MANUALE DI VOLO
Contents
1. me COSTRUZIONI AERONAUTICHE X TECNAM FLIGHT MANUAL PERFORMANCE CROSSWIND Maximum demonstrated crosswind velocity is 15 Kts Example Given Find Wind direction 30 Headwind z 17 5 Kts Wind velocity 20 Kts Crosswind 10 Kts 0 17 10 20 56 LL Jw 50 Jl 30 KC gt Ki 40 A 40 501 gt 50 ZONA RACCOMANDATA ZONA NON RACCOMANDATA 55 Hr lt 60 ndi s E mI 411 E Le 70 __ 17 5 7 NS o nm d e E z 10 l E Tips z JL LL ET n LATO EST z SE ee 2 0 90 E Pt 104 100 INIM TN n D 220 80 112160 140 130 120 10 D 10 20 50 40 50 COMPONENTE TRAVERSO Kts Fig 5 1 CROSSWIND CHART I edition 23 March 2009 Doc n 92 13 030 00 5 4 P92 Classic Deluxe TEC NAM FLIGHT MANUAL PERFORMANCE TAKEOFF PERFORMANCE TAKEOFF DISTANCE CONDITIONS ISA Flaps 15 Engine full throttle Slope 0 Wind zero Ground roll Distance m Runway dry compact grass Ground roll P92 Classic Ground roll 92 100 DISTANCE 922. 7 CRUISE 8 CONSEQUENCES FROM RAIN AND 8 I edition 23 March 2009 Doc n 92 13 030 00 5 1 P92 Classic Deluxe lt lt lt TECNAM FLIGHT MANUAL PERFORMANCE INTRODUCTION This section provides all necessary data for accurate and comprehensive planning of flight activity from takeoff to landing Data reported in graphs and or tables were determined using e aircraft and engine in good condition e average piloting techniques Each graph or table was determined according to ICAO Standard Atmos phere ISA m s 1 evaluations of the impact on performance was carried out by theoretical means for e airspeed e external temperature e altitude e weight I edition 23 March 2009 Doc n 92 13 030 00 5 2 COSTRUZIONI AERONAUTICHE P92 Classic Deluxe M TECNAM FLIGHT MANUAL PERFORMANCE AIRSPEED CALIBRATION The difference between indicated airspeed and calibrated airspeed is within JAR VLA limits of 3 for all speeds above 1 3 Vs STALL SPEEDS CONDITIONS weight 450 kg engine idle no ground effect LATERAL BANKING D I edition 23 March 2009 92 13 030 00 5 3 P92 Classic Deluxe
3. List of Effective Page sain ve om 0 1 1 23 March 2009 23 March 2009 ec ec I edition 23 March 2009 Doc n 92 13 030 00 i 3 COSTRUZIONI AERONAUTICHE P92Classic Deluxe TECNAM FLIGHT MANUAL iwrropuction 7 7 1 23 March 2009 7 2 x 7 3 7 4 at 7 5 7 6 2 8 2 8 4 ec 8 5 ec I edition 23 March 2009 Doc n 92 13 030 00 1 4 COSTRUZIONI AERONAUTICHE P92Classic Deluxe TABLE OF CONTENTS General Section 1 Limitations Section 2 Emergency procedures Section 3 Normal procedures Section 4 Performance Section 5 Weight and balance Section 6 Systems description Section 7 Ground handling and servicing Section 8 I edition 23 March 2009 Doc n 92 13 030 00 i 5 I edition 23 March 2009 Doc n 92 13 030 00 TECNAM FLIGHT MANUAL cenenar 7 SECTION 1 GENERAL TABLE OF CONTENTS INI ROP NEE 2 WARNINGS CAUTIONS NOTES 2 THREE VIEW DRAWING atsa A a E ea Ea Ees 2 DESCRIPTIVE DA E 3 CONTROL SURFACES TRAVEL UAMITx 4 ENGINE d 5 AN GTA EE 5 KEE 6 OOD EE 6 918 B EE 6 IUDICIUM 7 SPECIFIC LOADING Eeer eege Eeer ee ee sd 7 ABBREVIATIONS AND TERAMINOL OCH 8 UNIT CONVERSION PACT ORS totae exta 11 COSTRUZIONI AERONAUTICHE P92 Classic INTRODUCTION The P92 CLASSIC peLuxe is twin seat single engine a
4. 7 DISTANCE P92Classic 100 400 410 420 430 440 450 460 470 480 490 500 WEIGHT Kg Fig 5 2 TAKEOFF I edition 23 March 2009 Doc n 92 13 030 00 5 5 COSTRUZIONI AERONAUTICHE P92 Classic Deluxe TECNAM FLIGHT MANUAL PERFORMANCE LANDING GROUND ROLL DISTANCE AND LANDING DISTANCE CONDITIONS Flaps 359 Runway dry compact grass Engine throttle idle Slope 0 Wind zero Distance over a 15 m obstacle 300 250 Ground roll DISTANCE 150 100 Ground roll Distance m 400 410 420 430 440 450 460 470 480 490 500 WEIGHT Kg Fig 5 3 LANDING I edition 23 March 2009 Doc n 92 13 030 00 5 6 P92 Classic Deluxe PERFORMANCE TEC CNAM FLIGHT MANUAL CLIMB PERFORMANCE CLIMB RATE IN CLEAN CONFIGURATION CONDITIONS ISA Flaps 0 Weight 450 kg Engine full throttle P92 Echo E P92 Echo 100 R C m sec 500 1000 1500 2000 2500 3000 Altitude m Fig 5 4 CLIMB RATE Rotax 912 UL Vy 120 Km h Rotax 912 015 120 Km h NOTE For each 10 kg weight increase R C decreases by 0 15 m sec 30 ft min For each 10 kg weight decrease R C increases by 0 15 m sec 30 ft min I edition 23 March 2009 Doc n 92 13 030 00 5 7 COSTRUZIONI AERONAUTICHE
5. 912 UL 912 ULS Minimum below 3500 rpm eng Normal above 3500 rpm eng 2 0 5 0 bar CAUTION Admissible pressure for cold start is 7 bar maximum for short periods I edition 23 March 2009 Doc n 92 13 030 00 2 4 P92 Classic Detuse E FLIGHT MANUAL LIMITATIONS OIL VISCOSITY Use viscosity grade oil as specified in the following table Klima Mehrbereichs Ole multi grade oils climatic conditions tropisch tropical gemaBigt temperate SAE 10W 40 SAE 5W 50 SAE 5W 40 arktisch arctic CAUTION Use of Aviation Grade Oil with or without additives is not permitted COOLANT Coolant type and specifications are detailed into the Rotax Operator s Manual PROPELLER Rotax 912 UL Rotax 912 ULS F lli Tonini Giancarlo amp Felice F lli Tonini Giancarlo amp Felice GT 2 166 VSU FW 101 SRTC GT 2 173 VRR FW 101 SRTC Wood twin blade fixed pitch Wood twin blade fixed pitch 1660 mm 1730 mm I edition 23 March 2009 Doc n 92 13 030 00 2 5 COSTRUZIONI AERONAUTICHE P92 Classic Detuse FLIGHT MANUAL LIMITATIONS POWERPLANT INSTRUMENT MARKINGS Powerplant instrument markings and their color code significance are shown below Rotax 912 UL RED LINE GREEN ARC YELLOW ARC RED LINE INSTRUMENT Minimum Normal Caution Maximum limit imi operating Engine tachometer EINEN 1400 5500 5500 5800 5800 Oil Temp 90 110 50 90 110 140 Cylinder
