Tecnam P92-JS Flight Manual Download

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P92-JS

I N TRODUCTI ON

LIGHT

ANUAL

Date

Issue 3, 25

May 2010

i-1

FLIGHT MANUAL

Doc. n° 92/61 Issue n°3: 25

May 2010

Revision No.0

P92-JS

ANUFACTURER

COSTRUZIONI AERONAUTICHE

TECNAM

S.r.l.

IRCRAFT MODEL

P92-JS

YPE CERTIFICATION

: n° EASA A.412 (SO/A-340)

ERIAL NUMBER

............................................................….....

UILD YEAR

..............................................................…….....

EGISTRATION MARKINGS

: .......................................................

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.

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.

Section 9 (supp.3) is approved under DOA privileges: n° MOD92/51.10.06.2009

Section 9 (supp.4) is approved under DOA privileges: n° MOD92/52.10.06.2009

Section 9 (supp.5) is approved under DOA privileges: n° MOD92/53.10.06.2009

Summary of Contents for P92-JS

Page 1: ...ther 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 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 Section 9 supp 3 ...

Page 2: ...g 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 No Affected sections Affected pages Date Approval EASA Date Date Inserted Signature ...

Page 3: ...ection 0 Pages 1 thru 4 Rev 0 Section 1 Pages 1 thru 12 Rev 0 Section 2 Pages 1 thru 10 Rev 0 Section 3 Pages 1 thru 8 Rev 0 Section 4 Pages 1 thru 12 Rev 0 Section 5 Pages 1 thru 14 Rev 0 Section 6 Pages 1 thru 12 Rev 0 Section 7 Pages 1 thru 16 Rev 0 Section 8 Pages 1 thru 4 Rev 0 Section 9 Pages 1 thru 24 Rev 0 ...

Page 4: ...ns Section 2 Emergency procedures Section 3 Normal procedures Section 4 Performance Section 5 Weight 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 ...

Page 5: ...TRODUCTION 2 CERTIFICATION BASIS 2 WARNINGS CAUTIONS NOTES 2 THREE VIEW DRAWING 3 DESCRIPTIVE DATA 4 CONTROL SURFACES TRAVEL LIMITS 4 ENGINE 5 PROPELLER 5 FUEL 6 OIL SYSTEM 6 COOLING 6 MAXIMUM CERTIFIED WEIGHTS 7 STANDARD WEIGHTS 7 SPECIFIC LOADINGS 7 ABBREVIATIONS AND TERMINOLOGY 8 UNIT CONVERSION CHART 11 ...

Page 6: ...nology 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 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 Means that the non observation of ...

Page 7: ... DRAWING Dimensions shown refer to aircraft weight of 550kg and 600 kg and normal operating tire pressure Propeller ground clearance 320mm Propeller ground clearance with deflated front tire and nosewheel shock absorber compressed by 102mm Minimum ground steering radius 5 5m NOTE ...

Page 8: ...GE Overall length 6 400 m 6 400 m Overall width 1 100 m 1 100 m Overall height 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 Cleveland wheel hub and brakes kit 5 00 5 199 102 5 00 5 199 102 Nose gear tire Sava 4 00 6 4 00 6 CONTROL SURFACES TRAVEL LIMITS Ailer...

Page 9: ...erall displacement of 1352 c c mixed cooling water cooled heads and air cooled cylinders twin carburettors integrated reduction gear with torque damper Maximum power engine s rpm 73 5 kW 98 6 hp 5800 rpm max 5 min 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 ...

Page 10: ...ainer 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 cl...

Page 11: ...XIMUM 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 m2 50 kg m2 Power Loading 5 6 kg hp 6 1 kg hp ...

Page 12: ...imum 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 VS0 Stalling speed in landing configuration VS1 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 ...

Page 13: ...NING TERMINOLOGY Crosswind Velocity is the velocity of the crosswind component for which adequate control of the airplane during takeoff and landing is guaranteed Usable fuel is the fuel available for flight planning Unusable fuel is 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 poi...

