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T-6B Texan II/Primary > Notes, Warnings, and Cautions > Flashcards

Notes, Warnings, and Cautions Flashcards

1
Q

ABORT START PROCEDURE - 1N

  1. PCL - OFF; or STARTER SWITCH - AUTO/RESET - 2N
  2. Perform Motoring Run Procedure - 3C, 4C, 5N, 6N

MOTORING RUN PROCEDURE

  1. PCL - OFF
  2. IGNITION switch - NORM
  3. Propeller area - CLEAR
  4. STARTER switch - MANUAL FOR 20 SECONDS - 7C, 8N
  5. STARTER switch - NORM
A

Note: Note and report to maintenance the degree and duration of any overtemperature.

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2
Q

ABORT START PROCEDURE - 1N

  1. PCL - OFF; or STARTER SWITCH - AUTO/RESET - 2N
  2. Perform Motoring Run Procedure - 3C, 4C, 5N, 6N

MOTORING RUN PROCEDURE

  1. PCL - OFF
  2. IGNITION switch - NORM
  3. Propeller area - CLEAR
  4. STARTER switch - MANUAL FOR 20 SECONDS - 7C, 8N
  5. STARTER switch - NORM
A

Note: If start is initiated with PCL in the OFF position, abort by reselecting AUTO/RESET on the STARTER switch. If start is initiated with PCL out of the OFF position, but not past the IDLE gate, abort by placing the PCL to OFF or reselecting AUTO/RESET on the STARTER switch. If the PCL is past the IDLE gate, abort by placing the PCL to OFF.

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3
Q

ABORT START PROCEDURE - 1N

  1. PCL - OFF; or STARTER SWITCH - AUTO/RESET - 2N
  2. Perform Motoring Run Procedure - 3C, 4C, 5N, 6N

MOTORING RUN PROCEDURE

  1. PCL - OFF
  2. IGNITION switch - NORM
  3. Propeller area - CLEAR
  4. STARTER switch - MANUAL FOR 20 SECONDS - 7C, 8N
  5. STARTER switch - NORM
A

Caution: If a start using external power is aborted (PMU or manual abort) due to an actual or suspected aircraft malfunction, do not attempt subsequent starts.

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4
Q

ABORT START PROCEDURE - 1N

  1. PCL - OFF; or STARTER SWITCH - AUTO/RESET - 2N
  2. Perform Motoring Run Procedure - 3C, 4C, 5N, 6N

MOTORING RUN PROCEDURE

  1. PCL - OFF
  2. IGNITION switch - NORM
  3. Propeller area - CLEAR
  4. STARTER switch - MANUAL FOR 20 SECONDS - 7C, 8N
  5. STARTER switch - NORM
A

Caution: Repeated PMU aborted start attempts are
indicative of engine malfunction.

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5
Q

ABORT START PROCEDURE - 1N

  1. PCL - OFF; or STARTER SWITCH - AUTO/RESET - 2N
  2. Perform Motoring Run Procedure - 3C, 4C, 5N, 6N

MOTORING RUN PROCEDURE

  1. PCL - OFF
  2. IGNITION switch - NORM
  3. Propeller area - CLEAR
  4. STARTER switch - MANUAL FOR 20 SECONDS - 7C, 8N
  5. STARTER switch - NORM
A

Note: During ground starts, certain parameters (weak battery, high OAT, high pre-start ITT, high density altitude, tailwind) may cause the PMU to abort a battery start attempt. Though these parameters are not directly monitored by the PMU, they cause a rate of rise in N1 and/or ITT that are indicative of an impending hung or hot start.

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6
Q

ABORT START PROCEDURE - 1N

  1. PCL - OFF; or STARTER SWITCH - AUTO/RESET - 2N
  2. Perform Motoring Run Procedure - 3C, 4C, 5N, 6N

MOTORING RUN PROCEDURE

  1. PCL - OFF
  2. IGNITION switch - NORM
  3. Propeller area - CLEAR
  4. STARTER switch - MANUAL FOR 20 SECONDS - 7C, 8N
  5. STARTER switch - NORM
A

Note: If a battery start was aborted (PMU or manual abort), connect external power (if available) and perform Motoring Run Procedure. Subsequent starts may be attempted if no engine malfunctions are evident and no limits have been exceeded.

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7
Q

ABORT START PROCEDURE - 1N

  1. PCL - OFF; or STARTER SWITCH - AUTO/RESET - 2N
  2. Perform Motoring Run Procedure - 3C, 4C, 5N, 6N

MOTORING RUN PROCEDURE

  1. PCL - OFF
  2. IGNITION switch - NORM
  3. Propeller area - CLEAR
  4. STARTER switch - MANUAL FOR 20 SECONDS - 7C, 8N
  5. STARTER switch - NORM
A

Caution: STARTER switch is not spring-loaded from
MANUAL to NORM.

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8
Q

ABORT START PROCEDURE - 1N

  1. PCL - OFF; or STARTER SWITCH - AUTO/RESET - 2N
  2. Perform Motoring Run Procedure - 3C, 4C, 5N, 6N

MOTORING RUN PROCEDURE

  1. PCL - OFF
  2. IGNITION switch - NORM
  3. Propeller area - CLEAR
  4. STARTER switch - MANUAL FOR 20 SECONDS - 7C, 8N
  5. STARTER switch - NORM
A

Note: Observe starter duty cycle cool-down period.

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9
Q

EMERGENCY ENGINE SHUTDOWN ON THE GROUND

  1. PCL - OFF
  2. FIREWALL SHUTOFF HANDLE - PULL
  3. EMERGENCY GROUND EGRESS - AS REQUIRED
A

No associated notes, warnings or cautions

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10
Q

EMERGENCY GROUND EGRESS - 1N

  1. ISS - mode selector - 2W
  2. Seat safety pin - INSTALL (BOTH) - 3W
  3. PARKING BRAKE - As required
  4. Canopy - OPEN

If cannopy cannot be opened, or situation requires right side egress:

  1. CFS handle - ROTATE AND PULL (BOTH) - 4W, 5W, 6W
  2. Upper fittings, lower fittings, and leg restraint garters - RELEASE (BOTH) - 7N
  3. BAT, GEN, and AUX BAT switches - OFF
  4. Evacuate aircraft
A

Note: In a situation requiring immediate ground egress, the ejection system has the capability for 0/0 ejection.

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11
Q

EMERGENCY GROUND EGRESS - 1N

  1. ISS - mode selector - 2W
  2. Seat safety pin - INSTALL (BOTH) - 3W
  3. PARKING BRAKE - As required
  4. Canopy - OPEN

If cannopy cannot be opened, or situation requires right side egress:

  1. CFS handle - ROTATE AND PULL (BOTH) - 4W, 5W, 6W
  2. Upper fittings, lower fittings, and leg restraint garters - RELEASE (BOTH) - 7N
  3. BAT, GEN, and AUX BAT switches - OFF
  4. Evacuate aircraft
A

Warning: Failure to ensure that the ISS mode selector is set to SOLO may result in the inadvertent ejection of one or both seats.

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12
Q

EMERGENCY GROUND EGRESS - 1N

  1. ISS - mode selector - 2W
  2. Seat safety pin - INSTALL (BOTH) - 3W
  3. PARKING BRAKE - As required
  4. Canopy - OPEN

If cannopy cannot be opened, or situation requires right side egress:

  1. CFS handle - ROTATE AND PULL (BOTH) - 4W, 5W, 6W
  2. Upper fittings, lower fittings, and leg restraint garters - RELEASE (BOTH) - 7N
  3. BAT, GEN, and AUX BAT switches - OFF
  4. Evacuate aircraft
A

Warning: Failure to insert both ejection seat safety pins (if occupied) before ground egress may result in inadvertent activation of ejection sequence and subsequent injury or death when performing emergency ground egress.

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13
Q

EMERGENCY GROUND EGRESS - 1N

  1. ISS - mode selector - 2W
  2. Seat safety pin - INSTALL (BOTH) - 3W
  3. PARKING BRAKE - As required
  4. Canopy - OPEN

If cannopy cannot be opened, or situation requires right side egress:

  1. CFS handle - ROTATE AND PULL (BOTH) - 4W, 5W, 6W
  2. Upper fittings, lower fittings, and leg restraint garters - RELEASE (BOTH) - 7N
  3. BAT, GEN, and AUX BAT switches - OFF
  4. Evacuate aircraft
A

Warning: If the canopy fracturing system malfunctions in conjunction with a canopy latch failure in the locked position, ejection may be the only option remaining to exit the aircraft. Aircrew shall ensure shoulder straps, lap straps, and leg restraint garters are still attached prior to pulling ejection handle.

