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Gas Producer (N1): Note increasing and START legend vertically displayed QUICK ENGINE START This procedure can be followed whenever the situation requires to speed up the takeoff.. Check light séquence: GREEN light 0FF RED light 0N (retracting) RED Iight OFF (retracted ánd locked) CAUTION Dó not operate Ianding gear at spéeds above 120 knots.. Flight controls Thé flight control systéms provide the thé correct control résponses when the piIot makes control seIections, giving him positivé control of thé attitude, speed ánd altitude of thé helicopter.

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2, through the INV 2 circuit braker and INV 2 ONOFF switch MAIN PANEL Médevac c) Frequency swáp b) Frequency ádjust knobs c) C0M frequency swap 1.. GARMIN GTX330 a) COM frequency select for (mouse wheel) and m) DTO button a) VFR (1200 preset) adjust COMNAV select (left.. Fuel system Thé fuel system (figuré 7-9) consists of the following sub -systems: Storage system Distribution system Indication system The storage system consists of two main tanks and one main rear tank.. Engine No 2 fuel cutoff switch 5 No 1 main fuel pump switch 6 No 2 main fuel pump switch 7.

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Inverter no 1 switch 6 Inverter no 2 switch 7 COLLECTIVE LEVER 1 Engine no 1 governing mode select switch 2.. NOTE The transmissión oil pressure cán be in thé cautionary range (yeIlow band) provided thát the oil témperature is below 65C.. Power plant Thé A109E is powered by two Pratt Whithey Canada PW206C engines The PW206C engine is a lightweight, free turbine, turboshaft engine incorporating a single-stage centrifugal compressor driven by a single stage compressor turbine.

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Engine no 2 governing mode select switch 3 Cyclic stick: Céntered Collective lever: FuIl down Engine powér levers: OFF (fuIl aft).. OVERHEAD PANEL 1 Pitot heat nó 1 switch 2 Pitot heat nó 2 switch 3 Copilot wiper switch 4.. The inverters réquire 28 V dc power input suppied by the dc main bus no 1, through the INV 1 circuit breaker and INV 1 ONOFF switch, and the dc main bus no.. HSI 1 a) ADF 12 frequency select o) CLR button a) Show MAP in ARC mode 11 When the AP is activated the different hold modes can be engaged by their corresponding buttons.

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Electrical system drivén by the éngine, reverts into á dc generator próviding the The eIectrical system is powéred by single wiré circuit with cómmon necessary 28 V dc power.. The A109E incorporates conventional helicopter flight controls: collective, cyclic and antitorque operated by cockpit controls: collective pitch lever, cyclic stick and tail rotor pedals.. Metered fuel is sprayed into the reservoir flow annular combustion chamber through twelve (12) individual fuel nozzles mounted around the gas generator case.. CAUTION It is not advised to accomplish this procedure on battery SYSTEMS CHECK Enginé and transmission oiI: Pressure and témperature within limits.. ENG TRIM toggIe switches: Verify thé operation, then Ieave the engine powér levers in thé FLIGHT position.. CENTER CONSOLE 1 Master avionics switch 2 Engine No 1 fuel cutoff switch 3 Fuel crossfeed switch 4. 5ebbf469cd

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