Tecnam P2006T Aircraft Flight Manual

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Aircraft Flight Manual

Doc. No. 2006/044

4th Edition – Rev. 2

2017, March 16th

TECNAM P2006T

MANUFACTURER: COSTRUZIONI AERONAUTICHE TECNAM S.r.l. AIRCRAFT MODEL: P2006T EASA TYPE CERTIFICATE NO: A .185 (DATED 2009, JUNE 5TH)

SERIAL NUMBER: ……………..............

BUILD YEAR: ……….………................

REGISTRATION MARKINGS: ……………..

This Aircraft Flight Manual is approved by European Aviation Safety Agency (EASA).

This Manual contains information required by the FAA to be furnished to the pilot for operation in the U.S.A. plus information supplied by the manufacturer. It is approved by EASA on behalf of the FAA per FAR 21.29.

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 (CE) – Italy Tel. +39 (0) 823.62.01.34 WEB: www.tecnam.com

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4th Edition - Rev. 0

Aircraft Flight Manual

INDEX

SECTION 0

INDEX

1. RECORD OF REVISIONS ...................................................................... 3

2. LIST OF EFFECTIVE PAGES ................................................................ 7

3. FOREWORD ........................................................................................ 10

4. SECTIONS LIST .................................................................................. 11

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4th Edition - Rev. 0

Aircraft Flight Manual

RECORD OF REVISIONS

1. RECORD OF REVISIONS

Any revision to the present Manual, except actual weighing data, is recorded: a Record of Revisions is provided at the front of this manual and the operator is advised to make sure that the record is kept up-to-date.

The Manual issue is identified by Edition and Revision codes reported on each page, lower right side.

The revision code is numerical and consists of the number "0"; subsequent revisions are identified by the change of the code from "0" to "1" for the first revision to the basic publication, "2" for the second one, etc.

Should 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 edition, “3” for the third edition etc).

Additions, deletions and revisions to existing text will be identified by a revision bar (black line) in the left-hand margin of the page, adjacent to the change.

When technical changes cause expansion or deletion of text which results in unchanged text appearing on a different page, a revision bar will be placed in the right-hand margin adjacent to the page number of all affected pages providing no other revision bar appears on the page.

These pages will be updated to the current regular revision date. NOTE: It is the responsibility of the owner to maintain this handbook in a current

status when it is being used for operational purposes.

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4th Edition - Rev. 2

Aircraft Flight Manual

RECORD OF REVISIONS

Rev

Revised

page

Description of

Revision

Tecnam Approval

EASA Approval or

Under DOA

Privileges

OoA

HDO

First issue

D. Ronca

M. Oliva

0-4

Amend ROR

D. Ronca

M. Oliva

Approved under the au-

thority of DOA,

ref. EASA.21J.335

(MOD2006/270.160429)

0-8

Amend LOEP

D. Ronca

M. Oliva

6-12

Amend Equipment List

D. Ronca

M. Oliva

9-1 & 2

Amend Supplement List Index

D. Ronca

M. Oliva

9-5

Amend Supplement List

D. Ronca

M. Oliva

9-7

Amend Supplement List

D. Ronca

M. Oliva

Add Supplement A24

D. Ronca

M. Oliva

Add Supplement A25

D. Ronca

M. Oliva

Add Supplement G14

D. Ronca

M. Oliva

Add Supplement G16

D. Ronca

M. Oliva

Add Supplement G17

D. Ronca

M. Oliva

4-3, 4

Amend General recommendation

D. Ronca

M. Oliva

Approved under the au-

thority of DOA,

ref. EASA.21J.335

(MOD2006/290.170316)

4-18, 19

Amend “Prior to Takeoff” procedure

D. Ronca

M. Oliva

5-16

Amend Cruise performances

D. Ronca

M. Oliva

9-1,2,4,5,7

Amend Supplement List Index

D. Ronca

M. Oliva

Add Supplement A13B

D. Ronca

M. Oliva

Add Supplement A26

D. Ronca

M. Oliva

Add Supplement A27

D. Ronca

M. Oliva

Add Supplement G18

D. Ronca

M. Oliva

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Aircraft Flight Manual

LIST OF EFFECTIVE PAGES

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2. LIST OF EFFECTIVE PAGES

The List of Effective Pages (LOEP), applicable to manuals of every operator, lists all the basic AFM pages: each manual could contain either basic pages or one variant of these pages when the pages of some Supplements are embodied.

Should the Supplements be embodied in accordance with approved instructions, make reference to the LOEP addressed on the Supplements themselves.

1st Edition, Rev 0 ..................... May 25, 2009

2nd Edition, Rev 0 ..................... March 29, 2010

2nd Edition, Rev 1 ..................... April 27, 2010

2nd Edition, Rev 2 ..................... November 12, 2010

2nd Edition, Rev 3 ..................... March 4, 2011

3rd Edition, Rev 0 ..................... December 22, 2011

3rd Edition, Rev 1 ..................... October 15, 2012

3rd Edition, Rev 2 ..................... June 4, 2013

3rd Edition, Rev 3..................... February 13, 2014

3rd Edition, Rev 4..................... May 5, 2014

3rd Edition, Rev 5..................... June 10, 2015

4th Edition, Rev 0 ..................... July 25, 2015

4th Edition, Rev 1 ..................... April 6, 2016

4th Edition, Rev 2 ..................... March 16, 2017

Section

Pages

Revision

Section 0

Pages 1 thru 3, 5, 6, 8 trhu 11

Rev 0

Pages 4,7

Rev 1

Section 1

Pages 1 thru 18

Rev 0

Section 2

Pages 1 thru 32

Rev 0

Section 3

Pages 1 thru 58

Rev 0

Section 4

Pages 1,2,5 thru 17 and Pages 20 thru 29

Rev 0

Pages 3,4,18, 19

Rev 2

Section 5

Pages 1 thru 15 and Pages 17 thru 23

Rev 0

Page 16

Rev 2

Section 6

Pages 1 thru 10

Rev 0

Pages 11 thru 12

Rev 1

Pages 13 thru 14

Rev 0

Section 7

Pages 1 thru 44

Rev 0

Section 8

Pages 1 thru 10

Rev 0

Supplements

Section 9

Pages 1, 2, 5, 7

Rev 1

Pages 3, 4, 6, 8

Rev 0

Supplements LOEP: make reference to the Supplements Cover Pages

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Aircraft Flight Manual

FOREWORD

3. FOREWORD

Tecnam P2006T is a twin-engine four-seat aircraft with high cantilevered wing and tricycle retractable landing gear.

Section 1 supplies general information and it contains definitions, symbols explanations, acronyms and terminology used.

Before using the airplane, you are recommended to read carefully this manual: a deep knowledge of airplane features and limitations will allow you for operating the airplane safely.

For further information, please contact:

COSTRUZIONI AERONAUTICHE TECNAM s.r.l.

Via MAIORISE

CAPUA (CE) - ITALY

 +39 (0) 823.62.01.34  www.tecnam.com

4th Edition - Rev. 0

Aircraft Flight Manual

SECTIONS LIST

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4. SECTIONS LIST

General

Section 1 (a non-approved Chapter)

Limitations

Section 2 - EASA Approved Chapter

Emergency Procedures

Section 3 (a non-approved Chapter)

Normal Procedures

Section 4 (a non-approved Chapter)

Performances

Section 5 (a non-approved Chapter)

Weight and Balance

Section 6 (a non-approved Chapter)

Airframe and Systems description

Section 7 (a non-approved Chapter)

Airplane Care and Maintenance

Section 8 (a non-approved Chapter)

Supplements

Section 9 (*)

(*) EASA approved parts, if any, are reported on the supplements

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Section 1 – General

INDEX

4th Edition, Rev 0

SECTION 1 - GENERAL

INDEX

1. Introduction .................................................................................. 3

2. Three-view and dimensions .......................................................... 4

3. Control Surfaces Travel Limits .................................................... 6

4. Engine ........................................................................................... 6

5. Propeller ....................................................................................... 6

6. Governor ....................................................................................... 7

7. Fuel ............................................................................................... 7

8. Lubrication .................................................................................... 7

9. Cooling .......................................................................................... 8

10. Maximum weights ...................................................................... 8

11. Standard weights ....................................................................... 8

12. Specific loadings ....................................................................... 8

13. Acronyms and terminology ...................................................... 10

14. Unit conversion chart .............................................................. 15

15. Litres / US gallons conversion chart ....................................... 16

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Section 1 – General

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Section 1 – General

INTRODUCTION

4th Edition, Rev 0

1. INTRODUCTION

The Aircraft Flight Manual has been implemented to provide the owners with information for a safe and efficient use of the aircraft TECNAM P2006T.

Warning – Caution – Note

Following definitions apply to warnings, cautions and notes used in the Aircraft Flight Manual.

WARNING

The non-observation of the corresponding procedure can lead, as immediate effect, to a significant reduction of the flight safety.

CAUTION

The non-observation of the corresponding procedure can lead to an equipment damage which leads to a reduction of the flight safety in a short or longer time interval.

Draws the attention to a procedure not directly related to safety of flight.