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14
Q

EMERGENCY GROUND EGRESS - 1N

  1. ISS - mode selector - 2W
  2. Seat safety pin - INSTALL (BOTH) - 3W
  3. PARKING BRAKE - As required
  4. Canopy - OPEN

If cannopy cannot be opened, or situation requires right side egress:

  1. CFS handle - ROTATE AND PULL (BOTH) - 4W, 5W, 6W
  2. Upper fittings, lower fittings, and leg restraint garters - RELEASE (BOTH) - 7N
  3. BAT, GEN, and AUX BAT switches - OFF
  4. Evacuate aircraft
A

Warning: To prevent injury, ensure oxygen mask is on
and visor is down prior to actuating the CFS
system.

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15
Q

EMERGENCY GROUND EGRESS - 1N

  1. ISS - mode selector - 2W
  2. Seat safety pin - INSTALL (BOTH) - 3W
  3. PARKING BRAKE - As required
  4. Canopy - OPEN

If cannopy cannot be opened, or situation requires right side egress:

  1. CFS handle - ROTATE AND PULL (BOTH) - 4W, 5W, 6W
  2. Upper fittings, lower fittings, and leg restraint garters - RELEASE (BOTH) - 7N
  3. BAT, GEN, and AUX BAT switches - OFF
  4. Evacuate aircraft
A

Warning: Each internal CFS handle activates only the CFS charge for the respective transparency. Both internal CFS handles must be activated in order to fracture both transparencies (if required).

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16
Q

EMERGENCY GROUND EGRESS - 1N

  1. ISS - mode selector - 2W
  2. Seat safety pin - INSTALL (BOTH) - 3W
  3. PARKING BRAKE - As required
  4. Canopy - OPEN

If cannopy cannot be opened, or situation requires right side egress:

  1. CFS handle - ROTATE AND PULL (BOTH) - 4W, 5W, 6W
  2. Upper fittings, lower fittings, and leg restraint garters - RELEASE (BOTH) - 7N
  3. BAT, GEN, and AUX BAT switches - OFF
  4. Evacuate aircraft
A

Note: Oxygen hose, emergency oxygen hose, communication leads, and anti-G suit hose will pull free while vacating cockpit and leg restraint lines will pull through leg restraint garter D rings if released with quick-release lever.

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17
Q

ABORT

  1. PCL - IDLE
  2. BRAKES - As required - 1W
A

Warning: After a stop which required maximum effort braking and if overheated brakes are suspected, do not taxi into or park in a congested area until brakes have had sufficient time to cool. Do not set parking brake.

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18
Q

ENGINE FAILURE IMMDEIATELY AFTER TAKEOFF (sufficient runway remaining striaght ahead) - 1W, 2W

  1. AIRSPEED - 110 KIAS (minimum)
  2. PCL - As required - 3N
  3. EMER LDG GR handle - PULL (as required) - 4N
  4. Flaps - As required
A

Warning: If insufficient runway remains to land straight ahead, consider immediate ejection.

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19
Q

ENGINE FAILURE IMMDEIATELY AFTER TAKEOFF (sufficient runway remaining striaght ahead) - 1W, 2W

  1. AIRSPEED - 110 KIAS (minimum)
  2. PCL - As required - 3N
  3. EMER LDG GR handle - PULL (as required) - 4N
  4. Flaps - As required
A

Warning: Do not sacrifice aircraft control while troubleshooting or lowering gear with emergency system.

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20
Q

ENGINE FAILURE IMMDEIATELY AFTER TAKEOFF (sufficient runway remaining striaght ahead) - 1W, 2W

  1. AIRSPEED - 110 KIAS (minimum)
  2. PCL - As required - 3N
  3. EMER LDG GR handle - PULL (as required) - 4N
  4. Flaps - As required
A

Note: The pilot should select IDLE to use the increased drag of the not yet feathered propeller or select OFF to reduce the sink rate.

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21
Q

ENGINE FAILURE IMMDEIATELY AFTER TAKEOFF (sufficient runway remaining striaght ahead) - 1W, 2W

  1. AIRSPEED - 110 KIAS (minimum)
  2. PCL - As required - 3N
  3. EMER LDG GR handle - PULL (as required) - 4N
  4. Flaps - As required
A

Note: With a loss of hydraulic pressure, landing gear and flaps cannot be lowered by normal means.

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22
Q

LOW FUEL PRESSURE

  1. PEL - EXECUTE - 1N
  2. BOOST PUMP switch - ON - 2C
A

Note: If the FUEL PX warning remains illuminated, the engine driven high pressure fuel pump is suction feeding. Engine operation with high pressure pump suction feeding is limited to 10 hours

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23
Q

LOW FUEL PRESSURE

  1. PEL - EXECUTE - 1N
  2. BOOST PUMP switch - ON - 2C
A

Caution: unless a greater emergency exists, do not reset boost pump circuit breaker if open

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24
Q

OBOGS SYSTEM MALFUNCTION —————– 1W

  1. PCL - ADVANCE
  2. OBOGS - CHECK (BOTH):
    1. OBOGS supply lever - ON
    2. OBOGS concentration lever - MAX
    3. OBOGS pressure lever - EMERGENCY

If OBOGS FAIL warning remains illuminated:

  1. OBOGS Inoperative Procedure - EXECUTE
A

Warning: If the battery fails, OBOGS will be inoperative.

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25
Q

OBOGS SYSTEM MALFUNCTION

  1. PCL - ADVANCE ————————— 2N
  2. OBOGS - CHECK (BOTH):
    1. OBOGS supply lever - ON
    2. OBOGS concentration lever - MAX
    3. OBOGS pressure lever - EMERGENCY

If OBOGS FAIL warning remains illuminated:

  1. OBOGS Inoperative Procedure - EXECUTE
A

Note- advance PCL as required to extinguish OBOGS FAIL warning. At low bleed air pressure conditions, bleed air pressure may drop sufficiently to illuminate the OBOGS FAIL warning. This does not necessarily indicate an OBOGS failure. If OBOGS FAIL warning extinguishes, continue flight.

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26
Q

OBOGS SYSTEM MALFUNCTION

  1. PCL - ADVANCE
  2. OBOGS - CHECK (BOTH):
    1. OBOGS supply lever - ON
    2. OBOGS concentration lever - MAX
    3. OBOGS pressure lever - EMERGENCY ————————— 3W

If OBOGS FAIL warning remains illuminated:

  1. OBOGS Inoperative Procedure - EXECUTE
A

Warning: It is possible to experience hypoxia symptons if OBOGS has malfunctioned and cabin altitude is above 10,000 feet.

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27
Q

OBOGS SYSTEM MALFUNCTION

  1. PCL - ADVANCE
  2. OBOGS - CHECK (BOTH):
    1. OBOGS supply lever - ON
    2. OBOGS concentration lever - MAX
    3. OBOGS pressure lever - EMERGENCY ————————— 4C

If OBOGS FAIL warning remains illuminated:

  1. OBOGS Inoperative Procedure - EXECUTE
A

Caution: When breathing oxygen nder increased pressure, breath at a rate and depth slightly less than normal to preculed hyperventilation.

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28
Q

OBOGS SYSTEM MALFUNCTION

  1. PCL - ADVANCE
  2. OBOGS - CHECK (BOTH):
    1. OBOGS supply lever - ON
    2. OBOGS concentration lever - MAX
    3. OBOGS pressure lever - EMERGENCY ————————— 5N

If OBOGS FAIL warning remains illuminated:

  1. OBOGS Inoperative Procedure - EXECUTE
A

Note: The OBOGS FAIL warning will illuminate if both supply levers are set to OFF with the engine running.

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29
Q

OBOGS INOPERATIVE —————–1W

  1. GREEN RING - PULL (AS REQUIRED)
  2. Descent below cabin altitude of 10,000 feet - INITIATE
  3. Disconnect main oxygen supply hose from CRU-60/P
  4. OBOGS - OFF (BOTH)
  5. Land as soon as practical
A

Warning: If hypoxia is experienced or suspected, land as soon as possible.

