22mm is NO STEP Date Issue 3 25 May 2010 7 17 P92 JS 44 TECNAM FLIGHT MANUAL eeu LANDING amp SERVICE SECTION 8 GROUND HANDLING amp SERVICE TABLE OF CONTENTS INTRODUCTION tei ERR ERU HERE EE EID OLG HE WEM 2 AIRCRAFT INSPECTION 2 AIRCRAFT ALTERATIONS OR REPAIRS 2 2 GROUND HANDLEJINQG 2 CLEANING AND ete tiet froide re 3 Date Issue 3 25 May 2010 8 1 COSTRUZIONI AERONAUTICHE P92 JS TECNAM MANUAL SECTIONS GROUND HANDLING amp SERVICE INTRODUCTION This section contains factory recommended procedures for proper ground handling and routine care and servicing It also identifies certain inspection and maint
19. altitude lt 3000 ft Banner s surface 90 Take off weight 550 kg The rate of climb is higher than 2 m s 2 6 WEIGHT amp BALANCE EQUIPMENT LIST In the following table are listed all the equipment that Tecnam has installed on the P92 JS for towing banners Date Issue 3 rev 1 25 February 2015 9 14 P92 JS MX TECNAM FLIGHT MANUAL 22 See DESCRIPTION amp P N a INST WEIGHT kg DATUM m Es 27 SYSTEMS The P92 JS for towing banners is equipped with a hook located in the rear part of the fuselage This hook is supported by a tubular beam 1 that transfers the towing loads to the tail cone structure The forward part of the beam is connected to the bulkhead 4 by means of two vertical stringers 5 6 and two longitudinal stringers 7 not present in the P92 JS standard configuration The rear link to the bulkhead 45 is realised by a steel support 2 connected by means of two steel ties 4 3 to the stabilator s fitting plates The hook is a TOST E85 and is connected to the aluminium tubular beam by means of aluminium plates e SS Supporting beam assembly Hook connection Date Issue 3 rev 1 25 February 2015 9 15 P92 JS TECNAM FLIGHT MANUAL 22 The towing is released by the Hook simply operating the release lever located in cabin between the two seats Release lever
20. an obstacle on the ground it automatically detaches from the towing rope by means of a calibrated collapsible link The load at which the link collapses depends on the banner 5 dimension For further information please refer to the banner s manufacturer manual 2 4 NORMAL PROCEDURES In addition to what has been specified in Section 4 before each flight it is necessary to carry out the extra inspections listed below CABIN INSPECTION Weight and airfield altitude check for compatibility with the Section 9 2 Limitations Release lever check EXTERNAL INSPECTION e Adjust the rear view mirror and check for a proper fastening Date Issue 3 25 May 2010 9 9 P92 JS COSTRUZIONI AERONAUTICHE S E C TI 9 Release hook check functionality BEFORE TAKE OFF banner will be either unfolded along the runway or placed properly folded Place the banner behind the a c so as to straighten the towing ropes see picture below Check the banner and its link to the aeroplane to insure that the connection has properly done and in compliance with the manufacturer instructions TAKE OFF AND CLIMB WARNING In order to reduce the banner s ground drag the take off should be done on a paved runway or on a short dry grass runway Date Issue 3 25 May 2010 9 10 P92 JS Check the banner position through the rear view mirror CRUISE While cruising pleas
21. and anchoring shall be provided by ramp tie downs Nose gear fork can be used for front tie down location Flight controls shall be secured to avoid possible weathervaning damage to moving surfaces For this purpose seatbelts may be used to latch control stick to prevent its movement Date Issue 3 25 May 2010 8 2 P92 JS COSTRUZIONI AERONAUTICHE SECTION 8 TECNAM FLIGHT MANUAL GROUND HANDLING amp SERVICE JACKING Given the light empty weight of the aircraft lifting one of the main wheels can easily be 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 spar immediately before the wingtip another person will place a suitable stand with protective cover under the steel spring attachment LEVELING Aircraft leveling may become necessary to check wing incidence dihedral or the exact location of CG Leveling is obtained when the cabin floor and in transverse direction the main gear support beam are horizontal ROAD TRANSPORT It is recommended to secure tightly all aircraft components onto the cart to avoid damage during transport Minimum cart size is 7x2 5 meters It is suggested to place wings under the aircraft s bottom secured by specific clamps Secondary components such as stabilator and struts shall be protected from accidental hits using plastic or other material For correct rigging and de riggi
22. ft Weight 550 Kg Date Issue 3 25 May 2010 Find Rate of climb 700 ft min P92 JS COSTRUZIONI AERONAJTICHE X FLIGHT MANUAL SECTIONS CRUISE CONDITIONS ISA Maximum takeoff weight for both MTOW 1 Fuel tanks 2x35 liters less the unusable fuel 2 Fuel tanks 2x45 liters less the unusable fuel Pressure altitude Hp 15 Speed Endurance hrs 1 Range N m RPM KTAS h 1 2 1 2 65 2050 102 18 3 7 4 0 382 495 0 2 Pressure altitude Hp 2000 jt 11T Propeller Speed Consumption Endurance hrs Range N m RPM KTAS 1 2 1 2 55 1950 98 15 4 5 5 8 440 571 65 2070 106 18 3 7 4 9 397 215 73 2150 109 19 3 5 4 6 387 501 Pressure altitude Hp 4000 jt OAT 7C Endurance hrs 1 Range N m RPM KTAS 1 1 2 1 2 55 2020 101 15 4 5 5 8 454 588 60 2080 105 17 4 0 5 1 416 540 70 2150 110 18 5 3 6 4 7 401 520 Pressure altitude Hp 6000 ft 3 Consumption Endurance hrs 1 Range N m RPM KTAS 1 2 1 2 60 2150 108 17 4 0 5 1 429 556 Range and endurance are intended approximate and referred to zero wind condition Date Issue 3 25 May 2010 5 10 P92 JS COSTRUZSON AERONAJZTICHE SECTION 5 14 TECNAM Fucur MANUAL Pressure altitude Hp 8000 ft OAT 0 8 C Propeller Speed Con
23. gt DIS SPD nmkt select navigation unit to nautical miles ALT VS ftfpm select altitude to feet and feet per minute gt MAPDATUM WGS 84 select map datum WGS84 gt POSN deg min select grid for nav unit to decimal minutes Date Issue 3 25 May 2010 9 4 92 JS COSTRUZIONI AERONAUTICHE S E C TI 9 4 FLIGHT MANUAL _ 1 4 EMERGENCY PROCEDURES 1 If the information provided by the Garmin GNS430 is not available or manifestly wrong it is necessary to use other navigation instruments 2 If the message WARN appears in the lower left portion of the display the receiver cannot be considered useful as a navigation aid The pilot must use the VLOC receiver or an alternative navigation system 3 If the message INTEG appears in the lower left portion of the display the RAIM function is unavailable The pilot must use the VLOC receiver or an alternative navigation system 4 In emergency flight conditions pressing the COM flip flop knob for 2 seconds will automatically tune in the 121 500MHz emergency frequency 1 5 NORMAL OPERATION 1 DETAIL FOR NORMAL OPERATION Normal operation is described in the Pilot s guide and Reference P N 190 00140 00 rev F dated July 2000 or later versions 2 GARMIN GNS 430 DISPLAY Data for GNS 430 system appears on GARMIN GNS430 display Data source is either the GPS or the VLOC as indicated above the CDI s
24. in case of emergency see section 3 Date Issue 3 25 May 2010 7 3 P92 JS TECNAM FLIGHT MANUAL SECTION 7 INSTRUMENT PANEL The conventional type instrument panel allows placement of a broad range of equipment Instruments marked with an asterisk are optional Indic OR Loc 611064 Altineter Trim N Vacum gt 22959959595 LH throttle Breakers Wen RH Throttle Clock Throttle lock Ignitions Fuel Pump Light Choke Cark Heating Gyro compass NS SEE aster HE GPS e GARMIN GNS 430 contr Fig 7 2 INSTRUMENT PANEL CARBURETOR HEAT Carburetor heat control knob is square shaped and is located just to the left of the center throttle control when the knob is pulled fully outward from the instrument panel carbs receive maximum hot air During normal operation the knob is OFF CABIN HEAT The cabin heat control knob is positioned on the lower left side of the instrument panel when knob is pulled fully outward cabin receives maximum hot air Vents are located by the rudder pedals and above instrument panel If necessary outside fresh air can be circulated inside cabin by opening door vents
25. of the aircraft or engine are extremely rare if appropriate maintenance and pre flight inspections are carried out In case of emergency suggestions of the present section should be considered and applied as necessary to correct the problem Before operating the aircraft the pilot should become thoroughly familiar with the present manual and in particular with the present section Further a continued and appropriate training should be provided AIRSPEEDS FOR SAFE OPERATION IN EMERGENCY SITUATIONS IAS 550 kg MTOW 600 kg MTOW Engine failure after takeoff 60 Kts 60 Kts Engine failure during flight 66 Kts 69 Kts Manoeuvring speed 93 Kts 97 Kts Maximum glide 66 Kts 69 Kts ENGINE FAILURES Should an emergency arise the basic guidelines described in this section should be considered and applied as necessary to correct the problem ENGINE FAILURE DURING TAKEOFF RUN Throttle idle fully out Brakes apply as needed Magnetos OFF Flap retract Generator switch and Master switch OFF Fuel shutoff valves OFF Electric fuel pump OFF Inform TWR Date Issue 3 25 May 2010 3 2 P92 JS COSTRUZSON AERONAJTICHE SECTION 3 TECNAM FLIGHT MANUAL EMERGENCY PROCEDURES ENGINE FAILURE IMMEDIATELY AFTER TAKEOFF Speed 60 KIAS Locate landing area Throttle idle fully out Fuel shutoff valves OFF Electric fuel pump OFF Magnetos OFF Flaps as needed Generator switch and Master switch OFF Inform
