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edition – 23

March 2009 Doc. n° 92-13-030-00

i-1

P92Classic

Deluxe

I N TRODUCTI ON

LIGHT MANUAL

FLIGHT MANUAL

P92 Echo C

LASSIC

Deluxe

ANUFACTURER

COSTRUZIONI AERONAUTICHE

TECNAM

S.r.l.

IRCRAFT TYPE

P92 C

LASSIC

deluxe

ERIAL NUMBER

:...............................................................

ANUFACTURING DATE

:....................................................

WARNING

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.

HIS MANUAL IS VALID FOR THE

P92

LASSIC

DELUXE

WITH EITHER

OTAX

912

HP ENGINE OR

OTAX

912ULS

100

P ENGINE

OR 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

Содержание P92 Echo Classic Deluxe

Страница 1: ... 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 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 WIT...

Страница 2: ...ta 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 Rev N Affected Sections Affected Pages Date Date inserted ...

Страница 3: ...ection Page Date 0 i 1 23th March 2009 4 4 1 23th March 2009 i 2 4 2 i 3 4 3 i 4 4 4 i 5 4 5 4 6 4 7 1 1 1 23th March 2009 4 8 1 2 1 3 1 4 1 5 1 6 5 5 1 23th March 2009 1 7 5 2 1 8 5 3 1 9 5 4 1 10 5 5 1 11 5 6 5 7 5 8 2 2 1 23th March 2009 2 2 2 3 6 6 1 23th March 2009 2 4 6 2 2 5 6 3 2 6 6 4 2 7 2 8 3 3 1 23th March 2009 3 2 3 3 3 4 3 5 ...

Страница 4: ...dition 23th March 2009 Doc n 92 13 030 00 i 4 P92Classic Deluxe INTRODUCTION FLIGHT MANUAL Section Page Date Section Page Date 7 7 1 23th March 2009 7 2 7 3 7 4 7 5 7 6 8 8 1 23th March 2009 8 2 8 3 8 4 8 5 ...

Страница 5: ...xe INTRODUCTION FLIGHT MANUAL 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 ...

Страница 6: ...0 1 1 SECTION 1 GENERAL TABLE OF CONTENTS INTRODUCTION 2 WARNINGS CAUTIONS NOTES 2 THREE VIEW DRAWING 2 DESCRIPTIVE DATA 3 CONTROL SURFACES TRAVEL LIMITS 4 ENGINE 5 PROPELLER 5 FUEL 6 OIL 6 COOLING 6 WEIGHTS 7 SPECIFIC LOADINGS 7 ABBREVIATIONS AND TERMINOLOGY 8 UNIT CONVERSION FACTORS 11 ...

Страница 7: ...logy commonly used WARNINGS CAUTIONS NOTES The following definitions apply to warnings cautions and notes used in the Flight Manual means that the non observation of the corresponding procedure leads to an immediate or important degrada tion of the flight safety means that the non observation of the corresponding procedure leads to a minor or to a more or less long term degradation of the flight s...

Страница 8: ...P92 Classic Deluxe GENERAL FLIGHT MANUAL 1st edition 23th March 2009 Doc n 92 13 030 00 1 3 ...

Страница 9: ...tio 1 0 Dihedral 1 5 FUSELAGE Overall length 6 5 m Overall width 1 1 m Overall height 2 5 m EMPENNAGE Stabilator span 2 9 m Vertical tail span 1 23 m LANDING GEAR Wheel track 1 8 m Wheel base 1 6 m Main gear tire Air Trac Wheel hub and brake Marc Ingegno 5 00 5 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 2 12 1 Rudder RS 25 ...

Страница 10: ...ession ratio 9 0 1 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 Maximum power 80hp 59 6 kW at 5800 rpm max 5 min 100 hp 73 5 kW at 5800 rpm max 5 min PROPELLER Propeller for 912 UL Propeller for 912 ULS Manufac...

Страница 11: ...ge reservoir located in engine cowling Capacity of each wing tank 45 litres Total capacity 90 litres See Rotax Operator s Manual for more details OIL Oil system Forced with external oil reservoir Oil Lubricant specifications and grade are detailed into the Rotax Operator s Manual and in its re lated documents Oil Capacity Max 3 0 liters min 2 0 litres COOLING Cooling system Mixed air and liquid pr...

Страница 12: ...HT MANUAL 1st edition 23th March 2009 Doc n 92 13 030 00 1 7 WEIGHTS Maximum takeoff 450 kg Standard empty weight 289kg SPECIFIC LOADINGS Rotax 912 UL Rotax 912 ULS Wing Loading 34 2 kg m2 34 2 kg m2 Power Loading 5 5 kg hp 4 5 kg hp ...

