Flight Manual Falco F8L : I-DIET

......................................................................................... 2.1 Speed Limitations 29 Flight Manual Falco F8L / I-DIET 3rd Revision 4 of 67 ........................................................................ 2.2 Airspeed Indicator Markings 29 ................................................................ 2.3 Load Limit Factors and Markings 30 ................................................................ 2.4 Markings on Analog Fuel Gauges 30 .......................... 2.5 Limitations and Markings on AuRACLE System Monitor 30 .................................................................................... 2.5 Approved Maneuvers 31 ................................................................................................................ 2.5.1 Utility Category: 31 ............................................................................................................ 2.5.2 Acrobatic Category: 32 ......................................................................................... 2.6 Operating altitude 32 ................................................................................................... 2.7 Flight Crew 32 ........................................................................................ 2.8 kinds of Operation 33 ....................................................................... 2.8.1 Minimum operational equipment (serviceable) 33 ........................................................................................... 2.9 Other limitations 34 ....................................................................................................................... 2.9.1 Temperature 34 ................................................................................................................... 2.9.2 Battery Charge 35 ........................................................................................................... 2.9.3 Electronic equipment 35 ................................................ 3 Normal Operating Procedures 36 ............................................................................. 3.1 Ground Pre-Flight Check 36 ....................................... 3.2 Cockpit Pre-Flight Check, Before Starting Engine 38 ............................................................................ 3.3 Engine Starting Procedure 39 ........................................................................................... 3.4 Warm Up / Taxi 40 .............................................................................................. 3.5 Run-Up Check 40 .............................................................................................. 3.6 Before TakeOff 41 ................................................................................ 3.7 Take Off / Inital Climb 41 Flight Manual Falco F8L / I-DIET 3rd Revision 5 of 67 ............................................................................ 3.8 Climb / Cruise / Descend 42 ..................................................................................... 3.9 Approach / Landing 43 .............................................................................................. 3.10 After Landing 43 ......................................................................... 3.11 Engine Shut Off / Parking 44 ............................................................ 4 Emergency Procedures 45 ............................................................................... 4.1 Electrical System Failure 45 ..................................................................... 4.2 Electrical System Malfunctions 45 ............................................................................................................... 4.2.1 Alternator Failure 45 ............................................................................................... 4.2.2 Short in an Electrical Circuit 45 .................................................................................... 4.3 Drop in Fuel Pressure 46 ........................................................................... 4.4 Restarting Engine in Flight 46 .............................................................................. 4.5 Propeller Spinner Failure 48 .................................................................................... 4.6 Emergency Landings 49 ................................................................................................................... 4.6.1 Engine Failure 49 ................................................................................. 4.6.2 Emergency Extension of Landing Gear 50 ................................................................................................... 4.6.3 Failure of Flaps to Lower 51 .................................................................................................... 4.6.4 Failure of Flaps to Raise 51 .................................................................................................... 4.7 Engine Fire 51 ......................................................... 4.8 Primary Flight Control System Failure 52 ........................................................................................................... 4.8.1 Yaw Control Failure 52 ........................................................................................................... 4.8.2 Roll Control Failure 52 .......................................................................................................... 4.8.3 Pitch Control Failure 52 ............................................................... 4.9 Secondary Control System Failure 53 ............................................................................................. 4.9.1 Elevator Trim Control Failure 53 Flight Manual Falco F8L / I-DIET 3rd Revision 6 of 67 ................................................................................ 4.10 Evacuation of Aircraft 53 ........................................................................................... 4.11 Crash Landings 54 ............................................................................ 5 Performance 55 .................................................................... 5.1 Takeoff and Landing Distances 55 ...................................................................................... 5.2 Cruise Performance 56 ........................................................................................................ 5.2.1 Endurance and Range: 57 ...................................................................... 