Aircraft Flight Manual
TECNAM P2008 · Pilot's Operating Handbook
Overview
The Tecnam P2008 Aircraft Flight Manual provides essential information for the safe and efficient operation of the P2008 JC model, a single-engine two-seat aircraft. It includes details on aircraft specifications, performance, limitations, and operational procedures.
- The P2008 JC is a single-engine, two-seat aircraft.
- It features a strut-braced high wing and fixed landing gear.
- The manual must be carried in the aircraft at all times.
- It is approved for EASA CS-VLA certified airplanes.
- The aircraft has a maximum takeoff weight of 650 kg.
- The engine is a Bombardier-Rotax 912 S2 with a maximum power of 73.5 kW.
- The propeller is a Hoffman HO 17GHM A 174 177C with a diameter of 1740 mm.
- The manual includes emergency procedures and performance data.
Document
Source
Originally published by squarespace.com. Sprinkle hosts a reference copy with an added summary, specifications and searchable full text.
Document details
- Type ·
- Pilot's Operating Handbook
- Year ·
- 2018
- File size ·
- 18 MB
- Publisher ·
- squarespace.com
- Language ·
- en
Specifications & performance
Extracted from this document.
Specifications
- Wing span m ·
- 9.00
- Wing area m2 ·
- 12.16
- Overall width m ·
- 2.90
- Overall height m ·
- 2.67
- Overall length m ·
- 6.93
- Stabilator span m ·
- 1.8
- Stabilator area m2 ·
- 2.03
- Vertical tail area m2 ·
- 1.06
Performance
- Max takeoff weight kg ·
- 650
- Wing loading kg per m2 ·
- 53.5
- Power loading kg per (hp) ·
- 6.59
Weight & balance
- Max takeoff weight kg ·
- 650
What is the Aircraft Flight Manual?
The Aircraft Flight Manual is a pilot's operating handbook for the TECNAM P2008, dated 2018.
Where does the Aircraft Flight Manual come from?
This copy of the Aircraft Flight Manual was originally published by squarespace.com and is hosted on Sprinkle as a free, searchable reference copy.
What year was the Aircraft Flight Manual published?
The Aircraft Flight Manual — the TECNAM P2008 pilot's operating handbook on file — is dated 2018.
Most owners only have the POH. Here's the essential set for the TECNAM P2008.
- Pilot's Operating Handbook / AFM
- Checklist
- Maintenance Manual
- Parts Catalog (IPC)
- Systems & Wiring
- Service Bulletins on file
- Type Certificate (TCDS)
More TECNAM P2008manuals & documents
In this document
General
This section provides an introduction to the aircraft, certification basis, and definitions of warnings, cautions, and notes used in the manual.
Limitations
Details the operational limitations and procedures that must be followed to ensure safe operation of the aircraft.
Emergency Procedures
Outlines the necessary actions to take in various emergency situations to ensure pilot and passenger safety.
Normal Procedures
Describes standard operating procedures for the aircraft during normal flight operations.
Performance
Provides performance data including speeds, ranges, and other critical performance metrics for the aircraft.
Weight and Balance
Includes information on weight limits and center of gravity considerations for safe operation.
Safety notes
- Non-observance of procedures may lead to immediate degradation of flight safety.
- Warnings indicate critical safety procedures that must be followed.
- Cautions indicate procedures that may lead to minor safety degradation if not followed.
- The manual must be kept up-to-date by the owner.
- The aircraft must be operated in compliance with the procedures and limitations contained in the manual.
