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FSD International

Commander 115 TC

Pilot Operating Handbook

- 35 –

Copyright© 2008 by FSD International. All rights reserved.

For use with Microsoft Flight Simulator only. Not to be used for real-world aviation.

4.16.3 TAXIING

When taxiing, move at a safe speed using the minimum power necessary to sustain that speed
without dragging the brakes. If taxiing over gravel surfaces use the minimum engine power

necessary to avoid damage to propeller leading edges.

While taxiing, the airplane controls should be positioned to minimize any potential overturning
tendency brought on by winds or prop/jet blast from nearby aircraft. Into a headwind, use slight up
elevator to lighten the nose gear load and hold ailerons into any crosswind component. Taxiing

downwind, keep the elevator down to prevent any lifting tendency at the tail and hold the ailerons
away from any crosswind component, again to prevent any lifting of the upwind wing.

4.16.4 BEFORE TAKEOFF

WARM-UP

The engine is closely cowled to produce minimum drag in cruising flight. However, except under
the most extreme conditions, no special procedures are necessary during ground operations.
Maximum power runups are net recommended except as necessary to correct maintenance

discrepancies.

MAGNETO CHECK
Check the operation of the magnetos at 1800 RPM. When operating on a single magneto the drop

in engine speed should not exceed 175 RPM. The difference in engine speed while operating on
each single magneto should be no more than 50 RPM. If there is reason to question the magneto

check, the mixture may be leaned to peak power and the magnetos rechecked. At higher altitudes
this leaning may be required for a smooth magneto check. If doubt still remains, a magneto check
at a higher power, say 2000 to 2200 RPM, should confirm the presence or absence of a problem. If

a magneto problem is present, do not fly the airplane until the problem is corrected.
An absence of an apparent drop in engine speed during a magneto check may be an indication of

faulty grounding of one side of the ignition system and should be checked because of the hazard
this condition presents to ground personnel in the vicinity of the airplane while parked.

ALTERNATOR CHECKS

Alternator function can be verified prior to flight by noting ammeter and voltmeter indications. The
ammeter should be showing a gradually decreasing charge indication as the battery recovers from
the engine start. The voltmeter will show a nominal 28 volts if the alternator is on line or a nominal

24 volts if only the battery is functioning.

TAKEOFFS
POWER APPLICATION

Power should be checked early in the takeoff run for adequacy. Manifold pressure should be
approximately equivalent to 29 inches less 1 inch per 1000 feet above sea level. Engine speed

should be 2700 RPM.

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Содержание Commander 115 TC

Страница 1: ...ion and function of the Realism Module Totalizer Handbook Detailed description of the functions and usage of the fuel Totalizer GNS 480 Manual Complete pilot handbook for the Garmin GNS 480 included with the Commander SL30 Manual Handbook for the Apollo NAV2 COM2 radio included with the Commander KR 87 Manual Manual for the Bendix King KR 87 ADF radio ST55X Autopilot Manual Pilot handbook for the ...

Страница 2: ...ICAL SYSTEM EMERGENCIES 19 3 6 MISCELLANEOUS ABNORMALITIES 20 3 7 AMPLIFIED EMERGENCY PROCEDURES 21 4 Normal Procedures 26 4 1 AIRSPEEDS FOR NORMAL OPERATION 26 4 2 PREFLIGHT INSPECTION 27 4 3 EXTERNAL 28 4 4 STARTING ENGINE 30 4 5 BEFORE TAXI 30 4 7 BEFORE TAKEOFF 31 4 8 NORMAL TAKEOFF 31 4 10 BEFORE LANDING 32 4 11 LANDING NORMAL LANDING 32 4 12 SHORT FIELD LANDING 32 4 13 BALKED LANDING GO AROU...

Страница 3: ...FSD International Commander 115 TC Pilot Operating Handbook 3 Copyright 2008 by FSD International All rights reserved For use with Microsoft Flight Simulator only Not to be used for real world aviation ...

Страница 4: ...FSD International Commander 115 TC Pilot Operating Handbook 4 Copyright 2008 by FSD International All rights reserved For use with Microsoft Flight Simulator only Not to be used for real world aviation ...

