ka350 pilot checklist pn-73.pdf

PILOT CHECKLIST

BEECHCRAFT SUPER KING AIR350 & 350C

FlightSafetyinternational

Models B300 & B300C

FL-111 THRU FL-382, EXCEPT FL-381; FM-9 THRU FM-11

P/N 130-590031-73DFebruary 2007—Revision 9

Copyright © 2007 Hawker Beechcraft Corporation/FlightSafety International, Inc.All rights reserved. Printed in the United States of America.

INSERT LATEST REVISED PAGES, DESTROY SUPERSEDED PAGES

LIST OF EFFECTIVE PAGES

This document is an abbreviation of the procedures contained in the Pilot’s Operating Handbook and FAA Approved Airplane Flight Manual, P/N 130-590031-71.

Dates of issue for original and changed pages are:

Original.......0 ......FEBRUARY, 1999 Incorporates A6 of the POH/AFMRevision ....1 ........OCTOBER, 2000 Incorporates B reissue of the POH/AFMRevision .....2....SEPTEMBER, 2001 Incorporates B1 revision of the POH/AFMRevision .....3 .................JULY, 2002 Incorporates B2 revision of the POH/AFMRevision .....4 ...........AUGUST, 2003 Incorporates B3–B5 revision of the POH/AFMRevision .....5 ......FEBRUARY, 2004 Incorporates B6 revision of the POH/AFMRevision .....6 ........OCTOBER, 2004 Incorporates B7 revision of the POH/AFMRevision .....7 .....NOVEMBER, 2005 Incorporates B8 revision of the POH/AFMRevision .....8................APRIL, 2006 Incorporates B9 revision of the POH/AFMRevision .....9 ......FEBRUARY, 2007 Incorporates B10 revision of the POH/AFM

TOTAL NUMBER OF PAGES IN THIS PUBLICATION IS 142,CONSISTING OF THE FOLLOWING:

Page *RevisionNo. No.

E-15 – E-16......................................1E-17 – E-22......................................0E-23 – E-24......................................1E-25 – E-28......................................0E-29 .................................................3E-30 .................................................0A-i – A-ii ...........................................0A-1 ...................................................4A-2 ...................................................0A-3 – A-4..........................................9A-5 – A-6..........................................0A-7 ...................................................5A-8 ...................................................0A-9 ...................................................5A-10 – A-12......................................0A-13 .................................................6A-14 .................................................0A-15 .................................................6A-16 – A-18......................................0A-19 .................................................6A-20 .................................................0A-21 .................................................6A-22 – A-28......................................0A-29 .................................................1A-30 .................................................0A-31 .................................................3A-32 .................................................0P-1 – P-5..........................................0P-6 – P-9..........................................1P-10 .................................................0P-11 .................................................1P-12 – P-15......................................0P-16 .................................................1P-17 – P-21......................................0P-22 .................................................1P-23 – P-28......................................0SI-1 – SI-3........................................0ANN-1 – ANN-2 ...............................8

Page *RevisionNo. No.

Title ..................................................9A – B ................................................9N-i ....................................................3N-ii....................................................0N-1 ...................................................6N-2 ...................................................0N-3 – N-4 .........................................6N-5 – N-7 .........................................0N-8 – N-9 .........................................6N-10 .................................................1N-11 – N-14 .....................................9N-15 – N-16 .....................................1N-17 – N-18 .....................................2N-18A – N-18B.................................3N-19 – N-20 .....................................1N-21 .................................................8N-22 .................................................2N-23 .................................................3N-24 .................................................0N-25 .................................................3N-26 .................................................1N-27 – N-28 .....................................9N-29 .................................................6N-30 .................................................4N-31 .................................................0N-32 .................................................1N-33 – N-35 .....................................0N-36 .................................................1E-i.....................................................8E-ii ....................................................0E-1 ...................................................1E-2 – E-4..........................................0E-5 – E-6..........................................9E-7 ...................................................1E-8 – E-10........................................0E-11 – E-12......................................1E-13 .................................................9E-14 .................................................6

FEBRUARY 2007 A P/N 130-590031-73D9

FEBRUARY 2007BP/N 130-590031-73D9


This document is an abbreviation of the checklists and procedurescontained in Section III (EMERGENCY PROCEDURES), Section IIIA(ABNORMAL PROCEDURES) and Section IV (NORMALPROCEDURES) of the Pilot’s Operating Handbook and FAA ApprovedAirplane Flight Manual (POH/AFM) for the Model B300/B300C (P/N 130-590031-71). When Revisions to Sections III, IIIA and IV of the POH/AFMare received, applicable Revisions to this Abbreviated Checklist will beprovided and must be updated accordingly. Since this is an AbbreviatedChecklist, most explanatory items, notes and cautions have been omittedfor brevity, although applicable warnings have not. Consequently, usersof this Abbreviated Checklist must be familiar with and operate theairplane in accordance with the official applicable POH/AFM.

*Zero in this column indicates an original page.Revision 1 is a complete reprint.

Raytheon Aircraft Company, which has been renamedHawker Beechcraft Corporation, is now owned byHawker Beechcraft, Inc. Neither Hawker Beechcraft,Inc. nor Hawker Beechcraft Corporation are affiliatedany longer with Raytheon Company. Any Raytheonmarks contained in this document are owned byRaytheon Company and are employed pursuant to alimited license granted by Raytheon Company.

NORMAL PROCEDURES

AIRSPEEDS FOR SAFE OPERATION .................................................N-1

PROCEDURES BY FLIGHT PHASE .....................................................N-3

PREFLIGHT INSPECTION.....................................................................N-3

BEFORE ENGINE STARTING...............................................................N-8

ENGINE STARTING (BATTERY).........................................................N-10

ENGINE STARTING(EXTERNAL POWER) ........................SEE EXPANDED PROCEDURES

HOT START OR HUNG START...........................................................N-11

NO LIGHT START................................................................................N-11

ENGINE CLEARING.............................................................................N-11

BEFORE TAXI ......................................................................................N-12

BEFORE TAKEOFF (RUNUP) .............................................................N-12

BEFORE TAKEOFF (FINAL ITEMS)....................................................N-13

TAKEOFF .............................................................................................N-14

ROLLING TAKEOFF ............................................................................N-14

CLIMB...................................................................................................N-14

CRUISE ................................................................................................N-15

DESCENT.............................................................................................N-17

BEFORE LANDING..............................................................................N-18

NORMAL LANDING .............................................................................N-18

STEEP APPROACH LANDING .........................................................N-18A

MAXIMUM REVERSE THRUST LANDING..........................................N-19

BALKED LANDING...............................................................................N-19

AFTER LANDING.................................................................................N-19

SHUTDOWN/SECURING.....................................................................N-20

EXPANDED PROCEDURES ...............................................................N-21

AIRSTAIR DOOR CIRCUITRY CHECK (B300) ...................................N-21

AIRSTAIR DOOR CIRCUITRY CHECK (B300C).................................N-21

OXYGEN SYSTEM PREFLIGHT INSPECTION ..................................N-21

OXYGEN DURATION...........................................................................N-22

LOCKING THE AIRSTAIR DOOR (B300) ............................................N-24

LOCKING THE CARGO DOOR (B300C) .............................................N-24

LOCKING THE AIRSTAIR DOOR (B300C)..........................................N-24

FUEL SYSTEM.....................................................................................N-24

ENGINE STARTING (EXTERNAL POWER)........................................N-25

ELECTRICAL SYSTEM........................................................................N-26

INVERTERS .........................................................................................N-27

ENVIRONMENTAL SYSTEM...............................................................N-28

PRESSURIZATION ..............................................................................N-29

JULY 2002N-iP/N 130-590031-73D3


AUTOPILOT .........................................................................................N-29

YAW DAMP ..........................................................................................N-30

ELECTRIC PITCH TRIM ......................................................................N-30

OVERSPEED GOVERNORS/RUDDER BOOST.................................N-30

LOW PITCH STOPS AND PRIMARY GOVERNORS ..........................N-31

AUTOFEATHER...................................................................................N-31

INSTRUMENT VACUUM AND DEICE PRESSURE ............................N-32

ENGINE ANTI-ICE................................................................................N-32

ICE PROTECTION EQUIPMENT (IF REQUIRED) ..............................N-33

OTHER PROCEDURES.......................................................................N-35

SIMULATING ONE-ENGINE-INOPERATIVE (ZERO THRUST)..........N-35

PRACTICE DEMONSTRATION OF VMCA............................................N-35

PRACTICE LANDING GEAR MANUAL EXTENSION..........................N-36

LANDING GEAR RETRACTION AFTER PRACTICE MANUALEXTENSION.......................................................................................N-36

PILOT CHECKLIST–BEECH MODEL B300/B300C

FEBRUARY 1999 N-ii P/N 130-590031-73D

All airspeeds quoted in this section are indicated airspeeds (IAS) andassume zero instrument error.

Closed [BRACKETS] in this section denote annunciator(s).

Expanded procedures are noted by reference to a page number after the command.

AIRSPEEDS FOR SAFE OPERATION

(15,000 LBS (6804 KG))

Maximum Demonstrated Crosswind Component...........................20 Knots

Two-Engine Best-Angle-of-Climb (VX)..........................................125 Knots

Two-Engine Best-Rate-of-Climb (VY) ...........................................140 Knots

Cruise Climb:

Sea Level to 10,000 Ft...........................................................170 Knots

10,000 to 15,000 Ft................................................................160 Knots

15,000 to 20,000 Ft................................................................150 Knots

20,000 to 25,000 Ft................................................................140 Knots

25,000 to 30,000 Ft................................................................130 Knots

30,000 to 35,000 Ft................................................................120 Knots

Maneuvering Speed (VA)..............................................................184 Knots

Turbulent Air Penetration .............................................................170 Knots

Maximum Airspeed for Effective Windshield Anti-icing ......................226 Knots

Intentional One-Engine-lnoperative Speed (VSSE) .......................110 Knots

Air Minimum Control Speed (VMCA):

Flaps Up ..................................................................................94 Knots

Flaps Approach .......................................................................93 Knots

OCTOBER 2004N-1P/N 130-590031-73D6


PILOT NOTES


FEBRUARY 1999 N-2 P/N 130-590031-73D

PROCEDURES BY FLIGHT PHASE

PREFLIGHT INSPECTION

NOTE

After the first flight of the day, the Preflight Inspectionmay be omitted except for items marked with a “+”(Fuel Tank Caps and Engine Oil Quantity/Filler Capneed not be checked unless system(s) were serviced.)

Cabin/Cockpit

1. Monogram Electric Toilet Knife Valve (if installed ) ..................OPEN

+2. Baggage ..............................................................................SECURE

3. Aft Exit Sign ........................................................................ON-TESTCheck sign illumination, then OFF-RESET

4. Forward Exit Sign................................................................ON-TESTCheck sign illumination, then OFF-RESET

5. Emergency Exits ....................................SECURE AND UNLOCKED

+6. Control Locks ......................................................................REMOVE

+7. Parking Brake ..............................................................................SET

8. Landing Gear Control ..............................................................DOWN

9. ELT (cockpit installations)...........................................................ARM

10. Condition Levers ........................................................FUEL CUTOFF

11. Trim Controls:

a. Elevator ............................................SET TO 2 UNITS NOSE UP

b. Rudder and Aileron.........................................SET TO “0” UNITS

12. Battery Bus ..............................................................................NORM

13. Voltmeter:

a. BAT Position ...............................................23 VOLTS MINIMUM

b. All Other Positions..........................................................0 VOLTS

+14. Battery ...........................................................................................ON

15. Landing Gear...............................[L], [R], & [NOSE] - ILLUMINATED

+16. Fuel Quantity.........................................CHECK MAIN & AUXILIARY

17. Voltmeter:

a. TPL FED .....................................................22 VOLTS MINIMUM

b. R GEN and L GEN .........................................................0 VOLTS

c. CTR.............................................................23 VOLTS MINIMUM

d. EXT PWR.......................................................................0 VOLTS

18. Gen Ties ........................................................................MAN CLOSE

19. Voltmeter .......................R GEN AND L GEN - 23 VOLTS MINIMUM

20. Flaps (if desired) ....................................................................CHECK

a. Move to and verify they stop at TAKEOFF AND APPROACH

b. Move to and verify they stop at DOWN

OCTOBER 2004N-3P/N 130-590031-73D6


Continued on Next Page

PREFLIGHT INSPECTION (Cont)

21. Airstair Door (B300) Circuitry (N-21) ......................................CHECK

+22. Battery (B300) .............................................................................OFF

23. Airstair Door (B300C) Circuitry (N-21) ...................................CHECK

+24. Battery (B300C)...........................................................................OFF

25. Oxygen System Preflight Inspection (N-21)....................COMPLETE

Left Wing and Nacelle

1. Cabin Door Seal, Step Extension Cable,Light Wire, Damper, and Handrails ........................................CHECK

2. Left Side Windows .................................................................CHECK

3. Flaps (condition, asymmetry protection, and flap tracks) .............CHECK

4. Aileron and Tab......................................................................CHECK

5. Static Wicks (aileron and winglet) ..........................................CHECK

6. Siphon Break Vent..................................................................CLEAR

7. Lights......................................................................................CHECK

+8. Main Fuel Tank Cap ............................................................SECURE

9. Stall Warning Vane ................................................................CHECK

+10. Tie-down .............................................................................REMOVE

11. Flush Outboard Fuel Drain ......................................................DRAIN

12. Outboard Deice Boot and Stall Strip ......................................CHECK

13. Wing Panels.........................................................................SECURE

14. Leading-Edge Fuel Tank and Gravity-Line Drains ..................DRAIN

15. Inverter Cooling Louvers.........................................................CLEAR

16. Flush Fuel Vent and Heated Fuel Vent...................................CLEAR

+17. Landing Gear (doors, tires, strut, wheel well).........................CHECK

18. Engine Oil Vent.......................................................................CLEAR

19. Brake Line and Brake Deice Plumbing (if installed) ...............CHECK

20. Torque Knee Assembly and Safety Switch ............................CHECK

21. Brakes ....................................................................................CHECK

22. Fire Extinguisher Pressure.....................................................CHECK

FIRE EXTINGUISHER PRESSURE VS. TEMPERATURE

°F -40 -20 0 20 40 60 80 100 120°C -40 -29 -18 -7 4 16 27 38 49

PSI 190 220 250 290 340 390 455 525 605Range to to to to to to to to to

240 275 315 365 420 480 550 635 730

+23. Chocks ................................................................................REMOVE

24. Fuel Strainer and Fuel Filter Drains.........................................DRAIN

25. Collector Drain ........................................................................CLEAR


OCTOBER 2004 N-4 P/N 130-590031-73D6


26. Ice Vane and Oil Radiator Exhaust.........................................CLEAR

27. Ice Light..................................................................................CHECK

+28. Engine Oil ..................................CHECK QUANTITY, CAP SECURE

29. Cowling Air Exhaust................................................................CLEAR

30. Engine Cowling, Doors, and Panels (left side) ....................SECURE

31. Exhaust Stack and Fairing(if installed) (left side) ....................................CHECK FOR CRACKS

32. Top Cowling Camlocks (Left Side) ......................................SECURE

+33. Propeller..............................................................CHECK & ROTATE

34. Forward Air Intakes on Top Cowling.......................................CLEAR

35. Engine and Oil Radiator Air Intakes .......................................CHECK

36. Top Cowling Camlocks (right side) ......................................SECURE

37. Exhaust Stack and Fairing(if installed) (right side) ..................................CHECK FOR CRACKS

38. Swing Check Valve Exhaust...................................................CLEAR

39. Generator Air Intake ...............................................................CLEAR

40. Engine Cowling, Doors, Panels, and VGs (right side) .........SECURE

+41. Auxiliary Fuel Tank Cap.......................................................SECURE

42. Hydraulic Gear Service Door ...............................................SECURE

43. Inboard Deice Boot ................................................................CHECK

44. Heat Exchanger Air Intake and Exhaust.................................CLEAR

45. Hydraulic Gear Overfill and Vent Lines...................................CLEAR

46. Auxiliary Fuel Tank Drain ........................................................DRAIN

47. Lower Antennas and Panels................................................SECURE

Nose

1. OAT Probe/Relief Tube Vent .................................................CHECK

2. Brake Reservoir Vent..............................................................CLEAR

3. Left Avionics Access Panel..................................................SECURE

4. Air Conditioner Condenser Exhaust Duct ...............................CLEAR

5. Windshield and Wipers ..........................................................CHECK

6. Radome Condition .................................................................CHECK

7. Pitot Masts ..............................................................................CLEAR

8. Landing and Taxi Lights .........................................................CHECK

+9. Nose Gear (shimmy damper, stop block,torque knee, strut, tire) ...........................................................CHECK

+10. Chocks ................................................................................REMOVE

11. Nose Gear Doors and Wheel Well .........................................CHECK

12. Air Conditioner Condenser Intake Duct ..................................CLEAR

13. Right Avionics Access Panel ...............................................SECURE

FEBRUARY 1999N-5P/N 130-590031-73D



Right Wing and Nacelle

1. Ejector Exhaust.......................................................................CLEAR

2. Auxiliary Fuel Tank Drain ........................................................DRAIN

3. Battery Box Drain....................................................................CLEAR

4. Battery Air Inlet(Airplanes Prior To FL-215 and FM-10)..................................CLEAR

5. Lower Panels .......................................................................SECURE

6. Heat Exchanger Air Intake and Exhaust.................................CLEAR

7. Inboard Deice Boot ................................................................CHECK

8. Battery Exhaust(Airplanes Prior To FL-215 and FM-10)..................................CLEAR

9. Battery Access Panel...........................................................SECURE

+10. Auxiliary Fuel Tank Cap.......................................................SECURE

+11. Engine Oil ..................................CHECK QUANTITY, CAP SECURE

12. Cowling Air Exhaust................................................................CLEAR

13. Engine Cowling, Doors, and Panels (left side) ....................SECURE

14. Collector Drain ........................................................................CLEAR

15. Exhaust Stack and Fairing(if installed) (left side) ....................................CHECK FOR CRACKS

16. Top Cowling Camlocks (left side) ........................................SECURE

+17. Propeller.........................................................CHECK AND ROTATE

18. Forward Air Intakes on Top Cowling.......................................CLEAR

19. Engine and Oil Radiator Air Intakes .......................................CHECK

20. Top Cowling Camlocks (right side) ......................................SECURE

21. Exhaust Stack and Fairing(if installed) (right side) ..................................CHECK FOR CRACKS

22. Swing Check Valve Exhaust...................................................CLEAR

23. Generator Air Intake ...............................................................CLEAR

24. Engine Cowling, Doors, and Panels (right side) ..................SECURE

25. Ice Light..................................................................................CHECK

26. Oil Radiator and Ice Vane Exhaust.........................................CLEAR

27. Fuel Filter and Fuel Strainer Drains.........................................DRAIN

+28. Landing Gear (doors, tires, strut, wheel well) ........................CHECK

29. Fire Extinguisher Pressure.....................................................CHECK

30. Engine Oil Vent.......................................................................CLEAR

31. Brake Line and Brake Deice Plumbing (if installed) ...............CHECK

32. Torque Knee Assembly and Safety Switch ............................CHECK

33. Brakes ....................................................................................CHECK

+34. Chocks ................................................................................REMOVE

35. Heated Fuel Vent and Flush Fuel Vent...................................CLEAR

36. Inverter Cooling Louvers.........................................................CLEAR

37. Gravity-Line and Leading-Edge Fuel Tank Drains ..................DRAIN


FEBRUARY 1999 N-6 P/N 130-590031-73D

FEBRUARY 1999N-7P/N 130-590031-73D



38. External Power Door............................................................SECURE

39. Outboard Deice Boot and Stall Strip ......................................CHECK

+40. Tie-down .............................................................................REMOVE

41. Flush Outboard Fuel Drain ......................................................DRAIN

42. Wing Panels.........................................................................SECURE

+43. Main Fuel Tank Cap ............................................................SECURE

44. Lights......................................................................................CHECK

45. Static Wicks (winglet and aileron) ..........................................CHECK

46. Siphon Break Vent .................................................................CHECK

47. Aileron ....................................................................................CHECK

48. Flaps (condition, asymmetry protection, flap tracks,limit switches, position transmitter) ........................................CHECK

49. Right Side Windows ...............................................................CHECK

Right Aft Fuselage

1. Lower Antennas and Beacon .................................................CHECK

2. Oxygen Service Access Door ..............................................SECURE

3. Static Ports .............................................................................CLEAR

4. ELT (aft fuselage installations) .................................................AUTO

5. ELT Antenna ..........................................................................CHECK

6. Aft Compartment Bottom Access Door................................SECURE

+7. Tie-down .............................................................................REMOVE

8. Ventral Fin Drain Holes...........................................................CLEAR

9. Cabin Air Exhaust ...................................................................CLEAR

10. Access Panel .......................................................................SECURE

Tail

1. Ventral Fin and Static Wick ....................................................CHECK

2. VOR Antennas (right and left) ................................................CHECK

3. Rudder, Rudder Tab, Stinger and Static Wicks .....................CHECK

4. Horizontal Stabilizer, Boots, andStatic Wicks (right and left) ....................................................CHECK

5. Elevator, Tab, and Static Wicks .............................................CHECK

6. Tabs In Neutral Position ........................................................VERIFY

7. Position Light, Tail Floodlights (if installed)(left and right) .........................................................................CHECK

Left Aft Fuselage

1. Access Panels .....................................................................SECURE

2. Static Ports .............................................................................CLEAR

3. Oxygen Overpressure Discharge andAft Compartment Drain Tubes ................................................CLEAR

4. Relief Tube .............................................................................CLEAR

BEFORE ENGINE STARTING

NOTE

Items marked with an “*” may be omitted at pilot’sdiscretion after the first flight of each day.

1. Weight, CG, Performance, and V-Speeds ........................CHECKED

Only a crew member or properly trained groundpersonnel should close and lock the airstair door andcargo door (if installed).

