KA350 Pilot Checklist PN-73.pdf

FlightSafety international

BEECHCRAFT SUPER KING AIR 350 & 350C

Models B300 & B300C

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

P/N 130-590031-73D February 2007—Revision 9

PILOT CHECKLIST

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INSERT LATEST REVISED PAGES, DESTROY SUPERSEDED PAGES LIST OF EFFECTIVE PAGES This document is an abbreviation of the procedures contained in the Pilot’s Operating Handbook and FAA Approved Airplane Flight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 Revision ....1 ........OCTOBER, 2000 Revision .....2....SEPTEMBER, 2001 Revision .....3 .................JULY, 2002 Revision .....4 ...........AUGUST, 2003 Revision .....5 ......FEBRUARY, 2004 Revision .....6 ........OCTOBER, 2004 Revision .....7 .....NOVEMBER, 2005 Revision .....8................APRIL, 2006 Revision .....9 ......FEBRUARY, 2007

Incorporates A6 of the POH/AFM Incorporates B reissue of the POH/AFM Incorporates B1 revision of the POH/AFM Incorporates B2 revision of the POH/AFM Incorporates B3–B5 revision of the POH/AFM Incorporates B6 revision of the POH/AFM Incorporates B7 revision of the POH/AFM Incorporates B8 revision of the POH/AFM Incorporates B9 revision of the POH/AFM Incorporates B10 revision of the POH/AFM

TOTAL NUMBER OF PAGES IN THIS PUBLICATION IS 142, CONSISTING OF THE FOLLOWING: Page No.

*Revision No.

Page No.

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

FEBRUARY 2007

*Revision No.

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

A

P/N 130-590031-73D9


Raytheon Aircraft Company, which has been renamed Hawker Beechcraft Corporation, is now owned by Hawker Beechcraft, Inc. Neither Hawker Beechcraft, Inc. nor Hawker Beechcraft Corporation are affiliated any longer with Raytheon Company. Any Raytheon marks contained in this document are owned by Raytheon Company and are employed pursuant to a limited license granted by Raytheon Company. *Zero in this column indicates an original page. Revision 1 is a complete reprint. This document is an abbreviation of the checklists and procedures contained in Section III (EMERGENCY PROCEDURES), Section IIIA (ABNORMAL PROCEDURES) and Section IV (NORMAL PROCEDURES) of the Pilot’s Operating Handbook and FAA Approved Airplane Flight Manual (POH/AFM) for the Model B300/B300C (P/N 130590031-71). When Revisions to Sections III, IIIA and IV of the POH/AFM are received, applicable Revisions to this Abbreviated Checklist will be provided and must be updated accordingly. Since this is an Abbreviated Checklist, most explanatory items, notes and cautions have been omitted for brevity, although applicable warnings have not. Consequently, users of this Abbreviated Checklist must be familiar with and operate the airplane in accordance with the official applicable POH/AFM.

P/N 130-590031-73D9

B

FEBRUARY 2007


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 P/N 130-590031-73D3

N-i

JULY 2002

PILOT CHECKLIST–BEECH MODEL B300/B300C 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 MANUAL EXTENSION .......................................................................................N-36

FEBRUARY 1999

N-ii

P/N 130-590031-73D


All airspeeds quoted in this section are indicated airspeeds (IAS) and assume 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

P/N 130-590031-73D6

N-1

OCTOBER 2004

PILOT CHECKLIST–BEECH MODEL B300/B300C

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 Inspection may be omitted except for items marked with a “+” (Fuel Tank Caps and Engine Oil Quantity/Filler Cap need 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-TEST Check sign illumination, then OFF-RESET 4. Forward Exit Sign................................................................ON-TEST Check 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 Continued on Next Page P/N 130-590031-73D6

N-3

OCTOBER 2004


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 °C

-40 -40

-20 -29

0 -18

20 -7

40 4

60 16

80 27

100 38

120 49

PSI Range

190 to 240

220 to 275

250 to 315

290 to 365

340 to 420

390 to 480

455 to 550

525 to 635

605 to 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


PREFLIGHT INSPECTION (Cont) 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

P/N 130-590031-73D

N-5

FEBRUARY 1999


PREFLIGHT INSPECTION (Cont) 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


PREFLIGHT INSPECTION (Cont) 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, and Static 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 and Aft Compartment Drain Tubes ................................................CLEAR 4. Relief Tube .............................................................................CLEAR

P/N 130-590031-73D

N-7

FEBRUARY 1999


BEFORE ENGINE STARTING NOTE Items marked with an “*” may be omitted at pilot’s discretion after the first flight of each day. 1. Weight, CG, Performance, and V-Speeds ........................CHECKED

WARNING Only a crew member or properly trained ground personnel should close and lock the airstair door and cargo 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

OCTOBER 2004

N-8

P/N 130-590031-73D6


BEFORE ENGINE STARTING (Cont) c. Condition Levers ..................................................FUEL CUTOFF d. Oxygen Controls: 1) Passenger Manual Drop-Out .........CONFIRM PUSHED OFF 2) System Ready .................................................CONFIRM ON e. EFIS Power (if installed) ........................................................OFF f. Landing Gear Alternate Extension Handle....................STOWED 16. Copilot’s Subpanel and Instrument Panel ..............................CHECK a. Window Defog .......................................................................OFF b. Vent Blower ........................................................................AUTO c. Cabin Temp Mode .................................................................OFF d. Environmental Bleed Air .......................................................LOW e. Bleed Air Valves ........................................................ENVIR OFF f. Aft Blower ..............................................................................OFF g. Electric Heat ..........................................................................OFF h. Aft Heat ................................................................AS REQUIRED i. 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 ............................................TEST Left & Right [ENG FIRE] – ILLUMINATED Left & Right [EXTINGUISHER PUSH] & [DISCHARGED] – ILLUMINATED

P/N 130-590031-73D6

N-9

OCTOBER 2004


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 hung start has been corrected.

NO LIGHT START If no ITT rise is observed within 10 seconds after moving the Condition Lever to LOW IDLE: 1. Condition Lever..........................................................FUEL CUTOFF 2. Ignition and Engine Start .............................................................OFF 3. Allow 5 minutes for fuel to drain and starter to cool, then follow ENGINE CLEARING Procedure.

ENGINE CLEARING 1. Condition Lever..........................................................FUEL CUTOFF 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.

P/N 130-590031-73D9

N-11

FEBRUARY 2007


BEFORE TAXI NOTE Items marked with an “*” may be omitted at pilot’s discretion after the first flight of each day. *1. 2. 3. 4. 5. 6. 7. 8.

9. 10. 11. 12. 13. 14.

15. 16.

17.

EIectrical System (N-26) ........................................................CHECK Inverters (N-27) ............................................................CHECK & ON Avionics Master .............................................................................ON Master Panel and Cockpit Lights ...............................AS REQUIRED Mic Switches .......................................................................NORMAL Cabin Lights ...............................................................AS REQUIRED Furnishings ................................................................AS REQUIRED Cabin Sign: a. Standard Configuration...........................................NO SMK/FSB b. No Smoking Configuration.....................................................FSB Standby Horizon (if installed) ........................................................ON Prop Sync......................................................................................ON Exterior Lights ............................................................AS REQUIRED EFIS Power (if installed)................................................................ON Environmental System Controls (N-28) .......................................SET Flight and Engine Instruments ...............................................CHECK a. Altimeters ................................................................................SET b. Standby Horizon (if installed) .........................................UNCAGE Flaps ..............................................................................................UP Flight Controls...................................CHECK FOR FULL FREEDOM OF MOVEMENT AND PROPER DIRECTION OF TRAVEL Brakes ...............................................................RELEASE & CHECK

BEFORE TAKEOFF (RUNUP) NOTE Items marked with an “*” may be omitted at pilot’s discretion after the first flight of each day. 1. 2. 3. *4. *5. 6. 7. 8. *9.

Avionics and Radar ................................................................CHECK Pressurization (N-29)...................CHECK AS REQUIRED AND SET Autopilot (N-29) ......................................................................CHECK Yaw Damp (N-30) ..................................................................CHECK EIectric Pitch Trim (N-30 ........................................................CHECK Trim Tabs.....................................................................................SET Engine Controls Friction Locks ....................................................SET Flaps......................................................................CHECK AND SET 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 REQUIRED a. Windshield Anti-ice................................NORMAL/HI (if required) b. Prop Deice.......................................................AUTO (if required) c. Left and Right Fuel Vent Heat .................................................ON d. Stall Warning Heat ..................................................................ON e. 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 P/N 130-590031-73D9

N-13

FEBRUARY 2007


TAKEOFF WARNING 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 7. Flaps (at 125 knots, minimum) ......................................................UP

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

FEBRUARY 2007

N-14

P/N 130-590031-73D9


CRUISE WARNING Do not lift Power Levers in flight 1. Cruise Power..........................................SET PER CRUISE POWER TABLES OR GRAPHS 2. Autofeather ..................................................................................OFF 3. Aft Blower...................................................................AS REQUIRED 4. Engine Instruments............................................................MONITOR 5. Fuel Gages ........................................................................MONITOR (ensure that fuel is being transferred from auxiliary tanks) Icing Conditions

WARNING Due to distortion of the wing airfoil, an accumulation of one inch of ice on the leading edges can cause a loss in rate of climb of 500 FPM, a cruise speed reduction of up to 75 knots TAS, as well as a significant buffet and stall speed increase (up to 15 knots IAS). Even after cycling the deicing boots, the ice accumulation remaining on the boots and unprotected areas of the airplane can cause large performance losses. For the same reason, the aural stall warning system may not be accurate and should not be relied upon. However, with ice accumulation on the airplane, significant aerodynamic buffet will occur in advance of the stall. Maintain a comfortable margin of airspeed above the normal stall airspeed. In order to minimize ice accumulation on unprotected surfaces of the wing, maintain a minimum of 140 knots during operations in sustained icing conditions. In the event of windshield icing, reduce airspeed to 226 knots or below. Prior to a landing approach, cycle the deicing boots 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] – ILLUMINATED b. Check for proper operation by noting torque drop.

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

P/N 130-590031-73D1

N-15

OCTOBER 2000


CRUISE (Cont) 2. Engine Auto-lgnition....................................................................ARM 3. Prop Deice ................................................................................AUTO a. The system may be operated continuously in flight, and will function automatically until the switch is turned off. b. Relieve propeller imbalance due to ice by increasing rpm briefly and returning to the desired setting. Repeat as necessary. 4. Surface Deice

WARNING All components of the surface deice system must be monitored during icing flight to ensure the system is functioning normally. These components include: Pneumatic Pressure Gage. The gage should indicate 12.0–20.0 psi before boots are activated. The pressure will momentarily decrease when the boots are activated. Gyro Suction Gage. The gage should indicate in the area of the green arc corresponding to the airplane altitude. The vacuum will momentarily decrease when the boots are activated. WING DEICE & TAIL DEICE annunciators. The WING DEICE annunciator will illuminate within 6 seconds and the TAIL DEICE annunciator will illuminate within 10 seconds of switch activation when using the SINGLE mode. All annunciators will illuminate within 6 seconds of switch activation when using the MANUAL mode. Pneumatic Boots. Visually monitor the boots, where possible, to ensure ice is being removed. If either surface deice annunciator fails to illuminate or extinguish during a boot cycle, refer to Surface Deice Failure 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 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 PRESSURIZATION CONTROLLER SETTING FOR LANDING

Closest Altimeter Setting

Add to Airport Elevation

Closest Altimeter Setting (Cont)

Add to Airport Elevation (Cont)

28.00

+2400

29.50

+900

28.10

+2300

29.60

+800

28.20

+2200

29.70

+700

28.30

+2100

29.80

+600

28.40

+2000

29.90

+500

28.50

+1900

30.00

+400

28.60

+1800

30.10

+300

28.70

+1700

30.20

+200

28.80

+1600

30.30

+100

28.90

+1500

30.40

0

29.00

+1400

30.50

-100

29.10

+1300

30.60

-200

29.20

+1200

30.70

-300

29.30

+1100

30.80

-400

29.40

+1000

30.90

-500

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

P/N 130-590031-73D2

N-17

SEPTEMBER 2001


BEFORE LANDING 1. Approach Speeds ..............................................................CONFIRM • Landing (VREF) • Approach Climb (VREF + 10 Knots) • Balked Landing (VREF) LANDING APPROACH SPEED 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

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


STEEP APPROACH LANDING Prior to the Final Approach Fix, or no later than 3 nm from the runway during a visual approach: 1. TAWS (if installed) ...........ACTIVATE STEEP APPROACH SWITCH 2. Prop Levers ............................................................FULL FORWARD 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 8. Brakes........................................................................AS REQUIRED

P/N 130-590031-73D3

N-18A

JULY 2002


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 6. Prop Levers ............................................................FULL FORWARD After Touchdown: 7. Power Levers ..........................................LIFT THROUGH GROUND FINE AND LIFT TO REVERSE 8. Brakes........................................................................AS REQUIRED 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 5. Flaps (at 125 knots, minimum) ......................................................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

P/N 130-590031-73D1

N-19

OCTOBER 2000


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

*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 RETURN TO PAGE N-4, STEP 24

*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) P/N 130-590031-73D8

N-21

APRIL 2006


*OXYGEN DURATION NOTE A bottle pressure of 1850 psig at 15° C is fully charged (100% capacity). Read duration directly from the following table. 1. Read the oxygen pressure from the gage. 2. Read the IOAT (with battery on). (Assume IOAT to be equal to BOTTLE 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 by multiplying the full bottle duration by the percent of usable capacity, e.g., a. Pilot and copilot with masks set at 100% plus 6 passengers = 10 people using oxygen.

NOTE Pilot and copilot are each counted as 2 people with the diluter 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) STATED CYLINDER

*NUMBER OF PEOPLE USING 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 the 100% or EMERG mode.

RETURN TO PAGE N-4, STEP 1 OR PAGE N-8, STEP 13.