Страница 5: ...s 1 478 71 kg Maximum Take off 3 250 lbs 1 474 17 kg Standard Empty 2 102 lbs 953 45 kg Max Baggage Compartment 200 lbs 90 72 kg Standard Useful Load 1 158 lbs 525 26 kg 1 4 FUEL OIL CAPACITY Fuel 90 US gal 88 usable 340 65 liters 333 08 usable Oil 8 quarts 7 57 l 1 5 WING AREA LOADINGS Wing Area 152 sq ft 14 12 sq m Wing Loading 21 4 lbs sq ft 104 48 kg sq m Power Loading 12 5 lbs hp 5 67 kg hp 1...

Страница 6: ...by the Federal Aviation Regulations Similarly all required instrument markings and placards must be maintained in a legible and usable condition on the airplane 2 1 SPEED LIMITATIONS SPEED SYMBOL KCAS KIAS SIGNIFICANCE Never Exceed ASL 12500 ft 16000 ft 20000 ft 24000 ft VNE 186 175 161 147 187 176 161 147 Do not exceed this speed in any operation Maximum Structural Cruise ASL 12500 ft 16000 ft 20...

Страница 7: ... MARKING KCAS VALUE OR RANGE SIGNIFICANCE White Arc 58 114 Full Flap Operating Range Lower limit is maximum weight zero thrust stall speed in the landing configuration Upper limit is maximum speed allowable with flaps fully extended Green Arc 65 160 Normal Operating Range Lower limit is maximum weight zero thrust stall speed with flaps and landing gear retracted Upper Inuit is maximum structural c...

Страница 8: ...s 86 KIAS 2600 Lbs 76 KIAS 2023 Lbs 66 KIAS Precautionary Landing With Engine Power approach speed 75 KIAS Without Engine Power approach speed 75 KIAS Flaps 35 2 6 POWER PLANT AND PROP LIMITATIONS Maximum Power 260 BHP Rating Engine Operating Limits for Takeoff and Continuous Operations Maximum Engine Speed 2700 RPM Maximum Cylinder Head Temperature 500 F 260 C Maximum Oil Temperature 245 F 118 C ...

Страница 9: ...d for real world aviation 2 7 ENGINE INSTRUMENT MARKINGS 2 8 CENTER OF GRAVITY LIMITS Instrument RED LINE MIN YELLOW ARC GREEN ARC RED LINE MAX Manifold Pressure InHg 10 29 39 Tachometer RPM 2500 2700 2200 2400 2100 Fuel Flow GPH PSI 0 22 Cylinder Head Temp 500 550 200 500 500 Oil Temperature F 100 250 250 270 Oil Pressure PSI 30 90 110 60 90 115 Fuel Pressure PSI 10 10 58 58 ...

Страница 10: ...ter X X X Auxiliary fuel pump X X X Battery X X X Circuit breakers X X X Compass X X X Flap position indicator X X X Engine Gauges X X X Gear locked lights 3 X X X Gear system emergency X X X Gear warn light X X X Gear warning horn system X X X Gyro attitude X Gyro directional X Gyro turn bank indicator or turn coordinator X Instrument panel lighting X Exterior Lights X Propeller governor X X X Pr...

Страница 11: ...ernational Commander 115 TC Pilot Operating Handbook 11 Copyright 2008 by FSD International All rights reserved For use with Microsoft Flight Simulator only Not to be used for real world aviation 2 10 PLACARDS ...

Страница 12: ...obtaining FAA pilot certification Checklists are provided to assist a pilot where it would be reasonable for a pilot to refer to one Where reference to a checklist would be impractical or where the material is not amenable to a checklist form or where additional material is helpful amplified procedures are provided following the checklist section 3 1 ENGINE FAILURES 3 1 1 ENGINE FAILURE DURING TAK...