2. Airstair Door (B300) (N-24) ..................................................LOCKED

3. Cargo Door (B300C) (N-24).................................................LOCKED

4. Airstair Door (B300C) (N-24) ...............................................LOCKED

5. Load and Baggage ..........................................CONFlRM SECURED

6. Passenger Briefing..........................................................COMPLETE

7. Seats and Tables ..........................................................POSlTlONED

a. All Seats – Seat backs upright; Headrests fully extended

b. Lateral-tracking seats – Outboard position

c. Tables – Stowed

8. Pilot Seats and Rudder Pedals........................................ADJUSTED

9. Seat Belts and Shoulder Harnesses................................FASTENED

10. Parking Brake ............................................................CONFIRM SET

11. Control Locks..................................................CONFIRM REMOVED

*12. Oxygen System Preflight Inspection (N-21)...........................................CONFlRM COMPLETE

13. Fuel Panel ..............................................................................CHECK

a. Standby Pumps .....................................................................OFF

b. Crossfeed ..............................................................................OFF

c. Aux Transfer Switches........................................................AUTO

d. Circuit Breakers.........................................................................IN

14. Pilot’s Instrument Panel and Subpanel ..................................CHECK

a. Pilot’s Gyro ..........................................................SLAVED (OUT)

*b. Standby Horizon (if installed)...............................................TEST

c. Battery Bus ......................................................CONFIRM NORM

d. Engine Anti-Ice...........................................................ON & MAIN

e. Landing Gear Relay Circuit Breaker .........................................IN

f. Landing Gear Control ........................................................DOWN

*g. Clock (control wheel) ............................................CHECK & SET

15. Power Console and Pedestal.................................................CHECK

a. Power Levers ........................................................................lDLE

b. Prop Levers ......................................................FULL FORWARD

WARNING


OCTOBER 2004 N-8 P/N 130-590031-73D6

BEFORE ENGINE STARTING (Cont)

c. Condition Levers ..................................................FUEL CUTOFFd. Oxygen Controls:

1) Passenger Manual Drop-Out .........CONFIRM PUSHED OFF2) System Ready .................................................CONFIRM ON

e. EFIS Power (if installed) ........................................................OFFf. Landing Gear Alternate Extension Handle....................STOWED

16. Copilot’s Subpanel and Instrument Panel ..............................CHECKa. Window Defog .......................................................................OFFb. Vent Blower ........................................................................AUTOc. Cabin Temp Mode.................................................................OFFd. Environmental Bleed Air .......................................................LOWe. Bleed Air Valves ........................................................ENVIR OFFf. Aft Blower ..............................................................................OFF

g. Electric Heat ..........................................................................OFFh. Aft Heat ................................................................AS REQUIREDi. Copilot’s Gyro ......................................................SLAVED (OUT)

*j. Clock (control wheel) ............................................CHECK & SET

17. Right Panel Circuit Breakers ...........................................................IN

*18. Pilot’s Static Air Source .......................................................NORMAL

19. Battery ...........................................................................................ON

*20. Annunciators..............................................................................TEST

*21. Fuel System (N-24) ................................................................CHECK

22. Fuel Quantity (Main and Auxiliary) .........................................CHECK

23. Pilot’s Subpanel .....................................................................CHECK

*a. Landing Gear Control Lights................................................TEST

*b. Hydraulic Fluid Sensor ........................................................TEST[HYD FLUID LO ] – ILLUMINATED

c. Beacon ....................................................................................ON

*24. Copilot’s Subpanel .................................................................CHECK

*a. Cabin Altitude Warning........................................................TEST[CABIN ALT Hl] &

[CABIN ALTITUDE] – ILLUMINATED(note aural warning)

*b. Cabin Differential Warning...................................................TEST[CABIN DIFF Hl] – ILLUMINATED

*c. Overspeed Warning.............................................................TEST(note aural warning)

*d. Stall and Landing Gear Warning .........................................TEST(note aural warning)

*e. Fire Detector and Extinguisher ............................................TESTLeft & Right [ENG FIRE] – ILLUMINATED

Left & Right [EXTINGUISHER PUSH] & [DISCHARGED] – ILLUMINATED

OCTOBER 2004N-9P/N 130-590031-73D6


ENGINE STARTING (BATTERY)

1. Gen Ties (for night operation)........................................MAN CLOSE

2. Propeller Area.........................................................................CLEAR

3. Right Ignition and Engine Start......................................................ON[R IGNITION ON] – ILLUMINATED

[R FUEL PRES LO] – EXTINGUISHED

4. Right Condition Lever (after 12% N1, minimum)................LOW IDLE

5. Right ITT and N1 ................................................................MONITOR(1000° C maximum)

6. Right Oil Pressure ..................................................................CHECK

7. Right Ignition and Engine Start (at 50% N1 or above) .................OFF

8. Right Condition Lever .......................................................HIGH IDLE

9. Right Generator ....................................................RESET, THEN ON[R DC GEN], [L GEN TIE OPEN]

& [R GEN TIE OPEN] – EXTINGUISHED

10. Battery .................................................................................CHARGE(until loadmeter reads

approximately 50% or less)

11. Left Ignition and Engine Start ........................................................ON[L IGNITION ON] – ILLUMINATED

[L FUEL PRES LO] – EXTINGUISHED

12. Left Condition Lever (after 12% N1, minimum) ..................LOW IDLE

13. Left ITT and N1 ..................................................................MONITOR(1000° C maximum)

14. Left Oil Pressure ....................................................................CHECK

15. Left Ignition and Engine Start (at 50% N1 or above)....................OFF

16. Right Condition Lever..................................REDUCE TO LOW IDLE

17. Left and Right Prop RPM...........................................1050 MINIMUM

18. [L PROP PITCH] and [R PROP PITCH] .....................ILLUMINATED

19. Voltmeter..................................................................................L GEN(voltmeter –27.5 TO 29.0 volts)

20. Left Generator ......................................................RESET, THEN ON[L DC GEN] – EXTINGUISHED

21. Right Generator ....................................................RESET, THEN ON[L GEN TIE OPEN] & [R GEN TIE OPEN] – REMAIN EXTINGUISHED WITH SWITCH

IN THE RESET POSITION


OCTOBER 2000 N-10 P/N 130-590031-73D1

ENGINE STARTING (EXTERNAL POWER)

Expanded Procedure on Page N-25.

HOT START OR HUNG START

1. Condition Lever..........................................................FUEL CUTOFF

2. Ignition and Engine Start .........................................STARTER ONLY

3. ITT Below 400°C .................IGNITION AND ENGINE START – OFF

4. Do not attempt another start until the cause of the hot start or hungstart has been corrected.

NO LIGHT START

If no ITT rise is observed within 10 seconds after moving the ConditionLever to LOW IDLE:


2. Ignition and Engine Start .............................................................OFF

3. Allow 5 minutes for fuel to drain and starter to cool, then followENGINE CLEARING Procedure.

ENGINE CLEARING


2. Ignition and Engine Start .........................................STARTER ONLY(for a maximum of 30 seconds)

3. Ignition and Engine Start .............................................................OFF

4. Allow 5 minutes before attempting another start.

FEBRUARY 2007N-11P/N 130-590031-73D9


BEFORE TAXI

NOTE


*1. EIectrical System (N-26) ........................................................CHECK

2. Inverters (N-27) ............................................................CHECK & ON

3. Avionics Master .............................................................................ON

4. Master Panel and Cockpit Lights ...............................AS REQUIRED

5. Mic Switches .......................................................................NORMAL

6. Cabin Lights ...............................................................AS REQUIRED

7. Furnishings ................................................................AS REQUIRED

8. Cabin Sign:a. Standard Configuration...........................................NO SMK/FSBb. No Smoking Configuration.....................................................FSB

9. Standby Horizon (if installed) ........................................................ON

10. Prop Sync......................................................................................ON

11. Exterior Lights ............................................................AS REQUIRED

12. EFIS Power (if installed)................................................................ON

13. Environmental System Controls (N-28) .......................................SET

14. Flight and Engine Instruments ...............................................CHECKa. Altimeters ................................................................................SETb. Standby Horizon (if installed) .........................................UNCAGE

15. Flaps ..............................................................................................UP

16. Flight Controls...................................CHECK FOR FULL FREEDOMOF MOVEMENT AND PROPER

DIRECTION OF TRAVEL

17. Brakes ...............................................................RELEASE & CHECK

BEFORE TAKEOFF (RUNUP)

NOTE


1. Avionics and Radar ................................................................CHECK

2. Pressurization (N-29)...................CHECK AS REQUIRED AND SET

3. Autopilot (N-29) ......................................................................CHECK

*4. Yaw Damp (N-30) ..................................................................CHECK

*5. EIectric Pitch Trim (N-30 ........................................................CHECK

6. Trim Tabs.....................................................................................SET

7. Engine Controls Friction Locks ....................................................SET

8. Flaps......................................................................CHECK AND SET

*9. Overspeed Governors and Rudder Boost (N-30)...................CHECK

*10. Low Pitch Stops and Primary Governors (N-31) ....................CHECK

*11. Autofeather (N-31) .................................................................CHECK


FEBRUARY 2007 N-12 P/N 130-590031-73D9

BEFORE TAKEOFF (RUNUP) (Cont)

12. Autofeather .................................................................................ARM[AUTOFTHER OFF] – EXTINGUISHED

13. Manual Propeller Feathering..................................................CHECK

*14. Instrument Vacuum and Deice Pressure (N-32) ....................CHECK

*15. Engine Anti-ice (N-32)............................................................CHECK

16. Ice Protection Equipment (if required) (N-33) ........................CHECK

17. Fuel Quantity, Flight, and Engine Instruments .......................CHECK

18. V1, VR, V2, Static Take-Off Power......................................CONFIRM

BEFORE TAKEOFF (FINAL ITEMS)

1. Engine Auto Ignition ................................................ARM (if required)[L IGNITION ON] & [R IGNITION ON] – ILLUMINATED if armed

2. Engine Anti-ice...........................................................AS REQUIRED[L ENG ANTI-ICE] & [R ENG ANTI-ICE] – ILLUMINATED, if ON

3. Exterior Lights ............................................................AS REQUIRED

4. Ice Protection .............................................................AS REQUIREDa. Windshield Anti-ice................................NORMAL/HI (if required)b. Prop Deice.......................................................AUTO (if required)c. Left and Right Fuel Vent Heat .................................................ONd. Stall Warning Heat ..................................................................ONe. Left and Right Pitot Heat .........................................................ON

5. Transponder.................................................................................ALT

6. Prop Levers ..........................................CONFIRM FULL FORWARD

7. Trim............................................................................CONFIRM SET

8. Flaps ..........................................................................CONFIRM SET

9. Environmental Bleed Air ..............................................................SET

a. OAT above 10°C ..................................................................LOW

b. OAT at or below 10°C ...................................................NORMAL

10. Bleed Air Valves.........................................................AS REQUIRED

11. Electric Heat ................................................................................OFF[ELEC HEAT ON] – EXTINGUISHED

12. Aft Blower...................................................................AS REQUIRED

13. Interior Lights .............................................................AS REQUIRED

14. Generator Load ......................................................................CHECK

a. When OAT is greater than 10°C:

1) A/C ON: Loadmeters must be 30% or less

2) A/C OFF: Loadmeters must be 50% or less

15. Battery Ammeter (Airplanes FL-215 thru FL-382,except FL-381; FM-10 and FM-11)...............CHECK (charge current

10 amps or less if required)

16. Annunciators ................................................OFF OR CONSIDERED

FEBRUARY 2007N-13P/N 130-590031-73D9


TAKEOFF

Do not cycle boots during takeoff.

1. Brakes.......................................................................................HOLD

2. Power Levers.................................SET STATIC TAKEOFF POWER(observe ITT limits)

3. Autofeather Annunciators ...........................................ILLUMINATED

4. Brakes ................................................................................RELEASE

5. VR .............................................ROTATE TO APPROXIMATELY 10°

6. Landing Gear (when positive climb established) .......................... UP

7. Airspeed .................MAINTAIN V35 UNTIL CLEAR OF OBSTACLES

8. Flaps (at 125 knots, minimum) ......................................................UP

ROLLING TAKEOFF

1. Brakes ................................................................................RELEASE

2. Power Levers.................................SET STATIC TAKEOFF POWER(within 10 seconds of brake release;

observe ITT limits)

3. Autofeather Annunciators ...........................................ILLUMINATED

4. VR .............................................ROTATE TO APPROXIMATELY 10°

5. Landing Gear (when positive climb established) ...........................UP

6. Airspeed .................MAINTAIN V35 UNTIL CLEAR OF OBSTACLES


CLIMB

1. Bleed Air Valves .......................................................................OPEN

2. Environmental Bleed Air ............................................AS REQUIRED

3. Yaw Damp.....................................................................................ON

4. Climb Power ................................................................................SET

5. Props ...................................................1600 RPM, OR AS DESIRED

6. Windshield Anti-Ice..............................................................NORMAL

7. Engine Instruments............................................................MONITOR

8. Cabin Sign .................................................................AS REQUIRED

9. Pressurization ........................................................................CHECK

10. Lights .........................................................................AS REQUIRED

WARNING


FEBRUARY 2007 N-14 P/N 130-590031-73D9

CRUISE

Do not lift Power Levers in flight

1. Cruise Power..........................................SET PER CRUISE POWERTABLES OR GRAPHS

2. Autofeather ..................................................................................OFF


4. Engine Instruments............................................................MONITOR

5. Fuel Gages ........................................................................MONITOR(ensure that fuel is being

transferred from auxiliary tanks)

Icing Conditions

Due to distortion of the wing airfoil, an accumulation of oneinch of ice on the leading edges can cause a loss in rate ofclimb of 500 FPM, a cruise speed reduction of up to 75knots TAS, as well as a significant buffet and stall speedincrease (up to 15 knots IAS). Even after cycling the deicingboots, the ice accumulation remaining on the boots andunprotected areas of the airplane can cause largeperformance losses. For the same reason, the aural stallwarning system may not be accurate and should not berelied upon. However, with ice accumulation on the airplane,significant aerodynamic buffet will occur in advance of thestall. Maintain a comfortable margin of airspeed above thenormal stall airspeed. In order to minimize ice accumulationon unprotected surfaces of the wing, maintain a minimum of140 knots during operations in sustained icing conditions. Inthe event of windshield icing, reduce airspeed to 226 knotsor below. Prior to a landing approach, cycle the deicingboots to shed any accumulated ice.

1. Engine Ice Protection

When visible moisture is encountered at + 5° C and below, or:

At night when freedom from visible moisture is not assured at +5° C and below(operation of strobe lights will sometimes show ice crystals not normally visible).

a. Engine Anti-ice ........................................................................ON[L ENG ANTI-ICE] &

[R ENG ANTI-ICE] – ILLUMINATEDb. Check for proper operation by noting torque drop.

If in doubt, actuate the Engine Anti-ice System. Engineicing can occur even though no surface icing is present. Iffreedom from visible moisture can not be assured, engineice protection should be activated. Visible moisture ismoisture in any form; clouds, ice crystals, snow, rain, sleet,hail or any combination of these.

WARNING

WARNING

WARNING

OCTOBER 2000N-15P/N 130-590031-73D1


CRUISE (Cont)

2. Engine Auto-lgnition....................................................................ARM

3. Prop Deice ................................................................................AUTO

a. The system may be operated continuously in flight, and willfunction automatically until the switch is turned off.

b. Relieve propeller imbalance due to ice by increasing rpm brieflyand returning to the desired setting. Repeat as necessary.

4. Surface Deice

All components of the surface deice system must bemonitored during icing flight to ensure the system isfunctioning normally. These components include:

Pneumatic Pressure Gage. The gage should indicate12.0–20.0 psi before boots are activated. The pressurewil l momentari ly decrease when the boots areactivated.

Gyro Suction Gage. The gage should indicate in thearea of the green arc corresponding to the airplanealtitude. The vacuum will momentarily decrease whenthe boots are activated.

WING DEICE & TAIL DEICE annunciators. The WINGDEICE annunciator will illuminate within 6 seconds andthe TAIL DEICE annunciator will illuminate within 10seconds of switch activation when using the SINGLEmode. All annunciators will illuminate within 6 secondsof switch activation when using the MANUAL mode.

Pneumatic Boots. Visually monitor the boots, wherepossible, to ensure ice is being removed.

If either surface deice annunciator fails to illuminate orextinguish during a boot cycle, refer to Surface DeiceFailure in ABNORMAL PROCEDURES.

When Ice Accumulates To 1/2 To 1 Inch:

a. Surface Deice Switch ............................SINGLE AND RELEASE[WING DEICE] & [TAIL DEICE] – ILLUMINATED,

THEN EXTINGUISHED

b. Repeat as required.

If Single Position Of The Surface Deice Switch Fails:

c. Surface Deice ......................................MANUAL & HOLD UNTIL[WING DEICE] & [TAIL DEICE] ILLUMINATE

(within 6 seconds), THEN RELEASE

d. Repeat as required.

5. Windshield Anti-ice .........................................................NORMAL/HI

6. Left and Right Fuel Vent Heat .......................................................ON

7. Left and Right Pitot Heat ...............................................................ON

WARNING


OCTOBER 2000 N-16 P/N 130-590031-73D1

CRUISE (Cont)

8. Stall Warn Heat .............................................................................ON

9. Wing Ice Lights ..........................................................AS REQUIRED

10. Alternate Static Source ................SEE ABNORMAL PROCEDURES

DESCENT

1. Pressurization ..............................................................................SET

a. Cabin Altitude ........................................................................SET

b. Rate Control............................................................AS DESIRED

2. Altimeter.......................................................................................SET

3. Cabin Sign .................................................................AS REQUIRED

4. Windshield Anti-ice ....................................................AS REQUIRED

5. Windshield Defrost.....................................................AS REQUIRED

6. Window Defog............................................................AS REQUIRED

7. Fuel Balance ..........................................................................CHECK

8. Seats and Tables..........................................................POSITIONED

a. All Seats – Seatbacks upright; Headrests fully extended

b. Lateral-tracking Seats – Outboard position

c. Tables – Stowed

SEPTEMBER 2001N-17P/N 130-590031-73D2


ClosestAltimeterSetting

28.00

28.10

28.20

28.30

28.40

28.50

28.60

28.70

28.80

28.90

29.00

29.10

29.20

29.30

29.40

Add to AirportElevation

+2400

+2300

+2200

+2100

+2000

+1900

+1800

+1700

+1600

+1500

+1400

+1300

+1200

+1100

+1000

ClosestAltimeter

Setting (Cont)

29.50

29.60

29.70

29.80

29.90

30.00

30.10

30.20

30.30

30.40

30.50

30.60

30.70

30.80

30.90

Add to AirportElevation

(Cont)

+900

+800

+700

+600

+500

+400

+300

+200

+100

0

-100

-200

-300

-400

-500

PRESSURIZATION CONTROLLER SETTING FOR LANDING

BEFORE LANDING

1. Approach Speeds ..............................................................CONFIRM

• Landing (VREF)

• Approach Climb (VREF + 10 Knots)

• Balked Landing (VREF)

2. Autofeather .................................................................................ARM

3. Environmental Bleed Air .............................................................LOW

4. Cabin Sign

a. Standard Configuration...........................................NO SMK/FSB

b. No Smoking Configuration.....................................................FSB

5. Flaps...............................................................................APPROACH

6. Landing Gear...........................................................................DOWN

7. Exterior and Interior Lights.........................................AS REQUIRED

8. Radar .........................................................................AS REQUIRED

9. Surface Deice ............................................................AS REQUIRED

NORMAL LANDING

1. Flaps........................................................................................DOWN

2. Airspeed ......................................................................................VREF

3. Yaw Damp ...................................................................................OFF

4. Power Levers..............................................................................IDLE

5. Prop Levers ............................................................FULL FORWARD

After Touchdown:

6. Power Levers.............................LlFT AND SELECT GROUND FINE

7. Brakes........................................................................AS REQUIRED


SEPTEMBER 2001 N-18 P/N 130-590031-73D2

LANDING WT LBS (KGS)

15,000 (6804)

14,000 (6350)

13,000 (5897)

12,000 (5443)

11,000 (4989)

10,000 (4536)

VREF – KNOTS

109

105

102

100

100

100

LANDING APPROACH SPEED

STEEP APPROACH LANDING

Prior to the Final Approach Fix, or no later than 3 nm from the runway duringa visual approach:

1. TAWS (if installed) ...........ACTIVATE STEEP APPROACH SWITCH


3. Flaps..............................................................................FULL DOWN

4. Airpseed.....................................................................................VREF

Prior to Landing:

5. Yaw Damp ...................................................................................OFF

6. Power Levers..............................................................................IDLE

After Touchdown:

7. Power Levers.............................LIFT AND SELECT GROUND FINE


JULY 2002N-18AP/N 130-590031-73D3


PILOT NOTES


JULY 2002 N-18B P/N 130-590031-73D3

MAXIMUM REVERSE THRUST LANDING

1. Flaps........................................................................................DOWN

2. Airspeed ......................................................................................VREF

3. Yaw Damp ...................................................................................OFF

4. Condition Levers...............................................................HIGH IDLE

5. Power Levers ..............................................................................lDLE


After Touchdown:

7. Power Levers ..........................................LIFT THROUGH GROUNDFINE AND LIFT TO REVERSE


9. Condition Levers................................................................LOW IDLE

BALKED LANDING

1. Power..........................................................MAXlMUM ALLOWABLE

2. Airspeed....................................................................MAINTAIN VREF

(when clear of obstacles, establish a normal climb)

3. Flaps (at VREF + 10 knots) ..............................................APPROACH

4. Landing Gear (when a positive climb is established).....................UP


AFTER LANDING

1. Engine Auto-Ignition ....................................................................OFF

2. Engine Anti-ice ..............................................................................ON

3. Lights .........................................................................AS REQUIRED

4. Ice Protection...............................................................................OFF

5. Transponder ......................................................................STANDBY

6. Radar ..................................................................STANDBY OR OFF

7. Trim..............................................................................................SET

8. Flaps ..............................................................................................UP

9. Pressurization Differential ...................................................VERIFY 0

10. Bleed Air Valves ..............................................................ENVIR OFF

OCTOBER 2000N-19P/N 130-590031-73D1


SHUTDOWN AND SECURING

1. Parking Brake ..............................................................................SET

2. Electric Heat ................................................................................OFF

3. EFIS Power (if installed) ..............................................................OFF

4. Standby Horizon (if installed) .....................................CAGED & OFF

5. Avionics Master ...........................................................................OFF

6. Inverters.......................................................................................OFF

7. Autofeather ..................................................................................OFF

8. Exterior Lights..............................................................................OFF

9. Vent Blower ..............................................................................AUTO

10. Cabin Temp Mode .......................................................................OFF

11. Aft Blower ....................................................................................OFF

12. Aft Heat .........................................................................AS DESIRED

13. Oxygen Controls...............................................................PUSH OFF

14. Battery ..............................................................................CHARGED

15. Brake Deice (if installed, last flight of the day) ..........ON, THEN OFF

a. [L BK DEICE ON] & [R BK DEICE ON].................ILLUMINATED(when the brake deice is turned on)

b. [L BK DEICE ON] & [R BK DEICE ON] .............EXTINGUISHED(when the brake deice is turned off)

16. ITT ...................................STABILIZED AT MINIMUM OBTAINABLETEMPERATURE FOR ONE MINUTE

17. Instrument Emergency Lights(if desired for a night shutdown) ....................................................ON

18. Condition Levers ........................................................FUEL CUTOFF

19. Prop Levers........................................................................FEATHER

20. Overhead Panel Switches ...........................................................OFF

21. Battery and Generator Switches (below 15% N1)........................OFF

22. Control Locks .......................................................................INSTALL

23. Instrument Emergency Lights......................................................OFF

24. Tie-downs and Chocks.........................................................INSTALL

25. External Covers....................................................................INSTALL

26. Parking Brake ..............................................................................OFF

27. Baggage Compartment Lights.....................................................OFF

28. Cabin Entry Lights .......................................................................OFF


OCTOBER 2000 N-20 P/N 130-590031-73D1

EXPANDED PROCEDURES

NOTE


*AIRSTAIR DOOR CIRCUITRY CHECK (B300)

Perform Annunciator Circuitry Check With Battery Switch ON:

1. Airstair Door Closed And Locked[DOOR UNLOCKED] ...............................................EXTINGUISHED

2. Airstair Door Closed, But Not Locked[DOOR UNLOCKED] ..................................................ILLUMINATED

3. Airstair Door Open And Mechanism In Locked Position[DOOR UNLOCKED] ..................................................ILLUMINATED

RETURN TO PAGE N-4, STEP 22

*AIRSTAIR DOOR CIRCUITRY CHECK (B300C)

Perform Annunciator Circuitry Check With Battery Switch ON:

1. Cargo Door.........................................................CONFIRM LOCKED

2. Airstair Door Open[DOOR UNLOCKED] ..................................................ILLUMINATED

3. Airstair Door Closed and Locked[DOOR UNLOCKED] ...............................................EXTINGUISHED

4. Battery .........................................................................................OFF

5. Airstair Door Closed, but Not Latched[DOOR UNLOCKED] ..................................................ILLUMINATED

6. Airstair Door Open[DOOR UNLOCKED] ...............................................EXTINGUISHED


*OXYGEN SYSTEM PREFLIGHT INSPECTION

1. Passenger Manual Drop-Out............................................PUSH OFF

2. System Ready .....................................................................PULL ON

3. Oxygen Masks (Pilot & Copilot) .............................................CHECK

a. Select EMER Position .................CHECK CONTINUOUS FLOW

b. Set 100%

4. Oxygen Duration............................................................DETERMINE(SEE PAGE N-22)

APRIL 2006N-21P/N 130-590031-73D8


*OXYGEN DURATION

NOTE

A bottle pressure of 1850 psig at 15° C is fully charged(100% capacity). Read duration directly from thefollowing table.