Страница 13: ...e speed that should not be exceeded except in smooth air then only with caution VNE Never Exceed Speed is the speed limit that may not be exceeded at any time VS Stalling Speed VS0 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 ...

Страница 14: ...CE AND FLIGHT PLANNING TERMINOLOGY Crosswind Velocity is the velocity of the crosswind component for which adequate con 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 a...

Страница 15: ...total moment by the total weight of the airplane Standard Empty Weight is the weight of a standard airplane including unusable fuel full oper ating fuels and full engine oil Basic Empty Weight is the standard empty weight plus the weight of optional equipment Useful Load is the difference between takeoff weight and the basic empty weight Maximum Weight is the maximum weight of the aircraft Maximum...

Страница 16: ...te ft min 0 00508 Meters per second m s Knots kts 1 853 Kilometers hour km h Kilometers hour km h 0 5396 Knots kts PRESSURE Atmosphere atm 14 7 Pounds sq in psi Pounds sq in psi 0 068 Atmosphere atm LENGTH Kilometers km 0 5396 Nautical miles nm Nautical miles nm 1 853 Kilometers km Meters m 3 281 Feet ft Feet ft 0 3048 Meters m Centimeters cm 0 3937 Inches in Inches in 2 540 Centimeters cm VOLUME ...

Страница 17: ...030 00 2 1 SECTION 2 LIMITATIONS TABLE OF CONTENTS INTRODUCTION 2 AIRSPEED LIMITATIONS 2 AIRSPEED INDICATOR MARKINGS 3 POWERPLANT LIMITATIONS 4 PROPELLER 5 POWERPLANT INSTRUMENT MARKINGS 6 OTHER INSTRUMENT MARKINGS 7 WEIGHT LIMITS 7 CENTER OF GRAVITY LIMITS 7 APPROVED MANEUVERS 7 FUEL 8 ...

Страница 18: ...rd equipment AIRSPEED LIMITATIONS Rotax 912 UL ULS SPEED Km h IAS REMARKS VNE Never exceed speed 260 Never exceed this speed in any operation VNO Maximum Structural Cruising Speed 200 Never exceed this speed unless in smooth air and then only with caution VA Maneuvering speed 150 Do not make full or abrupt control move ments above this speed as this may cause stress in excess of limit load factor ...

Страница 19: ...RKING 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 110 200 Normal Operating Range lower limit is VFE at maxi mum weight and upper limit is maximum structural speed VNO Yellow arc 200 260 Operations must be conducted with caution and only in smooth air Red line 260 Ma...

Страница 20: ... Power kW hp Max RPM 912UL 912 ULS 912UL 912 ULS Maximum max 5 minutes 59 6 80 73 5 100 5800 5500 Maximum continuous 58 76 69 93 5800 5500 TEMPERATURES 912 UL 912 ULS Max Cylinder Head Temperature max CHT 150 C 135 C min Max Oil temperature 50 140 C 50 130 C Oil normal operating temperature approx 90 110 C OIL PRESSURE 912 UL 912 ULS Minimum below 3500 rpm eng 0 8 bar Normal above 3500 rpm eng 2 0...

Страница 21: ...il with or without additives is not permitted COOLANT Coolant type and specifications are detailed into the Rotax Operator s Manual PROPELLER PROPELLER FOR Rotax 912 UL Rotax 912 ULS MANUFACTURER F lli Tonini Giancarlo Felice F lli Tonini Giancarlo Felice MODEL GT 2 166 VSU FW 101 SRTC GT 2 173 VRR FW 101 SRTC PROP TYPE Wood twin blade fixed pitch Wood twin blade fixed pitch DIAMETER 1660 mm 1730 ...

Страница 22: ...n RED LINE Maximum limit Engine tachometer RPM 1400 5500 5500 5800 5800 Oil Temp C 50 90 110 50 90 110 140 140 Cylinder heads temper ature CHT C 75 150 150 Oil pressure bar 0 8 2 0 5 0 0 8 2 0 5 0 7 0 7 0 Rotax 912 ULS INSTRUMENT RED LINE Minimum limit GREEN ARC Normal operating YELLOW ARC Caution RED LINE Maximum limit Engine tachometer RPM 1400 5500 5500 5800 5800 Oil Temp C 50 90 110 50 90 110 ...

Страница 23: ...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 è intended for non aerobatic operation only Non aerobatic operation includes Any maneuver pertaining to normal flight Stalls except whip stalls Lazy eights Chandelle...

