P92-JS Flight Manual

P92-JS S E C T I O N 1 GENERAL THREE-VIEW DRAWING  Dimensions shown refer to aircraft weight of 550kg (and 600 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 FLIGHT MANUAL Date: Issue 3: 25th May2010 1-4 P92-JS S E C T I O N 1 GENERAL DESCRIPTIVE DATA WING For 550 kg MTOW For 600 kg MTOW Wing span: 8.7 m 8.7 m Wing chord 1.4 m 1.4 m Wing surface 12 m2 12 m2 Wing loading 45.8 kg/m2 50.0 kg/m2 Aspect ratio 6.31 6.31 Taper ratio 1.0 1.0 Dihedral 1.5° 1.5° FUSELAGE Overall length 6.400 m 6.400 m Overall width 1.100 m 1.100 m Overall height 2.500 m 2.500 m EMPENNAGE Stabilator span 2.900 m 2.900 m Vertical tail span 1.230 m 1.230 m LANDING GEAR Wheel track: 1.800 m 1.800 m Wheel base: 1.600 m 1.600 m Main gear tires: Air Trac; Cleveland wheel hub and brakes kit: 5.00-5 199-102 5.00-5 199-102 Nose gear tire: Sava 4.00-6 4.00-6 CONTROL SURFACES TRAVEL LIMITS Ailerons Up 20° down 15 °  2° Stabilator Up 18° down 3°  1° Trim-Tab 2° ; 12°  1° Rudder RH 25° LH 25°  1° Flaps 0° -38°  1° FLIGHT MANUAL Date: Issue 3: 25th May2010 1-5 P92-JS S E C T I O N 1 GENERAL ENGINE Manufacturer: Bombardier-Rotax GmbH Model 912 S2 Certification basis FAR 33 Amendment 15 Austrian Type- Certification No. n° TW 9-ACG of 27 Nov. 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: (engine’s rpm) 73.5 kW (98.6 hp) @ 5800 rpm (max.5 min.) 69.0 kW (92.5 hp) @ 5500 rpm (continuous) PROPELLER Manufacturer: HOFFMANN Propeller Certification basis: CAR Part 14 Type-Certification No.: SO/E 30 of 10/12/1999 Model: HO17GHM A 174 177C Number of blades: 2 Diameter: 1740 mm (no reduction permitted) Type: Fixed pitch - wood FLIGHT MANUAL P92-JS S E C T I O N 1 GENERAL Date: Issue 3rev2: 16th June 2015 1-6 FUEL Fuel grade:  EN 228 Premium  EN 228 Premium plus  AVGAS 100LL (see Section 2.9) Fuel tanks: 2 wing tanks integrated within the wing's leading edge with fuel strainer located in engine cowling. Capacity of each wing tank 35 liters (optional 45 liters) Total capacity: 70 liters (optional 90 liters) Total usable fuel 66.8 liters. (86.8 liters) OIL SYSTEM Oil system type: Forced, with external oil reservoir Oil: Automotive grade API "SF" or "SG" type oil preferably synthetic or semi-synthetic Oil Capacity: 3.0 liters COOLING Cooling system: Mixed air and liquid pressurized closed circuit system Coolant: Antifreeze and water liquid mixture Capacity 3 liters FLIGHT MANUAL P92-JS S E C T I O N 1 GENERAL Date: Issue 3: 25th May2010 1-7 MAXIMUM CERTIFIED WEIGHTS Maximum take-off weight: 550 kg 600 kg Maximum landing weight: 550 kg 600 kg Maximum baggage weight 20 kg 20 kg STANDARD WEIGHTS Standard Empty Weight 325 kg 325 kg Maximum Useful Load 225 kg 275 kg SPECIFIC LOADINGS Wing Loading 45.8 kg/m2 50 kg/m2 Power Loading 5.6 kg/hp 6.1 kg/hp FLIGHT MANUAL P92-JS S E C T I O N 1 GENERAL Date: Issue 3: 25th May 2010 1-8 ABBREVIATIONS AND TERMINOLOGY GENERAL AIRSPEED TERMINOLOGY AND SYMBOLS KCAS Knots Calibrated Airspeed is indicated airspeed corrected for position and instrument error and expressed in knots. KIAS Knots Indicated Airspeed is the speed shown on the airspeed indicator and expressed in knots. KTAS Knots True Airspeed is the airspeed expressed in knots relative to undisturbed air which is KCAS corrected for altitude and temperature. VFE Maximum Flap Extended Speed is the highest speed permissible with wing flaps in a prescribed extended position. VNO Maximum Structural Cruising Speed is the 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 in landing configuration VS1 Stalling speed in clean configuration (flap 0°) 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 VLO 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 MANUAL P92-JS S E C T I O N 1 GENERAL Date: Issue 3: 25th May2010 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. HP 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 MANUAL P92-JS S E C T I O N 1 GENERAL Date: Issue 3: 25th May 2010 1-10 WEIGHT AND BALANCE TERMINOLOGY 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. Standard Empty Weight Standard Empty Weight is the weight of a standard airplane, including unusable fuel, full operating 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 certified weight of the aircraft. 