Страница 13: ... ENGINE POWER Seatbacks UPRIGHT LOCKED Seats Belts Harnesses SECURE Loose Objects SECURE Emergency Locator Transmitter ON Transponder CODE 7700 Airspeed MAINTAIN 85 KIAS flaps UP MAINTAIN 75 KIAS flaps 35 Deg Auxiliary Fuel Pump OFF Fuel Selector OFF Landing Gear DOWN CHECK LOCKED NOTE If the landing site chosen appears to have an extremely soft surface recommended that landing gear remains retrac...

Страница 14: ...ion OFF Auxiliary Fuel Pump OFF Fuel Selector BOTH Landing Gear DOWN VERIFY LOCKED Mixture FULL RICH Propeller Control FULL INCREASE RPM Flaps 35 Deg recommended Power AS REQUIRED Airspeed 75 KIAS Battery Alternator Master Switches OFF when landing assured NOTE Stall warning will not be available with electrical system turned off Touchdown TAIL LOW Brakes AS REQUIRED 3 2 3 DITCHING NOTE AIRCRAFT H...

Страница 15: ... ENCOUNTER 1 Pitot Heat ON 2 Defrost Control FULL ON 3 Engine RPM INCREASE TO 2700 enrich mixture as required 4 Alternate Air PULL ON 5 Course REVERSE OR ALTER as required to avoid icing Evasive action should be initiated immediately when icing conditions are encountered 6 Altitude CHANGE to an altitude less conducive to icing IF ICING CONDITIONS CANNOT BE ESCAPED 6 Airplane LAND AT NEAREST AIRPOR...

Страница 16: ...ear Locked Light s Fails To Illuminate and Red Gear Warn Light Remains On 1 Gear Light Press To Test Switch CHECK green light bulb integrity 2 Gear Motor Circuit Breaker CHECK IN 3 Landing Gear Switch RECYCLE If an unsafe indication persists proceed as follows 4 Gear Motor Circuit Breaker PULL 5 Landing Gear Switch CHECK DN 6 Wing Flaps FULL EXTEND NOTE Gear Warning horn will activate as flaps exc...

Страница 17: ...ulder Harnesses SECURE 3 Loose Objects SECURE 4 Radio TRANSMIT MAYDAY to A TC or on 121 5 mHz if circumstances so warrant 5 Emergency Locator Transmitter ON if circumstances so warrant 6 Transponder CODE 7700 if circumstances so warrant 7 Airspeed 85 KIAS flaps UP 1 75 KIAS flaps 20 7 Fuel Selector Valve BOTH OFF if power is oft 8 Mixture FULL RICH IDLE CUT OFF if power is oft 10 Propeller Control...

Страница 18: ...he good main gear tire 7 Touchdown ON GOOD MAIN GEAR FIRST 8 Aileron BANK AWAY FROM DEFECTIVE GEARITIRE as long as possible 9 If one main gear was still retracted or the airplane begins to lower the wing on the defective 10 Mixture IDLE CUT OFF 11 Fuel Selector OFF 12 Battery Alternator Master Switches OFF 3 4 7 LANDING WITH A DEFECTIVE NOSE GEAR Or Flat Nose Tire 1 Before Landing Checklist COMPLE...

Страница 19: ...1 Voltmeter CHECK between 24 28 volts 12 Ammeter CHECK If ammeter now shows charging alternator is now back on line Electrical equipment may be turned on as desired If ammeter continues to show discharge 13 Alternator Master Switch OFF 14 All Non Essential Electrical Equipment OFF 15 Flight TERMINATE as soon as practical NOTE Excessive load on alternator or alternator failure will cause discharge ...

Страница 20: ... EXTREME TURBULENCE ENCOUNTER 1 Airspeed MANEUVERING SPEED observe speed for flight weight 2 Flaps UP 3 Landing Gear RETRACTED 4 Seat Belts Shoulder Harnesses SECURED 5 Loose Objects SECURE 3 6 2 EMERGENCY DESCENT 1 Landing Gear DOWN below 130 KIAS 2 Flaps UP 3 Throttle IDLE 4 Prop Control HIGH RPM 5 Airspeed 187 KIAS below 12 500 ft 3 6 3 VACUUM PUMP FAILURE INDICATED BY ILLUMINATION OF FAILURE I...

