FLIGHT MANUAL P2002-JF

Noise Certification Basis: EASA CS-36 1st edition dated 17th October 2003, with reference to ICAO/Annex 16 3rd edition dated 1993, Vol.1 Chapter 10. 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 degradation 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 safety. Draws the attention to any special item not directly related to safety but which is important or unusual. WARNING CAUTION NOTE FLIGHT M ANUAL P2002-JF S E C T I O N 1 G e n e r a l 1 st Edition – 29th March 2004 1-3 THREE-VIEW DRAWING • Dimensions shown refer to aircraft weight of 580 kg and normal operating tire pressure. • Propeller ground clearance 320mm • Propeller ground clearance with deflated front tire and nosewheel shock absorber compressed by 102mm • Minimum ground steering radius 5.5m NOTE 8.6 m 6.61 m 2.43 m FLIGHT M ANUAL P2002-JF S E C T I O N 1 G e n e r a l 1 st Edition – 29th March 2004 1-4 DESCRIPTIVE DATA WING Wing span: 8.6 m Wing surface 11.5 m2 Wing loading 50.4 kg/m2 Aspect ratio 6.4 Taper ratio 0.6 Dihedral 5° FUSELAGE Overall length 6.61 m Overall width 1.11 m Overall height 2.43 m EMPENNAGE Stabilator span 2.90 m Vertical tail span 1.10 m LANDING GEAR Wheel track: 1.85 m Wheel base: 1.62 m Main gear tires: Air Trac 5.00-5 Wheel hub and brakes: Cleveland 199-102 Nose gear tire: Sava 4.00-6 CONTROL SURFACES TRAVEL LIMITS Ailerons Up 20° down 15 ° ± 2° Stabilator Up 15° down 3° ± 1° Trim-Tab 2° ; 9° ± 1° Rudder RH 30° LH 30° ± 2° Flaps 0°; 40° ± 1° FLIGHT M ANUAL P2002-JF S E C T I O N 1 G e n e r a l 1 st Edition – 29th March 2004 1-5 ENGINE Manufacturer: Bombardier-Rotax GmbH Model 912 S2 Certification basis FAR 33 Amendment 15 Austrian T.C. No. TW 9-ACG dated 27th November 1998 Type: 4 cylinder horizontally-opposed twins with overall displacement of 1352 c.c., mixed cooling, (water-cooled heads and air-cooled cylinders), twin carburettors, integrated reduction gear with torque damper. Maximum power: 73.5 kW (98.5 hp) @ 5800 rpm (max. 5’) 69.0 kW (92.5 hp) @ 5500 rpm (cont.) PROPELLER Manufacturer: Hoffmann Propeller Certification Basis CAR Part 14 Type Certificate No. SO/E 30 dated 10 December 1999 Model: HO17GHM A 174 177 C Number of blades: 2 Diameter: 1740 mm (no reduction permitted) Type: Fixed pitch – wood FLIGHT M ANUAL P2002-JF S E C T I O N 1 G e n e r a l 1 st Edition – 29th March 2004 1-6 FUEL Fuel grade: • Min. RON 95 • EN 228 Premium • EN 228 Premium plus • AVGAS 100LL (see Section 2 page 11) Fuel tanks: 2 wing tanks integrated within the wing’s leading edge. Equipped with finger strainers outlet and with drain fittings. Capacity of each wing tank 50 liters Total capacity: 100 liters Total usable fuel 99 litres OIL SYSTEM Oil system type: Forced, with external oil reservoir Oil: Lubricant specifications and grade are detailed into the “Rotax Operator’s Manual” and in its related documents. Oil Capacity: Max. 3.0 litres – min. 2.0 liters COOLING Cooling system: Mixed air and liquid pressurized closed circuit system Coolant: Coolant type and specifications are detailed into the “Rotax Operator’s Manual” and in its related documents. 