P/N 130-590031-73D3

N-23

JULY 2002


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 align within the indicator windows. 4. Check the engagement of both upper door hooks by means of the illuminated viewing ports. 5. Attempt to turn handle to unlocked position without depressing the release button. RETURN TO PAGE N-8, STEP 3

LOCKING THE CARGO DOOR (B300C) 1. Check upper handle position – closed and latched. (Observe through the handle access cover window.) 2. Check that the orange index marks on each of the four rotary cam locks align within the indicator windows. 3. Check lower pin latch handle position – closed and latched. (Observe through the handle access cover window.) 4. Check that the orange-colored indicator aligns with orange stripe on carrier rod. (Observe through window at lower left corner.) RETURN TO PAGE N-8, STEP 4

LOCKING THE AIRSTAIR DOOR (B300C) 1. Close and lock the door. 2. Check the position of the safety arm and diaphragm plunger. (Lift the door step) 3. Check that the orange index marks on each of the six rotary cam locks align within the indicator windows. RETURN TO PAGE N-8, STEP 5

*FUEL SYSTEM 1. Firewall Fuel Valves ...............................................................CLOSE Left & Right [EXTINGUISHER PUSH] & [CLOSED] – ILLUMINATED 2. Standby Pumps .............................................................................ON [L FUEL PRES LO] & [R FUEL PRES LO] – ILLUMINATED 3. Firewall Fuel Valves .................................................................OPEN Left & 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 RETURN TO PAGE N-9, STEP 22

ENGINE STARTING (EXTERNAL POWER)

CAUTION NEVER CONNECT AN EXTERNAL POWER SOURCE TO THE AIRPLANE UNLESS A BATTERY INDICATING A CHARGE OF AT LEAST 20 VOLTS IS IN THE AIRPLANE. If the battery voltage is less than 20 volts, the battery must be recharged, or replaced with a battery indicating at least 20 volts, before connecting 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 OFF CONNECT 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) P/N 130-590031-73D3

N-25

JULY 2002


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 OFF DISCONNECT 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 31. Prop Levers ............................................................FULL FORWARD 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% RETURN TO PAGE N-12, BEFORE TAXI, STEP 2

INVERTERS NOTE Items marked with an “*” may be omitted at pilot’s discretion after the first flight of each day. 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 RETURN TO PAGE N-12, BEFORE TAXI, STEP 3

P/N 130-590031-73D9

N-27

FEBRUARY 2007


ENVIRONMENTAL SYSTEM Observe N1, ITT, and generator limits if air conditioning or electric heat is used. 1. Vent Blower................................................................AS REQUIRED Vent Blower Mode

Cabin Temp Mode Selection

Vent Blower Speed

Auto

Off

Off

Auto

Auto, Man Heat, Man Cool

Low

Lo

Any

Low

High

Any

High

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. 6. Aft Blower...................................................................AS REQUIRED a. For maximum cooling, the vent blower should be selected to HIGH, and the aft blower should be selected on. b. For maximum heating without electric heat, the vent blower should be selected to HIGH, the aft blower should be selected off, 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 the Cabin/Cockpit Air Control fully out if increased windshield defrost airflow is required. RETURN TO PAGE N-12, STEP 14

FEBRUARY 2007

N-28

P/N 130-590031-73D9


PRESSURIZATION NOTE Items marked with an “*” may be omitted at pilot’s discretion after the first flight of each day. 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 field pressure 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 cruise altitude plus 1,000 feet. This setting must not result in an outer scale (CABIN ALT) indication of less than 500 feet above departure 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 travels nose-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. RETURN TO PAGE N-12, BEFORE TAKEOFF (RUNUP), STEP 4

P/N 130-590031-73D6

N-29

OCTOBER 2004


*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 RETURN TO PAGE N-12, BEFORE TAKEOFF (RUNUP), STEP 5

*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 trim operates 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

WARNING Operation of the electric pitch trim system should occur only when both elements of the dual-element switch are activated. Any movement of the elevator trim wheel while activating only one element denotes a system malfunction. The electric pitch trim must then be turned off and the flight conducted only by manual operation of the elevator trim control. RETURN TO PAGE N-12, BEFORE TAKEOFF (RUNUP), STEP 6

*OVERSPEED GOVERNORS/RUDDER BOOST 1. Rudder Boost Switch .............................................RUDDER BOOST 2. Prop Levers ............................................................FULL FORWARD 3. Prop Governor Test Switch........................................HOLD TO GOV 4. Power Levers (Individually) ...................INCREASE UNTIL PROP IS STABILIZED AT 1500 TO 1610 RPM. CONTINUE TO INCREASE UNTIL RUDDER MOVEMENT IS NOTED (right power lever, right rudder, left power lever, left rudder. Observe ITT and torque limits.) AUGUST 2003

N-30

P/N 130-590031-73D4


*OVERSPEED GOVERNORS/RUDDER BOOST (Cont) 5. AP/Trim Disconnect .............................................DEPRESS TO 1ST LEVEL 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 RETURN TO PAGE N-12, BEFORE TAKEOFF (RUNUP), STEP 10

*LOW PITCH STOPS AND PRIMARY GOVERNORS 1. Prop Levers ............................................................FULL FORWARD 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 decreases then 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 RETURN TO PAGE N-12, BEFORE TAKEOFF (RUNUP), STEP 11

*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 ANNUNCIATOR EXTINGUISHED b. At approximately 10% torque – BOTH ANNUNCIATORS EXTINGUISHED (prop starts to feather) 4. Power Levers..............................................................................IDLE [L AUTO FEATHER] & [R AUTO FEATHER] – EXTINGUISHED (neither prop feathers) 5. Autofeather Switch .............................................................RELEASE RETURN TO PAGE N-13, BEFORE TAKEOFF (RUNUP), STEP 12

P/N 130-590031-73D

N-31

FEBRUARY 1999


*INSTRUMENT VACUUM AND DEICE PRESSURE 1. Left Bleed Air Switch .........................................PNEU & ENVIR OFF a. Pneumatic Pressure and Gyro Suction Gages..............NORMAL PRESSURE b. [L BLEED FAIL] & [R BLEED FAIL] ...................EXTINGUISHED 2. Right Bleed Air Switch.......................................PNEU & ENVIR OFF a. Pneumatic Pressure and Gyro Suction Gages ...................ZERO PRESSURE b. [L BLEED FAIL] & [R BLEED FAIL] ......................ILLUMINATED 3. Left Bleed Air Switch......................................OPEN OR ENVIR OFF a. Pneumatic Pressure and Gyro Suction Gages..............NORMAL PRESSURE b. [L BLEED FAIL] & [R BLEED FAIL] ...................EXTINGUISHED 4. Right Bleed Air Switch ...................................OPEN OR ENVIR OFF RETURN TO PAGE N-13, BEFORE TAKEOFF (RUNUP), STEP 15

*ENGINE ANTI-ICE

WARNING Either the MAIN or STANDBY actuator must be operational 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

RETURN TO PAGE N-13, BEFORE TAKEOFF (RUNUP), STEP 16

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 the manual 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

P/N 130-590031-73D

N-33

FEBRUARY 1999


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 POSSIBLE FOR INFLATION AND HOLD DOWN d. Inflation Time......................................6 SECONDS FOR WINGS FOLLOWED 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, WHERE POSSIBLE, FOR INFLATION 5. Surface Deice Switch .........................................................RELEASE a. [WING DEICE] & [TAIL DEICE] .........................EXTINGUISHED b. Boots ..............................................CHECK VISUALLY, WHERE POSSIBLE, FOR HOLD DOWN 6. Condition Levers................................................................LOW IDLE RETURN TO PAGE N-13, STEP 17

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 listed below. By using this power setting to establish zero thrust, one avoids the inherent delays of restarting a shut-down engine and preserves almost instant power to counter any attendant hazard. 1. Prop ...................................................................................1700 RPM 2. Power ............................................................................5% TORQUE

NOTE This setting will approximate zero thrust at low altitudes using recommended one-engine-inoperative climb speeds.

WARNING INTENTIONAL IN-FLIGHT ENGINE CUTS SHOULD BE SIMULATED BY RETARDING THE POWER LEVER TO ZERO THRUST AT OR ABOVE THE VSSE SPEED OF 110 KNOTS. For training, this setting will approximate zero thrust at low altitudes using recommended one-engine inoperative climb speeds. The propeller autofeather system is disabled with a power lever retarded.

PRACTICE DEMONSTRATION OF VMCA

WARNING INTENTIONAL IN-FLIGHT ENGINE CUTS SHOULD BE SIMULATED BY RETARDING THE POWER LEVER TO ZERO THRUST AT OR ABOVE THE VSSE SPEED OF 110 KNOTS. For training, this setting will approximate zero thrust at low altitudes using recommended one-engine inoperative climb speeds. The propeller autofeather system is disabled with a power lever retarded.

Continued on Next Page. P/N 130-590031-73D

N-35

FEBRUARY 1999


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 KNOT PER 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 PRACTICE MANUAL EXTENSION After a practice manual extension of the landing gear, the gear may be retracted 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


#1 AC BUS

#2 AC BUS

8

8 DOOR UNLOCKED

7 L FUEL PRES LO

R FUEL PRES LO

4

4

CABIN ALT HI

PASS OXYGEN ON

12

12

CABIN DIFF HI

12 L OIL PRES LO

R OIL PRES LO

3

3 L BLEED FAIL

R BLEED FAIL

13

13

ENG FIRE

2 L DC GEN

R DC GEN

9

P/N 130-590031-73D8

9

E-i

APRIL 2006


PILOT NOTES

FEBRUARY 1999

E-ii

P/N 130-590031-73D

international

EMERGENCY PROCEDURES 1

EMERGENCY AIRSPEEDS ENGINE FAILURE ENGINE FIRE OR FAILURE IN FLIGHT ENGINE FIRE ON GROUND EMERGENCY ENGINE SHUTDOWN ON THE GROUND

2

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 MINIMUM CONTROL SPEED (VMCA) OIL PRESSURE LOW

3

FUEL SYSTEM FUEL PRESSURE LOW

4

SMOKE AND FUME ELIMINATION WINDSHIELD ELECTRICAL FAULT

5

ELECTRICAL SMOKE OR FIRE ENVIRONMENTAL SYSTEM SMOKE OR FUMES

6

AIRSTAIR DOOR/CARGO DOOR UNLOCKED EMERGENCY DESCENT EMERGENCY LANDING

7

GLIDE ELECTRICAL SINGLE INVERTER FAILURE DUAL INVERTER FAILURE

8

DUAL GENERATOR FAILURE LOAD MANAGEMENT WITH A DUAL GENERATOR FAILURE

9

FLIGHT CONTROLS UNSCHEDULED ELECTRIC PITCH TRIM ACTIVATION UNSCHEDULED RUDDER BOOST ACTIVATION

10

ENVIRONMENTAL SYSTEMS USE OF OXYGEN

11

PRESSURIZATION LOSS HIGH DIFFERENTIAL PRESSURE AUTO–DEPLOYMENT OXYGEN SYSTEM FAILURE

12

BLEED AIR FAIL EMERGENCY EXIT

13

SPINS

14

P/N 130-590031-73D1

E-1

OCTOBER 2000

EMERGENCY

FlightSafety


1

PILOT NOTES

FEBRUARY 1999

E-2

P/N 130-590031-73D


All airspeeds quoted in this section are Indicated Airspeeds (IAS) and assume zero instrument error. Closed [BRACKETS] in this section denote annunciator(s)

EMERGENCY AIRSPEEDS (15,000 LBS (6804 KG)) One-Engine-lnoperative Best-Angle-of-Climb (VXSE)...........................................................125 Knots One-Engine-lnoperative Best-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

P/N 130-590031-73D

E-3

FEBRUARY 1999

1


PILOT NOTES

2

FEBRUARY 1999

E-4

P/N 130-590031-73D


ENGINE FAILURE ENGINE FIRE OR FAILURE IN FLIGHT

ENG FIRE

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

ENG FIRE

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 ON THE 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

P/N 130-590031-73D9

E-5

FEBRUARY 2007

2


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)

3 WARNING Do not use reverse thrust with one engine inoperative. Care must be exercised when using single-engine ground fine on surfaces with reduced traction.

ENGINE FAILURE DURING TAKEOFF (AT OR ABOVE V1) — TAKEOFF CONTINUED 1. VR Speed ......................................ROTATE TO APPROXIMATELY 10° PITCH ATTITUDE 2. Landing Gear (when positive climb established) ....................UP 3. Airspeed ..........................................MAINTAIN V2 TO 400 FT AGL 4. Propeller (inoperative engine) ....................VERIFY FEATHERED

WARNING Do not retard the failed engine power lever until the autofeather system has completely stopped propeller rotation. 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 cleanup procedures 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 9. Brake Deice (if installed).............................................................OFF 10. Electrical Load ..................................................................MONITOR

FEBRUARY 2007

E-6

P/N 130-590031-73D9


ENGINE FAILURE IN FLIGHT BELOW AIR MINIMUM CONTROL 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)

3

OIL PRESSURE LOW

L OIL PRES LO

OR

R OIL PRES LO

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 power required to sustain flight.

P/N 130-590031-73D1

E-7

OCTOBER 2000


PILOT NOTES

4

FEBRUARY 1999

E-8

P/N 130-590031-73D


FUEL SYSTEM FUEL PRESSURE LOW

L FUEL PRES LO

OR

R FUEL PRES LO

1. Standby Pump (failed side) ..........................................................ON 2. [FUEL PRES LO] ....................................................EXTINGUISHED 3. Oil Temperature Gage (failed side) ..................................MONITOR

4

P/N 130-590031-73D

E-9

FEBRUARY 1999


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 the pilot’s or copilot’s windshield, the opposite windshield (without the overheat condition) may be operated in the NORMAL or HI windshield heat mode.

P/N 130-590031-73D1

E-11

OCTOBER 2000

5


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

6

10. Cabin Air ........................................................PULL TO DECREASE 11. Cockpit Door............................................................................OPEN

WARNING Dissipation of smoke is not sufficient evidence that a fire has been extinguished. If it cannot be visually confirmed that 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 RESTORE COMM 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 of the following procedures may be used. Verify proper voltage on the voltmeter. 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

Continued on Next Page OCTOBER 2000

E-12

P/N 130-590031-73D1


b. To restore Right Generator Bus and Triple Fed Bus only: 1) Gen Ties ....................................................................OPEN 2) Right Generator .....................................RESET, THEN ON 3) Avionics Master (if required) ...........................................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 5) Avionics Master (if required) ...........................................ON d. To restore the Battery Bus, Triple Fed Bus, and Center Bus only: 1) Battery ............................................................................ON 2) Avionics Master (if required) ...........................................ON

ENVIRONMENTAL SYSTEM SMOKE OR FUMES 6 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. 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 15. Land ..............................................NEAREST SUITABLE AIRPORT

P/N 130-590031-73D9

E-13

FEBRUARY 2007


AIRSTAIR DOOR/CARGO DOOR UNLOCKED

DOOR UNLOCKED

WARNING Do not attempt to check the security of the airstair door or cargo door in flight. Remain as far from the door as possible with seatbelts securely fastened.

