Pilatus pc-12 aircraft flight manual

Air Conditioning: ..........................As required 13. ECS: .....................................................Auto 14. Pressurization: .................Set Cruise Alt +500ft 15. Flaps: ................................................Set 15º Pre- Taxi: 1. 2. 3. 4. 5. 6. 7. 8. 9. 10. Engine Instruments: .........................Checked 11. Fuel Quantity: .................................Re-check 12. 10. Trim Inter Switch: ....................................Normal 11. Flap Inter Switch: ....................................Normal 12. MOR Lever: ..................................................Off 13. PCL Lever: ..................................................Idle 14. Condition Lever: .....................................Cut Off 15. Flap Lever: ....................................................0º 16. Fuel Emerg Shutoff: .................................Full In 17. ECS Emerg Shutoff: .................................Full In 18. Oxygen Lever : ..............................................On 4. Pax Oxy Supply: .........................................Auto 5. Oxygen Mask: ......................................Checked 6. Circuit Breakers: ..................................Checked 7. EPS: ..............................................Check + Arm 8. Ldg Gear Handle: ......................................Down 9. 10. Trim Inter Switch: ....................................Normal 11. Flap Inter Switch: ....................................Normal 12. MOR Lever: ..................................................Off 13. PCL Lever: ..................................................Idle 14. Condition Lever: .....................................Cut Off 15. Flap Lever: ....................................................0º 16. Fuel Emerg Shutoff: .................................Full In 17. ECS Emerg Shutoff: .................................Full In 18. Doors/DV Windows: ................................Closed 19. Standby Bus Switch : ....................................On 20. Overhead Switches: .................................All Off 21. Electrical Switches: ..................................All Off 22. Clearance: ..............................................Obtain 23. GPS Flight Plan: ..........................................Set 24. Battery Switch: ............................................On 25. Battery Voltage: ........................................>24V 26. Beacon/Nav Lights: ......................................On 27. Fuel Pumps: ..........................Audio/Visual Check 28. Lamp: .................................................Checked 29. Fire Warning: .......................................Checked 30. EIS: ....................................................Checked 31. Fuel Contents: .................................Checked/Set Kennair.com.au FLIGHTSIM USE ONLY Engine Start: 1. 2. 3. 4. 5. 6. 7. 8. 9. 10. Pax Advisory: ..........................................On 11. Standby Bus: .........................................OFF 12. Air Conditioning: ..........................As required 13. ECS: .....................................................Auto 14. Oxygen Lever : ..............................................On 4. Pax Oxy Supply: .........................................Auto 5. Oxygen Mask: ......................................Checked 6. Circuit Breakers: ..................................Checked 7. EPS: ..............................................Check + Arm 8. Ldg Gear Handle: ......................................Down 9. 10. Trim Inter Switch: ....................................Normal 11. Flap Inter Switch: ....................................Normal 12. MOR Lever: ..................................................Off 13. PCL Lever: ..................................................Idle 14. Condition Lever: .....................................Cut Off 15. Flap Lever: ....................................................0º 16. Fuel Emerg Shutoff: .................................Full In 17. ECS Emerg Shutoff: .................................Full In 18. Doors/DV Windows: ................................Closed 19. Standby Bus Switch : ....................................On 20. Overhead Switches: .................................All Off 21. Electrical Switches: ..................................All Off 22. Clearance: ..............................................Obtain 23. GPS Flight Plan: ..........................................Set 24. Battery Switch: ............................................On 25. Battery Voltage: ........................................>24V 26. Beacon/Nav Lights: ......................................On 27. Fuel Pumps: ..........................Audio/Visual Check 28. Lamp: .................................................Checked 29. Fire Warning: .......................................Checked 30. EIS: ....................................................Checked 31. Fuel Contents: .................................Checked/Set Kennair.com.au FLIGHTSIM USE ONLY Engine Start: 1. 2. 3. 4. 5. 6. 7. 8. 9. 10. Pax Advisory: ..........................................On 11. Standby Bus: .........................................OFF 12. Air Conditioning: ..........................As required 13. ECS: .....................................................Auto 14. Pressurization: .................Set Cruise Alt +500ft 15. Flaps: ................................................Set 15º Pre- Taxi: 1. 2. 3. 4. 5. 6. 7. 8. 9. 10. Engine Instruments: .........................Checked 11. Fuel Quantity: .................................Re-check 12. Com/Nav: ................................................Set 13. EGPWS/Traffic: ................................Checked 14. 15. FD/ALT : ..................................................Set 11 May 2007 Kennair.com.au Pilatus PC-12 Checklist Prop Area: ............................................Clear Starter Switch: ......................Press 2 Seconds Condition Lever >12%Ng: ..............Ground Idle Oil Pressure: .......................................Check ITT and Ng: ....................................Monitored Engine Instruments: .........................Checked Gen 1 then Gen 2: ....................................On Inverter: .......................................Batt or Gen Avionics 1 and 2: .....................................On Flaps 15º: ........................................Checked AHRS: ..............................................No Flag Autopilot: ........................................Checked Pusher : ................................................Test CAWS: ............................................Checked Inertial Separator: ........................Check Open De-Ice: .......................................Check (if ice) Flight Controls: ......................................Free Trim Set: ..................................................+3 Cabin Pressurization/ECS: ................Checked FLIGHTSIM USE ONLY 11 May 2007 Page 1 PILOT’S INFORMATION MANUAL PC-12 SERIES 10 AND 10A... Page 2 P .O. Box 992 6371 Stans, Switzerland Phone +41 41 619 67 00 +41 41 619 92 30 Certified to EN 9100/ISO 14001 standards info@pilatus- aircraft.com This Approval may be extended or withdrawn in writing by Pilatus at any time www.pilatus-aircraft.com... Page 5 LETTER OF TRANSMITTAL Pilatus Aircraft Ltd P.O. Box 992 CH-6371 Stans Switzerland Tel: +41 (0)41 619 6111 Fax: +41 (0)41 610 9230 TO HOLDERS OF PC-12 PILOT’S OPERATING HANDBOOK PC-12 PILOT’S OPERATING HANDBOOK REPORT NO. 02211 REVISION 17 DATED November 03, 2021... Page 6 LETTER OF TRANSMITTAL Remove and insert the Supplement pages listed below (if applicable): Supplement/Report No. Remove Insert... Page 7 LIST OF EFFECTIVE PAGES LIST OF EFFECTIVE PAGES Page No. Rev. No. Page No. Rev No. Page No. Rev. No. Title Page LOEP-1 thru -4 2-ii 3-6 thru 3-10 LOTR-1 2-iii 3-11 LOTR-2 2-iv 3-12 LOTR-3 3-13 LOTR-4 2-2 thru 2-4 3-14 thru 3-19 LOR-1 thru -4 3-20... Page 8 LIST OF EFFECTIVE PAGES LIST OF EFFECTIVE PAGES Page No. Rev. No. Page No. Rev No. Page No. Rev. No. 4-16 6-13 7-4-4 4-17 6-14 and 6-15 7-4-5 4-18 6-16 7-4-6 4-19 thru 4-21 6-17 thru 6-25 7-4-7 thru 7-4-16 4-22 6-26 7-5-1 and 7-5-2... Page 9 LIST OF EFFECTIVE PAGES LIST OF EFFECTIVE PAGES Page No. Rev. No. Page No. Rev No. Page No. Rev. No. 7-21-5 and 7-21-6 10-ii 7-22-1 thru 7-22-4 10-1 thru 10-3 7-23-1 and 7-23-2 10-4 thru 10-24 7-23-3 7-23-4 and 7-23-5 7-23-6 7-23-7 and 7-23-8 7-24-1 thru 7-24-4... Page 10 LIST OF EFFECTIVE PAGES INTENTIONALLY LEFT BLANK Report No: 02211 Issued: March 30, 2001 LOEP-4 Revision 17: November 03, 2021... Page 11 LOG OF TEMPORARY REVISIONS The incorporation of Temporary Revisions into this manual are to be recorded on the sheet below. Instructions for the removal of Temporary Revisions will be given in the Instruction Sheet issued with each regular revision. DATE OF CANCELLED TEMPORARY REVISION TITLE ISSUE... Page 12 LOG OF TEMPORARY REVISIONS DATE OF CANCELLED TEMPORARY REVISION TITLE ISSUE OTHER LIMITATIONS