1 st revision, August 3 rd 2005 FLIGHT M ANUAL P2002-JF S E C T I O N 1 G e n e r a l 1 st Edition – 29th March 2004 1-7 MAXIMUM WEIGHTS Maximum take-off weight: 580 kg Maximum landing weight: 580 kg Maximum baggage weight 20 kg STANDARD WEIGHTS Standard Empty Weight 337 kg Maximum useful load 243 kg SPECIFIC LOADINGS Wing Loading 50.4 kg/m2 Power Loading 5.9 kg/hp FLIGHT M ANUAL P2002-JF S E C T I O N 1 G e n e r a l 1 st Edition – 29th March 2004 1-8 ABBREVIATIONS AND TERMINOLOGY GENERAL AIRSPEED TERMINOLOGY AND SYMBOLS KCAS Calibrated Airspeed is the indicated airspeed corrected for position and instrument error and expressed in knots. KIAS Indicated Airspeed is the speed shown on the airspeed indicator and expressed in knots. KTAS True Airspeed is the airspeed expressed in knots relative to undisturbed air which is KCAS corrected for altitude and temperature. V FE Maximum Flap Extended Speed is the highest speed permissible with wing flaps in a prescribed extended position. V NO Maximum Structural Cruising Speed is the speed that should not be exceeded except in smooth air, then only with caution. V NE Never Exceed Speed is the speed limit that may not be exceeded at any time. V S Stalling Speed. V S0 Stalling speed in landing configuration V S1 Stalling speed in clean configuration (flap 0°) V X Best Angle-of-Climb Speed is the speed which results in the greatest gain of altitude in a given horizontal distance. V Y 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 V LO Lift off speed: is the speed at which the aircraft generally lifts off from the ground. Vobs Obstacle speed: is the speed at which the aircraft flies over a 15m obstacle during takeoff or landing FLIGHT M ANUAL P2002-JF S E C T I O N 1 G e n e r a l 1 st Edition – 29th March 2004 1-9 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 decreased by 2°C for each 1000 ft of altitude. H P Pressure Altitude is the altitude read from an altimeter when the barometric subscale has been set to 1013 mb. ENGINE POWER TERMINOLOGY RPM Revolutions Per Minute: is the number of revolutions per minute of the propeller, multiplied by 2.4286 yields engine RPM. AIRPLANE PERFORMANCE AND FLIGHT PLANNING TERMINOLOGY Crosswind Velocity is the velocity of the crosswind component for which adequate control of the airplane during takeoff and landing is guaranteed. 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 clearing GR is the distance measured during landing from actual touchdown to stop point LD is the distance measured during landing, from 15m obstacle clearing 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 used. FLIGHT M ANUAL P2002-JF S E C T I O N 1 G e n e r a l 1 st Edition – 29th March 2004 1-10 WEIGHT AND BALANCE TERMINOLOGY Datum “Reference datum” is an imaginary vertical plane from which all horizontal distances are measured for balance purposes. Arm is the horizontal distance from the reference datum to the center of gravity (C.G.) of an item. Moment is the product of the weight of an item multiplied by its arm. C. G. Center of Gravity is the point at which the airplane, or equipment, would balance if suspended. Its distance from the reference datum is found by dividing the total moment by the total weight of the airplane. Empty Weight Empty Weight is the weight of the aeroplane with engine fluids and oil at operating levels. Useful Load is the difference between takeoff weight and the basic empty weight. Maximum Takeoff Weight is the maximum weight approved for the start of the takeoff run. Maximum Landing Weight is the maximum weight approved for the landing touch down. Tare 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. FLIGHT M ANUAL P2002-JF S E C T I O N 1 G e n e r a l 1 st Edition – 29th March 2004 1-11 UNIT CONVERSION CHART MULTIPLYING BY Î YIELDS TEMPERATURE Fahrenheit [°F] ( ) 5 9 32 ⋅ − F Celsius [°C] Celsius [°C] 9 5 32 ⋅       + C Fahrenheit [°F] FORCES Kilograms [kg] 2.205 Pounds [lbs] Pounds [lbs] 0.4536 Kilograms [kg] S PEED Meters per second [m/s] 196.86 Feet per minute [ft/min] Feet per minute [ft/min] 0.00508 Meters per second. [m/s] Knots [kts] 1.853 