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Tecnam P2010 Flight Manual Download Page 425

AFMS N°D07 FOR GARMIN GFC700 AUTOPILOT AND VARIABLE PITCH PROPELLER EQUIPPED 

AEROPLANES 

 

 

 

Page APV2-9 

Ed 1, Rev. 1 

 

Section 2 – Limitations

 -

 

PAINT, PROPELLER, MAX ALTITUDE AND OAT 

 

Approved 

 

7.

 

PAINT 

To  ensure  that  the  temperature  of  the  composite  structure  does 
not  exceed  limits,  the  outer  surface  of  the  aeroplane  must  be 
painted  with  white  paint,  except  for  areas  of  registration  marks, 
placards, and ornament. 

Refer to Aircraft Maintenance Manual (AMM), ATA Chapter 4 and 
51, for specific paint requirements. 

8.

 

PROPELLER 

 

MANUFACTURER

: .……..  MT Propeller 

MODEL

: …………….…….   MTV 15B/193-52 

TYPE

: .……………….……   wood/composite 2-blade, variable pitch 

DIAMETER

: ……………...  1930 mm (76 in) (no reduction is permitted) 

 

9.

 

MAXIMUM

 

OPERATING

 

ALTITUDE 

Maximum operating altitude is 12000 ft (3658 m) MSL. 

 

 

 

 

10.

 

 

AMBIENT

 

TEMPERATURE 

Ambient temperature: from -25°C to +50°C. 

 

 

 

 

 

 

 

 

 

 

 

 

At  altitudes above 10000  ft  (3048  m)  up  to  and  including  12000 ft 
(

3658 

m), flight crew is recommended to use supplemental oxygen.

 

 

 

Flight in expected and/or known icing conditions is forbidden

 

Summary of Contents for P2010

Page 1: ... 26TH SERIAL NUMBER BUILD YEAR REGISTRATION MARKINGS This manual is approved in accordance with 14 CFR 21 29 for US registered air craft and is approved by the Federal Aviation Administration This Manual must be carried in the airplane at all times The airplane has to be operated in compliance with procedures and limitations contained herein Costruzioni Aeronautiche TECNAM srl Via Maiorise CAPUA C...

Page 2: ...Page 0 2 2nd Edition Rev 0 Aircraft Flight Manual INDEX INDEX 1 RECORD OF REVISIONS 3 2 LIST OF EFFECTIVE PAGES 7 3 FOREWORD 8 4 SECTIONS LIST 9 ...

Page 3: ... be necessary to completely reissue a publication for contents and format changes 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...

Page 4: ...regulation D Ronca C Caruso M Oliva Approved under the au thority of DOA ref EASA 21J 335 Approval No MOD2010 070 160118 9 3 Supplement List Index amended D Ronca C Caruso M Oliva EASA approval N 10055692 Add Supplement D04 D Ronca C Caruso M Oliva 2 5 13 thru 14 Amended cruise performance to add fuel consumption for differ ent power setting D Ronca C Caruso M Oliva Approved under the au thority o...

Page 5: ...Page 0 5 2nd Edition Rev 0 Aircraft Flight Manual RECORD OF REVISIONS Rev Revised page Description of Revision Tecnam Approval EASA Approval Or Under DOA Privileges DO OoA HDO ...

Page 6: ...Page 0 6 2nd Edition Rev 0 Aircraft Flight Manual INTENTIONALLY LEFT BLANK ...

Page 7: ...P addressed on Supplements themselves 1st Edition Rev 0 September 26 2014 1st Edition Rev 1 April 8 2015 2nd Edition Rev0 October 30 2015 2nd Edition Rev1 January 18 2016 2nd Edition Rev2 November 25 2016 Section Pages Revision Section 0 Pages 1 thru 10 Rev 0 Section 1 Pages 1 thru 16 Rev 0 Section 2 Pages 1 thru 4 Rev 0 Pages 5 thru 16 Rev 1 Section 3 Pages 1 thru 30 Rev 0 Section 4 Pages 1 thru ...

Page 8: ...yms 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 TECNAM s r l Via MAIORISE CAPUA CE ITALY 39 0823 99 75 38 airworthiness tecnam com www tecnam com ...

Page 9: ...ncy Procedures Section 3 Normal Procedures Section 4 Performances Section 5 Weight and Balance Section 6 Airframe and Systems description Section 7 Airplane Care and Maintenance Section 8 Supplements Section 9 non approved Section approved Section partially approved Section approved parts if any are reported in the supplements ...

Page 10: ...Page 0 10 2nd Edition Rev 0 Aircraft Flight Manual INTENTIONALLY LEFT BLANK ...

Page 11: ... 1 INTRODUCTION 3 2 CERTIFICATION BASIS 3 3 WARNING CAUTION NOTE 3 4 THREE VIEW AND DIMENSIONS 4 5 ENGINE 6 6 PROPELLER 6 7 FLIGHT CONTROL SURFACES TRAVEL 7 8 SPECIFIC LOADINGS 7 9 ACRONYMS AND TERMINOLOGY 9 10 UNIT CONVERSION CHART 14 11 LITRES US GALLONS CONVERSION CHART 15 ...

Page 12: ...Page 1 2 Section 1 General 2nd Edition Rev 0 INTENTIONALLY LEFT BLANK ...

Page 13: ...26th September 2014 Category of Airworthiness Normal Noise Certification Basis EASA CS 36 Amendment 2 This type of aircraft has been validated also in the normal category of 14 CFR part 23 and part 36 3 WARNING CAUTION NOTE Following definitions apply to warnings cautions and notes used in the Aircraft Flight Manual WARNING means that the non observation of the corresponding procedure leads to an ...

Page 14: ...Page 1 4 Section 1 General THREE VIEW AND DIMENSIONS 2nd Edition Rev 0 4 THREE VIEW AND DIMENSIONS Figure 1 General views ...

Page 15: ...m 26 15 ft Overall height 2 64 m 8 66 ft Stabilator Span 3 35 m 10 99 ft Wing Wing surface 13 9 m2 149 6 ft2 Mean Geometric Chord 1 349 m 4 427 ft Dihedral 1 Aspect ratio 7 63 Fuselage Cabin width 1 14 m 3 74 ft Cabin length 2 3 m 7 54 ft Landing Gear Wheels Track 2 1 m 6 89 ft Wheels base 2 15 m 7 05 ft Main Gear Tire 6 00 6 Nose Gear Tire 5 00 5 ...

Page 16: ...type Fuel injected IO direct drive four cylinder horizontally opposed air cooled with down exhaust outlets Maximum power Maximum continuous power 134 0 kW 180 hp 2700 rpm 134 0 kW 180 hp 2700 rpm 6 PROPELLER Manufacturer MT Propeller Model MT 188 R 145 4G Type Certificate EASA TCDS no P 006 Blades hub 2 wood composite blades aluminium hub Diameter 1880 mm 74 in no reduction allowed Type Fixed pitc...

Page 17: ...L Ailerons Up 19 Down 14 2 Stabilator Up 6 Down 17 2 Stabilator trim tab Up 3 Down 15 1 Rudder RH 25 LH 25 2 Rudder trim tab RH 20 LH 20 2 Flaps 0 20 40 1 degrees are measured from the Stabilator Leading Edge 8 SPECIFIC LOADINGS MTOW 1160 kg 2557 lb Wing Loading 83 45 kg m2 17 09 lb ft2 Power Loading 6 44 kg hp 14 21 lb hp ...

Page 18: ...Page 1 8 Section 1 General 2nd Edition Rev 0 TERMINOLOGYSP ECIFIC LOADINGS INTENTIONALLY LEFT BLANK ...

Page 19: ...t be exceeded except in smooth air and only with caution VNE Never Exceed Speed is the speed limit that may not be exceeded at any time VO Operating Manoeuvring speed is the speed above the which it is not allowed to make full or abrupt control movement VS Stall Speed VS0 Stall Speed in landing configuration flaps and landing gear ex tended VS1 Stall speed in clean configuration flaps 0 VX Best An...

Page 20: ...t to the official airport level QNH Theoretical atmospheric 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 decreased by 2 ...

Page 21: ...fuel that cannot be safely used in flight G is the acceleration of gravity TOR is the takeoff distance measured from actual start to MLG wheel liftoff point TOD is total takeoff distance measured from start to 15m obstacle clearing GR is the distance measured during landing from actual touchdown to stop point LD is the distance measured during landing from 15m obstacle clearing to actual stop S R ...

Page 22: ...t would balance if suspended Its distance from the reference datum is found by dividing the total moment by the total weight of the aircraft Standard Empty Weight is the weight of the aircraft with engine flu ids 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 takeoff weight...

Page 23: ...Page 1 13 Section 1 General 2nd Edition Rev 0 INTENTIONALLY LEFT BLANK ...

Page 24: ...0508 Meters per se cond 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 1 853 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 2...

Page 25: ... 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 9 100 26 4 26 98 4 110 29 1 28 106 0 120 31 7 30 113 6 130 34 3 32 121 1 140 37 7 34 128 7 150 39 6 36 136 3 160 42 3 38 143 8 170 44 9 40 151 4 180 47 6 42 159 190 50 2 45 170 3 200 52 8 47 177 9 210 55 5 50 189 3 220 58 1 55 208 2 230 60 7 60 227 1 24...

Page 26: ...Page 1 16 Section 1 General 2nd Edition Rev 0 INTENTIONALLY LEFT BLANK ...

Page 27: ...TING ALTITUDE 9 10 AMBIENT TEMPERATURE 9 11 POWERPLANT INSTRUMENT MARKINGS 10 12 OTHER INSTRUMENT MARKINGS 10 13 WEIGHTS 11 14 CENTER OF GRAVITY RANGE 11 15 FLIGHT CREW 11 16 APPROVED MANEUVERS 12 16 1 Types of Surface 12 17 MANEUVERS LOAD FACTOR LIMITS 12 18 KINDS OF OPERATION EQUIPMENT LIST KOEL 13 19 LIMITATIONS PLACARDS 15 19 1 Speed limitations 15 19 2 Operating limitations 15 19 3 No Smoking...

Page 28: ...Page 2 2 Section 2 Limitations 2nd Edition Rev 0 INTENTIONALLY LEFT BLANK ...

Page 29: ...v 0 Section 2 Limitations INTRODUCTION 1 INTRODUCTION Section 2 includes operating limitations instrument markings and basic placards necessary for safe operation of the aeroplane its engine and standard systems and equipment ...

Page 30: ...Page 2 4 2nd Edition Rev 0 Section 2 Limitations INTENTIONALLY LEFT BLANK ...

Page 31: ...exceed this speed in any operation VNO Maximum Structural Cruising Speed 132 130 Do not exceed this speed except in smooth air and only with caution VA Design Manoeuvring speed 120 119 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 VO Operating Manoeuvring speed VFE Maximum flaps extended spee...

Page 32: ...Flap Operating Range lower limit is VSO at specified maximum weight and upper limit is the maximum speed permissi ble with landing flaps extension Green arc 59 132 Normal Operating Range lower limit is VS1 at specified maximum weight and most for ward c g with flaps retracted and upper limit is maximum structural speed VNO Yellow arc 132 166 Manoeuvres must be conducted with caution and only in sm...

Page 33: ...ngines ENGINE MODEL IO 360 M1A MAXIMUM POWER Max Power hp Max rpm Prop rpm Max T O 180 2700 Max Cont 180 2700 Temperatures Max CHT 500 F 260 C Max Oil 245 F 118 C Oil Pressure Minimum Idling 25 psi 1 7 Bar Minimum Normal 55 psi 3 8 Bar Maximum Normal 95 psi 6 5 Bar Starting Warm up taxi and take off Max 115 psi 7 9 Bar Fuel pressure At Inlet to fuel injector Minimum 14 psi 0 96 Bar Maximum 35 psi ...

Page 34: ...Service Instruction No 1070 latest issue 6 LUBRICANT Recommended Grade Oil Average Ambient Temperature All Temperatures Above 80 F Above 60 F 30 F to 90 F 0 F to 70 F Below 10 F MIL L 6082B or SAEJ1966 Spec Mineral Grades SAE60 SAE50 SAE40 SAE30 SAE20 MIL L 22851 or SAEJ1899 Spec Ashless Dispersant Grades SAE15W50 or SAE20W 50 SAE60 SAE40 or SAE50 SAE40 SAE40 SAE30 SAE20W40 SAE30 or SAE20W30 For a...

Page 35: ...ATA Chapter 4 and 51 for specific paint requirements 8 PROPELLER MANUFACTURER MT Propeller MODEL MT 188 R 145 4G TYPE wood composite 2 blade fixed pitch DIAMETER 1880 mm 74 in no reduction is permitted 9 MAXIMUM OPERATING ALTITUDE Maximum operating altitude is 12000 ft 3658 m MSL CAUTION At altitudes above 10000 ft 3048 m up to and including 12000 ft 3658 m flight crew is recommended to use supple...

Page 36: ...tion RED ARC Maximum limit PROPELLER RPM 950 2700 0 950 2700 2800 OIL TEMP F 140 245 0 140 245 255 CHT F 435 line 150 475 0 150 475 500 500 510 EGT F 1000 1500 1375 line 1500 1550 OIL PRESS psi 0 25 55 95 25 55 95 115 115 125 FUEL PRESS psi 0 14 14 35 35 40 FUEL QTY litres 0 0 115 gal 0 0 30 4 FUEL FLOW l hr 0 75 gal hr 0 20 12 OTHER INSTRUMENT MARKINGS INSTRUMENT RED ARC Minimum limit GREEN ARC S...

Page 37: ...m 10 3 in 19 MAC aft of datum for all weights Aft limit 0 440 m 17 3 in 32 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 tions 15 FLIGHT CREW Minimum crew 1 pilot Maximum seating configuration 4 people including the pilot Condition Weight Maximum takeoff weight 1160 kg 2557 lb Maximum l...

Page 38: ...proved for such a category In addition Intentional shutdown of engine in flight is forbidden WARNING Limit load factor could be exceeded by moving flight controls to maxi mum deflection at a speed above VA VO 120 KIAS Manoeuvring Speed WARNING Flight in expected and or known icing conditions in proximity of storms or in severe turbulence is forbidden 16 1 TYPES OF SURFACE This aircraft may operate...

Page 39: ...illing these requirements Equipment VFR Day VFR Night IFR Day IFR Night Note External Power Circuit Breakers As Required Battery Safety Equipment Furnishing First Aid kit Fire extinguisher ELT Torch with spare batteries Ice Protection Pitot heating system Landing Gear Wheel pants Removable Lights Landing taxi lights Strobe lights NAV lights Cabin lights Instrument lights Emergency light Dimming De...

Page 40: ...Page 2 14 Section 2 Limitations 2nd Edition Rev 1 Approved INTENTIONALLY LEFT BLANK ...

Page 41: ...nel above on the left it is placed the following plac ard reporting the speed limitations 19 2 OPERATING LIMITATIONS On the central side of the instrument panel the following placard is placed remind ing the observance of aircraft operating limitations according to installed equipment configuration see KOEL paragraph 18 19 3 NO SMOKING PLACARD On the right hand side of the instrument panel the fol...

Page 42: ...Page 2 16 Section 2 Limitations LIMITATIONS PLACARDS 2nd Edition Rev 1 Approved 19 4 BAGGAGE COMPARTMENT PLACARD Behind the baggage compartment door the following placard is placed ...

Page 43: ...al speed information 9 3 6 Loss of heading information 9 3 7 Display failure 10 4 Engine securing 11 5 Aircraft evacuation 11 6 Engine failures 13 6 1 Engine failure during takeoff run 13 6 2 Engine failure after Take off 13 6 3 Propeller overspeed 14 6 4 Irregular rpm 14 6 5 CHT limit exceedance 15 6 6 Oil temperature limit exceedance 15 6 7 Oil pressure limits exceedance 16 Low oil pressure 16 H...

Page 44: ...gencies 25 10 1 Loss of Essential Bus 25 10 2 Loss of Main Bus 25 10 3 Electrical system overall failure 26 10 4 Static port failure 26 10 5 Unintentional flight into icing conditions 27 10 6 Flaps control failure 27 10 7 Electrical Rudder Trim control failure 28 11 Landing emergencies 29 11 1 Forced landing without engine power 29 11 2 Power on forced landing 29 11 3 Landing with nose landing gea...

Page 45: ... recognized These procedures characters are boxed and highlighted as shown below BEFORE ROTATION ABORT TAKE OFF 1 Throttle IDLE 2 Rudder Keep heading control 3 4 b Other procedures which should be well theoretically know and mastered but that are not time critical and can be executed entering and following step by step the AFM appropriate checklist In case of emergency the pilot should acts as fol...

Page 46: ...Page 3 4 Section 3 Emergency procedures 2nd Edition Rev 0 INTENTIONALLY LEFT BLANK ...

Page 47: ...N AMBER to indicate no hazard situations which have to be considered and which require a proper crew action RED to indicate emergency conditions 2 1 ALTERNATOR FAILURE Annunciation window Alert window ALT FAIL Alternator failure If ALT FAIL caution is ON 1 Circuit breaker s Check 2 Generator SWITCH OFF 3 Generator SWITCH ON If ALT FAIL CAUTION REMAINS on 4 Generator SWITCH OFF A fully charged batt...

Page 48: ...on and the amber PITOT HEAT caution light turns OFF indi cating that the Pitot Heating system is functioning properly If the amber PITOT HEAT caution light is ON when the green PITOT HEAT ON light is on then the Pitot Heating system is not functioning properly In this case apply following procedure 1 Pitot heat switch OFF 2 Pitot heat circuit breaker CHECK IN 3 Pitot heat switch ON 4 PITOT HEAT ca...

Page 49: ...led data In most of cases the red X annunciation is accompanied by a message advisory alert issuing a flashing ADVISORY Softkey annunciation which once selected acknowledges the presence of the message advisory alert and displays the alert text message in the Alerts Window 3 2 LOSS OF AIRSPEED INFORMATION AIRSPEED FAIL RED X ON DISPLAY FIELD Display system is not receiving airspeed input from Air ...

Page 50: ...TITUDE FAIL RED X ON DISPLAY FIELD Display system is not receiving attitude information from AHRS INSTRUCTION revert to standby instrument 3 4 LOSS OF ALTITUDE INFORMATION ALTITUDE FAIL RED X ON DISPLAY FIELD Display system is not receiving altitude input from Air Data Computer INSTRUCTION revert to standby instrument ...

Page 51: ...AIL RED X ON DISPLAY FIELD Display system is not receiving vertical speed input from Air Data Computer INSTRUCTION determine vertical speed on the basis of altitude information 3 6 LOSS OF HEADING INFORMATION HDG RED X ON DISPLAY FIELD Display system is not receiving valid heading input from AHRS INSTRUCTION revert to magnetic compass ...

Page 52: ...change to backup path is completely automated for all LRUs and no pilot action is required if the system fails to detect a display problem 1 REVERSIONARY MODE button PUSH REVERSIONARY MODE button is red and located on the bot tom of the audio panel CAUTION If a display fails the related Integrated Avionics Unit IAU is cut off and can no longer communicate with the remaining dis play subsequently t...

Page 53: ...e in flight 1 Throttle Lever IDLE 2 Ignition key OFF 3 Fuel Selector OFF 4 Electrical fuel pump OFF 5 Generator switch OFF 5 AIRCRAFT EVACUATION With the engine secured and propeller stopped if practical 1 Parking brake ON 2 Seat belts Unstrap 3 Headphones Remove 4 Door OPEN 5 MASTER SWITCH OFF 6 Escape away from flames hot engine compartment spilling fuel tanks hot brakes ...

Page 54: ...Page 3 12 2nd Edition Rev 0 Section 3 Emergency procedures INTENTIONALLY LEFT BLANK ...

Page 55: ... engine fails immediately after becoming airborne Abort on the runway if possible In case low altitude precludes a runway stop and or engine restart 1 establish a glide attitude 85 KIAS Find a suitable place on the ground to land safely CAUTION The landing should be planned straight ahead with only small changes in directions not exceeding 45 to the left and 45 to the right Any turn would reduce t...

Page 56: ...ecrease propeller rpm land as soon as possible applying Forced landing procedure See Para 11 CAUTION Maximum propeller rpm exceedance may cause engine components damage Apply caution while accelerating with power lever close to max and monitor engine RPM RPM overspeed shall be prevented by retard ing power lever 6 4 IRREGULAR RPM 1 Fuel pump ON 2 Fuel quantity and pressure indicators CHECK 3 If ne...

Page 57: ...ture exceeds maximum limit 245 F Maximum oil temperature limit exceedance can be the final effect of different causes excessive friction between moving engine components oil leakage from the circuit with related pressure reduction etc 1 Throttle Lever REDUCE engine power 2 Mixture lever Enrich as required 3 OIL TEMP CHECK if oil temperature does not decrease 4 Airspeed INCREASE 5 OIL TEMP CHECK If...

Page 58: ...d temperature exceeds limits Reduce engine power to minimum required Land as soon as possible applying Forced landing procedure See Para 11 Be prepared for engine failure and emergency landing If oil pressure tends to zero combined with vibration loss of oil unusual metallic smoke and noise Apply Forced landing procedure See Para 11 HIGH OIL PRESSURE If oil pressure exceeds upper limit 115 psi 1 T...

Page 59: ...ank if NOT empty 3 Fuel quantity CHECK If fuel pressure doesn t build up 1 Land as soon as practical Prepare for potential engine failure and pre pare to apply Forced landing procedure See Para 11 6 9 HIGH FUEL PRESSURE If fuel pressure increases above the upper limit 35 psi 1 Land as soon as possible Prepare for potential engine shut down and apply Forced landing procedure See Para 11 Possible in...

Page 60: ...wer setting A lean mixture can lead to engine roughness and loss of power Landing approach must be planned accordingly WARNING Go around may then be impossible Defective Throttle Control Cable If power is sufficient to continue flight 1 Approach nearest airfield 2 Perform landing with shut down engine applying Forced landing proce dure See Para 11 If power is not sufficient to continue flight 1 Ca...

Page 61: ... 500 RPM to be confirmed by other engine instrument OIL Pressure CHT EGT running down abnormally Inflight engine restart may be performed during 1g flight anywhere within the normal operating envelope of the airplane 1 Master switch Check ON 2 Fuel pump ON 3 Fuel quantity indicator CHECK 4 Fuel Selector SWITCH TANK 5 Throttle Lever Minimum 1cm 0 39in above IDLE 6 Mixture FULL rich 7 Throttle lever...

Page 62: ...Page 3 20 2nd Edition Rev 0 Section 3 Emergency procedures INTENTIONALLY LEFT BLANK ...

Page 63: ...tion ABORT TAKE OFF 1 Throttle Lever IDLE 2 Mixture CUT OFF 3 Brakes As required With aircraft under control 4 Fuel Selector OFF 5 Electrical fuel pump OFF 6 Ignition key OFF 7 Cabin Heat OFF 8 Field Master Switches OFF 9 Parking Brake ENGAGED 10 Aircraft Evacuation PERFORM Para 4 8 3 ENGINE FIRE IN FLIGHT 1 Cabin heat and defrost BOTH OFF 2 Mixture CUTOFF 3 Fuel Selector OFF 4 Throttle Lever FULL...

Page 64: ...OFF With propeller stopped evacuate the aircraft 8 5 ELECTRICAL SMOKE IN CABIN DURING FLIGHT 1 Cabin heat OFF 2 Cabin ventilation OPEN 3 In case of fire direct the fire extinguisher toward the base of flame If smoke persists 4 Generator switch OFF If smoke persists 5 Generator switch ON 6 Keep RPM above 1000 7 Master switch OFF If smoke persists 8 Generator switch OFF CAUTION If the Generator SWIT...

Page 65: ...der Fully opposite to the direction of spin 3 Control Yoke Centralize and hold neutral When rotation stops 4 Rudder Neutral 5 Attitude Recovery promptly but smoothly averting speed close to in excess of VNE 6 Throttle As required WARNING Keep full rudder against rotation until spin has stopped One complete turn and recovery will take about 800 to 1000 feet alti tude loss ...

Page 66: ...Page 3 24 2nd Edition Rev 0 Section 3 Emergency procedures INTENTIONALLY LEFT BLANK ...

Page 67: ...st Flaps extension and retraction will be lost apply Flaps control failure procedure See Para 10 6 Strobe and landing lights will be lost NAV and taxi lights are still available taxi light will be the only visual aid for landing in night conditions 10 2 LOSS OF MAIN BUS In case of loss of main bus the main bus voltage will drop to zero The following will be lost related breakers are listed AUDIO P...

Page 68: ...andby instrument is still available providing the internal bat tery is in good charge status 80 it will provide at least 1 hr of runtime WARNING An electrical system overall failure prevents flaps operation landing distance without flaps increases of about 25 See also Para 10 6 10 4 STATIC PORT FAILURE In case failure the alternate static port in the cabin must be activated In this case apply foll...

Page 69: ...symmetric In case of stabilator ice accretion it may loose its efficiency lead ing to lack of aircraft pitch control and loss of control 10 6 FLAPS CONTROL FAILURE DURING TAKEOFF CAUTION In case of unintentional flaps retraction or if the flaps control fails and if the takeoff cannot be aborted consider that the dis tances without flaps increase by about 20 1 Flap position Check and confirm 2 Airs...

Page 70: ...vent of trim runaway 1 Speed adjust to control aircraft without excessive pedal force 2 Rudder As required 3 Land aircraft as soon as practical Trim Jamming Should trim control be jammed inoperative 1 Breaker CHECK IN 2 Speed adjust to control aircraft without excessive pedal force 3 Rudder As required 4 Land aircraft as soon as practical ...

Page 71: ...er IDLE 8 Mixture CUTOFF 9 Fuel Selector OFF 10 Ignition key OFF 11 Fuel pump OFF 12 Seat belts Tightly fastened When landing is assured 13 Flaps As required 14 Generator and Master switches OFF Be prepared for aircraft evacuation Para 4 11 2 POWER ON FORCED LANDING 1 Flaps UP 2 Best Glide Speed 85KTS 3 Locate the most suitable terrain for emergency landing plan to approach upwind 4 Safety belts T...

Page 72: ... Para 4 11 4 LANDING WITH A MAIN LANDING GEAR TIRE DEFLATED 1 Pre landing checklist Complete 2 Flaps Land 3 Land the aeroplane on the side of runway opposite to the defective tire to compensate the change in direction which is to be expected during final rolling put the drag in the middle 4 Touchdown with the GOOD TIRE FIRST and hold aircraft with the flat tire off the ground as long as possible b...

Page 73: ...alk around 10 5 CHECKLISTS 15 5 1 Before Starting engine After Preflight Inspection 15 5 2 Engine Starting 16 5 3 Before taxiing 17 5 4 Taxiing 18 5 5 Before takeoff 19 5 6 Takeoff 20 5 7 Climb 21 5 8 Cruise 22 5 9 Mixture adjustment recommendation 22 5 10 Descent 23 5 11 Before landing 24 5 12 Balked landing missed approach 24 5 13 Go around 24 5 14 After landing 24 5 15 Engine shut down 25 5 16 ...

Page 74: ...Section 4 Normal procedures 2nd Edition Rev 0 Page 4 2 INTENTIONALLY LEFT BLANK ...

Page 75: ...Section 4 Normal procedures INTRODUCTION 2nd Edition Rev 0 Page 4 3 1 INTRODUCTION Section 4 describes checklists and recommended procedures for the conduct of normal operations for P2010 aircraft ...

Page 76: ...aining on the computer assisted software and pre flight training before flight Furthermore as a minimum during training it s strongly recommended using the avionic suite in IFR with incremental steps after initial basic IFR instruction 1 Initial use of a single radio aids No GPS 2 Use of two radio aids No GPS 3 Use of GPS for point to point navigation No approaches 4 Use of VNAV feature 5 Full use...