1. Read the oxygen pressure from the gage.

2. Read the IOAT (with battery on). (Assume IOAT to be equal toBOTTLE TEMPERATURE.)

3. Determine the percent of usable capacity from the following graph(e.g., 1100 psig at 0° C = 57%)

4. Compute the oxygen duration in minutes from the following table bymultiplying the full bottle duration by the percent of usable capacity, e.g.,

a. Pilot and copilot with masks set at 100% plus 6 passengers = 10people using oxygen.

NOTE

Pilot and copilot are each counted as 2 people with thediluter demand masks set at the 100% or EMERG mode.

b. Cylinder volume = 115 cubic feet.

c. Duration with full bottle = 73 minutes.

d. Duration with 57% capacity = .57 x 73 = 41 minutes.


SEPTEMBER 2001 N-22 P/N 130-590031-73D2

*OXYGEN DURATION (Cont)

Oxygen Available With Partially Full Bottle

Oxygen Duration With Full Bottle (100% Capacity)

RETURN TO PAGE N-4, STEP 1 OR

PAGE N-8, STEP 13.

JULY 2002N-23P/N 130-590031-73D3


STATED *NUMBER OF PEOPLE USING

CYLINDER 1 2 3 4 5 6 7 8 9

SIZE

CU FT LITERS DURATION IN MINUTES

50 1416 317 158 105 79 63 52 45 39 35

77 2181 488 244 162 122 97 81 69 61 54

115 3257 732 366 244 183 146 122 104 91 81

STATED *NUMBER OF PEOPLE USING

CYLINDER 10 11 12 13 14 15 16 17

SIZE

CU FT LITERS DURATION IN MINUTES

50 1416 31 28 26 24 22 21 19 18

77 2181 48 44 40 37 34 32 30 28

115 3257 73 66 61 56 52 48 45 43

*The pilot and copilot are each counted as 2 people with crew masks set at the100% or EMERG mode.

LOCKING THE AIRSTAIR DOOR (B300)

1. Close and lock the door.

2. Check the position of the safety arm and diaphragm plunger.

3. Check that the green index marks on each of the 4 latch bolts alignwithin the indicator windows.

4. Check the engagement of both upper door hooks by means of theilluminated viewing ports.

5. Attempt to turn handle to unlocked position without depressing therelease button.


LOCKING THE CARGO DOOR (B300C)

1. Check upper handle position – closed and latched. (Observe throughthe handle access cover window.)

2. Check that the orange index marks on each of the four rotary camlocks align within the indicator windows.

3. Check lower pin latch handle position – closed and latched. (Observethrough the handle access cover window.)

4. Check that the orange-colored indicator aligns with orange stripe oncarrier rod. (Observe through window at lower left corner.)


LOCKING THE AIRSTAIR DOOR (B300C)

1. Close and lock the door.

2. Check the position of the safety arm and diaphragm plunger. (Liftthe door step)

3. Check that the orange index marks on each of the six rotary camlocks align within the indicator windows.


*FUEL SYSTEM

1. Firewall Fuel Valves ...............................................................CLOSELeft & Right [EXTINGUISHER PUSH] & [CLOSED] – ILLUMINATED

2. Standby Pumps .............................................................................ON[L FUEL PRES LO] & [R FUEL PRES LO] – ILLUMINATED

3. Firewall Fuel Valves .................................................................OPENLeft & Right [EXTINGUISHER PUSH] & [CLOSED] – EXTINGUISHED

[L FUEL PRES LO] & [R FUEL PRES LO] – EXTINGUISHED


FEBRUARY 1999 N-24 P/N 130-590031-73D

*FUEL SYSTEM (Cont)

4. Standby Pumps ...........................................................................OFF[L FUEL PRES LO] & [R FUEL PRES LO] – ILLUMINATED

5. Crossfeed ...................................ALTERNATELY LEFT AND RIGHT[FUEL CROSSFEED] – ILLUMINATED

[L FUEL PRES LO] & [R FUEL PRES LO] – EXTINGUISHED

6. Crossfeed ....................................................................................OFF

7. Fuel Quantity .............................................................................TEST[L FUEL QTY] & [R FUEL QTY] – ILLUMINATED


ENGINE STARTING (EXTERNAL POWER)

NEVER CONNECT AN EXTERNAL POWERSOURCE TO THE AIRPLANE UNLESS A BATTERYINDICATING A CHARGE OF AT LEAST 20 VOLTS ISIN THE AIRPLANE. If the battery voltage is less than20 volts, the battery must be recharged, or replacedwith a battery indicating at least 20 volts, beforeconnecting external power.

1. Battery .............................................................................VERIFY ON

2. Gen Ties (for night operation)........................................MAN CLOSE

3. Voltmeter ..............................................BAT- 20.0 VOLTS MINIMUM

4. External Power ..............................................................VERlFY OFF

5. Avionics Master .............................................................VERlFY OFF

6. Left and Right Generators .............................................VERlFY OFF

7. Battery Bus ................................................................VERIFY NORM

8. Beacon ............................................................................VERIFY ON

9. External Power Source.....................................................TURN OFFCONNECT TO AIRPLANE; TURN ON

10. Voltmeter .......................................EXT PWR - 28.0 TO 28.4 VOLTS

11. External Power ..............................................................................ON[EXT PWR] – ILLUMINATED

12. Prop Levers........................................................................FEATHER

13. Propeller Area.........................................................................CLEAR

14. Right Ignition and Engine Start......................................................ON[R IGNITION ON] – ILLUMINATED

[R FUEL PRES LO] – EXTINGUISHED

15. Right Condition Lever (after 12% N1, minimum)................LOW IDLE

16. Right ITT and N1 ................................................................MONITOR(1000° C maximum)

CAUTION

JULY 2002N-25P/N 130-590031-73D3


ENGINE STARTING (EXTERNAL POWER) (Cont)

17. Right Oil Pressure ..................................................................CHECK

18. Right Ignition and Engine Start (at 50% N1 or above) .................OFF

19. Left Ignition and Engine Start ........................................................ON[L IGNITION ON] – ILLUMINATED

[L FUEL PRES LO] – EXTINGUISHED

20. Left Condition Lever (after 12% N1, minimum) ..................LOW IDLE

21. Left ITT and N1 ..................................................................MONITOR(1000° C maximum)

22. Left Oil Pressure ....................................................................CHECK

23. Left Ignition and Engine Start (at 50% N1 or above)....................OFF

24. External Power ............................................................................OFF

25. External Power Source.....................................................TURN OFFDISCONNECT FROM AIRPLANE;

SECURE DOOR

26. [EXT PWR] ................................................VERIFY EXTINGUISHED

27. Right Generator ....................................................RESET, THEN ON[R DC GEN], [L GEN TIE OPEN]

& [R GEN TIE OPEN] – EXTINGUISHED

28. Voltmeter..................................................................................L GEN(voltmeter – 27.5 to 29.0 volts)

29. Left Generator ......................................................RESET, THEN ON[L DC GEN] – EXTINGUISHED

30. Right Generator ....................................................RESET, THEN ON[L GEN TIE OPEN] & [R GEN TIE OPEN] – REMAIN

EXTINGUISHED WITH SWITCH IN THE RESET POSITION


32. Left and Right Prop RPM...........................................1050 MINIMUM

33. [L PROP PITCH] & [R PROP PITCH] .........................ILLUMINATED

RETURN TO PAGE N-12, BEFORE TAXI, STEP 1

*ELECTRICAL SYSTEM

1. Gen Ties ...................................................................................OPEN[L GEN TIE OPEN] & [R GEN TIE OPEN] – ILLUMINATED

2. Voltmeter:

a. TPL FED .....................................................26.5 TO 28.0 VOLTS

b. R GEN and L GEN......................................27.5 TO 29.0 VOLTS(within 1.0 volt of each other)

c. CTR ............................................................23 VOLTS MINIMUM


OCTOBER 2000 N-26 P/N 130-590031-73D1

*ELECTRICAL SYSTEM (Cont)

3. Gen Ties ..................................................................................NORM[L GEN TIE OPEN] & [R GEN TIE OPEN] – EXTINGUISHED

4. Bus Sense................................................MOMENTARILY TO TEST[L GEN TIE OPEN], [R GEN TIE OPEN]

& [BAT TIE OPEN] – ILLUMINATED

5. Voltmeter ..................................................................CTR – 0 VOLTS

6. Bus Sense .............................................MOMENTARILY TO RESET[L GEN TIE OPEN], [R GEN TIE OPEN]

& [BAT TIE OPEN] – EXTINGUISHED

7. Voltmeter ................................................CTR - 27.5 TO 29.0 VOLTS

8. Generator Load ...................OBSERVE PARALLELED WITHIN 10%


INVERTERS

NOTE


1. Both Inverters ................................................................................ON[#1 AC BUS] & [#2 AC BUS] – EXTINGUISHED

*2. No. 1 Inverter...............................................................................OFF[#1 AC BUS] – ILLUMINATED

*3. No.1 Inverter ...........................................................BUS TRANSFER[#1 AC BUS] & [#2 AC BUS ] – EXTINGUISHED

*4. No. 1 Inverter.................................................................................ON[#1 AC BUS] & [#2 AC BUS] – EXTINGUISHED

*5. No. 2 Inverter...............................................................................OFF[#2 AC BUS] – ILLUMINATED

*6. No. 2 Inverter ..........................................................BUS TRANSFER[#1 AC BUS] & [#2 AC BUS] – EXTINGUISHED

*7. No. 2 Inverter.................................................................................ON[#1 AC BUS] & [#2 AC BUS] – EXTINGUISHED


FEBRUARY 2007N-27P/N 130-590031-73D9


ENVIRONMENTAL SYSTEM

Observe N1, ITT, and generator limits if air conditioning or electric heat is used.

1. Vent Blower................................................................AS REQUIRED

2. Cabin Temp Control ...................................................AS REQUIRED

3. Cabin Temp Mode ....................................................................AUTO

4. Environmental Bleed Air ......................................LOW OR NORMAL

5. Bleed Air Valves.............................................OPEN OR ENVIR OFF

a. Use OPEN for more efficient heating on the ground.

b. Use ENVIR OFF for more efficient cooling on the ground.


a. For maximum cooling, the vent blower should be selected toHIGH, and the aft blower should be selected on.

b. For maximum heating without electric heat, the vent blowershould be selected to HIGH, the aft blower should be selectedoff, and the aft heat should be selected on.

7. Electric Heat...............................................................AS REQUIRED

a. Cabin Temp Mode ....................................AUTO OR MAN HEAT

b. Vent Blower .........................................................................HIGH

c. Aft Blower ................................................................................ON

d. Electric Heat ............................................................................ON[ELEC HEAT ON] – ILLUMINATED

8. Aft Heat ......................................................................AS REQUIRED

9. Cabin/Cockpit Air .......................................................AS REQUIRED

a. Pull to increase airflow to the cockpit.

b. Push to increase airflow to the cabin.

10. Copilot Air ..................................................................AS REQUIRED

11. Pilot Air.......................................................................AS REQUIRED

12. Windshield Defrost.....................................................AS REQUIRED

a. Pull to increase; push to decrease.

b. Push the pilot and copilot air controls fully in and pull theCabin/Cockpit Air Control fully out if increased windshielddefrost airflow is required.



FEBRUARY 2007 N-28 P/N 130-590031-73D9

Vent BlowerMode

Auto

Auto

Lo

High

Cabin Temp ModeSelection

Off

Auto, Man Heat, Man Cool

Any

Any

Vent BlowerSpeed

Off

Low

Low

High

PRESSURIZATION

NOTE


1. Environmental Bleed Air ......................................................NORMAL

2. Bleed Air Valves .......................................................................OPEN

*3. Pressurization Controller .............................................................SET

a. Adjust cabin altitude knob to indicate 1,000 feet below fieldpressure altitude.

b. Set rate knob to 12 o’clock position.

*4. Cabin Pressure Switch ...................HOLD AT THE TEST POSITION

*5. Cabin Altimeter and VSI ........CHECK FOR DESCENT INDICATION

*6. Cabin Pressure Switch .................RELEASE TO PRESS POSITION

7. Pressurization Controller .............................................................SET

• The inner scale (ACFT ALT) should indicate planned cruisealtitude plus 1,000 feet. This setting must not result in an outerscale (CABIN ALT) indication of less than 500 feet abovedeparture field pressure altitude.

RETURN TO PAGE N-12, BEFORE TAKEOFF (RUNUP), STEP 3

AUTOPILOT

1. Pitch Trim.........................................................TAKEOFF POSITION

2. Electric Pitch Trim .........................................................................ON[PITCH TRIM OFF] – EXTINGUISHED

3. Elevator..........................................................FORWARD POSITION

4. Autopilot ..............................................................................ENGAGE[YAW] & [AP] – ILLUMINATED

5. Electric Pitch Trim.......................OPERATE IN BOTH DIRECTIONS(AP disengages with each operation

and the YD remains engaged)

6. Elevator...........................................................................CENTERED

7. Autopilot ..............................................................................ENGAGE

a. Apply rearward pressure on the elevator – Pitch trim travelsnose-down.

b. Apply forward pressure on the elevator – Pitch trim travels nose-up.

8. AP/Trim Disconnect .............................DEPRESS TO FIRST LEVEL [YAW DIS] & [AP DIS] – ILLUMINATED,

FLASHING AND THEN EXTINGUISHED

9. Repeat items 1 through 8 for copilot’s side.


OCTOBER 2004N-29P/N 130-590031-73D6


*YAW DAMP

1. Yaw Damp.....................................................................................ON[YAW] – ILLUMINATED

2. Rudder Pedals .........................CHECK FOR ADDED RESISTANCE

3. Rudder Boost Switch .....................................YAW CONTROL TEST[RUD BOOST OFF] – ILLUMINATED

(yaw damp system disconnects)

4. Rudder Boost Switch .............................................RUDDER BOOST[RUD BOOST OFF] – EXTINGUISHED


*ELECTRIC PITCH TRIM

1. Electric Pitch Trim .........................................................................ON

2. Pilot’s and Copilot’s Trim Switches ..................CHECK OPERATION

a. Move each dual-element switch fore and aft – Verify trim is inop.

b. Move both dual-element switches fore and aft – Verify trimoperates nose down and nose up.

c. Ensure pilot’s trim switch overrides copilot’s trim switch.

3. AP/Trim Disconnect .....................................PRESS TO 2ND LEVEL[PITCH TRIM OFF] – ILLUMINATED

4. Electric Pitch Trim .....................................................OFF, THEN ON[PITCH TRIM OFF] – EXTINGUISHED

Operation of the electric pitch trim system should occuronly when both elements of the dual-element switchare activated. Any movement of the elevator trim wheelwhile activating only one element denotes a systemmalfunction. The electric pitch trim must then be turnedoff and the flight conducted only by manual operationof the elevator trim control.


*OVERSPEED GOVERNORS/RUDDER BOOST

1. Rudder Boost Switch .............................................RUDDER BOOST


3. Prop Governor Test Switch........................................HOLD TO GOV

4. Power Levers (Individually) ...................INCREASE UNTIL PROP ISSTABILIZED AT 1500 TO 1610 RPM.

CONTINUE TO INCREASE UNTILRUDDER MOVEMENT IS NOTED

(right power lever, right rudder, left power lever,left rudder. Observe ITT and torque limits.)

WARNING


AUGUST 2003 N-30 P/N 130-590031-73D4

*OVERSPEED GOVERNORS/RUDDER BOOST (Cont)

5. AP/Trim Disconnect .............................................DEPRESS TO 1STLEVEL AND RELEASE

(rudder boost is interrupted)

6. Power Lever................................................................................lDLE

7. Repeat steps 4 through 6 on the opposite engine.

8. Prop Governor Test Switch ................................................RELEASE


*LOW PITCH STOPS AND PRIMARY GOVERNORS


2. Low Pitch Stop Switch ...........................HOLD TO GND IDLE STOP[L PROP PITCH] & [R PROP PITCH] – ILLUMINATED

3. Power Levers.............................................................SET 1500 RPM

4. Prop Levers..................................CYCLE TO LOW AND HIGH RPM(propeller RPM decreasesthen returns to 1500 RPM)

5. Low Pitch Stop Switch........................................................RELEASE[L PROP PITCH] & [R PROP PITCH] – EXTINGUISHED

6. Prop RPM .........................................STABILIZED AT 1150 TO 1250


*AUTOFEATHER

1. Autofeather Switch ...................................................HOLD TO TEST

2. Power Levers...............................APPROXIMATELY 22% TORQUE[L AUTO FEATHER] & [R AUTO FEATHER] – ILLUMINATED

3. Power Levers .............................................RETARD INDIVIDUALLY

a. At approximately 17% torque – OPPOSITE ANNUNCIATOREXTINGUISHED

b. At approximately 10% torque – BOTH ANNUNCIATORSEXTINGUISHED (prop starts to feather)

4. Power Levers..............................................................................IDLE[L AUTO FEATHER] & [R AUTO FEATHER] – EXTINGUISHED

(neither prop feathers)

5. Autofeather Switch .............................................................RELEASE


FEBRUARY 1999N-31P/N 130-590031-73D


*INSTRUMENT VACUUM AND DEICE PRESSURE

1. Left Bleed Air Switch .........................................PNEU & ENVIR OFF

a. Pneumatic Pressure and Gyro Suction Gages..............NORMALPRESSURE

b. [L BLEED FAIL] & [R BLEED FAIL] ...................EXTINGUISHED

2. Right Bleed Air Switch.......................................PNEU & ENVIR OFF

a. Pneumatic Pressure and Gyro Suction Gages...................ZEROPRESSURE

b. [L BLEED FAIL] & [R BLEED FAIL] ......................ILLUMINATED

3. Left Bleed Air Switch......................................OPEN OR ENVIR OFF

a. Pneumatic Pressure and Gyro Suction Gages..............NORMALPRESSURE

b. [L BLEED FAIL] & [R BLEED FAIL] ...................EXTINGUISHED

4. Right Bleed Air Switch ...................................OPEN OR ENVIR OFF


*ENGINE ANTI-ICE

Either the MAIN or STANDBY actuator must beoperational on each engine before takeoff.

With system initially ON:

1. Engine Anti-ice Actuators ..................................................STANDBY

2. Engine Anti-ice ............................................................................OFF[L ENG ANTI-ICE] & [R ENG ANTI-ICE] – EXTINGUISHED

3. Engine Anti-ice Actuators ..........................................................MAIN

4. Engine Anti-ice ..............................................................................ON[L ENG ANTI-ICE] & [R ENG ANTI-ICE] – ILLUMINATED


WARNING


OCTOBER 2000 N-32 P/N 130-590031-73D1

ICE PROTECTION EQUIPMENT (IF REQUIRED)

Engine Auto-Ignition

1. Power Levers ..............................................................................lDLE

2. Engine Auto-Ignition Switches ....................................................ARM[L IGNITION ON] & [R IGNITION ON] – ILLUMINATED

3. Power Levers ........................ADVANCE TO ABOVE 17% TORQUE[L IGNITION ON] & [R IGNITION ON] – EXTINGUISHED

4. Power Levers ..............................................................................lDLE[L IGNITION ON] & [R IGNITION ON] – ILLUMINATED

5. Engine Auto-Ignition Switches.....................................................OFF[L IGNITION ON] & [R IGNITION ON] – EXTINGUISHED

Windshield Anti-ice (check pilot’s & copilot’s one at a time)

1. Windshield Anti-ice..........................................................................Hl(observe increase on

left and right loadmeters)

2. Windshield Anti-ice..........................................OFF, THEN NORMAL(observe increase on

left and right loadmeters)

3. Windshield Anti-ice ......................................................................OFF

Electrothermal Propeller Deice

1. Automatic Prop Deice....................................................................ON

2. Deice Ammeter.........................................................26 TO 32 AMPS(monitor for 90 seconds to ensure

automatic timer operation)

3. Manual Prop Deice ............................HOLD IN MANUAL POSITION

a. A small needle deflection on both loadmeters indicates that themanual system is operating.

b. Deice Ammeter................................................................0 AMPS

4. Manual Prop Deice.............................................................RELEASE

5. Deice Ammeter.........................................................26 TO 32 AMPS

6. Automatic Prop Deice..................................................................OFF

Surface Deice

1. Condition Levers......................................HIGH IDLE, IF REQUIRED

2. Pneumatic Pressure...............................................................CHECK

FEBRUARY 1999N-33P/N 130-590031-73D


ICE PROTECTION EQUIPMENT (IF REQUIRED)(Cont)

3. Surface Deice Switch ..................................SINGLE AND RELEASE

a. Pneumatic Pressure .........................MOMENTARY DECREASE

b. [WING DEICE] & [TAIL DEICE] ...........................ILLUMINATED,THEN EXTINGUISHED

c. Boots.............................CHECK VISUALLY WHERE POSSIBLEFOR INFLATION AND HOLD DOWN

d. Inflation Time......................................6 SECONDS FOR WINGSFOLLOWED BY 4 SECONDS FOR

HORIZONTAL STABILIZER

4. Surface Deice Switch .......................................MANUAL AND HOLD

a. Pneumatic Pressure .........................MOMENTARY DECREASE

b. [WING DEICE] & [TAIL DEICE] ............................ILLUMINATED

c. Boots ..............................................CHECK VISUALLY, WHEREPOSSIBLE, FOR INFLATION

5. Surface Deice Switch .........................................................RELEASE

a. [WING DEICE] & [TAIL DEICE] .........................EXTINGUISHED

b. Boots ..............................................CHECK VISUALLY, WHEREPOSSIBLE, FOR HOLD DOWN

6. Condition Levers................................................................LOW IDLE



FEBRUARY 1999 N-34 P/N 130-590031-73D

OTHER PROCEDURES

SIMULATING ONE-ENGINE-INOPERATIVE(ZERO THRUST)

When establishing zero thrust operation, use the power setting listedbelow. By using this power setting to establish zero thrust, one avoids theinherent delays of restarting a shut-down engine and preserves almostinstant power to counter any attendant hazard.

1. Prop ...................................................................................1700 RPM

2. Power ............................................................................5% TORQUE

NOTE

This setting will approximate zero thrust at lowaltitudes using recommended one-engine-inoperativeclimb speeds.

INTENTIONAL IN-FLIGHT ENGINE CUTS SHOULDBE SIMULATED BY RETARDING THE POWERLEVER TO ZERO THRUST AT OR ABOVE THE VSSESPEED OF 110 KNOTS. For training, this setting willapproximate zero thrust at low alt i tudes usingrecommended one-engine inoperative climb speeds.The propeller autofeather system is disabled with apower lever retarded.

PRACTICE DEMONSTRATION OF VMCA

INTENTIONAL IN-FLIGHT ENGINE CUTS SHOULDBE SIMULATED BY RETARDING THE POWERLEVER TO ZERO THRUST AT OR ABOVE THE VSSESPEED OF 110 KNOTS. For training, this setting willapproximate zero thrust at low alt i tudes usingrecommended one-engine inoperative climb speeds.The propeller autofeather system is disabled with apower lever retarded.

WARNING

WARNING

FEBRUARY 1999N-35P/N 130-590031-73D


Continued on Next Page.