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 MANUAL P92-JS S E C T I O N 1 GENERAL Date: Issue 3: 25th May2010 1-11 UNIT CONVERSION CHART MULTIPLYING BY  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] SPEED 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 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 Liters [l] 0.2642 U.S. Gallons [US Gal] U.S. Gallons [US Gal] 3.785 Liters [l] AREA Square meters [m2] 10.76 Square feet [sq ft] Square feet [sq ft] 0.0929 Square meters [m2] FLIGHT MANUAL P92-JS S E C T I O N 1 GENERAL Date: Issue 3: 25th May 2010 1-12 INTENTIONALLY LEFT BLANK FLIGHT MANUAL Date: Issue 3: 25th May 2010 2-1 P92-JS S E C T I O N 2 LIMITATIONS SECTION 2 LIMITATIONS TABLE OF CONTENTS INTRODUCTION ...................................................................................................... 2 AIRSPEED LIMITATIONS ....................................................................................... 2 AIRSPEED INDICATOR MARKINGS..................................................................... 3 POWERPLANT LIMITATIONS ............................................................................... 4 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 ........................................................................................................................ 10 MAXIMUM PASSENGER SEATING .................................................................... 11 CROSSWIND LIMITATIONS ................................................................................ 11 LIMITATION PLACARDS ..................................................................................... 11 FLIGHT MANUAL Date: Issue 3: 25th May 2010 2-2 P92-JS S E C T I O N 2 LIMITATIONS INTRODUCTION Section 2 includes operating limitations, instrument markings, and basic placards necessary for safe operation of the P92-JS, its engine, standard systems and standard equipment. Refer to section 9 for possible variations to: AIRSPEED LIMITATIONS Airspeed limitations and their operational significance are shown below: S P E E D 550 kg MTOW 600 kg MTOW REMARKS KIAS KCAS KIAS KCAS VNE Never exceed speed 134 128 141 135 Never exceed this speed in any operation. VNO Maximum Structural Cruising Speed 106 102 110 106 Never exceed this speed unless in smooth air, and then only with caution. VA Maneuvering speed 93 90 97 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 68 66 71 69 Never exceed this speed for any given flap setting. NOTE FLIGHT MANUAL Date: Issue 3: 25th May 2010 2-3 P92-JS S E C T I O N 2 LIMITATIONS AIRSPEED INDICATOR MARKINGS Airspeed indicator markings and their color 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 550 kg MTOW 600 kg MTOW SIGNIFICANCE KIAS White arc 43* - 68 41 - 71 Positive Flap Operating Range (lower limit is VSO, at maximum weight and upper limit is maximum speed permissible with flaps extension to maximum positive) Green arc 48* – 106 46 - 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 VNO). Yellow arc 106 - 134 110- 141 Maneuvers must be conducted with caution and only in smooth air. Red line 134 141 Maximum speed for all operations. For P92-JS with MTOW = 550kg the low limit of the white arc is 1.1 VS0 while the low limit of the green arc is 1.1VS1 CAUTION FLIGHT MANUAL P92-JS S E C T I O N 2 LIMITATIONS Date: Issue 3 rev2 : 16th June 2015 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 (eng.) Time max. (min.) Maximum 73.5 (98.6) 2388 (5800) 5 Max cont. 69 (92.5) 2265 (5500) - The static rpm range at full throttle (carburetors heat: Off) is 2100  100 prop. rpm. TEMPERATURES: Max cylinder heads* 135° C Max coolant temperature 120° C Max Oil: 130° C Min Oil 50° C  applicable for Engines up to serial no. 4924543(included) and repaired