Page 77: ...ise handling The following prescriptions other than those already present in the G1000 manu al shall be observed Use of GPS for precision approach navigation mode is not allowed Use of GPS is prohibited as primary means for navigation GPS is approved as sup plemental means for navigation Use of GPS is prohibited for IFR in terminal area or in non precision approach op erations If Receiver Autonomo...

Page 78: ...Page 4 6 Section 4 Normal procedures 2nd Edition Rev 0 INTENTIONALLY LEFT BLANK ...

Page 79: ...perations FLAPS 1160 kg 2557 lb Rotation Speed VR T O 60 KIAS Best Angle of Climb Speed VX T O 65 KIAS Best Angle of Climb Speed VX 0 76 KIAS Best Rate of Climb speed VY 0 82 KIAS Flaps VFE T O LAND 91 KIAS No flaps approach 0 80 KIAS Approach speed T O 75 KIAS Final Approach Speed FULL 70 KIAS Manoeuvring speed VA 0 120 KIAS Glide Speed Vglide 0 85 KIAS Never Exceed Speed VNE 0 166 KIAS ...

Page 80: ...Page 4 8 Section 4 Normal procedures 2nd Edition Rev 0 INTENTIONALLY LEFT BLANK ...

Page 81: ...ate of Airworthiness Noise certificate Radio COM certificate AFM check current and on board 2 Weight and balance calculate ref to Section 6 and check within limits 3 Breaker all IN 4 Safety belts connected to hard points check condition 5 Ignition key OFF key extracted 6 Master switch ON 7 Voltmeter check within the limits 8 Lights all ON check for operation 9 Acoustic stall warning check for oper...

Page 82: ...sual in spection also involves additional check for freedom of movement and security Red lubber lines on bolts and nuts shall be intact WARNING Fuel level indicated by the fuel quantity indicators must be veri fied by visual check of actual fuel quantity embarked in the tanks graduated dipstick must be used WARNING If ignitions key is in L R BOTH position a propeller movement can cause the engine ...

Page 83: ...her contaminants Make sure filler cap is closed B Pitot tube REMOVE pitot plug and check the pitot for obstructions Do not blow inside pitot tube C Left side leading edge and wing skin Visual inspection check stall strips if pre sent D Left strobe light Visual inspection CHECK for integrity and fixing E Left aileron hinges and LH tank vent line CHECK aileron and hinges for damage and freedom from ...

Page 84: ...s integrity gear structure and brakes hoses there should be no sign of hydraulic fluid leakage M Right flap and hinges Visual inspection Copper bonding strips CHECK for proper connection N Right aileron hinges and RH tank vent line Visual inspection check free of play friction Copper bonding strips CHECK for proper connection Right side tank vent check for obstructions O Right strobe light leading...

Page 85: ... tank check for correct level and replenish as required 2 Check V belt for general condition 3 Exhaust inspect for damages leakage and general condition 4 Check engine mount and silent blocks for condition e At cold engine Check engine oil level and replenish as required Prior to long flights oil should be added so that the oil level reaches the max mark f Drain off Gascolator for water and sedime...

Page 86: ...Page 4 14 Section 4 Normal procedures 2nd Edition Rev 0 0 INTENTIONALLY LEFT BLANK ...

Page 87: ...d into the tanks see Pre flight inspection External inspection and update the Garmin fuel content in the totalizer accordingly The totalizer function available on Garmin Engine page allows input only up to 230lts maximum usable fuel Fuel calculations on totalizer do not use the air craft fuel quantity indicators and are calculated from the last time the fuel was re set Fuel consumption on totalize...

Page 88: ...e it for more than 10 seconds After operating the starter motor let it cool off for 20 seconds After 6 attempts to start the engine let the starter cool off for half an hour 6 Ignition key BOTH 7 Ignition key START 8 Mixture rapidly move to FULL RICH 9 Throttle set 1000 1200 RPM 10 Check oil pressure rises within 10 sec 11 Check OIL PRESSURE LOW extinguished 12 Electric fuel pump OFF 13 Check fuel...

Page 89: ...ey START 7 Mixture rapidly to FULL RICH 8 Throttle set 1000 1200 RPM 9 Check oil pressure rises within 10 sec 10 Electric fuel pump OFF 11 Check fuel pressure within limits 12 Generator switch ON 13 Voltmeter increase and check within green arc 14 ALT FAIL caution extinguished 15 Engine instruments check within green arc 16 Check G1000 for warning caution messages Avoid idling operations on the gr...

Page 90: ...ound or at high ambient temperatures the following indications of fuel vapor lock may appear Arbitrary changes in idle RPM and fuel flow Slow reaction of the engine to operation of throttle Engine will not run with throttle in IDLE position Solution 1 For about 1 to 2 minutes or until the engine settles run at a speed of 1800 to 2000 RPM Oil and cylinder head temperatures must stay within limits 2...

Page 91: ...ing of the engine or a loss of performance The mixture may be adjusted to obtain smooth engine operations 8 Throttle set 1500 RPM a Alternate Air check Alternate Air PULL Check drop 50 100 RPM b Mixture check Mixture reduce EGT check increase FF check decrease Mixture FULL RICH 9 Throttle 2100 RPM 10 Magneto Check L BOTH R BOTH Max RPM drop 175 RPM Max difference 50 RPM 11 Throttle Idle 12 Flaps c...

Page 92: ... mark 1 Pitot HEAT ON if required 2 Fuel pump ON 3 Brakes apply 4 Throttle FULL and check approximately 2100 100 RPM WARNING Engine proper performance at full throttle shall be checked early in the ground roll in order to abandon take off if necessary A rough engine sluggish RPM increase or failure to reach take off RPM are reasons for abandoning the take off If the engine oil is cold an oil press...

Page 93: ...ll Throttle prior to take off where airports are at 5000ft density altitude or higher During climb a rough method of correctly leaning is to slowly reduce mixture lever until an increase of appr ly 50 100 RPM is noticed at constant IAS or EGT reaches 1375 F mark 1 Flaps UP minimum speed 73KIAS Expect to adjust pitch trim pitch up when retracting flaps after take off 2 Establish climb Vy 82KIAS 3 E...

Page 94: ... Care should always be taken that the cylinders do not cool down too quickly The cooling rate should not exceed 50 F per minute For maximum service life cylinder head temperature should be kept below 475 F high performance cruise and below 435 F for economy cruise Best Cruise Economy Mixture The best economy mixture setting may only be used up to a power setting of 75 In order to obtain the lowest...

Page 95: ...ractice and avoid potential illumination of ALT FAIL due to low propeller speed the following best practice should be observed Reducing power to maintain a minimum descent speed of 82 KIAS best glide and or a blade angle to maintain 850 RPM Opening the ALTER AIR command to full open to avoid ice accretion CAUTION The maximum permissible cylinder head temperature 500 F must never be exceeded The mi...

Page 96: ...efore touching wheels down Taking into account local environmental constraints consider the possibility to adjust aiming point for a better touchdown point control CAUTION In conditions such as e g strong wind danger of windshear or turbulence a higher approach speed shall be selected 5 12 BALKED LANDING MISSED APPROACH 1 Throttle FULL 2 Speed keep over 80 KIAS climb to VY or VX as applicable 3 Fl...

Page 97: ...Strobe light OFF 9 Avionic Master OFF 10 Master Generator switches OFF 11 Fuel selector valve OFF WARNING For safety verify propeller is fully stopped before any other action CAUTION Instruct passenger to fully open RH door and depart avoiding contact with wheels and sharp wing control surfaces edges 5 16 POSTFLIGHT CHECKS 1 Flight controls lock by means of seat belts 2 Wheel chocks and wing moori...

Page 98: ...ff distance and maximum Horizontal speed The effect on flight characteristics is minimal 5 18 REFUELLING Before refuelling the airplane must be connected to electrical ground 5 19 FLIGHT AT HIGH ALTITUDE At high altitudes the provision of oxygen for the occupant is necessary Legal re quirements for the provision of oxygen should be adhered to see para 2 9 ...

Page 99: ...of Performance Charts 2 3 Airspeed Indicator System Calibration 3 4 ICAO Standard Atmosphere 5 5 Stall speed 6 6 Crosswind 7 7 Take Off performances 8 8 Take off Rate of Climb 11 9 En Route Rate of Climb 12 10 Cruise Performance 13 11 Landing performances 15 12 Balked Landing Performance 16 13 Noise Data 17 ...

Page 100: ...age 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 2 USE OF PERFORMANCE CHARTS Performances data are presented in tabular or graphical form to illustrate the effect of different variables su...

Page 101: ...as a function of indicated airspeed VCAS 50 60 70 80 90 100 110 120 130 140 150 160 170 50 60 70 80 90 100 110 120 130 140 150 160 Indicated Airspeed KIAS Calibrated Airspeed KCAS Airspeed Indication System Calibration Flap UP Flap T O Flap LN FIG 5 1 CALIBRATED VS INDICATED AIRSPEED Example Given Find KIAS 75 0 Flap UP KCAS 74 7 Indicated airspeed assumes 0 as an instrument error NOTE ...

Page 102: ...020 61 1020 70 72 1020 72 1020 71 1020 90 92 1020 91 1020 91 1020 FLAP UP 5000 70 72 5020 72 5020 71 5020 90 94 5030 93 5020 92 5020 110 114 5030 113 5020 112 5020 133 137 5040 136 5030 135 5020 FLAP T O 60 62 5010 62 5020 61 5010 70 74 5020 73 5020 72 5020 90 93 5030 93 5020 93 5020 FLAP LND 60 63 5030 62 5020 61 5000 70 72 5020 72 5010 71 5010 90 92 5020 92 5020 91 5010 FLAP UP 8000 70 72 8020 7...

Page 103: ...HERE 2nd Edition Rev 0 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 104: ...WEIGHT BANK ANGLE STALL SPEED FLAPS 0 FLAPS T O FLAPS FULL kg lb deg KIAS KCAS KIAS KCAS KIAS KCAS 1160 2557 FWD C G 0 59 60 53 55 50 52 15 60 61 54 56 51 53 30 64 65 58 59 54 56 45 71 71 64 65 61 62 60 85 85 77 78 73 74 Altitude loss during conventional stall recovery as demonstrated during flight tests is approximately 350 ft with banking below 15 NOTE ...

Page 105: ...OSSWIND 2nd Edition Rev 0 6 CROSSWIND Maximum demonstrated crosswind is 12 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 106: ...6 1365 At 50 ft AGL 442 1450 552 1811 678 2224 818 2684 626 2054 1000 Ground Roll 317 1040 399 1309 492 1614 597 1959 446 1463 At 50 ft AGL 481 1578 601 1972 737 2418 890 2920 670 2198 2000 Ground Roll 346 1135 436 1430 538 1765 652 2139 479 1572 At 50 ft AGL 523 1716 ft 655 2149 ft 803 2635 ft 969 3179 ft 718 2356 3000 Ground Roll 378 1240 476 1562 587 1926 712 2336 515 1690 At 50 ft AGL 570 1870...

Page 107: ...63 2175 507 1663 1000 Ground Roll 255 837 321 1053 397 1302 481 1578 359 1178 At 50 ft AGL 389 1276 487 1598 598 1962 721 2365 543 1781 2000 Ground Roll 279 915 351 1152 433 1421 525 1722 386 1266 At 50 ft AGL 424 1391 530 1739 651 2136 785 2575 582 1909 3000 Ground Roll 304 997 383 1257 473 1552 574 1883 414 1358 At 50 ft AGL 462 1516 578 1896 709 2326 856 2808 624 2047 4000 Ground Roll 333 1092 ...

Page 108: ...0 526 1726 402 1319 1000 Ground Roll 201 659 253 830 313 1027 379 1243 283 928 At 50 ft AGL 309 1014 387 1270 474 1555 572 1877 431 1414 2000 Ground Roll 220 722 277 909 341 1119 414 1358 304 997 At 50 ft AGL 337 1106 421 1381 516 1693 623 2044 462 1516 3000 Ground Roll 240 787 302 991 373 1224 452 1483 327 1073 At 50 ft AGL 367 1204 459 1506 563 1847 679 2228 495 1624 4000 Ground Roll 262 860 330...

Page 109: ... 531 365 216 482 6000 72 571 389 226 79 368 8000 72 427 247 87 57 253 10000 72 283 107 51 192 139 12000 72 139 34 188 327 25 14000 72 4 174 325 462 90 1060 2337 S L 72 1162 956 772 606 843 2000 72 1005 803 622 459 721 4000 72 849 650 472 312 598 6000 72 694 498 323 166 476 8000 72 539 346 175 20 353 10000 72 384 195 27 125 230 12000 72 230 45 121 270 108 14000 72 77 105 268 414 15 960 2116 S L 71 ...

Page 110: ...451 307 564 6000 82 649 474 317 176 454 8000 82 510 338 184 45 344 10000 82 372 202 51 85 234 12000 82 233 67 82 215 123 14000 82 95 68 213 345 13 1060 2337 S L 81 1222 1023 846 686 914 2000 81 1071 875 701 544 796 4000 81 920 728 557 402 678 6000 81 770 581 413 261 560 8000 81 620 435 270 120 441 10000 81 471 289 127 20 323 12000 81 323 144 16 159 205 14000 81 175 1 157 299 86 960 2116 S L 81 140...

Page 111: ...uel Consumption gal hr l hr Endurance hr mm Range nm Specific Range nm gal nm l 0 15 2700 137 16 6 62 7 3 40 502 8 3 2 2 2600 131 15 3 57 8 3 59 521 8 6 2 3 2500 125 14 1 53 4 4 18 538 8 8 2 3 2400 119 13 1 49 4 4 39 553 9 1 2 4 2200 107 11 3 42 8 5 22 573 9 4 2 5 2000 11 2700 136 15 9 60 1 3 50 521 8 6 2 3 2600 130 14 7 55 6 4 08 538 8 9 2 3 2500 124 13 6 51 5 4 28 554 9 1 2 4 2400 118 12 6 47 9 ...

Page 112: ... hr l hr Endurance hr mm Range nm Specific Range nm gal nm l 6000 3 2600 128 13 6 51 6 4 27 573 9 4 2 5 2500 122 12 7 48 2 4 47 585 9 6 2 5 2400 116 11 9 45 1 5 06 594 9 8 2 6 2200 104 10 6 40 1 5 44 598 9 8 2 6 8000 1 2600 128 13 2 49 9 4 37 588 9 7 2 6 2500 122 12 3 46 7 4 55 598 9 8 2 6 2400 116 11 6 44 0 5 14 605 9 9 2 6 2200 104 10 4 39 5 5 49 603 9 9 2 6 10000 5 2600 127 12 8 48 3 4 46 603 9...

Page 113: ...37 778 At 50 ft AGL 488 1601 509 1670 529 1736 550 1804 521 1709 1000 Ground Roll 212 696 233 764 254 833 276 906 244 801 At 50 ft AGL 496 1627 517 1696 538 1765 560 1837 528 1732 2000 Ground Roll 220 722 242 794 264 866 286 938 251 823 At 50 ft AGL 504 1654 526 1726 548 1798 570 1870 535 1755 3000 Ground Roll 228 748 251 823 274 899 297 974 259 850 At 50 ft AGL 512 1680 535 1755 558 1831 581 1906...

Page 114: ...6 3 6 7 1000 10 4 7 5 4 9 2 6 6 1 2000 9 3 6 4 3 9 1 6 5 3 3000 8 2 5 3 2 8 0 5 4 4 4000 7 1 4 3 1 8 0 5 3 5 5000 6 3 2 0 7 1 5 2 7 6000 4 9 2 1 0 3 2 6 1 8 7000 3 8 1 1 1 4 3 6 0 9 1060 2337 S L 13 6 10 4 7 6 5 8 7 1000 12 4 9 2 6 4 3 9 7 7 2000 11 2 8 5 3 2 7 6 8 3000 10 6 9 4 1 1 6 5 8 4000 8 8 5 7 2 9 0 5 4 9 5000 7 6 4 5 1 8 0 7 3 9 6000 6 4 3 3 0 6 1 8 3 7000 5 2 2 2 0 5 2 9 2 960 2116 S L 1...

Page 115: ...n accordance with ICAO Annex 16 6th Ed July 2011 Vol I Chapter 10 and 14 CFR Part 36 is 77 576 dB A NOTE No determination has been made by the Federal Aviation Administration that the noise levels of this aircraft are or should be acceptable or unacceptable for operation at into or out of any airport ...

Page 116: ...Page 5 18 Section 5 Performances 2nd Edition Rev 0 INTENTIONALLY LEFT BLANK ...

Page 117: ... INTRODUCTION 3 2 WEIGHING PROCEDURES 4 2 1 Preparation 4 2 2 Levelling 4 2 3 Weighing 4 2 4 Determination of C G location 4 2 5 Weighing record 5 2 6 Weighing record II 6 3 WEIGHTS AND C G 7 3 1 C G CALCULATION SAMPLES 8 3 1 1 FULL FUEL 8 3 1 2 FULL PAYLOAD 8 4 BAGGAGE LOADING 9 5 EQUIPMENT LIST 11 ...

Page 118: ...Page 6 2 Section 6 Weight and Balance 2nd Edition Rev 0 INTENTIONALLY LEFT BLANK ...

Page 119: ... aircraft Loading procedure information is also provided Aircraft must be operated in accordance with the limits con cerning the maximum takeoff 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 120: ...NG Level the aircraft the reference for longitudinal levelling is made putting a spirit level on the cabin floor as shown in the Aircraft Maintenance Manual Adjust longitudinal attitude deflating nose tire 2 3 WEIGHING Record weight shown on each scale Repeat weighing procedure three times Calculate empty weight 2 4 DETERMINATION OF C G LOCATION Drop a plumb bob tangent to the wing leading edge an...

Page 121: ...Nose wheel weight W1 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 Plumb bob distance from nose wheel B Empty weight We W1 W2 kg or lbs We B W A W D 13 13 1 2 m or ft 100 378 1 D D Empty weight moment M D We m kg or ft lbs Maximum takeoff weight WT kg or lbs Empty weight We kg or lbs Max useful load WT We Wu ...

Page 122: ...t Nose wheel weight W1 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 Plumb bob distance from nose wheel B Empty weight We W1 W2 kg or lbs We B W A W D 13 13 1 2 m or ft 100 378 1 D D Empty weight moment M D We m kg or ft lbs Maximum takeoff weight WT kg or lbs Empty weight We kg or lbs Max useful load WT We W...

Page 123: ...ed by means of the chart below The pilot is responsible for ensuring the correct useful load loading Figure 1 Example A C empty mass moment 188 kg m 1360 lb ft A C empty mass 765 kg 1687 lb Occ front seats 160 kg 353 lb Occ rear seats 140 kg 309 lb Fuel 75 kg 165 lb Baggage 20 kg 44 lb A C T O weight 1160 kg 2557 lb ...

Page 124: ...Useful load 253 558 lb 460 1 5 ft 116394 837 lb ft WTO 1028 2266 lb 347 1 14 ft 356219 2583 lb ft CoG pos 26 1 3 1 2 FULL PAYLOAD kg Arm mm Moment kg mm Empty weight 775 1708 lb 309 1 01 ft 239475 1726 lb ft CoG pos 23 4 USEFUL LOAD Pilot 80 176 lb 133 0 44 ft 10640 77 lb ft Pilot 80 176 lb 133 0 44 ft 10640 77 lb ft PAX 80 176 lb 1057 3 47 ft 84560 278 lb ft PAX 80 176 lb 1057 3 47 ft 84560 278 l...

Page 125: ... accord ance with diagram addressed on PAR 03 and with C G excursion and weight lim itations reported in Section 2 Pilot is provided with a red tie down net and snap fasteners allowing for securing the loads on the compartment floor CAUTION Loading the baggage make sure that you correctly stretched the net which must be secured to the four vertices of the floor ...

Page 126: ...Page 6 10 Section 6 Weight and Balance 2nd Edition Rev 0 INTENTIONALLY LEFT BLANK ...

Page 127: ...pment which may be installed in the P2010 The items marked with an X were installed on the airplane described at the be ginning of the list and they are included in the Basic Empty Weight It is the owner s responsibility to retain this equipment list and amend it to reflect changes in equipment installed in this airplane ...

Page 128: ... 0 69 A12 JP Instruments EDM 930 790000 c XXX 1 36 0 69 A13 Remote Alarm Display RAD 790749 0 1 0 69 A14 Rudder trim indicator N0911R0L2R000W 0 1 0 69 AVIONICS MISCELLANEOUS B1 ELT ACK E 04 0 73 1 61 1 61 5 28 ELT Kannad 406 AF 1 10 2 42 1 61 5 28 B2 Front seats GEVEN E5 01 009 T03 LH E5 01 010 T03 RH 10x2 20 22x2 44 0 50 1 64 B3 Rear seats GEVEN E5 01 009 T03 LH E5 01 010 T03 RH 10x2 20 22x2 44 1...

Page 129: ...ing Taxy Light WHELEN Mod 7167400 01 0771674 00 2 4 4 1 52 4 99 PITOT STATIC B14 Pitot Heated Falcon Gauge 24 AN5812 1 3 6 6 0 5 1 64 Garmin Gap26 Pitot Tubes 26 9 8032 000 3 6 6 0 5 1 64 GARMIN GFC700 Autopilot B15 Servo pitch GSA 80 011 00877 20 1 44 5 3 B16 Servo roll GSA 80 011 00877 20 1 44 2 05 B17 Servo pitch trim GSA 81 011 00878 20 1 03 5 3 LANDING GEAR ACCESSORIES C1 Nose Landing Gear Wh...

Page 130: ...Page 6 14 Section 6 Weight and Balance 2nd Edition Rev 0 INTENTIONALLY LEFT BLANK ...

Page 131: ...ar 7 3 FLIGHT CONTROLS 8 4 INSTRUMENT PANEL 9 4 1 Engine control lever 10 4 2 Alternate Air 11 4 3 Defrost and Cabin Heat 11 5 SEATS AND SAFETY HARNESS 13 6 DOORS 14 7 POWERPLANT 16 7 1 ENGINE 16 7 2 PROPELLER 16 8 FUEL SYSTEM 18 9 ELECTRICAL SYSTEM 20 9 1 Stall Warning System 21 9 2 Avionics 22 9 3 External Power Supply 23 10 PITOT STATIC PRESSURE SYSTEMS 24 11 LIGHTS 26 11 1 External lights 26 1...

Page 132: ...ght alloy torsion box a light alloy lead ing edge is attached to the front spar whereas the flap slotted and the aileron frise are attached to a rear spar through two hinges each The torsion box consists of a front and rear spar that represent its front and rear vertical walls a series of ribs and wrap around panels complete the structure Front and rear spars are integrated with wing fuselage atta...

Page 133: ... Fuselage and vertical fin are thus a unique body 2 3 EMPENNAGES 2 3 1 HORIZONTAL TAIL The horizontal tail is an all moving type the stabilizer and elevator form a single uniform plane called stabilator that rotates to the desired pitch setting The stabilator structure see Figure 7 2 is made up by two aluminium spar and ribs Aluminium skin panels are riveted to the above elements A trim tab provid...

Page 134: ... and ribs 2 Aluminium skin panels 3 are riveted to the above elements It is connected to the fin through two hing es at the lower hinge a bellcrank 4 is connected for the movement transmission A trim tab 5 provides stick force adjustment and lateral compensation through a rocker switch located between pilot and co pilot seats Fig 7 3 RUDDER STRUCTURE 1 3 2 4 5 ...

Page 135: ...an independent hydraulically actuated brake system for each main wheel A master cylinder is attached to each pilot s rudder pedal Hydraulic pressure ap plied via the master cylinders enters the brake via lines connected to an inlet fitting on the caliper A parking brake valve mounted in correspondence of the cabin floor and operated by a knob on the cockpit central pedestal intercepts the hydrauli...

Page 136: ...stems description AIRFRAME 2nd Edition Rev 0 Left wheel brake Right wheel brake Left wheel brake Right wheel brake Fig 7 5 RUDDER PEDALS AND BRAKE MASTER CYLINDERS PILOT AND CO PILOT SIDE Fig 7 6 BRAKE SYSTEM SCHEMATIC Master Cylinders ...

Page 137: ...g nose gear is attached to the firewall reinforcement plate The shock absorber is fitted on the upper machined component and directly on the nose landing gear structure In Figure 10 is shown 1 Hydraulic shock absorber 2 Firewall 3 Nose wheel 5 00 5 tire inflated at 32 PSI 2 2 BAR Fig 7 7 NOSE LANDING GEAR 1 2 3 ...

Page 138: ...a switch on the instrument panel Flaps act in continuous mode the indicator displays three markings related to 0 takeoff T O and landing FULL positions A breaker positioned on the right side of the instrument panel protects the electric circuit The control of the stabilator trim is operated by means of a control wheel located between the two front seats that acts directly on the control cables Sta...

Page 139: ...l area holds the standby unit for PFI parameters MD 302 suite and the ELT button The right area holds Garmin G1000 MFD and breaker panel The lower LH portion of the instrument panel holds Ignition key Master and Generator switches Emergency fuel pump Avionic Master switch The lower Central portion of the instrument panel holds Fuel selector valve Flap Control The lower RH portion of the instrument...

Page 140: ...pplied to the engine which at higher performance setting contributes to engine cooling In cruise the mixture should be made leaner in order to reach the appropriate fuel air mixture The leaning procedure is given in Chapter 4 Lever forward RICH Mixture rich in fuel Lever to rear LEAN Mixture lean in fuel To shut off the engine the mixture control lever is pulled to the rear stop air without fuel i...

Page 141: ...al operation the knob is set in OFF position 4 3 DEFROST AND CABIN HEAT Two knobs located on the lower side of the central pedestal allow Defrost and Cabin Heat function The one marked as Defrost and Cabin Heat allows hot air to perform windshield defrost and partially cabin heat The cabin heat control knob when fully outward allows cabin to receive maximum hot air When both cabin heat and defrost...

Page 142: ...Page 7 12 Section 7 Airframe and Systems description 2nd Edition Rev 0 INTENTIONALLY LEFT BLANK ...

Page 143: ...ia the sliding buckle located on the belt metal hook Seats are built with light allow tube structure and synthetic material cushioning It is possible to perform following seat adjustments Horizontal pulling the lower front lever and sliding the seat Vertical operating the lever located on the outward seat side Seat back inclination unlocking it via the lateral knob These adjustments ensure the cre...

Page 144: ... as an emergency exit On the right side of the cabin is located an additional door which gives access to the baggage compartment Baggage door can be opened from the inside of the cabin where near the rear RH seat a dedicated knob is located Fig 7 11 DOORS AND BAGGAGE DOOR OPENING NOTE opening of baggage compartment is only provided inside the cockpit Occu pants of rear seat shall be briefed in ord...

Page 145: ...f a hook located nearby the handle itself and upper safety block following pictures show the functioning Fig 7 12 HANDLE LOCKING In case of rapid escapes or door handles malfunction an emergency opening is provided on the rear side of the door The opening is operated by means of a hook moved forward that bypasses the normal door opening Fig 7 13 EMERGENCY OPENING ...

Page 146: ...ets Maximum power Maximum continuous power 134 0 kW 180hp 2700 rpm 134 0 kW 180hp 2700 rpm Oil Consumption Operation RPM HP Max Oil Cons Qts Hr Max Cyl Head Temp Normal Rated 2700 180 80 500 F 260 C Performance Cruise 75 2450 135 45 500 F 260 C Economy Cruise 60R Rated 2350 117 39 500 F 260 C 7 2 PROPELLER Manufacturer MT Propeller Model MT 188 R 145 4G Type Certificate EASA TCDS no P 006 Blades h...