Kilometres / hour [km/h] Kilometres / hour [km/h] 0.5396 Knots [kts] PRESSURE Atmosphere [atm] 14.7 Pounds / sq. in [psi] Pounds / sq. in [psi] 0.068 Atmosphere [atm] LENGTH 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] V OLUME Liters [l] 0.2642 U.S. Gallons [US Gal] U.S. Gallons [US Gal] 3.785 Liters [l] A REA Square meters [m2 ] 10.76 Square feet [sq ft] Square feet [sq ft] 0.0929 Square meters [m2 ] FLIGHT M ANUAL P2002-JF S E C T I O N 1 G e n e r a l 1 st Edition – 29th March 2004 1-12 INTENTIONALLY LEFT BLANK FLIGHT M ANUAL P2002-JF S E C T I O N 2 L imitations 1 st Edition – 29th March 2004 2-1 SECTION 2 LIMITATIONS TABLE OF CONTENTS INTRODUCTION.................................................................................................... 2 AIRSPEED LIMITATIONS .................................................................................... 2 AIRSPEED INDICATOR MARKINGS.................................................................. 3 POWERPLANT LIMITATIONS ............................................................................ 4 LUBRICANT........................................................................................................... 5 COOLANT............................................................................................................... 6 PROPELLER ........................................................................................................... 6 POWERPLANT INSTRUMENT MARKINGS ...................................................... 7 OTHER INSTRUMENT MARKINGS.................................................................... 7 WEIGHTS................................................................................................................ 8 CENTER OF GRAVITY RANGE........................................................................... 8 APPROVED MANEUVERS ................................................................................... 9 MANEUVERING LOAD FACTOR LIMITS ......................................................... 9 FLIGHT CREW ..................................................................................................... 10 KINDS OF OPERATION ...................................................................................... 10 FUEL...................................................................................................................... 11 MAXIMUM PASSENGER SEATING ................................................................. 11 DEMONSTRATED CROSS WIND SAFE OPERATIONS ................................. 11 LIMITATION PLACARDS................................................................................... 12 FLIGHT M ANUAL P2002-JF S E C T I O N 2 L imitations 1 st Edition – 29th March 2004 2-2 INTRODUCTION Section 2 includes operating limitations, instrument markings, and basic placards necessary for safe operation of the P2002-JF, its engine and standard systems and equipment. AIRSPEED LIMITATIONS Airspeed limitations and their operational significance are shown below: SPEED KIAS KCAS REMARKS VNE Never exceed speed 138 135 Never exceed this speed in any operation. VNO Maximum Structural Cruising Speed 110 106 Never exceed this speed unless in smooth air, and then only with caution. VA Manoeuvring speed 96 94 Do not make full or abrupt control movements above this speed as this may cause stress in excess of limit load factor VFE Maximum flap extended speed 67 69 Never exceed this speed for any flap setting. FLIGHT M ANUAL P2002-JF S E C T I O N 2 L imitations 1 st Edition – 29th March 2004 2-3 AIRSPEED INDICATOR MARKINGS Airspeed indicator markings