Tecnam P92 Echo MKII Flight Manual Download

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Section 5 - Performance

CROSSWIND

Edition - Rev. 0

ROSSWIND

Maximum demonstrated crosswind is 15 Kts



Example:

Given

Find

Wind direction (

with respect to aircraft longitudinal axis

) = 30° Headwind = 17.5 Kts

Wind speed = 20 Kts

Crosswind = 10 Kts

. 5-3. C

ROSSWIND

HART

Summary of Contents for P92 Echo MKII

Page 1: ...he aircraft The aircraft is to be operated in compliance with information and limitations contained herein Costruzioni Aeronautiche TECNAM S p A Via Maiorise CAPUA CE Italy Tel 39 0 823 62 01 34 WEB www tecnam com This document and the information thereon is the property of Costruzioni Aeronautiche Tecnam S p A and may only be used for the purpose for which Tecnam products are supplied and or use ...

Page 2: ...Page 0 2 Aircraft Flight Manual INDEX 1st Edition Rev 0 Section 0 INDEX 1 Record of Revisions 3 2 List Of effective Pages 5 3 Foreword 6 4 Section Lists 7 ...

Page 3: ...s the Edition code will change to the next number 2 for the second edi tion 3 for the third edition etc Additions deletions and revisions to existing text will be identified by a revision bar black line in the left hand margin of the page adjacent to the change When technical changes cause expansion or deletion of text which results in un changed text appearing on a different page a revision bar w...

Page 4: ...Page 0 4 Aircraft Flight Manual RECORD OF REVISIONS 1st Edition Rev 0 Rev Revised page Description of Revision 0 All First issue ...

Page 5: ...c pages or one variant of these pages when the pages of some Supplements are embodied Pages affected by the current revision are indicated by an asterisk following the revi sion code 1st Edition Rev 0 February 26h 2020 Section Pages Revision Section 0 All Rev 0 Section 1 All Rev 0 Section 2 All Rev 0 Section 3 All Rev 0 Section 4 All Rev 0 Section 5 All Rev 0 Section 6 All Rev 0 Section 7 All Rev ...

Page 6: ...plies general information and it contains definitions symbols explanations acronyms and terminology used Before using the airplane you are recommended to read carefully this manual a deep knowledge of airplane features and limitations will allow you for operating the airplane safely For further information please contact COSTRUZIONI AERONAUTICHE TECNAMS p A Via MAIORISE CAPUA CE ITALY 39 0 823 62 ...

Page 7: ... LISTS General Section 1 Limitations Section 2 Emergency Procedures Section 3 Normal Procedures Section 4 Performances Section 5 Weight and Balance Section 6 Airframe and Systems Description Section 7 Ground Handling Servicing and Maintenance Section 8 Supplements Section 9 ...

Page 8: ...Page 0 8 Aircraft Flight Manual SECTION LISTS 1st Edition Rev 0 Intentionally left blank ...

Page 9: ...Surfaces Travel Limits 5 Engine 5 Propeller 5 Fuel 6 Lubrication 6 Cooling 6 weights 7 Standard weights 7 Specific Loading 7 4 Acronyms and terminology 8 General Airspeed Terminology And Symbols 8 Meteorological terminology 9 Engine Power terminology 9 Aircraft performance and flight planning terminology 10 Weight and balance terminology 11 5 Unit conversion chart 12 6 Litres US gallons conversion...

Page 10: ...d to provide pilots and instructors with infor mation for the safe and efficient operation of this aeroplane WARNING CAUTION NOTE Following definitions apply to warnings cautions and notes used in the Aircraft Flight Manual The non observation of the corresponding procedure can lead as immediate effect to a significant reduction of the flight safety WARNING CAUTION The non observation of the corre...

Page 11: ...tion Rev 0 2 THREE VIEW AND DIMENSIONS THREE VIEW Fig 1 1 General views Dimensions shown refer to normal operating tire pressure Propeller ground clearance 336 mm Propeller ground clearance with deflated front tire and nose wheel shock ab sorber compressed 84mm ...

Page 12: ...ingspan 8 77 m 28 77 ft Length 6 81 m 22 34 ft Overall height 2 66 m 8 72 ft Wing Wing surface 12 1 m2 130 24 ft2 Mean Geometric Chord 1 40 m 4 59 ft Dihedral 1 30 Aspect ratio 6 35 Main Landing Gear Wheel Track 1 84 m 6 04 ft Wheelbase 1 74 m Tire Air Trac 5 00 5 Nose Landing Gear Tire Air Trac 5 00 5 ...

Page 13: ... Model 912 ULS2 Engine type 4 cylinder horizontally opposed twins with overall displacement of 1352 c c mixed cooling water cooled heads and air cooled cylinders twin carburetors integrated reduction gear with torque damper Maximum power at declared rpm 73 5kW 98 5hp 5800rpm max 5 69 0kW 92 5hp 5500rpm cont PROPELLER Manufacturer Sensenich Model W68T2ET 70J Number of blades 2 Diameter 1730 mm no r...

Page 14: ...n fittings Capacity of each wing tank 45 litres Tanks overall capacity 90 litres Overall usable fuel 86 9 litres Overall unusable fuel 3 1 litre LUBRICATION Lubrication system Forced type with external reservoir Oil Lubricant specifications and grade are detailed into the Rotax Operators Manual and in its re lated documents Oil capacity Max 3 litres min 2 0 litres COOLING Cooling system Mixed air ...

Page 15: ...CES TRAVEL LIMITS ARE REPORTED IN THE AIRCRAFT MAINTENANCE MANUAL 1st Edition Rev 0 WEIGHTS See Section 2 STANDARD WEIGHTS Empty Weight see weighing record on Section 6 SPECIFIC LOADING MTOW 600 kg Wing Loading 49 6 kg m2 Power Loading 6 1 kg hp ...

Page 16: ... to make full or abrupt control movement VFE Maximum Flap Extended speed is the highest speed permissible with flaps extended VNO Maximum Structural CruisingSpeed is the speed that should not be exceeded except in smooth air and only with caution VNE Never Exceed Speed is the speed limit that maynot be exceeded at any time VS Stall Speed VS0 Stall Speed in landing configuration full flaps VS1 Stal...

Page 17: ...eric pressure at sea level is the atmospheric pressure reported at the medium sea level through the standard air pressure altitude relationship starting from the airport QFE OAT Outside Air Temperature is the air static temperature expressed in degrees Celsius C TS Standard Temperature is 15 C at sea level pressure altitude and de creased by 2 C for each 1000 ft of altitude HP Pressure Altitude is...

Page 18: ...RMINOLOGY Crosswind Velocity is the velocity of the crosswind component for which adequate control of the airplane during take off and landing is assured 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 ...

Page 19: ... by the total weight of the aircraft Standard Empty Weight is the weight of the aircraft with engine fluids and oil at operating levels Basic Empty Weight is the standard empty weight to which it is added the optional equipment weight Useful Load is the difference between maximum take off weight and the basic empty weight Maximum Take off Weight is the maximum weight approved to perform the take o...

Page 20: ...0508 Meters per second m s Knots kts 1 853 Kilometres hour km h Kilometres 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 Kilometres km 0 5396 Nautical miles nm Nautical miles nm 1 852 Kilometres km Meters m 3 281 Feet ft Feet ft 0 3048 Meters m Centimetres cm 0 3937 Inches in Inches in 2 540 Centimetres cm VOLUME Litres l 0 26...

Page 21: ...0 6 LITRES US GALLONS CONVERSIONCHART Litres US Gallons US Gallons Litres 5 1 3 1 3 8 10 2 6 2 7 6 15 4 0 3 11 4 20 5 3 4 15 1 25 6 6 6 22 7 30 7 9 8 30 3 35 9 2 10 37 9 40 10 6 12 45 4 45 11 9 14 53 0 50 13 2 16 60 6 60 15 9 18 68 1 70 18 5 20 75 7 80 21 1 22 83 3 90 23 8 24 90 9 ...

