CPT 3

Cockpit Procedural Trainer THREE

=Discuss=

1. Caution system

 * Switch the Trans Oil Temp and Trans Oil Press lights.**

HYDRAULIC PRESSURE (Hydraulic System Failure)
Indications:
 * HYDRAULIC PRESSURE LIGHT
 * Increased force required for control movement
 * Feedback in control

Procedure:
 * 1. Airspeed	Adjust (to obtain most comfortable control movement level)
 * 2. HYDRAULIC BOOST switch	Check ON
 * 3. HYD BOOST circuit breaker	Out

If system is restored:
 * 4. Land as soon as practicable

If system is not restored:
 * 5. HYD BOOST circuit breaker	In
 * 6. HYDRAULIC BOOST switch	Off
 * 7. FORCE TRIM (FT)	On                                  <-- 15 Jan 10 NATOPS change
 * 8. ©	AFCS STAB 	On
 * 9. ©	AFCS ALT	Off
 * 10. Land as soon as practicable

ENGINE FIRE (Engine Fire in Flight)
Indication:
 * FIRE light
 * Smoke
 * Flames

Procedure:

WARNING: Be prepared for complete power loss.


 * 1. Confirm existence of fire.

If fire exists:
 * 2. Land immediately
 * 3. Emergency shutdown	Complete after landing

If fire not confirmed:
 * 4. Land as soon as possible

DUCT TEMP HIGH (Heater Malfunction)
Indication: Procedure:
 * DUCT HIGH TEMP caution light illuminated
 * 1. CABIN HEAT valve	Off
 * 2. AIR COND/FAN switch	FAN
 * 3. HI/FAN/LO switch	HI

If light extinguishes:
 * 4. Continue flight

If light does not extinguish:
 * 5. Land as soon as practicable.

GENERATER FAILURE
Indication:
 * Loadmeter reads zero
 * GEN FAIL caution light illumination
 * DC voltmeter indicates battery voltage

WARNING
 * With the battery switch OFF or battery exhaustion, both fuel boost pumps are inoperative. Descend below 6,000 ft pressure altitude and land as soon as possible.
 * With one or both boost pumps inoperative, fuel quantity below 20 gallons shall be considered unusable.

Note:
 * Prior to shutting off all electrical power, the pilot must determine the equipment that is essential to the particular flight environment that will be encountered (e.g. flight instruments and boost pumps).
 * © In the TH-57C, time of operation of ESS No. 2 bus on battery power is approximately 40 minutes with pitot OFF and an 80% charged battery (approximately 35 minutes with pitot heat ON). To conserve battery power as needed for extended flights or for use of landing lights at destination, turn BAT switch OFF during flight.
 * © With the NORMAL/RECOVER switch on NORMAL, failure of the main generator will result in illumination of the FUEL PUMP caution light because of loss of power to nonessential bus.
 * © Resetting the bus/tie relay circuit breaker will cause the main battery to power the nonessential bus, accelerating main battery depletion.

Procedure:
 * 1. GEN FIELD and GEN RESET circuit breaker	Check in
 * 2. MAIN GEN switch	Reset, then ON

If generator power is not restored: If power is restored:
 * 3. MAIN GEN switch	Off
 * 4. Unnecessary electrical equipment	Off
 * 5. © NORMAL/Recover switch	Recover as Desired
 * 6. Descend below 6,000 ft
 * 7. Land as soon as practical
 * 8. Continue flight

Note:
 * © In the TH-57C, with the loss of the main battery after a main generator failure, the HSI and both RMIs will be inoperative for TACAN, LOC and VOR approaches. However, the RMIs will still provide relative ADF bearing.  VMC should be attained as soon as possible.
 * Be prepared for a possible electrical and / or engine compartment fire because of excessive wiring load or generator meltdown.

FUEL LOW
Indication:
 * FUEL LOW caution light illuminated

Procedure:
 * 1. Monitor fuel quantity
 * 2. Land with minimum of 10 gallons indicated

If FUEL PUMP light is illuminated:
 * 3. Land as soon as possible

A/F FUEL FILTER
Indication:
 * A/F FUEL FILTER caution light illuminated

Procedure:
 * 1. Land as soon as possible

TAIL ROTOR CHIP
Indication:
 * T/R CHIP caution light illuminated

Procedure:
 * 1. Land as soon as possible

ENGINE CHIP
Indication:
 * ENG CHIP caution light illuminated

Procedure: If secondary indication are present:
 * 1. Engine Instruments	Check for secondary Indications
 * 2. Land as soon as possible

If no secondary indications exist:

First Chip Light
 * 3. Clear Chip
 * 4. Note time
 * 5. Continue flight (if chip light goes out, land as soon as possible if not)

Second Chip Light

If sustained within 30 minutes of first chip:
 * 6. Land as soon as possible

If more than 30 min. have elapsed since first light:
 * 7. Press clear chip
 * 8. Continue flight

Any subsequent Chip light
 * 9. If within 50 flight hours of the first, land as soon as possible and make no attempt to clear chip.