Full document text
/ 1 MANlJF ACTURER: AIRCRAFTMODEL: Aircraft Flight Manual Doc. No. 2008/100 Ed. 2 - Rev. 1 2018, March 12th .-····-··-····-······--··\ : l :....~•············~ · TECNAM P2008 JC C. A. TECNAM S.r.l. P2008JC EASA T YPE CERTTFICAT E NR. : A .583 (DATED2013, 27 SEPTEMBER) SERJAL NUMBER: ....J.043 ............ . B UILDYEAR: ...... ~ oJ.5......... . REGISTRATION MARKINGS: ..qb.-~.~.8 ..1...... This Aircrafl Flight Manual is approved and applies on/y to EASA CS-VLA certifled airplanes. This Manual must be carried in the airplane at all times. This aeroplane has to be operated in compliance with procedures and limitations contained herein. Costruzioni AeronauticheTECNAM srl Via Maiorise CAPUA (CE) - Italy Tel. +39-0823 997538 WEB: www.tecnam.com SECTION 0 INDEX 1. RECORD OF REVISIONS .......................................................................................... 3 2 . LIST OF EFFECTIVE PAGES .................................................................................... 7 3. FOREWORD .............................................................................................................. 9 4. SECTIONS LIST ...................................................................................................... 10 Aircraft Flight Manual INDEX Ed. 2, Rev. 0 1. RECORD OF REVISIONS Any revision to the present Manual, except actual weighing data, is recordecl:a Record of Revisions is provided in this Section and the operator is advised to make sure that the record iskepl up-to-date. Thc Manual issue is identificd by Edition and Revision codcs rcported on each page, lower right siele. The revision code is numerical and consists of the number "O"; subsequentrevi- sions are identified by the change of the code from "O"to "1" for the firstrevision to the basic publication, "2" for the second one, etc. Should be necessary tocompletely 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 which results in un- changed 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: lt is the responsibility of the owner to maintain this handbook in a current status when it is being used for operational purposes. Aircraft Flight Manual RECORD OF REVISIONS Ed. 2, Rev. 0 .p· .. ···. ·,,.. Rev ..Rev:ised No ·:.pl,lge . '· \. '· .· ., 0 all 0-1,4,7 2-6 3-20 4-3, 4-4 J 4-9, 4-12 tbru 17 6-9 6-11 tbrn 13 7-1,5 tbru 16 9-3 .Des~Hptiön of Rev'isidn. ,,.. ,,c''·. : . "' Editorial revision. Cover, RoR and LOEP updated. Airspeed indicator markings amended; the indicationis now proper for both analogue and dig- ital instruments. Note amended. Note amended;informationhave been added to airspeed for nor- mal operationstable; paragraph shifted from page 3 to page 4. Checklists amended;note to PFI revised; spced infonnation have been moved to page 4-3. W&B calculationsample. Equipment list. Contents rearranged. Supplements!ist updated. A. Sabino C. Carnso A. Sabino C. Caruso Aircraft Flight Manual RECORD OF REVISIONS M. Oliva M. Oliva Approvedunder the authority ofDOA, ref. EASA.2IJ.335 (MOD2008/097.180126) .Approvedunder the authority ofDOA, ref. EASA.211.335 (MOD2008/l03.180312) Ed. 2, Rev. 1 INTENTTONALLY LEFT BLANK Ed 2, Rev. 0 Aircraft Flight Manual lNTENTlONALL Y LEFT BLANK Ed. 2, Rev. 0 Aircraft Flight Manual 2. LIST OF EFFECTIVE PAGES The List of Effective Pages (LOEP), applicable to manuals of every operator, Iists all the basic AFM pages: each manual could contain either basic pages or one variant of these pages when the pages of some Supplementsare embodied. Pages affected by the ciment revision are indicated by an asterisk (*) following the re- vision code. Edition 1, Rev 0 Edition 1, Rev 1 Editi on 1, Rev 2 Editi on 1, Rev 3 Edition 1, Rev 4 Edition 1, Rev 5 Edition 1, Rev 6 Edition 2, Rev 0 Edition 2, Rev 1 Section 0 Section 