Aircraft Flight Manual 20081100 Doc. No. Ed.1-Rev.6 2016, 2a1h Jan uary ,
i' TECNAM P2008 JC
MANUFACTURER: COSTRUZJONtAERONAUTtCHE TECNAMs.r.l. AIRCRAFf JC EASA TYPEMODEL:P2008 CERTIFICATE No:A .583 (DATED 2013, 27 SEPTEMBER)
SERIAL NUMBER: . . j<{):f .O......
REGISTRATION MARKI . . . . GS: .H.B. K,ML
This Aircraft Flight Manual is approved by European Aviation Safety Agency (EASA) and applies only EASA CS-VLAcertified airplanes.
This Manual must be carried in the airplane at all times. The airplanehas to be operated in compliance with procedures and limitations contained herein.
Costruzioni Aeronautiche TECNAM srl Via Maiorise CAPUA (CE)- Italy Tel. +39 (0) 823 997538
WEB: www II .tecnam.com
ll Page - 2 0
SECTION 0 1. RECORD OF REVISIONS
Any revision to the present Manual, except actual weighing data, is recorded: a of Revisions is in this Section and the operator is advised to INDEX Recordsure that the recordprovid eup-to-d date. make iskepl 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 subsequentrevi RECORD OF REVISIONS . . . 3 1. sions are identifiedby the change of the code from "O" to "l" Ofor; the firstrevision ...... 2. LIST OF EFFECTIVE PAGES ...... 8
...... to the basic publication, "2" forthe second one, etc. 3, FOREWORD ...... 11 4. SECTIONS LIST ...... 12 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" forthe 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: It is the responsibility of the owner to maintain this handbook in a current status when it is being used for operational purposes.
0 Ed.J,Rev.O Ed. l,Rev. Aircraft Flight Manual Aircraft Flight Manual
INDEX RECORD OF REVISIONS 4 Page 0 r Page - 5 0 - �rEc'N'A'M
Tecnam Approval EASA Approval or EASA Approval or Revised Description of Tecnam Approval Rev Under DOA of Under DOA page Revision Revised Description DO OoA HOO Privileges Rev OoA HDO Privileges page Revision DO Amended to add the wording "Ap- as part approved pi oved" in orde1 to better identify of Type 2-5 thru 30 "'D. Ronca C. Caruso M.O iva M.Oliva EASA the pages approved according to l Paduano M. Landi First issue G. 0 EASA regulation lnves1ion1ion . M.Oliva Amended to add the wording .Ap- D. Ronca M.Oliva 0-4 AmendROR proved" in orde1 to better identify 3-3 thru 22 D. Ronca C. Camso M.Oliva M.Oliva EASA approval D. Ronca M.Oliva the pages approved according to Approved under the au- Amend LOEP 0-8 N" 10052448 EASA regulation thority of DOA, ref M.Oliva Ronca M. Oliva 1 List Index D. Amended to add the wording "Ap- EASA.2 IJ 335 9-3 Amend Supplement . Oliva M.Oliva M. pioved" in 01de1 to bdter identify (MOD2008/068. I 60 l 20) S3 D. Ronca 6 4-3 thru 8 D. Ronca C. Caruso M.Oliva Add Supplement l the pages approved according to .Oliva M.Oliva - D. Ronca M EASA r�gulation 0-4 Amend ROR .Oliva M.Oliva Amended to add the wording "Ap- D. Ronca M 5-5, 0-8 Amend LOEP proved" in order to better identify M.Oliva 5-7 thru 5-10. D. Ronca C.Caruso M.Oliva D. Ronca M.Oliva the pages approved according to 3-5 and 7 Update procedure 14 M.Oliva EASA regulation D. Ronca M.Oliva procedure 4-12 thru 13 Update au- Approved lhe Supplement List Index amended D. Ronca C.Caruso M. Oliva M.Oliva M.Oliva under EASA approval D. Ronca ref Update procedure thor\ty 4-16 thru 17 DOA, N° 10041226 M.Oliva D. Ronca M,Oliva EASAof.21J.335 Add Supplement S7 D. Ronca C. Caruso M.Oliva procedure 3N-5 thru 6 Update .150401) - '.! M.Oliva (MOD2008/038 D. Ronca M.Oliva procedure 4N-l2 thru 13 Update M.Oliva D. Ronca M.Oliva procedure 4N-15 thru 17 Update M.Oliva D. Ronca M. Oliva Supplement List Index 9-3 Amend .Oliva M. Oliva ] D. Ronca M Add Supplement S2 Oliva M.Oliva - S3 D. Ronca M. Updated layout Supplement M_Oliva EASA approval i D. Ronca M,Oliva Supplement List Index l. 9-3 Amend N°l00530 l5 M.Oliva M. Oliva 3 S4 D. Ronca ] Add Supplement - of coolant tern- Add max limit M.Oliva ' D. Ronca M.Oliva and coolant liquid 2-7,8,10 perature specification amended I M.Oliva . D. Ronca M.Oliva Coolant placard amended EASA approval ] 2-23 N°l0054 136 - amended for include M. Oliva M.Oliva 4 Procedure D. Ronca 3-12, 13 CT
include M.Oliva Procedure amended for D. Ronca M.Oliva 4-14,15 CT ] M.Oliva M.Oliva list D. Ronca 6-12 Updated equipment the au- C. Caruso M. Oliva List Index D. Ronca underDOA, ref 9-3 Amend Supplement ApprovedLhority EASA.201' \J.335 M_ Oliva 5 . Ronca C.Caruso 215) Add Supplement SS D 5 I (M002008J067.l
Ed.l, Rev.5 Rev. Ed. 1, 6 Aircraft Flight Manual Aircraft Flight Manual RECORD OF REVISIONS RECORD OF REVISIONS
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Ed.1, Rev. 0 Ed. Rev. 0 J, Aircraft Flight Manual Aircraft Flight Manual 2. LIST OF EFFECTIVE PAGES [ J 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. Pages affected by the current revision are indicated by an asterisk (*) following the re vision code.
Edition 1, Rev 0 ...... 30111 July, 2013 Edition Rev 1 ...... z5•h March, 2015 Edition 1, Rev 2 ...... 071h April, 2015 Edition 1, Rev 3 ...... 13th April, 2015
Edition 1, Rev 4 ...... 14111 July, 2015 Edition 1, Rev 5 ...... 15•h December, 2015 Edition 1, Rev 6 ...... 20•h December, 2016
INTENTIONALLY LEFT BLANK Section Pages Revision Section 0 Pages thru 3, 6, 7, 9 thru 12 Rev O Section 0 Page 4 I Rev 5 Section 0 Page 5, 8 Rev6 Section 1 Pages thru 14 Rev O Section 2 Pages 1I thru Rev O Section 2 Pages 5 thru 430 Rev6 Section 3 Pages thru2 Rev O Section 3 Pages 3I thru 22 Rev6 1 Section 4 Pages 1 thru 3 Rev O Section 4 Pages 4 thru 22 Rev6 Section 5 Pages thru 11. 12. 13, Rev O Section 5 Pages 5_,I 7 thru4, 6, 10 14 15. 16 Rev6 Section 6 Pages thru 11 Rev O Section 6 Page 12I Rev 4 Section 7 Pages thru 16 Rev 0 Section 8 Pages I thru l 0 Rev O Section 9 Pages I 2, 4 Rev O Page 3 I, Rev6
1 Rev. Rev. 0 Ed. I, 6 Ed. l, Aircraft Flight Manual Aircraft Flight Manual LOEP 1 3. FOREWORD is a single-engine two-seat aircraftwith a strut braced high wing and Tccnamfixed landing P2008 JC gear. Section 1 provides gen eral information an d it contains definitions, sy mbols ex plana tions, acronyms and terminology used. using airplone, you ar e recommended to read car efully this manual: a deep knowledgeBefore ofthe airplan.e and limitations will al low you for oper atin g the airplane femure a ely f . For further information, please contact:
INTENTIONALLY LEFT BLANK COSTRUZIONI AERONAUTICHETECNAMs.r.l. Via MAIORISE
CAPUA (CE)- ITALY
'il+39 (0)823 997538
Ed.l, Rev. O Ed.l, Rev. 0 Aircraft Flight Manual Aircraft Flight Manual
FOREWORD Page I - I
SECTION 1 - GENERAL 4. SECTIONS LIST
General(*) Section INDEX I Limitations(**) Section2 1- INTRODUCTION ••••••••••••••••••••••••• ••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••• 3 Emergency Procedures (**) Section 3 2. CERTIFICATION BASIS ••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••• 3 3. WARNINGS - CAUTIONS - NOTES •••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••• 3 Normal Procedures(**) Section 4 4. THREE-VIEW AND DIMENSIONS ••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••• 4 5. ENGINE ......
Performance(***) Section 5 PROPELLER...... -...... 6
6. FLIGHT CONTROL SURFACES TRAVEL ...... 6 Weight and balance(*) Section 6 7. SPECIFIC LOADINGS ...... 7 8. 7 9. ACRONYMS AND TERMINOLOGY ...... Airframe and Systems description (*) Section 7 10. UNIT CONVERSION CHART ...... 138 11. LITRES I US GALLONS CONVERSION CHART ...... 14 Ground Handling and Service(*) Section 8
AFM Supplements(***) Section 9
(*) non-approved Section (**)approved Section (***) partially approved Section
Rev. 0 0 Ed. 1, Section - General Ed. 1, Rev Aircraft Flight Manual 1 INDEX SECTIONS LIST Page 1 2 1 - Page - 3
1. INTRODUCTION
The Flight Manual has been prepared to provide pilots and instructors with in formationfor the safe and efficientopenition of this very light airplane.
This manual includes the material required to be furnished to the pilot of CS VLA. It also contains supplemental data supplied by the airplane manufacturer.
2. CERTIFICATION BASIS
!his type of airc�aft has been approved by the European Aviation Safety Agency with CS-VLA including Amendment and the Type Certificate ino.EASA.A.583 nccordnnce has been issued on (date) 27•h cptembcr2013.1
Category of Airworthiness: Normal Noise Certification Basis: EASA CS Amendment 2. 36
3. WA RNINGS - CAUTIONS - NOTES
INTENTIONALLY LEFT BLANK Following definitions apply to warnings, cautions and notes used in the Aircraft Flight Manual.
means that the non-observation of the corresponding procedure leads to an immediate or important degradation of the flight safety.
I means that the non-observation of the corresponding procedure leads to . a minor or to a more or less long term degradation ofthe flight safety.
draws the attention to any special item not directly related to safety but which is important or unusual.
Ed. Rev 0 Ed. Rev 0 Section General 1. Section 1 - General J, 1 - INTRODUCTION Page l - 4 Page l - [ _] 5 Dimensions 4. THREE-VIEW AND DIMENSIONS [ ] Wing
Wing Span 9.00 m (29.5 ft) • Wing Area l 2. l 6 m2 (130.9 ft2) Aspect Ratio 6.7 Taper Ratio 0.8 Wing chord 1.373 m (4.5 ft)
Fuselage
Overall length 6. 93 m (22.9 ft)
Overall width l.20 m (3.9 ft) Overall height 2.67 m (8 .8 ft)
Empennage Stabilator span 2.90 (9.51 ft) m Stabilator area 2.03 m2 (2 1.8 ft2)
- Figure 1 General views Vertical tail area l.06 m2 (11.4 ft2)
Landing Gear
Wheel track 1.8 m (5.9 ft)
Wheel base l .94 m (6.4 ft) Main gear tire 5.00-5 Nose Gear tire 5.00-5
Ed. 0 Ed. 0 Section 1 - General 1, Rev Section 1 - General 1, Rev THREE-VIEW AND DIMENSIONS ] GENERAL FEATURES AFMS N"S7 for Hoffman propeller equipped airplanes with Increment at 650 AFMS N"S7 for Hoffman propeller equipped airplanes with Increment at 650 MTOW kg [p�@@@ JJ@ &/l!J'@LJ'®OO MTOW kg �®@@ c!J@c &IJIJ'@[]'� lJiDH@lliJ�!N](ID [ii)l!!J@D c rfDH@lliJ� �[ii)l!!J@D �TEcNAM Page WHl-6 �TECNAM Page WHl-7
7. FLIGHT CONTROL SURFACES TRAVEL 5 ENGINE Ailerons Up 22° Down 14 ° (± 2°) Manufacturer Bombardier-Rotax GmbH Stabilator (refer to Trailing Edge) Up 4° Down \5° (± 2°) Model 912 S2 Stabilator trim tab (refer to Trailing Edg ) Up 2°; Down 12° (± Engine type 4 cylinders horizontally opposed with : J 0) 1352 c.c. of overall displacement, liquid Rudder RH 25° LH 25° (± 2°) cooled cylinder heads, ram-air cooled cylinders, two carburetors, integrated re Flaps 0°; 35° (± 1°) duction gear box with torsional shock ab sorber and overload clutch. Maximum power (at declared rpm) 73.5 kW (98.6hp) @ 5800 rpm -5 [ ] 8. SPECIFIC LOADINGS minutes maximum. 69.0 kW (92.5hp)@ 5500 rpm (continu MTOW 650 kg (1433lb) ous) Wing Loading 53.5 kg/m2 (10.9 lb/sqft ) Power Loading 6.59 kg/hp (14.53 lb/hp ) 6 PROPELLER [1 l Manufacturer Hoffman Propeller Model H017GHM A 174 177C Blades 2 blades of Laminated hard wood. Com I l posite structure, epoxy fibre glass cover Diameter 1740 mm Type Fixed pitch I l · 1 l . ] I � l ]
Ed Ed
- I, Rev. 0 Section 1 General Section 1 - General I, Rev. 0 GENERAL FEATURES GENERAL FEATURES Page - Page - I 8 I 9
Meteorological terminology 9. ACRONYMS AND TERMINOLOGY
ISA lntenmtional t·andard Ahno phere: is the air atmospheric standard KCAS Calibrated Ail'Soecd is the indicated airspeed expressed in knots, condition at sea level, 15°C (59°F) corrected taking into account the errors related to the instmment ul and at l013.25hPa (29.92i11Hg). itself and its installation. QFE Official atn10.pheric pressure at aimort level: it indicates the air KIAS Indicated Airspeed is the speed shown on the airspeed indicator [ ] craft absolute altitude with reipec1 the airport level. and it is expressed in knots. to official c: QNH Theoretical !llmospheri . level; is the atmospheric KTAS Tme Airspeed is the KCAS airspeed corrected taking into ac pressure reported at the cmedium oressure sea at level,ea lltrough the standard air count altitude and temperature. ] pressure-altitude relationship, starting from the airport QFE. Design anoeuvrinl!speed is the speed above the which it is not OAT Outside Air Temperanire is the air static temperature expressed in allowedM to make full or abmpt control movement. [I degrees Celsius (0C). Maximum Extended soecd is the highest speed permissible 1 Ts Standard Temperature is 5°C at sea level pressure altitude and with flaps extended.Flap J decrea ·ed by 2°C for each I 000 ftof altitude. I Crnising Speed is the speed that should not Pressure Altitude is the altitude read from an altimeter when the beMaximum exceeded, tructural except smooth air and only with caution. [I ] barometric ubscale has been set to l O 13 mb. in Speed is the speed limit that may not be exceeded atNever any time.Exceed l
Opcrntinn Manocuvrinll.speed is the speed above the which it is Vo not allowed to make fullor abrupt control movement / Stall Speed. J Vs Stall Speed in landing configuration (flaps extended). Yso speedin the eiv�n flapconfiguration. Vs1 Stall Best Angle-of-Climb. peed is the speed which allows best ramp Yx climb perfomiances.
Best Rate-of- limb is the speed which allows the best Yv gain in altitude over a peedgiven time. Rorntionspeed : is the speed at which the aircraft rotates about the pitch ax is during takeoff
Section - General 1 Ed. 1, Rev 0 Section 1 - General Ed. I, Rev 0 ACRONYMS AND TERMINOLOGY ACRONYMS AND TERMINOLOGY J - l l Page l - 10 Page I
Aircraft performance and flight planning terminology Weight and balance terminology [ ] Crosswind Velocity is the velocity of the crosswind component Datum "Reference datum" is vertical for the which adequate control of the air plane from which all anhorizontal imaginary distances a e measured for balance purposes. plane during takeoff and landing is assured. � Us able fi1el is the fuel available for flight planning. [ ] is the horizontal distance of an item meas Ann ured from the reference datum. Unusable fuel is the quantity of fuel that cannot be safely used in flight. Moment is the product of the weight of an item multiplied by its arm. G is the acceleration of gravity. [ C.G. of is the point at which the TOR is the takeoff distance measured from actual ] enter Gravityequipment, would balance if start to wheel liftoff point. or suspended.airplane, Its distance from the reference is total takeoff distance measured from start TOD datum is found by dividing the total mo to 5m obstacle clearing. ment by the total weight of the aircraft. \ is the distance measured during landing GR Standard Empty Weight the weight of the aircraft with engine flu from actual touchdown to stop point. idsis and oil at operating levels. is the distance measured during landing, LD Basic Empty We ight is the empty weight to which it is from 5m obstacle clearing to actual stop. added standardlhe oplional equipment weight. \ is the specific range, that is the distance (in SIR Us eful load is the difference between takeoff nautical miles) which can be expected at a weight and 1he bn maximumweight. specific power setting and/or flight configu ic empty ration per kilogram of fuel used. Maximum Takeof!Weight is the maximum weight approved to perform the takeoff. J .] J
I J
Ed. Rev I J Ed. I, Rev Section 1 - General !, 0 Section 1 - General 0 ACRONYMS AND TERMINOLOGY ] ACRONYMS AND TERMINOLOGY Page - Page - 12 13 I I
10. UNIT CONVERSION CHART
MnT TIPT VTNr. . RY .. VTRT '"' TEMPERATURE Fahrenheit (oF) 5 Celsius (OCJ [ 9·(F-32) Celsius [OCJ Fahrenheit (oF) (�·c)+32
FORCES Kilograms [kg] Pounds [lbs] 2.205 Pounds (lbs] Kilograms [kg] 0.4536 SPEED Meters per second [mis] Feet per minute [ft/min] 196.86 Feet per minute [ft/min] Meters per second [mis] 0.00508 INTENTIONALLY LEFT BLANK Knots [kts] Kilometres hour [km/h] 1.853 I Kilometres hour [km/h] Knots [kts] I 0.5396 PRESSURE Atmosphere [atm] Pounds sq. in [psi] 14.7 I Pounds sq. in [psi] Atmosphere [atm] I 0.068 LENGTH Kilometres [km] Nautical miles [nm] 0.5396 Nautical miles [nm] Kilometres [km] 1.853 Meters [m] Feet [ft] 3.281 Feet Meters [m] [ft] 0.3048 Centimetres [cm] Inches [in] 0.3937 Inches [in] Centimetres [cm] 2.540 VOLUME Litres [I] U.S. Gallons [US Gal] 0.2642 U.S. Gallons [US Gal] Litres [l] 3.785 AREA Square meters (m'] Square feet [sq ft] 10.76 Square feet [sq ft] Square meters [m'J -] 0.0929
Ed. I, Rev 0 I, Rev 0 Section 1 - General Section 1 - General Ed. UNIT CONVERSION CHART AFMS forVFR NIGHT equipped airplanes
I TECNA'M [p22@@@ dJ@ &rl!f@[f� lfDD@llilU�@Ui)()j]@O 2N - [� J [:!{) c Page
SECTION 2 - LIMITATIONS CHART 11. LITRES I US GALLONS CONVERSION [ J INDEX
Litres Litres US Gallons US Gallons 1 3.8 5 1.3
2 7.6 10 2.6 [ J .,. 3 11.4 1. INTRODUCTION ...... 3 15 4.0 2. AIRSPEED LIMITATIONS ...... 5 4 15.l 20 5.3 J 3. AIRSPEED INDICATOR MARKINGS ...... 6 22.7 25 6.6 6 [ 4. POWERPLANT LIMITATIONS ...... 7 �. 8 30.3 5. FUEL...... •...... 8 30 7.9 6. LUBRICANT ...... 8 10 37.9 35 9.2 J 7. COOLANT LIQUID ...... 8 45.4 10.6 12 [ 40 8. PAINT ...... 8 ....,. 14 53.0 9. PROPELLER...... •...... 9 45 11.9 10. MAXIMUM OPERATING ALTITUDE ...... 9 60.6 13.2 16 ... 50 11. AMBIENT TEMPERATURE ...... 9 18 68.l [ 60 15.9 12. POWERPLANT INSTRUMENTS MARKINGS ...... •...... 10
20 75.7 13. OTHER INSTRUMENTS MARKINGS ...... 10 70 18.5 � 14. WEIGHTS ...... 12 22 83.3 80 21.l J 15. CENTER OF GRAVITY RANGE ...... 14 24 90.9 [ 90 23.8 16. APPROVED MANOEUVRES ...... •...... •...... 16
26 98.4 17. MANOEUVRES LOAD FACTOR LIMITS ...... 17 100 26.4
...... •...... •...... 106.0 18. DEMONSTRATED CROSS WIND SAFE OPERATIONS 18 29.1 28 110 19. FLIGHT CREW ...... 18 113.6 120 31.7 30 20. KINDS OF OPERATION EQUIPMENT LIST (KOEL) ...... 19
32 121.1 130 34.3 21. LIMITATIONS PLACARDS...... 21 22. OTHER PLACARDS ...... 23 34 128.7 140 37.7
136.3 150 39.6 36
38 143.8 160 42.3
151.4 170 44.9 40
45 170.3 180 47.6
50 189.3 190 50.2
55 208.2 200 52.8
Ed.J, Rev. 0 I, Rev 0 Ed. Section 2 - Limitations Section 1 - General INDEX
�- AFMS forVFR NIGHT equipped airplanes NIGHT equipped airplanes AFMS forVFR r?�®®® dJ© &l![J'@IJ'IIDOO (PaH@lfilU liYAltruUilontrua Page 2N - &n[J'@[J'� @Uillliltrua Page 2N -2 CJ 3 r?�®®® dJ© CJ (PaH@lfilU liYAl .... I J [ 1. INTRODUCTION Section 2 includes operat�ng limitation�, instrument markings and basic placards necessary fo; safe operation of the aeroplane, its engine, standard systems and [ j standard equipment.