and their colour code are explained in the following table. Refer to section 9 of this Flight Manual for operational limitations for aircraft fitted with optional equipment. MARKING KIAS (knots) SIGNIFICANCE White arc 26 - 67 Positive Flap Operating Range (lower limit is VSO , at maximum weight and upper limit is the maximum speed permissible with flaps extension) Green arc 39 - 110 Normal Operating Range (lower limit is VS1 at maximum weight and most forward c.g. with flaps retracted and upper limit is maximum structural speed V NO ). Yellow arc 110 - 138 Manoeuvres must be conducted with caution and only in smooth air. Red line 138 Maximum speed for all operations. FLIGHT M ANUAL P2002-JF S E C T I O N 2 L imitations 1 st Edition – 29th March 2004 2-4 POWERPLANT LIMITATIONS The following table lists operating limitations for aircraft installed engine: ENGINE MANUFACTURER : Bombardier Rotax GmbH. ENGINE MODEL: 912 S2 MAXIMUM POWER : (see table below) Max Power kW (hp) Max rpm. rpm prop.(engine) Time max. (min.) Max. 73.5 (98.5) 2388 (5800) 5 Max cont. 69 (92.5) 2265 (5500) - With full throttle, at fixed point in no wind conditions, the maximum propeller’s rpm should be 2100 ± 100. TEMPERATURES: Max cylinder heads 135° C Max. / min. Oil 50° C / 130° C Oil normal operating temperature (approx.) 90° C – 110° C OIL PRESSURE: Min 0.8 bar (below 1400 rpm prop.) Normal 2.0 - 5.0 bar (above 1400 rpm prop.) ENGINE START, OPER. TEMP: OAT Min -25° C OAT Max +50° C NOTE 1 st revision, August 3 rd 2005 FLIGHT M ANUAL P2002-JF S E C T I O N 2 L imitations 1 st Edition – 29th March 2004 2-5 Admissible pressure for cold start is 7 bar maximum for short periods. FUEL PRESSURE: Min 2.2 psi (0.15 bar) Max 5.8 psi (0.40 bar) LUBRICANT VISCOSITY Use viscosity grade oil as specified in the following table: Use of Aviation Grade Oil with or without additives is not permitted WARNING WARNING FLIGHT M ANUAL P2002-JF S E C T I O N 2 L imitations 1 st Edition – 29th March 2004 2-6 COOLANT Coolant type and specifications are detailed into the “Rotax Operator’s Manual” and in its related documents. PROPELLER MANUFACTURER : Hoffmann Propeller GmbH MODEL: HO17GHM A 174 177 C P ROPELLER TYPE: Wood twin blade fixed pitch DIAMETER : 1740 mm (no reduction permitted) 1 st revision, August 3 rd 2005 FLIGHT M ANUAL P2002-JF S E C T I O N 2 L imitations 1 st Edition – 29th March 2004 2-7 POWERPLANT INSTRUMENT MARKINGS Powerplant instrument markings and their colour code significance are shown below: INSTRUMENT RED LINE Minimum limit GREEN ARC Normal operating YELLOW ARC Caution RED LINE Maximum limit Prop. tach rpm ---- 580 - 2265 2265 - 2388 2388 Oil Temp. °C 50 90 - 110 50 - 90 110 - 130 130 Cylinder heads temp. °C ---- 0 - 135 ---- 135 Oil pressure bar 0.8 2 – 5 0.8 – 2 5 – 7 (1) 7 Fuel press. psi 2.2 2.2 – 5.8 ---- 5.8 Fuel q.ty litres ---- (2) ---- ---- ---- OTHER INSTRUMENT MARKINGS INSTRUMENT RED LINE Minimum limit GREEN ARC Normal operating YELLOW ARC Caution RED LINE Maximum limit Voltmeter 10 Volt 12 - 14 Volt ---- ---- Suction gage 4.0 in. Hg 4.5 – 5.5 in. Hg ---- ---- 1 Admissible pressure for cold start is 7 bar maximum for short periods. 2 The unusable fuel quantity for each tank is 0.5 litres FLIGHT M ANUAL P2002-JF S E C T I O N 2 L imitations 1 st Edition – 29th March 2004 2-8 WEIGHTS Maximum takeoff weight: 580 kg Maximum landing weight: 580 kg Maximum zero fuel weight. 