5.3 Glide with Engine Inoperative 58 ................................................................................................ 5.4 Stalling Speed 58 ....................................... 6 Mass and Balance / Equipment List 60 ............................................................................................ 6.1 Maximum Mass 60 ...................................................................... 6.2 Center of Gravity Limitations 60 ................................ 6.3 F8L / I-DIET Zero Fuel Mass and Centre of Gravity 60 .............................................................................. 6.3.1 Centre of Gravity Range and Limitations 61 .......................................................... 6.3.2 Centre of Gravity Calculation Example + Empty Sheet 61 .............................................................................................. 6.4 Equipment List 62 Flight Manual Falco F8L / I-DIET 3rd Revision 7 of 67 1. Description of the Airplane and its Systems The F.8L Falco is a two seat aircraft with side by side seating for the pilot and passenger and provisions for adding a third seat in the luggage compartment behind the pilot and passenger's seat. This third seat is limited to a maximum weight of 90 pounds. On I-DIET this seat is not installed. 1.1 ENGINE AND ENGINE CONTROLS The engine is the 180 hp Lycoming AEIO-360 B1E with a constant-speed propeller installed. The engine controls consist of throttle, propeller and mixture control levers located in a center throttle quadrant. These controls are connected to the engine by Teflon-lined stainless- steel push-pull control cables. A friction control knob is located on the left side of the throttle quadrant. Alternate air (for the fuel injected engine) are provided. The control is located below the center throttle quadrant. 1.2 LANDING GEAR The tricycle landing gear is retractable, operated by a single electric motor which drives screw-jacks to each of the gear legs. A hand crank is provided for emergency operation. The hand crank is located under a cover on the console between the pilot and passenger's seats. The landing gear switch is located in the middle of the instrument panel. The switch has a wheel-shaped knob, and the switch is of the lever-lock type to prevent the accidental operation of the switch. The landing gear switch has two positions, “Up” and “Down”, and the knob must be pulled out before the switch will move. The landing gear indicator lights are located at the top center of the instrument panel next to the landing gear switch. Three green lights indicate that the landing gear is down. A red light indicates that the landing gear is “in transit”: specifically that the landing gear motor is running to retract or extend the landing gear. When the landing gear is fully retracted, both the red and green lights are extinguished. A landing gear warning light is provided in the annunciator panel. In addition, a landing gear warning horn is available. The landing gear circuit has a pitot- pressure switch which senses airspeed and a throttle lever microswitch which senses throttle position. The system is calibrated such that in case a landing is attempted (IAS ≤ 85 knots, MAP ≤ 15 inches) with the landing gear in „UP“ position a warning horn will sound and the red warning light next to the gear lever will flash. Flight Manual Falco F8L / I-DIET 3rd Revision 8 of 67 The landing gear horn may be switched off (for e.g. acrobatics). This switch is located in the annunciator panel, along with a “horn off ” warning light. The landing gear warning light will continue to operate when the horn is switched off. 1.3 FLIGHT CONTROLS AND FLAPS Dual control sticks are provided, and the stick on the right side is removable to allow for freedom of movement for the passenger. The control system transfers the control forces of the sticks to the ailerons and elevator via pushrods and control cables. Rudder pedals are provided for both pilot and passenger. The rudder pedals are connected to the steerable nose gear and rudder with control cables. When the landing gear is retracted, the nose gear is automatically disengaged from the control system. Brakes are provided for the pilot only, and a parking brake valve is located in the console between the pilot's and passenger's seats. An elevator trim tab is provided. It is manually operated by a trim control wheel located in the console between the pilot's and passenger's seats or using the trim switch („U“ for trim up and „D“ for trim down) located on top of the pilot control stick. Alternatively if the AP is switched on but the VNAV modes are not engaged the rotary encoder and pushbutton on the Pro Pilot autopilot control head can be used to electrically operate the elevator trim. The elevator trim control wheel is attached to an angle drive which operates a screw-jack. The electrical trim system is driven by a motor underneath of the trim control wheel which is connected through an elastic ring to the manual trim control wheel. This ring has enough friction to allow the motor to drive the wheel and also enables the pilot to manually override the electrical trim with minimal force if required. The motion of the screw-jack is transferred to the elevator tab by a single push-pull control cable. An indicator for the elevator trim is located on the instrument panel left of the gear handle and indications. The electrical trim system is connected to the two axis autopilot system allowing auto-trimming. The Falco is provided with large, effective slotted flaps for landing and take-off. The flaps are controlled by an electric actuator. The flap switch has a shaped handle and is located on the instrument panel underneath the variometer. The flap indication is located to the right of the flap switch. The flaps can be set to 4 positions briefly moving and holding (more that 0.5 seconds) the flap switch in the desired direction. The flaps will automatically move to the next position (up or down). The 4 positions are "up", "take-off (about 10 degrees down)", "30 degrees down" and "45 degrees down". For normal landing and/or moderate to strong wind situations the flaps are set to the „30 degrees down“ position. The „45 degrees down“ enables slightly lower touch-down speeds and is used for short or grass field landings. Flight Manual Falco F8L / I-DIET 3rd Revision 9 of 67 1.4 AUDIO SYSTEM The audio system is based on a Garmin GMA 340 audio panel with integrated intercom system. The audio panel is located at the bottom of the avionics stack. The push-to-talk switches are located on each control