Page 22: ...Page 1 14 Section 1 General 1st Edition Rev 0 INTENTIONALLY LEFT BLANK ...

Page 23: ... 6 6 Coolant Liquid 6 7 Propeller 7 8 Maximum operating altitude 8 9 Ambient Temperature 8 10 Powerplant instruments markings 9 11 Other Instruments Markings 9 12 Weights 10 13 Center of gravity range 10 14 Approved maneuvers 11 15 Maneuvers load factor limits 11 16 Flight crew 12 17 Maximum passenger seating 12 18 Fuel 13 19 Demonstrated Cross Wind Safe Operations 14 20 Rescue System Deployment 1...

Page 24: ... 2 Section 2 Limitations INTRODUCTION 1st Edition Rev 0 1 INTRODUCTION Section 2 includes operating limitations and instrument markings of P92 Echo MKII aircraft its engines and standard systems and equipment ...

Page 25: ...eed 145 138 Do not exceed this speed in any operation VRA Maximum speed for rough air 113 109 Do not exceed this speed except in smooth air and only with caution VA Design Manoeuvring speed 98 95 Do not make full or abrupt control movement above this speed because under certain conditions the air craft may be overstressed by full control movement VFE Maximum flaps extended speed 70 70 Do not excee...

Page 26: ...rlimit is 1 1VSO at specified maximum weight and upper limit is the maximum speed permissi ble with landing flaps extension Green arc 51 113 Normal Operating Range lower limit is 1 1VS1 at specified maximum weight and most forward c g with flaps retracted and up per limit is maximum speed for rough air VRA Yellow arc 113 145 Manoeuvres must be conducted with caution and only in smooth air Red line...

Page 27: ...0 Temperatures Max CHT 135 C Max CT 120 C Min Max Oil 50 C 130 C Oil normal operating range approx 90 C 110 C applicable for En repaired engine one part no 413 gines up to serial no 4924543 included and hich doesn t change the cylinder head n 3 with new 195 Oil Pressure Minimum 0 8 Bar 12 psi Normal 2 5 Bar 29 73 psi Maximum 7 Bar 102 psi Engine starting allowable temperature range OAT Min 25 C OA...

Page 28: ...ions LUBRICANT 1st Edition Rev 0 5 LUBRICANT Use viscosity grade oil as specified in the following table 6 COOLANT LIQUID Coolant type and specifications are detailed into the Rotax Operator s Manual and in its related documents ...

Page 29: ...Page 2 7 Section 2 Limitations PROPELLER 1st Edition Rev 0 7 PROPELLER MANUFACTURER Sensenich Propeller MODEL W68T2ET 70J TYPE Wood twin blade fixed pitch DIAMETER 1730 mm no reduction permitted ...

Page 30: ...ERATING ALTITUDE Maximum operating altitude is 14000 ft 4260 m MSL CAUTION Flight crew is required to use supplemental oxygen according to Air Oper ation Rules 9 AMBIENT TEMPERATURE Ambient temperature from 25 C to 50 C WARNING Flight in expected and or known icing conditions is forbidden ...

Page 31: ...ar 0 15 0 15 0 4 or 0 5 4 0 4 or 0 5 3 Fuel Q ty litres 0 5 11 OTHER INSTRUMENTS MARKINGS INSTRUMENT RED RANGE Minimum limit GREEN RANGE Normal operating YELLOW RANGE Caution RED RANGE Maximum limit Voltmeter 10 5 Volt 12 14 Volt 1 Applicable for Engines up to serial no 494543 included and repaired engine which doesn t change thecyl inder head n 3 with new one part no 413195 2 In event of cold sta...

Page 32: ...eight 20 kg 13 CENTER OF GRAVITY RANGE Datum Propeller support flange without spacer Levelling Seat track supporting trusses ref to sect 6 for the procedure Forward limit 1 841 m 23 0 MAC aft of datum for all weights Aft limit 1 939 m 30 MAC aft of datum for all weights WARNING The pilot is responsible for ensuring that the airplane is properly loaded Refer to Section 6 for appropriate instruc tio...

Page 33: ...which the angle of bank is not more than 60 WARNING Aerobatic manoeuvres including spins and turns with angle of bank of more than 60 are not approved for such a category WARNING Limit load factor could be exceeded by moving abruptly flight controls at their end run at a speed above VA 15 MANEUVERS LOAD FACTOR LIMITS Maneuver load factors limits are as follows Positive Negative 4 0 g 2 0 g Maneuve...

Page 34: ...tions FLIGHT CREW 1st Edition Rev 0 16 FLIGHT CREW Minimum crew for flight is one pilot seated on the left side 17 MAXIMUM PASSENGER SEATING With the exception of the pilot only one passenger is allowed on board of this aircraft ...

Page 35: ...els byacting on the fuel selector valve located into the cabin APPROVED FUEL MOGAS ASTM D4814 MOGAS EN 228 Super Super plus min RON 95 AVGAS 100 LL ASTM D910 CAUTION Prolonged use of Aviation Fuel Avgas 100LL results in greater wear of valve seats and greater combustion deposits inside cylinders due to higher lead content Make referenceto Rotax Maintenance Manual which prescribes dedicated checks ...

Page 36: ...t Edition Rev 0 19 DEMONSTRATED CROSS WIND SAFE OPERATIONS The aircraft controllability during take offs and landings has been demonstrated with a cross wind components up to 15 kts 28 km h 20 RESCUE SYSTEM DEPLOYMENT Maximum airspeed for rescue system deployment is145kts IAS ...

Page 37: ...Off Run 7 4 2 Engine Failure Immediately After Take off 7 4 3 Engine Failures During Flight 8 4 3 1 Low Fuel Pressure 8 4 3 2 Oil Pressure limits exceedance 8 4 3 3 High Oil Temperature 9 4 3 4 CHT CT limit exceedance 10 5 In Flight Engine Restart 11 6 Smoke And Fire 12 6 1 Engine fire on the ground 12 6 2 Engine Fire DuringTake off 12 6 3 Engine Fire In Flight 13 6 4 Cabin Fire Electrical smoke i...

Page 38: ...7 2 Power OnForced Landing 14 7 3 Landing With A FlatNose Tire 14 7 4 Landing With A FlatMain Tire 15 8 Stall Recovery 16 9 Recovery From Unintentional Spin 17 10 Rescue System deployment 18 11 Other Emergencies 19 11 1 Unintentional Flight Into Icing Conditions 19 ...

Page 39: ... 4 Inform the Air Traffic Control if time and conditions allow Two types of emergency procedures are hereby given a Bold faces which must be known byheart and executed in the correct and complete sequence as soon as possible as the failure is detected and recognized These procedures characters are boxed and highlighted an example is shown below b Other procedures which should be well theoretically...

Page 40: ...rt NOTE Generator message alert ALT may appear on PFD for a faulty al ternator or when voltage is above 16V in this case the over voltage sensor automatically shuts down the alternator 1 Generator switch OFF 2 Master switch OFF 3 Generator switch ON 4 Master switch ON If the problem persists 5 Generator switch OFF 6 Non vital electric equipment Shed ...

Page 41: ...H CHECK for correct position 3 Speed adjust to control aircraft without excessive stick force 4 Land aircraft as soon as possible Runaway In event of trim runaway act as follows 1 Pull TRIM Breaker as soon as possible 2 Speed adjust to control aircraft without excessive stick force 3 Land aircraft as soon as possible 2 4 AIRPLANE EVACUATION With the engine secured and propeller stopped if practica...