Page 14: ...eight of the airplane Standard Empty Weight Standard Empty Weight is the weight of a standard airplane including unusable fuel full operating fuels and full engine oil Basic Empty Weight is the standard empty weight plus the weight of optional equipment Useful Load is the difference between takeoff weight and the basic empty weight Maximum Weight is the maximum certified weight of the aircraft Max...

Page 15: ...0508 Meters per second m s Knots kts 1 853 Kilometers hour km h Kilometers hour km h 0 5396 Knots kts PRESSURE Atmosphere atm 14 7 Pounds sq in psi Pounds sq in psi 0 068 Atmosphere atm LENGTH Kilometers km 0 5396 Nautical miles nm Nautical miles nm 1 853 Kilometers km Meters m 3 281 Feet ft Feet ft 0 3048 Meters m Centimeters cm 0 3937 Inches in Inches in 2 540 Centimeters cm VOLUME Liters l 0 26...

Page 16: ...FLIGHT MANUAL Date Issue 3 25th May2010 I 12 P92 JS SECTION 1 GENERAL INTENTIONALLY LEFT BLANK ...

Page 17: ...ATIONS 2 AIRSPEED INDICATOR MARKINGS 3 POWERPLANT LIMITATIONS 4 PROPELLER 5 POWERPLANT INSTRUMENT MARKINGS 6 OTHER INSTRUMENT MARKINGS 6 WEIGHTS 7 CENTER OF GRAVITY RANGE 7 APPROVED MANEUVERS 8 MANEUVERING LOAD FACTOR LIMITS 8 FLIGHT CREW 8 KINDS OF OPERATION 9 FUEL 9 MAXIMUM PASSENGER SEATING 10 CROSSWIND LIMITATIONS 10 LIMITATION PLACARDS 10 ...

Page 18: ... operational significance are shown below S P E E D 550 kg MTOW 600 kg MTOW REMARKS KIAS KCAS KIAS KCAS VNE Never exceed speed 134 128 141 135 Never exceed this speed in any operation VNO Maximum Structural Cruising Speed 106 102 110 106 Never exceed this speed unless in smooth air and then only with caution VA Maneuvering speed 93 90 97 94 Do not make full or abrupt control movements above this s...

Page 19: ... Flap Operating Range lower limit is VSO 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 VS1 at maximum weight and most forward c g with flaps retracted and upper limit is maximum structural speed VNO Yellow arc 106 134 110 141 Maneuvers must be conducted with caution and only in s...

Page 20: ... Max Power kW hp Max RPM RPM prop eng Time max min Maximum 73 5 98 6 2388 5800 5 Max cont 69 92 5 2265 5500 The static rpm range at full throttle carburetors heat Off is 2100 100 prop rpm TEMPERATURES Max cylinder heads 135 C Cooling liquid monitored at cylinder heads 135 C Max Oil 130 C Min Oil 50 C OIL PRESSURE Min 0 8 bar Max 5 bar ENGINE START OPER TEMP OAT Min 25 C OAT Max 50 C Admissible pre...

Page 21: ...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 20 demineralized water PROPELLER MANUFACTURER HOFFMANN Propeller MODEL HO17GHM 174 177C or HO17GHM A 174 177C PROPELLER TYPE Wood twin blade fixed pitch DIAMETER 1740 mm no reduction permitted WARNING ...

Page 22: ...0 2265 2265 2388 2388 Oil Temp C 50 90 110 50 90 110 130 130 Cylinder heads and coolant temp C 0 135 135 Oil pressure bar 0 8 2 5 0 8 2 5 7 1 7 Fuel Press psi 2 2 2 2 5 8 5 8 Fuel quantity liters 2 OTHER INSTRUMENT MARKINGS INSTRUMENT RED LINE Minimum limit GREEN ARC Normal operating YELLOW ARC Caution RED LINE Maximum limit Suction gage 4 in Hg 4 5 5 5 in Hg Voltmeter 10 Volt 12 14 Volt 1 Admissi...

Page 23: ...2 18 m from datum 20 kg 20 kg 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 It is the pilot s responsibility to insure that the airplane is properly loaded Refer to se...

Page 24: ... eights Chandelles 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 f...

Page 25: ...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 APPROVED FUEL High octane gasoline DIN 51600...