Page 147: ...2nd Edition Rev 0 Section 7 Airframe and Systems description Page 7 17 INTENTIONALLY LEFT BLANK ...

Page 148: ...ox The capacity of each tank is 120 liters 31 7 gal total capacity is thus 240 liters 63 4 gal The internal side of fuel tank is accessible for inspection through 4 upper dedicat ed caps Two bottom inspection panels allow the inspection of vent line and tank structure An anti sloshing movable wall is located within each fuel tank this prevents fuel centrifugation which is a possible cause of undes...

Page 149: ...Page 7 19 2nd Edition Rev 0 Section 7 Airframe and Systems description INTENTIONALLY LEFT BLANK ...

Page 150: ...y sources is automatic and no action is required in order to activate the alternate energy source For ground maintenance and or starting an external power socket is provided The alternator and battery are connected to the battery bus in order to provide en ergy for the electric equipment Each electrically fed instrument is connected to a dedicated circuit breaker which protects the cable from the ...

Page 151: ...ption ELECTRICAL SYSTEM FIG 7 15 ELECTRICAL SYSTEM ARCHITECTURE 9 1 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 warning horn located near the in strument panel ...

Page 152: ...FD failure the reversionary mode is automatically enabled In the event of a failure of the automatic reversion logic the pilot can force rever sionary mode by pressing reversionary mode button marked in red and located on the audio panel When reversionary mode is activated primary flight and engine information are presented together on the remaining display In order to provide the pilot with main ...

Page 153: ...of ground external power CAUTION Exercise caution while applying external power Exercise extreme caution while disconnecting external power with engine running due to airflow coming from the propeller Approach the power supply receptacle from rear of the wing Make a positive check upon disconnection that the power chord is free from any aircraft structure the receptacle is firmly closed Follow thi...

Page 154: ...n correspondence of engine firewall on left and right side of fuselage Flexible hoses connects total pressure and static ports to primary analogue instru ments anemometer and altimeter Garmin G1000 suite and standby MD 302 unit are connected to both static and total pressure lines providing both air speed and altitude information GARMIN G1000 LH STATIC PORT RH STATIC PORT T JOINT MD 302 ALTERNATE ...

Page 155: ...Page 7 25 2nd Edition Rev 0 Section 7 Airframe and Systems description INTENTIONALLY LEFT BLANK ...

Page 156: ...llowing external lights 2 combined LED NAV POS Strobe integrated lights located on RH and LH wing 1 POS strobe combined light located on the rear fixed on the rudder 1 combined LED landing and taxi light located on the lower engine cowling The following schematic shows the configuration layout for external lights FIG 7 17 EXTERNAL LIGHTS ...

Page 157: ...ar area passengers In the central area of the cabin ceiling is located a spot light used to illuminate the pedestal during night flight operations All ceiling lights are dimmable by a dedicat ed dimmer FIG 7 18 CABIN CEILING LIGHTS LAYOUT The instrument panel can be illuminated by 8 incandescence light strips all dimma ble FIG 7 19 INSTRUMENT PANEL LIGHTS LAYOUT FWD From mid MAP light ceiling ...

Page 158: ... placards are installed on the aircraft Additionally nearby the placards listed below English lan guage directly translated placards in the language of the country in which the airplane is registered can be installed when required by the specific NAA 12 1 EXTERNAL PLACARDS Aircraft Registration Placard External Power Socket and baggage compartment placards NOTE ...

Page 159: ...Page 7 29 2nd Edition Rev 0 Section 7 Airframe and Systems description PLACARDS Static Ports Lift Point Wheel Fairing No Step ...

Page 160: ...Page 7 30 2nd Edition Rev 0 Section 7 Airframe and Systems description PLACARDS Allowed Fuel Placard Tire Pressure placard Stabilator degrees placard ...

Page 161: ...Page 7 31 2nd Edition Rev 0 Section 7 Airframe and Systems description PLACARDS Emergency exit placards ...

Page 162: ...Page 7 32 2nd Edition Rev 0 Section 7 Airframe and Systems description PLACARDS 12 2 INTERNAL PLACARDS Safety equipment placards ...

Page 163: ...Page 7 33 2nd Edition Rev 0 Section 7 Airframe and Systems description PLACARDS ELT unit position placard Breaker Panel placards ...

Page 164: ...Page 7 34 2nd Edition Rev 0 Section 7 Airframe and Systems description PLACARDS Magnetic Compass placard Battery Placard ...

Page 165: ...Page 7 35 2nd Edition Rev 0 Section 7 Airframe and Systems description PLACARDS Oil Filler placard Emergency exit placards ...

Page 166: ...Page 7 36 2nd Edition Rev 0 Section 7 Airframe and Systems description PLACARDS Pedestal placards ...

Page 167: ...on 7 Airframe and Systems description PLACARDS Fuel selector valve and Flap control knob Baggage Door opening knob Oil brake reservoir placard A Oil brake reservoir placard B Oil brake reservoir placard if MOD2010 020 is installed A B ...

Page 168: ...Page 7 38 2nd Edition Rev 0 Section 7 Airframe and Systems description INTENTIONALLY LEFT BLANK ...

Page 169: ... Refuelling 7 4 2 Engine and Brakes Oil level control 7 4 3 Landing gear tires pressure control 9 5 Engine Cowling Check 10 5 1 Upper cowling 10 5 2 Lower Cowling 10 6 Ground Handling 11 6 1 Towing 11 6 2 Parking and Tie Down 11 6 3 Mooring 13 6 4 Jacking 14 6 5 Road Transport 14 7 Cleaning And Care 15 7 1 Windows 15 7 2 External surfaces 15 7 3 Propeller 15 7 4 Engine 15 7 5 Internal surfaces 15 ...

Page 170: ...Page 8 2 Section 8 Aircraft Care and Maintenance 2nd Edition Rev 0 INTENTIONALLY LEFT BLANK ...

Page 171: ...ins factory recommended procedures for proper ground han dling and routine care and servicing It also identifies certain inspection and maintenance requirements It is recommended to follow a planned schedule of lubrication and preventive maintenance based on climatic and flying conditions encountered locally ...

Page 172: ...Page 8 4 Section 8 GROUND HANDLING SERVICE 2nd Edition Rev 0 INTENTIONALLY LEFT BLANK ...

Page 173: ...s an annual inspection has to be performed All required inspections are reported in the Aircraft Maintenance Manual As far as the scheduled unscheduled engine maintenance is concerned refer to the engine manufacturer Maintenance Manual CAUTION Unscheduled inspections maintenance tasks are necessary when one or more of following conditions occur 1 Emergency landing 2 Breaking damage of propeller or...

Page 174: ...OUND HANDLING SERVICE AIRCRAFT CHANGES OR REPAIRS 2nd Edition Rev 0 3 AIRCRAFT CHANGES OR REPAIRS Aircraft changes or repairs must be performed in accordance with Aircraft Maintenance Manual and Job cards provided by TECNAM ...

Page 175: ...lling Do not operate switches and or pushbuttons inside the aircraft dur ing refuelling operation make sure that crew left the aircraft be fore performing refuelling Make sure that the aircraft is electrically connected to the ground 4 2 ENGINE AND BRAKES OIL LEVEL CONTROL 1 Open the engine cowling RH 2 Clean the dipstick and soak it in the reservoir 3 Remove dipstick and read oil level 4 If requi...

Page 176: ...age 8 8 Section 8 GROUND HANDLING SERVICE MAINTENANCE 2nd Edition Rev 0 FIG 8 1 BIS OIL CHECK A Oil brake reservoir placard B Oil brake reservoir placard if MOD2010 020 is installed LH Engine Cowling A B ...

Page 177: ... CONTROL For each wheel proceed as follows 1 Remove wheel fairing 2 Unscrew the tire cap 3 Connect a gauge 4 Read the pressure value 5 If required rectify the pressure nose tire 2 2 Bar 32 psi main landing gear tires 2 5 Bar 36 psi 6 Fit the tire cap 7 Install wheel fairing FIG 8 2 TIRE PRESSURE PLACARDS ...

Page 178: ...se reference pins 8 Secure latches by applying light pressure check for proper assembly and fasten Cam locks WARNING Butterfly Cam locks are locked when tabs are horizontal and open when tabs are vertical Verify tab is below latch upon closing 5 2LOWER COWLING 1 After disassembling upper cowling move the propeller to a horizontal position 2 Using a standard screwdriver press and rotate 90 the two ...

Page 179: ...rvicing without regard to prevailing winds Ensure that it is sufficiently protected against adverse weather conditions and present no danger to other aircraft Procedure 1 Position airplane on levelled surface headed into the prevailing wind if prac tical 2 Engage parking brake 3 Secure pilot control wheel by wrapping the seat belt around it Do not engage the parking brakes at low ambient temperatu...

Page 180: ...Page 8 12 Section 8 GROUND HANDLING SERVICE 2nd Edition Rev 0 INTENTIONALLY LEFT BLANK ...

Page 181: ...nt temperature when an accumulation of moisture may cause the brakes to freeze or when they become hot from severe use In these cases use wheel chocks 3 Secure pilot control stick by wrapping the seat belt around it 4 Assure that flaps are retracted 5 Electrically ground airplane by connecting ground cable to the engine muffle 6 Install control locks 7 Install protective plugs 8 Close and lock cab...

Page 182: ...tenance Manual 6 5ROAD TRANSPORT It is recommended to secure tightly all aircraft components onto the cart to avoid damage during transport Minimum cart size is 9x4 meters It is suggested to place wings under the aircraft s bottom secured by specific clamps Secondary components like the stabilator shall be protected from accidental hits using plas tic or other material For correct rigging and de r...

Page 183: ...the aircraft in the hangar 7 3 PROPELLER To preserve its functionality avoiding wear and corrosion the propeller manufac turer uses for external surface painting an acrylic paint which is resistant to all solvents In any case it is advisable to clean the propeller using exclusively soapy water 7 4 ENGINE Engine cleaning is part of the scheduled maintenance Refer to the engine manu facturer Mainten...

Page 184: ... Section8 Aircraft Care and Maintenance ICE REMOVAL 2nd Edition Rev 0 8 ICE REMOVAL Anti icing products are not allowed To remove ice tow the aircraft in the hangar and operate with a soft brush or a humid cloth ...

Page 185: ...Page 9 1 Section 9 AFM Supplements INDEX 2nd Edition Rev 0 SECTION 9 AFM SUPPLEMENTS INDEX INDEX 1 1 Introduction 2 2 Supplements list 3 ...

Page 186: ...dition Rev 0 1 INTRODUCTION This Section concerns the supplemental manuals of additional or optional instrumen tation equipping the P2010 and or information and limitations related to installed equipment configuration or needed to fit local national rules ...

Page 187: ...NO D01 GARMIN GFC700 Autopilot Ed1rev2 25 11 16 D02 Variable Pitch Propeller Ed2rev2 25 11 16 D03 Alternative avionic configuration Ed1rev2 25 11 16 D04 Automotive Fuel Ed1rev0 18 01 16 D05 Argentine AFMS Ed1rev0 30 10 15 D06 Reserved D07 GFC700 Autopilot for Variable Pitch Propeller equipped aeroplanes Ed1rev2 25 11 16 D08 Alternative avionics configuration for variable pitch propeller equipped a...

Page 188: ...Page 9 4 Section 9 AFM Supplements 2nd Edition Rev 0 INTENTIONALLY LEFT BLANK ...

Page 189: ... Amended to add the wording Approved in order to better identify the pages approved ac cording to EASA regulation D Ronca C Caruso M Oliva Approved under the au thority of DOA ref EASA 21J 335 Approval No MOD2010 070 160118 2 6A 11 thru 12 Pages removed D Ronca C Caruso M Oliva Approved under the au thority of DOA ref EASA 21J 335 Approval No MOD2010 103 161026 List of Effective Pages Page Revisio...

Page 190: ...GATION ELIGIBILITY Ed 1 Rev 0 INDEX INDEX 2 INTRODUCTION 3 Section 1 GENERAL 5 Section 2 LIMITATIONS 8 Section 3 EMERGENCY PROCEDURES 11 Section 4 NORMAL PROCEDURES 14 Section 5 PERFORMANCE 16 Section 6 WEIGHT AND BALANCE 18 Section 7 AIRFRAME AND SYSTEMS DESCRIPTION 20 Section 8 GROUND HANDLING SERVICE 22 ...

Page 191: ...ev 0 INTRODUCTION This section contains supplemental information to operate in a safe and efficient manner the aircraft when equipped with Garmin GFC 700 autopilot device inter facing Garmin G1000 It is the owner s responsibility to replace the mentioned pages in accordance with the instructions herein addressed section by section ...

Page 192: ...Page D01 4 Section 9 Supplements Supplement no D01 GARMIN GFC700 AUTOPILOT INSTALLATION AND RNAV RNP NAVIGATION ELIGIBILITY Ed 1 Rev 0 INTENTIONALLY LEFT BLANK ...

Page 193: ... GENERAL Make sure you first applied instructions reported on the basic AFM Section 1 General According to A C configuration apply following pages replacement Supplement D01 GENERAL page AFM Section 1 page 1A 13 REPLACES 1 13 of basic AFM Section 1 1A 16 thru 31 REPLACES 1 16 of basic AFM Section 1 Supplement D01 pages replacement instructions ...

Page 194: ...Page D01 6 Section 9 Supplements Supplement no D01 GARMIN GFC700 AUTOPILOT INSTALLATION AND RNAV RNP NAVIGATION ELIGIBILITY Ed 1 Rev 0 INTENTIONALLY LEFT BLANK ...

Page 195: ...ot LRU Line Repleaceable Unit APR Approach LVL Level ARP Aerospace Recommended Practice MAG Magnetometer ASI Air Speed Indicator MET Manual Electric Trim BC Back Course MFD Multi Function Display CAS Caution Advisory System NAV Navigation CDI Course Deviation Indicator OAT Outside Air Temperature CS Certification Specifications PFD Primary Flight Display CWS Control Wheel steering PFI Primary Flig...

Page 196: ...FD The installed MFD display is different with respect to standard P2010 con figuration since it is GDU 1044 The autopilot suite installed on P2010 is based on the following configuration 1 Roll servo 1 Pitch servo 1 Pitch Trim servo Neither yaw axis nor rudder trim tab control is provided The autopilot is connected to electric system through the below listed circuit breakers connected to the avio...

Page 197: ...RINC 429 ARINC 429 REVERSIONARY SWITCH REVERSIONARY SWITCH RS 232 RS 232 RS 232 DME ADF HSDB MD 302 STAND BY INSTR STATIC PRESSURE PORT TOTAL PRESSURE PORT STATIC PRESSURE TOTAL PRESSURE HSDB ROLL SERVO PITCH SERVO PITCH TRIM SERVO RS 485 RS 485 The multifunction display MFD provides the pilot with a dedicated set of keys for autopilot control see red frame in the below picture The roll servo is l...

Page 198: ...ector command bars PFD NORMAL MFD REVER SIONARY Attitude Heading information Air data information Navigational database Parameters GPS WAAS VOR and ILS naviga tional data Mode logic flight director computa tions and servo management Autopilot computations and monitor ing Aircraft control surface Actuation Trim functionality In control of the roll axis the autopilot senses turn rate as well as clos...

Page 199: ...ond figure below It is the user interface for P2010 avionics suite GDU 1044 unit replaces the GDU 1040 unit on instrument panel RH side MFD GDU 1044 MFD Reversionary mode In the event of a single display failure the system is able to automatically switch the critical information including flight and engine parameters on the remaining display presenting them in a compact view In the event of a fail...

Page 200: ...ages the autopilot 2 FD Key Activates deactivates the flight director only 3 NAV Key Selects deselects Navigation Mode 4 ALT Key Selects deselects Altitude Hold Mode 5 VS Key Selects deselects Vertical Speed Mode 6 FLC Key Selects deselects Flight Level Change Mode 7 HDG Key Selects deselects Heading Select Mode 8 APR Key Selects deselects Approach Mode 9 VNV Key Selects deselects Vertical Path Tr...

Page 201: ...sed to disengage the autopilot and to acknowledge an autopilot dis connect alert and mute the associated aural tone Manual trim commands are generated only when both sides of the switch are operated simultaneously If either side of the switch is ac tive separately for more than three seconds MET function is disabled and PTRM is displayed as the AFCS Status Annun ciation on the PFD The function rem...

Page 202: ...STALLATION AND RNAV RNP NAVIGATION ELIGIBILITY Page 1A 22 Section 1 General AUTOPILOT DESCRIPTION Ed 1 Rev 0 The above mentioned AFCS controls are depicted in the below figures where 1 PTT switch 2 AP DISC Switch 3 AP Trim Switch 4 CWS Button ...

Page 203: ...AFMS N D01 FOR GARMIN GFC700 AUTOPILOT INSTALLATION AND RNAV RNP NAVIGATION ELIGIBILITY Page 1A 23 Section 1 General AUTOPILOT DESCRIPTION Ed 1 Rev 0 ...

Page 204: ...opilot operation occurs within the pitch roll and pitch trim servo and provides servo monitoring and automatic flight control in response to flight director steering commands AHRS attitude and rate information and air speed Manual Electric Trim MET The pitch trim servo provides manual electric trim capability when the autopilot is not engaged ESP Electronic Stability Protection keeps the aircraft ...

Page 205: ...the aircraft s autopilot system although it uses the same control servos so it basically operates in back ground whenever the pilot is hand flying the airplane The ESP feature will only function with GPS available A P MASTER SWITCH ON but autopilot not engaged and aircraft above 200ft AGL ESP enabling As a standard ESP will automatically set to enable at power up The system is configured in order ...

Page 206: ...FD by the advisory ESP not available on alert window ESP will turn OFF upon loss of both GPS The ADVSY ESP OFF will appear on the alert window in case of loss of both GPS 13 1 1 PITCH MODE Pitch attitude boundaries are set based on P2010 aircraft performances Since pitch ESP augments the natural aircraft longitudinal stability no special simbolo gy is required Value that have been set up for the P...

Page 207: ...pper disengagement limit specified in the certification gain file ESP will be disabled 13 1 2 ROLL MODE Roll mode is similar to pitch mode and also utilizes configurable gain file parame ters to define engagement and disengagement limits as well as the speed and torque curves The engagement and disengagement attitude limits are displayed with double hash marks on the roll indicator when ESP is ava...

Page 208: ...ircraft operation below minimum established airspeeds Pilot will be warned of impending low speed conditions and if no action will be taken FD will directly react in a way that allows the A P to remain engaged but prevents the airplane from stalling WARNING USP function has been developed in order to warn pilot of impending low speed conditions and if no action will be taken FD will directly react...

Page 209: ... PIT or VS turning green on the annunciation panel CAUTION USP engagement is a consequence of autopilot failing to properly moni toring A P and aircraft behaviour This is mainly caused by a pilot re quest that cannot be fulfilled due to lack of power coupled with unattain able pitch input Pilot need to continuously monitor autopilot performance while checking that mode selections are compatible wi...

Page 210: ...d and the autopilot will provide input causing the aircraft to pitch down and the wings to level The aural AIRSPEED alert will sound every five seconds If aircraft is unintentionally decelerated to 65 KIAS a MINSPD annunciation posts above the airspeed tape on PFD in alternating amber and black text A red UNDERSPEED PROTECT ACTIVE annunciation will appear to the right of the vertical speed indicat...

Page 211: ... 65 Kts for P2010 a red UNDERSPEED PROTECT AC TIVE annunciation appear to the right of the vertical speed indicator Vertical flight director mode will change from active to armed Flight Director and autopilot will command the aircraft to pitch down until reaching a pitch atti tude at which IAS equals at least the minimum commandable autopilot airspeed avoiding the development of a stall condition ...

Page 212: ...Page D01 7 Section 9 Supplements Supplement no D01 GARMIN GFC700 AUTOPILOT INSTALLATION AND RNAV RNP NAVIGATION ELIGIBILITY Ed 1 Rev 0 INTENTIONALLY LEFT BLANK ...

Page 213: ...ATIONS Make sure you first applied instructions reported on the basic AFM Section 2 Limitations According to A C configuration apply following pages replacement Supplement D01 LIMITATIONS page AFM Section 2 page 2A 15 REPLACES 2 15 of basic AFM Section 2 2A 17 thru 20 REPLACES 2 17 of basic AFM Section 2 Supplement D01 pages replacement instructions ...

Page 214: ...Page D01 9 Section 9 Supplements Supplement no D01 GARMIN GFC700 AUTOPILOT INSTALLATION AND RNAV RNP NAVIGATION ELIGIBILITY Ed 1 Rev 0 INTENTIONALLY LEFT BLANK ...

Page 215: ...on the left it is placed the following placard reporting the speed limitations 19 2 OPERATING LIMITATIONS On the central side of the instrument panel the following placard is placed re minding the observance of aircraft operating limitations according to installed equipment configuration see KOEL paragraph 18 When the Autopilot is installed next placard is added on the instrument panel to the righ...

Page 216: ...0 ft AGL 61 m During Autopilot operation a pilot with seat belt fastened must be seated at the left pilot position Maximum speed for Autopilot operation is 150 KIAS Do not use autopilot for airspeed below 70 KIAS Minimum approach speed is 70 KIAS The autopilot must be OFF during takeoff and landing Minimum altitude AGL for Autopilot operation is b Cruise and Descent 800 ft 244 m AGL c Climb after ...

Page 217: ... ICAO Annex 10 for IFR en route terminal area precision and non precision approach operations The G1000 System meets the requirements for GPS GNSS as a Primary Means of Navigation for Oceanic Remote Operations RNP 10 per AC 20 138C FAA No tice N8110 60 FAA Order 8400 12C and FAA Order 8700 1 Both GPS GNSS receivers are required to be operating and receiving usable signals except for routes requiri...

Page 218: ...ion Pilots and opera tors can view navigation data base alerts at www Garmin com In the Air Nav Data Alerts For flight planning purposes in areas where SBAS coverage is not available the pilot must check RAIM availability Within Europe RAIM availability can be determined using the G1000 WFDE Prediction program or Europe s AUGER GPS RAIM Prediction Tool at http augur ecacnav com augur app home This...

Page 219: ...Navigation database Pilots planning on flying an RNAV instrument approach must ensure that the Navigation database contains the planned RNAV Instrument Approach Procedure and that approach procedure must be loaded from the Navigation database into the FMS flight plan by its name The navigation equipment required to join and fly an instrument approach proce dure is indicated by the title of the pro...

Page 220: ...Page D01 10 Ed 1 Rev 0 Section 9 Supplements Supplement no D01 GARMIN GFC700 AUTOPILOT INSTALLATION AND RNAV RNP NAVIGATION ELIGIBILITY INTENTIONALLY LEFT BLANK ...

Page 221: ...GENCY PROCEDURES Make sure you first applied instructions reported on the basic AFM Section 3 Emergency Procedures According to A C configuration apply following pages replacement Supplement D01 EMERGENCY PROCEDURES page AFM Section 3 page 3A 31 thru 35 REPLACES Added at the end of Section 3 of basic AFM Supplement D01 pages replacement instructions ...

Page 222: ...Page D01 12 Ed 1 Rev 0 Section 9 Supplements Supplement no D01 GARMIN GFC700 AUTOPILOT INSTALLATION AND RNAV RNP NAVIGATION ELIGIBILITY INTENTIONALLY LEFT BLANK ...

Page 223: ...cted 12 1 AUTOPILOT HARDOVER OR FAILURE TO HOLD THE SELECTED HEADING In case of A P hardover or failure to hold selected heading apply following pro cedure Accomplish items 1 and 2 simultaneously 1 Airplane control wheel GRASP FIRMLY and OVERPOWER if necessary to regain aircraft control 2 AP DISC TRIM INTR switch PRESS 3 AP MASTER SWITCH OFF 4 AP Circuit Breaker PULL WARNING Following an A P or ME...

Page 224: ...apply following proce dure 1 AP DISC TRIM INTR switch PRESS and HOLD 2 TRIM MASTER SWITCH OFF 3 TRIM Circuit Breaker PULL 4 AP DISC TRIM INTR switch RELEASE CAUTION When Autopilot is disconnected because of a pitch trim malfunction hold the control wheel firmly When electric trim is disconnected it is necessary operate the pitch trim through the Trim Wheel When electric trim is disconnected Autopi...

Page 225: ...ontrol of the airplane Immediately grasp the control wheel and push and hold the A P DISC TRIM INT switch throughout the recovery Manipulate the controls as required to safely keep the airplane within all of its operating limitations Ele vator trim should be used manually as needed to relieve control forces Switch the AP MASTER SWITCH to OFF and when time is available after aircraft recovery open ...

Page 226: ... C M red cross on MFD SYS page A P can t be engaged FD is operative in all modes X X only MINSPD warning X X A P disconnect MEPT Unavailable AFCS red annunciation on PFD 1 ESP Fail on alert window PTCH C M red cross on MFD SYS page ROLL C M red cross on MFD SYS page PTRM C M red cross on MFD SYS page A P can t be engaged FD is operative in all modes X X only MINSPD warning X ENGAGED MEPT Unavailab...

Page 227: ...s in case of loss of PFD or MFD PFD MFD NOTES ON OFF ON A P reverts to PIT ROLL from any mode selected No aurals from A P both A P DISC USP ON ON OFF A P stays in the selected mode A P control keyboard unavailable A P can be disconnected with A P DISC button on control wheel FD command bars cannot be eliminated ESP Off on alert window on PFD ON OFF ON OFF A P automatically disconnects after 4 to 5...

Page 228: ...Page D01 13 Section 9 Supplements Supplement no D01 GARMIN GFC700 AUTOPILOT INSTALLATION AND RNAV RNP NAVIGATION ELIGIBILITY Ed 1 Rev 0 INTENTIONALLY LEFT BLANK ...

Page 229: ... NORMAL PROCEDURES Make sure you first applied instructions reported on the basic AFM Section 4 Normal Procedures According to A C configuration apply following pages replacement Supplement D01 NORMAL PROCEDURES page AFM Section 4 page 4A 27 thru 38 REPLACES Added at the end of Section 4 of basic AFM Supplement D01 pages replacement instructions ...

Page 230: ...Page D01 15 Section 9 Supplements Supplement no D01 GARMIN GFC700 AUTOPILOT INSTALLATION AND RNAV RNP NAVIGATION ELIGIBILITY Ed 1 Rev 0 INTENTIONALLY LEFT BLANK ...

Page 231: ...ASTER SWITCH BAT ON 2 AVIONICS MASTER SWITCH ON 3 AUTOPILOT MASTER SWITCH ON 4 POWER APPLICATION and SELFCTEST The autopilot tests itself when power is first made available The test is a sequence of internal checks before starting normal system operation The test sequence is shown on PFD left upper corner by the red AFCS label followed by the white PFT label ending with double AP disengagement ton...

Page 232: ...engagement Use the CWS Button to disengage the pitch and roll while the autopilot remains active HDG Pressing the HDG knob synchronizes the Selected Heading to the cur rent heading In this case expect a small heading overshoot that will be subsequently corrected VS MODE WARNING Selection of a vertical speed beyond the capability of the aircraft can create a condition of reduced airspeed and possib...

Page 233: ... ALTS is armed rather than ALTV Altitude preselect must show an altitude below the flight plan s Target Altitude If the selected altitude is not at least 75 ft below the VNV Target Alti tude the FD captures the Selected Altitude once Vertical Path Tracking Mode become active ALTS is armed rather than ALTV If VPTH is armed more than 5 minutes prior to descent path capture acknowledgement is require...

Page 234: ...ther GPS related information e g wind will turn to yellow If GPS nave mode is being selected the HSI on the PFD will not display the devi ation bar If GPS is selected as navigation source a AHRS1 GPS AHRS1 oper ating exclusively in no GPS mode CAS message will appear inside the alert win dow Dead Reckoning Mode only functions in Enroute ENR or Oceanic OCN phase of flight In all other phases an inv...