INTENTIONALLY LEFT BLANK J
Ed. I, Rev. Ed. I, Rev. 0 0 Section 2 Limitations Section 2 - Limitations - INTRODUCTION AFMS N"S7 for Hoffman propeller equipped airplanes with MTOW Increment at 650 AFMS VFR NIGHT equipped airplanes kg for @ dJ@ &!!!I'@[[� [F lliJ Page WH2-5 - �@® c O�@ Q [Ji)QJJ@O dJ© &!IU'©U'IIDOO [FOa@UuU�@[Ji) QJJ@O Page 2N 4 [K'i]@ 0 [ J E«J'f'ECNAM TECNAM !?�®®® 1
2. AIRSPEED LIMITATI ONS
The following table addresses the airspeed limitations and their operational signif- • 1 J icance: [ J AIRSPEED KIAS KCAS REMARKS �, VNE Never exceed speed 143 139 Do not exceed this speed in any operation.
VNO Maximum Structural 110 Do not exceed this speed III except in smooth air, and ., Cruising speed l only wilh caution. J VA Design Manoeuvring speed 98 97 Do not make full or abrupt control movement above Vo Operating Manoeuvring INTENTIONALLY LEFT BLANK th is speed, becau c under speed certain conditions the air- craft may be overstressed by control movement. full VFE Maximum flaps extended 70 71 Do not exceed this speed speed for indicated flaps setting. [ J
0 I, Rev. 0 Ed. Section 2 - Limitations Ed/, Rev. Approved Section 2 - Limitations AIRSPEED LIMITATIONS AFMS for VFR NIGHT equipped airplanes Increment at 650 kg Hoffman propeller equipped airplanes with for IP�®®@ &ll!f©li'� Page 2N - 1 MTOW Page WH2-6 CJ lfU�@lliln�Cfil!Jil [!!]@U AFMS N'S7 IP�@@@ &!J!f@[j'� lfU�@lliJQ[}Yij @!Jil[!!]@U �TECNAM �© � TECNAM �@ CJ 3. AIRSPEED INDICATOR MARKINGS 4. POWERPLANT LIMITATIONS Airspeed indicator markings and their colour code are explained in the following Following table reports the powerplant operating limitations: table. ENGINE MANUFACTURER: Bombardier Rotax GmbH. ENGINE MODEL: 912 $2 MAXIMUM POWER:
MARKING KIAS EXPLANATION White arc 40-70 Positive Flap Operating Range (lower limit Max Power Max rpm. Time max. is Yso, at specified maximum weight and kW (lip) Prop. rpm(e11gi11e) (minutes) upper limit is the maximum speed permissi- ble with landing flaps extension). Max. T.O. 73.5 (98. 6) 2388 (5800) 5 Green arc 49- 111 Normal Operating Range (lower limit is Ys1 at specified maximum weight and most for- ward e.g. with flapsretracted and upper limit Max. Coot. (92.5) 2265 (5500) - 69 is maximum structural speed VNo). Manoeuvres must be conducted with caution Yellow arc 111- 143 Temperatures: and only in smooth air. Max CHT* 135° c Red line 143 Maximum speed for all operations. Max CT 120°c Min/Max Oil 50° CI 130° C
* app/ic�blefor Engines up to no. 4924543(incfuded) and engine which doesn t cy li. nder headserial11°3 with11e11• one (part no. repaired clwnge the 4L3195) Oil Pressure: Minimum 12 psi (below 1440propeller rpm) Maximum 102 psi (above 1440 propeller rpm)
•I In event of cold starting operation, ii is permilled a maximum pre ssure of 7 barfor a short period 011
Engine starting: allowable te mperature range [ OAT Min -25° C OAT Max +50° c
Fuel pressure: Minimum 2.2 psi Maximum 7.26 psi
't/
Ed Rev. 0 Approved Edi, Rev. 2 I, • ji Section 2 - Limitations Approved Section 2 - Limitations AIRSPEED INDICATOR MARKINGS POWERPLANT LIMITATIONS
• 1 . I AFMS for VFR NIGHT equipped airplanes for Hoffman propeller equipped airplanes with MTOW Increment at 650 kg AFMS N°57 TECNA.M [?�®@® &ll!?©U'� Page 2N Page WH2-9 CJ l?Ua@GuQ [ty,i]@[ii)lYJ@U - s [p�@@@ &lllf@[f� [fU�@[}uQ [tyA](ID[ii)lYJ@U t«J d)@ �TECNAM d)@c -, 9. PROPELLER I 5. FUEL -Ll MANUFACTURER: Hoffman Propeller 2 TANKS: 62 litres each one (I 6.38 US gallons) MODEL: HOL7GHM A 174 l77C BLADES: MAXIMUM CAPACITY: 124 litres (32. 76 US gallons) 2 blades Qf Laminated hard wood. Composite structure, epoxy fi bre glass cover MAXIMUM USABLE FUEL: 120 litres (32 US gallons) TYPE: Fixed pitch DIAMETER: APPROVED FUEL: MOGAS ASTM 04814 (min RON 95/AKI 91) 1740 mm
� MOGAS EN 228 Super/Super plus (min. RON 95/AKI 91) i 10. MAXIMUM OPERATI NG ALTITUDE AVGAS 100 LL (ASTM 0910) Maximum operating altitude is 13000ft(3962 m) MSL. J Prolonged use of Aviation Fuel Avgas IOOLL results in greater wear of valve seats and greater combustion deposits •I inside cylinders due to higher lead content. Make reference to Rotax Maintenance Manual which prescribes dedicated J At altitudes above 10000/t (3 048 m) up to and including 13000 /t (3 962 checks due to the prolonged use of Avgas. CAUTION! m) ,j/ight crew is recommended to use supplemental oxygen.
6. LUBRICANT Recommended by Rotax: 11. AMBIENT TEMPERATURE BRAND DESCRIPTION SPECIFICATION VISCOSITY CODE SHELL AeroShell Sport API SL SAE 10 W-40 2 Ambient temperature: from-25°C to +50°C. Plus 4
Use only oil with classification "SG" or higher. I see Rotax AP! R4 list of recommended commercial brands and types lrH'lT• Sl-912-016 for
7. COOLANT LIQUID Flight in expected and/or known icing conditions isfo rbidden. Refer to "Rotax Operators Manual" - last issue -, "Operating Media" Section. NOTE: For the Engines affected by Rotax SB-912-066 Rl, the waterless coolant is not permitted)
8. PAINT To ensure that the temperature of the composite structure does not exceed limits, the out er surfaceof the airplane must be painted with white paint, except for areas of registration marks, placards, and ornament. Refer to AircraftMaintenance Manual (AMM), Chapter 51, forspecific paint requirements.
Approved Ed. I, Rev. 2 Ed Approved I, Rev. 0 Section 2 - Limitations Section 2 - Limitations AIRSPEED INDICATOR MARKINGS POWERPLANT LIMITATIONS AFMS forVFR NIGHT equipped airplanes AFMS forVFR NIGHT equipped airplanes TECNAM [?�@®@ dl@ &ilU'©U'@m Page 2N - 11 !?�®®®dl@ &t!U'©U'@m rPOo@[}u�!iYAl@Uil (!!]®0 Page 2N - 10 0 rPOo@[}u� !iYAl@Uil(!!]@O (1()fE'ciiA'iW 0 (1()
I 12. POWERPLANT INSTRUMENTS MARKINGS -.J Powerplant instrument markings and their colour code significance are shown be
low: · I � � REDLINE GREEN ARC YELLOW ARC REDLINE I INSTRUMENT Minimum Normal Caution Maximum limit operating limit i Propeller rpm -- 577 - 2265 2265 - 2388 2388 .,,...I Oil temp. 50 50-130 -- 130 1 oc CHT* -- 0-135 -- 135 oc CT -- 0-120 -- 120 oc j OP LOW ··-- - Oil pressure psi - -- 102 l WARNING 12 psi I
Fuel press. psi FPLOW 2.2-7.26 -- 7.26 WARNING 2.2 psi 1 ..J INTENTIONALLY LEFT BLANK *- 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 l] ,..,,, 13. OTHER INSTRUMENTS MARKINGS '
REDARC GREEN ARC YELLOW ARC REDARC INSTRUMENT Minimum limit Normal operating Caution Maximum limit
Voltmeter 10-10.5 Volt 12-16 Volt -· 16-16,5
Ed.I,Rev. Ed.I, Rev. 2 Approved 2 Section 2 - Limitations Section 2 - Limitations
POWERPLANT INSTRUMENTS MARKINGS J for Hoffman propeller equipped airplanes with MTOW Increment at 650 kg AFMS N"S7 AFMS forVFR NIGHT equipped airplanes JJ@0 &ll[J'@d �On@UuU �[]\)Q!l@a Page �- JJ@0 &rl[J'@[J'lfilOO �On@!Ju� �lfil[]\)Q!llfila �TEcNAM rw2®®@ wH2-12 E«JrE'CNA'M Page 2N - 13
14. WEIGHTS
Condition Weight
Maximum takeoffweight 650 kg 1433lb Maximum landing weight 650 kg 1433lb
Baggage Compartment
Maximum weight 20 kg 44lb Maximum specific pressure 12,5 kg/dm2 256 lbs/sq in
INTENTIONALLY BLANK LEFT
Ed 1, Rev, 0 Approved Approved Ed. I, Rev. 2 Section 2 - Limitations Section 2 - Limitations WEIGHTS WEIGHTS AFMS for VFR NIGHT equipped airplanes AFMS for VFR NIGHT equipped airplanes age 2N - Cl r?an�� P 14 �- Cl rPan�IA'll @ooQ!l@(J a 2 - E«Jr'Ecil'A'M � �@ &!Iii'� �lYl&lll (-«JT'ic'NA'M �@ &II� P ge N ls
15. CENTER OF GRAVITY RANGE
Vertical plane tangent to the propeller flange (the aircraft Datum must be levelled in the longitudinal plane)
Refer to the seat track supporting beams (see procedure in Levelling Section 6)
1.841 m (20% MAC) aft of datum for all weights Forward limit 1.978 m (30% MAC) of datum for all weights Aft limit aft
The pilot is responsible for ensuring that the airplane is properly loaded. Refer to Section for appropriate instruc tions. 6
INTENTIONALLY LEFT BLANK
Ed.I, Rev. 2 Approved Section 2 - Limitations Ed.I, Rev. 2 Section 2 - Limitations CENTER OF GRAVITY RANGE for Hoffman propeller equipped airplanes with MTOW Increment at 650 for Hoffman propeller equipped AFMS N"S7 airplanes with MTOW Increment at 650 kg F 7 J)@ &llU'@U'@OO A MS N'S kg CJ [fO�@lfil� lt:'iJ@[Jj)(!fl@O Page WH2-l 6 &llU'@U'@OO 7 �®@@ JJ@ CJ [f0�@� lt:'iJ@[Jj)(!fl@O Page WH2-l � TECNAM [?�@@@ � TECNAM 17. MANOEUVRES LOAD FACTOR LIMITS 16. APPROVED MANOEUVRES
The aircraft is certified in Normal Category in accordance with EASA CS-VLA regu Manoeuvre load factors limits are as follows: lation applying to aeroplanes intended fornon-aerobatic operation only. Positive Negative Non aerobatic operation includes: + 3.8 g - 1.9 g Any manoeuvre pertainingto "nonnal" flight Stalls (except whip stalls) Manoeuvre load factorslimi ts with flapsextended are as follows: Lazy eights Positive Negative Chandelles + 1.9 g Og Steep turns in which the angle of bank is not more than 60°
Recommended entry speeds for each approved manoeuvre are as follows:
Manoeuvre Speed [KIAS] ·�1
Lazy eight 98 Chandelle 111 LI J Steep tum (max 60°) 98 Stall Slow deceleration (1 ktsls) [l ]
Acrobatic manoeuvres, including sp ins and turns ivith angle of bank of [ l J more than 60°, are not approvedfo r such a catego1y.
Limit load fa ctor could be exceedl!.d abruptly jl1ghl controls at : by moving [ their end run at a speed above (Manoeuvring Speed: KIAS). /!,. 98 I
Flight in expected and/or known icing conditions, in proximity of storms or in severe turbulence is fo rbidde n. [ 1 ] J "l
:1i
J Ed 1, Rev. 0 Approved Ed 1, Rev. Section 2 - Limitations Approved 0 Section 2 - Limitations APPROVED MANOEUVRES MANOEUVRES LOAD FACTOR LIMITS AFMS forVFR NIGHT equipped airplanes AFMS for VFR NIGHT equipped airplanes &!IU'@U'®OO - IP�®®® d]@ &ilU'@d rfDO@� �@IJillYl@D 1 s t«)'f'Ec'N'A"iJ rP�®®® dJ@ 0 rfDo@lfil�ltiYAl@IJil[)!]@O Page 2N (1()TECNAM 0 Page 2N - 19
18. DEMONSTRATED CROSS WIND SAFE OPERATIONS 20. KINDS OF OPERATION EQUIPMENT LIST (KOEL)
The aircraft controllability during take-offs and landings has been demonstrated with a cross wind components of 15kts. This paragraph reports the KOEL table, concerning the equipment list required on under CS-VLA regulations to aUow flight operations in VFR Day and VFR board Night. 19. FLIGHT CREW Flight in VFR Day and Night is permitted only if the prescribed equipment is in Minimum crew: I pilot stalled and operational. Maximum number of occupants: 2people (including the pilot)
VFR NIGHT operatio11 is limited to airfields providi11g centre fi11e illumi11atio11.
Additional equipment, or a different equipment list, for the intended operation may be required by national operational requirements and also depends on the airspace classificationand route to be flown. The owner is responsible for fulfillingthese re quirements.
Primary jliglu i11for111a//011 (a irspeed, a/1il11de, heading and a11i /11de) is provided by analogue instruments. informalion provid- All WARMNG ed by G3X is only intendedfo r sit11atio11al awareness.
Ed. 1, Approved Rev. Approved Ed. 1..R ev. 2 Section 2 - Limitations 2 Section 2 - Limitations
Demonstrated Cross Wind Safe Operations Kinds of Operation Equipment List (KOEL) [" .J for Hoffman propeller equipped AFMS VFR NIGHT equipped airplanes airplanes with MTOW Increment at 650 kg TECNAM [?�®@@ for &lj[j'@[j'@OO �Oa@Ou� liYAl@DilOO@O AFMS N"S7 CJ Page 2N - 20 �®@@ &Hrr@IT'@OO �O�@� �@Dil(!!]@O Page WHN2-21 �@ l«)T EcNAM �@ 0 Equipment VFR Day VFR Night 21. LIMITATIONS PLACARDS
ANALOGUE ALTIMETER . . The following limitation placards are placed in plain view on the pilot.
ANALOGUE AIRSPEED INDICATOR . .
MAGNETIC DIRECTION INDICATOR . . On the left side instrument panel, above on the left, it is placed the following placard reporting the speed limitations: ANALOGUE ATTITUDE INDICATOR .
ANALOGUE FUEL QUANTITY INDICATORS . • Manoeuvring Speed
ANALOGUE CHT INDICATOR . • VA � 98 kts
ANALOGUE RPM INDICATOR . • On the side of the instrument central panel, the following pla m nding the observance card is placed re • • of aircraft operating limitat o ANALOGUE OIL TEMPERATURE INDICATOR i i ns according to installed equipment con.figumtion(see KOEL, ANALOGUE VOLTMETER . . Para. 20): This ale is GARMIN GJX SUITE classified as VLA
TRANSPONDER . . approved for ALTITUDE ENCODER . . DAY OR NIGHT VFR SLIP INDICATOR . • (with required equipment)
LONGITUDINAL TRIM INDICATOR • . in non·icing conditions.
FLAP POSITION INDICATOR . . all aerobatics manoeuvres including COMM/NAY EQUIPMENT . . spinning are prohibited.
AUDIO PANEL/MARKER BEACON . . For operating limitations refer to the LANDINGffAXI LIGHT . KOEL in
STROBE LIGHTS . FLIGHT MANUAL
NAY LIGHTS . . ANNUNCIATOR PANEL . On the right hand side of the instrument panel the followingplacard is placed re minding BREAKERS PANEL • . the observance for "no smoking":
STALL WARNING SYSTEM . .
FIRSTAlD KIT . .
HAND-HELD FIRE EXTINGUISHER . . NO SMOKING
ELT . .
PITOT HEAT . In the baggage compartment following placard is placed: . TORCH (WITH SPARE BATTERIES) TIE-DOWN HARNESS PANEL LIGHTS . MAX WEIGHT EMERGENCY LIGHT . 20kg [44 lbs]
DIMMING DEVICES .