Page 26: ... the airspeed indicator a placard will state the following MANEUVERING SPEED VA 93 KIAS MANEUVERING SPEED VA 97 KIAS On the left hand side of the dashboard a placard will state the following THIS AIRPLANE IS CLASSIFIED AS A VERY LIGHT AIRPLANE APPROVED FOR DAY VFR ONLY IN NON ICING CONDITIONS ALL AEROBATIC MANEUVERS INCLUDING INTENTIONAL SPIN ARE PROHIBITED SEE FLIGHT MANUAL FOR OTHER LIMITATIONS ...

Page 27: ...10 3 1 P92 JS SECTION 3 EMERGENCY PROCEDURES SECTION 3 EMERGENCY PROCEDURES TABLE OF CONTENTS INTRODUCTION 2 ENGINE FAILURES 2 AIR START 4 SMOKE AND FIRE 4 GLIDE 5 LANDING EMERGENCIES 5 RECOVERY FROM UNINTENTIONAL SPIN 6 OTHER EMERGENCIES 7 ...

Page 28: ...ar 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 ari...

Page 29: ...eel 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 Land at closest airport LOW OIL PRESSURE 1 Check oil temperature ...

Page 30: ... for Forced landing SMOKE AND FIRE ENGINE FIRE WHILE PARKED OR DURING TAKEOFF 1 Fuel shutoff valves OFF 2 Electric fuel pump OFF 3 Cabin heat OFF 4 Abort takeoff if possible 5 If engine is running use up remaining fuel in carburetors 6 Magnetos OFF 7 Master switch OFF 8 Generator switch OFF 9 Warn bystanders to clear the area as fast as possible 10 Without removing the engine cowling use a CO2 or ...

Page 31: ...dure 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 Suggested airspeed 69 KIAS for 600kg MTOW 66 KIAS for 550kg MTOW 60 KIAS for 450kg 2 Locate most suitable terrain for...

Page 32: ...cklist complete 2 Flaps full 3 Land and maintain aircraft NOSE HIGH attitude as long as possible After touchdown LANDING WITH A FLAT MAIN TIRE 1 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 ...

Page 33: ...dge 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 MALFUNCT...

Page 34: ...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 swi...

Page 35: ...ANUAL Date Issue 3 25th May 2010 4 1 P92 JS SECTION 4 NORMAL PROCEDURES SECTION 4 NORMAL PROCEDURES TABLE OF CONTENTS INTRODUCTION 2 RIGGING AND DERIGGING ENGINE COWLING 2 PRE FLIGHT INSPECTIONS 3 CHECKLISTS 6 ...

Page 36: ...ugh 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 Butterfly Cam locks are locked when tabs are horizontal and open when tabs are vertical Verify tab is below latch upon closing LOWER COWLING I After disassembling upper cowling bring propeller to horizontal ...

Page 37: ...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 full extension checking t...

Page 38: ...To carry out the external inspection it will be necessary to follow the checklist below with the station order outlined in fig 4 1 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 Lef...

Page 39: ...ht 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 obstructi...

Page 40: ...f 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 Z Remove tow bar and chocks NOTE Avoid blowing inside left strut mounted pitot and inside airspeed indicator system s static vents as this may damage instruments CHECKLISTS BEFORE STARTING ENGINE after prefligh...

Page 41: ...Engine throttle to idle VI Choke as needed VII Set Magnetos switch to BOTH VIII Propeller area CLEAR Check to insure no person or object is present in the area close to propeller IX Ignition key set to START X Generator switch ON and check Ammeter green XI 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 El...

Page 42: ...rking brake ON II Turn on navigation lights strobe light and landing light III 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 i...

Page 43: ...for 550 kg MTOW and Vr 48 Kts for 600kg MTOW VIII Rotation and takeoff 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 II Set power and engine rpm s for cruise III Check engine instruments Oil temperature 90 110 C Temperature cylinder heads 90 135 C Oil pressure...

Page 44: ...way final and establish descent and approach to final V Extend flaps gradually to maximum deflection of 38 VI Optimal touchdown speed 44Kts for 550kg MTOW and 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 0 III Parking brake ON IV Turn off landing navigation and strobe lights ENGINE ...

Page 45: ... PROCEDURES III 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 ...