Page 42: ...y Procedure ENGINE SECURING 1st Edition Rev 0 3 ENGINE SECURING Following procedure is applicable to shut down the engine in flight Throttle Lever Magnetos Fuel Selector Electrical fuel pump Generator switch IDLE OFF OFF OFF OFF ...

Page 43: ...netos 6 Fuel selector valve 7 Electric fuel pump 8 Generator Master switches IDLE fully out OFF OFF OFF OFF WARNING A single engine aircraft take off should always be preceded by a thorough take off emergency pilot self briefing Decision to try an engine emergency restart right after take off should betaken only if environmental situation requires it pilot shall never ig nore the priority of atten...

Page 44: ... as possible monitoring fuel pressure If engine stops 5 Land as soon as possible applying forced landing procedure See Para 7 4 3 2 Oil Pressure limits exceedance If oil pressure exceeds upper limit 7 bar 1 Throttle Lever REDUCE engine power as practical 2 OIL PRESS and OIL TEMP CHECK within limits 3 Land as soon as practical If oil pressure is under the lower limit 0 8 bar 1 Throttle Lever REDUCE...

Page 45: ...temperature does not decrease 2 Airspeed INCREASE If oil temperature does not come back within limits the thermostatic valve if embodied regulating the oil flow NOTE to the heat exchangers could be damaged or an oil leakage can be present in the oil supply line 3 Land as soon as practical If engine roughness vibrations erratic behaviour or high CHT CT is detected 4 Land as soon as possible applyin...

Page 46: ...4 CHT CT limit exceedance If CHT is above 135 C or CT is above 120 C 1 Throttle Lever REDUCE Minimum practical 2 Land as soon as practical If CHT CT continues to rise and engine shows roughness or power loss 3 Land as soon as possible applying forced landing procedure See Para 7 ...

Page 47: ...gnetos BOTH 5 Magnetos START 6 Throttle lever SET as required CAUTION After engine restart if practical moderate propeller RPM and throt tle increase to allow OIL and CHT CT temperatures for stabilizing in the green arcs NOTE If the fuel quantity in the tank which feeds the stopped engine is low select the opposite side fuel tank by means of the fuel selector In case of unsuccessful engine restart...

Page 48: ... Generator Master Switches OFF Parking Brake ENGAGED Aircraft Evacuation carry out immediately 6 2 ENGINE FIRE DURING TAKE OFF BEFORE ROTATION ABORT TAKE OFF Throttle Lever Rudder Brakes Fuel Selector IDLE Keep heading control As required With aircraft under control OFF Electrical fuel pump OFF Magnetos OFF Cabin Heat OFF Generator Master Switches OFF Parking Brake ENGAGED Aircraft Evacuation carr...

Page 49: ...aster switches OFF 2 Land as soon as possible and evacuate the aircraft CAUTION If the MASTER SWITCH is set to OFF consider that flaps extension and pitch trim operation would be not possible 6 4 1 2 3 4 CABIN FIRE ELECTRICAL SMOKE IN CABIN DURING FLIGHT Cabin heating Cabin vents Door OFF OPEN OPEN if necessary Try to choke the fire Direct the fire extinguisher if on board towards flame base 6 5 E...

Page 50: ...t Above Ground Level it is possible to cover about 1 5 NM about 3 km 7 2 POWER ON FORCED LANDING 1 Airspeed Best glide speed 65 kts IAS 2 Flaps UP 3 Locate the most suitable terrain for emergency landing plan to approach it upwind 4 Safety belts Tighten 5 Canopy locks CHECK LOCKED When certain to land right before touch down 6 Flaps as necessary 7 Fuel selector valve OFF 8 Electric fuel pump OFF 9...

Page 51: ...3 Land the aeroplane on the side of runway opposite to the defective tire if detected to compensate the change in direction which is to be expected during final rolling 4 Touchdown with the GOOD TIRE FIRST if detected and hold aircraft with the flat tire off the ground as long as possible by mean of aileron and rudder control As aircraft stops 5 Engine securing Perform see Para 3 6 Airplane evacua...

Page 52: ...al departure pitch down stall warning 1 Pitch nose down APPLY until impending stall indications are eliminated 2 Wings level Obtain and Maintain 3 Power As required 4 Return to the desired flight path CAUTION Apply smooth and coordinated flight control movements to return the airplane to the desired flight path being careful to avoid a sec ondary stall ...

Page 53: ...g recovery procedure should be used 1 Throttle IDLE 2 Rudder full in the opposite direction of the spin 3 Stick forward As the spin stops 4 Rudder 5 Aeroplane attitude 6 Throttle SET NEUTRAL smoothly recover averting speeds in excess of VNE and maximum load factor n 4 0 Readjust to restore engine power WARNING Keep full rudder against rotation until spin has stopped ...

Page 54: ...Successful deployment depends on aircraft attitude and air speed greater deployment altitude yields better chances for successful deployment Shown below the procedure to be followed 1 Airspeed MINUM POSSIBLE max speed 145 kts IAS 2 Pull activation handle firmly and toend travel After deployment Fuel selector Magnetos Master Switch Seat Belts and Harnesses OFF OFF OFF TIGHTEN Before impact Assume e...

Page 55: ...ible moisture outside visibility less than 5 km vicinity of fog mist clouds rain snow or hail and OAT less than 10 C 1 Immediately fly away from icing conditions changing altitude and direc tion of flight out of clouds visible moisture precipitations 2 Controls surfaces continue to move to maintain their movability 3 Engine increase rpm WARNING In case of ice formation on wing leading edge stall s...

Page 56: ...Page 3 20 Section 3 Emergency Procedure OTHER EMERGENCIES 1st Edition Rev 0 INTENTIONALLY LEFT BLANK ...

Page 57: ...ections 3 3 1 Cabin Inspection 3 3 2 Aircraft walk around 3 4 Checklists 6 4 1 Before Engine Starting After Preflight Inspection 6 4 2 Engine Starting 7 4 3 Before Taxiing 7 4 4 Taxiing 8 4 5 Prior To Take Off 8 4 6 Take off And Climb 9 4 7 Cruise 10 4 8 Before Landing 10 4 9 Balked Landing 10 4 10 After Landing 11 4 11 Engine Shut Down 11 4 12 Postflight Check 11 ...

Page 58: ... of normal op eration 2 AIRSPEEDS FOR NORMAL OPERATIONS Following airspeeds are significant for normal operations at MTOW 600 kg FLAPS IAS kts Rotation Speed in take off VR T O 45 Best Angle of Climb Speed VX 0 62 Best Rate of Climb speed VY 0 65 Approach speed T O 54 Final Approach Speed FULL 50 Manoeuvring speed VA 0 98 Never Exceed Speed VNE 0 145 ...

Page 59: ... luggage stowage and fastened with restraint net 3 2 AIRCRAFT WALK AROUND To perform the aircraft walk around carry out the checklist according to the sta tion shown in Figure 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 inspec tion also involves a...

Page 60: ...ment 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 align ment 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 dete...

Page 61: ...ck 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 contam inants U Nose wheel str...

Page 62: ...onic Master switch ON instruments check then set in OFF 10 Flap control cycle fully extended and then set T O 11 Pitch Trim cycle fully up and down from both left and right controls 12 Pitch trim set neutral WARNING Pitch trim other than in neutral position would affect take off per formance and take off rotation execution at the correct VR IAS 13 Nav light Strobe light if installed ON 14 Fuel qua...

Page 63: ... propeller Forward lower sector visibility is not possible from inside the cockpit 7 Magnetos BOTH 8 Magnetos START 9 Check oil pressure rise within 10 sec maximum cold value 7 bar 10 Generator switch ON 11 Check ALT message disappears 12 Voltmeter check more than 14V 13 Engine parameters Check 14 Choke OFF 15 Throttle lever 2430 2915 rpm 16 Electric fuel pump OFF 17 Check fuel pressure min 2 2 ps...

