AW119/ TH-73

The ___________________________ engine is a ________________________ free ____________________ engine.

PT6B- 37A is a lightweight free turbine engine.

The "Free Power Turbine" allows the _______________. ________________(NF) and the ________________. ______________ ( NR) to turn at a constant speed.

Power turbine and Main rotor to turn at a constant speed

When does NR Rotor Low come on?

Rotor RPM between 75 and 96%

How much fuel?

Safe bet is 60 minutes but technically, DAY VFR: Destination + 30 minutes at cruising speed Night VFR: Destination + 45 minutes at cruising speed IFR : Destination + Alternate + 45 minutes at cruising speed

Should a single SAS system fail, aircraft stabilisation will still be provided by the remaining ___________ system.

Should a single SAS system fail, aircraft stabilisation will still be provided by the remaining SAS system.

Ep- Engine Fire On Ground

Shut down engine as follows: 1. Engine throttle: OFF; 2. FUEL VALVE switch: CLOSED; 3. FUEL PUMP 1 and 2 switches: OFF; 4. Xfer PUMP switch: OFF. 5. GEN switch: OFF; 6. BAT switch: OFF. 7. Evacuate helicopter as soon as possible.

Class E VFR Weather Minimums

500 feet below clouds, 1000 feet above clouds, and 2,000 horizontally from the clouds. Less then 10,000 feet

Starter cranking torque is __________, since only the compressor section rotates on ____________.

Low since only the compressor section rotates on start.

Maximum baggage load

Maximum baggage load - 150 kg (331 lb)

TQ Limits

Maximum continuous .................................................................: 100% Take-off (5 minutes) .....................................................: 100 to 108.5% Maximum take-off (5 minutes).................................................: 108.5% Transient (6 seconds)................................................................. : 115%

Maximum gross weight

Maximum gross weight - 2850 kg (6284 lb) A 139 is over 15,000 lbs

N2 limits

Minimum ...................................................................................... : 95% Cautionary......................................................................... : 95 to 101% Continuous operation......................................................: 101 to 103% Maximum ................................................................................... : 103% Transient (10 seconds) .............................................................. : 108%

Minimum airspeed in autorotation:

Minimum airspeed in autorotation: 60 KIAS (without close external references

Minimum gross weight

Minimum gross weight - 1725 kg (3803 lb)

The configuration of the completed aircraft is defined by 11 areas or item designations for the pilot to reference:

Nose compartment Cabin (includes cockpit) Main rotor Upper deck aerodynamic fairings Tail boom Tail rotor Tail cone aerodynamic fairing Rear fuselage Avionics equipment Fuel tank compartment Skid landing gear.

Slope limits:

Nose up: 12 degrees Side-up: 10 degrees Nose down operation: 2 degrees Nose down ( unobstructed tail): 5 degrees

Complete Loss of Tail Rotor Control in Cruise

Nose will YAW RIGHT Lower collective to drive nose LEFT and slow to 60 knots If uncontrollable set up for a field and AUTO

With rotor RPM between _________ and __________, a cabin acoustic signal is activated.

With rotor RPM between 75 and 96%, a cabin acoustic signal is activated.

What are the six AWG MESSAGES?

"ROTOR LOW" "ENGINE OUT" "ENGINE FIRE" "WARNING" "ROTOR HIGH" "ONE HUNDRED FIFTY FEET"

The fuel system consists of the following subsystems:

- The storage system - The distribution system - The indicating system.

For managing NR droop compensation the pilot can select:

-Electronic Engine Control (EEC) - a completely automatic system -Mechanical Engine Control (MEC) - an automatic mode allowing the pilot to use the NR TRIM switch function. Governor is on RGB.

For managing engine fuel control modes the pilot can select:

-Manual (MAN) and correlate (marry) the N2 and NR needles without governance using the twist grip -Normal (NOR) which allows engagement of the functions as selected by the pilot on the EEC/MEC switch.