Page 46: ...FLIGHT MANUAL Date Issue 3 25th May 2010 4 12 P92 JS SECTION 4 NORMAL PROCEDURES INTENTIONALLY LEFT BLANK ...

Page 47: ...RFORMANCE 2 INTRODUCTION 2 USE OF PERFORMANCE CHARTS 2 AIRSPEED INDICATOR SYSTEM CALIBRATION APPROVED DATA 3 STALL SPEED APPROVED DATA 5 CROSSWIND 6 TAKEOFF PERFORMANCE APPROVED DATA 7 CLIMB PERFORMANCE 9 CRUISE 10 BALKED LANDING 12 LANDING DISTANCE Approved data 13 CONSEQUENCES FROM RAIN AND INSECT 14 NOISE DATA 14 ...

Page 48: ...etermined according to ICAO Standard Atmosphere ISA m s l evaluations of the impact on performance was carried out by theoretical means for airspeed external temperature 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 graphica...

Page 49: ...ata Graph shows calibrated airspeed VCAS as a function of indicated airspeed VIAS Fig 5 1 CALIBRATED VS INDICATED AIRSPEED BOTH MTOW Example Given Find VIAS 78 Kts VCAS 75 Kts NOTE Indicated airspeed assumes 0 instrument error 40 50 60 70 80 90 100 110 120 130 140 40 50 60 70 80 90 100 110 120 130 140 IAS kts CAS kts 78 75 ...

Page 50: ...FLIGHT MANUAL Date Issue 3 25th May 2010 5 4 P92 JS SECTION 5 PERFORMANCE Fig 5 2 ICAO CHART Example Given Find Temperature 20 C Ts 12 Pressure altitude 1600 ft ...

Page 51: ...AS 0 44 43 47 46 52 51 63 61 15 42 41 45 44 50 49 60 58 38 40 39 42 41 47 46 56 55 CONDITIONS weight 600 kg engine idle no ground effect LATERAL BANKING 0 30 45 60 FLAPS KIAS KCAS KIAS KCAS KIAS KCAS KIAS KCAS 0 46 45 49 48 54 53 66 64 15 44 43 47 46 52 51 63 61 38 41 40 44 43 49 48 58 56 NOTE Altitude loss during conventional stall recovery as demonstrated during test flights is approximately 100...

Page 52: ... 3 25th May 2010 5 6 P92 JS SECTION 5 PERFORMANCE CROSSWIND Maximum demonstrated crosswind velocity is 15 Kts Example Given Find Wind direction 30 Headwind 17 5 Kts Wind velocity 20 Kts Crosswind 10 Kts Fig 5 3 CROSSWIND CHART ...

Page 53: ...S 48 KIAS Runway dry compact grass Vobs 56 KIAS 58 KIAS Slope 0 Wind zero VLO 49 KIAS 51KIAS R C 200 ft min 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 run by 6 NOTE Example Given Find O A T 15 C TOD 253m Pressure altitude 2900 ft MTOW 600kg Weight 450 Kg TOR 117 m Fig 5 4 TAKEOFF P...

Page 54: ...IN TAKEOFF CONFIGURATION Approved data CONDITIONS 550 kg MTOW 600 kg MTOW Flaps 15 15 Engine full throttle full throttle Vobs 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 ...

Page 55: ...g MTOW VY 73KIAS for 600kg MTOW R C residual 100 ft min 12000 14000 8000 10000 4000 6000 2000 2000 PRESSURE ALTITUDE ft RATE OF CLIMB ft m 10 TEMPERATURE deg C 20 10 0 20 200 30 400 0 1400 1000 600 800 1200 0 2000 4000 I S A 5 5 0 k g 5 0 0 4 5 0 8000 6000 10000 14000 12000 16000 6 0 0 k g Example Given Find O A T 17 C Rate of climb 700 ft min Pressure altitude 5600 ft Weight 550 Kg ...

Page 56: ... 2000 ft OAT 11 C Propeller RPM Speed KTAS Consumption l h 1 Endurance hrs 1 Range N m 1 2 1 2 55 1950 98 15 4 5 5 8 440 571 65 2070 106 18 3 7 4 9 397 515 73 2150 109 19 3 5 4 6 387 501 Pressure altitude HP 4000 ft OAT 7 C Propeller RPM Speed KTAS Consumption l h 1 Endurance hrs 1 Range N m 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 Pres...