Страница 21: ...airplane on the remaining runway Those extra items in the checklist are to add protection should the runway be too short for the resulting rollout In flight prompt reduction of pitch attitude to obtain and maintain a proper glide speed upon experiencing an engine failure is paramount If the failure has occurred shortly after takeoff a landing should be planned straight ahead with only small change...

Страница 22: ...e needed to maintain airspeed Upon reaching flare height slowly reduce power while adding small amounts of nose up trim to allow touchdown on the main gear 3 7 5 FIRES Engine fires in flight are extremely rare in properly maintained airplanes However the appropriate checklist procedures should be followed if one is encountered After the fire is extinguished execute a forced landing Do not attempt ...

Страница 23: ...NETO MALFUNCTION A sudden engine roughness or misfiring is usually evidence of magneto problems Switching from BOTH to either L or R ignition switch position will identify which magneto is malfunctioning Select different power settings and enrich the mixture to determine if continued operation on BOTH magnetos is possible If not switch to the good magneto and proceed to the nearest airport for rep...

Страница 24: ...accept higher than normal charge rates during the initial part of the flight However after approximately 30 minutes the ammeter indication should have decreased steadily toward a zero reading and the voltmeter should indicate between 24 and 30 volts If the charging rate remains above this value for an extended period of time there is a possibility that the battery may overheat and evaporate electr...

Страница 25: ...ure indicators These indicators are either mechanical SIN 14541 thru 14653 or electrical SIN 14654 and subsequent A vacuum pump failure will be indicated when the suction of that pump drops to 3 5 inches of mercury If the failure of one vacuum pump is indicated then flight may be continued under VFR night and IFR conditions One vacuum pump is adequate to provide suction for the direction gyro and ...

Страница 26: ...ractical or where the material is not amenable to a checklist form or where additional material is helpful amplified procedures are provided following the checklist section 4 1 AIRSPEEDS FOR NORMAL OPERATION Except as noted the following speeds are based on a maximum weight of 3250 pounds and may be used at any lesser weight TAKEOFF Normal Initial Climb 80 90 KIAS Short Field Takeoff Flaps 20 at 5...

Страница 27: ...or Switch ON 7 Alternate Static Source OFF 8 Ignition Switch OFF 9 Electrical Switches OFF 10 Avionics Master Switch OFF 11 Circuit Breakers SET 12 Battery Master Switch ON NOTE Do not activate the airplane s electrical system when anyone is within or near the propeller s arc to prevent potential injury which could result from an electrical malfunction 13 Landing Gear Locked Lights 3 GREEN 14 Fuel...

Страница 28: ...ie Down REMOVE RIGHT SIDE OF TAILCONE AND RIGHT WING TRAILING EDGE 1 1 Static Port UNOBSTRUCTED 2 2 Wing Flap INSPECT 3 3 Aileron CHECK freedom of movement security RIGHT WING LEADING EDGE 1 1 Fuel Vent UNOBSTRUCTED 2 2 Wing Tie Down REMOVE 3 3 Fuel Quantity CHECK VISUALLY for level agreement with gauge NOTE A reduced fuel indicator is located in the fuel filler neck to show a useable fuel quantit...

Страница 29: ... Engine Induction Air Inlet CHECK UNOBSTRUCTED 9 Cowl Flap CHECK POSITION SECURITY 10 Oil Quantity CHECK minimum 6 quarts 11 Chocks REMOVED STOWED LEFT WING LEADING EDGE 1 Fuel Vent UNOBSTRUCTED 2 Wing Tie Down REMOVE 3 Fuel Quantity CHECK VISUALLY for level NOTE A reduced fuel indicator is located in the fuel filler neck to show a useable fuel quantity of approximately 24 gallons 4 Fuel Filler Ca...