Page 235: ...tion using GPS SBAS source data resumes automatically once a valid GPS solution is restored As a result of operating in DR Mode all GPS derived data is computed based upon an estimated position and is displayed as yellow text on the display to denote degraded navigation source information Also while the G1000 is in DR Mode some terrain functions are not available Additionally the accuracy of all n...

Page 236: ...d as an equipment function or from an alter native method acceptable to the Authority Where a navigation data base is installed the data base validity current AIRAC cycle should be checked before flight Traditional navigation equipment e g VOR DME and ADF should be selected to available aids so as to allow immediate cross checking or reversion in the event of loss of GPS navigation capability a Pr...

Page 237: ...he insertion in the flight plan of waypoints loaded from the database During the procedure and where feasible flight progress should be monitored for navigational reasonableness by cross checks with conventional navigation aids using the primary display c Arrival Prior to the arrival phase the flight crew should verify that the correct terminal procedure has been loaded The active flight plan shou...

Page 238: ...dent on GPS data and for which the weather is forecast to be suitable to enable a landing to be made from that approach or 2 There is at least one alternate destination within range where a different type of approach system is available which is not dependent on GPS data and for which the weather is forecast to be suitable to enable a landing to be made from that approach 9 1 APPROACH APPLICATIONS...

Page 239: ... ate navigation receiver must be used for the selected approach e g VOR or ILS The final course segment of ILS approaches for example must be flown by tuning the NAV receiver to the proper frequency and selecting that NAV receiver on the CDI The G1000 SBAS GPS allows for flying LNAV LP LP V and LPV approach service levels according to the published chart The V designation adds adviso ry vertical g...

Page 240: ...on This is a Non Precision or 2D Approach with Lateral only navigation guidance provided by GNSS and an Aircraft Based Augmentation System ABAS Re ceiver Autonomous Integrity Monitoring RAIM is a form of ABAS Lateral guidance is linear with accuracy to within 0 3 NM parallel to either side of the final approach track LP Localiser Performance This is a Non Precision or 2D Approach with Lateral only...

Page 241: ...system correctly past the MAP in order to follow the published MAP correctly Pilots should be fully competent in the necessary selection routines required by their own equipment in order to transition to the MAP and preserve accurate nav igation throughout When GPS navigation is NOT available for the MAP it may be necessary to re set the display function of the HSI CDI to disengage GPS information...

Page 242: ...roach should always be discontinued If the receiver fails to engage the correct approach mode or In case of Loss Of Integrity LOI monitoring or Whenever the HSI CDI indication or GP indication where applicable ex ceeds half scale displacement or If a RAIM or equivalent warning is activated or If RAIM or equivalent function is not available and annunciated before passing the FAF ...

Page 243: ...ATION AND RNAV RNP NAVIGATION ELIGIBILITY Ed 1 Rev 0 SECTION 5 PERFORMANCE Make sure you first applied instructions reported on the basic AFM Section 5 Performance According to A C configuration refer to the basic AFM Section 5 Performance Supplement D01 pages replacement instructions ...

Page 244: ...Page D01 17 Section 9 Supplements Supplement no D01 GARMIN GFC700 AUTOPILOT INSTALLATION AND RNAV RNP NAVIGATION ELIGIBILITY Ed 1 Rev 0 INTENTIONALLY LEFT BLANK ...

Page 245: ...nts Supplement no D01 GARMIN GFC700 AUTOPILOT INSTALLATION AND RNAV RNP NAVIGATION ELIGIBILITY Ed 1 Rev 0 SECTION 6 WEIGHT AND BALANCE Refer to the basic AFM Section 6 Weight and Balance Supplement D01 pages replacement instructions ...

Page 246: ...Page D01 19 Section 9 Supplements Supplement no D01 GARMIN GFC700 AUTOPILOT INSTALLATION AND RNAV RNP NAVIGATION ELIGIBILITY Ed 1 Rev 0 INTENTIONALLY LEFT BLANK ...

Page 247: ... basic AFM Section 7 Airframe and Systems Description According to A C configuration apply following pages replacement Supplement D01 AIRFRAME AND SYSTEMS DESCRIPTION page AFM Section 7 page 7A 8 thru 9 REPLACES 7 8 thru 9 of basic AFM Section 7 7A 20 thru 21 REPLACES 7 20 thru 21 of basic AFM Section 7 7A 27 REPLACES 7 27 of basic AFM Section 7 7A 33 REPLACES 7 33 of basic AFM Section 7 Supplemen...

Page 248: ...Page D01 21 Section 9 Supplements Supplement no D01 GARMIN GFC700 AUTOPILOT INSTALLATION AND RNAV RNP NAVIGATION ELIGIBILITY Ed 1 Rev 0 INTENTIONALLY LEFT BLANK ...

Page 249: ...tch on the instru ment panel Flaps act in continuous mode the indicator displays three markings relat ed to 0 takeoff T O and landing FULL positions A breaker positioned on the right side of the instrument panel protects the electric circuit The control of the stabilator trim is operated by means of both a control wheel locat ed between the two front seats that acts directly on the control cables ...

Page 250: ...entral area holds the standby unit for PFI parameters MD 302 suite and the ELT button The right area holds Garmin G1000 MFD with dedicated AP control buttons and breaker panel The lower LH portion of the instrument panel holds Ignition key Master and Generator switches Emergency fuel pump Avionic Master switch AP Master switch Trim Disconnect switch The lower Central portion of the instrument pane...

Page 251: ...nator failure The switch between the energy sources is automatic and no action is required in order to activate the alternate energy source For ground maintenance and or starting an external power socket is provided The alternator and battery are connected to the battery bus in order to provide energy for the electric equipment Each electrically fed instrument is connected to a dedicated circuit b...

Page 252: ... 7 Airframe and Systems description ELECTRICAL SYSTEM Ed 1 Rev 0 FIG 7 15 ELECTRICAL SYSTEM ARCHITECTURE 12 3 STALL WARNING SYSTEM The aircraft is equipped with a stall warning system consisting of a sensor locat ed on the right wing leading edge connected to a warning horn located near the instrument panel ...

Page 253: ...n the front area pilot and two in the rear area passengers In the central area of the cabin ceiling is located a spot light used to illuminate the pedestal during night flight operations All ceiling lights are dimmable by a dedicat ed dimmer FIG 7 18 CABIN CEILING LIGHTS LAYOUT The instrument panel can be illuminated by 8 incandescence light strips all dimma ble FIG 7 19 INSTRUMENT PANEL LIGHTS LA...

Page 254: ... N D01 FOR GARMIN GFC700 AUTOPILOT INSTALLATION AND RNAV RNP NAVIGATION ELIGIBILITY Page 7A 33 Ed 1Rev 0 Section 7 Airframe and Systems description PLACARDS ELT unit position placard Breaker Panel placards ...

Page 255: ...AFMS N D01 FOR GARMIN GFC700 AUTOPILOT INSTALLATION AND RNAV RNP NAVIGATION ELIGIBILITY Page 7A 33 Ed 1Rev 0 Section 7 Airframe and Systems description PLACARDS ...

Page 256: ...D RNAV RNP NAVIGATION ELIGIBILITY SECTION 8 GROUND HANDLING SERVICE Make sure you first applied instructions reported on the basic AFM Section 8 Ground Handling Service According to A C configuration refer to the basic AFM Section 8 Ground Handling Service Supplement D01 pages replacement instructions ...

Page 257: ...Page D01 23 Ed 1Rev 0 Section 9 Supplements Supplement no D01 GARMIN GFC700 AUTOPILOT INSTALLATION AND RNAV RNP NAVIGATION ELIGIBILITY INTENTIONALLY LEFT BLANK ...

Page 258: ...2010 070 160118 2 V5 13 thru 16 Amended cruise performance to add fuel consumption for different power setting D Ronca C Caruso M Oliva Approved under the au thority of DOA ref EASA 21J 335 Approval No MOD2010 103 161026 List of Effective Pages Page Page Revision Cover Pages D02 1 thru 17 Rev 0 Section 1 V1 6 Rev 1 Section 2 V2 7 Rev 1 Section 2 V2 9 10 Rev 1 Section 3 V3 14 Rev 0 Section 3 V3 18 ...

Page 259: ...ided to allow the owner for replac ing the AFM pages containing information amended as per MT variable pitch propeller in subject It is the owner s responsibility to replace the mentioned pages in accordance with the instructions herein addressed section by section Section 9 Supplements Supplement no D02 Variable pitch propeller 2nd Edition Rev 0 ...

Page 260: ...n the basic AFM Section 1 General Apply following pages replacement Supplement D02 GENERAL page AFM Section 1 page 1 6 REPLACES Page 1 6 of AFM Section 1 Supplement D02 pages replacement instructions Section 9 Supplements Supplement no D02 Variable pitch propeller 2nd Edition Rev 0 ...

Page 261: ...Page D02 4 INTENTIONALLY LEFT BLANK Section 9 Supplements Supplement no D02 Variable pitch propeller 2nd Edition Rev 0 ...

Page 262: ...led with down exhaust outlets Maximum power Maximum continuous power 134 0 kW 180hp 2700 rpm 129 2 kW 173 3hp 2600 rpm 6 PROPELLER Manufacturer MT Propeller Model MTV 15 B 193 52 Type Certificate EASA TCDS no P 098 Blades hub wood composite 2 blades aluminum hub Diameter 1930 mm 76 in no reduction is permitted Type Variable pitch Governor Manufacturer MT Propeller Model P 860 23 Type Hydraulic Sec...

Page 263: ...Page D02 5 INTENTIONALLY LEFT BLANK Section 9 Supplements Supplement no D02 Variable pitch propeller 2nd Edition Rev 0 ...

Page 264: ...following pages replacement Supplement D02 LIMITATIONS page AFM Section 2 page V2 7 REPLACES Page 2 7 of AFM Section 2 V2 9 REPLACES Page 2 9 of AFM Section 2 V2 10 REPLACES Page 2 10 of AFM Section 2 Supplement D02 pages replacement instructions Section 9 Supplements Supplement no D02 Variable pitch propeller 2nd Edition Rev 0 ...

Page 265: ...Page D02 7 INTENTIONALLY LEFT BLANK Section 9 Supplements Supplement no D02 Variable pitch propeller 2nd Edition Rev 0 ...

Page 266: ...R Max Power hp Max rpm Prop rpm Max T O 180 2700 Max Cont 173 3 2600 Temperatures Max CHT 500 F 260 C Max Oil 245 F 118 C Oil Pressure Minimum Idling 25 psi 1 7 Bar Minimum Normal 55 psi 3 8 Bar Maximum Normal 95 psi 6 5 Bar Starting Warm up taxi and take off Max 115 psi 7 9 Bar Fuel pressure At Inlet to fuel injector Minimum 14 psi 0 96 Bar Maximum 35 psi 2 41 Bar Section 9 Supplements Powerplant...

Page 267: ...s 6 PROPELLER MANUFACTURER MT Propeller MODEL MTV 15B 193 52 TYPE wood composite 2 blade variable pitch DIAMETER 1930 mm 76 in no reduction is permitted 7 MAXIMUM OPERATING ALTITUDE Maximum operating altitude is 12000 ft 3658 m MSL CAUTION At altitudes above 10000 ft 3048 m up to and including 12000 ft 3658 m flight crew is recommended to use supplemental oxygen 8 AMBIENT TEMPERATURE Ambient tempe...

Page 268: ...700 2700 line OIL TEMP F 140 245 0 140 245 255 CHT F 435 line 150 475 0 150 475 500 500 510 EGT F 1000 1500 1375 line 1500 1550 OIL PRESS psi 0 25 55 95 25 55 95 115 115 125 FUEL PRESS psi 0 14 14 35 35 40 FUEL QTY litres 0 0 115 gal 0 0 30 4 FUEL FLOW l hr 0 75 gal hr 0 20 5 OTHER INSTRUMENT MARKINGS INSTRUMENT RED ARC Minimum limit GREEN ARC Safe operation YELLOW ARC Caution RED ARC Maximum limi...

Page 269: ...Page D02 8 INTENTIONALLY LEFT BLANK Section 9 Supplements Supplement no D02 Variable pitch propeller 2nd Edition Rev 0 ...

Page 270: ...rocedures Apply following pages replacement Supplement D02 Emergency Procedures page AFM Section 3 page V3 14 REPLACES Page 3 14 of AFM Section 3 V3 18 thru 19 REPLACES Page 3 18 thru 19 of AFM Section 3 Supplement D02 pages replacement instructions Section 9 Supplements Supplement no D02 Variable pitch propeller 2nd Edition Rev 0 ...

Page 271: ...Page D02 10 INTENTIONALLY LEFT BLANK Section 9 Supplements Supplement no D02 Variable pitch propeller 2nd Edition Rev 0 ...

Page 272: ...e to decrease propeller rpm land as soon as possible applying Forced landing procedure See Para 11 CAUTION Maximum propeller rpm exceedance may cause engine components damage Monitor engine RPM overspeed shall be prevented by retarding propeller lever 6 4 IRREGULAR RPM 1 Fuel pump ON 2 Fuel quantity and pressure indicators CHECK 3 If necessary SWITCH TANK If engine continues to run irregularly Lan...

Page 273: ...to continue flight 1 Approach nearest airfield control engine power with Propeller lever 2 Perform landing with shut down engine applying Forced landing proce dure See Para 11 If power is not sufficient to continue flight 1 Carry out Forced landing procedure See Para 11 Defective Propeller Lever Control Cable If power is sufficient to continue flight 1 Approach nearest airfield control engine powe...

Page 274: ...Pressure CHT EGT running down abnormally Inflight engine restart may be performed during 1g flight anywhere within the normal operating envelope of the airplane 1 Master switch Check ON 2 Fuel pump ON 3 Fuel quantity indicator CHECK 4 Fuel Selector SWITCH TANK 5 Throttle Lever Minimum 1cm above IDLE 6 Propeller Lever Full forward 7 Mixture FULL rich 8 Throttle lever SET as required In case of unsu...

Page 275: ...Page D02 11 INTENTIONALLY LEFT BLANK Section 9 Supplements Supplement no D02 Variable pitch propeller 2nd Edition Rev 0 ...

Page 276: ...owing pages replacement Supplement D02 Normal Procedures page AFM Section 4 page V4 7 REPLACES Page 4 7 of AFM Section 4 V4 15 REPLACES Page4 15 of AFM Section 4 V4 19 thru 26 REPLACES Page4 19 thru 26 of AFM Section 4 Supplement D02 pages replacement instructions Section 9 Supplements Supplement no D02 Variable pitch propeller 2nd Edition Rev 0 ...

Page 277: ...Page D02 13 INTENTIONALLY LEFT BLANK Section 9 Supplements Supplement no D02 Variable pitch propeller 2nd Edition Rev 0 ...

Page 278: ...peed VR T O 60 KIAS Best Angle of Climb Speed VX T O 65 KIAS Best Angle of Climb Speed VX 0 75 KIAS Best Rate of Climb speed VY 0 82 KIAS Flaps VFE T O LAND 91 KIAS No flaps approach 0 80 KIAS Approach speed T O 75 KIAS Final Approach Speed FULL 70 KIAS Manoeuvring speed VA 0 120 KIAS V glide 0 84 KIAS Never Exceed Speed VNE 0 166 KIAS Section 4 Normal procedures AIRSPEED FOR NORMAL OPERATIONS 2nd...

Page 279: ...Pre flight inspection External inspection then update the Garmin fuel content in the totalizer accordingly The totalizer function available on Garmin Engine page allows input only up to 230lts maximum usable fuel Initial Fuel indication on totalizer must be correct ed manually as it does not use the aircraft fuel quantity indicators as input Once correctly initialized fuel consumption on totalizer...

Page 280: ...tain smooth engine operations 8 Throttle set 1500 RPM a Alternate Air check Alternate Air PULL Check drop 50 100 RPM b Mixture check Mixture reduce EGT check increase FF check decrease Mixture FULL RICH 9 Throttle 2100 RPM 10 Propeller Lever Pull back until a drop of max 500 RPM is reached then high RPM Cycle 3 times 11 Magneto Check L BOTH R BOTH Max RPM drop 175 RPM Max difference 50 RPM 12 Thro...

Page 281: ...d at constant IAS or EGT reaches 1375 F mark 1 Pitot HEAT ON if required 2 Fuel pump ON 3 Brakes apply 4 Throttle FULL and check approximately 2680 20 RPM WARNING Engine proper performance at full throttle shall be checked early in the ground roll in order to abandon take off if necessary A rough engine sluggish RPM increase or failure to reach take off RPM are reasons for abandoning the take off ...

Page 282: ...f where airports are at 5000ft density altitude or higher During climb a rough method of correctly leaning is to slowly reduce mixture lever un til an increase of appr ly 50 100 RPM is noticed at constant IAS or EGT reaches 1375 F mark 1 Flaps UP minimum speed 73 KIAS Expect to adjust pitch trim pitch up when retracting flaps after take off 2 Establish climb Vy 82 KIAS 3 Electrical fuel pump OFF 4...

Page 283: ...d always be taken that the cylinders do not cool down too quickly The cooling rate should not exceed 50 F per minute For maximum service life cylinder head temperature should be kept below 475 F high performance cruise and below 435 F for economy cruise Best Cruise Economy Mixture The best economy mixture setting may only be used up to a power setting of 75 In order to obtain the lowest specific f...

Page 284: ...avoid potential illumination of ALT FAIL due to low propeller speed the following best practice should be observed Reducing power to maintain a minimum descent speed of 84 KIAS best glide and or a blade angle to maintain 850 RPM Opening the ALTER AIR command to full open to avoid ice accretion CAUTION The maximum permissible cylinder head temperature 500 F must never be exceeded The mixture contro...

Page 285: ...ptimal touchdown speed 60 KIAS CAUTION In conditions such as e g strong wind danger of windshear or turbulence a higher approach speed shall be selected 5 12 BALKED LANDING MISSED APPROACH 1 Throttle FULL 2 Speed keep over 80 KIAS climb to VY or VX as applicable 3 Flaps position T O Above a safe height 4 Propeller lever 2600 RPM 5 Landing lights OFF 5 13 GO AROUND 1 Throttle FULL 2 Speed keep over...

Page 286: ...Master OFF 10 Master Generator switches OFF 11 Fuel selector valve OFF WARNING For safety verify propeller is fully stopped before any other action CAUTION Instruct passenger to fully open RH door and depart avoiding contact with wheels and sharp wing control surfaces edges 5 16 POSTFLIGHT CHECKS 1 Flight controls lock by means of seat belts 2 Wheel chocks and wing mooring lines Set 3 Parking brak...

Page 287: ...izontal speed The effect on flight characteristics is minimal 5 18 REFUELLING Before refuelling the airplane must be connected to electrical ground 5 19 FLIGHT AT HIGH ALTITUDE At high altitudes the provision of oxygen for the occupant is necessary Legal requirements for the provision of oxygen should be adhered to see para 2 9 Section 4 Normal procedures CHECKLISTS 2nd Edition Rev 0 ...

Page 288: ...ION 5 PERFORMANCES Supplement D02 Performances pages replace basic AFM Section 5 as whole Supplement D02 pages replacement instructions Section 9 Supplements Supplement no D02 Variable pitch propeller 2nd Edition Rev 0 ...

Page 289: ...Page D02 15 INTENTIONALLY LEFT BLANK Section 9 Supplements Supplement no D02 Variable pitch propeller 2nd Edition Rev 0 ...

Page 290: ...arts 2 3 Airspeed Indicator System Calibration 3 4 ICAO Standard Atmosphere 5 5 Stall speed 6 6 Crosswind 7 7 Take Off performances 8 8 Take off Rate of Climb 11 9 En Route Rate of Climb 12 10 Cruise Performance 13 11 Landing performances 17 12 Balked Landing Performance 18 13 Noise Data 19 Section 5 Performances INDEX 2nd Edition Rev 0 ...

Page 291: ...ach graph or table was determined according to ICAO Standard Atmosphere ISA s l evaluations of the impact on performances were carried out by theo retical means for Airspeed External temperature Altitude Weight Runway type and condition 2 USE OF PERFORMANCE CHARTS Performances data are presented in tabular or graphical form to illustrate the effect of different variables such as altitude temperatu...

Page 292: ...Calibrated vs Indicated Airspeed Example Given Find KIAS 75 0 Flap UP KCAS 74 7 Indicated airspeed assumes 0 as an instrument error 50 60 70 80 90 100 110 120 130 140 150 160 170 50 60 70 80 90 100 110 120 130 140 150 160 Indicated Airspeed KIAS Calibrated Airspeed KCAS Airspeed Indication System Calibration Flap UP Flap T O Flap LN NOTE Section 5 Performances AIRSPEED INDICATOR SYSTEM CALIBRATION...

Page 293: ... 91 1020 91 1020 FLAP UP 5000 70 72 5020 72 5020 71 5020 90 94 5030 93 5020 92 5020 110 114 5030 113 5020 112 5020 133 137 5040 136 5030 135 5020 FLAP T O 60 62 5010 62 5020 61 5010 70 74 5020 73 5020 72 5020 90 93 5030 93 5020 93 5020 FLAP LND 60 63 5030 62 5020 61 5000 70 72 5020 72 5010 71 5010 90 92 5020 92 5020 91 5010 FLAP UP 8000 70 72 8020 72 8020 71 8020 90 93 8030 92 8020 92 8020 110 113...

Page 294: ...RD 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 Section 5 Performances ICAO STANDARD ATMOSPHERE 2nd Edition Rev 0 ...

Page 295: ... SPEED FLAPS 0 FLAPS T O FLAPS FULL kg lb deg KIAS KCAS KIAS KCAS KIAS KCAS 1160 2557 FWD C G 0 59 60 53 55 50 52 15 60 61 54 56 51 53 30 64 65 58 59 54 56 45 71 71 64 65 61 62 60 85 85 77 78 73 74 Altitude loss during conventional stall recovery as demonstrated during flight tests is approximately 350 ft with banking below 15 NOTE Section 5 Performances STALL SPEED 2nd Edition Rev 0 ...

Page 296: ...V5 7 6 CROSSWIND Maximum demonstrated crosswind is 12 kts Example Given Find Wind direction with respect to air craft longitudinal axis 30 Headwind 17 5 kts Wind speed 20 kts Crosswind 10 kts FIG 5 3 CROSSWIND CHART Section 5 Performances CROSSWIND 2nd Edition Rev 0 ...

Page 297: ...526 1726 644 2113 776 2546 595 1952 1000 Ground Roll 256 840 322 1056 397 1302 482 1581 360 1181 At 50 ft AGL 458 1503 572 1877 701 2300 844 2769 637 2090 2000 Ground Roll 279 915 352 1155 434 1424 526 1726 387 1270 At 50 ft AGL 499 1637 622 2041 762 2500 918 3012 682 2238 3000 Ground Roll 305 1001 384 1260 474 1555 575 1886 415 1362 At 50 ft AGL 543 1781 678 2224 830 2723 1000 3281 731 2398 4000 ...

Page 298: ... 206 676 259 850 320 1050 388 1273 290 951 At 50 ft AGL 372 1220 464 1522 569 1867 685 2247 517 1696 2000 Ground Roll 225 738 283 928 349 1145 424 1391 311 1020 At 50 ft AGL 405 1329 505 1657 619 2031 745 2444 554 1818 3000 Ground Roll 246 807 309 1014 382 1253 463 1519 334 1096 At 50 ft AGL 441 1447 550 1804 674 2211 812 2664 593 1946 4000 Ground Roll 268 879 338 1109 417 1368 506 1660 359 1178 A...

Page 299: ... Roll 162 531 204 669 252 827 306 1004 229 751 At 50 ft AGL 296 971 369 1211 452 1483 545 1788 411 1348 2000 Ground Roll 177 581 223 732 275 902 334 1096 245 804 At 50 ft AGL 322 1056 402 1319 492 1614 593 1946 440 1444 3000 Ground Roll 194 636 244 801 301 988 365 1198 264 866 At 50 ft AGL 350 1148 438 1437 536 1759 645 2116 472 1549 4000 Ground Roll 212 696 266 873 329 1079 399 1309 283 928 At 50...

Page 300: ...96 437 296 169 419 8000 68 470 315 176 51 320 10000 67 345 193 56 67 221 12000 67 221 71 63 184 122 14000 66 96 51 182 300 23 1060 2337 S L 70 1118 943 787 647 848 2000 69 985 813 660 522 744 4000 69 853 684 533 397 640 6000 68 721 555 406 273 536 8000 68 589 426 280 149 431 10000 67 458 298 155 26 327 12000 66 327 170 29 97 223 14000 66 197 43 95 220 119 960 2116 S L 69 1288 1103 937 787 1001 200...

Page 301: ...367 224 506 8000 78 563 388 232 91 394 10000 77 423 251 97 41 282 12000 76 282 113 37 173 171 14000 76 142 23 171 305 59 1060 2337 S L 82 1284 1085 907 747 976 2000 81 1133 937 762 605 857 4000 80 982 789 618 463 739 6000 79 831 642 474 322 621 8000 78 682 496 330 181 502 10000 77 532 350 187 40 384 12000 76 383 204 45 99 265 14000 75 235 59 97 239 147 960 2116 S L 81 1465 1251 1060 888 1134 2000 ...

Page 302: ...4 71 121 13 6 51 5 22 69 113 13 3 50 3 65 113 12 8 48 5 62 113 12 4 46 9 20 59 105 11 9 45 56 104 11 5 43 5 53 103 11 1 42 2450 29 9 103 133 17 9 67 8 98 135 17 1 64 7 93 136 16 5 62 5 28 95 129 16 8 63 6 90 130 16 1 60 9 85 131 15 5 58 7 26 85 123 15 4 58 3 80 124 14 8 56 76 125 14 3 54 1 24 75 117 14 1 53 4 71 117 13 5 51 1 67 118 13 1 49 6 22 65 110 12 8 48 5 62 110 12 3 46 6 59 110 11 9 45 20 ...

Page 303: ... 47 7 60 111 12 1 45 8 57 110 11 7 44 3 2600 18 53 101 11 1 42 50 99 10 7 40 5 47 97 10 4 39 4 2450 26 8 94 132 16 6 62 8 89 132 15 9 60 2 84 133 15 3 57 9 2450 26 90 129 16 1 60 9 85 129 15 4 58 3 81 130 14 8 56 2450 24 80 123 14 7 55 6 75 123 14 2 53 8 72 124 13 7 51 9 2450 22 70 116 13 5 51 1 66 116 12 9 48 8 63 117 12 5 47 3 2450 20 60 108 12 1 45 8 57 108 11 6 43 9 54 107 11 3 42 8 2450 18 50...

Page 304: ...47 3 59 112 12 45 4 56 111 11 6 43 9 2600 18 57 108 11 7 44 3 54 106 11 3 42 8 51 104 10 9 41 3 2450 23 9 85 129 15 4 58 3 80 130 14 8 56 76 131 14 2 53 8 2450 23 80 126 14 8 56 75 127 14 2 53 8 72 127 13 7 51 9 2450 22 75 123 14 1 53 4 71 123 13 6 51 5 67 123 13 1 49 6 2450 20 64 114 12 7 48 1 61 114 12 2 46 2 58 113 11 8 44 7 2450 19 59 110 12 45 4 56 109 11 6 43 9 53 107 11 2 42 4 2450 18 54 10...