Normal Approach

1. 1000 feet agl and 100 knots conduct "Before Landing Checks" aka Pre-Landing Checklist 2. Abeam intended point of landing ( landing site) Power reduce to 30 % or by 15% 3. Attitude 5-7 degree nose up for Descending decelerating turn 4. Trim 30 degree AOB and slow to 90 knots 5. 90 at 500 feet agl 6. Final 500 feet and 75 knots plus wind speed 7. Descend at 300-500 fpm 4-7 degree glide slope 8. 300 feet 90 knots 9. 150 feet 75 knots 10. 75 feet coming through 60-70 knots

ITT START LIMITS

1. Below 100 degrees 2. Maximum is 870 degrees C 3. Transient 871- 979 degrees for 10 seconds 4. MAX Transient is 980 - 1090 for 2 seconds

The transmission also drives external system accessories such as:

1. Both hydraulic system pumps 2. The rotor magnetic pickup 3. The oil cooler fan drive.

Normal Takeoff/ Transition to Forward Flight

1. Establish 3 foot hover and note Torque 2. Engage FTR and forward cyclic for ten (10) degrees NOSE down( 119 hovers 5 degrees nose high). Which indicated as 5 degrees above the horizon. Add slight torque to prevent altitude loss. 3. After approximately 5 seconds and at 30 knots Add 15% more power ( approximately 65-80% TQ displayed if not too high, hot or heavy) above hover torque ( approx 45-60%) 3. At 30 knots level to 0 degrees on the horizon and accelerate to 60 knots 4. Release FTR and trim 5. Climb at Vy 60 knots and 70% torque. Do not turn until 600 ft agl.

Six most common weather hazards

1. IFR 2. Mountain obscurantism 3. Turbulence 4. Wind shear 5.

Complete Loss of Tail Rotor Control in Hover

1. Twist grip: IDLE 2. Collective: Cushion Landing Caution: A slight rotation to the right can be expected on touchdown

The tail rotor drive system includes:

1. Two driveshafts supported by bearing and damper assemblies 2. 90° gearbox 3. Tail rotor assembly and blade pitch control

How many basic WARNING messages are there?

10 but they may vary depending on Garmin or Genesys and optional kits

Best WX tools and sites

10. Weather risk Assessment Chart 6. Graphical Forecast Aviation(aviation weather.gov) 5. Aviation forecast discussion 7. The overview( aviation weather.gov)... radar

The Pratt and Whitney PT 6B-37A has how many engine and RGB bearings

15

Autorotation flare ( cyclic) altitude?

180-150 feet AGL

Standard hover altitude

3 feet

Class B VFR minimums

3 miles and Clear of Clouds

Basic VFR minimums below 10,000 feet

3 sm visibility, 500 feet below, 1000 feet above and 2,000 feet horizontally

Taxi wind maximum

30 knots

Take-off and landing vertically wind maximum

40 knots

Basic TQ required for 90 knots straight and level

45%

The PT6B-37A engine has ________ structural cases, referred to as sections, each with a distinct function:

5 Accessory gearbox section Compressor section Combustion section Exhaust section Reduction gearbox section.

Maximum GS touchdown for autorotation

50 knots

Basic TQ required for straight and level at 100 knots

50%

Although the configuration of each Class C airspace area is individually tailored, the airspace usually consists of a ________ nm radius core surface area that extends from the surface up to ____________ feet above the airport elevation, and a ________ nm radius shelf area that extends no lower than _______________ feet up to _____________ feet above airport elevation.

5nm core, 4000 feet and a 10nm radius and extends no lower than 1200 feet up to 4000.

How many AWG messages are there?

6

Jet Fuel A1 capacity

605 liters/ kilos or 159 gallons or 476kgs which is 1050 lbs

TQ required for 500 fpm rate of climb at 100 knots

63%

Autorotation airspeed below 10,000? NR ?

