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.

ID#	System or Function	CAS (Flag)	G1000 Nxi Alerts Flag	Conditions (to activate Flag)
1	CHT	LH CHT HI	LH CHT HI	LH CHT (whichever cylinder#) > 501°F
2	CHT	RH CHT HI	RH CHT HI	RH CHT (whichever cylinder#) > 501°F
5	Doors	LH CRW DR OPEN	LH CREW DOOR OPEN	LH CREW DOOR OPEN
6	Doors	RH CRW DR OPEN	RH CREW DOOR OPEN	RH CREW DOOR OPEN
7	Doors	MAIN DR OPEN	MAIN DOOR OPEN	MAIN DOOR OPEN
8	EGT	LH EGT HI	LH EGT HI	LH EGT (whichever thermocouple) ≥ 1651°F
9	EGT	RH EGT HI	RH EGT HI	RH EGT (whichever thermocouple) ≥ 1651°F
10	Electrical	LH ALT FAIL	LH ALT FAIL	LH ALTERNATOR FAILURE
11	Electrical	RH ALT FAIL	RH ALT FAIL	RH ALTERNATOR FAILURE
12	Electrical	LH-RH ALT FAIL	LH & RH ALT FAIL	LH AND RH ALTERNATOR FAILURE
13	Electrical	EXT POWER	EXT POWER ON	EXTERNAL POWER CONNECTED to the aircraft
14	Electrical	BATT MAIN FAIL	MAIN BATTERY FAIL	MAIN BATTERY FAILURE
15	Electrical	BATT MAIN FAULT	MAIN BATTERY FAULT	MAIN BATTERY FAULT
16	Electrical	CHARGING MAIN	MAIN BATTERY RECHARGES	MAIN BATTERY CHARGING
17	Engine	LH FIRE	LH ENG FIRE	FIRE ON LH ENGINE
18	Engine	RH FIRE	RH ENG FIRE	FIRE ON RH ENGINE
19	Flap	FLAP OVSPD T/O	FLAP OVERSPEED T/O	Flap in T/O position AND KIAS > 124* kts (VFE)
20	Flap	FLAP OVSPD LND	FLAP OVERSPEED LND	Flap in LANDING position AND KIAS > 119** kts (VFE)
21	Fuel	LH FUEL PMP ON	LH FUEL PUMP ON	LH FUEL PUMP ON
22	Fuel	RH FUEL PMP ON	RH FUEL PUMP ON	RH FUEL PUMP ON
23	Fuel	LH-RH FUEL PMP ON	LH-RH FUEL PUMP ON	This Flag is ON when BOTH FUEL Pumps are ON. Note: This flag (when active), extinguishes both single flags of fuel pump ON
24	Fuel	LH FUEL PRS LO	LH FUEL RAIL PRESS. LOW	LH FUEL PRESS ≤ 35 psi
25	Fuel	LH FUEL PRS HI	LH FUEL RAIL PRESS HIGH	LH FUEL PRESS ≥ 73 psi
26	Fuel	RH FUEL PRS LO	RH FUEL RAIL PRESS LOW	RH FUEL PRESS ≤ 35 psi
27	Fuel	RH FUEL PRS HI	RH FUEL RAIL PRESS HIGH	RH FUEL PRESS ≥ 73 psi
28	Fuel	LH FUEL LVL LOW	LH FUEL LEVEL LOW	LH Fuel quantity reading is < 65 Litres (17 USg)
29	Fuel	RH FUEL LVL LOW	RH FUEL LEVEL LOW	RH Fuel quantity reading is < 65 Litres (17 USg)
30	Fuel	L&R FUEL LVL LOW	LH & RH FUEL LEVEL LOW	LH and RH FUEL LEVEL LOW both ON
31	MAP	LH MAP HI	LH MAP HI	LH MAP ≥ 61 inHg
32	MAP	RH MAP HI	RH MAP HI	RH MAP ≥ 61 inHg
33	Oil	LH O TEMP HI	LH OIL TEMP HI	LH OIL TEMP ≥ 246°F
34	Oil	RH O TEMP HI	RH OIL TEMP HI	RH OIL TEMP ≥ 246°F
35	Oil	LH OIL PRS LOW	LH OIL PRESS LOW	LH OIL PRESS ≤ 25 psi
36	Oil	RH OIL PRS LOW	RH OIL PRESS LOW	RH OIL PRESS ≤ 25 psi
37	Oil	LH OIL PRS HI	LH OIL PRESS HIGH	LH OIL PRESS ≥ 116 psi
38	Oil	RH OIL PRS HI	RH OIL PRESS HIGH	RH OIL PRESS ≥ 116 psi
39	Oil	LH O TEMP LOW	LH OIL TEMP LOW	50°F ≤ LH OIL TEMP ≤ 139 °F
40	Oil	RH O TEMP LOW	RH OIL TEMP LOW	50°F ≤ RH OIL TEMP ≤ 139 °F
41	Oil	LH OIL PRS HI	LH OIL PRESS HIGH	96 psi ≤ LH OIL Press ≤ 115 psi
42	Oil	RH OIL PRS HI	RH OIL PRESS HIGH	96 psi ≤ RH OIL Press ≤ 115 psi
43	Pneumatic	PITOT HEAT1 ON	PITOT HEAT #1 ON	LH PITOT HEAT ON
44	Pneumatic	PITOT HEAT1	PITOT HEAT #1	LH PITOT HEAT OFF OR FAIL
45	Pneumatic	PITOT HEAT2 ON	PITOT HEAT #2 ON	RH PITOT HEAT ON
46	Pneumatic	PITOT HEAT2	PITOT HEAT #2	RH PITOT HEAT OFF OR FAIL
47	Propeller	LH RPM HI	LH RPM HI	LH RPM > 2700 RPM
48	Propeller	RH RPM HI	RH RPM HI	RH RPM > 2700 RPM
49	TIT	LH TIT HI	LH TIT HI	LH TIT ≥ 1651°F
50	TIT	RH TIT HI	RH TIT HI	RH TIT ≥ 1651°F
51	Anti ICE	PIT HTRS SET ON	PITOT HEATERS SET ON	LH PITOT OR RH PITOT are OFF AND the temperature detected by OAT probe is ≤ 5°C
52	Autopilot	SPD NOT AVAIL	SPD NOT AVAIL- SPD Function not available	This flag is ON when SPD button on GMC 710 is pressed (with AP operative or not operative)
53	Flight Control	STALL	IMPENDING STALL	This Flag is ON when a stall condition is detected by stall sensor
54	Flight Control	STALL HTR ON	STALL HEATER ON	STALL HEATER ON
55	Flight Control	STALL HTR SET ON	STALL HEATER SET ON	STALL HEATER is OFF AND the temperature detected by OAT probe is ≤ 5°C
56	Flight Control FIKI	ST HTR REDCD PWR	STALL HTR IN REDUCED POWER	Stall Heater Switch in ON position and WoW switch in Ground Position (a/c on ground)
57	Flight Control FIKI	ST HTR FULL PWR	STALL HTR IN FULL POWER	Stall Heater Switch in ON position and WoW switch in Air Position (a/c in flight)