If The [DOOR UNLOCKED] Illuminates, Or If An Unlatched Airstair Door/Cargo Door Is Suspected: 1. All Occupants ..................................SEATED WITH SEAT BELTS SECURELY FASTENED 2. Cabin Sign ..................................................................................FSB

7

3. Cabin Differential Pressure..............REDUCE TO LOWEST VALUE PRACTICAL (zero preferred) a. Descend and/or b. Select higher cabin altitude setting. 4. Oxygen......................................................................AS REQUIRED 5. Land ..............................................NEAREST SUITABLE AIRPORT

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

OCTOBER 2004

E-14

P/N 130-590031-73D6


EMERGENCY LANDING 1. Approach Speed (VREF).....................................................CONFIRM LANDING APPROACH SPEED 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

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 P/N 130-590031-73D1

E-15

OCTOBER 2000

7


GLIDE 1. Landing Gear .........................................................................UP 2. Flaps .......................................................................................UP

WARNING Do not feather second engine propeller if a No Starter Assist Air Start is to be conducted. Air starts with a windmilling propeller will result in lower starting temperatures. Refer to Abnormal Procedures for Air Start procedures.

3. Prop Levers ................................................................FEATHERED 4. Airspeed........................................................................135 KNOTS 5. Glide Ratio..............2.3 nautical miles for each 1000 feet of altitude. Decrease by 0.2 nautical miles for each 10 knots of headwind

8

OCTOBER 2000

E-16

P/N 130-590031-73D1


ELECTRICAL SINGLE INVERTER FAILURE

#1 AC BUS

OR

#2 AC BUS

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 Bus circuit breaker is also inoperative, set engine fuel flow to match the fuel flow on the side of the operative torque meter. Observe ITT limits.

DUAL INVERTER FAILURE

#1 AC BUS

&

#2 AC BUS

8

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: 4. Prop Levers ...........................................................FULL FORWARD 5. Power...............SET FUEL FLOW PER CRUISE POWER TABLES. IF MANEUVERING, DO NOT EXCEED 500 POUNDS PER HOUR. OBSERVE ITT LIMITS.

P/N 130-590031-73D

E-17

FEBRUARY 1999


DUAL GENERATOR FAILURE

L DC GEN

&

R DC GEN

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 7. Land ..............................................NEAREST SUITABLE AIRPORT 8. Pressurization .............................................................................SET 9. Altimeter......................................................................................SET 10. Cabin Sign .....................................VERBAL BRIEFING REQUIRED 11. Autofeather ................................................................................ARM 12. Fuel Balance .........................................................................CHECK 13. VREF + 20 ......................................................................DETERMINE

9

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

14. Environmental Bleed Air ............................................................LOW 15. Flaps .............................................................................................UP

FEBRUARY 1999

E-18

P/N 130-590031-73D


DUAL GENERATOR FAILURE (Cont)

L DC GEN

&

R DC GEN

16. Landing Gear ..................................................EXTEND MANUALLY 17. Taxi Light ..................................................................AS REQUIRED 18. Surface Deice ...........................................................AS REQUIRED

When Landing Is Assured: 19. Airspeed ................................................................VREF + 20 KNOTS 20. Yaw Damp ..................................................................................OFF 21. Prop Levers ...........................................................FULL FORWARD 22. Power Levers.............................................................................IDLE

After Touchdown: 23. Power Levers ...................................GROUND FINE OR REVERSE 24. Brakes.......................................................................AS REQUIRED

LOAD MANAGEMENT WITH A DUAL GENERATOR FAILURE

WARNING Do not place the GEN TIES switch in the MAN CLOSE position. This action reconnects the left and right generator bus loads to the battery, severely limiting battery duration.

After a dual generator failure, a charged battery will discharge in the following times: Battery Discharge Rate–Amps 60 50 40 30 20 10

P/N 130-590031-73D

Time to Discharge–Min 27 32 40 54 81 162

E-19

FEBRUARY 1999

9


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 the engines indicates a failure of the system. 1. AP/Trim Disconnect .............................DEPRESS TO 1ST LEVEL AND HOLD 2. Rudder Boost............................................................................OFF

If Condition Persists: 3. Rudder Boost Circuit Breaker...............................................PULL 4. Perform normal landing.

10

P/N 130-590031-73D

E-21

FEBRUARY 1999


PILOT NOTES

11

FEBRUARY 1999

E-22

P/N 130-590031-73D


ENVIRONMENTAL SYSTEMS USE OF OXYGEN WARNING Beards and mustaches should be carefully trimmed so that they will not interfere with the proper sealing of an oxygen mask. The fit of the oxygen mask around the beard or mustache should be checked on the ground for proper sealing. Studies conducted by the military and the FAA conclude that oxygen masks do not seal over beards and mustaches. Hats and “ear-muff” type headsets must be removed prior to donning crew oxygen masks. Headsets and eyeglasses worn by crew members may interfere with quick-donning capabilities.

WARNING The following table sets forth the average time of useful consciousness (TUC) (time from onset of hypoxia until loss of effective performance) at various altitudes. Rapid decompressions can reduce these times to 1/3 – 1/2 of their original value. Cabin Pressure Altitude

TUC

35,000 Feet

1/2–1 Minute

30,000 Feet

1–2 Minutes

25,000 Feet

3–5 Minutes

22,000 Feet

5–10 Minutes

12–18,000 Feet

30 Minutes or more

Crew 1. Oxygen Mask(s) .......................................................................DON 2. Headset(s)...............................DON, OR AUDIO SPEAKER(S) ON 3. Mic Switch(es).......................................................OXYGEN MASK 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

P/N 130-590031-73D1

E-23

OCTOBER 2000

11


USE OF OXYGEN (CONT) Passengers WARNING The highest recommended cabin altitude for sustained flight 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 4. Oxygen Duration ...............................................................CONFIRM (refer to Oxygen Duration in Normal Procedures)

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 is below 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:

12

4. ON/OFF Valve ............................................................................OFF 5. Mask ................................................RETURN TO COMPARTMENT 6. Compartment Cover ..............................................................CLOSE

OCTOBER 2000

E-24

P/N 130-590031-73D1


PRESSURIZATION LOSS

CABIN ALT HI

1. Oxygen Mask(s) .......................................................................DON 2. Headset(s)...............................DON, OR AUDIO SPEAKER(S) ON 3. Mic Switch(es).......................................................OXYGEN MASK 4. Passenger Manual Drop-Out...........................................PULL ON [PASS OXYGEN ON] – ILLUMINATED 5. Descend...................................................................AS REQUIRED 6. Passengers.................................PULL LANYARD PIN, DON MASK

WARNING The highest recommended cabin altitude for sustained flight is 25,000 feet. 7. Range ......................DETERMINE FOR FINAL CRUISE ALTITUDE 8. Oxygen Duration ...............................................................CONFIRM (refer to Oxygen Duration in Normal Procedures)

HIGH DIFFERENTIAL PRESSURE

CABIN DIFF HI

1. Bleed Air Valves ...........................................................ENVIR OFF 2. Oxygen (crew and passengers).............................AS REQUIRED 3. Descend...................................................................AS REQUIRED

AUTO-DEPLOYMENT OXYGEN SYSTEM FAILURE CABIN ALT HI

– ILLUMINATED &

PASS OXYGEN ON

– EXTINGUISHED

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

P/N 130-590031-73D

E-25

FEBRUARY 1999

12


BLEED AIR FAIL

L BLEED FAIL

OR

R BLEED FAIL

Illumination of an annunciator in flight indicates a possible rupture of a bleed 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 3. Brake Deice (if installed).............................................................OFF

13

FEBRUARY 1999

E-26

P/N 130-590031-73D


EMERGENCY EXIT Escape Hatch Handle..........................................................................PULL

13

P/N 130-590031-73D

E-27

FEBRUARY 1999


PILOT NOTES

14

FEBRUARY 1999

E-28

P/N 130-590031-73D


SPINS Intentional spins are prohibited. If an unintentional spin is encountered, perform the following procedure IMMEDIATELY—THE LONGER THE DELAY, THE MORE DIFFICULT RECOVERY WILL BECOME. Steps 1 through 3 should be done AGGRESSIVELY and SIMULTANEOUSLY. The full forward position of the control column may be reduced slightly, if required, to prevent the airplane from exceeding a 90° nose down (inverted) 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.

14

P/N 130-590031-73D3

E-29

JULY 2002


PILOT NOTES

FEBRUARY 1999

E-30

P/N 130-590031-73D


L DC GEN

R DC GEN

6

6

L GEN TIE OPEN

R GEN TIE OPEN

7

7

HYD FLUID LOW

10 PROP GND SOL

3 L CHIP DETECT

R CHIP DETECT

4

4

L NO FUEL XFR

R NO FUEL XFR

5

5 BAT TIE OPEN

7 DUCT OVERTEMP

11 L ENG ICE FAIL

R ENG ICE FAIL

13

13 L FUEL QTY

R FUEL QTY

6

P/N 130-590031-73D

6

BATTERY CHARGE

PITCH TRIM OFF

6

9

A-i

FEBRUARY 1999


FEBRUARY 1999

A-ii

P/N 130-590031-73D


AIR START STARTER ASSIST (PROPELLER FEATHERED OR WINDMILLING)

1

NO STARTER ASSIST (PROPELLER FEATHERED OR WINDMILLING) LANDING FLAPS UP LANDING

2

ONE-ENGINE-INOPERATIVE APPROACH AND LANDING ONE-ENGINE-INOPERATIVE GO-AROUND PROPELLER GROUND IDLE STOP SOLENOID FAILURE

3

ENGINE OIL SYSTEM LOW OIL PRESSURE INDICATION HIGH OIL PRESSURE INDICATION CHIP DETECT

4

FUEL SYSTEM CROSSFEED (ONE-ENGINE-INOPERATIVE OPERATION) NO FUEL TRANSFER

5

FUEL QUANTITY LOW ELECTRICAL SYSTEM SINGLE GENERATOR FAILURE BATTERY CHARGE RATE

6

GENERATOR TIE OPEN BOTH GENERATOR TIES OPEN BATTERY TIE OPEN CIRCUIT BREAKER TRIPPED

7

AVIONICS MASTER POWER SWITCH FAILURE

8

FLIGHT CONTROLS YAW DAMP/RUDDER BOOST SYSTEM INOPERATIVE ELECTRIC PITCH TRIM INOPERATIVE

9

LANDING GEAR SYSTEM HYDRAULIC FLUID LOW LANDING GEAR MANUAL EXTENSION

10

ENVIRONMENTAL SYSTEMS DUCT OVERTEMPERATURE

11

ICE PROTECTION SYSTEMS ELECTROTHERMAL PROPELLER DEICE (AUTO SYSTEM) ELECTROTHERMAL PROPELLER DEICE (MANUAL SYSTEM)

12

ENGINE ANTI-ICE FAILURE SURFACE DEICE FAILURE STATIC AIR SYSTEM PILOT’S ALTERNATE STATIC AIR SOURCE

13

CRACKED OR SHATTERED WINDSHIELD CRACK IN ANY SIDE WINDOW (COCKPIT OR CABIN)

14

SEVERE ICING CONDITIONS (ALTERNATE METHOD OF COMPLIANCE WITH FAA AD 98-04-24)

15

P/N 130-590031-73D4

A-1

AUGUST 2003

ABNORMAL

ABNORMAL PROCEDURES


PILOT NOTES

1 FEBRUARY 1999

A-2

P/N 130-590031-73D

1 FlightSafety international

All airspeeds quoted in this section are Indicated Airspeeds (IAS) and assume zero instrument error. Closed [BRACKETS] in this section denote annunciator(s)

AIR START STARTER ASSIST (PROPELLER FEATHERED OR WINDMILLING) WARNING Air start using the STARTER ASSIST procedures may momentarily cause the loss of attitude display on Electronic Flight Instrument System (EFIS) equipped airplanes, and lead to premature system failures. IF FLIGHT CONDITIONS DO NOT PERMIT THE TEMPORARY LOSS OF ATTITUDE REFERENCE, CONDUCT AIR START USING 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

P/N 130-590031-73D9

A-3

FEBRUARY 2007

2 PILOT CHECKLIST–BEECH MODEL B300/B300C

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 FORWARD CONFIRM 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

FEBRUARY 2007

A-4

P/N 130-590031-73D9


2

LANDING FLAPS UP LANDING 1. Approach Speed (VREF+ 20 Knots) ...................................CONFIRM 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

2. Pressurization .......................................................................CHECK 3. Cabin Sign a. Standard Configuration .........................................NO SMK/FSB b. No Smoking Configuration....................................................FSB 4. Autofeather ................................................................................ARM 5. Flaps .............................................................................................UP 6. Landing Gear..........................................................................DOWN 7. Exterior and Interior Lights........................................AS REQUIRED 8. Radar ........................................................................AS REQUIRED 9. Environmental Bleed Air ............................................................LOW 10. Surface Deice ...........................................................AS REQUIRED

When Landing Assured: 11. Airspeed ................................................................VREF + 20 KNOTS 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

P/N 130-590031-73D

A-5

FEBRUARY 1999


3

ONE-ENGINE-INOPERATIVE APPROACH AND LANDING 1. Approach Speed (VREF).....................................................CONFIRM LANDING APPROACH SPEED 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

2. Pressurization .......................................................................CHECK 3. Cabin Sign a. Standard Configuration .........................................NO SMK/FSB b. No Smoking Configuration....................................................FSB 4. Fuel Balance .........................................................................CHECK 5. Radar ........................................................................AS REQUIRED 6. Environmental Bleed Air ............................................................LOW 7. Surface Deice ...........................................................AS REQUIRED 8. Flaps..............................................................................APPROACH 9. Landing Gear..........................................................................DOWN 10. Exterior and Interior Lights........................................AS REQUIRED 11. Prop Lever.............................................................FULL FORWARD 12. Airspeed ................................................................VREF + 15 KNOTS

When It Is Certain There Is No Possibility Of Go-Around: 13. Flaps.......................................................................................DOWN 14. Airspeed......................................................................................VREF 15. Execute Normal Landing

WARNING Care must be exercised when using single-engine ground fine on surfaces with reduced traction. Do not use reverse thrust with one engine inoperative.

FEBRUARY 1999

A-6

P/N 130-590031-73D


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 STOP SOLENOID FAILURE (FL-115 THRU FL-382, EXCEPT FL-381; FM-10 AND FM-11)

PROP GND SOL

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 ON APPROACH AT 1450 RPM. DO NOT REDUCE POWER UNTIL IN THE FLARE. PLAN ON SLIGHTLY LONGER LANDING DISTANCES.