engine which doesn’t change the cylinder head n°3 with new one (part no. 413195) OIL PRESSURE: Min 0.8 bar Max 5 bar ENGINE START, OPER. TEMP: OAT Min -25° C OAT Max +50° C Admissible pressure for cold start is 7 bar maximum for short periods. NOTE WARNING FLIGHT MANUAL P92-JS S E C T I O N 2 LIMITATIONS Date: Issue 3 rev2 : 16th June 2015 2-5 FUEL PRESSURE:Min 2.2 psi Max 5.8 psi Max* 7.2 psi *only applicable for fuel pump part no. 893110 and 893114 VISCOSITY Use viscosity grade oil as specified in the following table: Use of Aviation Grade Oil with or without additives is not permitted COOLANT: Mixture: 80% concentrated antifreeze (e.g. BASF Glysantin Anticorrosion or equivalent) with anticorrosion additive and 20% demineralized water. WARNING FLIGHT MANUAL P92-JS S E C T I O N 2 LIMITATIONS Date: Issue 3: 25th May 2010 2-6 PROPELLER MANUFACTURER: HOFFMANN Propeller MODEL: HO17GHM-174 177C or HO17GHM A 174 177C PROPELLER TYPE: Wood twin blade fixed pitch DIAMETER: 1740 mm (no reduction permitted) FLIGHT MANUAL P92-JS S E C T I O N 2 LIMITATIONS Date: Issue 3 rev2: 16h June 20105 2-7 POWERPLANT INSTRUMENT MARKINGS Powerplant instrument markings and their color 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(4) . °C -------- 0 - 135 ------ 135 Coolant temp. °C 0 - 120 120 Oil pressure bar 0.8 2 – 5 0.8 – 2 5 – 7 (1) 7 Fuel Press. psi 2.2 2.2–5.8 or 7.26(3) ---- 5.8 or 7.26(3) Fuel quantity liters -------- (2) ---- ---- ----- OTHER INSTRUMENT MARKINGS INSTRUMENT RED LINE Minimum limit GREEN ARC Normal operating YELLOW ARC Caution RED LINE Maximum limit Suction gage 4 in. Hg 4,5 - 5,5 in. Hg. ------ ------ Voltmeter 10 Volt 12 - 14 Volt ------ ------ 1 Admissible pressure for cold start is 7 bar maximum for short periods. 2 - Unusable fuel for each tank is 1.6 litres 3 – When fuel pump part no. 893110 and 893114.is installed 4 - Applicable for Engines up to serial no. 4924543(included) and repaired engine which doesn’t change the cylinder head n°3 with new one (part no. 413195). FLIGHT MANUAL P92-JS S E C T I O N 2 LIMITATIONS Date: Issue 3: 25th May 2010 2-8 WEIGHTS 550 kg MTOW 600 kg MTOW Maximum takeoff weight 550 kg 600 kg Maximum landing weight 550 kg 600 kg Maximum zero fuel weight 550 kg 600 kg Maximum baggage weight (2.18 m from datum) 20 kg 20 kg NOTE Refer to section 6 for correct stowing and loading of baggage. CENTER OF GRAVITY RANGE Ref. for levelling Cabin floor Datum Propeller support flange without spacer Forward limit 1.727 m (23% MAC) aft of datum for all weights Aft limit 1.769 m (26% 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 MANUAL P92-JS S E C T I O N 2 LIMITATIONS Date: Issue 3 rev2: 16h June 20105 2-9 APPROVED MANEUVERS This aircraft is certified in the CS-VLA category. CS-VLA applies to airplanes intended for non-aerobatic operation only. Non- aerobatic operation includes:  Any maneuver pertaining to “normal” flight  Stalls (except whip stalls)  Lazy eights  Chandelles  Turns in which the angle of bank is not more than 60° Acrobatic maneuvers, including spins, are not approved Recommended entry speed for each approved maneuver is as follows: MANEUVER KIAS 550 kg MTOW 600 kg MTOW Lazy eights 93 97 Chandelles 93 97 Steep turns max 60° 93 97 Stalls Slow Deceleration (1 Kts/sec.) Slow Deceleration (1 Kts/sec.) MANEUVERING LOAD FACTOR LIMITS Maneuvering load factors are as follows: FLAPS 0° +3.8 - 1.9 38° +1.9 0 FLIGHT MANUAL P92-JS S E C T I O N 2 LIMITATIONS Date: Issue 3: 25th May 2010 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 Gage  Oil Pressure Indicator  Oil Temp. Indicator  Cylinder Heads Temp. Indicator  Outside Air Temp. indicator  Tachometer  Chronometer  First Aid Kit  Hand-held fire extinguisher For further standard equipment refer to section 6. Flight into expected and/or known icing conditions is prohibited. FUEL TWO TANKS: 35 liters each (45 liters optional) TOTAL FUEL CAPACITY: 70 liters (90 liters) USABLE FUEL: 66.8 liters (86.8 liters) UNUSABLE FUEL: 3.2 liters (3.2 liters) During all phases of flight engine fuel feed must be supplied by both tanks. Compensate uneven fuel tank levels by acting on fuel taps located in cabin. FLIGHT MANUAL P92-JS S E C T I O N 2 LIMITATIONS Date: Issue 3 rev2: 16h June 20105 2-11 APPROVED FUEL  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 Only one passenger is allowed on board this aircraft. CROSSWIND LIMITATIONS Maximum allowed crosswind component is 15 Kts (refer to section 5 for further details). 