580 kg Maximum baggage weight: 20 kg (2.26m aft from datum) CENTER OF GRAVITY RANGE Datum Propeller support flange without spacer Ref. for levelling Seat track supporting trusses (ref. to sect.6 for the procedure) Forward limit 1.693 m (26.0% MAC) aft of datum for all weights Aft limit 1.782 m (32.5% MAC) aft of datum for all weights It is the pilot's responsibility to insure that the airplane is properly loaded. Refer to section 6 for appropriate instructions. WARNING FLIGHT M ANUAL P2002-JF S E C T I O N 2 L imitations 1 st Edition – 29th March 2004 2-9 WARNING APPROVED MANEUVERS This aircraft is certified in normal category under EASA CS-VLA. CS-VLA applies to aeroplanes intended for non-aerobatic operation only. Non aerobatic operation includes: • Any manoeuvre pertaining to “normal” flight • Stalls (except whip stalls) • Lazy eights • Chandelles • Turns in which the angle of bank is not more than 60° Acrobatic manoeuvres, including spins, are not approved. Recommended entry speeds for each approved manoeuvre are as follows: M ANOEUVRE Speed (KIAS) Lazy eight 96 Chandelle 110 Steep turn (max 60°) 96 Stall Slow deceleration (1 kts/s) Limit load factor could be exceeded by moving abruptly flight controls at their end run at a speed above VA (96 KIAS, Manoeuvring Speed). MANEUVERING LOAD FACTOR LIMITS Manoeuvring load factors are as follows: FLAPS 0° +3.8 - 1.9 40° +1.9 0 FLIGHT M ANUAL P2002-JF S E C T I O N 2 L imitations 1 st Edition – 29th March 2004 2-10 FLIGHT CREW Minimum crew for flight is one pilot seated on the left side. KINDS OF OPERATION The airplane, in standard configuration, is approved only for day VFR operation with terrain visual contact. Minimum equipment required is as follows: • Altimeter • Airspeed Indicator • Heading Indicator • Fuel Gauges • Oil Pressure Indicator • Oil Temp. Indicator • Cylinder Heads Temp. Indicator • Outside Air Temp. indicator • Tachometer • Chronometer • First Aid Kit • Hand-held fire extinguisher • Emergency hammer For further standard equipment refer to section 6. Flight into expected and/or known icing conditions is prohibited. Additional equipments may be asked to fulfill national or specific requirements. It’s a responsibility of the continued airworthiness manager to be compliant with these requirements. NOTE FLIGHT M ANUAL P2002-JF S E C T I O N 2 L imitations 1 st Edition – 29th March 2004 2-11 FUEL TWO TANKS : 50 liters each TOTAL FUEL CAPACITY : 100 liters U SABLE FUEL Q . TY: 99 litres U NUSABLE FUEL Q . TY : 0.5 litres each (1.0 litres total) Compensate uneven fuel tank levels by acting on the fuel selector valve located into the cabin. APPROVED FUEL ∗ Min. RON 95 ∗ EN 228 Premium ∗ EN 228 Premium plus ∗ AVGAS 100LL (see Warning below) Prolonged use of Aviation Fuel Avgas 100LL results in greater wear of valve seats and greater combustion deposits inside cylinders due to higher lead content. It is therefore suggested to avoid using this type of fuel unless strictly necessary. MAXIMUM PASSENGER SEATING With the exception of the pilot, only one passenger is allowed on board of this aircraft. DEMONSTRATED CROSS WIND SAFE OPERATIONS The aircraft controllability during take-offs and landings has been demonstrated with a cross wind components of 22 kts. WARNING 1 st revision, August 3 rd 2005 FLIGHT M ANUAL P2002-JF S E C T I O N 2 L imitations 1 st Edition – 29th March 2004 2-12 LIMITATION PLACARDS The following limitation placards must be placed in plain view on the aircraft. Near the airspeed indicator a placard will state the following: MANEUVERING SPEED V A=96 K IAS On the left hand side of the dashboard a placard will state the following: THIS AIRPLANE IS CLASSIFIED AS A VERY LIGHT AIRPLANE APPROVED FOR DAY VFR ONLY , IN NON - ICING CONDITIONS . A LL AEROBATIC MANEUVERS INCLUDING INTENTIONAL SPIN ARE