DAY/NIGHT SWITCH . DO NOT PLACE SHARP OBJECTS ON THE FLOOR
Ed. I, Rev. Ed Rev. - 2 Approved Approved Section 2 Limitations Section 2 - Limitations I, J
Kinds of Operation Equipment List (KOEL) LIMITATIONS PLACARDS equipped airplanes AFMS for VFR NIGHT equipped airplanes AFMS forVFR NIGHT !i'©li'� @ @ll Page &110'@0'@00 �Un@[}uQ @ @ TECNAM �®@@d]@ &ll �Un@!filQ [K'A] oooo 2N - 22 TECNAM [?�®@@ dJ@ c [K'Al IJi)Q!l U Page E«J c � 2N - 23 Below the screens and analogue instruments, the fo llowing labels are placed: G3X 22. OTHER PLACARDS
Engine compartment placards
l,
[ COOLANT OVERFLOW BOTTLE ] LEVEL BETWEEN MINIMUM AND MAXIMUM KEEP l 1 Oil brakes reservoir placard
• c
• c •c •c •c • c ( �Oil Brakes • MIL·PRF·5606H) l Ed. I, Rev. 2 Approved Approved Ed. I, Rev. I Section 2 - Limitations Section 2 - Limitations Limitations placards OTHER PLACARDS AFMS forVFR NIGHT equipped airplanes TECNAM [p�@®@ &/l!i'@[j'@OO lfU�@lfil� �@Ui)O!l@U AFMS forVFR NIGHT equipped airplanes CJ Page 2N - 24 lP�®®® &l!!i'@li'®OOlfUn@ltu� �IIDUilO!l@U 2s E«J dJ@ I � 'T'EC'NiM dl©CJ Page 2N - I Usable fuel markings Throttle marking
Left Ta nk Right Ta nk Usable Fuel Usable Fuel
60 litres 60 litres T H R 0 Allowed fuel placards T T L E
MOGASASTM 048 14 �mm RON 95/AKl9 1) EN 228 Super/Super Plus I (min RON 951AKl91 I
AVGAVGAS AS 100 LL (ASTM 0910)
Capoclly • 62 LT US G. _ Fuel selector valve marking I (1G.3 llonJ I
TOP WING
...... , . Emergency exit placard ...... Choke placard E M E RGE N CY EXIT
Parking brake placard Alternate static port placard
FREE LOCK
Approved Ed. I, Rev. 2 Approved Ed. I, Rev. 2 Section 2 - Limitations Section 2 - Limitations OTHER PLACARDS OTHER PLACARDS l AFMS forVFR NIGHT equipped airplanes AFMS forVFR NIGHT equipped airplanes &!l!J'@U'@m - TECNAM [?�@@® &11!1'@!1'®™ lPOtl@!filQ [i"il@ITilQ!l@O �@@@ c f?Otl@Uil� !AYAl@ITilQ!J@Q Page 2N 27 d)@c Page 2N - 26 I �TECNAM JJ@ j Cabin heat/defrost placard Flap indicator placard
FLAP
Backrest lever placard Carb heat placard BACKREST: PRESS • TO UNLOCK
Ignition key placard Safety equipment location placard
FIRST AID KIT FIRE EXTINGUISHER are in the luggage l ] compartment
Master/Generator placards Elt placard
ON ll .. M e. A .. • s R T " T . E 0 R .. l I OFF Map-light placard Battery placard
•• ] BATTERY INSIDE BEHIND THIS PANEL MAP - LIGHT [ J 1 Ed. Approved Ed. 1, Approved 1, Rev. 2 Rev. 2 Section 2 - Limitations Section 2 - Limitations OTHER PLACARDS r· l OTHER PLACARDS I r-·-1 AFMS forVFR NIGHT equipped airplanes E«)TECNAM [?�@®® &ll!i'©!i'@OO l?Un@Uu� �&lITil(l!)@U Page - 2s dl©CJ 2N I Annunciator panel ll�b�I Upper panel labels
["f'
Y Switches labels [ ..., lNTENTIONALL LEFT BLANK
AV IONIC PITOT STROSE LANDING NAV FUEL PUMP I MASTER HEAT LIGtfT LIGHT LIGHT
DayfNightswitch label
Door lock lever
CLOSED
OPEN
- ... Ed. I, Rev. Approved 2 Approved Section 2 - Limitations Ed. I, Section 2 - Limitations Rev. 6 OTHER PLACARDS 1 OTHER placards 1 AFMS forVFR NIGHT equipped airplanes
&ll[[@!Y@OO age - [?�@®�@ c [fO�@��@Uil l!!l@O P �TECNAM 3N I I [ 10.1. SECTION 3 - EMERGENCY PROCEDURES INDEX
1. INTRODUCTION ...... 3 2. AIRPLANE ALERTS •••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••• 4
2.1. Electric Power System Malfunction ••••••••••••••• ••••••••••••••••••••••••••••••••••••••• •••• ••••• 5
2.2. Pltot Heating System Failure •••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••• 6 2.3. G3X Failures ...... 7
3. AIRPLANE EVACUATION ...... 8
4. ENGINE SECURING ...... 8 [ 5. ENGINE FAILURE ...... 9 5.1 . Engine Failure During Take·Off Run ...... 9
5.2. Engine Failure Immediately After Take·off...... 9 INTENTIONALLY LEFT BLANK 5.3. Engine Failures During Flight ...... 10 5.3.1 Low Fuel Pressure ...... 10
5.3.2 Low Oil Pressure ...... 11
5.3.3 High Oil Temperature ...... 12
5.3.4 CHT/CT limit exceedance .••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••• 13
[ 6. IN-FLIGHT ENGINE RESTART ...... 14
SMOKE AND FIRE ...... 15 7. 7.1. Engine fire on the ground ••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••• ••••••••••• 15
7.2. Engine Fire During Takeoff ...... 15 7.3. Engine Fire ln·Fllght ...... 16
7.4. Cabin Fire Electrical smoke in cabin during flight ••••••••••••••••••••••••••••••••••••• 16 l 7.5. Electrical smokI e/fire in cabin on the ground ...... 16
8. LANDING EMERGENCIES ...... 18
8.1. Forced Landing Without Engine Power ...... 18
8.2. Power-On Forced Landing ••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••• 18
8.3. Landing With A Flat Nose Tire ...... 18
8.4. Landing With A Flat Main Tire ...... 19
9. RECOVERY FROM UNINTENTIONAL SPIN...... 20
10. OTHER EMERGENCIES ...... 21
10.1. Unintentional Flight Into Icing Conditions ...... 21
10.2. Trim System Failure ...... 22
10.3. Static ports failure ...... 23
10.4. Flaps Failure ••••••••••••••••••••••••••••••••••••••••••••••••••.••••••••••••••••••••••••••••••••••••••••••••• 23
Approved Ed. /, 6 Ed. I, 0 Rev. Rev. Section 2 - Limitations Section 3 - Emergency procedures OTHER placards ] INDEX AFMS forVFR NIGHT equipped airplanes AFMS for VFR NIGHT equipped airplanes U'@d - &ll TECNAM [?�@@�@ &llU'©U'� lfO�@froU �@Ui)(!!]@a �TECNAM [?�@@@ad]@ a lfOo@ltoU �@uuma Page 3N - 3 t«l a Page 3N 2 I
1. INTRODUCTION
Section 3 includes checklists and detailed procedures to be used in the event of emergencies. Emergencies caused by a malfunction of the aircraft or engine are extremely rare if appropriate maintenance and pre-flight inspections are carried out. Before operating the aircraft, the pilot should become thoroughly familiarwith the present Manual and, in particular, with the present Section. Further, a con tinued and appropriate training should and self-study should be done. In case of emergency the pilot should acts as follows: 1. Keep control of the aeroplane Analyse the situation 2. 3. Apply the pertinent procedure 4. Inform the Air Traffic Control if time and conditions allow. Two types of emergency procedures are hereby given: a. "Bold faces" which must be known by heart and executed in the correct and com plete sequence, as soon as possible as the failure is detected and recognized; INTENTIONALLY LEFT BLANK These procedures characters are boxed and highlighted, an example is shown below: OFF BEFORE ROTATION: ABORT TA KE
l. Throttle IDLE Rudder Keep headi11g co11trol 2. 3, 4.
b. Other procedures which should be well theoretically know and mastered, but that are not time critical and can be executed entering and following step by step the AFM appropriate checklist.
For the safe co11d11ct of farerflights, any anomaly andlorfailure 11111st be com1111111icated to the National 1lwhoriries i11 charge. /11 order f(I plll the aircmfl In a/111/y operar/0110/and srife co11ditio11.
In this Chapter, fo llowing definitions app ly : Lant/ as soon rrs possible: land without delay at the nearest area at which a safe approach and landing is assured. suitable Land as soon as practical: land at the nearest approved landing ar ea where suitable repairs can be made.
Ed. 1, Rev. 0 Ed. I, Rev. 0 Section 3 - Emergency procedures Section 3 - Emergency procedures INDEX J INTRODUCTION [� J forVFR NIGHT equipped airplanes AFMSfor VFR NIGHT equipped airplanes AFMS age JN - !J'@d Page 3N - 4 �®®W© [] &ll!J'©d P E«J TEC NAM �@@W@ [] &ll l?Dn@IIDQ�@ITilU!l@D �TECNAM l?Dn@IIDQ�@ITilU!l@ D I s I 2. AIRPLANE ALERTS 2.1. ELECTRIC POWl!R SYSTEM MALFUNCTION
The alert lights, located on the annunciator panel, feature the following colours:
to indicate that pertinent device is turnedON to indicate no-hazard situations which have to be considered and which require a proper crew action 11���1 to indicate emergency conditions Alternator light may illuminate for a faulty alternator or when voltage is above in this case the over-voltage sensor auto matically shuts downI 6V; the alternator.
lfALTOUT caution is ON:
J. Verifyfailure 2. Circuit breaker(s) Check 3. Generator switch: OFF sec. then back ON I
ifALTOUTcaulion persists ON:
4. Generator switch: OFF 5. Reduce electrical load as much as possible
Land as soon as practical. 6.
The battery can supply electrical power for al least 30 minutes.
Ed. I, Rev. 0 Ed. Rev. 2 Approved I, Section 3 - Emergency procedures Section 3 - Emergency procedures AIRPLANE ALl!RTS AIRPLANE ALERTS c-- -- AFMS forVFR NIGHT equipped airplanes AFMS for VFR NIGHT equipped airplanes �TECNAM [p�@@@::.d]@ [] &llU'@d �Oo@llu��@ITil Ull@O Page 3N -6 �TECNA0M [p�@@�@ c &Jl[[@U'@OO �OO@IJu��@!Ji) Ull@O I Page 3N-7 I 2.2. PITOT HEATING SYSTEM FAILURE
PITOT HEAT ON When the Pi tot Heat system is activated, the green safe operating 2.3. G3X FAILURES annunciation is ON;
In case of LH or RH display failure, navigation and engine data will be automati cally available in the remaining display(spl it mode).
If the amber PITOT HEAT is turned ON, but the caution remains ON, the Pitot Heat system is not functioning properly.
In this case apply followingprocedure:
OFF 1. Pilot Heat switch Check Pilot Heat circuit breaker JN 2. INSTRUCTION: 3. ON revert to the remaining display. Pilot Heat switch 4. Check PITOT HEAT caution light: If the amber light stays ON, assume PITOT HEAT malfunction. Avoid visible moisture conditions.
Ed. I, Rev. Ed. 1. Rev. Approved 2 Approved - 2 Section 3 Emergency procedures Section 3 - Emergency procedures
AIRPLANE ALERTS AIRPLANE ALERTS AFMS N'S7 for Hoffman propeller equipped airplanes with MTOW Increment at 650 kg AFMS for VFR NIGHT equipped airplanes �@@@ dJ@ &l!U'@d - 9 �TECNAM CJ lfUH@� �@[ii)Q!l@U Page WH3 �TECNAM l?�@@f&,JJ@ &l!U'@d lfUH@IJil� �@[ii)Q!l@U - 8 CJ Page 3N I
3. AIRPLANE EVACUATION 5. ENGINE FAILURE
With the engine secured and propeller stopped (if practical): 5.1. ENGINE FAILURE DURING TAKE-OFF RUN I. Parking brake: ON Seat belts: u11strap completely I. Throttle: IDLE (keep fl11/y out) 2. Headphones: REMOVE Rudder: Keep lleadi11g colltro/ 3. 2. OPEN 3. Brakes: app lyas 11eeded 4. Door: 5. Escape away fr om flames/ /w t e11gi11e compartme11tlsp illi11gfu el ta11ks/ Hot Whensa fe ly stopped: brakes. OFF. 4. Ignition key: OFF 5. Fuel selector valve: 6. Electric fuelpump: OFF Alternator&Master switches: OFF. 4. ENGINE SECURING 7. 5.2. ENGINE FAILURE IMMEDIATELY AFTER TAKE-OFF Following procedure is applicable to shut-down the engine in flight: I. Speed: keep mi11imum KIA S Throttle Lever IDLE 61 2. Find n sui!Bble nlace to lnnd safclv. I OFF 2. Ignition key Fuel Selector OFF 711e immediale landi11g slto11ld be planned slra/g/11 ahead with 3. 4. Electrical fuel pump OFF small changes in directions not exceeding 45° to the left Generator switch OFF or011/ y the 1·igl11. 5. 45° to �
3 Flaps: as needed
Stall sp eed increases with bank angle and long iludinal load
fa ctor. Acoustic slall warning will in any case provides a cor- reel anticipated cue of incipient stall. WARNING
At, or right before, touch down
4. Throttle: IDLE (fu lly out a11d llold) 5, Ignition key: OFF 6. Fuel selector valve: OFF 7. Electric fuel pump: OFF 8. Alternator& Master switches: OFF
A single engine aircraft take off should always be preceded by a thorough lake off emergency pilot self-briefing. Decision to try an engine emergency restart right af ter take off should be taken only ife11 viro11111e111a/ situation requires Ir: pi/or shall never ignore the priority of atlentively fo llow an immediate emergency landing. Af ter possible mechanical engine sei=ure, fire or a major pro peller damage, engine reswrt ollempl is not recommended.
Ed. I, Rev. 2 Approved Approved Ed I, 0 Section - Emergency procedures Rev. 3 Section 3 - Emergency procedures AIRPLANE EVACUATION ENGINE FAILURE AFMS for VFR NIGHT equipped airplanes AFMS forVFR NIGHT equipped airplanes &fl[J'@[J'film - lo �©©�@ CJ l¥Da@lfil��@[Ji)O!l@D Page 3N lP�©©�@ &fl[J'@!i'@OO l¥Da@� �TECNAM I CJ �@UUO!l@O Page 3N - 11 �TECNAM I 5.3. ENGINE FAILURES DURING FLIGHT Oil Pres ure S.3.2 Low
If oil pressure is below12 psi/OP LOW warningis ON: If the fuel pressure indicator fallsbelow 2.2 psi/FP LOW warningis ON: 1_ Throttle Lever REDUCE Minimum practical Land as soon as practical to ON 2, I. Electric fuel pump: select oppositeft1el tank ifNOT empty 2. Fuel selector valve: OP LOW Check both If oil pressure does not increase and warningpersists ON: 3. Fuel quantity indicators:
Land as soon as possible 8) 3, applying forced landing procedure (See Para. If fuelpressure does not build up: Land as soon as possible 8) -1 applying forced landing procedure (See Para.
[ ] [ ]
[] J
Ed. /, Rev. 2 Approved l J Approved Ed. 1, Rev. Section - Emergency procedures 3 2 Section 3 - Emergency procedures ENGINE FAILURE J ENGINE FAILURE ] AFMS for VFR NIGHT equipped airplanes AFMS for VFR NIGHT equipped airplanes �£W@ M IMJml)!lffl Page 3N - 12 c !¥Dnoo D l«J rE'C NA'M �N@ E«JrE'cNA"Xf &II� I c !¥DnoolfilaIMJgoo &llJ Page 3N -13 &II� I HT/CT limit cxcccdancc S.3.3 High Oil Te.mpe.rall1re 5.3.4 If high OT occurs, apply following procedure:
If CHT is above 135°C or CT is above I20°C, apply following procedure:
IfOP LOW warning is ON, see para. 5.3.2 "Low Oil Pressure". - oil pressure is within limits (OP HIGH and OP LOW warning are IfOP LOW warning is ON, see Para. 5.3.2 "Low Oil Pressure". OFF):If oil pressure is within limits (OP HIGH and OP LOW warnings are OFF): If 1. Throttle Lever REDUCE to Minimum practical 1. Throttle Lever REDUCE Mi nimum practical 2. Land as soon as practical
The thermostatic valve regulating the water flow to If oil temperature does not decrease the cylinder heads, could be damaged or a coolant 2. Airspeed if practical INCREASE leakage can be present in the coolant supply line.
Ifoil 1e111pera/11re does 1101 come back within limits, lhe If CHT/CT does not decrease and engine shows roughness or power loss: thermos/aliC 1•alve reg11/a/ing the oil flow to the heat exchangers, could be damaged or an oil leakage can 3. Land as soon as possible applying forced landing procedure (See Para. 8) be present in lhe oil supp ly line.
3. Land as soon as practical If engine roughness, vibrations, erraticbehaviour, or high CHT/CT occurs: 4. Land as soon as possible applying forcedlanding procedure (See Para. 8)
Ed. Rev. 2 Approved 1, Rev. 2 Section 3 - Emergency procedures Approved Ed I, Section 3 - Emergency procedures ENGINE FAILURE ENGINE FAILURE AFMS for VFR NIGHT equipped airplanes �TECNAM AFMS for VFR NIGHT equipped airplanes [?��© &ll[J'@� - �TECNAM &ll!J'©d c lfOH�Ou��@!JU(]!]@O Page 3N 14 [?�@®�@ 0 lfO��lfil� �&l!JU(]!]@a - ls I Page 3N I
6. IN-FLIGHT ENGINE RESTART 7. SMOKE AND FIRE
7.1. ENGINE FIRE ON THE GROUND Afl er a mechanical engine fire or a mqjor propeller da mage I. Fuel Selector OFF .tei=l1re, engine restart is not recommended 2. Electrical ru e! pump OFF 3. Ignition key OFF 4. Throttle lever FULL POWER 5, Cabin Heat OFF 6, Alternator&Master Switches OFF ON if required 7. Parking Brake ENGA GED l. Carburettor heat ON Aircraft Evacuation 2 Electrical fuel pump 8, carry out immediately CHECK 3 Fuel quantity indicator select opposite tank ifnot empty 4_ Fuel Selector BOTH 7.2. ENGINE FIRE DURING TAKEOFF 5. lgn ition key START 6. Ignition key BEFORE ROTATION: ABORT TAKE OFF 7. Throttle lever SET as required Throttle Lever IDLE (fu lly out a11d /t old) 1. Rudder Ifthe fu el quantity in the selected tank which feeds the engine is 2. Keep /1eadi11g co11trol Brakes low, select the opposite side ji1el tank by of the fi1el se 3, As required means lector. With aircraft under control I. Fuel Selector OFF In case or unsuccessful engi ne reslnrl: 2. Electrical fuel pump OFF Ignition key SECURE(see engine securing 3. OFF Engine Cabin Heat I. procedure on Para. 4) 4. OFF 5, Alternator&Master Switches OFF Parking Brake Land as soon as possible 6, ENGAGED 2. applying forced landing procedure (See Para. 8) Aircraft Evacuation carry out immediately 7.