Page 64: ...ter check green 4 Electric Fuel pump ON 5 Fuel valve select the fullest tank 6 Fuel pressure check 7 Throttle lever advance to 4000 rpm a Ignition magnetos test select LEFT check RPM drop within 315 rpm b Select BOTH check propeller speed 4000 rpm c Select RIGHT check RPM drop within 315 rpm d Maximum difference of speed between LEFT and RIGHT 120 rpm e Select BOTH check engine 4000 rpm 8 Flaps se...

Page 65: ...tion speed 50 kts IAS MTOW 600kg Best of Rate Climb Speed VY 65 kts IAS 6 Electric fuel pump OFF 7 Fuel pressure check green arc 8 Engine speed reduce at or below 5500 rpm NOTE Take off into crosswind is performed with the flaps normally set at 15 T O With the ailerons deflected into the wind accelerate the air plane to a speed slightly higher than normal while decreasing the aileron deflection as...

Page 66: ...mal touchdown speed 43 KIAS NOTE Normal crosswind landings are made with full flaps Avoid pro longed slips Increase airspeed depending on wind intensity and direction as required above normal approach and landing speeds to accommodate increased stall speed when side slip is added After touchdown hold a straight course with rudder and brakes as required The maximum allowable crosswind velocity is d...

Page 67: ...bout 2900 rpm for about one minute in order toreduce latent heat 3 Avionic equipment OFF 4 Magnetos OFF keys extracted 5 Strobe light if installed OFF 6 Master Generator switches OFF 7 Fuel selector valve OFF 4 12 POSTFLIGHT CHECK 1 Flight controls surfaces lock by means of gust lock if available 2 Wheel chocks and wing mooring lines Set if available 3 Parking brake release 4 Doors Close and lock ...

Page 68: ...Page 4 12 Section 4 Normal Procedures CHECKLISTS 1st Edition Rev 0 INTENTIONALLY LEFT BLANK ...

Page 69: ...ERFORMANCES INDEX INDEX 1 1 Introduction 2 2 Use of performances charts 3 3 Airspeed indicator system calibration 4 4 ICAO Standard Atmosphere 5 5 Stall speed 6 6 Crosswind 7 7 Take off performance 8 8 Rate of Climb 11 9 Cruise performance 12 10 Landing performance 13 ...

Page 70: ... take off to landing Data reported in graphs and or in tables were determined using aircraft and engine in good condition average piloting techniques Each graph or table was determined according to ICAO Standard Atmosphere ISA s l evaluations of the impact on performances were carried out by theoretical means for Airspeed External temperature Altitude Weight Runway type and condition ...

Page 71: ...HARTS Performances data are 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 the mission with required precision and safety Additional information is provided for each table or graph ...

Page 72: ...tion Rev 0 3 AIRSPEED INDICATOR SYSTEM CALIBRATION Graph shows indicated airspeed VIAS as a function of calibrated airspeed VCAS FIG 5 1 INDICATED VS CALIBRATED AIRSPEED Example Given Find KCAS 75 FLAP UP KIAS 76 FLAP UP NOTE Indicated airspeed assumes 0 as an instrument error ...

Page 73: ...HERE 1st Edition Rev 0 4 ICAO STANDARD ATMOSPHERE Examples FIG 5 2 ICAO CHART Scope Given Find Density Altitude A Pressure altitude 1600ft B Temperature 20 C C Density Altitude 2550ft ISA Temperature D Pressure altitude 1600ft E ISA Air Temperature 12 C ...

Page 74: ... STALL SPEED FLAPS 0 FLAPS T O FLAPS FULL deg KIAS KCAS KIAS KCAS KIAS KCAS 0 45 47 40 43 37 39 15 46 48 41 44 38 40 30 49 50 43 46 40 42 45 55 56 49 51 45 46 60 67 67 60 61 54 55 Altitude loss during conventional stall recovery as demonstrated during flight tests is approximately 200 ft with banking below 20 For Stall Recovery procedure see Section 3 NOTE ...

Page 75: ...OSSWIND 1st Edition Rev 0 6 CROSSWIND Maximum demonstrated crosswind is 15 Kts Example Given Find Wind direction with respect to aircraft longitudinal axis 30 Headwind 17 5 Kts Wind speed 20 Kts Crosswind 10 Kts FIG 5 3 CROSSWIND CHART ...

Page 76: ...0 Ground Roll 163 205 253 307 230 At 50 ft AGL 284 355 434 523 395 2000 Ground Roll 178 224 277 337 247 At 50 ft AGL 309 386 473 573 423 3000 Ground Roll 194 245 302 377 265 At 50 ft AGL 336 420 515 639 453 4000 Ground Roll 213 268 331 422 285 At 50 ft AGL 367 458 561 712 486 5000 Ground Roll 232 293 370 472 306 At 50 ft AGL 400 499 627 794 521 6000 Ground Roll 254 320 415 528 329 At 50 ft AGL 436...

Page 77: ...oll 132 167 206 249 186 At 50 ft AGL 232 290 355 428 323 2000 Ground Roll 144 182 224 274 200 At 50 ft AGL 253 315 386 468 346 3000 Ground Roll 158 199 245 306 215 At 50 ft AGL 275 344 421 522 370 4000 Ground Roll 172 217 268 342 231 At 50 ft AGL 300 374 459 582 397 5000 Ground Roll 189 237 300 383 248 At 50 ft AGL 327 408 512 649 426 6000 Ground Roll 206 260 337 428 267 At 50 ft AGL 356 445 572 7...

Page 78: ...Roll 105 133 164 198 148 At 50 ft AGL 186 233 285 343 259 2000 Ground Roll 115 145 179 218 159 At 50 ft AGL 203 253 310 375 277 3000 Ground Roll 126 158 195 244 171 At 50 ft AGL 221 276 337 419 297 4000 Ground Roll 137 173 213 272 184 At 50 ft AGL 240 300 368 467 318 5000 Ground Roll 150 189 239 305 198 At 50 ft AGL 262 327 411 520 342 6000 Ground Roll 164 207 268 341 212 At 50 ft AGL 286 357 459 ...

Page 79: ...9 957 2000 1140 911 706 522 818 4000 964 738 537 355 679 6000 788 566 368 190 540 8000 612 394 200 25 401 10000 437 223 32 141 261 550 S L 1482 1230 1006 803 1092 2000 1290 1043 822 623 942 4000 1100 857 640 444 793 6000 910 671 458 265 643 8000 720 486 276 87 493 10000 532 301 95 91 343 500 S L 1677 1402 1156 935 1251 2000 1468 1198 957 740 1088 4000 1260 994 757 544 925 6000 1052 791 558 349 761...

Page 80: ... gal less the unusable fuel Pressure altitude HP 0 ft OAT 15 C Engine RPM Speed KTAS Consumption lt h 4300 102 14 4800 107 18 5200 110 21 Pressure altitude HP 3000 ft OAT 9 C Engine RPM Speed KTAS Consumption lt h 4300 100 14 4800 107 18 5200 109 21 Pressure altitude HP 6000 ft OAT 3 C Engine RPM Speed KTAS Consumption lt h 4300 97 14 4800 105 18 5200 108 21 ...

Page 81: ...37 151 165 179 158 At 50 ft AGL 269 296 324 351 311 2000 Ground Roll 142 157 171 185 163 At 50 ft AGL 279 307 336 364 320 3000 Ground Roll 148 162 177 192 168 At 50 ft AGL 290 319 348 377 330 4000 Ground Roll 153 169 184 199 173 At 50 ft AGL 301 331 361 392 340 5000 Ground Roll 159 175 191 207 178 At 50 ft AGL 312 344 375 406 350 6000 Ground Roll 165 182 198 215 184 At 50 ft AGL 324 357 389 422 36...