stick. Microphone and phone jacks are located at the center console between the pilot and passenger seat. This audio interface console also provides a stereo audio input jack (3.5 mm) for e.g. music or warnings generated from an external GPS unit. 1.5 ELECTRICAL SYSTEM The Falco has a 14 volts triple bus, noise suppressed electrical system driven by a 60 ampere alternator and backed up by two batteries (one for the main electrical bus and a second for the essential electrical bus). The electrical bus system consists of the main electrical bus, the avionics bus and the essential bus. Each system can be switched separately through switches located to the right of the starter/ignition switch on the instrument panel. The circuit breakers of the push-pull type on the right side of the instrument panel are associated to each bus system and each circuit breaker is marked to which electrical subsystem it belongs. The main bus electrical system is the system which is used for normal operation in combination with the avionics bus. It is connected to the alternator and a battery. In case of an alternator failure the battery is capable of providing at least 30 minutes of power for the main systems in day and night operation. In addition the primary flight display has its own backup battery allowing autarkic and automatic emergency operation if the main bus voltage drops below 12.5 volts. The voltage regulator is set at 14 volts. In the event that the system voltage reaches 16 volts, the voltage regulator will automatically cut off the alternator. The voltage regulator may be reset by switching the alternator switch “off ” and then back “on”. The avionics bus through the separate switching allows the avionics sub-systems to be activated after engine start using only one switch. The essential bus electrical system may be used before starting the engine for getting clearances while using no power from the main battery. The essential bus is supported by its own battery. The essential bus is also a backup electrical system supplying the CRM 2100 engine and systems monitoring, NavCom 1 (Bendix), external NAV input, glare-shield lights, gear and flap systems. The essential battery is rated at 7.5 Ah and provides additional time to land the aircraft at an appropriate airport in case of an alternator failure. The ignition switch is located to the bottom left of the instrument panel. To its right are the separate master and alternator switch. The master switch is provided with a green indicator light. Next to the alternator is the avionics bus switch with a green light on top when switched on. Again next to the avionics switch is the essential bus switch. A read light indicates the essential bus is on. Flight Manual Falco F8L / I-DIET 3rd Revision 10 of 67 Schematic Electrical Diagram of I-DIET 1.6 ENGINE AND AIRPLANE SYSTEMS MONITORING All engine, electrical and the vacuum systems are monitored by an electronic display based monitoring system with integrated LED based backup in case of display failure - the AuRACLE CRM 2100 system. In case of a display failure four green LEDs show whether RPM, oil pressure, amperage and vacuum are within normal operation limits. If one of these systems exceed either the upper of lower limits the corresponding LED will indicate red. The monitoring system display is located in the centre of the instrument panel just above the throttle quadrant for Alt. Start Main Bus Essential Bus Essential Avionics Bus Avionics Bus Alternator 14V / 60 A Main Battery 12 V 33 Ah Ess. Battery 12 V 7.5 Ah Ess. Sw. Avionics Sw. Starter Sw. Alternator Sw. Master Sw. Voltage Regulator Aspen PFD EBB58 Emergency Backup Battery 30 min Flight Manual Falco F8L / I-DIET 3rd Revision 11 of 67 easy reading and accessibility. It includes am automatic visual and aural warning system (annunciation panel) if the system detects and exceeding of limits of the sub-systems it monitors. The system is controlled through a rotating, push knob and a function button. The system provides the following information: • engine rotation per minute (RPM) • manifold pressure • engine power output in horse power and % power • cylinder heat and exhaust gas temperatures in degrees celsius for each of the 4 cylinders including leaning assistance • oil temperature and pressure • fuel pressure • outside air temperature • voltage of main electrical bus (and essential electrical bus is main electrical bus is switched off) and ampere drawn from the alternator • vacuum produced by the dry vacuum pump • fuel information including: fuel remaining, fuel flow, endurance remaining at current fuel flow and endurance remaining at destination (based on flight plan set in NavCom 2) Further information about the operation of the monitoring system is provided in the manual („AuRACLE-Pilots-Guide-Rev-E“). 1.7 INSTRUMENTATION The aircraft contains a complete analog and digital primary instrumentation consisting of • analog (round dial) and digital (tape) airspeed indication, • analog and digital altitude indication, • analog and digital variometer, • artificial vacuum driven horizon, • solid state micro-electro-mechanical systems (MEMS) based digital artificial horizon. The digital indications for airspeed, altitude and vertical speed can be switched off while the analog indications are always on. The primary instrumentation is driven by the same pitot and static system. The two static ports are located on the sides of the fuselage tail cone. In the event that these two ports become clogged, an alternate static source is provided. This is located at the base of the instrument panel Flight Manual Falco F8L / I-DIET 3rd Revision 12 of 67 on the left. The alternate static source is a drain valve, and it is opened by pushing up and turning the two protruding rods to the locked-open position. The pitot tube is located on the left wing and is heated. The switch for the pitot heat is located on the upper, middle part of the instrument panel. The analog airspeed indicator is marked with the operating speeds of the aircraft. The white arc indicates the flap speeds. The white arc is stepped. Full flaps may be used only for the speeds indicated by the broad white arc, while 20° of flaps may be used for the full range indicated by the white arc. The maximum landing gear retraction or extension speed is indicated by a small G . The maneuvering speeds are also indicated, MU for the utility category and MA for the acrobatic category. The digital airspeed indicator replicates the markings on the tape based indication. The rate of climb and altimeter share the pitot