1 Section 2 Section 3 Section 4 Section 5 Section 6 Section 7 Section 8 Section 9 30 Jul y 2013 25 March 201 5 7 April 2015 13 April 2015 14 July 2015 15 December 2015 20 December 2016 15 January 2018 12 March 2018 2, 3, 5, 6, 8,9, 10 1, 4, 7 1 thru 14 1 thru 5, 7thrn 30 6 1 tluu 19, 21, 22 20 1, 2, 5 thru 11, 13, 14, 18 3, 4, 12, 15 thru 17 1 thrn 16 1 tluu 8, 10, 14 9, 11 thru 13 2 thru 4 1, 5 thru 16 1 thrul0 1, 2 and4 3 Aircraft Flight Ma nual LOEP Rev0 Rev 1 Rev0 Rev0 Rev 1 RevO Rev 1 Rev0 Rev 1 Rev0 Rev0 Rev 1 Rev0 Rev 1 Rev0 Rev0 Rev 1 Ed. 2, Rev. 1 INTENTIONALL Y LEFT BLANK Ed. 2, Rev. 0 Aircraft Flight Manual 3. FOREWORD Tecnam P2008 JC is a single-engine two-seat aircraft with a strut braced high wing and fixed landing gear. Section l provides general information and it contains definitions, symbols explana- tions, 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 AERONAUT!CHE TECNAMs.r.l. Via MAIORISE CAPUA (CE) - ITALY a+39 (0)823 997538 ~ airworthness@tecnam.com Aircraft Flight Manual FOREWORD Ed. 2, Rev. 0 4. SECTIONS LIST Ge neral (*) Section l Limitation s (**) Section 2 E merge ncy Procedures (**) Section 3 Normal Proceclures (**) Section 4 Performance(* **) Section 5 Wei ght ancl balance (*) Section 6 Airframe and Systems de scription (*) Section 7 Ground Handlin g and Serv ice (*) Section 8 AFM S uppl emen ts list (*) Sectio n 9
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(*) non-approved Section (**) appr oved Section (** '') appro ved Section exccpt l'or pages 5-1 thru 5-4, 5-6, 5-11 thru 5-13 Aircraft Flight Manual SECTIONS LIST Ed. 2, Rev. 0 SECTION 1 • GENERAL INDEX 1. INTRODUCTION .................................................................................................. 3 2. CERTIFICATION BASIS .................................................... ............................... .... 3 3. WARNINGS - CAUTIONS - NOTES ...................................................................... 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 ....................................................................... 8 10, UNIT CONVERSION CHART .............................................................................. 13 11. LITRES / US GALLONS CONVERSION CHART .................................................. 14 Section 1 - General INDEX Ed. 2. Rev 0 lNTENTIONALLY LEFT BLANK Section 1 - General Ed 2, Rev 0 1. INTRODUCTION The Flight Manual has been prepared to provide pilots and instructors with in- formation for the safe and efficient operation of this very light airplane. This manual includes the material required to be furnished to the pilot of CS- VLA. Ttalso contains supplernental data supplied by the airplane manufacturer. 2. CERTI FICATION BASIS This type of aircraft has been approved by the European Aviation Safety Agency in accordance with CS-YLA including Amendment I and the Type Certificate No.EASA.A.583 has been issued on (date) 27th September 2013. Category of Airworthiness: Normal Noise Certification Basis: EASA CS 36 Amendment 2. 3. WARNINGS - CAUT IONS - NOTES Following definitions apply to warnings, cautions and notes used in the Aircraft Flight Manual. WARNl NG CAUTTON 1 :;m :i meansthat the non-observationof the correspondingprocedureleads to an immediate or importantdegradationof the flight safety. meansthat the non-observationofthe correspondingprocedure leads to a minoror to a moreor less long termdegradation ofthe flight safety. drawsthe attentionto any special iternnot directlyrelated to safety but which is importantor unusual. Page 1 - 3 S ection 1 - General INTRODUCTION Ed. 2, Rev 0 4. THREE-VIEW AND DIMENSIONS Figure 1 - General views Section 1 - General THREE-VIEW AND DIMENSIONS Ed. 2, Rev 0 Dimensions Wing Wing Span Wing Area Aspect Ratio Taper Ratio Wing chord Fuse/age Overall length Overall width Overall height Empennage Stabilator span Stabilator area Vertical tail area Landing Gear Wheel track Wheel base Main gear t ire Nose Gear tire 9.00 m (29.5 ft) 12.16m 2 (l30.9ft 2) 6.7 0.8 l.373 m (4.5 ft) 6.93 m (22.9 ft) l.20 m (3.9 ft) 2.67 m (8.8 ft) 2.90 m (9.5 1 ft) 2.03 m2 (21.8 ft2) 1.06 m2 (11.4 ft2) 1.8 m (5.9 ft) 1.94 m (6.4 ft) 5.00-5 5.00-5 Section 1 - General GENERAL FEATURES Page 1 - 5 Ed 2, Rev 0 AFMS N °S7 for Hoffman propeller equipped airplanes with MTOW lncrement at 650 kg ~TECNÄ"'id [?