Mar 14/05 POH REV 2 SUPPLEMENT No.33 – MSN 727 ONLY May 16/06 S 33 REV 1 FLIGHT CONTROLS Nov 22/07 POH REV 6 FLIGHT CONTROLS BEFORE TAXI AND Oct 05/10 POH REV 7 BEFORE TAKE-OFF CHECK. Page 13 LOG OF TEMPORARY REVISIONS DATE OF CANCELLED TEMPORARY REVISION TITLE ISSUE SECTION 6 - WEIGHT AND BALANCE Dec 18/18 TR 28 COMMUTER SEAT Jun 12/19 POH REV 15 FUEL PLACARD Apr 30/21 POH REV 17 SERVICING Jul 07/21 POH REV 17 ELECTRICAL SYSTEM FAILURES Sep 10/21 POH REV 17... Page 14 LOG OF TEMPORARY REVISIONS DATE OF CANCELLED TEMPORARY REVISION TITLE ISSUE Report No: 02211 Issued: March 30, 2001 LOTR-4 Revision 15: Dec 12, 2019... Page 15 LOG OF REVISIONS LOG OF REVISIONS Revision Page Number Number Description and Date LOTR-1 & 2 Log of Temporary Revisions updated, page 2 issued 1 Mar 03 LOR-1 thru 3 Log of Revisions pages issued Sect 2 Executive Code No. corrected to EX 6S-2 2-ii &... Page 16 LOG OF REVISIONS LOG OF REVISIONS (CONT.) Revision Page Number Number Description and Date Note ref CAWS test deleted. Update to Post SB 31-004 Booster pumps operational check step added 4-10 Steps re-numbered 4-11 Voice callout info deleted. Update to Post SB 31-004 4-14 Voice callout info updated to Post SB 31-004 4-14 &... Page 17 LOG OF REVISIONS LOG OF REVISIONS (CONT.) Revision Page Number Number Description and Date 7-38 Optional second oil chip detector info added 7-46 Voice callout info deleted. Update to Post SB 31-004 7-64 Gen 2 amp rating figure changed 7-66 Caution ref Gen 2 load figures changed 7-67 Systems connected to Standby bus corrected... Page 18 WX-500 Stormscope – initial issue Supp 28 DC-DC Converter – initial issue Supp 29 Pilot’s Relief Tube – initial issue FOCA signed original held on file by Pilatus Aircraft Ltd. Signature date: 25 August 2003 Report No: 02211 Issued: June 10, 1994 LOR-4... Page 19 LOG OF REVISIONS LOG OF REVISIONS (CONT.) Revision Page Number Number Description and Date 28 Feb 05 LOTR-1 & 2 Log of Temporary Revisions updated Sect 2 2-28 TR No. 15 Limitation for aft facing seats and all seat belts added 2-45 TR No. Page 20 PC-12 and PC-12/45 Registered in the CIS – Initial issue Sect 10 10-10 & 11 Passenger seat headrests and seat belts briefing info updated FOCA signed original held on file by Pilatus Aircraft Ltd. Signature date: 4 November 2005 Report No: 02211 Issued: June 10, 1994... Page 21 9-00-1 Supplements List of Effective Pages updated Supp 33 PC- 12/47 (4740 kg MTOW variant) – Initial issue FOCA signed original held on file by Pilatus Aircraft Ltd. Signature date: 30 November 2005 Issued: March 30, 2001 Report No: 02211 Revision 3: October 28, 2005... Page 22 Sect 9 9-ii Table of Contents updated 9-00-1 Supplements List of Effective Pages updated FOCA signed original held on file by Pilatus Aircraft Ltd. Signature date: 3 September 2007 Report No: 02211 Issued: June 10, 1994 LOR-8 Revision 4: April 30, 2007... Page 23 7-39 Deleted old text number, that was brought back in error by revision mark formatting FOCA signed original held on file by Pilatus Aircraft Ltd. Signature date: 26 November 2007 Issued: March 30, 2001 Report No: 02211... Page 24 LOG OF REVISIONS LOG OF REVISIONS (CONT.) Revision Page Number Number Description and Date Title page Copyright information added. Fill in the aircraft MSN and Registration details on the new page. Jun 30, 2010 LOEP-1 and 2 List updated LOTR-2 List updated LOR 10 thru 12 Pages issued. Page 25 10-6 to 10-12 Pages run on. 10-13 and 10- EIS fault codes and crew actions added. Approved under P-EASA 0010004233-001 FOCA signed original held on file by Pilatus Aircraft Ltd. Issued: March 30, 2001 Report No: 02211 Revision 6: Jun 30, 2010... Page 26 LOG OF REVISIONS LOG OF REVISIONS (CONT.) Revision Page Number Number Description and Date Jul 20, 2011 LOEP-1 and 2 List updated. LOTR-2 List updated. LOR 12 thru 14 Pages issued. Section 2 2-ii Page numbering updated. Circuit breaker reset limitation added. Warning added for anti-icing fuel additive. Page 27 Section 9 9-00-1 Revision status updated. Approved under EASA Project No. 0010011375-001: Signed: Paul Hatton (EASA Project Certification Manager) Date: 31.08.2011 Signed original held by Pilatus Aircraft Ltd. Dec 01, 2012 LOEP 1&2 List updated. LOTR 2 List updated. LOR 13 and 14 Pages updated. Page 28 Section 10 10-i Contents updated. 10-4 thru 10-24 TR 20 incorporated. Text roll-on. Approved under P-EASA 0010020967-001 FOCA signed original held on file by Pilatus Aircraft Ltd. Report No: 02211 Issued: March 30, 2001 LOR-14 Revision 8: December 01, 2012... Page 29 LOG OF REVISIONS LOG OF REVISIONS (CONT.) Revision Page Number Number Description and Date LOEP 1 and 2 List updated. 01 Jun 2014 LOR 15 and 16 New pages. Section 1 Propeller model added. Section 2 2-6 and 2-7 Note 10 added regarding permitted RPM variation. Propeller model added. Page 30 LOG OF REVISIONS THIS PAGE INTENTIONALLY LEFT BLANK Report No: 02211 Issued: March 30, 2001 LOR-16 Revision 9: June 01, 2014... Page 31 LOG OF REVISIONS LOG OF REVISIONS (CONT.) Revision Page Number Description Number and Date LOEP 1 and 2 List updated. 02 March LOR 17 and 18 New pages. 2015 Section 3 3-ii Contents updated. Editorial change. Editorial change. 3-42 thru 3-45 Trim runaway procedure revised. Page 32 LOG OF REVISIONS LOG OF REVISIONS (CONT.) Revision Page Number Number Description and Date LOEP-1 and -2 List updated. 30 Jan LOR-18 and -20 List updated. New pages 19 and 20. 2016 Section 0 0-i and 0-ii Contents updated. Revision marking text changed, revision issue/dates added. Copyright and legal statements added. Page 33 LOG OF REVISIONS LOG OF REVISIONS (CONT.) Revision Page Number Description Number and Date Section 7 30 Jan 7-23-6 Fuel pump advisory indications clarified. (Continued) 7-26-1 Text removed. Section 8 8-17 Oil replenishment procedure expanded. Section 9 9-00-1 LOEP updated. Supp 18 PC-12 Registered in France - Rev 3 issued. Page 34 LOG OF REVISIONS LOG OF REVISIONS (CONT.) Revision Page Number Number Description and Date LOEP-1 thru -4 List updated. New pages 3 and 4 25 Nov LOTR- 2 List updated 2016 LOR-20 thru -22 List updated. New pages 21 and 22 Section 0 Editorial (updated layout of Warning and Caution to latest standard) Page 35 LOG OF REVISIONS LOG OF REVISIONS (CONT.) Revision Page Number Description Number and Date 4-44 Editorial (updated layout of Caution to latest standard) 25 Nov 4-48 16477 - Post icing situations wording added 2016 4-51 16477 - Post icing situations wording added (Continued) 4-49 thru 4-52 Editorial (text run on) Page 36 LOG OF REVISIONS LOG OF REVISIONS (CONT.) Revision Page Number Number Description and Date LOEP-1 thru -4 List updated. 06 Oct LOR-22 thru -24 List updated. New pages 23 and 24 2017 Section 1 1-17 16805 - Editorial (Duplicate EIS and ELT abbreviations deleted) 1-18 thru 1-20 17692 - Editorial (Minor update to layout of pages) Page 37 LOG OF REVISIONS LOG OF REVISIONS (CONT.) Revision Page Number Number Description and Date 7-4-3 16805 - Changed ESSENTIAL BUS to NON ESSENTIAL 06 Oct 2017 7-4-5 17692 - Editorial (Issue date in footer updated) (Continued) 7-4-7 and 7-4-8 17692 - Editorial (Issue date in footer updated) 7-4-9 16805 - Flap settings updated 7-4-10... Page 38 LOG OF REVISIONS LOG OF REVISIONS Revision Page Number Number Description and Date LOEP-1 thru -4 List updated 08 Oct LOR-24 LOR updated for Revision 14 2018 Section 3 3-11 17779 - Sequence of GEN 2 and GEN 1 switches changed Section 4 4-12 17779 - Sequence of GEN 2 and GEN 1 switches changed... Page 39 LOG OF REVISIONS LOG OF REVISIONS (CONT.) Revision Page Number Number Description and Date LOEP-1 thru -4 List updated for Revision 15 12 Dec LOTR-3 and -4 19046 - New LOTR pages for Revision 15 2019 LOR-25 and -26 LOR updated for Revision 15. New pages LOR-25 and LOR-26 Section 1 19880 - Updated name for "passenger door"... Page 40 LOG OF REVISIONS Revision Page Number Number Description and Date Section 7 12 Dec 7-2-1 19880 - Updated name for "passenger door" (editorial) 2019 7-7-1 20565 - Incorporated TR 28 (Continued) 7-8-1 19880 - Updated name for "passenger door" (editorial) 7-13-1 and 7-13-2 19696 - Added drain valve to air separator 7-13-4... Page 41 LOG OF REVISIONS LOG OF REVISIONS Revision Page Number Number Description and Date LOEP-1 thru -4 List updated 18 Dec LOR-27 and -28 LOR updated for Revision 16. New pages LOR- 27 and 2020 LOR-28 Section 0 21766 - Updated for Revision 16 21766 - Updated revision/issue dates description 21766 - Added “Supplements”... Page 42 LOG OF REVISIONS LOG OF REVISIONS Revision Page Number Number Description and Date Title Page 23223 - Statement added. Fill in the aircraft MSN and 03 Nov Registration details on the new page 2021 LOEP-1 thru -4 23223 - List updated for Revision 17 LOTR-3 23223 - LOTR updated for Revision 17 LOR-28... Page 43 CONTENTS CONTENTS Section Subject Page INTRODUCTION GENERAL LIMITATIONS EMERGENCY PROCEDURES NORMAL PROCEDURES PERFORMANCE WEIGHT AND BALANCE AIRPLANE AND SYSTEMS DESCRIPTION