NOTE

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Section 1 – General

THREE-VIEW AND DIMENSIONS

4th Edition, Rev 0

2. THREE-VIEW AND DIMENSIONS

P2006 T

GENERAL VIEW

Figure 1 – General views

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Section 1 – General

THREE-VIEW AND DIMENSIONS

4th Edition, Rev 0

Dimensions

Overall dimensions

Wingspan 11,4 m 37,4 ft

Length 8,7 m 28,5 ft

Overall height 2,58 m 8,46 ft

Wing

Wing surface 14,76 m2 158,9 ft2

Mean Geometric Chord 1,295 m 4,25 ft

Dihedral 1°

Aspect ratio 8,80

Main Landing Gear

Track 2.0 m

Wheelbase 2.9 m

Tire 6.00-6

Wheel rim assembly (Cleveland) P/N 40-59A

Nose Landing Gear

Tire 5.00 – 5

Wheel rim assembly (Cleveland) P/N 40-77C

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Section 1 – General

GENERAL FEATURES

4th Edition, Rev 0

3. CONTROL SURFACES TRAVEL LIMITS

Ailerons

Up 20° Down 17 ° ( 2°)

Stabilator (refer to Trailing Edge)

Up 4° Down 15° ( 2°)

Stabilator trim tab (refer to Trailing Edge)

Up 2°; Down 19° ( 2°)

Rudder

RH 26° LH 26° ( 2°)

Rudder trim tab

RH 20° LH 20° ( 2°)

Flaps

0°; 40° (- 2°)

4. ENGINE

Manufacturer

Bombardier-Rotax GmbH

Model

912 S3

Certification basis

FAR 33 - Amendment 15

Type Certificate

EASA TCDS no. E.121 dated 1 April 2008

Engine type

4 cylinders horizontally opposed with 1352 c.c. of overall displacement, liquid cooled cylinder heads, ram-air cooled cylinders, two carburetors, integrated reduction gear box with torsional shock absorber and overload clutch.

Maximum power (at declared rpm)

73.5 kW (98.6hp) @ 5800 rpm –5 minutes maximum.

69.0 kW (92.5hp) @ 5500 rpm (continuous)

5. PROPELLER

Manufacturer

MT Propeller

Type Certificate

LBA 32.130/086 (MTV-21 series)

Model

MTV-21-A-C-F/CF178-05

Blades/hub

2 wood/composite blades – aluminum hub

Diameter

1780 mm (no reduction allowed)

Type

Variable pitch - hydraulically controlled

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Section 1 – General

GENERAL FEATURES

4th Edition, Rev 0

6. GOVERNOR

Manufacturer

Mt Propeller

Model

P-875-12

Type

Hydraulic

7. FUEL

Approved fuel: MOGAS ASTM D4814

MOGAS EN 228 Super/Super plus (min. RON 95)

AVGAS 100LL (ASTM D910)

(see also Section 2)

Fuel tanks

Two integrated tanks (one in each wing) fitted with drainable sump and drain valve

Capacity of each wing tan

100 litres (26,42 US gallons)

Tanks overall capacity

200 litres (52,8 US gallons)

Overall usable fuel

194.4 litres (51,35 US gallons)

Overall unusable fuel

5.6 litres (1,48 US gallons)

8. LUBRICATION

Lubrication system

Forced type with external reservoir

Oil

Use only oil with API classification “SG” or higher. For additional info, refer to “Rotax Operators Manual” – last issue -, “Operating Media” Section.

Oil capacity

Max. 3.0 litres – min. 2.0 litres (per

tank)

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Section 1 – General

GENERAL FEATURES

4th Edition, Rev 0

9. COOLING

Cooling system

Ram-air cooled cylinders, liquid cooled cylinder heads (closed and pressurized circuit)

Coolant liquid

Certified for Water/Coolant mixture.

Make reference to “Rotax Operators Manual” – last issue

Overall circuit capacity

1410 cm

10. WEIGHTS

See Section 2.

11. STANDARD WEIGHTS

Empty Weight: see weighing record on Section 6

12. SPECIFIC LOADINGS

NOTE. Reference is made to both MTOW: 1180 kg and 1230 kg (if Supplement A19 or G10 - Increased MTOW @1230 KG - is applicable).

MTOW 1180 kg (2601 lb)

MTOW 1230 kg (2712 lb)

Wing Loading

80 kg/m2 (16,37 lb/sqft )

83 kg/m2 (17,1 lb/sqft )

Power Loading

6.0 kg/hp (13,26 lb/hp )

6.28 kg/hp (13,84 lb/hp )

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Section 1 – General

GENERAL FEATURES

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Section 1 – General

ACRONYMS AND TERMINOLOGYACRONYMS AND

4th Edition, Rev 0

13. ACRONYMS AND TERMINOLOGY

KCAS

Calibrated Airspeed is the indicated airspeed expressed in knots, corrected taking into account the errors related to the instrument itself and its installation.

KIAS

Indicated Airspeed is the speed shown on the airspeed indicator and it is expressed in knots.

KTAS

True Airspeed is the KCAS airspeed corrected taking into account altitude and temperature.

VA Design Manoeuvring speed is the speed above the which it is not allowed to make full or abrupt control movement.

VFE

Maximum Flap Extended speed is the highest speed permissible with flaps extended.

VLO

Maximum Landing Gear Operating speed is the maximum speed allowed to retract or to extend the landing gear.

Maximum Landing Gear Extended speed is the maximum speed allowed with the landing gear extended.

VMC

Minimum control speed: is the minimum speed necessary to ensure an efficient aircraft control in case of one engine inoperative.

VNO

Maximum Structural Cruising Speed is the speed that should not be exceeded, except in smooth air and only with caution.

VNE

Never Exceed Speed is the speed limit that may not be exceeded at any time.

Operating Manoeuvring speed is the speed above the which it is not allowed to make full or abrupt control movement

Stall Speed.

VS0

Stall Speed in landing configuration (flaps and landing gear extended).

VS1

Stall speed in the given flap and landing gear configuration.

SSE

Recommended safe simulated OEI speed is the minimum speed at which simulated OEI training operation should be executed.

Best Angle-of-Climb Speed is the speed which allows best ramp climb performances.

Best Rate-of-Climb Speed is the speed which allows the best gain in altitude over a given time.

Rotation speed: is the speed at which the aircraft rotates about the pitch axis during takeoff

YSE

Best Rate-of-Climb speed in case of one engine inoperative.

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Section 1 – General

ACRONYMS AND TERMINOLOGYACRONYMS AND

4th Edition, Rev 0

Meteorological terminology

ISA

International Standard Atmosphere: is the air atmospheric standard condition at sea level, at 15°C (59°F) and at 1013.25hPa (29.92inHg).

QFE

Official atmospheric pressure at airport level: it indicates the aircraft absolute altitude with respect 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).

Standard Temperature is 15°C at sea level pressure altitude and decreased by 2°C for each 1000 ft of altitude.

Pressure Altitude is the altitude read from an altimeter when the barometric subscale has been set to 1013 mb.

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Section 1 – General

ACRONYMS AND TERMINOLOGYACRONYMS AND

4th Edition, Rev 0

Aircraft performance and flight planning terminology

Crosswind Velocity

is the velocity of the crosswind component for the which adequate control of the airplane during takeoff and landing is assured.

Usable fuel

is the fuel available for flight planning.

Unusable fuel

is the quantity of fuel that cannot be safely used in flight.

is the acceleration of gravity.

TOR

is the takeoff distance measured from actual start to wheel liftoff point.

TOD

is total takeoff distance measured from start to 15m obstacle clearing.

is the distance measured during landing from actual touchdown to stop point.

is the distance measured during landing, from 15m obstacle clearing to actual stop.

S/R

is the specific range, that is the distance (in nautical miles) which can be expected at a specific power setting and/or flight configuration per kilogram of fuel used.

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Section 1 – General

ACRONYMS AND TERMINOLOGYACRONYMS AND

4th Edition, Rev 0

Weight and balance terminology

Datum

“Reference datum” is an imaginary vertical plane from which all horizontal distances are measured for balance purposes.

Arm

is the horizontal distance of an item measured from the reference datum.

Moment

is the product of the weight of an item multiplied by its arm.

C.G.

Center of Gravity is the point at which the airplane, or equipment, would balance if suspended. Its distance from the reference datum is found by dividing the total moment by the total weight of the aircraft.

Standard Empty Weight

is the weight of the aircraft with engine fluids and oil at operating levels.

Basic Empty Weight

is the standard empty weight to which it is added the optional equipment weight.

Useful Load

is the difference between maximum takeoff weight and the basic empty weight.

Maximum Takeoff Weight

is the maximum weight approved to perform the takeoff.

Maximum Landing Weight

is the maximum weight approved for the landing touchdown (for P2006T it is equivalent to the Maximum Takeoff Weight).