Страница 30: ...rcuit Breakers SET 7 Cowl Flap OPEN 8 Fuel Selector Valve BOTH 9 Brakes TEST SET NOTE FLIGHTSIM does not model the startup procedure of the Lycoming engine which requires engine cranking with mixture at idle cut off Normal Flight Sim engine start up procedures apply NORMAL START 1 Throttle OPEN 1 2 INCH 2 Propeller Control HIGH RPM 3 Mixture FULL RICH 4 Alternate Induction Air PUSH COLD 5 Propelle...

Страница 31: ...T as desired 11 SET Throttle for run up check ENGINE SPEED 1800 RPM 12 Magnetos CHECK R BOTH L RPM drop should not exceed 175 on either magneto 13 Constant Speed Propeller control EXERCISE CHECK RPM CONTROL 14 RETURN THROTTLE TO IDLE CHECK IDLE SPEED MAINTAINED WITH THROTTLE CLOSED 15 Engine Instruments CHECK 16 Suction Gauge CHECK vacuum operation of both pumps 12 Throttle 1000 RPM 13 Quadrant Fr...

Страница 32: ...ING 1 Seats Seat Belts Shoulder Harnesses SECURE 2 Auxiliary Fuel Pump Switch ON 3 Fuel Selector Valve BOTH 4 Landing Gear EXTEND 3 GREEN 5 Mixture FULL RICH or set for altitude 6 Propeller HIGH RPM 4 11 LANDING NORMAL LANDING 1 Airspeed 80 to 90 KIAS 2 Wing Flaps AS REQUIRED 35 Deg recommended 3 Airspeed 75 to 85 flaps 35 4 Trim ADJUST as required 5 Gear CHECK 3 GREEN 6 Touchdown ON MAIN WHEELS 7...

Страница 33: ...speed 70 to 75 KIAS NOTE When positive rate of climb is established 5 Wing Flaps RETRACT progressively as airspeed increases 6 Cowl Flaps OPEN 4 14 AFTER LANDING 1 Auxiliary Fuel Pump Switch OFF 2 Strobe Lights OFF 3 Cowl Flaps OPEN 4 Wing Flaps UP 4 15 SHUTDOWN 1 Throttle IDLE 2 Parking Brake SET 2 CHECK EGT WAIT UNTIL IN GREEN 3 Electrical Equipment OFF 4 Avionics Master Switch OFF 5 Mixture IDL...

Страница 34: ...at switch should be examined for cleanliness and serviceability If operations have included gravel fields the propeller leading edges should have any nicks dressed out as they are discovered Fuel caps should be inspected for any deterioration periodically to avoid fuel leakage in flight or water infiltration while parked If night flight is contemplated the operation of all lighting interior and ex...

Страница 35: ...s at 1800 RPM When operating on a single magneto the drop in engine speed should not exceed 175 RPM The difference in engine speed while operating on each single magneto should be no more than 50 RPM If there is reason to question the magneto check the mixture may be leaned to peak power and the magnetos rechecked At higher altitudes this leaning may be required for a smooth magneto check If doubt...

Страница 36: ...f is approved with flap settings from 0 to 20 For normal takeoffs a setting of 10 is recommended to provide a shorter ground roll than will be achieved with no flaps and a better initial climb than will result with 20 The use of 20 flaps is recommended for obstacle clearance takeoffs in accordance with the Short Field Takeoff chart in Section 5 or for any minimum ground run takeoff Due to low clim...

Страница 37: ...feet at the rate of 1 knot per 2000 fect Maximum power for climb is with full throttle 2700 rpm and mixture set full rich Above 8000 feet if necessary the mixture may be leaned for smooth operation If a nearby obstruction requires a steeper climb angle the best angle of climb speed should be used along with maximum available power Best angle of climb speed is 75 KlAS at sea level increasing linear...

Страница 38: ...nough for smoothness As always monitor fuel consumption as the flight progresses The engine may also be leaned to a best power mixture strength for approximately a 3 KTAS increase in speed at a 6 to 10 reduction in range STALLS Stall characteristics for this airplane are entirely conventional with flaps up and down An aural warning of an approaching stall is provided when the airplane angle of att...

