2

BATTERY CHARGE = Airplanes prior to FL-215 and FM-10.

PROP GND SOL = Optional Equipment FL-115 adn after, FM-10 and after.

Battery charge rate is too high.

Airplanes prior to FL-215 and FM-10.

External power connector is plugged in.

28V being delivered to one or both ground idle low pitch stop solenoids.

Optional Equipment FL-115 and after, FM-10 and after.

Left brake deice system in operation.

Optional Equipment.

1. A/P TRIM FAIL.

2. A/P FAIL.

Improper trim or no trim from autopilot trim command.

Optional Equipment.

Autopilot monitor has sensed a failure.

Optional Equipment.

1. CONDITION LEVER = FUEL CUTOFF

2. PROPELLER LEVER = FEATHER

3. FIREWALL FUEL VALVE = CLOSE

4. FIRE EXTINGUISHER = ACTUATE (IF REQUIRED)

5. GENERATOR = OFF

6. ENGINE AUTO IGNITION = OFF

7. AUTOFEATHER = OFF

8. PROP SYNC = OFF

9. BRAKE DEICE = OFF

10. ELECTRICAL LOAD = MONITOR

1. CONDITION LEVER = FUEL SHUTOFF

2. FIREWALL FUEL VALVE = CLOSE

3. STARTER SWITCH = STARTER ONLY (30 SECONDS)

4. FIRE EXTINGUISHER (IF WARNING PERSISTS) = ACTUATE

1. CONDITION LEVER = FUEL SHUTOFF

2. PROP LEVERS = FEATHER

3. FIREWALL FUEL VALVE = CLOSE

4. MASTER SWITCH (GANG BAR) = OFF

5. BATTERY BUS = EMER OFF

6. ESIS/STANDBY GYRO = OFF

1. POWER LEVERS = GROUND FINE

2. BRAKES = MAXIMUM

WARNING: DO NOT USE REVERSE THRUST WITH ONE ENGINE INOPERATIVE.  CARE MUST BE EXERCISED WHEN USING SINGLE-ENGINE GROUND FINE ON SURFACES WITH REDUCED TRACTION.

-TAKEOFF CONTINUED-

1. VR SPEED = ROTATE APPROXIMATELY 10 DEGREES PITCH

2. LANDING GEAR = UP

3. AIRSPEED = MAINTAIN V2 TO 400 FEET AGL

4. PROPELLER (INOPERATIVE ENG) = VERIFY FEATHERED

WARNING: DO NOT RETARD THE FAILED ENGINE POWER LEVER UNTIL THE AUTOFEATHER SYSTEM HAS COMPLETELY STOPPED PROPELLER ROTATION.  TO DO SO WILL DEACTIVATE THE AUTOFEATHER CIRCUIT AND PREVENT AUTOMATIC FEATHERING.

5. FLAPS (400 FEET AGL) = UP AT V2+9KTS

6. AIRSPEED = INCREASE TO 125 KTS

7. CLIMB TO 1,500 FEET, THEN FOLLOW WITH CLEAN UP PROCEDURES: 

A. CONDITION LEVER = FUEL CUTOFF

B. PROPELLER LEVER = FEATHER

C. FIREWALL FUEL VALVE = CLOSE

D. GENERATOR = OFF

E. ENG AUTO IGNITION = OFF

8. AUTOFEATHER = OFF

9. PROP SYNC = OFF

10. BRAKE DEICE = OFF

11. ELECTRICAL LOAD = MONITOR

L OR R OIL PRESS LO ANNUNCIATOR: 

1. OIL PRESSURE = CONFIRM <60 PSI

2. IF CONFIRMED = SECURE ENGINE, OR: LAND AT THE NEAREST SUITABLE AIRPORT USING THE MINIMUM POWER REQUIRED TO SUSTAIN FLIGHT

[L/R OIL PRES LO]

L OR R FUEL PRESS LO ANNUNCIATOR: 

1. STANDBY PUMP (FAILED SIDE) = ON

2. [FUEL PRESS LO] = EXTINGUISHED

3. OIL TEMP GAGE (FAILED SIDE) = MONITOR

[L/R FUEL PRESS LO]

1. OXYGEN MASKS = DON

2. MASK SELECTOR SWITCH = EMER POSITION

3. MIC SWITCHES = OXY

4. INSTRUMENT EMERGENCY LIGHTS = ON

5. GENERATORS = OFF

TO FACILITATE SMOKE REMOVAL: 

6. PILOT AND COPILOT AIR = PULL ON

7. DEFROST AIR = PULL ON

8. CABIN AIR = PULL TO DECREASE

9. COCKPIT DOOR = OPEN

IF SMOKE PERSISTS OR IF EXTINGUISHING OF FIRE IS NOT CONFIRMED: 

10. AVIONICS MASTER = OFF

11. CABIN PRESSURIZATION (IF DESIRED) = DUMP

12. MASTER SWITCH (GANG BAR) = OFF

13. STORM WINDOW (IF REQUIRED) = OPEN BELOW 13,500 FEET

14. GND COMM SWITCH = PRESS TO RESTORE COMM

15. PLAN ON FLAPS UP LANDING

16. MANUALLY EXTEND GEAR

17. LAND AT NEAREST SUITABLE AIRPORT

WARNING: DISSIPATION OF SMOKE IS NOT SUFFICENT EVIDENCE THAT A FIRE HAS BEEN EXTINGUISHED.  IF IT CANNOT BE VISUALLY CONFIRMED THAT NO FIRE EXISTS, LAND AT THE NEAREST SUITABLE AIRPORT.