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30
Q

OBOGS INOPERATIVE —————– 2W

  1. GREEN RING - PULL (AS REQUIRED)
  2. Descent below cabin altitude of 10,000 feet - INITIATE
  3. Disconnect main oxygen supply hose from CRU-60/P
  4. OBOGS - OFF (BOTH)
  5. Land as soon as practical
A

Warning: Anytime cabin pressure exceeds 10,000 feet and either OBOGS and/or cabin pressure is lost, an emergency descent to a cabin altitude of 10,000 feet or below must be accomplished. Use of emergency oxygen is required when OBOGS is lost and cabin pressure exceeds 10,000 feet pressure equivalent. Once emergency oxygen is activated, descent to aircraft altitudes at or below 10,000 feet MSL is essential within 10 minutes of activation of emergency oxygen.

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31
Q

OBOGS INOPERATIVE —————– 3W

  1. GREEN RING - PULL (AS REQUIRED)
  2. Descent below cabin altitude of 10,000 feet - INITIATE
  3. Disconnect main oxygen supply hose from CRU-60/P
  4. OBOGS - OFF (BOTH)
  5. Land as soon as practical
A

Warning: If the battery fails, OBOGS will be inoperative.

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32
Q

OBOGS INOPERATIVE

  1. GREEN RING - PULL (AS REQUIRED) ———- 4C
  2. Descent below cabin altitude of 10,000 feet - INITIATE
  3. Disconnect main oxygen supply hose from CRU-60/P
  4. OBOGS - OFF (BOTH)
  5. Land as soon as practical
A

Caution: When breathing oxygen under increased pressure, breath at a rate and depth slightly less than normal to preclude hyperventilation.

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33
Q

OBOGS INOPERATIVE

  1. GREEN RING - PULL (AS REQUIRED) ———- 5N
  2. Descent below cabin altitude of 10,000 feet - INITIATE
  3. Disconnect main oxygen supply hose from CRU-60/P
  4. OBOGS - OFF (BOTH)
  5. Land as soon as practical
A

Note: When the emergency oxygen system is actuated, high-pressure air may make verbal communication with the other crewmember or ATC more difficult.

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34
Q

OBOGS INOPERATIVE

  1. GREEN RING - PULL (AS REQUIRED) ———- 6N
  2. Descent below cabin altitude of 10,000 feet - INITIATE
  3. Disconnect main oxygen supply hose from CRU-60/P
  4. OBOGS - OFF (BOTH)
  5. Land as soon as practical
A

Note: Once activated, emergency oxygen cannot be shut off and will provide oxygen flow until the cylinder is depleted (10 minutes).

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35
Q

OBOGS INOPERATIVE

  1. GREEN RING - PULL (AS REQUIRED)
  2. Descent below cabin altitude of 10,000 feet - INITIATE
  3. Disconnect main oxygen supply hose from CRU-60/P —————– 7N
  4. OBOGS - OFF (BOTH)
  5. Land as soon as practical
A

Note: Avoid inadvertently disconnecting COMM cable when disconnecting main oxygen hose.

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36
Q

OBOGS INOPERATIVE

  1. GREEN RING - PULL (AS REQUIRED)
  2. Descent below cabin altitude of 10,000 feet - INITIATE
  3. Disconnect main oxygen supply hose from CRU-60/P —————– 8N
  4. OBOGS - OFF (BOTH)
  5. Land as soon as practical
A

Note: Disconnecting the main oxygen supply hose from the CRU-60/P is recommended as it improves breathing capability by providing pressure relief and improves anti-suffocation capability by reducing resistance.

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37
Q

UNCOMMANDED POWER CHANGES/LOSS OF POWER/UNCOMMANDED PROPELLER FEATHER

  1. PCL - PCL MID RANGE —————-1N
  2. PMU SWITCH - OFFF
  3. PROP SYS CIRCUIT BREAKER - PULL, IF NP STABLE BELOW 40%
  4. PCL - ADVANCE AS REQUIRED

If power is sufficient for continued flight:

  1. PEL - EXECUTE

If power is insufficient for continued flight:

  1. PROP SYS circuite breaker - RESET; AS REQUIRED
  2. PCL - OFF
  3. FIREWALL SHUTOFF handle - PULL
  4. Execute forced landing or eject
A

Note: Mid-range is a physical PCL angle that approximates the midway position between IDLE and MAX.

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38
Q

UNCOMMANDED POWER CHANGES/LOSS OF POWER/UNCOMMANDED PROPELLER FEATHER

  1. PCL - PCL MID RANGE —————-2N
  2. PMU SWITCH - OFFF
  3. PROP SYS CIRCUIT BREAKER - PULL, IF NP STABLE BELOW 40%
  4. PCL - ADVANCE AS REQUIRED

If power is sufficient for continued flight:

  1. PEL - EXECUTE

If power is insufficient for continued flight:

  1. PROP SYS circuite breaker - RESET; AS REQUIRED
  2. PCL - OFF
  3. FIREWALL SHUTOFF handle - PULL
  4. Execute forced landing or eject
A

Note: A PCL position above IDLE will provide the best chance for the engine to recover.

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39
Q

UNCOMMANDED POWER CHANGES/LOSS OF POWER/UNCOMMANDED PROPELLER FEATHER

  1. PCL - PCL MID RANGE —————- 3N
  2. PMU SWITCH - OFFF
  3. PROP SYS CIRCUIT BREAKER - PULL, IF NP STABLE BELOW 40%
  4. PCL - ADVANCE AS REQUIRED

If power is sufficient for continued flight:

  1. PEL - EXECUTE

If power is insufficient for continued flight:

  1. PROP SYS circuite breaker - RESET; AS REQUIRED
  2. PCL - OFF
  3. FIREWALL SHUTOFF handle - PULL
  4. Execute forced landing or eject
A

Note: A mid-range PCL position will minimize the potential of engine overtorque and/or overtemperature when the PMU is turned OFF.

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40
Q

UNCOMMANDED POWER CHANGES/LOSS OF POWER/UNCOMMANDED PROPELLER FEATHER

  1. PCL - PCL MID RANGE
  2. PMU SWITCH - OFF ———————– 4C
  3. PROP SYS CIRCUIT BREAKER - PULL, IF NP STABLE BELOW 40%
  4. PCL - ADVANCE AS REQUIRED

If power is sufficient for continued flight:

  1. PEL - EXECUTE

If power is insufficient for continued flight:

  1. PROP SYS circuite breaker - RESET; AS REQUIRED
  2. PCL - OFF
  3. FIREWALL SHUTOFF handle - PULL
  4. Execute forced landing or eject
A

Caution: There is a potential for ITT limits to be exceeded if the PMU switch is turned OFF with ITT ≥820 °C.

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41
Q

UNCOMMANDED POWER CHANGES/LOSS OF POWER/UNCOMMANDED PROPELLER FEATHER

  1. PCL - PCL MID RANGE
  2. PMU SWITCH - OFF ———————– 5C
  3. PROP SYS CIRCUIT BREAKER - PULL, IF NP STABLE BELOW 40%
  4. PCL - ADVANCE AS REQUIRED

If power is sufficient for continued flight:

  1. PEL - EXECUTE

If power is insufficient for continued flight:

  1. PROP SYS circuite breaker - RESET; AS REQUIRED
  2. PCL - OFF
  3. FIREWALL SHUTOFF handle - PULL
  4. Execute forced landing or eject
A

Caution: Ground idle will not be available during landing rollout and taxi. Plan for increased landing distances due to higher IDLE N1 (approximately 67%).

42
Q

UNCOMMANDED POWER CHANGES/LOSS OF POWER/UNCOMMANDED PROPELLER FEATHER

  1. PCL - PCL MID RANGE
  2. PMU SWITCH - OFF
  3. PROP SYS CIRCUIT BREAKER - PULL, IF NP STABLE BELOW 40% ——————— 6N
  4. PCL - ADVANCE AS REQUIRED

If power is sufficient for continued flight:

  1. PEL - EXECUTE

If power is insufficient for continued flight:

  1. PROP SYS circuite breaker - RESET; AS REQUIRED
  2. PCL - OFF
  3. FIREWALL SHUTOFF handle - PULL
  4. Execute forced landing or eject
A

Note: With constant airspeed and torque, RPM can be considered stable if below 40% and no upward change for a 3-second period.