6. MIIA 2150 2 0027 052 ANHIA Ser 9091502 AHIA ACIS 059 7 A Sa e c dOL UORINASUOD 2uEIeu 4 ubiseq Doc n 92 13 030 00 1 edition 23 March 2009 COSTRUZIONI AERONAUTICHE P92 Classic Deluxe TECNAM FLIGHT MANUAL Genera DESCRIPTIVE DATA WING Wing span 9 4m Wing chord 1 4m Wing surface 13 2 m Wing loading 34 2 kg m Aspect ratio 6 714 Taper ratio 1 0 Dihedral 1 5 FUSELAGE Overall length 6 5m Overall width 1 1m Overall height 2 5m EMPENNAGE Stabilator span 2 9m Vertical tail span 1 23 m LANDING GEAR Wheel track 1 8m Wheel base 1 6m Main gear tire Air Trac 5 00 5 Wheel hub and brake Marc Ingegno Nose gear tire Sava 4 00 6 CONTROL SURFACES TRAVEL LIMITS Ailerons Up 20 down 15 2 Stabilator Up 16 down 3 1 Trim Tab 42 412 1 Rudder RS 25 LS 25 1 Flaps 09 359 2 I edition 23 March 2009 Doc n 92 13 030 00 1 4 COSTRUZIONI AERONAUTICHE lt lt ENGINE Model Manufacturer Engine type Maximum power PROPELLER Manufacturer Model Number of blades Diameter Type I edition 23 March 2009 FLIGHT MANUAL Rotax 912 UL Bombardier Rotax GmbH Four cylinder horizontally opposed twins with overall displacement of 1211 2 c c mixed c
7. Q mum iy Check integrity of left side main landing gear tire inflation 1 6 bar condition and alignment check fuselage skin condition I edition 23 March 2009 Doc n 92 13 030 00 4 3 Bou Woo uw Se n COSTRUZIONI AERONAUTICHE P92 Classic SS TECNAM FLIGHT MANUAL normal PROCEDURES Horizontal tail and tab check integrity and unhindered movement Vertical tail and rudder check integrity and unhindered movement Check integrity of right side main landing gear tire pressure 1 6 bar condition and alignment check fuselage skin condition Right flap and hinges check integrity Right aileron check integrity and unhindered movement Leading edge and wing skin check integrity Check right side tank cap is fastened and blow out plug is unobstructed Check right side static vent is unobstructed do not blow inside vents read note Check integrity of nose landing gear strut tire inflation 1 0 bar and condition check condition of rubber shock absorbers Propeller and spinner condition check for nicks and fastening Open engine cowling and perform the following checklist 1 II Check foreign objects are present Check the cooling circuit for losses from tubing check coolant reservoir lev el insure radiator honeycomb cooling fins are unobstructed Check lubrication circuit for losses from tubing check oil reservoir level in sure radiator honeycomb
8. OFF SMOKE AND FIRE ENGINE FIRE WHILE PARKED OR DURING TAKEOFF ok S T Fuel shutoff valves OFF Abort takeoff if possible If engine is running let it use up remaining fuel in carburetors Magnetos and Master switch OFF Warn bystanders to clear the area as fast as possible Without removing the engine cowling use a CO or a powder fire extin guisher to put out flames directing spray towards cowling s air intakes I edition 23 March 2009 Doc n 92 13 030 00 3 3 COSTRUZIONI AERONAUTICHE P92 Classic Deluxe 14 FLIGHT MANUAL NOTE DO NOT USE WATER to put out fire and do not open engine cowling until absolutely certain fire is extinguished In case an appropriate fire extinguisher is not handy still keeping engine cowling closed it is possi ble to use a woolen blanket sand or dirt to try smothering the fire ENGINE COMPARTMENT FIRE IN FLIGHT Fuel shutoff valves OFF Throttle fully inward Magnetos OFF Do not try airstarting engine Extend flaps as needed Carry out forced landing emergency procedure Master switch OFF GROS NS CABIN FIRE DURING FLIGHT 1 Master switch OFF 2 Door vents open 3 Extinguish fire with on board fire extinguisher if available directing spray towards flame base 4 as soon as possible RECOVERY FROM UNINTENTIONAL SPIN In case of unintentional spin entry follow the emergency procedure described below Adjust th
9. detergents but in any case never use products such as gasoline alcohol acetone or other solvents To clean cabin interior seats upholstery and carpet it is generally recommended to use foam type detergents I edition 23 March 2009 Doc n 92 13 030 00 8 5
10. 030 00 4 7 COSTRUZIONI AERONAUTICHE P92 ic Deluxe CRUISE 1 II Temperature cylinder heads lt 135 C NORMAL PROCEDURES Reach cruising altitude Set power and engine rpm s for cruise Check engine parameters 912 UL 912 ULS IV Carburetor heat as needed see paragraph on carb heat in Section 3 Compensate unpredicted asymmetrical fuel consumption between left and right fuel tanks by shutting off appropriate fuel tap located inside cabin LANDING I Turn on landing light if installed II Check runway final and establish descent and approach to final III Extend flaps gradually to maximum deflection of 35 IV Optimal touchdown speed 70 Km h V Land and taxi VI Flaps to 0 VII Parking brake ON Turn off landing light navigation lights and strobe light ENGINE SHUT DOWN I Keep engine running at 3000 RPM for about two minutes in order to reduce latent heat II Turn off all electrical utilities Set magnetos switch and Master switch to OFF IV Set both fuel taps to OFF V Insert hood over pitot tube on left side wing strut I edition 23 March 2009 Doc n 92 13 030 00 4 8 COSTRUZIONI AERONAUTICHE P92 Classic Deluxe TECNAM FLIGHT MANUAL PERFORMANCE SECTION 5 PERFORMANCE TABLE OF CONTENTS INTRODUCTION E 2 AIRSPEED CALIBRATION E 3 STALE SPEEDS 3 CROSSWIND 4 TAKEOFF ENEE eege 5 P p qe 6 CLIMB PERFORMANCE
11. 4 CLEANING AND EE 5 I edition 23 March 2009 Doc n 92 13 030 00 8 1 P92 Classic Deluxe INTRODUCTION This section contains factory recommended procedures for proper ground han dling and routine care and servicing It also identifies certain inspection and main tenance requirements which must be followed if the aircraft is to retain its new plane performance and dependability It is wise to follow a planned schedule of lubrication and preventive maintenance based on climatic and flying conditions encountered locally AIRPLANE INSPECTION PERIODS Inspection intervals occur at 50 100 hours and in accordance with special in spection schedules which are added to regularly scheduled inspections Correct maintenance procedures are described in the aircraft s Service Manual or in the engine s Service Manual GROUND HANDLING TOWING 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 can be fixed onto nose gear fork Aircraft may be steered by turning rudder or for steep turns by pushing lightly on tailcone to lift nose wheel PARKING AND TIE DOWN When parking airplane outdoors head it into the wind and set the parking brake If chocks or wedges are available it is preferable to use the latter In severe weather and high wind conditions it is wise to tie the airplane down Tie down ropes shall be fastened to the