1. HEADSET(S) = OFF

2. OXYGEN MASKS = DON

3. MASK SELECTOR SWITCH = EMER POSITION

4. AUDIO SPEAKERS = ON

5. MIC SWITCHES = OXYGEN MASK

6. CABIN TEMP MODE = OFF

7. VENT BLOWER = HIGH

8. LEFT BLEED AIR VALVE = PNEU AND ENVIRO OFF

IF SMOKE DECREASES: 

9. CABIN TEMP MODE = OFF

IF SMOKE DOES NOT DECREASE: 

10. LEFT BLEED AIR VALVE = OPEN

11. RIGHT BLEED AIR VALVE = PNEU AND ENVIRO OFF

IF SMOKE DECREASES: 

12. CONTINUE OPERATION WITH RIGHT BLEED AIR OFF

IF SMOKE PERSISTS: 

13. BLEED AIR VALVES = PNEU AND ENVIRO OFF

14. CABIN PRESSURIZATION = DUMP

15. STORM WINDOW (IF REQUIRED) = OPEN BELOW 13,500 FEET

16. LAND AT THE NEAREST SUITABLE AIRPORT

IF THE DOOR UNLOCKED ANNUNCIATOR ILLUMINATES, OR IF AN UNLATCHED AIRSTAIR DOOR/CARGO DOOR IS SUSPECTED: 

1. ALL OCCUPANTS = SEATED WITH BELTS SECURELY FASTENED

2. CABIN SIGN - FSB

3. CABIN DIFFERENTIAL PRESSURE = REDUCE TO LOWEST VALUE PRACTICAL (O)

A. DESCENT AND/OR

B. SELECT HIGHER CABIN ALTITUDE SETTING

4. OXYGEN = AS REQUIRED 

5. LAND AT NEAREST SUITABLE AIRPORT

[DOOR UNLOCKED]

EMGERNCY DESCENT

1. POWER LEVERS = IDLE

2. PROP LEVERS = FULL FOWARD

3. FLAPS (202 KTS MAX) = APPROACH

4. LANDING GEAR (184 KTS MAX) = DOWN

5. AIRSPEED = 184 KTS MAX

15,000 POUNDS = 109 KTS VREF

14,000 POUNDS = 105 KTS VREF

13,000 POUNDS = 102 KTS VREF

12,000 POUNDS = 100 KTS VREF

11,000 POUNDS = 100 KTS VREF

10,000 POUNDS = 100 KTS VREF

1. APPROACH SPEED (VREF) = CONFIRM

2. CABIN SIGN = FSB

3. AUTOFEATHER = ARM

4. FLAPS = APPROACH

5. LANDING GEAR = DOWN

6. POWER LEVERS = IDLE

7. EXTERIOR AND INTERIOR LIGHTS = AS REQUIRED

8. RADAR = AS REQUIRED

9. SURFACE DEICE = AS REQUIRED

WHEN LANDING ASSURED: 

10. PRESSURIZATION = DUMP

11. FLAPS = DOWN

12. AIRSPEED = VREF

13. YAW DAMP = OFF

14. PROPELLER LEVERS = FULL FORWARD

AFTER TOUCHDOWN: 

15. POWER LEVERS = LIFT AND SELECT GROUND FINE

16. BRAKES = AS REQUIRED

AFTER AIRPLANE COMES TO A STOP: 

17. CONDITION LEVERS = FUEL CUTOFF

18. FIREWALL FUEL VALVES = CLOSE

19. MASTER SWITCH (GANG BAR) = OFF

20. BATTERY BUS = EMER OFF

1. LANDING GEAR = UP

2. FLAPS = UP

WARNING: DO NOT FEATHER SECOND ENGINE PROPLLER IF A NO STARTER ASSIST AIR START IS TO BE CONDUCTED.  AIR STARTS WITH A WINDMILLING PROPELLER WILL RESULT IN LOWER STARTING TEMPERATURES.  REFER TO ABNORMAL PROCEDURES FOR AIR START PROCEDURES.

3. PROP LEVERS = FEATHERED

4. AIRSPEED = 135 KTS

5. GLIDE RATIO = 2.3 NAUTICAL MILES

FOR EACH 1000 FEET OF ALTITUDE, DECREASE 0.2 NAUTICAL MILES FOR EACH 10 KTS HEADWIND.