26. on navigation lights strobe light and landing light Check engine instruments Oil temperature 50 110 Cylinder heads temperature max 135 Oil pressure 2 5 bar Fuel pressure 2 2 5 8 psi IV Check ammeter to insure alternator is charging V Propeller at 1700 rpm and test Magnetos speed drop with only one ignition circuit must not exceed 130 propeller s rpm VI Check fuel level indicators VII Flaps at 15 takeoff VIII Stick free and zero trim IX Seat belts fastened and doors secured TAKEOFF AND CLIMB I TWR OK for takeoff II Check for clear final and wind on runway III Parking brake OFF IV Carburetor heat OFF V Taxi to line up VI Full throttle approx 2100 100 propeller rpm VII Rotation speed Vr 47 for 550 kg MTOW and Vr 48 Kts for 600kg MTOW VIII Rotation and takeoff Date Issue 3 25 May 2010 4 8 P92 JS COSTRUZIONI AERONAJTICHE SECTION 4 SE TECNAM _ MANUAL _ wommaimocrus gt IX Slight braking to stop wheel spinning X Flaps retracted XI Landing light OFF XII Trim adjustment XIII Establish climb rate XIV Electric fuel pump OFF CRUISE I Reach cruising altitude Set power and engine rpm s for cruise III Check engine instruments Oil temperature 90 110 C Temperature cylinder heads 909 135 Oil pressure 2 5 bar Fuel pressure 2 2 5 8 psi IV Carburetor heat as needed see paragraph on carb heat in Section 3 Compensate
27. unpredicted asymmetrical fuel consumption between left and right fuel tanks by closing appropriate fuel shutoff valve inside cabin BEFORE LANDING I Contact TWR II Electric fuel pump ON III Turn on landing light IV Check runway final and establish descent and approach to final V Extend flaps gradually to maximum deflection of 38 Date Issue 3 25 May 2010 4 9 P92 JS COSTRUZIONI AERONAJTICHE FLIGHT MANUAL NORMAL PROCEDURES VI Optimal touchdown speed 44Kts for 550kg MTOW 45Kts for 600kg MTOW BALKED LANDING I Full throttle II Flaps position TO III Speed 60 KIAS 63KIAS for 550kg MTOW 600kg NORMAL LANDING I Land and taxi II Flaps to 09 III Parking brake ON IV Turn off landing navigation and strobe lights ENGINE SHUT DOWN I Keep engine running at 1200 rpm for about two minutes in order to reduce latent heat II Electric fuel pump OFF Turn off all electrical utilities IV Set magnetos switch to OFF V Set Generator switch and Master switch to OFF VI Set both fuel shutoff valves to OFF POSTFLIGHT CHECK I Insert hood over pitot tube on left side wing strut II Lock controls using seat belts Date Issue 3 25 May 2010 4 10 P92 JS COSTRUZIONI AERONAJTICHE SECTIO N 4 14 TECNAM MANUAL NofaLrroceoures_ INTENTIONALLY LEFT BLANK Date Issue 3 25 May 2010 4 11 P92 JS COSTRUZION AERONAJTICHE SECTI 5 F
28. 0 42 2 7 Vertical Speed Indicator Wultrad Inc p n 2 Turn and Bank Indicator FALCON GAUGER 2 3 2 Turn and Bank Indicator Mid Continent p n 1394T100 TZ D10 Attitude Indicator FALCON G GH02V 3 D11 Attitude Indicator ALLEN INSTR RCA 22 7 a EE UA C6 C7 CA EN e e E Date Issue 3rev1 25 February 2015 6 11 aw COSTRUZIONI AERONAUTICHE P92 JS CIENTO WE Desde FALCON BGA 130 DH osi wo _ 3 D15 Head temp Ind 641 011 7047 7048 VDO 0 10 1 20 N 020 Prop RPM Ind D1 112 5040 Aircraft N 1 10 Mitchell Fuel lve Ind Road XID4 0008 00 Oil pressure Ind Sorlini SOR50 90 120 Nav CommTrans Bendix King KX155 224 12 NavIndicator Bendix King 208 046 120 R T VHF COMM Garmin 0 12 33 Tramponder BendivKingKT76A 136 120 ES Receiver 251 32m Lm RT VHF COMMIC ADODICOM 135 33 _ 0 ES TawpmkrGamnGTXES 9 33m 9 Audio pane 95 3 EIS instr Garmin GTOGA 95 33m Antenna 03 150 Date Issue 3rev1 25 February 2015 6 12 P92 JS COSTRUZIONI AERONAUTICHE S E C TI N 6 FLIGHT MANUAL WEIGHT amp BALANCE E18
29. 3 25 May 2010 7 10 P92 JS COSTRUZIONI AERONAUTICHE SECTION 7 BRAKES The aircraft s braking system is a single system acting on both wheels of main landing gear through disk brakes the same circuit acts as parking brake via an intercept valve To activate brakes it is sufficient to verify that brake shut off valve positioned on tunnel between pilots is OFF then activate brake lever as necessary To activate parking brake pull brake lever and set brake shut off valve to ON MARKING amp PLACARDS To compensate for deviation errors of the magnetic compass the following correction card is located immediately below compass 1 1 DATE RADIO ON AIRPATH This placard has to be compiled by certified operator with valid and proper instrumentation The following placard is located on the cabin s floor tunnel near the hydraulic brake circuit shutoff valve PARKING BRAKE PULL BRAKE LEVER and ON Refer to section 9 for possible variations Date Issue 3 25 May 2010 7 11 TECNAM MANUAL Two throttle control knobs are located on instrument panel One is positioned centrally while the other is on the upper left hand side The following placard is near each one A throttle friction lock is located on the instrument panel to maintain desired setting The following placard is positioned near friction lock Refer to section 9 for possible v
30. 40 mm no reduction permitted Date Issue 3 25 May 2010 2 6 Am COSTRUZIONI AERONAUTICI P92 JS FLIGHT MANUAL POWERPLANT INSTRUMENT MARKINGS Powerplant instrument markings and their color code significance are shown below RED LINE GREEN ARC YELLOW ARC RED LINE INSTRUMENT Minimum limit Normal Caution Maximum operating E Oil Temp 90 110 90 110 130 Cylinder 0 135 heads and coolant temp Oil pressure 0 8 2 5 7 OTHER INSTRUMENT MARKINGS INSTRUMENT RED LINE GREEN ARC YELLOW ARC RED LINE Minimum Normal operating Caution Maximum limit limit 1 Admissible pressure for cold start is 7 bar maximum for short periods 2 Unusable fuel for each tank is 1 6 litres Date Issue 3 25 May 2010 2 7 P92 JS MTEGNAM Fuer M SECTION 2 ANUAL LIMITATIONS WEIGHTS 550 kg MTOW 600 kg MTOW Maximum takeoff weight 550 kg 600 kg Maximum landing weight 550 kg 600 kg Maximum zero fuel weight 550 kg 600 kg Maximum baggage weight 20 kg 20 kg 2 18 m from datum NOTE Refer to section 6 for correct stowing and loading of baggage CENTER OF GRAVITY RANGE Ref for levelling Cabin floor Datum Propeller support flange without spacer Forward limit 1 727 m 23 MAC aft of datum for all weights Aft limit 1 769 m 26 MAC aft of datum for all weights WARNING It is the pilot s responsibility to insure that the airplane is properly loaded Refer
31. 5 STROBE LIGHT N 52 N B BREAKER 25A SS 7 oe BATTERY RELAY di C d 8 LIGHT NA Ji de STALL WARNING BATTERY 36 FUSE 50A E 4 MASTER SWITCH a B GENERATOR SWITCH gt lt EN 9 TRANSP a CN RECTIFIER REGULATOR gt GPS J 29 gt 00 ihe OVERVOLTAGE GENERATOR LIGHT OVERVOLTAGE RELAY ENC SENSOR 7 x EM es FUEL Q oP S ii lt Tui J AVAILABLE VOLTMETER 7 INSTRUMENTS FIG 7 4 ELECTRICAL SYSTEM SCHEMATIC Date Issue 3 25 May 2010 7 8 P92 JS COSTRUZIONI AERONAUTICHE SECTION 7 4 TECNAM MANUAL SYSTEMS GENERATOR LIGHT Generator light red illuminates for the following conditions e Generator failure e Failure of regulator rectifier with consequent overvoltage sensor set off The battery can support energy requirements for 26 min see page 3 8 VOLT AMMETER The voltmeter indicates voltage on bus bar a positive value of the ammeter indicates the generator is charging the battery a negative value indicates the battery s discharge rate OIL AND CYLINDER HEADS TEMP OIL PRESSURE These instruments are connected in series with their respective sensors The same breaker protects all temperature instruments while a second breaker protects oil pressure indicator and other instruments O A T INDICATOR A digital Outside Air Temperature indicator is l
32. 5 697 0 33 8 9 8 Air filter K amp N p n 33 2544 Vacuum instr system RA215CC Rapco AIO Vacuum valve RA2H3 12 Fuel pump p n 21 11 342 000 0 100 0 71 0 200 0 71 LANDING GEAR AND ACCESSORIES Main gear spring leafs p n 92 8 300 1 Main gear wheel rims Cleveland 40 78B Main gear tires Air Trac 5 00 5 aaip4 Disk brakes Cleveland 30 9 Nose gear wheel rim p n 92 8 880 1 B6 Nose gear tire 4 00 6 N 1 200 0 460 Nose gear tire 5 00 5 1 500 0 460 Nose gear fairing p n 92 8 410 1 2 1 500 0 460 B9 Nose gear fairing p n 27 8 420 1 1 500 0 460 Main gear fairing p n 92 8 420 1 2 1 500 1 930 Nose gear shock p n 92 8 200 000 1 450 0 465 Date Issue 3rev1 25 February 2015 6 10 mn ee N w Fuel tank 45 Lr P N 21 1 340 001 2 7 aw COSTRUZIONI AERONAUTICHE P92 JS Regulator rectifier p n 945 345 0 Battery relay p n 111 226 5 Flaps actuator control SIR Mod AO 01 M Trim actuator control Ray Allen C T2 10A f Overvoltage sensor OS75 14 Overvoltage sensor B00289 2 05 M C12 Landing light AS GE 4509 Landing light Pled1L INSTRUMENTS 1 Altimeter MIKROTECHINA p n 1128 12B6 2 Altimeter United Instruments p n 5934PM 3 Airspeed ind MIKROTECHINA 116 B0B2 Compass Airpath C2400 Clock DAVTRON mod M 800 Vertical Speed Indicator MIKROTECHINA UL 3
33. COSTRUZIONI AERONAUTICHE P92 JS FLIGHT MANUAL INTRODUCTION FLIGHT MANUAL Doc n 92 61 Issue n 3 25 May 2010 Revision No 1 25 February 2015 P92 JS MANUFACTURER COSTRUZIONI AERONAUTICHE TECNAM S r 1 AIRCRAFT MODEL P92 JS TYPE CERTIFICATION n EASA A 412 SO A 340 SERIAL NUMBER oie ce neies BUIED YEAR e emer eios REGISTRATION MARKINGS 2202 2500 440 This manual contains information to be furnished to the pilot as required by EASA in addition to further information supplied by manufacturer This manual must always be present on board the aircraft The aircraft is to be operated in compliance with information and limitations contained herein Date Issue 3 rev 1 25 February 2015 i 1 TEC NAM P92 JS FLIGHT MANUAL FEE RECORD OF REVISIONS Any revisions to the present Manual except actual weighing data must be recorded in the following table and in case of approved Sections endorsed by the responsible airworthiness authority 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 page RECORD OF REVISIONS Revision Affected Affected pages D Approval t sections EASA DOA 10 to 14 25 02 2015 14 16 25 02 2015 22 24 25 02 2015 25 to 28 25 02 2015 Date Issue 3 25 M