~@@@ dJ@• füO[?@[r@~ [?'~•@Du~ [R-'Ä]@lli)(!!]@~ Page WHl-6 5 ENGINE Manufacturer Model Engine type Bombardier-Rotax GmbH 912 S2 4 cylinders horizontally opposed with 1352 c.c. of overall displacement, liquid cooled cylinder heads, ram-air cooled cylinders, two carburetors, inl<::gratt:<l n:- duction gear box with torsional shock ab- sorber and overload clutch. Maximum power (at declared rpm) 73.5 kW (98.6hp) @ 5800 rpm - 5 minutes maximum. 6 PROPELLER Manufacturer Model Blades Diameter Type 69.0 kW (92.5hp) @ 5500 rpm (continu- ous) Hoffman Propeller HO 17GHM A 174 177C 2 blades of Laminated hard wood. Com- posite structure, epoxy fibre glass cover 1740 mm Fixed pitch Section 1 - General GENERAL FEATURES Ed. 2, Rev. 0 AFMS N °S7 for Hoffman propeller equipped airplanes with MTOW lncrement at 650 kg ~ r'i'cNÄM[p~@@® cD© 0 &•!?@!?® ~ !?D •@OuQ ~®[füQD@D Page WH 1-7 7. FLIGHT CONTROL SURFACES TRAVEL Ailerons Up 22° Down 14 ° (± 2°) Stabilator (refer to Trailing Edge) Up 4° Down 15° (± 2°) Stabilator trim tab (refer to Trailing Edge) Up 2°; Down J2° (± 1°) Rudde r RII 25° LH 25° (± 2°) Flaps 0°; 35° (± 1°) 8. SPECIFIC LOADINGS Wing Loading Power Loading MT OW 650 kg (14331b) 53.5 kg/m2 ( 10.9 lb/sqft) 6.59 kg/hp (14.53 lb/hp) Section 1 - General GENERAL FEATURES Ed. 2, Rev. 0 Page l - 8 9. ACRONYMS AND TERMINOLOGY KCAS KlAS KTAS Vo Vs Vso Vs1 V x Vv Calibrated Airspeed is the indicated airspeed expressed in knots , corrected taking into account the errors related to the instrument itself and its installation. Tndicated Airspeed is the speed shown on the airspeed indicator and it is expressed in knots. True Airspeed is the KCAS airspeed corrected taking into ac- count altitude and temperature. Design Manoeuvring speed is the speed above the which it is not allowed to make full or abrupt contro l movement. Max imum Flap Extended speed is the highest speed permissib le with flaps extended . Max imum Structural Cruising Speed is the speed that should not be exceeded , except in smooth air and only with caution. Never Exceed Speed is the speed limit that may not be exceeded at any time. Operating Manoeuvr ing speed is the speed above the which it is not allowed to make füll or abrupt control movement Stall Speed. Stall Speed in landing configuration (flaps extended). Stall speed in the given flap configuration . Best Angle-of-Climb Speed is the speed which allows best ramp climb perfonnances. Best Rate -of-C limb 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 Section 1 - General ACRONYMS AND TERMINOLOGY Ed. 2, Rev 0 Page 1 - 9 Meteorological terminology ISA QFE QNH OAT Ts HP International Standard Atmosphere: is the air atmospheric standard condition at sea level, at 15°C (59°F) and at 1013.2511Pa (29.92inHg). Official atmospheric pressure at airport level: it indicates the air- craft absolute altitude with respect to the official airport level. 