75 knots 101-103%

Inspections Done

A Annual Inspection & AD. Every 12 months V VOR check every 30 days 1 100 hour inspection ( if used for hire or flight instruction) every 100 hours A Altimeter & Pitot- Static system every 24 months Transponder every 24 months E ELT operation and batter currency every 12 months G GPS every 28 days

A hydro- ________________ fuel control _________________ unit is installed where and for what?

A hydro-pneumatic Fuel control metering unit is installed on the fuel pump to regulate fuel flow to the 14 fuel nozzles in response to power requirements and flight conditions

Rotor high comes on when?

Above 108% NR

Mark 2 QRH Autorotative Landing

Airspeed: trim the aircraft in autorotation with airspeed - 75 KIAS from SL to 10000 ft Hp, or - 70 KIAS from 10000 to 15000 ft Hp; and a rotor speed of - 101 to 103 % NR (-1800 to - 2000 ft/min vertical speed). Cyclic: initiate a flare at approximately - 180 to 150 ft AGL (from SL to 10000 ft Hp), or - 140 to 130 ft AGL (from 10000 to 15000 ft Hp) applying the cyclic at approximately 5 to 7 deg/s pitch rate, to a maximum of 25 to 30 deg nose-up pitch attitude. Cyclic: hold the flare to reduce the rate of descent (500±100 ft/min) and the forward speed (30±10 KIAS). Collective pitch: adjust as required to maintain NR as high as possible (maximum 110%) during the flare. Cyclic: at approximately 20 to 30 ft AGL, forward to obtain a near level attitude (landing skid parallel to ground). Collective: as the helicopter settles, at approximately 4 ft AGL, apply as required to cushion touchdown with: - less than 50 kts ground speed (as required by surface characteristics and conditions), and - less than 400 ft/min vertical speed. Collective pitch: continue application to cushion the touchdown. Pedals: maintain direction. Note In case of contact on the aft portion of the landing skid, avoid counteracting the pitch down with cyclic.

All ___________ magnetic brakes are located under the pilot seats. Essentially, the force trim system uses magnetic brakes (force trim actuators) for attitude hold, artificial feel and beep trim capabilities allowing limited hands free flight operations.

All three magnetic brakes are located under the pilot seats. Essentially, the force trim system uses magnetic brakes (force trim actuators) for attitude hold, artificial feel and beep trim capabilities allowing limited hands free flight operations.

Air Data Sensor TH-73 is located where?

Avionics shelf in baggage compartment

What are the ten basic WARNING messages?

Battery Hot, Battery Off, ENG FIRE, ENG OIL HOT, ENG OIL PRESS, ENG OUT, ROTOR HIGH, ROTOR LOW, XMSN OIL HOT, and XMSN OIL PRESS.

N1 Limits

Continuous operation.....................................................: 60 to 100.1% Take-off (5 minutes) .................................................. : 100.1 to 103.2% Maximum take-off (5 minutes)................................................. : 103.2%

_______________ is the direction in which the aircraft is flying over the ground. ______________ is the direction in which the aircraft is ____________________.

Course is the direction traveling over the ground. Heading is he direction in which the aircraft is pointing.

DAU stands for what?

Data Acquisition Unit : receives analog signals from the engine and airframe and converts to digital words for the IDU-680 displays.

The fuel system controls the main rotor speed ( NR) by varying the engine's output as a function of the load demand set by the pilot. This is achieved by the ___________ controlled _______________ _________________ or by the _____________________ N2 ____________________ ( backup mode), aka MEC.

EEC CONTROLLED Electronic Governor ( EEC mode) or by the Mechanical N2 Governor.

Where is the oil tank in both the AW-119 and the AW-139?

Engine AGB

Mark 2 QRH: ENGINE FIRE IN FLIGHT

Enter autorotation as follows: - Collective: immediately reduce as required to maintain NR between 90 and 110%. - Cyclic: adjust to obtain desired autorotative speed. Airspeed for minimum rate of descent is 70 KIAS. Airspeed for maximum glide distance is 100 KIAS. Shut down engine as follows: Engine thottle: OFF; FUEL VALVE switch: CLOSED; FUEL PUMP 1 and 2 switches: OFF; Xfer PUMP switch: OFF. GEN switch: OFF. Perform an autorotative descent and landing. Refer to the AUTOROTATIVE LANDING procedure. After landing: - BAT switch: OFF. Evacuate helicopter as soon as possible.