12. cause aircraft tail to lower I edition 23 March 2009 Doc n 92 13 030 00 6 4 COSTRUZIONI AERONAUTICHE P92 Classic Deluxe SECTION 7 AIRPLANE AND SYSTEM DESCRIPTIONS TABLE OF CONTENTS INTRODUCGCHEION rrr E E HERD eo e sees 2 AIRFRAME 2 FLIGHT CONTROLS 4 ry ies Dire iet toco v iex 2 INSTRUMENT PANBEL 5 iiti eds E et Ie HUE de oe Ie 3 SEATS AND SAFETY en een 4 DOORS i 4 BAGGAGE COMPARITMENT AAA 4 IU Curam 4 a M 5 ELECTRICAL SYSTEM tet Re ES EH i Ne bn EVER EU 5 AIRSPEED INDICATOR 5 5 eene trennen ene 6 BRAKES A 6 I edition 23 March 2009 Doc n 92 13 030 00 7 1 COSTRUZIONI AERONAUTICHE P92 Classic Deluxe FLIGHT MANUAL SYSTEMS INTRODUCTION This section provides description and operation of the aircraft and its systems AIRFRAME WING The wing is made up of a central light alloy torque box a composite leading edge is attached to the front spar and geometrically similar flap and aileron are hinged to rear Flaps and ailerons are both made up of an aluminum spar connected to formed sheet metal leading edge and ribs and are covered by a thermoretractible synthetic material FUSEL
13. heads temper 75 150 ature CHT Rotax 912 016 RED LINE GREEN ARC YELLOW ARC INSTRUMENT Minimum Normal Caution Maximum limit imi operating 1400 5500 5500 5800 5800 Oil Temp 90 110 50 90 110 130 Cylinder heads temper ature CHT Rum I edition 23 March 2009 Doc n 92 13 030 00 2 6 COSTRUZIONI AERONAUTICHE P92 Classic Detuse FLIGHT MANUAL LIMITATIONS OTHER INSTRUMENT MARKINGS INSTRUMENT RED LINE GREEN ARC YELLOW ARC RED LINE Minimum limit Normal operating Caution Maximum limit WEIGHT LIMITS Maximum takeoff weight 450 kg CENTER OF GRAVITY LIMITS Forward limit 20 MAC Aft limit 33 MAC Datum Propeller support flange w o spacer Bubble Level Cabin floor It is the pilot s responsibility to insure that airplane is properly loaded APPROVED MANEUVERS This aircraft is intended for non aerobatic operation only Non aerobatic operation includes e Any maneuver pertaining to normal flight e Stalls except whip stalls e Lazy eights e Chandelles e Turns in which the angle of bank is not more than 60 Acrobatic maneuvers including spins are not approved I edition 23 March 2009 Doc n 92 13 030 00 2 7 COSTRUZIONI AERONAUTICHE P92 Classic Detuse E TECNAM FLIGHT MANUAL LIMITATIONS FUEL TWO TANKS 45 litres TOTAL FUEL CAPACITY 90 litres Rotax 912 UL APPROVED FUELS Min RON 90 EN 228 Regular EN 228 Premium EN 228 Prem
14. 12 UL Four stroke horizontally opposed 4 cylinder mixed air and water cooled twin electronic ignition forced lubrication Maximum rating 81Hp 59 6 kW at 5800 RPM Reduction gearbox 2 273 1 Prop GT 2 166 VSU FW 101 SRTC I edition 23 March 2009 Doc n 92 13 030 00 7 4 COSTRUZIONI AERONAUTICHE P92 Classic Deluxe FLIGHT MANUAL SYSTEMS gt Rotax 912 ULS Four stroke horizontally opposed 4 cylinder mixed air and water cooled twin electronic ignition forced lubrication Maximum rating 100 Hp 73 5 kW a 5800 g min Reduction gearbox 2 4286 1 Prop GT 2 173 VRR FW 101 SRTC For further information please refer to Rotax Operator s Manual FUEL SYSTEM The system consists of two aluminum fuel tanks that are integral part of the leading edge featuring a level sensor in each tank Capacity is 45 liters each Each tank is equipped with cabin installed shut off valve and of a main filter located on the firewall and equipped with a drainage valve The fuel system features a mechanical pump operated by the engine and an emergency electric pump that allows feed in case of main pump failure ELECTRICAL SYSTEM The aircraft s electrical system consists of a 12 Volt DC circuit controlled by a Master switch located on dashboard Electricity is provided by an alternator or by a buffer battery placed in tailcone Generator light is located on the right side of the instrument panel OIL AND CYLINDER HEADS TE
15. 2 RIGGING AND DERIGGING ENGINE COWLING 2 PREFLIGHT EE 3 I edition 23 March 2009 Doc n 92 13 030 00 4 1 COSTRUZIONI AERONAUTICHE P92 Classic 14 FLIGHT MANUAL ememr INTRODUCTION Section 4 contains checklists and amplified procedures for the conduct of normal opera tion RIGGING AND DERIGGING ENGINE COWLING UPPER COWLING I Parking brake ON IL Fuel shutoff valves OFF III Master switch OFF Magnetos OFF IV Unlatch all four butterfly Cam locks mounted on the cowling by rotating them 90 counterclockwise while slightly pushing inwards V Remove engine cowling paying attention to propeller shaft passing through nose VI To assemble rest cowling horizontal insuring proper fitting of nose base refer ence pins VII Secure latches by applying light pressure check for proper assembly and fasten Cam locks WARNING Butterfly Cam locks are locked when tabs are horizontal and open when tabs are vertical Verify tab is below latch upon closing LOWER COWLING I After disassembling upper cowling bring propeller to horizontal position II Using a standard screwdriver press and rotate 90 the two Cam locks positioned on lower cowling by the firewall Disconnect landing light wire IV Pull out the first hinge pin positioned on the side of the firewall then while hold ing cowling