P/N 130-590031-73D5

A-7

FEBRUARY 2004

3


PILOT NOTES 4

FEBRUARY 1999

A-8

P/N 130-590031-73D


ENGINE OIL SYSTEM LOW OIL PRESSURE INDICATION (60–90 PSI, YELLOW ARC) 4 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

L CHIP DETECT

OR

R CHIP DETECT

1. Engine Instruments...........................................................MONITOR 2. If Abnormal ........SHUT DOWN ENGINE AT PILOT’S DISCRETION

P/N 130-590031-73D5

A-9

FEBRUARY 2004


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 inoperative engine side if the firewall fuel valve is left closed)

WARNING Aux Transfer switch must be in AUTO position on side being crossfeed. If the firewall valve is closed, the auxiliary fuel supply will not be available (usable), and the fuel pressure annunciator will remain illuminated on the side 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

L NO FUEL XFR

OR

R NO FUEL XFR

1. Aux Transfer (same side)................................................OVERRIDE 2. Fuel Quantity ..............MONITOR TO CONFIRM FUEL TRANSFER

P/N 130-590031-73D

A-11

FEBRUARY 1999

5


FUEL QUANTITY LOW

L FUEL QTY

OR

R FUEL QTY

1. Fuel Quantity.........................................................................CHECK If Low Fuel Quantity Is Confirmed By Fuel Gage: 2. Standby Pump..............................................................................ON 3. Fuel Quantity ....................................................................MONITOR 4. Land ..............................................NEAREST SUITABLE AIRPORT

6

FEBRUARY 1999

A-12

P/N 130-590031-73D


ELECTRICAL SYSTEM SINGLE GENERATOR FAILURE

L DC GEN

OR

R DC GEN

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)

BATTERY CHARGE

Ground Operation: 1. Illumination of the [BATTERY CHARGE] indicates an abovenormal charge current. 2. [BATTERY CHARGE] should extinguish within 5 minutes after a battery start. 3. [BATTERY CHARGE] should be extinguished when charge current is 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 without considering the following: a. The battery ammeter must indicate a decreasing charge current to ensure that the battery is not in a state of thermal runaway. b. The [BATTERY CHARGE] must be extinguished in order to meet the battery duration times noted in the Dual Generator Emergency Procedure.

In Flight: In-Flight Illumination Of [BATTERY CHARGE] Indicates A Possible Battery Malfunction. 1. Battery Ammeter ...............................................................MONITOR

If Battery Charge Current Is Decreasing: 2. Battery Ammeter......................................CONTINUE TO MONITOR 3. [BATTERY CHARGE] .............................................EXTINGUISHED (when charge current drops below 6 amps)

If Battery Charge Current Is Not Decreasing: 4. Battery .........................................................................................OFF [BAT TIE OPEN] – ILLUMINATED 5. [BATTERY CHARGE] Extinguished ..........................CONTINUE TO DESTINATION

If [BATTERY CHARGE] Is Illuminated, and Battery Ammeter Continues To Indicate A Charge Current: 6. GEN TIES................................................................................OPEN 7. Land ..............................................NEAREST SUITABLE AIRPORT P/N 130-590031-73D6

A-13

OCTOBER 2004

6


GENERATOR TIE OPEN

L GEN TIE OPEN

OR

R GEN 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:

7

5. Loadmeters.......................................................................MONITOR

BOTH GENERATOR TIES OPEN

L GEN TIE OPEN

&

R GEN TIE 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, Manual Prop Deice, Beacons, Ice Lights, Taxi Light, Landing Gear Motor)

If Battery Is Depleted: 5. Landing Gear ..................................................EXTEND MANUALLY

FEBRUARY 1999

A-14

P/N 130-590031-73D


BATTERY TIE OPEN

BAT 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

P/N 130-590031-73D6

A-15

OCTOBER 2004

7


PILOT NOTES

8

FEBRUARY 1999

A-16

P/N 130-590031-73D


AVIONICS MASTER POWER SWITCH FAILURE If The Avionics Master Pwr Switch Fails To Operate In The On Position: • Avionics Master Circuit Breaker ....................................................PULL

8

P/N 130-590031-73D

A-17

FEBRUARY 1999


PILOT NOTES

9

FEBRUARY 1999

A-18

P/N 130-590031-73D


FLIGHT CONTROLS YAW DAMP/RUDDER BOOST SYSTEM INOPERATIVE 1. Descend to 5000 feet MSL or below (if conditions permit). (If dual aft 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

PITCH TRIM OFF

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

9

P/N 130-590031-73D6

A-19

OCTOBER 2004


PILOT NOTES

10

FEBRUARY 1999

A-20

P/N 130-590031-73D


LANDING GEAR SYSTEM HYDRAULIC FLUID LOW

HYD 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 Gear Control Down, Perform The Following: 1. Landing Gear Relay Circuit Breaker (pilot’s right subpanel).....PULL 2. Landing Gear Control ............................................... CONFIRM DN 3. Alternate Extension Handle ...........................UNSTOW AND PUMP a. Pump handle up and down until the three green gear-down annunciators are illuminated. b. While pumping, do not lower handle to the level of the securing clip 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 Circuit Breaker MUST NOT BE ACTIVATED. b. The landing gear should be considered UNSAFE until the airplane is on jacks and the system has been cycled and checked. If One Or More Green Gear-Down Annunciators Do Not Illuminate For Any 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 the stroke. 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 the stroke. 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 maintain hydraulic pressure until the gear can be mechanically secured. b. DO NOT STOW HANDLE. c. DO NOT ACTIVATE THE LANDING GEAR CONTROL OR THE LANDING GEAR RELAY CIRCUIT BREAKER. d. The landing gear should be considered UNLOCKED until the airplane is on jacks and the system has been cycled and checked.

P/N 130-590031-73D6

A-21

OCTOBER 2004

10


PILOT NOTES

11

FEBRUARY 1999

A-22

P/N 130-590031-73D


ENVIRONMENTAL SYSTEMS DUCT OVERTEMP

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

11

P/N 130-590031-73D

A-23

FEBRUARY 1999


PILOT NOTES

12

FEBRUARY 1999

A-24

P/N 130-590031-73D


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; position the 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 ice removal. 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 ice removal. c. If the Auto Prop Deice circuit breaker switch trips, use manual system. Monitor loadmeters to ensure normal operation. (An approximate 10% increase on each meter is normal.) d. If the Prop Deice Control circuit breaker trips, or the loadmeters indicate the manual system is not working, (no increase or an excessive increase in current drain) avoid icing conditions.

12

ELECTROTHERMAL PROPELLER DEICE (MANUAL SYSTEM) 1. Manual Prop Deice.............................MANUAL FOR 90 SECONDS 2. Loadmeters ..................................MONITOR FOR SMALL NEEDLE DEFLECTION (approx. 10%) 3. Repeat as required.

P/N 130-590031-73D

A-25

FEBRUARY 1999


ENGINE ANTI-ICE FAILURE

L ENG ICE FAIL

OR

R ENG ICE FAIL

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 Inflation Cannot Be Confirmed Visually: 2. Exit icing conditions 3. Refer to POH/AFM Section V, PERFORMANCE, for recommended landing approach speeds and performance with ice on the airplane.

WARNING Intentional stalls are prohibited with a surface deice system failure and ice on the airplane.

13

FEBRUARY 1999

A-26

P/N 130-590031-73D


STATIC AIR SYSTEM PILOT’S ALTERNATE STATIC AIR SOURCE Whenever Any Obstruction Exists In The Normal Static Air System, Or When The Alternate Static Air System Is Desired For Use: 1. Pilot’s Static Air Source ................................................ALTERNATE 2. For Airspeed Calibration and Altimeter Correction, refer to POH/AFM Section V, PERFORMANCE

13

P/N 130-590031-73D

A-27

FEBRUARY 1999


PILOT NOTES

14

FEBRUARY 1999

A-28

P/N 130-590031-73D


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 DIFFERENTIAL PRESSURE OF 2.0 TO 4.6 PSI (A cabin differential pressure of 4.6 psi will produce approximately a 10,500-foot cabin altitude at an airplane altitude of 25,000 feet.) b. Before Landing........................DEPRESSURIZE CABIN PRIOR TO TOUCHDOWN 3. Other In-flight Considerations a. Visibility through a shattered windshield may be sufficiently reduced to dictate flying the airplane from the opposite side of the cockpit. b. Precautions should be taken to prevent particles or flakes of glass from a shattered inner ply of the windshield from interfering with the crew’s vision. c. A cracked outer windshield ply may damage operating windshield 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, LIMITATIONS IN 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, LIMITATIONS IN POH/AFM

P/N 130-590031-73D1

A-29

OCTOBER 2000

14


PILOT NOTES

15

FEBRUARY 1999

A-30

P/N 130-590031-73D


SEVERE ICING CONDITIONS (Alternate Method Of Compliance With FAA AD 98-04-24) THE FOLLOWING WEATHER CONDITIONS MAY BE CONDUCIVE TO SEVERE IN-FLIGHT ICING: • Visible Rain At Temperatures Below 0 Degrees Celsius Ambient Air Temperature. • Droplets That Splash or Splatter On Impact At Temperatures Below 0 Degrees 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 temperatures as cold as -18 degrees Celsius, increased vigilance is warranted at temperatures around freezing with visible moisture present. If the visual cues specified in the Limitations Section of the POH/AFM for identifying severe icing conditions are observed, accomplish the following: 1. Immediately request priority handling from Air Traffic Control to facilitate a route or an altitude change to exit the severe icing conditions in order to avoid extended exposure to flight conditions more severe than those for which the airplane has been certificated. 2. Avoid abrupt and excessive maneuvering that may exacerbate control difficulties. 3. Do not engage the autopilot. 4. If the autopilot is engaged, hold the control wheel firmly and disengage the autopilot. 5. If an unusual roll response or uncommanded roll control movement is observed, reduce the angle-of-attack. 6. Do not extend flaps when holding in icing conditions. Operation with flaps extended can result in a reduced wing angle-of-attack with the possibility of ice forming on the upper surface further aft on the wing than normal, possibly aft of the protected area. 7. If the flaps are extended, do not retract them until the airframe is clear of ice. 8. Report these weather conditions to Air Traffic Control.

15

P/N 130-590031-73D3

A-31

JULY 2002


PILOT NOTES

FEBRUARY 1999

A-32

P/N 130-590031-73D

international

PERFORMANCE WIND COMPONENTS.........................................................................................P-3 TAKE-OFF SPEEDS AND FIELD LENGTHS -- FLAPS UP -(A/C AND BLEED AIR ON) SEA LEVEL........................................................................................................................P-4 1000 FEET.........................................................................................................................P-5 2000 FEET.........................................................................................................................P-6 3000 FEET.........................................................................................................................P-7 4000 FEET.........................................................................................................................P-8 5000 FEET.........................................................................................................................P-9 6000 FEET.......................................................................................................................P-10 7000 FEET.......................................................................................................................P-11 8000 FEET.......................................................................................................................P-12 9000 FEET.......................................................................................................................P-13 10,000 FEET....................................................................................................................P-14 TAKE-OFF SPEEDS AND FIELD LENGTHS -- FLAPS APPROACH -(A/C AND BLEED AIR ON) SEA LEVEL .....................................................................................................................P-15 1000 FEET.......................................................................................................................P-16 2000 FEET.......................................................................................................................P-17 3000 FEET.......................................................................................................................P-18 4000 FEET.......................................................................................................................P-19 5000 FEET.......................................................................................................................P-20 6000 FEET.......................................................................................................................P-21 7000 FEET.......................................................................................................................P-22 8000 FEET.......................................................................................................................P-23 9000 FEET.......................................................................................................................P-24 10,000 FEET....................................................................................................................P-25 ENROUTE MAXIMUM CRUISE POWER AT 1500 RPM.................................................................P-26 NORMAL CRUISE POWER AT 1500 RPM...................................................................P-27

P/N 130-590031-73D

P-1

FEBRUARY 1999

PERFORMANCE

FlightSafety

PERFORMANCE


PILOT NOTES

FEBRUARY 1999

P-2

P/N 130-590031-73D


WIND COMPONENTS

P/N 130-590031-73D

P-3

FEBRUARY 1999


TAKE-OFF SPEEDS AND FIELD LENGTHS- FLAPS UP (A/C AND BLEED AIR ON) PRESSURE ALTITUDE: SEA LEVEL TO WEIGHT 15,000 LBS 6804 KG 14,500 LBS 6577 KG 14,000 LRS 6350 KG 13,500 LBS 6123 KG 13,000 LBS 5897 KG 12,500 LBS 5670 KG 12,000 LBS 5443 KG 11,500 LBS 5216 KG 11,000 LBS 4989 KG 10,500 LBS 4763 KG AND UNDER

OUTSIDE AIR TEMPERATURE – °C -5 5 15 25 35

ITEM

-35

-15

45

52

V1 - KIAS VR - KIAS V2 - KIAS TOFL - FT

106 109 117 3085

106 110 117 3505

106 110 117 3716

106 110 117 3949

106 110 117 4192

106 110 117 4541

108 111 117 5181

110 111 117 5919

111 112 117 6493


105 108 115 2884

104 108 115 3278

104 108 115 3483

104 108 115 3693

104 108 115 3903

104 109 115 4253

106 109 115 4847

108 110 115 5522

109 110 115 6033


103 106 114 2682

102 106 114 3057

102 106 114 3255

102 107 114 3459

102 107 114 3654

102 107 114 3955

104 107 114 4504

106 108 114 5129

107 108 114 5607


101 105 112 2495

101 105 112 2847

100 105 112 3028

100 105 112 3217

100 105 112 3415

101 105 112 3701

102 106 112 4199

104 106 112 4776

105 107 112 5203


101 104 112 2373

99 104 111 2692

99 104 111 2857

99 104 111 3026

99 104 111 3203

99 104 111 3458

100 104 111 3910

102 105 110 4430

103 105 110 4843

V1 - KIAS VR - KIAS V2- KIAS TOFL - FT

100 104 112 2285

99 104 111 2589

99 104 111 2750

98 104 111 2912

98 104 111 3080

98 104 111 3324

99 104 110 3735

100 104 110 4189

101 104 109 4528


99 104 112 2199

98 104 112 2489

98 104 112 2646

98 104 111 2799

97 104 111 2960

97 104 111 3193

99 104 110 3602

100 104 110 4037

101 104 110 4361


99 104 112 2113

98 104 112 2389

97 104 112 2538

97 104 112 2688

97 104 111 2841

97 104 111 3061

98 104 110 3450

99 104 110 3879

100 104 110 4197

V1 - KIAS VR - KIAS V2 - KIAS TOFL- FT

98 104 112 2028

97 104 112 2290

97 104 112 2431

96 104 112 2577

96 104 112 2722

96 104 111 2931

97 104 111 3301

99 104 110 3733

99 104 110 4021


97 104 112 1943

97 104 112 2192

96 104 112 2326

96 104 112 2465

95 104 112 2606

95 104 111 2803

96 104 111 3155

98 104 110 3562

99 104 110 3861

flmmtab3

FEBRUARY 1999

P-4

P/N 130-590031-73D


TO WEIGHT 15,000 LBS 6804 KG 14,500 LBS 6577 KG 14,000LBS 6350 KG 13,500 LBS 6123 KG 13,000 LBS 5897 KG 12,500 LBS 5670 KG 12,000 LBS 5443 KG 11,500 LBS 5216 KG 11,000 LBS 4989 KG 10,500 LBS 4763 KG AND UNDER NOTE:


ITEM

-35

-15

45

52

V1 - KIAS VR - KIAS V2 - KIAS TOFL-FT

106 110 117 3264

106 110 117 3702

106 110 117 3944

106 110 117 4195

106 110 117 4437

107 110 117 4915

108 111 117 5609

110 112 117 6451

111 112 117 7047

V1 - KIAS VR - KiAS V2 - KIAS TOFL- FT

105 108 115 3055

104 108 115 3471

104 108 115 3688

104 108 115 3906

104 108 115 4144

105 109 115 4592

106 109 115 5236

108 110 115 6001

109 110 115 6566

V1 - KIAS VR KIAS V2 - KIAS TOFL.FT

103 106 114 2844

102 106 114 3243

102 107 114 3455

102 107 114 3657

102 107 114 3873

103 107 114 4292

104 108 114 4889

106 108 114 5590

107 109 1l4 6091


101 105 112 2645

100 105 112 3017

100 105 112 3213

100 105 112 3417

100 105 112 3623

101 106 112 3989

102 1C6 112 4543

104 107 112 5188

105 107 112 5658


100 104 111 2508

99 104 111 2848

99 104 111 3023

99 104 111 3206

98 104 111 3393

99 104 111 3733

101 104 110 4226

102 105 110 4821

103 105 110 5239


100 104 112 2413

99 104 111 2741

98 104 111 2908

98 104 111 3083

98 104 111 3263

98 104 111 3582

99 104 110 4014

101 104 109 4509

101 104 109 4879


99 104 112 2321

98 104 112 2637

98 104 111 2796

97 104 111 2963

97 104 111 3135

98 104 111 3439

99 104 110 3871

100 104 110 4356

101 104 109 4707

V1 - KIAS VR - KIAS V2 - KIAS TOFL FT

98 104 112 2229

97 104 112 2529

97 104 112 2685

97 104 111 2843

96 104 111 3007

97 104 111 3297

98 104 110 3725

100 104 110 4192

100 104 109 4524


98 104 112 2138

97 104 112 2423

96 104 112 2574

96 104 112 2725

96 104 111 2880

96 104 111 3157

98 104 110 3560

99 104 110 4020

100 104 110 4346


97 104 112 2049

96 104 112 2318

96 104 112 2462

95 104 112 2608

95 104 112 2755

95 104 111 3018

97 104 110 3400

98 104 110 3864

99 104 110 4157

INTERSECTION IN SHADED AREAS EXCEED OPERATING LIMITATIONS AND ARE PRESENTED AS INTERPOLATION AIDS ONLY. flmmtab3a

P/N 130-590031-73D

P-5

FEBRUARY 1999

TAKEOFF FLAPS UP

TAKE-OFF SPEEDS AND FIELD LENGTHS- FLAPS UP (A/C AND BLEED AIR ON) PRESSURE ALTITUDE: 1000 FT


TAKE-OFF SPEEDS AND FIELD LENGTHS- FLAPS UP (A/C AND BLEED AIR ON) PRESSURE ALTITUDE: 2000 FT TO WEIGHT

TAKEOFF FLAPS UP

15,000 LBS 6804 KG 14,500 LBS 6577 KG 14,000 LBS 6350 KG 13,500 LBS 6123 KG 13,000 LBS 5897 KG 12,500 LBS 5670 KG 12,000 LBS 5443 KG 11,500 LBS 5216 KG 11,000 LBS 4989 KG 10,500 LBS 4763 KG AND UNDER NOTE:


ITEM

-35

-15

45

52


106 110 117 3458

106 110 117 3931

106 110 117 4191

106 110 117 4443

106 110 117 4713

107 111 117 5324

109 111 117 6109

111 112 117 7017

1t2 112 117 7667


104 108 115 3241

104 108 115 3676

104 108 115 3902

104 108 115 4149

104 109 115 4409

105 109 115 4969

107 110 115 5684

109 110 115 6532

110 110 115 7129


103 106 114 3014

102 107 114 3443

102 107 114 3654

102 107 114 3878

102 107 114 4108

103 107 114 4637

105 108 114 5295

107 108 114 6068

108 109 114 6630


101 105 112 2807

100 105 112 3203

100 105 112 3414

100 105 112 3628

100 105 112 3839

101 106 112 4330

103 106 112 4941

105 107 112 5649

106 107 112 6151


100 104 111 2655

99 104 111 3014

99 104 111 3204

98 104 111 3397

98 104 111 3586

99 104 111 4028

101 105 110 4585

103 105 110 5233

104 106 110 5702


99 104 111 2554

98 104 111 2899

98 104 11 3080

98 104 111 3267

98 104 111 3448

99 104 110 3854

100 104 110 4336

101 104 109 4878

102 104 109 5297


98 104 112 2455

98 104 111 2788

97 104 111 2960

97 104 111 3139

97 104 111 3313

98 104 110 3709

99 104 110 4169

100 104 109 4693

101 104 109 5071


90 104 112 2357

97 104 112 2677

97 104 111 2841

96 104 111 3010

96 104 111 3179

97 104 111 3554

99 104 110 4012

100 104 110 4525

100 104 109 4885

V1 - KIAS VR- KIAS V2 - KIAS TOFL - FT

97 104 112 2259

96 104 112 2566

96 104 112 2722

96 104 111 2883

95 104 111 3044

96 104 111 3400

98 104 110 3855

99 104 110 4348

100 104 109 4689


97 104 112 2163

96 104 112 2455

95 104 112 2606

95 104 112 2759

95 104 111 2910

96 104 111 3250

97 104 110 3679

98 104 110 4161

99 104 170 4500

INTERSECTION IN SHADED AREAS EXCEED OPERATING LIMITATIONS AND ARE PRESENTED AS INTERPOLATION AIDS ONLY. flmmtab3b

OCTOBER 2000

P-6

P/N 130-590031-73D1


TAKE-OFF SPEEDS AND FIELD LENGTHS- FLAPS UP (A/C AND BLEED AIR ON) PRESSURE ALTITUDE: 3000 FT TO WEIGHT 15,000 LBS 6804KG 14,500 LBS 6577 KG 14,000 LBS 6350 KG 13,500 LBS 6123 KG 13,000 LBS 5897 KG 12,500 LBS 5670 KG 12,000 LBS 5443 KG 11,500 LBS 5216 KG 11,000 LBS 4989 KG 10,500 LBS 4763 KG AND UNDER NOTE:


ITEM

-35

-15

45

52

V1- KIAS VR - KIAS V2 - KIAS TOFL - FT

106 110 117 3652

106 110 117 4179

106 110 117 4440

106 110 117 4721

106 110 117 5091

108 111 117 5781

110 112 117 6635

112 112 117 7624

– – – –


104 108 115 3426

104 108 115 3831

104 108 115 4147

104 109 115 4416

104 109 115 4765

106 109 115 5392

108 110 115 6181

I09 110 115 7091

111 111 115 7805


102 106 114 3199

102 107 114 3644

102 107 114 3876

102 107 114 4115

102 107 114 4453

104 108 114 5024

105 108 114 5740

107 109 114 6589

109 105 114 7242


101 105 112 2977

100 105 112 3405

100 105 112 3626

100 105 112 3844

100 106 112 4151

102 106 112 4686

193 107 112 5346

105 107 112 6120

107 107 112 6738


99 104 111 2812

99 104 111 3195

98 104 111 3395

98 104 111 3600

99 104 111 3878

100 104 110 4368

102 105 110 4977

103 105 110 5682

104 106 110 6235


99 104 111 2707

98 104 111 3072

98 104 111 3266

98 104 111 3461

98 104 111 3721

99 104 110 4153

100 104 110 4673

101 104 109 5257

102 1O4 109 5771


98 104 112 2602

97 104 111 2953

97 104 111 3137

97 104 111 3326

97 104 111 3572

98 104 110 3999

99 104 110 4505

101 104 109 5063

101 104 109 5490


97 104 112 2496

97 104 111 2834

96 104 111 3009

96 104 111 3191

96 104 111 3425

97 104 110 3842

99 104 110 4323

100 104 109 4865

101 104 109 5290


97 104 112 2391

96 104 112 2715

96 104 111 2882

95 104 111 3056

95 104 111 3279

97 104 110 3674

98 104 110 4153

99 104 110 4683

100 104 109 5095


96 104 112 2289

95 104 112 2599

95 104 112 2757

95 104 111 2922

95 104 111 3136

96 104 111 3509

97 104 110 3983

99 104 110 4495

100 104 109 4877

INTERSECTION IN SHADED AREAS EXCEED OPERATING LIMITATIONS AND ARE PRESENTED AS INTERPOLATION AIDS ONLY. flmmtab3c

P/N 130-590031-73D1

P-7

OCTOBER 2000


TAKE-OFF SPEEDS AND FIELD LENGTHS- FLAPS UP (A/C AND BLEED AIR ON) PRESSURE ALTITUDE: 4000 FT TO WEIGHT 15,000 LBS 6804 KG 14,500 LBS 6577 KG 14,000 LBS 6350 KG 13,500 LBS 6123 KG 13,000 LBS 5897 KG 12,500 LBS 5670 KG 12,000 LBS 5443 KG 11,500 LBS 5216 KG 11,000 LBS 4989 KG 10,500 LBS 4763 KG AND UNDER NOTE:


ITEM

-35

-15

45

52


106 110 117 3879

106 110 117 4429

106 110 117 4719

106 110 117 5016

107 111 117 5531

108 111 117 6300

110 112 117 7219

112 117 117 8326

– – –


104 108 115 3630

104 108 115 4136

104 109 115 4415

104 109 115 4689

104 109 115 5158

106 110 115 5859

108 110 115 6713

110 111 115 7731

– – – –


102 107 114 3399

102 107 114 3866

102 107 114 4114

102 107 114 4370

103 107 114 4819

104 108 114 5454

106 108 114 6244

108 109 114 7177

109 109 114 7960


100 105 112 3161

100 105 112 3617

100 105 112 3843

100 105 112 4083

101 106 112 4503

102 106 112 5079

104 107 112 5796

106 107 112 6665

107 108 112 7380


99 104 111 2977

98 104 111 3387

98 104 111 3600

98 104 111 3821

99 104 111 4191

100 105 110 4728

102 105 110 5388

104 106 110 6181

105 106 110 6839


98 104 111 2864

98 104 111 3258

98 104 111 3461

97 104 111 3671

98 104 110 4022

99 104 110 4490

100 104 109 5039

102 104 109 5732

103 104 109 6324


98 104 111 2755

97 104 111 3130

97 104 111 3325

97 104 111 3526

97 104 110 3860

98 104 110 4316

100 104 110 4853

101 104 109 5473

102 104 108 5993


97 104 112 2645

96 104 111 3002

96 104 111 3191

96 104 111 3382

97 104 111 3699

98 104 110 4148

99 104 110 4671

100 104 109 5264

101 104 109 5761


96 104 112 2535

96 104 111 2875

95 104 111 3056

95 104 111 3239

96 104 111 3538

97 104 110 3978

98 104 110 4477

100 104 108 5051

101 104 109 5531


96 104 112 2424

95 104 112 2751

95 104 111 2922

94 104 111 3099

95 104 111 3381

96 104 111 3797

98 104 110 4297

99 104 109 4854

100 104 109 5306

INTERSECTION IN SHADED AREAS EXCEED OPERATING LIMITATIONS AND ARE PRESENTED AS INTERPOLATION AIDS ONLY. flmmtab3d

OCTOBER 2000

P-8

P/N 130-590031-73D1


TAKE-OFF SPEEDS AND FIELD LENGTHS- FLAPS UP (A/C AND BLEED AIR ON) PRESSURE ALTITUDE: 5000 FT TO WEIGHT 15,000 LBS 6804 KG 14,500 LBS 6577 KG 14,000 LBS 6350 KG 13,500 LBS 6123 KG 13,000LBS 5897 KG 12,500 LBS 5670 KG 12 000 LBS 5443 KG 11,500 LBS 5216 KG 11,000 LBS 4989 KG 10,500 LBS 4763 KG AND UNDER NOTE:


ITEM

-35

-15

45

52


106 110 117 4127

105 110 117 4709

106 110 117 5016

106 110 117 5336

107 111 117 6009

109 111 117 6836

111 112 117 7860

– – – –

– – – –


104 108 115 3854

104 109 115 4405

104 109 115 4689

104 109 115 4995

105 109 115 5605

107 110 115 6372

109 110 115 7318

111 111 115 8476

– – – –


102 107 114 3601

102 107 114 4106

102 107 114 4371

102 107 114 4673

103 108 114 5218

105 108 114 5930

107 109 114 6791

109 109 114 7852

– – – –


100 105 112 3364

100 105 112 383

100 105 112 4084

100 106 112 4356

101 106 112 4872

103 106 112 5518

105 107 112 6313

107 108 112 7285

108 108 112 8154


99 104 111 3158

98 104 111 3592

98 104 111 3822

98 104 111 4067

99 104 110 4545

101 105 110 5128

102 105 110 5848

104 106 110 6752

106 106 110 7529


98 104 111 3037

98 104 111 3454

97 104 111 3672

97 104 111 3904

98 104 110 4328

100 104 110 4838

102 104 109 5437

104 104 109 6951

104 105 109 6951


97 104 111 2919

97 104 111 3319

97 104 111 3527

97 104 111 3749

98 104 110 4178

99 104 110 4669

100 104 109 5244

101 104 109 5950

102 104 108 6551


97 104 111 2801

96 104 111 3184

96 104 111 3383

96 104 111 3593

91 104 110 4000

98 104 110 4481

99 104 109 5039

101 104 109 5712

102 104 108 6296


96 104 112 2685

95 104 111 3050

95 104 111 3240

95 104 111 3440

96 104 111 3826

97 104 110 4300

99 104 110 4842

100 104 109 5485

101 104 109 6047


95 104 112 2570

95 104 111 2916

94 104 111 3100

94 104 111 3289

95 104 111 3655

97 104 110 4116

98 104 110 4634

99 104 109 6262

101 104 109 5799

INTERSECTION IN SHADED AREAS EXCEED OPERATING LIMITATIONS AND ARE PRESENTED AS INTERPOLATION AIDS ONLY. flmmtab3e

P/N 130-590031-73D1

P-9

OCTOBER 2000


TAKE-OFF SPEEDS AND FIELD LENGTHS- FLAPS UP (A/C AND BLEED AIR ON) PRESSURE ALTITUDE: 6000 FT TO WEIGHT 15,000 LBS 6804 KG 14,500 LBS 6577 KG 14,000 LBS 6350 KG 13,500 LBS 6123 KG 13,000LBS 5897 KG 12,500 LBS 5670 KG 12,000 LBS 5443 KG 11,500 LBS 5216 KG 11,000 LBS 4989 KG 10,500 LBS 4763 KG AND UNDER NOTE:


ITEM

-35

-15

45

52


106 110 117 4378

106 110 117 5007

106 110 117 5332

106 111 117 5795

108 111 117 6535

110 112 117 7448

111 112 117 8599

– – – –

– – – –


104 108 115 4087

104 109 115 4681

104 109 115 4989

104 109 115 5405

106 109 115 6093

107 110 115 6931

109 111 115 7981

– – – –

– – – –


102 107 114 3823

102 107 114 4363

102 107 114 4664

102 107 114 5050

104 108 114 5674

105 108 114 6448

107 109 114 7419

– – – –

– – – –


100 105 112 3575

100 105 112 4077

100 106 112 4347

100 106 112 4721

102 106 112 5280

103 107 112 6001

106 107 112 6878

107 108 112 7975

– – – –


98 104 111 3351

98 104 111 3815

98 104 110 4053

98 104 111 4397

100 104 110 4921

101 105 110 5572

103 106 110 6381

105 106 110 7384

106 106 110 8275


98 104 111 3222

97 104 111 3666

97 104 111 3904

98 104 110 4221

98 104 110 4675

100 104 109 5213

101 104 109 5910

103 104 109 6821

104 105 109 7626


97 104 111 3095

97 104 111 3S21

97 104 111 3749

97 104 110 4049

98 104 110 4499

99 104 110 5029

100 104 109 5667

102 104 108 6454

103 104 108 7142


96 104 111 2969

96 104 111 3377

96 104 111 3594

96 104 111 3880

97 104 110 4337

98 104 110 4847

100 104 109 5461

101 104 109 6205

102 104 108 6854

V1 KIAS VR - KIAS V2 - KIAS TOFL - FT

96 104 111 2844

95 104 111 3235

95 104 111 3440

95 104 111 3713

96 104 110 4144

98 104 110 4642

99 104 100 5235

100 104 100 5959

102 104 108 6537


95 104 112 2722

94 104 111 3094

94 104 111 3290

94 104 111 3548

96 104 110 3958

97 104 110 4449

98 104 109 5023

100 104 109 5715

101 104 108 6318

INTERSECTION IN SHADED AREAS EXCEED OPERATING LIMITATIONS AND ARE PRESENTED AS INTERPOLATION AIDS ONLY. flmmtab3f

FEBRUARY 1999

P-10

P/N 130-590031-73D




ITEM

-35

-15

45

52


105 110 117 4659

106 110 117 5324

106 111 117 5696

107 111 117 6295

108 111 117 7109

110 112 117 8140

– – – –

– – – –

– – – –


104 108 115 4354

104 109 115 4981

104 109 115 5315

105 109 115 5878

106 110 115 6632

108 110 115 7551

110 111 115 8752

– – – –

– – – –


102 107 114 4062

102 107 114 4657

102 107 114 4960

103 108 114 5472

104 108 114 6170

106 109 114 7026

108 103 114 8106

– – – –

– – – –


100 105 112 3795

100 106 112 4341

100 106 112 4628

101 106 112 5110

102 106 112 5745

104 107 112 6533

106 107 112 7533

– – – –

– – – –


98 104 111 3555

98 104 111 4058

98 104 110 4319

99 10 110 4767

100 4105 110 5334

102 105 110 6068

104 106 110 6966

106 106 110 8111

– – – –


98 104 111 3418

97 104 111 3899

97 104 110 4153

98 104 110 4544

99 104 110 5043

100 104 109 5645

102 104 109 6450

104 105 109 7480

– – –


97 104 111 3285

97 104 111 3744

96 104 111 3986

97 104 110 4375

98 104 110 4861

99 104 109 5434

101 104 109 6139

102 104 108 7024

103 104 108 7822


96 104 111 3152

96 104 111 3589

96 104 111 3821

96 104 110 4199

97 104 110 4668

99 104 110 5231

100 104 109 5911

102 104 108 6760

103 104 108 7514


95 104 111 3018

95 104 111 3436

95 104 111 3657

96 104 111 4015

97 104 110 4492

98 104 110 5034

99 104 109 5677

101 104 108 6489

102 104 108 7228


95 104 111 2886

94 104 111 3286

94 104 111 3496

95 104 111 3835

96 104 110 4287

97 104 110 4812

99 104 109 5445

100 104 109 6215

102 104 108 6915

INTERSECTION IN SHADED AREAS EXCEED OPERATING LIMITATIONS AND ARE PRESENTED AS INTERPOLATION AIDS ONLY. flmmtab3g

P/N 130-590031-73D1

P-11

OCTOBER 2000


TAKE-OFF SPEEDS AND FIELD LENGTHS- FLAPS UP (A/C AND BLEED AIR ON) PRESSURE ALTITUDE: 8000 FT TO WEIGHT 15,000LBS 6804 KG 14,500 LBS 6577 KG 14,000 LBS 6350 KG 13,500 LBS 6123 KG 13,000 LBS 5897 KG 12,500LBS 5670 KG 12,000 LBS 5443 KG 11,500 LBS 5216 KG 11,000 LBS 4989 KG 10,500LBS 4763 KG AND UNDER NOTE:


ITEM

-35

-15

45

52

V1- KIAS VR - KIAS V2 - KIAS TOFL - FT

105 110 117 4956

106 111 117 5689

106 111 117 6127

107 111 117 6850

109 112 117 7761

111 112 117 8926

– – – –

– – – –

– – – –


104 109 115 4634

104 109 115 5310

104 109 115 5722

105 110 115 6388

107 110 115 7220

109 110 115 8283

– – – –

– – – –

– – – –


102 107 114 4317

102 107 114 4955

102 107 114 5341

103 108 114 5956

105 108 114 6723

107 109 114 7673

109 109 114 8913

– – – –

– – – –


100 105 112 4036

100 106 112 4623

100 106 112 4996

101 106 112 5542

103 107 112 6250

105 107 112 7130

106 108 112 8249

– – – –

– – – –


98 104 111 3778

98 104 110 4314

98 104 110 4641

99 105 110 5166

101 105 110 5811

102 106 110 6616

104 106 110 7634

– – – –

– – – –


97 104 111 3631

97 104 111 4154

97 104 110 4453

98 104 110 4907

99 104 109 5437

100 104 109 6142

102 104 109 7049

104 105 109 8249

– – – –


97 104 111 3487

97 104 111 3987

97 104 110 4286

97 104 110 4721

98 104 110 5250

100 104 109 5893

101 104 108 6683

103 104 108 7702

– – – –


96 104 111 3345

96 104 111 3821

96 104 111 4104

97 104 110 4551

98 104 110 5052

99 104 109 5667

101 104 109 6423

102 104 108 7411

103 104 108 8277


95 104 111 3204

95 104 111 3658

95 104 111 3926

96 104 110 4350

97 104 110 4842

98 104 109 5442

100 104 109 6167

102 104 108 7100

103 104 108 7940


94 104 111 3065

94 104 111 3497

94 104 111 3751

95 104 110 4153

96 104 110 4652

98 104 110 5231

99 104 109 5916

101 104 108 6806

102 104 108 7613

INTERSECTION IN SHADED AREAS EXCEED OPERATING LIMITATIONS AND ARE PRESENTED AS INTERPOLATION AIDS ONLY. flmmtab3h

FEBRUARY 1999

P-12

P/N 130-590031-73D




ITEM

-35

-15

45

52


105 110 117 5271

106 111 117 6070

107 111 117 6653

108 111 117 7466

110 112 117 8500

– – – –

– – – –

– – – –

– – – –


104 109 115 4935

104 109 115 566O

104 109 115 6213

106 110 115 6960

108 110 115 7897

109 111 115 9103

– – – –

– – – –

– – – –


102 107 114 4612

102 107 114 5289

102 108 114 5794

104 108 114 6475

105 109 114 7332

107 109 114 8429

– – – –

– – – –

– – – –


100 105 112 4301

100 106 112 4942

100 106 112 5406

102 106 112 6034

103 107 112 6823

105 107 112 7810

107 108 112 102

– – – –

– – – –


98 104 111 4021

98 104 110 4606

99 104 110 5047

100 105 110 5604

101 105 110 6330

103 106 110 7235

105 106 110 8403

– – – –

– – – –


97 104 111 3864

97 104 110 4418

97 104 110 4801

98 104 110 5299

99 104 109 5902

101 104 109 6699

103 105 109 7745

– – – –

– – – –


97 104 111 3710

96 104 111 4250

97 104 110 4622

98 104 110 5107

99 104 109 5674

100 104 109 6394

102 104 108 7295

103 104 108 8485

– – – –


96 104 111 3557

96 104 111 4071

96 104 110 4442

97 104 110 4903

98 104 110 5466

99 104 109 6148

101 104 108 7008

103 104 108 8146

– – – –


95 104 111 3405

95 104 111 3895

95 104 110 4248

96 104 110 4716

98 104 110 5253

99 104 109 5910

100 104 109 6739

102 104 108 7316

103 104 107 8806


94 104 111 3257

94 104 111 3722

94 104 111 4055

95 104 110 4500

97 104 110 5025

98 104 109 5665

100 104 109 6448

102 104 108 7486

103 104 108 8443

INTERSECTION IN SHADED AREAS EXCEED OPERATING LIMITATIONS AND ARE PRESENTED AS INTERPOLATION AIDS ONLY. flmmtab3i

P/N 130-590031-73D

P-13

FEBRUARY 1999


TAKE-OFF SPEEDS AND FIELD LENGTHS- FLAPS UP (A/C AND BLEED AIR ON) PRESSURE ALTITUDE: 10,000 FT TO WEIGHT 15,000 LBS 6804 KG 14,500 LBS 6577 KG 14,000 LBS 6350 KG 13,500 LBS 6123 KG 13,000 LBS 5897 KG 12,500 LBS 5670 KG 12,000 LBS 5448 KG 11,500 LBS 5216 KG 11,000 LBS 4989 KG 10,5OO LBS 4763 KG AND UNDER NOTE:


ITEM

-35

-15

45

52


106 111 117 5693

106 111 117 6599

107 111 117 7329

109 112 117 8242

110 112 117 9437

– – – –

– – – –

– – – –

– – – –


104 109 115 5316

104 109 115 6178

105 110 115 6823

107 110 115 7666

108 110 115 8754

– – – –

– – – –

– – – –

– – – –


102 107 114 4962

102 108 114 5756

103 108 114 6360

104 108 114 7134

106 109 114 8117

108 109 114 9379

– – – –

– – – –

– – – –


100 106 112 4628

100 106 112 5371

101 106 112 5930

102 107 112 6631

104 107 112 7530

106 108 112 8678

– – – –

– – – –

– – – –


98 104 110 4320

98 104 110 5007

99 105 110 5523

100 105 110 6168

102 106 110 6996

104 106 110 8080

– – – –

– – – –

– – – –


97 104 111 4160

97 104 110 4783

98 104 110 5246

99 104 109 5776

100 104 109 6464

102 104 109 7407

104 105 109 8648

– – – –

– – – –


96 104 111 3993

97 104 110 4613

97 104 110 5041

98 104 110 5575

99 104 109 6224

101 104 109 7032

102 104 108 8088

– – – –

– – – –


96 104 111 3828

96 104 110 4419

96 104 110 4845

97 104 110 5363

99 104 109 5981

100 104 109 6745

102 104 108 7757

– – – –

– – – –


95 104 111 3664

95 104 111 4226

96 104 110 4646

97 104 110 5140

98 104 109 5751

99 104 109 6487

101 104 108 7450

103 104 103 8751

– – – –


94 104 111 3502

94 104 111 4036

95 104 110 4436

96 104 110 4936

97 104 110 5521

99 104 109 6234

100 104 108 7141

102 104 108 8384

– – – –

INTERSECTION IN SHADED AREAS EXCEED OPERATING LIMITATIONS AND ARE PRESENTED AS INTERPOLATION AIDS ONLY. flmmtab3j

FEBRUARY 1999

P-14

P/N 130-590031-73D


TO WEIGHT 15,000 LBS 6804 KG 14,500 LBS 6577 KG 14,000 LBS 6350 KG 13,500 LBS 6123 KG 13,000 LBS 6097 KG 12,500 LBS 5670 KG 12,000 LBS 5443 KG 11,500 LBS 5216 KG 11,000 LBS 4989 KG 10,500 LBS 4763 KG AND UNDER