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Section 1 – General

UNIT CONVERSION CHART

4th Edition, Rev 0

14. UNIT CONVERSION CHART

MOLTIPLYING

BY 

YIELDS

TEMPERATURE

Fahrenheit

[°F]

 

5 9

32 F

Celsius

[°C]

Celsius

[°C]

9 5

32

 



 



C

Fahrenheit

[°F]

FORCES

Kilograms

[kg]

2.205

Pounds

[lbs]

Pounds

[lbs]

0.4536

Kilograms

[kg]

SPEED

Meters per second

[m/s]

196.86

Feet per minute

[ft/min]

Feet per minute

[ft/min]

0.00508

Meters per second

[m/s]

Knots

[kts]

1.853

Kilometres / hour

[km/h]

Kilometres / hour

[km/h]

0.5396

Knots

[kts]

PRESSURE

Atmosphere

[atm]

14.7

Pounds / sq. in

[psi]

Pounds / sq. in

[psi]

0.068

Atmosphere

[atm]

LENGTH

Kilometres

[km]

0.5396

Nautical miles

[nm]

Nautical miles

[nm]

1.853

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]

0.2642

U.S. Gallons

[US Gal]

U.S. Gallons

[US Gal]

3.785

Litres

[l]

AREA

Square meters

[m2]

10.76

Square feet

[sq ft]

Square feet

[sq ft]

0.0929

Square meters

[m2]

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Section 1 – General

LITRES / US GALLONS CONVERSION CHART

4th Edition, Rev 0

15. LITRES / US GALLONS CONVERSION CHART

Litres

US Gallons

Litres

1.3 1

3.8

2.6 2

7.6

4.0 3

11.4

5.3 4

15.1

6.6 6

22.7

7.9 8

30.3

9.2 10

37.9

10.6 12

45.4

11.9 14

53.0

13.2 16

60.6

15.9 18

68.1

18.5 20

75.7

21.1 22

83.3

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 45

170.3

190

50.2 50

189.3

200

52.8 55

208.2

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Section 2 – Limitations

INDEX

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EASA Approved

SECTION 2 – LIMITATIONS

INDEX

1. Introduction ....................................................................................................... 3

2. Speed limitations ............................................................................................... 5

3. Airspeed indicator markings ............................................................................... 7

4. Powerplant limitations ....................................................................................... 9

5. Lubricant ......................................................................................................... 10

6. Coolant liquid .................................................................................................. 10

7. Propeller .......................................................................................................... 10

8. Governor ......................................................................................................... 10

9. Maximum operating altitude ............................................................................ 11

10. Ambient temperature ...................................................................................... 11

11. Powerplant instruments markings .................................................................... 12

12. Other instruments markings ............................................................................. 12

13. Warnings, cautions and advisories lights .......................................................... 13

14. Weights ........................................................................................................... 15

15. Center of gravity range ..................................................................................... 17

16. Approved maneuvers ....................................................................................... 19

17. Maneuvers load factor limits ............................................................................ 19

18. Flight crew ....................................................................................................... 19

19. Flight conditions .............................................................................................. 20

20. Fuel ................................................................................................................. 20

21. Limitations placards ......................................................................................... 21

21.1. Speed limitations ......................................................................................... 21

21.2. Operating limitations ................................................................................... 22

21.3. Inflight engine restart .................................................................................. 23

21.4. Baggage compartment capacity ................................................................... 23

21.5. Engine oil level ............................................................................................ 24

21.6. Fuel type ..................................................................................................... 24

21.7. Landing Gear Hydraulic System .................................................................... 25

21.8. Rear seats .................................................................................................... 26

21.9. Other placards ............................................................................................. 27

22. Kinds of Operations Equipment List .................................................................. 29

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Section 2 – Limitations

INTRODUCTION

EASA Approved

1. INTRODUCTION

Section 2 includes operating limitations, instrument markings and basic placards necessary for safe operation of P2006T aircraft, its engines and standard systems and equipment.

This AFM Section is EASA approved.

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GARMIN G950 IFDS – Increased MTOW (1230 kg)

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Section 2 – Limitations

SPEED LIMITATIONS

3rd Edition, Rev. 0

EASA Approved

2 SPEED LIMITATIONS

The following table addresses the airspeed limitations and their operational significance:

SPEED

KIAS

KCAS

REMARKS

Never exceed speed

171

172

Do not exceed this speed in any operation.

Maximum Structural Cruising Speed

138

136

Do not exceed this speed except in smooth air, and only with caution.

Design Manoeuvring speed

122 119

Do not make full or abrupt control movement above this speed, because under certain conditions the aircraft may be overstressed by full control movement.

Operating Manoeuvring speed

VLE

Maximum Landing Gear extended speed

Do not exceed this speed with the landing gear extended.

VLO

Maximum Landing Gear operating speed

Do not exceed this speed when operating the landing gear.

VFE

Maximum flaps extended speed

FULL

Do not exceed this speed for indicated flaps setting.

T.O.

122

119

VMC

Aircraft minimum control speed with one engine inoperative

Do not reduce speed below this value in event of one engine inoperative condition.

GARMIN G950 IFDS – Increased MTOW (1230 kg)

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EASA Approved

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GARMIN G950 IFDS – Increased MTOW (1230 kg)

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Section 2 – Limitations

AIRSPEED INDICATOR MARKINGS

3rd Edition, Rev. 0

EASA Approved

3 AIRSPEED INDICATOR MARKINGS

Airspeed indicator markings and their colour code are explained in the following table.

MARKING

KIAS

EXPLANATION

White band

54-93

Lower limit is VSO, upper limit is the maximum allowable speed with flaps extended in FULL position.

Red line

Minimum aircraft control speed with one engine inoperative and flaps set to T.O.

Green band

66-138

Normal aircraft operating range (lower limit is VS1, stall speed in “clean” configuration, and upper limit is the maximum structural cruise speed VNO).

Blue line

Best rate-of-climb speed with one engine inoperative at sea level.

Yellow band

138-171

Speed range where manoeuvres must be conducted with caution and only in smooth air.

Red line

171

Maximum speed for all operations.

GARMIN G950 IFDS – Increased MTOW (1230 kg)

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Section 2 – Limitations

POWERPLANT LIMITATIONS

EASA Approved

Page 2 - 9

4. POWERPLANT LIMITATIONS

Following table reports the operating limitations for both engines installed:

ENGINE MANUFACTURER: Bombardier Rotax GmbH. ENGINE MODEL: 912 S3

MAXIMUM POWER:

Max Power

kW (hp)

Max rpm.

Prop. rpm (engine)

Time max.

(minutes)

Max. T.O.

73.5 (98.6)

2388 (5800)

Max. Cont.

69 (92.5)

2265 (5500)

Temperatures:

Max CHT* 135° C Max CT 120° C Min/Max Oil 50° C / 130° C Oil normal operating range (approx.) 90° C / 110° C

 applicable for Engines up to serial no. 4924543(included) and repaired engine which

doesn’t change the cylinder head n°3 with new one (part no. 413195)

Oil Pressure:

Minimum 0.8 Bar / 12psi (below 1400 rpm prop) Normal 2 – 5 Bar / 29-73psi (above 1400 rpm prop)

Maximum 7 Bar / 102 psi (above 1400 rpm prop)

Engine starting: allowable temperature range

OAT Min -25° C OAT Max +50° C

CAUTION

In event of cold starting operation, it is permitted a maximum oil pressure of 7 bar for a short period.

4th Edition, Rev. 0

Section 2 – Limitations

POWERPLANT LIMITATIONS

EASA Approved

Page 2 - 10

Fuel pressure:

Minimum 2.2 psi (0.15 Bar) Maximum 5.8 psi (0.40 Bar) or 7.26 psi* (0.5 Bar)

*only applicable for fuel pump part no. 893110 or 893114

5. LUBRICANT

Use only oil with API classification “SG” or higher. For additional info, refer to “Rotax Operators Manual” – last issue -, “Operating

Media” Section.

6. COOLANT LIQUID

Refer to “Rotax Operators Manual” – last issue -, “Operating Media” Section.

7. PROPELLER

MANUFACTURER: MT Propeller MODEL: MTV-21-A-C-F-/CF178-05 TYPE: wood/composite 2-blade, variable pitch hydraulically con-

trolled and fully featherable

DIAMETER: 1780 mm (no reduction is permitted)

8. GOVERNOR

MANUFACTURER: MT Propeller MODEL: P-875-12 OPERATION: Hydraulically controlled (oil pressure to reduce the

pitch)

4th Edition, Rev. 0

Section 2 – Limitations

ALTITUDE AND OAT LIMITATIONS

EASA Approved

Page 2 - 11

9. MAXIMUM OPERATING ALTITUDE

Maximum operating altitude is 14000 ft (4260 m) MSL.

CAUTION

At altitudes above 12500 ft (3810 m) up to and including 14000 ft (4260 m), flight must be limited to 30 minutes, unless the required minimum flight crew is provided with and uses supplemental oxygen for that part of the flight at those altitudes that is of more than 30 minutes duration.

10. AMBIENT TEMPERATURE

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

WARNING

Flight in expected and/or known icing conditions is forbidden.

4th Edition, Rev. 0

Section 2 – Limitations

POWERPLANT INSTRUMENTS MARKINGS

EASA Approved

Page 2 - 12

11. POWERPLANT INSTRUMENTS MARKINGS

Powerplant instrument markings and their colour code significance are shown below:

INSTRUMENT

RED LINE

Minimum

limit

GREEN ARC

Normal

operating

YELLOW ARC

Caution

RED LINE

Maximum

limit

Propeller

rpm

----

580 - 2265

2265 - 2388

2388

Oil temp.

°C

90 - 110

50 - 90

110 - 130

130

°C

----

50 – 120

----

120

CHT1

°C

----

50 – 135

----

135

Oil pressure

bar

0.8

2 - 5

0.8 - 2

5 - 7

(2)

Fuel press.

psi

2.2

2.2 - 5.8 or

7.23

----

5.8 or 7.23

Fuel Q.ty

litres

(4)

----

12. OTHER INSTRUMENTS MARKINGS

INSTRUMENT

RED LINE

Minimum limit

GREEN ARC

Normal operating

YELLOW ARC

Caution

RED LINE

Maximum limit

Voltmeter

10,5 Volt

12 - 14 Volt

----

applicable for Engines up to serial no. 4924543(included) and repaired engine which doesn’t change the

cylinder head n°3 with new one (part no. 413195)

- In event of cold starting operation, it is permitted a maximum oil pressure of 7 bar for a short period.