static system of the airspeed indicator. The analog artificial horizon is of a special design for acrobatic flight, thus no special procedures are required for acrobatic flight. The analog artificial horizon is operated by the vacuum system, and a suction gauge indication is provided on the engine monitoring system. A filter is provided to supply clean air to this instruments This filter is located on the forward—away from the pilot— side of the instrument panel, directly in front of the master switch. The suction gauge is vented into the filter, thus the gauge is a proper “differential” gauge, indicating both a clogged filter or a failure of the vacuum pump. The turn-and-bank, slip-skit indicator is integrated in the digital primary flight display as part of the artificial horizon. An alternate analog slip-skit indicator is integrated in the autopilot head unit. Refer to the documentation of the digital primary flight instrument (PFD) for further information (see „EFD1000_PFD_Pilots_Guide“). 1.8 AUTOPILOT SYSTEM A digital two axis autopilot with automatic flight envelope protection is available and located on the instrument panel next to the avionics stack. The flight envelope protection system, which is automatically engaged when the autopilot and servos are activated, prevents the aircraft from stalling, over-speeding or over-stressing. The autopilot has a pilot override function through a clutch system integrated in the servos driving the aircraft aileron and elevator control. This way the pilot may at any time override an engaged servo if required. The autopilot is connected to the internal GPS 1 / NAV 2 or PFD system. It may also be connected to an external source (GPS via RS 232 or ARINC 429). The source may be selected through two switches located on the instrument panel above the PFD. The selected source is Flight Manual Falco F8L / I-DIET 3rd Revision 13 of 67 indicated through the switch position and a corresponding LED light (see Autopilot Source Setup diagram). Aspen EFD1000 Pro PFD [NAV 2, GPS 1] Garmin 430W Garmin 695 OFF AUTO PILOT OFF AVIONICS ON OFF START BOTH ALTERNATE STATIC OFF ALTERNATOR ON MASTER ON RIGHT LEFT OFF EXTERNAL PFD GPS PITOT HEAT OFF OFF NAV LIGHT INT LIGHT OFF OFF OFF OFF FUEL PUMP LNDG LIGHT STROBE LIGHT AUTOPILOT SOURCE OFF ESSENTIAL ON TRIM UP WARN TRIM DOWN HORN OFF Pro Pilot AP GPS 1 (GPSS/GPSV) GPS 1 GPS FTPLN Autopilot Sources Setup If the autopilot is directly switched to the Garmin 430W GPS source and a flight-plan is active the autopilot will follow the flight plan route using GPSS steering (blue LED is illuminated). Alternatively if a Garmin 430W GPS flight-plan is active but the autopilot source switch selects the Aspen PFD as a source the autopilot tracks the route on a waypoint basis rather than through GPSS steering. In GPSS mode the Pro Pilot autopilot will follow the ARINC roll commands to the extent that it will fly complete horizontal flight plans (as entered into the GPS receiver), including procedure turns and some holding patterns. The autopilot is capable of flying the aircraft shortly after takeoff until short before landing (even providing RNAV(GNSS) APV approach capabilities) using horizontal and vertical modes. The power setting and leaning has to be done by the pilot. Flight Manual Falco F8L / I-DIET 3rd Revision 14 of 67 In horizontal mode the autopilot requires a valid GPS position either from the internal or external GPS source. The internal GPS source (being the GPS from the NavCom 2) only provides GPS position data if either a valid flight plan or at least a direct-to is activated. The autopilot will indicate "no GPS" if neither is activated and only the wing leveling function can be used. If a flight plan is available to the autopilot in horizontal mode the autopilot can be used to follow the flight plan, follow a selected course or intercept a track after a course deviation. The horizontal mode supports GPSS if it is provided by the GPS source. In the vertical mode the autopilot can be used to hold an altitude, follow a selected vertical speed and automatically level off at a target altitude. The vertical mode also provides an airspeed capture mode which might be used to climb or descend at a given airspeed. The vertical airspeed mode supports GPSV if the GPS source is programmed to follow an APV approach. The vertical modes also interface to the electrical trim system performing automatic trimming of the aircraft if required. This feature is especially helpful in vertical speed modes in combination with automatic leveling off, or during APV approaches done to minimums providing the pilot a properly trimmed aircraft upon disengagement of the autopilot on short final. The automatic trimming is only available with flaps up (zero position). This is a safety feature to prevent any out- of-trim situation during approach with speed below 100 knots IAS. Electric trimming from the control stick or manual trimming using the trim wheel is available. The autopilot is capable of executing an APV approach as provided by an appropriate GPS navigation system. On the left control stick there is an autopilot disconnect switch (black rocker switch) which can be used to disengage all servos from the controls. The autopilot disconnect switch also provides the „pilot control steering“ functionally. Upon pressing and holding the button (for more than 5 seconds) the aircraft can be manually flown to a given course, vertical speed (min. 200 feet/min) and altitude which is then hold by the autopilot switching to the appropriate modes upon depressing the button again. The autopilot is dually switched. The system itself has an on/off switch on the control head. In addition a separate switch and LED indication is provided on the instrument panel. The autopilot system is powered from the avionics bus. Refer to the autopilot manual for further information on the operation of the autopilot (see „Pro Pilot Manual“). 