PRACTICE DEMONSTRATION OF VMCA (Cont)

1. Landing Gear .................................................................................UP

2. Flaps ..............................................................................................UP

3. Airspeed..................................................ABOVE 110 KNOTS (VSSE)

4. Prop Levers ......................................................................HIGH RPM

5. Power Lever (simulated inoperative engine).............ZERO THRUST(5% torque)

6. Power Lever (other engine) ........................MAXlMUM ALLOWABLE

7. Airspeed .................................REDUCE APPROXIMATELY 1 KNOTPER SECOND UNTIL EITHER VMCA OR

STALL WARNING IS OBTAINED

PRACTICE LANDING GEAR MANUAL EXTENSION

1. Airspeed ............................................................BELOW 184 KNOTS

2. Landing Gear Relay Circuit Breaker (pilot’s right subpanel) ...............PULL

3. Landing Gear Control ..............................................................DOWN

4. Alternate Extension Handle ................................................UNSTOW

5. Alternate Extension Handle...........................PUMP UP AND DOWN(until the [L], [R], &[NOSE] illuminate

and further resistance is felt)

6. Alternate Extension Handle .....................................................STOW

LANDING GEAR RETRACTION AFTER PRACTICEMANUAL EXTENSION

After a practice manual extension of the landing gear, the gear may beretracted as follows:

1. Alternate Extension Handle .....................................................STOW

2. Landing Gear Relay Circuit Breaker(pilot’s right subpanel) ..........................................................PUSH IN

3. Landing Gear .................................................................................UP


OCTOBER 2000 N-36 P/N 130-590031-73D1

APRIL 2006E-iP/N 130-590031-73D8

#1 AC BUS #2 AC BUS

DOORUNLOCKED

L BLEED FAIL

ENG FIRE

CABIN ALT HI

CABIN DIFF HI

R BLEED FAIL

7

L FUEL PRES LO R FUEL PRES LO

L OIL PRES LO R OIL PRES LO

8

4

12

12

3

13

8

4

3

13

2

PASS OXYGEN ON

12

R DC GEN

9

FlightSafety international

L DC GEN

9

PILOT NOTES


FEBRUARY 1999 E-ii P/N 130-590031-73D

OCTOBER 2000E-1P/N 130-590031-73D1

EM

ER

GE

NC

Y

EMERGENCY PROCEDURES

EMERGENCY AIRSPEEDS

ENGINE FAILUREENGINE FIRE OR FAILURE IN FLIGHTENGINE FIRE ON GROUNDEMERGENCY ENGINE SHUTDOWN ON THE GROUND

ENGINE FAILURE DURING TAKEOFF(AT OR BELOW V1)–TAKEOFF ABORTED

ENGINE FAILURE DURING TAKEOFF(AT OR ABOVE V1)–TAKEOFF CONTINUED

ENGINE FAILURE IN FLIGHT BELOW AIR MINIMUMCONTROL SPEED (VMCA)

OIL PRESSURE LOW

FUEL SYSTEMFUEL PRESSURE LOW

SMOKE AND FUME ELIMINATIONWINDSHIELD ELECTRICAL FAULT

ELECTRICAL SMOKE OR FIREENVIRONMENTAL SYSTEM SMOKE OR FUMES

AIRSTAIR DOOR/CARGO DOOR UNLOCKEDEMERGENCY DESCENTEMERGENCY LANDING

GLIDEELECTRICALSINGLE INVERTER FAILUREDUAL INVERTER FAILURE

DUAL GENERATOR FAILURELOAD MANAGEMENT WITH A DUAL GENERATOR FAILURE

FLIGHT CONTROLSUNSCHEDULED ELECTRIC PITCH TRIM ACTIVATIONUNSCHEDULED RUDDER BOOST ACTIVATION

ENVIRONMENTAL SYSTEMSUSE OF OXYGEN

PRESSURIZATION LOSSHIGH DIFFERENTIAL PRESSUREAUTO–DEPLOYMENT OXYGEN SYSTEM FAILURE

BLEED AIR FAILEMERGENCY EXIT

SPINS

1

2

3

5

6

7

4

8

9

10

11

12

13


14

PILOT NOTES


FEBRUARY 1999 E-2 P/N 130-590031-73D

1

All airspeeds quoted in this section are Indicated Airspeeds (IAS) andassume zero instrument error.

Closed [BRACKETS] in this section denote annunciator(s)

EMERGENCY AIRSPEEDS

(15,000 LBS (6804 KG))

One-Engine-lnoperativeBest-Angle-of-Climb (VXSE)...........................................................125 Knots

One-Engine-lnoperativeBest-Rate-of-Climb (VYSE) ............................................................125 Knots

One-Engine-lnoperative Enroute Climb........................................125 Knots

Air Minimum Control Speeds (VMCA):

Flaps Up ..............................................................................94 Knots

Flaps Approach ...................................................................93 Knots

Emergency Descent .....................................................................184 Knots

Maximum Range Glide.................................................................135 Knots


1

FEBRUARY 1999E-3P/N 130-590031-73D

PILOT NOTES

2


FEBRUARY 1999 E-4 P/N 130-590031-73D

ENGINE FAILURE

ENGINE FIRE OR FAILURE IN FLIGHT

Affected Engine:

1. Condition Lever ......................................................FUEL CUTOFF

2. Prop Lever .......................................................................FEATHER

3. Firewall Fuel Valve ..............................................................CLOSE[EXTINGUISHER PUSH] & [CLOSED] – ILLUMINATED

4. Fire Extinguisher (if fire warning persists) ..................ACTUATE[DISCHARGED] – ILLUMINATED

5. Generator ...................................................................................OFF

6. Engine Auto-Ignition ...................................................................OFF

7. Autofeather .................................................................................OFF

8. Brake Deice (if installed).............................................................OFF

9. Electrical Load ..................................................................MONITOR

ENGINE FIRE ON GROUND

Affected Engine:

1. Condition Lever ......................................................FUEL CUTOFF

2. Firewall Fuel Valve ..............................................................CLOSE[EXTINGUISHER PUSH] & [CLOSED] – ILLUMINATED

3. Starter Switch.......................................................STARTER ONLY

4. Fire Extinguisher (if fire warning persists) ..................ACTUATE[DISCHARGED] – ILLUMINATED

EMERGENCY ENGINE SHUTDOWN ONTHE GROUND

1. Condition Levers ....................................................FUEL CUTOFF

2. Prop Levers .....................................................................FEATHER

3. Firewall Fuel Valves ............................................................CLOSE[EXTINGUISHER PUSH] & [CLOSED] – ILLUMINATED

4. Master Switch (gang bar).........................................................OFF

5. Battery Bus .................................................................EMERG OFF


2

FEBRUARY 2007E-5P/N 130-590031-73D9

ENG FIRE

ENG FIRE

ENGINE FAILURE DURING TAKEOFF(AT OR BELOW V1) — TAKEOFF ABORTED

1. Power Levers ..........................................................GROUND FINE

2. Brakes .............................................................................MAXIMUM(or as required to achieve stopping distance)

Do not use reverse thrust with one engine inoperative.Care must be exercised when using single-engineground fine on surfaces with reduced traction.

ENGINE FAILURE DURING TAKEOFF(AT OR ABOVE V1) — TAKEOFF CONTINUED

1. VR Speed ......................................ROTATE TO APPROXIMATELY10° PITCH ATTITUDE

2. Landing Gear (when positive climb established) ....................UP

3. Airspeed ..........................................MAINTAIN V2 TO 400 FT AGL

4. Propeller (inoperative engine) ....................VERIFY FEATHERED

Do not retard the failed engine power lever until theautofeather system has completely stopped propellerrotation.

5. Flaps (at 400 ft AGL minimum) ....................................UP AT V2 + 9

6. Airspeed................................................INCREASE TO 125 KNOTS

7. Climb to 1500 ft AGL, then accomplish the following cleanupprocedures on the inoperative engine:

a. Condition Lever...................................................FUEL CUTOFF

b. Prop Lever ..................................................................FEATHER

c. Firewall Fuel Valve ..........................................................CLOSE[EXTINGUISHER PUSH] & [CLOSED] – ILLUMINATED

d. Generator .............................................................................OFF

e. Engine Auto-Ignition .............................................................OFF

8. Autofeather .................................................................................OFF


10. Electrical Load ..................................................................MONITOR

WARNING

WARNING3


FEBRUARY 2007 E-6 P/N 130-590031-73D9

ENGINE FAILURE IN FLIGHT BELOW AIR MINIMUMCONTROL SPEED (VMCA)

1. Power ...........REDUCE AS REQUIRED TO MAINTAIN CONTROL

2. Nose...............................LOWER TO ACCELERATE ABOVE VMCA

3. Power........................................................................AS REQUIRED

4. Engine.................................................................................SECURE(see Engine Fire or Failure In Flight)

OIL PRESSURE LOW

1. Oil Pressure ............................................CONFIRM BELOW 60 PSI

If Confirmed:

2. Engine.................................................................................SECURE(see Engine Fire or Failure In Flight)

Or:

3. Land at the nearest suitable airport using the minimum powerrequired to sustain flight.


3

OCTOBER 2000E-7P/N 130-590031-73D1

L OIL PRES LO R OIL PRES LOOR

PILOT NOTES

4


FEBRUARY 1999 E-8 P/N 130-590031-73D

FUEL SYSTEM

FUEL PRESSURE LOW

1. Standby Pump (failed side) ..........................................................ON

2. [FUEL PRES LO] ....................................................EXTINGUISHED

3. Oil Temperature Gage (failed side) ..................................MONITOR


4

FEBRUARY 1999E-9P/N 130-590031-73D

L FUEL PRES LO R FUEL PRES LOOR

PILOT NOTES

5


FEBRUARY 1999 E-10 P/N 130-590031-73D

SMOKE AND FUME ELIMINATION

WINDSHIELD ELECTRICAL FAULT

1. WSHLD ANTI-ICE Switches ......................................................OFF

If Smoke and/or Fire Does Not Cease:

2. Conduct ELECTRICAL SMOKE OR FIRE procedure.

If Smoke and/or Fire Ceases:

3. Continue flight with Windshield Anti-Ice OFF if possible.

If Windshield Anti-Ice is Required:

4. If the source of the smell, smoke, or fire can be isolated to thepilot’s or copilot’s windshield, the opposite windshield (without theoverheat condition) may be operated in the NORMAL or HI wind-shield heat mode.


5

OCTOBER 2000E-11P/N 130-590031-73D1

ELECTRICAL SMOKE OR FIRE

1. Oxygen Mask(s) .......................................................................DON

2. Mask Selector Switch..........................................EMERG Position

3. Headset(s)............................DON, OR AUDIO SPEAKER(S) – ON

4. Mic Switch(es).......................................................OXYGEN MASK

5. Instrument Emergency Lights (if required) ...................................ON

6. Avionics Master ..........................................................................OFF

7. Generators..................................................................................OFF

To Facilitate Smoke Removal:

8. Pilot and Copilot Air............................................................PULL ON

9. Defrost Air ..........................................................................PULL ON

10. Cabin Air ........................................................PULL TO DECREASE

11. Cockpit Door............................................................................OPEN

Dissipation of smoke is not sufficient evidence that a firehas been extinguished. If it cannot be visually confirmedthat no fire exists, land at the nearest suitable airport.

If Smoke Persists Or If Extinguishing Of Fire Is Not Confirmed:

12. Cabin Pressurization (if desired) .............................................DUMP

13. Master Switch (gang bar) ...........................................................OFF

14. Storm Window (if required) ......................OPEN BELOW 13,500 FT

15. Land ..............................................NEAREST SUITABLE AIRPORT

a. GND COMM Switch (if installed).............PRESS TO RESTORECOMM 1

b. Flaps .....................................PLAN ON A FLAPS-UP LANDING

c. Landing Gear .............................................LOWER MANUALLY

16. If conditions require the partial restoration of power, one or more ofthe following procedures may be used. Verify proper voltage on thevoltmeter. Each set of procedures assumes the Master Switch(gang bar) is initially off.

a. To restore Left Generator Bus and Triple Fed Bus only:

1) Gen Ties ....................................................................OPEN

2) Left Generator........................................RESET, THEN ON

3) Avionics Master (if required) ...........................................ON

WARNING

6


OCTOBER 2000 E-12 P/N 130-590031-73D1

Continued on Next Page

b. To restore Right Generator Bus and Triple Fed Bus only:

1) Gen Ties ....................................................................OPEN

2) Right Generator .....................................RESET, THEN ON


c. To restore all buses except the Center Bus:

1) Gen Ties ....................................................................OPEN

2) Left and Right Generators .....................RESET, THEN ON

3) Battery ............................................................................ON

4) Bus Sense Switch.......................................................TEST


d. To restore the Battery Bus, Triple Fed Bus, and Center Bus only:

1) Battery ............................................................................ON


ENVIRONMENTAL SYSTEM SMOKE OR FUMES

1. Oxygen Mask(s) .......................................................................DON

2. Mask Selector Switch..........................................EMERG Position

3. Headset(s)............................DON, OR AUDIO SPEAKER(S) – ON


5. Cabin Temp Mode ......................................................................OFF

6. Vent Blower ..............................................................................HIGH

7. Left Bleed Air Valve..........................................PNEU & ENVIR OFF

If Smoke Decreases:

8. Continue operation with left bleed air off.

If Smoke Does Not Decrease:

9. Left Bleed Air Valve .................................................................OPEN

10. Right Bleed Air Valve .......................................PNEU & ENVIR OFF

If Smoke Decreases:

11. Continue operation with right bleed air off.

If Smoke Persists:

12. Bleed Air Valves .............................................................ENVIR OFF

13. Cabin Pressurization ...............................................................DUMP

14. Storm Window (if required) ......................OPEN BELOW 13,500 FT



6

FEBRUARY 2007E-13P/N 130-590031-73D9

AIRSTAIR DOOR/CARGODOOR UNLOCKED

Do not attempt to check the security of the airstair dooror cargo door in flight. Remain as far from the door aspossible with seatbelts securely fastened.

If The [DOOR UNLOCKED] Illuminates, Or If An Unlatched AirstairDoor/Cargo Door Is Suspected:

1. All Occupants ..................................SEATED WITH SEAT BELTSSECURELY FASTENED

2. Cabin Sign ..................................................................................FSB

3. Cabin Differential Pressure..............REDUCE TO LOWEST VALUEPRACTICAL (zero preferred)

a. Descend and/or

b. Select higher cabin altitude setting.

4. Oxygen......................................................................AS REQUIRED


EMERGENCY DESCENT

1. Power Levers ...........................................................................IDLE

2. Prop Levers .........................................................FULL FORWARD

3. Flaps (202 knots maximum) .......................................APPROACH

4. Landing Gear (184 knots maximum) ..................................DOWN

5. Airspeed .....................................................184 KNOTS MAXIMUM

WARNING

7


OCTOBER 2004 E-14 P/N 130-590031-73D6

DOORUNLOCKED

EMERGENCY LANDING

1. Approach Speed (VREF).....................................................CONFIRM

2. Cabin Sign

a. Standard Configuration .........................................NO SMK/FSB

b. No Smoking Configuration....................................................FSB

3. Autofeather ................................................................................ARM

4. Flaps..............................................................................APPROACH

5. Landing Gear..........................................................................DOWN

6. Exterior and Interior Lights........................................AS REQUIRED

7. Radar ........................................................................AS REQUIRED

8. Surface Deice ...........................................................AS REQUIRED

When Landing Assured:

9. Pressurization .........................................................................DUMP

10. Flaps.......................................................................................DOWN

11. Airspeed......................................................................................VREF

12. Yaw Damp..................................................................................OFF

13. Prop Levers ...........................................................FULL FORWARD

14. Power Levers.............................................................................IDLE

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[EXTINGUISHER PUSH] & [CLOSED] – ILLUMINATED

19. Master Switch (gang bar) ...........................................................OFF

20. Battery Bus......................................................................EMER OFF


7

OCTOBER 2000E-15P/N 130-590031-73D1


15,000 (6804)

14,000 (6350)

13,000 (5897)

12,000 (5443)

11,000 (4989)

10,000 (4536)

VREF – KNOTS

109

105

102

100

100

100


GLIDE

1. Landing Gear .........................................................................UP

2. Flaps .......................................................................................UP

Do not feather second engine propeller if a No StarterAssist Air Start is to be conducted. Air starts with awindmilling propeller will result in lower starting tem-peratures. Refer to Abnormal Procedures for Air Startprocedures.

3. Prop Levers ................................................................FEATHERED

4. Airspeed........................................................................135 KNOTS

5. Glide Ratio..............2.3 nautical miles for each 1000 feet of altitude.Decrease by 0.2 nautical milesfor each 10 knots of headwind

WARNING

8


OCTOBER 2000 E-16 P/N 130-590031-73D1

ELECTRICAL

SINGLE INVERTER FAILURE

1. AC Bus Circuit Breakers ....................................................CHECK

If Circuit Breaker is Not Tripped:

2. Failed Inverter.......................................SELECT BUS TRANSFER

If Circuit Breaker Is Tripped:

3. Circuit Breaker .....................................................................RESET

4. If Circuit Breaker Trips Again..................................DO NOT RESET

5. Inverter Bus Transfer.......................................DO NOT TRANSFER

NOTE

Serials FL-111 Thru FL-119, FL-121:If the torquemeter on the side of the tripped AC Buscircuit breaker is also inoperative, set engine fuel flowto match the fuel flow on the side of the operativetorque meter. Observe ITT limits.

DUAL INVERTER FAILURE

1. Attitude/Heading Control .............USE BACKUP INSTRUMENTS

2. AC Bus Circuit Breakers (if tripped) ..................................RESET

3. If Circuit Breakers Trip Again..................................DO NOT RESET

Serials FL-111 Thru FL-119, FL-121:


5. Power...............SET FUEL FLOW PER CRUISE POWER TABLES.IF MANEUVERING, DO NOT EXCEED 500

POUNDS PER HOUR. OBSERVE ITT LIMITS.


8

FEBRUARY 1999E-17P/N 130-590031-73D

#1 AC BUS #2 AC BUSOR

#1 AC BUS #2 AC BUS&

DUAL GENERATOR FAILURE

1. Instrument Emergency Lights (if required)..............................ON

2. Generators .........................................................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


8. Pressurization .............................................................................SET

9. Altimeter......................................................................................SET

10. Cabin Sign .....................................VERBAL BRIEFING REQUIRED

11. Autofeather ................................................................................ARM

12. Fuel Balance .........................................................................CHECK

13. VREF + 20 ......................................................................DETERMINE

14. Environmental Bleed Air ............................................................LOW

15. Flaps .............................................................................................UP

9


FEBRUARY 1999 E-18 P/N 130-590031-73D

L DC GEN R DC GEN&


15,000 (6804)

14,000 (6350)

13,000 (5897)

12,000 (5443)

11,000 (4989)

10,000 (4536)

(VREF + 20)-KNOTS

129

125

122

120

120

120

LANDING APPROACH SPEED—FLAPS UP

DUAL GENERATOR FAILURE(Cont)

16. Landing Gear ..................................................EXTEND MANUALLY

17. Taxi Light ..................................................................AS REQUIRED


When Landing Is Assured:

19. Airspeed ................................................................VREF + 20 KNOTS

20. Yaw Damp..................................................................................OFF



After Touchdown:

23. Power Levers ...................................GROUND FINE OR REVERSE


LOAD MANAGEMENT WITH ADUAL GENERATOR FAILURE

Do not place the GEN TIES switch in the MAN CLOSEposition. This action reconnects the left and right gen-erator bus loads to the battery, severely limiting batteryduration.

After a dual generator failure, a charged battery will discharge in thefollowing times:

Battery Discharge Rate–Amps Time to Discharge–Min

60 2750 3240 4030 5420 8110 162

WARNING


9

FEBRUARY 1999E-19P/N 130-590031-73D

L DC GEN R DC GEN&

PILOT NOTES

10


FEBRUARY 1999 E-20 P/N 130-590031-73D

FLIGHT CONTROLS

UNSCHEDULED ELECTRIC PITCH TRIM ACTIVATION

1. Airplane Attitude............MAINTAIN USING ELEVATOR CONTROL

2. AP/Trim Disconnect...........................................DEPRESS FULLY[PITCH TRIM OFF] – ILLUMINATED

3. Manually retrim airplane.

4. Pitch Trim ...................................................................................OFF

UNSCHEDULED RUDDER BOOST ACTIVATION

Rudder boost operation without a large variation of power between theengines indicates a failure of the system.

1. AP/Trim Disconnect .............................DEPRESS TO 1ST LEVELAND HOLD

2. Rudder Boost............................................................................OFF

If Condition Persists:

3. Rudder Boost Circuit Breaker...............................................PULL

4. Perform normal landing.


10

FEBRUARY 1999E-21P/N 130-590031-73D

PILOT NOTES

11


FEBRUARY 1999 E-22 P/N 130-590031-73D

ENVIRONMENTAL SYSTEMS

USE OF OXYGEN

Beards and mustaches should be carefully trimmed sothat they will not interfere with the proper sealing of anoxygen mask. The fit of the oxygen mask around thebeard or mustache should be checked on the ground forproper sealing. Studies conducted by the military and theFAA conclude that oxygen masks do not seal overbeards and mustaches. Hats and “ear-muff” type head-sets must be removed prior to donning crew oxygenmasks. Headsets and eyeglasses worn by crew mem-bers may interfere with quick-donning capabilities.

The following table sets forth the average time of usefulconsciousness (TUC) (time from onset of hypoxia untilloss of effective performance) at various altitudes. Rapiddecompressions can reduce these times to 1/3 – 1/2 oftheir original value.

Crew

1. Oxygen Mask(s) .......................................................................DON

2. Headset(s)...............................DON, OR AUDIO SPEAKER(S) ON


4. Oxygen Duration ...............................................................CONFIRM(refer to Oxygen Duration in Normal Procedures)

To Discontinue Use:

5. Oxygen Mask(s) ................RETURN TO OVERHEAD CONTAINER

6. Mic Switch(es) ....................................................................NORMAL

WARNING

WARNING


11

OCTOBER 2000E-23P/N 130-590031-73D1

Cabin Pressure Altitude

35,000 Feet

30,000 Feet

25,000 Feet

22,000 Feet

12–18,000 Feet

TUC

1/2–1 Minute

1–2 Minutes

3–5 Minutes

5–10 Minutes

30 Minutes or more

OCTOBER 2000 E-24 P/N 130-590031-73D1

USE OF OXYGEN (CONT)

Passengers

The highest recommended cabin altitude for sustainedflight is 25,000 feet.

1. Passenger Manual Drop-Out..............................................PULL ON[PASS OXYGEN ON] – ILLUMINATED

2. Lanyard Pin For Each Mask Used ...................................PULL OUT

3. Mask ..........................................................................................DON


To Discontinue Use:

5. Passenger Manual Drop-Out...........................................PUSH OFF

6. Lanyard Pin ..........................................................................INSERT

7. Mask ................................................RETURN TO COMPARTMENT

8. Compartment Cover (if cabin altitude isbelow 10,000 feet) .................................................................CLOSE

First Aid Oxygen

1. Oxygen Compartment................................PULL COVER TO OPEN

2. ON/OFF Valve..............................................................................ON

3. Mask ..........................................................................................DON

To Discontinue Use:

4. ON/OFF Valve ............................................................................OFF

5. Mask ................................................RETURN TO COMPARTMENT

6. Compartment Cover ..............................................................CLOSE

WARNING

12


FEBRUARY 1999E-25P/N 130-590031-73D

PRESSURIZATION LOSS

1. Oxygen Mask(s) .......................................................................DON

2. Headset(s)...............................DON, OR AUDIO SPEAKER(S) ON


4. Passenger Manual Drop-Out...........................................PULL ON[PASS OXYGEN ON] – ILLUMINATED

5. Descend...................................................................AS REQUIRED

6. Passengers.................................PULL LANYARD PIN, DON MASK

The highest recommended cabin altitude for sustainedflight is 25,000 feet.