Ep-ENGINE FIRE IN FLIGHT

Enter autorotation as follows: 1. Collective: immediately reduce as required to maintain NR between 90 and 110%. 2. Cyclic: adjust to obtain desired autorotative speed. NOTE: Airspeed for minimum rate of descent is 70 KIAS. Airspeed for maximum glide distance is 100 KIAS. Shut down engine as follows: 3. Engine thottle: OFF; 4. FUEL VALVE switch: CLOSED; 5. FUEL PUMP 1 and 2 switches: OFF; 6. Xfer PUMP switch: OFF. 7. GEN switch: OFF. Perform an autorotative descent and landing. Refer to the AUTOROTATIVE LANDING procedure. After landing: 8. BAT switch: OFF. Evacuate helicopter as soon as possible.

Essentially, the SAS uses _______________ to determine a cyclic and pedal control position and _____________ ______________actuators to dampen instabilities and assist with pilot control inputs.

Essentially, the SAS uses synchros to determine a cyclic and pedal control position and linear actuators to dampen instabilities and assist with pilot control inputs.

If starting with external power, be sure to check the Ground Power Unit (GPU) setting so that _________________________ amperage is not inadvertently delivered. What is the normal starter range.

Excessive. The normal range is 0-200 amps

What is the primary use of AC power on the TH-73?

For the Stability Augmentation System (SAS) actuators and gyros. This is why when you turn off the INVERTERS.the SAS turns off.

Three things the MAGNETIC BRAKES are used for.

Force Trim: The cyclic control system is equipped with two force trim actuators ( magnetic brakes for pitch and roll). The magnetic brakes permit 1. variation of cyclic stick reference points, 2. allow a beeper trim capability and 3. also create artificial feel (which is proportional to the degree of cyclic stick movement). Parallel actuator is also another term synonymous with magnetic brake or force trim actuator

TH-73: Traffic Information System

From ADS-B

Traffic Advisory System

Gets information from onboard systems

Helipilot control panel - the aircraft is flown with SAS 1, SAS 2 and ATTD HOLD selected to ________ for normal flight operations. Roll, pitch and yaw indicator bars show linear actuator movements.

Helipilot control panel - the aircraft is flown with SAS 1, SAS 2 and ATTD HOLD selected to ON for normal flight operations. Roll, pitch and yaw indicator bars show linear actuator movements.

Main Rotor Controls Seizure

If hovering: Land vertically If at low speed (less than 35 KIAS): Proceed to a running landing at the speed at which the seize occurred. If at High Speed: Land as Soon as Practicable into the wind using a running landing and speed of 35 KIAS

If you want to fly a RNAV route, you can couple your _______ bug and then couple to ___________, regardless of your nav source. However, if you want to couple to a __________ based navaid, your nav source must be __________ 1 or 2 so that you are receiving the ground based signal, for example a ________ or __________. If the source is a FMS, then you would not be able to couple to the VOR or Localizer

If you want to fly a RNAV route, you can couple your HDG bug and then couple to NHDG, regardless of your nav source. However, if you want to couple to a ground based navaid, your nav source must be VLOC 1 or 2 so that you are receiving the ground based signal, for example a VOR or Localizer. If the source is a FMS, then you would not be able to couple to the VOR or Localizer

IMSAFE Checklist

Illness Medication Stress Alcohol Fatigue Emotion

What is the purpose of the DAU and what is the similar component in the AW-139.