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. Outside Air Temperature is the air static temperature expressed in degrees Celsius (0 C). Standard Temperature is l 5°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 whcn the barometric subscale has been set to 1013 mb. Section 1 - General ACRONYMS AND TERMINOLOGY Ed. 2, Rev 0 Page 1 - 10 Aircraft performance and flight planning terminology Crosswind Velocity Usablejuel Unusablejuel G TOR TOD GR LD SIR is the velocity of the crosswind component for the which adequate control of the air- plane during takeoff and landing is assured. is the fuel available for flight planning. is the quantity of fuel that cannot be safely used in tlight. is the acceleration of gravity. is the takeoff distance measured from actual start to wheel liftoff point. is total takeoff distance measured from start to l Sm obstacle clearing. is the distance measured during landing from actual touchdown to stop point. is the distance measured during landing, from 15111obstacle clearing to actual stop. is the specific range, that is the distance (in nautical miles) which can be expected at a specific power setting and/or tl ight configu- ration per kilogramof fuel used. Section 1 - General ACRONYMS AND TERMINOLOGY Ed. 2, Rev 0 Page 1 - 11 We ight and ba la nce termin ology Datum Arm Moment C.G. Standard Empty Weight Basic Empty Weight Usefu/Load Maximum Takeo.ff Weight "Reference datum" is an imaginary vertical plane from which all horizontal distances are measured for balance purposes. is the horizontal clistanceof an item meas- ured from the reforencedatum. is the product of the weight of an item multiplied by its arm. Center of Gravity is the point at which the airplane, or equipment, would balance if suspended. lts distance from the reference datum is found by dividing the total mo- ment by the total weight of the aircraft. is the weight of the aircraft with engine flu- ids and oil at operating levels. is the standard empty weight to which it is added the optional equipment weight. is the difference between maximum takeoff weight and the basic empty weight. is the maximum weight approved to perform the takeoff. Se ction 1 - General A CRON Y MS AND TERMINOLOG Y Ed. 2, Rev 0 lNTENTlONALLY LEFT BLANK Section 1 - General Ed. 2, Rev 0 10. UNIT CONVERSION CHART MOLTIPLYJNG T EMP ERAT URE Fahrenheit Celsius F ORCES Kilograms Pounds S PEED Meters per second Feet per minute Knots Kilometres / hour PR ESSUR E Atmosphcre Pounds/ sq. in LE NGTH Kilometres Nautical miles Meters Feet Centimetres Inches VO LUi\l.E Litres U.S. Gallons AR EA Square meters Square feet BY ~ [OF] 5 - ,(F - 32) 9 (OC] (;.c:)+3 2 [kg) 2.205 (Ibs] 0.4536 [m/s] 196.86 [ft/min] 0.00508 fktsl l.853 [km/h) 0.5396 [alm) 14.7 (psi) 0.068 [km) 0.5396 [nm] 1.853 [m] 3.281 lftJ 0.3048 fcm) 0.3937 [in] 2.540 [I) 0.2642 [US Gai] 3.785 [m2] 10.76 [sq tt] 0.0929 Section 1 - General UNIT CONVERSION CHART Page 1 - 13 YTELDS Celsius (OC] Fahrenheit l"FJ Pounds (lbs] Kilograms (kg) Feet per minule [fl/min] Meters per second (111/s) Kilometres/ hour (km/h) Knots [kts) Pounds/ sq. in [psi] Atmosphere [atm) Nautical miles [nm] Kilometres [km] Feet [ft] Meters lmJ Inches [in] Centimetres [cm) U.S. Gallons [US Gai) Litres (1) Square feet [sq ft] Square meters [111 2] Ed. 2, Rev 0 11. LITRES / US GALLONS CONVERSION CHART Litres US Gallo ns US Gallon s Lit res 5 1.3 1 3.8 10 2.6 2 7.6 15 4.0 .., J 11.4 20 5.3 4 15.1 25 6.6 6 22.7 30 7.9 8 30.3 35 9.2 10 37.9 40 10.6 12 45.4 45 11.9 14 53.0 50 13.2 16 60.6 60 15.9 18 68.1 70 18.5 20 75.7 80 21.1 22 83.3 90 23.8 24 90.9 100 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 Section 1 - General Ed. 2, Rev 0 AFMS for VFR Nl GHT equipped airplanes l« lrEcNÄM[p~@®® J@ 0 &oIT'@IT'@{m lfD•@Du~ [iYÄ)@llilßD@D Page 2N - 1 SECTION 2 - LIMITATIONS INDEX 1. 2 . 3. 4. 5. 6. 7. 8. 9. 10. 11. 12. 13. 14. 15. 16. 17. 18. 19. 20. 21. 22 . INTRODUCTION .... ......... ....... ............ .. .......... ......... ....... ..... .. .... ...... ........ .. 3 AIRSPEED LIMITATIONS .................... ......... .................. .......... .. ............... 