Section 3 - Emergency Procedures

Section 3 includes checklists and detailed procedures for coping with various types of emergency conditions that could arise.

ANNUNCIATOR / ALERTS

Annunciation Window: The Annunciation Window displays abbreviated annunciation text. Text color is based on alert levels described in the following section. The Annunciation Window is located to the right of the Altimeter and Vertical Speed Indicator. All P2012 annunciations can be displayed simultaneously in the Annunciation Window. A white horizontal line separates annunciations that are acknowledged from annunciations that are not yet acknowledged. Higher priority annunciations are displayed toward the top of the window. Lower priority annunciations are displayed toward the bottom of the window.

Alerts Window: The Alerts Window displays text messages for up to 64 prioritized alert messages. Pressing the Alerts Softkey displays the Alerts Window. Pressing the Alerts Softkey a second time removes the Alerts Window from the display.

Softkey Annunciation: During certain alerts, a Warning or Caution Softkey may appear as a flashing annunciation to accompany an alert. The Alerts Softkey assumes a new label consistent with the alert level (Warning, Caution). By pressing the softkey when flashing an annunciation, the alert is acknowledged. The softkey label then returns to Alerts. If alerts are still present, the Alerts label is displayed in white with black text. Pressing the Alerts Softkey a second time views the alert text messages.

System Annunciations: Typically, a large red ‘X’ appears over instruments whose information is supplied by a failed Line Replaceable Unit (LRU).

Alert Level Definition

Warning: This level of alert requires immediate attention. A warning alert appears in the Annunciation Window. Text appearing in the Annunciation Window is red. A warning alert is also accompanied by a flashing Warning Softkey annunciation. Pressing the Warning Softkey acknowledges the warning alert and stops the aural tone, if applicable. When a parameter exceeds its maximum value or a red caption is generated, an aural is provided to the pilot. An internal logic prevents triggering of the aural during minor and time limited exceedances which do not require immediate corrective pilot action.

Caution: This level of alert indicates the existence of abnormal conditions on the aircraft that may require pilot intervention. When a new caution alert appears in the Annunciation Window, it is shown in black on amber inverse video in conjunction with the Caution Softkey. Pressing the Caution Softkey acknowledges all amber messages and extinguishes the softkey. Once acknowledged, caution messages are displayed until the issue is corrected.

Safe Operating Advisory: This level of alert indicates crew awareness is required. It is shown in green text in the Annunciation Window.

System Message Advisory: This level of alert provides general information to the pilot. Message Advisories appear in the Alerts Window and are not shown in the Annunciation Window. When a Message Advisory occurs, the system provides a white flashing Messages Softkey annunciation. Pressing the softkey acknowledges the message advisory alert, and displays the associated text in the Alerts Window.

CAS Messages Summary

The following table shows a summary of all Crew Alerting Message (CAS), divided for System or Function.

POWERPLANT

Propeller Overspeeding

The aircraft is fitted with propeller/governor set by MT Propellers such a way that the maximum propeller RPM exceedance is prevented. In case of propeller overspeeding in flight, apply following procedure.

Affected engine:

1. Propeller lever ..................................................................... REDUCE

2. RPM indicator ......................................................................... CHECK

If propeller overspeeding continues:

3. Throttle lever ................................................................. REDUCE

If it is not possible to decrease propeller RPM, apply engine securing procedure and land as soon as possible applying one engine inoperative landing procedure.

Maximum propeller RPM exceedance may cause engine components damage. Apply caution while increasing RPM and always monitor engine parameters. In the case of maximum RPM exceedance, refer to propeller and engine Maintenance Manuals.

Partial loss of engine power

Partial loss of engine power can be detected by variable fuel flow, variable fuel pressure or un-commanded variation of manifold pressure or RPM.