16. AGE The front part of the fuselage is made up of a truss structure with special steel tub ing and beginning at the cabin s rear section by an aluminum alloy semi monococque structure The engine housing is isolated from the cabin by a stainless steel firewall the steel stringers engine mount is attached to the cabin s truss struc ture in four points EMPENNAGE The vertical tail is entirely metal the vertical stabilizer is made up of a twin spar with load carrying skin while the rudder consists of an aluminum torque stringer connected to light alloy ribs and skin The horizontal tail is an all moving type stabilator its structure consists of an aluminum tubular spar connected to ribs and leading edge the entire structure is covered aluminum material FLIGHT CONTROLS Aircraft flight controls consist of aileron rudder and stabilator control surfaces The control surfaces are manually operated using a control stick for ailerons and stabilator and rudder pedals for the rudder longitudinal control acts through a sys tem of push rods and is equipped with a trim tab Aileron control is of mixed type with push rods and cables the cable control circuit is confined within the cabin and is connected to a pair of push rods positioned in the wings that control ailerons dif ferentially Aileron trimming is carried out on ground through a small tab posi tioned on left aileron I edition 23 March 2009 Doc n 92 13 030 00 7 2 COSTRUZ
17. COSTRUZIONI AERONAUTICHE P92CI INTRODUCTION FLIGHT MANUAL P92 Echo CLASSIC Qetuse MANUFACTURER COSTRUZIONI AERONAUTICHE 5 AIRCRAFT TYPE P92 CLASSIC deluxe WARNING THIS MANUAL IS VALID FOR THE P92 CLASSIC DELUXE WITH EITHER ROTAX 912 80 HP ENGINE OR ROTAX 912ULS 100 HP ENGINE FOR EVIDENT SAFETY REASONS AND UPON READING THIS MANUAL FOR THE FIRST TIME IT IS NECESSARY TO UNDERLINE PERHAPS ALSO HIGHLIGHT WITH A COLORED MARKER ANY DIFFERENCES IN CHARTS AND TABLES AS APPLICABLE TO PERSONAL AIRCRAFT The Flight Manual must always be kept on board the aircraft The aircraft described herein is to be operated in accordance with procedures and limitations described in this Flight Manual I edition 23 March 2009 Doc n 92 13 030 00 i 1 E COSTRUZIONI AERONAUTICHE P92Classic Deluxe SS TECNAM FLIGHT MANUAL RECORD OF REVISIONS All revisions to the current Manual except for actual weighing data must be recorded in the following table and in case of approved sections must be endorsed by the Responsible Airworthiness Authority New text or amendments to revised pages shall be clearly marked by a vertical black line on the left hand margin with revision N and date indicated on left side of page RECORD OF REVISIONS I edition 23 March 2009 Doc n 92 13 030 00 i 2 E COSTRUZIONI AERONAUTICHE P92Classic Deluxe SS TECNAM FLIGHT MANUAL
18. IONI AERONAUTICHE P92 Classic Deluxe FLIGHT MANUAL SYSTEMS Flaps are extended via an electric servo actuator controlled by a switch on the dashboard Flaps act in continuous mode The electric circuit is protected by a breaker positioned on the right side of the dashboard Longitudinal trim is performed by a small tab positioned on the stabilator and controlled via an electric servoactuator by pushing an Up Down push button located on the control stick or between the seats INSTRUMENT PANEL The instrument panel is of conventional type allowing space for a broad range of equipment Instruments marked with an asterisk are optional Speaker Dimmer HF RADIO RPM INDICATOR Flap Indic Heads xATtizude ind ALTIMETER TRIM INDICATOR LH Fuel qty indic TURN INDICATOR MASTER Gasen d VSI IGNITION THROTTLE xBeeokee Fuel Pump Choke aes Strobe light xGyro compass xAvionics Fuel pressure THROTTLE FRICTION tick e Socket XNAV ligh
19. LOGY Crosswind is the velocity of the crosswind component for which adequate con Velocity trol of the airplane during takeoff and landing was actually demon strated Usable fuel is the fuel available for flight planning Unusable fuel is the quantity of fuel that cannot be safely used in flight G is the acceleration of gravity TOR is the takeoff distance measured from actual start to wheel liftoff point TOD is total takeoff distance measured from start to 15m obstacle clear ing GR is the distance measured during landing from actual touchdown to stop point LD is the distance measured during landing from 15m obstacle clear ing to actual stop S R is specific range that is the distance in nautical miles which can be expected at a specific power setting and or flight configuration per kilo of fuel consumed I edition 23 March 2009 Doc n 92 13 030 00 1 9 COSTRUZIONI AERONAUTICHE lt lt TECNAM P92 Classic Detluse FLIGHT MANUAL GENERAL WEIGHT AND BALANCE TERMINOLOGY Datum Arm Moment G Standard Empty Weight Basic Empty Weight Useful Load Maximum Weight Maximum Takeoff Weight Maximum Landing Weight Tare I edition 23 March 2009 is an imaginary vertical plane from which all horizontal distances are measured for balance purposes is the horizontal distance from the reference datum to the center of gravity C G of an item is the product of the we
20. MP OIL PRESSURE These instruments are connected in series with their respective sensors Temperature instruments are protected by the same breaker oil pressure indicator and a second breaker protects other instruments AVIONICS The central part of the dashboard holds room for avionics equipment System s manufacturer furnishes features for each system I edition 23 March 2009 Doc n 92 13 030 00 7 5 COSTRUZIONI AERONAUTICHE P92 Classic Deluxe FLIGHT MANUAL SYSTEMS AIRSPEED INDICATOR SYSTEM The aircraft s airspeed indicator system is shown below and consists of two static vents located on both sides of the aircraft forward of cabin and by a pitot tube lo cated on left wing strut FIG 7 2 AIRSPEED INDICATOR SYSTEM BRAKES The aircraft s braking system is a single system acting on both wheels of main landing gear through disk brakes the same circuit acts as parking brake via an intercept valve To activate brakes it is sufficient to verify that brake shut off valve positioned on tunnel between pilots is OFF then activate brake lever as necessary To activate parking brake pull brake lever and set brake shut valve to ON I edition 23 March 2009 Doc n 92 13 030 00 7 6 P92 Classic Deluxe Furet MANUAL ZZ SECTION 8 GROUND HANDLING AND SERVICE TABLE OF CONTENTS EE 2 AIRPLANE INSPECTION PERIODS EE 2 GROUND z TEV D D IN O ee 2 GROUND ROUND ANCHORAGE Optional