43
Q

UNCOMMANDED POWER CHANGES/LOSS OF POWER/UNCOMMANDED PROPELLER FEATHER

  1. PCL - PCL MID RANGE
  2. PMU SWITCH - OFF
  3. PROP SYS CIRCUIT BREAKER - PULL, IF NP STABLE BELOW 40% ——————— 7N
  4. PCL - ADVANCE AS REQUIRED

If power is sufficient for continued flight:

  1. PEL - EXECUTE

If power is insufficient for continued flight:

  1. PROP SYS circuite breaker - RESET; AS REQUIRED
  2. PCL - OFF
  3. FIREWALL SHUTOFF handle - PULL
  4. Execute forced landing or eject
A

Note: If NP indicator is displaying red X’s, switching the PMU to NORM and back OFF will reset the PMU and should restore the NP indication.

44
Q

UNCOMMANDED POWER CHANGES/LOSS OF POWER/UNCOMMANDED PROPELLER FEATHER

  1. PCL - PCL MID RANGE
  2. PMU SWITCH - OFF
  3. PROP SYS CIRCUIT BREAKER - PULL, IF NP STABLE BELOW 40% ——————— 8N
  4. PCL - ADVANCE AS REQUIRED

If power is sufficient for continued flight:

  1. PEL - EXECUTE

If power is insufficient for continued flight:

  1. PROP SYS circuite breaker - RESET; AS REQUIRED
  2. PCL - OFF
  3. FIREWALL SHUTOFF handle - PULL
  4. Execute forced landing or eject
A

Note: Propeller should come out of feather within
15-20 seconds.

45
Q

UNCOMMANDED POWER CHANGES/LOSS OF POWER/UNCOMMANDED PROPELLER FEATHER

  1. PCL - PCL MID RANGE
  2. PMU SWITCH - OFF
  3. PROP SYS CIRCUIT BREAKER - PULL, IF NP STABLE BELOW 40%
  4. PCL - ADVANCE AS REQUIRED - 9W

If power is sufficient for continued flight:

  1. PEL - EXECUTE

If power is insufficient for continued flight:

  1. PROP SYS circuite breaker - RESET; AS REQUIRED
  2. PCL - OFF
  3. FIREWALL SHUTOFF handle - PULL
  4. Execute forced landing or eject
A

Warning: If rate of descent (indicated on the VSI while stabilized at 125 KIAS with gear, flaps, and speed brake retracted and 4-6% torque) is greater than 1500 ft/min, increase torque as necessary (up to 131%) to achieve approximately 1350-1500 ft/min rate of descent. If engine power is insufficient to produce a rate of descent less than 1500 ft/min, set PCL to OFF.

46
Q

UNCOMMANDED POWER CHANGES/LOSS OF POWER/UNCOMMANDED PROPELLER FEATHER

  1. PCL - PCL MID RANGE
  2. PMU SWITCH - OFF
  3. PROP SYS CIRCUIT BREAKER - PULL, IF NP STABLE BELOW 40%
  4. PCL - ADVANCE AS REQUIRED - 10N

If power is sufficient for continued flight:

  1. PEL - EXECUTE

If power is insufficient for continued flight:

  1. PROP SYS circuite breaker - RESET; AS REQUIRED
  2. PCL - OFF
  3. FIREWALL SHUTOFF handle - PULL
  4. Execute forced landing or eject
A

Note: The pilot should consider moving the PCL
through the full range of motion to determine
power available.

47
Q

UNCOMMANDED POWER CHANGES/LOSS OF POWER/UNCOMMANDED PROPELLER FEATHER

  1. PCL - PCL MID RANGE
  2. PMU SWITCH - OFF
  3. PROP SYS CIRCUIT BREAKER - PULL, IF NP STABLE BELOW 40%
  4. PCL - ADVANCE AS REQUIRED -

If power is sufficient for continued flight:

  1. PEL - EXECUTE

If power is insufficient to complete PEL: —– 11C

  1. PROP SYS circuite breaker - RESET; AS REQUIRED
  2. PCL - OFF
  3. FIREWALL SHUTOFF handle - PULL
  4. Execute forced landing or eject
A

Caution: Consideration should be given to leaving the
engine operating with PCL at mid range.

48
Q

UNCOMMANDED POWER CHANGES/LOSS OF POWER/UNCOMMANDED PROPELLER FEATHER

  1. PCL - PCL MID RANGE
  2. PMU SWITCH - OFF
  3. PROP SYS CIRCUIT BREAKER - PULL, IF NP STABLE BELOW 40%
  4. PCL - ADVANCE AS REQUIRED -

If power is sufficient for continued flight:

  1. PEL - EXECUTE

If power is insufficient to complete PEL:

  1. PROP SYS circuite breaker - RESET; AS REQUIRED ———– 12W
  2. PCL - OFF
  3. FIREWALL SHUTOFF handle - PULL
  4. Execute forced landing or eject
A

Warning: With the PROP SYS circuit breaker pulled and the PMU switch OFF, the feather dump solenoid will not be powered. The propellerwill feather at a slower rate as oil pressure decreases and the feathering spring takes effect. Glide performance will be considerably reduced and it may not be possible to intercept or fly the emergency landing pattern.

49
Q

COMPRESSOR STALLS:

  1. PCL - SLOWLY RETARD BELOW STALL THRESHOLD
  2. DEFOG switch - ON ————————- 1N
  3. PCL - SLOWLY ADVANCED (AS REQUIRED)

If power is sufficient for continued flight:

  1. PEL - EXECUTE

If power is insufficient to complete PEL:

  1. PCL - OFF
  2. FIREWALL SHUTOFF handle - PULL
  3. Execute forced landing or eject
A

Note: Setting the DEFOG switch to ON automatically selects high bleed air inflow and will alleviate back pressure on the engine compressor.

50
Q

COMPRESSOR STALLS:

  1. PCL - SLOWLY RETARD BELOW STALL THRESHOLD
  2. DEFOG switch - ON
  3. PCL - SLOWLY ADVANCED (AS REQUIRED)

If power is sufficient for continued flight:

  1. PEL - EXECUTE

If power is insufficient to complete PEL:

  1. PCL - OFF ——————————— 2W
  2. FIREWALL SHUTOFF handle - PULL
  3. Execute forced landing or eject
A

Warning: When the engine is so underpowered that
high rates of descent occur, any delay in shutting
down the engine to feather the propellor
may result in insufficient altitude to reach a
suitable landing site.

51
Q

FIRE IN FLIGHT:

If fire is confirmed: —————- 1W

  1. PCL - OFF
  2. FIREWALL SHUTOFF handle - PULL

If fire is extinguished:

  1. Forced landing - EXECUTE

If fire is not extinguished

  1. Eject (BOTH)

If fire is not confirmed:

  1. PEL - EXECUTE
A

Warning: Illumination of the fire warning light accompanied by one or more of the following indications is confirmation of an engine fire: smoke; flames; engine vibration; unusual sounds; high ITT; and fluctuating oil pressure, oil temperature, or hydraulic pressure.

52
Q

FIRE IN FLIGHT:

If fire is confirmed:

  1. PCL - OFF
  2. FIREWALL SHUTOFF handle - PULL

If fire is extinguished:

  1. Forced landing - EXECUTE

If fire is not extinguished

  1. Eject (BOTH)

If fire is not confirmed:

  1. PEL - EXECUTE ———————– 2W
A

Warning: A fire warning light with no accompanying indication is not a confirmed fire. Do not shut down an engine for an unconfirmed fire.

53
Q

FIRE IN FLIGHT:

If fire is confirmed:

  1. PCL - OFF
  2. FIREWALL SHUTOFF handle - PULL

If fire is extinguished:

  1. Forced landing - EXECUTE

If fire is not extinguished

  1. Eject (BOTH)

If fire is not confirmed:

  1. PEL - EXECUTE ———————– 3W
A

Warning: High engine compartment temperatures resulting from a bleed air leak may cause illumination of the fire warning light. Reducing the PCL setting towards IDLE will decrease the amount of bleed air and possibly
extinguish the fire warning light; however, advancing the PCL might be required to intercept the ELP. Regardless of reducing or advancing the PCL, continue to investigate for indications confirming an engine fire.