HANDLING, SERVICING, AND MAINTENANCE SUPPLEMENTS SAFETY AND OPERATIONAL TIPS 10-1 THE CONTENTS OF SECTIONS 2, 3, 4, 5, 6, AND 9 ARE EASA APPROVED Issued: March 30, 2001 Report No: 02211 Revision 6: Jun 30, 2010... Page 44 CONTENTS INTENTIONALLY BLANK Report No: 02211 Issued: March 30, 2001 CONTENTS-2... Page 45 SECTION 0 INTRODUCTION SECTION 0 INTRODUCTION TABLE OF CONTENTS Subject Page GENERAL WARNINGS, CAUTIONS, AND NOTES REVISION MARKINGS REVISION / ISSUE DATES REVISION PROCEDURE Transmittal Letter Log of Revisions List of Effective Pages New or Revised Pages Temporary Revisions Supplements Copyright and Legal Statement Issued: March 30, 2001 Report No: 02211... Page 46 SECTION 0 INTRODUCTION THIS PAGE INTENTIONALLY LEFT BLANK Report No: 02211 Issued: March 30, 2001 0-ii... Page 47 SECTION 0 INTRODUCTION GENERAL This Pilot's Operating Handbook (POH) is designed to provide the information required for the operation of the airplane. Each airplane is delivered with a POH that reflects the standard airplane with all of the approved options plus any special equipment installed on an individual basis. Page 48 SECTION 0 INTRODUCTION REVISION MARKINGS Additions, technical changes, and revisions to existing POH material will be identified by a vertical revision bar (black line) in the outside margin of the applicable page, next to the change. The revision bar will only indicate the current change on each page. Physical relocation of material or the correction of typographical or grammatical errors, outside of the material revised, will not be identified by a revision bar. Page 49 SECTION 0 INTRODUCTION LIST OF EFFECTIVE PAGES The List of Effective Pages will list all of the current POH page numbers with the applicable revision number. NEW OR REVISED PAGES In accordance with the instructions of the Transmittal Letter, new or revised pages will be incorporated into the POH and superseded pages destroyed. Page 50 Pilatus Aircraft Ltd. In connection with the use of this document, Pilatus does not provide any express or implied warranties and expressly disclaims any warranty of merchantability or fitness for a particular purpose. SECTION 1 GENERAL SECTION 1 GENERAL TABLE OF CONTENTS Subject Page GENERAL INTRODUCTION DESCRIPTIVE DATA ENGINE PROPELLER FUEL MAXIMUM WEIGHTS TYPICAL AIRPLANE WEIGHTS CABIN AND ENTRY DIMENSIONS SPECIFIC LOADINGS SYMBOLS, ABBREVIATIONS, AND TERMINOLOGY GENERAL AIRSPEED TERMINOLOGY AND SYMBOLS METEOROLOGICAL TERMINOLOGY 1-10 POWER TERMINOLOGY 1-12... SECTION 1 GENERAL THIS PAGE INTENTIONALLY LEFT BLANK Report No: 02211 Issued: March 30, 2001 1-ii... SECTION 1 GENERAL GENERAL This section contains basic data and information of general interest to the pilot. It also contains definitions and explanations of symbols, abbreviations, and terminology that is used throughout this POH. INTRODUCTION This POH includes the material required to be furnished by the Federal Aviation Regulations and additional information provided by the manufacturer and constitutes the FOCA Approved Airplane Flight Manual. Page 54 SECTION 1 GENERAL Figure 1-1. Airplane Three View and Dimensions Report No: 02211 Issued: March 30, 2001 Revision 3: March 30, 2005... Page 55 SECTION 1 GENERAL Figure 1-2. Airplane Ground Turning Clearance – MWS only (No Braking) Issued: March 30, 2001 Report No: 02211 Revision 6: Jun 30, 2010... Page 56 SECTION 1 GENERAL Figure 1-3. Airplane Ground Turning Clearance – NWS and Braking Report No: 02211 Issued: March 30, 2001 1-3A Revision 6: Jun 30, 2010... Page 57 SECTION 1 GENERAL THIS PAGE INTENTIONALLY LEFT BLANK Issued: March 30, 2001 Report No: 02211 Revision 6: Jun 30, 2010 1-3B... SECTION 1 GENERAL DESCRIPTIVE DATA ENGINE Number of Engines Engine Manufacturer Pratt & Whitney Canada Engine Model Number PT6A-67B Engine Type This airplane incorporates a twin shaft turboprop engine with 4 axial and 1 centrifugal compressor stages, an annular combustion chamber, and a 3 stage turbine where one stage drives the compressor and two stages power the propeller. SECTION 1 GENERAL FUEL APPROVED FUELS JET A, JET-A-1, JET B, JP-4 Any other fuel which complies with the latest revision of Pratt & Whitney Service Bulletin 14004. TOTAL CAPACITY 406.8 US gal, 2,736.5 lb (1,540 liters, 1,241.3 kg) USABLE FUEL 402 US gal, 2,703.6 lb (1,521.5 liters, 1,226.4 kg) ANTI-ICING ADDITIVE Anti-Icing additive conforming to MIL-DTL-27686 or MIL-DTL-85470. SECTION 1 GENERAL MAXIMUM WEIGHTS Maximum Ramp Weight 9965 lb (4520 kg) Maximum Takeoff Weight 9921 lb (4500 kg) Maximum Landing Weight 9921 lb (4500 kg) Maximum Zero Fuel Weight 9039 lb (4100 kg) Maximum Cargo Weight Baggage Area 400 lb (180 kg) Cabin Area 3300 lb (1500 kg) TYPICAL AIRPLANE WEIGHTS... SECTION 1 GENERAL Overwing Emergency Exit Width 1' 6" (0.49 m) Height 2' 2" (0.68 m) Compartment Volume 34.3 ft 3 (0.97 m 3 ) Baggage 326 ft 3 (9.23 m 3 ) Cabin SPECIFIC LOADINGS Wing Loading 35.7 lb/sq ft (174.4 kg/sq m) Power Loading 9.9 lb/shp (4.5 kg/shp) Issued: March 30, 2001... SECTION 1 GENERAL SYMBOLS, ABBREVIATIONS, AND TERMINOLOGY GENERAL AIRSPEED TERMINOLOGY AND SYMBOLS Calibrated airspeed means the indicated airspeed of an aircraft, corrected for position and instrument error. Calibrated airspeed is equal to true airspeed in standard atmosphere at sea level. Ground speed is the speed of an airplane relative to the ground. Page 63 SECTION 1 GENERAL V MO Maximum operating speed is the speed limit that may not be exceed at any time. V is expressed in knots. Maximum Operating Maneuvering airspeed is the maximum speed at which application of full available aerodynamic control will not overstress the airplane. NOTE V O is defined in accordance with FAR 23 Amendment 45. SECTION 1 GENERAL METEOROLOGICAL TERMINOLOGY Indicated The number actually read from an altimeter when the Altitude barometric subscale has been Pressure set to 29.92 in hg (1013.2 mbar). IOAT Indicated Outside Air Temperature is the temperature obtained from an indicator and not corrected for instrument error and compressibility effects. Page 65 SECTION 1 GENERAL Icing Can exist when the OAT on the ground and for take-off Conditions (Continued) is 10°C or colder when operating on ramps, taxiways or runways, where surface snow, ice, standing water, or slush may be ingested by the engine, or freeze on the engine, or the engine nacelle. SECTION 1 GENERAL POWER TERMINOLOGY Cruise The power recommended to operate the airplane in a Climb Power cruise climb (a continuous, gradual climb) profile. Flight Idle Power The power required to run an engine, in flight, at the lowest speed that will ensure satisfactory engine and systems operation and airplane handling characteristics. SECTION 1 GENERAL ENGINE CONTROLS AND INSTRUMENTS TERMINOLOGY Adjustable The Power Control Lever position selects the minimum Minimum Prop pitch in flight (6° to 12°) when forward of the idle detent. Pitch in flight This pitch can only be reached when the propeller is underspeeding at low power and low airspeed conditions. SECTION 1 GENERAL Py Pressure P3 pressure (after engine compressor) to limit fuel flow during engine acceleration in order to not cause compressor surges. The torque limiter and the N f governor reduce P3 pressure (which is called Py pressure) to limit fuel flow so that the torque and N f limits are not exceeded. SECTION 1 GENERAL WEIGHT AND BALANCE TERMINOLOGY A.O.D. Aft of Datum. The horizontal distance from the reference datum to the center of gravity (C.G.) of an item. Basic Empty Weight Standard empty weight plus optional equipment. Center of Gravity The point at which an airplane would balance if suspended. (C.G.) Its distance from the reference datum is found by dividing the total moment by the total weight of the airplane. SECTION 1 GENERAL GENERAL ABBREVIATIONS AND SYMBOLS Celsius Moment in meters/kilograms Cubic Minimum Fahrenheit Millimeters Federal Aviation Administration Nautical Mile (U.S.A.) FOCA Federal Office for Civil Aviation Not Applicable (Switzerland) Feet per Minute Pounds per Square Inch Feet Revolutions Per Minute Unit of acceleration measured Second against the force of gravity... SECTION 1 GENERAL ELECTRICAL / AVIONIC ABBREVIATIONS Autopilot Flight Director Automatic Direction Finder FDWU Flap Drive Warning Unit Autopilot Altitude hold mode Heading Autopilot Approach mode High Frequency Band Communication EFIS sectored display Autopilot Airspeed hold mode Airspeed Indicator Multi Function Display Marker Beacon Transponder with altitude XPNDR... Page 72 SECTION 1 GENERAL CONVERSION INFORMATION All numerical data contained in this AFM is shown in standard format with the metric equivalent immediately following in parenthesis, ex. 7' 3" (2.1 m). The following formulas can be used to make required conversions. GENERAL Fahrenheit (°F) = (°C x 1.8) + 32 Celsius (°C) = (°F - 32) x 0.556... Page 73 SECTION 1 GENERAL METRIC TO STANDARD Inches (in) = Millimeters (mm) x 0.039 Inches (in) = Centimeters (cm) x 0.393 Feet (ft) = Meters (m) x 3.281 Yards (yd) = Meters (m) x 1.094 Statute Miles (sm) = Kilometers (km) x 0.621 Nautical Miles (nm) = Kilometers (km) x 0.54 US Gallons (US gal) = Liters x 0.264 Imperial Gallons (IMP gal) = Liters x 0.22... Page 74 SECTION 1 GENERAL INTENTIONALLY LEFT BLANK Report No: 02211 Issued: March 30, 2001 1-20 Revision 13: Oct 06, 2017... Page 75 SECTION 2 LIMITATIONS SECTION 2 LIMITATIONS TABLE OF CONTENTS Subject Page GENERAL AIRSPEED LIMITATIONS AIRSPEED INDICATOR MARKINGS POWER PLANT LIMITATIONS ENGINE Oil Grade or Specification Oil Quantity ENGINE OPERATING LIMITS FUEL Approved Fuel Grades Anti-Icing Additive PROPELLER STARTER GENERATOR 2- 10 POWER CONTROL LEVER OPERATION 2-10 CHIP DETECTOR... SECTION 2 LIMITATIONS Subject Page CENTER OF GRAVITY LIMITS 2-13 MANEUVER LIMITS 2-14 FLIGHT LOAD FACTOR LIMITS 2-14 FLIGHT CREW LIMITS 2-14 KINDS OF OPERATION 2-14 PNEUMATIC DEICING BOOT SYSTEM 2-15 ICING LIMITATIONS 2-15 SEVERE ICING CONDITIONS 2-16 KINDS OF OPERATION EQUIPMENT LIST 2-17 FUEL LIMITATIONS 2-22... Page 77 SECTION 2 LIMITATIONS Subject Page OTHER LIMITATIONS 2-28 PASSENGER SEAT LAP BELT EXTENSION 2-28 STANDARD PASSENGER SEAT TYPES 2-28 CARGO LIMITATIONS 2-28 EXECUTIVE CABIN FLOODLIGHTS 2-28 ALL PASSENGER SEATS 2-28 LUGGAGE LIMITATIONS 2-29 STRUCTURAL LIMITATIONS 2-29 SMOKING 2-29 PLACARDS 2-30 EXTERIOR 2-30 COCKPIT... Page 78 SECTION 2 LIMITATIONS THIS PAGE INTENTIONALLY LEFT BLANK Report No: 02211 Issued: March 30, 2001 2-iv... SECTION 2 LIMITATIONS GENERAL This section contains the FOCA Approved operating limitations, instrument markings, color coding, and basic placards necessary for the operation of the airplane, its engine, systems, and equipment. Compliance with approved limitations is mandatory. With the exception of circuit breakers on the Battery Bus, Avionic 1 Bus and 26V AC Bus, and unless detailed otherwise in procedures, all tripped open circuit breakers are not allowed to be reset in flight. SECTION 2 LIMITATIONS AIRSPEED LIMITATIONS AIRSPEED KCAS KIAS SIGNIFICANCE Maximum operating speed Do not exceed this speed in any operations. Refer to V schedule for maximum speed above 15,200 ft. (See Fig No. 2-1, V mo Schedule) 0.48 Maximum Operating Do not make full or abrupt control Maneuvering Speed - V movements above this speed. Page 81 SECTION 2 LIMITATIONS Figure 2-1, V Schedule Issued: March 30, 2001 Report No: 02211... SECTION 2 LIMITATIONS AIRSPEED INDICATOR MARKINGS MARKING KIAS VALUE REMARKS OR RANGE Red Line 236 or 0.48 M Maximum operating limit (V whichever is Red/White lower Needle Normal operating range. Lower limit is Green Arc 91 to 236 maximum weight stall speed in the clean configuration (V ). SECTION 2 LIMITATIONS POWER PLANT LIMITATIONS ENGINE Number of Engines Engine Manufacturer Pratt & Whitney Canada Engine Model Number PT6A-67B OIL GRADE OR SPECIFICATION Any oil specified by brand name in the latest revision of Pratt & Whitney Service Bulletin 14001 is approved. SECTION 2 LIMITATIONS ENGINE OPERATING LIMITS The limits presented in each column shall be observed. The limits presented do not necessarily occur simultaneously. Refer to the Pratt & Whitney Engine Maintenance Manual for specific action if limits are exceeded. OPERATING TORQUE CONDITION PRESS... Page 85 SECTION 2 LIMITATIONS ( 1 ) Torque limit applies within a range of 1000 to 1700 propeller rpm. Torque is limited to 23.9 psi below 1000 propeller rpm. ( 2 ) Normal oil pressure is 90 to 135 psi at gas generator speeds above 72%. SECTION 2 LIMITATIONS FUEL APPROVED FUEL GRADES JET A, JET-A-1, JET B, JP-4 Any other fuel which complies with the latest revision of Pratt & Whitney Service Bulletin 14004. ANTI-ICING ADDITIVE Anti-icing additive must be used for all flight operations in ambient temperatures below 0°... SECTION 2 LIMITATIONS PROPELLER Propeller Manufacturer Hartzell Propeller Model Number HC-E4A-3D/E10477K HC-E4A-3D/E10477SK Number of Propellers Number of Propeller Blades Propeller Diameter Minimum 104" (2.642 m) Maximum 105" (2.667 m) Propeller Operating Limits (N p ) Maximum Normal Operation 1,700 rpm Maximum transient ( 20 sec.) 1,870 rpm Maximum reverse... SECTION 2 LIMITATIONS GENERATOR Maximum generator load limit as follows GENERATOR MAX CONTINUOUS LOAD MAX LOAD FOR 2 MINUTES * Starter / Generator 300 AMP 450 AMP Second Generator 115 AMP *Maximum load permitted for a 2 minute period per each one hour of operation. POWER CONTROL LEVER OPERATION Power Control Lever operation aft of the idle detent is prohibited: 1. SECTION 2 LIMITATIONS POWER PLANT INSTRUMENT MARKINGS YELLOW GREEN YELLOW DIA/RAD RAD/DIA Min. Limit Caution Norm Ops. Caution Max. Limit Engine 60 to 104% Speed (N g ) 104% 400° to 760° to 800°/ 760° C 800° C 1,000° C 10°... SECTION 2 LIMITATIONS WEIGHT LIMITS Maximum Ramp Weight 9965 lb (4520 kg) Maximum Takeoff Weight 9921 lb (4500 kg) Maximum Landing Weight 9921 lb (4500 kg) Maximum Zero Fuel Weight 9039 lb (4100 kg) Maximum Baggage Weight 400 lb (180 kg) Maximum Floor Loading - On Seat Rails 205 lb/ft... SECTION 2 LIMITATIONS CENTER OF GRAVITY LIMITS Weight Forward Limit Aft Limit Pounds (kilograms) A.O.D.: In. / M A.O.D.: In. / M 9921 (4500) 232.20 / 5.898 240.94 / 6.120 8158 (3700) 224.13 / 5.693 7938 (3600) 242.99 / 6.172 6615 (3000) 242.99 / 6.172 5733 (2600) Minimum required flight crew is one pilot in the left hand seat. KINDS OF OPERATION The Pilatus PC-12 is approved for the following types of operation when the required equipment is installed and operational as defined within the Kinds of Operation Equipment List: 1. SECTION 2 LIMITATIONS PNEUMATIC DEICING BOOT SYSTEM The pneumatic deice system boots are required to be installed for all flights. Preflight function test required before takeoff and flight into known icing conditions. The system is required to function properly for flight into known icing conditions. Operation of the pneumatic de-ice boot system in ambient temperatures below -40°C and above +40°C may cause permanent damage to the boots. SECTION 2 LIMITATIONS In the event of a balked landing go-around with residual ice on the airframe, the flaps should not be retracted from the 15° position. Flight in freezing rain, freezing fog, freezing drizzle and mixed conditions causing ice accretion beyond the protected areas of the pneumatic boots is not approved. SECTION 2 LIMITATIONS KINDS OF OPERATION EQUIPMENT LIST This airplane is approved for operations under day or night VFR, day or night IFR and flight into known icing conditions when the required equipment is installed and operating properly. The following systems and equipment list is predicated on a crew of one pilot and does not include specific flight and radio/navigation equipment required by any particular country's operating regulations. Page 96 SECTION 2 LIMITATIONS SYSTEM / EQUIPMENT ICING NIGHT NIGHT Miscellaneous Instrs (EIS) (con’d): DC Voltmeter DC Ammeter Outside Air Temperature Gauge Engine: Starter Generator Second Generator Inertial Separator INERT SEP Annunciator Engine Driven Low Pressure Fuel Pump FUEL PRESS Annunciator Electric Wing Tank Fuel Boost Pump L FUEL PUMP Annunciator R FUEL PUMP Annunciator... Page 97 SECTION 2 LIMITATIONS SYSTEM / EQUIPMENT ICING NIGHT NIGHT Electrical (cont'd): AV 1 LED AV 2 LED BAT 1 LED BAT 1 HOT LED BAT 2 LED (if installed) BAT 2 HOT LED (if installed) Longitudinal (Stab) Trim System Alternate Stab Trim System STAB TRIM Annunciator Lateral Trim System Directional Trim System... Page 98 SECTION 2 LIMITATIONS SYSTEM / EQUIPMENT ICING NIGHT NIGHT Electrical (cont'd): Propeller Deice Timer Propeller Deice Brush Propeller Deice MOV Propeller Deice Boots Propeller Deice OAT Sensor PROP DE ICE Annunciator Left Wing Inspection Light A/P TRIM Annunciator A/P DISENG Annunciator PITOT 1 Annunciator PITOT 2 Annunciator STATIC Annunciator... Page 99 SECTION 2 LIMITATIONS SYSTEM / EQUIPMENT ICING NIGHT NIGHT For Pressurized Flight: Pressurization Control System (CPCS) Cabin Altimeter Cabin Vertical Speed Indicator Cabin Differential Pressure Indicator Maximum Cabin Altitude Warning CAB PRESS Annunciator ECS Annunciator Issued: March 30, 2001 Report No: 02211 2-21... SECTION 2 LIMITATIONS FUEL LIMITATIONS Total Fuel Capacity 406.8 US gal, 2,736.5 lb (1,540 liters, 1,241.3 kg) Total Usable Fuel 402 US gal, 2,703.6 lb (1,521.5 liters, 1,226.4 kg) Total Unusable Fuel 4.8 US gal, 32.9 lb (18.5 liters, 14.9 kg) Maximum Fuel Imbalance 26.4 US gal, 178 lb (100 liters, 80.6 kg) Executive Interior Code EX-4S-STD-4S four executive seats and four standard seats. Pilatus must be contacted to determine the modification work required to the aircraft, before any change to an interior configuration is made. Issued: March 30, 2001 Report No: 02211 Revision 15;... SECTION 2 LIMITATIONS SYSTEMS AND EQUIPMENT LIMITS STALL WARNING/STICK PUSHER SYSTEM Preflight function test required before takeoff. System is required to function properly in normal mode for all flights and in ice mode for flight into known icing conditions. TRIM SYSTEMS Stabilizer normal and