Страница 39: ...ED LANDING If a go around is necessary the wing flaps should be reduced to 200 immediately after full power is applied If obstacle clearance is not a factor and the airplane will remain in the traffic pattern for another landing approach it is recommended that the landing gear remain extended COLD WEATHER OPERATION STARTING Prior to starting on a cold morning pull the propeller through several bla...

Страница 40: ...n a trip with less than a ten gallon margin Pilot training for FAA airman certification experience in the particular airplane good judgment conservative planning and attention to all FAR rules applicable to the flight will contribute to a safe and enjoyable trip 5 1 COMMANDER 115 TC PERFORMANCE AND OPERATING LIMITATIONS Engine Management The turbo supercharged engine in this particular installatio...

Страница 41: ...ce over 50 ft Obstacle 1 985 ft 605 02 m CLIMB PERFORMANCE Initial S L Rate of Climb 1 070 ft min 326 14 m min Service Ceiling 16 800 ft 5 120 64 m RANGE Range Performance Cruise 855 NM 14 3 gph 54 13 lph Range Economy Cruise 940 NM 12 6 gph 47 69 lph Range Long Range Cruise 1005 NM 11 2 gph 42 39 lph LANDING PERFORMANCE Ground Roll 720 ft 219 46 m Distance over 50 ft Obstacle 1 200 ft 365 77 m 5 ...

Страница 42: ...TAKEOFF Performance in Standard Atmospheric conditions Airport Elevation In Feet Ground Roll Feet Takeoff over a 50 ft Obstacle In Feet Sea Level 1250 2150 2 000 1450 2300 4 000 1700 2800 6 000 1970 3850 8 000 2300 6900 5 2 Airframe Performance Specifications VA MANEUVERING TURBULENT AIR PENETRATION SPEED Speed KIAS Aircraft Weight lbs 117 3 305 113 3 000 103 2 491 VFE MAXIMUM FLAPS EXTENDED SPEED...

Страница 43: ... NEVER EXCEED SPEED 186 KIAS to 12 500 ft 176 KIAS at 15 000 ft 167 KIAS at 17 500 ft 158 KIAS at 20 000 ft 150 KIAS at 22 500 ft 141 KIAS at 25 000 ft VS STALL SPEED AT MAXIMUM WEIGHT 65 KIAS VS STALL SPEED LANDING CONFIGURATION VX OBSTACLE CLEARANCE CLIMB SPEED VY BEST INITIAL RATE OF CLIMB SPEED Maneuvering Speeds Weight lbs Speed KIAS 3 305 117 3 000 113 2 494 103 60 KIAS 85 KIAS 75 KIAS Best ...

Страница 44: ...imulator only Not to be used for real world aviation Emergency Descent Smooth Air Rough Air Altitude ft ASL Speed KIAS Weight lbs Speed KIAS 25 000 139 3 305 117 22 500 149 3 000 113 20 000 157 2 491 103 17 500 167 15 000 176 12 500 187 VNE This space intentionally left blank Maximum Glide Performance Weight lbs Speed KIAS 3 305 85 3 000 81 2 494 74 ...

Страница 45: ...here it is jointed to the aft fuselage section The center fuselage section houses the seats for pilot and three passengers and has two doors that afford access to the airplane from either side The pilot area is equipped with a wide vision windshield and large door windows The aft fuselage section extending from fuselage station 178 00 to 263 00 is permanently secured to the center fuselage section...

Страница 46: ...ach outboard end for streamlined appearance 6 3 FLIGHT CONTROLS AILERON CONTROL SYSTEM The aileron control wheels are mechanically interconnected through a series of control chains sprockets and cables Control cables extend aft from the control column passing under the floor structure and through idler pulleys to a bracket assembly The cables are then routed through the bracket assembly and out th...

Страница 47: ... the rudder The rudder pedals are connected to rudder bars which in turn are connected to the rudder bell crank with push pull rods Cables are attached to the bell crank and are routed aft through a series of pulleys to the rudder horn When force is applied to one rudder pedal the cables move in opposite directions turning the rudder horn and rudder The pedals are connected to the nose wheel steer...