7. Range ......................DETERMINE FOR FINAL CRUISE ALTITUDE


HIGH DIFFERENTIAL PRESSURE

1. Bleed Air Valves ...........................................................ENVIR OFF

2. Oxygen (crew and passengers).............................AS REQUIRED

3. Descend...................................................................AS REQUIRED

AUTO-DEPLOYMENT OXYGEN SYSTEM FAILURE

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

4. Passenger Manual Drop-Out...........................................PUSH OFF

WARNING

12

CABIN ALT HI

CABIN DIFF HI

CABIN ALT HI PASS OXYGEN ON– ILLUMINATED & – EXTINGUISHED


FEBRUARY 1999 E-26 P/N 130-590031-73D


BLEED AIR FAIL

Illumination of an annunciator in flight indicates a possible rupture of ableed air line aft of the engine firewall.

1. Bleed Air Valve (affected engine) .................PNEU & ENVIR OFF[L BL AIR OFF] or [R BL AIR OFF] – ILLUMINATED

2. Cabin VSI and Pneumatic Pressure .................................MONITOR


L BLEED FAIL R BLEED FAILOR

13

EMERGENCY EXIT

Escape Hatch Handle..........................................................................PULL


FEBRUARY 1999E-27P/N 130-590031-73D

13

PILOT NOTES


FEBRUARY 1999 E-28 P/N 130-590031-73D

14

SPINS

Intentional spins are prohibited. If an unintentional spin is encountered,perform the following procedure IMMEDIATELY—THE LONGER THEDELAY, THE MORE DIFFICULT RECOVERY WILL BECOME. Steps 1through 3 should be done AGGRESSIVELY and SIMULTANEOUSLY.The full forward position of the control column may be reduced slightly, ifrequired, to prevent the airplane from exceeding a 90° nose down (invert-ed) attitude.

1. Control Column............FULL FORWARD, AILERONS NEUTRAL

2. Full Rudder ........................OPPOSITE THE DIRECTION OF SPIN

3. Power Levers ...........................................................................IDLE

4 Rudder ..........................NEUTRALIZE WHEN ROTATION STOPS

5. Execute a smooth pullout.


JULY 2002E-29P/N 130-590031-73D3

14

PILOT NOTES


FEBRUARY 1999 E-30 P/N 130-590031-73D

FEBRUARY 1999A-iP/N 130-590031-73D

L DC GEN R DC GEN

R FUEL QTY

L GEN TIE OPEN

BAT TIE OPEN

L ENG ICE FAIL

PROP GND SOL

DUCTOVERTEMP

L CHIP DETECT

R ENG ICE FAIL

7

HYD FLUID LOW

R CHIP DETECT

L NO FUEL XFR R NO FUEL XFR

6

10

3

4

5

11

6

4

5

13

6

13

R GEN TIE OPEN

L FUEL QTY

6

BATTERYCHARGE

6

7

7


PITCH TRIM OFF

9

FEBRUARY 1999 A-ii P/N 130-590031-73D


AUGUST 2003A-1P/N 130-590031-73D4

AB

NO

RM

AL

ABNORMAL PROCEDURES

AIR STARTSTARTER ASSIST (PROPELLER FEATHERED OR WINDMILLING)

NO STARTER ASSIST (PROPELLER FEATHERED OR WINDMILLING)LANDINGFLAPS UP LANDING

ONE-ENGINE-INOPERATIVE APPROACH AND LANDINGONE-ENGINE-INOPERATIVE GO-AROUNDPROPELLER GROUND IDLE STOP SOLENOID FAILURE

ENGINE OIL SYSTEMLOW OIL PRESSURE INDICATIONHIGH OIL PRESSURE INDICATIONCHIP DETECT

FUEL SYSTEMCROSSFEED (ONE-ENGINE-INOPERATIVE OPERATION)NO FUEL TRANSFER

FUEL QUANTITY LOWELECTRICAL SYSTEMSINGLE GENERATOR FAILUREBATTERY CHARGE RATE

GENERATOR TIE OPENBOTH GENERATOR TIES OPENBATTERY TIE OPENCIRCUIT BREAKER TRIPPED

AVIONICS MASTER POWER SWITCH FAILURE

FLIGHT CONTROLSYAW DAMP/RUDDER BOOST SYSTEM INOPERATIVEELECTRIC PITCH TRIM INOPERATIVE

LANDING GEAR SYSTEMHYDRAULIC FLUID LOWLANDING GEAR MANUAL EXTENSION

ENVIRONMENTAL SYSTEMSDUCT OVERTEMPERATURE

ICE PROTECTION SYSTEMSELECTROTHERMAL PROPELLER DEICE (AUTO SYSTEM)ELECTROTHERMAL PROPELLER DEICE (MANUAL SYSTEM)

ENGINE ANTI-ICE FAILURESURFACE DEICE FAILURESTATIC AIR SYSTEMPILOT’S ALTERNATE STATIC AIR SOURCE

CRACKED OR SHATTERED WINDSHIELDCRACK IN ANY SIDE WINDOW (COCKPIT OR CABIN)

SEVERE ICING CONDITIONS(ALTERNATE METHOD OF COMPLIANCE WITH FAA AD 98-04-24)

1

2

3

5

6

7

4

9

10

11

12

13

14


8

15

PILOT NOTES


FEBRUARY 1999 A-2 P/N 130-590031-73D

1

All airspeeds quoted in this section are Indicated Airspeeds (IAS) andassume zero instrument error.

Closed [BRACKETS] in this section denote annunciator(s)

AIR START

STARTER ASSIST(PROPELLER FEATHERED OR WINDMILLING)

Air start using the STARTER ASSIST procedures maymomentarily cause the loss of attitude display on ElectronicFlight Instrument System (EFIS) equipped airplanes, andlead to premature system failures. IF FLIGHT CONDI-TIONS DO NOT PERMIT THE TEMPORARY LOSS OFATTITUDE REFERENCE, CONDUCT AIR STARTUSING THE NO STARTER ASSIST PROCEDURES.

1. Cabin Temp Mode ......................................................................OFF

2. Vent Blower .............................................................................AUTO

3. Bleed Air Valve (inoperative engine) ..............................ENVIR OFF

4. Aft Blower ...................................................................................OFF

5. Radar....................................................................STANDBY or OFF

6. Furnishings .................................................................................OFF

7. EFIS Power (if installed/if conditions permit) ..............................OFF

8. Power Lever...............................................................................IDLE

9. Prop Lever ........................................................................LOW RPM

10. Condition Lever.........................................................FUEL CUTOFF

11. Firewall Fuel Valve ..................................................................OPEN[EXTINGUISHER PUSH] & [CLOSED] – EXTINGUISHED

12. Ignition and Engine Start ..............................................................ON[IGNITION ON] – ILLUMINATED

13. Condition Lever (10% N1 or above)..................................LOW IDLE

14. ITT and N1 .......................................MONITOR (1000° C maximum)

15. Ignition and Engine Start (N1 above 50%)..................................OFF

16. Prop Lever ................................................................AS REQUIRED

17. Power Lever..............................................................AS REQUIRED

18. Generator ............................................................RESET, THEN ON

19. EFIS Power (if installed)...............................................................ON

20. Engine Auto-Ignition..................................................AS REQUIRED

21. Electrical Equipment .................................................AS REQUIRED

22. Aft Blower..................................................................AS REQUIRED

23. Bleed Air Valve ........................................................................OPEN

24. Cabin Temp Mode ...................................................................AUTO

WARNING


1

FEBRUARY 2007A-3P/N 130-590031-73D9

NO STARTER ASSIST(PROPELLER FEATHERED OR WINDMILLING)

1. Power Lever...............................................................................IDLE

2. Prop Lever

a. For Prop Feathered Airstarts......................................LOW RPM

b. For Prop Windmilling Airstarts.........................FULL FORWARDCONFIRM 1700 RPM

3. Condition Lever.........................................................FUEL CUTOFF

4. Firewall Fuel Valve ..................................................................OPEN[EXTINGUISHER PUSH] & [CLOSED] – EXTINGUISHED

5. Engine Anti-ice ...........................................................................OFF

6. Generator (inoperative engine)...................................................OFF

7. Bleed Air Valve (inoperative engine) ..............................ENVIR OFF

8. Airspeed ........................................................140 KNOTS MINIMUM

9. Altitude............................................................BELOW 20,000 FEET

10. Engine N1 ..................................................................10% MINIMUM

11. Engine Auto-Ignition ..................................................................ARM[IGNITION ON] – ILLUMINATED

12. Condition Lever ................................................................LOW IDLE

13. ITT and N1 ........................................MONITOR (1000°C maximum)

14. Power (after ITT has peaked) ...................................AS REQUIRED

15. Generator ............................................................RESET, THEN ON

16. Engine Auto-Ignition..................................................AS REQUIRED

17. Bleed Air Valve ........................................................................OPEN

18. Electrical Equipment .................................................AS REQUIRED

2


FEBRUARY 2007 A-4 P/N 130-590031-73D9

LANDING

FLAPS UP LANDING

1. Approach Speed (VREF+ 20 Knots) ...................................CONFIRM

2. Pressurization .......................................................................CHECK

3. Cabin Sign



4. Autofeather ................................................................................ARM

5. Flaps .............................................................................................UP






When Landing Assured:


12 Yaw Damp..................................................................................OFF



After Touchdown:

15. Power Levers............................LIFT AND SELECT GROUND FINE



2

FEBRUARY 1999A-5P/N 130-590031-73D

LANDING APPROACH SPEED - FLAPS UP

LANDING WT LBS (KGS) (VREF + 20)-KNOTS

15,000 (6804) 129

14,000 (6350) 125

13,000 (5897) 122

12,000 (5443) 120

11,000 (4989) 120

10,000 (4536) 120

ONE-ENGINE-INOPERATIVEAPPROACH AND LANDING

1. Approach Speed (VREF).....................................................CONFIRM

2. Pressurization .......................................................................CHECK

3. Cabin Sign



4. Fuel Balance .........................................................................CHECK




8. Flaps..............................................................................APPROACH



11. Prop Lever.............................................................FULL FORWARD


When It Is Certain There Is No Possibility Of Go-Around:

13. Flaps.......................................................................................DOWN

14. Airspeed......................................................................................VREF

15. Execute Normal Landing

Care must be exercised when using single-engineground fine on surfaces with reduced traction. Do notuse reverse thrust with one engine inoperative.

WARNING

3


FEBRUARY 1999 A-6 P/N 130-590031-73D


LANDING WT LBS (KGS) VREF – KNOTS

15,000 (6804) 109

14,000 (6350) 105

13,000 (5897) 102

12,000 (5443) 100

11,000 (4989) 100

10,000 (4536) 100

ONE-ENGINE-INOPERATIVE GO-AROUND

1. Power ........................................................MAXIMUM ALLOWABLE

2. Landing Gear ................................................................................UP

3. Airspeed................................................INCREASE TO 125 KNOTS

4. Flaps .............................................................................................UP

PROPELLER GROUND IDLE STOPSOLENOID FAILURE

(FL-115 THRU FL-382, EXCEPT FL-381; FM-10 AND FM-11)

1. PROP GOV TEST Circuit Breaker............................................PULL

2. [PROP GND SOL] Extinguished .......FLY A NORMAL APPROACH.PLAN ON SLIGHTLY LONGER

LANDING DISTANCES.

3. [PROP GND SOL] Illuminated ........FLY A SHALLOW, POWER ONAPPROACH AT 1450 RPM. DO NOT

REDUCE POWER UNTIL IN THE FLARE.PLAN ON SLIGHTLY LONGER

LANDING DISTANCES.


3

FEBRUARY 2004A-7P/N 130-590031-73D5

PROP GND SOL

PILOT NOTES

4


FEBRUARY 1999 A-8 P/N 130-590031-73D

ENGINE OIL SYSTEM

LOW OIL PRESSURE INDICATION

(60–90 PSI, YELLOW ARC)

1. Do not exceed 62% torque.

2. Correct fault prior to next flight.

HIGH OIL PRESSURE INDICATION

(ABOVE 135 PSI, BUT NOT EXCEEDING 200 PSI)

Ground operation, excluding transients during cold starts:

• Correct fault prior to flight.

In Flight:

1. Continue flight to destination at pilot’s discretion.

2. Correct fault prior to next flight.

CHIP DETECT

1. Engine Instruments...........................................................MONITOR

2. If Abnormal ........SHUT DOWN ENGINE AT PILOT’S DISCRETION


4

FEBRUARY 2004A-9P/N 130-590031-73D5

L CHIP DETECT R CHIP DETECTOR

PILOT NOTES

5


FEBRUARY 1999 A-10 P/N 130-590031-73D

FUEL SYSTEM

CROSSFEED(ONE-ENGINE-INOPERATIVE OPERATION)

1. Standby Pumps ..........................................................................OFF

2. Aux Transfer Switches.............................................................AUTO

3. Fuel Crossfeed....................................LEFT or RIGHT (as required)

a. [FUEL CROSSFEED] ..........................................ILLUMINATED

b. [L FUEL PRES LO] & [R FUEL PRES LO] ..............EXTINGUISHED(annunciator will be illuminated on the inoperativeengine side if the firewall fuel valve is left closed)

Aux Transfer switch must be in AUTO position on sidebeing crossfeed. If the firewall valve is closed, the aux-iliary fuel supply will not be available (usable), and thefuel pressure annunciator will remain illuminated on theside supplying fuel.

4. Fuel Quantity ....................................................................MONITOR(max fuel imbalance - 300 lbs)

If Aux Fuel From Inoperative Side Is Required:

5. Firewall Fuel Valve (inoperative engine) .................................OPEN

To Discontinue Crossfeed:

6. Fuel Crossfeed ...........................................................................OFF

NO FUEL TRANSFER

1. Aux Transfer (same side)................................................OVERRIDE

2. Fuel Quantity ..............MONITOR TO CONFIRM FUEL TRANSFER

WARNING


5

FEBRUARY 1999A-11P/N 130-590031-73D

L NO FUEL XFR R NO FUEL XFROR

FUEL QUANTITY LOW

1. Fuel Quantity.........................................................................CHECK

If Low Fuel Quantity Is Confirmed By Fuel Gage:

2. Standby Pump..............................................................................ON

3. Fuel Quantity ....................................................................MONITOR


6


FEBRUARY 1999 A-12 P/N 130-590031-73D

L FUEL QTY R FUEL QTYOR

ELECTRICAL SYSTEM

SINGLE GENERATOR FAILURE

1. Generator .............................................................RESET, THEN ON

If Generator Will Not Reset:

2. Generator ....................................................................................OFF

3. Electrical Load...................................................................MONITOR

BATTERY CHARGE RATE(AIRPLANES PRIOR TO FL-215 AND FM-10)

Ground Operation:

1. Illumination of the [BATTERY CHARGE] indicates an above-normal charge current.

2. [BATTERY CHARGE] should extinguish within 5 minutes after abattery start.

3. [BATTERY CHARGE] should be extinguished when charge currentis 6 amps or less.

4. Check battery ammeter every 90 seconds for decreasing charge current.

5. No decrease in charge current indicates an unsatisfactory condition.

6. Do not take off with the [BATTERY CHARGE] illuminated withoutconsidering the following:

a. The battery ammeter must indicate a decreasing charge currentto ensure that the battery is not in a state of thermal runaway.

b. The [BATTERY CHARGE] must be extinguished in order tomeet the battery duration times noted in the Dual GeneratorEmergency Procedure.

In Flight:

In-Flight Illumination Of [BATTERY CHARGE] Indicates A PossibleBattery Malfunction.

1. Battery Ammeter ...............................................................MONITOR

If Battery Charge Current Is Decreasing:

2. Battery Ammeter......................................CONTINUE TO MONITOR

3. [BATTERY CHARGE] .............................................EXTINGUISHED(when charge currentdrops below 6 amps)

If Battery Charge Current Is Not Decreasing:

4. Battery.........................................................................................OFF[BAT TIE OPEN] – ILLUMINATED

5. [BATTERY CHARGE] Extinguished ..........................CONTINUE TODESTINATION

If [BATTERY CHARGE] Is Illuminated, and Battery Ammeter ContinuesTo Indicate A Charge Current:

6. GEN TIES................................................................................OPEN



6

OCTOBER 2004A-13P/N 130-590031-73D6

L DC GEN R DC GENOR

BATTERYCHARGE

GENERATOR TIE OPEN

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

BOTH GENERATOR TIES OPEN

1. Gen Ties .......................................................................MAN CLOSE[MAN TIES CLOSE] – ILLUMINATED

[L GEN TIE OPEN] & [R GEN TIE OPEN] – EXTINGUISHED

If Gen Ties Do Not Close:

2. Bus Sense Switch..................................................................RESET[L GEN TIE OPEN] & [R GEN TIE OPEN] – EXTINGUISHED

If Gen Ties do not close, center bus will be powered only by the battery,eventually depleting the battery.

3. No. 1 Inverter .........................................................BUS TRANSFER

4. Center Bus Equipment ..........................................OFF (as required)

(Equipment Powered By The Center Bus = Condenser Blower, ManualProp Deice, Beacons, Ice Lights, Taxi Light, Landing Gear Motor)

If Battery Is Depleted:

5. Landing Gear ..................................................EXTEND MANUALLY

7


FEBRUARY 1999 A-14 P/N 130-590031-73D

L GEN TIE OPEN R GEN TIE OPENOR

L GEN TIE OPEN R GEN TIE OPEN&

BATTERY TIE OPEN

1. Center Bus Voltage...........................................................MONITOR

If Center Bus Voltage Is Normal (27.5 - 29 Volts)

2. Bus Sense Switch..................................................................RESET[BAT TIE OPEN] – EXTINGUISHED

If Center Bus Voltage Is Zero:

3. Gen Ties ..................................................................................OPEN[L GEN TIE OPEN] & [R GEN TIE OPEN] – ILLUMINATED

4. Landing Gear Relay Circuit Breaker .........................................PULL

NOTE

Battery will not charge.Systems powered by the center bus will not be operational.Landing gear will have to be manually extended.

CIRCUIT BREAKER TRIPPED

1. Nonessential Circuit .............................DO NOT RESET IN FLIGHT

2. Essential Circuit (necessary for continued safe flight):

a. Circuit Breaker (after allowing to cool for a minimum of 10 seconds) ........................PUSH TO RESET

If Circuit Breaker Trips Again:

b Circuit Breaker..................................................DO NOT RESET


7

OCTOBER 2004A-15P/N 130-590031-73D6

BAT TIE OPEN

PILOT NOTES


FEBRUARY 1999 A-16 P/N 130-590031-73D

8

AVIONICS MASTER POWER

SWITCH FAILURE

If The Avionics Master Pwr Switch Fails To Operate In The On Position:

• Avionics Master Circuit Breaker ....................................................PULL


FEBRUARY 1999A-17P/N 130-590031-73D

8

PILOT NOTES


FEBRUARY 1999 A-18 P/N 130-590031-73D

9

FLIGHT CONTROLS

YAW DAMP/RUDDER BOOST SYSTEM INOPERATIVE

1. Descend to 5000 feet MSL or below (if conditions permit). (If dualaft body strakes are installed, refer to STC Supplement 91-111.)

2. Single engine rudder forces may exceed 150 Ibs (68 kg).

ELECTRIC PITCH TRIM INOPERATIVE

1. Electric Pitch Trim ....................................................OFF, THEN ON

2. [PITCH TRIM OFF] .................................................EXTINGUISHED

If [PITCH TRIM OFF] Remains Illuminated:

3. Electric Pitch Trim.......................................................................OFF

4. Manually trim airplane


OCTOBER 2004A-19P/N 130-590031-73D6

PITCH TRIMOFF

9

PILOT NOTES


FEBRUARY 1999 A-20 P/N 130-590031-73D

10

LANDING GEAR SYSTEM

HYDRAULIC FLUID LOW

If The [HYD FLUID LOW] 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 procedures.

LANDING GEAR MANUAL EXTENSION

If The Landing Gear Fails To Extend After Placing The Landing GearControl Down, Perform The Following:

1. Landing Gear Relay Circuit Breaker (pilot’s right subpanel).....PULL2. Landing Gear Control ............................................... CONFIRM DN3. Alternate Extension Handle ...........................UNSTOW AND PUMP

a. Pump handle up and down until the three green gear-downannunciators are illuminated.

b. While pumping, do not lower handle to the level of the securingclip as this will result in loss of pressure.

If All Three Green Gear-Down Annunciators Are Illuminated:4. Alternate Extension Handle ....................................................STOW 5. Landing Gear Controls ......................................DO NOT ACTIVATE

a. The Landing Gear Control and the Landing Gear Relay CircuitBreaker MUST NOT BE ACTIVATED.

b. The landing gear should be considered UNSAFE until the air-plane is on jacks and the system has been cycled and checked.

If One Or More Green Gear-Down Annunciators Do Not Illuminate ForAny Reason And A Decision Is Made To Land In This Condition:

6. Alternate Extension Handle...........................CONTINUE PUMPING

a. Continue to pump the handle until maximum resistance is felt.

b. When pumping is complete, leave handle at the top of thestroke. DO NOT LOWER AND STOW.

Prior To Landing:7. Alternate Extension Handle.........................................PUMP AGAIN

a. Pump the handle again until maximum resistance is felt.

b. When pumping is complete, leave handle at the top of thestroke. DO NOT LOWER AND STOW.

After Landing:8. Alternate Extension Handle.............................PUMP AGAIN WHEN

CONDITIONS PERMIT

a. Pump the handle again, when conditions permit, to maintainhydraulic pressure until the gear can be mechanically secured.

b. DO NOT STOW HANDLE.

c. DO NOT ACTIVATE THE LANDING GEAR CONTROL ORTHE LANDING GEAR RELAY CIRCUIT BREAKER.

d. The landing gear should be considered UNLOCKED until the air-plane is on jacks and the system has been cycled and checked.


OCTOBER 2004A-21P/N 130-590031-73D6

HYD FLUID LOW

10

PILOT NOTES


FEBRUARY 1999 A-22 P/N 130-590031-73D

11

ENVIRONMENTAL SYSTEMS

DUCT OVERTEMPERATURE

1. Electric Heat ...............................................................................OFF

2. Vent Blower ..............................................................................HIGH

3. Cabin/Cockpit Air ........PUSH TO INCREASE AIRFLOW TO CABIN

If Condition Persists:

4. Cabin Temp Mode...........................................................MAN HEAT

5. Manual Temp.....................................................DECR (60 seconds)

If The Condition Persists Further:

6. Left Bleed Air Valve ........................................................ENVIR OFF

If The [DUCT OVERTEMP] Does Not Extinguish After 2 Minutes:

7. Right Bleed Air Valve......................................................ENVIR OFF

8. Oxygen......................................................................AS REQUIRED

9. Descend....................................................................AS REQUIRED


FEBRUARY 1999A-23P/N 130-590031-73D

DUCTOVERTEMP

11

PILOT NOTES


FEBRUARY 1999 A-24 P/N 130-590031-73D

12

ICE PROTECTION SYSTEMS

ELECTROTHERMAL PROPELLER DEICE(AUTO SYSTEM)

Abnormal Readings on Deice Ammeter:(Normal Operation: 26 to 32 amps)

1. Zero amps:

a. Automatic Prop Deice..............................................CHECK, ON

b. If OFF, reposition to ON after 30 seconds

c. If ON with zero amps reading, system is inoperative; positionthe switch to OFF.

d. Use manual backup system.

2. Below 26 amps:

a. Continue operation.

b. If propeller imbalance occurs, increase RPM briefly to aid in iceremoval.

3. Over 32 amps:

a. If the Auto Prop Deice circuit breaker switch does not trip,continue operation.

b. If propeller imbalance occurs, increase RPM briefly to aid in iceremoval.

c. If the Auto Prop Deice circuit breaker switch trips, use manualsystem. Monitor loadmeters to ensure normal operation. (Anapproximate 10% increase on each meter is normal.)

d. If the Prop Deice Control circuit breaker trips, or the loadmetersindicate the manual system is not working, (no increase or anexcessive increase in current drain) avoid icing conditions.