L DC GEN AND R DC GEN AUUNCIATORS: 

1. INSTRUMENT EMERGENCY LIGHTS = ON IF REQUIRED

2. GENERATOR SWITCHES = RESET, THEN ON

IF EITHER GENERATOR WILL RESET: 

3. OPERATING GENERATOR LOADMETER = MONITOR

IF NEITHER GENERATOR WILL RESET: 

4. NON-ESSENTIAL EQUIPMENT = OFF

5. AUTOPILOT = DISENGAGE

6. BATTERY AMMETER = MONITOR

7. LAND AT THE NEAREST SUITABLE AIRPORT (NO FLAPS AND MANUALLY EXTENDED LANDING GEAR)

[L/R DC GEN]

1. AIRPLANE ATTITUDE = MAINTAIN USING ELEVATOR CONTROL

2. A/P = DISCONNECT (PRESS AND HOLD FULLY...CONTINUE TO HOLD)

3. MANUALLY RETRIM AIRPLANE

4. A/P TRIM DISCONNECT = RELEASE

IF TRIM CONTINUES TO RUN: 

5. A/P TRIM DISCONNECT = PRESS FULLY AND HOLD...CONTINUE TO HOLD

6. PITCH TRIM CIRCUIT BREAKER = PULL (4 DOWN, 3 RIGHT)

7. A/P TRIM DISCONNECT = RELEASE

8. RETRIM AIRPLANE

9. AUTOPILOT = DO NOT ENGAGE

1. A/P TRIM DISCONNECT = DEPRESS TO FIRST DETENT AND HOLD

2. RUDDER BOOST = OFF

IF CONDITION PERSISTS: 

3. YD/AP DISC (ON FLIGHT GUIDANCE PANEL) = PULL DOWN

4. PERFORM NORMAL LANDING

CREW: 

1. OXYGEN MASK(S) = DON

2. HEADSET(S) = DON

3. MIC SELECTOR SWITCH(S) = OXYGEN MASK

4. OXYGEN DURATION = CONFIRM

PASSENGERS: 

5. PASSENGER MANUAL DROPOUT = PULL OUT

6. LANYARD PIN FOR EACH MASK USED = PULL OUT

7. MASK = DON

8. OXYGEN DURATION = CONFIRM

WARNING: THE HIGHEST RECOMMENDED CABIN ALTITUDE FOR SUSTAINED FLIGHT IS 25,000 FEET.

1. OXYGEN MASK(S) = DON

2. HEADSET(S) = DON

3. MIC SELECTOR SWITCHE(S) = OXYGEN MASK

4. PASSENGER MANUAL DROPOUT = PULL OUT

5. DESCEND = AS REQUIRED

6. PASSENGERS = PULL LANYARD PIN

7. RANGE = DETERMINE FOR CRUISE ALT

8. OXYGEN DURATION = CONFIRM

[CABIN ALT HI]

WARNING: THE HIGHEST RECOMMENDED CABIN ALTITUDE FOR SUSTAINED FLIGHT IS 25,000 FEET.

1. BLEED AIR VALVE(S) = ENVIRO OFF

2. OXYGEN (CREW AND PASSENGERS) = AS REQUIRED

3. DESCENT = AS REQUIRED

[CABIN DIFF HI]

1. PASSENGER MANUAL DROP OUT = PULL ON

2. FIRST AID MASK (IF REQUIRED) = DEPLOY MANUALLY

TO ISOLATE OXYGEN SUPPLY TO THE CREW AND FIRST AID MASK: 

3. OXY CONTROL CIRCUIT BREAKER = PULL (3 UP, 5 RIGHT)

[CABIN ALT HI]

[PASS OXYGEN ON]

MONITOR BLEED FAIL ANNUNCIATOR DURING ENG START; EITHER ENGINE WILL EXTINGUISH BOTH ANNUNCIATORS.  ILLUMINATION IN FLIGHT INDICATES POSSIBLE RUPTURE OF BLEED AIR LINE AFT OF ENGINE.

1. BLEED AIR VALVE (AFFECTED ENG) = CLOSE

2. CABIN VSI AND PNEUMATIC PRESS = MONITOR

ESCAPE HATCH HANDLE = PULL

IF A SPIN IS ENTERED INADVERTENTLY: 

1. CONTROL COLUMN = FULL FORWARD

2. FULL RUDDER = OPPOSITE DIRECTION OF SPIN

3. POWER LEVERS = IDLE

4. CONTROLS = NEUTRALIZE WHEN ROTATION STOPS

5. EXECUTE A SMOOTH PULLOUT

PROPELLER FEATHERED OR WINDMILLING: 

1. ECS/TEMP MODE = OFF

2. COCKPIT/CABIN/VENT BLOWER = OFF

3. BLEED AIR VALVE (INOP ENGINE) = ENVIRO OFF

4. AFT BLOWER = OFF

5. RADAR = STANDBY OR OFF

6. FURNISHINGS = OFF

7. POWER LEVER = LOW RPM OR FEATHER

8. PROPELLER LEVER = LOW RPM OR FEATHER

9. CONDITION LEVER = FUEL CUTOFF

10. FIRWALL FUEL VALVE = ON

11. IGNITION AND STARTER SWITCH = ON

12. CONDITION LEVER = LOW IDLE

13. ITT AND N1 (1000 DEGREES MAX) = MONITOR

14. IGNITION AND START SWITCH = OFF (N1 ABOVE 50%)

15. PROP LEVER = AS REQUIRED

16. POWER LEVER = AS REQUIRED

17. GENERATOR = RESET, THEN ON

18. ENG AUTO IGNITION = AS REQUIRED

19. BLEED AIR VALVE = OPEN

20. ENVIRONMENTAL = RESTORE

PROPELLER FEATHERED OR WINDMILLING: 