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 VA=93 KIAS MANEUVERING SPEED VA=97 KIAS For 550 kg MTOW For 600 kg MTOW WARNING FLIGHT MANUAL P92-JS S E C T I O N 2 LIMITATIONS Date: Issue 3: 25th May 2010 2-12 On the Middle panel of the instrument panel a placard will state the following: THIS AIRPLANE IS CLASSIFIED AS A VERY LIGHT AIRPLANE APPROVED FOR DAY VFR ONLY, IN NON-ICING CONDITIONS. ALL AEROBATIC MANEUVERS INCLUDING INTENTIONAL SPIN ARE PROHIBITED. SEE FLIGHT MANUAL FOR OTHER LIMITATIONS. NO SMOKING Near baggage compartment a placard will state the following: FASTEN TIE-DOWN NET MAXIMUM WEIGHT 20 kg MAX. PRESS 12.5 Kg/dm2 FLIGHT MANUAL Date: Issue 3: 25th May 2010 3-1 P92-JS S E C T I O N 3 EMERGENCY PROCEDURES SECTION 3 EMERGENCY PROCEDURES TABLE OF CONTENTS INTRODUCTION ...................................................................................................... 2 ENGINE FAILURES .................................................................................................. 2 AIR START ................................................................................................................ 4 SMOKE AND FIRE ................................................................................................... 4 GLIDE ........................................................................................................................ 5 LANDING EMERGENCIES...................................................................................... 5 RECOVERY FROM UNINTENTIONAL SPIN ........................................................ 6 OTHER EMERGENCIES .......................................................................................... 7 FLIGHT MANUAL Date: Issue 3: 25th May 2010 3-2 P92-JS S E C T I O N 3 EMERGENCY PROCEDURES 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. AIRSPEEDS FOR SAFE OPERATION IN EMERGENCY SITUATIONS - IAS 550 kg MTOW 600 kg MTOW Engine failure after takeoff 60 Kts 60 Kts Engine failure during flight 66 Kts 69 Kts Manoeuvring speed 93 Kts 97 Kts Maximum glide 66 Kts 69 Kts ENGINE FAILURES Should 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. Flap: retract 5. Generator switch and Master switch: OFF. 6. Fuel shutoff valves: OFF 7. Electric fuel pump: OFF 8. Inform TWR FLIGHT MANUAL Date: Issue 3: 25th May 2010 3-3 P92-JS S E C T I O N 3 EMERGENCY PROCEDURES ENGINE FAILURE IMMEDIATELY AFTER TAKEOFF 1. Speed 60 KIAS 2. Locate landing area 3. Throttle: idle (fully out) 4. Fuel shutoff valves: OFF. 5. Electric fuel pump: OFF 6. Magnetos OFF. 7. Flaps: as needed. 8. Generator switch and Master switch: OFF. 9. Inform TWR ENGINE FAILURE DURING FLIGHT IRREGULAR ENGINE RPM 1. Throttle: check position and adjustment wheel 2. Carb heat: ON 3. Electric fuel pump: ON 4. Fuel shutoff valves: both ON 5. If engine RPMs remain irregular land as soon as possible at closest airport. LOW FUEL PRESSURE If the fuel pressure indicator falls below the 2.2 psi limit, it is necessary to apply the following procedure: 1. Electric fuel pump: ON 2. Fuel shutoff valves: both ON 3. Land at closest airport LOW OIL PRESSURE 1. Check oil temperature: If stable within green arc: Land as soon as possible at closest airport If increasing: 2. Reduce engine throttle to 70 KIAS 3. Land as soon as possible and be alert for impending engine fault and consequent emergency landing. FLIGHT MANUAL Date: Issue 3: 25th May 2010 3-4 P92-JS S E C T I O N 3 EMERGENCY PROCEDURES AIR START 1. Altitude: preferably below 4000 ft 2. Carb heat: ON 3. Fuel shutoff valves: both ON 4. Electric fuel pump: ON 5. Throttle: middle position 6. Generator switch and Master switch: ON. 7. Magnetos: BOTH. 8. Ignition key to START 9. If engine restarts, keep an eye on instrument readings and land as soon as possible, otherwise see procedure for: Forced landing SMOKE AND FIRE ENGINE FIRE WHILE PARKED OR DURING TAKEOFF 1. Fuel shutoff valves: OFF 2. Electric fuel pump: OFF 3. Cabin heat: OFF 4. Abort takeoff if possible. 