ELECTROTHERMAL PROPELLER DEICE(MANUAL SYSTEM)

1. Manual Prop Deice.............................MANUAL FOR 90 SECONDS

2. Loadmeters ..................................MONITOR FOR SMALL NEEDLEDEFLECTION (approx. 10%)

3. Repeat as required.


FEBRUARY 1999A-25P/N 130-590031-73D

12

FEBRUARY 1999 A-26 P/N 130-590031-73D

ENGINE ANTI-ICE FAILURE

1. Engine Anti-Ice Actuator....................SELECT OTHER ACTUATOR

If [ENG ICE FAIL] Does Not Extinguish:

2. Exit icing conditions

3. Assume engine anti-ice is ON for performance calculations.

SURFACE DEICE FAILURE

1. Surface Deice ......................................ATTEMPT MANUAL CYCLE

If [WING DEICE] or [TAIL DEICE] Do Not Illuminate, Or If Boot InflationCannot Be Confirmed Visually:

2. Exit icing conditions

3. Refer to POH/AFM Section V, PERFORMANCE, for recommendedlanding approach speeds and performance with ice on the airplane.

Intentional stalls are prohibited with a surface deicesystem failure and ice on the airplane.

WARNING


13

L ENG ICE FAIL R ENG ICE FAILOR

FEBRUARY 1999A-27P/N 130-590031-73D

STATIC AIR SYSTEM

PILOT’S ALTERNATE STATIC AIR SOURCE

Whenever Any Obstruction Exists In The Normal Static Air System, OrWhen The Alternate Static Air System Is Desired For Use:

1. Pilot’s Static Air Source ................................................ALTERNATE

2. For Airspeed Calibration and Altimeter Correction, refer toPOH/AFM Section V, PERFORMANCE


13

PILOT NOTES


FEBRUARY 1999 A-28 P/N 130-590031-73D

14

CRACKED OR SHATTERED WINDSHIELD

1. Altitude....................MAINTAIN 25,000 FT OR LESS, IF POSSIBLE

2. Pressurization Controller .......................................................RESET

a. Cruise and Descent..........MAINTAIN A CABIN DIFFERENTIALPRESSURE OF 2.0 TO 4.6 PSI

(A cabin differential pressure of 4.6 psi will produce approxi-mately a 10,500-foot cabin altitude at an airplane altitude of25,000 feet.)

b. Before Landing........................DEPRESSURIZE CABIN PRIOR TO TOUCHDOWN

3. Other In-flight Considerations

a. Visibility through a shattered windshield may be sufficientlyreduced to dictate flying the airplane from the opposite side ofthe cockpit.

b. Precautions should be taken to prevent particles or flakes ofglass from a shattered inner ply of the windshield from interfer-ing with the crew’s vision.

c. A cracked outer windshield ply may damage operating wind-shield wipers.

d. Windshield heat may be inoperative in the area of the crack(s).

e. The structural integrity of the windshield will be maintained.

4. Postflight Considerations ...............SEE SECTION II, LIMITATIONSIN POH/AFM

CRACK IN ANY SIDE WINDOW(COCKPIT OR CABIN)

1. Altitude .....................................................DESCEND IF REQUIRED

a. Descend to an altitude not requiring oxygen, if possible – or

b. Descend to at least 25,000 feet if passengers are on board.

2. Crew and Passengers ........DON OXYGEN MASKS, IF REQUIRED

3. Pressurization Controller..............................RESET AS REQUIRED TO DEPRESSURIZE CABIN

4. Cabin Pressure Switch............................................................DUMP

5. Postflight Considerations ...............SEE SECTION II, LIMITATIONSIN POH/AFM


OCTOBER 2000A-29P/N 130-590031-73D1

14

PILOT NOTES


FEBRUARY 1999 A-30 P/N 130-590031-73D

15


JULY 2002A-31P/N 130-590031-73D3

SEVERE ICING CONDITIONS

(Alternate Method Of Compliance With

FAA AD 98-04-24)

THE FOLLOWING WEATHER CONDITIONS MAY BE CONDUCIVE TOSEVERE IN-FLIGHT ICING:

• Visible Rain At Temperatures Below 0 Degrees Celsius Ambient AirTemperature.

• Droplets That Splash or Splatter On Impact At Temperatures Below 0Degrees Celsius Ambient Air Temperature

PROCEDURES FOR EXITING THE SEVERE ICING ENVIRONMENT

These procedures are applicable to all flight phases from takeoff to landing.Monitor the ambient air temperature. While severe icing may form at temper-atures as cold as -18 degrees Celsius, increased vigilance is warranted attemperatures around freezing with visible moisture present. If the visual cuesspecified in the Limitations Section of the POH/AFM for identifying severeicing conditions are observed, accomplish the following:

1. Immediately request priority handling from Air Traffic Control to facili-tate a route or an altitude change to exit the severe icing conditions inorder to avoid extended exposure to flight conditions more severethan those for which the airplane has been certificated.

2. Avoid abrupt and excessive maneuvering that may exacerbate con-trol difficulties.

3. Do not engage the autopilot.

4. If the autopilot is engaged, hold the control wheel firmly and disen-gage the autopilot.

5. If an unusual roll response or uncommanded roll control movementis observed, reduce the angle-of-attack.

6. Do not extend flaps when holding in icing conditions. Operationwith flaps extended can result in a reduced wing angle-of-attackwith the possibility of ice forming on the upper surface further aft onthe wing than normal, possibly aft of the protected area.

7. If the flaps are extended, do not retract them until the airframe isclear of ice.

8. Report these weather conditions to Air Traffic Control.

15

PILOT NOTES


FEBRUARY 1999 A-32 P/N 130-590031-73D

FEBRUARY 1999P-1P/N 130-590031-73D

PERFORMANCEWIND COMPONENTS.........................................................................................P-3

TAKE-OFF SPEEDS AND FIELD LENGTHS -- FLAPS UP --(A/C AND BLEED AIR ON)SEA LEVEL........................................................................................................................P-41000 FEET.........................................................................................................................P-52000 FEET.........................................................................................................................P-63000 FEET.........................................................................................................................P-74000 FEET.........................................................................................................................P-85000 FEET.........................................................................................................................P-96000 FEET.......................................................................................................................P-107000 FEET.......................................................................................................................P-118000 FEET.......................................................................................................................P-129000 FEET.......................................................................................................................P-1310,000 FEET....................................................................................................................P-14

TAKE-OFF SPEEDS AND FIELD LENGTHS -- FLAPS APPROACH --(A/C AND BLEED AIR ON)SEA LEVEL .....................................................................................................................P-151000 FEET.......................................................................................................................P-162000 FEET.......................................................................................................................P-173000 FEET.......................................................................................................................P-184000 FEET.......................................................................................................................P-195000 FEET.......................................................................................................................P-206000 FEET.......................................................................................................................P-217000 FEET.......................................................................................................................P-228000 FEET.......................................................................................................................P-239000 FEET.......................................................................................................................P-2410,000 FEET....................................................................................................................P-25

ENROUTE

MAXIMUM CRUISE POWER AT 1500 RPM.................................................................P-26

NORMAL CRUISE POWER AT 1500 RPM...................................................................P-27P

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PILOT NOTES

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FEBRUARY 1999 P-2 P/N 130-590031-73D

FEBRUARY 1999P-3P/N 130-590031-73D


WIND COMPONENTS

TAKE-OFF SPEEDS AND FIELD LENGTHS- FLAPS UP(A/C AND BLEED AIR ON)

PRESSURE ALTITUDE: SEA LEVEL


FEBRUARY 1999 P-4 P/N 130-590031-73D

T O OUTSIDE AIR TEMPERATURE – °CWEIGHT ITEM -35 -15 -5 5 15 25 35 45 52

15,000 LBS V1 - KIAS 106 106 106 106 106 106 108 110 111VR - KIAS 109 110 110 110 110 110 111 111 112

6804 KG V2 - KIAS 117 117 117 117 117 117 117 117 117TOFL - FT 3085 3505 3716 3949 4192 4541 5181 5919 6493

14,500 LBS V1 - KIAS 105 104 104 104 104 104 106 108 109VR - KIAS 108 108 108 108 108 109 109 110 110

6577 KG V2 - KIAS 115 115 115 115 115 115 115 115 115TOFL - FT 2884 3278 3483 3693 3903 4253 4847 5522 6033

14,000 LRS V1 - KIAS 103 102 102 102 102 102 104 106 107VR - KIAS 106 106 106 107 107 107 107 108 108

6350 KG V2 - KIAS 114 114 114 114 114 114 114 114 114TOFL - FT 2682 3057 3255 3459 3654 3955 4504 5129 5607

13,500 LBS V1 - KIAS 101 101 100 100 100 101 102 104 105VR - KIAS 105 105 105 105 105 105 106 106 107

6123 KG V2 - KIAS 112 112 112 112 112 112 112 112 112TOFL - FT 2495 2847 3028 3217 3415 3701 4199 4776 5203

13,000 LBS V1 - KIAS 101 99 99 99 99 99 100 102 103VR - KIAS 104 104 104 104 104 104 104 105 105

5897 KG V2 - KIAS 112 111 111 111 111 111 111 110 110TOFL - FT 2373 2692 2857 3026 3203 3458 3910 4430 4843

12,500 LBS V1 - KIAS 100 99 99 98 98 98 99 100 101VR - KIAS 104 104 104 104 104 104 104 104 104

5670 KG V2- KIAS 112 111 111 111 111 111 110 110 109TOFL - FT 2285 2589 2750 2912 3080 3324 3735 4189 4528

12,000 LBS V1 - KIAS 99 98 98 98 97 97 99 100 101VR - KIAS 104 104 104 104 104 104 104 104 104

5443 KG V2- KIAS 112 112 112 111 111 111 110 110 110TOFL - FT 2199 2489 2646 2799 2960 3193 3602 4037 4361

11,500 LBS V1 - KIAS 99 98 97 97 97 97 98 99 100VR - KIAS 104 104 104 104 104 104 104 104 104

5216 KG V2- KIAS 112 112 112 112 111 111 110 110 110TOFL - FT 2113 2389 2538 2688 2841 3061 3450 3879 4197

11,000 LBS V1 - KIAS 98 97 97 96 96 96 97 99 99VR - KIAS 104 104 104 104 104 104 104 104 104

4989 KG V2 - KIAS 112 112 112 112 112 111 111 110 110TOFL- FT 2028 2290 2431 2577 2722 2931 3301 3733 4021

10,500 LBS V1 - KIAS 97 97 96 96 95 95 96 98 994763 KG VR - KIAS 104 104 104 104 104 104 104 104 104

AND V2- KIAS 112 112 112 112 112 111 111 110 110UNDER TOFL - FT 1943 2192 2326 2465 2606 2803 3155 3562 3861

flmmtab3


FEBRUARY 1999P-5P/N 130-590031-73D

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PRESSURE ALTITUDE: 1000 FT

NOTE: INTERSECTION IN SHADED AREAS EXCEED OPERATING LIMITATIONS AND AREPRESENTED AS INTERPOLATION AIDS ONLY.