TRANSMISSION CHIP
Indication: Procedure: If secondary indications are present:
 * TRANSMISSION CHIP caution light illuminated
 * 1. Check Transmission Instruments for secondary indications of impending failure.

If no secondary incations exist:
 * 2. Land Immediately
 * Exactly the same as engine chip light

BATTERY HOT
Indication: Procedure:
 * BATT HOT caution light illuminated
 * 1. BAT	Off
 * 2. Land as soon as possible

BATTERY TEMP
Indication: Procedure:
 * BATTERY TEMP caution light illuminated
 * 1. BAT	Off
 * 2. Continue flight

TRANSMISSION OIL PRESS
Indication: Procedure:
 * TRANSMISSION OIL PRESS caution light illuminated


 * Note: Check the transmission oil pressure with the twist grip full open. Illumination of the TRANS OIL PRESS caution light is common, while the twist grip is at flight idle, after power off maneuver.  However the gauge should indicate positive transmission oil pressure.


 * 1. Land as soon as possible.

TRANSMISSION OIL TEMPERATURE
Indication: Procedure:
 * TRANS OIL TEMP caution light illuminated
 * 1. Land as soon as possible

ENGINE OUT
Indication: Procedure:
 * ENGINE OUT caution light illuminated
 * Aural signal
 * Monitor Nr and Engine instruments and enter autorotation if power failure is confirmed.
 * If actuation of the warning system is the result of Ng tachometer generator or speed sensor switch failure, Land as soon as practicable.

ROTOR LOW RPM
Indication: Procedure:
 * ROTOR LOW RPM caution light illuminated
 * Aural signal
 * Collective - lower to preserve Nr. Check twist grip full open.  If still no power, engine failure procedures.
 * If actuation of the warning system is the result of Nr tachometer generator, monitor engine instruments and land as soon as practical.

2. Hydraulic system

 * System Pressure at 100% Nr	600±50 psi (600±25 psi per maint. manual)
 * System Capacity	2.25 pints MIL-H-83282

System Components include: Power pack contains cooling reservoir (1 pint), pump, regulating valve, and Nr mounting pad. Metal filter with no bypass provisions. Pressure switch closes when pressure falls below 300 psi and opens when pressure rises above 400 psi. Spring loaded to the open position and requires 28 VDC to close and turn off Hydraulic pressure to servos. {By bypassing them}
 * 1. Hydraulic power pack
 * 2. Filter
 * 3. Low pressure switch
 * 4. Solenoid valve
 * 5. Servos – contain 3 valves:
 * Pilot Valve
 * Differential Valve
 * Sequence Valve

3. PAN / Mayday reports

 * Aviate / Navigate / Communicate – In that order
 * ISPI Format
 * I-Identification
 * S-Situation
 * P-Position
 * I-Intentions

Information on this topic can be found in the FAR/AIM on the FAA website at: http://www.faa.gov/air_traffic/publications/ATpubs/AIM/Chap6/aim0603.html

DEFINITIONS FROM PILOT GLOSSARY IN FAR/AIM

PAN-PAN- The international radio-telephony urgency signal. When repeated three times, indicates uncertainty or alert followed by the nature of the urgency.

MAYDAY- The international radiotelephony distress signal. When repeated three times, it indicates imminent and grave danger and that immediate assistance is requested.

URGENCY (PAN)- A condition of being concerned about safety and of requiring timely but not immediate assistance; a potential distress condition.

DISTRESS (MAYDAY)- A condition of being threatened by serious and/or imminent danger and of requiring immediate assistance.

Recently(10/07), some bad gouge has been going around regarding the origin of 'Pan' & 'Mayday'. The SIM contractors have picked up on this, and are asking about them.