Ed Rev. Approved 1, 2 Approved Ed 1, Rev. 2 Section - Emergency procedures 3 Section 3 - Emergency procedures IN-FLIGHT ENGINE RESTART SMOKE AND FIRE ------
AFMS for VFR NIGHT equipped airplanes AFMS for VFR NIGHT equipped airplanes ��®®�@ CJ&ll rr©d lfOn@lfilU�@Uil Ull@O ��®®�© CJ&ll rr@d lfOn@!filU lMJ®UilUll®O Page 3N - 11 E«Jf£cNiAi Page 3N- 16 I (!{)r'EcNiAi I
7.3. ENGINE FIRE IN-FLIGHT
1. Cabin heat: OFF 2. Fuel selector valve: OFF 3. Electric fuel pump: OFF ./. Throttle: FUL L FOR WA RD 11ntil the engine stops 5. Ignition key: OFF 6. Cabin vents: OPEN
Do not attempt engine restart
7. Land as soon as possible applying forced landing procedure(See Para. 8).
7.4, CABIN FIRE / ELECTRICAL SMOKE IN CABIN DURING FLIGHT I. Cabin heating: OFF Cabin vents: OPEN 23. Try to choke the fire. Direct the fireext inguisher towards flamebase INTENTIONALLY LEFT BLANK If smoke pe rsists: OFF I. Alternator&Master switches: Land as soon as possible 2. and evacuate the aircraft
Ifthe MASTER SWITCH is set to OFF, consider that flaps ex tension and pi/ch trim operation is prevented. .I
7.5. ELECTRICAL SMOKl!!/FIRE IN CABIN ON THE GROUND
I. Generator switch: OFF 2. Throttle Lever: IDLE 3, Ignition key: OFF 4. Fuel Selector Valve: OFF 5. Master Switch: OFF 6, Aircraft Evacuation carry 011t immediately
Approved Ed. I. Rev. Approved Ed. I, Rev. 2 2 Section 3 - Emergency procedures Section 3 - Emergency procedures SMOKE AND FIRE SMOKE AND FIRE AFMS forVFR NIGHT equipped airplanes AFMS for VFR NIGHT equipped airplanes
�®®�© CJ&ll U'@!ralOO - ��@ CJ&JlU'@ !raJOO @UiJQ �Ua@UiJQ �@Uil(ll]@D Page 3N D� �@Uil(lli)U Page 3N - �TECNAM 1s I E«}TECNAM � 19 I 8.4. LANDING WITH A FLAT MAIN TIRE 8. LANDING EMERGENCIES If it's suspected a main tire defect or it's reported to be defective: 8.1. FORCED LANDING WITHOUT ENGINE POWER I. Pre-landing checklist: Complete Flaps: Land I. Flaps: UP 2. 3. Land the aeroplane on the side of runway opposite to the defectivetire to 2. 7I K!A S Airspeed: compensate the change in direction which is to be expected during final 3. Find a suitable place to land safely, plan to approach it upwind. rolling -1. Fuel selector valve: OFF 4. Touchdown with the GOOD TIRE FIRST and hold aircraftwith the flat 5. Electric fuelpump: OFF tire offthe ground as long as possible by mean of aileron and rudder con 6. Ignition key: OFF Tighten trol. 7. Safety belts: Wh en certain lo land [ As aircraft stops 5. Pe1form(see Para. 4) 8. Flaps: as necessaJy Engine securing: OFF. Pe1form(see Para3) 9. Airplane evacuation: Generator and Master switches: 6. Glide ratio is therefo re in =ero wind conditions eve1y IOOOft [ above Ground level12.8, it is possible to cover ca. 2 NM
8.2. POWER-ON FORCED LANDING [,
Airspeed: 7I K!A S 1. UP 2. Flaps: 3. Locate the most suitable terrain for emergency landing, plan to approach [ it upwind. 4. Safety belts: Tighten Wh en certain to land, righl before touch down 5. Flaps: as necessaJy [ OFF 6. Fuel selector valve: 7. Electric fuelpump: OFF OFF 8 Ignition key: OFF 9. Generator and Master switches: r. 8.3. LANDING WITH A FLAT NOSE TIRE I. Pre-landing checklist: Complele 2. Flaps: land 3. Land and maintain aircraftNOSE HIGH attitude as long as possible. As aircraftstops
4. Engine securing: Perform (see Para. 4) 5. Airplane evacuation: Pe1form (s ee Para. 3)
Approved Ed. I, Rev. Ed.I, Rev. 2 Approved 2 Section 3 - Emergency procedures Section 3 - Emergency procedures LANDING EMERGENCIES LANDING EMERGENCIES AFMS forVFR NIGHT equipped airplanes AFMS for VFR NIGHT equipped airplanes TECNAM [p�@@@=J)@ &tJ[[@afilm �UH@Gu� �@[fillliJ@U ag - TECNAM IP�®®�© &ll[f@afilm �Ua@Gu� �®ITilllil@U - � c P e 3N 20 I � 0 Page 3N 21 I
9. RECOVERY FROM UNINTENTIONAL SPIN 10. OTHER EMERGENCIES If unintentional spin occurs, the followingrecovery procedure should be used: 10.1. UNINTENTIONAL FLIGHT INTO ICING CONDITIONS I. Throttle: IDLE (fu ll out positio11 mid ilold) 2 Rudder: fu ll, i11 tileopp osite directio11 of tilesp i11 Carburettor ice is possible when fly ing al low engine rpm in visi 3. Stick: ce11tralize a11d liold11eutral ble moisture (o utside visibiltty less than 5 km. vicinity offo g. mist. As tile sp i11 stops: clouds, rain, snow or hail). Airbox carburettor heater is designed prevent carburettor ice, less ef fectively fu nctions as a de Rudder: SET NE UTRA L to help -1. icing system. 5 Aeroplane attitude: smootilly recover averti11g sp eeds i11 excess of VNE ON Throttle: Reatljust to restore e11gi11e power. I. Carburettor heating: 6. [ 2. Immediately fly away from icing conditions ( changing altitude and di rection of flight, out and below of clouds, visible moisture, precipita tions) 3. contin11e to move to keep fr eefrom ice b11ild 11p Keepfu ll rudder against rotation until sp in has stopp ed. Controls surfaces: [ 4 Throttle speed: increase rpm. One complete turn and recovery takes around 500 fe el. Cabin heat: ON Jn case of ice fo rmation on wing leading edge. stall speed co11ld highly increase and stall may become asymmetric. In case of sta bilator ice accretion ii may lose its effi ciency, leading to aircraft pitch up response and loss of control.
]
Approved Ed. Rev. Ed. I, Rev. I. 2 Approved Section - Emergency procedures 2 3 Section 3 - Emergency procedures RECOVERY FROM UNINTENTIONAL SPIN OTHER EMERGENCIES Hoffman propeller equipped airplanes with MTOW Increment at 650 k AFMS N"S7 for 9 &l!!J'@!J'@OO �O�@[}i)Q AFMS forVFR NIGHT equipped airplanes 0 lR9J@!Ji)(!!]@0 Page WHN3 - 23 &ll!J'@[J'@OO �U�@[}i)Q �@!Ji)[]!)@O l«JTEC NAM [p�@@@ dJ@ t«lrlc'N'A'M [p�@@N@ c Page 3N - 22 J
10.2. TRIM SYSTEM FAILURE 10.3 STATIC PORTS FAILURE
l _ , In case ofstatic ports fai ure the alternate static port in the cabin (identifiedb y the Trim Jamming placard below) must be acttvated. Should trim control be inoperative, act as follows: 1. Breaker: CHECK JN CHECK/or correct position 2. LH/RH Trim switch:
Ifjamming persists
CHECK ON 1. Trim cutout switch: dj ust to control aircraft without excessive stick fo rce In this case apply followingprocedure: 2. Speed: � Land aircraftas soon as possible. I. Cabin heat OFF 2. ALTERNATE STATIC PORT VALVE OPEN 3. Continue the mission Trim Runaway In event of trim runaway, act as follows: 10.4 FLAPS FAILURE I, Trim cutout switch: OFF cljust Jo control aircraft ivilhout excessive stickfo rce 2. Speed: � In event of flaps up landing, account for: 3. Land aircraftas soon as possible. - Approach speed: 65 K!A S Landing length: 35% increased
Approved Ed. I, Rev. Ed 2 Approved I, Rev. I Section 3 - Emergency procedures Section 3 - Emergency procedures OTHER EMERGENCIES OTHER EMERGENCIES AFMS for VFR NIGHT equipped airplanes AFMS for VFR NIGHT equipped airplanes
- Page 3N 24 �®®00 JJ@ &lllf©d - �®®�© &llir©� l?Un@OilQli"il&i!Iiloo&ia CJ l?Un@OilQli"il&i liiloo&iUP age 4N E!(]rEc NAM CJ I �TECNAM i
SECTION 4 - NORMAL PROCEDURES
INDEX
1. Introduction ...... 3 . . . . 2. Airspeeds for normal operations ...... 3
3. Pre-flight Inspections ...... 5
3.1 . Cabin Inspection ...... -...... 5
3.2. Aircraft Walk-around ...... 6
4. Checkllsts ...... 12 ...... 4.1. Before Engine Starting (After Pre-flight Inspection) ...... 12 . . 4.2. Engine Starting ...... 13 ...... 4.3. Before taxiing ...... 13
4.4. T-llng ...... 14 ...... INTENTIONALLY LEFT BLANK 4.5. Prior to takeoff ...... 14 . . . . 4.6. Takeoff and cllmb ...... - .•••••• 15
4.7. Cruise...... 15
4.8. Before Landing ...... 16
4.9. Balked landing/missed approach...... 16
4.1 After landing ...... 16 4.1o.1. Engine shut down ...... 17
4.12. Post-flight checks ...... 17 ......
2 Ed. Rev. Ed. Rev. Approved 1, J, 0 Section 3 - Emergency procedures Section 4 - Normal procedures OTHER EMERGENCIES TABLE OF CONTENTS AFMS N"S7 for Hoffman propeller equipped airplanes with MTOW Increment at 650 kg TEC NAM [p�@@@ dJ@ CJ &IJ[?@� [?O�@OiJ� �@ITi)(\(]@O Page WH4-3 AFMS for VFR NIGHT equipped airplanes � &lj[J'@� [?O�@OiJQ �@ITi)(\(]@O -2 TECNAM �®@@ dJ@ CJ Page 4N
1. INTRODUCTION
Section 4 describes checklists and recommended procedures for the conduct of normal operations for aircraft. P2008JC
l Garmin G3X provides primmy engine and electric system pa rameters iriformation, supported by caution/warning lights in the annunciator panel and backup CHT indicator.
Analogue is a backup fo r !he informal ion provided by Since [ the pick-upCHT location fo r the sensors is differenl (cylinder 2G3X and re spectively) , analogue CHT could indicate a temperature up to 20°.f less than the G3X [ Garmin G3X indeed is NOT intended to be used as primmy ref J erence fo r flight and navigation information but only provides iriformation fo r increased situational awareness: primary flight iriformation {a ltitude, airspeed and heading) is provided by ana r.- logue instruments. !NTENTIONALL LEFT BLANK Y 2. AIRSPEEDS FOR NORMAL OPERATIONS
The following airspeeds are those which are significant fornon nal operations.
FLAPS 650kg
Rotation Speed (in takeoff, VR ) TIO 50 KIAS Best Angle-of-Climb Speed (Vx) oo 63 KIAS Best Rate-of-Climb speed 67 KIAS ( Vr) oo Approach speed TIO 61 KIAS r 'I l Final Approach Speed FULL 55 KIAS Manoeuvring speed (VA) oo 98 KIAS
Never Exceed Speed VNE) 143 KIAS LJ J ( oo
Ed. 1, Rev. 0 1! Approved Ed Rev. 0 Section 4 Normal procedures J, Section 4 Normal procedures - - J INTRODUCTION TABLE OF CONTENTS AFMS for VFR NIGHT equipped airplanes AFMS forVFR NIGHT equipped airplanes TECNAM �@®@ JJ@ &IJ!i'@d [?0�@� �@[Ji)OO@O �@®@ JJ@ c &IJ!i'@!i'®™ [?O�@� �@[Ji)[fil@O � " Page 4N - 4 �TECNAM Page 4N -5
3. PRE-FLIGHT INSPECTIONS
Before each flight, it is necessary to carryout a complete aircraft check including a cabin inspection followed by an external as below detailed. .
3. 1. CABIN INSPECTION
A Aircraft documents (ARC, Certificate of Airworthiness, Noise certificate, Radio COM certificate, AFM): check current and on board calculate (r ef this AFM sect. 6) check within lim its B Weight and balance: connected to hardpoints, check condition c Safety belts: OFF, o Ignition key: key extracted ON E Master switch: F Voltmeter: check (10- 12 V); G Lights: all ON, checkfor operation H Acoustic stall warning: check op eration INTENTIONALLY LEFT BLANK Master switch: OFF Baggage: check first aid kit, ELT, fire extinguisher, luggage stowed and fa stened with restraint net.
If
Ed. I, Rev. 2 Approved Approved Ed. I, Rev. 2 Section Normal procedures 4 - Section 4 - Normal procedures AIRSPEEDS for normal operations PRE-FLIGHT Inspections AFMS for VFR NIGHT equipped airplanes airplanes AFMS for VFR NIGHT equipped [?�@®® Jl@ &t!U'@d lfO�@[}uG [AVlli}[Ji)O!J@O 7 0 - J)@ �lf©dr?Un @� (K'Al@Uil(l!J@U Page 4N - 6 Page 4N �®®@ c
J.2. AIRCRAFT WALK-AROUND
the pattern carry out the checklists according to To perform the aircraft walk-around, ------shown in Figure 4-1. ,-- - -®-©- -© -© r or defects, cracks, I inspection is defined as fo llows: check/ I Visual ation as I or improper install I' tachments, excessive play, unsafe de in I For control swfaces, visual ' well as fo r general condition. _ tional check fo r freedom of movement sp ection also involves addi I nuts shall be imact. lines on bolts and I -�------and security. Red lubber '------{9- <1'.)- �
indico/ors must be veri n ed theji1el quantity Fuel i cat \\ by quantityembarked in the tanks: bylevel visual di check Of {lctualjiiel \ fied I must be used. \ d e ' uat d dipstick I gra I I a propeller movement " Jf ignitions key is in position, -· (------UWBOTH consequent lza:ardfor people can cause the engine with I stoning [. nearby. : I'�------II
Figure 4.1 carried out with the aircraft Fuel (//'(l/11age operation must be Fuel Selector Va lve to a level surface. Set Cockpit on A CHECK desired ji1el level (use graduated parkedprior to dral11f11el. Leftfuel fillercap OFF dipstick). Drain the left ji1el tank sump by quick drain valve using a cup to collect fi1el (drainage operation must be carried with the aircraftparked on a level surface). Check fo r water or other contaminants. Ma ke sure filler cap is closed B Pitot tube REMO VE pilot plug and check the pilot fo r obstrnctions. Do not blow inside pilot tube. Left side leading edge and wing Visual inspection, CHECK stall strips c skin D Leftstrobe light Visual inspection, CHECK fo r integrity and fixing E Leftaileron, hinges and Lefttank CHECK/or damage, freedomjrompla ys; vent left lank vent: CHECK fo r obstructions. F Leftflap and hinges Visual inspection
Ed. J, Rev. 2 Approved Ed 1, Rev. Section 4 - Normal procedures 2 Approved Section 4 - Normal procedures PRE-FLIGHT Inspections PRE-FLIGHT Inspections AFMS forVFR NIGHT equipped airplanes equipped airplanes AFMS for VFR NIGHT [p�@@@ �@ &/l[[@ufilfil lfO�@lfil\k - 0 WAJ@UilOO@O 4N 9 �@ &!\U'@!f®OO lfOfi@Gu� WAJ@UilOO@O Page 4N - 8 Page (p�®@@ 0 �'fEc'N'A'M E«)TECHAM T engine cowling surface conditions, then open both engine inspection heck the CHECK infla tion, tire condition, alignment, the following checks: doors and perfom1 G Leftmain landing gear fu selage skin condition Check fu selage skin a) Nacelle inlets and exhausts op enings must be free of obstructions. Check status, tire stallts (c uts, bruises, cracks and r:_om1ec�lo11 and integrity of air intake system, visually inspect that ram air excessive wea1), slippage markers integrity, mtake is unobstructed. Ifinlet and outlet plugs are installed, they must be gear structure and brakes hoses :there should removed. be no sign of hydra11licfluidleakage. b) Check radiators. Th ere should be no indication of leakage of fl11idand they [ I have to be ji-ee of obs/ructions. CHECK stabi/ator leading edge. Check the c) Checkforforeign objects H Stabilator and tab actuating mechanism of stabi/ator and the d) Onlvbe/Ore 1he fir st flight ofa dav : connection with related tab: CHECK ji"ee of (I) VerifY coola11t le ve in the e.tp<111sio11 tank, replenish as required up play, friction. CHECK f1 1selage bottom and to top mu l at l a of the e.rpa11slon tank). [, st be e st top skin. CHECK antennas fo r integrity. (level 213 (2) Ve rifY C1Jola11l e1•el in the ove1jlow bo//le: /e1>e/ must be betiveen min. and max. mark.l Vis11al inspection, checkfree of play, friction. Vertical tail and rudder ment, CHECK inflation. tire condition, align Before proceeding lo the next step be sure that magnetos and Mas L skin Right main landing gear fu selage skin condition. Check fu selage ter switch are OFF with the key extracted. and status, tire status (c 11ts. bruises, cracks excessive wea1), slippage markers integrity, (3) Tum the propeller by hond to andji-0111. fe eling the fi·ee ro1ation of brakes hoses: there should gear structure and 5°or 30° befo re the crankshaft stans to rowte. Ifthe propeller ccm be no sign of hydra111icfluidleakage. [ :1 beI tumed be/ween lite dogs with practically 110 jf icllon at all fu r Vis11al inspection ther inves1igation is necesswy. Tum propeller by hand in dlrec11011 M Right flap and hinges Visual inspection, checkfree of play, friction; of engine rotation several limes and observe engine fo r odd noises N Right aileron, hinges and Right Right side tank vent: checkfo r obstructions. or excessive resistance and normal compression. side tank vent (4) Carburettors: check the throttle and choke cables fo r condition Vis11al inspection, CHECK stall strips, and installation. Right strobe light, leading edge CHECK strobe light fo r integrity andfixing 0 (5) Exhaust: inspect fo r damages. leakage and general condition. and wing skin (6) Check engine mount and silent-blocks fo r condition. CHECKfor integrity and free of play, Stall indicator micro switch e) Chee� o'.l le vel tm� replenish as required. Prior to oil check, s1vitch of f p CHECK desired fu el level (use graduated _ . both '.g11111011s cir�mts and turn the propeller by hand in dire tion of engine Right side fuel filler cap tank sump by c di psr1ck) . Dr(li11 the righr fu el rotauon several 11111es to pump oil fr om the engine into the oil tank or /et Q 10 collect fu el quick drain valve 11si11g a up the engine id/� fo r minute. This process f/11ished when <1ir 1s re 11ming the ; operation must be carried with I is (drainage back to �he tank and can be noticed by a 11111r11111r ji·om the open oil s111ft1ce). Check fo r aircraft parked 011 a le vel tank. Pnor to01' lo g ghts 0tl sho ld be t/i(lf the oil /eve/ reaches r J n jl1 u sure fille water or other c Ed. Rev. Ed. /, Rev. 2 I, Approved 2 Section 4 Normal procedures Approved Section 4 - Normal procedures - PRE-FLIGHT Inspections PRE-FLIGHT Inspections AFMS for VFR NIGHT equipped airplanes AFMS forVFR NIGHT equipped airplanes Page 4N - dJ@ 0 lfOH@lfilQIK'AJ@!Ji1!Yl@0 dJ@ 10 0 l?OH@lfilQ ag - I 1 �TEcNAM �@@@ &fl[J'@lf@OO �- &fl� IK'AJ1ID!Ji1!Yl@0 P e 4N Tow bar and chocks REMOVE, stow on board pitot, static ports z and stall warning protective plugs. Avoid blowing inside Pilot tube and inside airspeed indicator system's static ports as this may damage instruments. INTENTIONALLY LEFT BLANK Ed. Rev. 2 Approved 1, Approved Ed. Section 4 - Normal procedures Rev. 2 Section 4 - Normal procedures 1, PRE-FLIGHT Inspections PRE-FLIGHT Inspections _------ AFMS for VFR NIGHT equipped airplanes airplanes AFMS forVFR NIGHT equipped [?�@@® dJ© &!llJ'©� lPO�@UilU li'1J@!Jil(![]@a - &!llJ'@O'®OO lPO�@OuQ �@[Ji)(![]@O - CJ Page 4N 13 [?