Page 82: ...8 150 133 At 50 ft AGL 226 249 272 295 261 2000 Ground Roll 120 132 144 156 137 At 50 ft AGL 235 258 282 306 269 3000 Ground Roll 124 137 149 161 141 At 50 ft AGL 243 268 293 317 277 4000 Ground Roll 129 142 155 168 145 At 50 ft AGL 253 278 304 329 285 5000 Ground Roll 134 147 160 174 150 At 50 ft AGL 262 289 315 342 294 6000 Ground Roll 139 153 167 181 154 At 50 ft AGL 272 300 327 355 303 7000 Gr...

Page 83: ...4 124 110 At 50 ft AGL 187 206 225 244 216 2000 Ground Roll 99 109 119 129 113 At 50 ft AGL 194 214 233 253 222 3000 Ground Roll 102 113 123 133 117 At 50 ft AGL 201 221 242 262 229 4000 Ground Roll 106 117 128 138 120 At 50 ft AGL 209 230 251 272 236 5000 Ground Roll 110 122 133 144 124 At 50 ft AGL 217 239 260 282 243 6000 Ground Roll 115 126 138 149 128 At 50 ft AGL 225 248 270 293 251 7000 Gro...

Page 84: ...Page 5 16 Section 5 Performance LANDING PERFORMANCE 1st Edition Rev 0 INTENTIONALLY LEFT BLANK ...

Page 85: ...T and BALANCE INDEX Introduction 2 Weighing Procedure 3 2 1Preparation 3 2 2 Levelling 3 2 3 Weighing 3 2 4 Determination of C G Location 3 Weighing Report I 5 Weighing Report II 6 Weight and Balance Determination for Flight 7 5 1 USE OF WEIGHT BALANCE CHART 7 Equipment List 12 ...

Page 86: ... aircraft Loading procedure information is also provided Aircraft must be operated in accordance with the limits con cerning the maximum take off weight and CG excursion as re ported in Flight Manual Section 2 Pilot is responsible for checking the weight and CG excursion are compliant with the related limits CG excursion and weight limits are reported in Section 2 Lim itations NOTE ...

Page 87: ...n Place scales min capacity 200 kg under each wheel LEVELLING Level the aircraft Reference for levelling remove a seat and then place a level between the two seat s fwd and aft supporting trusses Center bubble on level by deflating nosetire WEIGHING Record weight shown on each scale Repeat weighing procedure three times Calculate emptyweight DETERMINATION OF C G LOCATION Drop a plumb bob tangent t...

Page 88: ...Page 6 4 1rd Edition Rev 0 Section 6 Weight and Balance WEIGHING PROCEDURES Fig 6 1 P92 Echo MkII ...

Page 89: ...y weight We Kg Maximum payload WT We Wu Kg 1 To determine the Mean Aerodynamic Chord MAC and the plumb line see FIG 6 1 Kg Nose wheel weight W1 LH wheel weight WL RH wheel weight WR W2 WL WR meters Plumb bob distance 1 LH wheel AL Plumb bob distance 1 RH wheel AR Average distance AL AR 2 A Bob distance from nose wheel 1 B Empty weight We W1 W2 D D 100 1 400 D W2 A W1 B We Empty weight moment M D 1...

Page 90: ...eight WT Kg Empty weight We Kg Maximum payload WT We Wu Kg 1 To determine the Mean Aerodynamic Chord MAC and the plumb line see FIG 6 1 D D 100 1 400 Kg Nose wheel weight W1 LH wheel weight WL RH wheel weight WR W2 WL WR meters Plumb bob distance 1 LH wheel AL Plumb bob distance 1 RH wheel AR Average distance AL AR 2 A Bob distance from nose wheel 1 B Empty weight We W1 W2 Empty weight moment M D ...

Page 91: ...he pilot co pilot in the Weight and C G Form Table 6 1 Calculate the moment as Moment weight X arm where the arm is read in Table 6 1 Alternatively the moment can be read from the Loading Diagram Figure 6 3 It is strongly recommended to perform a cross check with Loading Tables Table 6 3 to assure an accurate loading value 3 Repeat the procedure described in 2 for the fuel and baggage loads 4 The ...

Page 92: ...red Fuel liters ρfuel 0 72 kg 1 774 Landing condition WL WTO Wfuel_req ML MTO Mfuel_req Table 6 2 Weight and C G Example W kg Arm m Moment M W Arm kg m Empty weight 380 1 898 721 24 LOADING Pilot 80 1 948 155 84 Co pilot 1 948 Baggage 5 2 320 11 6 Usable fuel Fuel liters ρfuel 0 72 kg 80 litres 57 6 1 774 102 18 TAKE OFF CONDITION Take off condition WTO W 523 MTO M 990 86 LANDING CONDITION Fuel re...

Page 93: ...AM Load Weight Kg 100 95 90 Pilot Copilot Sample Calculation 85 80 75 70 65 60 55 50 45 40 35 30 25 20 15 10 5 0 Fuel Quantity Liters 100 95 90 85 80 75 70 65 60 55 50 45 40 35 30 25 20 15 10 5 0 Fuel Baggage Kgm 10 20 30 40 50 60 70 80 90 100 110 120 130 140 150 160 170 180 190 200 0 Load Moment ...

Page 94: ...3 9 60 43 2 76 6 65 46 8 83 0 70 50 4 89 4 75 54 0 95 8 80 57 6 102 2 85 61 2 108 6 90 64 8 115 0 95 68 4 12 8 100 72 0 25 5 Pilot Co pilot loading W kg M kg m 5 9 7 10 19 5 15 29 2 20 39 0 30 58 4 40 77 9 50 97 4 60 116 9 65 126 6 70 136 4 75 146 1 80 155 8 85 165 6 90 175 3 95 185 1 100 194 8 Baggage loading W kg M kg m 2 4 6 4 9 3 6 13 9 8 18 6 10 23 2 12 27 8 14 32 5 16 37 1 18 41 8 20 46 4 ...

Page 95: ...n Rev 0 Section 6 Weight and Balance WEIGHT AND BALANCE Fig 6 3 WEIGHT MOMENT ENVELOPE 650 MTOW 600 Kg 600 550 Take off 500 Landing 450 Sample Calculation 400 650 700 750 800 850 900 950 1000 1050 1100 1150 1200 Moment Kgm ...

Page 96: ...ev 0 Section 6 Weight and Balance EQUIPMENT LIST Fig 6 4 C G RANGE CHART 300 350 400 450 500 550 600 650 1750 1800 1850 1900 1950 2000 2050 WEIGHT kg CG POSITION mm from datum Weight and balance 23 CMA 1841 mm 30 CMA 1939 mm ...

Page 97: ...ngine and accessories B Landing gear C Electrical system D Instruments E Avionics the following information describes each listing Part number to uniquely identify the itemtype Item description Serial number Weight in kilograms Distance in meters from datum Items marked with an asterisk are part of basic installation Equipment marked with X in the Inst column are those actually installed on board ...

Page 98: ...PMENT LIST EQUIPMENT LIST S N DATE RIF DESCRIPTION P N INST WEIGHT kg DATUM m ENGINE ACCESSORIES A1 A2 A3 A4 A5 A6 A7 A8 A9 A10 A11 A12 LANDING GEAR AND ACCESSORIES B1 B2 B3 B4 B5 B6 B7 B8 B9 ELECTRICAL SYSTEM C1 1 C1 2 C1 3 C2 1 C3 C4 C5 C6 C7 C8 C9 C10 C11 C12 ...

Page 99: ...1rd Edition Rev 0 Section 6 Weight and Balance EQUIPMENT LIST EQUIPMENT LIST S N DATE RIF DESCRIPTION P N INST WEIGHT kg DATUM m INSTRUMENTS D1 D2 D3 D4 D5 D6 D7 D8 D9 D10 D11 D12 D13 D14 D15 D16 D17 D18 D19 D20 ...