- only applicable for fuel pump part no. 893110 or 893114

- “0” indication shows the unusable fuel quantity (2,8 litres for each fuel tank).

GARMIN G950 IFDS - Supplement

Section 2 – Limitations

WARNING/CAUTION ALERTS AND SAFE OPERATING ANNUNCIATIONS

4th Edition, Rev. 0

Page S2 - 13

EASA Approved

13 Warning/caution alerts and safe operating annuncia-

tions

Following table addresses the warning and caution alerts and safe operating annunciations shown (unless differently specified) on the Annunciation Window:

Warning alert (RED)

Cause

L BUS VOLT HIGH

LH electric system overvoltage

R BUS VOLT HIGH

RH electric system overvoltage

L COOLANT LOW

Left engine - coolant liquid low level

L COOLANT LOW

Right engine - coolant liquid low level

PILOT DR OPEN

Main door open and/or unlocked

REAR DR OPEN

Rear door open and/or unlocked

LH ENGINE FIRE

Left engine compartment: fire detected

RH ENGINE FIRE

Right engine compartment: fire detected

LG TRANSITION

(warning light installed near the landing gear control lever)

One or more legs are in transition phase and/or the selected retracted/extended position is not yet reached.

Caution alert (AMBER)

Cause

L ALT FAIL

LH generator failure

R ALT FAIL

RH generator failure

PITOT HEAT

Pitot heating system failure/not activated

EXT POWER ON

External electrical supply connected

GEAR PUMP ON

LG pump electrically supplied

Safe operating annunciation (GREEN)

Indication

L FUEL PUMP ON

Left engine - electrical fuel pump ON

R FUEL PUMP ON

Right engine - electrical fuel pump ON

PITOT HEAT ON

Pitot heating system ON

LG Down & Locked

(3 advisory lights, one for each leg, installed near the landing gear control lever)

Landing gear extended and locked

GARMIN G950 IFDS - Supplement

Page S2 - 14

Section 2 – Limitations

WARNING/CAUTION ALERTS AND SAFE OPERATING ANNUNCIATIONS

4th Edition, Rev. 0

EASA Approved

Aural means are provided by Garmin G950 System: a repeating tone is associated to the warning alerts and a single chime is associated to the caution alerts. Safe operating annunciations do not have any aural chime generated.

Make reference to Garmin G950 Pilot’s Guide for P2006T, last issue, “Annunciations and alerts” (Appendix A).

GARMIN G950 IFDS – Increased MTOW (1230 kg)

Page SW2-15

Section 2 – Limitations

WEIGHTS

3rd Edition, Rev. 0

EASA Approved

14 WEIGHTS

Refer to Para. 21.4 of this AFM Section for baggage loading limitations.

Condition

Weight

Maximum takeoff weight

1230 kg

2712 lb

Maximum landing weight

1230 kg

2712 lb

Maximum zero wing fuel weight

1195 kg

2635 lb

NOTE

GARMIN G950 IFDS – Increased MTOW (1230 kg)

Page SW2-16

Section 2 – Limitations

3rd Edition, Rev. 0

INTENTIONALLY LEFT BLANK

Section 2 – Limitations

CENTER OF GRAVITY RANGE

4th Edition, Rev. 0

EASA Approved

Page 2 - 17

15. CENTER OF GRAVITY RANGE

Datum

Vertical plane tangent to the wing leading edge (the aircraft must be levelled in the longitudinal plane)

Levelling

Refer to the seat track supporting beams (see procedure in Section 6)

Forward limit

0.221 m (16.5% MAC) aft of datum for all weights

Aft limit

0.415 m (31% 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 instructions.

Section 2 – Limitations

4th Edition, Rev. 0

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INTENTIONALLY LEFT BLANK

Section 2 – Limitations

APPROVED MANEUVERS

4th Edition, Rev. 0

EASA Approved

Page 2 - 19

16. APPROVED MANEUVERS

The aircraft is certified in normal category in accordance with EASA CS-23 regulation.

Non aerobatic operations include:

 Any manoeuvre pertaining to “normal” flight  Stalls (except whip stalls)  Lazy eights  Turns in which the angle of bank is not more than 60°  Chandelle

WARNING

Acrobatic manoeuvres, including spins and turns with angle of bank of more than 60°, are not approved for such a category. In addition, stall with one engine inoperative is forbidden.

WARNING

Limit load factor could be exceeded by moving flight controls to maximum deflection at a speed above VA=VO (118 KIAS, Manoeuvring Speed).

17. MANEUVERS LOAD FACTOR LIMITS

Maneuver load factors limits are as follows:

Positive

Negative

+ 3.8 g

- 1.78 g

Maneuver load factors limits with flaps extended are as follows:

Positive + 2 g

Negative 0 g

18. FLIGHT CREW

Minimum crew: 1 pilot Maximum number of occupants: 4 people (including the pilot)

Section 2 – Limitations

FLIGHT CONDITIONS

4th Edition, Rev. 0

EASA Approved

Page 2 - 20

19. FLIGHT CONDITIONS

The aircraft can be equipped for following flight operations (make reference to Para. 22 concerning the equipment list required on board to allow them):

 VFR Day and Night  IFR Day and Night including IMC

WARNING

Flight in expected and/or known icing conditions, in proximity of storms or in turbulence is forbidden.

Additional equipment can be required to fulfil national or specific operational requirements. The owner is responsible for fulfilling these requirements.

Equipment list is addressed in Section 6.

20. FUEL

2 TANKS: 100 litres each one (26,42 US gallons)

MAXIMUM CAPACITY: 200 litres (52,8 US gallons) MAXIMUM USABLE FUEL: 194.4 litres (51,35 US gallons) APPROVED FUEL: MOGAS ASTM D4814

MOGAS EN 228 Super/Super plus (min. RON 95)

AVGAS 100 LL (ASTM D910)

CAUTION

Prolonged use of Aviation Fuel Avgas 100LL results in greater wear of valve seats and greater combustion deposits inside cylinders due to higher lead content. It is therefore suggested to avoid using this type of fuel unless strictly necessary. Make reference to Rotax Maintenance Manual which prescribes dedicated checks due to the prolonged use of Avgas.

NOTE

GARMIN G950 IFDS – Increased MTOW (1230 kg)

Page SW2-21

Section 2 – Limitations

LIMITATIONS PLACARDS

3rd Edition, Rev. 1

EASA Approved

21. LIMITATIONS PLACARDS

Hereinafter the placards, related to the operating limitations and installed on P2006T, are reported.

21.1. SPEED LIMITATIONS

On the left side instrument panel, the following placards reporting the speed limi-

tations are placed:

Speed limitations placard for MTOW @1230 kg (2712 lb)

GARMIN G950 IFDS – Increased MTOW (1230 kg)

Page SW2-22

Section 2 – Limitations

LIMITATIONS PLACARDS

3rd Edition, Rev. 0

EASA Approved

21.2. OPERATING LIMITATIONS

On the instrument panel, it is placed the following placard reminding the ob-

servance of aircraft operating limitations; make reference to Para. 22 for the list of

equipment required on board to allow flight operations in VFR Day, VFR Night,

IFR Day and IFR Night conditions.

This A/C can be operated only in normal category DAY-NIGHT-VFR-IFR (with required equipment) in

non-icing conditions. All aerobatics manoeuvres in-

cluding spinning are prohibited. For operational lim-

itations refer to FLIGHT MANUAL

Section 2 – Limitations

LIMITATIONS PLACARDS

4th Edition, Rev. 0

EASA Approved

Page 2 - 23

21.3. INFLIGHT ENGINE RESTART

The inflight engine restart procedure is reported on a placard (shown below) installed on the central console.

21.4. BAGGAGE COMPARTMENT CAPACITY

The placard shown below, and installed on the baggage compartment (vertical panel), concerns the baggage compartment load limitations herein reported:

 Maximum allowable load: 80kg/176lb  Maximum intensity of loading: 0.9 kg/dm

– 19 lbs/sqft

Page 2 - 24

Section 2 – Limitations

LIMITATIONS PLACARDS

4th Edition, Rev.0

EASA Approved

21.5. ENGINE OIL LEVEL

On the engine nacelle, in correspondence of the engine oil reservoir access door, it is located the following placard addressing the limitations concerning the oil level, the oil volume and the oil type.

21.6. FUEL TYPE

In correspondence of each fuel tank filler cap, it is located the following placard reporting the approved fuel type and the tank usable fuel.

Page 2 - 25

Section 2 – Limitations

LIMITATIONS PLACARDS

4th Edition, Rev. 0

EASA Approved

21.7. LANDING GEAR HYDRAULIC SYSTEM

The placard shown below, and located on the tail cone, concerns the allowed low pressure limit for the landing gear emergency accumulator.

The low pressure limit is 20 bar. If during pre-flight inspection the value is below 20 bar, the system must be re-

charged by means of the override button (see Section 7, Para. 9).