5 AIRSPEED INDICATOR MARKINGS ....................... .. .......................... ....... 6 POWERPLANT LIMITATIONS ....... ....................... . .................................... 7 FUEL ........... ......................................................... .......... ........... .............. .. 8 LUBRICANT ........................•.............. ........ .................. .................. ........... 8 COOLANT LIQUID .. ... ............ ................................. .. ...... ..................... ...... 8 PAINT ............... ............................ .................. ....... .. ...... ..... ........... ........... 8 PROPELLER ........... .. ....... .............. ..... ..................... ....... ........... ............... . 9 MAXIMUM OPERATING ALTITUDE .......................................................... 9 AMBIENT TEMPERATURE ......................... ...................•... .•.. .... ................ 9 POWERPLANT INSTRUMENTS MARKINGS ... ......................................... 10 OTHER INSTRUMENTS MARKINGS ....................................................... 10 WEIGHTS ... ... ...... ....... ................................................................. ............ 12 CENTER OF GRAVITY RANGE ............. ................................................... 14 APPROVED MANOEUVRES .......... ............. ...... ...... ................. ................. 16 MANOEUVRES LOAD FACTOR LIMITS .. .... .. ........................................... 17 DEMONSTRATED CROSS WIND SAFE OPERATIONS .... ......................... 18 FLIGHT CREW ...... ........................... ..................... .................................. 18 KINDS OF OPERATION EQUIPMENT LIST (KOEL) .... .. ........................... 19 LIMITATIONS PLACARDS ................................ ... .......... ..... .......... ........... 21 OTHER PLACARDS ................ ........... ....... ...... .•. .. ......... ... .... ........•..... ...... 23 Section 2 - Limitations INDEX Ed.2, Rev. 0 AFMS for VFR NlGHT equipped airplanes E«J TECNÄM [p~@@® J @ 0 füO[f@[f@~ ~OO@DuQ ~@[ruruJ@O Page 2N - 2 INTENTIONALLY LEFT BLANK Ed. 2, Rev. 0 Section 2 - Limitations AFMS for VFR NIGHT equippeclairplanes ~TECNÄ Ut M IP~®®® J@ 0 & •[?@[?@~ l?D o@[}QQ ~@[n)Q!J@O Page 2N - 3 1. INTRODUCTION Section 2 includes operating limitations, instrument markings and basic placards necessary for safe operation of the aeroplane, its engine, standarcl systems ancl Standardequipment. Section 2 - Limitations INTRODUCTION Ed.2, Rev. 0 AFMS for VFR NlGHT equipped airplanes ~TECNÄM[p~@®® J@ • &örr@ rr @~~O•@Du~ ~@[fi)llil@D Page 2N - 4 [NTENTIONALLY LEFT BLANK Ed.2, Rev. 0 Section 2 - Limitations AFMS N °S7 for Hoffman propeller equipped airplanes with MTOW lncrement at 650 kg ~ TECNAM [?~@@@ d]@• &•[?@[?@~ [f~o@DüQ ~@[ru(!!]@O Page WH2-5 2. AIRSPEED LIMITATIONS The following table addresses the airspeed lirnitationsand their operational signif- icance: "NE VNO VA VO "rE Appr oved ATRSPEED KIAS KCAS REMARKS Never exceed speed 143 139 Do not excecd this speed in any operation. Maximum Structural 111 110 Do not exceed this speed Cruising speed except in smooth air, and only with caution. Design Manoeuvring speed 98 97 Do not make full or abrupt control movement above Operating Manoeuvring this speed, because under speed certain conditions the air- craft may be overstressed by full control movement. Maximum flaps extended 70 71 Do not exceed this speed speed for indicated flaps setting. Ed 2, Rev. 0 Section 2 - Limitations AIRSPEED LIMITATIONS AFMS N°S7 for Hoffman propeller equipped airplanes with MTOW lncrement at 650 kg ~ TECNAiÄ [?~@®@ d]@• &a[?@[?