�@@@ dJ@ CJ Page 4N 12 4.2. ENGINE STARTING 4. CHECKLISTS I. Engine throttle: idle INSPECTION) STARTING AFTER PRE·FLIGHT as needed 4.1. BEFORE ENGINE ( Choke: 2. adjust belts: Fuel selector valve: select the iank with lessfi1e/ Seat position and safety 3. I. occupied ON suat release cause the of airpl 14. Nav. information wilhfuel quan- light & Str9belighi: ON 111/yintlica/ors 4.3. BEFORE TAXIING 1hef11e/ q11a1 ternal inspec- 15. Fuel ity: compare inspection - Ex tityv/s quantually into w11ks (s e.e Pre.-jllght the lion) checked ON seat belts around the seat so as to pre Radio and Avionics: Jn absence of RH seat occupant: fa sten I. flight control operation and with rap. set vent any interference with the aeroplane 2. Altimeter: 3. OFF egress in an emergency. Parking brake: Doors: Closed and locked 16. l Avionic Mas/er switch must be set OFF during the engine 's start-up to pre I vent avionic equipment damage. • L Ed. I, Rev. 2 Ed. 1, Rev. 2 Approved Section 4 - Normal procedures Approved Section 4 - Normal procedures CHECKLISTS CHECKLISTS AFMS N'S7 for Hoffman propeller equipped airplanes with MTOW Increment at 650 kg �- dJ@ &n!i'@d l?O�@llilQ �Uilon&ia wH4-l5 AFMS for VFR NIGHT equipped airplanes �TECNAM Cl Page lP�®®@ dJ@ Cl &11Ii'©d r?aa@llilQ �&JUil(Y]@a � f'EcNi'M Page 4N - 14 4.6 TAKEOFF AND CLIMB 4.4. TAXIING Prima1yflight information (a irspeed, altitude and heading) is pro vided by analogue instruments. Flight information provided by 1. Brakes: checkfo r op eration G3X is onlyfo r situational awqreness. 2. Flight instruments: check altimeter and attitude indicator alignment 4.5. PRIOR TO TAKEOFF On uncontrolled fields, before line· up, check runway wind direc arking brake: ON, brake pedal press tion and speed and check fortraffic on final I. P 2. Engine parameters: check all cautions/warnings OFF , OT within the limits arking brake: OFF 3. ALT OUT caution: check OFF I. P OFF 4. Electric Fuel pump: ON 2. Carburetor heat: 3. set and check approximately 2100 ± 100 propeller rpm 5. Fuel selector valve: select the fu llest tank Full throttle: . check parameters within the limits Fuel pressure: check FP LOW warning OFF 4 Engine instruments: 6. 50 KIA S 7. Throttle speed: advance throttle to I 640 rpm 5. Rotation speed VR: select LEFT, check sp eed drop within 130 propel- Flaps: retract (a bovejlap retraction speed 61 KIA S) a. Ignition key test: 6. ler rpm ; 67 KIA S check propeller sp eed 1640 rp m; 7. Establish Climb rate Vy: b. Select BOTH: 8. OFF c. Select RIGHT: check speed drop within 130 propeller 1p m, Electric fuel pump: Max imum difference of speed between LEFT and RIGHT 50 rpm, d. 9. Fuel pressure: check minimum 2.2 psi e. Select BOTH: check propeller sp eed 1640 rpm . 10. Throttle speed: reduce at or below 2250 rpm 8. Carburettor heat test: a. Pull selectorfully out b. check JOO rpm drop Throttle speed: 4.7 CRUISE c. Push selectorji1lly IN d. check 1640 rp m Set power at or below maximum continuous: 2250 propeller rp m Throttle speed: \. 9. Flaps: set TIO 2. Check engine instruments check neutral • Oil temperature: 50°-130 ° 10. Pitch trim: C. Flight controls: check free • Max. 135 °C I I. Temperature cylinder heads: checkedfastened I2. Seat belts: • Oil pressure: 12 - 102psi. check closed and locked. • minimum 2.2 psi 13. Doors: Fuel pressure: 3. Carburettor heat: as needed. Mo nitor and manually compensate asymmetrical ji1el consump tion by switching fi1el selector valve. Switch on the electric ji1e/ pump prior to swap theji1elfeedingfrom one tank to another. Ed. !, Rev. 2 Ed 1, Rev. 0 Approved Approved Section 4 - Normal procedures Section 4 - Normal procedures CHECKLISTS CHECKLISTS propeller equipped airplanes with MTOW Incre AFMS N"S 7 for H offman ment at 650 kg �®®© d)@ &!J[l'@d AFMS for VFR NIGHT equipped airplanes c (fOn@� [M:]@!Ji)(![]@O Page WH4- t6 TECNAM �®®© d)@ &Hlf©� l«JTEcNAM 0 (fO�@� [M:l@!Ji)(![]@O - 11 � Page 4N BEFORE LANDING 4.8 4.1 1. ENGINE SHUT DOWN I. ON engage Electric fuelpump: 1. Parking brake: 2. Fuel valve: select the fit/lest tank 2. Keep engine running at 1200 propeller rpm for about one minute in order to 3. Landing Light: ON reduce latent heat. OFF 4. On downwind, leg abeam touch down point: 3. Avionic equipment: Flaps: set TIO 4. Ignition key: OFF, keys extracted OFF Approach speed: 6JKIAS 5. Strobe light 5. On finalleg: J Master & Generator switches: OFF 6. Flaps: set LAND 7. Fuel selector valve: OFF Final Approach Speed: 55 KJAS Carburettor heat: OFF (ju // IN) l 6. 55 Before disembarkation verifYpropeller isfidly stopped. 7. Optimal touchdown speed: KJAS Instruct passenger to jitlly open RH door and depart, avoiding contact with J •I 4.9 BALKED LANDING/MISSED APPROACH wheels and sharp wing control s111faces edges. � 1. Throttle: FULL 4.12. POST•FLIGHT CHECKS 2. Speed: keep over 61 K!A S, climb to Vr or Vx as applicable 3. Flaps position: TO [I 1 ON Flight controls: lock by mean of seal belts 4. Electric fuel pump: I. [ ' ' 2. Wheel chocks and wing mooring cables: Set 3. Parking brake: Release 4.10 AFTER LANDING Close and lock 4. Doors: 5. Protection plugs: set over pilot tube, stall warning, static ports Flaps: UP 1. OFF 2. Electric Fuel Pump: 3. Landing light: OFF Ed /, Rev. 0 Approved Approved Ed. I, Rev. 2 Section 4 - Normal procedures Section 4 - Normal procedures CHECKLISTS CHECKLISTS AFMS N'S7 for Hoffman propeller equipped airplanes with MTOW Increment at 650 kg AFMS for VFR NIGHT equipped airplanes �®@@ &f!U'@O'filfil Page WH5-1 dJ@0 lfOH@� ltYAJ@!Jil!YJ@O E«)TECNAM !?�®®® dJ@ &!kr@d Pag - 1s 0 lfOH@M ltYAJ@!Jil!Yl@O e 4N �TEcNAM SECTION 5 • PERFORMANCE INDEX INTRODUCTION ••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••• 3 Section 1 - GENERAL •••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••• 5 Section 2 - LIMITATIONS ...... 7 Section 3 - EMERGENCY PROCEDURES...... 9 Section 4 - NORMAL PROCEDURES ...... 12 Section 5 - PERFORMANCE ...... 15 Section 6 - WEIGHT AND BALANCE ...... 18 Section 7 - AIRFRAME AND SYSTEMS DESCRIPTION ...... 21 INTENTIONALLY LEFT BLANK Section 8 - GROUND HANDLING SERVICE ...... 24 & [. Ed Rev. 0 Ed. Rev. 2 1, Approved 1, Section 5 - Performance Section 4 - Normal procedures INDEX CHECKLISTS AFMS N"S7 for Hoffman propeller equipped airplanes with MTOW Increment at 650 kg AFMS N"S7 for Hoffman propeller equipped airplanes with MTOW Increment at 650 kg Ei(JrE'CilTM �®®� dJ@[] &nLI'©d l?Dnoolfil�IAVilm l!!l�D Page wHs-3 1. INTRODUCTION 3. AIRSPEED INDICATOR SYSTEM CALIBRAT ION This section provides all necessary data for an accurate and comprehensive Graph shows calibrated airspeed as a function of indicated airspeed V planning of flight activity from take-offto landing. YrAs CAS· Data reported in graphs and/or in tables were determined using: 160 "Flight Test Data" under conditions prescribed by EASA CS-VLA regulation ./ aircraftand engine in good condition ./ 150 ./ average piloting techniques ,..... Each graph or table was determined according to !CAO Standard Atmosphere 140 (ISA - s.l.); evaluations of the impact on performancewere carried out by theo retical means for: 130 ./ Airspeed 120 ./ Externaltemperature 'iii' Altitude �HO ./ Weight � ./ Runway type and condition i: 100 ./ K 90 2. USE OF PERFORMANCE CHARTS � [ 50 40 r r 30 20 40 50 60 70 BO 90 100 110 llO 130 140 150 B Calibrated Airspeed [KCAS] FIG, 5-1. CALIBRATED VS INDICATED AIRSPEED Example: [ !iiJ!EJ_ 75. 0 KIAS 74.5 Flap: UP KCAS [ Indicated airspeed assumes 0 as an instrument error [- �-·::../ Ed I, Rev. 0 J Ed I, Rev. 0 Section 5 Performance ' - a1: Section 5 - Performance INTRODUCTION AIRSPEED INDICATOR SYSTEM CALIBRATION ..- •.. \_ .._ N'S7 for Hoffman propeller equipped airplanes with MTOW Increment at 650 kg AFMS N°57 for Hoffman propeller equipped airplanes with MTOW Increment at 650 kg AFMS [p�@@@ JJ@ &JlLJ'@[j'� ge [plJ®@@ JJ@ &JlO'©IJ'� �TECNAM 0 !fD�@Ilu� �@lli)l!!l@O Pa WH5 5 � 0 lfD�@Ilu�!AYAl@lli)O!J @O - TECNAM Page WH5-4 r.r-�l' 4. ICAO STANDARD AT MOSPHERE 5. STALL SPEED n- j 16 Weight: 650 . kg a Throttle Levers: 1 IDLE(2 0%} 14 NCG:o ground Most Forward effect � 12 STALL SPEED WEIGHT J ANGLEBANK fLAPS O' fLAPST/0 FLAPSFuu 10 g [deg] .... [k ] KIAS KCAS KIAS KCAS KIAS KCAS w w 0 L._ 8 49 51 46 48 40 44 D , --,J 15 2 D D 650 30 50 5 46 49 41 447 x 45 53 55 49 5751 44 452 6 (FWD C.G.) w 60 5971 7261 6755 67 49 "':J c J 60 62 .... 4 _J ;:::: -2 . -4 ( -6 '""'- ...... t.'-- ..L:. :::..!...... £...;.,.�..::J. ...l.<��� --l �- �-'--� �� � � �� -40 30 -20 -10 10 E 20 B 30 40 OUTSIDE AIR TEMPERATURE 'C FIG. 5-2. !CAO CHART c Examples: Given Fin d /\! Prt$ 11re nltirud c JWOj1 C: = LJ Don 6. CROSSWIND To account fo r likely in service performance variations apply a fa ctored to distances of I.JO Max imum de monstrated crosswind is 15Kts L T J I =>Example: Weigh t = 650 kg . Corrections Fi11d Flaps: Headwind: - 5 m e (16 ft/k t) !iiJ!£!! [. Speed T/Oat Lift-Off = 50 Tailwind: + 15 for ach kt m KIAS for each kt (49 ft/kt) Wind direction (with respect to aircraji longitudinal axi>)= 30° Headwind = 17.5 Kts Speed Over 50/t Obstacle = 61 Paved Runway: -10% I J Throttle Levers: KIAS Runway slope: + to Ground Roll 20 Crosswind = 0 Kts Wind speed = Kts I Runway: FullForward 7% to Ground Roll for each +1% r Pressure Grass Distance [m) ___ Altitude Temperature ['CJ .._ ,_t- - _ ISA ,_,,�.....,...,,.,,. _ -1- - 1- _,_ -l-�-� · -- - [ft) -25 0 25 50 ·l::-1- -1-•- - l-1- [ - ur 1 t- � �-HH-+-I S.L. Ground Roll 144 182 224 272 207 1-1--11-14-1+-i-l-l-1-11::4�-+-¥-!'1-F�H-+-!-t-+++-l-- r ] SO '-1-. +-H---H-l At ftAGL 304 379 463 557 428 fil:t:'M± t't11rt3<1·•t,,trr'.1 s1't.1- ""0 tJ:tjjlf .. Ground Roll 157 198 245 297 222 •o 1--1+-1-1t-h,11-t-!!l--1.....l��N-A-1µ,,'o'.. u1_vr "f�= 1000 SO � I ' -,,,..�-1-_ 1-1-...-1- i At ftAGL 330 412 503 605 458 1, I I� r J Ground Roll 172 216 267 ' 324 238 2000 SO At ftAGL 359 448 547 658 490 Ground Roll 188 236 292 354 256 3000 SO 7 r ] At ftAGL 391 48 595 717 525 Ground Roll 205 258 319 387 275 4000 SO At ft AGL 425 530 648 780 562 Ground Roll 224 283 349 423 295 5000 [ At 50/tAGL 463 578 706 850 603 Ground Roll 246 309 381 463 318 6000 sos At 50/tAGL 630 770 927 646 Ground Roll 269 339 418 507 342 J 7000 SO ""' ·- At ftAGL 551 687 840 1011 693 ·- I -10 ....� Ground Roll '""'" ,__ ,0<1_ 295 371 458 555 368 Ul �.._ ,� � L � 8000 SO I At ftAGL 917 1104 744 -Ill I\ I)I\!'I.I\. I� :<;; '"P.. "1<: ""r- -"'t- :/..... 1-=R:::-_:: 601 750 x •-r-h •- [, ] Ground Roll 323 502 609 397 1ea ..k. ·�f\1� ii'K- ,J0'111t-;;- , 2o'.IJ �,...�-- 10-�H-J 407 -20 B, h- 9000 c 10 I 20 30 40 50 At 50/tAGL 657 819 1002 1205 800 (Kts) Ground Roll 354 446 551 668 428 CROSSWIND COMPONENT 10000 SO At ftAGL 718 895 1095 1318 859 FIG. 5-2 CROSSWIND CHART J. Ila Ed 1, Rev. 0 Ed 1, Rev. 0 Approved Approved Section 5 - Performance Section 5 - Performance TAKE-OFF PERFORMANCE TAKE-OFF PERFORMANCE AFMS N"S7 for Hoffman propeller equipped airplanes with MTOW Increment at 650 kg propeller equipped airplanes with MTOW Increment at 650 kg AFMS N"S7 for Hoffman JJ@ �@ CJ lfO�@� Page wHs-9 d)@ �@[ii)(!()@O Page WH -8 � !?�®®@ CJ &tl!i'@!i'� [f0�@� S �TECNAM &tl!i'©!i'&lOO [jyA]&JIJilW r'iCNAM Weigh t = 450 kq Corrections Headwind: Flaps: - 5 m (16 ft/kt) Corrections Speed TIOat Lift-Off = 50 KIAS Tailwind: + 15 foreach kt Weigh t =S!iO kq m = • for each (49 ft/kt) Headwind: -5 for kt (16ft/ kt) Speed Over 50/t Obstacle 61 KIA S Paved Runway: 10% to Ground Roll la : m [. for each kt Throttle Levers: Runway slope: + 7% to Ground Roll for F ps r;oLilt- Off = sq, l(IAS Tailwind: + 15 m Speed at FullForward each +1% Paved 10%each to Ground (49 ft/k Rollt) Runway: Sp ed Over .Obstacle = 61 KIAS e Grass 50/t RunYl'ayRuslope: nway:+ - 7% to Ground Roll for Pressure Distance (ml Throttle. Levers! each +1% . For.wor Ed 1, Rev. 0 Ed 1, Rev. 0 Approved Approved Section 5 Performance Section 5 Performance - - TAKE-OFF PERFORMANCE TAKE-OFF PERFORMANCE AFMS N"S7 for Hoffman propeller equipped airplanes with MTOW Increment at 650 k with MTOW Increment at 650 kg propeller equipped airplanes AFMS N"S7 for Hoffman �TEcNAM [?�®@@ dJ@ &n!J'©� [i\'.i;J@[Ji)l!!l@U l!!l " CPU�@[];)� Page WH -11 t«)TECNAM �®®@ d)@ c &n!J'©� CPU�@Uu��®Uil ®U Page WHs-10 : 9. EN-ROUTE RATE OF CLIMB 8. TAKE-Off RAT E Of CLIMB account fo r likely in service pe1formance variations apply a variations apply a account fo r likely in service pe1formance faToctored to rate of climb of 0.90 faToclored to rate of climb of 0.90 Throttle Level'S! . Full Forward Throttle levers: Full Forward Flaps: UP (15") Pressure Climb Rate Climb (ft/min) Flops: Toko Off of Rate of Climb !ft/min] Weight Pressure Climb Altitude Speed V, Temperature ("CJ Weight ISA Speed Vv Temperature rCJ - Altitude ISA [KIAS) 25 0 25 50 0 25 50 (KIAS) -25 (kg) S.l.(ft) 67 981 835 704 586 5 7 5 lkcl 557 725 951 BOS 675 S.L.[ft\ 70 2000 67 870 726 597 481 667 53 638 B40 696 568 4 69 6 759 617 491 377 2000 4000 7 580 349 551 729 588 462 4000 6B 6000 67 648 509 385 273 493 245 464 650 619 480 357 6000 67 8000 67 538 401 279 170 406 142 377 650 509 373 251 L J 65 8000 10000 67 428 294 174 66 319 39 290 399 266 146 10000 64 12000 67 319 187 69 -37 232 42 -64 204 63 290 159 12000 14000 67 210 80 -35 -139 145 -166 117 181 -63 14000 62 53 S.L. 67 1104 948 809 683 863 913 776 652 829 70 1067 S.L. 2000 67 985 832 695 572 770 664 542 737 6B 950 799 2000 4000 67 867 717 582 461 677 552 433 646 67 833 685 4000 6000 67 750 602 470 351 585 441 324 555 600 66 717 571 6000 [ ] 8000 67 632 487 357 240 492 215 463 600 602 458 330 8000 65 10000 66 515 373 245 131 399 220 106 372 64 486 345 10000 12000 66 399 259 134 21 307 110 -2 280 63 371 233 12000 14000 66 283 145 23 -88 214 121 0 -109 189 62 257 14000 S.L. 67 1245 1078 929 794 987 760 948 1201 1038 892 S.L. 69 6 1118 954 675 2000 7 807 887 773 644 851 68 1077 916 2000 4000 67 992 830 686 556 788 654 527 754 67 953 795 4000 6 865 565 438 6000 6 707 688 536 411 657 550 66 830 675 6000 8000 66 740 584 445 319 589 419 296 560 550 65 707 555 8000 10000 66 614 461 325 202 490 301 181 462 64 584 435 10000 12000 66 489 339 205 84 390 184 66 365 ) ' 63 462 315 12000 14000 66 365 218 86 -33 291 196 68 -48 268 1 61 341 14000 --..I ,, ] Ed 1, Rev. 0 Ed I, Rev. 0 Approved Section 5 - Performance Section 5 - Performance EN-ROUTE RATE OF CLIMB TAKE-OFF RATE OF CLIMB ro eller equi ed air AFMS N°57 for Hoffman p p pp planes with MTOW Increment at 650 ed airplanes with MTOW Increment at 650 k Hoffman propeller equipp AFMS N°57 for kg !?�@@@ c!J@ £tl[j@[j'� [?O� [}u� INJ@Oi)Q!l@O �TECNAM c @ Page dJ@ £tl!Y@lY� [?O�@[}u� INJ@Oi)Q!l@O Page WHS- 12 WH:-13 �TECNAM !?�©@@ c - Weight 650 kg_ 1 O. CRUISE PERFORMANCE CORRECTIONS Fuel Specific KTAS to 51nin. Endurance Range Propeller sp eed over 2265 RPMis restricted Consumption Range I• CAUTION For each +15°C of OAT -2% -2.5% +2% +1 % +1 % For each -15°C of OAT +1% +3% -4% -2% -1% For -100kg of weight - +3.3% - +3% +4% = CRUISE PERFORMANCE Weigh t 650 kg_ CORRECTIONS OAT Fuel Specific Specific Propeller Endurance Range Fuel Pressure Endurance Range ISA KTAS Consumption Range KTAS Range RPM Consumption Altitude [hr:mm] [nm] [ft] [deg CJ [It/hr] [nm/It] For each +l5°C of OAT +1% +1% 2250 111 22.5 5:20 595 4.9 -2% -2.5% +2% For each -15°C of OAT -2% -1% 2100 102 20.6 5:50 599 4.9 +1% +3% -4% - - 4000 2000 97 19.6 6:08 594 4.9 For -100kg of weight +3% +4% +3.3% 7 CRUISE PERFORMANCE 1900 91 18.8 6:23 581 4.8 Specific 1800 85 18.1 6:37 564 4.6 Fuel OAT Endurance Range J Propeller Range Consumption 2250 111 22.1 5:26 602 4.9 Pressure ISA KTAS RPM [hr:mm] [nm] Altitude [It/hr] [nm/It] [ft] [deg CJ 2100 102 20.4 5:53 602 4.9 552 4.5 120 26.2 6000 3 2000 96 19.6 6:08 591 4.9 2388 4:35 574 4.7 23.5 5:06 1900 90 18.9 6:21 574 4.7 2250 112 , 5:40 589 4.8 1800 83 18.5 6:30 550 4.5 2100 103 21.2 15 0 6:02 592 4.9 2250 110 21.8 5:30 607 5.0 2000 98 19.9 4.8 2100 101 20.3 5 :55 600 4.9 18.8 6:22 588 1900 92 8000 -1 2000 95 19.6 6:07 586 4.8 6:39 575 4.7 1800 86 18 1900 89 19.1 6:17 564 4.6 5:13 586 4.8 2250 112 23 2250 109 21.4 5:37 615 5.1 5:46 596 4.9 2100 103 20.8 2100 101 20.4 5:53 594 4.9 I' 6:06 595 4.9 10000 -5 2000 97 19.7 2000 11 2000 95 19.7 6:05 578 4.7 6:24 586 4.8 1900 91 18.8 1900 89 19.1 6:18 561 4.6 6:37 568 4.7 1800 85 18.1 Ed /, Rev. 0 1, Rev. 0 Ed Section 5 - Performance Section 5 - Performance CRUISE PERFORMANCE CRUISE PERFORMANCE AFMS N·s7 for Hoffman propeller equipped airplanes with MTOW Increment at 650 kg S7 Hoffman AFMS N° for propeller equipped airplanes with MTOW Increment at 650 kg &110'@� wHs-14 d)@ c lfOH@� �@Uilllil@O Page dJ@ &/l[J'@IJ'� 0 f:PO�@!fil� IA'-:iJ@Uil@ E«Jr'ECNAM [p�®@@ E«JTECNAM �®@@ @fi Page WHS-15 11. LANDING PERFORMANCE 12. BALKED LANDING PERFORMANCE To account fo r likely in service petformance variations apply a r r] fa ctored to distances of i'.67 account fo r likely in service pe1Jor111ance variations apply a faToctored lo rate of climb and lo a11gle of climb of 0.90 = Weight Corrections r r] 650 kg Throttle Levers: Full Forward Flaps: Headwind: (13 ft/kt) Flaps: -4m foreach kt Short FinalLAND Approach Speed = Tailwind: (43 ft/k t) LAND 4 + Speed: 5 KIAS 13m for each kt Throttle Levers: Ground Roll 54 KIAS Rl.mway:-10"to Pressure Runway: Idle Pa ved (3round· Roll Angle of Climb [deg] Grass Runwav s.lope: for +1% Weight Altitude -3% to each Temperature (°CJ Pressure Distance (m) [kg] (ft] ISA Altitude Temperature ['C) -2 S.L. 5 0 25 so ISA 6.3 (ft] -25 0 25 ] 2000 8.4 7.0 5.8 4.7 so S.5 Ground Roll 173 S.L. 164 4000 7.4 6.0 4.8 3.7 149 179 194 4.6 382 At 50ftAGL 358 373 388 403 6000 6.3 5.0 3.8 2.7 650 .8 Ground Roll 178 1.7 1000 154 8000 5.3 3.9 2.8 170 186 201 3.03 387 At 50/tAGL 363 379 395 410 10000 4.2 2.9 1.8 0.7 2. Ground Roll 183 3.2 2000 160 176 192 209 12000 1.9 0.8 -0.3 1 392 At 50/tAGL 369 385 401 418 14000 2.1 0.9 -0.2 -1.2 1.3 Ground Roll 189 1.1 3000 166 183 200 216 ·0.1 -1.2 -2.2 o.s 398 At 50/tAGL 375 392 409 425 Ground Roll 195 4000 172 190 207 225 404 13. At50ftAGL 381 399 416 434 NOISE DATA Ground Roll 201 5000 179 197 215 233 Noise level, determined in accordance lh 410 with !CAO/Annex 16 6 Ed., July 2011, At50/tAGL 388 406 424 442 Vol. 1°, Chapter 10, is 68.06dB(A). Ground Roll 207 6000 186 205 223 242 416 At 50/tAGL 395 414 432 451 Ground Roll 213 7000 193 212 232 251 422 At50ftAGL 402 421 441 460 Ground Roll 220 8000 200 221 241 261 At 50/tAGL 410 430 450 470 429 Ground Roll 227 9000 208 229 250 271 436 At 50ftAGL 417 438 459 480 ] Ground Roll 234 10000 217 238 260 282 443 At 50ftAGL 426 447 469 491 Jl I Ed I, Rev. 0 Approved Section 5 - Performance Ed I, Rev. 0 Section 5 - Performance LANDING PERFORMANCE ] BALKED LANDING PERFORMANCE SECTION6-WEIGHT AND BALANCE INDEX 1. INTRODUCTION ...... 