15,000 LBS V1 - KIAS 106 106 106 106 106 107 108 110 111VR - KIAS 110 110 110 110 110 110 111 112 112

6804 KG V2 - KIAS 117 117 117 117 117 117 117 117 117TOFL-FT 3264 3702 3944 4195 4437 4915 5609 6451 7047

14,500 LBS V1 - KIAS 105 104 104 104 104 105 106 108 109VR - KiAS 108 108 108 108 108 109 109 110 110

6577 KG V2 - KIAS 115 115 115 115 115 115 115 115 115TOFL- FT 3055 3471 3688 3906 4144 4592 5236 6001 6566

14,000LBS V1 - KIAS 103 102 102 102 102 103 104 106 107VR KIAS 106 106 107 107 107 107 108 108 109

6350 KG V2 - KIAS 114 114 114 114 114 114 114 114 1l4TOFL.FT 2844 3243 3455 3657 3873 4292 4889 5590 6091

13,500 LBS V1 - KIAS 101 100 100 100 100 101 102 104 105VR - KIAS 105 105 105 105 105 106 1C6 107 107

6123 KG V2 - KIAS 112 112 112 112 112 112 112 112 112TOFL- FT 2645 3017 3213 3417 3623 3989 4543 5188 5658

13,000 LBS V1 - KIAS 100 99 99 99 98 99 101 102 103VR - KIAS 104 104 104 104 104 104 104 105 105

5897 KG V2 - KIAS 111 111 111 111 111 111 110 110 110TOFL-FT 2508 2848 3023 3206 3393 3733 4226 4821 5239

12,500 LBS V1 - KIAS 100 99 98 98 98 98 99 101 101VR - KIAS 104 104 104 104 104 104 104 104 104

5670 KG V2 - KIAS 112 111 111 111 111 111 110 109 109TOFL- FT 2413 2741 2908 3083 3263 3582 4014 4509 4879

12,000 LBS V1 - KIAS 99 98 98 97 97 98 99 100 101VR - KIAS 104 104 104 104 104 104 104 104 104

5443 KG V2 - KIAS 112 112 111 111 111 111 110 110 109TOFL- FT 2321 2637 2796 2963 3135 3439 3871 4356 4707

11,500 LBS V1 - KIAS 98 97 97 97 96 97 98 100 100VR - KIAS 104 104 104 104 104 104 104 104 104

5216 KG V2 - KIAS 112 112 112 111 111 111 110 110 109TOFL FT 2229 2529 2685 2843 3007 3297 3725 4192 4524

11,000 LBS V1 - KIAS 98 97 96 96 96 96 98 99 100VR - KIAS 104 104 104 104 104 104 104 104 104

4989 KG V2 - KIAS 112 112 112 112 111 111 110 110 110TOFL-FT 2138 2423 2574 2725 2880 3157 3560 4020 4346


AND V2 - KIAS 112 112 112 112 112 111 110 110 110UNDER TOFL-FT 2049 2318 2462 2608 2755 3018 3400 3864 4157

flmmtab3a


OCTOBER 2000 P-6 P/N 130-590031-73D1





15,000 LBS V1 - KIAS 106 106 106 106 106 107 109 111 1t2VR - KIAS 110 110 110 110 110 111 111 112 112

6804 KG V2 - KIAS 117 117 117 117 117 117 117 117 117TOFL - FT 3458 3931 4191 4443 4713 5324 6109 7017 7667

14,500 LBS V1 - KIAS 104 104 104 104 104 105 107 109 110VR - KIAS 108 108 108 108 109 109 110 110 110

6577 KG V2 - KIAS 115 115 115 115 115 115 115 115 115TOFL - FT 3241 3676 3902 4149 4409 4969 5684 6532 7129

14,000 LBS V1 - KIAS 103 102 102 102 102 103 105 107 108VR - KIAS 106 107 107 107 107 107 108 108 109

6350 KG V2 - KIAS 114 114 114 114 114 114 114 114 114TOFL - FT 3014 3443 3654 3878 4108 4637 5295 6068 6630

13,500 LBS V1 - KIAS 101 100 100 100 100 101 103 105 106VR - KIAS 105 105 105 105 105 106 106 107 107

6123 KG V2 - KIAS 112 112 112 112 112 112 112 112 112TOFL - FT 2807 3203 3414 3628 3839 4330 4941 5649 6151

13,000 LBS V1 - KIAS 100 99 99 98 98 99 101 103 104VR - KIAS 104 104 104 104 104 104 105 105 106

5897 KG V2 - KIAS 111 111 111 111 111 111 110 110 110TOFL - FT 2655 3014 3204 3397 3586 4028 4585 5233 5702

12,500 LBS V1 - KIAS 99 98 98 98 98 99 100 101 102VR - KIAS 104 104 104 104 104 104 104 104 104

5670 KG V2 - KIAS 111 111 11 111 111 110 110 109 109TOFL - FT 2554 2899 3080 3267 3448 3854 4336 4878 5297

12,000 LBS V1 - KIAS 98 98 97 97 97 98 99 100 101VR - KIAS 104 104 104 104 104 104 104 104 104

5443 KG V2 - KIAS 112 111 111 111 111 110 110 109 109TOFL- FT 2455 2788 2960 3139 3313 3709 4169 4693 5071

11,500 LBS V1 - KIAS 90 97 97 96 96 97 99 100 100VR - KIAS 104 104 104 104 104 104 104 104 104

5216 KG V2 - KIAS 112 112 111 111 111 111 110 110 109TOFL - FT 2357 2677 2841 3010 3179 3554 4012 4525 4885

11,000 LBS V1 - KIAS 97 96 96 96 95 96 98 99 100VR- KIAS 104 104 104 104 104 104 104 104 104

4989 KG V2 - KIAS 112 112 112 111 111 111 110 110 109TOFL - FT 2259 2566 2722 2883 3044 3400 3855 4348 4689


AND V2 - KIAS 112 112 112 112 111 111 110 110 170UNDER TOFL - FT 2163 2455 2606 2759 2910 3250 3679 4161 4500

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flmmtab3b


OCTOBER 2000P-7P/N 130-590031-73D1





15,000 LBS V1- KIAS 106 106 106 106 106 108 110 112 –VR - KIAS 110 110 110 110 110 111 112 112 –

6804KG V2 - KIAS 117 117 117 117 117 117 117 117 –TOFL - FT 3652 4179 4440 4721 5091 5781 6635 7624 –

14,500 LBS V1 - KIAS 104 104 104 104 104 106 108 I09 111VR - KIAS 108 108 108 109 109 109 110 110 111

6577 KG V2 - KIAS 115 115 115 115 115 115 115 115 115TOFL - FT 3426 3831 4147 4416 4765 5392 6181 7091 7805

14,000 LBS V1 - KIAS 102 102 102 102 102 104 105 107 109VR - KIAS 106 107 107 107 107 108 108 109 105

6350 KG V2 - KIAS 114 114 114 114 114 114 114 114 114TOFL - FT 3199 3644 3876 4115 4453 5024 5740 6589 7242

13,500 LBS V1 - KIAS 101 100 100 100 100 102 193 105 107VR - KIAS 105 105 105 105 106 106 107 107 107

6123 KG V2 - KIAS 112 112 112 112 112 112 112 112 112TOFL - FT 2977 3405 3626 3844 4151 4686 5346 6120 6738

13,000 LBS V1 - KIAS 99 99 98 98 99 100 102 103 104VR - KIAS 104 104 104 104 104 104 105 105 106

5897 KG V2 - KIAS 111 111 111 111 111 110 110 110 110TOFL - FT 2812 3195 3395 3600 3878 4368 4977 5682 6235

12,500 LBS V1 - KIAS 99 98 98 98 98 99 100 101 102VR - KIAS 104 104 104 104 104 104 104 104 1O4

5670 KG V2 - KIAS 111 111 111 111 111 110 110 109 109TOFL - FT 2707 3072 3266 3461 3721 4153 4673 5257 5771

12,000 LBS V1 - KIAS 98 97 97 97 97 98 99 101 101VR - KIAS 104 104 104 104 104 104 104 104 104

5443 KG V2 - KIAS 112 111 111 111 111 110 110 109 109TOFL - FT 2602 2953 3137 3326 3572 3999 4505 5063 5490

11,500 LBS V1 - KIAS 97 97 96 96 96 97 99 100 101VR - KIAS 104 104 104 104 104 104 104 104 104

5216 KG V2 - KIAS 112 111 111 111 111 110 110 109 109TOFL - FT 2496 2834 3009 3191 3425 3842 4323 4865 5290

11,000 LBS V1 - KIAS 97 96 96 95 95 97 98 99 100VR - KIAS 104 104 104 104 104 104 104 104 104

4989 KG V2 - KIAS 112 112 111 111 111 110 110 110 109TOFL - FT 2391 2715 2882 3056 3279 3674 4153 4683 5095



flmmtab3c


OCTOBER 2000 P-8 P/N 130-590031-73D1





15,000 LBS V1 - KIAS 106 106 106 106 107 108 110 112 –VR - KIAS 110 110 110 110 111 111 112 117 –

6804 KG V2 - KIAS 117 117 117 117 117 117 117 117 –TOFL - FT 3879 4429 4719 5016 5531 6300 7219 8326

14,500 LBS V1 - KIAS 104 104 104 104 104 106 108 110 –VR - KIAS 108 108 109 109 109 110 110 111 –

6577 KG V2 - KIAS 115 115 115 115 115 115 115 115 –TOFL - FT 3630 4136 4415 4689 5158 5859 6713 7731 –

14,000 LBS V1 - KIAS 102 102 102 102 103 104 106 108 109VR - KIAS 107 107 107 107 107 108 108 109 109

6350 KG V2 - KIAS 114 114 114 114 114 114 114 114 114TOFL - FT 3399 3866 4114 4370 4819 5454 6244 7177 7960

13,500 LBS V1 - KIAS 100 100 100 100 101 102 104 106 107VR - KIAS 105 105 105 105 106 106 107 107 108

6123 KG V2 - KIAS 112 112 112 112 112 112 112 112 112TOFL - FT 3161 3617 3843 4083 4503 5079 5796 6665 7380

13,000 LBS V1 - KIAS 99 98 98 98 99 100 102 104 105VR - KIAS 104 104 104 104 104 105 105 106 106

5897 KG V2 - KIAS 111 111 111 111 111 110 110 110 110TOFL - FT 2977 3387 3600 3821 4191 4728 5388 6181 6839

12,500 LBS V1 - KIAS 98 98 98 97 98 99 100 102 103VR - KIAS 104 104 104 104 104 104 104 104 104

5670 KG V2 - KIAS 111 111 111 111 110 110 109 109 109TOFL - FT 2864 3258 3461 3671 4022 4490 5039 5732 6324

12,000 LBS V1 - KIAS 98 97 97 97 97 98 100 101 102VR - KIAS 104 104 104 104 104 104 104 104 104

5443 KG V2 - KIAS 111 111 111 111 110 110 110 109 108TOFL - FT 2755 3130 3325 3526 3860 4316 4853 5473 5993

11,500 LBS V1 - KIAS 97 96 96 96 97 98 99 100 101VR - KIAS 104 104 104 104 104 104 104 104 104

5216 KG V2 - KIAS 112 111 111 111 111 110 110 109 109TOFL - FT 2645 3002 3191 3382 3699 4148 4671 5264 5761

11,000 LBS V1 - KIAS 96 96 95 95 96 97 98 100 101VR - KIAS 104 104 104 104 104 104 104 104 104

4989 KG V2 - KIAS 112 111 111 111 111 110 110 108 109TOFL - FT 2535 2875 3056 3239 3538 3978 4477 5051 5531



flmmtab3d


OCTOBER 2000P-9P/N 130-590031-73D1





15,000 LBS V1 - KIAS 106 105 106 106 107 109 111 – –VR - KIAS 110 110 110 110 111 111 112 – –

6804 KG V2 - KIAS 117 117 117 117 117 117 117 – –TOFL - FT 4127 4709 5016 5336 6009 6836 7860 – –

14,500 LBS V1 - KIAS 104 104 104 104 105 107 109 111 –VR - KIAS 108 109 109 109 109 110 110 111 –

6577 KG V2 - KIAS 115 115 115 115 115 115 115 115 –TOFL - FT 3854 4405 4689 4995 5605 6372 7318 8476 –

14,000 LBS V1 - KIAS 102 102 102 102 103 105 107 109 –VR - KIAS 107 107 107 107 108 108 109 109 –

6350 KG V2 - KIAS 114 114 114 114 114 114 114 114 –TOFL - FT 3601 4106 4371 4673 5218 5930 6791 7852 –

13,500 LBS V1 - KIAS 100 100 100 100 101 103 105 107 108VR - KIAS 105 105 105 106 106 106 107 108 108

6123 KG V2 - KIAS 112 112 112 112 112 112 112 112 112TOFL - FT 3364 383 4084 4356 4872 5518 6313 7285 8154

13,000LBS V1 - KIAS 99 98 98 98 99 101 102 104 106VR - KIAS 104 104 104 104 104 105 105 106 106

5897 KG V2 - KIAS 111 111 111 111 110 110 110 110 110TOFL - FT 3158 3592 3822 4067 4545 5128 5848 6752 7529

12,500 LBS V1 - KIAS 98 98 97 97 98 100 102 104 104VR - KIAS 104 104 104 104 104 104 104 104 105

5670 KG V2 - KIAS 111 111 111 111 110 110 109 109 109TOFL - FT 3037 3454 3672 3904 4328 4838 5437 6951 6951

12 000 LBS V1 - KIAS 97 97 97 97 98 99 100 101 102VR - KIAS 104 104 104 104 104 104 104 104 104

5443 KG V2 - KIAS 111 111 111 111 110 110 109 109 108TOFL - FT 2919 3319 3527 3749 4178 4669 5244 5950 6551

11,500 LBS V1 - KIAS 97 96 96 96 91 98 99 101 102VR - KIAS 104 104 104 104 104 104 104 104 104

5216 KG V2 - KIAS 111 111 111 111 110 110 109 109 108TOFL - FT 2801 3184 3383 3593 4000 4481 5039 5712 6296

11,000 LBS V1 - KIAS 96 95 95 95 96 97 99 100 101VR - KIAS 104 104 104 104 104 104 104 104 104

4989 KG V2 - KIAS 112 111 111 111 111 110 110 109 109TOFL - FT 2685 3050 3240 3440 3826 4300 4842 5485 6047



flmmtab3e


FEBRUARY 1999 P-10 P/N 130-590031-73D





15,000 LBS V1 - KIAS 106 106 106 106 108 110 111 – –VR - KIAS 110 110 110 111 111 112 112 – –

6804 KG V2 - KIAS 117 117 117 117 117 117 117 – –TOFL - FT 4378 5007 5332 5795 6535 7448 8599 – –

14,500 LBS V1 - KIAS 104 104 104 104 106 107 109 – –VR - KIAS 108 109 109 109 109 110 111 – –

6577 KG V2 - KIAS 115 115 115 115 115 115 115 – –TOFL - FT 4087 4681 4989 5405 6093 6931 7981 – –

14,000 LBS V1 - KIAS 102 102 102 102 104 105 107 – –VR - KIAS 107 107 107 107 108 108 109 – –

6350 KG V2 - KIAS 114 114 114 114 114 114 114 – –TOFL - FT 3823 4363 4664 5050 5674 6448 7419 – –

13,500 LBS V1 - KIAS 100 100 100 100 102 103 106 107 –VR - KIAS 105 105 106 106 106 107 107 108 –

6123 KG V2 - KIAS 112 112 112 112 112 112 112 112 –TOFL - FT 3575 4077 4347 4721 5280 6001 6878 7975 –

13,000LBS V1 - KIAS 98 98 98 98 100 101 103 105 106VR - KIAS 104 104 104 104 104 105 106 106 106

5897 KG V2 - KIAS 111 111 110 111 110 110 110 110 110TOFL - FT 3351 3815 4053 4397 4921 5572 6381 7384 8275

12,500 LBS V1 - KIAS 98 97 97 98 98 100 101 103 104VR - KIAS 104 104 104 104 104 104 104 104 105

5670 KG V2 - KIAS 111 111 111 110 110 109 109 109 109TOFL - FT 3222 3666 3904 4221 4675 5213 5910 6821 7626

12,000 LBS V1 - KIAS 97 97 97 97 98 99 100 102 103VR - KIAS 104 104 104 104 104 104 104 104 104

5443 KG V2 - KIAS 111 111 111 110 110 110 109 108 108TOFL - FT 3095 3S21 3749 4049 4499 5029 5667 6454 7142

11,500 LBS V1 - KIAS 96 96 96 96 97 98 100 101 102VR - KIAS 104 104 104 104 104 104 104 104 104

5216 KG V2 - KIAS 111 111 111 111 110 110 109 109 108TOFL - FT 2969 3377 3594 3880 4337 4847 5461 6205 6854

11,000 LBS V1 KIAS 96 95 95 95 96 98 99 100 102VR - KIAS 104 104 104 104 104 104 104 104 104

4989 KG V2 - KIAS 111 111 111 111 110 110 100 100 108TOFL - FT 2844 3235 3440 3713 4144 4642 5235 5959 6537



flmmtab3f


OCTOBER 2000P-11P/N 130-590031-73D1





15,000 LBS V1 - KIAS 105 106 106 107 108 110 – – –VR - KIAS 110 110 111 111 111 112 – – –

6804 KG V2 - KIAS 117 117 117 117 117 117 – – –TOFL - FT 4659 5324 5696 6295 7109 8140 – – –

14,500 LBS V1 - KIAS 104 104 104 105 106 108 110 – –VR - KIAS 108 109 109 109 110 110 111 – –

6577 KG V2 - KIAS 115 115 115 115 115 115 115 – –TOFL - FT 4354 4981 5315 5878 6632 7551 8752 – –

14,000 LBS V1 - KIAS 102 102 102 103 104 106 108 – –VR - KIAS 107 107 107 108 108 109 103 – –

6350 KG V2 - KIAS 114 114 114 114 114 114 114 – –TOFL - FT 4062 4657 4960 5472 6170 7026 8106 – –

13,500 LBS V1 - KIAS 100 100 100 101 102 104 106 – –VR - KIAS 105 106 106 106 106 107 107 – –

6123 KG V2 - KIAS 112 112 112 112 112 112 112 – –TOFL - FT 3795 4341 4628 5110 5745 6533 7533 – –

13,000 LBS V1 - KIAS 98 98 98 99 100 102 104 106 –VR - KIAS 104 104 104 10 4105 105 106 106 –

5897 KG V2 - KIAS 111 111 110 110 110 110 110 110 –TOFL - FT 3555 4058 4319 4767 5334 6068 6966 8111 –

12,500 LBS V1 - KIAS 98 97 97 98 99 100 102 104 –VR - KIAS 104 104 104 104 104 104 104 105 –

5670 KG V2 - KIAS 111 111 110 110 110 109 109 109 –TOFL - FT 3418 3899 4153 4544 5043 5645 6450 7480

12,000 LBS V1 - KIAS 97 97 96 97 98 99 101 102 103VR - KIAS 104 104 104 104 104 104 104 104 104

5443 KG V2 - KIAS 111 111 111 110 110 109 109 108 108TOFL - FT 3285 3744 3986 4375 4861 5434 6139 7024 7822

11,500 LBS V1 - KIAS 96 96 96 96 97 99 100 102 103VR - KIAS 104 104 104 104 104 104 104 104 104

5216 KG V2 - KIAS 111 111 111 110 110 110 109 108 108TOFL - FT 3152 3589 3821 4199 4668 5231 5911 6760 7514

11,000 LBS V1 - KIAS 95 95 95 96 97 98 99 101 102VR - KIAS 104 104 104 104 104 104 104 104 104

4989 KG V2 - KIAS 111 111 111 111 110 110 109 108 108TOFL - FT 3018 3436 3657 4015 4492 5034 5677 6489 7228



flmmtab3g


FEBRUARY 1999 P-12 P/N 130-590031-73D





15,000LBS V1- KIAS 105 106 106 107 109 111 – – –VR - KIAS 110 111 111 111 112 112 – – –

6804 KG V2 - KIAS 117 117 117 117 117 117 – – –TOFL - FT 4956 5689 6127 6850 7761 8926 – – –

14,500 LBS V1 - KIAS 104 104 104 105 107 109 – – –VR - KIAS 109 109 109 110 110 110 – – –

6577 KG V2 - KIAS 115 115 115 115 115 115 – – –TOFL - FT 4634 5310 5722 6388 7220 8283 – – –

14,000 LBS V1 - KIAS 102 102 102 103 105 107 109 – –VR - KIAS 107 107 107 108 108 109 109 – –

6350 KG V2 - KIAS 114 114 114 114 114 114 114 – –TOFL - FT 4317 4955 5341 5956 6723 7673 8913 – –

13,500 LBS V1 - KIAS 100 100 100 101 103 105 106 – –VR - KIAS 105 106 106 106 107 107 108 – –

6123 KG V2 - KIAS 112 112 112 112 112 112 112 – –TOFL - FT 4036 4623 4996 5542 6250 7130 8249 – –

13,000 LBS V1 - KIAS 98 98 98 99 101 102 104 – –VR - KIAS 104 104 104 105 105 106 106 – –

5897 KG V2 - KIAS 111 110 110 110 110 110 110 – –TOFL - FT 3778 4314 4641 5166 5811 6616 7634 – –

12,500LBS V1 - KIAS 97 97 97 98 99 100 102 104 –VR - KIAS 104 104 104 104 104 104 104 105 –

5670 KG V2 - KIAS 111 111 110 110 109 109 109 109 –TOFL - FT 3631 4154 4453 4907 5437 6142 7049 8249 –

12,000 LBS V1 - KIAS 97 97 97 97 98 100 101 103 –VR - KIAS 104 104 104 104 104 104 104 104 –

5443 KG V2 - KIAS 111 111 110 110 110 109 108 108 –TOFL - FT 3487 3987 4286 4721 5250 5893 6683 7702 –

11,500 LBS V1 - KIAS 96 96 96 97 98 99 101 102 103VR - KIAS 104 104 104 104 104 104 104 104 104

5216 KG V2 - KIAS 111 111 111 110 110 109 109 108 108TOFL - FT 3345 3821 4104 4551 5052 5667 6423 7411 8277

11,000 LBS V1 - KIAS 95 95 95 96 97 98 100 102 103VR - KIAS 104 104 104 104 104 104 104 104 104

4989 KG V2 - KIAS 111 111 111 110 110 109 109 108 108TOFL - FT 3204 3658 3926 4350 4842 5442 6167 7100 7940

10,500LBS V1 - KIAS 94 94 94 95 96 98 99 101 1024763 KG VR - KIAS 104 104 104 104 104 104 104 104 104


flmmtab3h


FEBRUARY 1999P-13P/N 130-590031-73D





15,000 LBS V1 - KIAS 105 106 107 108 110 – – – –VR - KIAS 110 111 111 111 112 – – – –

6804 KG V2 - KIAS 117 117 117 117 117 – – – –TOFL - FT 5271 6070 6653 7466 8500 – – – –

14,500 LBS V1 - KIAS 104 104 104 106 108 109 – – –VR - KIAS 109 109 109 110 110 111 – – –

6577 KG V2 - KIAS 115 115 115 115 115 115 – – –TOFL - FT 4935 566O 6213 6960 7897 9103 – – –

14,000 LBS V1 - KIAS 102 102 102 104 105 107 – – –VR - KIAS 107 107 108 108 109 109 – – –

6350 KG V2 - KIAS 114 114 114 114 114 114 – – –TOFL - FT 4612 5289 5794 6475 7332 8429 – – –

13,500 LBS V1 - KIAS 100 100 100 102 103 105 107 – –VR - KIAS 105 106 106 106 107 107 108 – –

6123 KG V2 - KIAS 112 112 112 112 112 112 112 – –TOFL - FT 4301 4942 5406 6034 6823 7810 102 – –

13,000 LBS V1 - KIAS 98 98 99 100 101 103 105 – –VR - KIAS 104 104 104 105 105 106 106 – –

5897 KG V2 - KIAS 111 110 110 110 110 110 110 – –TOFL - FT 4021 4606 5047 5604 6330 7235 8403 – –

12,500 LBS V1 - KIAS 97 97 97 98 99 101 103 – –VR - KIAS 104 104 104 104 104 104 105 – –

5670 KG V2 - KIAS 111 110 110 110 109 109 109 – –TOFL - FT 3864 4418 4801 5299 5902 6699 7745 – –

12,000 LBS V1 - KIAS 97 96 97 98 99 100 102 103 –VR - KIAS 104 104 104 104 104 104 104 104 –

5443 KG V2 - KIAS 111 111 110 110 109 109 108 108 –TOFL-FT 3710 4250 4622 5107 5674 6394 7295 8485 –

11,500 LBS V1 - KIAS 96 96 96 97 98 99 101 103 –VR - KIAS 104 104 104 104 104 104 104 104 –

5216 KG V2 - KIAS 111 111 110 110 110 109 108 108 –TOFL-FT 3557 4071 4442 4903 5466 6148 7008 8146 –

11,000 LBS V1 - KIAS 95 95 95 96 98 99 100 102 103VR - KIAS 104 104 104 104 104 104 104 104 104

4989 KG V2 - KIAS 111 111 110 110 110 109 109 108 107TOFL-FT 3405 3895 4248 4716 5253 5910 6739 7316 8806



flmmtab3i


FEBRUARY 1999 P-14 P/N 130-590031-73D


PRESSURE ALTITUDE: 10,000 FT



15,000 LBS V1 - KIAS 106 106 107 109 110 – – – –VR - KIAS 111 111 111 112 112 – – – –

6804 KG V2 - KIAS 117 117 117 117 117 – – – –TOFL - FT 5693 6599 7329 8242 9437 – – – –

14,500 LBS V1 - KIAS 104 104 105 107 108 – – – –VR - KIAS 109 109 110 110 110 – – – –

6577 KG V2 - KIAS 115 115 115 115 115 – – – –TOFL - FT 5316 6178 6823 7666 8754 – – – –

14,000 LBS V1 - KIAS 102 102 103 104 106 108 – – –VR - KIAS 107 108 108 108 109 109 – – –

6350 KG V2 - KIAS 114 114 114 114 114 114 – – –TOFL - FT 4962 5756 6360 7134 8117 9379 – – –

13,500 LBS V1 - KIAS 100 100 101 102 104 106 – – –VR - KIAS 106 106 106 107 107 108 – – –

6123 KG V2 - KIAS 112 112 112 112 112 112 – – –TOFL - FT 4628 5371 5930 6631 7530 8678 – – –

13,000 LBS V1 - KIAS 98 98 99 100 102 104 – – –VR - KIAS 104 104 105 105 106 106 – – –

5897 KG V2 - KIAS 110 110 110 110 110 110 – – –TOFL - FT 4320 5007 5523 6168 6996 8080 – – –

12,500 LBS V1 - KIAS 97 97 98 99 100 102 104 – –VR - KIAS 104 104 104 104 104 104 105 – –

5670 KG V2 - KIAS 111 110 110 109 109 109 109 – –TOFL - FT 4160 4783 5246 5776 6464 7407 8648 – –

12,000 LBS V1 - KIAS 96 97 97 98 99 101 102 – –VR - KIAS 104 104 104 104 104 104 104 – –

5448 KG V2 - KIAS 111 110 110 110 109 109 108 – –TOFL - FT 3993 4613 5041 5575 6224 7032 8088 – –

11,500 LBS V1 - KIAS 96 96 96 97 99 100 102 – –VR - KIAS 104 104 104 104 104 104 104 – –

5216 KG V2 - KIAS 111 110 110 110 109 109 108 – –TOFL - FT 3828 4419 4845 5363 5981 6745 7757 – –

11,000 LBS V1 - KIAS 95 95 96 97 98 99 101 103 –VR - KIAS 104 104 104 104 104 104 104 104 –

4989 KG V2 - KIAS 111 111 110 110 109 109 108 103 –TOFL - FT 3664 4226 4646 5140 5751 6487 7450 8751 –

10,5OO LBS V1 - KIAS 94 94 95 96 97 99 100 102 –4763 KG VR - KIAS 104 104 104 104 104 104 104 104 –

AND V2 - KIAS 111 111 110 110 110 109 108 108 –UNDER TOFL - FT 3502 4036 4436 4936 5521 6234 7141 8384 –

flmmtab3j


FEBRUARY 1999P-15P/N 130-590031-73D

TAK

EO

FF

FL

AP

S A

PP

RO

AC

H

TAKE-OFF SPEEDS AND FIELD LENGTHS- FLAPSAPPROACH (A/C AND BLEED AIR ON)