@~ l?Oa@Du~ ~@[n)Q!J@O Page WH2-6 3. AIRSPEED INDICATOR MARKINGS Airspeed indicator markings and their colow· code are explained in the following table. MARKING White arc/band Green arc/band Yellow arc/band Red linc Approved KIAS EXPLANATION 40 -7 0 Positive Flap Operating Range (lower limit is V so, at specified maximum weight and upper limit is the maximumspeed permissi- ble with landing flaps extension). 49 - 111 Normal OperatingRange (lower limit is Vs1 at specified maximum weight and most for- ward c.g. with flaps retractedand upper limit is maximum structural speed VNo). 111- 143 Manoeuvres must be conducted with caution and only in smooth air. 143 Maximum speed for all operations. Ed. 2, Rev.1 Sect ion 2 - Limitations AIRSPEED INDICATOR MARKINGS AFMS for YFR NIGHT equipped airplanes ~ TECNÄ"'iJ [p~@@@ JJ@ • &IJ[?@[?@~ f?D•@Du~ [ij]@[]i)QD@O Page 2N - 7 4. POWERPLANT LIMITATIONS Following table repo1ts the powerplant operating limitations: E NGI NE M ANUFACTU RER: Bombardier Rotax GmbH. ENGINE MODEL: 9 l2 S2 MAX IMUM POWER: Max. T.O. Max. Cont. Temperatures: Max CHT* MaxCT Min/Max Oil Max Power kW (hp) 73.5 (98.6) 69 (92.5) Max rpm. Prop. rpm(engine) 2388 (5800) 2265 (5500) 135° C 120°c 50°C/ 130°C Time max. (minutes) 5 - * 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 Maximum 12 psi 102 psi (below l 440propeller rpm) (above l 440 propel ler rpm) CAIJTIO N In event of cold starting operation, it is permitted a maximum oil pressure o/7 barfor a short period. Engine starti ng : allowable temperature range OAT Min -25° C OAT Max +50° C Fue l pre ss ure: Approved Min imum 2.2 psi Maximum 7.26 psi Section 2 - Limitations POWERPLANT LIMITATIONS Ecl.2,Rev. 0 AFMS for VFR NIGHT equipped airplanes ~TECNÄM[p~@@@ dJ@• füO[?@[?@~ ~~O@Gu ~ ~@[fü Q!J @O Page 2N - 8 5. FUEL 2 T ANKS: MAX IMUM CAPACITY: 62 litres each one (16.38 US gallom ) 124 litres (32. 76 USga llons) MA XI.\.JUM USA BLE FUE L: 120 li tres (32 l!S gallons) APPROVED HJ EL: MOGAS ASTM D48 14 (min RON 95/AKI 9 1) CA UTIO N MOGAS EN 22 8 Super/Super plus (min. RON 95/AKI 91) AVGAS 100 L L (ASTM 09 10) Prolonged use of Aviation Fuel Avgas I00LL results in greater wear oj valve seats and greater combustion deposits inside cylinders due to higher lead con1ent. Make reference to Rotax Maintenance Manual which p rescribes dedicated checks due to the prolonged use of Avgas. 6. LUBRICANT Recomrnenclecl by Rotax: BRAND DES CRIPTIO N SPECIFJCATION Vl SCOSITY CODE SHELL AeroShel I Sport API SL SAE 10 W-40 2 Plus 4 Use only o il with API c lassification "SG" or higher. [ij§iE :: 1 see Rotax SI-9 I2-0I6 R4 for !ist of recommendedcommercial brands and types 7. COOLANT LIQUID Refer to "Rotax Operators Manual" - last issue -, "Operating Media" Section. NOTE: For the Engines affected by Rotax SB-912-066 R 1, the waterless coolant is not permitted) 8. PAINT To ensure that the temperature of the composite structure does not exceed limits, the out- er surface of the airplane must be painted with white paint, except for areas of registration marks, placards, and ornament. Refer to Aircraft Maintenance Manual (AMM), Chapter 51, for specific paint requirements. Approved Section 2 - Limitations POWERPLANT LIMITATIONS Ed.2, Rev. 0 AFMS N °S7 for Hoffman propeller equipped airplanes with MTOW lncrement at 650 kg ~ TECNÄM [p~@@® cD@ 0 &•[?@[?cru®[?~o@Du~ ~@üi)(ill@~ Page WH2-9 9. PROPELLER MANUFACTURER: Hoffman Propeller HOI7GHMA 174177C MODEL: ßLADES: 2 blades of Laminated hard wood. Composite structure, epoxy fibre glass cover TYJ'E: Fixed pitch DIAMETER: 1740 mm 10. MAXIMUM OPERATING AL TITUDE Maximum operating altitude is 13000ft (3962 m) MSL. Fligh t crew is required to use supplemental oxygen according to applicable Air Operation Rules . CAUT ION 11 . AMBIENT TEMPERATURE Ambient temperature: from -25°C to +50°C. Flight in expected and!or known icing conditions isforbidden. WARNING Approved Sectio n 2 - Lim itations AIRSPEED INDIC AT OR MARKINGS Ed. 2, Rev. J AFMS for VFR NlGHT equipped airplanes ~TECNAM[p~@@@ dJ@ c:i ß O [?