Affected engine:

1. Fuel pump ...................................................................................... ON

2. Fuel quantity and pressure indicators .................................... CHECK

3. If necessary ................................................................ SWITCH TANK

If engine continues to run irregularly

4. Affected engine ........................... SECURE (see engine securing procedure)

5. Land as soon as possible applying one engine inoperative landing procedure.

CHT Limits Exceedance

LH CHT HI RH CHT HI

Affected engine:

1. Check CHT

CHT HIGH could be related to operations in MID POWER RANGE where mixture is leaner. Therefore, cooling could be achieved increasing power (richer mixture) or reducing power to minimum practical. RPM reduction may be beneficial.

2. Affected engine ..................................... CHANGE power as required

3. Maintain high airspeed if possible

4. 4. CHT ......................................................................... Verify decreasing

If CHT stabilizes in the green arc:

5. Continue the flight

If CHT continue to rise or engine shows roughness:

5. Affected engine ........................... SECURE (see engine securing procedure)

6. Land as soon as possible applying one engine inoperative or forced landing procedure as applicable.

Oil Temperature Limits Exceedance

LH O TEMP HI RH O TEMP HI

Affected engine:

1. Propeller lever ..................................................................... REDUCE

2. Oil TEMP ............................................................................... CHECK

If oil temperature does not decrease:

3. Throttle lever .......................................................... REDUCE

4. Oil TEMP ................................................................... CHECK

If oil temperature does not decrease:

5. Airspeed ............................................................. INCREASE

6. Oil TEMP ................................................................... CHECK

If oil temperature does not come back within limits:

7. Land as soon as practical with affected engine set to the minimum necessary power.

Oil Pressure Limits Exceedance

LH OIL PRS LOW RH OIL PRS LOW

Affected engine:

1. Throttle lever ..................................... REDUCE to minimum practical

2. Oil TEMP ............................................................ CHECK within limits

3. Oil PRESS .............................................................................. CHECK

Fuel Pressure Limits Exceedance

Low Fuel Pressure

LH FUEL PRS LO RH FUEL PRS LO

Affected engine:

1. Fuel pump ...................................................................................... ON

2. Fuel quantity .......................................................................... CHECK

3. Fuel selector valve .............................. Select opposite fuel tank if NOT empty

4. Fuel consumption ............................................................... MONITOR

High Fuel Pressure

LH FUEL PRS HI RH FUEL PRS HI

Land as soon as possible. Prepare for potential engine shutdown and to apply one engine inoperative landing procedure.

Manifold Pressure Limits Exceedance

LH MAP HI RH MAP HI

1. Affected engine power lever.................Reduce MAP to 57.9 inHg (or below)

High manifold pressure may be a result of cold oil and the effect of high associated oil pressure on wastegate controller. Maintain power at or below 52 inHg by power lever management; as an alternative option, propeller lever reduction can be beneficial in controlling the power level. However, closely monitoring engine parameters is recommended with either technique.

ELECTRICAL SYSTEM

Single Alternator Failure

LH ALT FAIL RH ALT FAIL

1. LH (or RH) FIELD switch ............................................................. OFF

2. LH (or RH) FIELD switch ............................................................... ON

If LH (or RH) ALT FAIL caution remains ON:

3. LH (or RH) FIELD switch ................................................. OFF

4. TIE BUS .......................................................................... OFF

Both Alternator Failure

LH-RH ALT FAIL

1. FIELD LH and RH switches .............................................. BOTH OFF

2. FIELD LH and RH switches ............................................... BOTH ON (one at time)

If single LH (or RH) ALT caution stays displayed:

3. Verify positive ammeter indications on restored alternator

4. Refer to Single Alternator Failure Procedure (END)

If both LH and RH ALT cautions stay displayed:

3. FIELD LH and RH switches ................................. BOTH OFF

4. CROSS LH and RH switches ............................... BOTH OFF

5. TIE BUS .......................................................................... OFF

6. EMERG. battery switch ...................................................... ON

7. Land as soon as possible. (END)

Batteries failure

Main Battery failure

BATT MAIN FAIL BATT MAIN FAULT

1. EMERG. battery switch ...................................................................... ON

2. MASTER switch ................................................................................. OFF

3. Land as soon as practical.

LH/RH Battery failure

BATT LH FAULT BATT RH FAULT

BATT LH FAIL BATT RH FAIL

1. (Affected battery) BCK BATT switch ............................................... OFF