Section 2 – Limitations

LIMITATIONS PLACARDS

4th Edition, Rev. 0

EASA Approved

Page 2 - 26

21.8. REAR SEATS

During Taxi, Take OFF, Landing (including Emergency Landing), both rear seats must be kept in the lowest and full aft position.

The following placard is located aside both rear seats.

Section 2 – Limitations

LIMITATIONS PLACARDS

4th Edition, Rev. 0

EASA Approved

Page 2 - 27

21.9. OTHER PLACARDS

Description

Placard

Place

Smoking ban

Instruments panel, right side

Ditching emergency exit: opening instructions

Ditching emergency exit handle: internal side

Ditching emergency exit: opening instructions

Ditching emergency exit handle: external side

Door locking system: bypass instructions

Main door and emergency exit: external side

Door locking system: bypass instructions

Main door and emergency exit: internal side

Main door: exit instructions

Main door, internal side

Emergency exit label

Emergency exit: internal and external side

Page 2 - 28

Section 2 – Limitations

4th Edition, Rev. 0

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GARMIN G950 IFDS - Supplement

Page S2 - 29

Section 2 – Limitations

KOEL

4th Edition, Rev. 0

EASA Approved

22. KINDS OF OPERATIONS EQUIPMENT LIST

This paragraph reports the KOEL table, concerning the equipment list required on board under CS-23 regulations to allow flight operations in VFR Day, VFR Night, IFR Day and IFR Night conditions.

Flight in VFR Day and Night, IFR Day and Night is permitted only if the prescribed equipment is installed and operational.

Additional equipment, or a different equipment list, for the intended operation may be required by national operational requirements and also depends on the route to be flown.

GARMIN G950 IFDS - Supplement

Section 2 – Limitations

KOEL

4th Edition, Rev. 0

Page S2 - 30

EASA Approved

Equipment

VFR Day

VFR Night

IFR Day

IFR Night

Magnetic compass

● ● ●

●

GDU 1040 - Display Unit (2)

● ● ●

●

GIA 63W - Integrated Avionics Unit (2)

● ● ●

●

GDC 74A - Air Data Computer

● ● ●

●

GTP 59 - OAT sensor

● ● ●

●

GRS 77 - AHRS

● ● ●

●

GMU 44 - Magnetometer

● ● ●

●

GMA 1347 - Audio panel/Marker beacon

● ● ●

●

GTX 33 - Transponder

● ● ●

●

Standby Airspeed indicator

● ● ●

●

Standby Attitude indicator (electric)

● ● ●

●

StandbyAltimeter

● ● ●

●

Pitot heating system

● ● ●

●

Clock

● ● ●

●

Breakers panels

● ● ●

●

First Aid kit

● ● ●

●

Fire extinguisher

● ● ●

●

Fire detectors (2)

● ● ●

●

Instruments lights

● ● ●

●

Position lights

● ● ●

●

Landing light

● ● ●

●

Taxi light

● ● ●

●

Strobe lights

● ● ●

●

Torch

● ●

●

Cabin light

● ●

●

Cockpit lights

● ●

●

Emergency light

● ● ●

●

Volt-Ammeter

● ● ●

●

LG position and transition lights

● ● ●

●

ELT

● ● ●

●

Alternate static source

● ● ●

●

MAP indicator (dual)

● ● ●

●

RPM indicator (2)

● ● ●

●

Oil pressure indicator (2)

● ● ●

●

Oil temperature indicator (2)

● ● ●

●

CHT (2)

● ● ●

●

Fuel pressure indicator (2)

● ● ●

●

Fuel quantity indicator (2)

● ● ●

●

Longitudinal trim indicator

● ● ●

●

Rudder trim indicator

● ● ●

●

Flaps position indicator

● ● ●

●

Stall warning system

● ● ●

●

DME

●

ADF

●

VFR Day

VFR Night

IFR Day

IFR Night

Section 2 – Limitations

4th Edition, Rev. 0

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Section 2 – Limitations

4th Edition, Rev. 0

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Garmin G950 IFDS -Supplement

Page S3 - 1

Section 3 – Emergency procedures

INDEX

4th Edition, Rev. 0

SECTION 3 – EMERGENCY PROCEDURES

INDEX

1. INTRODUCTION .................................................................................................. 3

1.1. Engine failure during takeoff run ........................................................................ 3

2. Airplane alerts .................................................................................................... 6

2.1 Single alternator failure / overvoltage................................................................ 7

2.2 Both alternators failure ...................................................................................... 8

2.3 Both alternators overvoltage ............................................................................. 9

2.4 Failed door closure ........................................................................................... 10

2.5 Pitot heating system failure ............................................................................. 11

2.6 Coolant liquid low level .................................................................................... 12

2.7 Gear Pump failure ............................................................................................. 13

2.8 Engine fire ......................................................................................................... 14

2.9 Loss of information displayed .......................................................................... 15

2.10 Loss of airspeed information ........................................................................... 15

2.10 Loss of attitude information ............................................................................. 16

2.11 Loss of altitude information ............................................................................. 16

2.12 Loss of vertical speed information ................................................................... 17

2.13 Loss of heading information ............................................................................. 17

2.14 Display failure ................................................................................................... 19

3. ENGINE SECURING ........................................................................................... 21

4. POWERPLANT EMERGENCIES .......................................................................... 23

4.1 Propeller overspeeding ..................................................................................... 23

4.2 CHT limit exceedance ...................................................................................... 24

4.3 Oil temperature limit exceedance ................................................................... 25

4.4 Oil pressure limits exceedance ........................................................................ 26

4.5 Low fuel pressure ............................................................................................. 27

5. Other emergencies .............................................................................................. 29

5.1 Emergency descent .......................................................................................... 29

5.2 Total electrical failure ...................................................................................... 29

5.3 Static ports failure ............................................................................................ 30

5.4 Unintentional flight into icing conditions .......................................................... 31

5.5 Carburettor icing ................................................................................................ 32

5.6 Flaps control failure ......................................................................................... 33

6 ONE ENGINE INOPERATIVE PROCEDURES ...................................................... 34

6.1 Characteristic airspeeds with one engine inoperative .................................... 35

6.2 Inflight engine restart ....................................................................................... 36

6.3 Engine failure during takeoff run ...................................................................... 37

6.4 Engine failure during climb ............................................................................... 39

6.5 Engine failure in flight ...................................................................................... 40

6.6 One engine inoperative landing ........................................................................ 41

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Page S3 - 2

Section 3 – Emergency procedures

INDEX

4th Edition, Rev. 0

7 LANDING GEAR SYSTEM FAILURES................................................................. 42

7.1 Emergency landing gear extension .................................................................. 42

7.2 Complete Gear up or nose gear up landing ...................................................... 43

7.3 Partial Main LG extension ................................................................................ 45

7.4 Failed retraction ............................................................................................... 47

7.5 Unintentional landing gear extension .............................................................. 47

8 SMOKE AND FIRE OCCURRENCE ..................................................................... 49

8.1 Engine fire on the ground ................................................................................ 49

8.2 Engine fire during takeoff run ........................................................................... 50

8.3 Engine fire in flight ......................................................................................... 52

8.4 Electrical smoke in cabin on the ground ........................................................ 52

8.5 Electrical smoke in cabin during flight ............................................................ 53

9 UNINTENTIONAL SPIN RECOVERY .................................................................. 55

10 LANDING EMERGENCIES .................................................................................. 56

10.1 Landing without engine power ......................................................................... 56

10.2 Landing with Nose landing gear tire deflated .................................................. 58

10.3 Landing with a known main landing gear tire deflated ................................... 59

10.4 Landing without brakes .................................................................................... 60

11 AIRCRAFT EVACUATION .................................................................................. 61

12 DITCHING .......................................................................................................... 62

Garmin G950 IFDS -Supplement

Page S3 - 3

Section 3 – Emergency procedures

INTRODUCTION

4th Edition, Rev. 0

1. INTRODUCTION

Section 3 includes checklists and detailed procedures for coping with various types of emergency conditions that could arise after a system failure.

Before operating the aircraft, the pilot should become thoroughly familiar with this manual and, in particular, with this Section. Further on a continued and appropriate training and self study should be done.

Two types of emergency procedures are hereby given.

a. “BOLD FACES” which must be known by heart by the pilot and executed, in

the correct and complete sequence, immediately after the failure is detected and confirmed. These procedures characters are boxed and highlighted:

1.1. ENGINE FAILURE DURING TAKEOFF RUN

BEFORE ROTATION: ABORT TAKE OFF

1. Throttle Lever BOTH IDLE

2. Rudder Keep heading control

3. - -

4. - -

b. “other procedures” which should be well theoretically known and mastered,

but that can be executed entering and following step by step the AFM current section appropriate checklist.

Additionally operating the aircraft, the pilot should become thoroughly familiar with the Garmin G950 Pilot’s Guide for Tecnam P2006T (P/N 190-01146-XX) – last issue - and, in particular, with the present AFM Section.

CAUTION

Garmin G950 Pilot’s Guide for Tecnam P2006T (P/N 19001146-XX) – last issue - must be carried onboard the airplane at all times.

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Page S3 - 4

Section 3 – Emergency procedures

INTRODUCTION

4th Edition, Rev. 0

WARNING

Garmin G950 has a very high degree of functional integrity. However, the pilot must recognize that providing monitoring and/or self-test capability for all conceivable system failures is not practical. Although unlikely, it may be possible for erroneous operation to occur without a fault indication shown by the G950. It is thus the responsibility of the pilot to detect such an occurrence by means of crosschecking with all redundant or correlated information available in the cockpit.