Страница 24: ...TANKS 45 litres TOTAL FUEL CAPACITY 90 litres Rotax 912 UL APPROVED FUELS Min RON 90 EN 228 Regular EN 228 Premium EN 228 Premium plus AVGAS 100LL refer to the Rotax Operator s Maunal Rotax 912 ULS APPROVED FUELS Min RON 95 EN 228 Premium EN 228 Premium plus AVGAS 100LL refer to the Rotax Operator s Maunal ...

Страница 25: ...1st edition 23th March 2009 Doc n 92 13 030 00 3 1 SECTION 3 EMERGENCY PROCEDURES TABLE OF CONTENTS INTRODUCTION 2 ENGINE FAILURE 2 FORCED LANDING 3 SMOKE AND FIRE 3 RECOVERY FROM UNINTENTIONAL SPIN 4 DEPLOYMENT OF EMERGENCY PARACHUTE optional equipment 5 ...

Страница 26: ...problem Before operating the aircraft the pilot should become thoroughly familiar with the present manual and in particular with the present section Further a continued 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 2 Brakes ...

Страница 27: ... 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 7 After touchdown Magnetos OFF Master switch OFF SMOKE AND FIRE ENGINE FIRE WHILE PARKED OR DURING TAKEOFF 1 Fuel shutoff valves OFF 2 Abort takeoff if p...

Страница 28: ...ded 6 Carry out forced landing emergency procedure 7 Master switch OFF 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 Land as soon as possible RECOVERY FROM UNINTENTIONAL SPIN In case of unintentional spin entry follow the emergency procedure described below 1 Adjust throttle to mini...

Страница 29: ...ircraft as much as possible 2 Minimum altitude for successful deployment is about 33m 100 ft 1 3 Pull firing clip firmly and to end travel 4 Shut off fuel valves magnetos and master switch 5 Tighten safety belt and helmet chinstrap 6 Release door safety lock and unlatch doors 7 Assume tucked position before touch down 1 This altitude is only representative successful deployment depends on aircraft...

Страница 30: ... NORMAL PROCEDURES FLIGHT MANUAL 1st edition 23th March 2009 Doc n 92 13 030 00 4 1 SECTION 4 NORMAL PROCEDURES TABLE OF CONTENTS INTRODUCTION 2 RIGGING AND DERIGGING ENGINE COWLING 2 PREFLIGHT INSPECTION 3 CHECKLISTS 6 ...

Страница 31: ...o 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 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 ...

Страница 32: ...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 ...

Страница 33: ...or nicks and fastening T Open engine cowling and perform the following checklist I Check no foreign objects are present II Check the cooling circuit for losses from tubing check coolant reservoir lev el insure radiator honeycomb cooling fins are unobstructed III Check lubrication circuit for losses from tubing check oil reservoir level in sure radiator honeycomb cooling fins are unobstructed IV Op...

Страница 34: ...S FLIGHT MANUAL 1st edition 23th March 2009 Doc n 92 13 030 00 4 5 Z Remove tow bar and chocks NOTE Avoid blowing inside left strut mounted pitot and inside airspeed indicator sys tem s static vents as this may damage instruments FIG 4 1 ...

Страница 35: ...ment IV Doors secured V Parking brake ON STARTING ENGINE I Master 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 Radio and utilities ON II Altimeter reset III ...

Страница 36: ...ar IV Check ammeter to insure alternator is charging V Engine s rpm at 4000 RPM and test magnetos VI Visual check of fuel indicators VII Flaps at 15 takeoff VIII 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 III Parking brake OFF full throttle IV Carburetor heat OFF V Taxi to line up VI Ro...

Страница 37: ...uel 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 VIII Turn off landing light navigation lights and strobe light ENGINE SHUT DOWN ...

Страница 38: ... edition 23th March 2009 Doc n 92 13 030 00 5 1 SECTION 5 PERFORMANCE TABLE OF CONTENTS INTRODUCTION 2 AIRSPEED CALIBRATION 3 STALL SPEEDS 3 CROSSWIND 4 TAKEOFF PERFORMANCE 5 LANDING 6 CLIMB PERFORMANCE 7 CRUISE 8 CONSEQUENCES FROM RAIN AND INSECT 8 ...

Страница 39: ...nning of flight activity from takeoff to landing Data reported in graphs and or tables were determined using aircraft and engine in good condition average piloting techniques Each graph or table was determined according to ICAO Standard Atmos phere ISA m s l evaluations of the impact on performance was carried out by theoretical means for airspeed external temperature altitude weight ...

Страница 40: ...RATION 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 0 30 45 60 FLAPS IAS Km h IAS Km h IAS Km h IAS Km h 0 74 78 84 101 15 69 76 79 97 35 64 69 76 91 ...