21. P92 Classic Deluxe M TECNAM FLIGHT MANUAL PERFORMANCE CRUISE CONDITIONS ISA Altitude 0 Wind 0 Rotax 912 UL wy common Rotax 912 ULS Jesse CONSEQUENCES FROM RAIN AND INSECT Flight tests have demonstrated that neither rain nor insect impact build up on leading edge has caused substantial variations on aircraft s flight qualities I edition 23 March 2009 Doc n 92 13 030 00 5 8 COSTRUZIONI AERONAUTICHE P92 Deluxe WEIGHT amp BALANCE SECTION 6 WEIGHT amp BALANCE TABLE OF CONTENTS INTRODUCTION 2 AIRCRAFT WEIGHING PROCEDURES ra ictor ode 2 EEN 3 CG EENEG 4 I edition 23 March 2009 Doc n 92 13 030 00 6 1 COSTRUZIONI AERONAUTICHE P92 Classic 9 14 FLIGHT MANUAL wenta satance INTRODUCTION This section describes the procedure for establishing the basic empty weight and moment of the aircraft Loading procedure information is also provided AIRCRAFT WEIGHING PROCEDURES PREPARATION Carry out weighing procedure inside closed hangar Remove from cabin all objects left unintentionally Align nose wheel Drain fuel using draining reservoir Oil hydraulic fluid and coolant to operating levels Position seats to most forward position Flaps retracted 0 Control surfaces in neutral position Place scales min capacity 200 kg under each wheel rpg hoe Boop LEVELING Level the aircraft using ca
22. bin floor as datum b Center bubble on level by deflating nose tire WEIGHING a Record weight shown on each scale b Repeat weighing procedure three times c Calculate empty weight DETERMINATION OF C G LOCATION a Drop a plumb bob tangent to the leading edge in non tapered area of one half wing approximately one meter from wing root and trace reference mark on the floor Repeat operation for other half wing c Stretch a taught line between the two marks d Measure the distance between the reference line and main wheel axis e Using recorded data it is possible to determine the aircraft s C G location and moment see following table I edition 23 March 2009 Doc n 92 13 030 00 6 2 COSTRUZIONI AERONAUTICHE P92 Classic Deluxe 14 TECNAM FLIGHT MANUAL weert stance WEIGHING REPORT Model P92 CLASSIC peLuxe s n Weighing n Date Datum Propeller support flange without spacer PLUMB BOB A Bok dice Rom aes viel B D Empty weight moment M D 1 39 We Kg m Maximum takeoff weight 450 kg Empty weight I edition 23 March 2009 Doc n 92 13 030 00 6 3 COSTRUZIONI AERONAUTICHE P92 Classic 4 14 FLIGHT MANUAL went satance C G TRAVEL Maximum admissible C G travel exceeds actual operational limits Moreover oc cupants and fuel impact only marginally on CG travel When on flat terrain exceeding CG travel aft limit will
23. ce Manual I edition 23 March 2009 Doc n 92 13 030 00 8 3 P92 Classic Deluxe GROUND ANCHORAGE OPTIONAL The airplane should be moored for immovability security and protection FAA Advisory Circular AC 20 35C Tiedown Sense contains additional information regarding preparation for severe weather tiedown and related information The following procedures should be used for the proper mooring of the airplane Head the airplane into the wind if possible Retract the flaps Chock the wheels Lock the control stick using safety belts Secure tie down ropes to the wing tie down rings and to the tail ring at approximately 45 degree angles to the ground in longitudinal direction see Fig 8 1 Cie port Tie Down Anchor Tie Down Ring Tie Down Rope Tie Down Anchor Tie Down Anchor os TieD R Tie Down Ring Tie Down Ring Tie Down Rope N ie Down Rope Cd Tie Down Anchor Tie Down Anchor Fig 8 1 CABLE POSITIONING I edition 23 March 2009 Doc n 92 13 030 00 8 4 P92 Classic Deluxe lt _ FircuT MANUAL 9 0 CLEANING AND CARE To clean painted surfaces use a mild detergent such as shampoo normally used for car finish use a soft cloth for drying The plastic windshield and windows should never be dusted when dry use luke warm soapy water and dry using chamois only It is possible to use special glass
24. cooling fins are unobstructed Open both fuel taps inspect fuel circuit for losses from tubing check integri ty of fireproof protection braids drain circuit using a container to collect fuel activating the specific drainage tap located on the firewall shut fuel taps Check for absence of water or other contaminants WARNING Drainage operation must be carried out with aircraft parked on level surface V VI VII Check integrity of silent blocks Check firmness and integrity of air intake system check externally that ram air intake is unobstructed Check that all parts are secure or safetied U Close engine cowling Check left side static port is unobstructed I edition 23 March 2009 Doc n 92 13 030 00 4 4 COSTRUZIONI AERONAUTICHE P92 Classic SS TECNAM FLIGHT MANUAL womwtPROCEDURES Z Remove tow bar and chocks Avoid blowing inside left strut mounted pitot and inside airspeed indicator sys tem s static vents as this may damage instruments I edition 23 March 2009 Doc n 92 13 030 00 4 5 COSTRUZIONI AERONAUTICHE P92 Classic 14 FLIGHT MANUAL ememr CHECKLISTS BEFORE STARTING ENGINE after preflight inspection I Flight planning fuel consumption refueling Aircraft loading and related inspections see section 6 III Seat and safety belts adjustment IV Doors secured V Parking brake ON STARTING ENGINE I Maste
25. er Exceed Speed is the speed limit that may not be exceeded at any time Vs Stalling Speed Vso Stalling Speed or the minimum steady flight speed at which the air plane is controllable in the landing configuration at the most forward center of gravity Vx Best Angle of Climb Speed is the speed which results in the greatest gain of altitude in a given horizontal distance Vy Best Rate of Climb Speed is the speed which results in the greatest gain in altitude in a given time Vr Rotation speed is the speed at which the aircraft rotates about the pitch axis during takeoff Vobs Obstacle speed is the speed at which the aircraft flies over a 15m obstacle during takeoff or landing I edition 23 March 2009 Doc n 92 13 030 00 1 8 COSTRUZIONI AERONAUTICHE P92 Classic lt lt lt TECNAM FLIGHT MANUAL GENERAL METEOROLOGICAL TERMINOLOGY OAT Outside Air Temperature is the free air static temperature expressed in degrees Celsius C Ts Standard Temperature is 15 C at sea level pressure altitude and de creased by 2 C for each 1000 ft of altitude Hp Pressure Altitude is the altitude read from an altimeter when the baro metric subscale has been set to 1013 mb ENGINE POWER TERMINOLOGY RPM Revolutions Per Minute is the number of revolutions per minute of the engine s crankshaft divided by 2 273 912UL or 2 4286 9125 yields propeller s RPM AIRPLANE PERFORMANCE AND FLIGHT PLANNING TERMINO