In any case, as a failure or abnormal behaviour is detected pilots should act as follows:

1. Keep self-control and maintain aircraft flight attitude and parameters

2. Analyse the situation identifying, if required, the area for a possible emergency landing

3. Apply the pertinent procedure

4. Inform the Air Traffic Control as applicable

For the safe conduct of later flights, any anomaly and/or failure must be communicated to the National Authorities in charge, in order to put the aircraft in a fully operational and safe condition.

In this Chapter, following definitions apply: Land as soon as possible: land without delay at the nearest suitable area at which a safe approach and landing is assured. Land as soon as practical: land at the nearest approved landing area where suitable repairs can be made.

NOTE

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Section 3 – Emergency procedures

INTRODUCTION

4th Edition, Rev. 0

INTENTIONALLY LEFT BLANK

Garmin G950 IFDS -Supplement

Page S3 - 6

Section 3 – Emergency procedures

FAILURE LIST

4th Edition, Rev. 0

2. AIRPLANE ALERTS

Annunciation Window, located to the right of the Altimeter and Vertical Speed Indicator, supplies 16 alerts for warnings and cautions along with safe operating annunciations. The colours 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

Warning alert text is shown in red in the Annunciation Window and is accom-

panied by a continuous chime and a flashing WARNING Softkey annunciation. Selecting the WARNING Softkey acknowledges the presence of the warning alert and stops the aural chime.

Caution alert text is shown in yellow in the Annunciation Window and is accompanied by a single chime and a flashing CAUTION Softkey annunciation. Selecting the CAUTION Softkey acknowledges the presence of the caution alert. Caution voice alerts repeat three times or until acknowledged by selecting the CAUTION Softkey.

All aircraft annunciations can be displayed simultaneously in the Annunciation Window. A white horizontal line separates annunciations that are acknowledged from annunciations that are not yet acknowledged. Higher priority annunciations are displayed towards the top of the window.

In order to give a short description about the airplane alerts, text messages are displayed on the Alerts Window: pressing the ALERTS Softkey displays the Alerts Window, pressing the ALERTS Softkey a second time removes the Alerts Window from the display. When the Alerts Window is displayed, the FMS knob can be used to scroll through the alert message list.

Garmin G950 IFDS -Supplement

Page S3 - 7

Section 3 – Emergency procedures

Single alternator failure / overvoltage

4th Edition, Rev. 0

2.1 SINGLE ALTERNATOR FAILURE / OVERVOLTAGE

Annunciation window

Alert window

L ALT FAIL

Lh Alternator

R ALT FAIL

Rh Alternator

1. FIELD LH (or RH)

OFF

2. FIELD LH (or RH)

If the LH (or RH) ALT caution stays displayed

3. FIELD LH (or RH)

4. Avionic LH

5. ADF

OFF OFF OFF

Switching OFF avionic LH and ADF will permit to shed nonessential electrical power. The battery and a single generator are able to supply the electrical power necessary for flight, but redundancy is lost.

If conditions permit:

Switching CROSS BUS OFF will further reduce alternator load; the decision mainly depends on weather conditions.

6. CROSS BUS LH (or RH) OFF

Equipment will be lost accordingly to the following table:

LH Gen Bus

LH Avionic Bus

RH Avionic Bus

RH Gen Bus

Pitot Heat

DME

ADF

NAV Lights

Landing Light

Transponder

COM 2

Rudder Trim

Taxi Light

A/P

NAV 2

Stall Warning

A/P Pitch Trim

MFD AHRS/ADC*

* AHRS /ADC are fed from battery bus if Mod 2006/135 is embodied

7. Land as soon as practicable

NOTE

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Page S3 - 8

Section 3 – Emergency procedures

AIRPLANE ALERTS

4th Edition, Rev. 0

2.2 BOTH ALTERNATORS FAILURE

Annunciation window

Alert window

L ALT FAIL

Lh Alternator

R ALT FAIL

Rh Alternator

In event of both L and R ALT FAIL caution alerts displayed:

1. FIELD LH and RH

BOTH OFF

2. FIELD LH and RH

BOTH ON

If the LH (or RH) ALT caution stays displayed

1. Verify good ammeter indications on restored alternator

2. Refer to Single alternator failure / overvoltage drill (Para 2.1)

If both LH and RH ALT cautions stay displayed

3. FIELD LH and RH

BOTH OFF

4. CROSS BUS LH and RH

BOTH OFF

If engine starting battery modification is applied

5. EMERG BATT switch

6. Land as soon as possible.

If engine starting battery modification is not applied

5. Land as soon as possible.

Equipment will be lost accordingly to the following table:

LH Gen Bus

LH Avionic Bus

RH Avionic Bus

RH Gen Bus

Pitot Heat

DME

ADF

NAV Lights

Landing Light

Transponder

COM 2

Rudder Trim

Taxi Light

A/P

NAV 2

Stall Warning

A/P Pitch Trim

MFD AHRS/ADC*

AHRS /ADC are fed from battery bus if Mod 2006/135 is embodied

The battery can supply electrical power for at least 30 minutes.

NOTE

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Page S3 - 9

Section 3 – Emergency procedures

Both alternators failure

4th Edition, Rev. 0

2.3 BOTH ALTERNATORS OVERVOLTAGE

Annunciation window

Alert window

L BUS VOLT HIGH

Lh overvoltage

R BUS VOLT HIGH

Rh overvoltage

In event of both L and R BUS VOLT HIGH warning alerts displayed:

1. FIELD LH and RH

BOTH OFF

2. FIELD LH and RH

BOTH ON (one at a time)

If the LH (or RH) BUS VOLT HIGH warning is still displayed

3. Verify good ammeter indications on restored alternator

4. Refer to Single alternator failure / overvoltage drill (Para 2.1)

If both LH and RH BUS VOLT HIGH warning are still displayed

3. CROSS BUS LH and RH

BOTH OFF

4. FIELD LH and RH

BOTH OFF

5. FIELD LH and RH

BOTH ON (one at a time)

If LH (or RH) BUS VOLT HIGH warning is still displayed

6. Verify good ammeter indications on restored alternator

7. Switch CROSS BUS on the restored alternator side

8. Refer to Single alternator failure / overvoltage drill (Para 2.1)

If both LH and RH BUS VOLT HIGH warning are still displayed

6. FIELD LH and RH

BOTH OFF

If engine starting battery modification is applied

7. EMERG BATT switch

8. Land as soon as possible.

If engine starting battery modification is not applied

7. Land as soon as possible

Equipment will be lost accordingly to the following table:

AHRS /ADC are fed from battery bus if Mod 2006/135 is embodied

LH Gen Bus

LH Avionic Bus

RH Avionic Bus

RH Gen Bus

Pitot Heat

DME

ADF

NAV Lights

Landing Light

Transponder

COM 2

Rudder Trim

Taxi Light

A/P

NAV 2

Stall Warning

A/P Pitch Trim

MFD

AHRS/ADC*

The battery can supply electrical power for at least 30 minutes.

NOTE

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Both alternators failure

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2.4 FAILED DOOR CLOSURE

Annunciation window

Alert window

PILOT DR OPEN

Main door open

REAR DR OPEN

Rear door open

In case of door opening / unlocking, related PILOT or REAR DR OPEN alert is displayed. In this case, apply following procedure:

ON THE GROUND

1. Passengers and crew seat belts

2. Affected door

Fasten and tighten Verify correctly closed

If door is open

3. Relevant engine

Shut down

4. Affected door

Close and check

If door is closed

3. Locking device

Check

If down in unlocked position

4. Abort mission.

IN FLIGHT

1. Passengers and crew seat belts

2. Affected door and locked device

Fasten and tighten Verify correctly closed

If door is open or locking device is unlocked

3. Land as soon as possible

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2.5 PITOT HEATING SYSTEM FAILURE

Annunciation window

Alert window

PITOT HEAT ON

Pitot heat

PITOT HEAT

Pitot heat

When the Pitot Heating system is activated, the green PITOT HEAT advisory light is turned ON. If the amber PITOT HEAT caution light turns OFF, then the Pitot Heating system is functioning properly. Anytime the amber PITOT HEAT caution light is ON at the same time the green PITOT HEAT light is ON, then the Pitot Heating system is not functioning properly.

1. Pitot heat switch

OFF

2. Verify Pitot Heating circuit breaker is IN

3. Pitot heat switch

4. Check PITOT HEAT caution light:

If the amber light stays ON, assume a failure in the pitot heating system. Avoid visible moisture and OATs below 10 deg C.

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2.6 COOLANT LIQUID LOW LEVEL

Annunciation window

Alert window

L COOLANT LOW

Lh Low Coolant

R COOLANT LOW

Rh Low Coolant

When the engine coolant liquid level goes under the lower limit, the related L or R COOLANT LOW warning alert is displayed. Low coolant level condition may lead to high CHT/CT. When the warning is displayed, apply following procedure:

1. Check affected engine CHT/CT

If CHT is above 135°C or CT is above 120°C

2. Affected engine

Reduce power setting to reduce CHT/CT up to the minimum practical

3. Land as soon as practical

If CH/CT continues to rise and engine shows roughness or power loss

4. Affected engine

SECURE (securing procedure on Para. 4)

5. Land as soon as possible applying one engine inoperative landing proce-

dure. See Para. 6.6

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2.7 GEAR PUMP FAILURE

Annunciation window

Alert window

GEAR PUMP ON

Gear powered

The GEAR PUMP ON caution light turns ON when the landing gear hydraulic pump is electrically supplied.