34. Comm antenna and a VHF Comm tranceiver The main function of the VHF Comm is to allow communication with the control tower The VOR ILS function is to receive and demodulate VOR and LOC signals The GPS section is dedicated to signal acquisition from the GPS satellite system and to furnish real time information with respect to position speed and time With appropriate signals the GPS GNS 430 can gt VFR IFR routes track waypoints and plan non precision instrument approaches GPS LORAN C VOR VOR DME TACAN NDB NDB DME RNAV in accordance with AC 20 138 Reference coordinates used for navigation are WGS 84 Date Issue 3 25 May 2010 9 3 P92 JS COSTRUZIONI AERONAUTICHE S E C TI 9 1 3 LIMITATIONS 1 The Pilot s guide and Reference p n 190 00140 00 rev dated July 2000 or later versions must be available for proper use of the instrument 2 Only use is permitted 3 The GPS section must use the following or more recently approved software versions Subsystem Software version 2 00 2 00 1 22 1 25 The software version of the main subsystem is displayed by the GNS 430 immediately after start up for 5 seconds Remaining subsystems software versions may be verified in sub page 2 of the AUX Group display for SOFTWARE DATA BASE VER 4 The following default settings must be keyed in in the SETUP 1 menu of the GNS430 receiver before any other operation
35. ERFORMANCE 4 7 18 16 14 12 6 2 2 0 A 4 LA A 8 lt lt 5 A 9 T7 d e 6 lt lt 0 4 VA T LA e E l 1600 ft 6 2 P o Ed 7 5 4 A E LH 0 07 T 4 EAE 0 4 2 D PT Pd 4 6 6 40 80 20 1B 0 101 20 30 40 OUTSIDE AIR TEMPERATURE C Fig 5 2 ICAO CHART Example Given Find Temperature 20 C Ts 129 Pressure altitude 1600 ft Date Issue 3 25 May 2010 5 4 P92 JS COSTRUZION AERONAJTICHE SECTION 5 14 MANUAL STALL SPEED Approved data CONDITIONS weight 550 kg engine idle no ground effect LATERAL BANKING gt fae a as oo EE CONDITIONS weight 600 kg engine idle no ground effect LATERAL BANKING Altitude loss during conventional stall recovery as demonstrated during test flights is approximately 100 ft with banking under 30 Date Issue 3 25 May 2010 5 5 COSTRUZ ON AERONASTICHE P92 JS TECNAM FLIGHT MANUAL PERFORMANCE CROSSWIND Maximum demonstrated crosswind velocity is 15 Kts gt Example Given Find Wind direction 30 Headwind 17 5 Kts W
36. LIGHT MANUAL PERFORMANCE SECTION 5 PERFORMANCE TABLE OF CONTENTS PERFORMANCE Wee Pie 2 INTRODUCTION 2 USE OF PERFORMANCE CHARTESS enne tenen ens 2 AIRSPEED INDICATOR SYSTEM CALIBRATION APPROVED 3 STALL SPEED APPROVED DATA esee 5 CROSSWIND irainen ie e e E ee tU ee EROS 6 TAKEOFF PERFORMANCE APPROVED DATA eee ene 7 CLIMB PERFORMANCE ener enne enne nen enne nns 9 CRUISE scie ee SERIE 10 ntt E LO ERE ES EE VES ERU E 12 LANDING DISTANCE Approved eene 13 CONSEQUENCES FROM RAIN AND 14 NOISE DATA n 14 Date Issue 3 25 May 2010 5 1 gt COSTRUZIONI AERONAJTICHE P92 JS TECNAM FLIGHT MANUAL PERFORMANCE PERFORMANCE INTRODUCTION This section provides all necessary data for accurate and comprehensive planning of flight activity from takeoff to landing Data reported in graphs and or tables were determined by using flight test data with conditions as prescribed by JAR VLA e aircraft and engine in good condition e average piloting techniques Each graph or table was determined according to ICAO Standard Atmosphere ISA 5 1 evaluations of the impact on performance was carried out by theoretical means for e airsp
37. LOWER COWLING I X After disassembling upper cowling bring propeller to horizontal position IL Using a standard screwdriver press and rotate 90 the two Cam locks positioned on lower cowling by the firewall III Pull out the first hinge pin positioned on the side of the firewall then while holding cowling pull out second hinge pin remove cowling with downward motion IV For installation follow reverse procedure Date Issue 3 25 May 2010 4 2 s P92 JS COSTRUZIONI AERONAJTICHE SECTION 4 14 TECNAM MANUAL NofaLrroceoures PRE FLIGHT INSPECTIONS Before each flight it is necessary to carry out a complete inspection of the aircraft starting with an external inspection followed by an internal inspection as hereby detailed CABIN INSPECTION Flight Manual check that a copy is on board Weight and balance check if within limits Safety belts used to lock controls free gt Flight controls activate flight controls to insure unhindered movement of control rods and surfaces E Parking brake engage F Throttle adjust friction lock G Magnetos OFF H Master switch ON I Voltmeter check 10 12 V Ammeter check red J Generator switch ON check generator switch is illuminated K Fuel pump ON check light ON audible sound and correct operation of fuel pressure indicator L Avionics switch ON check operation when finished reposition switch to OFF M Flaps control activate control to fu
38. RIPTIVEB DATA atescceset ceo ceo eos eese et det ae eee CONTROL SURFACES TRAVEL LIMITS ENGINE up eked ee Se ee eke 225 Em OILSYSTEM ECC COOLING 3 etre roo et hes MAXIMUM CERTIFIED WEIGHTS 2 STANDARD 5 0 2 040000000 2 2 20222 000000000000 ener ener nere ABBREVIATIONS AND TERMINOLOGY UNIT CONVERSION 2 200000000000000 Date Issue 3 25 May2010 P92 JS SECTION 1 GENERAL 1 1 COSTRUZIONI AERONAUTICHE P92 JS TECNAM FLIGHT MANUAL SECTION 1 GENERAL INTRODUCTION The P92 JS is a twin seat single engine aircraft with a strut braced rectangular high wing fixed main landing gear and steerable nosewheel This Flight Manual has been prepared to provide pilots and instructors with information for the safe and efficient operation of this aircraft This Flight Manual contains 9 sections Section 1 provides basic data and information of general interest It also contains definitions and explanations of symbols abbreviations and commonly used terminology CERTIFICATION BASIS Aircraft This type of aircraft has been approved by EASA ENAC in accordance with JAR VLA of April 26 1990 with amendments 91 1 and
39. SPEC 256 15 54 1 12 5 kg dm 20 EXSUEHR7J12 5kg Date Issue 3rev1 25 February 2015 9 27 P92 JS COSTRUZIONI AERONAUTICHE S E C TI N 9 X TECNAM FLIGHT MANUAL 21 Placard Chinese AUTOMOTIVE FUEL AUTOMOTIVE FUEL 1 0 0 0 Ft LEADED OR UNLEADED LEADED OR UNLEADED AVGAS 100LL AVGAS 100LL d CAPACITY 501 13 2 US gal CAPACITY 50LT 13 2 US gal ay 100145 A SOF AUTOMOTIVE OIL APL SF OR SC AUTOMOTIVE OIL CAPACITY 3 5 LT APL SF or SG 223 5 BATTERY INSIDE ARE HEH EXTERNAL POWER RECEPTACLE 12 Volt DC 124K FIRE EXTINGUISHER ON BAGGAGE FLOOR ROK 8 FETT STEP Kg is applied Maneuvering speed 93 KIAS Maneuvering speed 97 KIAS Note 97 Kias when the weight increment to 600 93 KIAS 97 KIAS Date Issue 3rev1 25 February 2015 9 28
40. STRUZIONI AERONAUTICHE P92 JS MANUAL SECTION 2 LIMITATIONS On the Middle panel of the instrument panel a placard will state the following THIS AIRPLANE IS CLASSIFIED AS A VERY LIGHT AIRPLANE APPROVED FOR DAY VFR ONLY NON ICING CONDITIONS ALL AEROBATIC MANEUVERS INCLUDING INTENTIONAL SPIN ARE PROHIBITED SEE FLIGHT MANUAL FOR OTHER LIMITATIONS NO SMOKING Near baggage compartment a placard will state the following FASTEN TIE DOWN NET MAXIMUM WEIGHT 20 kg PRESS 12 5 Kg dm Date Issue 3 25 May 2010 2 12 P92 JS COSTRUZION AERONAJTICHE SECTI N 3 FLIGHT MANUAL EMERGENCY PROCEDURES SECTION 3 EMERGENCY PROCEDURES TABLE OF CONTENTS 2 ENGINE FAM URES EYE EXE TRE REOR C EE RUE ER 2 AIRS EAR CE 4 SMOKE 2 ee ete 4 Li ut 5 LANDING 5 RECOVERY FROM UNINTENTIONAL 6 OTHER EMERGENCIES ccccccesscccceceessnseceeececsesseaeeecececeeseaeceeeceesesseaseeseeeeeeseaees 7 Date Issue 3 25 May 2010 3 1 P92 JS COSTRUZION AERONAUTICHE SECTION 3 TECNAM FLIGHT MANUAL _ INTRODUCTION Section 3 includes checklists and detailed procedures to be used in the event of emergencies Emergencies caused by a malfunction
41. TWR ENGINE FAILURE DURING FLIGHT M1 9o MIL OS Ea P9 IRREGULAR ENGINE RPM 1 Throttle check position and adjustment wheel 2 Carb heat ON 3 Electric fuel pump ON 4 Fuel shutoff valves both ON 5 If engine RPMs remain irregular land as soon as possible at closest airport LOW FUEL PRESSURE If the fuel pressure indicator falls below the 2 2 psi limit it is necessary to apply the following procedure 1 Electric fuel pump ON 2 Fuel shutoff valves both ON 3 at closest airport LOW OIL PRESSURE 1 Check oil temperature If stable within green arc Land as soon as possible at closest airport If increasing 2 Reduce engine throttle to 70 KIAS 3 Land as soon as possible and be alert for impending engine fault and consequent emergency landing Date Issue 3 25 May 2010 3 3 P92 JS COSTRUZSON AERONAJTICHE SECTION 3 TECNAM FLIGHT MANUAL EMERGENCY PROCEDURES AIR START 1 Altitude preferably below 4000 ft 2 Carb heat ON 3 Fuel shutoff valves both ON 4 Hlectric fuel pump ON 5 Throttle middle position 6 Generator switch and Master switch ON 7 Magnetos BOTH 8 Ignition key to START 9 If engine restarts keep an eye on instrument readings and land as soon as possible otherwise see procedure for Forced landing SMOKE AND FIRE ENGINE FIRE WHILE PARKED OR DURING TAKEOFF Fuel shutoff valves OFF Electric fuel pump OFF Cabin heat OFF Abort takeoff if possi