1.9 ANGLE-OF-ATTACK / STALL WARNING SYSTEM An computer controlled angle-of-attack system is available supporting speed control during approaches, best gliding and it provides stall warning. The system consist of pressure ports on the upper and lower side of the starboard (i.e right) wing, interfaces to the pitot and static system of the aircraft and a computer supported by the main electrical bus. The angle-of-attack is calculated comparing the pressure differences from the pressure ports and is supported by a flaps Flight Manual Falco F8L / I-DIET 3rd Revision 15 of 67 switch for clean and landing configurations. The system provides visual indications to the pilot using an LED bar which is located on the instrument panel left of the accelerometer. In addition the system provides voice warnings through the intercom system if the angle-of-attack is reaching a critical level (i.e. stall warning if the speed drops to below 1.15 times the stall speed in either clean or landing configuration; this is an accordance with the CS-23 rules requiring a stall warning not later than 5 knots before an imminent stall and no warnings during normal landing an takeoff procedures). Angle-of-attack as a function of the pressure coefficient and corresponding LED indications An accelerometer is provided on the left side of the instrument panel. This instrument has a green arc for the Utility category. Red lines are provided for the Utility category and for the Acrobatic category, and each is marked with a U or A. 1.10 NAVIGATION SYSTEMS The aircraft has full set of navigation instruments with area navigation capability allowing normal instrument flying. The navigation instruments include: ADVANCED APPLICATIONS | Jan. 1, 2004 70 Sluing Angle advisory and Performance Data (only available on the Pro) We shall assume that the angle advisory coefficient of pressure was established by flying at 1.15Vs and the local pressures vary linearly with AOA. The design of the display is such that by maintaining an AOA abeam the donut (light bars 16 through 31), the aircraft is operating at about 1.4Vs. An AOA that lights up the split green segment and above (light bars 12 through 31) would result in the aircraft operating at about 1.5Vs. Flight Manual Falco F8L / I-DIET 3rd Revision 16 of 67 • localizer and glideslope information with minimums setting displayed as part of the ADI of the primary flight display; the marker beacons are integrated in the GMA 340 audio panel, • a digital horizontal situation indicator (HSI) with multiple source switching (NAV 1, NAV 2, Internal GPS and External GPS) and autopilot interface as part of the primary flight display, • conventional course deviation indicator (CDI) with localiser and glideslope information displaying information from NAV 1, and on the avionics stack a - BendixKing KX155 as NavCom 1 - Garmin GNS 430W as GPS 1 / NavCom 2 with integrated CDI - BendixKing KN64 DME linked to the NavCom 1 A magnetic compass is provided above the instrument panel at the center of the airplane. 1.11 AIRCRAFT LIGHTNING The Falco is provided with dual circuits for the instrument panel lighting and each is controlled with a solid state dimmer. The combined switch/dimmers are located on the right side of the instrument panel. The dimmers control the internal lighting of the cluster of instruments, most avionics, and the magnetic compass. In addition, the glare shield has green lighting strips which illuminate the instrument panel. The LEDs are dimmed as "high" or "low" illumination using a switch above the two dimmers. A landing light switch is located in the row of switches above the altimeter and standby vacuum horizon. The switches for the navigation and anti-collision (strobe) lights are located in the same row, along with their blue indicator lights. 1.12 FUEL CONTROL The fuel selector valve is located below the throttle quadrant. The valve has four positions, one for each tank, a "both" position and an “off ” positions. The front tank is normally used during takeoff. The "both" position may be used during cruise to balance fuel between the front and aft tank. The aft tank is used for aerobatics especially sustained inverted flight. Only the aft tank is connected to the inverted header tank with a capacity of 2 gallons for approximately 10 min flight time. An auxiliary electric fuel pump is provided for aircraft with fuel injected engines. The switch is located in the row above the altimeter, along with its red indicator light. 1.13 OTHER SYSTEMS Flight Manual Falco F8L / I-DIET 3rd Revision 17 of 67 Fresh air is provided from a vent located on the front side of the cockpit, below the instrument panel. The amount for fresh air is controlled through a knob located below the throttle quadrant. Cabin heat is controlled by a knob located below the throttle quadrant. Adjustable ball valves are located underneath the instrument panel, each for the pilot and passenger. The seats are adjustable fore-and-aft, and the seat or back cushions can be removed to accommodate a back-type or seat-type parachute. The restraint system consists of a five-point harness for pilot and passenger. Each belt end may be individually inserted into the buckle. After take-off, the two shoulder belts may be released by pressing on a metal tab on the upper back of the buckle. This allows the other belts to remain in place. 1.14 INSTRUMENT PANEL The instrument panel with systems operative Flight Manual Falco F8L / I-DIET 3rd Revision 18 of 67 ESS NAV COM 1 EXT NAV FLAP GEAR ENG MNTR GSHLD LIGHT RIGHT A O A OFF NAV COM 1 NAV COM 2 INT GPS XPDR DME MKR ACU A/P ALTERNATE STATIC START BOTH LEFT MASTER ON OFF OFF DIM TEST ALTERNATOR ON HORN OFF OFF L N D G G E A R OFF OFF OFF WARN OFF OFF OFF OFF OFF GPS PFD ESSENTIAL ON FLAPS 45 DEG 30 DEG T/O UP TRANSIT DOWN AUTO PILOT PITOT HEAT INT LIGHT NAV LIGHT STROBE LIGHT LNDG LIGHT FUEL PUMP MAIN AVIONICS AVIONICS ON EXTERNAL AUTOPILOT SOURCE GEAR ACT FLAPS ACT PITOT HEAT NAV LIGHTS ALT FLD PFD LNDG LIGHTS FUEL PUMP ACL AUX EXT NAV FLAP GEAR ENG MNTR GSHLD LIGHT PANEL LIGHT AOA TRIM FUEL QTY LED HIGH LOW DIMMER DOWN UP TRIM DOWN TRIM UP GLARESHLD 1 2 3 4 5 6 7 8 9 10 11 12 13 14 15 16 17 18 19 20 21 22 23 The instrument panel with numbers pointing to the different instrument, gauges and sections which are described in detail in the following table Number Description 1 Ignition switch (Off, Right, Left, Both, Start) 2 Main switches (buses): Master, Alternator, Avionics and Essential 3 Angle-of-Attack System (AOA) with indication, dimming and test switch 4 G-Meter 5 Digital Chronometer from Thommen 6 CDI from Bendix-King (connected to Bendix KX 155 = NAV 2), available on Master and Essential Bus with Avionics switched ON 7 Airspeed Indicator (analog) 8 Aspen EFD 1000 Pro as primary flight display (PFD) 9 Autopilot source switches: PFD/GPS (if internal) and External 10 System and Light switches: Fuel Pump, Landing Light, Strobe Lights, Navigation Lights, Internal (Instrument) Lights, Pitot Heat, Autopilot 11 Variometer (analog) 12 Altimeter (analog) 13 Vacuum driven Artificial Horizon (Attitude gyro) - backup for PFD Flight Manual Falco F8L / I-DIET 3rd Revision 19 of 67 Number Description 14 Trim Indication (LED based) 15 Trio