Page 100: ...tion 6 Weight and Balance EQUIPMENT LIST EQUIPMENT LIST S N DATE RIF DESCRIPTION P N INST WEIGHT kg DATUM m AVIONICS AND OTHER E1 E2 E3 E4 E5 E6 E7 E8 E9 E10 E11 E12 E13 E14 E15 E16 E17 E18 E19 E20 E21 E22 E23 E24 E25 E26 E27 E28 E29 ...

Page 101: ... SYSTEMS DESCRIPTION INDEX 1 Introduction 2 2 Airframe 2 2 1 Wing 2 2 2 Fuselage 2 2 3 Empennages 3 3 FLIGHT CONTROLS 4 4 LANDING GEAR 8 5 WHEEL AND BREAKES 9 6 AVIONIC SYSTEM 9 7 POWERPLANT 12 7 1 Engine 12 7 2 Propeller 12 7 3 Fuel System 13 8 LUGGAGE COMPARTMENT 14 9 DOORS 15 10 SEATS 16 11 RESCUE SYSTEM 17 ...

Page 102: ...sitioned on the lower part of the wing All struc tural parts are made of aluminum light alloy 2024 T3 and 6061 T6 except for tips and fairings which are in fiberglass Fig 7 1 RIGHT WING EXPLODED VIEW 2 2 FUSELAGE The P92 Echo MkII fuselage is mainly made by carbon fibers composite materi als The fuselage is made by two main shells that are later assembled bonding the two main bodies and the floor ...

Page 103: ...ntal trimmable tail plane is all moving type which allows a high con trol authority and a better stick free stability The vertical tail is conventional fin and rudder type Both horizontal and rudder structures are aluminum light alloy 2024 T3 and 6061 T6 except fin which is a carbon fiber unique body with the fuselage and tips which are in fiberglass ...

Page 104: ... STABILIZER TAB Fig 7 3 P92 Echo MkII stabilator and tab Fig 7 4 P92 Echo MkII vertical tail and fin 3 FLIGHT CONTROLS The primary flight controls are of conventional type operated by control stick and rudder pedals Stabilator as per Figure 7 4 is actuated by push pull rods and ca bles ...

Page 105: ... 7 Airframe and Systems description Flight Controls Fig 7 4 P92 Echo MkII stabilator control line system Ailerons as per Figure 7 5 are actuated by push pull rods on wing and cable in fuselage Fig 7 5 P92 Echo MkII aileron control line ...

Page 106: ...le line Fig 7 6 P92 Echo MkII rudder control line Trimming device for longitudinal is provided by push pull rod type system con trolled by an electrical actuator Trim position indicator is installed on A C cock pit In the following figure the pitch trim tab actuation is shown Actuator Trim tab connection Fig 7 7 P92 Echo MkII trim tab control line ...

Page 107: ... Flight Controls connection Actuator The flap control system is reported in Figure 7 8 The system is actuated by means of a linear electrical actuator connected to rods transmitting the movement to the flap surfaces To flap hinge Fig 7 8 P92 Echo MkII flap control system ...

Page 108: ...ing gear is realized with simple steel spring leaves 5 00x5 wheel and tires disc brakes renowed for their operational record of effectiveness and safety Fig 7 9 P92 Echo MkII Main Landing Gear The nose gear features a steerable wheel with a rubber doughnut shock absorber Fig 7 10 P92 Echo MkII Nose Landing Gear ...

Page 109: ...ocated on the back side of co pilot pedals 1 parking brake valve P N PVPVD located downstream the master cylinders used to trap a column of fluid between the valve itself and the brake calipers to firmly stop the wheels 1 oil reservoir with P N 03 3508 0264 3 Fig 7 11 P92 Echo MkII Brake System 6 AVIONIC SYSTEM The electric system installed on P92 Echo MkII is characterized by a rated voltage of 1...

Page 110: ...d on Garmin G3X touch integrated avionic suite in a dual screen configuration GDU 460 It provides flight information through GSU 25 that records air attitude and heading data GMU 22 magnetometer and GTP 59 temperature probe and primary engine information through the engine module GSA 24 Stand alone external COM NAV sources Garmin GTR 225A is installed The GTX 35R remote transponder unit is install...

Page 111: ...Page 7 11 1rd Edition Rev 0 Section 7 Airframe and Systems description Avionic System Fig 7 13 P92 Echo MkII instrument panel ...

Page 112: ... push rods OHV Liquid cooled cylinder heads Ram air cooled cylinders Dry sump forced lubrication Dual ignition of breakerless capacitor discharge design 2 constant depression carburettors Mechanical fuel pumps Electric starter 12 V 0 9 kW Integrated AC generator with external rectifier regulator Propeller drive via integrated gearbox with mechanical shock absorber and overload clutch 7 2 PROPELLER...

Page 113: ...having a 45t 11 8 US gal capacity total capacity is 90lt 23 7 US gal The engine is fed by means of an engine driven mechanical pump and as backup by an electric pump The fuel system has a sediment bowl or chamber that is ac cessible for drainage Fig 7 15 Fuel System A fuel selector is located in cabin Two resistive type fuel quantity senders are in stalled in each tank and provide the fuel indicat...

Page 114: ...ggage Compartment 8 LUGGAGE COMPARTMENT The Luggage compartment is located behind the pilots seats Luggage shall be uni formly distributed on utility shelf and its weight shall not exceed 20kg WARNING Before loading luggage check aircraft s weight and CG location see Sect 6 ...

Page 115: ...ors 9 DOORS Two doors are provided for P92 Echo MkII on pilot and co pilot side Given that the pro peller is located on the nose of the aircraft there are no chances to endanger person using those exits Fig 7 16 P92 Echo MkII Door Doors are also considered as emergency exits ...

Page 116: ...ame and Systems description Seats 10 SEATS Pilot and co pilot seats are characterized by aluminium structure Al 6061 manufactured by Tecnam It is covered by a cushion and connected to the fuselage structure Fig 7 17 P92 Echo MkII Seat Structure ...

Page 117: ...e by means of four bridles The front fitting points are dedicated fixations points near the front at tachments of the wing The rear two fitting points are located by the connection be tween fuselage and the rear wing attachments The parachute is a BRS 6 1050 mod el manufactured by BRS aerospace Fig 7 16 P92 Echo MkII Rescue system attachement FWD AFT Parachute bag ...

Page 118: ...Page 7 18 1rd Edition Rev 0 Section 7 Airframe and Systems description Rescue System INTENTIONALLY LEFT BLANK ...

Page 119: ... OF CONTENTS SEZIONE 8 AIRCRAFT CARE AND MAINTENANCE INDEX 1 Introduction 2 2 Aircraft Inspection Intervals 3 3 Aircraft Changes or Repairs 4 4 Ground Handling 5 4 1 Towing 5 4 2 Parking and Tie Down 5 4 3 Jacking 5 4 4 Leveling 5 4 5 Road Transport 5 5 Cleaning And Care 6 ...

Page 120: ...ground handling and rou tine care and servicing It also identifies certain inspection and maintenance requirements which must be followed if the aircraft is to retain its new plane performance and dependabil ity It is recommended to follow a planned schedule of lubrication and preventive mainte nance based on climatic and flying conditions encountered locally ...

Page 121: ...v 0 Section 8 Aircraft Care and Maintenance Aircraft Inspection Intervals 2 Aircraft Inspection Intervals Correct maintenance procedures are described in the aircraft s Maintenance Manual or in the engine s Maintenance Manual ...

Page 122: ...ection 8 Aircraft Care and Maintenance Aircraft Changes or Repairs 3 Aircraft Changes or Repairs Aircraft changes or repairs must be performed in accordance with Aircraft Maintenance Man ual and only by TECNAM authorized personnel ...