54
Q

FIRE IN FLIGHT:

If fire is confirmed:

  1. PCL - OFF
  2. FIREWALL SHUTOFF handle - PULL

If fire is extinguished:

  1. Forced landing - EXECUTE

If fire is not extinguished

  1. Eject (BOTH)

If fire is not confirmed:

  1. PEL - EXECUTE ———————– 4W
A

Warning: If the fire cannot be confirmed, the fire warning system may be at fault and should be tested as conditions permit. If only one fire loop annunciator is illuminated (top or bottom half only), a false fire indication may exist if the other loop tests good.

55
Q

CHIP DETECTOR WARNING

  1. PCL - MINIMUM NECESSARY TO INTERCEPT ELP; AVOID UNNECESSARY PCL MOVEMENTS ——————- 1C
  2. PEL - EXECUTE
A

Caution: Higher power settings may aggravate the existing condition.

56
Q

OIL SYSTEM MALFUNCTION OR LOW OIL PRESSURE ————– 1N

If only amber OIL PX caution illuminates:

  1. Terminate maneuver
  2. Check oil pressure; if pressure is normal, continue operations

If red OIL PX warning illuminates and/or amber OIL PX caution remains illuminated for 5 seconds:

  1. PCL - MINIMUM NECESSARY TO INTERCEPT ELP; AVOID UNNECESSARY PCL MOVEMENTS
  2. PEL - EXECUTE
A

Note: Use this procedure for any of the following: red OIL PX warning illuminated, amber OIL PX caution illuminated, oil pressure fluctuations, or oil temperature out of limits.

57
Q

OIL SYSTEM MALFUNCTION OR LOW OIL PRESSURE ————– 2N

If only amber OIL PX caution illuminates:

  1. Terminate maneuver
  2. Check oil pressure; if pressure is normal, continue operations

If red OIL PX warning illuminates and/or amber OIL PX caution remains illuminated for 5 seconds:

  1. PCL - MINIMUM NECESSARY TO INTERCEPT ELP; AVOID UNNECESSARY PCL MOVEMENTS
  2. PEL - EXECUTE
A

Note: If OIL PX warning illuminates and oil pressure indicates <5 psi, check OIL TRX circuit breaker on the battery bus circuit breaker panel (left front console). If the circuit breaker is open, it may be reset.

58
Q

OIL SYSTEM MALFUNCTION OR LOW OIL PRESSURE ————– 3N

If only amber OIL PX caution illuminates:

  1. Terminate maneuver
  2. Check oil pressure; if pressure is normal, continue operations

If red OIL PX warning illuminates and/or amber OIL PX caution remains illuminated for 5 seconds:

  1. PCL - MINIMUM NECESSARY TO INTERCEPT ELP; AVOID UNNECESSARY PCL MOVEMENTS
  2. PEL - EXECUTE
A

Note: Due to the sensitivity of the signal conditioning unit, a single, momentary illumination of the amber OIL PX caution while maneuvering is possible but may not indicate a malfunction.

59
Q

OIL SYSTEM MALFUNCTION OR LOW OIL PRESSURE ————- 4N

If only amber OIL PX caution illuminates:

  1. Terminate maneuver
  2. Check oil pressure; if pressure is normal, continue operations

If red OIL PX warning illuminates and/or amber OIL PX caution remains illuminated for 5 seconds:

  1. PCL - MINIMUM NECESSARY TO INTERCEPT ELP; AVOID UNNECESSARY PCL MOVEMENTS
  2. PEL - EXECUTE
A

Note: Illumination of both red and amber OIL PX message while the oil pressure gage indicates normal pressure indicates an SCU failure.

60
Q

OIL SYSTEM MALFUNCTION OR LOW OIL PRESSURE

If only amber OIL PX caution illuminates:

  1. Terminate maneuver
  2. Check oil pressure; if pressure is normal, continue operations

If red OIL PX warning illuminates and/or amber OIL PX caution remains illuminated for 5 seconds:

  1. PCL - MINIMUM NECESSARY TO INTERCEPT ELP; AVOID UNNECESSARY PCL MOVEMENTS —————- 5C
  2. PEL - EXECUTE
A

Caution: Higher power settings may aggravate the
existing condition.

61
Q

IMMEDIATE AIRSTART (PMU NORM) ———- 1W

  1. PCL - OFF
  2. STARTER switch - AUTO/RESET
  3. PCL - IDLE above 13% N1
  4. Enginge instruments- monitor ITT, N1, and OIL pressure

If airstart is unsuccessful:

  1. PCL - OFF
  2. FIREWALL SHUTOFF handle - PULL
  3. Execute forced landing or Eject

If airstart is successful:

  1. PCL - As required after N1 reaches idle RPM (approximately 67% N1)
  2. PEL - execute
  3. Confirm the position of the following:
    1. BOOST PUMP switch - ON
    2. IGNITION switch - ON
  4. STARTER switch - NORM
  5. BLEED AIR INFLOW switch - NORM
  6. GEN switch - verify ON, reset if necessary
  7. OBOGS - as required
A

Warning: Airstart attempts outside of the airstart envelope may be unsuccessful or result in engine overtemperature. Consideration should be given to ensure airstarts are attempted within the airstart envelope (125-200 KIAS for sea level to 15,000 feet, or 135-200 KIAS for 15,001 to 20,000 feet).

62
Q

IMMEDIATE AIRSTART (PMU NORM)

  1. PCL - OFF ——————————– 2W
  2. STARTER switch - AUTO/RESET
  3. PCL - IDLE above 13% N1
  4. Enginge instruments- monitor ITT, N1, and OIL pressure

If airstart is unsuccessful:

  1. PCL - OFF
  2. FIREWALL SHUTOFF handle - PULL
  3. Execute forced landing or Eject

If airstart is successful:

  1. PCL - As required after N1 reaches idle RPM (approximately 67% N1)
  2. PEL - execute
  3. Confirm the position of the following:
    1. BOOST PUMP switch - ON
    2. IGNITION switch - ON
  4. STARTER switch - NORM
  5. BLEED AIR INFLOW switch - NORM
  6. GEN switch - verify ON, reset if necessary
  7. OBOGS - as required
A

Warning: Do not delay ejection while attempting
airstart at low altitude if below 2000 feet
AGL.

63
Q

IMMEDIATE AIRSTART (PMU NORM)

  1. PCL - OFF ——————————– 3W
  2. STARTER switch - AUTO/RESET
  3. PCL - IDLE above 13% N1
  4. Enginge instruments- monitor ITT, N1, and OIL pressure

If airstart is unsuccessful:

  1. PCL - OFF
  2. FIREWALL SHUTOFF handle - PULL
  3. Execute forced landing or Eject

If airstart is successful:

  1. PCL - As required after N1 reaches idle RPM (approximately 67% N1)
  2. PEL - execute
  3. Confirm the position of the following:
    1. BOOST PUMP switch - ON
    2. IGNITION switch - ON
  4. STARTER switch - NORM
  5. BLEED AIR INFLOW switch - NORM
  6. GEN switch - verify ON, reset if necessary
  7. OBOGS - as required
A

Warning: PCL must be in OFF to feather the propeller, and ensure proper starter, ignition, boost pump, and PMU operation during airstart.

64
Q

IMMEDIATE AIRSTART (PMU NORM)

  1. PCL - OFF ——————————– 4C
  2. STARTER switch - AUTO/RESET
  3. PCL - IDLE above 13% N1
  4. Enginge instruments- monitor ITT, N1, and OIL pressure

If airstart is unsuccessful:

  1. PCL - OFF
  2. FIREWALL SHUTOFF handle - PULL
  3. Execute forced landing or Eject

If airstart is successful:

  1. PCL - As required after N1 reaches idle RPM (approximately 67% N1)
  2. PEL - execute
  3. Confirm the position of the following:
    1. BOOST PUMP switch - ON
    2. IGNITION switch - ON
  4. STARTER switch - NORM
  5. BLEED AIR INFLOW switch - NORM
  6. GEN switch - verify ON, reset if necessary
  7. OBOGS - as required
A

Caution: Ensure PCL is in OFF; otherwise, fuel may be prematurely introduced during start.