alternate, and rudder trim systems must function properly for all flights. Page 103 SECTION 2 LIMITATIONS OXYGEN SYSTEM A minimum oxygen supply of 10 minutes duration for each occupant is required for dispatch for pressurized flight above FL250. NOTE Some National Operating Requirements may require that a larger quantity of oxygen be carried on the aircraft. Page 104 SECTION 2 LIMITATIONS PROBE HEAT Preflight function test required before takeoff. The system is required to function properly for IFR flight and flight into known icing condition. ENGINE INSTRUMENT SYSTEM (EIS) EIS must function properly for all flights. EIS system test required before takeoff. Takeoff is not approved with the red EIS warning light illuminated after a system test. Page 105 The autopilot must be disengaged, when the airplane is below 1000 ft AGL, except in accordance with the conditions given below. For airplanes equipped with a functioning Pilatus option radar altimeter, the autopilot must be disengaged below 200 ft AGL during ILS approach operations provided that the autopilot is coupled to glideslope vertical guidance of 6°... Page 106 SECTION 2 LIMITATIONS OTHER LIMITATIONS PASSENGER SEAT LAP BELT EXTENSION The lap belt extension Part No. 959.30.01.588 (used only with restraint system Part No. 959.30.01.232 or 959.30.01.233 or 959.30.01.584 or 959.30.01.585) or lap belt extension Part No. 959.30.01.590 (used only with restraint system Part No. Page 107 35 lb (15.9 kg). All stowed luggage in the wardrobe must be secured with the safety net. STRUCTURAL LIMITATIONS Refer to Chapter 4 of the PC-12 Aircraft Maintenance Manual, Pilatus Report Number 02049. SMOKING Smoking is not permitted in the cabin of aircraft equipped with a standard interior unless ashtrays are installed. Page 108 SECTION 2 LIMITATIONS Report No: 02211 Issued: March 30, 2001 2-30 Revision 15: Dec 12, 2019... Page 109 SECTION 2 LIMITATIONS Issued: March 30, 2001 Report No: 02211 2-31... Page 110 SECTION 2 LIMITATIONS Report No: 02211 Issued: March 30, 2001 2-32... Page 111 SECTION 2 LIMITATIONS Issued: March 30, 2001 Report No: 02211 Revision 8: December 01, 2012 2-33... Page 112 SECTION 2 LIMITATIONS Report No: 02211 Issued: March 30, 2001 2-34 Revision 17: November 03, 2021... Page 113 SECTION 2 LIMITATIONS Issued: March 30, 2001 Report No: 02211 2-35... Page 114 SECTION 2 LIMITATIONS Report No: 02211 Issued: March 30, 2001 2-36... Page 115 SECTION 2 LIMITATIONS Issued: March 30, 2001 Report No: 02211 2-37... Page 116 SECTION 2 LIMITATIONS Report No: 02211 Issued: March 30, 2001 2-38 Revision 1: March 1, 2003... Page 117 SECTION 2 LIMITATIONS Issued: March 30, 2001 Report No: 02211 Revision 4: April 30, 2007 2-39... Page 118 SECTION 2 LIMITATIONS Report No: 02211 Issued: March 30, 2001 2-40 Revision 15: Dec 12, 2019... Page 119 SECTION 2 LIMITATIONS Issued: March 30, 2001 Report No: 02211 2-41... Page 120 SECTION 2 LIMITATIONS Report No: 02211 Issued: March 30, 2001 2-42... Page 121 SECTION 2 LIMITATIONS Issued: March 30, 2001 Report No: 02211 Revision 9: June 01, 2014 2-43... Page 122 SECTION 2 LIMITATIONS Report No: 02211 Issued: March 30, 2001 2-44 Revision 9: June 01, 2014... Page 123 SECTION 2 LIMITATIONS Issued: March 30, 2001 Report No: 02211 Revision 9: June 01, 2014 2-45... Page 124 SECTION 2 LIMITATIONS Report No: 02211 Issued: March 30, 2001 2-46... Page 125 SECTION 2 LIMITATIONS Issued: March 30, 2001 Report No: 02211 Revision 4: April 30, 2007 2-47... Page 126 SECTION 2 LIMITATIONS Report No: 02211 Issued: March 30, 2001 2-48 Revision 9: June 01, 2014... Page 127 SECTION 3 EMERGENCY PROCEDURES SECTION 3 EMERGENCY PROCEDURES CONTENTS Paragraph Subject Page EMERGENCY PROCEDURES GENERAL AIRSPEEDS FOR EMERGENCY OPERATIONS REJECTED TAKEOFF ENGINE FAILURE 3.4.1 ENGINE FAILURE BEFORE ROTATION 3.4.2 ENGINE FAILURE AFTER ROTATION - LANDING GEAR DOWN 3.4.3 ENGINE FAILURE AFTER ROTATION - LANDING GEAR UP 3.4.4 ENGINE FAILURE IN FLIGHT - PARTIAL POWER... Page 128 SECTION 3 EMERGENCY PROCEDURES Paragraph Subject Page FIRE, SMOKE OR FUMES 3-18 3.7.1 ENGINE FIRE - ON GROUND 3-18 3.7.2 ENGINE FIRE - IN FLIGHT 3-18 3.7.3 COCKPIT/CABIN FIRE, SMOKE OR FUMES AND 3-20 SMOKE EVACUATION EMERGENCY DESCENT 3-22 3.8.1 GENERAL 3-22 3.8.2... Page 129 SECTION 3 EMERGENCY PROCEDURES Paragraph Subject Page 3.15 ELECTRICAL SYSTEM FAILURES 3-44 3.15.1 ELECTRICAL POWER LOSS 3-44 3.15.2 ESNTL BUS 3-44 3.15.3 BAT HOT 3-47 3.15.4 GEN 1 OFF 3-47 3.15.5 GEN 2 OFF 3-49 3.15.6 BAT OFF 3-49 3.15.7 INVERTER 3-50 3.15.8... Page 130 SECTION 3 EMERGENCY PROCEDURES Paragraph Subject Page 3.20.7 WHEEL BRAKE FAILURE 3-78 3.20.8 CAWS MALFUNCTION 3-78 3.20.9 UNIDENTIFIED WARNING TONE 3-78 3.21 AUTOPILOT 3-79 3.21.1 CHECKLIST 3-79 3.21.2 AMPLIFIED MALFUNCTION PROCEDURES 3-81 Report No: 02211 Issued: March 30, 2001 3-iv Revision 17: November 03, 2021... SECTION 3 EMERGENCY PROCEDURES EMERGENCY PROCEDURES GENERAL The recommended action to be taken in case of failure or in emergency situations are contained in this section. Emergency procedures alone cannot protect against all situations. Good airmanship must be used in conjunction with the emergency procedures to manage the emergency. Page 132 SECTION 3 EMERGENCY PROCEDURES WARNING SYSTEMS: The PC-12 is fitted with a comprehensive warning system. The Central Advisory and Warning System (CAWS) contains: RED WARNINGS which require immediate action. AMBER CAUTIONS which advise that a system is not functioning or is an alert to a precautionary situation. SECTION 3 EMERGENCY PROCEDURES AIRSPEEDS FOR EMERGENCY OPERATIONS All airspeeds shown are with airplane in clean configuration under ISA conditions. Operating Maneuvering Speed (V 9921 lb (4500 kg) 158 KIAS 9480 lb (4300 kg) 155 KIAS 9039 lb (4100 kg) 151 KIAS 8380 lb (3800 kg) 145 KIAS... Page 134 SECTION 3 EMERGENCY PROCEDURES Landing Approach Speeds with ice accretion on the airframe: After failure of: Minimum Approach Speed: Pneumatic Deice Boots (flap position limit 0°) 130 KIAS AOA Probe Deice 108 KIAS and/or Pitot and Static Probe Deice 108 KIAS and/or Pusher Ice Mode (flap position limit 15°) SECTION 3 EMERGENCY PROCEDURES REJECTED TAKEOFF (Not engine related) Idle Reverse As required Braking As required If the aircraft cannot be stopped on the remaining runway: Idle CONDITION LEVER CUT-OFF/FEATHER FUEL EMERG SHUT OFF Press latch down (if installed) and pull lever up MASTER POWER switch EMERGENCY OFF After the aircraft has stopped... SECTION 3 EMERGENCY PROCEDURES ENGINE FAILURE 3.4.1 ENGINE FAILURE BEFORE ROTATION 1. PCL Idle 2. Braking As required If runway overrun or collision is likely, then: 3. CONDITION LEVER CUT-OFF/FEATHER 4. FUEL EMERG SHUT OFF Press latch down and pull lever up 5. Page 137 SECTION 3 EMERGENCY PROCEDURES 3.4.3 ENGINE FAILURE AFTER ROTATION - LANDING GEAR UP If partial power loss refer to 3.4.4. If total power loss: 1. Landing Gear DOWN 2. NON ESS OVRD switch NON ESS OVRD (Overhead Panel) 3. Flaps 40°... Page 138 SECTION 3 EMERGENCY PROCEDURES CAUTION WHEN THE STARTER SWITCH IS PUSHED ON AIRCRAFT WITH A SINGLE BATTERY INSTALLED, THE AUTOPILOT MAY DISENGAGE AND THE AHRS AND EFIS MAY GO OFF-LINE. 5. Manual Override Lever Move forward to required power (Ng > 80%) 6. SECTION 3 EMERGENCY PROCEDURES 3.4.5 ENGINE FAILURE IN FLIGHT – TOTAL POWER LOSS 1. PCL Idle 2. CONDITION LEVER CUT-OFF/FEATHER 3. Remaining fuel Check 4. Air start (refer to Sect. 3.5) 5. If above 13500 ft, make an emergency descent (refer to Sect. SECTION 3 EMERGENCY PROCEDURES AIR START 3.5.1 AIR START ENVELOPE Figure 3-1. Relight Envelope Report No: 02211 Issued: March 30, 2001 3-10 Revision 7: Jul 20, 2011... SECTION 3 EMERGENCY PROCEDURES 3.5.2 AIR START - WITH STARTER WARNING DO NOT ATTEMPT MORE THAN ONE AIR START. REPEATED START ATTEMPTS COULD DISCHARGE THE BATTERY TO A LEVEL THAT WOULD NOT BE ABLE TO SUPPORT ESSENTIAL ELECTRICAL SERVICES. 1. PCL Idle 2. SECTION 3 EMERGENCY PROCEDURES ENGINE EMERGENCIES 3.6.1 OIL PRESSURE Indications: EIS Caution oil blinking 40/min. (after 20 secs, EIS warning oil blinking 80/min). Oil Px 60 to 90 PSI: 1. Ng Check above 72 % 2. Torque Reduce to below 24 PSI 3. SECTION 3 EMERGENCY PROCEDURES B. IN FLIGHT 1. Check and monitor engine parameters 2. Reduce power to minimum required for safe flight Land as soon as practical After landing: Inspect chip detector(s) and engine, if required. 