 * Their origins are French words/phrases Wikipedia

4. Autorotation into the trees (Landing in the Trees)
An autorotation into a heavily wooded area should be accomplished by executing a normal autorotative approach. The flare should be executed so as to reach a zero rate of descent and zero ground speed as close to the top of the trees as possible. As the helicopter settles, increase collective to maximum. If time permits during the autorotation:

Procedure:
 * 1. Autorotate
 * 2. Shoulder harness	Lock

If time and altitude permit:
 * 3. Mayday	Transmit on Guard
 * 4. Transponder	Emergency
 * 5. Twist grip	Close
 * 6. Battery	Off

=Introduce= 1. Generator / electrical malfunctions

GENERATOR FAILURE
Indication:
 * Load meter zero
 * GEN FAIL caution light illumination
 * DC voltmeter indicates battery voltage

WARNING
 * With the battery switch OFF or battery exhaustion, both fuel boost pumps are in operative. Descend below 6,000 ft pressure altitude and land as soon as possible.
 * With one or both boost pumps inoperative, minimum fuel is 20 gallons; 10 gallons is unusable.

Note:
 * Prior to shutting off all electrical power, the pilot must determine the equipment that is essential to the particular flight environment that will be encountered (e.g. flight instruments and boost pumps).
 * In the TH-57C, time of operation of ESS No. 2 bus on battery power is approximately 40 minutes with pitot OFF and an 80% charged battery (approximately 35 minutes with pitot heat ON). To conserve battery power as needed for extended flights or for use of landing lights at destination, turn BAT switch OFF during flight.
 * With the NORMAL/RECOVER switch on NORMAL, failure of the main generator will result in illumination of the FUEL PUMP caution light because of loss of power to nonessential bus.
 * Resetting the bus/tie relay circuit breaker will cause the main battery to power the nonessential us, accelerating main battery depletion.

Procedure:

circuit breaker	Check in
 * 1. GEN FIELD and GEN RESET
 * 2. MAIN GEN switch	Reset, then ON

If generator power is not restored: If power is restored:
 * 3. MAIN GEN switch	Off
 * 4. Unnecessary electrical equipment	Off
 * 5. NORMAL/Recover switch	Recover as Desired
 * 6. Descend below 6,000 ft
 * 7. Land as soon as PRACTICABLE
 * 8. Continue flight

Note:
 * In the TH-57C, with the loss of the main battery after a main generator failure, the HIS and both RMIs will be inoperative for TACAN, LOC and VOR approaches. However, the RMIs will still provide relative ADF bearing.  VMC should e attained as soon as possible.
 * Be prepared for a possible electrical and / or engine compartment fire because of excessive wiring load or generator meltdown.

DC LOADMETER AND VOLTMETER
Indication: Loadmeter or voltmeter fluctuates erratically, pegs or goes to zero Procedure:
 * 1. Generator	Cycle

If the problem is corrected:
 * 2. Continue flight.

If the problem is not corrected:
 * 3. Use generator failure procedures

Caution Sustained loadmeter indications greater than 70 percent may be caused by an electrical fire.

HYDRAULIC SYSTEM FAILURE
Note: Odd or unusual stick forces will be felt in a boost-off situation. Because of excessive forces required for control manipulation, a shallow approach with a sliding landing is recommended.

Indications:
 * HYDRAULIC PRESSURE LIGHT
 * Increased force required for control movement
 * Feedback in control

Procedure:
 * 1. Airspeed	Adjust (to obtain most comfortable control movement level)
 * 2. HYDRAULIC BOOST switch	Check ON
 * 3. HYD BOOST circuit breaker	Out

If system is restored:
 * 4. Land as soon as practicable

If system is not restored: 10. Land as soon as practicable
 * 5. HYD BOOST circuit breaker	In
 * 6. HYDRAULIC BOOST switch	Off
 * 7. FORCE TRIM (FT)	On
 * 8. ©	AFCS STAB 	On
 * 9. ©	AFCS ALT	Off

HYDRAULIC POWER CYLINDER MALFUNCTION
Indications: Cyclic / collective control displaces to abnormal position Pilot control of cyclic / collective is difficult or impossible. Procedure:
 * 1. HYDRAULIC BOOST switch	Off

WARNING Hydraulic system will not secure if HYD BOOST circuit breaker is out.


 * 2. Helicopter	Regain Control

Adjust airspeed as desired to obtain most comfortable control movement level.


 * 3. Land as soon as Possible

WARNING In the event of a complete power failure in the TH-57B or a failure of the ESS No.2 bus in the TH-57C, the hydraulic system will reenergize in the malfunction mode. The pilot will be unable to override the hydraulic boost solenoid.