26. ight of an item multiplied by its arm Center of Gravity is the point at which the airplane or equipment would balance if suspended Its distance from the reference datum is found by dividing the total moment by the total weight of the airplane is the weight of a standard airplane including unusable fuel full oper ating fuels and full engine oil is the standard empty weight plus the weight of optional equipment is the difference between takeoff weight and the basic empty weight is the maximum weight of the aircraft is the maximum weight approved for the start of the takeoff run is the maximum weight approved for the landing touch down is the weight of chocks blocks stands etc used when weighing an airplane and is included in the scale readings Tare is deducted from the scale reading to obtain the actual net airplane weight Doc n 92 13 030 00 1 10 COSTRUZIONI AERONAUTICHE TECNAM FLIGHT MANUAL P92 Classic Detluse GENERAL UNIT CONVERSION FACTORS MULTIPLYING TEMPERATURE Fahrenheit F Celsius FORCES Kilograms Pounds SPEED Meters per second m s Feet per minute ft min Knots kts Kilometers hour km h PRESSURE Atmosphere Pounds sq in LENGTH Kilometers Nautical miles Meters Feet Centimeters Inches VOLUME Liters U S Gallons AREA Square meters Square feet I edition 23 March 2009 YIELDS Celsius Fahrenheit Pounds Kilograms Feet per mi
27. ircraft with a strut braced rectangular high wing fixed main landing gear and steerable nose wheel This Flight Manual has been prepared to provide pilots and instructors with information for the safe and efficient operation of this aircraft This Flight Manual contains 8 sections Section 1 provides basic data and in formation of general interest in addition to definitions and explanations of symbols abbreviations and terminology commonly used WARNINGS CAUTIONS NOTES The following definitions apply to warnings cautions and notes used in the Flight Manual WARNING means non observation of the procedure leads to an immediate or important degrada tion of the flight safety poco that the non observation of the corresponding i CAUTION procedure leads to a minor or to a more or less long term degradation of the flight safety NOTE draws the attention to any special item not directly re lated to safety but which is important or unusual THREE VIEW DRAWINGS e Dimensions shown refer to aircraft weight of 450 kg and normal operat ing tire pressure e Propeller clearance 360mm e Propeller clearance with deflated front tire and compressed shock absor ber 142mm e Minimum ground steering radius 5 5m I edition 23 March 2009 Doc n 92 13 030 00 1 2 P92 Classic Detuse GENERAL FLIGHT MANUAL COSTRUZIONI AERONAUTICHE
28. ium plus AVGAS 100LL refer to the Rotax Operator s Maunal X X Rotax 912 ULS APPROVED FUELS Min RON 95 EN 228 Premium EN 228 Premium plus AVGAS 100LL refer to the Rotax Operator s Maunal x X I edition 23 March 2009 Doc n 92 13 030 00 2 8 COSTRUZIONI AERONAUTICHE P92 Classic Deluxe 14 FLIGHT MANUAL SECTION 3 EMERGENCY PROCEDURES TABLE OF CONTENTS INTRODUNGCTION te t et ER ev Ris us dee EELER 2 ENGINE EAILURE tette tet tea enee 2 FORGED LANDING ertt tate tree e eere REDE ee 3 SMOKE AND FIRE eei arte treo lee Ie Ig CREE 3 RECOVERY FROM UNINTENTIONAL 4 DEPLOYMENT OF EMERGENCY PARACHUTE optional equipment 5 I edition 23 March 2009 Doc n 92 13 030 00 3 1 TEC CNAM FLIGHT MANUAL INTRODUCTION P92 Classic EMERGENCY PROCEDURES Section 3 includes checklists and detailed procedures to be used in the event of emer gencies Emergencies caused by a malfunction of the aircraft or engine are extremely rare if appropriate maintenance and pre flight inspections are carried out In case of emergency suggestions presented in this section should be considered and applied as necessary to correct the problem Before operating the aircraft the pilot should become thoroughly familiar with the present manual and in particular with the present section Further a con
29. ng I edition 23 March 2009 Doc n 92 13 030 00 2 2 COSTRUZIONI AERONAUTICHE P92 Classic Detuse FLIGHT MANUAL LIMITATIONS AIRSPEED INDICATOR MARKINGS Airspeed indicator markings and their color code are explained in the following table Rotax 912 UL ULS MARKING IAS km h SIGNIFICANCE White arc 71 110 Flap Operating Range lower limit is Vso at maximum weight and upper limit is maximum speed permissible with flaps extended at 35 Green arc Normal Operating Range lower limit is Vre at maxi mum weight and upper limit is maximum structural speed V yo Yellow arc 200 260 Operations must be conducted with caution and only in smooth air Maximum speed for all operations I edition 23 March 2009 Doc n 92 13 030 00 2 3 COSTRUZIONI AERONAUTICHE P92 Classic Detuse FLIGHT MANUAL LIMITATIONS POWERPLANT LIMITATIONS The following table lists operating limitations for aircraft installed engine ENGINE MANUFACTURER Bombardier Rotax GmbH ENGINE MODELS 912 UL 912 ULS MAXIMUM POWER Maximum max 5 minutes 59 6 80 73 5 100 5800 5500 Maximum continuous 58 76 69 93 5800 5500 TEMPERATURES 912 ULS Max Cylinder Head Temperature max CHT 150 C 135 min Max Oil temperature 50 140 C 50 130 C Oil normal operating temperature approx 90 110 OIL PRESSURE
