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Section 3 - Emergency Procedures
Section 3 includes checklists and detailed procedures for coping with various types of emergency conditions that could arise.
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).
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.
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 |
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 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.
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.
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.
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
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
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.
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.
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
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)
BATT MAIN FAIL BATT MAIN FAULT
- 1.EMERG. battery switch ...................................................................... ON
- 2.MASTER switch ................................................................................. OFF
- 3.Land as soon as practical.
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.
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
- 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
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
- 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
- 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