3.6.4 OIL QUANTITY ON GROUND Indication: CAWS OIL QTY warning caption (only on ground, before engine start and voice callout “Warning, Oil”... SECTION 3 EMERGENCY PROCEDURES 3.6.6 PROPELLER - LOW PITCH Indications: CAWS PROP LOW P warning caption and voice callout “Warning, Prop Low Pitch”. Possible excessive propeller speed or height loss. 1. PCL Ensure forward of idle detent. If it is not possible to maintain speed and height: 2. SECTION 3 EMERGENCY PROCEDURES 3.6.8 PROPELLER - UNDERSPEED A. IN FLIGHT Indications: EIS caution, propeller digits blink 40/min Propeller speed below 1640 RPM 1. PCL Increase power 2. Aircraft speed Increase B. ON GROUND Indications: EIS caution, prop digits blink 40/min. Prop speed below 950 RPM. Page 146 SECTION 3 EMERGENCY PROCEDURES 3.6.9 ENGINE TORQUE Indications: EIS caution and torque digits blinking 40/min, or EIS warning and torque digits blinking 80/min. 1. TORQUE Check torque indication If torque above 44.3 psi: 2. PCL Reduce power If torque warning remains: 3. Page 147 SECTION 3 EMERGENCY PROCEDURES 3.6.11 ENGINE NG Indication: EIS caution and NG digits blinking 40/min, or EIS warning and NG digits blinking 80/min. 1. NG Check NG % indication If NG is above 104%: 2. PCL Reduce power 3. Aircraft speed Reduce to 120 KIAS or below 4. Page 148 SECTION 3 EMERGENCY PROCEDURES FIRE, SMOKE OR FUMES 3.7.1 ENGINE FIRE - ON GROUND Indications: CAWS warning ENG FIRE and voice callout “Fire, Fire, Fire”. Possible smoke and/or fumes. 1. PCL Idle 2. CONDITION LEVER CUT-OFF/FEATHER 3. ECS EMER shut off Pull 4. Page 149 SECTION 3 EMERGENCY PROCEDURES 6. Fuel EMER shut off Press latch down and pull lever 7. CONDITION LEVER CUT-OFF/FEATHER 8. Carry out emergency descent (Sect. 3.8) and/or emergency landing (Sect. 3.9) procedures. Issued: March 30, 2001 Report No: 02211 Revision 7: Jul 20, 2011 3-19... Page 150 SECTION 3 EMERGENCY PROCEDURES 3.7.3 COCKPIT/CABIN FIRE, SMOKE OR FUMES AND SMOKE EVACUATION 1. Oxygen masks ON (all occupants) Procedure to put on the crew oxygen masks: a. Remove the normal headset. b. Put the oxygen mask on. c. Put the normal headset back on. d. Page 151 SECTION 3 EMERGENCY PROCEDURES If smoke/fumes still persist and source is suspected electrical: 9. BUS TIE CB (overhead panel) Pull 10. GEN 2 TIE CB (overhead panel) Pull 11. GEN 1 / BATT 2 (if installed) If smoke/fumes persists and source is suspected electrical: 12. Page 152 SECTION 3 EMERGENCY PROCEDURES EMERGENCY DESCENT 3.8.1 GENERAL The type of emergency descent will depend on the kind of failure and the aircraft situation. Two types of descent are considered: 1. Engine failure, aircraft flown for maximum range. 2. Engine running, maximum descent rate. The factors to be considered are: Cabin altitude and oxygen duration. Page 153 SECTION 3 EMERGENCY PROCEDURES 3.8.2 MAXIMUM RANGE DESCENT - AFTER ENGINE FAIL – SINGLE BATTERY 1. PCL Idle 2. CONDITION LEVER CUT-OFF/FEATHER (to feather propeller) 3. Aircraft configuration Landing gear UP and flaps to 0°. CAUTION IF LANDING GEAR AND OR FLAPS ARE EXTENDED GLIDE RANGE WILL BE SEVERELY REDUCED. Page 154 SECTION 3 EMERGENCY PROCEDURES d. Nav/Com 2 e. ADF Transponder Off if radar communication is not required g. Wx Radar Off, if in IMC – as required If time permits, pulling the following CB’s will assist to reduce electrical load: RMI 1 Avionics 1 bus / Panel LH rear-V2 AHRS 2 (if installed) Page 155 SECTION 3 EMERGENCY PROCEDURES 3.8.3 MAXIMUM RANGE DESCENT - AFTER ENGINE FAIL – DUAL BATTERY 1. PCL Idle 2. CONDITION LEVER CUT-OFF/FEATHER (to feather propeller) 3. Aircraft configuration Landing gear UP and flaps to 0°. CAUTION IF LANDING GEAR AND OR FLAPS ARE EXTENDED GLIDE RANGE WILL... Page 156 SECTION 3 EMERGENCY PROCEDURES 9. Electrical load Monitor battery amps and reduce load as follows: a. External lights All OFF or as required b. De-ice systems In icing conditions, all OFF – except probes c. LH PITOT DE ICE Pull circuit breaker (Generator 1 bus / Panel RH front-K1) Page 157 SECTION 3 EMERGENCY PROCEDURES 3.8.4 MAXIMUM RATE DESCENT 1. PCL IDLE 2. Landing gear Below 177 KIAS, down 3. Aircraft speed M MO /V MO 4. All occupants Check seat lap and shoulder belts are fastened and the lap belt tightened. Page 158 SECTION 3 EMERGENCY PROCEDURES Report No: 02211 Issued: March 30, 2001 3-28 Revision 7: Jul 20, 2011... Page 159 SECTION 3 EMERGENCY PROCEDURES EMERGENCY LANDING 3.9.1 GLIDE DISTANCE AND SPEED Configuration: 1. Landing gear 2. Flaps 0° 3. CONDITION LEVER CUT-OFF/FEATHER 4. Best glide speed 114 KIAS for 9921 lb (4500 kg) (for best glide speed see para 3.2.B) NOTE A fully loaded battery will last as follows: 60 Amps for 20 minutes. Page 160 SECTION 3 EMERGENCY PROCEDURES 3.9.2 FORCED LANDING (ENGINE CUT- OFF/FEATHER) 1. PCL Idle 2. CONDITION LEVER CUT-OFF/FEATHER 3. FUEL EMERG SHUT OFF Pull 4. Electrical load Reduce 5. CABIN PRESS switch DUMP 6. Best glide speed 114 KIAS for 9921 lb (4500 kg) (for best glide speed see para 3.2.B) 7. Page 161 SECTION 3 EMERGENCY PROCEDURES 3.9.3 LANDING WITH MAIN LANDING GEAR UNLOCKED 1. Confirm landing gear position by control tower or other aircraft. CAUTION IF ONE MAIN LANDING GEAR IS NOT DOWN, IT IS RECOMMENDED TO LAND WITH GEAR UP. If failed gear is down but not locked: 2. Page 162 SECTION 3 EMERGENCY PROCEDURES 3.9.4 LANDING WITH NOSE LANDING GEAR UNLOCKED 1. Passengers Brief 2. Flaps 40° 3. Final approach speed 84 KIAS 4. Land on main wheels, keep nose high. 5. CONDITION LEVER CUT-OFF/FEATHER 6. Electrical Power EMERGENCY OFF (use MASTER POWER switch) 7. Page 163 SECTION 3 EMERGENCY PROCEDURES 3.9.6 LANDING WITHOUT ELEVATOR CONTROL 1. Passengers Brief 2. Landing gear Down 3. Flaps 40° 4. Final approach speed 90 KIAS 5. Set power as necessary to maintain speed and 300 to 500 ft rate of descent. 6. Page 164 SECTION 3 EMERGENCY PROCEDURES 3.9.8 LANDING WITHOUT FLAPS 1. Proceed as for normal approach 2. Landing gear DOWN 3. Final approach speed 118 KIAS 4. Landing Normal 5. Braking As required 6. Reverse As required NOTE Landing distance will increase by 80% 3.9.9 DITCHING 1. Page 165 SECTION 3 EMERGENCY PROCEDURES 3.10 LANDING GEAR/HYDRAULIC SYSTEM FAILURE 3.10.1 LANDING GEAR FAILS TO RETRACT Indications: All Landing Gear Indicator Lights do not extinguish. If CAWS N ESNTL BUS caution is ON 1. Refer to electrical failure (Sect. 3.15) If CAWS HYDR Caution is ON 2. Page 166 SECTION 3 EMERGENCY PROCEDURES 3.10.3 EMERGENCY EXTENSION Indications: Incorrect Indication on landing gear indicator lights. Red unlocked lights on and/or green lights not illuminated. 1. Airspeed 110 KIAS 2. Landing gear selector DOWN If 3 green lights not illuminated within 30 sec: 3. Page 167 SECTION 3 EMERGENCY PROCEDURES 3.11 FLAPS FAILURE ON GROUND Indication: CAWS FLAPS caution illuminated - means flap system failed 1. FLAP circuit breaker Check. If tripped, wait 5 minutes, (Battery bus / reset (max. 2 attempts) and Panel LH front-M2) continue normal operation if caption goes off. Page 168 SECTION 3 EMERGENCY PROCEDURES FAILURE IN FLIGHT - WITH POTENTIAL FLAP ASYMMETRY Indication: CAWS FLAPS caution illuminated shortly followed by PUSHER caution illuminating and voice callout “Flap Asymmetry Detected, Pusher Safe Mode” - means flap system failed and stick pusher remains available in ‘safe’ mode 1. Page 169 SECTION 3 EMERGENCY PROCEDURES 3.12 STICK PUSHER FAILURE Indication: CAWS PUSHER caution illuminated ON GROUND: 1. Pusher Test Carry out If pusher caution persists: 2. Aircraft No flight permitted, requires maintenance. IN FLIGHT: 1. Pusher Test Carry out If Shaker 1 and 2 active and PUSHER caution extinguished: 2. Page 170 SECTION 3 EMERGENCY PROCEDURES 3.13 INADVERTENT PUSHER/SHAKER OPERATION 3.13.1 PUSHER Indication: Non-commanded pusher operation, rapid nose pitch- down motion. NOTE Control wheel force to stop pusher operation is 60 to 65 pounds. 1. Control wheel HOLD against pusher action 2. PUSHER INTR switch PRESS and HOLD 3. Page 171 SECTION 3 EMERGENCY PROCEDURES CAUTION STALL SPEEDS IN TURNS ARE HIGHER. AOA MAY NOT BE RELIABLE 6. Pusher Test Carry out to check shaker availability. If shaker 1 or 2 not active: WARNING APPROACHES TO STALLS ARE NOT WARNED AND NATURAL STALLS ARE NOT PREVENTED WITH THE STICK SHAKER INOPERATIVE. Page 172 SECTION 3 EMERGENCY PROCEDURES WARNINGS APPROACHES TO STALLS ARE NOT WARNED AND NATURAL STALLS ARE NOT PREVENTED WITH THE STICK SHAKER INOPERATIVE. STALLS MUST BE AVOIDED WHEN THE STICK PUSHER IS INOPERATIVE. EXCESSIVE WING DROP AND ALTITUDE LOSS MAY RESULT DURING STALL WITH FLAPS DOWN AND/OR WHEN POWER IS APPLIED. Page 173 SECTION 3 EMERGENCY PROCEDURES If CAWS A/P TRIM green advisory caption and/or A/P trim light on triple trim indicator is not on: 2. CB of failed trim PULL NOTE STAB TRIM on Battery bus / Panel LH front-A1 AIL TRIM CBs on Battery bus / Panel LH front-B1 STAB ALTERN on Generator 1 bus / Panel RH front-A1 RUD TRIM CBs on Generator 1 bus / Panel RH front-B1 3. Page 174 SECTION 3 EMERGENCY PROCEDURES 3.15 ELECTRICAL SYSTEM FAILURES 3.15.1 ELECTRICAL POWER LOSS Indication: Loss of electrical power 1. MASTER POWER switch Check ON and guarded 2. BATT and GEN switches Check ON If indication remains: 3. Aircraft Land as soon as possible 3.15.2 ESNTL BUS CAWS warning Voice callout ”Warning Essential Bus, Battery”... Page 175 SECTION 3 EMERGENCY PROCEDURES Aircraft Descend below 12,500 ft 6. Land as soon as possible. CAUTION THE FOLLOWING SYSTEMS ARE INOPERATIVE: Engine Start/relight Stick pusher Propeller feather Landing gear Indications Fire detection Fuel quantity sensing ... Page 176 SECTION 3 EMERGENCY PROCEDURES CAUTION THE FOLLOWING SERVICES ARE INOPERATIVE: Auto pilot (pitch modes) Auto fuel pump and fuel quantity measuring system Alternate pitch trim RH fuel pump Rudder trim Oxygen contents Air/ground system ... Page 177 SECTION 3 EMERGENCY PROCEDURES 3.15.3 BAT HOT CAWS CAUTION Indicates that the battery temperature is excessive. 