30. nute Meters per second Kilometers hour Knots Pounds sq in Atmosphere Nautical miles Kilometers Feet Meters Inches Centimeters U S Gallons Liters Square feet Square meters Doc n 92 13 030 00 COSTRUZIONI AERONAUTICHE P92 Classic Detuse FLIGHT MANUAL LIMITATIONS SECTION 2 LIMITATIONS TABLE OF CONTENTS REENEN 2 AIRSPEEPLEDWETATIONS eege ee 2 AIRSPEED INDICATOR MARKINGS secteur erection tiet 3 POWERPLANT cauce E QNNM qt UR LR d 4 Ee 5 POWERPLANT INSTRUMENT MARKINGS eene 6 OTHER INSTRUMENT ee 7 EEN 7 CENTER OF GRAVITY LIMITS 7 APPROVED MANEUVERS EE 7 DURI e 8 I edition 23 March 2009 Doc n 92 13 030 00 2 1 COSTRUZIONI AERONAUTICHE P92 Classic Detuse FLIGHT MANUAL LIMITATIONS INTRODUCTION Section 2 includes operating limitations instrument markings and basic placards necessary for safe operation of the P92 CLASSIC peLuxe their engines standard systems and standard equipment AIRSPEED LIMITATIONS Rotax 912 UL ULS SPEED Km h IAS REMARKS Never exceed this speed in any operation Never exceed this speed unless in smooth air and then only with caution Do not make full or abrupt control move ments above this speed as this may cause stress in excess of limit load factor VEE Maximum flap extended 110 Never exceed this speed for any given flap speed setti
31. ooling water cooled heads and air cooled cylinders twin carburetors integrated re duction gear 2 273 1 with torque damper Com pression ratio 9 0 1 80hp 59 6 kW at 5800 rpm max 5 min Propeller for 912 UL Tonini Giancarlo amp Felice S n c GT 2 166 VSU FW 101 SRTC 2 1660 mm Fixed pitch wood Doc n 92 13 030 00 P92 Classic Detluse GENERAL Rotax 912 ULS Bombardier Rotax GmbH Four cylinder horizontally opposed twins with overall displacement of 1352 c c mixed cooling water cooled heads and air cooled cylinders twin carburetors integrated re duction gear 2 4286 1 with torque damper Com pression ratio 10 3 1 100 hp 73 5 kW at 5800 rpm max 5 min Propeller for 912 ULS F lli Tonini Giancarlo amp Felice S n c GT 2 173 VRR FW 101 SRTC 2 1730 mm Fixed pitch wood COSTRUZIONI AERONAUTICHE lt lt FUEL Fuel grade Fuel tanks Capacity of each wing tank Total capacity OIL Oil system Oil Oil Capacity COOLING Cooling system Coolant I edition 23 March 2009 FLIGHT MANUAL Rotax 912 UL Min RON 90 EN 228 Regular EN 228 Premium EN 228 Premium plus AVGAS 100 LL P92 Classic Detluse GENERAL Rotax 912 ULS Min RON 95 EN 228 Premium EN 228 Premium plus AVGAS 100 LL 2 wing tanks integrated within the wing s leading edge with drainage reservoir located in engine c
32. owling 45 litres 90 litres See Rotax Operator s Manual for more details Forced with external oil reservoir Lubricant specifications and grade are detailed into the Rotax Operator s Manual and in its re lated documents Max 3 0 liters min 2 0 litres Mixed air and liquid pressurized closed circuit system Coolant type and specifications are detailed into the Rotax Operator s Manual and in its related documents Doc n 92 13 030 00 1 6 COSTRUZIONI AERONAUTICHE P92 Classic WEIGHTS Maximum takeoff 450 kg Standard empty weight 289kg SPECIFIC LOADINGS Rotax 912 UL Rotax 912 ULS Wing Loading 34 2 kg m 34 2 kg m Power Loading 5 5 kg hp 4 5 kg hp I edition 23 March 2009 Doc n 92 13 030 00 1 7 COSTRUZIONI AERONAUTICHE P92 Classic TECNAM FLIGHT MANUAL GENERAL ABBREVIATIONS AND TERMINOLOGY AIRSPEED TERMINOLOGY AND SYMBOLS CAS Calibrated Airspeed is indicated airspeed corrected for position and instrument error IAS Indicated Airspeed is the speed shown on the on board airspeed in dicator TAS True Airspeed is calibrated airspeed corrected for altitude and tem perature Vre Maximum Flap Extended Speed is the highest speed permissible with wing flaps in a prescribed extended position Maximum Structural Cruising Speed is the speed that should not be exceeded except in smooth air then only with caution Nur Nev
33. pull out second hinge pin remove cowling with downward motion V For installation follow reverse procedure I edition 23 March 2009 Doc n 92 13 030 00 4 2 AERONAUTICHE P92 Classic Deluse PREFLIGHT INSPECTION Before each flight it is necessary to carry out a complete inspection of the aircraft as hereby detailed CABIN INSPECTION A Weight and balance check if within limits B Safety belts used to lock controls free C Flight controls activate flight controls to insure unhindered movement of control rods and surfaces D Parking brake engage E Master switch ON F Check generator switch is illuminated and ammeter is operational G Flaps control activate control to full extension checking end travel and instrument indication H Trim control activate control to full scale checking end travel and instrument indica tion I Master switch OFF J Fuel level check level on the basis of flight plan EXTERNAL INSPECTION To carry out the external inspection it will be necessary to follow the checklist below with the station order outlined in fig 4 1 A Left side tank cap Check proper fastening B Left fuel tank blow out plug check for obstructions C Remove protection cap and check pitot is unobstructed do not blow inside vents place protection cap inside aircraft Leading edge and wing skin check integrity Left aileron check integrity and unhindered movement Left flap and hinges check integrity
34. r switch ON II Both fuel taps ON III Engine throttle to idle IV Choke as needed V Magnetos switch to ON VI Prop area free VII Ignition key set to START VIII Engine RPM 2000 2500 RPM IX Choke OFF X Check engine instruments XI Check oil pressure rise maximum value cold 7 bar BEFORE TAXING I and utilities ON Altimeter reset III Navigation lights as required TAXING I Brakes check operation IL Flight instruments check operation I edition 23 March 2009 Doc n 92 13 030 00 4 6 COSTRUZIONI AERONAUTICHE P92 Classic TECNAM FLIGHT MANUAL womarocrbuts HOLDING I Parking brake ON II Turn on navigation lights strobe light and landing light optional equip ment Check engine parameters Oil pressure 2 0 5 0 bar IV Check ammeter to insure alternator is charging V Engine s rpm at 4000 RPM and test magnetos VI Visual check of fuel indicators Flaps at 15 takeoff Stick free and zero trim IX Seat belts fastened and doors secured TAKEOFF AND CLIMB I Control Tower for takeoff II Check for clear final and wind on runway Parking brake OFF full throttle IV Carburetor heat OFF V Taxi to line up VI Rotation and takeoff Slight braking to stop wheel spinning Flaps retracted IX Landing light OFF X Trim adjustment XI Establish climb rate I edition 23 March 2009 Doc n 92 13