65
Q

IMMEDIATE AIRSTART (PMU NORM)

  1. PCL - OFF
  2. STARTER switch - AUTO/RESET
  3. PCL - IDLE above 13% N1 ————-5W
  4. Enginge instruments- monitor ITT, N1, and OIL pressure

If airstart is unsuccessful:

  1. PCL - OFF
  2. FIREWALL SHUTOFF handle - PULL
  3. Execute forced landing or Eject

If airstart is successful:

  1. PCL - As required after N1 reaches idle RPM (approximately 67% N1)
  2. PEL - execute
  3. Confirm the position of the following:
    1. BOOST PUMP switch - ON
    2. IGNITION switch - ON
  4. STARTER switch - NORM
  5. BLEED AIR INFLOW switch - NORM
  6. GEN switch - verify ON, reset if necessary
  7. OBOGS - as required
A

Warning: Movement of the PCL above IDLE before N1 stabilizes at approximately 67% will cause an increase in fuel flow which may cause engine failure due to a severe ITT overtemperature.

66
Q

IMMEDIATE AIRSTART (PMU NORM)

  1. PCL - OFF
  2. STARTER switch - AUTO/RESET
  3. PCL - IDLE above 13% N1 ————-5W
  4. Enginge instruments- monitor ITT, N1, and OIL pressure

If airstart is unsuccessful:

  1. PCL - OFF
  2. FIREWALL SHUTOFF handle - PULL
  3. Execute forced landing or Eject

If airstart is successful:

  1. PCL - As required after N1 reaches idle RPM (approximately 67% N1)
  2. PEL - execute
  3. Confirm the position of the following:
    1. BOOST PUMP switch - ON
    2. IGNITION switch - ON
  4. STARTER switch - NORM
  5. BLEED AIR INFLOW switch - NORM
  6. GEN switch - verify ON, reset if necessary
  7. OBOGS - as required
A

Warning: Movement of the PCL above IDLE before N1 stabilizes at approximately 67% will cause an increase in fuel flow which may cause engine failure due to a severe ITT overtemperature.

67
Q

IMMEDIATE AIRSTART (PMU NORM)

  1. PCL - OFF
  2. STARTER switch - AUTO/RESET
  3. PCL - IDLE above 13% N1 ————- 6C
  4. Enginge instruments- monitor ITT, N1, and OIL pressure

If airstart is unsuccessful:

  1. PCL - OFF
  2. FIREWALL SHUTOFF handle - PULL
  3. Execute forced landing or Eject

If airstart is successful:

  1. PCL - As required after N1 reaches idle RPM (approximately 67% N1)
  2. PEL - execute
  3. Confirm the position of the following:
    1. BOOST PUMP switch - ON
    2. IGNITION switch - ON
  4. STARTER switch - NORM
  5. BLEED AIR INFLOW switch - NORM
  6. GEN switch - verify ON, reset if necessary
  7. OBOGS - as required
A

Caution: If N1 does not rise within 5 seconds, discontinue the airstart attempt and proceed to IF AIRSTART IS UNSUCCESSFUL.

68
Q

IMMEDIATE AIRSTART (PMU NORM)

  1. PCL - OFF
  2. STARTER switch - AUTO/RESET
  3. PCL - IDLE above 13% N1
  4. Enginge instruments- monitor ITT, N1, and OIL pressure

If airstart is unsuccessful:

  1. PCL - OFF —————————– 7C
  2. FIREWALL SHUTOFF handle - PULL
  3. Execute forced landing or Eject

If airstart is successful:

  1. PCL - As required after N1 reaches idle RPM (approximately 67% N1)
  2. PEL - execute
  3. Confirm the position of the following:
    1. BOOST PUMP switch - ON
    2. IGNITION switch - ON
  4. STARTER switch - NORM
  5. BLEED AIR INFLOW switch - NORM
  6. GEN switch - verify ON, reset if necessary
  7. OBOGS - as required
A

Caution: If there is no rise in ITT within 10 seconds after fuel flow indications, place the PCL to OFF and abort the start.

69
Q

IMMEDIATE AIRSTART (PMU NORM)

  1. PCL - OFF
  2. STARTER switch - AUTO/RESET
  3. PCL - IDLE above 13% N1
  4. Enginge instruments- monitor ITT, N1, and OIL pressure

If airstart is unsuccessful:

  1. PCL - OFF
  2. FIREWALL SHUTOFF handle - PULL
  3. Execute forced landing or Eject

If airstart is successful:

  1. PCL - As required after N1 reaches idle RPM (approximately 67% N1)
  2. PEL - execute
  3. Confirm the position of the following:
    1. BOOST PUMP switch - ON ———– 8C
    2. IGNITION switch - ON
  4. STARTER switch - NORM
  5. BLEED AIR INFLOW switch - NORM
  6. GEN switch - verify ON, reset if necessary
  7. OBOGS - as required
A

Caution: Continuous operation with the BOOST PUMP switch in the ON position will cause damage to the engine-driven low pressure fuel pump. Upon landing, notify maintenance of the duration of flight with BOOST PUMP switch in the ON position.

70
Q

IMMEDIATE AIRSTART (PMU NORM)

  1. PCL - OFF
  2. STARTER switch - AUTO/RESET
  3. PCL - IDLE above 13% N1
  4. Enginge instruments- monitor ITT, N1, and OIL pressure

If airstart is unsuccessful:

  1. PCL - OFF
  2. FIREWALL SHUTOFF handle - PULL
  3. Execute forced landing or Eject

If airstart is successful:

  1. PCL - As required after N1 reaches idle RPM (approximately 67% N1)
  2. PEL - execute
  3. Confirm the position of the following:
    1. BOOST PUMP switch - ON
    2. IGNITION switch - ON
  4. STARTER switch - NORM
  5. BLEED AIR INFLOW switch - NORM
  6. GEN switch - verify ON, reset if necessary —- 9N
  7. OBOGS - as required
A

Note: If generator will not reset, verify the STARTER switch is in NORM. The starter will drain battery power in 10 minutes if left in MANUAL.

71
Q

PRECAUTIONARY EMERGENCY LANDING (PEL) —————— 1W

  1. Turn to nearest suitable field
  2. Climb or accelerate to intercept ELP
  3. Gear, flaps, speed brake - UP
  4. Conduct a systematic check of the aircraft and instruments for additional signs of impending engine failure
  5. BOOST PUMP switch - as required
  6. IGNITION switch - as required
  7. Plan to intercept the emergency landing pattern at or below high key in the appropriate configuration and a minimum airspeed of 120 KIAS
A

Warning: If the engine should fail while flying the PEL, refer to the Engine Failure During Flight checklist, and transition to the Forced Landing procedure.

72
Q

PRECAUTIONARY EMERGENCY LANDING (PEL) —————— 2W

  1. Turn to nearest suitable field
  2. Climb or accelerate to intercept ELP
  3. Gear, flaps, speed brake - UP
  4. Conduct a systematic check of the aircraft and instruments for additional signs of impending engine failure
  5. BOOST PUMP switch - as required
  6. IGNITION switch - as required
  7. Plan to intercept the emergency landing pattern at or below high key in the appropriate configuration and a minimum airspeed of 120 KIAS
A

Warning: If rate of descent (indicated on the VSI while stabilized at 125 KIAS with gear, flaps, and speed brake retracted and 4 to 6% torque) is greater than 1500 ft/min, increase torque as necessary (up to 131%) to achieve approximately 1350 to 1500 ft/min rate of descent. If engine power is insufficient to produce a rate of descent less than 1500 ft/min, set PCL to OFF.

73
Q

PRECAUTIONARY EMERGENCY LANDING (PEL) —————— 3W

  1. Turn to nearest suitable field
  2. Climb or accelerate to intercept ELP
  3. Gear, flaps, speed brake - UP
  4. Conduct a systematic check of the aircraft and instruments for additional signs of impending engine failure
  5. BOOST PUMP switch - as required
  6. IGNITION switch - as required
  7. Plan to intercept the emergency landing pattern at or below high key in the appropriate configuration adn a minimum airspeed of 120 KIAS
A

Warning: Once on profile, if engine is vibrating excessively, or if indications of failure are imminent, set PCL to OFF.