PROHIBITED. S EE FLIGHT MANUAL FOR OTHER LIMITATIONS . NO SMOKING Near baggage compartment a placard will state the following: F ASTEN TIE- DOWN NET MAXIMUM WEIGHT 20 kg MAX . P RESS 12.5 Kg/dm2 On the wing root there is the following placard: NO STEP For other placards see Maintenance Manual doc. 2002/30. P2002-JF S E C T I O N 3 E m e r g e n c y P r o c e d u r e s 1 st edition – 29th March 2004 3-1 FLIGHT M ANUAL SECTION 3 EMERGENCY PROCEDURES TABLE OF CONTENTS INTRODUCTION.................................................................................................... 2 ENGINE FAILURES............................................................................................... 2 IN-FLIGHT ENGINE RESTART............................................................................ 5 SMOKE AND FIRE................................................................................................. 5 GLIDE...................................................................................................................... 6 LANDING EMERGENCY...................................................................................... 7 RECOVERY FROM UNINTENTIONAL SPIN ..................................................... 8 OTHER EMERGENCIES........................................................................................ 8 P2002-JF S E C T I O N 3 E m e r g e n c y P r o c e d u r e s 1 st edition – 29th March 2004 3-2 FLIGHT M ANUAL 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. In case of emergency, suggestions of the present 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 continued and appropriate training should be provided. In case of emergency the pilot should acts as follows: 1. Keep control of the aeroplane 2. Analyze the situation 3. Apply the pertinent procedure 4. Inform the Air Traffic Control if time and conditions allow. ENGINE FAILURES If an emergency arise, the basic guidelines described in this section should be considered and applied as necessary to correct the problem. ENGINE FAILURE DURING TAKEOFF RUN 1. Throttle: idle (fully out) 2. Brakes: apply as needed 3. Magnetos: OFF. 4. Generator & Master switches: OFF. With the aeroplane under control 5. Fuel selector valve: OFF 6. Electric fuel pump: OFF P2002-JF S E C T I O N 3 E m e r g e n c y P r o c e d u r e s 1 st edition – 29th March 2004 3-3 FLIGHT M ANUAL ENGINE FAILURE IMMEDIATELY AFTER TAKEOFF 1. Speed: check 2. Find a suitable place on the ground to land safely. The landing should be planned straight ahead with only small changes in directions not exceeding 45° to the left and 45° to the right 3. Flaps: as needed. 4. Throttle: as required At touch down 5. Magnetos: OFF 6. Generator & Master switches: OFF. 7. Fuel selector valve: OFF 8. Electric fuel pump: OFF ENGINE FAILURE DURING FLIGHT IRREGULAR ENGINE RPM 1. Throttle: check position and adjustable friction 2. Check engine gauges. 3. Check both fuel quantity indicators. 4. Carburettors heating: ON 5. Electric fuel pump: ON If the engine continues to run irregularly: 6. Fuel selector valve: change the fuel feeding to the tank not in use (e.g. if you are drawing fuel from the LEFT tank, change to RIGHT or v.v.) If the engine continues to run irregularly: 7. Land as soon as possible. P2002-JF S E C T I O N 3 E m e r g e n c y P r o c e d u r e s 1 st edition – 29th March 2004 3-4 FLIGHT M ANUAL LOW FUEL PRESSURE If the fuel pressure indicator falls below the 2.2 psi (0.15 bar) limit, it is necessary to apply the following procedure: 1. Fuel quantity indicators: check 2. Electric fuel pump: ON If the engine continues to run irregularly: 