5. If engine is running, use up remaining fuel in carburetors. 6. Magnetos: OFF. 7. Master switch: OFF. 8. Generator switch: OFF. 9. Warn bystanders to clear the area as fast as possible. 10. Without removing the engine cowling use a CO 2 or a powder fire extinguisher to put out flames directing spray towards cowling's air intakes. DO NOT USE WATER to put out fire and do not open engine cowling until absolutely confident that fire is extinguished. WARNING FLIGHT MANUAL Date: Issue 3: 25th May 2010 3-5 P92-JS S E C T I O N 3 EMERGENCY PROCEDURES ENGINE FIRE DURING FLIGHT 1. Fuel shutoff valves: OFF. 2. Electric fuel pump: OFF 3. Cabin heat: OFF 4. Throttle: all in. 5. Magnetos: OFF. 6. Do not attempt air start. 7. Flaps as necessary. 8. Carry out emergency procedure for forced landing. CABIN FIRE DURING FLIGHT 1. Master switch: OFF 2. Cabin heat: OFF 3. Door vents: open 4. Direct fire extinguisher towards flame base 5. Carry out emergency procedure for forced landing GLIDE 1. Flaps: retract 2. Speed at: 600 kg 69KIAS 550 kg 66KIAS 450 kg 60KIAS 3. Glide ratio is 12.2 therefore with 1000ft elevation it is possible to cover ~3.8 km (~2 nautical miles) in zero wind conditions. LANDING EMERGENCIES FORCED LANDING WITHOUT ENGINE POWER 1. Suggested airspeed 69 KIAS for 600kg MTOW, 66 KIAS for 550kg MTOW, 60 KIAS for 450kg. 2. Locate most suitable terrain for emergency landing, possibly upwind. 3. Fuel shutoff valves: OFF. 4. Electric fuel pump: OFF. 5. Magnetos: OFF. 6. Tighten safety belts, release door safety lock and unlatch doors. 7. Flaps: full 8. When certain to land, Generator switch and Master switch: OFF. 9. Touchdown at 42 KIAS FLIGHT MANUAL Date: Issue 3: 25th May 2010 3-6 P92-JS S E C T I O N 3 EMERGENCY PROCEDURES POWER-ON FORCED LANDING 1. Prompt descent slope. 2. Flaps as required. 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. Electric fuel pump: OFF 7. Carb heat: OFF 8. Flaps: full 9. After touchdown: magnetos: OFF. 10. Generator switch and Master switch: OFF. LANDING WITH A FLAT NOSE TIRE 1. Pre-landing checklist: complete 2. Flaps: full 3. Land and maintain aircraft NOSE HIGH attitude as long as possible. After touchdown. LANDING WITH A FLAT MAIN TIRE 1. Pre-landing checklist: complete 2. Landing approach as usual. 3. Touchdown with GOOD TIRE FIRST and hold aircraft off flat tire as long as possible. RECOVERY FROM UNINTENTIONAL SPIN Should an unintentional spin occur, the following recovery procedure should be used: 1. Adjust throttle to idle (full outward position) 2. Apply and hold full rudder opposite to the direction of spin. 3. Move and hold stick forward until spin is halted. 4. Neutralize rudder 5. Make a smooth recovery by pulling the stick back gently averting speeds in excess of V NE and maximum load factor. 6. Readjust throttle to restore engine power. FLIGHT MANUAL Date: Issue 3: 25th May 2010 3-7 P92-JS S E C T I O N 3 EMERGENCY PROCEDURES OTHER EMERGENCIES UNINTENTIONAL FLIGHT INTO ICING CONDITIONS 1. Get away from icing conditions by changing altitude or direction of flight in order to reach an area with warmer external temperature. 2. Avoid possible freeze-up of control surfaces by recurrently moving them. 3. Carb heat: ON 4. Increase RPMs to avoid ice formation on propeller blades. 