In the TH-73 the Data Acquisition Unit receives analog signals from the aircraft engine and airframe sensors and calibrates the signals and then converts them each to a digital words whack are assembled into a data stream for transmission to the EFIS IDU-680 displays. In the AW-139, the similar component to is the DCU on the engine but collects info. The NIM in the 139 converts Audi on analog to digital. The EEC provides engine digital information via a digital bus to the MAU

Mark 2 QRH: ROTOR UNDER SPEED

Indications Rotor Low light Rotor NR between 75 and 96%. AW119MKII G1000H - QRH Emergency & Malfunction Audio tone, horn and "ROTOR LOW" voice warning. 1. Check NR. IF rotor speed low: 2. Lower collective to increase rotor speed

Mark 2 QRH: ROTOR OVERSPEED

Indications Rotor high light Rotor NR above 108 %. 1. Check NR. IF rotor speed high: 2. Raise collective to decrease rotor speed

Mark 2 QRH: Main Gearbox Oil Pressure Low

Indications Transmission oil pressure Light Transmission oil pressure below minimum limit. 1.Monitor transmission oil pressure. 2. Reduce power as soon as operational conditions permit. 3. Land as soon as possible.

Mark 2 QRH: MAIN GEARBOX OIL TEMPERATURE HIGH

Indications XSMN OIL HOT light Transmission oil temperature above maximum limit. 1. Monitor transmission oil temperature. 2. Reduce power as soon as operational conditions permit. 3. Land as soon as possible.

Battery High Temperature EP

Indications: 1. BATT HOT LIGHT 2. Audio tone and WARNING 3. Battery temperature exceeding limits PROCEDURES 1. BAT Switch: OFF 2. Land As Soon As Possible

BATTERY DISCONNECTED EP

Indications: 1. BATT OFF LIGHT 2. Audio tone and WARNING voice warning 3. Battery Disconnected PROCEDURES: 1. Check BAT switch If Battery switch is OFF. 2. BAT switch: ON 3. Continue Flight If Battery switch is ON. 4. Land as soon as practicable

SMOKE in CABIN, TOXIC FUMES, ETC

Indications: Smoke, toxic fumes, etc. in the cabin. Procedures: 1. VENT switch: ON. 2. Sliding windows (if installed): Open. IF the altitude permits and the source is suspected to be of an electrical origin: 3. Attempt to isolate source by switching OFF every not essential electrical circuit. If SMOKE PERSISTS: 4. LAND IMMEDIATELY 5. EMERGENCY SHUTDOWN If no sign of smoke or fire disappears: 6. LAND AS SOON AS POSSIBLE

The AW119Kx has both __________________ _________________and Alternating Current (AC) power systems (radios and SAS). The DC system is comprised of __________ starter generator, main battery and an external power receptacle for DC power sources. The DC system is a 28 V system.

The AW119Kx has both Direct Current (DC) and Alternating Current (AC) power systems. The DC system is comprised of one starter generator, main battery and an external power receptacle for DC power sources. The DC system is a 28 V system.

The G1000H GSC 46 (number 1 signal conditioner) converts _____ tachometer generator signals for display on the PFD and MFD EIS full page format.

The G1000H GSC 46 (number 1 signal conditioner) converts NR tachometer generator signals for display on the PFD and MFD EIS full page format.

The G1000H ______________________. converts NR tachometer generator signals for display on the PFD and MFD EIS full page format.

The G1000H GSC 46 (number 1 signal conditioner) converts NR tachometer generator signals for display on the PFD and MFD EIS full page format.

The ____________________( two installed) is a remote-mounted avionics unit that houses ____________/______________ , VHF COM, VHF NAV, and _________________ receivers in addition to supporting I/O processing, aural alert generation, and flight director functions.

The GIA 63H houses a GPS/WAAS, VHF COM,VHF NAV and Glideslope receivers

The __________ engine is a lightweight turboshaft unit driving a ______ shaft output ________ to the main rotor ___________, then another output rearward to the _____ ____________ to drive the tail rotor. The engine reduction gearbox section ___________ power turbine RPM speed (N2) via a _____________ ________________reduction process down to a useable RPM for both rotors.