1. AIRSPEED = 140 KTS MIN

2. ALTITUDE = BELOW 20,000 FEET

3. POWER LEVER = IDLE

4. PROP LEVER = FULL FORWARD

5. CONDITION LEVER = FUEL CUTOFF

6. FIREWALL FUEL VALVE = OPEN

7. ENGINE ANTI-ICE = OFF

8. GENERATOR (INOP ENG) = OFF

9. BLEED AIR VALVE (INOP ENG) = ENVIRO OFF

10. ENGINE N1 = MONITOR (10% MIN)

11. ENG AUTO IGNITION = ARM

12. CONDITION LEVER = LOW IDLE

13. ITT AND N1 (1,000 DEGREES MAX)

14. POWER (AFTER ITT HAS PEAKED) = AS REQUIRED

15. GENERATOR = RESET, THEN ON

16. ENG AUTO IGNITION = AS REQUIRED

17. BLEED AIR VALVE = ON

18. PROP SYNC = AS REQUIRED

19. ELECTRICAL EQUIPMENT = AS REQUIRED

1. ECS MODE = OFF

2. COCKPIT/CABIN BLOWER = AUTO

3. BLEED AIR VALVE (INOP ENG) = ENVIR OFF

4. RADAR = STANDBY OR OFF

5. POWER LEVER = IDLE

6. PROP LEVER = LOW RPM

7. CONDITION LEVER = FUEL CUTOFF

8. FIREWALL FUEL VALVE = OPEN

9. IGNITION AND ENG START = ON

10. CONDITION LEVER (10% N1 OR ABOVE) = LOW IDLE

11. ITT & N1 = MONITOR (1,000 DEGREES MAX)

12. IGNITION AND ENGINE START SWITCH (N1 ABOVE 50%) = OFF

13. PROP LEVER = AS REQUIRED

14. POWER LEVER = AS REQUIRED

15. GENERATOR = RESET, THEN ON

16. ENG AUTO IGNITION SWITCH = AS REQUIRED

17. ELECTRICAL EQUIPMENT = AS REQUIRED

18. COCKPIT/CABIN BLOWER = AUTO

19. BLEED AIR VALVE OPEN

20. ECS MODE = AUTO

SAME AS NORMAL LANDING EXCEPT: 

1. PROPS = FULL FORWARD

2. AIRSPEED = VREF +20 KTS

3. GPWS FLAP OVERRIDE = SELECT

1. APPROACH SPEED (VREF) = CONFIRM

2. PRESSURIZATION = CHECK

3. CABIN SIGN = FSB

4. FUEL BALANCE = CHECK

5. RADAR = AS REQUIRED

6. ENVIRONMENTAL BLEED AIR = LOW

7. SURFACE DEICE = AS REQUIRED

8. FLAPS = APPROACH

9. LANDING GEAR = DOWN

10. EXTERIOR AND INTERIOR LIGHTS = AS REQUIRED

11. PROP LEVER = FULL FOWARD

12. AIRSPEED = VREF +15 KTS

WHEN CERTAIN THAT THERE IS NO POSSIBILITY OF GO-AROUND: 

13. FLAPS = FULL DOWN

14. AIRSPEED = VREF

15. EXECUTE = NORMAL LANDING

1. POWER = MAX ALLOWABLE

2. LANDING GEAR = UP

3. AIRSPEED = INCREASE TO 125 KTS

4. FLAPS = UP

1. PROP GOV TEST CB = PULL

2. PROP BND SOL ANNUNCIATOR = IF EXTINGUISHED:

FLY NORMAL APPROACH, PLAN FOR LONGER LANDING DISTANCES.

3. PROP GND SOL ANNUNCIATOR = IF ILLUMINATED:

FLY SHALLOW, POWER ON APPROACH (1,450 RPM), DO NOT REDUCE POWER UNTIL IN THE FLARE, PLAN FOR LONGER LANDING DISTANCES.

LOW OIL PRESSURE: 

1. OIL PRESSURE VALUES BETWEEN 60-90 ARE UNDESIRABLE AND SHOULD BE TOLERATED ONLY FOR COMPLETION OF THE FLIGHT AT A REDUCED POWER SETTING NOT EXCEEDING 62% TORQUE.

1. ANNUNCIATOR ILLUMINATION INDICATES POSSIBLE METAL CONTAMINATION IN THE ENGINE OIL SUPPLY.  MONITOR ENGINE PARAMETER FOR ABNORMAL INDICATIONS, AND IF PARAMETERS ARE ABNORMAL PRECAUTIONARY SHUTDOWN MADE AT THE PILOT'S DESCRETION.  CORRECT MALFUNTION PRIOR TO NEXT FLIGHT.