74
Q

PRECAUTIONARY EMERGENCY LANDING (PEL) —————— 4W

  1. Turn to nearest suitable field
  2. Climb or accelerate to intercept ELP
  3. Gear, flaps, speed brake - UP
  4. Conduct a systematic check of the aircraft and instruments for additional signs of impending engine failure
  5. BOOST PUMP switch - as required
  6. IGNITION switch - as required
  7. Plan to intercept the emergency landing pattern at or below high key in the appropriate configuration adn a minimum airspeed of 120 KIAS
A

Warning: Engine failure or shutdown will completely disable the bleed air system. Depending on environmental conditions, this may cause significant canopy icing and/or fogging, severely hampering visibility, especially from the rear cockpit.

75
Q

PRECAUTIONARY EMERGENCY LANDING (PEL) —————— 5C

  1. Turn to nearest suitable field
  2. Climb or accelerate to intercept ELP
  3. Gear, flaps, speed brake - UP
  4. Conduct a systematic check of the aircraft and instruments for additional signs of impending engine failure
  5. BOOST PUMP switch - as required
  6. IGNITION switch - as required
  7. Plan to intercept the emergency landing pattern at or below high key in the appropriate configuration adn a minimum airspeed of 120 KIAS
A

Caution: Inducing yaw (side slipping) with a known engine/oil malfunction could result in impaired windshield visibility due to oil leakage spraying onto the windshield.

76
Q

PRECAUTIONARY EMERGENCY LANDING (PEL)

  1. Turn to nearest suitable field
  2. Climb or accelerate to intercept ELP
  3. Gear, flaps, speed brake - UP
  4. Conduct a systematic check of the aircraft and instruments for additional signs of impending engine failure ———————– 6N
  5. BOOST PUMP switch - as required
  6. IGNITION switch - as required
  7. Plan to intercept the emergency landing pattern at or below high key in the appropriate configuration adn a minimum airspeed of 120 KIAS
A

Note: Do not set the boost pump and ignition to ON for engine malfunctions, such as oil system, chip light, fire, or FOD. In these cases, turning the boost pump ON may provide an undesirable immediate relight.

77
Q

PRECAUTIONARY EMERGENCY LANDING (PEL)

  1. Turn to nearest suitable field
  2. Climb or accelerate to intercept ELP
  3. Gear, flaps, speed brake - UP
  4. Conduct a systematic check of the aircraft and instruments for additional signs of impending engine failure
  5. BOOST PUMP switch - as required
  6. IGNITION switch - as required
  7. Plan to intercept the emergency landing pattern at or below high key in the appropriate configuration adn a minimum airspeed of 120 KIAS ————— 7N
A

Note: For uncontrollable high power, the pilot must shut down the engine once landing is assured.

78
Q

ENGINE FAIULURE DURING FLIGHT

  1. ZOOM/GLIDE - 125 KIAS (minimum) ———— 1N
  2. PCL - OFF
  3. INTERCEPT ELP
  4. Airstart - attempt if warranted

If conditions do not warrant an airstart:

  1. FIREWALL SHUTOFF handle - PULL
  2. Execute Forced Landing or Eject
A

Note: Crosscheck N1 against other engine indications to assess condition of engine and determine if an airstart is warranted. At 125 KIAS, an engine which has flamed out will rotate below 8% N1 and indicate 0% N1. The engine oil pressure indicator may display oil pressures up to 4 psi with an N1 of 0%.

79
Q

ENGINE FAIULURE DURING FLIGHT

  1. ZOOM/GLIDE - 125 KIAS (minimum) ———— 2N
  2. PCL - OFF
  3. INTERCEPT ELP
  4. Airstart - attempt if warranted

If conditions do not warrant an airstart:

  1. FIREWALL SHUTOFF handle - PULL
  2. Execute Forced Landing or Eject
A

Note: If experiencing uncommanded power changes/loss of power/uncommanded propeller feather or compressor stalls, refer to appropriate procedure.

80
Q

ENGINE FAIULURE DURING FLIGHT

  1. ZOOM/GLIDE - 125 KIAS (minimum)
  2. PCL - OFF —————————— 3N
  3. INTERCEPT ELP
  4. Airstart - attempt if warranted

If conditions do not warrant an airstart:

  1. FIREWALL SHUTOFF handle - PULL
  2. Execute Forced Landing or Eject
A

Note: Propeller will not feather unless the PCL is fully in OFF.

81
Q

ENGINE FAIULURE DURING FLIGHT

  1. ZOOM/GLIDE - 125 KIAS (minimum)
  2. PCL - OFF
  3. INTERCEPT ELP ———————– 4W
  4. Airstart - attempt if warranted

If conditions do not warrant an airstart:

  1. FIREWALL SHUTOFF handle - PULL
  2. Execute Forced Landing or Eject
A

Warning: If a suitable landing surface is available, turn immediately to intercept the nearest suitable point on the ELP. Any delay could result in insufficient gliding distance to reach a landing surface.

82
Q

ENGINE FAIULURE DURING FLIGHT

  1. ZOOM/GLIDE - 125 KIAS (minimum)
  2. PCL - OFF
  3. INTERCEPT ELP ———————– 5W
  4. Airstart - attempt if warranted

If conditions do not warrant an airstart:

  1. FIREWALL SHUTOFF handle - PULL
  2. Execute Forced Landing or Eject
A

Warning : Do not delay decision to eject below 2000 feet AGL.

83
Q

ENGINE FAIULURE DURING FLIGHT

  1. ZOOM/GLIDE - 125 KIAS (minimum)
  2. PCL - OFF
  3. INTERCEPT ELP
  4. Airstart - attempt if warranted —– 6W

If conditions do not warrant an airstart:

  1. FIREWALL SHUTOFF handle - PULL
  2. Execute Forced Landing or Eject
A

Warning : Airstart procedure is not recommended below 2000 feet AGL, as primary attention should be to eject or safely recover the aircraft.

84
Q

FORCED LANDING —————— 1W

  1. Airspeed - 125 KIAS prior to extending landing gear
  2. EMER LDG GR handle - PULL (as required)
  3. Airspeed - 120 KIAS minimum until intercepting final; 110 KIAS minimum on final
  4. Flaps - As required

Accomplish the following as conditions permit:

  1. Distress call - TRANSMIT
  2. ELT switch - As required
  3. Transponder - 7700 (as required)
  4. Harness - LOCKED (BOTH)
  5. Emergency Ground Egress procedure - EXECUTE (as required)
A

Warning: Landing distance will increase with the propeller
feathered.

85
Q

FORCED LANDING —————— 2W

  1. Airspeed - 125 KIAS prior to extending landing gear
  2. EMER LDG GR handle - PULL (as required)
  3. Airspeed - 120 KIAS minimum until intercepting final; 110 KIAS minimum on final
  4. Flaps - As required

Accomplish the following as conditions permit:

  1. Distress call - TRANSMIT
  2. ELT switch - As required
  3. Transponder - 7700 (as required)
  4. Harness - LOCKED (BOTH)
  5. Emergency Ground Egress procedure - EXECUTE (as required)
A

Warning: Landing on an unprepared surface may cause
structural damage making it impossible to
open the canopy or fracture it using the CFS.

86
Q

FORCED LANDING —————— 3W

  1. Airspeed - 125 KIAS prior to extending landing gear
  2. EMER LDG GR handle - PULL (as required)
  3. Airspeed - 120 KIAS minimum until intercepting final; 110 KIAS minimum on final
  4. Flaps - As required

Accomplish the following as conditions permit:

  1. Distress call - TRANSMIT
  2. ELT switch - As required
  3. Transponder - 7700 (as required)
  4. Harness - LOCKED (BOTH)
  5. Emergency Ground Egress procedure - EXECUTE (as required)
A

Warning: Engine failure or shutdown will completely disable the bleed air system. Depending on environmental conditions, this may cause significant canopy icing and/or fogging, and severely hamper visibility, especially from the rear cockpit.

87
Q

FORCED LANDING —————— 4C

  1. Airspeed - 125 KIAS prior to extending landing gear
  2. EMER LDG GR handle - PULL (as required)
  3. Airspeed - 120 KIAS minimum until intercepting final; 110 KIAS minimum on final
  4. Flaps - As required

Accomplish the following as conditions permit:

  1. Distress call - TRANSMIT
  2. ELT switch - As required
  3. Transponder - 7700 (as required)
  4. Harness - LOCKED (BOTH)
  5. Emergency Ground Egress procedure - EXECUTE (as required)
A

Caution: Ejection is recommended if a suitable landing area is not available. If circumstances dictate an emergency landing and ejection is not possible or the ejection system malfunctions, the pilot may perform an ELP to an unprepared surface or ditch the aircraft. The aircraft structure can survive either type of forced landing; however, the risk of injury increases significantly due to crash loads and the complexity of ground or water egress.