Page 57: ...445 578 58 2150 102 16 4 2 5 4 428 556 Pressure altitude HP 10000 ft OAT 5 C Propeller RPM Speed KTAS Consumption l h 1 Endurance hrs 1 Range N m 1 2 1 2 55 2150 100 15 4 5 5 8 450 585 Pressure altitude HP 12000 ft OAT 9 C Propeller RPM Speed KTAS Consumption l h 1 Endurance hrs 1 Range N m 1 2 1 2 50 2150 98 14 4 8 6 2 475 617 1 Range and endurance are intended approximate and referred to a zero ...

Page 58: ... Flaps 38 VObs 48 KIAS 50 KIAS Engine full throttle max 5 NOTE During balked landing maneuver flaps should be retracted immediately after applying full power Fig 5 6 BALKED LANDING MTOW 550KG Example Given Find Pressure altitude 7000 ft Rate of climb 230 ft min Conditions ISA NOTE If the maximum takeoff weight is 600 kg the rate of climb decreases about 10 ...

Page 59: ... dry compact grass Slope 0 Wind zero Conditions ISA Flaps 38 Hp ft 0 1000 2000 3000 4000 5000 6000 7000 GR m 120 124 127 131 134 139 143 148 LD m 302 307 312 317 322 328 335 338 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 increase ground run by 10 3 If it becomes necessary to land without flap...

Page 60: ...used substantial variations to aircraft s flight qualities Such variations fall within JAR VLA tolerance limits as they are not above 5 Kts for 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 Issue 1993 and results are shown in the following table 550 kg MTOW 600 kg MTOW Noise Level db ...

Page 61: ...ue 3 25th May 2010 P92 JS SECTION 6 WEIGHT BALANCE 6 1 SECTION 6 WEIGHT BALANCE EQUIPMENT LIST TABLE OF CONTENTS INTRODUCTION 2 AIRCRAFT WEIGHING PROCEDURES 2 WEIGHING REPORT 3 WEIGHT AND BALANCE 5 LOADING 8 EQUIPMENT LIST 8 ...

Page 62: ...rd position h Raise flaps to fully retracted position 0 i Place control surfaces in neutral position j Place scales min capacity 150 kg under each wheel 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 LOCATIO...

Page 63: ... Plumb bob distance LH wheel AL LH wheel weight WL Plumb bob distance RH wheel AR RH wheel weight WR Average distance AL AR 2 A W2 WL WR Bob distance from nose wheel B Empty weight 1 We W1 W2 D W A W B We 2 1 m D D 14 100 Empty weight moment M D 1 405 We Kg m Maximum takeoff weight WT 550 kg WT 600 kg Empty weight We We Sign ____________ Maximum payload WT We Wu Wu 1 Including unusable fuel 2 3 kg...

Page 64: ... Plumb bob distance LH wheel AL LH wheel weight WL Plumb bob distance RH wheel AR RH wheel weight WR Average distance AL AR 2 A W2 WL WR Bob distance from nose wheel B Empty weight 1 We W1 W2 D W A W B We 2 1 m D D 14 100 Empty weight moment M D 1 405 We Kg m Maximum takeoff weight WT 550 kg WT 600 kg Empty weight We We Sign ____________ Maximum payload WT We Wu Wu 1 Including unusable fuel 2 3 kg...

Page 65: ...o limit 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 d...

Page 66: ...HT BALANCE 1100 536 50 Fuel Lt 0 72 kg l 0 30 90 70 600 500 Total weight Kg 550 450 400 350 100 Pilot Passenger Kg Moment empty Kg m 900 1000 800 600 700 562 500 0 20 40 60 80 50 120 140 160 200 180 Luggage Kg 10 0 20 2 6 C M A 2 3 C M A F IG 6 1 Weight balance chart ...

Page 67: ...FLIGHT MANUAL Date Issue 3 25th May 2010 P92 JS SECTION 6 WEIGHT BALANCE 6 7 Fig 6 2 C G RANGE CHART Fig 6 3 LOAD POSITION WITH RESPECT TO DATUM ...