Page 123: ...e weather vaning damage to moving surfaces 4 3 JACKING Given the light empty weight of the aircraft lifting one of the main wheels can easily be ac complished even without the use of hydraulic jacks For an acceptable procedure please refer to the Maintenance Manual 4 4 LEVELING Aircraft levelling may become necessary to check wing incidence dihedral or the exact loca tion of CG Longitudinal levell...

Page 124: ...nish 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 sol vents To clean cabin interior seats upholstery and carpet it is generally recommended to use foam type detergents ...

Page 125: ...Page 9 1 Section 9 AFM Supplements 1st Edition Rev 0 INDEX SECTION 9 AFM SUPPLEMENTS INDEX 1 Introduction 2 2 Supplements List 3 ...

Page 126: ...DUCTION 1 INTRODUCTION This section concerns the supplemental manuals of additional or optional instru mentation equipping the P92 Echo MKII and or information and limitations re lated to installed equipment configuration or needed to fit local national rules ...

Page 127: ...Page 9 3 Section 9 AFM Supplements 1st Edition Rev 0 SUPPLEMENTS LIST 2 SUPPLEMENTS LIST Aircraft S N Registration marks Date Sup N Title Rev N Date APPLICABLE YES NO S01 Alternative Units for Speed 0 ...

Page 128: ...Page 9 4 Section 9 AFM Supplements 1st Edition Rev 0 INTENTIONALLY LEFT BLANK ...

Page 129: ...native Units for Speed RECORD OF REVISIONS Rev Revised page Description of Revision 0 All First issue LIST OF EFFECTIVE PAGES Section Pages Revision Section 0 All Rev 0 Section 1 All Rev 0 Section 2 All Rev 0 Section 3 All Rev 0 Section 4 All Rev 0 Section 5 All Rev 0 Section 6 All Rev 0 Section 7 All Rev 0 Section 8 All Rev 0 ...

Page 130: ...n supplements or supersedes the basic Aircraft Flight Manual detailed instructions are provided to allow the owner for replacing the AFM pages containing information amended per considering speeds in km h IT IS THE OWNER S RESPONSIBILITY TO REPLACE THE MENTIONED PAGES IN ACCORDANCE WITH THE INSTRUCTIONS HEREIN ADDRESSED SECTION BY SECTION ...

Page 131: ...Page S01 3 Section 9 Supplements 1st Edition Rev 0 Supplement N S01 Alternative Unit for Speed SECTION 1 GENERAL Refer to the basic AFM Section 1 General Supplement S01 pages replacement instructions ...

Page 132: ...TATIONS Make sure you first applied instructions reported on the basic AFM Section 2 Limitations According A C configuration apply following pages replacement Supplement S01 LIMITATIONS Page AFM Section 2 Page S2 3 REPLACES 2 3 S2 4 REPLACES 2 4 S2 14 REPLACES 2 14 Supplement S01 pages replacement instructions ...

Page 133: ...r exceed speed 268 255 Do not exceed this speed in any operation VRA Maximum speed for rough air 209 202 Do not exceed this speed except in smooth air and only with caution VA Design Manoeuvring speed 181 176 Do not make full or abrupt control movement above this speed because under certain conditions the air craft may be overstressed by full control movement VFE Maximum flaps extended speed 130 1...

Page 134: ...ng Range lower limit is 1 1VSO at specified maximum weight and upper limit is the maximum speed permissi ble with landing flaps extension Green arc 94 209 Normal Operating Range lower limit is 1 1VS1 at specified maximum weight and most forward c g with flaps retracted and up per limit is maximum speed for rough air VRA Yellow arc 209 268 Manoeuvres must be conducted with caution and only in smoot...

Page 135: ...Alternative Unit for Speed Page S2 14 Section 2 Limitations 1st Edition Rev 0 RESCUE SYSTEM DEPLOYMENT 20 RESCUE SYSTEM DEPLOYMENT Maximum airspeed for rescue system deployment is 268 km h IAS ...

Page 136: ...S Make sure you first applied instructions reported on the basic AFM Section 3 Emergency Procedures According A C configuration apply following pages replacement Supplement S01 EMERGENCY PROCEDURES Page AFM Section 3 page S3 7 REPLACES 3 7 S3 14 REPLACES 3 14 S3 18 REPLACES 3 18 Supplement S01 pages replacement instructions ...

Page 137: ... to the right 3 Flaps as needed WARNING Stall speed increases with bank angle and longitudinal load fac tor Acoustic stall warning will in any case provide a correct anticipated clue of incipient stall At or right before touch down 4 Throttle IDLE fully out 5 Magnetos OFF 6 Fuel selector valve OFF 7 Electric fuel pump OFF 8 Generator Master switches OFF WARNING A single engine aircraft take off sh...

Page 138: ...y 1000ft Above Ground Level it is possible to cover ca 1 5 NM about 3 km 7 2 POWER ON FORCED LANDING 1 Airspeed 120 km h IAS 2 Flaps UP 3 Locate the most suitable terrain for emergency landing plan to approach it upwind 4 Safety belts Tighten 5 Canopy locks CHECK LOCKED When certain to land right before touch down 6 Flaps as necessary 7 Fuel selector valve OFF 8 Electric fuel pump OFF 9 Magnetos O...

Page 139: ...UTION Successful deployment depends on aircraft attitude and air speed greater deployment altitude yields better chances for successful deploymen t Shown below the procedure to be followed 1 Airspeed MINUM POSSIBLE max speed 268 km h IAS 2 Pull activation handle firmly and to end travel After deployment 3 Fuel selector OFF 4 Magnetos OFF 5 Master Switch OFF 6 Seat Belts and Harnesses TIGHTEN Befor...

Page 140: ...e sure you first applied instructions reported on the basic AFM Section 4 Normal Procedures According A C configuration apply following pages replacement Supplement S01 NORMAL PROCEDURES Page AFM Section 3 page S4 2 REPLACES Page 4 2 S4 9 REPLACES Page 4 9 S4 10 REPLACES Page 4 10 Supplement S01 pages replacement instructions ...

Page 141: ... conduction of normal op eration 2 AIRSPEEDS FOR NORMAL OPERATIONS Following airspeeds are significant for normal operations at MTOW 600 kg FLAPS IAS km h Rotation Speed in take off VR T O 83 Best Angle of Climb Speed VX 0 115 Best Rate of Climb speed VY 0 120 Approach speed T O 100 Final Approach Speed FULL 93 Manoeuvring speed VA 0 181 Never Exceed Speed VNE 0 268 ...

Page 142: ...ap retraction speed 93 km h IAS MTOW 600kg Best of Rate Climb Speed VY 120 km h IAS 6 Electric fuel pump OFF 7 Fuel pressure check green arc 8 Engine speed reduce at or below 5500 rpm Takeoffs into crosswinds are performed with the flaps normally set at 15 T O With the ailerons deflected into the wind accelerate the air plane to a speed slightly higher than normal while decreasing the aileron defl...

Page 143: ...h IAS 6 Optimal touchdown speed 80 km h IAS Normal crosswind landings are made with full flaps Avoid pro longed slips Increase airspeed depending on wind intensity and direction as required above normal approach and landing speeds to accommodate increased stall speed when side slip is added After touchdown hold a straight course with rudder and brakes as required The maximum allowable crosswind ve...

Page 144: ...on 9 Supplements 1st Edition Rev 0 Supplement N S01 Alternative Unit for Speed SECTION 5 PERFORMANCES Supplement S01 Performances pages replace basic AFM Section 5 as whole Supplement S01 pages replacement instructions ...

Page 145: ... INDEX Section 5 PERFORMANCES INDEX 1 Introduction 2 2 Use of performances charts 3 3 Airspeed indicator system calibration 4 4 ICAO Standard Atmosphere 5 5 Stall speed 6 6 Crosswind 7 7 Take off performance 8 8 Rate of Climb 11 9 Cruise performance 12 10 Landing performance 13 ...