Страница 41: ...HT MANUAL 1st edition 23th March 2009 Doc n 92 13 030 00 5 4 CROSSWIND Maximum demonstrated crosswind velocity is 15 Kts Example Given Find Wind direction 30 Headwind 17 5 Kts Wind velocity 20 Kts Crosswind 10 Kts Fig 5 1 CROSSWIND CHART ...

Страница 42: ...e PERFORMANCE FLIGHT MANUAL 1st edition 23th March 2009 Doc n 92 13 030 00 5 5 TAKEOFF PERFORMANCE TAKEOFF DISTANCE CONDITIONS ISA Flaps 15 Engine full throttle Slope 0 Wind zero Runway dry compact grass Fig 5 2 TAKEOFF ...

Страница 43: ...NDING GROUND ROLL DISTANCE AND LANDING DISTANCE CONDITIONS Flaps 35 Runway dry compact grass Engine throttle idle Slope 0 Wind zero Distance over a 15 m obstacle Fig 5 3 LANDING 0 50 100 150 200 250 300 400 410 420 430 440 450 460 470 480 490 500 WEIGHT Kg Ground roll Distance m Ground roll DISTANCE ...

Страница 44: ...MANCE CLIMB RATE IN CLEAN CONFIGURATION CONDITIONS ISA Flaps 0 Weight 450 kg Engine full throttle Fig 5 4 CLIMB RATE Rotax 912 UL VY 120 Km h Rotax 912 ULS VY 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 ...

Страница 45: ...RPM CAS km h Hourly consumption lt h 4300 155 13 4800 170 14 5000 180 16 Rotax 912 ULS RPM CAS km h Hourly consumption lt h 4300 165 14 4800 180 18 5000 196 20 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 ...

Страница 46: ...sic Deluxe WEIGHT BALANCE FLIGHT MANUAL 1st edition 23th March 2009 Doc n 92 13 030 00 6 1 SECTION 6 WEIGHT BALANCE TABLE OF CONTENTS INTRODUCTION 2 AIRCRAFT WEIGHING PROCEDURES 2 WEIGHING REPORT 3 C G TRAVEL 4 ...

Страница 47: ...retracted 0 h Control surfaces in neutral position i Place scales min capacity 200 kg under each wheel LEVELING a Level the aircraft using cabin 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 no...

Страница 48: ...upport flange without spacer Kg meters Nose wheel weight W1 Plumb bob distance from LS wheel AL LS wheel weight WL Plumb bob distance from RS wheel AR RS wheel weight WR Average distance AL AR 2 A W2 WL WR Bob distance from nose wheel B Empty weight We W1 W2 D W A W B We 2 1 m D D 14 100 Empty weight moment M D 1 39 We Kg m Maximum takeoff weight WT 450 kg Empty weight We Maximum useful load WT We...

Страница 49: ...3th March 2009 Doc n 92 13 030 00 6 4 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 cause aircraft tail to lower ...

Страница 50: ...92 13 030 00 7 1 SECTION 7 AIRPLANE AND SYSTEM DESCRIPTIONS TABLE OF CONTENTS INTRODUCTION 2 AIRFRAME 2 FLIGHT CONTROLS 2 INSTRUMENT PANEL 3 SEATS AND SAFETY HARNESS 4 DOORS 4 BAGGAGE COMPARTMENT 4 ENGINE 4 FUEL SYSTEM 5 ELECTRICAL SYSTEM 5 AIRSPEED INDICATOR SYSTEM 6 BRAKES 6 ...

Страница 51: ...in 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 enti...

Страница 52: ...d 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 Fig 7 1 INSTRUMENT PANEL THROTTLE FRICTION LOCK It is possible to ad...

Страница 53: ...wer 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 framewor...

Страница 54: ...irewall 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 tailc...

Страница 55: ...t 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 necess...

Страница 56: ...RVICE FLIGHT MANUAL 1st edition 23th March 2009 Doc n 92 13 030 00 8 1 SECTION 8 GROUND HANDLING AND SERVICE TABLE OF CONTENTS INTRODUCTION 2 AIRPLANE INSPECTION PERIODS 2 GROUND HANDLING 2 GROUND ROUND ANCHORAGE Optional 4 CLEANING AND CARE 5 ...

Страница 57: ...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...

Страница 58: ...nt 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 t...

Страница 59: ...on The following procedures should be used for the proper mooring of the airplane 1 Head the airplane into the wind if possible 2 Retract the flaps 3 Chock the wheels 4 Lock the control stick using safety belts 5 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 Tie Down Ring Tie Down Rope Tie...

Страница 60: ...ed 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 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 dete...

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