Page 305: ...50 19 64 116 12 6 47 7 60 115 12 1 45 8 57 114 11 7 44 3 2450 18 59 111 11 9 45 55 109 11 4 43 2 52 106 11 1 42 2350 19 66 121 12 9 48 8 62 120 12 4 46 9 59 117 11 9 45 2350 18 60 115 12 2 46 2 57 113 11 7 44 3 54 110 11 3 42 8 Weight 1160 kg Mixture FULL RICH Pressure Altitude 12000 ft Corrections Best Power 10 to Full Rich F C Best Economy 20 to Full Rich F C ISA 30 C 39 C ISA 9 C ISA 30 C 21 C ...

Page 306: ...529 1736 550 1804 521 1709 1000 Ground Roll 212 696 233 764 254 833 276 906 244 801 At 50 ft AGL 496 1627 517 1696 538 1765 560 1837 528 1732 2000 Ground Roll 220 722 242 794 264 866 286 938 251 823 At 50 ft AGL 504 1654 526 1726 548 1798 570 1870 535 1755 3000 Ground Roll 228 748 251 823 274 899 297 974 259 850 At 50 ft AGL 512 1680 535 1755 558 1831 581 1906 543 1781 4000 Ground Roll 236 774 260...

Page 307: ... 6 9 4 9 3 1 6 0 3000 8 3 6 1 4 1 2 3 5 3 4000 7 4 5 2 3 2 1 4 4 6 5000 6 6 4 4 2 4 0 6 3 9 6000 5 7 3 5 1 6 0 2 3 3 7000 4 8 2 7 0 7 1 0 2 6 1060 2337 S L 12 9 10 4 8 1 6 1 9 0 1000 11 9 9 4 7 2 5 2 8 3 2000 11 0 8 5 6 3 4 3 7 5 3000 10 0 7 6 5 4 3 4 6 8 4000 9 1 6 7 4 5 2 5 6 0 5000 8 1 5 7 3 6 1 7 5 3 6000 7 2 4 8 2 7 0 8 4 5 7000 6 2 3 9 1 8 0 1 3 8 960 2116 S L 15 2 12 4 10 7 7 10 9 1000 14 1...

Page 308: ... Annex 16 6th Ed July 2011 Vol I Chapter 10 and 14 CFR 36 1581 c is 80 58 dB A NOTE No determination has been made by the Federal Aviation Administration that the noise levels of this aircraft are or should be acceptable or unacceptable for operation at into or out of any airport Section 5 Performances NOISE DATA 2nd Edition Rev 0 ...

Page 309: ...AFMS N D02 FOR VARIABLE PITCH PROPELLER EQUIPPED AIRPLANES Page D02 16 INTENTIONALLY LEFT BLANK Section 9 Supplements Supplement no D02 Variable pitch propeller 2nd Edition Rev 0 ...

Page 310: ...s Description Apply following pages replacement Supplement D02 Performances page AFM Section 7 page V7 10 thru 11 REPLACES Page 7 10 thru 11 of AFM Section 7 V7 16 REPLACES Page 7 16 of AFM Section 7 V7 27 REPLACES Page 7 27 of AFM Section 7 V7 36 REPLACES Page 7 36 of AFM Section 7 Supplement D02 pages replacement instructions Section 9 Supplements Supplement no D02 Variable pitch propeller 2nd E...

Page 311: ...AFMS N D02 FOR VARIABLE PITCH PROPELLER EQUIPPED AIRPLANES Page D02 18 INTENTIONALLY LEFT BLANK Section 9 Supplements Supplement no D02 Variable pitch propeller 2nd Edition Rev 0 ...

Page 312: ...he cylinders that shuts down Throttle This lever left hand with large knob is used to control manifold pressure MAP High manifold pressure means a large quantity of fuel air mixture is being supplied to engine while low manifold pressure means a lesser quantity of fuel air mixture is being supplied Propeller lever By means of this lever central lever with blue handle the propeller governor control...

Page 313: ...position 4 3 DEFROST AND CABIN HEAT Two knobs located on the lower side of the central pedestal allow Defrost and Cabin Heat function The one marked as Defrost and Cabin Heat allows hot air to perform windshield defrost and partially cabin heat The cabin heat control knob when fully outward allows cabin to receive maximum hot air When both cabin heat and defrost and cabin heat are pulled air is pa...

Page 314: ... 129 2 kW 173 3hp 2600 rpm Oil Consumption Operation RPM HP Max Oil Cons Qts Hr Max Cyl Head Temp Normal Rated 2700 180 80 500 F 260 C Performance Cruise 75 2450 135 45 500 F 260 C Economy Cruise 60R Rated 2350 117 39 500 F 260 C 7 2 PROPELLER Manufacturer MT Propeller Model MTV 15 B 193 52 Type Certificate EASA TCDS no P 098 Blades hub wood composite 2 blades aluminium hub Diameter 1930 mm 6 33 f...

Page 315: ...ntral area of the cabin ceiling is located a spot light used to illuminate the pedestal during night flight operations All ceiling lights are dimmable by a dedicat ed dimmer FIG 7 18 CABIN CEILING LIGHTS LAYOUT The instrument panel can be illuminated by 8 incandescence light strips all dimma ble FIG 7 19 INSTRUMENT PANEL LIGHTS LAYOUT FWD From mid MAP light ceiling Section 9 Supplements LIGHTS 2nd...

Page 316: ...AFMS N D02 FOR VARIABLE PITCH PROPELLER EQUIPPED AIRPLANES Page V7 36 Pedestal placards Section 9 Supplements PLACARDS 2nd Edition Rev 0 ...

Page 317: ... order to better identify the pages approved according to EASA regulation D Ronca C Caruso M Oliva Approved under the au thority of DOA ref EASA 21J 335 Approval No MOD2010 070 160118 2 6G 11 12 Pages removed D Ronca C Caruso M Oliva Approved under the au thority of DOA ref EASA 21J 335 Approval No MOD2010 103 161026 List of Effective Pages Page Revision Cover Pages D03 1 thru 22 Rev 0 Section 2 2...

Page 318: ...ION Ed 1 Rev 0 INDEX INTRODUCTION 3 Section 1 GENERAL 5 Section 2 LIMITATIONS 7 Section 3 EMERGENCY PROCEDURES 10 Section 4 NORMAL PROCEDURES 13 Section 5 PERFORMANCE 16 Section 6 WEIGHT AND BALANCE 18 Section 7 AIRFRAME AND SYSTEMS DESCRIPTION 20 Section 8 GROUND HANDLING SERVICE 22 ...

Page 319: ...ein supplements or supersedes the basic Aircraft Flight Manual detailed instructions are provided to allow the owner for replacing the AFM pages containing information amended as per Garmin G500 in subject It is the owner s responsibility to replace the mentioned pages in accordance with the instructions herein addressed section by section ...

Page 320: ...Page D03 4 Section 9 Supplements Supplement no D03 ALTERNATIVE AVIONICS CONFIGURATION Ed 1 Rev 0 INTENTIONALLY LEFT BLANK ...

Page 321: ...TIVE AVIONICS CONFIGURATION Ed 1 Rev 0 SECTION 1 GENERAL Make sure you first applied instructions reported on the basic AFM Section 1 General According to A C configuration refer to the basic AFM Section 1 General Supplement D03 pages replacement instructions ...

Page 322: ...Page D03 6 Section 9 Supplements Supplement no D03 ALTERNATIVE AVIONICS CONFIGURATION Ed 1 Rev 0 INTENTIONALLY LEFT BLANK ...

Page 323: ... LIMITATIONS Make sure you first applied instructions reported on the basic AFM Section 2 Limitations According A C configuration apply following pages replacement Supplement D03 LIMITATIONS page AFM Section 2 page 2G 13 REPLACES Page 2 13 of basic AFM Section 2 Supplement D03 pages replacement instructions ...

Page 324: ...Page D03 8 Section 9 Supplements Supplement no D03 ALTERNATIVE AVIONICS CONFIGURATION Ed 1 Rev 0 INTENTIONALLY LEFT BLANK ...

Page 325: ...t IFR Day IFR Night Note External Power Circuit Breakers As Required Battery Safety Equipment Furnishing First Aid kit Fire extinguisher ELT Torch with spare batt Ice Protection Pitot heating system Landing Gear Wheel pants Removable Lights Landing taxi lights Strobe lights NAV lights Cabin lights Instrument lights Emergency light Dimming Devices Day Night switch COM Navigation Engine parameters M...

Page 326: ...Page D03 09 Section 9 Supplements Supplement no D03 ALTERNATIVE AVIONICS CONFIGURATION Ed 1 Rev 0 INTENTIONALLY LEFT BLANK ...

Page 327: ...figuration apply following pages replacement Supplement D03 EMERGENCY PROCEDURES page AFM Section 3 page 3G 5 REPLACES 3 5 of basic AFM Section 3 3G 6 REPLACES 3 6 of basic AFM Section 3 3G 7 REPLACES 3 7 of basic AFM Section 3 3G 10 REPLACES 3 10 of basic AFM Section 3 3G 16 REPLACES 3 16 of basic AFM Section 3 3G 17 REPLACES 3 17 of basic AFM Section 3 3G 25 REPLACES 3 25 of basic AFM Section 3 ...

Page 328: ...Page D03 11 Section 9 Supplements Supplement no D03 ALTERNATIVE AVIONICS CONFIGURATION Ed 1 Rev 0 INTENTIONALLY LEFT BLANK ...

Page 329: ...rs are as follows GREEN to indicate that pertinent device is turned ON AMBER to indicate no hazard situations which have to be considered and which require a proper crew action RED to indicate emergency conditions WHITE to indicate advisory messages 2 1ALTERNATOR FAILURE If ALT FAIL caution is ON 1 Circuit breaker s Check 2 Generator SWITCH OFF 3 Generator SWITCH ON If ALT FAIL CAUTION REMAINS on ...

Page 330: ...HEAT caution light turns OFF indicating that the Pitot Heating system is functioning properly If the amber PITOT HEAT caution light is ON when the green PITOT HEAT ON light is on then the Pitot Heating system is not functioning proper ly In this case apply following procedure 1 Pitot heat switch OFF 2 Pitot heat circuit breaker CHECK IN 3 Pitot heat switch ON 4 PITOT HEAT caution light CHECK if th...

Page 331: ...ociated with the failed data In most of cases the red X annunciation is accompanied by a message advisory alert issuing a flashing ADVISORY Softkey annunciation which once selected acknowledges the presence of the message advisory alert and displays the alert text message in the Alerts Window 3 2LOSS OF AIRSPEED INFORMATION AIRSPEED FAIL RED X ON DISPLAY FIELD Display system is not receiving airsp...

Page 332: ...ation and to GTN650 for navigation information 3 8LOW FUEL QUANTITY LEFT If fuel quantity LH is under 24 litres 1 Fuel tank selector Switch to RH fuel tank 3 9LOW FUEL QUANTITY RIGHT If fuel quantity RH is under 24 litres 1 Fuel tank selector Switch to LH fuel tank 3 10 LOW FUEL QUANTITY LEFT AND RIGHT If fuel quantity LH and RH is under 24 litres 1 Land as soon as practical land at the nearest ap...

Page 333: ...e does not increase and temperature exceeds limits Reduce engine power to minimum required Land as soon as possible applying Forced landing procedure See Para 11 Be prepared for engine failure and emergency landing If oil pressure tends to zero combined with vibration loss of oil unusual metallic smoke and noise Apply Forced landing procedure See Para 11 HIGH OIL PRESSURE If oil pressure exceeds u...

Page 334: ... Select opposite fuel tank if NOT empty 3 Fuel quantity CHECK If fuel pressure doesn t build up 1 Land as soon as practical Prepare for potential engine failure and prepare to apply Forced landing procedure See Para 11 6 9HIGH FUEL PRESSURE If fuel pressure increases above the upper limit 35 psi 1 Land as soon as possible Prepare for potential engine shut down and apply Forced landing procedure Se...

Page 335: ...eters and related warnings cautions are lost Flaps extension and retraction will be lost apply Flaps control failure procedure See Para 10 6 Strobe and landing lights will be lost NAV and taxi lights are still available taxi light will be the only visual aid for landing in night conditions 10 2 LOSS OF MAIN BUS In case of loss of main bus the main bus voltage will drop to zero The following will b...

Page 336: ...Page D03 12 Section 9 Supplements Supplement no D03 ALTERNATIVE AVIONICS CONFIGURATION Ed 1 Rev 0 INTENTIONALLY LEFT BLANK ...

Page 337: ...PROCEDURES page AFM Section 4 page 4G 4 REPLACES Page 4 4 of basic AFM Section 4 4G 5 REPLACES Page 4 5 of basic AFM Section 4 4G 9 REPLACES Page 4 9 of basic AFM Section 4 4G 15 REPLACES Page 4 15 of basic AFM Section 4 4G 16 REPLACES Page 4 16 of basic AFM Section 4 4G 17 REPLACES Page 4 17 of basic AFM Section 4 4G 18 REPLACES Page 4 18 of basic AFM Section 4 4G 20 REPLACES Page 4 20 of basic A...

Page 338: ...Page D03 14 Section 9 Supplements Supplement no D03 ALTERNATIVE AVIONICS CONFIGURATION Ed 1 Rev 0 INTENTIONALLY LEFT BLANK ...

Page 339: ...ht training before flight Furthermore as a minimum during training it s strongly recommended using the avionic suite in IFR with incremental steps after initial basic IFR instruction 1 Initial use of a single radio aids No GPS 2 Use of two radio aids No GPS 3 Use of GPS for point to point navigation No approaches 4 Use of VNAV feature 5 Full use of avionic suite The flight training syllabus for IF...

Page 340: ...nd precise handling The following prescriptions other than those already present in the G500 manu al shall be observed Use of GPS for precision approach navigation mode is not allowed Use of GPS is prohibited as primary means for navigation GPS is approved as sup plemental means for navigation Use of GPS is prohibited for IFR in terminal area or in non precision approach op erations If Receiver Au...

Page 341: ...icate of Airworthiness Noise certificate Radio COM certificate AFM check current and on board 2 Weight and balance calculate ref to Section 6 and check within limits 3 Breaker all IN 4 Safety belts connected to hard points check condition 5 Ignition key OFF key extracted 6 Master switch ON 7 Voltmeter check within the limits 8 Lights all ON check for operation 9 Annunciator panel check all lights ...

Page 342: ...flight inspection External inspection then update the EDM930 fuel con tent in the totalizer accordingly The totalizer function available on EDM930 Engine page allows input only up to 230lts maximum usable fuel Initial Fuel indication on totalizer must be corrected manually as it does not use the aircraft fuel quantity indicators as input Once correctly initial ized fuel consumption on totalizer is...

Page 343: ...re than 10 seconds After operating the starter motor let it cool off for 20 seconds After 6 attempts to start the engine let the starter cool off for half an hour 6 Ignition key BOTH 7 Ignition key START When engine start turning and first indication of a starting condition exist 8 Mixture rapidly move to FULL RICH 9 Throttle set 1000 1200 RPM 10 Check oil pressure rises within 10 sec 11 Check OIL...

Page 344: ... let it cool off for 20 seconds After 6 attempts to start the engine let the starter cool off for half an hour 5 Ignition key BOTH 6 Ignition key START When engine start turning and first indication of a starting condition exist 7 Mixture rapidly move to FULL RICH 8 Throttle set 1000 1200 RPM 9 Check oil pressure rises within 10 sec 10 Check OIL PRESSURE LOW extinguished 11 Electric fuel pump OFF ...

Page 345: ... to preserve a full loaded battery minimise annunciator nuisance and assure maximum battery performance during flight Furthermore this is particularly true dur ing cold weather to prevent lead fouling of spark plugs CAUTION Following extended operation on the ground or at high ambient temperatures the following indications of fuel vapor lock may appear Arbitrary changes in idle RPM and fuel flow S...

Page 346: ...ning is to slowly reduce mixture lever until an increase of appr ly 50 100 RPM is noticed at constant IAS or EGT reaches 1375 F mark 1 Pitot HEAT ON if required 2 Fuel pump ON 3 Brakes apply 4 Throttle FULL and check approximately 2100 100 RPM WARNING Engine proper performance at full throttle shall be checked early in the ground roll in order to abandon tak off if necessary A rough engine sluggis...

Page 347: ...Flaps LAND 8 Final Approach Speed set 9 Optimal touchdown speed 60 KIAS CAUTION In conditions such as e g strong wind danger of windshear or turbulence a higher approach speed shall be selected 5 12 BALKED LANDING MISSED APPROACH 1 Throttle FULL 2 Speed keep over 80 KIAS climb to VY or VX as applicable 3 Flaps position T O Above a safe height 4 Landing lights OFF 5 13 GO AROUND 1 Throttle FULL 2 S...

Page 348: ...Page D03 15 Section 9 Supplements Supplement no D03 ALTERNATIVE AVIONICS CONFIGURATION Ed 1 Rev 0 INTENTIONALLY LEFT BLANK ...

Page 349: ...AVIONICS CONFIGURATION Ed 1 Rev 0 SECTION 5 PERFORMANCE Make sure you first applied instructions reported on the basic AFM Section 5 Performance According to A C configuration refer to the basic AFM Section 5 Performance Supplement D03 pages replacement instructions ...

Page 350: ...Page D03 17 Section 9 Supplements Supplement no D03 ALTERNATIVE AVIONICS CONFIGURATION Ed 1 Rev 0 INTENTIONALLY LEFT BLANK ...

Page 351: ... Section 9 Supplements Supplement no D03 ALTERNATIVE AVIONICS CONFIGURATION Ed 1 Rev 0 SECTION 6 WEIGHT AND BALANCE Refer to the basic AFM Section 6 Weight and Balance Supplement D03 pages replacement instructions ...

Page 352: ...Page D03 19 Section 9 Supplements Supplement no D03 ALTERNATIVE AVIONICS CONFIGURATION Ed 1 Rev 0 INTENTIONALLY LEFT BLANK ...

Page 353: ...es replacement Supplement D03 AIRFRAME AND SYSTEMS page AFM Section 7 page 7G 8 REPLACES Page 7 8 of basic AFM Section 7 7G 9 REPLACES Page 7 9 of basic AFM Section 7 7G 20 REPLACES Page 7 20 of basic AFM Section 7 7G 21 REPLACES Page 7 21 of basic AFM Section 7 7G 22 REPLACES Page 7 22 of basic AFM Section 7 7G 23 REPLACES Page 7 23 of basic AFM Section 7 7G 24 REPLACES Page 7 24 of basic AFM Sec...

Page 354: ...Page D03 21 Section 9 Supplements Supplement no D03 ALTERNATIVE AVIONICS CONFIGURATION Ed 1 Rev 0 INTENTIONALLY LEFT BLANK ...

Page 355: ...ctuator controlled by a switch on the in strument panel Flaps act in continuous mode the indicator displays three markings related to 0 takeoff T O and landing FULL positions A breaker positioned on the right side of the instrument panel protects the electric circuit The control of the stabilator trim is operated by means of a control wheel located be tween the two front seats that acts directly o...

Page 356: ... 1 Garmin GDU 620 PFD MFD 5 N 1 Garmin GTN 650 Com Nav Gps 9 N 1 Garmin GNC 255A Com Nav 10 N 1 Garmin GMA 340 Audio Panel 8 N 1 Bendix King KN 572 DME unit 14 N 1 Bendix King KR87 ADF unit 11 N 1 JP Instruments EDM 930 EIS unit 13 N 1 JP Instruments EDM 930 Remote Alarm Display 12 N 1 Mid Continent MD 302 Stand by Instrument 6 N 1 Annunciator panel 7 N 1 Pitch trim indicator 3 N 1 Rudder trim ind...

Page 357: ...witch between the energy sources is automatic and no action is required in order to activate the alternate energy source For ground maintenance and or starting an external power socket is provided The alternator and battery are connected to the battery bus in order to provide energy for the electric equipment Each electrically fed instrument is connected to a dedicated circuit breaker which protec...

Page 358: ...stems description ELECTRICAL SYSTEM Ed 1 Rev 0 FIG 7 15 ELECTRICAL SYSTEM ARCHITECTURE 9 1STALL WARNING SYSTEM The aircraft is equipped with a stall warning system consisting of a sensor locat ed on the right wing leading edge connected to a warning horn located near the instrument panel ...

Page 359: ...ure or in the event of an AHRS and ADC units combined failure an inte grated digital stand by instrument Mid Continent MD 302 featuring airspeed altitude attitude and slip information is installed An ELT device is installed and its control switch is located in the upper left area of the cockpit The Com Nav functions are embodied into two devices GNC 255 and GTN 650 The second one provides also GPS...

Page 360: ...r upon disconnection of ground external power CAUTION Exercise caution while applying external power Exercise extreme caution while disconnecting external power with engine running due to airflow coming from the propeller Approach the power supply receptacle from rear of the wing Make a positive check upon disconnection that the power chord is free from any aircraft structure the receptacle is fir...

Page 361: ...d in correspondence of engine firewall on left and right side of fuselage Flexible hoses connects total pressure and static ports to primary ana logue instruments anemometer and altimeter Garmin G500 suite and standby MD 302 unit are connected to both static and to tal pressure lines providing both air speed and altitude information 0 T O LND FLAP LH STATIC PORT RH STATIC PORT T JOINT ALTERNATE ST...

Page 362: ...lot and two in the rear area passengers In the central area of the cabin ceiling is located a spot light used to illuminate the pedestal during night flight operations All ceiling lights are dimmable by a dedicat ed dimmer FIG 7 18 CABIN CEILING LIGHTS LAYOUT The instrument panel can be illuminated by 8 incandescence light strips all dimma ble FIG 7 19 INSTRUMENT PANEL LIGHTS LAYOUT FWD From mid M...

Page 363: ...RNATIVE AVIONICS CONFIGURATION SECTION 8 GROUND HANDLING SERVICE Make sure you first applied instructions reported on the basic AFM Section 8 Ground Handling Service Refer to the basic AFM Section 8 Ground Handling Service Supplement D03 pages replacement instructions ...

Page 364: ...Page D03 23 Ed 1Rev 0 Section 9 Supplements Supplement no D03 ALTERNATIVE AVIONICS CONFIGURATION INTENTIONALLY LEFT BLANK ...

Page 365: ...rivileges DO OoA HDO 0 First Issue D Ronca C Caruso M Oliva 1 2AF 8 Amended to add the wording Ap proved in order to better identify the pages approved according to EASA regulation D Ronca C Caruso M Oliva Approved under the au thority of DOA ref EASA 21J 335 Approval No MOD2010 070 160118 List of Effective Pages Page Revision Cover Pages D04 1 thru 23 Rev 0 Section 2 2AF 8 Rev 1 Section 6 6AF 8 R...

Page 366: ...ev 0 INDEX INTRODUCTION 3 Section 1 GENERAL 5 Section 2 LIMITATIONS 7 Section 3 EMERGENCY PROCEDURES 10 Section 4 NORMAL PROCEDURES 12 Section 5 PERFORMANCE 14 Section 6 WEIGHT AND BALANCE 16 Section 7 AIRFRAME AND SYSTEMS DESCRIPTION 19 Section 8 GROUND HANDLING SERVICE 22 ...

Page 367: ...ON This section contains supplemental information to operate in a safe and efficient manner the aircraft when it uses Automotive Fuel MOGAS EN 228 2008 E It is the owner s responsibility to replace the mentioned pages in accordance with the instructions herein addressed section by section ...

Page 368: ...Page D04 4 Section 9 Supplements Supplement no D04 AUTOMOTIVE FUEL Ed 1 Rev 0 INTENTIONALLY LEFT BLANK ...

Page 369: ...04 AUTOMOTIVE FUEL Ed 1 Rev 0 SECTION 1 GENERAL Make sure you first applied instructions reported on the basic AFM Section 1 General According to A C configuration refer to the basic AFM Section 1 General Supplement D04 pages replacement instructions ...

Page 370: ...Page D04 6 Section 9 Supplements Supplement no D04 AUTOMOTIVE FUEL Ed 1 Rev 0 INTENTIONALLY LEFT BLANK ...

Page 371: ...IONS Make sure you first applied instructions reported on the basic AFM Section 2 Limitations According to A C configuration apply following pages replacement Supplement D04 LIMITATIONS page AFM Section 2 page 2AF 8 REPLACES 2 8 of basic AFM Section 2 Supplement D04 pages replacement instructions ...

Page 372: ...Page D04 8 Section 9 Supplements Supplement no D04 AUTOMOTIVE FUEL Ed 1 Rev 0 INTENTIONALLY LEFT BLANK ...

Page 373: ...refer to Lycoming Service Instruction No 1070 and No SI1070S latest issue 6 LUBRICANT Recommended Grade Oil Average Ambient Temperature All Temperatures Above 80 F Above 60 F 30 F to 90 F 0 F to 70 F Below 10 F MIL L 6082B or SAEJ1966 Spec Mineral Grades SAE60 SAE50 SAE40 SAE30 SAE20 MIL L 22851 or SAEJ1899 Spec Ashless Dispersant Grades SAE15W50 or SAE20W 50 SAE60 SAE40 or SAE50 SAE40 SAE40 SAE30...

Page 374: ...Page D04 9 Section 9 Supplements Supplement no D04 AUTOMOTIVE FUEL Ed 1 Rev 0 INTENTIONALLY LEFT BLANK ...

Page 375: ...d 1 Rev 0 SECTION 3 EMERGENCY PROCEDURES Make sure you first applied instructions reported on the basic AFM Section 3 Emergency Procedures According to A C configuration refer to the basic AFM Section 3 Emergency Proce dures Supplement D04 pages replacement instructions ...

Page 376: ...Page D04 11 Section 9 Supplements Supplement no D04 AUTOMOTIVE FUEL Ed 1 Rev 0 INTENTIONALLY LEFT BLANK ...

Page 377: ...FUEL Ed 1 Rev 0 SECTION 4 NORMAL PROCEDURES Make sure you first applied instructions reported on the basic AFM Section 4 Normal Procedures According to A C configuration refer to the basic AFM Section4 Normal Procedures Supplement D04 pages replacement instructions ...

Page 378: ...Page D04 13 Section 9 Supplements Supplement no D04 AUTOMOTIVE FUEL Ed 1 Rev 0 INTENTIONALLY LEFT BLANK ...

Page 379: ...OMOTIVE FUEL Ed 1 Rev 0 SECTION 5 PERFORMANCE Make sure you first applied instructions reported on the basic AFM Section 5 Performance According to A C configuration refer to the basic AFM Section 5 Performance Supplement D04 pages replacement instructions ...

Page 380: ...Page D04 15 Section 9 Supplements Supplement no D04 AUTOMOTIVE FUEL Ed 1 Rev 0 INTENTIONALLY LEFT BLANK ...

Page 381: ...ANCE Make sure you first applied instructions reported on the basic AFM Section 6 Weight and Balance According to A C configuration apply following pages replacement Supplement D04 LIMITATIONS page AFM Section 6 page 6AF 8 REPLACES 6 8 of basic AFM Section 6 Supplement D04 pages replacement instructions ...

Page 382: ...Page D04 17 Section 9 Supplements Supplement no D04 AUTOMOTIVE FUEL Ed 1 Rev 0 INTENTIONALLY LEFT BLANK ...

Page 383: ...0 PAX 0 1041 0 PAX 0 1041 0 Baggages 0 1583 0 Fuel liters 240 576 103680 Useful load 260 435 113100 WTO 989 316 312524 CoG pos 25 0 3 1 2 FULL PAYLOAD kg Arm mm Moment kg mm Empty weight 729 273 199017 CoG pos 21 9 USEFUL LOAD Pilot 80 117 9360 Pilot 80 117 9360 PAX 80 1041 83280 PAX 80 1041 83280 Baggages 0 1583 0 Fuel liters 148 576 63936 Useful load 431 578 249118 WTO 1160 381 441960 CoG pos 29...

Page 384: ...Page D04 18 Section 9 Supplements Supplement no D04 AUTOMOTIVE FUEL Ed 1 Rev 0 INTENTIONALLY LEFT BLANK ...