3 2. WEIGHING PROCEDURES ...... 3 INTENTIONALLY LEFT BLANK �:�: ��=��=���:::::::::::::::::::::::::::::::::::::::::::::::::::::::::::::::::::=:::::::::::::::::::::::::::::: 2.4. Determination of C.G. location ...... 4! 2.5. Weighing record ...... : 5 2.6. Weighing record (II) ...... 6 3. WEIGHTS AND C.G ...... 7 BAGGAGE LOADING ...... 4. g 5. EQUIPMENT LIST ...... 10 0 l, Rev. O Ed. I, Rev. Ed. Section 6 - Weight and balance Section • Performances 5 INDEX .J t«! ricNAM 1. INTRODUCTION This section describes the procedure foresta blishing the basic empty weight and the moment of the aircraft. Loading procedure information is also provided. Aircraft must be op erated in accordance with the limits con cerning the maximum takeoffweight and excursion as re ported in Flight Ma nual Section 2. CG Pilot is responsible forchecking the weight and CG excursion are compliant with the related limits. CG excursion and weight limits are reportedin Section 2 - Lim itations. 2. WEIGHING PROCEDURES !NTENTIONALL LEFT BLANK Y 2.1. PREPARATION • Carryout weighing procedure inside closed hangar • Remove from cabin any objects unintentionally left • Insure Flight Manual and mandatory documents are on board • Align nose wheel • Drain fuel via the specific drain valve • Oil, hydraulic fluidand coolant to operating levels • Move sliding seats to most forwardposition • Raise flapsto fullyretracted position (0°) • Place control surfaces in neutral position • Place scales under each wheel 2.2. LEVELLING Level the aircraft (the reference for longitudinal levelling is made putting a spirit-level on the cabin flooras shown in the Aircraft Maintenance Manual). If needed, adjust longitudinal attitude deflatingnose tire 2.3. WEIGHING Record weight shown on each scale Repeat weighing procedure three times Calculate empty weight Ed. I, Rev. 0 Ed. Rev. 0 I, Section 6 - Weight and balance Section 6 - Weight and balance INTRODUCTION .J n propeller equipped airplanes with MTOW Increment AFMS N"S7 for Hoffma at 650 kg l?�®®@ �@ &Ila'©� r?anoolfil�IK'il&iUil oo&iU Page �rE'CNA'M c wH6-5 2.5. WEIGHING RECORD DETERMINATION OF C.G. LOCATION 2.4. Mode!P2008 JCS/N: \O '{=o We ighing no. L Date: z¥z,./a.., 7- Datum: mark Propeller Flange - Drop a plumb bob tangent to the wing leading edge and trace a reference on the floor(see Figure on Para. 2.5 or 2.6) Repeat the operation forother wing e two marks .56&----1--1}.- Streich a 1aught line between t between hthe Measure the distance reference line and both main and nose wheel axis(A and B distances respectively) C.G. and the Using recorded data it is possible to determine the aircraft location aircraft moment (see followingtable) ______fuk_ttnc� Kg or fs/>ls" Meters qp{l!'f/ 84 Nose wheel weight w, = .--:J Plumb bob distance LH wheel AL= 0, 61,,..., LH wheel weight WL=JM. r.. Plumb bob distance wheel A. = {it.ri RH 0 wheel weight w. Average distance (AL+ A )/2 A RH =){/{..- R = o b6o .)3.f , Q B W2 =WL+WR= Plumb bob distance fromnose wheel - A, 15 0 Empty weight We W1+ W2 = 4 Z...(. [kg � [ = O ] ' W,·A-W,·B D D We D% 111 ·100 = Z. I I 8 1.373 (or4.5fi) Empty weight moment M= [(D+l.566) -We] = [m · kg] o� t85,5 Maximum takeoffweight WT = 650 kg (1433 lbs) Empty weight We J.,U, [kg] o� = o Max. useful load WT - We Wu = 2.l9, [kg] or 0 .!;ies1 Ed Rev. 0 Ed. Rev. 0 1, I, Section 6 Weight and balance Section 6 - Weight and balance - AFMS N"S7 for Hoffman propeller equipped airplanes with MTOW Increment at 650 kg dJ@ &IJ[J'@� [?UH@GiJU �@(]j)[!!]@U Page WH6-6 �TEcNAM [?�@@@ " 2.6. WEIGHING RECORD (II) 3. Mo de!P2008 JCSIN:___ We igh ing no. __ Date;___ _ WEIGHTS AND C.G. In order to compute the weight and balance of this aircraft, the following loading Datum: Propeller Flange charts are provided. To compute weight and balance use the formula: Weight * �rm = Moment. Pilot&Passenger Fuel Baggage Mo- Mo- Mo- Weight(k Li- Weight Weight(k ment ment ment g) ter (kg) g) (k11:m) (k11:m) (kgm) 10 18 10 7.2 15.91 5 12.05 20 36 20 14.4 31.82 10 24. 10 30 54 30 21.6 47.74 15 36.15 40 72 40 28.8 63.65 20 48.20 50 90 50 36 79.56 60 108 60 43.2 95.47 70 126 70 50.4 111.38 80 144 80 57.6 127.30 90 162 90 Kg or lbs Me ters or fe el 64.8 143.21 100 180 100 72 159.12 Nose wheel weight Plumb bob distance LH wheel A L W, = = 110 198 110 79.2 174.95 LH wheel weight Plumb bob distance wheel W RH A. = 120 216 120 190.86 L= = 86.4 wheel weight R Average distance (AL+ AR)/2 RH W = A 130 234 124 89.3 197.26 Plumb bob distance from nose wheel B = 140 252 W2 =WL+WR = 150 270 Empty weight + [kg] or [lbs] I We = W1 W2 = 160 288 170 306 [m] or [ft] =W,-A-W.·B D 180 324 D 0% = m -100= We 1.373 (or4.5ft) 190 342 Empty weight moment: M = [(D+1.566) 'We] = [m · kg] or [ft' lbs] 200 360 210 378 Maximum takeoffweight 650 kg (1433 lbs) 220 396 Signature WT = Empty weight We = [kg] or [lbs] 230 414 Max. useful load - We Wu = [kg] or [lbs] Wr Ed Rev. 0 Ed. l, Rev. 0 Section 6 - Weight and balance 1, Section 6 - Weight and balance Increment at 650 kg equipped airplanes with MTOW for Hoffman propeller &1Ui)00&10 Page wH6-9 t.a•S7 &IJU'©IY@ffil l?Oa@M� AfNIS 0 EcNAM �©@@dJ© �r- Max Max FWD C.G.Range AFT 1.978 Meter Inches Meters 1.841 Pounds Kilograms Max Weight Pilot and PAX 1.800 70.90 FUEL 650.00 2.209 86.97 1433.00 BAGGAGE 2.417 95.16 example ent Ann Ann Moment Mom Weight Weight m\ llbs x lnl Ubs x lnl To compute weight and balance: (lbsl !Inches\ I 60531.97 691.88 lkal 1.89 Empty Weight 813.5 366.075 74.41 13051.16 149.18 87.01 2.21 Get moments fromloading chart Fuel 150 67.5 1. 21270.00 243.00 1.80 the empty w>' t weight Passenger 300 135 70.90 2. Obtain d the most recent and balance Pilot & 0.00 0.00 the weights a�;lgt�ea�o•I :��:��fr�� 94.88 2.41 3. r e ' occupants and baggage fromthe previous Baggage 0 0 Insert 94853.12 1084.06 chart 75.07 1.84 Total 1263.5 568.575 4· S�� the weight and the moment columns get the 5. the total moment by the total weight to arm (J � D1v1de P the weight of 630 kg ( 1388 Check . is under max gross 6. that the total weight does not excee d maximum gross weight or o Kg (1388 In this example, the gross weight listed above. jl within C.G. range lb) lbs) and the Armor C.G. is the 7, Check that the armfalls within the C.G. range LOADING CoG Position Computation Chart 4. BAGGAGE must A"fi k/Y/ the pilots' seats, The in the dedicated compartment, behind Moment baggage loading limitations reported Weight (kg) Arm (m)' be with C.G. excursion and weight (kg*m) carried out in accordance in Section 2. ted on compartment floor. Baggage must be uniformly distribu EmptyWeight Q/?' allowing forsecuring �,/f ;2'/ r t- is tie-down net and snap fasteners ' Pilot provided with a red Fuel 2.209 floor. - the loads on the compartment Pilot&Passenger 1.800 y stretched 1/le · make sure tbat you correctl - loading the baggage. t- Baggage 2.417 to the fo ur vertices of the compar I net which must be secured . ment. MOMENT Total WEIGHT Total "D"=MOMENTDistance /WEIGHT ,, """ *ADD to the distance "D" the value 1.566m (62in) I "' Ed Rev. 0 1, Ed. l, Rev. O and balance Section 6 - Weight Section 6 - Weight and balance AFMS N" man propeller equipped airplanes � with MTOW Increment at 650 kg N"S7 for Hoffman propeller equipped airplanes with MTOW Increment at 650 kg �@@ffi MS JJ@ CJ &Jj[j'@� Page f J)@ &ll!i'©� Page WH6-11 lfiln@!Ju�IAYAJ@!Ji)(YJ @Il WH6-IO " �®®® CJ lfD�@llu� �@!Ji)(ll]@Il �TECNAM E!(JrlCN.iM 5. EQUIPMENT LIST P2008 .JCEQU IPMENT LIST DATE: 2/2ot;z- The following is a �OmJ>re � '2� l'.ensive list of all TE NAM supplied WEiGHT DATUM Q.TY the P2008 equipment for RIF. DESCRIPTION &PIN INST JC. The consists of the following [mm] N list ... £kal £ °l A Engine and accessories groups: ENGINE & ACCESSORIES Landing gear Al * 6. 0 -144 I B Hojfmann Propellers -pln HOl7GHM A 174 177C Heal exchanKer -pi n 28-10-8000-000 * 2.00 754 1 C Electrical system A2 AJ Oil Reservoir {full) -pin 956508 * 4.00 760 1 D Instruments A4 Oil radiator -vl n 886029 * 0.50 25 1 E Avio,,ics A5 Liouid coolant radiator. -pi n 995.697 * 1.50 129 1 the following infonnation describes each listing: A6 Ai1:filter K&N- vln 33-2544 * 0.40 315 1 Part-number A7 Electric Fuel vum in 21-11-342-000 * 1.20 764 1 to uniquely identify the item type. pp ):;> Item description AS Thermostatic water valve 26-9-9100-000 * 0.35 316 1 ):;> Weight in kilograms A9 Thermostatic oil valve 26-9-9000-000 * 0.35 316 I ):;> Distance in meters fromDatum ):;> Item marked with a11 asterisk {'") are a installation. � p n of basic marked with X 111 the Inst. co/1111111 are those actually LANDING GEAR AND ACCESSORIES �q111p111e111 Bl Ma in Ke ar wheel rims. - Cleveland 40-78B * 2. 05 2229 2 mstal/ed 011 board relative to aircrajl SfN. B2 Ma in Kear tires.-Air Trac 5. 00-5 * 2.58 2229 2 BJ Disk brakes - Cleveland 164-17 * 0.80 2229 2 B4 Nose J?ear wheel rim - Cleveland 0101120 * 1.30 418 1 B5 Nose J?eartire -Air Trac 5. 00-5 * 1.20 418 I B6 Nose J?ear fa irinf! vln 210-4-3001-401A l-401P * 1.50 418 1 B7 Ma in f!ear fa irinf! vln 27-8-410-11-2 * 1.50 2229 2 BS Nose f!ear shock vln28-8-500-000 * 1.45 770 I ELECTRICAL SYSTEM Cl Batterv FIA MM 6H4P 12 V 18Ah 4.70 1900 I C2 Batterv GILL-Teledyn e G-25 12V 18Ah N 9.53 1900 1 CJ Buffer Batterv Sonnenschein A51212 S ,.c* 1.0 1900 2 CJ Battervre/av - v n 111-226-5 * 0.30 1900 1 C4 Flaps actuator controll -22-5-176-1 * 2.20 2206 1 C5 Trim actuator control BRISTOL SG B6-J JC * 0.40 5818 1 ] C6 Overvoltage sensor Electrode/ta OS75-14 0.30 772 1 Overvoltage sensor LAMAR B-00289-2 tJ 0.30 772 1 C7 Aveo NA VIPOSIStrobe plnA VE-WP ST RIG-54G }(* 0.20 2130 2 Landing Led light pin PLED1L * 0.40 130 1 cs Ed 1, Rev. I Ed 1, Rev. 1 Section - Weight and balance 6 Section 6 - Weight and balance AFMS for VFR NIGHT equipped airplanes Page - &!JIJ'@IJ'&J@ �fin@[}j)Q N7 I 0 ll!J@!I dJ@ �@rri) @TECNAM- �®@@ PTION AND SYSTEMS DESCRI SECTION 7 - AIRFRAME INDEX INSTRUMENTS D1 Altimeter * 1.00 1084 1 11/11 LUN lMIKR128.12OTB6ECHNA TSO C/Ob 02 Airspeed indicator LUN * 1.00 1084 1 •••••••••••• 2 ••••••••••••••••••••••••••••••••••••••••• 1116F2B2 - TSO C2bMIKROTECHINA •••••••••••••••••••••••••••• Introduction .. ... 2 1...... D3 • !AP TSO C7c * ...... Co11111ass Aima11iC2400 0.29 1000 1 ...... Airframe ...... 2...... 04 Clock DA R mod. M 800 * 0. 15 1084 1 ...... 2 Wlng ...... OS IndicatorVI' ON * 0.56 1 Slio Sl-20 1084 ...... 3 ...... 2.1 fuselage ...... 06 ...... Aulwde cato1· - RC Allen ln slr. 1.30 1084 1 ...... 34 2.2. Empennages ...... 07 _ l'.1�i RCA26EK-12 x 1 ...... Tnm Pos111011 Ind. UMA o/11N09l * 0.20 1084 ...... 2.3. Landing gear 5 08 Fuel Ind. Road ISOU2DROOO * 11f1111iry GmbH XJD4000800 0.45 1090 2 . ••••.••••••••••••••••••••••••••••••••••••.•••••••••••••••••••••••••••••••••.• s. ••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••.••. OIS - . . G3X GMU * 0.23 1 6. Doors . . . . 10 MtlJ!IWIOl/11]/{!/" 44 4697 ...... 016 - 1 ...... GTP 59 * ant ...... 10 0.10 2060 Powerpl ...... 7...... Dl7 OAT nrobe ...... CT /emoerature indicator (S1Jrlini) SOR 59 0.30 1084 1 ENGINE ...... 10 ...... X! ...... 7.1. PROPELLER ...... 11 ...... A 7.2...... Fuel System ...... 12 8...... VTONICS AND OTHER ...... El System ...... Na v/Comm - Garmin Sl30 Pack and connectors N 1.50 1084 1 9. Electrical ...... 12 1 System ...... ELT Artex ME 406 N 1.10 1900 Stall Warning ...... E3'E2 1 ...... 13 Trm1soo11der-Gtmuin OTX328 * 1.00 1084 9.1. Avionics ...... E4 Power Supply ...... 14 Audio -Garmin * 9.2. External . . 15 oa11el GMA 340 0.50 1084 1 ...... Systems ...... ES Tn111soo11der Antenna Garmin 010-l0l60_00 * 0.17 985 1 9.3. Pressure 10. Pitot-Static . 16 ...... E6 GPS * ...... A111e1111a.Gar111i11GA-35 0.27 807 I 11. Brakes ...... E7 Comm Anlenna Comant Industries CI-121 * 0.34 4253 1 ES ELT Antenna Kit Model ME 406 N 0.21 1900 I E9 First Aid Kit * 0.30 1800 1 ElO Fire Extirt�ui.�/lerH3 Rs fla/011 * 0.60 1800 1 RTA600 El l Garmin GNC 255A COMINA V * 1.80 1084 1 El2 Ma rker beacon Amemw Co11111111 Industries CI /OZ * 0.30 2917 1 El3 Nav Antenna Com11111 Industrias Cl-158C * 0.30 5782 1 El4 Altitude Encoder ACK tedmologics ACK A30 * 0.35 975 I EIS ELT Kannad 406 Cv;11paci * 1900 I El6 AF I.JO ELT A11te1111a ANT200 * 0.21 0.11 I Ed. Rev 0 J, description Ed. I.Rev. 4 and Systems Section 7 - Airframe Section 6 - Weight and balance INDEX AFMS for VFR NIGHT equipped airplanes AFMS forVFR NIGHT equipped airplanes dJ@ &lj[j'@[j'f!JOO �@[Ji)mJ@U Page N7 c &ll[j'@IT'@OO [?�@®@ [p�@®@dJ@ �O�@[fil� �@[Ji)mJ@O Page N7 - 2 c �UH@lfilQ TECNAM �'fEcNAM - 3 - 1. INTRODUCTION FUSELAGE This Section provides description and operation of the aircraft and its systems. The P2008 JC fuselage is mainly made by carbon fibres composite materials. The fuselage is made by two main shells that are later assembled bonding the two 2. AIRFRAME main bodies and the floor (composite) and adding aluminium stiffeners that allow the connection of the main landing geaf, seats, wing and instrument panel. In this context the fuselageand vertical fin are a unique body. P2008 JC's airframe can be divided in the followingmain groups, as highlighted be low on: 2.3. EMPENNAGES The horizontal tail is an all-moving type; the stabilizer and elevator form a single 1) Wings uniform plane called stabilator that rotates to the desired pitch setting. 2) Fuselage The stabilator structure is made-up by an aluminium spar (1) and ribs (2). 3) Empennage Aluminium skin panels are riveted to the above elements 4) landing gear (3). Fig. 7-2.STABlLATOR STRUCTURE A trim tab ( 4) provides stick force adjustment and longitudinal compensation. The rudder structure is made-up by a single aluminium spar and ribs. Aluminium skin panels are riveted to the above elements. At the lower hinge a bellcrank is connected for the movement transmission. Fig. 7-l .P2008JC AIRFRAME 2.1. WING Each wing is connected to the fuselage by means of two bolt attachments and a sing.le strm brnce per side. The wings arc made up of a central light allo tor·ion n light alloy leading edge is attached to the spar wherc;is the Oapy (slot ted)box; and front the aileron ( .. fr isc") are a11ached to a rear spar through two hinge each. The torsion box consi. ts a and rear spar that represent its front and rear vertical walls; a seric ofof ribs front and wrnp uro uad panels comp te the strncturc. Front end rear spars are integrated with ' ing-f- uselngc allachmcntle filling . ailerons nap are made by on aluminium spar allached to n Jbm1cd sheet Th� metal leadingand edge and ribs: an aluminium skin u.rrounds the aileron struc ture. metal Ed. Rev 0 Ed. I, Rev 0 I, iption Section 7 Airframe and Systems description Section 7 Airframe and Systems descr - - INTRODUCTION AIRFRAME AFMS for VFR NIGHT equipped airplanes AFMS for VFR NIGHT equipped airplanes TECNAM l?