1. STANDBY PUMPS = OFF

2. AUX TRANSFER SWITCHES = AUTO

3. FUEL CROSSFEED = L OR R AS REQUIRED

     A. FUEL CROSSFEED = ILLUMINATED

     B. L OR R FUEL PRESS LO = EXTINGUISHED

4. FUEL QUANTITY = MONITOR (FUEL TRANSFER)

IF AUX FUEL FROM INOPERATIVE SIDE IS REQUIRED: 

5. FIREWALL FUEL VALVE (INOP ENG) = OPEN

TO DISCONTINUE CROSSFEED: 

6. FUEL CROSSFEED = OFF

1. AUX TRANSFER = OVERRIDE

2. FUEL QUANTITY = MONITOR (FUEL TRANSFER)

1. FUEL QUANTITY = CHECK

IF LOW QAUNTITY IS CONFIRMED BY FUEL GAGE: 

2. STANDBY FUEL PUMP = ON

3. FUEL QUANTITY = MONITOR

1. GENERATOR = RESET, THEN ON

IF GENERATOR WILL NOT RESET: 

2. GENERATOR = OFF

3. ELECTRICAL LOAD = MONITOR

1. LOADMETER (SAME SIDE) = MONITOR

IF INDICATION IS APPROPRIATE: 

2. BUS SENSE SWITCH = RESET

IF GREATER THAN 100%: 

3. GENERATOR (SAME SIDE) = OFF

4. OPPOSITE LOADMETER = MONITOR

IF GEN TIE WILL NOT RESET: 

5. LOADMETERS = MONITOR

1. GEN TIES SWITCH = MAN CLOSE

IF GEN TIES DO NOT CLOSE: 

2. BUS SENSE SWITCH = RESET

IF GEN TIES DO NOT CLOSE, CENTER BUS WILL BE POWERED ONLY BY THE BATTERY, EVENTUALLY DEPLETING THE BATTERY.

3. CENTER BUS EQUIPMENT = OFF

IF BATTERY IS DEPLETED: 

4. LANDING GEAR = EXTEND MANUALLY

1. VERIFY GENERATOR IS OFFLINE

2. CHECK VOLTAGES ON BUSES

IF A BUS INDICATES A 0 VOLTAGE, A POSSIBLE SHORT MAY EXIST

1. CENTER BUS VOLTAGE = MONITOR

IF CENTER BUS VOLTAGE IS NORMAL (27.5-29 VDC)

2. BUS SENSE SWITCH = RESET

IF CENTER BUS VOLTAGE IS ZERO: 

3. GEN TIES = OPEN

4. LANDING GEAR RELAY CB = PULL

1. NONESSENTIAL CIRCUIT = DO NOT RESET IN FLIGHT

2. ESSENTIAL CIRCUIT: 

     A. CIRCUIT BREAKER = PUSH TO RESET

     B. IF CIRCUIT BREAKER TRIPS AGAIN = DO NOT RESET

IF THE AVIONICS MASTER PWR SWITCH FAILS TO OPERATE IN THE ON POSITION: 

1. AVIONICS MASTER CB = PULL

1. DESCEND TO 5,000 FEET MSL OR BELOW (IF CONDITIONS PERMIT)

2. SINGLE ENGINE RUDDER FORCES MAY EXCEED 150 POUNDS.

IF [HYD FLUID FLOW] ILLUMINATES DURING FLIGHT: 

1. ATTEMPT TO EXTEND LANDING GEAR NORMALLY UPON REACHING DESTINATION

IF LANDING GEAR FAILS TO EXTEND: 

2. FOLLOW LANDING GEAR MANUAL EXTENSION PROCEDURE

1. ELECTRIC HEAT = OFF

2. VENT BLOWER = HI

3. CABIN/COKPIT AIR = PUSH TO INCREASE AIRLFLOW INTO CABIN

IF CONDITION PERSISTS: 

4. CABIN TEMP MODE = MAN HEAT

5. MANUAL TEMP = DECREASE (60 SECONDS)

IF CONDITION PERSISTS FURTHER: 

6. LEFT BLEED AIR VALVE = ENVIRO OFF

IF DUCT OVERTEMP DOES NOT EXTINGUISH AFTER 2 MINUTES: 

7. RIGHT BLEED AIR VALVE = ENVIRO OFF

8. OXYGEN = AS REQUIRED

9. DESCEND = AS REQUIRED

IF THE LANDING GEAR FAILS TO EXTEND: 

1. LANDING GEAR RELAY CIRCUIT BREAKER = PULL

2. LANDING GEAR CONTROL = DOWN

3. ALTERNATE EXTENSION HANDLE = PUMP UP AND DOWN UNTIL 3-GREEN GEAR DOWN LIGHTS ARE ILLUMINATED

LOSS OF PRESSURE WILL RESULT IF HANDLE IS LOWERED TO THE LEVEL OF THE SECURING CLIP DURING DOWNSTROKE.