Page 385: ...ure you first applied instructions reported on the basic AFM Section 7 Airframe and Systems Description According to A C configuration apply following pages replacement Supplement D04 AIRFRAME AND SYSTEMS DESCRIPTION page AFM Section 7 page 7AF 30 REPLACES 7 30 of basic AFM Section 7 Supplement D04 pages replacement instructions ...

Page 386: ...Page D04 20 Section 9 Supplements Supplement no D04 AUTOMOTIVE FUEL Ed 1 Rev 0 INTENTIONALLY LEFT BLANK ...

Page 387: ...AFMS N D04 FOR AUTOMOTIVE FUEL Page 7AF 30 Ed 1 Rev 0 Section 7 Airframe and Systems description PLACARDS Allowed Fuel Placard Tire Pressure placard Stabilator degrees placard ...

Page 388: ...Page D04 21 Ed 1 Rev 0 Section 9 Supplements Supplement no D04 AUTOMOTIVE FUEL INTENTIONALLY LEFT BLANK ...

Page 389: ... FUEL SECTION 8 GROUND HANDLING SERVICE Make sure you first applied instructions reported on the basic AFM Section 8 Ground Handling Service According to A C configuration refer to the basic AFM Section 8 Ground Handling Service Supplement D04 pages replacement instructions ...

Page 390: ...Page D04 23 Ed 1 Rev 0 Section 9 Supplements Supplement no D04 AUTOMOTIVE FUEL INTENTIONALLY LEFT BLANK ...

Page 391: ...IRCRAFT FLIGHT MANUAL SUPPLEMENT Record of Revisions Rev Revised page Description of Revision Tecnam Approval EASA Approval or Under DOA Privileges DO OoA HDO 0 D Ronca M Oliva M Oliva DOA List of Effective Pages Page Revision Page Revision D5 1 Rev 0 D5 2 Rev 0 D5 3 Rev 0 D5 4 Rev 0 D5 5 Rev 0 D5 6 Rev 0 D5 7 Rev 0 ...

Page 392: ...Page D5 2 Supplements no D5 Supplement no D5 Argentine AFM supplement 1st Edition Rev 0 INDEX INTRODUCTION 3 LIMITATION 3 Limitation placards 3 Other placards 4 ...

Page 393: ...dures and performance information not contained in this supple ment refer to the EASA Approved Aircraft Flight Manual LIMITATION The information contained herein complements or supersedes the basic information in the EASA Approved Aircraft Flight Manual LIMITATION PLACARDS On the right side of the instrument panel the following placard is placed reminding the observance for NO FUMAR Behind the bag...

Page 394: ...Page D5 4 Supplements no D5 Supplement no D5 Argentine AFM supplement 1st Edition Rev 0 OTHER PLACARDS Door Placard Baggage Door Internal door Placard ...

Page 395: ...Page D5 5 Supplements no D5 Supplement no D5 Argentine AFM supplement 1st Edition Rev 0 Emergency Exit internal placard Open baggage placard Door Handle locking Or ...

Page 396: ...ge D5 6 Supplements no D5 Supplement no D5 Argentine AFM supplement 1st Edition Rev 0 External Power Socket and baggage compartment placards Static source placards No Step placard Fuel Limitation placard ...

Page 397: ...Page D5 7 Supplements no D5 Supplement no D5 Argentine AFM supplement 1st Edition Rev 0 Safety equipment location placard ELT placard ...

Page 398: ...au thority of DOA ref EASA 21J 335 Approval No MOD2010 070 160118 2 APV 6 11 thru 12 Pages removed D Ronca C Caruso M Oliva Approved under the au thority of DOA ref EASA 21J 335 Approval No MOD2010 103 161026 APV5 13 thru 16 Amended to add fuel consumption for different power setting D Ronca C Caruso M Oliva List of Effective Pages Page Revision Cover Pages D07 1 thru 19 Rev 0 Section 1 APV 1 6 AP...

Page 399: ...OPLANES Page D07 2 Ed 1 Rev 0 INDEX INDEX 2 INTRODUCTION 3 Section 1 GENERAL 5 Section 2 LIMITATIONS 7 Section 3 EMERGENCY PROCEDURES 9 Section 4 NORMAL PROCEDURES 11 Section 5 PERFORMANCE 13 Section 6 WEIGHT AND BALANCE 13 Section 7 AIRFRAME AND SYSTEMS DESCRIPTION 15 Section 8 GROUND HANDLING SERVICE 37 ...

Page 400: ...N This section contains supplemental information to operate in a safe and efficient manner the aircraft when equipped with Garmin GFC 700 autopilot device in terfacing Garmin G1000 and MT variable pitch propeller It is the owner s responsibility to replace the mentioned pages in accordance with the instructions herein addressed section by section ...

Page 401: ...Section 9 Supplements Supplement no D07 GARMIN GFC700 AUTOPILOT AND VARIABLE PITCH PROPELLER EQUIPPED AEROPLANES Page D07 4 Ed 1 Rev 0 INTENTIONALLY LEFT BLANK ...

Page 402: ...rst applied instructions reported on the basic AFM Section 1 General According to A C configuration apply following pages replacement Supplement GENERAL page AFM Section 1 page APV1 6 REPLACES 1 6 of basic AFM Section 1 APV1 13 REPLACES 1 13 of basic AFM Section 1 APV1 16 thru 31 REPLACES 1 16 thru 31 of basic AFM Section 1 Supplement D07 pages replacement instructions ...

Page 403: ...Section 9 Supplements Supplement no D07 GARMIN GFC700 AUTOPILOT AND VARIABLE PITCH PROPELLER EQUIPPED AEROPLANES Page D07 6 Ed 1 Rev 0 INTENTIONALLY LEFT BLANK ...

Page 404: ...jected IO direct drive four cylinder horizontally opposed air cooled with down exhaust outlets Maximum power 134 0 kW 180hp 2700 rpm Maximum continuous power 129 2 kW 173 3hp 2600 rpm 6 PROPELLER Manufacturer MT Propeller Model MTV 15 B 193 52 Type Certificate EASA TCDS no P 098 Blades hub wood composite 2 blades aluminum hub Diameter 1930 mm 76 in no reduction is permitted Type Variable pitch GOV...

Page 405: ...Localizer Line Repleaceable Unit APR Approach LVL Level ARP ASI AerospaceRecommended Practice Air Speed Indicator MAG MET Magnetometer Manual Electric Trim BC Back Course MFD Multi FunctionDisplay CAS Caution Advisory System NAV Navigation CDI CS Course Deviation Indicator CertificationSpecifications OAT PFD Outside Air Temperature Primary Flight Display CWS Control Wheel steering PFI Primary Flig...

Page 406: ...FD The installed MFD dis play is different with respect to standard P2010 configuration since it is GDU 1044 The autopilot suite installed on P2010 is based on the following configuration 1 Roll servo 1 Pitch servo 1 Pitch Trim servo Neither yaw axis nor rudder trim tab control is provided The autopilot is connected to electric system through the below listed circuit breakers connected to the avio...

Page 407: ... multifunction display MFD provides the pilot with a dedicated set of keys for autopi lot control see red frame in the below picture The roll servo is located under the pilot seat and is fixed to a c structure using a dedicated mount Pitch and pitch trim servos are located in the tail cone and are installed on a dedicated mount which hosts both the servos ...

Page 408: ...director com mand bars PFD NORMAL MFD REVER SIONARY Attitude Headinginformation Air data information Navigational database Parameters GPS WAAS VOR and ILS naviga tional data Mode logic flight director computa tions and servo management Autopilot computations and monitor ing Aircraft control sur face Actuation Trimfunctionality In control of the roll axis the autopilot senses turn rate as well as c...

Page 409: ...ond figure below It is the user interface for P2010 avionics suite GDU 1044 unit replaces the GDU 1040 unit on instrument panel RH side MFD GDU 1044 MFD Reversionary mode In the event of a single display failure the system is able to automatically switch the critical information including flight and engine parameters on the remaining display pre senting them in a compact view In the event of a fai...

Page 410: ...gages the autopilot 2 FD Key Activates deactivates the flight director only 3 NAV Key Selects deselects Navigation Mode 4 ALT Key Selects deselects Altitude Hold Mode 5 VS Key Selects deselects Vertical Speed Mode 6 FLC Key Selects deselects Flight Level Change Mode 7 HDG Key Selects deselects Heading Select Mode 8 APR Key Selects deselects Approach Mode 9 VNV Key Selects deselects Vertical Path T...

Page 411: ... used to disengage the autopilot and to acknowledge an autopilot disconnect alert and mute the associated aural tone Manual trim commands are generated only when both sides of the switch are oper ated simultaneously If either side of the switch is ac tive separately for more than three seconds MET func tion is disabled and PTRM is displayed as the AFCS Status Annunciation on the PFD The function r...

Page 412: ... VARIABLE PITCH PROPELLER EQUIPPED AEROPLANES Page APV1 22 Section 1 General AUTOPILOT DESCRIPTION Ed 1 Rev 0 The above mentioned AFCS controls are depicted in the below figures Where 1 PTT switch 2 AP DISC Switch 3 AP Trim Switch 4 CWS Button ...

Page 413: ...AFMS N D07 FOR GARMIN GFC700 AUTOPILOT AND VARIABLE PITCH PROPELLER EQUIPPED AEROPLANES Page APV1 23 Section 1 General AUTOPILOT DESCRIPTION Ed 1 Rev 0 ...

Page 414: ...utopilot operation occurs within the pitch roll and pitch trim servo and provides servo monitoring and automatic flight control in response to flight director steering commands AHRS attitude and rate information and airspeed Manual Electric Trim MET The pitch trim servo provides manual electric trim capability when the autopilot is not engaged ESP Electronic Stability Protection keeps the aircraft...

Page 415: ...he aircraft s autopi lot system although it uses the same control servos so it basically operates in back ground whenever the pilot is hand flying the airplane The ESP feature will only function with GPS available A P MASTER SWITCH ON but autopilot not engaged and aircraft above 200ft AGL ESP enabling As a standard ESP will automatically set to enable at power up The system is configured in order ...

Page 416: ... PFD by the advisory ESP not available on alert window ESP will turn OFF upon loss of both GPS The ADVSY ESP OFF will appear on the alert window in case of loss of both GPS 13 1 1 PITCH MODE Pitch attitude boundaries are set based on P2010 aircraft performances Since pitch ESP augments the natural aircraft longitudinal stability no special simbology is required Value that have been set up for the ...

Page 417: ...e upper disengage ment limit specified in the certification gain file ESP will be disabled 13 1 2 ROLL MODE Roll mode is similar to pitch mode and also utilizes configurable gain file parameters to de fine engagement and disengagement limits as well as the speed and torque curves The engagement and disengagement attitude limits are displayed with double hash marks on the roll indicator when ESP is...

Page 418: ...courage aircraft operation below minimum established airspeeds Pilot will be warned of impending low speed conditions and if no action will be taken FD will directly react in a way that allows the A P to remain engaged but prevents the air plane from stalling USP function has been developed in order to warn pilot of impending low speed conditions and if no action will be taken FD will directly rea...

Page 419: ...opilot with PIT or VS turn ing green on the annunciation panel USP engagement is a consequence of autopilot failing to properly moni toring A P and aircraft behaviour This is mainly caused by a pilot re quest that cannot be fulfilled due to lack of power coupled with unattain able pitch input Pilot need to continuously monitor autopilot performance while checking that mode selections are compatibl...

Page 420: ...ed and the autopilot will provide input causing the aircraft to pitch down and the wings to level The aural AIRSPEED alert will sound every five seconds If aircraft is unintentionally decelerated to 65 KIAS a MINSPD annunciation posts above the airspeed tape on PFD in alternating amber and black text A red UNDERSPEED PRO TECT ACTIVE annunciation will appear to the right of the vertical speed indic...

Page 421: ...d 65 Kts for P2010 a red UNDERSPEED PROTECT ACTIVE annunciation appear to the right of the vertical speed indicator Vertical flight director mode will change from active to armed Flight Director and autopilot will command the aircraft to pitch down until reaching a pitch attitude at which IAS equals at least the minimum commandable autopilot airspeed avoiding the development of a stall condi tion ...

Page 422: ...n the basic AFM Section 2 Limitations According to A C configuration apply following pages replacement Supplement D07 LIMITATIONS page AFM Section 2 page APV 2 7 REPLACES 2 7 of basic AFM Section 2 APV 2 9 thru 10 REPLACES 2 9 thru 10 of basic AFM Section 2 APV 2 15 REPLACES 2 15 of basic AFM Section 2 APV 2 17 thru 20 REPLACES 2 17 thru 20of basic AFM Section 2 Supplement D07 pages replacement in...

Page 423: ...Page D07 8 Section 9 Supplements Supplement no D07 GARMIN GFC700 AUTOPILOT AND VARIABLE PITCH PROPELLER EQUIPPED AEROPLANES Ed 1 Rev 0 INTENTIONALLY LEFT BLANK ...

Page 424: ...lled engine ENGINE MANUFACTURER Lycoming Engines ENGINE MODEL IO 360 M1A MAXIMUM POWER Max Power hp Max rpm Prop rpm Max T O 180 2700 Max Cont 173 3 2600 Temperatures Max CHT 500 F 260 C Max Oil 245 F 118 C Oil Pressure Minimum Idling 25 psi 1 7 Bar Minimum Normal 55 psi 3 8 Bar Maximum Normal 95 psi 6 5 Bar Starting Warm up taxi and take off Max 115 psi 7 9 Bar Fuel pressure At Inlet to fuel inje...

Page 425: ... and ornament Refer to Aircraft Maintenance Manual AMM ATA Chapter 4 and 51 for specific paint requirements 8 PROPELLER MANUFACTURER MT Propeller MODEL MTV 15B 193 52 TYPE wood composite 2 blade variable pitch DIAMETER 1930 mm 76 in no reduction is permitted 9 MAXIMUM OPERATING ALTITUDE Maximum operating altitude is 12000 ft 3658 m MSL 10 AMBIENT TEMPERATURE Ambient temperature from 25 C to 50 C A...

Page 426: ... GREEN ARC Safe ope ration YELLOW ARC Caution RED ARC Maximum limit PROPELLER RPM 950 2600 0 950 2600 2700 2700 line OIL TEMP F 140 245 0 140 245 255 CHT F 435 line 150 475 0 150 475 500 500 510 EGT F 1000 1500 1375 line 1500 1550 OIL PRESS psi 0 25 55 95 25 55 95 115 115 125 FUEL PRESS psi 0 14 14 35 35 40 FUEL QTY litres 0 0 115 gal 0 0 30 4 FUEL FLOW l hr 0 75 gal hr 0 20 12 OTHER INSTRUMENT MA...

Page 427: ...the left it is placed the following placard reporting the speed limitations 19 2 OPERATING LIMITATIONS On the central side of the instrument panel the following placard is placed re minding the observance of aircraft operating limitations according to installed equipment configuration see KOEL paragraph 18 When the Autopilot is installed next placard is added on the instrument panel to the right o...

Page 428: ...IAS Minimum approach speed is 70 KIAS The autopilot must be OFF during takeoff and landing Minimum altitude AGL for Autopilot operation is b Cruise and Descent 800 ft 244 m AGL c Climb after Take off 400 ft 122 m AGL d ILS CAT I precision approach 200 ft 61 m AGL Use of the autopilot or manual electric trim system is prohibited before the satisfactory completion of the Pre flight procedure Autopil...

Page 429: ... ICAO Annex 10 for IFR en route terminal area precision and non precision approach operations The G1000 System meets the requirements for GPS GNSS as a Primary Means of Navigation for Oceanic Remote Operations RNP 10 per AC 20 138C FAA Notice N8110 60 FAA Order 8400 12C and FAA Order 8700 1 Both GPS GNSS receivers are required to be operating and receiving usable sig nals except for routes requiri...

Page 430: ...on Pilots and operators can view navigation data base alerts at www Garmin com In the Air NavData Alerts For flight planning purposes in areas where SBAS coverage is not available the pi lot must check RAIM availability Within Europe RAIM availability can be determined using the G1000 WFDE Pre diction program or Europe s AUGER GPS RAIM Prediction Tool at http augur ecacnav com augur app home This ...

Page 431: ...Navigation da tabase Pilots planning on flying an RNAV instrument approach must ensure that the Navigation database contains the planned RNAV Instrument Approach Procedure and that approach procedure must be loaded from the Navigation database into the FMS flight plan by its name The navigation equipment required to join and fly an instrument approach procedure is indicated by the title of the pro...

Page 432: ... reported on the basic AFM Section 3 Emergency Procedures According to A C configuration apply following pages replacement Supplement D07 EMERGENCY PROCEDURES page AFM Section 3 page APV 3 14 REPLACES 3 14 of basic AFM Section 3 APV 3 18 thru 19 REPLACES 3 18 thru 19 of basic AFM Section 3 APV 3A 31 thru 35 REPLACES Added at the end of Section 3 of basic AFM Supplement D07 pages replacement instru...

Page 433: ...Page D7 10 Ed 1 Rev 0 Section 9 Supplements Supplement no D07 GARMIN GFC700 AUTOPILOT AND VARIABLE PITCH PROPELLER EQUIPPED AEROPLANES INTENTIONALLY LEFT BLANK ...

Page 434: ...ver Decrease RPM 3 Mixture Lever As required 4 RPM indicator CHECK If it is not possible to decrease propeller rpm land as soon as possible ap plying Forced landing procedure See Para 11 6 4 IRREGULAR RPM 1 Fuel pump ON 2 Fuel quantity and pressure indicators CHECK 3 If necessary SWITCH TANK If engine continues to run irregularly Land as soon as possible Maximum propeller rpm exceedance may cause ...

Page 435: ...tive Throttle Control Cable If power is sufficient to continue flight 1 Approach nearest airfield control engine power with Propeller lever 2 Perform landing with shut down engine applying Forced landing procedure See Para 11 If power is not sufficient to continue flight 1 Carry out Forced landing procedure See Para 11 Defective Propeller Lever Control Cable If power is sufficient to continue flig...

Page 436: ...se of successful engine restart Land as soon as possible In case of engine shutdown propeller will keep windmilling and will not stop preventing the use of ignition key Engine inflight restart must be performed without using ignition key with propel ler windmilling in order to avoid possible engine damages Typical indication of a potential engine shutdown with windmill ing propeller will be RPM ru...

Page 437: ...WER if necessary to regain aircraft control 2 AP DISC TRIM INTR switch PRESS 3 AP MASTER SWITCH OFF 4 AP Circuit Breaker PULL In the event of autopilot malfunction or when the system is not per forming as expected or commanded take immediately the aircraft control disconnecting the autopilot which must be set inoperative until the failure has been identified and corrected Following an A P or MET s...

Page 438: ...tch apply following procedure 1 AP DISC TRIM INTR switch PRESS and HOLD 2 TRIM MASTER SWITCH OFF 3 TRIM Circuit Breaker PULL 4 AP DISC TRIM INTR switch RELEASE When Autopilot is disconnected because of a pitch trim malfunction hold the control wheel firmly When electric trim is disconnected it is necessary operate the pitch trim through the Trim Wheel When electric trim is disconnected Autopilot s...

Page 439: ...ol of the airplane Immediately grasp the control wheel and push and hold the A P DISC TRIM INT switch throughout the recovery Manipu late the controls as required to safely keep the airplane within all of its operating limitations Elevator trim should be used manually as needed to relieve control forces Switch the AP MASTER SWITCH to OFF and when time is available af ter aircraft recovery open pul...

Page 440: ...P can t be en gaged FD is operative in all modes A P can t be en gaged FD is operative in all modes A P can t be en gaged FD is operative in all modes NOTES MEPT Unavailable PTRM red on PFD NO VERT MODES on PFD PTRM C M red cross on MFD SYS page A P disconnect PTCH red annunciation on PFD NO VERT MODES on PFD ESP Fail on alert window PTCH C M red cross on MFD SYS page ROLL C M red cross on MFD SYS...

Page 441: ...D NOTES ON OFF ON A P reverts to PIT ROLL from any mode select ed No aurals from A P both A P DISC USP ON ON OFF A P stays in the selected mode A P control keyboard unavail able A P can be disconnected with A P DISC button on con trol wheel FD command bars cannot be eliminat ed ESP Off on alert window on PFD ON OFF ON OFF A P automatically disconnects after 4 to 5 se conds A P disconnection tone p...

Page 442: ...sic AFM Section 4 Normal Procedures According to A C configuration apply following pages replacement Supplement D07 NORMAL PROCEDURES page AFM Section 4 page APV 4 7 REPLACES 4 7 of basic AFM Section 4 APV 4 15 REPLACES 4 15 of basic AFM Section 4 APV 4 19 thru 26 REPLACES 4 19 thru 26 of basic AFM Section 4 APV 4 27 thru 38 REPLACES Added at the end of Section 4 of basic AFM Supplement D07 pages ...

Page 443: ...Section 9 Supplements Supplement no D07 GARMIN GFC700 AUTOPILOT AND VARIABLE PITCH PROPELLER EQUIPPED AEROPLANES Page D7 12 Ed 1 Rev 0 INTENTIONALLY LEFT BLANK ...

Page 444: ...ONS The following airspeeds are those which are significant for normal operations FLAPS 1160kg 2557lbs Rotation Speed VR T O 60 KIAS Best Angle of Climb Speed VX 0 75 KIAS Best Rate of Climb speed VY 0 82 KIAS Flaps VFE T O LAND 91 KIAS No flaps approach 0 80 KIAS Approach speed T O 75 KIAS Final Approach Speed FULL 70 KIAS Manoeuvring speed VA 0 120 KIAS Vglide 0 84 KIAS Never Exceed Speed VNE 0 ...

Page 445: ...ity indicators information with fuel quantity visually checked into the tanks see Pre flight inspection External inspection then update the Garmin fuel content in the totalizer accordingly The totalizer function available on Garmin Engine page allows input only up to 230lts maximum usable fuel Initial Fuel indication on totalizer must be corrected manually as it does not use the aircraft fuel quan...

Page 446: ...ing of the engine or a loss of performance The mixture may be adjusted to obtain smooth engine operations 8 Throttle set 1500 RPM a Alternate Air check Alternate Air PULL Check drop 50 100 RPM b Mixture check Mixture reduce EGT check increase FF check decrease Mixture FULL RICH 9 Throttle 2100 RPM 10 Propeller Lever Pull back until a drop of max 500 RPM is reached then high RPM Cycle 3 times 11 Ma...

Page 447: ...s to slowly reduce mixture lever until increase of appr ly 50 100 RPM is noticed at constant IAS or EGT reaches 1375 F mark 1 Pitot HEAT ON if required 2 Fuel pump ON 3 Brakes apply 4 Throttle FULL and check approximately 2680 20 RPM Engine proper performance at full throttle shall be checked early in the ground roll in order to abandon take off if necessary A rough engine sluggish RPM increase or...

Page 448: ...btain smooth engine operations Lean to maximum RPM at Full Throttle prior to take off where airports are at 5000ft density altitude or higher During climb a rough method of correctly leaning is to slowly reduce mixture lever until an increase of appr ly 50 100 RPM is noticed at constant IAS or EGT reaches 1375 F mark 1 Flaps UP minimum speed 73 KIAS Expect to adjust pitch trim pitch up when retrac...

Page 449: ...ccasion be moved slowly to fully RICH before throttle adjustment Care should always be taken that the cylinders do not cool down too quickly The cooling rate should not exceed 50 F per minute For maximum service life cylinder head temperature should be kept below 475 F high performance cruise and below 435 F for economy cruise Best Cruise Economy Mixture The best economy mixture setting may only b...

Page 450: ...emperature should not exceed 50 F per minute In order to ensure best practice and avoid potential illumination of ALT FAIL due to low propeller speed the following best practice should be observed Reducing power to maintain a minimum descent speed of 84 KIAS best glide and or a blade angle to maintain 850 RPM Opening the ALTER AIR command to full open to avoid ice accretion The maximum permissible...

Page 451: ...ver RICH 7 Propeller Lever HIGH RPM 8 Flaps LAND 9 Final Approach Speed set 10 ptimal touchdown speed 60 KIAS In conditions such as e g strong wind danger of windshear or turbulence a higher approach speed shall be selected 5 12 BALKED LANDING MISSED APPROACH 1 Throttle FULL 2 Speed keep over 80 KIAS climb to VY or VX as applicable 3 Flaps position T O Above a safe height 4 Propeller lever 2600 RP...

Page 452: ... 6 Mixture closed 7 Ignition key OFF key extracted 8 Strobe light OFF 9 Avionic Master OFF 10 Master Generator switches OFF 11 Fuel selector valve OFF For safety verify propeller is fully stopped before any other action Instruct passenger to fully open RH door and depart avoiding contact with wheels and sharp wing control surfaces edges 5 16 POSTFLIGHT CHECKS 1 Flight controls lock by means of sea...

Page 453: ...s in rain this applies particularly to take off distance and maxi mum Horizontal speed The effect on flight characteristics is minimal 5 18 REFUELLING Before refuelling the airplane must be connected to electrical ground 5 19 FLIGHT AT HIGH ALTITUDE At high altitudes the provision of oxygen for the occupant is necessary Legal require ments for the provision of oxygen should be adhered to see para ...

Page 454: ...IGHT CHECKS 1 MASTER SWITCH BAT ON 2 AVIONICS MASTER SWITCH ON 3 AUTOPILOT MASTER SWITCH ON 4 POWER APPLICATION and SELFCTEST The autopilot tests itself when power is first made available The test is a sequence of internal checks before starting normal system operation The test sequence is shown on PFD left upper corner by the red AFCS label followed by the white PFT label ending with double AP di...

Page 455: ...ervo en gagement disengagement Use the CWS Button to disengage the pitch and roll while the autopilot remains active HDG Pressing the HDG knob synchronizes the Selected Heading to the cur rent heading In this case expect a small heading overshoot that will be subsequently corrected VS MODE Selection of a vertical speed beyond the capability of the aircraft can create a condition of reduced airspee...

Page 456: ...g Mode become active ALTS is armed rather than ALTV Altitude preselect must show an altitude below the flight plan s Target Alti tude If the selected altitude is not at least 75 ft below the VNV Target Altitude the FD captures the Selected Altitude once Vertical Path Tracking Mode become active ALTS is armed rather than ALTV If VPTH is armed more than 5 minutes prior to descent path capture acknow...

Page 457: ...nd all other GPS related information e g wind will turn to yellow If GPS nave mode is being selected the HSI on the PFD will not display the deviation bar If GPS is selected as navigation source a AHRS1 GPS AHRS1 operating exclusively in no GPS mode CAS message will appear inside the alert window Dead Reckoning Mode only functions in Enroute ENR or Oceanic OCN phase of flight In all other phases a...

Page 458: ...avigation using GPS SBAS source data resumes automatically once a valid GPS so lution is restored As a result of operating in DR Mode all GPS derived data is computed based upon an estimated position and is displayed as yellow text on the display to denote de graded navigation source information Also while the G1000 is in DR Mode some terrain functions are not available Additionally the accuracy o...

Page 459: ...ded as an equipment function or from an alternative method acceptable to the Authority Where a navigation data base is installed the data base validity current AIRAC cycle should be checked before flight Traditional navigation equipment e g VOR DME and ADF should be selected to available aids so as to allow immediate cross checking or reversion in the event of loss of GPS navigation capability 1 P...

Page 460: ...the insertion in the flight plan of waypoints loaded from the database During the procedure and where feasible flight progress should be monitored for naviga tional reasonableness by cross checks with conventional navigation aids using the pri mary display 3 Arrival Prior to the arrival phase the flight crew should verify that the correct terminal proce dure has been loaded The active flight plan ...