The PT6B-37A engine is a lightweight turboshaft unit driving a single shaft output forward to the main rotor transmission, then another output rearward to the 90° gearbox to drive the tail rotor. The engine reduction gearbox section reduces power turbine RPM speed (N2) via a two-stage reduction process down to a useable RPM for both rotors.

The aircraft has a total of __________ seats. Minimum crew is _______ pilot in the forward right position. This allows seating for up to _________ passengers.

The aircraft has a total of eight seats. Minimum crew is one pilot in the forward right position. This allows seating for up to seven passengers. There are restrictions for the Observer's Seat.

The cyclic pitch control system incorporates _______ control tubes with two sets of pitch and roll ____________ ________________.

The cyclic pitch control system incorporates two control tubes with two sets of pitch and roll linear actuators.

The main rotor assembly has _______ composite blades and is a _________ _______________ design using modern ________________ with composite tension links coupled to a ___________________ hub for blade retention.

The main rotor assembly has four composite blades and is a fully articulated design using modern elastomerics with composite tension links coupled to a titanium hub for blade retention.

The primary purpose of the transmission is to drive the _____________ ____________. The transmission accepts the input drive from the front of the _________________ ____________ ______________, reduces and changes the direction of the drive and transmits it via the mast to the __________ ___________.

The primary purpose of the transmission is to drive the main rotor. The transmission accepts the input drive from the front of the engine reduction gearbox, reduces and changes the direction of the drive and transmits it via the mast to the main rotor.

The tail boom attaches to the forward fuselage with _________ _______________ _________ to complete the fuselage assembly.

The tail boom attaches to the forward fuselage with four structural bolts to complete the fuselage assembly. 139 has six.

The tail rotor drive system transmits _____________ from the engine _____________ ________________ to the tail rotor through ______ driveshafts and the 90° gearbox. The _______ gearbox, to which the tail rotor assembly is attached, provides a 90° change in the direction of drive.

The tail rotor drive system transmits power from the engine reduction gearbox to the tail rotor through two driveshafts and the 90° gearbox. The 90° gearbox, to which the tail rotor assembly is attached, provides a 90° change in the direction of drive.

TH-73 busbar system has how many buses?

Three. Battery Bus, 28VDC bus, and EMERGENCY BUS. This is different from AW139 which has a Battery Bus, 2x ESSENTIAL Bus, 2x MAIN buses, and 2x NON-ESS BUS.

How many igniters for the 37 and 67?

Two

_______ pilot viewable sight glass windows provide assurance of proper oil levels throughout the entire transmission assembly.

Two pilot viewable sight glass windows provide assurance of proper oil levels throughout the entire transmission assembly.

Required VFR equipment 14 CFR 91.207; 14 CFR 91.209

VFR: Oil pressure each engine Oil temp each engine Tachometer each engine Temp ( if liquid cooled) Altimeter Airspeed indicator Magnetic Compass Fuel gauge each tank Anti-collisions Position lights Landing gear indicator Safety belts ELT Fuses Landing light

Vne Never-exceed speed

VNE: 152 kt or as corrected per RFM VNE limitations chart for density altitude and air temperature

What are the minimum flight planning requirements?

We forecasted 1 hr before and after Expected Performance and WB Alternates and Mins (200 feet above minimum and 1sm vis) Length of Runways and Taxi info Traffic delays, TFRs, Terrain H How much fuel is required

Preflight Checks and Brief

Weather reports and forecasts Expected performance of aircraft, discrepancy book, airworthiness certification Alternatives available Length of runways and NOTAMs Traffic delays and terrain avoidance How much fuel is required

Supplement 21 Seating configuration limitations

When using jumpseat there can be no other passengers

#1 cause of aircraft mishaps for weather, fatal crashes?

Winds, IFR

With engine oil temperature below _________ °C, leave the engine twist grip in the ________detent until the engine oil temperature reaches _______ degrees C.

With engine oil temperature below 10 °C, leave the engine twist grip in the idle detent until the engine oil temperature reaches 10 °C.