After the landing gear retraction, if the red TRANS light turns OFF and the GEAR PUMP ON caution stays turned ON, this could indicate a gear pump relay failure to ON.

If TRANS light is OFF

1. Continue the mission monitoring the caution light.

If TRANS light is ON

2. Landing gear is not locked in UP position

The electrical gear pump, continuously supplied, causes a current absorption which does not affect the mission unless this failure is coupled with the overall electrical failure. In this case, the residual battery endurance may be consistently lower than 30 minutes.

NOTE

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2.8 ENGINE FIRE

Annunciation window

Alert window

LH ENGINE FIRE

Left engine fire detected

RH ENGINE FIRE

Right engine fire detected

In event of engine fire, the LH or RH ENGINE FIRE warning alert is displayed. Refer to following procedures:

FIRE ON THE GROUND: see Para. 8.1 FIRE DURING TAKEOFF RUN: see Para. 8.2 FIRE IN FLIGHT: see Para. 8.3

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G950 SYSTEM FAILURES

4th Edition, Rev. 0

2.9 LOSS OF INFORMATION DISPLAYED

When a LRU or a LRU function fails, a large red ‘X’ is typically displayed on the display field associated 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. Refer to G950 Pilot’s Guide for Tecnam P2006T (P/N 190-01146-00), last issue, Appendix A, Message Advisories list.

2.10 LOSS OF AIRSPEED INFORMATION

AIRSPEED FAIL

(RED X ON DISPLAY FIELD)

Display system is not receiving airspeed input

from the Air Data Computer.

INSTRUCTION: revert to standby analogical airspeed indicator

NOTE

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G950 SYSTEM FAILURES

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2.10 LOSS OF ATTITUDE INFORMATION

ATTITUDE FAIL

(RED X ON DISPLAY FIELD)

Display system is not receiving attitude information

from the AHRS.

INSTRUCTION: revert to standby analogical attitude indicator

2.11 LOSS OF ALTITUDE INFORMATION

ALTITUDE FAIL

(RED X ON DISPLAY FIELD)

Display system is not receiving altitude input

from the Air Data Computer.

INSTRUCTION: revert to standby analogical altitude indicator

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G950 SYSTEM FAILURES

4th Edition, Rev. 0

2.12 LOSS OF VERTICAL SPEED INFORMATION

VERT SPEED FAIL

(RED X ON DISPLAY FIELD)

Display system is not receiving vertical speed input

from the Air Data Computer.

INSTRUCTION: determine vertical speed on the basis of altitude information

2.13 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

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G950 SYSTEM FAILURES

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2.14 DISPLAY FAILURE

In the event of a display failure, the G950 System automatically switches to reversionary (backup) mode. In reversionary mode, all important flight information is presented on the remaining display in the same format as in normal operating mode. The change to backup paths is completely automated for all LRUs and no pilot action is required.

if the system fails to detect a display problem

1. DISPLAY BACKUP button

PUSH

CAUTION

If a display fails, the related Integrated Avionics Unit (IAU) is cut off and can no longer communicate with the remaining display: consequently the NAV and COM functions provided to the failed display by the Integrated Avionics Unit are flagged as invalid on the remaining display.

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Section 3 – Emergency procedures

ENGINE SECURING

4th Edition, Rev. 0

3. ENGINE SECURING

Following procedure is applicable to shut-down one engine in flight:

1. Throttle Lever IDLE

2. Ignition BOTH OFF

3. Propeller Lever FEATHER

4. Fuel Selector OFF

5. Electrical fuel pump OFF

After securing engine(s), after analysing situation, refer immediately to following procedures:

ENGINE FAILURE IN FLIGHT: see Para. 6.5

SINGLE GENERATOR FAILURE: see Para. 2.1

or BOTH GENERATOR FAILURE: see Para. 2.2

INFLIGHT ENGINE RESTART: see Para. 6.2

ONE ENGINE INOPERATIVE LANDING: see Para. 6.6

or LANDING WITHOUT ENGINE POWER: see Para. 10.1

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Section 3 – Emergency procedures

POWERPLANT EMERGENCIES

4th Edition, Rev. 0

4. POWERPLANT EMERGENCIES

4.1 PROPELLER OVERSPEEDING

The aircraft is fitted with propeller/governor set by MT-Propeller such a way that the maximum propeller rpm exceedance is prevented. In case of propeller overspeeding in flight, apply following procedure:

1. Throttle Lever REDUCE power to minimum practical

2. Propeller Lever REDUCE as practical (not in feathering)

3. RPM indicator CHECK

If it is not possible to decrease propeller rpm, apply engine securing procedure (see Para. 3) and land as soon as possible applying one engine inoperative land- ing procedure (See Para. 6.6).

CAUTION

Maximum propeller rpm exceedance may cause the engine components damage. Propeller and engine shall be inspected in accordance with related Operators Manuals.

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POWERPLANT EMERGENCIES

4th Edition, Rev. 0

4.2 CHT LIMIT EXCEEDANCE

If CHT/CT exceeds its limit, apply following procedure:

1. Check affected engine CHT/CT

If CHT is above 135°C or CT is above 120°C

2. Affected engine

Reduce power setting to reduce CHT/CT up to the minimum practical

3. Land as soon as practical

If CHT/CT continues to rise and engine shows roughness or power loss

4. Affected engine

SECURE (securing procedure on Para. 3)

5. Land as soon as possible applying one engine inoperative landing proce-

dure. See Para. 6.6

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POWERPLANT EMERGENCIES

4th Edition, Rev. 0

4.3 OIL TEMPERATURE LIMIT EXCEEDANCE

If oil temperature exceeds maximum limit (130°C):

1. OIL PRESS

CHECK

If oil pressure is within limits

2. Affected engine

Reduce power setting to minimum applicable

3. Affected engine

Keep propeller speed higher than 2000 RPM

If oil pressure does not decrease

4. Airspeed

INCREASE

If oil temperature does not come back within limits, the thermostatic valve, regulating the oil flow to the heat exchangers, could be damaged or an oil leakage can be present in the oil supply line.

5. Land as soon as practical keeping the affected engine to the mini-

mum necessary power

6. Monitor OIL PRESS and CHT/CT

if engine roughness / vibrations or erratic behaviour is detected:

7. Affected engine

SECURE (engine securing procedure on Para. 3)

8. Land as soon as possible applying one engine inoperative landing pro-

cedure. See Para. 6.6

WARNING

Excessive oil pressure drop leads to a high pitch propeller configuration with consequent propeller feathering and engine stopping.

NOTE

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POWERPLANT EMERGENCIES

4th Edition, Rev. 0

4.4 OIL PRESSURE LIMITS EXCEEDANCE

If oil pressure exceeds its lower or upper limit (0.8 – 7 bar), apply following procedure:

WARNING

Excessive oil pressure drop leads to a high pitch propeller configuration with consequent propeller feathering and engine stopping.

An excessive oil pressure value can be counteracted by decreasing propeller rpm.

1. OIL PRESS CHECK

If oil pressure exceeds upper limit (7 bar)

2. Throttle Lever first REDUCE affected engine power by 10%

3. Propeller Lever Keep low rpm

4. OIL PRESS CHECK (verify if came back within the limits)

5. Land as soon as practical

If oil pressure is under the lower limit (0.8 bar)

2. Land as soon as practical

If oil pressure is continuously decreasing

3. Affected engine

SECURE (see engine securing procedure on Para. 3)

4. Land as soon as possible applying one engine inoperative landing procedure.

See Para. 6.6

NOTE

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POWERPLANT EMERGENCIES

4th Edition, Rev. 0

4.5 LOW FUEL PRESSURE

If fuel pressure decreases below the lower limit (2.2 psi), apply following procedure:

1. Fuel press CHECK

2. Fuel quantity CHECK

3. Fuel consumption MONITOR

If a fuel leakage is deemed likely

5. Land as soon as possible.

If a fuel leakage can be excluded:

4. Electrical fuel pump ON

5. Feed the affected engine by means of opposite side fuel tank

If pressure does not come back within the limits

6. Land as soon as practical

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OTHER EMERGENCIES

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5. OTHER EMERGENCIES

5.1 EMERGENCY DESCENT

CAUTION

Descent with airspeed at VLE, idle power and gear down will provide high descent rates and pitch attitudes up to -15°.

Anticipate altitude capture and return to level flight during emergency descent in order to assure a safe and smooth recovery from maneuver.

1. Power levers IDLE

2. Flaps UP

3. IAS below VLO/VLE

4. Landing gear DOWN

5. Airspeed Up to VLE

5.2 TOTAL ELECTRICAL FAILURE

In case of electrical system overall failure, apply following procedure:

1. Emergency light ON if necessary

2. MASTER SWITCH OFF

3. FIELD LH and RH BOTH OFF

4. MASTER SWITCH ON

5. FIELD LH and RH BOTH ON

If failure persists

9. EMERG BATT switch ON (if engine starting battery

installed)

10. Land as soon as possible applying emergency landing gear extension

procedure (see Para. 7.1)

WARNING

An electrical system overall failure prevents flaps operation: landing distance without flaps increases of about 25%.