IF ALL THREE GREEN DOWN ANNUNCIATORS ARE ILLUMINATED: 

4. ALTERNATE EXTENSION HANDLE = STOW

5. LANDING GEAR CONTROLS = DO NOT ACTUATE

IF ONE OR MORE GREEN GEAR DOWN ANNUNCIATORS DO NOT ILLUMINATE AND A DECISION IS MADE TO LAND IN THIS CONDITION: 

6. ALTERNATE EXTENSION HANDLE = CONTINUE PUMPING UNTIL MAX RESISTANCE IS FELT 

7. ALTERNATE EXTENSION HANDLE = DO NOT LOWER LEAVE AT THE TOP OF THE UP STROKE

PRIOR TO LANDING: 

8. ALTERNATE EXTENSION HANDLE = PUMP UNTIL MAX RESISTANCE IS FELT; DO NOT STOW

AFTER LANDING: 

9. ALTERNATE EXTENSION HANDLE...CONTINUE PUMPING WHEN CONDITIONS PERMIT TO MAINTAIN HYDRAULIC PRESSURE UTIL THE GEAR CAN BE MECHANICALLY SECURED.  DO NOT STOW HANDLE.  DO NOT ACTIVATE THE LANDING GEAR CONTROL OR THE LANDING GEAR CIRCUIT BREAKER.  THE LANDING GEAR IS CONSIDERED UNLOCKED UNTIL THE SYSTEM IS CYCLED AND CHECKED WITH THE AIRPLANE ON JACKS.

1. MANUAL PROP DEICE (MAN POS) = MAINTAIN FOR 90 SECONDS

2. LOADMETERS = MONITOR FOR SMALL NEEDLE DEFLECTION (APPROXIMATELY 10%)

1. ENGINE ANTI-ICE ACTUATOR = SELECT OTHER ACTUATOR

IF ENG ICE FAIL ANNUCIATOR DOES NOT EXTINGUISH: 

2. EXIT ICING CONDITIONS

3. ASSUME ENGINE ANTI-ICE IS ON FOR PERFORMANCE CALCULATIONS

1. SURFACE DEICE = ATTEMPT MANUAL CYCLE

IF [WING DEICE] OR [TAIL DEICE] DO NOT ILLUMINATE OR IF BOOT INFLATION CANNOT BE CONFIRMED VISUALLY: 

2. EXIT ICING CONDITIONS

3. REFER TO PERFORMANCE SECTION FOR RECOMMENDED LANDING APPROACH SPEEDS AND PERFORMANCE WITH ICE ON THE AIRPLANE

1. ALTITUDE = MAINTAIN 25,000 FEET OR LESS

2. PRESSURIZATION CONTROLLER = RESET

     A. CRACKED WINDSHIELD = 4 PSI

     B. CRACKED SIDE WINDOW = MINIMUM PRACTICAL

THE FOLLOWING CONDITIONS MAY INDICATE SEVERE IN-FLIGHT ICING: 

1. VISIBLE AT AMBIENT AIR TEMPERATURES BELOW 10 DEGREES

2. DROPLETS SPLASH OR SPATTER AT AMBIENT TEMPS BELOW 0 DEGREES CELCIUS

PROCEDURES FOR EXITING THE SEVERE ICING: 

1. REQUEST PRIORITY HANDLING FROM AIR TRAFFIC CONTROL TO FACILITATE A ROUTE OR AN ALTITUDE CHANGE

2. AVOID ABRUPT AND EXCESSIVE MANEUVERING

3. DO NOT ENGAGE AUTOPILOT

4. IF AUTOPILOT IS ENGAGED, HOLD CONTROL WHEEL FIRMLY, THEN DISENGAGE

5. IF UNCOMMANDED ROLL MOVEMENT - REDUCE THE ANGLE OF ATTACK

6. DO NOT EXTEND FLAPS

7. FLAPS EXTENDED - DO NOT RETRACT UNTIL THE AIRFRAME IS CLEAR OF ICE

8. REPORT WEATHER CONDITIONS TO TRAFFIC CONTROL

MFD FAILURE WILL BE PRESENTED AS A BLANK MFD: 

1. PFD/MFD SWITCH = SELECT PFD

2. ENGINE INFORMATION WILL BE DISPLAYED AT THE TOP OF THE PILOT AND COPILOT PFD.

PILOT PFD FAILURE WILL BE PRESENTED AS A BLANK PFD: 

1. PFD/MFD SWITCH = SELECT MFD

2. PRIMARY FLIGHT INFORMATION WILL BE DISPLAYED ON THE MFD

1. "SINK RATE" = LEVEL WINGS AND REDUCE RATE OF DESCENT UNTIL VISUAL AND VOICE ALERTS CEASE

2. "TERRAIN, TERRAIN" = IMMEDIATELY ADJUST FLIGHT PATH AWAY FROM TERRAIN

3. "DON'T SINK, DON'T SINK" = LEVEL WINGS AND IMMEDIATELY ESTABLISH A POSITIVE RATE OF CLIMB

4A. "TOO LOW GEAR" EXECUTE A GO-AROUND IF PROPER TERRAIN CLEARANCE OR LANDING GEAR POSITION CANNOT BE IMMEDIATELY VERIFIED

4B. "TOO LOW FLAPS" = EXECUTE GO-AROUND IF PROPER TERRAIN CLEARANCE OR FLAP POSITION CANNOT BE IMMEDIATELY VERIFIED

4C. "TOO LOW TERRAIN" = ADJUST FLIGHT PATH TO RECOVER SAFE TERRAIN CLEARANCE UNTIL VISUAL AND VOICE ALERTS CEASE

5. "GLIDESLOPE" IMMEDIATELY CLIMB TO RE-ESTABLISH PROPER GLIDE PATH OR EXECUTE A GO-AROUND

6. "BANK ANGLE, BANK ANGLE" = REDUCE BANK ANGLE (THERE WILL BE NO GND PROX ANNUNCIATOR WITH THE CAUTION)

AMBER [GND PROX] AND "CAUTION TERRAIN, CAUTION TERRAIN" OR CAUTION OBSTACLE, CAUTION OBSTACLE" VOICE ALERT: 

NOTE: IN THE EVENT OF A TERRAIN ALERT, THE MFD WILL AUTOMATICALLY SWITCH TO DISPLAY TERRAIN, IF NOT DISPLAYING TERRAIN, THE PILOT'S PFD ADN THE MFD WILL AUTO RANGE IN 10 MILES.