�®®® dJ© &llU'©U'®lm lfUD@llilUliYAl@Uil Oll@U N7 4 lP�®®® dJ©CJ &llU'©U'®lm lfUo@llilU liYAl@UilOll@U N7 CJ Page - Page - t«J'fEcNAM s 2.4. LANDING GEAR 3. FLIGHT CONTROLS 7-3) The main landing gear (see Figure consists of two special steel leaf-springs posi Aircraftflight controls are operated through conventional stick and rudder pedals. tioned crossways to the fuselage. Longitudinal control acts through a system of push-rods and is equipped with a trim tab. a cable control circuit is confined within the cabin and it is connected to a pair of push-pull rod systems positioned in each main wing which control ailer ons differentially. Aileron trimming is carried out on ground through a small tab positioned on leftaileron. L l ' �Jl �JJ�- Flaps are extended via an electric servo actuator controlled by a switch on the in strument panel. Flaps act in continuous mode; the indicator displays three mark ings related to 0°, takeoff(TIO) and landing (FULL) positions. A breaker posi tioned on the right side of the instrument panel protects the electric circuit. Longitudinal trim is performedby the trim tab located on the stabilator through an electric actuator controlled by the pilot or co-pilot by a switch located on the con trol stick, another switch on the instrument panel, gives full authority to pilot or co-pilot control switch analogue trim indicator provides informationabout the . An 7-3.MAIN LANDING GEAR STRUCTURE Fig. surface position. In case of a trim control runaway a trim disconnect switch is available on the instrument panel The steel leaf-springs are attached to the fuselage structure via two couples of ma chined aluminium beams. Wheels are cantilevered on gear struts and fe ature hydraulically actuated disc brakes controlled by toe. A Pivoting nose gear is attached to the firewall reinforcement plate. The Hydraulic shock absorber is fitted on the upper machined component and directly on the nose landing gear structure. In the followingfigure is shown: 2)1) Hydraulic shock absorber Firewall 3) Nose wheel J Fig. 7-4.NOSE LANDINGGEAR STRUCTURE Ed. 1, Rev 0 Ed. I, Rev 0 Section 7 Airframe and Systems description - Section 7 - Airframe and Systems description AIRFRAME FLIGHT CONTROLS AFMS forVFR NIGHT equipped airplanes AFMS for VFR NIGHT equipped airplanes &ilU'©U'lfilOO &l!U'@[J'@OO f?O� Q @[ii)U!J@O E«JrE'CNiM l?�®®® 0 lfO�@DuU[iYA]@ [ii)U!J@O 0 @[Ju [iYAJ Page N7 - 7 �@ Page N7 - 6 � TEcNAM �@®@ �@ �INSTRUMENT PANEL The instrument panel is divided in four areas: • The left area holds primary (analogue) and pilot's situational awareness (G3X LH display) flight instruments, a chronometer, a pitch trim indicator and a holds Day/night switch (selecting between two brightness levels forwarning lights in the annunciator panel); • The right area holds thus a voltmeter, the breaker panel and primary analogue engine instruments: Oil Temperature indicator > RPM indicator > CHT indicator > • The central area holds the stabilator trim cut out switch and LH/RH selector INSTRUMENT PANEL switch, the dimming devices (for G3X, forflexible support mounted panel lights Fig. 7-5. and for instruments), Nav/Com instrument (Garmin GNC 255A) , the GTX 328 transponder and the annunciator panel,, Electric fuel pump ON (GREEN) 4.1. INTERNAL LIGHTS SYSTEM > Low Oil Pressure (RED) > Low Fuel Pressure (RED) An internal lights system is provided; it's based on the followingelements ; > Alternator Fail (AMBER) > • dimmable panel lights (with flexible and adj ustable supports) located in both sides of the > Pitot heat operation lights (GREEN/AMBER) High Oil Pressure warning light (RED) 2dashboard and LED lights above the annunciator panel (Panel DIMdevice); > • emergency li2ghts located in side area of the cabin ceiling and LED light above the annunciator • The lower-LH portion of the instrument panel holds: panel2 (all controlled by red Emergency Switch); l Ignition key; • l adj ustable map-light located in the center area of the cabin ceiling. > Master and Generator switches; > Emergency fuel pump; > Avionic Master switch; > Pitot heat switch; l"AMll',dir(t,,11j > Emergency light switch; > Carburetor heat knob; > • The lower-Central portion of the instrument panel holds: Throttle; > Two analogue fuel quantity indicators; > Fuel selector valve; > • The lower-RH portion of the instrument panel holds: , Flap indicator and toggle switch; Cabin heating knob; 4.2. CARBURETTOR HEAT > NA V, land and strobe switches. > Carburettor heat control knob is located lower-LH portion of the instrument panel; when the knob is pulled fully outward fromthe instrument panel, carburettors re ceive maximum hot air. During normal operation, the knob is set in OFF position. Ed I, Rev 0 Ed I, Rev 0 Section 7 - Airframe and Systems description Section 7 - Airframe and Systems description INSTRUMENT PANEL INSTRUMENT PANEL for Hoffman propeller equipped airplanes with MTOW Increment at 650 kg AFMS N°S7 AFMS for VFR NIGHT equipped airplanes &ll!l'@d �©©@c!J© &il!l'©d O 9 �TECNAM �®®@ c!J©c !fOnoo[fil{k [K9;1&Jlii)(]JJ@0 Page 0 !fDnoo�IAYAJ&J lii)OO&J Page N7 - wi;,'I [J()rE'CNA'M 7. POWERPLANT 5. SEATS AND SAFETY HARNESS 7.1. ENGINE Aircraft fe atures fourfitting point forsafety belts equipped with waist and shoul der harnesses adjustable via sliding metal buckle. Manufacturer: Bombardier-Ro/ax GmbH Seats are built with light alloy tube stcucture and synthetic material cushioning. A Model: ROTAX 912 S2 lever located on the right lower side of each seat allows for seat adjustment ac Type: 4 stroke, horizontally-opposed 4 cylinder, mixed air and cording to pilot size .. water cooled, twin electronic ign ition, fo rced lubrication. Maximum rating: 98. 6hp (73. 5kW) @ 5800 rpm/min (2 388 rpm/min. prop) . Gear reduction - 2.4286: I 6. DOORS ra/Jo Max oil consumption: Max: 0.1 litres/hour Two doors are provided for P2008 JC, on Pilot and co-pilot side. A sketch of the door is shown below (RH and LH doors are specular): 7.2. PROPELLER Manufacturer: Hoffinan Propellers Model: H01 7GHMA 174 177C N° of blades: 2 Upper safety block Diameter: 1740 mm Type: fixedpitch ' ' Lower Hln�e Latch system Fig. 7-6.DOOR The door is equipped with a gas spring fixed to the fuselage that facilitates door opening. Ed 1, Rev. O Section 7 - Airframe and system descriptions Ed 1, Rev 0 POWERPLANT Section 7 - Airframe and Systems description SEATS AND SAFETY HARNESS AFMS for VFR NIGHT equipped airplanes AFMS forVFR NIGHT equipped airplanes dJ@ &llU'©U'IIDOO N7 - 2 lP�®®® dJ@c &llU'©U'IIDOO f'ECNIM l?�®®® c lfaooo!filtl �@llil()!]@a Page lfaooo!filtl �@llil()!]@a Page N7 - 3 � r'Ec'NAM 1. INTRODUCTION 2.2. FUSELAGE P2008 This Section provides description and operation of the aircraftand its systems. The JC fuselage is mainly made by carbon fibres composite materials. The fuselage is made by two main shells that are later assembled bonding the two 2. AI RFRAME main bodies and the floor (composite) and adding aluminium stiffeners that allow the connection of the main landing gear, seats, wing and instrument panel. In this context the fuselageand verticalfin are a unique body. P2008 JC's airframe can be divided in the following main groups, as highlighted be low on: 2.3. EMPENNAGES 1) Wings The horizontal tail is an all-moving type; the stabilizer and elevator form a single 2) Fuselage uniformplane called stabilator that rotates to the desired pitch setting. (2). 3) Empennage The stabilator structure is made-up by an aluminium spar (I) and ribs 4) Landing gear Aluminium skin panels are riveted to the above elements (3). Fig. 7-2 .STABILATOR STRUCTURE A trim tab (4) provides stick force adjustment and longitudinal compensation. The rudder structure is made-up by a single aluminium spar and ribs. Aluminium skin panels are riveted to the above elements. At the lower hinge a bellcrank is Fig. 7- 1.P2008JC AIRFRAME connected for the movement transmission. 2.1. WING Each wing is connected to the fuselage by means of two bolt attachments and a single strut brace per side. The wings are made up of a central light alloy torsion box; a light alloy leading edge is attached to the front spar whereas the flap (slot ted) and the aileron ("frise") are attached to a rear spar through two hinges each. The torsion box consists of a front and rear spar that represent its front and rear vertical walls; a series of ribs and wrap-around panels complete the structure. Front and rear spars are integrated with wing-fuselage attachment fittings. The ailerons and flaps are made by an aluminium spar attached to a formedsheet metal leading edge and metal ribs; an aluminium skin surrounds the aileron struc ture. Ed. 1, Rev 0 Ed. 1, Rev 0 Section 7 - Airframe and Systems description Section 7 - Airframe and Systems description INTRODUCTION AIRFRAME AFMS for VFR NIGHT equipped airplanes AFMS forVFR NIGHT equipped airplanes �@@®c!J@ &ll!Y@lralOO Page N7 - �- �!Y©lralOO Page N7 - CJ [¥0�@��IIDIJilU!J@D c!J© CJ 1¥0��� IID!JUU!llIDD TEcNAM 4 �TEcNAM s 2.4. LANDING GEAR 3. FLIGHT CONTROLS The main landing gear (see Figure 7-3) consists of two special steel leaf-springs posi Aircraft flight controls are operated through conventional stick and rudder pedals. tioned crossways to the fuselage. Longitudinal control acts through a system of push-rods and is equipped with a trim tab. a cable control circuit is confinedwithin the cabin and it is connected to a pair of push-pull rod systems positi�ned in each main wing which control ailer ons differentially. Aileron trimming is carried out on ground through a small tab positioned on leftaileron. Flaps are extended via an electric servo actuator controlled by a switch on the in strument panel. Flaps act in continuous mode; the indicator displays three mark ings related to 0°, takeoff (T/O) and landing (FULL) positions. A breaker posi tioned on the right side of the instrument panel protects the electric circuit. Longitudinal trim is performed by the trim tab located on the stabilator through an electric actuator controlled by the pilot or co-pilot by a switch located on the con trol stick, another switch on the instrument panel, gives full authority to pilot or j co-pilot control switch. An analogue trim indicator provides information about the Fig. 7-3.MAIN LANDING GEAR STRUCTURE surface position. In case of a trim control runaway a trim disconnect switch is available on the instrument panel The steel leaf-springs are attached to the fuselage structure via two couples of ma chined aluminium beams. Wheels are cantilevered on gear struts and feature hydraulically actuated disc brakes controlled by toe. P o i g gear is attached to the firewall reinforcement plate. The Hydraulic shockA iv absorbert n nose littcd on the upper machined and directly on the nose gear truisc turc. component Inlanding the following figure is shown: I) Hydraulic shock absorber 2) Firewall 3) Nose wheel Fig. 7-4.NOSE LANDING GEAR STRUCTURE Ed. I, Rev 0 Ed. I, Rev 0 - Section 7 Airframe and Systems description Section 7 - Airframe and Systems description AIRFRAME FLIGHT CONTROLS AFMS forVFR NIGHT equipped airplanes AFMS forVFR NIGHT equipped airplanes cl]@ &nU'@d ®UilOO®O Page N7 - 1 TEcNAM [p�@XQ)@dJ@ &nU'©rr@OO 1¥00@� �@[ii)()!]@O Page N7 - �@XQ)® c 1¥0�@� � c 6 �rEciiA'M 4. INSTRUMENT PANEL The instrument panel is divided in four areas: • The left area holds primary (analog e) and pilot's situational awareness (G3X LH display) flight instruments, a chronometer,u a pitch trim indicator and a holds Day/night switch (selecting between two brightness levels forwarning lights in the annunciator panel); • The right area holds thus a voltmeter, the breaker panel and primary analogue engine instruments: Oi Temperature indicator )> RPMl indicator > CHT indicator l> • The central area holds the stabilator trim cut out switch and LH/RH selector switch, the dimming (for for flexible support mounted panel lights Fig. 7-5. INSTRUMENT PANEL and fo r instruments), devNav/Coices m instrG3X.ument (Garmin GNC 255A) , the GTX 328 lrnnsponder the panel,. and annunciator Electric fuel pump ON (GREEN) 4. 1. INTERNAL LIGHTS SYSTEM > Low Oil Pressure (RED) > Low Fuel Pressure (RED) An internal lights system is provided; it's based on the followingelements: > AlternatorFail (AMBER) > Pitot heat operation lights (GREEN/AMBER) • dimmable panel lights (with flexible and adj ustable supports) located in both sides of the > High Oil Pressure warning light (RED) 2dashboard and LED lights above the annunciator panel (Panel DIM device); > • emergency lig2hts located in side area of the cabin ceiling and LED light above the annunciator • The lower-LH portion of the instrument panel holds: 2panel (all controlled by red Emergency Switch); I Ignition key; • adjustable map-light located in the center area of the cabin ceiling. > Master and Generator switches; I > Emergency fuel pump; l> Avionic Master switch; P11ntl Hght(l H) :.0. Pilot heat switch; )> Emergency light switch; l> Carburetor heat knob; > • The lower-Central portion of the instrument panel holds: Thro ttle; > Two analogue fuel quantity indicators; > > Fuel selector valve; • The lower-RH portion of the instrument panel holds: :r Flap indicator and toggle switch; Cabin heating knob; 4.2. CARBURETTOR HEAT )> NAV, land and strobe switches. > Carburettor heat control knob is located lower-LH portion of the instrument panel; when the knob is pulled fully outward from the instrument panel, carburettors re ceive maximum hot air. During normal operation, the knob is set in OFF position. Ed. I. Rev 0 Ed. Rev 0 1, Section 7 - Airframe and Systems description Section 7 - Airframe and Systems description INSTRUMENT PANEL INSTRUMENT PANEL AFMS N'S7 for Hoffman propeller equipped airplanes with MTOW Increment at 650 kg AFMS for VFR NIGHT equipped airplanes �@®@ &l!IT'©� P JJ© age �@XID@JJ© &l!IT'©d Page N7 - c Ui'Onoo�lt:'Al @UilQ!J®O _ c Ui'OnoollilQ lt:'Al@UilQ!l@O 9 E«JrlCNA'M wli7:i �;EcN.iM 7. POWERPLANT 5. SEATS AND SAFETY HARNESS 7.1. ENGINE Aircraft fe atures four fitting point for safety belts equipped with waist and shoul der harnesses adjustable via sliding metal buckle. Manufacturer: Bombardier-Ro/ax GmbH Seats are built with light alloy tube stQ.Icture and synthetic material cushioning. A Model: ROTAX912 S2 lever located on the right lower side of each seat allows for seat adjustment ac Type: 4 stroke, horizontally-opposed 4 cy linder, mixed air and cording to pilot size .. water cooled, twin electronic ignition, fo rced lubrication. Maximum rating: 98. 6hp (73.5kW) @ 5800 rp m/m in (2 388 rp m/min. prop) . Gear reduction ratio - 2. 4286: 1 6. DOORS Max oil consumption: Max : 0.1 /itres/hour P Two doors are provided for P2008 JC, on ilot and co-pilot side. A sketch of the door is shown below (RH and LH doors are specular): 7.2. PROPELLER Ma nufacturer: Hoffman Propellers Model: H017GHMA 174 177C N° of blades: 2 Upper safety block Diameter: 1740 mm Type: fixedp itch Latch system Inspection panel �C'.!�'t---"-.,,..,...� Gas spring support (Door side) Lower Hinge Latch svstem Fig. 7-6.DOOR The door is equipped with a gas spring fixed to the fuselage that facilitates door opening. Ed 1, Rev. O Section 7 - Airframe and system descriptions Ed. I, Rev 0 POWE RPLANT Section 7 - Airframe and Systems description SEATS AND SAFETY HARNESS AFMS forVFR NIGHT equipped airplanes AFMS forVFR NIGHT equipped airplanes TEcNAM [p�@@® CJ &Jl!J'@!J'@OO Jl@ [?O - O �- Jl@ &D!i'@!J'®OO �[}u� IMJ@[jj](ll]@D Page N7 CJ l?D�@� !Ml@Uil(ll]@D Page N7 l l1(]rEcNAM - l t 7. POWERPLANT 8. FUEL SYSTEM 7.1. ENGINE The fuel system is designed to supply the reciprocating engine (Bombardier-Rotax Manufacturer: Bombardier-Rotw; GmbH 912 S2) with the suitable flow rate and pressure according to engine limitations re- quired by Rotax manuals. • Model: ROTAX912 S2 Following figure shows the fuel system schematic of P2008JC airplane. Type: 4 stroke, hori::.onta/ly-opposed 4 cylinder, mixed air and water cooled, twin electronic ignition.forced lubrication. LH rUEL QUANTlTY CNDICATOR RH f"UEL IJUMH[TY INDICATOR Maximum rating: 98.6hp (73.5kW) @ 5800 rp m/min (2 388 rp m/m in, prop). Gear reduction ratio - 2.4286: l Max oil consumption: Max : 0.1 litres/hour 7.2. PROPELLER Manufacturer: GT Propellers Model: GT-211 73/VRR-FWlOl SRTC N° of blades: 2 Diameter: 1730 mm (n o reduction permitted) Type: ivood, fixedpitch ruEL PRESSURE SENDER fUEL PRESSINE SVJTCH ...... Fig.7-7. FUEL SYSTEM SCHEMATIC Each fuel tank is integrated within the wing ribs box. The capacity of each tank is 62 liters fora total of 124 liters. The internal side of fuel tank is accessible for inspection through two dedicated doors. The fuel tank filler cap is located on the top of the wing, in the area outside of the tank and it is easily accessible from the leading edge of the aircraft. At the lowest point of the tank it is positioned a drain sump. The engine is equipped with an engine gear pump, mechanical (primary). An addi tional auxiliary electrical fuelpump is provided (auxiliary). The fuel selector is operated by a fuel selector control knob located in the cabin on the central panel. The fuel selector control and the fuelvalve are connected via a rigid control rod. Ed. 1, Rev 0 Ed. 1, Rev 0 Section 7 - Airframe and Systems description Section 7 - Airframe and Systems description POWERPLANT FUEL SYSTEM AFMS forVFR NIGHT equipped airplanes lP�®])& &HU'@U'@OO AFMS for VFR NIGHT equipped airplanes 0 !?U�Dutl �mootIDU [?�@@® &ll!J'@!i'� !?OH@�!AYAlmootIDO JI@ Page N7 - 12 �@ c Page N7 - 13 9. ELECTRICAL SYSTEM 9.2. AVIONICS · The avionic system installed P2008 JC is based on five analogue indicators, an air olccmator speed indicator, an attitude indicator, an altimeter, magnetic compass and a slip in Primary D o · nn t t a p 5800wer is provided by external with t rn nn VDC 0 pu dicator, which provide primary flight information on the left side of the instrument ��:o �mpso® rpm. l a 14 1 · , ed on r During noby operations, a a {M it rcdiarges11• c the. ba ttc; panel. nry banery a 11 l powe is · provided w 13 e . . theI ) 1 1 provides ccssaryfor · cctnca m evc111 the energy ne- On the right side of the instrument panel three analogue indicators provides primary feed ing the. essem 1 1, oads of a failure Ac ::����� 1 1 alternatori information of engine parameters, an RPM indicator, oil temperature indicator and a ;;�ry11. atcr1 1va'.