Pro Pilot Autopilot System 16 Gear System: Gear Up/Down lever, Warning switch, Transition Light, Horn Off Light, Warning Light, Gear Down Lights 17 Avionics Stack (from top): Bendix-King KX155 Nav/Com (NAV 2 / COM 1), Bendix King KN64 DME, Garmin 430W (GPS/Nav/Com (GPS 1 / NAV 1 / COM 2), Garmin GTX 328 Mode S Transponder, Garmin GMA 340 Audio/Intercom Panel 18 Lighting Regulation: LED intensity high/low, Internal light dimmer, Glare- shield light on/dimming 19 Circuit Breaker Board for Main, Avionics and Essential Buses 20 AuRACLE CRM 2100 Engine and System Monitoring Display including interfaces and backup LEDs (RPM, Oil Pressure, Ampere, Suction Inst.) 21 Flaps System: Lever and Indication (UP, T/O, 30°, 45°) 22 Analog Fuel Gauges: Front Tank and Aft Tank 23 Alternate Static Source Lever (underneath Instrument Panel) 1.14.1 Placards Lights and Dimming FLAP GEAR PITOT HEAT ENG MNTR NAV LIGHTS HIGH LED DIMMER LOW AUX EXT NAV FLAPS ACT GEAR ACT GLARESHLD INT GPS XPDR NAV COM 2 NAV COM 1 UP T/O 30 DEG 45 DEG FLAPS Flight Manual Falco F8L / I-DIET 3rd Revision 20 of 67 AVIONICS FLAP GEAR PITOT HEAT PFD AOA LNDG LIGHTS PANEL LIGHT GSHLD LIGHT ENG MNTR ALT FLD NAV LIGHTS MAIN FUEL QTY TRIM ACL FUEL PUMP HIGH LED DIMMER LOW AUX EXT NAV FLAPS ACT GEAR ACT GLARESHLD INT GPS FLAP GEAR EXT NAV NAV COM 1 ACU MKR DME XPDR ENG MNTR A/P GSHLD LIGHT ESS NAV COM 2 NAV COM 1 UP T/O 30 DEG 45 DEG FLAPS Flaps System and indications FLAP GEAR EXT NAV AUX TRIM FUEL QTY GSHLD LIGHT ENG MNTR PANEL LIGHT AOA ACL FUEL PUMP MAIN LNDG LIGHTS ALT FLD NAV LIGHTS PITOT HEAT GEAR ACT FLAPS ACT EXT NAV MKR GSHLD LIGHT A/P ENG MNTR ACU FLAP GEAR PFD ESS AVIONICS NAV COM 1 DME XPDR NAV COM 1 NAV COM 2 INT GPS Main, Avionics and Essential Buses Flight Manual Falco F8L / I-DIET 3rd Revision 21 of 67 OFF AUTO PILOT OFF AVIONICS ON OFF START BOTH ALTERNATE STATIC OFF ALTERNATOR ON MASTER ON RIGHT LEFT OFF EXTERNAL PFD GPS PITOT HEAT OFF OFF NAV LIGHT INT LIGHT OFF OFF OFF OFF FUEL PUMP LNDG LIGHT STROBE LIGHT AUTOPILOT SOURCE OFF ESSENTIAL ON A O A TRIM UP UP WARN DOWN TRIM DOWN DOWN HORN OFF TRANSIT L N D G G E A R DIM TEST Systems, Lights, Autopilot, Trim Indication and Gear System OFF AUTO PILOT OFF AVIONICS ON OFF START BOTH ALTERNATE STATIC OFF ALTERNATOR ON MASTER ON RIGHT LEFT OFF EXTERNAL PFD GPS PITOT HEAT OFF OFF NAV LIGHT INT LIGHT OFF OFF OFF OFF FUEL PUMP LNDG LIGHT STROBE LIGHT AUTOPILOT SOURCE OFF ESSENTIAL ON TRIM UP WARN TRIM DOWN HORN OFF Autopilot Sources switches and indications OFF AUTO PILOT OFF AVIONICS ON OFF ALTERNATE STATIC ALTERNATOR ON MASTER ON OFF ERNAL PITOT HEAT OFF OFF NAV LIGHT INT LIGHT OFF CE OFF ESSENTIAL ON A O A TRIM UP UP WARN DOWN TRIM DOWN DOWN HORN OFF TRANSIT L N D G G E A R DIM TEST Angle-of-Attack System including switches and indication OFF AUTO PILOT OFF AVIONICS ON OFF START BOTH ALTERNATE STATIC OFF ALTERNATOR ON MASTER ON RIGHT LEFT OFF EXTERNAL PFD GPS PITOT HEAT OFF OFF NAV LIGHT INT LIGHT OFF OFF OFF OFF FUEL PUMP LNDG LIGHT STROBE LIGHT AUTOPILOT SOURCE OFF ESSENTIAL ON A O A TRIM UP UP WARN DOWN TRIM DOWN DOWN HORN OFF TRANSIT DIM TEST Ignition, Main switches (Master, Alternator, Avionics and Essential) and Alternate Static Source Flight Manual Falco F8L / I-DIET 3rd Revision 22 of 67 FRESH AIR CABIN WARM / COLD AIR BLENDER ALTERNATE AIR INTAKE Fuel Selector Push/Pull Levers for Warm/Cold Air, Fresh Air and Alternate Air Intake Middle: Fuel Selector (Off, Front, Both, Aft) 1.15 AIRCRAFT DIMENSIONS AND SPECIFICATIONS 1.15.1 Aircraft Dimensions Flight Manual Falco F8L / I-DIET 3rd Revision 23 of 67 Three-side view of the F8L Dimensions Dimensions Wings Wings Wing Area 107.5 sq ft (9.9871 m2) Wing span 26’ 3'' (8.001 m) Aspect ratio 6.4 Dihedral 5.5° Washout 3° Flight Manual Falco F8L / I-DIET 3rd Revision 24 of 67 Dimensions Dimensions Airfoil, wing root NACA 642 212-1/2 Airfoil, wing tip NACA 642 210 Ailerons Ailerons Percent of wing span 38 % Average relative chord 30 % Movement 24° up, 16° down Area (each) 3.45 sq ft (0.3205 m2) Flaps Flaps Percent of wing span 39 % Average relative chord 30 % Movement Neutral to 45° down Surface area (each) 5.06 sq ft (0.4701 m2) Fuselage Fuselage Overall length 21’ 4” (6.502 m) Interior width (cockpit) 40” (1.016 m) Height 7’ 6” (2.286 m) Horizontal tail surfaces Horizontal tail surfaces Span 9’ 10.11” (3 m) Total area 23.44 sq ft (2.1776 m2) Aspect ratio 4.1 Fixed surface 14.44 sq ft (1.3415 m2) Movable surface 9 sq ft (0.8361 m2) Movement 22° up, 16° down Elevator trim tab Elevator trim tab Flight Manual Falco F8L / I-DIET 3rd Revision 25 of 67 Dimensions Dimensions Surface area .39 sq ft (0.0362 m2) Movement 20° up, 20° down Vertical tail surfaces Vertical tail surfaces Height 4’ 2.6” (1.285 m) Total area 10.88 sq ft (1.0108 m2) Movable surface 5.21 sq ft (0.484 m2) Movement 20° left, 20° right 1.15.2 Landing Gear Specifications Landing Gear Specifications Landing Gear Specifications Landing gear, main Landing gear, main Width 6’ 10” (2.083 m) Tire size 5.00 x 5 or 5.30 x 6 Tire pressure 30 psi (2.1 bar) Oleo strut pressure 600 psi (41.4 bar) Cleveland wheel (40-78B) and brake (30-9) with upgrade #199-93 kit installed for increased braking capacity. Cleveland wheel (40-78B) and brake (30-9) with upgrade #199-93 kit installed for increased braking capacity. Landing gear, nose Landing gear, nose Tire size 11.4 x 5 Tire pressure 30 psi (2.1 bar) Oleo strut pressure 115 psi (7.9 bar) 1.15.3 Engine & Propeller Specifications Engine & Propeller Specifications Engine & Propeller Specifications Engine Engine Lycoming AEIO-360-B1E Lycoming AEIO-360-B1E Flight Manual Falco F8L / I-DIET 3rd Revision 26 of 67 Engine & Propeller Specifications Engine & Propeller Specifications Nominal power 180 hp at 2,700 RPM Cruising RPM, 75% power 2450 Cruising RPM, 65% power 2350 Propeller Propeller MT-Propeller MTV-12-B 183-59b hub serial no.: 110090 blade serial no.1: ABK-41358 no.2: ABK-41359 no.3: ABK-41360 MT-Propeller MTV-12-B 183-59b hub serial no.: 110090 blade serial no.1: ABK-41358 no.2: ABK-41359 no.3: ABK-41360 Pitch setting at 30” station low: 13° high: 30° Diameter: 72” (1.829 m) Spinner MT-Propeller P-615-1, MTV-12-B 1.15.4 Fuel and Lubrication Specifications Fuel and Lubrication Specifications Fuel and Lubrication Specifications Fuel Capacity Fuel Capacity Front tank 21 U.S. gallons (79.5 liter) Aft tank 19 U.S. gallons (71.9 liter) Inverted header tank 2 U.S. gallons (7.6 liter) Total 42 U.S. gallons (159 liter) Total cruise usable 40 U.S. gallons (151.4 liter) Fuel Grade Avgas 100LL Oil Capacity 8 qts (7.5 liter) Oil Used Oil Used Above 60°F (15.5 °C) SAE 50 32°F to 90°F (0°C to 32.2 °C) SAE 40 Flight Manual Falco F8L / I-DIET 3rd Revision 27 of 67 Fuel and Lubrication Specifications Fuel and Lubrication Specifications -4°F to 68°F (-20°C to 20°C) SAE 30 Below 14°F (-10°C) SAE 20 Note: Mineral oil is recommended during engine break-in (first 50 hours). Note: Mineral oil is recommended during engine break-in (first 50 hours). Flight Manual Falco F8L / I-DIET 3rd Revision 28 of 67 2 Operating Limitations The following limitations must be observed when flying the F8L Falco I-DIET with the Lycoming AEIO 360 B1E engine. 