42. able terrain for emergency landing possibly upwind Fuel shutoff valves OFF Electric fuel pump OFF Magnetos OFF Tighten safety belts release door safety lock and unlatch doors Flaps full When certain to land Generator switch and Master switch OFF Touchdown at 42 KIAS Date Issue 3 25 May 2010 3 5 o P92 JS COSTRUZIONI AERONAUTICHE SECTION 3 TECNAM FLIGHT MANUAL _ POWER ON FORCED LANDING 1 Prompt descent slope 2 Flaps as required 3 Select terrain area most suitable for emergency landing and flyby checking for obstacles and wind direction Tighten safety belts release door safety lock and unlatch doors Before touchdown fuel shutoff valves OFF Electric fuel pump OFF Carb heat OFF Flaps full After touchdown magnetos OFF 0 Generator switch and Master switch OFF LANDING WITH A FLAT NOSE TIRE l Pre landing checklist complete 2 Hlaps full 3 Land and maintain aircraft NOSE HIGH attitude as long as possible After touchdown LANDING WITH A FLAT MAIN TIRE l Pre landing checklist complete 2 Landing approach as usual 3 Touchdown with GOOD TIRE FIRST and hold aircraft off flat tire as long as possible RECOVERY FROM UNINTENTIONAL SPIN Should an unintentional spin occur the following recovery procedure should be used 1 Adjust throttle to idle full outward position 2 Apply and hold full rudder opposite to the d
43. aircraft as soon as possible Date Issue 3 25 May 2010 3 8 P92 JS COSTRUZSON AERONAJTICHE SECTION 4 lt lt TECNAM FLIGHT MANUAL NORMAL PROC EDURES SECTION 4 NORMAL PROCEDURES TABLE OF CONTENTS INTRODUCTION see eec ie Po ee ee ooo eroe eee Ee neto dedere vue Meinen 2 RIGGING AND DERIGGING ENGINE COWDLING rte 2 PRE ELIGHT INSPECTIONS esee cod co et ara as 3 CHECE LISTS CURES 6 Date Issue 3 25 May 2010 4 1 P92 JS COSTRUZIONI AERONAJTICHE SECTION 4 TECNAM FLIGHT MANUAL NORMAL PROCEDURES INTRODUCTION Section 4 contains checklists and the procedures for the conduct of normal operation RIGGING AND DERIGGING ENGINE COWLING UPPER COWLING I Parking brake ON Fuel shutoff valves OFF III IV Generator switch OFF Master switch OFF Magnetos OFF Unlatch all four butterfly Cam locks mounted on the cowling by rotating them 90 counterclockwise while slightly pushing inwards V Remove engine cowling paying attention to propeller shaft passing through nose VI To assemble rest cowling horizontal insuring proper fitting of nose base reference pins VII Secure latches by applying light pressure check for proper assembly and fasten Cam locks WARNING Butterfly Cam locks are locked when tabs are horizontal and open when tabs are vertical Verify tab is below latch upon closing
44. ariations P92 JS SECTION 7 SYSTEMS THROTTLE THROTTLE LOCK 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 wrt truss member the valve is closed 20x8mm OPEN CLOSED placard is placed near each shutoff valve The following placard is placed near the RH forward truss member shutoff valve LHFUELTANK OFF ON LH FUEL TANK OFF SHUT OFF VALVE a i SHUT OFF VALVE The cabin heat control knob is located on the instrument panel central area just to the right of the throttle control the following placard is next to it The carburetor heat control knob is located on the instrument panel central area just to the left of the throttle control the following placard is next to it Date Issue 3 25 May 2010 CABIN HEAT Pull on CARB HEAT Pull on 7 12 P92 JS COSTRUZIONI AERONAUTICHE SECTION 7 MANUAL SYSTEMS The trim switch control is located on the upper central area of the instrument panel alternatively allocating trim TR control to either RH or LH control stick The following placard is positioned just above it A swit
45. ated Airspeed is the speed shown on the airspeed indicator and expressed in knots KTAS Knots True Airspeed is the airspeed expressed in knots relative to undisturbed air which is KCAS corrected for altitude and temperature Maximum Extended Speed is the highest speed permissible with wing flaps in a prescribed extended position Maximum Structural Cruising Speed is the speed that should not be exceeded except in smooth air then only with caution VNE Never Exceed Speed is the speed limit that may not be exceeded at any time Vs Stalling Speed Vso Stalling speed in landing configuration Vai Stalling speed in clean configuration flap 0 Vx Best Angle of Climb Speed is the speed which results in the greatest gain of altitude in a given horizontal distance Vy Best Rate of Climb Speed is the speed which results in the greatest gain in altitude in a given time Vr Rotation speed is the speed at which the aircraft rotates about the pitch axis during takeoff Vio Lift off speed 15 the speed at which the aircraft generally lifts off from the ground Vobs Obstacle speed is the speed at which the aircraft flies over a 15m obstacle during takeoff or landing Date Issue 3 25 May2010 1 8 P92 JS COSTRUZIONI AERONAUTICHE S E C TI N 1 METEOROLOGICAL TERMINOLOGY OAT Ts Hp Outside Air Temperature is the free air static temperature expressed in degrees Celsius Standard Temperatur
46. ay 2010 i 2 COSTRUZIONI AERONAUTICHE P92 JS e TECNAM FLIGHT MANUAL INTRODUCTION INTENTIONALLY LEFT BLANCK Date Issue 3 rev 1 25 February 2015 i 3 COSTRUZIONI AERONAUTICHE P92 JS TECNAM FLIGHT MANUAL INTRODUCTION LIST OF EFFECTIVE PAGES Section Revision Section 0 Section 1 Section 2 Section 3 Section 4 Section 5 Section 6 Section 7 Section 8 Section 9 Date Issue 3 25 May 2010 i 4 COSTRUZIONI AERONAUTICHE P92 JS e TECNAM FLIGHT MANUAL INTRODUCTION TABLE OF CONTENTS General Section 1 Limitations Section 2 Emergency procedures Section 3 Normal procedures Section 4 Performance Section 5 Weight amp Balance Equipment list Section 6 Aircraft and Systems description Section 7 Aircraft handling servicing and maintenance Section 8 Supplements Section 9 Section approved by EASA Section partially approved by EASA Sections 2 3 4 5 are approved by EASA n 10030344 on 11 06 2010 Section 9 supp 1 is approved by EASA n 2004 1787 on 02 03 2004 Section 9 supp 2 is approved by EASA n 2004 6324 on 17 06 2004 Date Issue 3 rev 1 25 February 2015 i 5 COSTRUZIONI AERONAUTICHE TECNAM FLIGHT MANUAL SECTION 1 GENERAL TABLE OF CONTENTS INTRODUC TO 25 pete ue he seed CERTIFICATION BASIS eese eene enne eren WARNINGS CAUTIONS THREE VIEW DRAWING eere eer nnne nennen DESC
47. ble If engine is running use up remaining fuel in carburetors Magnetos OFF Master switch OFF Generator switch OFF Warn bystanders to clear the area as fast as possible Without removing the engine cowling use or a powder fire extinguisher to put out flames directing spray towards cowling s air intakes DO NOT USE WATER to put out fire and do not open engine cowling until absolutely confident that fire is extinguished Lo Date Issue 3 25 May 2010 3 4 P92 JS COSTRUZSON AERONAJTICHE SECTION 3 14 TECNAM FLIGHT MANUAL ENGINE FIRE DURING FLIGHT M tac om P Fuel shutoff valves OFF Electric fuel pump OFF Cabin heat OFF Throttle all in Magnetos OFF Do not attempt air start Flaps as necessary Carry out emergency procedure for forced landing CABIN FIRE DURING FLIGHT 1 Master switch OFF 2 Cabin heat OFF 3 Door vents open 4 Direct fire extinguisher towards flame base 5 Carry out emergency procedure for forced landing GLIDE 1 Flaps retract 2 Speed at 600 kg 69KIAS 550 kg 66KIAS 450 kg 60KIAS 3 Glide ratio is 12 2 therefore with 1000ft elevation it is possible to cover 3 8 km 2 nautical miles in zero wind conditions LANDING EMERGENCIES FORCED LANDING WITHOUT ENGINE POWER 1 SANAMWKRWN Suggested airspeed 69 KIAS for 600kg MTOW 66 KIAS for 550kg MTOW 60 KIAS for 450kg Locate most suit
48. ch located on the upper central area of the instrument panel interrupts power supply to the trim system in case of malfunction The following placard 15 positioned near switch Circuit breakers are located on lower right side of instrument panel and each breaker 15 individually marked as follows from left to right RIM FLAP 7 5A STROBE 5 BATT 254 STALL 14 34 Televel OP INSTR 7 54 T 104 Fuel PUMP 7 54 COM 10 GPS 5A Transp ENC 24 Audio 5 INAV L 7 54 AVAILABLE AVAILABLE AVAILABLE The flap control switch is located on the lower portion of the instrument panel slightly towards the right The following placards are just next to it FLAP A placard measuring 74x7 mm is located on the instrument panel to indicate fire extinguisher position FIRE EXTINGU SHER ON BA gt Q Date Issue 3 25 May 2010 7 13 COSTRUZIONI AERONAUTICHE P92 JS FLIGHT MANUAL SECTION Generator and Master switches are located on the lower left side of the instrument panel and 4 labels are placed around them one on top one on RH side one on bottom and one on LH side gt god generator warning light is located the upper right side of the in
49. e Datum Propeller support flange w o spacer Equipment list date MAC 1400 mm 1405 D DATUM Horizontal Reference Plumb Line 9 W2 WL WR Plumb bob distance LH wheel Nose wheel weight Wi LH wheel weight WL RH wheel weight WR Wi Wg Plumb bob distance RH wheel Average distance Ag 2 Bob distance from nose wheel B Empty weight moment M D 1 405 Kg m Maximum takeoff weight 550kg W4 2 600kg Maximum payload Wz We 1 Including unusable fuel 2 3 kg Date Issue 3rev1 25 February 2015 6 4 P92 JS COSTRUZIONI AERONAUTICHE S E C TI N 6 XX TECNAM __ MANUAL _ WEIGHT AND BALANCE To determine the aircraft s CG location and to verify that the CG falls within the predetermined CG travel range it is necessary to use the chart in the following page Chart reports CG location as a function of the empty weight moment with respect to the datum as yielded by weighing report USE OF WEIGHT amp BALANCE CHART page 6 6 In order to use the graph it is necessary to know the value of the moment arm with respect to the datum Once this value is found on the abscissa a parallel to the oblique lines is drawn until it intersects the ordinate relative to the weight of pilot and passenger From this point a new line is drawn horizontally up to limi