�� only d�1ring engine start-up t i nd� ; y . i. installed; his nte d to a b t e durmg engine srart-up .. CHT indicator. ve �fbuta ·t ca o ·d nal ri power i�l rhe e nt of an alternator failur o � J ll � :i� � ��r���� idccr c�I A dedicated analogue voltmeter is installed, located below engine instruments, which s.. l�1e e r yt ta lo e e � master and · ?aue7 :��blcd by1110111 switch l 1 provides primaryinformation of the electrical power supplied. """ bn is on connect d 10 111.sta e. idc the e and ebox· · the 03)'�1��;th �s 1 n ry is housed in a dedicated The fuel quantity information is provided by two dedicated analogue indicators lo The . automatic swnch betweenq the e �l� i r ir in ( 1 e���;,1�;�1::�����f�� ) and cated in the bottom central instruments panel. •�o action is e _u ed or�:;�� ��:;: t or ground ma nuenance nnd/or an Garmin G3X integrated avionic suite in a dual screen configuration is installed. It nnd starting, externalpower socket i� provided . rhe alternator bnuery nre lhe . O . provides flight and engine information intended for the pilot's situational awareness connected to buttery b 11 . for lhc clcc1ric equi,Pmcnt. in rder to provide eDcrgy only. G3X also embodies a GPS WAAS receiver whose information, intended for situ Each electrically fed instrument e . . . ational awareness only, are presented on RH display moving map. is conne te d to a dedicated c1rc�1t protects the cable from breaker which Two dedicated indicators provide the pilot with informationabout the flaps and pitch the battery b us o the associa_ ted electric t equipment. trim position. Stand-alone external COM/NAV and transponder sources (Garmin GNC 255A and if Ille GTX 328) are installed. Garmin GNC 255A navigation infom1ation is presented on lg11ilic111 Is in • · the position L R• or BO"' , 1 "H• an , the display (course and direction) along with the informationrelated to active/standby ,, propeller start the . move111e111 engine with possiblacc1e« eda11tnal ger/or bystaOJnd theer s. may frequency. This information is supplemented by an HSI indicator on G3X LH dis play. GTX 328 transponder provides SSR (Secondary Surveillance Radar) responses; this unit is capable of both mode "S" and mode "C". An external altitude encoder (ACK 9.1. STALL WARNING SYSTEM A-30) allows altitude reporting, this information is also presented on GTX 328 dis · play. The equipped with st An automatic reversion mode is integrated within the system in order to continue aircrn fl is II n s�s:; �ons�sting of a sensor loca�ed on lhc right wing leading ed e c nn o providing the pilot with the flightand engine information in the event of a LH or RH : mmg om located near the m- strume1u panel. � :��� f display failure. . Seven warning lights located on the top centre area of the instrument panel are avail able: ). Electricfuel ON (GREEN) Low Oil Pressurepump (RED) >). Low Fuel Pressure (RED) ). Alternator Fail (AMBER) ). High Oil Pressure (RED) ). Pitot heat ON (GREEN) Pitot heat fail (AMBER) > Ed.I, Rev O Ed. I, Rev 0 Section 7 A"rf rame and Systems description - 1 Section 7 - Airframe and Systems description ELECTRICAL SYSTEM ELECTRICAL SYSTEM AFMS for VFR NfGH T equipped airplanes �@@® AFMS for VFR NIGHT equipped airplanes JJ@0 D�@ � fA'fil@UilMtIDD /j,\fj11©� f? Page N7 - �®®®JJ© &1111@d i;san@l1iuQ ltYil®UiJ()!]ooa Page N7 -15 llu 14 c 9.3. - EXTERNA L POWER SUPPLY he �n L _right side of1hc tail cone, an external p is pos 1ble to wer is pr ent. 10. PITOT-STATIC PRESSURE SYSTEMS feedlhe c!cclric sysie es Using rhis device it m directl o 1hc . . s u c . on bus bar, The P2008 air speed/altitude indicating systems are connected with. a •to St t used y on power JC gineo r e JI shou m star1-up cold by : � slart belowld be OAT the engin in weather condiextetion.rnal en system based on a total pressure/Pitot probe (Heated Pitot tube) moun e un er �e� ii is ndviseablc ro . � -17° use externalpowe Follow lhis proc r source.F'or mg a two static ressure ports conn�cted in parallel and lo ated m co espon edure to start the n 1bc � � e g e using the exte . n rnal power source. e engine fire all 011 and right side of fuselage Flexible plumbmg con Magnetos, Mast i er swilch, ra o : left J. e e r switch: OFF n; total; pressure �and static ports to primary an�logue instruments, anem 2. Open recepiacle G n . door and in rthe extern and:� � altimeter. An alternate static source is located m the cabm, operated by ��=��� socket lhc en al power source's plu g into the cated o stnrt- � 3. up proc1:d11re (see Sect. 4 in ��� ADAHRS (GSU73) unit installed on the rear side of the fuselage near 4. D1scE1.1gi11e lhis manual) onnec1 lhe external power source's plug close ery, acts as an air data compute� forGarmin �BX suit�, it is con c door. the receptacle � : 1� � � ond firmly static:r:� and total pressure lines providmg on that smteboth air speed a ;; � t � � � formation. G3X ADAHRS Pitot probe FlG.7-8. PITOT-STATIC SYSTEM S ec tion 7 - Airfr ame and Syster Ed. I, Rev 0 ms description Ml�O ELE CTRICAL SYSTEM Section 7 - Airframe and Systems description PITOT-STATIC PRESSURE SYSTEMS AFMS for VFR NIGHT equipped airplanes lP�@@® dJ@CJ &UU'@U'@m r?Utl@Oua Page �®UilOO®U - 16 8 - N7 Page I - SECTION 8 - GROUND HANDLING & SERVICE 11. BRAKES The P2008 is provided with an i11d.,pend.,n1 JC hyd raulically actuated brake system 111am whe el. ':' 111 !er cylinder is attached INDEX foreach � to each pilol's rudder pedal tlmullc pressure, apphed vm the masler cylinders, enters the brnke Hy nected to the Jines con caliper. via A parking brake valve' mounted in correspondence of the cabin noor and ope t a knob on the coc . ra ed kpit central pedestal in1crcep1s b.y the hydraulic lines, once pressu nzed by toe br kc..'S, lo hold � the brake assemblies linings lightened h ro und the main w �els brake discs. Brake �n be operated from either pilot and 1. INTRODUCTION ...... 2 a single co-pilot's pedals: �cnted reservoir fe eds lh" pilot ide master cylinders which nected, vm OJI . are con hoses, wuh the co-pilol's side ones. 2...... AIRCRAFT INSPECTION INTERVALS . 3 3. AIRCRAFT CHANGES OR REPAIRS ...... 4 ...... 5 P-1co 4. MAINTENANCE \.'ENTl..:V 1u:s1mvo1R CAP 4.1. Refuelling ...... 5 4.2. Oil level control ...... 5 4.3. Landing gear tires pressure control ...... 5 5. ENGINE COWLING CHECK ...... 6 5.1...... 6 Upper cowling . 5.2. Lower Cowling ...... 6 6...... 7 GROUND HANDLING . . 6. 1...... 7 Towing . . . NC:-t! 6.2. Parking and Tie-Down ...... 7 6. 3. Mooring ...... 8 6.4. Jacking ...... 8 6.5. Road Transport...... 8 7...... 9 CLEANING AND CARE . . FJG. 7. 1...... 9 Windows .. . 7-9. BRAKE SYSTEM SCHEMATIC 7.2...... 9 External surfaces . 7...... 9 3 Propeller . 7.4. Engine ...... 9 7.5...... 9 Internal surfaces . I, Rev 0 Section 7 - Airframe and Systems description Ed. 0 BRAKES Section8-Aircraft Care and Maintenance Ed. I, Rev. INDEX .. Page - Page - 3 8 2 8 1 . INTRODUCTION Tl�is section c�nrains AI RCRAFT INSPECTION INTERVALS factory-rec�i:nrnended procedures 2. dlu�g. and rouun� forproper ground han Scheduled inspections must be performed in accordance with the instru tions care and It also idenri fies � serv1crng. certain inspection and addressed on the AircraftMaintenance Manual. Independently from the aircraft maintenance It is recommendedrequirement s. flight hours, an annual inspection has to be performed. to follow a planned schedule mamte11ance of lubrication and preventi based on chrnaticand flying e All required inspections are reported the Aircraft Maintenance Manual. conditions encountered locally. i� � As far as the scheduled/unscheduled engine maintenance is concerned, refer to the engine manufacturer Maintenance Manual. Unscheduled inspections/maintenance tasks are necessary when one or more of fo llowing conditions occur: Emergency landing I. 2. Breaking damage of propeller (or in case of .I simple impact)I 3. Enginefire 4. Lighting damage 5. Any type of damage orfai/ure Section Ed. 8 - GROUND HANDLING Rev. Ed. 1, Rev. 0 & SERVICE I, o INTRODUCTION Section 8 - GROUND HANDLING & SERVICE AIRCRAFT INSPECTION INTERVALS 8 -"""""""' Page - 8 - 5 4 AM Page - �TECN 3. AIRCRAFT CHANGES OR REPAIRS MAINTENANCE Aircraft change-s or Mnnunl repairs must be performed tenance in accordance with Aircraft Main- 4. nnd Job cards provided by TECNAM. 4.1. REFUELLING . Do not perfo rm aircraft refuellingnear flames, sparks or similar. Avoidfuelcont acfwith the skin: a skin corrosion could occ�r. Make sure that a fire extinguisher is available nearby during refu elling operations. Make sure that overall aircraft instrumentation is turned be- fo re performing the refuelling. OFF . . Do not operate switches and/or pushbuttons mszde. the az�craftdur ing refuelling operation; make sure that crew left the aircraft be fo re performing refuelling. Make sure that the aircraf t is electrically connected to the ground. 4.2. OIL LEVEL CONTROL 1. Open the engine cowling (RH) 2. Prior to oil check, switch off ignition circuit and tum the p�opeller by hand in direction of engine rotation several times to pump from the 1 011_ engine into the oil tank, or let the engine idle for mmute. This pro�ess is finished when air is returning back to the oil tank and can be noticed by a murmur from the open oil tank. 3. Clean the dipstick and soak it in the reservoir 4. Remove dipstick and read oil level 5. If required, replenish oil: oil level should be between max. and min. Marks shown on thedipstick 6. Close the engine cowling 4.3. LANDING GEAR TIRES PRESSURE CONTROL For each wheel proceed as follows: 1. Remove wheel fairing 2. Unscrew the tire cap 3. Connect a gauge 4. Read the pressure value 5. If required, rectify the pressure (nose tire 2.2 Bar I 32 Psi, main landing gear tires 2. 8 Bar I 40 Psi) 6. Fit the tire cap 7. Install wheel fairing S ec t.ion 8 G RO Ed. l,Rev. O - UND HANDLING & Ed. Rev. 0 SERVICE I, AIRCRAFT Section 8 GROUND HANDLING & SERVICE CHANGES OR REPAIRS - MAINTENANCE 5. ENGINE COWLING CHECK 6. GROUND HANDLING 5.1 . UPPER COWLING 6.1. TOWING I. Parking brake: ON II. Fuel selector valve: OFF The aircraft is most easily and safely maneuvered by hand by pushing on wing struts near attachments or by pulling it by its propeller near the axle. A tow bar III. Magnetos: OFF can be fixed onto nose gear fork. Aircraft may be steered by turningrudder or, IV. OFF steep turns,by pushing lightly on tail cone to lift nose wheel. Generator & Master switches: for Unlatch all b.uttertly Cam-locks the cowling by rotat v. four mounte.d on ing them 90° councer clockwise while pushing inwards. sl ighLly 6.2. PARKING AND TIE-DOWN VI. Remove engine cowling paying attention to propeller shaft passing through nose. VII. To assemble: rest cowling horizontal insuring proper fitting of nose General Under normal weather conditions, the airplane may be parked and headed in a di base reference pins. rection that will facilitate servicing without regard to prevailing winds. Ensure VIII. Secure latches by applying light pressure, check for proper assembly that it is sufficientlyprotected against adverse weather conditions and present no and fasten Cam-locks. danger to other aircraft. Procedure Butterfly Cam-locks are locked when tabs are horizontal and open Position airplane on levelled surface, headed into the prevailing wind, if practical. I. when tabs are vertical. Verify tab is below latch upon closing. 2. Engage parking brake 3. Secure pilot control stick by wrapping the seat belt around it WARNING Do not engage the parking brakes at low ambient 5.2. LOWER COWLING temperature, when an accumulation of moisture may NOTE: cause the brakes to freeze, or when they become hot I. After disassembling upper cowling, move the propeller to a horizontal fromsevere use. In this case use wheel chocks. position. II. Using a standard screwdriver, press and rotate 90° the two Cam-locks In case of long time parking or overnightparking, it is recommended to moor the positioned on lower cowling by the firewall. as shown on Para.6.3. ale III. Disconnect the ram-air duct from the NACA intake. Pull out the first Mooring is strongly recommended when the wind is more than hinge pin positioned on the side of the firewall, then, while holding knots and the ale is completely refuelled. 15 cowling, pull out second hinge pin; remove cowling with downward motion. IV. For installation follow reverse procedure. Ed. J, Rev. 0 Ed. l, Rev. 0 - Section 8 GROUND HANDLING & SERVICE Section 8 - GROUND HANDLING & SERVICE ENGINE COWLING CHECK GROUND HANDLING CLEANING AND CARE 6.3. MOORING 1. The aircraft is moored to insure its immovability, protection, and security under Aircraft swface must be kept clean to ensure expected flight pe1Jormance. Excessively dirty surfaces can af fect normal various weather conditions. I. flightconditions. Mooring is strongly the wind is more than 7.1 . WINDOWS I knots and the ale rei:is o111111e11dedref whenuelle d. of acrylic products employed for glass CAUTION 15 completely For windows cleaning, it is allowed the use and Plexiglas surfacescleaning. ProcedurePosition airplane on levelled surface and headed into the prevailing wind, if I. practical 7.2. EXTERNAL SURFACES 2. Centre nose wheel and engage parking brake and/oruse the wheel chocks Aircraft surface is cleaned with soapy water; they are not allowed solvents or al cohol based products. Died insects must be removed using hot water. Do not engage the parking brakes at low ambient It is advisable to avoid outside aircraft parking for long periods; it is always con temperature, when an accumulation of moisture may venient to keep the aircraft in the hangar. !Norn: : cause the brakes to freeze, or when they become hot from severe use. In these cases use wheel chocks. 7 .3. PROPELLER To preserve its functionality avoiding wear and corrosion, the propeller manufac 3. Secure pilot control stick by wrapping the seat belt around it turer uses, for external surface painting, an acrylic paint which is resistant to all 4. Assure that flaps are retracted solvents. In any case it is advisable to clean the propeller using exclusively soapy Electrically ground airplane, by connecting ground cable to the engine muffle 5. water. 6. Install control locks 7. Install protective plugs 7.4. ENGINE 8. Close and lock cabin doors. 9. Secure tie-down cables to the nose gear leg (and to the wings (in correspondence Engine cleaning is part of the scheduled maintenance. �efe� to the �ngine manu of wing stmts) and tail cone tie-down rings at approximately 45 degree with re facturerMai ntenance Manual for operating and for planning its cleaning. spect to the ground. [NO'iiE' Additional prepm'(lfio11for high winds includes tie-down ropes from the 7.5. INTERNAL SURFACES main landing. employment. • genr Interiors must be cleaned with a rate of 3 to 6 months. Any object present in the cabin (like pens, lost property, maps etc) must be removed. 6.4. JACKING The instrumentation as a whole must be cleaned with a humid cloth; plastic sur The aircraft can be lifted up by hydraulic jacks in correspondence of the points faces can be cleaned with suitable products. shown by externalplacards. For parts not easily accessible, perform cleaning with a small bmsh; seats must be cleaned with a humid cloth. For the correct procedure please refer to the Maintenance Manual. 6.5. ROAD TRANSPORT is �ecure tightly all onto IL recommended to aircran components the cart to ovoid MinimlJm cart meters. ro dnnmge1>lacc wi durinngs g transport.the size is 7x2.5by spec ific It is suggested Iii«!under nircratr 's bottomprotected secured from accidentlllclamps. hits usingSec,ondary 1:omponentsor other mater theial. stabi Por tatorcorrect shnll be de-rigging procedure, refer toplns Lic Manual. rigging and the Maintenance Ed. I, Rev. 0 Ed. I, Rev. 0 & SERVICE - GROUND HANDLING Section 8 - GROUND HANDLING & SERVICE Section 8 AND CARE GROUND HANDLING CLEANING Page S - 10 Page 9-1 8. - ICE REMOVAL Anti icing pro ducts are not allo . wed. To remove and operate ice, tow the SECTION _ AFM SUPPLEMENTS with a soft brush aircraft in the hang or a humid cloth. ar g INDEX ...... 1 INDEX...... Introduction...... 2 3 ;: Supplements list ...... I Se I ction 8 GRO Ed. I, - UN Rev. Rev. 0 D HANDLING Ed., & SERVICE o J" ICE REMOVAL SECTION 9 - AFM Supplements SUPPLEMENTS LIST Page 9-3 1. INTRODUCTION SUPPLEMENTS LIST Thi ection 2. concerns the .·uppl emcntal manuals of additional tation equipping the P2008JC (or optional) inst n or iafonnnt rumen equipment a ion and l mi t on configiu:ationor neededd/ ta i s related to installed local ircraftSIN: - Date: national rules.i A Registration marks: .\.\B k.M � 10 fit L 2.f-k/&:;.C to;z Sup. APPLICABLE: Title Rev. no. Date No. YES NO Night equipment configura- SI VFR Edlrev2 20/01/2016 JZI D tion AveoMaxx Hercules Landing/Taxi S2 Edlrev2 20/01/2016 li.,hts jQ D S3 Hoffman propeller Ed2rev2 2010112016 D � S4 MTOW increment at 650Kg Edlrevl 20/01/2016 D � SS Argentine AFMS EdlrevO 15/10/2015 D es] � S6 Reserved MTOW increment at 650Kg for S7 airplane equipped with Hoffmann EdlrevO 20/0 1/2016 � D propeller I" Rev. SECTI 0 Ed., Rev. 6 ON - AFM Ed., 9 Supplements J" SUPPLEMENTS LIST SECTION 9 - AFM Supplements SUPPLEMENTS LIST INTENTIONALLY LEFT BLANK I II J" Ed, Rev. O Section 9 - Supplements SUPPLEMl!NTS LIST