88
Q

FORCED LANDING —————— 5C

  1. Airspeed - 125 KIAS prior to extending landing gear
  2. EMER LDG GR handle - PULL (as required)
  3. Airspeed - 120 KIAS minimum until intercepting final; 110 KIAS minimum on final
  4. Flaps - As required

Accomplish the following as conditions permit:

  1. Distress call - TRANSMIT
  2. ELT switch - As required
  3. Transponder - 7700 (as required)
  4. Harness - LOCKED (BOTH)
  5. Emergency Ground Egress procedure - EXECUTE (as required)
A

Caution: Inducing yaw (side slipping) with a known engine/oil malfunction could result in impaired windshield visibility due to oil leakage spraying onto the windshield.

89
Q

FORCED LANDING

  1. Airspeed - 125 KIAS prior to extending landing gear
  2. EMER LDG GR handle - PULL (as required) —————— 6W
  3. Airspeed - 120 KIAS minimum until intercepting final; 110 KIAS minimum on final
  4. Flaps - As required

Accomplish the following as conditions permit:

  1. Distress call - TRANSMIT
  2. ELT switch - As required
  3. Transponder - 7700 (as required)
  4. Harness - LOCKED (BOTH)
  5. Emergency Ground Egress procedure - EXECUTE (as required)
A

Warning: If landing on an unprepared surface or ditching, do not extend the landing gear. Flaps will not be available without emergency gear extension.

90
Q

FORCED LANDING

  1. Airspeed - 125 KIAS prior to extending landing gear
  2. EMER LDG GR handle - PULL (as required) ————- 7N
  3. Airspeed - 120 KIAS minimum until intercepting final; 110 KIAS minimum on final
  4. Flaps - As required

Accomplish the following as conditions permit:

  1. Distress call - TRANSMIT
  2. ELT switch - As required
  3. Transponder - 7700 (as required)
  4. Harness - LOCKED (BOTH)
  5. Emergency Ground Egress procedure - EXECUTE (as required)
A

Note: Normal safe indications with electrical power, when the emergency extension system has been used to lower the gear, are two green main gear lights, two red main door lights, green nose gear light, and red light in handle.

91
Q

FORCED LANDING

  1. Airspeed - 125 KIAS prior to extending landing gear
  2. EMER LDG GR handle - PULL (as required)
  3. Airspeed - 120 KIAS minimum until intercepting final; 110 KIAS minimum on final
  4. Flaps - As required ————- 8N

Accomplish the following as conditions permit:

  1. Distress call - TRANSMIT
  2. ELT switch - As required
  3. Transponder - 7700 (as required)
  4. Harness - LOCKED (BOTH)
  5. Emergency Ground Egress procedure - EXECUTE (as required)
A

Note: Selecting either TO or LDG flaps will extend the flaps to the commanded position if the landing gear has been extended using the emergency extension system and if battery power is available.

92
Q

FORCED LANDING

  1. Airspeed - 125 KIAS prior to extending landing gear
  2. EMER LDG GR handle - PULL (as required)
  3. Airspeed - 120 KIAS minimum until intercepting final; 110 KIAS minimum on final
  4. Flaps - As required ————- 9N

Accomplish the following as conditions permit:

  1. Distress call - TRANSMIT
  2. ELT switch - As required
  3. Transponder - 7700 (as required)
  4. Harness - LOCKED (BOTH)
  5. Emergency Ground Egress procedure - EXECUTE (as required)
A

Note: Landing gear/flap retraction is not possible when the emergency extension system has been used.

93
Q

FORCED LANDING

  1. Airspeed - 125 KIAS prior to extending landing gear
  2. EMER LDG GR handle - PULL (as required)
  3. Airspeed - 120 KIAS minimum until intercepting final; 110 KIAS minimum on final
  4. Flaps - As required ————- 10N

Accomplish the following as conditions permit:

  1. Distress call - TRANSMIT
  2. ELT switch - As required
  3. Transponder - 7700 (as required)
  4. Harness - LOCKED (BOTH)
  5. Emergency Ground Egress procedure - EXECUTE (as required)
A

Note: Nose wheel steering is unavailable with an inoperative engine. Maintain directional control with rudder and differential braking.

94
Q

FORCED LANDING

  1. Airspeed - 125 KIAS prior to extending landing gear
  2. EMER LDG GR handle - PULL (as required)
  3. Airspeed - 120 KIAS minimum until intercepting final; 110 KIAS minimum on final
  4. Flaps - As required

Accomplish the following as conditions permit:

  1. Distress call - TRANSMIT
  2. ELT switch - As required ————- 11N
  3. Transponder - 7700 (as required)
  4. Harness - LOCKED (BOTH)
  5. Emergency Ground Egress procedure - EXECUTE (as required)
A

Note: Activating the ELT at a higher altitude will transmit emergency signal for a longer distance and could aid in rescue/recovery.

95
Q

INADVERTENT DEPARTURE FROM CONTROLLED FLIGHT

  1. PCL - IDLE
  2. CONTROLS - NEUTRAL ———- 1W
  3. ALTITUDE - CHECK
  4. Recover from unusual attitude
A

Warning: Improperly positioning the control stick/elevator aft of the neutral position may significantly delay or prevent the aircraft from recovering from an OCF/spin which could result in loss of aircraft and/or crew.

96
Q

INADVERTENT DEPARTURE FROM CONTROLLED FLIGHT

  1. PCL - IDLE
  2. CONTROLS - NEUTRAL ———- 2N
  3. ALTITUDE - CHECK
  4. Recover from unusual attitude
A

Note: Cycling of control positions or applying antispin controls prematurely can aggravate aircraft motion and significantly delay recovery.

97
Q

INADVERTENT DEPARTURE FROM CONTROLLED FLIGHT

  1. PCL - IDLE
  2. CONTROLS - NEUTRAL
  3. ALTITUDE - CHECK ——————– 3W
  4. Recover from unusual attitude
A

Warning: Recommended minimum altitude for ejection is 6000 feet AGL.

98
Q

INADVERTENT DEPARTURE FROM CONTROLLED FLIGHT

  1. PCL - IDLE
  2. CONTROLS - NEUTRAL
  3. ALTITUDE - CHECK
  4. Recover from unusual attitude —- 4C
A

Caution: Power-on and inverted departures or spins will result in high loads on the engine and torque shaft. If an inverted or power-on departure is encountered, land as soon as conditions permit. The pilot should suspect possible engine damage and may experience unusual engine operation accompanied by low oil pressure or CHIP detector warning. In all cases of inverted or power-on departures, the engine shall be inspected by qualified maintenance personnel after flight.

99
Q

EJECT

  1. EJECTION HANDLE - PULL (BOTH) —- 1W
A

Warning: To avoid injury, grasp handle and pull sharply toward abdomen, keeping elbows against the body.

100
Q

EJECT

  1. EJECTION HANDLE - PULL (BOTH) —- 2W
A

Warning: The emergency escape system incorporates an explosive canopy fracturing system. The force of detonation blows numerous shards and small fragments outward from the canopy and into the cockpit. Some metallic fragments may be extremely hot and may cause burns upon contact with the skin. Aircrew should ensure exposed skin is covered, the oxygen mask is on, and visor is down prior to ejection or actuating the CFS system to prevent injury from shards and hot fragments.

101
Q

EJECT

  1. EJECTION HANDLE - PULL (BOTH) —- 3W
A

Warning: When ejecting over mountainous terrain exceeding 8000 feet MSL, the manual override (MOR) handle should be used to manually separate from the seat and deploy the parachute.

102
Q

EJECT

  1. EJECTION HANDLE - PULL (BOTH) —- 4N
A

Note: If ejecting at low speed, one or both sets of risers may remain velcroed together following seat separation. This may create a slight increase in descent rate and/or an uncommanded turn. Manually separate the risers if time permits. The steering lines (toggles) are located on the backside of each of the front risers. To counter any uncommanded turns, unstow the opposite steering line or use risers for controllability.

T-6B Texan II/Primary (20 decks)

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