ITEM

-35

-15

45

52


100 103 109 2387

99 103 109 2733

99 103 109 2916

99 103 109 3103

99 104 109 3300

99 104 109 3612

101 104 109 4154

103 104 109 4746

104 105 109 5199


98 102 107 2260

97 102 107 2541

97 102 107 2712

97 102 107 2889

97 102 107 3068

97 102 107 3354

99 103 107 3862

101 103 107 4407

102 103 107 4826


98 102 107 2179

97 102 107 2450

97 102 107 2607

96 102 107 2774

96 102 107 2939

96 102 106 3181

98 102 106 3629

99 102 106 4114

100 102 105 4476


97 102 107 2099

96 102 107 2365

96 102 107 2515

96 102 107 2675

95 102 107 2836

96 102 107 3066

97 102 106 3482

99 102 106 3968

99 102 106 4314


97 102 108 2020

96 102 107 2282

96 102 107 2425

95 102 107 2578

95 102 107 2736

95 102 107 2955

96 102 106 3346

98 102 106 3828

99 102 106 4169


96 102 108 1947

95 102 108 2201

95 102 107 2338

95 102 107 2484

94 102 107 2638

94 102 107 2847

96 102 106 3216

97 102 106 3662

98 102 106 4007


96 102 108 1879

95 102 108 2122

94 102 108 2253

94 102 107 2392

94 102 107 2539

94 102 107 2742

95 102 107 3091

96 102 106 3505

98 102 106 3850


95 102 108 1812

94 102 108 2044

94 102 108 2169

94 102 108 2301

93 102 108 2441

93 102 107 2637

94 102 107 2968

96 102 106 3362

97 102 106 3675


94 102 108 1744

94 102 108 1966

93 102 108 2085

93 102 108 2211

93 102 108 2344

93 102 107 2534

94 102 107 2847

95 102 106 3223

96 102 106 3513


94 102 108 1678

93 102 108 1889

93 102 108 2002

92 102 108 2122

92 102 108 2248

92 102 107 2428

93 102 107 2729

94 102 107 3085

95 102 106 3360

flmmtab7

P/N 130-590031-73D

P-15

FEBRUARY 1999

TAKEOFF FLAPS APPROACH

TAKE-OFF SPEEDS AND FIELD LENGTHS- FLAPS APPROACH (A/C AND BLEED AIR ON) PRESSURE ALTITUDE: SEA LEVEL


TAKE-OFF SPEEDS AND FIELD LENGTHS- FLAPS APPROACH (A/C AND BLEED AIR ON) PRESSURE ALTITUDE: 1000 FT TO WEIGHT 15,000 LBS 6804 KG 14,500 LBS 6577 KG 14,000 LBS

TAKEOFF FLAPS APPROACH

6350 KG 13,500 LBS 6123 KG 13,000 LBS 5897 KG 12,500 LBS 5670 KG 12,000 LBS 5443 KG 11,500 LBS 5216 KG 11,000 LBS 4989 KG 10,500 LBS 4763 KG AND UNDER


ITEM

-35

-15

45

52

V1 - KIAS VR- -KIAS V2 - KIAS TOFL - FT

99 103 109 2533

99 103 109 2906

99 103 109 3099

99 104 109 3303

99 104 109 3512

100 104 109 3942

102 104 109 4504

103 105 109 5173

105 105 109 5669


98 102 107 2363

97 102 107 2702

97 102 107 2885

97 102 107 3071

97 102 107 3265

98 102 107 3648

100 103 107 4191

101 103 107 4807

102 103 107 5250

V1 - KIAS VR - KIAS V2 - KIAS TOFL - Fl

97 102 107 2294

97 102 107 2598

96 102 107 2771

96 102 107 2941

96 102 107 3117

96 102 106 3442

98 102 106 3933

99 102 106 4464

100 102 105 4872


97 102 107 2210

96 102 107 2506

96 102 107 2672

95 102 107 2839

95 102 107 3007

96 102 106 3316

97 102 106 3782

99 102 106 4303

100 102 105 4676


96 102 107 2129

96 102 107 2417

95 102 107 2575

95 102 107 2739

95 102 107 2900

95 102 107 3192

97 102 106 3624

98 102 106 4149

99 102 105 4504


96 102 108 2055

95 102 107 2330

95 102 107 2481

94 102 107 2641

94 102 107 2795

95 102 107 3072

96 102 106 3478

98 102 106 4003

99 102 106 4337


95 102 108 1982

95 102 108 2246

94 102 107 2390

94 102 107 2542

93 102 107 2693

94 102 107 2956

95 102 106 3343

97 102 106 3824

98 102 106 4175


95 102 108 1910

94 102 108 2161

94 102 108 2299

93 102 108 2443

93 102 107 2592

93 102 107 2841

95 102 106 3210

96 102 106 3654

97 102 106 4007


94 102 108 1839

93 102 108 2078

93 102 108 2209

93 102 108 2346

92 102 108 2489

93 102 107 2728

94 102 107 3078

95 102 106 3498

96 102 106 3821


93 102 108 1768

93 102 108 1996

92 102 108 2120

92 102 108 2250

92 102 108 2385

92 102 107 2617

93 102 107 2946

95 102 106 3347

96 102 106 3647

flmmtab7a

OCTOBER 2000

P-16

P/N 130-590031-73D


TAKE-OFF SPEEDS AND FIELD LENGTHS- FLAPS APPROACH (A/C AND BLEED AIR ON) PRESSURE ALTITUDE: 2000 FT TO WEIGHT 15,000 LBS 6804 KG 14,500 LBS 6577 KG 14,000 LBS 6350 KG 13,500 LBS 6123 KG 13,000 LBS 5897 KG 12,500 LBS 5670 KG 12,000 LBS 5443 KG 11,500 LBS 5216 KG 11,000 LBS 4989 KG 10,500 LBS 4763 KG AND UNDER NOTE:


ITEM

-35

-15

45

52


99 103 109 2693

99 103 109 3089

99 104 109 3300

99 104 109 3516

99 104 109 3744

100 104 109 4274

102 104 109 4904

104 105 109 5636

– – –


98 102 107 2504

97 102 107 2876

97 102 107 3069

97 102 107 3270

97 102 107 3482

98 102 107 3981

100 103 107 4558

102 103 107 5231

103 103 107 5728


97 102 107 2419

96 102 107 2763

96 102 107 2939

96 102 107 3122

96 102 106 3310

97 102 106 3733

98 102 106 4262

100 102 105 4863

101 102 105 5299


95 102 107 2333

96 102 107 2664

95 102 107 2837

95 102 107 3011

95 102 107 3190

96 102 106 3584

98 102 106 4110

99 102 105 4676

100 102 105 5069


96 102 107 2251

95 102 107 2567

95 102 107 2737

95 102 107 2904

94 102 107 3075

95 102 106 3450

97 102 106 3951

99 102 106 4498

100 102 105 4883


95 102 108 2172

95 102 107 2474

94 102 107 2639

94 102 107 2799

94 102 107 2962

95 102 106 3320

96 102 106 3781

98 102 106 4321

99 102 105 4694


95 102 108 2095

94 102 107 2382

94 102 107 2540

93 102 107 2696

93 102 107 2852

94 102 107 3195

96 102 106 3623

98 102 106 4177

98 102 106 4526


94 102 108 2017

94 102 108 2292

93 102 108 2441

93 102 107 2595

93 102 107 2744

94 102 107 3067

95 102 106 3476

97 102 106 3985

98 102 106 4351


94 102 108 1941

93 102 108 2202

93 102 108 2344

92 102 108 2492

92 102 107 2636

93 102 107 2943

94 102 106 3333

96 102 106 3803

97 102 106 4171


93 102 108 1865

92 102 108 2114

92 102 108 2248

92 102 108 2388

91 102 108 2530

92 102 107 2820

93 102 107 3191

95 102 106 3634

96 102 106 3969

INTERSECTION IN SHADED AREAS EXCEED OPERATING LIMITATIONS AND ARE PRESENTED AS INTERPOLATION AIDS ONLY. flmmtab7b

P/N 130-590031-73D

P-17

FEBRUARY 1999


TAKE-OFF SPEEDS AND FIELD LENGTHS- FLAPS APPROACH (A/C AND BLEED AIR ON) PRESSURE ALTITUDE: 3000 FT TO WEIGHT 15,000LBS 6804 KG 14,500 LBS 6577 KG 14,000 LBS 6350 KG 13,500 LBS 6123 KG 13,000 LBS 5897 KG 12,500 LBS 5670 KG 12,000 LBS 5443 KG 11,500 LBS 5216 KG 11,000 LBS 4989 KG 10,500 LBS 4763 KG AND UNDER NOTE:


ITEM

-35

-15

45

52


99 103 109 2867

99 104 109 3291

99 104 109 3515

99 104 109 3747

99 104 109 4090

101 104 109 4648

103 105 109 5324

– – – –

– – – –


97 102 107 2664

97 102 107 3060

97 102 107 3268

97 102 107 3483

97 102 107 3789

99 103 107 4325

101 103 107 4954

102 103 107 5688

– – – –


97 102 107 2563

96 102 107 2932

96 102 107 3121

96 102 107 3320

96 102 106 3579

97 102 106 4067

99 102 106 4614

100 102 105 5275

102 102 105 5801


96 102 107 2473

95 102 107 2829

95 102 107 3010

95 102 107 3200

95 102 106 3450

97 102 106 3898

98 102 106 4451

100 102 105 5053

101 102 105 5526


96 102 107 2385

95 102 107 2729

95 102 107 2902

94 102 107 3084

95 102 107 3325

96 102 106 3738

98 102 106 4288

99 102 105 4877

100 102 105 5320


95 102 107 2300

94 102 107 2632

94 102 107 2798

94 102 107 2971

94 102 107 3203

95 102 105 3592

97 102 106 4116

98 102 106 4690

99 102 105 5121


95 102 108 2217

94 102 107 2533

93 102 107 2695

93 102 107 2861

93 102 107 3081

94 102 106 3453

96 102 106 3937

98 102 106 4504

99 102 105 4932


94 102 108 2134

93 102 108 2435

93 102 107 2594

93 102 107 2752

93 102 107 2961

94 102 107 3317

95 102 106 3768

97 102 106 4346

98 102 106 4740


93 102 108 2052

93 102 108 2338

92 102 108 2491

92 102 107 2644

92 102 107 2842

93 102 107 3183

95 102 106 3609

96 102 106 4139

98 102 106 4555


93 102 108 1971

92 102 108 2242

92 102 108 2388

91 102 108 2537

91 102 107 2726

92 102 107 3051

94 102 106 3453

96 102 106 3945

97 102 106 4371

INTERSECTION IN SHADED AREAS EXCEED OPERATING LIMITATIONS AND ARE PRESENTED AS INTERPOLATION AIDS ONLY. flmmtab7c

FEBRUARY 1999

P-18

P/N 130-590031-73D




ITEM

-35

-15

45

52


99 103 109 3048

99 104 109 3506

99 104 109 3747

99 104 109 4002

100 104 109 4452

101 104 109 5056

103 105 109 5803

– – – –

– – – –


97 102 107 2839

97 102 107 3260

97 102 107 3483

97 102 107 3711

98 102 107 4138

99 103 107 4706

101 103 107 5380

– – – –

– – – –


96 102 107 2726

96 102 107 3113

96 102 107 3320

96 102 106 3528

96 102 106 3887

98 102 106 4405

99 102 105 4997

101 102 105 5751

– – – –


96 102 107 2629

95 102 107 3003

95 102 107 3200

95 102 107 3402

96 102 106 3733

97 102 106 4248

99 102 106 4818

100 102 105 5491

– – – –


95 102 107 2534

95 102 107 2896

94 102 107 3083

94 102 107 3280

95 102 106 3594

96 102 106 4068

98 102 106 4650

99 102 105 5287

101 102 105 5826


95 102 107 2442

94 102 107 2791

94 102 107 2971

94 102 107 3160

94 102 106 3459

96 102 106 3898

97 102 106 4475

99 102 105 5090

100 102 105 5640


94 102 108 2352

93 102 107 2689

93 102 107 2861

93 102 107 3041

94 102 107 3329

95 102 106 3742

97 102 106 4291

98 102 105 4899

99 102 105 5392


94 102 108 2263

93 102 107 2588

93 102 107 2752

92 102 107 2923

93 102 107 3200

94 102 106 3591

96 102 106 4097

98 102 106 4706

99 102 105 5183


93 102 108 2175

92 102 108 2485

92 102 107 2644

92 102 107 2807

92 102 107 3072

93 102 107 3443

95 102 106 3916

97 102 105 4537

98 102 105 4979


93 102 108 2088

92 102 108 2382

91 102 108 2537

91 102 107 2692

92 102 107 2943

93 102 107 3297

94 102 106 3745

96 102 106 4318

98 102 106 4774

INTERSECTION IN SHADED AREAS EXCEED OPERATING LIMITATIONS AND ARE PRESENTED AS INTERPOLATION AIDS ONLY. flmmtab7d

P/N 130-590031-73D

P-19

FEBRUARY 1999




ITEM

-35

-15

45

52


99 104 109 3249

99 104 109 3739

99 104 109 4003

99 104 109 4294

100 104 109 4850

102 104 109 5507

– – – –

– – – –

– – – –


97 102 107 3022

97 102 107 3475

97 102 107 3712

97 102 107 3983

98 103 107 4507

100 103 107 5121

102 103 107 5874

– – – –

– – – –


96 102 107 2897

96 102 107 3313

96 102 106 3529

95 102 106 3761

97 102 106 4231

98 102 106 4777

100 102 105 5442

– – – –

– – – –


95 102 107 2796

95 102 107 3193

95 102 107 3403

95 102 106 3624

96 102 106 4057

97 102 106 4610

99 102 105 5227

101 102 105 5995

– – – –

V1 - KIAS VR - KIA5 V2 - KIAS TOFL - FT

95 102 107 2698

94 102 107 3077

94 102 107 3281

94 102 107 3492

95 102 106 3893

97 102 106 4443

98 102 105 5036

100 102 105 5766

– – – –


94 102 107 2599

94 102 107 2965

94 102 107 3161

94 102 107 3364

95 102 106 3744

96 102 106 4248

98 102 106 4861

99 102 105 5542

101 102 106 6161


94 102 107 2502

93 102 107 2855

93 102 107 3041

93 102 107 3239

94 102 106 3599

95 102 106 4065

97 102 106 4671

99 102 105 5339

100 102 105 5922


93 102 108 2406

93 102 107 2746

92 102 107 2924

92 102 107 3115

93 102 107 3457

95 102 106 3897

96 102 106 4479

98 102 105 5133

100 102 105 5692


93 102 108 2310

92 102 107 2639

92 102 107 2808

92 102 107 2990

92 102 107 3317

94 102 106 3734

96 102 106 4271

98 102 106 4934

99 102 105 5466


92 102 108 2216

91 102 108 2532

91 102 107 2693

91 102 107 2866

92 102 107 3179

93 102 106 3575

95 102 106 4076

97 102 106 4731

98 102 105 5240

INTERSECTION IN SHADED AREAS EXCEED OPERATING LIMITATIONS AND ARE PRESENTED AS INTERPOLATION AIDS ONLY. flmmtab7e

FEBRUARY 1999

P-20

P/N 130-590031-73D




ITEM

-35

-15

45

52


98 104 109 3465

99 104 109 3995

99 104 109 4278

99 104 109 4678

101 104 109 5254

103 105 109 6007

– – – –

– – – –

– – – –


97 102 107 3221

97 102 107 3705

97 102 107 3967

97 102 107 4343

99 103 107 4914

101 103 107 5577

– – – –

– – – –

– – – –


96 102 107 3078

95 102 106 3523

95 102 106 3755

96 102 106 4081

97 102 106 4600

99 102 105 5183

100 102 105 5949

– – – –

– – – –


95 102 107 2969

95 102 107 3398

95 102 106 3620

95 102 106 3921

97 102 106 4424

98 102 106 4996

100 102 105 5691

– – – –

– – – –


95 102 107 2863

94 102 107 3276

94 102 107 3489

94 102 106 3774

96 102 106 4238

97 102 106 4816

99 102 105 5476

101 102 105 6316

– – – –

V1 - KIAS VR - KIAS V2 - KlAS TOFL - FT

94 102 107 2761

94 102 107 3155

94 102 107 3361

94 102 106 3632

95 102 106 4062

97 102 106 4644

98 102 105 5263

100 102 105 6061

– – – –


93 102 107 2660

93 102 107 3036

93 102 107 3236

93 102 107 3495

94 102 106 3902

96 102 106 4440

98 102 106 5074

99 102 105 5843

– – – –


93 102 107 2560

92 102 107 2919

92 102 107 3113

92 102 107 3358

94 102 106 3746

95 102 106 4241

97 102 106 4879

99 102 105 5602

100 102 105 6234


92 102 108 2457

92 102 107 2803

92 102 107 2988

92 102 107 3225

93 102 107 3592

94 102 106 4058

96 102 106 4676

98 102 105 5371

100 102 105 5988


92 102 108 2355

91 102 107 2689

91 102 107 2864

91 102 107 3092

92 102 107 3440

93 102 106 3881

95 102 106 4452

98 102 105 5160

99 102 105 5749

INTERSECTION IN SHADED AREAS EXCEED OPERATING LIMITATIONS AND ARE PRESENTED AS INTERPOLATION AIDS ONLY. flmmtab7f

P/N 130-590031-73D

P-21

FEBRUARY 1999




ITEM

-35

-15

45

52


99 104 109 3696

99 104 109 4272

99 104 109 4587

100 104 109 5092

101 104 109 5740

103 105 109 6565

– – – –

– – – –

– – – –


97 102 107 3438

97 102 107 3961

97 102 107 4243

98 103 107 4739

99 103 107 5326

101 103 107 6094

– – – –

– – – –

– – – –


96 102 107 3277

95 102 106 3752

95 102 106 4003

96 102 106 4446

98 102 106 4996

99 102 105 5655

– – – –

– – – –

– – – –


95 102 107 3159

95 102 106 3616

95 102 106 3855

96 102 106 4264

97 102 106 4810

98 102 105 5441

100 102 105 6205

– – – –

– – – –


94 102 107 3045

94 102 107 3485

94 102 106 3713

95 102 106 4091

96 102 106 4628

98 102 106 5231

99 102 105 5973

– – – –

– – – –


94 102 107 2934

94 102 107 3357

93 102 107 3575

94 102 106 3935

95 102 106 4432

97 102 106 5027

99 102 105 574

– – – –

– – – –


93 102 107 2825

93 102 107 3232

93 102 107 3440

93 102 106 3784

95 102 106 4241

97 102 106 4857

98 102 105 5531

100 102 105 6379

– – – –


93 102 107 2718

92 102 107 3109

92 102 107 3308

93 102 107 3635

94 102 106 4067

96 102 106 4635

98 102 105 5314

99 102 105 6132

– – – –


92 102 107 2612

92 102 107 2984

91 102 107 3177

92 102 107 3487

93 102 106 3897

95 102 106 4424

97 102 106 5103

99 102 105 5891

100 102 105 6578


91 102 108 2507

91 102 107 2507

91 102 107 2860

91 102 107 3048

92 102 107 3341

94 102 106 3731

96 102 106 4229

98 102 105 4889

100 102 105 6314

INTERSECTION IN SHADED AREAS EXCEED OPERATING LIMITATIONS AND ARE PRESENTED AS INTERPOLATION AIDS ONLY. flmmtab7g

OCTOBER 2000

P-22

P/N 130-590031-73D1




ITEM

-35

-15

45

52


99 104 109 3952

99 104 109 4582

99 104 109 4956

101 104 109 5537

102 105 109 6269

– – – –

– – – ––

– – – –

– – – –


97 102 107 3667

97 102 107 4239

97 103 107 4616

99 103 107 5164

100 103 107 5824

102 103 107 6669

– – – –

– – – –

– – – –


95 102 106 3489

95 102 106 4002

96 102 106 4329

97 102 106 4837

98 102 105 5403

100 102 105 6183

– – – –

– – – –

– – – –


95 102 107 3365

95 102 106 3856

95 102 106 4157

96 102 106 4654

97 102 106 5220

99 102 105 5918

– – – –

– – – –

– – – –


94 102 107 3244

94 102 107 3714

94 102 106 3999

95 102 106 4461

97 102 106 5032

98 102 105 5698

100 102 105 6525

– – – –

– – – –

V1 - KIAS VR - KIAS V2 - KlAS TOFL - FT

94 102 107 3124

93 102 107 3575

94 102 106 3850

95 102 106 4275

96 102 106 4840

98 102 105 5485

99 102 105 6278

– – – –

– – – –


93 102 107 3006

93 102 107 3441

93 102 107 3703

94 102 106 4106

95 102 106 4628

97 102 106 5274

99 102 105 6040

– – – –

– – – –


92 102 107 2891

92 102 107 3308

92 102 107 3558

93 102 106 3941

94 102 106 4426

97 102 106 5087

98 102 105 5807

100 102 105 6736

– – – –


92 102 107 2776

91 102 107 3177

92 102 107 3415

92 102 107 3779

94 102 106 4240

96 102 106 4845

98 102 105 5576

100 102 105 6468

– – – –


91 102 108 2663

91 102 107 3048

91 102 107 3273

92 102 107 3620

93 102 106 4054

95 102 106 4615

97 102 106 5334

99 102 105 6215

– – – –

INTERSECTION IN SHADED AREAS EXCEED OPERATING LIMITATIONS AND ARE PRESENTED AS INTERPOLATION AIDS ONLY. flmmtab7h

P/N 130-590031-73D

P-23

FEBRUARY 1999




ITEM

-35

-15

45

52


99 104 109 4229

99 104 109 4904

100 104 109 5389

101 104 109 6043

103 105 109 6854

– – – –

– – – –

– – – –

– – – –


97 102 107 3922

97 102 107 4556

98 103 107 5023

99 103 107 5619

101 103 107 6367

– – – –

– – – –

– – – –

– – – –


95 102 106 3717

95 102 106 4282

96 102 106 4720

97 102 106 5257

99 102 105 5914

101 102 105 6767

– – – –

– – – –

– – – –


95 102 106 3583

95 102 106 4116

95 102 106 4528

97 102 106 5062

98 102 105 5679

100 102 105 6457

– – – –

– – – –

– – – –


94 102 107 3453

94 102 106 3963

95 102 106 4343

96 102 106 4867

97 102 106 5473

99 102 105 6214

– – – –

– – – –

– – – –


93 102 107 3327

93 102 107 3816

94 102 106 4173

95 102 106 4661

97 102 106 5272

99 102 105 5986

100 102 105 6891

– – – –

– – – –


93 102 107 3204

93 102 107 3671

93 102 106 4011

94 102 106 4464

96 102 106 5069

98 102 105 5761

99 102 105 6614

– – – –

– – – –


92 102 107 3081

92 102 107 3528

93 102 107 3852

93 102 106 4283

95 102 106 4838

97 102 106 5542

99 102 105 6362

– – – –

– – – –


92 102 107 2957

91 102 107 3386

92 102 107 3696

93 102 106 4103

94 102 106 4618

96 102 106 5316

98 102 105 6105

– – – –

– – – –


91 102 107 2835

91 102 107 3247

91 102 107 3541

92 102 106 3927

93 102 106 4417

96 102 106 5072

98 102 105 5857

100 102 105 6849

– – – –

INTERSECTION IN SHADED AREAS EXCEED OPERATING LIMITATIONS AND ARE PRESENTED AS INTERPOLATION AIDS ONLY. flmmtab7i

FEBRUARY 1999

P-24

P/N 130-590031-73D


TAKE-OFF SPEEDS AND FIELD LENGTHS- FLAPS APPROACH (A/C AND BLEED AIR ON) PRESSURE ALTITUDE: 10,000 FT TO WEIGHT 15,000 LBS 6804 KG 14,500 LBS 6577 KG 14,000 LBS 6350 KG 13,500 LBS 6123 KG 13,000 LBS 5897 KG 12,500 LBS 5670 KG 12,000 LBS 5443 KG 11,500 LBS 5216 KG 11,000 LBS 4989 KG 10,500 LBS 4763 KG AND UNDER NOTE:


ITEM

-35

-15

45

52


99 104 109 4583

99 104 109 5346

100 104 109 5928

102 105 109 6661

– – – –

– – – –

– – – –

– – – –

– – – –


97 102 107 4242

98 103 107 5001

98 103 107 5524

100 103 107 6195

102 103 107 7046

– – – –

– – – –

– – – –

– – – –


95 102 106 4008

96 102 106 4685

97 102 106 5178

98 102 105 5762

99 102 105 6354

– – – –

– – – –

– – – –

– – – –


95 102 106 3861

95 102 106 4496

96 102 106 4987

97 102 106 5555

99 102 105 6260

– – – –

– – – –

– – – –

– – – –


94 102 107 3719

94 102 106 4317

95 102 106 4779

97 102 106 5354

98 102 105 6041

100 102 105 6866

– – – –

– – – –

– – – –


93 102 107 3581

94 102 106 4153

94 102 106 4582

96 102 106 5145

97 102 105 5806

99 102 105 6608

– – – –

– – – –

– – – –


93 102 107 3447

93 102 106 3993

94 102 106 4400

95 102 106 4919

97 102 106 5587

98 102 105 6355

– – – –

– – – –

– – – –


92 102 107 3314

92 102 107 3836

93 102 106 4222

94 102 106 4703

96 102 106 5370

98 102 105 6103

100 102 105 7067

– – – –

– – – –


91 102 107 3183

91 102 107 3681

92 102 107 4047

93 102 106 4506

95 102 106 5116

97 102 105 5867

99 102 105 6784

– – – –

– – – –


91 102 107 3057

91 102 107 3527

91 102 107 3875

92 102 106 4312

94 102 106 4875

96 102 106 5629

98 102 105 6507

– – – –

– – – –

INTERSECTION IN SHADED AREAS EXCEED OPERATING LIMITATIONS AND ARE PRESENTED AS INTERPOLATION AIDS ONLY. flmmtab7j

P/N 130-590031-73D

P-25

FEBRUARY 1999


MAXIMUM CRUISE POWER

FEBRUARY 1999

P-26

P/N 130-590031-73D


CRUISE

NORMAL CRUISE POWER

P/N 130-590031-73D

P-27

FEBRUARY 1999


CRUISE

PILOT NOTES

FEBRUARY 1999

P-28

P/N 130-590031-73D


SUPPLEMENTAL INFORMATION FUEL SYSTEM SCHEMATIC...........................................................................................SI-2

SUPPLEMENTAL INFORMATION

POWER DISTRIBUTION SCHEMATIC–DC...................................................................SI-3

P/N 130-590031-73D

SI-1

FEBRUARY 1999

FEBRUARY 1999

SI-2

AIR INLET

VENT FLOAT VALVE

W.S. 290.92

INTERGRAL (WET CELL) 35 GALLONS

DRAIN

WING LEADING EDGE 13 GALLONS

HEATED RAM VENT

RECESSED VENT

25 GALLONS BOX SECTION

FLAME ARRESTOR

23 GALLONS BOX SECTION

WING LEADING EDGE 40 GALLONS

DRAIN VALVE

FUEL LOW LEVEL SENSOR

PRESSURE SWITCH FOR LEFT NO FUEL TRANSFER LIGHT ON CAUTION PANEL

MOTIVE FLOW VALVE

AUX - 79.5 GAL

CHECK VALVE

GRAVITY FLOW CHECK VALVE

LEFT FUEL PRESSURE ANNUNCIATOR PRESSURE SWITCH

FUEL CONTROL PURGE LINE

AIR FILTER

FUEL HEATER

ENGINE DRIVEN HIGH PRESSURE FUEL PUMP

P3 BLEED AIR LINE

FUEL FLOW TRANSMITTER AND INDICATOR

STRAINER AND DRAIN VALVE

FUEL PRESSURE ANNUNCIATOR

FUEL FLOW INDICATOR

CHECK VALVE

SUCTION RELIEF VALVE

PROBE

FILLER

FUEL VENT

P3 AIR LINE FOR FUEL PURGE

FUEL RETURN

FUEL CROSSFEED

FUEL UNDER PUMP PRESSURE

FUEL AT STRAINER OR FILTER

AVIATION FUEL

MAIN - 190 GAL

LEGEND

SUPPLEMENTAL INFORMATION

FLOAT CHECK VALVE DRAIN VALVE

TRANSFER JET PUMP

79.5 GALLONS

AUXILIARY

STRAINER, DRAIN & FUEL SWITCH

CROSSFEED VALVE

PRESSURE RELIEF VALVE

VENT FLOAT VALVE

NACELLE TANK 54 GALLONS

STANDBY BOOST PUMP

FIREWALL SHUTOFF VALVE

ENGINE DRIVEN BOOST PUMP DRAIN VALVE

FIREWALL FUEL FILTER

FUEL PURGE TANK

FUEL CONTROL UNIT

ENGINE FUEL MANIFOLD


FUEL SYSTEM SCHEMATIC

P/N 130-590031-73D

P/N 130-590031-73D

GENERATOR CONTROL

60

LEFT STARTER RELAY

SI-3

DUAL-FED BUS

BAT BUS

LEFT GEN. BUS TIE

250

LEFT LINE CONTACTOR

STARTER/ GENERATOR

BAT BUS SWITCH NORMAL

LOAD METER

LEFT GEN. BUS

LEFT GENERATOR SWITCH

TO GENERATOR FIELD

BATTERY MONITOR AMMETER

BAT BUS CONTROL .5A

E D

275 H

RCCB

BATTERY

GPU

275

BATT. SW.

TRIPLE FED BUS

20A

60

HED

BATT. BUS TIE

CENTER BUS D

BATTERY RELAY

FROM BAT BUS

E

275 H

250

RIGHT GEN. BUS TIE

RIGHT LINE CONTACTOR

STARTER/ GENERATOR

RIGHT STARTER RELAY

RIGHT GENERATOR SWITCH

60

RIGHT GEN. BUS

GENERATOR CONTROL

LOAD METER

TO GENERATOR FIELD


POWER DISTRIBUTION SCHEMATIC–DC

FEBRUARY 1999

KA350 Pilot Checklist PN-73.pdf

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