CAUTION

A fully charged battery can supply electrical power for at least 30 minutes.

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5.3 STATIC PORTS FAILURE

In case of static ports failure, the alternate static port in the cabin (shown below) must be activated.

1. Cabin ventilation OFF (hot and cold air)

2. ALTERNATE STATIC PORT VALVE OPEN

3. Continue the mission

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5.4 UNINTENTIONAL FLIGHT INTO ICING CONDITIONS

1. Carburettor heat BOTH ON

2. Pitot heat ON

3. Fly as soon as practical toward a zone clear of visible moisture, precipita-

tion and with higher temperature, changing altitude and/or direction.

4. Control surfaces Move continuously to avoid locking

5. Propellers rpm INCREASE to prevent ice build-up on the blades

WARNING

In event of ice build-up in correspondence of wing leading edges, stall speed increases.

WARNING

Ice build-up on wing, tail fin or flight control surfaces unexpected sudden roll and/or pitch tendencies can be experienced and may lead to unusual attitude and loss of aircraft control.

WARNING

Do not use Autopilot when icing formation is suspected or detected.

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OTHER EMERGENCIES

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5.5 CARBURETTOR ICING

DURING TAKEOFF

The carburettor icing in “full throttle” mode is unlikely. Take off in known or suspected icing formation is forbidden; in order to dispose

of full engine take off power, take-off must be performed with carburettor heating OFF.

IN FLIGHT

Carburettor icing is considered probable when external air temperature is below 15° C and visible air moisture (clouds, mist, haze or fog) or atmospheric precipitation are present.

Generally, an OAT-to-dew point temperature spread lower than 10°C and OAT less than 15°C with visibility lower than 5 km is a positive indication of likely icing formation condition.

Should an inadvertent flight into known or forecast icing condition happen carburettor heating should be selected “ON” as soon as possible: the greater the advance carburettors are warmed the better the chances not to form ice and avoid engine power loss or reduction.

Keep Carb Heating “ON” until engine power is restored and area of possible icing condition is exited.

CAUTION

Carburettor Heating selected to “ON” will cause engine RPM reduction of about 100 RPM causing a sensible available engine power decrease.

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OTHER EMERGENCIES

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5.6 FLAPS CONTROL FAILURE

DURING TAKEOFF

CAUTION

Flap UP take off, requires a T/O distance (50 ft height obstacle distance) increased by about 20%.

1. Airspeed Keep below 93 KIAS

2. Land as soon as practical

DURING APPROACH/LANDING

CAUTION

If the flaps control fails, consider the higher stall speed (see Section 5, Para. 6, “Stall Speed”) and an increased landing distance of about 25%.

1. Airspeed Keep over 75 KIAS

2. Land as soon as practical on a runway of appropriate length

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ONE ENGINE INOPERATIVE PROCEDURES

6 ONE ENGINE INOPERATIVE PROCEDURES

CAUTION

The ineffectiveness of one engine results in asymmetric traction which tends to yaw and bank the aircraft towards the inoperative engine. In this condition it is essential to maintain the direction of flight compensating the lower traction and counteracting the yawing effects by mean of rudder pedals. To improve directional control, it is advisable to bank the aircraft of about 5° to the side of the operating engine.

In addition, reduced available overall power and extended control surfaces will lead to a performances drop: a quick pitch attitude reduction will allow to keep a minimum safety airspeed.

The higher is the airspeed the better will be lateral and directional control efficiency: never allow airspeed to drop below V

MCA

CAUTION

Best residual climb performances in OEI (One Engine Inoperative) condition have been recorded in Flap Up configuration and at V

YSE

, which is marked as a Blue Line on the Airspeed indicator (calculated for maximum Take Off Weight and Sea, Level ISA condition) For actual condition V

YSE

refer to Section 5 Para. 13, “One engine rate of

climb”.

XSE

is actually very close to V

YSE

in any condition, thus best climb performance will also be associated with best climb angle (gradient) performance. Refer to Section 5 Para. 14, One-Engine Rate of Climb at V

xSE

, for relevant data.

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ONE ENGINE INOPERATIVE PROCEDURES

6.1 CHARACTERISTIC AIRSPEEDS WITH ONE ENGINE INOPERATIVE

In case of one engine inoperative condition (OEI), pilot shall take into account the airspeeds shown below:

Conditions

Speed

(KIAS)

Minimum aircraft control speed with one engine inoperative and flaps set to T.O. (VMC)

Best rate-of-climb speed OEI (V

YSE

)

MTOW 1180 kg

MTOW 1230 kg

Best gradient speed OEI (V

XSE

)

Reference is made to MTOW, 1180 kg and 1230 kg, at Sea Level and ISA condition (if Supplement G10- Increased MTOW @1230 KG - is applicable).

NOTE

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Section 3 – Emergency procedures

ONE ENGINE INOPERATIVE PROCEDURES

6.2 INFLIGHT ENGINE RESTART

WARNING

After:

- mechanical engine seizure;

- fire;

- major propeller damage

engine restart is not recommended.

1. Carburettor heat ON if required

2. Electrical fuel pump ON

3. Fuel quantity indicator CHECK

4. Fuel Selector CHECK (Crossfeed if required)

5. FIELD OFF

6. Ignition BOTH ON

7. Operating engine Throttle Lever SET as practical

8. Stopped engine Throttle Lever IDLE

9. Stopped engine Propeller Lever FULL FORWARD

10. Start push-button PUSH

11. Propeller Lever SET at desired rpm

12. FIELD ON (check for positive ammeter)

13. Engine throttle levers SET as required

If engine restart is unsuccessful

14. EMERG BATT switch ON (if starting battery installed)

15. Repeat engine restart procedure

CAUTION

After engine restart, if practical, moderate propeller rpm and throttle increase to allow OIL and CHT/CT temperatures for stabilizing in the green arcs.

If the fuel quantity in the tank which feeds the stopped engine is low, select the opposite side fuel tank by means of the fuel selector.

If engine restart is still unsuccessful:

16. Affected engine

SECURE (see engine securing procedure Para. 3)

17. Land as soon as possible applying one engine inoperative landing procedure. See

Para. 6.6

NOTE

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Section 3 – Emergency procedures

ONE ENGINE INOPERATIVE PROCEDURES

6.3 ENGINE FAILURE DURING TAKEOFF RUN

BEFORE ROTATION: ABORT TAKE OFF

1. Throttle Lever BOTH IDLE

2. Rudder Keep heading control

3. Brakes As required

When safely stopped:

4. Failed Engine Ignition BOTH OFF

5. Failed Engine Field OFF

6. Failed Engine Electrical fuel pump OFF

IF THE DECISION IS TAKEN TO CONTINUE THE TAKEOFF:

WARNING

A take-off abort should always be preferred if a safe stop can be performed on ground.

A suggested “GO-NO-GO” criteria is: abort take-off until LG is still down and locked.

Once airborne accelerate to Blue Line Speed (V

YSE

) before command-

ing LG retraction. Take-off planning should take into account that high density altitude

and aircraft mass may result in OEI negative climb rate. V

YSE

with flap up shall be flown in order to achieve best possible rate

of climb after landing gear retraction and engine feathering.

1. Operating engine Throttle Lever FULL POWER

2. Operating engine Propeller Lever FULL FORWARD

3. Heading Keep control using rudder and

ailerons

4. Attitude Reduce as appropriate to keep

airspeed over 62 KIAS

5. Inoperative engine Propeller Lever FEATHER

6. Landing gear control lever UP

7. Airspeed V

XSE/VYSE

as required

8. Flaps 0°

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ONE ENGINE INOPERATIVE PROCEDURES

At safe altitude

9. Inoperative engine Confirm and SECURE

10. Operative engine Electrical fuel pump Check ON

11. Operating engine Check engine instruments

12. Operating engine Fuel Selector Check correct feeding (crossfeed

if needed)

If engine restart is recommended:

13. Apply INFLIGHT ENGINE RESTART procedure see Para 6.2

If engine restart is unsuccessful or it is not recommended:

13. Land as soon as possible

14. One engine inoperative landing procedure. see Para. 6.6

WARNING

Following:

- mechanical engine seizure;

- fire;

- major propeller damage

engine restart is not recommended.

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ONE ENGINE INOPERATIVE PROCEDURES

6.4 ENGINE FAILURE DURING CLIMB

1. Autopilot OFF

2. Heading Keep control using rudder and ailerons

3. Attitude Reduce as appropriate to keep airspeed

over 62 KIAS

4. Operating engine Throttle Lever FULL THROTTLE

5. Operating engine Propeller Lever FULL FORWARD

6. Operative engine Electrical fuel pump Check ON

7. Inoperative engine Propeller Lever FEATHER

8. Inoperative engine Confirm and SECURE

If engine restart is possible:

9. Apply INFLIGHT ENGINE RESTART procedure see Para 6.2

If engine restart is unsuccessful or it is not recommended:

9. Land as soon as possible

10. One engine inoperative landing procedure. see Para. 6.6

WARNING

Following a mechanical engine seizure, fire or a major propeller damage engine restart is not recommended.

WARNING

Continuation of flight to a safe landing runway must be planned taking into account maximum operating ceiling in OEI condition. Refer to Section 5 Para 1, “One-engine rate of climb”.

Tecnam P2006T Aircraft Flight Manual

Specifications and Main Features

Frequently Asked Questions

User Manual