2.1 SPEED LIMITATIONS Airspeed TIAS TIAS Remarks Vne Maximum speed, never exceed speed in smooth air 208.5 knots 208.5 knots do not exceed this speed in any operation Vno Maximum structural cruise speed 161 knots 161 knots do not exceed this speed except in smooth air and with caution Utility Acrobatic Va Maneuvering speed 122 knots 135 knots do not make full or abrupt control surface movements above this speed vle Maximum landing gear extension speed 108.5 knots 108.5 knots do not extend the gear above this speed (except in emergencies; inspection is required in this case) Flaps extension speed for flaps beyond T/O setting 97.5 knots 97.5 knots beginning of white arc (analog indicator) beginning of white strip (PFD) vfe Maximum full flaps extension speed 87 knots 87 knots beginning of broader white arc (analog indicator) 2.2 AIRSPEED INDICATOR MARKINGS Marking CAS Significance White arc / band 53 - 97.5 knots operating range from Vs0 (stall speed with full flaps) to maximum flaps extension speed Flight Manual Falco F8L / I-DIET 3rd Revision 29 of 67 Marking CAS Significance Green arc / band 65 - 161 knots normal operating range Yellow arc / band 161 - 208.5 knots caution range (only smooth air) Red line 208.5 knots never exceed speed only on analog airspeed indicator only on analog airspeed indicator only on analog airspeed indicator MA 135 knots maneuvering speed, acrobatic MU 122 knots maneuvering speed, utility G 108.5 knots maximum speed gear down 2.3 LOAD LIMIT FACTORS AND MARKINGS Category Positive Negative Markings Utility category 4.4 g 2.2 g green arc on analog G-Meter; red line „U“ on upper and lower limits Acrobatic category 6 g 3 g red line „A“ on upper and lower limits 2.4 MARKINGS ON ANALOG FUEL GAUGES Tank Markings Quantity Front Tank green band 3 - 21 US gallons Front Tank red band 0 - 3 US gallons Aft Tank green band 3 - 19 7/8 US gallons Aft Tank red band 0 - 3 US gallons 2.5 LIMITATIONS AND MARKINGS ON AURACLE SYSTEM MONITOR Flight Manual Falco F8L / I-DIET 3rd Revision 30 of 67 Item Markings Values RPM red line 2700 RPM RPM normal range (blue arc) 0 - 2700 RPM Oil Pressure Minimum Pressure (red arc) 25 psi Oil Pressure Caution Range, idling (yellow arc) 25 - 60 psi Oil Pressure Normal range (green arc) 60 - 90 psi Oil Pressure Caution Range, warm up (yellow arc) 90 - 100 psi Oil Pressure Maximum pressure (red arc) 100 psi Oil Temperature Caution range, warm up (yellow arc) 0 - 100°F (0 - 38°C) Oil Temperature Normal range (green arc) 100 - 245°F (38 - 118°C) Oil Temperature Maximum (red arc) from 245°F (118°C) Fuel Pressure Normal operating range 0 - 9.5 psi Fuel Pressure Maximum pressure (red; warning) from 9.5 psi Cylinder Head Temperature (CHT) Normal operating range (green bars) 65 - 224°C Cylinder Head Temperature (CHT) Caution range (yellow bar) 224 - 260°C Cylinder Head Temperature (CHT) Maximum temperature (red, warning) 260°C Suction Gauge Normal operating range (green arc) 4.5 - 5.4 inches Hg. (0.152 - 0.183 bar) Alternator Amp Markings Normal operating range (green arc) 0 - 48 Amps Alternator Amp Markings Caution Range (yellow arc) 48 - 60 Amps Alternator Amp Markings Maximum (red arc) 60 Amps 2.5 APPROVED MANEUVERS 2.5.1 Utility Category: Flight Manual Falco F8L / I-DIET 3rd Revision 31 of 67 It is prohibited to apply full flight controls at speeds higher than maximum maneuvering speed. Only the following aerobatic maneuvers are permitted with the recommended entry speeds shown: Steep turn: 126 knots Chandelle: 126 knots Lazy eight: 126 knots Stall (except snap roll): 65 knots 2.5.2 Acrobatic Category: It is prohibited to apply full flight controls at speeds higher than maximum maneuvering speed. Recent wind-tunnel research in France has shown that abrupt maneuvers can put excessive loads on the wings of some aircraft, even below the maneuvering speed. This phenomenon is particularly apparent in aircraft with very clean wings, like the Falco. For this reason, the full and quick deflection of the elevator as speeds below or equal to the maneuvering speed can cause loads in excess of the limit load factors and cause structural damage and failure. Because of this, the maximum speed for snapped maneuvers is 105 kts. The recommended entry speeds for the main acrobatic maneuvers are as follows: Spin: Stall Loop: 160 knots Roll: 135 knots Immelman: 160 knots 2.6 OPERATING ALTITUDE The maximum demonstrated operating altitude is 16 500 feet (5 030 meters). Under normal conditions and above 12 500 feet it is mandatory for the pilot to use supplemental oxygen. 2.7 FLIGHT CREW Minimum Crew member: 1 person (pilot) Maximum number of occupants: 2 persons (pilot and passenger) Flight Manual Falco F8L / I-DIET 3rd Revision 32 of 67 It is mandatory for each pilot flying I-DIET as pilot in command to be operationally checked out by the owner/ manufacturer and primary pilot Dr. Raoul Schild. The successful check-out has to be approved by ENAC. The minimum conditions for a pilot-in-command according to ENAC NAV-15D apply. 2.8 KINDS OF OPERATION Provided that national operational requirements are met, the following kinds of operation are approved: • daytime flights according to Visual Flight Rules (VFR) with visibility of the ground; • daytime flights according to Visual Flight Rules (VFR) without visibility of the ground; and • IFR daytime flights in visual meteorological conditions (VMC). Flights into known or forecast icing conditions are prohibited. Flights into areas of known thunderstorms or expected lightning activity are prohibited. Flights in the vicinity of installation with known HIRF activity (e.g. defined in navigation maps; usually are restricted or prohibited areas) such as weather and (military) surveillance radar or equivalent facilities are prohibited as they may cause harm to the electronic and navigation equipment of the aircraft. The category of operation is stated in the actual, valid permit-to-fly as approved by ENAC. 2.8.1 Minimum operational equipment (serviceable) The following