50. e 3 25 May 2010 7 1 P92 JS TECNAM FLIGHT MANUAL SECTION 7 INTRODUCTION This section provides description and operation of the aircraft and its systems AIRFRAME WING The wing is constructed of a central light alloy torque box an aluminum leading edge with integrated fuel tank is attached to the front spar while flap and aileron are hinged to rear spar Flaps are constructed of a center spar to which front and rear ribs are joined wrap around aluminum skin panels cover the flap structure The aileron is constructed of an aluminum spar to which a formed sheet metal leading edge and metal ribs are attached a wrap around thermosetting synthetic material covers aileron structure Fig 7 1 RIGHT WING EXPLODED VIEW Date Issue 3 25 May 2010 7 2 P92 JS COSTRUZIONI AERONAUTICHE SECTION 7 MANUAL SYSTEMS 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 and a light alloy semi monocoque structure for the cabin s bottom section The aft part of the fuselage is constructed of an aluminum alloy semi monocoque structure The engine housing is isolated from the cabin by a stainless steel firewall the steel stringers engine mount is attached to the cabin s truss structure in four points EMPENNAGES The vertical tail is entirely metal the vertical stabilizer is made up of a twin spar with stressed skin while t
51. e is 15 C at sea level pressure altitude and decreased by 2 C for each 1000 ft of altitude Pressure Altitude is the altitude read from an altimeter when the barometric subscale has been set to 1013 mb ENGINE POWER TERMINOLOGY RPM Revolutions Per Minute is the number of revolutions per minute of the propeller multiplied by 2 4286 yields engine RPM AIRPLANE PERFORMANCE AND FLIGHT PLANNING TERMINOLOGY Crosswind is the velocity of the crosswind component for which adequate Velocity control of the airplane during takeoff and landing is guaranteed Usable fuel is the fuel available for flight planning Unusable fuel 15 the quantity of fuel that cannot be safely used in flight g is the acceleration of gravity TOR is the takeoff distance measured from actual start to wheel liftoff point TOD is total takeoff distance measured from start to 15m obstacle clearing GR is the distance measured during landing from actual touchdown to stop point LD is the distance measured during landing from 15m obstacle clearing to actual stop S R is specific range that is the distance in nautical miles which can be expected at a specific power setting and or flight configuration per kilo of fuel used Date Issue 3 25 May2010 1 9 COSTRUZIONI AERONAUTICHE TECNAM P92 JS FLIGHT MANUAL GENERAL WEIGHT AND BALANCE TERMINOLOGY Datum Arm Moment C G Standard Empty Weight Basic Empty Weight Useful Load Maximu
52. e remember that the banner flies approx 50ft below the aeroplane BEFORE LANDING Check the banner attitude Set a glide to release the banner on the runway To avoid banner s damage release it at a height above ground level not exceeding 100ft Pull the release lever Proceed with a normal landing and check that the banner has been removed from the runway 2 5 PERFORMANCE INTRODUCTION This section provides all necessary data for accurate and comprehensive planning of flight activity from take off to landing in towing conditions Sections approved by EASA are marked by Approved data immediately following the paragraph head line Date Issue 3 25 May 2010 9 11 COSTRUZIONI AERONAUTICHE S E C TI 9 P92 JS COSTRUZIONI AERONAUTICHE SECTION 9 TECNAM FLIGHT MANUAL SUPPLEMENTS TAKE OFF PERFORMANCES Approved data TAKE OFF RUN AND DISTANCE TOWING A BANNER UP TO 140 CONDITIONS 15 Runway dry compact grass runway Take off weight 460 kg Runway slope 0 Engine throttle Full Wind zero Banner surface 140 Press GRND DISTANCE GHND DISTANCE GRND DISTANCE GRND DISTANCE Alt mn 15m 1 15 15m d iig 15m v 332 363 WARNING To obtain take off climb rate of 2m s or higher form every airfield altitude and temperature conditions the maximum take off weight with a banner of 140m should not exceed 460kg Date Issue 3 25
53. eed e external temperature e altitude weight type and condition of runway Sections approved by ENAC are highlighted by the writing Approved data immediately following the paragraph USE OF PERFORMANCE CHARTS Performance data is presented in tabular or graphical form to illustrate the effect of different variables such as altitude temperature and weight Given information is sufficient to plan journey with required precision and safety Additional information is provided for each table or graph Date Issue 3 25 May 2010 5 2 CAS kts P92 JS COSTRUZIONI AERONAJTICHE SECTION 5 14 TECNAM MANUAL Promance AIRSPEED INDICATOR SYSTEM CALIBRATION Approved data Graph shows calibrated airspeed Vcas as a function of indicated airspeed V js 110 120 130 140 40 50 60 70 80 90 100 78 IAS kts Fig 5 1 CALIBRATED VS INDICATED AIRSPEED BOTH MTOW Example Given Find Vias 78 Kts Vecas 75 Kts Indicated airspeed assumes 0 instrument error Date Issue 3 25 May 2010 P92 JS COSTRUZIONI AERONAJTICHE FLIGHT MANUAL P
54. enance requirements which must be followed if the aircraft is to retain its new plane performance and dependability It is recommended to follow a planned schedule of lubrication and preventive maintenance based on climatic and flying conditions encountered locally AIRCRAFT INSPECTION PERIODS Inspection intervals occur at 100 hours and in accordance with special inspection schedules which are added to regularly scheduled inspections Correct maintenance procedures are described in the aircraft s Service Manual or in the engine s Service Manual AIRCRAFT ALTERATIONS OR REPAIRS It is essential that the responsible Airworthiness Authority be contacted prior to any alterations on the aircraft to ensure that airworthiness of the aircraft is not violated For repairs refer to aircraft s Service Manual GROUND HANDLING TOWING The aircraft 15 most easily and safely maneuvered by hand by pushing on wing struts near attachments or by pulling it by its propeller near the axle A tow bar can be fixed onto nose gear fork Aircraft may be steered by turning rudder or for steep turns by pushing lightly on tailcone to lift nose wheel PARKING AND TIE DOWN When parking airplane outdoors head it into the wind and set the parking brake If chocks or wedges are available it is preferable to use the latter In severe weather and high wind conditions it is wise to tie the airplane down Tie down ropes shall be fastened to the wing strut attachments
55. er 9 MANEUVERING LOAD FACTOR LIMITS eere 9 BEIGHEGREW E E 10 KINDS OF 2 ee on pne Pagus 10 PETRA 10 MAXIMUM PASSENGER 5 26 20 11 CROSSWIND LIMITATIONS eee eene 11 LIMITATION 5 5 2 0 07 1 100 000000 11 Date Issue 3 25 May 2010 2 1 COSTRUZIONI AERONAUTICHE lt lt TECNAM INTRODUCTION MANUAL P92 JS SECTION 2 LIMITATIONS Section 2 includes operating limitations instrument markings and basic placards necessary for safe operation of the P92 JS standard equipment NOTE Refer to section 9 for possible variations to AIRSPEED LIMITATIONS its engine standard systems and Airspeed limitations and their operational significance are shown below 550 kg 600 kg KIAS KCAS KIAS Never exceed Maximum Structural 106 102 110 Cruising Speed Maximum flap extended speed Maneuverin V g speed Date Issue 3 25 May 2010 REMARKS Never exceed this speed in any operation Never exceed this speed unless in smooth air and then only with caution Do not make full or abrupt control movements above this speed as this may cause stress in
56. excess of limit load factor Never exceed this speed for any given flap setting 2 2 COSTRUZIONI AERONAUTICI P92 JS FLIGHT MANUAL AIRSPEED INDICATOR MARKINGS Airspeed indicator markings and their color code are explained in the following table Refer to section 9 of this Flight Manual for operational limitations for aircraft fitted with optional equipment 550kg 600 kg MARKING MTOW MTOW SIGNIFICANCE KIAS White arc 43 68 41 71 Flap Operating Range lower limit is at maximum weight and upper limit is maximum speed permissible with flaps extension to maximum positive Green arc 48 106 46 110 Normal Operating Range lower limit is Vsi at maximum weight and most forward c g with flaps retracted and upper limit is maximum structural speed V yo Yellow 106 134 110 141 Maneuvers must be conducted with caution arc and only in smooth air Maximum speed for all operations d CAUTION P92 JS with MTOW 550kg the low limit of the white arc tM 1 1 1 Vso while the low limit of the green arc is 1 1Vs Date Issue 3 25 May 2010 2 3 COSTRUZIONI AERONAUTICHE P92 JS MANUAL SECTION POWERPLANT LIMITATIONS The following table lists operating limitations for aircraft installed engine ENGINE MANUFACTURER Bombardier Rotax GmbH ENGINE MODEL 912 52 MAXIMUM POWER