Page 68: ...NSIONS 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 Part number to uniquely identify the item type Item description Serial number Weight in kilograms Distance in meters...

Page 69: ...1 A11 0 110 0 71 A12 Fuel pump p n 21 11 342 000 0 200 0 71 A13 Fuel tank 35 LT P N 21 1 300 001 2 A14 Fuel tank 45 LT P N 21 1 340 001 2 LANDING GEAR AND ACCESSORIES B1 Main gear spring leafs p n 92 8 300 1 5 700 1 930 B2 Main gear wheel rims Cleveland 40 78B 2 050 1 930 B3 Main gear tires Air Trac 5 00 5 AA1D4 2 580 1 930 B4 Disk brakes Cleveland 30 9 0 800 1 930 B5 Nose gear wheel rim p n 92 8 ...

Page 70: ...2 0 30 1 20 D4 Compass Airpath C2400 L4P 0 29 1 20 D5 Clock DAVTRON mod M 800 0 15 1 20 D6 Vertical Speed Indicator MIKROTECHINA UL 30 42 2 0 35 1 20 D7 Vertical Speed Indicator Wultrad Inc p n BC 2A 0 35 1 20 D8 Turn and Bank Indicator FALCON GAUGER TC02E 3 2 0 56 1 20 D9 Turn and Bank Indicator Wunltrad Inc p n TC 001 0 56 1 20 D10 Attitude Indicator IFR85 TSOC4c 1 10 1 20 D11 Attitude Indicator...

Page 71: ...x King KT76A 1 36 1 20 E5 Receiver GPS NAV e r t COM GNS 430W 2 31 1 20 E6 R T VHF COMM IC A200 ICOM 1 20 1 20 E7 ELT ARTEX ME 406 1 10 2 70 E8 Transponder Garmin GTX328 1 00 1 20 E9 Audio panel Garmin GMA 340 0 50 1 20 E10 Vor Loc Indicator Garmin GI106A 0 64 1 20 E11 Antenna KA 92 GPS 0 27 1 07 E12 Antenna Transp Bendix King KA60 0 35 1 50 E13 Antenna GPS Garmin 1012 0 17 1 07 E14 Microphone Tel...

Page 72: ...FLIGHT MANUAL Date Issue 3 25th May 2010 6 12 P92 JS SECTION 6 WEIGHT BALANCE LEFT INTENTIONALLY BLANK ...

Page 73: ...TEMS DESCRIPTION TABLE OF CONTENTS INTRODUCTION 2 AIRFRAME 2 FLIGHT CONTROLS 3 INSTRUMENT PANEL 4 SEATS AND SAFETY HARNESS 5 DOORS 5 Baggage COMPARTMENT 5 POWERPLANT 6 FUEL SYSTEM 6 ELECTRICAL SYSTEM 8 PITOT AND STATIC PRESSURE SYSTEMS 10 BRAKES 11 MARKING PLACARDS 11 PLACARDS OUTSIDE CABIN 14 ...

Page 74: ... 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 mat...

Page 75: ...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 differentiall...

Page 76: ...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...

Page 77: ...cated 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 frame...

Page 78: ...tem 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 35lt 45lt optional and total usable fuel is 66 8lt 86 8 lt 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 i...

Page 79: ...FLIGHT MANUAL Date Issue 3 25th May 2010 7 7 P92 JS SECTION 7 SYSTEMS Fig 7 3 FUEL SYSTEM SCHEMATIC ...

Page 80: ...ocated 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 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 FIG 7 4 ELECTRICAL SYSTEM SCHEMATIC WARNING ...

Page 81: ...ure instruments while a second breaker protects oil pressure indicator and other instruments O A T INDICATOR A digital Outside Air Temperature indicator C is located on the upper left side of the instrument panel The sensor is placed on cabin top STALL WARNING SYSTEM The aircraft is equipped with a stall warning system consisting of a sensor located on the right wing leading edge connected to a wa...

Page 82: ...power source s plug into the socket 3 Engine start up procedure see Sect 4 in this manual 4 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 ...