35. rottle to minimum full outward position Activate rudder bar by pushing foot opposite spin direction Push control stick full forward and keep in position until spin is halted Center rudder bar Gradually recover flight attitude easing back on the control stick avoiding to exceed Vyg and maximum load factor Readjust throttle to restore engine power OS MS gt I edition 23 March 2009 Doc n 92 13 030 00 3 4 COSTRUZIONI AERONAUTICHE P92 Classic Deluxe 14 MANUAL rrocenunes DEPLOYMENT OF EMERGENCY PARACHUTE optional equipment Keeping in mind that full deployment of parachute is achieved after two seconds the following procedure is recommended Try leveling aircraft as much as possible Minimum altitude for successful deployment is about 33m 100 ft Pull firing clip firmly and to end travel Shut off fuel valves magnetos and master switch Tighten safety belt and helmet chinstrap Release door safety lock and unlatch doors Assume tucked position before touch down This altitude is only representative successful deployment depends on aircraft attitude and speed greater deployment altitude yields better chances for successful deployment I edition 23 March 2009 Doc n 92 13 030 00 3 5 COSTRUZIONI AERONAUTICHE P92 Classic 14 FLIGHT MANUAL ememr SECTION 4 NORMAL PROCEDURES TABLE OF CONTENTS EE
36. tinued and appropriate training should be provided ENGINE FAILURE Depending on the case that may apply the emergency procedure should follow the guidelines listed below ENGINE FAILURE DURING TAKEOFF RUN 1 Throttle idle fully out Brakes apply as needed Magnetos OFF Flaps retract Master switch OFF Fuel shutoff valves OFF ok S ENGINE FAILURE IMMEDIATELY AFTER TAKEOFF Locate landing area Throttle idle fully out Fuel shutoff valves OFF Magnetos OFF Flaps as needed Master switch OFF Land with wings level Ak I edition 23 March 2009 Doc n 92 13 030 00 3 2 COSTRUZIONI AERONAUTICHE P92 Classic Deluxe 14 FLIGHT MANUAL FORCED LANDING EMERGENCY LANDING WITHOUT ENGINE POWER MOON AR ot NS Set glide speed to optimal value of 110 Km h Select terrain area most suitable for emergency landing possibly upwind Fuel shutoff valves OFF Magnetos OFF Tighten safety belts release door safety lock and unlatch doors Flaps as needed When ready to land Master switch OFF POWER ON FORCED LANDING 1 Adjust descent slope 2 Extend flaps as needed 3 Select terrain area most suitable for emergency landing and flyby checking for obstacles and wind direction 4 Tighten safety belts release door safety lock and unlatch doors 5 Before touchdown fuel shutoff valves OFF 6 Flaps extended e After touchdown Magnetos OFF Master switch
37. ts CABIN HERT e Q Parking Brake Fig 7 1 INSTRUMENT PANEL THROTTLE FRICTION LOCK It is possible to adjust the engine s throttle friction by tightening appropriately the friction lock located on the dashboard near center throttle control I edition 23 March 2009 Doc n 92 13 030 00 7 3 COSTRUZIONI AERONAUTICHE P92 Classic Deluxe FLIGHT MANUAL SYSTEMS SEATS AND SAFETY HARNESS Aircraft features three point fitting safety belts with waist and diagonal straps ad justable via a sliding metal buckle Seats on the P92 can be of two types e Standard seats are fiberglass with easily removable cushions Seats may be ad justed on ground by operating on the latch mechanism located below seating cushion Optional seats type J are built with light alloy tube structure and synthetic ma terial cushioning A lever located on the right lower side of each seat allows ad justment of seat position according to pilot size DOORS Doors are equipped with handles on both sides of doors and left side external door handle is equipped with a door lock An internal safety latch mechanism is positioned in proximity of door s upper edge and must be used before flight to secure door Mechanism rotates to engage door frame to cabin tubular framework BAGGAGE COMPARTMENT The baggage compartment is located behind the pilots seats Baggage shall be uniformly distributed on utility shelf ENGINE gt Rotax 9
38. wing strut attachments and anchoring shall be provided by ramp tie downs Nose gear fork can be used for front tie down lo cation Flight controls shall be secured to avoid possible weathervaning to end travel damage of moving surfaces For this purpose seatbelts may be used to latch con trol stick to prevent its movement I edition 23 March 2009 Doc n 92 13 030 00 8 2 P92 Classic Deluxe COSTRUZIONI AERONAUTICHE GROUND HANDLING FLIGHT MANUAL AND SERVICE JACKING Given the light empty weight lifting one of the main wheels can easily be ac complished even without the use of hydraulic jacks It is in fact sufficient that while one person lifts one half wing by acting on the spar immediately before the wingtip another person places a suitable stand below the steel spring attachment LEVELING Aircraft leveling may become necessary to check wing incidence dihedral or the exact location of CG Leveling is obtained when the lower cabin edge and the main gear support beam are horizontal ROAD TRANSPORT It is recommended to secure tightly all aircraft components onto the cart to avoid damage during transport Minimum cart size are 7x2 5 meters It is suggested to place wings under the aircraft s bottom secured by specific clamps Secondary components such as stabilators and struts shall be protected from accidental hits using plastic or other material For correct rigging and derigging procedure refer to Servi
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