5. Cabin heat: ON In case of ice formation on wing leading edge, stall speed may increase. CARBURETOR HEAT AT TAKEOFF At takeoff, given the unlikely possibility of ice formation at full throttle, carburetor 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 carb 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 Service 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 overvoltage sensor automatically shuts down the alternator. WARNING FLIGHT MANUAL Date: Issue 3: 25th May 2010 3-8 P92-JS S E C T I O N 3 EMERGENCY PROCEDURES In both cases proceed as follows: 1. Generator switch and master switch: OFF. 2. Generator switch and master switch: ON. If the problem no longer persists, normal alternator charging will resume and the warning light will turn off proving voltage surcharge was temporary; no further action is required. If light remains illuminated, a generator malfunction is confirmed. In this case, set Generator switch to OFF and continue flight on battery power alone; the battery is capable of supplying the electrical system for about 26 min. with normal flight loads including operation of: com/nav, flap and trim. TRIM SYSTEM FAILURE LOCKED CONTROL In case the trim control should not respond, act as follows: 1. Check switch for correct position 2. Adjust speed to control aircraft without excessive stick force 3. 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. Adjust speed to control aircraft without excessive stick force 3. Land aircraft as soon as possible. FLIGHT MANUAL Date: Issue 3: 25th May 2010 4-1 P92-JS S E C T I O N 4 NORMAL PROCEDURES SECTION 4 NORMAL PROCEDURES TABLE OF CONTENTS INTRODUCTION...................................................................................................... 2 RIGGING AND DERIGGING ENGINE COWLING ............................................... 2 PRE-FLIGHT INSPECTIONS................................................................................... 3 CHECKLISTS............................................................................................................ 6 FLIGHT MANUAL Date: Issue 3: 25th May 2010 4-2 P92-JS S E C T I O N 4 NORMAL PROCEDURES INTRODUCTION Section 4 contains checklists and the procedures for the conduct of normal operation. RIGGING AND DERIGGING ENGINE COWLING UPPER COWLING: I. Parking brake ON. II. Fuel shutoff valves OFF. III. Generator switch OFF, 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 reference 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. Using a standard screwdriver, press and rotate 90° the two Cam-locks positioned on lower cowling by the firewall. III. Pull out the first hinge pin positioned on the side of the firewall, then, while holding cowling, pull out second hinge pin; remove cowling with downward motion. IV. For installation follow reverse procedure. WARNING FLIGHT MANUAL Date: Issue 3: 25th May 2010 4-3 P92-JS S E C T I O N 4 NORMAL PROCEDURES PRE-FLIGHT INSPECTIONS Before each flight, it is necessary to carry out a complete inspection of the aircraft starting with an external inspection followed by an internal inspection as hereby detailed. CABIN INSPECTION A Flight Manual: check that a copy is on board B Weight and balance: check if within limits C Safety belts used to lock controls: free D Flight controls: activate flight controls to insure unhindered movement of control rods and surfaces. E Parking brake: engage F Throttle: adjust friction lock G Magnetos: OFF H Master switch: ON I Voltmeter: check (10-12 V); Ammeter check (red). J Generator switch: ON, check generator switch is illuminated. K Fuel pump: ON, check light ON, audible sound and correct operation of fuel pressure indicator. L Avionics switch: ON, check operation; when finished, reposition switch to OFF M Flaps control: activate control to full extension checking travel limits and instrument indication. N Trim control: activate control to full scale checking travel limits and instrument indication O Acoustic stall warning: check operation P Navigation lights and strobe-light: check operation Q Landing light: check operation R Generator switch: OFF S Master switch: OFF T Fuel level: check level on the basis of flight plan U Baggage: check for proper stowage with tie-down net.