Page 83: ...tivate brake lever as necessary To activate parking brake pull brake lever and set brake shut off valve to ON MARKING PLACARDS To compensate for deviation errors of the magnetic compass the following correction card is located immediately below compass This placard has to be compiled by certified operator with valid and proper instrumentation The following placard is located on the cabin s floor t...

Page 84: ...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 A 20x8mm OPEN CLOSED placard is placed near each shutoff valve The following placard is placed near the RH forward truss member shutoff valve ON OFF LH FUEL TANK SHUT OFF VALVE ON OFF LH FUEL TANK SHUT OFF VALVE The cabin heat control knob is located on the instr...

Page 85: ...ystem in case of malfunction The following placard is positioned near switch Circuit breakers are located on lower right side of instrument panel and each breaker is individually marked as follows from left to right 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 A placard measuring 74x7 mm is loc...

Page 86: ...around them one on top one on RH side one on bottom and one on LH side ON G E N E R A T O R M A S T E R OFF A generator warning light is located on the upper right side of the instrument panel and is marked with the following label PLACARDS OUTSIDE CABIN The overflow reservoir cap for antifreeze liquid bears the following placard Brake fluid reservoir cap bears the following placard ...

Page 87: ...r The following label is located below each door for emergency opening 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 ...

Page 88: ... CERT N A 340 On the right side of the tail cone next to the battery case access door is present the following placard 69x17mm On the right side of the tail cone on the power receptacle s door is present the following placard 135x25mm 12 Volt DC EXTERNAL POWER RECEPTACLE On both the main landing gear fairings the following placard 120x22mm is present NO STEP BATTERY INSIDE ...

Page 89: ... 25th May 2010 8 1 P92 JS SECTION 8 GROUND HANDLING SERVICE SECTION 8 GROUND HANDLING SERVICE TABLE OF CONTENTS INTRODUCTION 2 AIRCRAFT INSPECTION PERIODS 2 AIRCRAFT ALTERATIONS OR REPAIRS 2 GROUND HANDLING 2 CLEANING AND CARE 3 ...

Page 90: ...nual 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 is most easily and safely maneuvered by hand by pushing on wing struts near attachments or by pulling it...

Page 91: ...in 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 acci...

Page 92: ...FLIGHT MANUAL Date Issue 3 25th May 2010 8 4 P92 JS SECTION 8 GROUND HANDLING SERVICE LEFT INTENTIONALLY BLANK ...

Page 93: ...OMM NAV 3 1 INTRODUCTION 3 1 2 GENERAL 3 1 3 LIMITATIONS 4 1 4 EMERGENCY PROCEDURES 5 1 5 NORMAL OPERATION 5 1 6 PERFORMANCE 5 1 7 WEIGHT AND BALANCE 6 1 8 SYSTEMS 6 BANNER TOWING 7 2 INTRODUCTION 7 2 1 GENERAL 7 2 2 LIMITATIONS 7 2 3 EMERGENCY PROCEDURES 9 2 4 NORMAL PROCEDURES 9 2 5 PERFORMANCE 11 2 6 WEIGHT BALANCE 14 EQUIPMENT LIST 14 ...

Page 94: ...8 3 6 WEIGHT AND BALANCE 18 3 7 SYSTEMS 19 CENTRAL THROTTLE CONTROL SYSTEM 21 4 INTRODUCTION 21 4 1 GENERAL 21 4 2 LIMITATIONS 21 4 3 EMERGENCY PROCEDURES 21 4 4 NORMAL OPERATION 21 4 5 PERFORMANCE 21 4 6 WEIGHT AND BALANCE 21 4 7 SYSTEMS 21 NEW ANALOGICAL INSTRUMENTS PANEL 23 5 INTRODUCTION 23 5 2 GENERAL 23 5 3 LIMITATIONS 23 5 4 EMERGENCY PROCEDURES 23 5 5 NORMAL OPERATION 23 5 6 PERFORMANCE 23...

Page 95: ...nna for GPS a receiver for GPS a VOR LOC antenna a VOR ILS receiver a VHF Comm antenna and a VHF Comm tranceiver 3 The main function of the VHF Comm is to allow communication with the control tower 4 The VOR ILS function is to receive and demodulate VOR and LOC signals 5 The GPS section is dedicated to signal acquisition from the GPS satellite system and to furnish real time information with respe...