2. Land as soon as practical.

LANDING EMERGENCIES

Forced Landing without Engine Power

In case of double engine failure both propellers should be feathered to achieve maximum efficiency. Best glide speed is attained with flap UP. Flap can be set to T/O or LAND when sure on final to reduce landing ground roll on short FIELD.

The landing should be planned straight ahead with only small changes in directions not exceeding 45° to the left and 45° to the right. Any turn would reduce the glide performance.

1. LH and RH throttle levers ................................................. IDLE

2. LH and RH propeller levers ................................................. FEATHER

3. Flaps ............................................................................................. UP

4. Best glide speed .................................................................... 96 KIAS

5. Radio .................................................. Transmit MAYDAY giving location and intentions

6. Transponder .............................................. Set EMERGENCY CODE

7. If off airport, ELT ........................................................................... ON

8. Find a suitable place to land safely.

Emergency landing strip should be chosen considering surface condition, length and obstacles. Wind can be estimated by smoke plumes direction and tree tops or grass bending. Select touchdown direction according to the furrows of a plowed FIELD, not across.

9. Ignition switches ............................................................... BOTH OFF

10. Fuel pumps ...................................................................... BOTH OFF

11. Fuel selectors ............................................................... BOTH OFF

12. Seat belts ...................................... Tightly fastened / Passenger advise

13. Flaps ............................................................................. As required

When landing is assured:

14. FIELD LH and RH and MASTER switches .............................. OFF

Landing with brake system inoperative

1. Safety belts .......................................................................... FASTEN

After touch down if runway is deemed insufficient to decelerate:

2. Ignition switches .......................................................................... OFF

3. All electric / lights switches .......................................................... OFF

4. Fuel pumps .................................................................................. OFF

5. Fuel selectors .............................................................................. OFF

IN FLIGHT INOPERATIVE ENGINE SECURING PROCEDURES

The following procedure is applicable to shut down one engine in flight:

1. Throttle lever .............................................................................. IDLE

2. Propeller lever .................................................................... FEATHER

3. Fuel selector .............................................................................. OFF

4. Ignition switch ............................................................................. OFF

5. Fuel pump ................................................................................... OFF

6. FIELD switch ............................................................................... OFF

ONE ENGINE INOPERATIVE PROCEDURES

Inflight Engine Restart (prop in windmilling)

1. Electrical fuel pump (Inoperative engine) ........................................... ON

2. Fuel quantity indicators ................................................... CHECK BOTH

3. Fuel selectors ........................................ CHECK (Cross-feed if required)

4. FIELD switch (Inoperative engine) .............................................. OFF

5. Ignition switches ................................................................. Check ON

6. Throttle lever (Operative engine) .................................. SET as required

7. Throttle lever (Inoperative engine) .............................................. IDLE

8. Propeller lever (Inoperative engine) ............................. FULL FORWARD

Inflight Engine Restart (prop in feather)

1. Fuel quantity indicators ............................................... CHECK BOTH

2. Fuel selectors …………………….. CHECK and SELECT the suitable one

3. Electrical fuel pump (Inoperative engine) ............................................. ON

4. FIELD switch (Inoperative engine) .............................................. OFF

5. Ignition switches ................................................................. Check ON

6. Throttle lever (Operative engine) .............................. SET as practical

7. Propeller lever (Inoperative engine) ....................... FULL FORWARDs

8. Affected engine FIELD ................ ON (check for positive ammeter)

9. Affected engine propeller lever ........................... SET as required

10. Engine throttle levers .......................................... SET as required

11. Affected engine electrical fuel pump ................................... AUTO