Page 146: ... activity from take off to landing Data reported in graphs and or in tables were determined using aircraft and engine in good condition average piloting techniques Each graph or table was determined according to ICAO Standard Atmosphere ISA s l evaluations of the impact on performances were carried out by theoretical means for Airspeed External temperature Altitude Weight Runway type and condition...

Page 147: ...PERFORMANCES CHARTS Performances data are 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 the mission with required precision and safety Additional information is provided for each table or graph ...

Page 148: ...NDICATOR SYSTEM CALIBRATION 3 AIRSPEED INDICATOR SYSTEM CALIBRATION Graph shows indicated airspeed VIAS as a function of calibrated airspeed VCAS FIG 5 1 INDICATED VS CALIBRATED AIRSPEED Example Given Find CAS 139 km h IAS 141 km h Indicated airspeed assumes 0 as an instrument error NOTE ...

Page 149: ...ition Rev 0 ICAO STANDARD ATMOSPHERE 4 ICAO STANDARD ATMOSPHERE FIG 5 2 ICAO CHART Examples Scope Given Find Density Altitude A Pressure altitude 1600ft B Temperature 20 C C Density Altitude 2550ft ISA Temperature D Pressure altitude 1600ft E ISA Air Temperature 12 C ...

Page 150: ...BANK ANGLE STALL SPEED km h FLAPS 0 FLAPS T O FLAPS FULL deg IAS CAS IAS CAS IAS CAS 0 83 87 74 80 68 72 15 85 89 76 81 70 74 30 91 93 80 85 74 78 45 102 104 91 94 83 85 60 124 124 111 113 100 102 Altitude loss during conventional stall recovery as demonstrated during flight tests is approximately 200 ft with banking below 20 For Stall Recovery procedure see Section 3 NOTE ...

Page 151: ...ormance 1st Edition Rev 0 CROSSWIND 6 CROSSWIND Maximum demonstrated crosswind is 15 Kts 28 km h Example Given Find Wind direction with respect to aircraft longitudinal axis 30 Headwind 17 5 Kts Wind speed 20 Kts Crosswind 10 Kts FIG 5 3 CROSSWIND CHART ...

Page 152: ...326 399 481 369 1000 Ground Roll 163 205 253 307 230 At 50 ft AGL 284 355 434 523 395 2000 Ground Roll 178 224 277 337 247 At 50 ft AGL 309 386 473 573 423 3000 Ground Roll 194 245 302 377 265 At 50 ft AGL 336 420 515 639 453 4000 Ground Roll 213 268 331 422 285 At 50 ft AGL 367 458 561 712 486 5000 Ground Roll 232 293 370 472 306 At 50 ft AGL 400 499 627 794 521 6000 Ground Roll 254 320 415 528 3...

Page 153: ... 302 1000 Ground Roll 132 167 206 249 186 At 50 ft AGL 232 290 355 428 323 2000 Ground Roll 144 182 224 274 200 At 50 ft AGL 253 315 386 468 346 3000 Ground Roll 158 199 245 306 215 At 50 ft AGL 275 344 421 522 370 4000 Ground Roll 172 217 268 342 231 At 50 ft AGL 300 374 459 582 397 5000 Ground Roll 189 237 300 383 248 At 50 ft AGL 327 408 512 649 426 6000 Ground Roll 206 260 337 428 267 At 50 ft...

Page 154: ...5 242 1000 Ground Roll 105 133 164 198 148 At 50 ft AGL 186 233 285 343 259 2000 Ground Roll 115 145 179 218 159 At 50 ft AGL 203 253 310 375 277 3000 Ground Roll 126 158 195 244 171 At 50 ft AGL 221 276 337 419 297 4000 Ground Roll 137 173 213 272 184 At 50 ft AGL 240 300 368 467 318 5000 Ground Roll 150 189 239 305 198 At 50 ft AGL 262 327 411 520 342 6000 Ground Roll 164 207 268 341 212 At 50 f...

Page 155: ...00 S L 1318 1085 876 689 957 2000 1140 911 706 522 818 4000 964 738 537 355 679 6000 788 566 368 190 540 8000 612 394 200 25 401 10000 437 223 32 141 261 550 S L 1482 1230 1006 803 1092 2000 1290 1043 822 623 942 4000 1100 857 640 444 793 6000 910 671 458 265 643 8000 720 486 276 87 493 10000 532 301 95 91 343 500 S L 1677 1402 1156 935 1251 2000 1468 1198 957 740 1088 4000 1260 994 757 544 925 60...

Page 156: ...45 liters 11 9 gal less the unusable fuel Pressure altitude HP 0 ft OAT 15 C Engine RPM Speed KTAS Consumption lt h 4300 189 14 4800 198 18 5200 204 21 Pressure altitude HP 3000 ft OAT 9 C Engine RPM Speed KTAS Consumption lt h 4300 185 14 4800 198 18 5200 202 21 Pressure altitude HP 6000 ft OAT 3 C Engine RPM Speed KTAS Consumption lt h 4300 180 14 4800 194 18 5200 200 21 ...

Page 157: ... 1000 Ground Roll 137 151 165 179 158 At 50 ft AGL 269 296 324 351 311 2000 Ground Roll 142 157 171 185 163 At 50 ft AGL 279 307 336 364 320 3000 Ground Roll 148 162 177 192 168 At 50 ft AGL 290 319 348 377 330 4000 Ground Roll 153 169 184 199 173 At 50 ft AGL 301 331 361 392 340 5000 Ground Roll 159 175 191 207 178 At 50 ft AGL 312 344 375 406 350 6000 Ground Roll 165 182 198 215 184 At 50 ft AGL...

Page 158: ... Roll 115 127 138 150 133 At 50 ft AGL 226 249 272 295 261 2000 Ground Roll 120 132 144 156 137 At 50 ft AGL 235 258 282 306 269 3000 Ground Roll 124 137 149 161 141 At 50 ft AGL 243 268 293 317 277 4000 Ground Roll 129 142 155 168 145 At 50 ft AGL 253 278 304 329 285 5000 Ground Roll 134 147 160 174 150 At 50 ft AGL 262 289 315 342 294 6000 Ground Roll 139 153 167 181 154 At 50 ft AGL 272 300 327...

Page 159: ...d Roll 95 105 114 124 110 At 50 ft AGL 187 206 225 244 216 2000 Ground Roll 99 109 119 129 113 At 50 ft AGL 194 214 233 253 222 3000 Ground Roll 102 113 123 133 117 At 50 ft AGL 201 221 242 262 229 4000 Ground Roll 106 117 128 138 120 At 50 ft AGL 209 230 251 272 236 5000 Ground Roll 110 122 133 144 124 At 50 ft AGL 217 239 260 282 243 6000 Ground Roll 115 126 138 149 128 At 50 ft AGL 225 248 270 ...

Page 160: ... Section 9 Supplements 1st Edition Rev 0 Supplement N S01 Alternative Unit for Speed SECTION 6 WEIGHT and BALANCE Refer to the basic AFM Section 6 WEIGHT and BALANCE Supplement S01 pages replacement instructions ...

Page 161: ...plements 1st Edition Rev 0 Supplement N S01 Alternative Unit for Speed SECTION 7 AIRFRAME AND SYSTEMS DESCRIPTION Refer to the basic AFM Section 7 AIRFRAME AND SYSTEMS DESCRIPTION Supplement S01 pages replacement instructions ...

Page 162: ...tion 9 Supplements 1st Edition Rev 0 Supplement N S01 Alternative Unit for Speed SECTION 8 GROUND HANDLING SERVICE Refer to the basic AFM Section 8 GROUND HANDLING SERVICE Supplement S01 pages replacement instructions ...

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