Page 96: ...isplayed 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 DIS SPD nm kt select navigation unit to nautical miles and knots ALT VS ft fpm select altitude...

Page 97: ... 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 Refer...

Page 98: ...ay 2010 9 6 P92 JS SECTION 9 SUPPLEMENTS 1 7 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 F dated July 2000 or later versions for a complete description of the system ...

Page 99: ... 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 140m2 WEIGHT The aircraft s MTOW equipped with a 140m2 banner reaches 460kg For...

Page 100: ...cifications 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 KI...

Page 101: ...he banner is hold by 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 s 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 ou...

Page 102: ...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 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 Check the banner position through the rear view mirror WARNING ...

Page 103: ... 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 mark...

Page 104: ...To obtain a 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 140m2 should not exceed 460kg 5 C 15 C 25 C 35 C Peso A m Press Alt GRND ROLL DISTANCE 15 m OBS GRND ROLL DISTANCE 15 m OBS GRND ROLL DISTANCE 15 m OBS GRND ROLL DISTANCE 15 m OBS kg ft m m m m m m m m 460 0 106 232 199 437 279 612 357 784 1000 115 ...

Page 105: ... 35 C Peso A m Press Alt GRND ROLL DISTANCE 15 m OBS GRND ROLL DISTANCE 15 m OBS GRND ROLL DISTANCE 15 m OBS GRND ROLL DISTANCE 15 m OBS kg ft m m m m m m m m 550 0 104 229 196 431 275 604 352 773 1000 114 249 214 470 300 659 385 844 2000 124 272 234 513 328 719 420 921 3000 136 297 256 561 358 786 459 1006 5 C 15 C 25 C 35 C Peso A m Press Alt GRND ROLL DISTANCE 15 m OBS GRND ROLL DISTANCE 15 m O...

Page 106: ...face 140 m2 Take off weight 460 kg The rate of climb is higher than 2 m s CONDITIONS Flap 0 Engine throttle Full VY 53 KIAS OAT 35 Airfield pressure altitude 3000 ft Banner s surface 90 m2 Take off weight 550 kg The rate of climb is higher than 2 m s 2 6 WEIGHT BALANCE EQUIPMENT LIST In the following table are listed all the equipment that Tecnam has installed on the P92 JS for towing banners ...

Page 107: ...ported 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 5 is realised by a steel support 2 connected by means of two steel ties 4 3 to the stabilator s fitting...

Page 108: ...010 9 16 P92 JS SECTION 9 SUPPLEMENTS The towing rope is released by the Hook simply operating the release lever located in cabin between the two seats The towing hook is a TOST E85 approved type Type Certificate No 30 230 1 Hook TOST E85 ...

Page 109: ...5th May 2010 9 17 P92 JS SECTION 9 SUPPLEMENTS 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 ...

Page 110: ... section contains supplementary information for safe and efficient operation of the aircraft if equipped with the differential brake system 3 1 GENERAL No variations 3 2 LIMITATIONS No variations 3 3 EMERGENCY PROCEDURES No variations 3 4 NORMAL OPERATION No variations 3 5 PERFORMANCE No variations 3 6 WEIGHT AND BALANCE No variations ...

Page 111: ... 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 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 C C C C FW...

Page 112: ...FLIGHT MANUAL Date Issue 3 25th May 2010 9 20 P92 JS SECTION 9 SUPPLEMENTS The following placard is located on the central pedestal Figure 9 3 Parking brake placard ...

Page 113: ...on 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 4 7 SYSTEMS ...

Page 114: ...tral throttle control system The engine throttle lever is located on the left site and the choke lever is located on the right site The levers friction is located on the lateral right site of the central throttle control system T H R O T T C A R B H E A T ON OFF Figure 9 3 Central throttle control system ...

Page 115: ... section contains supplementary information for safe and efficient operation of the aircraft if equipped with the new analogical instruments panel 5 2 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 ...

Page 116: ...ned 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 instruments panel OBS Figure 9 4 ...

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