ENGINE CHIP
Indication: ENG CHIP caution light illuminated Procedure: If secondary indication are present:
 * 1. Engine Instruments	Check for secondary Indications
 * 2. Land as soon as possible

If no secondary indications exist: First Chip Light
 * 3. Clear Chip
 * 4. Note time
 * 5. Continue flight

Second Chip Light If sustained within 30 minutes of first chip:
 * 6. Land as soon as possible

If more than 30 min. have elapsed since first light:
 * 7. Press clear chip
 * 8. Continue flight

Any subsequent Chip light
 * 9. If within 50 flight hours of the first, land as soon as possible and make no attempt to clear chip.

TRANSMISSION CHIP
Indication: TRANSMISSION CHIP caution light illuminated Procedure:
 * NOT Exactly the same as engine chip!

Indication: TRANS CHIP caution light illuminated

Procedure:
 * 1. Check Transmission Instruments for secondary indications of impending failure.

If indications are present:
 * 2. Execute IMMINENT TRANSMISSION FAILURE procedures.

If no secondary indications exist:

First Chip Light
 * 3. Clear Chip
 * 4. Note time
 * 5. Continue flight

Second Chip Light If sustained within 30 minutes of first chip: If more than 30 min. have elapsed since first light:
 * 6. Land as soon as possible
 * 7. Press clear chip
 * 8. Continue flight

Any subsequent Chip light
 * 9. If within 50 flight hours of the first, land as soon as possible and make no attempt to clear chip.

Tail Rotor Chip
Indication: T/R chip caution light illuminated Procedure:
 * Land as soon as possible

FUEL CONTROL FAILURE
Indication: Erratic Nf Fluctuating Ng and / or TOT Procedure:
 * 1. Collective	Adjust (to maintain Nr in operating range).
 * 2. Twist grip	Adjust (to maintain Nf / Ng in operating range).
 * 3. Land as soon as possible

WARNING Be prepared for complete power loss.

FUEL BOOST PUMP FAILURE
Note:
 * With one of both boost pumps inoperative, minimum fuel is 20 gallons. A level-flight attitude should be maintained to prevent engine flameout that could be caused by the operating submersible pump being uncovered and allowing air to be drawn into the fuel lines or by both boost pumps being in operative and allowing air to be drawn into the engine driven fuel pump.

Indication: Procedure:
 * FUEL PUMP caution light illuminated
 * Indicated fuel pressure of zero (dual-pump failure)
 * 1. Descent	Initiate if Above 6,000 ft PA and Flight Permits.
 * 2. Fuel pressure and quantity 	Note

WARNING With one or both boost pumps inoperative, minimum fuel is 20 gallons; 10 gallons is unusable.

If both fuel boost pumps have failed (fuel pressure at Zero):

WARNING Be prepared for complete power loss.


 * 3. Land as soon as possible

If only one boost pump has failed (fuel pressure 4-30 psi);


 * 4. Land as soon as practical

WARNING If an air leak exists in the fuel lines between the boost pumps and engine, a total loss of boost pump pressure could cause an engine flameout.

FUEL LOW
Indication: Procedure:
 * FUEL LOW caution light illuminated
 * 1. Monitor fuel quantity
 * 2. Land with minimum of 10 gallons indicated

If FUEL PUMP light is illuminated:
 * 3. Land as soon as possible

A/F FUEL FILTER
Indication: Procedure:
 * A/F FUEL FILTER caution light illuminated
 * 1. Land as soon as possible

ENGINE FIRE IN FLIGHT
WARNING Be prepared for complete power loss. Indication: Procedure:
 * FIRE light
 * Smoke
 * Flames
 * 1. Confirm existence of fire.

If fire exists:
 * 2. Land immediately
 * 3. Emergency shutdown	Complete after landing

If fire not confirmed:
 * 4. Land as soon as possible

BATTERY HOT
Indication: Procedure:
 * BATT HOT caution light illuminated
 * 1. BAT	Off
 * 2. Land as soon as possible

BATTERY TEMP
Indication: Procedure:
 * BATTERY TEMP caution light illuminated
 * 1. BAT	Off
 * 2. Continue flight

=Practice=
 * 1. All FAM stage checklists and voice reports
 * 2. Normal starting / shutdown procedures
 * 3. Abnormal starts
 * 4. Engine oil system malfunction
 * 5. Transmission oil system malfunction
 * 6. Tach / Gen malfunction
 * 7. TOT malfunction
 * 8. Overtorque / overtemp / overspeed
 * 9. Torque malfunction