Page 461: ...n not de pendent on GPS data and for which the weather is forecast to be suitable to enable a landing to be made from that approach or 2 There is at least one alternate destination within range where a different type of approach system is available which is not dependent on GPS data and for which the weather is forecast to be suitable to enable a landing to be made from that approach 9 1 APPROACH ...

Page 462: ...ppropri ate navigation receiver must be used for the selected approach e g VOR or ILS The final course segment of ILS approaches for example must be flown by tuning the NAV receiver to the proper frequency and selecting that NAV receiver on the CDI The G1000 SBAS GPS allows for flying LNAV LP LP V and LPV approach service levels according to the published chart The V designation adds advisory vert...

Page 463: ...vigation This is a Non Precision or 2D Approach with Lateral only navigation guidance provided by GNSS and an Aircraft Based Augmentation System ABAS Receiver Autonomous Integrity Monitoring RAIM is a form of ABAS Lateral guidance is linear with accu racy to within 0 3 NM parallel to either side of the final approach track LP Localiser Performance This is a Non Precision or 2D Approach with Latera...

Page 464: ...the system correctly past the MAP in order to follow the published MAP correctly Pilots should be fully competent in the necessary selection routines required by their own equipment in order to transition to the MAP and preserve accurate navigation throughout When GPS navigation is NOT available for the MAP it may be necessary to reset the dis play function of the HSI CDI to disengage GPS informat...

Page 465: ...oach should always be discontinued a If the receiver fails to engage the correct approach mode or b In case of Loss Of Integrity LOI monitoring or c Whenever the HSI CDI indication or GP indication where applicable ex ceeds half scale displacement or d If a RAIM or equivalent warning is activated or e If RAIM or equivalent function is not available and annunciated before passing the FAF ...

Page 466: ...OPELLER EQUIPPED AEROPLANES Ed 1 Rev 0 SECTION 5 PERFORMANCE Make sure you first applied instructions reported on the basic AFM Section 5 Performance According to A C configuration Supplement D02 Performances pages replace basic AFM Section 5 as whole Supplement D07 pages replacement instructions ...

Page 467: ...Page D7 14 Section 9 Supplements Supplement no D07 GARMIN GFC700 AUTOPILOT AND VARIABLE PITCH PROPELLER EQUIPPED AEROPLANES Ed 1 Rev 0 INTENTIONALLY LEFT BLANK ...

Page 468: ...5 PERFORMANCE INDEX 1 Introduction 2 2 Use of Performance Charts 2 3 Airspeed IndicatorSystemCalibration 3 4 ICAO Standard Atmosphere 5 5 Stall speed 6 6 Crosswind 7 7 Take Off performances 8 8 Take off Rate of Climb 11 9 En Route Rate of Climb 12 10 Cruise Performance 13 11 Landing performances 17 12 Balked Landing Performance 18 13 Noise Data 19 ...

Page 469: ...rcraft and engine in good condition average piloting techniques Each graph or table was determined according to ICAO Standard Atmos phere 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 2 USE OF PERFORMANCE CHARTS Performances data are presented in tabular or graphical form to illust...

Page 470: ...rce Graph shows calibrated airspeed VIAS as a function of indicated airspeed VCAS Fig 5 1 Calibrated vs Indicated Airspeed Example Given Find KIAS 75 0 Flap UP KCAS 74 7 Indicated airspeed assumes 0 as an instrument error 50 60 70 80 90 100 110 120 130 140 150 160 170 50 60 70 80 90 100 110 120 130 140 150 160 Indicated Airspeed KIAS Calibrated Airspeed KCAS Airspeed Indication System Calibration ...

Page 471: ...0 92 1020 92 1020 FLAP LND 60 62 1020 61 1020 61 1020 70 72 1020 72 1020 71 1020 90 92 1020 91 1020 91 1020 FLAP UP 5000 70 72 5020 72 5020 71 5020 90 94 5030 93 5020 92 5020 110 114 5030 113 5020 112 5020 133 137 5040 136 5030 135 5020 FLAP T O 60 62 5010 62 5020 61 5010 70 74 5020 73 5020 72 5020 90 93 5030 93 5020 93 5020 FLAP LND 60 63 5030 62 5020 61 5000 70 72 5020 72 5010 71 5010 90 92 5020...

Page 472: ...NES Page APV5 5 Section 5 Performance ICAO STANDARD ATMOSPHERE Ed 1 Rev 0 4 ICAO STANDARD ATMOSPHERE 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 473: ... IDLE CG Most Forward 19 No ground effect WEIGHT BANK ANGLE STALL SPEED FLAPS 0 FLAPS T O FLAPS FULL kg lb deg KIAS KCAS KIAS KCAS KIAS KCAS 1160 2557 FWD C G 0 59 60 53 55 50 52 15 60 61 54 56 51 53 30 64 65 58 59 54 56 45 71 71 64 65 61 62 60 85 85 77 78 73 74 Altitude loss during conventional stall recovery as demonstrated during flight tests is approximately 350 ft with banking below 15 NOTE ...

Page 474: ... AEROPLANES Page APV5 7 Section 5 Performance CROSSWIND Ed 1 Rev 0 6 CROSSWIND Maximum demonstrated crosswind is 12 kts Example Given Find Wind direction with respect to air craft longitudinal axis 30 Headwind 17 5 kts Wind speed 20 kts Crosswind 10 kts FIG 5 3 CROSSWIND CHART ...

Page 475: ...ound Roll 234 768 295 968 364 1194 442 1450 336 1102 At 50 ft AGL 421 1381 526 1726 644 2113 776 2546 595 1952 1000 Ground Roll 256 840 322 1056 397 1302 482 1581 360 1181 At 50 ft AGL 458 1503 572 1877 701 2300 844 2769 637 2090 2000 Ground Roll 279 915 352 1155 434 1424 526 1726 387 1270 At 50 ft AGL 499 1637 622 2041 762 2500 918 3012 682 2238 3000 Ground Roll 305 1001 384 1260 474 1555 575 188...

Page 476: ...At 50 ft AGL 342 1122 427 1401 523 1716 630 2067 483 1585 1000 Ground Roll 206 676 259 850 320 1050 388 1273 290 951 At 50 ft AGL 372 1220 464 1522 569 1867 685 2247 517 1696 2000 Ground Roll 225 738 283 928 349 1145 424 1391 311 1020 At 50 ft AGL 405 1329 505 1657 619 2031 745 2444 554 1818 3000 Ground Roll 246 807 309 1014 382 1253 463 1519 334 1096 At 50 ft AGL 441 1447 550 1804 674 2211 812 26...

Page 477: ...3 699 At 50 ft AGL 272 892 340 1115 416 1365 501 1644 384 1260 1000 Ground Roll 162 531 204 669 252 827 306 1004 229 751 At 50 ft AGL 296 971 369 1211 452 1483 545 1788 411 1348 2000 Ground Roll 177 581 223 732 275 902 334 1096 245 804 At 50 ft AGL 322 1056 402 1319 492 1614 593 1946 440 1444 3000 Ground Roll 194 636 244 801 301 988 365 1198 264 866 At 50 ft AGL 350 1148 438 1437 536 1759 645 2116...

Page 478: ...59 525 717 2000 71 848 684 538 406 617 4000 70 721 560 417 287 518 6000 69 596 437 296 169 419 8000 68 470 315 176 51 320 10000 67 345 193 56 67 221 12000 67 221 71 63 184 122 14000 66 96 51 182 300 23 1060 2337 S L 70 1118 943 787 647 848 2000 69 985 813 660 522 744 4000 69 853 684 533 397 640 6000 68 721 555 406 273 536 8000 68 589 426 280 149 431 10000 67 458 298 155 26 327 12000 66 327 170 29 ...

Page 479: ...841 2000 81 989 804 639 491 729 4000 80 846 665 503 357 618 6000 79 705 526 367 224 506 8000 78 563 388 232 91 394 10000 77 423 251 97 41 282 12000 76 282 113 37 173 171 14000 76 142 23 171 305 59 1060 2337 S L 82 1284 1085 907 747 976 2000 81 1133 937 762 605 857 4000 80 982 789 618 463 739 6000 79 831 642 474 322 621 8000 78 682 496 330 181 502 10000 77 532 350 187 40 384 12000 76 383 204 45 99 ...

Page 480: ... 9 85 127 15 4 58 3 81 128 14 9 56 4 24 79 120 14 7 55 6 75 121 14 1 53 4 71 121 13 6 51 5 22 69 113 13 3 50 3 65 113 12 8 48 5 62 113 12 4 46 9 20 59 105 11 9 45 56 104 11 5 43 5 53 103 11 1 42 2450 29 9 103 133 17 9 67 8 98 135 17 1 64 7 93 136 16 5 62 5 28 95 129 16 8 63 6 90 130 16 1 60 9 85 131 15 5 58 7 26 85 123 15 4 58 3 80 124 14 8 56 76 125 14 3 54 1 24 75 117 14 1 53 4 71 117 13 5 51 1 ...

Page 481: ... 22 76 128 14 3 54 1 70 120 13 5 51 1 67 120 13 49 2 2600 20 63 111 12 6 47 7 60 111 12 1 45 8 57 110 11 7 44 3 2600 18 53 101 11 1 42 50 99 10 7 40 5 47 97 10 4 39 4 2450 26 8 94 132 16 6 62 8 89 132 15 9 60 2 84 133 15 3 57 9 2450 26 90 129 16 1 60 9 85 129 15 4 58 3 81 130 14 8 56 2450 24 80 123 14 7 55 6 75 123 14 2 53 8 72 124 13 7 51 9 2450 22 70 116 13 5 51 1 66 116 12 9 48 8 63 117 12 5 47...

Page 482: ...20 68 117 13 2 50 64 117 12 7 48 1 61 117 12 3 46 6 2600 19 63 113 12 5 47 3 59 112 12 45 4 56 111 11 6 43 9 2600 18 57 108 11 7 44 3 54 106 11 3 42 8 51 104 10 9 41 3 2450 23 9 85 129 15 4 58 3 80 130 14 8 56 76 131 14 2 53 8 2450 23 80 126 14 8 56 75 127 14 2 53 8 72 127 13 7 51 9 2450 22 75 123 14 1 53 4 71 123 13 6 51 5 67 123 13 1 49 6 2450 20 64 114 12 7 48 1 61 114 12 2 46 2 58 113 11 8 44 ...

Page 483: ...7 13 2 50 2450 20 69 121 13 3 50 3 65 121 12 8 48 5 62 119 12 3 46 6 2450 19 64 116 12 6 47 7 60 115 12 1 45 8 57 114 11 7 44 3 2450 18 59 111 11 9 45 55 109 11 4 43 2 52 106 11 1 42 2350 19 66 121 12 9 48 8 62 120 12 4 46 9 59 117 11 9 45 2350 18 60 115 12 2 46 2 57 113 11 7 44 3 54 110 11 3 42 8 Weight 1160 kg Mixture FULL RICH Pressure Altitude 12000 ft Corrections Best Power 10 to Full Rich F ...

Page 484: ...l 204 669 225 738 245 804 266 873 237 778 At 50 ft AGL 488 1601 509 1670 529 1736 550 1804 521 1709 1000 Ground Roll 212 696 233 764 254 833 276 906 244 801 At 50 ft AGL 496 1627 517 1696 538 1765 560 1837 528 1732 2000 Ground Roll 220 722 242 794 264 866 286 938 251 823 At 50 ft AGL 504 1654 526 1726 548 1798 570 1870 535 1755 3000 Ground Roll 228 748 251 823 274 899 297 974 259 850 At 50 ft AGL ...

Page 485: ...5 0 25 50 1160 2557 S L 10 9 8 6 6 6 4 7 7 4 1000 10 0 7 8 5 7 3 9 6 7 2000 9 2 6 9 4 9 3 1 6 0 3000 8 3 6 1 4 1 2 3 5 3 4000 7 4 5 2 3 2 1 4 4 6 5000 6 6 4 4 2 4 0 6 3 9 6000 5 7 3 5 1 6 0 2 3 3 7000 4 8 2 7 0 7 1 0 2 6 1060 2337 S L 12 9 10 4 8 1 6 1 9 0 1000 11 9 9 4 7 2 5 2 8 3 2000 11 0 8 5 6 3 4 3 7 5 3000 10 0 7 6 5 4 3 4 6 8 4000 9 1 6 7 4 5 2 5 6 0 5000 8 1 5 7 3 6 1 7 5 3 6000 7 2 4 8 2 ...

Page 486: ...0 13 NOISE DATA Noise level determined in accordance with ICAO Annex 16 6th Ed July 2011 Vol I Chapter 10 and 14 CFR 36 1581 c is 80 58 dB A No determination has been made by the Federal Aviation Admin istration that the noise levels of this aircraft are or should be ac ceptable or unacceptable for operation at into or out of any air port NOTE ...

Page 487: ...AFMS N D07 FOR GARMIN GFC700 AUTOPILOT AND VARIABLE PITCH PROPELLER EQUIPPED AEROPLANES Page APV5 20 Section 5 Performance NOISE DATA Ed 1 Rev 0 INTENTIONALLY LEFT BLANK ...

Page 488: ...ts Supplement no D07 GARMIN GFC700 AUTOPILOT AND VARIABLE PITCH PROPELLER EQUIPPED AEROPLANES Ed 1 Rev 0 SECTION 6 WEIGHT AND BALANCE Refer to the basic AFM Section 6 Weight and Balance Supplement D07 pages replacement instructions ...

Page 489: ...Page D7 17 Section 9 Supplements Supplement no D07 GARMIN GFC700 AUTOPILOT AND VARIABLE PITCH PROPELLER EQUIPPED AEROPLANES Ed 1 Rev 0 INTENTIONALLY LEFT BLANK ...

Page 490: ... According to A C configuration apply following pages replacement Supplement D07 AIRFRAME AND SYSTEMS DESCRIPTION page AFM Section 7 page APV 7 8 thru 11 REPLACES 7 8 thru 11 of basic AFM Section 7 APV 7 16 REPLACES 7 16 of basic AFM Section 7 APV 7 20 thru 21 REPLACES 7 20 thru 21 of basic AFM Section 7 APV 7 27 REPLACES 7 27 of basic AFM Section 7 APV 7 33 REPLACES 7 33 of basic AFM Section 7 AP...

Page 491: ...Page D7 19 Section 9 Supplements Supplement no D07 GARMIN GFC700 AUTOPILOT AND VARIABLE PITCH PROPELLER EQUIPPED AEROPLANES Ed 1 Rev 0 INTENTIONALLY LEFT BLANK ...

Page 492: ...a switch on the instrument panel Flaps act in continuous mode the indicator displays three markings related to 0 takeoff T O and landing FULL positions A breaker positioned on the right side of the instrument panel protects the electric circuit The control of the stabilator trim is operated by means of both a control wheel located be tween the two front seats that acts directly on the control cabl...

Page 493: ...Central area holds the standby unit for PFI parameters MD 302 suite and the ELT button The right area holds Garmin G1000 MFD with dedicated AP control buttons and breaker panel The lower LH portion of the instrument panel holds Ignition key Master and Generator switches Emergency fuel pump Avionic Master switch AP Master switch Trim Disconnect switch The lower Central portion of the instrument pan...

Page 494: ...the mixture control lever is pulled to the rear stop air with out fuel is drawn into the cylinders that shuts down Throttle This lever left hand with large knob is used to control manifold pressure MAP High manifold pressure means a large quantity of fuel air mixture is being sup plied to engine while low manifold pressure means a lesser quantity of fuel air mixture is being supplied Propeller lev...

Page 495: ...ctors receive maximum hot air During normal opera tion the knob is set in OFF position 4 3 DEFROST AND CABIN HEAT Two knobs located on the lower side of the central pedestal allow Defrost and Cabin Heat function The one marked as Defrost and Cabin Heat allows hot air to perform wind shield defrost and partially cabin heat The cabin heat control knob when fully outward allows cabin to receive maxim...

Page 496: ...ust outlets Maximum power 134 0 kW 180hp 2700 rpm Maximum continuous power 129 2 kW 173 3hp 2600 rpm Oil Consumption Operation RPM HP Max Oil Cons Qts Hr Max Cyl Head Temp Normal Rated 2700 180 80 500 F 260 C Performance Cruise 75 2450 135 45 500 F 260 C Economy Cruise 60R Rated 2350 117 39 500 F 260 C 7 2 PROPELLER Manufacturer MT Propeller Model MTV 15 B 193 52 Type Certificate EASA TCDS no P 09...

Page 497: ...lternator failure The switch between the energy sources is automatic and no action is required in order to ac tivate the alternate energy source For ground maintenance and or starting an external power socket is provided The alternator and battery are connected to the battery bus in order to provide energy for the electric equipment Each electrically fed instrument is connected to a dedicated circ...

Page 498: ...ev 0 Section 7 Airframe and Systems description ELECTRICAL SYSTEM FIG 7 15 ELECTRICAL SYSTEM ARCHITECTURE 12 3 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 warning horn located near the instru ment panel ...

Page 499: ...four map lights two in the front area pilot and two in the rear area passengers In the central area of the cabin ceiling is located a spot light used to illuminate the pedestal during night flight operations All ceiling lights are dimmable by a dedicated dimmer FWD FIG 7 18 CABIN CEILING LIGHTS LAYOUT The instrument panel can be illuminated by 8 incandescence light strips all dimmable FIG 7 19 INS...

Page 500: ...N D07 FOR GARMIN GFC700 AUTOPILOT AND VARIABLE PITCH PROPELLER EQUIPPED AEROPLANES Page APV 7 33 Ed 1Rev 0 Section 7 Airframe and Systems description PLACARDS ELT unit position placard Breaker Panel placards ...

Page 501: ...AFMS N D07 FOR GARMIN GFC700 AUTOPILOT AND VARIABLE PITCH PROPELLER EQUIPPED AEROPLANES Page APV 7 36 Ed 1Rev 0 Section 7 Airframe and Systems description PLACARDS Pedestal placards ...

Page 502: ...TCH PROPELLER EQUIPPED AEROPLANES SECTION 8 GROUND HANDLING SERVICE Make sure you first applied instructions reported on the basic AFM Section 8 Ground Handling Service According to A C configuration refer to the basic AFM Section 8 Ground Handling Service Supplement D07 pages replacement instructions ...

Page 503: ...Page D07 21 Ed 1Rev 0 Section 9 Supplements Supplement no D07 GARMIN GFC700 AUTOPILOT AND VARIABLE PITCH PROPELLER EQUIPPED AEROPLANES INTENTIONALLY LEFT BLANK ...

Page 504: ...ffective Pages Page Revision Cover Pages D08 1 thru 22 Rev 0 Section 1 GV 1 6 Rev 0 Section 2 GV 2 7 GV 2 9 thru 10 GV 2 13 Rev 0 Section 3 GV 3 5 thru 7 GV 3 10 GV 3 14 GV 3 16 thru 19 GV 3 25 Rev 0 Section 4 GV 4 4 thru 5 GV 4 7 GV 4 9 GV 4 15 thru 26 Rev 0 Section 5 GV 5 1 thru 19 Rev 0 Section 7 GV 7 8 thru 11 GV 7 16 GV 7 20 thru 24 GV 7 27 GV 7 36 Rev 0 Section 9 Supplements Supplement n D08...

Page 505: ... 10 Section 4 NORMAL PROCEDURES 12 Section 5 PERFORMANCES 14 Section 6 WEIGHT AND BALANCE 19 Section 7 AIRFRAME AND SYSTEMS DESCRIPTION 20 Section 8 GROUND HANDLING SERVICE 21 Section 9 Supplements Supplement n D08 ALTERNATIVE AVIONICS CONFIGURATION AND VARIABLE PITCH PROPELLER EQUIPPED AIRPLANES Ed 1 Rev 0 ...

Page 506: ...lacing the AFM pages containing information amended as per Garmin G500 and variable pitch propeller in subject It is the owner s responsibility to replace the mentioned pages in accordance with the instructions herein addressed section by section Section 9 Supplements Supplement n D08 ALTERNATIVE AVIONICS CONFIGURATION AND VARIABLE PITCH PROPELLER EQUIPPED AIRPLANES Ed 1 Rev 0 ...

Page 507: ...Page D08 4 INTENTIONALLY LEFT BLANK Section 9 Supplements Supplement n D08 ALTERNATIVE AVIONICS CONFIGURATION AND VARIABLE PITCH PROPELLER EQUIPPED AIRPLANES Ed 1 Rev 0 ...

Page 508: ...C configuration apply following pages replacement Supplement D08 LIMITATIONS page AFM Section 1 page GV 1 6 REPLACES Page 1 6 of basic AFM Section 1 Supplement D08 pages replacement instructions Section 9 Supplements Supplement n D08 ALTERNATIVE AVIONICS CONFIGURATION AND VARIABLE PITCH PROPELLER EQUIPPED AIRPLANES Ed 1 Rev 0 ...

Page 509: ...Page D08 6 INTENTIONALLY LEFT BLANK Section 9 Supplements Supplement n D08 ALTERNATIVE AVIONICS CONFIGURATION AND VARIABLE PITCH PROPELLER EQUIPPED AIRPLANES Ed 1 Rev 0 ...

Page 510: ...ontally opposed air cooled with down exhaust outlets Maximum power Maximum continuous power 134 0 kW 180 hp 2700 rpm 129 2 kW 173 3 hp 2600 rpm 6 PROPELLER Manufacturer MT Propeller Model MTV 15 B 193 52 Type Certificate EASA TCDS no P 098 Blades hub wood composite 2 blades aluminum hub Diameter 1930 mm 76 in no reduction is permitted Type Variable pitch Governor Manufacturer MT Propeller Model P ...

Page 511: ...Page D08 7 INTENTIONALLY LEFT BLANK Section 9 Supplements Supplement n D08 ALTERNATIVE AVIONICS CONFIGURATION AND VARIABLE PITCH PROPELLER EQUIPPED AIRPLANES Ed 1 Rev 0 ...

Page 512: ...plement D08 LIMITATIONS page AFM Section 2 page GV 2 7 REPLACES Page 2 7 of basic AFM Section 2 GV 2 9 thru 10 REPLACE Pages 2 9 thru 10 of basic AFM Section 2 GV 2 13 REPLACES Page 2 13 of basic AFM Section 2 Supplement D08 pages replacement instructions Section 9 Supplements Supplement n D08 ALTERNATIVE AVIONICS CONFIGURATION AND VARIABLE PITCH PROPELLER EQUIPPED AIRPLANES Ed 1 Rev 0 ...

Page 513: ...Page D08 9 INTENTIONALLY LEFT BLANK Section 9 Supplements Supplement n D08 ALTERNATIVE AVIONICS CONFIGURATION AND VARIABLE PITCH PROPELLER EQUIPPED AIRPLANES Ed 1 Rev 0 ...

Page 514: ...MODEL IO 360 M1A MAXIMUM POWER Max Power hp Max rpm Prop rpm Max T O 180 2700 Max Cont 173 3 2600 Temperatures Max CHT 500 F 260 C Max Oil 245 F 118 C Oil Pressure Minimum Idling 25 psi 1 7 Bar Minimum Normal 55 psi 3 8 Bar Maximum Normal 95 psi 6 5 Bar Starting Warm up taxi and take off Max 115 psi 7 9 Bar Fuel pressure At Inlet to fuel injector Minimum 14 psi 0 96 Bar Maximum 35 psi 2 41 Bar Sec...

Page 515: ...or spe cific paint requirements 8 PROPELLER MANUFACTURER MT Propeller MODEL MTV 15B 193 52 TYPE wood composite 2 blade variable pitch DIAMETER 1930 mm 76in no reduction is permitted 9 MAXIMUM OPERATING ALTITUDE Maximum operating altitude is 12000 ft 3658 m MSL CAUTION At altitudes above 10000 ft 3048 m up to and including 12000 ft 3658 m flight crew is recommended to use supplemental oxygen 10 AMB...

Page 516: ...ER RPM 950 2600 0 950 2600 2700 2700 line OIL TEMP F 140 245 0 140 245 255 CHT F 435 line 150 475 0 150 475 500 500 510 EGT F 1000 1500 1375 line 1500 1550 OIL PRESS psi 0 25 55 95 25 55 95 115 115 125 FUEL PRESS psi 0 14 14 35 35 40 FUEL QTY litres 0 0 115 gal 0 0 30 4 FUEL FLOW l hr 0 75 gal hr 0 20 12 OTHER INSTRUMENT MARKINGS INSTRUMENT RED ARC Minimum limit GREEN ARC Safe operation YELLOW ARC...

Page 517: ...t Note External Power Circuit Breakers As Required Battery Safety Equipment Furnishing First Aid kit Fire extinguisher ELT Torch with spare batt Ice Protection Pitot heating system Landing Gear Wheel pants Removable Lights Landing taxi lights Strobe lights NAV lights Cabin lights Instrument lights Emergency light Dimming Devices Day Night switch COM Navigation Engine parameters Magnetic compass GA...

Page 518: ...age GV 3 5 thru 7 REPLACE Pages 3 5 thru 7 of basic AFM Section 3 GV 3 10 REPLACES Page 3 10 of basic AFM Section 3 GV 3 14 REPLACES Page 3 14 of basic AFM Section 3 GV 3 16 thru 19 REPLACE Pages 3 16 thru 19 of basic AFM Section 3 GV 3 25 REPLACES Page 3 25 of basic AFM Section 3 Supplement D08 pages replacement instructions Ed 1 Rev 0 Section 9 Supplements Supplement n D08 ALTERNATIVE AVIONICS C...

Page 519: ...Page D08 11 INTENTIONALLY LEFT BLANK Ed 1 Rev 0 Section 9 Supplements Supplement n D08 ALTERNATIVE AVIONICS CONFIGURATION AND VARIABLE PITCH PROPELLER EQUIPPED AIRPLANES ...

Page 520: ... pertinent device is turned ON AMBER to indicate no hazard situations which have to be considered and which require a proper crew action RED to indicate emergency conditions WHITE to indicate advisory messages 2 1ALTERNATOR FAILURE If ALT FAIL caution is ON 1 Circuit breaker s Check 2 Generator SWITCH OFF 3 Generator SWITCH ON If ALT FAIL CAUTION REMAINS on 4 Generator SWITCH OFF A fully charged b...

Page 521: ...that the Pitot Heating system is functioning properly If the amber PITOT HEAT caution light is ON when the green PITOT HEAT ON light is on then the Pitot Heating system is not functioning proper ly In this case apply following procedure 1 Pitot heat switch OFF 2 Pitot heat circuit breaker CHECK IN 3 Pitot heat switch ON 4 PITOT HEAT caution light CHECK if the amber light stays ON avoid visible moi...

Page 522: ...cases the red X annunciation is accompanied by a message advisory alert issuing a flashing ADVISORY Softkey annunciation which once selected acknowledges the presence of the message advisory alert and displays the alert text message in the Alerts Window 3 2LOSS OF AIRSPEED INFORMATION AIRSPEED FAIL RED X ON DISPLAY FIELD Display system is not receiving airspeed input from Air Data Computer INSTRUC...

Page 523: ...TITY LEFT If fuel quantity LH is under 24 litres 1 Fuel tank selector Switch to RH fuel tank 3 9LOW FUEL QUANTITY RIGHT If fuel quantity RH is under 24 litres 1 Fuel tank selector Switch to LH fuel tank 3 10 LOW FUEL QUANTITY LEFT AND RIGHT If fuel quantity LH and RH is under 24 litres 1 Land as soon as practical land at the nearest approved landing area where suitable repairs can be made Section ...

Page 524: ...ECK If it is not possible to decrease propeller rpm land as soon as possible applying Forced landing procedure See Para 11 CAUTION Maximum propeller rpm exceedance may cause engine components damage Monitor engine RPM overspeed shall be prevented by retarding propeller lever 6 4IRREGULAR RPM 1 Fuel pump ON 2 Fuel quantity and pressure indicators CHECK 3 If necessary SWITCH TANK If engine continues...