1. Overhead Panel Identify the battery overtemp (If second battery installed) 2. Battery charge current Check If charge current high: 3. Affected BATT switch OFF (Do not select ON again) If charge current normal: 4. Page 178 SECTION 3 EMERGENCY PROCEDURES NOTE The engine starting is inoperative if the STARTER CB is pulled. 6. GEN 1 Master switch Confirm ON 7. GEN 1 reset Press 8. GEN 1 Master switch If GEN 1 does reset: 9. Aircraft Land as soon as practical If GEN 1 does not reset: 10. Page 179 SECTION 3 EMERGENCY PROCEDURES 3.15.5 GEN 2 OFF CAWS CAUTION 1. GEN 2 master switch Confirm ON 2. GEN 2 master switch OFF then ON If GEN 2 does not RESET: 3. Overhead Panel Confirm GEN 2 BUS failure, indicator off. (GEN 1 supplies GEN 2 BUS). Page 180 SECTION 3 EMERGENCY PROCEDURES 3.15.7 INVERTER CAWS CAUTION and/or RMI flag 1. Overhead panel Select alternate inverter 2. CONTINUE FLIGHT - REPORT ON LANDING. 3.15.8 BUS TIE CAWS CAUTION Indicates that the Generator 1 bus tie isolation relay is open. 1. Page 181 SECTION 3 EMERGENCY PROCEDURES NOTE If items of the above listed services are required, the NON ESS OVRD switch can be set to OVRD temporarily or permanently. First isolate any faulty consumer and make sure that the electrical system is stable and the battery (or batteries) are not discharging. Page 182 SECTION 3 EMERGENCY PROCEDURES 3.15.10 N ESNTL BUS CAWS CAUTION Indicates that the Non Essential busbar voltage is less than 22 VDC. Normally due to automatic load shedding after GEN 1 failure and/or a tripped BUS TIE circuit breaker. A. If GEN 1 OFF caution is illuminated - refer to GEN 1 OFF (Sect. 3.15.4) B. Page 183 SECTION 3 EMERGENCY PROCEDURES 3.15.11 BATTERY CAWS CAUTION Indicates an increase in battery current discharge or a high battery voltage. Normally due to a generator failure or a tripped BUS TIE circuit breaker. 1. Overhead panel Check BATT 1 and BATT 2 for normal volts/amps, identify... Page 184 SECTION 3 EMERGENCY PROCEDURES 3.16 ENGINE INSTRUMENT SYSTEM (EIS) FAILURE Indication: Torque or ITT suspect, frozen or blank. EIS MENU button Press Digital readouts of ITT and Torque will replace the normal digital OAT °C and ENDUR hours and minutes readouts on the EIS Display. Indication: Any indication other than Torque or ITT frozen or blank. Page 185 SECTION 3 EMERGENCY PROCEDURES PARAMETER OUT OF RANGE ACTION: ACTION: Torque See Sect. 3.6 - Engine emergencies See Sect. 3.6 - Engine emergencies Gas GEN RPM (NG) See Sect. 3.6 - Engine emergencies Oil Temperature See Sect. 3.6 - Engine emergencies Oil Pressure See Sect. Page 186 SECTION 3 EMERGENCY PROCEDURES 3.17 FUEL SYSTEM 3.17.1 LOW FUEL PRESSURE Indication: - FUEL PRESS CAWS caution, and/or - CAWS Advisory FUEL PUMP cycling on and off every 10 seconds 1. Power Reduce to minimum to sustain flight 2. FUEL PUMPS 3. Page 187 SECTION 3 EMERGENCY PROCEDURES 3.17.2 FUEL QUANTITY LOW Indication: CAWS caution – L FUEL LOW or R FUEL LOW or L + R FUEL LOW 1. FUEL indications Check If fuel leak from one wing is suspected: 2. Aircraft Carry out suspected fuel leak procedure (Para 3.17.4) If no fuel leak is suspected and both fuel low quantity cautions are on: 3. Page 188 SECTION 3 EMERGENCY PROCEDURES When fuel balanced: 5. FUEL PUMP AUTO B. IN FLIGHT 1. Fuel L and R indications Check for difference CAUTION THERE SEGMENTS MORE DIFFERENCE BETWEEN LEFT RIGHT, POSSIBLE AILERON DEFLECTION REQUIRED FOR WINGS LEVEL FLIGHT, ESPECIALLY AT LOW SPEED. Page 189 SECTION 3 EMERGENCY PROCEDURES If fuel is balanced: 8. FUEL PUMP CBs Reset (Battery bus / Panel LH front-F1 or Generator 1 bus / Panel RH front-F1) 9. FUEL PUMPS AUTO 3.17.4 SUSPECTED FUEL LEAK 1. FUEL PUMP (on leaking side) 2. Page 190 SECTION 3 EMERGENCY PROCEDURES 3.17.6 FUEL PUMP FAILURE Indication: - Fuel pump(s) on for more than 10 seconds with fuel balanced and no CAWS FUEL PRESS caution, or - Both fuel pumps on for more than 10 seconds with 2 or more segments difference between left and right and no CAWS FUEL PRESS caution, or - Fuel pump(s) not on with the CAWS PUMP advisory... Page 191 SECTION 3 EMERGENCY PROCEDURES 3.18 CABIN CONDITIONING FAILURES 3.18.1 CABIN PRESSURIZATION FAILURE Indication: CAWS CAB PRESS warning and voice callout “Warning, Cabin pressure” 1. Pressure Indication: Check A. If CAB P > 5.75 PSI: 1. Cabin Altitude Selector Check correct setting 2. Page 192 SECTION 3 EMERGENCY PROCEDURES B. If cab. alt. > 10,000 ft: 1. Oxygen masks Procedure to put on the crew oxygen masks: a. Remove the normal headset. b. Put the oxygen mask on. c. Put the normal headset back on. d. Page 193 SECTION 3 EMERGENCY PROCEDURES 3.18.3 ECS FAILURE Indication: CAWS ECS caution 1. ECS circuit breaker CHECK. Reset if tripped (Battery bus / Panel LH front-H3) If problem remains, reset the ECS: 2. ECS switch 3. ECS switch AUTO If unsuccessful: 4. Page 194 SECTION 3 EMERGENCY PROCEDURES 3.19 DEICE SYSTEMS 3.19.1 PROPELLER DEICE FAILURE IN ICING CONDITIONS Indication: PROP DE ICE CAWS caution WARNING LOSS OF PROPELLER DEICE IN ICING CONDITIONS CAN CAUSE SEVERE DEGRADATION IN AIRCRAFT SPEED AND CLIMB PERFORMANCE. 1. PROP switch Push to OFF and wait 10 seconds 2. Page 195 SECTION 3 EMERGENCY PROCEDURES 3.19.2 BOOT DEICE FAILURE IN ICING CONDITIONS Indication: DE ICE BOOTS CAWS caution with DE ICE BOOTS CAWS advisory OFF WARNING A BOOT DEICE FAILURE IN ICING CONDITIONS CAN CAUSE DEGRADATION OF AIRCRAFT SPEED AND CLIMB PERFORMANCE AND A PREMATURE STALL. Page 196 SECTION 3 EMERGENCY PROCEDURES CAUTION ON LANDING APPROACH AFTER BOOT FAILURE (FLAPS 0°), THE EFIS AOA FAST SLOW POINTER WILL NOT BE CORRECT AND SHOULD NOT BE USED AS REFERENCE. 3.19.3 INERTIAL SEPARATOR FAILURE Indication: INERT SEP CAWS caution WARNINGS AN INERTIAL SEPARATOR FAILURE IN ICING CONDITIONS CAN CAUSE DEGRADATION OF THE AIRCRAFT ENGINE PERFORMANCE (AN INCREASE... Page 197 SECTION 3 EMERGENCY PROCEDURES 7. Aircraft Avoid further icing conditions If any attained performance degradation continues: 8. Aircraft Land as soon as possible 3.19.4 WINDSHIELD DEICE FAILURE IN ICING CONDITIONS Indication: WSHLD HEAT CAWS caution 1. LH WSHLD circuit breaker Check. Page 198 SECTION 3 EMERGENCY PROCEDURES 3.19.5 AOA PROBE DEICE FAILURE IN ICING CONDITIONS Indication: AOA DE ICE CAWS caution WARNING AN AOA PROBE DEICE FAILURE IN ICING CONDITIONS CAN CAUSE A FALSE ACTIVATION OF THE STALL PROTECTION SYSTEM. 1. LH AOA SENS DE ICE Check. Page 199 SECTION 3 EMERGENCY PROCEDURES 10. Landing approach Keep minimum landing approach speed above 105 KIAS or shaker activation speed, whichever is highest. The total landing distance will be longer by up to 67%. CAUTION WHEN LANDING WITH AOA DEICE FAILURE THE EFIS AOA FAST SLOW POINTER MAY NOT BE CORRECT SHOULD... Page 200 SECTION 3 EMERGENCY PROCEDURES 3.19.6 PITOT AND STATIC PROBE DEICE FAILURE IN ICING CONDITIONS Indication: PITOT 1 or PITOT 2 or STATIC CAWS caution WARNING A PITOT AND STATIC DEICE FAILURE IN ICING CONDITIONS CAUSE INCORRECT INDICATION ON THE ASI AND/OR ALTIMETER AND VSI. Page 201 SECTION 3 EMERGENCY PROCEDURES 3.19.7 PUSHER ICE MODE FAILURE IN ICING CONDITIONS Indication: PUSHER CAWS caution on with PUSHER ICE MODE CAWS advisory off. WARNING A FAILURE OF THE STALL WARNING/STICK PUSHER SYSTEM TO RE-DATUM TO ICE MODE WHEN IN ICING CONDITIONS LEAVE AIRCRAFT... Page 202 SECTION 3 EMERGENCY PROCEDURES 10. Landing approach Keep minimum landing approach speed above 105 KIAS. total landing distance will be longer by up to 67% CAUTION WHEN LANDING WITH FAILED PUSHER ICE MODE, THE EFIS AOA FAST SLOW POINTER WILL NOT BE CORRECT AND SHOULD NOT BE USED AS REFERENCE. Page 203 SECTION 3 EMERGENCY PROCEDURES B. IN FLIGHT - the following systems could be affected: NOTE Consider fuel and range before extending landing gear. 1. Landing gear Cycle DOWN, UP (once only) If no effect: Stick pusher Inoperative Landing gear handle solenoid Goes to locked. Page 204 SECTION 3 EMERGENCY PROCEDURES B. IN FLIGHT: CAUTION DO NOT ADJUST THE POSITION OF THE DOOR HANDLES IN FLIGHT. 1. All occupants Check seat lap and shoulder belts are fastened and the lap belt tightened 2. Airspeed Reduce to practical minimum 3. Page 205 SECTION 3 EMERGENCY PROCEDURES 3.20.4 ATTITUDE AND HEADING REFERENCE SYSTEM (AHRS) FAILURE Indication: Attitude fail and/or heading fail ON EFIS. Aircraft with single AHRS installation NOTE Failure of the AHRS will cause the autopilot to disengage. 1. Attitude and Use standby attitude and heading reference compass 2. Page 206 SECTION 3 EMERGENCY PROCEDURES 3.20.5 EFIS FAILURE Indication: DU goes blank. 1. EFIS CMPST switch CMPST NOTE Operation of the EFIS CMPST switch with the autopilot engaged, will cause the autopilot to disengage. Indication: EFIS goes blank. 1. Use alternate instruments as required. 