3. Fuel selector valve: change the fuel feeding to the tank not in use (e.g. if you are drawing fuel from the LEFT tank, change to RIGHT or v.v.) If the fuel pressure continues to be low: 4. Land as soon as possible LOW OIL PRESSURE 1. Check oil temperature: check If the temperature tends to increase: 2. Throttle: set to reach a speed of 68 KIAS (maximum efficiency speed) 3. Land as soon as possible and be alert for impending engine fault and consequent emergency landing. If the temperature remains within the green arc limits: 4. Land as soon as possible P2002-JF S E C T I O N 3 E m e r g e n c y P r o c e d u r e s 1 st edition – 29th March 2004 3-5 FLIGHT M ANUAL IN-FLIGHT ENGINE RESTART 1. Altitude: preferably below 4000 ft 2. Carburettors heating: ON 3. Electric fuel pump: ON 4. Fuel selector valve: swap from one tank to another 5. Throttle: middle position 6. Generator & Master switch: ON 7. Magnetos: START If the restart attempt fails: 8. Procedure for a forced landing: apply In case of an engine restart: 9. Land as soon as possible. SMOKE AND FIRE ENGINE FIRE DURING TAKEOFF 1. Throttle: idle (fully out) 2. Brakes: as necessary With the aeroplane under control 3. Fuel selector valve: OFF 4. Electric fuel pump: OFF 5. Cabin heating: OFF 6. Magnetos: OFF 7. Generator & Master switch: OFF 8. Parking brake: engage 9. Escape rapidly from the aircraft. ENGINE FIRE WHILE PARKED 1. Fuel selector valve: OFF 2. Electric fuel pump: OFF 3. Magnetos: OFF 4. Generator & Master switches: OFF 5. Parking brake: ON 6. Do not attempt air start. 7. Escape rapidly from the aircraft. P2002-JF S E C T I O N 3 E m e r g e n c y P r o c e d u r e s 1 st edition – 29th March 2004 3-6 FLIGHT M ANUAL ENGINE FIRE IN-FLIGHT 1. Cabin heating: OFF 2. Fuel selector valve: OFF 3. Electric fuel pump: OFF 4. Throttle: full in until the engine stops running 5. Cabin vents: OPEN 6. Magnetos: OFF 7. Do not attempt an in-flight restart. 8. Procedure for a forced landing: apply CABIN FIRE DURING FLIGHT 1. Cabin heating: OFF 2. Cabin vents: OPEN 3. Canopy: open, if necessary 4. Master switch: OFF 5. Try to choke the fire. Direct the fire extinguisher towards flame base 6. Procedure for a forced landing: apply GLIDE 1. Flaps: retract 2. Speed: 68 KIAS (maximum efficiency speed) 3. Electric equipments (Landing, Strobo & Nav lights): OFF 4. In-flight engine restart: if conditions permit, try to restart several times Glide ratio is 12.8 therefore with 1000ft elevation it is possible to cover ~4 km (~2 nautical miles) in zero wind conditions. NOTE P2002-JF S E C T I O N 3 E m e r g e n c y P r o c e d u r e s 1 st edition – 29th March 2004 3-7 FLIGHT M ANUAL LANDING EMERGENCY FORCED LANDING WITHOUT ENGINE POWER 1. Procedure to glide: apply (suggested airspeed 68 KIAS) 2. Locate most suitable terrain for emergency landing, possibly upwind. 3. Fuel selector valve: OFF 4. Electric fuel pump: OFF 5. Magnetos: OFF 6. Tighten safety belts, canopy locks: tighten – lock When certain to land 7. Flaps: as necessary 8. Generator and Master switches: OFF. POWER-ON FORCED LANDING 1. Descent: set 2. Flaps: as necessary 3. Select terrain area most suitable for emergency landing and flyby checking for obstacles and wind direction. 