Страница 48: ...n landing gear wheels Landing shocks are absorbed in the nose gear by a conventional oleo strut assembly and by an oleo strut connecting rod arrangement connected to the trailing arm of the main landing gear Nose wheel steering is controlled by a cable pulley system attached to the nose gear and to the rudder brake pedal and is actuated by depressing the rudder brake pedals from either pilot s pos...

Страница 49: ...ting the gear is down and locked 6 4 BAGGAGE COMPARTMENT The baggage compartment is located in the aft portion of the cabin area Access is through the baggage door on the left side of the airplane or through the cabin area behind the rear passenger seats Volume of the baggage compartment is twenty two 22 cubic feet and maximum allowable baggage weight is two hundred 200 pounds When loading the air...

Страница 50: ... control unit are contained within the throttle body casting installed on the engine intake manifold air inlet Priming is provided by the fuel injection system A separate priming system is not required 6 9 ENGINE COOLING SYSTEM COWLING The cowling consists of two molded fiberglass assemblies which have contoured inlets to control expansion of cooling air as it enters a fixed opening around the tai...

Страница 51: ...FUEL MANAGEMENT It is the pilot s responsibility to ascertain that there is sufficient fuel on board the airplane to safely complete the planned flight A visual check of each fuel tank should be made and this should be compared with quantity indicated on the fuel tank gauges When fuel quantities are checked the airplane should be level to assure that any fuel quantity indication either visual or e...

Страница 52: ...r to start to retract Fluid on the DOWN side of the actuator flows back to the reservoir Movement of the gear from the DOWN and LOCKED position deactivates a down position switch located on each gear drag link causing the three gear DOWN and LOCKED lights to extinguish illuminating the red GEAR WARNING light As each gear is fully retracted it activates a gear up position switch and when all three ...

Страница 53: ...FSD International Commander 115 TC Pilot Operating Handbook 53 Copyright 2008 by FSD International All rights reserved For use with Microsoft Flight Simulator only Not to be used for real world aviation ...

Страница 54: ...d below approximately the 14 in Hg position at low altitude with the gear still retracted or when flaps are extended 25 degrees or more with the gear retracted regardless of throttle position The battery and or alternator master switches must be on for gear warning EMERGENCY GEAR EXTENSION VALVE A red emergency gear extension knob installed in the forward left side of the center console is provide...

Страница 55: ...is becoming overloaded If this situation occurs reduce the load by turning off non essential equipment Voltmeter reading should return to normal approximately 28 volts and the ammeter reading should increase If this occurs proceed with night but use caution in increasing electrical load A low voltage reading less than 12 volts or a slowly decreasing voltmeter reading accompanied by a discharge rea...

Страница 56: ...it breaker switch NOTE The anti collision light should not be used when flying through clouds haze or snow to avoid disorientation due to the flashback LANDING AND TAXI LIGHTS A landing light is mounted on both wing leading edges near the wing tip and a taxi light is mounted on each main landing gear strut These lights are controlled by the LOG LIGHTS and TAXI LIGHTS circuit breaker switches It is...

Страница 57: ... static ports become obstructed causing erroneous static pressure instrument readings the alternate static source valve should be placed in the ON position to provide an alternate source of static pressure When the alternate source valve is in the ON position the normal static ports are isolated and static pressure for the airspeed indicator altimeter and vertical speed indicator is supplied from ...

Страница 58: ...ated by the air flow generated by the aircraft vacuum system while electrical type is operated by aircraft power supply Emergency Pressurization System EPS Activates when the aircraft cabin altitude exceeds the safety limit of 10 500 feet Engine Speed RPM Gauge Indicates engine rotational speed based on a figure of 100 at 1540 propeller rpm Engine Torque Meter Indicates shaft output torque in perc...

Страница 59: ...ured from standard sea level pressure 29 92 inches of mercury 1013 2 millibars by a pressure or barometric altimeter It is the indicated pressure altitude corrected for position and instrument error In this handbook altimeter instrument errors are assumed to be zero Actual atmospheric pressure at field elevation Temperature Recovery Ram Rise Indicated Pressure Altitude Aerodynamic heating which oc...

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