1. STOP DESCENDING OR CLIMB, AND/OR TURN AS NECESSARY, BASED ON ANALYSIS OF ALL AVAILABLEINSTRUMENTS AND VISUAL OBSERVATIONS, IN ORDER TO CANCEL THE ALERT

2. ADVISE ATC AS NECESSARY

GPWS OR TERR OR TERRAIN FAIL MESSAGE: 

GPWS: ONE OR MORE OF HE BASIC GPWS MODES (1-6) ARE INOPERATIVE AND SOME OR ALL OF THE AURAL ALERTS AND VISUAL WARNINGS AND CAUTIONS MAY NOT BE PROVIDED

TERR: ENHANCED GPWS TAD AND/OR TCF MODE IS INOPERATIVE AND ASSOCIATED AURAL ALERTS ADN VISUAL WARNINGS AND CAUTIONS MAY NOT BE PROVIDED

TERRAIN FAIL: TERRAIN DISPLAY IS INOPERATIVE

DISAGRE OR GPS NOT AVAILABLE FMS MESSAGE: 

1. TERR INHIB = SELECT

NOTE: DURING BACK COURSE LOCALIZER ONLY APPROACHES, SELECTING G/S INHIBIT WILL PREVENT NUSIANCE G/S GPWS ALERTS.

1. CDU CB = CHECK

IN SINGLE FMS INSTALLED OR L FMS/CDU FAILED: 

2. RTU/CDU SWITCH = SELECT RTU

3. RADIOS = TUNE FROM RTU

1. CDU CB = CHECK

2. RTU/CDU SWITCH = SELECT RTU

3. RADIOS = TUNE FROM RTU

1. RTU CB = CHECK

2. RTU/CDU SWITCH = SELECT CDU

3. RADIOS = TUNE FROM CDU

1. AUDIO SWITCH (AFFECTED SIDE) = AUDIO ALTN

ILLUMINATION OF A YELLOW [E] ELEVATOR OR [A] AILERON ANNUNCIATION ON THE PFD'S INDICATES THE AUTOPILOT IS FLYING THE AIRPLANE IN A MISTRIMMED CONDITION: 

NOTE: INTENTIONAL OR AUTOMATIC DISENGAGEMENT OF THE AUTOPILOT WITHOUT RESTRAINING THE CONTROL WHEEL DURING A MISTRIM CONDITION WILL PRODUCE A SIGNIFICANT AIRPLANE RESPONSE IN TEH DIRECTION OF THE MISTRIM FORCE.

IF A MISTRIM INDICATION CONTINUES FOR MORE THAN A FEW SECONDS: 

1. FLIGHT CONTROLS = HOLD FIRMLY (CONTROL FORCES MAY EXCEED 15 POUNDS)

2. A/P = DISENGAGE

3. RETRIM AIRPLANE IF NECESSARY

4. FUEL BALANCE = CHECK (REBALANCE AS NECESSARY)

5. A/P = AS REQUIRED

MISCOMPARE ANNUNCIATORS ARE DISPLAYED ON THE PFD TO ALERT THE PILOT THAT REDUNDANT DATA FROM DUAL SYSTEMS IS NOT AGREEING WITHIN LIMITS.   ATTITUDE, HEADING, ALTITUDE AND AIRSPEED DATA ARE MONITORED FULL TIME.  FULL TIME COMPARATORS ARE PROVIDED FOR ENG N1, N2 AND ITT.

MISCOMPARE ANNUNCIATORS ARE DISPLAYED IN YELLOW, FLASHING FOR 5 SECONDS INITIALLY AND THEN REMAIN ILLUMINATED.  THE ANNUNCIATORS WILL EXTINGUISH WHEN THE MISCOMPARE CONDITION IS REMOVED.

TWO INDEPENDENT SOURCES ARE REQUIRED FOR EACH COMPARATOR FUNCTION ADN TEH COMPARATORS ARE DISABLED IF ADC OR AHRS REVERSION IS SELECTED OR EITHER SIDE HAS FAILED.

IF MISCOMPARE ANNUNCIATORS ARE OBSERVED, THE CREW SHOULD ATTEMPT TO ASCERTAIN WHICH SYSTEM/COMPONENT IS ERRONEOUS.  USE OF THE ELECTRONIC STANDBY INSTRUMENT SYSTEM MAY ASSIST THIS PROCESS.  THE APPLICABLE REVERSIONARY MODE FOR ADC OR AHRS WILL PROVIDE CROSS-SIDE DATA FOR DISPLAY.  NO REVISIONARY CAPABILITY FOR ENGINE MISCOMPARES IS AVAILABLE.