57. he rudder consists of an aluminum torque stringer connected to light alloy ribs and skin The horizontal tail is an all moving type stabilator its structure consists of an aluminum tubular spar connected to ribs and leading edge wrap around thermoretractible synthetic material covers the stabilator structure FLIGHT CONTROLS Aircraft flight controls are operated through conventional stick and rudder pedals Longitudinal control acts through a system of push rods and is equipped with a trim tab Aileron control is of mixed type with push rods and cables the cable control circuit is confined within the cabin and is connected to a pair of push rods positioned in the wings that control ailerons differentially Aileron trimming is carried out on ground through a small tab positioned on left aileron Flaps are extended via an electric servo actuator controlled by a switch on the instrument panel Flaps act in continuous mode the indicator displays the two positions relative to takeoff 15 and landing 38 A breaker positioned on the right side of the instrument panel protects the electric circuit Longitudinal trim is performed by a small tab positioned on the stabilator and controlled via an electric servo by pushing an Up Down push button on the control stick A shunt switch placed on the instrument panel enables control of either left or right stick in addition a safety switch positioned by the trim indicator shuts off power from the circuit
58. ht 2 500 m 2 500 m EMPENNAGE Stabilator span 2 900 m 2 900 m Vertical tail span 1 230 m 1 230 m LANDING GEAR Wheel track 1 800 m 1 800 m Wheel base 1 600 m 1 600 m Main gear tires Air Trac 5 00 5 5 00 5 Cleveland wheel hub and brakes kit 199 102 199 102 Nose gear tire Sava 4 00 6 4 00 6 CONTROL SURFACES TRAVEL LIMITS Ailerons Up 20 down 15 2 Stabilator Up 18 down 3 1 Trim Tab 29212 ae 12 Rudder 25 LH 25 1 Flaps 0 38 1 Date Issue 3 25 May2010 l 4 P92 JS COSTRUZIONI AERONAUTICHE S E C TI 1 K TECNAM FLIGHT MANUAL GENERAL ENGINE Manufacturer Bombardier Rotax GmbH Model 912 S2 Certification basis FAR 33 Amendment 15 Austrian Type n TW 9 ACG of 27 Nov 1998 Certification No Type 4 cylinder horizontally opposed twins with overall displacement of 1352 c c mixed cooling water cooled heads and air cooled cylinders twin carburettors integrated reduction gear with torque damper Maximum power 73 5 kW 98 6 hp 5800 rpm max 5 min engine s rpm 69 0 kW 92 5 hp 5500 rpm continuous PROPELLER Manufacturer HOFFMANN Propeller Certification basis CAR Part 14 Type Certification No SO E 30 of 10 12 1999 Model HO17GHM A 174 177C Number of blades 2 Diameter 1740 mm no reduction permitted Type Fixed pitch wood Date Issue 3 25 May2010 1 5 P92 JS COSTRUZIONI AERONAUTICHE SECTION 1 lt lt TECNAM FLIGHT MANUAL GENERAT FUEL Fuel grade High oc
59. idle Brakes maximum braking Runway dry compact grass Slope 0 Wind zero Conditions ISA Flaps 38 Hp ft 1000 2000 3000 4000 5000 Maximum weight 600kg Engine throttle idle Brakes maximum braking Runway dry compact grass Slope 0 Wind zero Conditions ISA Flaps 38 Hp ft 1000 2000 3000 4000 5000 1 Decrease distances by 10 for each 10 of headwind Increase distances 20 96 for each 10 Kts of tailwind For and paved runway operation increase ground run by 10 If it becomes necessary to land without flap extension flap malfunction increase approach speed by 10 Kts increase by 40 distance pertaining to flap setting at 38 and increase to 58 KIAS 61KIAS for 550 kg MTOW 600 kg 4 speed over obstacle is 48 KIAS 50 KIAS for 550 kg MTOW 600 kg Date Issue 3 25 May 2010 5 13 COSTRUZIONI lt FLIGHT MANUAL Flight tests have demonstrated that neither rain nor insect impact build up on leading edge have caused substantial variations to aircraft s flight qualities Such variations fall within JAR VLA tolerance limits as they are not above 5 Kts for P92 JS SECTION 5 PERFORMANCE CONSEQUENCES FROM RAIN AND INSECT stalls 100 ft min for climb rates and 50 m for takeoff runs NOISE DATA Noise level was determined according to JAR 36 Sub C Ed 23 May 1997 ICAO Annex 16 Chap 10
60. ind velocity 20 Kts Crosswind 10 Kts LL TL yy 20 50 30 46 40 P H Mul n 30 SAFE OPERATION UNSAFE OPERATION e X ju NI gt No z 20 5 5 70 175 7 f E Mi gt a t x t _ 1 e lt LEE ESSN 90 EE ER IN ERN 10 100 n E 80 160 B 149 igi 120 110 0 10 20 30 40 50 CROSSWIND COMPONENT Kts Fig 5 3 CROSSWIND CHART Date Issue 3 25 May 2010 5 6 P92 JS gt COSTRUZIONI AERONAJTICHE SECTIO N 5 14 TECNAM Fucur MANUAL TAKEOFF PERFORMANCE Approved data TAKEOFF DISTANCE CONDITIONS Flaps 15 MTOW 550kg MTOW 600kg Engine full throttle see Sect 4 47 48 KIAS Runway dry compact grass Vos 56 KIAS 58 KIAS Slope 0 Wind zero 49 KIAS 51 R C 2 200 ft min NOTE 1 Decrease distances by 10 for each 10 Kts of headwind Increase distances by 20 for each 10 Kts of tailwind 2 For dry and paved runway operation decrease ground 700 run by 6 5 650 Example 2 Given Find b d O A T 2 15 253m m Pressure altitude 2900 ft 117m MTOW 600kg s Weight 450 Kg 450 TOR 400 jT WR 350 300 2 609 253 250 REFERENCE LINE i yes 3000
61. inute Knots Kilometers hour PRESSURE Atmosphere Pounds sq in LENGTH Kilometers Nautical miles Meters Feet Centimeters Inches VOLUME Liters U S Gallons AREA Square meters Square feet Date Issue 3 25 May2010 FLIGHT MANUAL P92 JS YIELDS Celsius Fahrenheit Pounds Kilograms Feet per minute Meters per second Kilometers hour Knots Pounds sq in Atmosphere Nautical miles Kilometers Feet Meters Inches Centimeters U S Gallons Liters Square feet Square meters SECTION 1 GENERAL COSTRUZIONI AERONAUTICHE P92 JS FLIGHT MANUAL GENERAL INTENTIONALLY LEFT BLANK Date Issue 3 25 May2010 1 12 P92 JS TECNAM FLIGHT MANUAL SECTION 2 LIMITATIONS TABLE OF CONTENTS 2 AIRSPEED eese sene nen 2 AIRSPEED INDICATOR 2 0 3 POWERPLANT LIMITATIONS eere 4 PROPBELDER einn bete 6 POWERPLANT INSTRUMENT 00 7 OTHER INSTRUMENT 7 BASLER T 8 CENTER OF GRAVITY 2 2 40 00000000 8 APPROVED MANEUVERS eee eene entr
62. ions while towing banner of 140m is 30008 Date Issue 3 25 May 2010 9 7 P92 JS COSTRUZIONI AERONAUTICHE S E C TI 9 AIRSPEED For all flap settings the minimum towing airspeed is 53 KIAS WARNING The maximum towing airspeed depends on the banner s surface For further information please refer to banner manufacturer specifications limitations APPROVED MANEOUVRES The P92 JS while towing a banner is cleared to do only the manoeuvres pertinent to normal flight DEMONSTRATED CROSS WIND OPERATIONS The aircraft s controllability was investigated during take off with a cross wind velocity of 5 kts LIMITATION PALACARDS On the instrument panel the following limitation placards must be present MINIMUM TOWING AIRSPEED 53 KIAS REFER TO FLIGHT MANUAL SUPPLEMENT 9 2 FOR LIMITATIONS DURING TOWING OPERATIONS Date Issue 3 25 May 2010 9 8 P92 JS COSTRUZIONI AERONAUTICHE S E C TI 9 2 3 EMERGENCY PROCEDURES EMERGENCY RELEASE 1 Find a safe location on the ground for the banner s release 2 Activate the release lever If the banner is properly released 3 Control the a c 4 Land If the banner doesn t release 5 Hlap as necessary 6 Engine throttle as necessary 7 Ifthe runway s length allows set a landing glide so as to ground the banner at the runway s head Control the banner s position 9 Land If the banner is hold by
63. irection of spin 3 Move and hold stick forward until spin is halted 4 Neutralize rudder 5 a smooth recovery by pulling the stick back gently averting speeds in excess of and maximum load factor Readjust throttle to restore engine power gt Date Issue 3 25 May 2010 3 6 P92 JS DOSTRUZION AERCAAUTICHE SECTION 3 TECNAM FLIGHT MANUAL EMERGENCY PROC EDURES OTHER EMERGENCIES UNINTENTIONAL FLIGHT INTO ICING CONDITIONS 1 Getaway from icing conditions by changing altitude or direction of flight in order to reach an area with warmer external temperature 2 Avoid possible freeze up of control surfaces by recurrently moving them 3 Carb heat ON 4 Increase RPMs to avoid ice formation on propeller blades 5 Cabin heat ON In case of ice formation on wing leading edge stall speed may increase CARBURETOR HEAT AT TAKEOFF At takeoff given the unlikely possibility of ice formation at full throttle carburetor heat is normally OFF IN FLIGHT With external temperatures below 15 C or on rainy days or with humid cloudy hazy or foggy conditions or whenever a power loss is detected turn carb heat to ON until engine power is back to normal ELECTRIC POWER SYSTEM MALFUNCTION Electric power supply system malfunctions may be avoided by carrying out inspections as scheduled and prescribed in the Service Manual Causes for malfunctions are hard to establish but in any case problems of this nature mu
64. it e Hand held fire extinguisher For further standard equipment refer to section 6 Flight into expected and or known icing conditions is prohibited FUEL TWO TANKS 35 liters each 45 liters optional TOTAL FUEL CAPACITY 70 liters 90 liters USABLE FUEL 66 8 liters 86 8 liters UNUSABLE FUEL 3 2 liters 3 2 liters During all phases of flight engine fuel feed must be supplied by both tanks Compensate uneven fuel tank levels by acting on fuel taps located in cabin Date Issue 3 25 May 2010 2 10 P92 JS lt lt TECNAM FLIGHT MANUAL SAONE APPROVED FUEL High octane gasoline DIN 51600 O NORM 1103 Unleaded gasoline DIN 51603 O NORM 1101 AVGAS 100LL see Warning below WARNING Prolonged use of Aviation Fuel Avgas 100LL results greater wear of valve seats and greater combustion deposits inside cylinders due to higher lead content It is therefore suggested to avoid using this type of fuel unless strictly necessary MAXIMUM PASSENGER SEATING Only one passenger is allowed on board this aircraft CROSSWIND LIMITATIONS Maximum allowed crosswind component is 15 Kts refer to section 5 for further details LIMITATION PLACARDS The following limitation placards must be placed in plain view on the aircraft Near the airspeed indicator a placard will state the following MANEUVERING SPEED V 93 KIAS For 550 kg MTOW MANEUVERING SPEED 97 KIAS For 600 ks MTOW Date Issue 3 25 May 2010 2 11 CO