PRESSURE ALTITUDE: SEA LEVEL


15,000 LBS V1 - KIAS 100 99 99 99 99 99 101 103 104VR - KIAS 103 103 103 103 104 104 104 104 105

6804 KG V2 - KIAS 109 109 109 109 109 109 109 109 109TOFL - FT 2387 2733 2916 3103 3300 3612 4154 4746 5199

14,500 LBS V1 - KIAS 98 97 97 97 97 97 99 101 102VR - KIAS 102 102 102 102 102 102 103 103 103

6577 KG V2 - KIAS 107 107 107 107 107 107 107 107 107TOFL - FT 2260 2541 2712 2889 3068 3354 3862 4407 4826

14,000 LBS V1 - KIAS 98 97 97 96 96 96 98 99 100VR - KIAS 102 102 102 102 102 102 102 102 102

6350 KG V2 - KIAS 107 107 107 107 107 106 106 106 105TOFL - FT 2179 2450 2607 2774 2939 3181 3629 4114 4476

13,500 LBS V1 - KIAS 97 96 96 96 95 96 97 99 99VR - KIAS 102 102 102 102 102 102 102 102 102

6123 KG V2 - KIAS 107 107 107 107 107 107 106 106 106TOFL - FT 2099 2365 2515 2675 2836 3066 3482 3968 4314

13,000 LBS V1 - KIAS 97 96 96 95 95 95 96 98 99VR - KIAS 102 102 102 102 102 102 102 102 102

6097 KG V2 - KIAS 108 107 107 107 107 107 106 106 106TOFL - FT 2020 2282 2425 2578 2736 2955 3346 3828 4169

12,500 LBS V1 - KIAS 96 95 95 95 94 94 96 97 98VR - KIAS 102 102 102 102 102 102 102 102 102

5670 KG V2 - KIAS 108 108 107 107 107 107 106 106 106TOFL - FT 1947 2201 2338 2484 2638 2847 3216 3662 4007

12,000 LBS V1 - KIAS 96 95 94 94 94 94 95 96 98VR - KIAS 102 102 102 102 102 102 102 102 102

5443 KG V2 - KIAS 108 108 108 107 107 107 107 106 106TOFL - FT 1879 2122 2253 2392 2539 2742 3091 3505 3850

11,500 LBS V1 - KIAS 95 94 94 94 93 93 94 96 97VR - KIAS 102 102 102 102 102 102 102 102 102

5216 KG V2 - KIAS 108 108 108 108 108 107 107 106 106TOFL - FT 1812 2044 2169 2301 2441 2637 2968 3362 3675

11,000 LBS V1 - KIAS 94 94 93 93 93 93 94 95 96VR - KIAS 102 102 102 102 102 102 102 102 102

4989 KG V2 - KIAS 108 108 108 108 108 107 107 106 106TOFL - FT 1744 1966 2085 2211 2344 2534 2847 3223 3513



flmmtab7


OCTOBER 2000 P-16 P/N 130-590031-73D




15,000 LBS V1 - KIAS 99 99 99 99 99 100 102 103 105VR- -KIAS 103 103 103 104 104 104 104 105 105

6804 KG V2 - KIAS 109 109 109 109 109 109 109 109 109TOFL - FT 2533 2906 3099 3303 3512 3942 4504 5173 5669

14,500 LBS V1 - KIAS 98 97 97 97 97 98 100 101 102VR - KIAS 102 102 102 102 102 102 103 103 103

6577 KG V2 - KIAS 107 107 107 107 107 107 107 107 107TOFL - FT 2363 2702 2885 3071 3265 3648 4191 4807 5250

14,000 LBS V1 - KIAS 97 97 96 96 96 96 98 99 100VR - KIAS 102 102 102 102 102 102 102 102 102

6350 KG V2 - KIAS 107 107 107 107 107 106 106 106 105TOFL - Fl 2294 2598 2771 2941 3117 3442 3933 4464 4872

13,500 LBS V1 - KIAS 97 96 96 95 95 96 97 99 100VR - KIAS 102 102 102 102 102 102 102 102 102

6123 KG V2 - KIAS 107 107 107 107 107 106 106 106 105TOFL - FT 2210 2506 2672 2839 3007 3316 3782 4303 4676

13,000 LBS V1 - KIAS 96 96 95 95 95 95 97 98 99VR - KIAS 102 102 102 102 102 102 102 102 102

5897 KG V2 - KIAS 107 107 107 107 107 107 106 106 105TOFL - FT 2129 2417 2575 2739 2900 3192 3624 4149 4504

12,500 LBS V1 - KIAS 96 95 95 94 94 95 96 98 99VR - KIAS 102 102 102 102 102 102 102 102 102

5670 KG V2 - KIAS 108 107 107 107 107 107 106 106 106TOFL - FT 2055 2330 2481 2641 2795 3072 3478 4003 4337

12,000 LBS V1 - KIAS 95 95 94 94 93 94 95 97 98VR - KIAS 102 102 102 102 102 102 102 102 102

5443 KG V2 - KIAS 108 108 107 107 107 107 106 106 106TOFL - FT 1982 2246 2390 2542 2693 2956 3343 3824 4175

11,500 LBS V1 - KIAS 95 94 94 93 93 93 95 96 97VR - KIAS 102 102 102 102 102 102 102 102 102

5216 KG V2 - KIAS 108 108 108 108 107 107 106 106 106TOFL - FT 1910 2161 2299 2443 2592 2841 3210 3654 4007

11,000 LBS V1 - KIAS 94 93 93 93 92 93 94 95 96VR - KIAS 102 102 102 102 102 102 102 102 102

4989 KG V2 - KIAS 108 108 108 108 108 107 107 106 106TOFL - FT 1839 2078 2209 2346 2489 2728 3078 3498 3821



TAK

EO

FF

F

LA

PS

AP

PR

OA

CH

flmmtab7a


FEBRUARY 1999P-17P/N 130-590031-73D





15,000 LBS V1 - KIAS 99 99 99 99 99 100 102 104VR - KIAS 103 103 104 104 104 104 104 105 –

6804 KG V2 - KIAS 109 109 109 109 109 109 109 109 –TOFL - FT 2693 3089 3300 3516 3744 4274 4904 5636 –

14,500 LBS V1 - KIAS 98 97 97 97 97 98 100 102 103VR - KIAS 102 102 102 102 102 102 103 103 103

6577 KG V2 - KIAS 107 107 107 107 107 107 107 107 107TOFL - FT 2504 2876 3069 3270 3482 3981 4558 5231 5728

14,000 LBS V1 - KIAS 97 96 96 96 96 97 98 100 101VR - KIAS 102 102 102 102 102 102 102 102 102

6350 KG V2 - KIAS 107 107 107 107 106 106 106 105 105TOFL - FT 2419 2763 2939 3122 3310 3733 4262 4863 5299

13,500 LBS V1 - KIAS 95 96 95 95 95 96 98 99 100VR - KIAS 102 102 102 102 102 102 102 102 102

6123 KG V2 - KIAS 107 107 107 107 107 106 106 105 105TOFL - FT 2333 2664 2837 3011 3190 3584 4110 4676 5069

13,000 LBS V1 - KIAS 96 95 95 95 94 95 97 99 100VR - KIAS 102 102 102 102 102 102 102 102 102

5897 KG V2 - KIAS 107 107 107 107 107 106 106 106 105TOFL - FT 2251 2567 2737 2904 3075 3450 3951 4498 4883

12,500 LBS V1 - KIAS 95 95 94 94 94 95 96 98 99VR - KIAS 102 102 102 102 102 102 102 102 102

5670 KG V2 - KIAS 108 107 107 107 107 106 106 106 105TOFL - FT 2172 2474 2639 2799 2962 3320 3781 4321 4694

12,000 LBS V1 - KIAS 95 94 94 93 93 94 96 98 98VR - KIAS 102 102 102 102 102 102 102 102 102

5443 KG V2 - KIAS 108 107 107 107 107 107 106 106 106TOFL - FT 2095 2382 2540 2696 2852 3195 3623 4177 4526

11,500 LBS V1 - KIAS 94 94 93 93 93 94 95 97 98VR - KIAS 102 102 102 102 102 102 102 102 102

5216 KG V2 - KIAS 108 108 108 107 107 107 106 106 106TOFL - FT 2017 2292 2441 2595 2744 3067 3476 3985 4351

11,000 LBS V1 - KIAS 94 93 93 92 92 93 94 96 97VR - KIAS 102 102 102 102 102 102 102 102 102

4989 KG V2 - KIAS 108 108 108 108 107 107 106 106 106TOFL - FT 1941 2202 2344 2492 2636 2943 3333 3803 4171



flmmtab7b


FEBRUARY 1999 P-18 P/N 130-590031-73D





15,000LBS V1 - KIAS 99 99 99 99 99 101 103 – –VR - KIAS 103 104 104 104 104 104 105 – –

6804 KG V2 - KIAS 109 109 109 109 109 109 109 – –TOFL - FT 2867 3291 3515 3747 4090 4648 5324 – –

14,500 LBS V1 - KIAS 97 97 97 97 97 99 101 102 –VR - KIAS 102 102 102 102 102 103 103 103 –

6577 KG V2 - KIAS 107 107 107 107 107 107 107 107 –TOFL - FT 2664 3060 3268 3483 3789 4325 4954 5688 –

14,000 LBS V1 - KIAS 97 96 96 96 96 97 99 100 102VR - KIAS 102 102 102 102 102 102 102 102 102

6350 KG V2 - KIAS 107 107 107 107 106 106 106 105 105TOFL - FT 2563 2932 3121 3320 3579 4067 4614 5275 5801

13,500 LBS V1 - KIAS 96 95 95 95 95 97 98 100 101VR - KIAS 102 102 102 102 102 102 102 102 102

6123 KG V2 - KIAS 107 107 107 107 106 106 106 105 105TOFL - FT 2473 2829 3010 3200 3450 3898 4451 5053 5526

13,000 LBS V1 - KIAS 96 95 95 94 95 96 98 99 100VR - KIAS 102 102 102 102 102 102 102 102 102

5897 KG V2 - KIAS 107 107 107 107 107 106 106 105 105TOFL - FT 2385 2729 2902 3084 3325 3738 4288 4877 5320

12,500 LBS V1 - KIAS 95 94 94 94 94 95 97 98 99VR - KIAS 102 102 102 102 102 102 102 102 102

5670 KG V2 - KIAS 107 107 107 107 107 105 106 106 105TOFL - FT 2300 2632 2798 2971 3203 3592 4116 4690 5121

12,000 LBS V1 - KIAS 95 94 93 93 93 94 96 98 99VR - KIAS 102 102 102 102 102 102 102 102 102

5443 KG V2 - KIAS 108 107 107 107 107 106 106 106 105TOFL - FT 2217 2533 2695 2861 3081 3453 3937 4504 4932

11,500 LBS V1 - KIAS 94 93 93 93 93 94 95 97 98VR - KIAS 102 102 102 102 102 102 102 102 102

5216 KG V2 - KIAS 108 108 107 107 107 107 106 106 106TOFL - FT 2134 2435 2594 2752 2961 3317 3768 4346 4740

11,000 LBS V1 - KIAS 93 93 92 92 92 93 95 96 98VR - KIAS 102 102 102 102 102 102 102 102 102

4989 KG V2 - KIAS 108 108 108 107 107 107 106 106 106TOFL - FT 2052 2338 2491 2644 2842 3183 3609 4139 4555



flmmtab7c


FEBRUARY 1999P-19P/N 130-590031-73D





15,000 LBS V1 - KIAS 99 99 99 99 100 101 103 – –VR - KIAS 103 104 104 104 104 104 105 – –

6804 KG V2 - KIAS 109 109 109 109 109 109 109 – –TOFL - FT 3048 3506 3747 4002 4452 5056 5803 – –

14,500 LBS V1 - KIAS 97 97 97 97 98 99 101 – –VR - KIAS 102 102 102 102 102 103 103 – –

6577 KG V2 - KIAS 107 107 107 107 107 107 107 – –TOFL - FT 2839 3260 3483 3711 4138 4706 5380 – –

14,000 LBS V1 - KIAS 96 96 96 96 96 98 99 101 –VR - KIAS 102 102 102 102 102 102 102 102 –

6350 KG V2 - KIAS 107 107 107 106 106 106 105 105 –TOFL - FT 2726 3113 3320 3528 3887 4405 4997 5751 –

13,500 LBS V1 - KIAS 96 95 95 95 96 97 99 100 –VR - KIAS 102 102 102 102 102 102 102 102 –

6123 KG V2 - KIAS 107 107 107 107 106 106 106 105 –TOFL - FT 2629 3003 3200 3402 3733 4248 4818 5491 –

13,000 LBS V1 - KIAS 95 95 94 94 95 96 98 99 101VR - KIAS 102 102 102 102 102 102 102 102 102

5897 KG V2 - KIAS 107 107 107 107 106 106 106 105 105TOFL - FT 2534 2896 3083 3280 3594 4068 4650 5287 5826

12,500 LBS V1 - KIAS 95 94 94 94 94 96 97 99 100VR - KIAS 102 102 102 102 102 102 102 102 102

5670 KG V2 - KIAS 107 107 107 107 106 106 106 105 105TOFL - FT 2442 2791 2971 3160 3459 3898 4475 5090 5640

12,000 LBS V1 - KIAS 94 93 93 93 94 95 97 98 99VR - KIAS 102 102 102 102 102 102 102 102 102

5443 KG V2 - KIAS 108 107 107 107 107 106 106 105 105TOFL - FT 2352 2689 2861 3041 3329 3742 4291 4899 5392

11,500 LBS V1 - KIAS 94 93 93 92 93 94 96 98 99VR - KIAS 102 102 102 102 102 102 102 102 102

5216 KG V2 - KIAS 108 107 107 107 107 106 106 106 105TOFL - FT 2263 2588 2752 2923 3200 3591 4097 4706 5183

11,000 LBS V1 - KIAS 93 92 92 92 92 93 95 97 98VR - KIAS 102 102 102 102 102 102 102 102 102

4989 KG V2 - KIAS 108 108 107 107 107 107 106 105 105TOFL - FT 2175 2485 2644 2807 3072 3443 3916 4537 4979



flmmtab7d


FEBRUARY 1999 P-20 P/N 130-590031-73D





15,000 LBS V1 - KIAS 99 99 99 99 100 102 – – –VR - KIAS 104 104 104 104 104 104 – – –

6804 KG V2 - KIAS 109 109 109 109 109 109 – – –TOFL - FT 3249 3739 4003 4294 4850 5507 – – –

14,500 LBS V1 - KIAS 97 97 97 97 98 100 102 – –VR - KIAS 102 102 102 102 103 103 103 – –

6577 KG V2 - KIAS 107 107 107 107 107 107 107 – –TOFL - FT 3022 3475 3712 3983 4507 5121 5874 – –

14,000 LBS V1 - KIAS 96 96 96 95 97 98 100 – –VR - KIAS 102 102 102 102 102 102 102 – –

6350 KG V2 - KIAS 107 107 106 106 106 106 105 – –TOFL - FT 2897 3313 3529 3761 4231 4777 5442 – –

13,500 LBS V1 - KIAS 95 95 95 95 96 97 99 101 –VR - KIAS 102 102 102 102 102 102 102 102 –

6123 KG V2 - KIAS 107 107 107 106 106 106 105 105 –TOFL - FT 2796 3193 3403 3624 4057 4610 5227 5995 –

13,000 LBS V1 - KIAS 95 94 94 94 95 97 98 100 –VR - KIA5 102 102 102 102 102 102 102 102 –

5897 KG V2 - KIAS 107 107 107 107 106 106 105 105 –TOFL - FT 2698 3077 3281 3492 3893 4443 5036 5766 –

12,500 LBS V1 - KIAS 94 94 94 94 95 96 98 99 101VR - KIAS 102 102 102 102 102 102 102 102 102

5670 KG V2 - KIAS 107 107 107 107 106 106 106 105 106TOFL - FT 2599 2965 3161 3364 3744 4248 4861 5542 6161

12,000 LBS V1 - KIAS 94 93 93 93 94 95 97 99 100VR - KIAS 102 102 102 102 102 102 102 102 102

5443 KG V2 - KIAS 107 107 107 107 106 106 106 105 105TOFL - FT 2502 2855 3041 3239 3599 4065 4671 5339 5922

11,500 LBS V1 - KIAS 93 93 92 92 93 95 96 98 100VR - KIAS 102 102 102 102 102 102 102 102 102

5216 KG V2 - KIAS 108 107 107 107 107 106 106 105 105TOFL - FT 2406 2746 2924 3115 3457 3897 4479 5133 5692

11,000 LBS V1 - KIAS 93 92 92 92 92 94 96 98 99VR - KIAS 102 102 102 102 102 102 102 102 102

4989 KG V2 - KIAS 108 107 107 107 107 106 106 106 105TOFL - FT 2310 2639 2808 2990 3317 3734 4271 4934 5466



flmmtab7e


FEBRUARY 1999P-21P/N 130-590031-73D





15,000 LBS V1 - KIAS 98 99 99 99 101 103 – – –VR - KIAS 104 104 104 104 104 105 – – –

6804 KG V2 - KIAS 109 109 109 109 109 109 – – –TOFL - FT 3465 3995 4278 4678 5254 6007 – – –

14,500 LBS V1 - KIAS 97 97 97 97 99 101 – – –VR - KIAS 102 102 102 102 103 103 – – –

6577 KG V2 - KIAS 107 107 107 107 107 107 – – –TOFL - FT 3221 3705 3967 4343 4914 5577 – – –

14,000 LBS V1 - KIAS 96 95 95 96 97 99 100 – –VR - KIAS 102 102 102 102 102 102 102 – –

6350 KG V2 - KIAS 107 106 106 106 106 105 105 – –TOFL - FT 3078 3523 3755 4081 4600 5183 5949 – –

13,500 LBS V1 - KIAS 95 95 95 95 97 98 100 – –VR - KIAS 102 102 102 102 102 102 102 – –

6123 KG V2 - KIAS 107 107 106 106 106 106 105 – –TOFL - FT 2969 3398 3620 3921 4424 4996 5691 – –

13,000 LBS V1 - KIAS 95 94 94 94 96 97 99 101 –VR - KIAS 102 102 102 102 102 102 102 102 –

5897 KG V2 - KIAS 107 107 107 106 106 106 105 105 –TOFL - FT 2863 3276 3489 3774 4238 4816 5476 6316 –

12,500 LBS V1 - KIAS 94 94 94 94 95 97 98 100 –VR - KIAS 102 102 102 102 102 102 102 102 –

5670 KG V2 - KlAS 107 107 107 106 106 106 105 105 –TOFL - FT 2761 3155 3361 3632 4062 4644 5263 6061 –

12,000 LBS V1 - KIAS 93 93 93 93 94 96 98 99 –VR - KIAS 102 102 102 102 102 102 102 102 –

5443 KG V2 - KIAS 107 107 107 107 106 106 106 105 –TOFL - FT 2660 3036 3236 3495 3902 4440 5074 5843 –

11,500 LBS V1 - KIAS 93 92 92 92 94 95 97 99 100VR - KIAS 102 102 102 102 102 102 102 102 102

5216 KG V2 - KIAS 107 107 107 107 106 106 106 105 105TOFL - FT 2560 2919 3113 3358 3746 4241 4879 5602 6234

11,000 LBS V1 - KIAS 92 92 92 92 93 94 96 98 100VR - KIAS 102 102 102 102 102 102 102 102 102

4989 KG V2 - KIAS 108 107 107 107 107 106 106 105 105TOFL - FT 2457 2803 2988 3225 3592 4058 4676 5371 5988



flmmtab7f


OCTOBER 2000 P-22 P/N 130-590031-73D1





15,000 LBS V1 - KIAS 99 99 99 100 101 103 – – –VR - KIAS 104 104 104 104 104 105 – – –

6804 KG V2 - KIAS 109 109 109 109 109 109 – – –TOFL - FT 3696 4272 4587 5092 5740 6565 – – –

14,500 LBS V1 - KIAS 97 97 97 98 99 101 – – –VR - KIAS 102 102 102 103 103 103 – – –

6577 KG V2 - KIAS 107 107 107 107 107 107 – – –TOFL - FT 3438 3961 4243 4739 5326 6094 – – –

14,000 LBS V1 - KIAS 96 95 95 96 98 99 – – –VR - KIAS 102 102 102 102 102 102 – – –

6350 KG V2 - KIAS 107 106 106 106 106 105 – – –TOFL - FT 3277 3752 4003 4446 4996 5655 – – –

13,500 LBS V1 - KIAS 95 95 95 96 97 98 100 – –VR - KIAS 102 102 102 102 102 102 102 – –

6123 KG V2 - KIAS 107 106 106 106 106 105 105 – –TOFL - FT 3159 3616 3855 4264 4810 5441 6205 – –

13,000 LBS V1 - KIAS 94 94 94 95 96 98 99 – –VR - KIAS 102 102 102 102 102 102 102 – –

5897 KG V2 - KIAS 107 107 106 106 106 106 105 – –TOFL - FT 3045 3485 3713 4091 4628 5231 5973 – –

12,500 LBS V1 - KIAS 94 94 93 94 95 97 99 – –VR - KIAS 102 102 102 102 102 102 102 – –

5670 KG V2 - KIAS 107 107 107 106 106 106 105 – –TOFL - FT 2934 3357 3575 3935 4432 5027 574 – –

12,000 LBS V1 - KIAS 93 93 93 93 95 97 98 100 –VR - KIAS 102 102 102 102 102 102 102 102 –

5443 KG V2 - KIAS 107 107 107 106 106 106 105 105 –TOFL - FT 2825 3232 3440 3784 4241 4857 5531 6379 –

11,500 LBS V1 - KIAS 93 92 92 93 94 96 98 99 –VR - KIAS 102 102 102 102 102 102 102 102 –

5216 KG V2 - KIAS 107 107 107 107 106 106 105 105 –TOFL - FT 2718 3109 3308 3635 4067 4635 5314 6132 –

11,000 LBS V1 - KIAS 92 92 91 92 93 95 97 99 100VR - KIAS 102 102 102 102 102 102 102 102 102

4989 KG V2 - KIAS 107 107 107 107 106 106 106 105 105TOFL - FT 2612 2984 3177 3487 3897 4424 5103 5891 6578


AND V2 - KIAS 108 107 107 107 107 106 106 105 105UNDER TOFL- FT 2507 2507 2860 3048 3341 3731 4229 4889 6314

flmmtab7g


FEBRUARY 1999P-23P/N 130-590031-73D





15,000 LBS V1 - KIAS 99 99 99 101 102 – – – –VR - KIAS 104 104 104 104 105 – – – –

6804 KG V2 - KIAS 109 109 109 109 109 – – – –TOFL - FT 3952 4582 4956 5537 6269 – –– – –

14,500 LBS V1 - KIAS 97 97 97 99 100 102 – – –VR - KIAS 102 102 103 103 103 103 – – –

6577 KG V2 - KIAS 107 107 107 107 107 107 – – –TOFL - FT 3667 4239 4616 5164 5824 6669 – – –

14,000 LBS V1 - KIAS 95 95 96 97 98 100 – – –VR - KIAS 102 102 102 102 102 102 – – –

6350 KG V2 - KIAS 106 106 106 106 105 105 – – –TOFL - FT 3489 4002 4329 4837 5403 6183 – – –

13,500 LBS V1 - KIAS 95 95 95 96 97 99 – – –VR - KIAS 102 102 102 102 102 102 – – –

6123 KG V2 - KIAS 107 106 106 106 106 105 – – –TOFL - FT 3365 3856 4157 4654 5220 5918 – – –

13,000 LBS V1 - KIAS 94 94 94 95 97 98 100 – –VR - KIAS 102 102 102 102 102 102 102 – –

5897 KG V2 - KIAS 107 107 106 106 106 105 105 – –TOFL - FT 3244 3714 3999 4461 5032 5698 6525 – –

12,500 LBS V1 - KIAS 94 93 94 95 96 98 99 – –VR - KIAS 102 102 102 102 102 102 102 – –

5670 KG V2 - KlAS 107 107 106 106 106 105 105 – –TOFL - FT 3124 3575 3850 4275 4840 5485 6278 – –

12,000 LBS V1 - KIAS 93 93 93 94 95 97 99 – –VR - KIAS 102 102 102 102 102 102 102 – –

5443 KG V2 - KIAS 107 107 107 106 106 106 105 – –TOFL - FT 3006 3441 3703 4106 4628 5274 6040 – –

11,500 LBS V1 - KIAS 92 92 92 93 94 97 98 100 –VR - KIAS 102 102 102 102 102 102 102 102 –

5216 KG V2 - KIAS 107 107 107 106 106 106 105 105 –TOFL - FT 2891 3308 3558 3941 4426 5087 5807 6736 –

11,000 LBS V1 - KIAS 92 91 92 92 94 96 98 100 –VR - KIAS 102 102 102 102 102 102 102 102 –

4989 KG V2 - KIAS 107 107 107 107 106 106 105 105 –TOFL - FT 2776 3177 3415 3779 4240 4845 5576 6468 –

10,500 LBS V1 - KIAS 91 91 91 92 93 95 97 99 –4763 KG VR - KIAS 102 102 102 102 102 102 102 102 –


flmmtab7h


FEBRUARY 1999 P-24 P/N 130-590031-73D





15,000 LBS V1 - KIAS 99 99 100 101 103 – – – –VR - KIAS 104 104 104 104 105 – – – –

6804 KG V2 - KIAS 109 109 109 109 109 – – – –TOFL - FT 4229 4904 5389 6043 6854 – – – –

14,500 LBS V1 - KIAS 97 97 98 99 101 – – – –VR - KIAS 102 102 103 103 103 – – – –

6577 KG V2 - KIAS 107 107 107 107 107 – – – –TOFL - FT 3922 4556 5023 5619 6367 – – – –

14,000 LBS V1 - KIAS 95 95 96 97 99 101 – – –VR - KIAS 102 102 102 102 102 102 – – –

6350 KG V2 - KIAS 106 106 106 106 105 105 – – –TOFL - FT 3717 4282 4720 5257 5914 6767 – – –

13,500 LBS V1 - KIAS 95 95 95 97 98 100 – – –VR - KIAS 102 102 102 102 102 102 – – –

6123 KG V2 - KIAS 106 106 106 106 105 105 – – –TOFL - FT 3583 4116 4528 5062 5679 6457 – – –

13,000 LBS V1 - KIAS 94 94 95 96 97 99 – – –VR - KIAS 102 102 102 102 102 102 – – –

5897 KG V2 - KIAS 107 106 106 106 106 105 – – –TOFL - FT 3453 3963 4343 4867 5473 6214 – – –

12,500 LBS V1 - KIAS 93 93 94 95 97 99 100 – –VR - KIAS 102 102 102 102 102 102 102 – –

5670 KG V2 - KIAS 107 107 106 106 106 105 105 – –TOFL - FT 3327 3816 4173 4661 5272 5986 6891 – –

12,000 LBS V1 - KIAS 93 93 93 94 96 98 99 – –VR - KIAS 102 102 102 102 102 102 102 – –

5443 KG V2 - KIAS 107 107 106 106 106 105 105 – –TOFL - FT 3204 3671 4011 4464 5069 5761 6614 – –

11,500 LBS V1 - KIAS 92 92 93 93 95 97 99 – –VR - KIAS 102 102 102 102 102 102 102 – –

5216 KG V2 - KIAS 107 107 107 106 106 106 105 – –TOFL - FT 3081 3528 3852 4283 4838 5542 6362 – –

11,000 LBS V1 - KIAS 92 91 92 93 94 96 98 – –VR - KIAS 102 102 102 102 102 102 102 – –

4989 KG V2 - KIAS 107 107 107 106 106 106 105 – –TOFL - FT 2957 3386 3696 4103 4618 5316 6105 – –

10,500 LBS V1 - KIAS 91 91 91 92 93 96 98 100 –4763 KG VR - KIAS 102 102 102 102 102 102 102 102 –


flmmtab7i


FEBRUARY 1999P-25P/N 130-590031-73D


PRESSURE ALTITUDE: 10,000 FT



15,000 LBS V1 - KIAS 99 99 100 102 – – – – –VR - KIAS 104 104 104 105 – – – – –

6804 KG V2 - KIAS 109 109 109 109 – – – – –TOFL - FT 4583 5346 5928 6661 – – – – –

14,500 LBS V1 - KIAS 97 98 98 100 102 – – – –VR - KIAS 102 103 103 103 103 – – – –

6577 KG V2 - KIAS 107 107 107 107 107 – – – –TOFL - FT 4242 5001 5524 6195 7046 – – – –

14,000 LBS V1 - KIAS 95 96 97 98 99 – – – –VR - KIAS 102 102 102 102 102 – – – –

6350 KG V2 - KIAS 106 106 106 105 105 – – – –TOFL - FT 4008 4685 5178 5762 6354 – – – –

13,500 LBS V1 - KIAS 95 95 96 97 99 – – – –VR - KIAS 102 102 102 102 102 – – – –

6123 KG V2 - KIAS 106 106 106 106 105 – – – –TOFL - FT 3861 4496 4987 5555 6260 – – – –

13,000 LBS V1 - KIAS 94 94 95 97 98 100 – – –VR - KIAS 102 102 102 102 102 102 – – –

5897 KG V2 - KIAS 107 106 106 106 105 105 – – –TOFL - FT 3719 4317 4779 5354 6041 6866 – – –

12,500 LBS V1 - KIAS 93 94 94 96 97 99 – – –VR - KIAS 102 102 102 102 102 102 – – –

5670 KG V2 - KIAS 107 106 106 106 105 105 – – –TOFL - FT 3581 4153 4582 5145 5806 6608 – – –

12,000 LBS V1 - KIAS 93 93 94 95 97 98 – – –VR - KIAS 102 102 102 102 102 102 – – –

5443 KG V2 - KIAS 107 106 106 106 106 105 – – –TOFL - FT 3447 3993 4400 4919 5587 6355 – – –

11,500 LBS V1 - KIAS 92 92 93 94 96 98 100 – –VR - KIAS 102 102 102 102 102 102 102 – –

5216 KG V2 - KIAS 107 107 106 106 106 105 105 – –TOFL - FT 3314 3836 4222 4703 5370 6103 7067 – –

11,000 LBS V1 - KIAS 91 91 92 93 95 97 99 – –VR - KIAS 102 102 102 102 102 102 102 – –

4989 KG V2 - KIAS 107 107 107 106 106 105 105 – –TOFL - FT 3183 3681 4047 4506 5116 5867 6784 – –

10,500 LBS V1 - KIAS 91 91 91 92 94 96 98 – –4763 KG VR - KIAS 102 102 102 102 102 102 102 – –

AND V2 - KIAS 107 107 107 106 106 106 105 – –UNDER TOFL - FT 3057 3527 3875 4312 4875 5629 6507 – –

flmmtab7j


FEBRUARY 1999 P-26 P/N 130-590031-73D

MAXIMUM CRUISE POWER


FEBRUARY 1999P-27P/N 130-590031-73D

NORMAL CRUISE POWER

CR

UIS

E

PILOT NOTES


FEBRUARY 1999 P-28 P/N 130-590031-73D

CR

UIS

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FEBRUARY 1999SI-1P/N 130-590031-73D

SUPPLEMENTAL INFORMATION

FUEL SYSTEM SCHEMATIC...........................................................................................SI-2

POWER DISTRIBUTION SCHEMATIC–DC...................................................................SI-3


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ka350 pilot checklist pn-73.pdf

Documents

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