@[?@~ lfDO@DuG (hYA]@[füQ!J@O Page 2N - 10 12. POWERPLANT INSTRUMENTS MARKINGS PO\,verplant instrument markings and their colour code significance are shown be- low: REDLl NE GREENARC YELLOWARC REDLlNE INSTRUMENT Minimum Normal Caution Maximum limit operating limit Propeller rpm ---- 577 - 2265 2265 - 2388 2388 Oil temp. oc 50 50-130 ---- 130 CHT* oc ---- 0-135 ---- 135 CT oc ---- 0- 120 ---- 120 Oil pressure ps1 OPLOW ---- ----- 102 WARNING 12 psi Fuel press. psi FPL OW 2.2-7.26 ---- 7.26 WARNING 2.2 osi *- applicable for Engines up to serial no. 4924543(included) and repaired engine which doesn't change the cylinder head n°3 with new one (patt no. 413195 13. OTHER INSTRUMENTS MARKINGS RED ARC GREEN ARC YELLOWARC REDARC / J ,, I I NSTRUMENT Minimum limit Normal operating Caution Maximum limit Voltmeter 10-10.5 Volt l2 - l6Yolt -- 16-16,5 , Approved Ed2 , Rev. 0 Section 2 - Limitations POWERPLANT INSTRUMENTS MARKINGS AFMS for VFR NIGHT equipped airplanes ~ TECNÄM [p~@@@ dJ@0 ß •[?@[?@~ ~ D•@Du~ ~@[fü(!!]@O Page 2N - 11 INTENT IONALL Y LEFT BLANK E d.2, Rev. 0 Section 2 - Limitations AFMS N °S7 for Hoffman propeller equipped airplanes with MTOW lncrement at 650 kg ~TECNAM[?~@®@ J@ • &rlü'©ü'~ [pQ~@Du~ (i".Ä]@[ru(!!]@OPage WH2-12 14. WEIGHTS Appro ved Condition Wci ght Maximum takeoffwe ight 650 kg Maximum landing weight 650 kg Baggage Compartment Maximum weight 20 kg Maximum specific pressure 12,5 kg/dm2 Section 2 - Limitations WEIGHTS 14331b 14331b 441b 256 lbs/sq in Ed. 2, Rev. 0 AFMS for VFR NJGHT equipped airplanes ~ TECNÄM [p~@@® JJ@0 füO[?@[?@™ [f O ö@[fü~ lK'.Äl@llilOD@O Page 2N - 13 Approved INTENTLONALL Y LEFT BLANK Section 2 - Limitations WEIGHTS Ed.2, Rev. 0 AFMS for VFR NIGHT equipped airplanes ~ TECNÄM [p~@@® J@ 0 füOü'@ü'@~ L5 00 @Du~ ~@[ruOJJ@O Page 2N - 14 15. CENTER OF GRAVITY RANGE Datum Levelling Forward limit Aft limit WARNl NG Approv ed Vertical plane tangent to the propeller flange (the aircraft must be level led in the longitudinal plane) Refer to the seat track supporting beams (see procedure in Section 6) 1.841 m (20% MAC) aft of datum for all weights 1.978 m (30% MAC) aft of datum for alI weights The pilot is responsible for ensuring that the airplane is properly loaded. Refer to Section 6 for appropriate instruc- tions. Section 2 - Limitations CENTER OF GRAVITY RANGE Ed.2, Rev. 0 AFMS for VFR NIGHT equipped airplanes E«JTECNÄ0 M [p~@®® d]@D fü•[?@[?@{m [p0o~Du~ ~@ITi)(!!]@OPage 2N - 15 lNTENTIONALLY LEFT BLANK Ed.2, Rev. 0 Section 2 - Limitations AFMS N °S7 for Hoffman propeller equipped airplanes with MTOW lncrement at 650 kg l«JTECNÄM ~~®@® J@ 0 &•(r@(r@~ [?~o@DDQ [K'.Al @[ru(ill@D Page WH2-16 16. APPROVED MANOEUVRES The aircraft is certified in Normal Category in accordance with EASA CS-VLA regu- lation applying to aeroplanes intended for non-aerobatic operationonly. Non aerobatic operation inclucles: • Any manoeuvre pertaining to "normal" tlight • Stalls (ex.ceptwhip stalls) • Lazy eights • Chandelles • Steep turns in wbich the angle of bank is not more than 60° Recommended entry speeds for each approved manoeuvre are as follows: Manoeuvre Speed [KIAS] Lazy eight 98 Chandelle 111 Steep turn (max 60°) 98 Stall WARNlNG WARNING WARNlNG Approv ed Slow deceleration (1 ktsls) Acroba tic manoeuvres, including spins and turns with angle of bank of more than 60°, are not approvedfor such a category. Limit load factor could be exceeded by moving abruptly }light controls at their end run at a speed above VA(Manoeuvring Speed: 98 KJAS). Flight in expected andlor known icing condilions, in proximity of storms or in severe turbulence is forbidden. Section 2 - Limitations APPROVED MANOEUVRES Ed. 2, Rev. 0