65. ll extension checking travel limits and instrument indication N Trim control activate control to full scale checking travel limits and instrument indication Acoustic stall warning check operation Navigation lights and strobe light check operation Landing light check operation Generator switch OFF Master switch OFF Fuel level check level on the basis of flight plan Baggage check for proper stowage with tie down net Date Issue 3 25 May 2010 4 3 COSTRUZXON AERONAUTICHE P92 JS FLIGHT MANUAL NORMA CE WARNING Fuel level indicated by the fuel quantity indicators on the instrument panel is only indicative For flight safety pilot should verify actual fuel quantity embarked before takeoff EXTERNAL INSPECTION To carry out the external inspection it will be necessary to follow the checklist below with the station order outlined in fig 4 1 WARNING Visual inspection is defined as follows check for defects cracks detachments excessive play unsafe or improper installation as well as for general condition For control surfaces visual inspection also involves additional check for freedom of movement and security A Left hand fuel filler cap check visually for desired fuel level and secure Left tank vent check for obstructions i deos 1 l
66. m Weight Maximum Takeoff Weight Maximum Landing Weight Tare Date Issue 3 25 May2010 is an imaginary vertical plane from which all horizontal distances are measured for balance purposes is the horizontal distance from the reference datum to the center of gravity C G of an item is the product of the weight of an item multiplied by its arm Center of Gravity is the point at which the airplane or equipment would balance if suspended Its distance from the reference datum is found by dividing the total moment by the total weight of the airplane Standard Empty Weight is the weight of a standard airplane including unusable fuel full operating fuels and full engine oil is the standard empty weight plus the weight of optional equipment 15 the difference between takeoff weight and the basic empty weight is the maximum certified weight of the aircraft is the maximum weight approved for the start of the takeoff run is the maximum weight approved for the landing touch down is the weight of chocks blocks stands etc used when weighing an airplane and is included in the scale readings Tare is deducted from the scale reading to obtain the actual net airplane weight l 10 SECTION 1 COSTRUZIONI AERONAUTICHE TECNAM UNIT CONVERSION CHART MULTIPLYING TEMPERATURE Fahrenheit 5 g F 32 Celsius E 32 FORCES Kilograms Pounds SPEED Meters per second Feet per m
67. ments panel Figure 9 4 Date Issue rev 1 25 February 2015 9 24 P92 JS rur COSTRUZIONI AERONAUTICHE SECTION 9 TECNAM FLIGHT MANUAL SUPPLEMENTS SUPPLEMENT N 6 CHINESE AIRCRAFT FLIGHT MANUAL SUPPLEMENT Record of Revisions sui EASA Approval or Under DOA pag Privileges DOA Date Issue 3rev1 25 February 2015 9 25 COSTRUZIONI AERONAUTICHE lt lt lt TECNAM 1 MANUAL P92 JS SECTION 9 SUPPLEMENTS PLACARD IN CHINESE Placard Chinese THROTTLE 4 AA THROTTLE LOCK CABIN HEAT Pull on CARB HEAT Pull on BEJF TRIM DISCONNECT ON OFF x Date Issue 3rev1 25 February 2015 P92 JS TECNAM FLIGHT MANUAL SECTION 9 Placard CU EF GF FF BR RL 4 4 R OFF Left Tank Right Tonk 49 5 Usable fuel Usable fuel ody 49 5 litres 49 5 litres 49 54 ON X TIE DOWN HARNE ii Sin s E REGOLARE LE CINGHIE pisi PESO MASSIMO 20kg SPEC PRESS 12 5 kg dm i MAX PRESS
68. nd correct CG position see section 6 Seat position and safety belts adjustment IV Doors secured V Parking brake ON Avionics general switch must be OFF during engine startup to avoid damage to avionics instrumentation STARTING ENGINE I Circuit Breakers check IN IL Master switch ON Check Voltmeter and Ammeter Fuel shutoff valves both ON Date Issue 3 25 May 2010 4 6 P92 JS TECNAM FLIGHT MANUAL NORMAL PROCEDURES IV Electric fuel pump ON check for audible pump noise and fuel pressure V Engine throttle to idle VI Choke as needed VII Set Magnetos switch to BOTH VIII Propeller area CLEAR WARNING Check to insure no person or object is present in the area close to propeller IX Ignition key set to START X Generator switch and check Ammeter green Propeller rpm 1000 1100 rpm XII Choke OFF XIII Check engine instruments XIV Check oil pressure rise within10 sec maximum cold value 7 bar XV Hlectric fuel pump OFF XVI Check fuel pressure XVII Electric fuel pump ON BEFORE TAXIING I Radio and utilities ON IL Altimeter reset Navigation lights as required IV Request control tower O K parking brake OFF and taxi TAXIING I Brakes CHECK Date Issue 3 25 May 2010 4 7 COSTRUZION AERONAUTICHE P92 JS TECNAM FLIGHT MANUAL NORMAL PROCEDURES Flight instruments CHECK PRIOR TO TAKE OFF 1 Parking brake ON II Turn
69. ng procedure refer to Service Manual CLEANING AND CARE To clean painted surfaces use a mild detergent such as shampoo normally used for car finish use a soft cloth for drying The plastic windshield and windows should never be dusted when dry use lukewarm soapy water and dry using chamois only It is possible to use special glass detergents but in any case never use products such as gasoline alcohol acetone or other solvents To clean cabin interior seats upholstery and carpet it is generally recommended to use foam type detergents Date Issue 3 25 May 2010 8 3 COSTRUZIONI AERONAJTICHE P92 JS TECNAM FLIGHT MANUAL SECON 8 DUNG amp SERVICE LEFT INTENTIONALLY BLANK Date Issue 3 25 May 2010 8 4 P92 JS Date Issue 3 25 May 2010 9 1 COSTRUZIONI AERONAUTICHE SEC TI ON 9 lt lt TECNAM FLIGHT MANUAL SUPLEMENTE SECTION 9 SUPPLEMENTS TABLE OF CONTENTS GARMIN GNS 430 GPS VHF 0000000011 3 1 INTRODUCTION 3 1 2 T E Em 3 1 3 pel ccr 4 1 4 EMERGENCY PROCEDURES 5 1 5 NORMAL 5 1 6 PERFORMANCE e 5 1 7 WEIGHT 21 21 1 1 1 6 1 8 SISIBMS um necu A A Le eMe E E DLE 6 BANNER 7 2 IINTRODUGHON P 7 2 1 e
70. nner condition check for nicks and security T Open engine cowling and perform the following checklist I Check no foreign objects are present IL Check the cooling circuit for losses check coolant reservoir level insure radiator honeycomb is unobstructed Check lubrication circuit for losses check oil reservoir level insure radiator honeycomb is unobstructed IV Open both fuel shutoff valves inspect fuel circuit for losses check integrity of fireproof protection braids drain circuit using a cup to collect fuel by opening the specific drainage valve located on the firewall close shutoff fuel valves Check for water or other contaminants Date Issue 3 25 May 2010 4 5 COSTRUZION AERONAUTICHE P92 JS FLIGHT MANUAL NORMAL PROCEDURES Drainage operation must be carried out with aircraft parked on level surface V Check integrity of silent block suspensions VI Check connection and integrity of air intake system visually inspect that ram air intake is unobstructed VII Check that all parts are secure or safetied U Close engine cowling V Check left side static vent is unobstructed Avoid blowing inside left strut mounted pitot and inside airspeed indicator system s static vents as this may damage instruments Z Remove tow bar and chocks CHECKLISTS BEFORE STARTING ENGINE after preflight inspection L Hlight planning fuel consumption refueling II Check correct aircraft loading a
71. ocated on the upper left side of the instrument panel The sensor is placed on cabin top STALL W ARNING SYSTEM The aircraft is equipped with a stall warning system consisting of a sensor located on the right wing leading edge connected to a warning noisemaker located on the instrument panel AVIONICS The central part of the instrument panel holds room for avionics equipment The manufacturer of each individual system furnishes features for each system Date Issue 3 25 May 2010 7 9 P92 JS NAM FLIGHT MANUAL ESHON 7 EXTERNAL POWER SUPPLY On the right side of the tail cone an external power is present Using this device it is possible to feed the electric system by an external power source It should be used at the engine start up in cold weather condition Follow this procedure to start the engine using the external power source 1 99 Magnetos Master switch Generator switch OFF Open the receptacle door and insert the external power source s plug into the socket Engine start up procedure see Sect 4 in this manual Disconnect the external power source s plug and close firmly the receptacle door PITOT AND STATIC PRESSURE SYSTEMS The airspeed indicator system for the aircraft is shown below and consists of two static ports located on the sides of the aircraft forward of the cabin and by a pitot tube located on the left wing strut FIG 7 5 AIRSPEED INDICATOR SYSTEM Date Issue
72. s designed for a maximum load of 20 kg Baggage size shall prevent excessive loading of utility shelf maximum pressure 12 5 kg dm Maximum baggage size is 80x45x32 Baggage shall be secured using a tie down net to prevent any baggage movement during maneuvers OTILITY SHELF 05 1 Zin 0 45 1H 5in sn Fig 6 4 CABIN DIMENSIONS EQUIPMENT LIST The following is a comprehensive list of all TECNAM supplied equipment for the P92 JS The list consists of the following groups A Engine and accessories B Landing gear C Electrical system D Instruments E Avionics the following information describes each listing e Part number to uniquely identify the item type e description e Serial number e Weight in kilograms e Distance in meters from datum NOTE Items marked with an asterisk are part of basic installation Additionally further equipment marked with X in the Inst column are installed on the aircraft S N in subject Date Issue 3rev1 25 February 2015 6 9 COSTRUZIONI AERONAUTICI P92 JS DATE HEN 1 Engine Rotax 91252 p n 309 120 133 0 32 A2 Prop HOFFMANN petongmanane o 49 os Exhaust and manifolds 0 55 p n SSB 978 480 CC Heat exchanger p n 92 11 830 200 0 55 Oil Reservoir full p n 956 137 radiator p n 886 025 Liquid coolant radiator p n 99