4. Safety belts, canopy locks: tighten – lock When certain to land 5. Flaps: as necessary 6. Fuel selector valve: OFF 7. Electric fuel pump: OFF 8. Magnetos: OFF 9. Generator and Master switches: OFF LANDING WITH A FLAT NOSE TIRE 1. Pre-landing checklist: complete 2. Flaps: land 3. Land and maintain aircraft NOSE HIGH attitude as long as possible. P2002-JF S E C T I O N 3 E m e r g e n c y P r o c e d u r e s 1 st edition – 29th March 2004 3-8 FLIGHT M ANUAL LANDING WITH A FLAT MAIN TIRE 1. Pre-landing checklist: complete 2. Flaps: land 3. Land aeroplane on the side of runway opposite to the side with the defective tire to compensate for change in direction which is to be expected during final rolling 4. Touchdown with the GOOD TIRE FIRST and hold aircraft with the flat tire off the ground as long as possible. RECOVERY FROM UNINTENTIONAL SPIN If unintentional spin occur, the following recovery procedure should be used: 1. Throttle: idle (full out position) 2. Rudder: full, in the opposite direction of the spin 3. Stick: move and hold forward until spin is halted As the spin is halted 4. Rudder: neutralize 5. Aeroplane attitude: make a smooth recovery by pulling the stick back gently averting speeds in excess of VNE and maximum load factor (n=+3.8) 6. Throttle: readjust to restore engine power. OTHER EMERGENCIES UNINTENTIONAL FLIGHT INTO ICING CONDITIONS 1. Carburettor heating: ON 2. Get away from icing conditions by changing altitude or direction of flight in order to reach an area with warmer external temperature 3. Controls surfaces: continue to move to maintain their movability 4. Increase rpm to avoid ice formation on propeller blades. 5. Cabin heat: ON In case of ice formation on wing leading edge, stall speed may increase. WARNING P2002-JF S E C T I O N 3 E m e r g e n c y P r o c e d u r e s 1 st edition – 29th March 2004 3-9 FLIGHT M ANUAL CARBURETTOR ICE AT TAKEOFF At takeoff, given the unlikely possibility of ice formation at full throttle, carburettor heat is normally OFF. IN FLIGHT With external temperatures below 15° C, or on rainy days or with humid, cloudy, hazy or foggy conditions or whenever a power loss is detected, turn carburettor heat to ON until engine power is back to normal. ELECTRIC POWER SYSTEM MALFUNCTION Electric power supply system malfunctions may be avoided by carrying out inspections as scheduled and prescribed in the Maintenance Manual. Causes for malfunctions are hard to establish but, in any case, problems of this nature must be dealt with immediately. The following may occur: GENERATOR LIGHT ILLUMINATES Generator light may illuminate for a faulty alternator or when voltage is above 16V, in this case the over-voltage sensor automatically shuts down the alternator. In both cases proceed as follows: 1. Generator switch and master switch: OFF 2. Generator switch and master switch: ON If the problem persist 3. Generator switch: OFF 4. Non vital electric equipments: OFF 5. Radio calls: reduce at the strictly necessary The battery is capable of supply the electrical system enough time to complete flight in emergency conditions, with normal flight electric-loads including operation of flap and trim. NOTE P2002-JF S E C T I O N 3 E m e r g e n c y P r o c e d u r e s 1 st edition – 29th March 2004 3-10 FLIGHT M ANUAL TRIM SYSTEM FAILURE LOCKED CONTROL In case the trim control should not respond, act as follows: 1. Breakers: check 2. Trim switch Lh/Rh: check for correct position 3. Speed: adjust to control aircraft without excessive stick force 4. Land aircraft as soon as possible. RUNAWAY If trim position indicator reads displacement without pilot's action on trim control, follow procedure below: 1. Trim power switch: OFF 2. Speed: adjust speed to control aircraft without excessive stick force 3. Land aircraft as soon as possible. ESCAPING THROUGH A LOCKED CANOPY With the engine shut off: 1. Using the emergency hammer to break a canopy’s glass. 2. If it is possible, try to enlarge the hole and remove any splinter.