table lists the minimum serviceable equipment required by circolare NAV-15D, REGOLAMENTO TECNICO ENAC - TITOLO TERZO, and EASA CS-23 (as far as it applies). Additional minimum equipment for the intended operation may be required by national operating rules and also depends on the route to be flown. No ADF system is installed. Therefore procedures (i.e. NDB approaches) requiring an ADF system cannot be flown with the Falco F8L I-DIET. Flight Manual Falco F8L / I-DIET 3rd Revision 33 of 67 minimum operational equipment (serviceable) minimum operational equipment (serviceable) minimum operational equipment (serviceable) minimum operational equipment (serviceable) Equipment Categories daytime flights according to Visual Flight Rules (VFR) with visibility of the ground; daytime flights according to Visual Flight Rules (VFR) without visibility of the ground IFR daytime flights in visual meteorological conditions (VMC) Flight and navigation instruments • airspeed indicator • altimeter • magnetic compass • 1 headset • vertical speed indicator (VSI) • attitude gyro (artificial horizon) • turn & bank indicator • directional gyro • OAT indicator • chronometer with indication of hours, minutes, and seconds • VHF radio (COM) with speaker and microphone • VOR receiver • transponder (XPDR), mode A and mode C • second VHF radio (COM) • VOR-LOC- GP receiver • marker beacon receiver Engine instruments • fuel indicators • integrated engine instrument • ammeter (included in AURacle CRM) • voltmeter (included in AURacle CRM) Lighting • position lights • strobe lights (anti collision lights) • landing light • instrument lighting • flood light • flashlight Other operational minimum equipment • stall warning system • fuel quantity measuring device • safety belts for each occupied seat • airplane flight manual • pitot heating system • alternate static valve • essential bus • emergency battery 2.9 OTHER LIMITATIONS 2.9.1 Temperature The airplane must not be operated when its temperature is less than -40 °C (-40 °F). NOTE: Prolonged operation of the airplane in temperatures below -10 °C (14 °F) may have an adverse effect on the battery capacities in case of an alternator failure. Flight Manual Falco F8L / I-DIET 3rd Revision 34 of 67 CAUTION: For cold weather starting of the engine refer to the latest instructions given by the engine manufacturer. 2.9.2 Battery Charge Taking off for an IFR flight with an empty main battery is not permitted. The use of an external power supply for engine starting with an empty main battery is not permitted if the subsequent flight is intended to be an IFR flight. In this case the main battery must first be charged. 2.9.3 Electronic equipment Any electronic equipment may only be operated as long it does not interfere with the installed avionics or systems. Mobile phones shall only be used in emergency situations (e.g. a COM equipment failure) as a backup. Flight Manual Falco F8L / I-DIET 3rd Revision 35 of 67 3 Normal Operating Procedures 3.1 GROUND PRE-FLIGHT CHECK Ignition switch Off (remove key) Parking brake Set Overnight Covers Overnight Covers Pitot tube removed AOA port open/drained Aileron Locks removed Engine Covers removed Canopy Cover removed Engine Compartment Engine Compartment Engine Check condition Oil Check (min. 4q) Alternator Check belt Brake Check fluid level Gascolator Drain water All Openings Check clear Doors All closed Propeller/Spinner Check condition Landing Gear Landing Gear Tire Pressure Check (30 psi) Well Doors Check condition Oleo strut Check (115/600 psi) Flight Manual Falco F8L / I-DIET 3rd Revision 36 of 67 Front fuel tank cap secure, drain Canopy and windshield Clean L.H. Wing Walk L.H. Wing Walk Pitot tube Check condition L.H. Wing, Flap, Aileron Check condition L.H. Wing Nav, Strobe Check condition L.H. static port Check condition Battery compartment closed ELT Check Armed Aft fuel tank cap secure, drain Empennage Empennage Elevator Check condition Trim tab Check condition Rudder Check condition Nav, Strobe Check condition R.H. Wing Walk R.H. Wing Walk R.H. static port Check condition R.H. Wing, Flap, Aileron Check condition R.H. Wing Nav, Strobe Check condition AOA probes Clear, drain Check Maps, Documents, Flashlight, Tools, etc. Check Maps, Documents, Flashlight, Tools, etc. Check Equipment for Water, Alpine Environment if required! Check Equipment for Water, Alpine Environment if required! Check Overnight Equipment Check Overnight Equipment Flight Manual Falco F8L / I-DIET 3rd Revision 37 of 67 If the engine has been inactive for several hours, especially in cold weather, rotate the propeller by hand for two or three complete turns. During cold weather operation, make a thorough check of airplane for freedom from frost, snow and ice on exterior surfaces. 3.2 COCKPIT PRE-FLIGHT CHECK, BEFORE STARTING ENGINE Ignition switch Off (key inserted) Fuel/oil quantity Checked Load Secured Controls Checked Seats Adjusted Seat belts Fastened Parking brake On Canopy Closed (and locked) Landing gear switch Down Fuel selector Front Master switch On (green indicator) Alternator switch On Essential Bus On Strobe On Landing gear 3 x green lights Avionics Off Engine Monitor Check Initialized Fuel Indication Confirm OR Set Voltmeter Check voltage Fuel quantity Check gauges Flight Manual Falco F8L / I-DIET 3rd Revision 38 of 67 Compare to Engine Monitor Fuel Compare to Engine Monitor Fuel Flight controls Full movement 3.3 ENGINE STARTING PROCEDURE Alternate air Off Cold Engine Cold Engine Throttle Open 1/2 Travel Propeller RPM Full increase Mixture Rich Auxiliary fuel pump On until fuel pressure stabilizes (4-5 sec) then Off until fuel pressure stabilizes (4-5 sec) then Off Mixture Lean Throttle Open 1/4 Travel Ignition switch Start Mixture Slowly Move Rich Throttle Retard Oil Pressure Green (30 sec) Warm Engine Warm Engine Throttle Open 1/2 to Full Propeller RPM Full increase Mixture Lean Brakes Step On Ignition switch Start Mixture Slowly Move Rich Flight Manual Falco F8L / I-DIET 3rd Revision 39 of 67 Throttle Retard quickly Oil Pressure Green (30 sec) Essential Bus Off Avionics On 3.4 WARM UP / TAXI Parking brake Release Flaps T/O Brakes Check Instruments Set (Altimeters) 3.5 RUN-UP CHECK Mixture Check Rich Propeller RPM Check Full increase Throttle 1200 RPM, then: Throttle 1200 RPM, then: Suction gauge Green sector Cylinder Temp Green sector Oil Temp Green sector Oil pressure Green sector Ammeter on + side Fuel gauges Check Fuel pressure positive Voltmeter min 12.5 volts Voltmeter min 12.5 volts AOA Test Flight Manual Falco F8L / I-DIET 3rd Revision 40 of 67