THIS ANNUNCIATION INDICATES A MISMATCH BETWEEN THE PILOT'S AND COPILOT'S DISPLAYED AIR DATA INFORMATION: 

1. ESTABLISH AIRPLANE IN STRAIGHT ADN LEVEL, UNACCELERATED FLIGHT

2. COMPARE INDICATIONS WITH THE ELECTRONIC STANDBY INSTRUMENT SYSTEM

3. DETERMINE IF PILOT'S OR COPILOT'S AIR DATA DISPLAY IS IN ERROR

4. ADC SWITCH = SELECT OPERATIVE ADC

THIS ANNUCIATION INDICATES A MISMATCH BETWEEN THE PILOT'S AND COPILOT'S FLIGHT DIRECTOR DATA, OR PILOT'S AND COPILOT'S NAVIGATION SOURCE DISAGREE: 

1. A/P AND YD = DISENGAGE

2. DETERMINE NAVIGATION DATA MATCHES COUPLE SIDE ANNUNCIATION

3. CONTINUE THE APPRPOACH WITHOUT THE FLIGHT DIRECTOR IF ABLE;  OTHERWISE EXECUTE A MISSED APPROACH

THIS ANNUNCIATION INDICATES A MISMATCH BETWEEN THE PILOT'S AND COPILOT'S GLIDESLOPE DATA: 

1. DETERMINE CORRECT NAV SOURCE AND SELECT AS NECESSARY

2. IF UNABLE TO DETERMINE THE CORRECT SOURCE, PROCEED VISUALLY IF ABLE AND EITHER DESCENT TO LOC ONLY MINIMUMS OR EXECUTE A MISSED APPROACH

THIS ANNUNCIATION INDICATES A MISMATCH BETWEEN THE PILOT'S AND COPILOT'S DISPLAYED HEADING DATA: 

1. ESTABLISH AIRPLANE IN STRAIGHT AND LEVEL, UNACCELERATED FLIGHT

2. COMPARE INDICATIONS WITH THE ELECTRONIC STANDBY INSTRUMENT SYSTEM

3. DETERMINE IF PILOT'S OR COPILOT'S HEADING DISPLAY IS IN ERROR

4. AHRS SWITCH = SELECT OPERATIVE AHRS

THIS ANNUNCIATION INDICATES A MISMATCH BETWEEN THE PILOT'S AND COPILOT'S DISPLAYED LOCALIZER DATA: 

1. DETERMINE THE CORRECT NAV SOURCE AND SELECT AS REQUIRED

2. IF UNABLE TO DETERMINE THE CORRECT SOURCE, PROCEED VISUALLY IF ABLE OR EXECUTE A MISSED APPROACH

THIS ANNUNCIATION INDICATES A MISMATCH BETWEEN THE INDEPENDENT SOURCES OF ENGINE DATA: 

1. THRUST = IF FLIGHT CONTROLS WARRANT, REDUCE AS REQUIRED TO MAINTAIN ENGINE WITHIN LIMITS

THIS ANNUNCIATION INDICATES A MISMATCH BETWEEN THE PILOT'S AND COPILOT'S DISPLAYED ATTITUDE DATA: 

1. ESTABLISH AIRPLANE IN STRAIGHT ADN LEVEL, UNACCELERATED FLIGHT

2. COMPARE INDICATIONS WITH THE ELECTRONIC STANDBY INSTRUMENT SYSTEM

3. DETERMINE PILOT'S OR COPILOT'S ATTITUDE IS IN ERROR

4. AHRS SWITCH = SELECT OPERATIVE AHRS

NO COMPARE ANNUNCIATORS ARE DISPLAYED ON THE PFD WHEN COMPARED PARAMETERS ARE VALID, BUT NO VALID DATA IS BEING RECEIVED FROM A SECOND SOURCE ALLOWING THE COMPARATORS TO FUNCTION.

NO COMPARE ANNUNCIATORS ARE DISPLAYED IN WHITE, FLASH FOR 5 SECONDS INITIALLY AND THEN REMAIN ILLUMINATED.  THEY ARE EXTINGUISHED WHEN THE NO COMPARE CONDITION IS REMOVED.

1. NO IN-FLIGHT ACTION IS REQUIRED

REMEMBER PITCH, HEADING AND ROLL = AHRS

REMEMBER ATTITUDE AND AIRSPEED = ADC

A YELLOW BOXED XTLK FLAG APPEARS ABOVE THE LOCATION OF THE ATT AND IAS COMPARATOR FLAGS ON THE PFD, AND EQIVALENT MFD LOCATION WHEN APPLICABLE, WHEN ANY FLIGHT DISPLAY LOSES CROSSTALK INPUT FROM ANY OTHER PFD OR MFD.  THE YELLOW BOXED XTLK WILL BE REMOVED WHEN COMMUNICATION IS RESTORED.

DISPLAYS THAT HAVE BEEN DESELECTED BY PILOT REVERSION WILL NOT CAUSE THE YELLOW BOXED XLTK FLAG TO COME INTO VIEW.