58	Flight Control FIKI	STALL HTR FAIL	Stall Heater FAIL	Failure detected on Stall Heaters
59	Flight Control FIKI	SW ICE MODE ON	ICE MODE ON	Stall warning ice mode ON
60	Pneumatic FIKI	PIT HEAT 1-2 ON	PITOT HEAT #1 AND #2 ON	LH and RH PITOT HEAT ON This flag extinguishes items 55 and 57
61	Pneumatic FIKI	PIT 1 REDCD PWR	LH PITOT HTR IN REDUCED POWER	LH Pitot Heater Switch in ON position and WoW switch in Ground Position (a/c on ground)
62	Pneumatic FIKI	PIT 2 REDCD PWR	RH PITOT HTR IN REDUCED POWER	RH Pitot Heater Switch in ON position and WoW switch in Ground Position (a/c on ground)
63	Pneumatic FIKI	PIT 1-2 RDCD PWR	LH AND PITOT HTR IN REDUCED POWER	LH and RH Pitot Heater Switch in ON position and WoW switch in Ground Position (a/c on ground) This flag extinguishes items 86 and 87.
64	Pneumatic FIKI	PIT 1 FULL PWR	LH PITOT HTR IN REDUCED POWER	LH Pitot Heater Switch in ON position and WoW switch in Air Position (a/c in flight)
65	Pneumatic FIKI	PIT 2 FULL PWR	PWR RH PITOT HTR IN REDUCED POWER	RH Pitot Heater Switch in ON position and WoW switch in Air Position (a/c in flight)
66	Pneumatic FIKI	PIT 1-2 FULL PWR	LH AND PITOT HTR IN REDUCED POWER	LH and RH Pitot Heaters Switch in ON position and WoW switch in Air Position (a/c in flight) This flag extinguishes items 88 and 89.
67	Pneumatic FIKI	PT1 HTR FAIL	LH Pitot Heater FAIL	Failure detected on LH Pitot Heaters
68	Pneumatic FIKI	PT2 HTR FAIL	RH Pitot Heater FAIL	Failure detected on RH Pitot Heaters
69	Pneumatic FIKI	PT1 HTR OFF	LH Pitot Heater OFF	LH Pitot Heaters OFF
70	Pneumatic FIKI	PT2 HTR OFF	RH Pitot Heater OFF	RH Pitot Heaters OFF

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:

1. 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

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

2. 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.

1. Affected engine ..................................... CHANGE power as required

2. Maintain high airspeed if possible

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

If CHT stabilizes in the green arc:

1. Continue the flight

If CHT continue to rise or engine shows roughness:

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

2. 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:

1. Throttle lever .......................................................... REDUCE

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

If oil temperature does not decrease:

1. Airspeed ............................................................. INCREASE

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

If oil temperature does not come back within limits:

1. 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:

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

2. 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:

1. Verify positive ammeter indications on restored alternator

2. Refer to Single Alternator Failure Procedure (END)

If both LH and RH ALT cautions stay displayed:

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

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

3. TIE BUS .......................................................................... OFF

4. EMERG. battery switch ...................................................... ON

5. 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.

1. Ignition switches ............................................................... BOTH OFF

2. Fuel pumps ...................................................................... BOTH OFF

3. Fuel selectors ............................................................... BOTH OFF

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

5. Flaps ............................................................................. As required

When landing is assured:

1. 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:

1. Ignition switches .......................................................................... OFF

2. All electric / lights switches .......................................................... OFF

3. Fuel pumps .................................................................................. OFF

4. 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