73. st be dealt with immediately The following may occur GENERATOR LIGHT ILLUMINATES Generator light may illuminate for a faulty alternator or when voltage is above 16V in this case the overvoltage sensor automatically shuts down the alternator Date Issue 3 25 May 2010 3 7 u P92 JS COSTRUZIONI AERONAUTICHE SECTION 3 TECNAM FLIGHT MANUAL _ In both cases proceed as follows 1 Generator switch and master switch OFF 2 Generator switch and master switch ON If the problem no longer persists normal alternator charging will resume and the warning light will turn off proving voltage surcharge was temporary no further action is required If light remains illuminated a generator malfunction is confirmed In this case set Generator switch to OFF and continue flight on battery power alone the battery is capable of supplying the electrical system for about 26 min with normal flight loads including operation of com nav flap and trim TRIM SYSTEM FAILURE LOCKED CONTROL In case the trim control should not respond act as follows 1 Check switch for correct position 2 Adjust speed to control aircraft without excessive stick force 3 Land aircraft as soon as possible RUNAWAY If trim position indicator reads displacement without pilot s action on trim control follow procedure below 1 Trim power switch OFF 2 Adjust speed to control aircraft without excessive stick force 3 Land
74. strument panel and is marked with the following label ALT Date Issue 3 rev 1 25 February 2015 7 14 P92 JS COSTRUZIONI AERONAUTICHE S E C TI N 7 TECNAM MANUAL SYSTEMS PLACARDS OUTSIDE CABIN The overflow reservoir cap for antifreeze liquid bears 80 ANTIFREEZE the following placard A 20 WATER SPECIFY Brake fluid reservoir cap bears the following placard DRA E Sd PIE MIL s The following placard is located in proximity of fuel filler caps 28x63mm AUTOMOTIVE FUEL ROZ MIN 95 OCT AUTOMOTIVE FUEL ROZ MIN 95 OCT LEADED OR UNLEADED LEADED OR UNLEADED AVGAS 100LL AVGAS 100LL CAPACITY 35 LT 9 2 US gal CAPACITY 45 LT 11 9 US gal The following placards are located on oil reservoir AUTOMOTIVE OIL AUTOMOTIVE OIL API SE OR eo CAPACITY 50 The following label is located below each door for emergency opening IN CASE OF EMERGENCY Date Issue 3 25 May 2010 7 15 TECNAM MANUAL Main landing gear tire inflation pressure is indicated in the following label affixed on each spring leaf strut The following label indicates inflation pressure for nose gear tire and is affixed on nose gear assy The 0 reference mark for stabilator balance is located on left hand side of tail cone in proximity of stabilator P92 JS SECTION 7
75. sumption Endurance hrs Range N m RPM KTAS 1 2 1 2 55 2120 99 15 4 5 5 6 445 578 58 2150 102 16 4 2 5 4 428 556 Pressure altitude Hp 10000 ft OAT 5 Propeller Consumption Endurance hrs l Range N m RPM 15 Pressure altitude Hp _ 12000 ft OAT 9T Propeller Consumption Endurance hrs Range N m RPM d h Range and endurance are intended approximate and referred to zero wind condition Date Issue 3 25 May 2010 5 11 P92 JS COSTRUZIONI AERONAJTICHE TECNAM FLIGHT MANUAL 2 BALKED LANDING RATE OF CLIMB BALKED LANDING CONDITIONS Maximum weight 550 kg 600kg Haps 38 48 KIAS 50 KIAS Engine full throttle max 5 During balked landing maneuver flaps should be retracted immediately after applying full power 8000 7000 6000 4000 PRESSURE ALTITUDE ft 2000 0 100 200 500 400 500 RATE OF CLIMB ft min Fig 5 6 BALKED LANDING MTOW 550KG Example Given Find Pressure altitude 7000 ft Rate of climb 230 ft min Conditions ISA If the maximum takeoff weight is 600 kg the rate of climb decreases about 1096 Date Issue 3 25 May 2010 5 12 P92 JS COSTRUZIONI AERONAJTICHE SECTION 5 14 TECNAM Fucur MANUAL LANDING DISTANCE Approved data CONDITIONS Maximum weight 550 kg 600kg Engine throttle
76. t value of 180 kg and from here a parallel to the oblique lines is drawn until it intersects with the abscissa relative to fuel weight carried on board A horizontal line is then drawn through this point up to limit value of 70 liters and a new parallel to the oblique lines is drawn until abscissa is intercepted relative to baggage loaded on board behind the seats Another horizontal line is drawn and it is thus possible to verify that the intersection of this segment with the vertical abscissa relative to the aircraft s takeoff total weight falls within the shaded area which represents the admissible CG range as a function of total weight Pages 6 and 7 show charts of CG travel as a function of aircraft weight distances in meters of pilots and baggage from datum propeller support flange is also provided EXAMPLE see page 6 6 Empty weight moment 562 kg m Pilot and passenger 160 kg Fuel 50 Lit Baggage 15 kg Takeoff weight 536 kg Date Issue 3rev1 25 February 2015 6 5 P92 JS FLIGHT MANUAL WEIGHT amp BALANCE e 2 e 2 O SN S 2 MD 2 o 5 v S FB S S 5 d sj D S eut h o 50 N gt E
77. tane gasoline DIN 51600 O NORM 1103 red Unleaded gasoline DIN 51603 O NORM 1101 AVGAS 100LL see Section 2 9 Fuel tanks 2 wing tanks integrated within the wings leading edge with fuel strainer located in engine cowling Capacity of each wing tank 35 liters optional 45 liters Total capacity 70 liters optional 90 liters Total usable fuel 66 8 liters 86 8 liters OIL SYSTEM Oil system type Forced with external oil reservoir Oil Automotive grade API SF or SG type oil preferably synthetic or semi synthetic Oil Capacity 3 5 liters COOLING Cooling system Mixed air and liquid pressurized closed circuit system Coolant Antifreeze and water liquid mixture Capacity 3 liters Date Issue 3 25 May2010 6 COSTRUZIONI AERONAUTICI P92 JS MAXIMUM CERTIFIED WEIGHTS Maximum take off weight 550 kg 600 kg Maximum landing weight 550 kg 600 kg Maximum baggage weight 20 kg 20 kg STANDARD WEIGHTS Standard Empty Weight 325 kg 325 kg Maximum Useful Load 225 kg 275 kg SPECIFIC LOADINGS Wing Loading 45 8 kg m 50 kg m Power Loading 5 6 kg hp 6 1 kg hp Date Issue 3 25 May2010 1 7 COSTRUZIONI AERONAUTICHE P92 JS TECNAM FLIGHT MANUAL GENERAL ABBREVIATIONS AND TERMINOLOGY GENERAL AIRSPEED TERMINOLOGY AND SYMBOLS KCAS Knots Calibrated Airspeed is indicated airspeed corrected for position and instrument error and expressed in knots KIAS Knots Indic
78. to section 6 for appropriate instructions Date Issue 3 25 May 2010 2 8 P92 JS TECNAM MANUAL APPROVED MANEUVERS This aircraft is certified in the CS VLA category CS VLA applies to airplanes intended for non aerobatic operation only Non aerobatic operation includes e Any maneuver pertaining to normal flight e Stalls except whip stalls Lazy eights e Chandelles e Turns in which the angle of bank is not more than 60 Acrobatic maneuvers including spins are not approved Recommended entry speed for each approved maneuver is as follows MANEUVER KIAS 550 kg MTOW 600 kg MTOW Lazy eights 93 97 Chandelles 93 97 Steep turns max 60 93 97 Stalls Slow Deceleration 1 Kts sec Slow Deceleration 1 Kts sec MANEUVERING LOAD FACTOR LIMITS Maneuvering load factors are as follows FLAPS 0 13 8 1 9 38 411 9 0 Date Issue 3 25 May 2010 2 9 P92 JS TECNAM FLIGHT MANUAL FLIGHT CREW Minimum crew for flight is one pilot seated on the left side KINDS OF OPERATION The airplane in standard configuration is approved only for day VFR operation with terrain visual contact Minimum equipment required is as follows e Altimeter e Airspeed Indicator e Heading Indicator Fuel Gage e Pressure Indicator e Oil Temp Indicator e Cylinder Heads Temp Indicator e Outside Air Temp indicator Tachometer e Chronometer First Aid K
79. witch of the GARMIN 430 display 16 PERFORMANCE No variations Date Issue 3 25 May 2010 9 5 92 JS COSTRUZIONI AERONAUTICHE S E C TI 9 4 FLIGHT MANUAL _ 17 WEIGHT AND BALANCE See section 6 of the present manual 1 8 SYSTEMS See GNS 430 Pilot s Guide p n 190 00140 00 rev dated July 2000 or later versions for a complete description of the system Date Issue 3 25 May 2010 9 6 P92 JS COSTRUZIONI AERONAUTICHE S E C TI 9 SUPPLEMENT NO 2 BANNER TOWING 2 INTRODUCTION This section contains supplementary information for a safe and efficient operation of the aircraft if equipped with a hook for towing banners Mod Number 92 27 21 GENERAL CERTIFICATION BASIS This installation has been certified under the technical specifications listed into the Tecnam Report 92 104 2 2 LIMITATIONS Section 2 includes operating limitations instrument markings and basic placards necessary for safe banner towing operations APPROVED BANNER DIMENSION The banner approved to be operated with the P92 JS is of the type equipped with wheels The maximum banner surface that has been towed during the tests is 140m WEIGHT The aircraft s MTOW equipped with a 140m banner reaches 460kg For banners whose surface is lower than 140m please refer to the table in paragraf 2 5 in this Section AIRFIELD ALTITUDE The highest approved airfield altitude for take off operat

P92-JS - DigiSky

Contents

Download Pdf Manuals

Related Search

Related Contents