Page 525: ...ds limits Reduce engine power to minimum required Land as soon as possible applying Forced landing procedure See Para 11 Be prepared for engine failure and emergency landing If oil pressure tends to zero combined with vibration loss of oil unusual metallic smoke and noise Apply Forced landing procedure See Para 11 HIGH OIL PRESSURE If oil pressure exceeds upper limit 115 psi 1 Throttle Lever first...

Page 526: ... Fuel quantity CHECK If fuel pressure doesn t build up 1 Land as soon as practical Prepare for potential engine failure and prepare to apply Forced landing procedure See Para 11 6 9HIGH FUEL PRESSURE If fuel pressure increases above the upper limit 35 psi 1 Land as soon as possible Prepare for potential engine shut down and apply Forced landing procedure See Para 11 Possible injector failure or ob...

Page 527: ...If power is sufficient to continue flight 1 Approach nearest airfield control engine power with Propeller lever 2 Perform landing with shut down engine applying Forced landing proce dure See Para 11 If power is not sufficient to continue flight 1 Carry out Forced landing procedure See Para 11 Defective Propeller Lever Control Cable If power is sufficient to continue flight 1 Approach nearest airfi...

Page 528: ...engine instrument OIL Pressure CHT EGT running down abnormally Inflight engine restart may be performed during 1g flight anywhere within the normal operating envelope of the airplane 1 Master switch Check ON 2 Fuel pump ON 3 Fuel quantity indicator CHECK 4 Fuel Selector SWITCH TANK 5 Throttle Lever Minimum 1cm above IDLE 6 Propeller Lever Full forward 7 Mixture FULL rich 8 Throttle lever SET as re...

Page 529: ... lost Flaps extension and retraction will be lost apply Flaps control failure procedure See Para 10 6 Strobe and landing lights will be lost NAV and taxi lights are still available taxi light will be the only visual aid for landing in night conditions 10 2 LOSS OF MAIN BUS In case of loss of main bus the main bus voltage will drop to zero The following will be lost related breakers are listed AUDI...

Page 530: ...ES page AFM Section 4 page GV 4 4 thru 5 REPLACE Pages 4 4 thru 5 of basic AFM Section 4 GV 4 7 REPLACES Page 4 7 of basic AFM Section 4 GV 4 9 REPLACES Page 4 9 of basic AFM Section 4 GV 4 15 thru 26 REPLACE Pages 4 15 thru 26 of basic AFM Section 4 Supplement D08 pages replacement instructions Ed 1 Rev 0 Section 9 Supplements Supplement n D08 ALTERNATIVE AVIONICS CONFIGURATION AND VARIABLE PITCH...

Page 531: ...Page D08 13 INTENTIONALLY LEFT BLANK Ed 1 Rev 0 Section 9 Supplements Supplement n D08 ALTERNATIVE AVIONICS CONFIGURATION AND VARIABLE PITCH PROPELLER EQUIPPED AIRPLANES ...

Page 532: ...ining it s strongly recommended using the avionic suite in IFR with incremental steps after initial basic IFR instruction 1 Initial use of a single radio aids No GPS 2 Use of two radio aids No GPS 3 Use of GPS for point to point navigation No approaches 4 Use of VNAV feature 5 Full use of avionic suite The flight training syllabus for IFR instruction will need to address this incre mental approach...

Page 533: ...se already present in the G500 manu al shall be observed Use of GPS for precision approach navigation mode is not allowed Use of GPS is prohibited as primary means for navigation GPS is approved as sup plemental means for navigation Use of GPS is prohibited for IFR in terminal area or in non precision approach op erations If Receiver Autonomous Integrity Monitoring RAIM function becomes una vailab...

Page 534: ...60kg 2557lbs Rotation Speed VR T O 60 KIAS Best Angle of Climb Speed VX T O 65 KIAS Best Angle of Climb Speed VX 0 75 KIAS Best Rate of Climb speed VY 0 82 KIAS Flaps VFE T O LAND 91 KIAS No flaps approach 0 80 KIAS Approach speed T O 75 KIAS Final Approach Speed FULL 70 KIAS Manoeuvring speed VA 0 120 KIAS V glide 0 84 KIAS Never Exceed Speed VNE 0 166 KIAS Section 4 Normal procedures AIRSPEED FO...

Page 535: ...ate Radio COM certificate AFM check current and on board 2 Weight and balance calculate ref to Section 6 and check within limits 3 Breaker all IN 4 Safety belts connected to hard points check condition 5 Ignition key OFF key extracted 6 Master switch ON 7 Voltmeter check within the limits 8 Lights all ON check for operation 9 Annunciator panel check all lights 10 Acoustic stall warning check for o...

Page 536: ...ction External inspection then update the EDM930 fuel con tent in the totalizer accordingly The totalizer function available on EDM930 Engine page allows input only up to 230lts maximum usable fuel Initial Fuel indication on totalizer must be corrected manually as it does not use the aircraft fuel quantity indicators as input Once correctly initial ized fuel consumption on totalizer is very precis...

Page 537: ...perating the starter motor let it cool off for 20 seconds After 6 attempts to start the engine let the starter cool off for half an hour 6 Ignition key BOTH 7 Ignition key START When engine start turning and first indication of a starting condition exist 8 Mixture rapidly move to FULL RICH 9 Throttle set 1000 1200 RPM 10 Check oil pressure rises within 10 sec 11 Check OIL PRESSURE LOW extinguished...

Page 538: ...conds After 6 attempts to start the engine let the starter cool off for half an hour 5 Ignition key BOTH 6 Ignition key START When engine start turning and first indication of a starting condition exist 7 Mixture rapidly move to FULL RICH 8 Throttle set 1000 1200 RPM 9 Check oil pressure rises within 10 sec 10 Check OIL PRESSURE LOW extinguished 11 Electric fuel pump OFF 12 Check fuel pressure wit...

Page 539: ... battery minimise annunciator nuisance and assure maximum battery performance during flight Furthermore this is particularly true dur ing cold weather to prevent lead fouling of spark plugs CAUTION Following extended operation on the ground or at high ambient temperatures the following indications of fuel vapor lock may appear Arbitrary changes in idle RPM and fuel flow Slow reaction of the engine...

Page 540: ...ure may be adjusted to obtain smooth engine operations 8 Throttle set 1500 RPM a Alternate Air check Alternate Air PULL Check drop 50 100 RPM b Mixture check Mixture reduce EGT check increase FF check decrease Mixture FULL RICH 9 Throttle 2100 RPM 10 Propeller Lever Pull back until a drop of max 500 RPM is reached then high RPM Cycle 3 times 11 Magneto Check L BOTH R BOTH Max RPM drop 175 RPM Max ...

Page 541: ...f appr ly 50 100 RPM is noticed at constant IAS or EGT reaches 1375 F mark 1 Pitot HEAT ON if required 2 Fuel pump ON 3 Brakes apply 4 Throttle FULL and check approximately 2680 20 RPM WARNING Engine proper performance at full throttle shall be checked early in the ground roll in order to abandon tak off if necessary A rough engine sluggish RPM increase or failure to reach take off RPM are reasons...

Page 542: ...rottle prior to take off where airports are at 5000ft density altitude or higher During climb a rough method of correctly leaning is to slowly reduce mixture lever until an increase of appr ly 50 100 RPM is noticed at constant IAS or EGT reaches 1375 F mark 1 Flaps UP minimum speed 73 KIAS Expect to adjust pitch trim pitch up when retracting flaps after take off 2 Establish climb Vy 82 KIAS 3 Elec...

Page 543: ...le adjustment Care should always be taken that the cylinders do not cool down too quickly The cooling rate should not exceed 50 F per minute For maximum service life cylinder head temperature should be kept below 475 F high performance cruise and below 435 F for economy cruise Best Cruise Economy Mixture The best economy mixture setting may only be used up to a power setting of 75 In order to obta...

Page 544: ...sure best practice and avoid potential illumination of ALT FAIL due to low propeller speed the following best practice should be observed Reducing power to maintain a minimum descent speed of 84 KIAS best glide and or a blade angle to maintain 850 RPM Opening the ALTER AIR command to full open to avoid ice accretion CAUTION The maximum permissible cylinder head temperature 500 F must never be exce...

Page 545: ...h Speed set 10 Optimal touchdown speed 60 KIAS CAUTION In conditions such as e g strong wind danger of windshear or turbulence a higher approach speed shall be selected 5 12 BALKED LANDING MISSED APPROACH 1 Throttle FULL 2 Speed keep over 80 KIAS climb to VY or VX as applicable 3 Flaps position T O Above a safe height 4 Propeller lever 2600 RPM 5 Landing lights OFF 5 13 GO AROUND 1 Throttle FULL 2...

Page 546: ...obe light OFF 9 Avionic Master OFF 10 Master Generator switches OFF 11 Fuel selector valve OFF WARNING For safety verify propeller is fully stopped before any other action CAUTION Instruct passenger to fully open RH door and depart avoiding contact with wheels and sharp wing control surfaces edges 5 16 POSTFLIGHT CHECKS 1 Flight controls lock by means of seat belts 2 Wheel chocks and wing mooring ...

Page 547: ...distance and maximum Horizontal speed The effect on flight characteristics is minimal 5 18 REFUELLING Before refuelling the airplane must be connected to electrical ground 5 19 FLIGHT AT HIGH ALTITUDE At high altitudes the provision of oxygen for the occupant is necessary Legal requirements for the provision of oxygen should be adhered to see para 2 9 Section 4 Normal procedures CHECKLISTS Ed 1 Re...

Page 548: ...ment D08 Performances pages replace basic AFM Section 5 as whole Supplement D08 pages replacement instructions Section 9 Supplements Supplement n D08 ALTERNATIVE AVIONICS CONFIGURATION AND VARIABLE PITCH PROPELLER EQUIPPED AIRPLANES Ed 1 Rev 0 ...

Page 549: ...Page D08 15 INTENTIONALLY LEFT BLANK Section 9 Supplements Supplement n D08 ALTERNATIVE AVIONICS CONFIGURATION AND VARIABLE PITCH PROPELLER EQUIPPED AIRPLANES Ed 1 Rev 0 ...

Page 550: ... 2 Use of Performance Charts 2 3 Airspeed Indicator System Calibration 3 4 ICAO Standard Atmosphere 5 5 Stall speed 6 6 Crosswind 7 7 Take Off performances 8 8 Take off Rate of Climb 11 9 En Route Rate of Climb 12 10 Cruise Performance 13 11 Landing performances 17 12 Balked Landing Performance 18 13 Noise Data 19 Section 5 Performances INDEX Ed 1 Rev 0 ...

Page 551: ... 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 theo retical means for Airspeed External temperature Altitude Weight Runway type and condition 2 USE OF PERFORMANCE CHARTS Performances data are presented in tabular or graphical form to illustrate the ef fect of different variables suc...

Page 552: ... airspeed VCAS Fig 5 1 Calibrated vs Indicated Airspeed Example Given Find KIAS 75 0 Flap UP KCAS 74 7 Indicated airspeed assumes 0 as an instrument error 50 60 70 80 90 100 110 120 130 140 150 160 170 50 60 70 80 90 100 110 120 130 140 150 160 Indicated Airspeed KIAS Calibrated Airspeed KCAS Airspeed Indication System Calibration Flap UP Flap T O Flap LN NOTE Section 5 Performances AIRSPEED INDIC...

Page 553: ... 1020 71 1020 90 92 1020 91 1020 91 1020 FLAP UP 5000 70 72 5020 72 5020 71 5020 90 94 5030 93 5020 92 5020 110 114 5030 113 5020 112 5020 133 137 5040 136 5030 135 5020 FLAP T O 60 62 5010 62 5020 61 5010 70 74 5020 73 5020 72 5020 90 93 5030 93 5020 93 5020 FLAP LND 60 63 5030 62 5020 61 5000 70 72 5020 72 5010 71 5010 90 92 5020 92 5020 91 5010 FLAP UP 8000 70 72 8020 72 8020 71 8020 90 93 8030...

Page 554: ...age GV 5 5 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 Section 5 Performances ICAO STANDARD ATMOSPHERE Ed 1 Rev 0 ...

Page 555: ... WEIGHT BANK ANGLE STALL SPEED FLAPS 0 FLAPS T O FLAPS FULL kg lb deg KIAS KCAS KIAS KCAS KIAS KCAS 1160 2557 FWD C G 0 59 60 53 55 50 52 15 60 61 54 56 51 53 30 64 65 58 59 54 56 45 71 71 64 65 61 62 60 85 85 77 78 73 74 Altitude loss during conventional stall recovery as demonstrated during flight tests is approximately 350 ft with banking below 15 NOTE Section 5 Performances STALL SPEED Ed 1 Re...

Page 556: ...IPPED AIRPLANES Page GV 5 7 6 CROSSWIND Maximum demonstrated crosswind is 12 kts Example Given Find Wind direction with respect to air craft longitudinal axis 30 Headwind 17 5 kts Wind speed 20 kts Crosswind 10 kts FIG 5 3 CROSSWIND CHART Section 5 Performances CROSSWIND Ed 1 Rev 0 ...

Page 557: ...2 At 50 ft AGL 421 1381 526 1726 644 2113 776 2546 595 1952 1000 Ground Roll 256 840 322 1056 397 1302 482 1581 360 1181 At 50 ft AGL 458 1503 572 1877 701 2300 844 2769 637 2090 2000 Ground Roll 279 915 352 1155 434 1424 526 1726 387 1270 At 50 ft AGL 499 1637 622 2041 762 2500 918 3012 682 2238 3000 Ground Roll 305 1001 384 1260 474 1555 575 1886 415 1362 At 50 ft AGL 543 1781 678 2224 830 2723 ...

Page 558: ...3 1585 1000 Ground Roll 206 676 259 850 320 1050 388 1273 290 951 At 50 ft AGL 372 1220 464 1522 569 1867 685 2247 517 1696 2000 Ground Roll 225 738 283 928 349 1145 424 1391 311 1020 At 50 ft AGL 405 1329 505 1657 619 2031 745 2444 554 1818 3000 Ground Roll 246 807 309 1014 382 1253 463 1519 334 1096 At 50 ft AGL 441 1447 550 1804 674 2211 812 2664 593 1946 4000 Ground Roll 268 879 338 1109 417 1...

Page 559: ...44 384 1260 1000 Ground Roll 162 531 204 669 252 827 306 1004 229 751 At 50 ft AGL 296 971 369 1211 452 1483 545 1788 411 1348 2000 Ground Roll 177 581 223 732 275 902 334 1096 245 804 At 50 ft AGL 322 1056 402 1319 492 1614 593 1946 440 1444 3000 Ground Roll 194 636 244 801 301 988 365 1198 264 866 At 50 ft AGL 350 1148 438 1437 536 1759 645 2116 472 1549 4000 Ground Roll 212 696 266 873 329 1079...

Page 560: ...60 417 287 518 6000 69 596 437 296 169 419 8000 68 470 315 176 51 320 10000 67 345 193 56 67 221 12000 67 221 71 63 184 122 14000 66 96 51 182 300 23 1060 2337 S L 70 1118 943 787 647 848 2000 69 985 813 660 522 744 4000 69 853 684 533 397 640 6000 68 721 555 406 273 536 8000 68 589 426 280 149 431 10000 67 458 298 155 26 327 12000 66 327 170 29 97 223 14000 66 197 43 95 220 119 960 2116 S L 69 12...

Page 561: ...357 618 6000 79 705 526 367 224 506 8000 78 563 388 232 91 394 10000 77 423 251 97 41 282 12000 76 282 113 37 173 171 14000 76 142 23 171 305 59 1060 2337 S L 82 1284 1085 907 747 976 2000 81 1133 937 762 605 857 4000 80 982 789 618 463 739 6000 79 831 642 474 322 621 8000 78 682 496 330 181 502 10000 77 532 350 187 40 384 12000 76 383 204 45 99 265 14000 75 235 59 97 239 147 960 2116 S L 81 1465 ...

Page 562: ...4 7 55 6 75 121 14 1 53 4 71 121 13 6 51 5 22 69 113 13 3 50 3 65 113 12 8 48 5 62 113 12 4 46 9 20 59 105 11 9 45 56 104 11 5 43 5 53 103 11 1 42 2450 29 9 103 133 17 9 67 8 98 135 17 1 64 7 93 136 16 5 62 5 28 95 129 16 8 63 6 90 130 16 1 60 9 85 131 15 5 58 7 26 85 123 15 4 58 3 80 124 14 8 56 76 125 14 3 54 1 24 75 117 14 1 53 4 71 117 13 5 51 1 67 118 13 1 49 6 22 65 110 12 8 48 5 62 110 12 3...

Page 563: ...49 2 2600 20 63 111 12 6 47 7 60 111 12 1 45 8 57 110 11 7 44 3 2600 18 53 101 11 1 42 50 99 10 7 40 5 47 97 10 4 39 4 2450 26 8 94 132 16 6 62 8 89 132 15 9 60 2 84 133 15 3 57 9 2450 26 90 129 16 1 60 9 85 129 15 4 58 3 81 130 14 8 56 2450 24 80 123 14 7 55 6 75 123 14 2 53 8 72 124 13 7 51 9 2450 22 70 116 13 5 51 1 66 116 12 9 48 8 63 117 12 5 47 3 2450 20 60 108 12 1 45 8 57 108 11 6 43 9 54 ...

Page 564: ...6 6 2600 19 63 113 12 5 47 3 59 112 12 45 4 56 111 11 6 43 9 2600 18 57 108 11 7 44 3 54 106 11 3 42 8 51 104 10 9 41 3 2450 23 9 85 129 15 4 58 3 80 130 14 8 56 76 131 14 2 53 8 2450 23 80 126 14 8 56 75 127 14 2 53 8 72 127 13 7 51 9 2450 22 75 123 14 1 53 4 71 123 13 6 51 5 67 123 13 1 49 6 2450 20 64 114 12 7 48 1 61 114 12 2 46 2 58 113 11 8 44 7 2450 19 59 110 12 45 4 56 109 11 6 43 9 53 107...

Page 565: ...8 5 62 119 12 3 46 6 2450 19 64 116 12 6 47 7 60 115 12 1 45 8 57 114 11 7 44 3 2450 18 59 111 11 9 45 55 109 11 4 43 2 52 106 11 1 42 2350 19 66 121 12 9 48 8 62 120 12 4 46 9 59 117 11 9 45 2350 18 60 115 12 2 46 2 57 113 11 7 44 3 54 110 11 3 42 8 Weight 1160 kg Mixture FULL RICH Pressure Altitude 12000 ft Corrections Best Power 10 to Full Rich F C Best Economy 20 to Full Rich F C ISA 30 C 39 C...

Page 566: ... AGL 488 1601 509 1670 529 1736 550 1804 521 1709 1000 Ground Roll 212 696 233 764 254 833 276 906 244 801 At 50 ft AGL 496 1627 517 1696 538 1765 560 1837 528 1732 2000 Ground Roll 220 722 242 794 264 866 286 938 251 823 At 50 ft AGL 504 1654 526 1726 548 1798 570 1870 535 1755 3000 Ground Roll 228 748 251 823 274 899 297 974 259 850 At 50 ft AGL 512 1680 535 1755 558 1831 581 1906 543 1781 4000 ...

Page 567: ... 8 5 7 3 9 6 7 2000 9 2 6 9 4 9 3 1 6 0 3000 8 3 6 1 4 1 2 3 5 3 4000 7 4 5 2 3 2 1 4 4 6 5000 6 6 4 4 2 4 0 6 3 9 6000 5 7 3 5 1 6 0 2 3 3 7000 4 8 2 7 0 7 1 0 2 6 1060 2337 S L 12 9 10 4 8 1 6 1 9 0 1000 11 9 9 4 7 2 5 2 8 3 2000 11 0 8 5 6 3 4 3 7 5 3000 10 0 7 6 5 4 3 4 6 8 4000 9 1 6 7 4 5 2 5 6 0 5000 8 1 5 7 3 6 1 7 5 3 6000 7 2 4 8 2 7 0 8 4 5 7000 6 2 3 9 1 8 0 1 3 8 960 2116 S L 15 2 12 ...

Page 568: ...in accordance with ICAO Annex 16 6th Ed July 2011 Vol I Chapter 10 and 14 CFR 36 1581 c is 80 58 dB A NOTE No determination has been made by the Federal Aviation Administration that the noise levels of this aircraft are or should be acceptable or unacceptable for operation at into or out of any airport Section 5 Performances NOISE DATA Ed 1 Rev 0 ...

Page 569: ...Page D08 16 INTENTIONALLY LEFT BLANK Section 9 Supplements Supplement n D08 ALTERNATIVE AVIONICS CONFIGURATION AND VARIABLE PITCH PROPELLER EQUIPPED AIRPLANES Ed 1 Rev 0 ...

Page 570: ...LANCE Refer to the basic AFM Section 6 Weight and Balance Supplement D08 pages replacement instructions Section 9 Supplements Supplement n D08 ALTERNATIVE AVIONICS CONFIGURATION AND VARIABLE PITCH PROPELLER EQUIPPED AIRPLANES Ed 1 Rev 0 ...

Page 571: ...Page D08 18 INTENTIONALLY LEFT BLANK Section 9 Supplements Supplement n D08 ALTERNATIVE AVIONICS CONFIGURATION AND VARIABLE PITCH PROPELLER EQUIPPED AIRPLANES Ed 1 Rev 0 ...

Page 572: ...Section 7 page GV 7 8 thru 11 REPLACE Pages 7 8 thru 11 of basic AFM Section 7 GV 7 16 REPLACES Page 7 16 of basic AFM Section 7 GV 7 20 thru 24 REPLACE Pages 7 20 thru 24 of basic AFM Section 7 GV 7 27 REPLACES Page 7 27 of basic AFM Section 7 GV 7 36 REPLACES Page 7 36 of basic AFM Section 7 Supplement D08 pages replacement instructions Section 9 Supplements Supplement n D08 ALTERNATIVE AVIONICS...

Page 573: ...Page D08 20 INTENTIONALLY LEFT BLANK Section 9 Supplements Supplement n D08 ALTERNATIVE AVIONICS CONFIGURATION AND VARIABLE PITCH PROPELLER EQUIPPED AIRPLANES Ed 1 Rev 0 ...

Page 574: ...ent panel Flaps act in continuous mode the indicator displays three markings related to 0 takeoff T O and landing FULL positions A breaker positioned on the right side of the instrument panel protects the electric circuit The control of the stabilator trim is operated by means of a control wheel located be tween the two front seats that acts directly on the control cables Stabilator trim position ...

Page 575: ...Nav Gps 9 N 1 Garmin GNC 255A Com Nav 10 N 1 Garmin GMA 340 Audio Panel 8 N 1 Bendix King KN 572 DME unit 14 N 1 Bendix King KR87 ADF unit 11 N 1 JP Instruments EDM 930 EIS unit 13 N 1 JP Instruments EDM 930 Remote Alarm Display 12 N 1 Mid Continent MD 302 Stand by Instrument 6 N 1 Annunciator panel 7 N 1 Pitch trim indicator 3 N 1 Rudder trim indicator 4 N 1 Chronometer 2 Fig 7 8 INSTRUMENT PANEL...

Page 576: ...drawn into the cylinders that shuts down Throttle This lever left hand with large knob is used to control manifold pressure MAP High manifold pressure means a large quantity of fuel air mixture is being supplied to engine while low manifold pressure means a lesser quantity of fuel air mixture is be ing supplied Propeller lever By means of this lever central lever with blue handle the propeller gov...

Page 577: ... set in OFF position 4 3 DEFROST AND CABIN HEAT Two knobs located on the lower side of the central pedestal allow Defrost and Cabin Heat function The one marked as Defrost and Cabin Heat allows hot air to perform windshield defrost and partially cabin heat The cabin heat control knob when fully outward allows cabin to receive maximum hot air When both cabin heat and defrost and cabin heat are pull...

Page 578: ...80hp 2700 rpm 129 2 kW 173 3hp 2600 rpm Oil Consumption Operation RPM HP Max Oil Cons Qts Hr Max Cyl Head Temp Normal Rated 2700 180 80 500 F 260 C Performance Cruise 75 2450 135 45 500 F 260 C Economy Cruise 60R Rated 2350 117 39 500 F 260 C 7 2 PROPELLER Manufacturer MT Propeller Model MTV 15 B 193 52 Type Certificate EASA TCDS no P 098 Blades hub wood composite 2 blades aluminium hub Diameter 1...

Page 579: ...d no action is required in order to activate the alternate energy source For ground maintenance and or starting an external power socket is provided The alternator and battery are connected to the battery bus in order to provide energy for the electric equipment Each electrically fed instrument is connected to a dedicated circuit breaker which protects the cable from the battery bus to the associa...

Page 580: ...IG 7 15 ELECTRICAL SYSTEM ARCHITECTURE 9 1 STALL WARNING SYSTEM The aircraft is equipped with a stall warning system consisting of a sensor locat ed on the right wing leading edge connected to a warning horn located near the instrument panel Section 7 Airframe and Systems description ELECTRICAL SYSTEM Ed 1 Rev 0 ...

Page 581: ...mbined failure an inte grated digital stand by instrument Mid Continent MD 302 featuring airspeed altitude attitude and slip information is installed An ELT device is installed and its control switch is located in the upper left area of the cockpit The Com Nav functions are embodied into two devices GNC 255 and GTN 650 The second one provides also GPS signal A dedicated DME and an dedicated ADF re...

Page 582: ...AUTION Exercise caution while applying external power Exercise extreme caution while disconnecting external power with en gine running due to airflow coming from the propeller Approach the power supply receptacle from rear of the wing Make a positive check upon disconnection that the power chord is free from any aircraft structure the receptacle is firmly closed Follow this procedure to start the ...

Page 583: ...ide of fuselage Flexible hoses connects total pressure and static ports to primary ana logue instruments anemometer and altimeter Garmin G500 suite and standby MD 302 unit are connected to both static and to tal pressure lines providing both air speed and altitude information 0 T O LND FLAP LH STATIC PORT RH STATIC PORT T JOINT ALTERNATE STATIC PORT ALTERNATE STATIC PORT VALVE GARMIN G500 GDC 74A ...

Page 584: ...gers In the central area of the cabin ceiling is located a spot light used to illuminate the pedestal during night flight operations All ceiling lights are dimmable by a dedicat ed dimmer FIG 7 18 CABIN CEILING LIGHTS LAYOUT The instrument panel can be illuminated by 8 incandescence light strips all dimma ble FIG 7 19 INSTRUMENT PANEL LIGHTS LAYOUT FWD From mid MAP light ceiling Ed 1Rev 0 Section ...

Page 585: ...AFMS N D08 FOR ALTERNATIVE AVIONICS CONFIGRATION AND VARIABLE PITCH PROPELLER EQUIPPED AIRPLANES Page GV 7 36 Pedestal placards Ed 1Rev 0 Section 7 Airframe and Systems description PLACARDS ...

Page 586: ...orted on the basic AFM Section 8 Ground Handling Service Refer to the basic AFM Section 8 Ground Handling Service Supplement D08 pages replacement instructions Ed 1Rev 0 Section 9 Supplements Supplement n D08 ALTERNATIVE AVIONICS CONFIGURATION AND VARIABLE PITCH PROPELLER EQUIPPED AIRPLANES ...

Page 587: ...Page D08 22 INTENTIONALLY LEFT BLANK Ed 1Rev 0 Section 9 Supplements Supplement n D08 ALTERNATIVE AVIONICS CONFIGURATION AND VARIABLE PITCH PROPELLER EQUIPPED AIRPLANES ...

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