3.20.6 AIRSPEED AND/OR ALTITUDE INDICATION MALFUNCTION, PITOT / STATIC SYSTEM FAILURE Indications:... Page 207 SECTION 3 EMERGENCY PROCEDURES 4. PCL Set maximum cruise power torque and cross check resulting indicated airspeed from Max Cruise table (Section 5 page 46 onwards) against cockpit indications 5. Pilot If determined which system is correct, use the associated instruments. Page 208 SECTION 3 EMERGENCY PROCEDURES 3.20.7 WHEEL BRAKE FAILURE Indications: Wheel brakes ineffective Pedal excessively soft when pressed. 1. Landing + Taxi Use reverse power, BETA and Nose wheel steering. 3.20.8 CAWS MALFUNCTION Indication: CAWS FAIL caution on. 1. CAWS 1 circuit breaker Pull open then push to reset. Page 209 SECTION 3 EMERGENCY PROCEDURES 3.21 AUTOPILOT 3.21.1 CHECKLIST The four step procedure listed under paragraph A should be among the basic airplane emergency procedures that are committed to memory. It is important that the pilot be proficient in accomplishing all four steps without reference to this manual. Page 210 SECTION 3 EMERGENCY PROCEDURES B. Autopilot Disengagement. The autopilot may be manually disengaged by any of the following methods: 1. Press the Autopilot Disengage switch on the pilot's or copilot's control wheel. 2. Actuate the airplane Electric Stabilizer Manual Trim Engage switch (momentary). Page 211 SECTION 3 EMERGENCY PROCEDURES 3.21.2 AMPLIFIED MALFUNCTION PROCEDURES The following paragraphs are presented to supply additional information for the purpose of providing the pilot with a more complete understanding of the recommended course of action for an emergency situation. 1. An autopilot or autopilot trim disengage occurs when there is an uncommanded deviation in the airplane flight path due to a system malfunction. Page 212 SECTION 3 EMERGENCY PROCEDURES INTENTIONALLY BLANK Report No: 02211 Issued: March 30, 2001 3-82 Revision 7: Jul 20, 2011... Page 213 SECTION 4 NORMAL PROCEDURES SECTION 4 NORMAL OPERATING PROCEDURES CONTENTS Paragraph Subject Page NORMAL OPERATING PROCEDURES GENERAL AIRSPEEDS FOR NORMAL OPERATIONS PREFLIGHT INSPECTION 4.3.1 EMPENNAGE 4.3.2 RIGHT WING TRAILING EDGE 4.3.3 RIGHT WING LEADING EDGE 4.3.4 NOSE SECTION 4.3.5 LEFT WING LEADING EDGE 4.3.6 LEFT WING TRAILING EDGE 4.3.7... SECTION 4 NORMAL PROCEDURES Paragraph Subject Page 4.12 CRUISE 4-21 4.13 DESCENT 4-22 4.14 BEFORE LANDING 4-22 4.14.1 APPROACH CHECK 4-22 4.14.2 FINAL CHECK 4-23 4.15 BALKED LANDING (GO-AROUND) 4-24 4.16 LANDING 4- 25 4.16.1 NORMAL 4-25 4.16.2 SHORT FIELD 4-25 4.17 AFTER LANDING 4-25... SECTION 4 NORMAL PROCEDURES NORMAL OPERATING PROCEDURES GENERAL This section provides the normal operating procedures. All of the procedures required by regulation as well as those procedures which have been determined as necessary for the operation of this airplane are provided. Normal operating procedures associated with optional systems or equipment which require supplements are contained in Section 9, Supplements. SECTION 4 NORMAL PROCEDURES AIRSPEEDS FOR NORMAL OPERATIONS Airspeeds for normal operations are listed below. Unless otherwise noted, all airspeeds are based on a maximum takeoff weight of 9,921 lb (4,500 kg) at sea level under ISA standard day conditions. Takeoff (V Flaps 15°... SECTION 4 NORMAL PROCEDURES Maximum Demonstrated Crosswind for Takeoff and Landing (not a limitation): Flaps 0° 30 kts Flaps 15° 25 kts Flaps 30° 20 kts Flaps 40° (landing only) 15 kts PREFLIGHT INSPECTION 4.3.1 EMPENNAGE 1. Luggage CHECKED and SECURED 2. SECTION 4 NORMAL PROCEDURES 19. Battery compartment a. ELT CHECK CONDITION (If installed) b. Autopilot servos and cables CHECK CONDITION c. Steering bar STOWED and SECURED d. Battery CONNECTED e. Battery compartment CHECK CLOSED 4.3.2 RIGHT WING TRAILING EDGE 1. Flaps CHECK CONDITION 2. SECTION 4 NORMAL PROCEDURES 4.3.4 NOSE SECTION A. SERVICE BAY (RIGHT) (If a standard oxygen system is installed): 1. Oxygen Press CHECK 2. Oxygen and ECS Doors CLOSED 3. Oxygen rupture disc INTACT WARNING DO NOT TOUCH OUTPUT CONNECTORS OR COUPLING NUTS OF IGNITION EXCITER WITH BARE HANDS. SECTION 4 NORMAL PROCEDURES 11. General Condition CHECK 12. Cowling LH CHECK and SECURE 13. Windshield CHECK CLEAN C. SERVICE BAY (LEFT) 1. Fuel Filter SECURE INDICATOR FLUSH 2. Fuel Filter drain SAMPLE AND SECURE 3. Fuel Compartment Doors CLOSED 4. SECTION 4 NORMAL PROCEDURES 4.3.7 CABIN 1. Passenger Door CLOSED and LOCKED (check for 6 green flags) If required, fit thermal blanket. Make sure door handle and latch are accessible. 2. Hand luggage SECURED/STOWED 3. Passenger Seat CHECK Backrests in upright position (for takeoff and landing) 4. Page 222 SECTION 4 NORMAL PROCEDURES 16. PASS-WNG switches (if installed) 17. Circuit breakers CHECK IN 18. MSN 501 and UP. MASK/MIC switch CHECK set to MIC 19. EFIS CMPST switch NORM 20. AHRS SLAVE AHRS 1/AHRS 2 (if installed) SLAVE 21. Landing Gear Handle 22. SECTION 4 NORMAL PROCEDURES BEFORE STARTING ENGINE 4.4.1 PROCEDURE 1. Preflight inspection COMPLETE 2. Seats ADJUSTED and LOCKED 3. Seat belts FASTENED 4. BATT 1 switch BATT 2 switch ON (if 2 battery installed) 5. Overhead Panel Voltmeter CHECK (24 VDC min). Both indicators (if 2nd battery installed) 6. Page 224 SECTION 4 NORMAL PROCEDURES 14. Pilot ventilation window CLOSED and LOCKED 15. External lights AS REQUIRED NOTE Avoid prolonged use of the beacon and logo lights (if installed), as this can cause a decrease in battery power and affect the engine starting. SECTION 4 NORMAL PROCEDURES ENGINE STARTING 4.5.1 WITH OR WITHOUT EXTERNAL POWER Fuel quantity CHECK EIS System TEST TEST FIRE switch PUSH. (ENG FIRE and F DETECT lights on) TEST LAMP switch PUSH. (Warning, caution, advisory lights on). Overhead panel switches and red LED’s lit. Propeller area CLEAR, Confirm CLEAR of obstructions... Page 226 SECTION 4 NORMAL PROCEDURES Starter sequence COMPLETED Engine instruments CHECK Fuel Totalizer RESET EXT PWR switch OFF (If external power used) GEN 2 switch ON-Check CAWS Caution GEN 2 OFF is off GEN 1 switch ON-Check CAWS Caution GEN 1 OFF is off NOTE If the propeller rpm after start-up is below 950 rpm,... Page 227 SECTION 4 NORMAL PROCEDURES 4.5.2 DRY MOTORING RUN NOTE This procedure is used to remove internally trapped fuel and vapor or if there is evidence of fire within the engine gas path. Allow min 30 sec draining period, then: Condition Lever CUT-OFF/FEATHER Power Control Lever IDLE DETENT... SECTION 4 NORMAL PROCEDURES BEFORE TAXIING 1. AHRS 1/AHRS 2 (if installed) CHECK - NO FLAGS 2. Flaps Lever 15° 3. Autopilot TEST Button PRESS momentarily and NOTE: (Autopilot Mode Controller) a. All annunciator lights on (ROLL, PTRM and AP TRIM FAIL annunciators flashing). Page 229 SECTION 4 NORMAL PROCEDURES When pusher operates: e. PUSHER INTR switch PRESS and HOLD, (Control Wheel) check pusher interrupts TEST PUSHER switch RELEASE (Overhead Panel) g. CAWS PUSHER caution CHECK ON after 3 sec h. PUSHER INTR switch RELEASE CAWS PUSHER caution CHECK OFF and CAWS PUSHER ICE MODE advisory... SECTION 4 NORMAL PROCEDURES TAXIING Brakes CHECK CHECK beta is available, return to IDLE Flight instruments CHECK PASS-WNG switches (if installed) CAUTION TO AVOID POSSIBLE PROPELLER DAMAGE, DO NOT ALLOW STABILIZED PROPELLER OPERATION BETWEEN 350 AND 950 RPM (PROPELLER NOT FEATHERED). NOTE Beta range (aft of idle detent) may be used during taxi to control taxi speed and reduce wear on brakes. Page 231 SECTION 4 NORMAL PROCEDURES Condition Lever FLIGHT IDLE If icing conditions expected set the DE ICING switches as follows: DE-ICING PROP switch PUSH to ON DE-ICING INERT SEP PUSH to OPEN DE-ICING BOOTS PUSH to ON. Select 3 MIN or 1 MIN as required DE-ICING LH and RH WSH PUSH to ON. SECTION 4 NORMAL PROCEDURES TAKEOFF EHSI CHECK HDG ECS switch (If torque as per Static Takeoff Torque chart in Section 5 is below flat rating) Power Control Lever (Under certain hot and/or high airfield altitude the engine power is below the torque limiter setting and manual power setting is required according to Static Takeoff Torque chart in Section 5) SECTION 4 NORMAL PROCEDURES 4.10 FLIGHT INTO KNOWN ICING CONDITIONS Icing conditions are defined in Section 1. NOTE Flight in icing conditions is only permitted with full operational status of all aircraft deicing systems. The deicing systems may be activated before takeoff. WARNING FLIGHT IN ICING CONDITIONS IS PROHIBITED IF THERE IS A KNOWN FAILURE OF ANY OF THE ICE PROTECTION... Page 234 SECTION 4 NORMAL PROCEDURES During icing conditions: Wing leading edge MONITOR for continual shedding of CAWS MONITOR for correct function of ice protection systems WARNINGS IF ANY OF THE AIRCRAFT ICE PROTECTION SYSTEMS FAIL DURING FLIGHT IN ICING CONDITIONS, EXIT ICING CONDITIONS. SECTION 4 NORMAL PROCEDURES 4.11 CLIMB Ice Protection system AS REQUIRED Autopilot AS REQUIRED Power Control Lever (According to Climb Torque chart for best performance or 720°C ITT recommended) ECS switch AUTO Temperature setting AS REQUIRED Cabin pressure Monitor Engine instruments: a. SECTION 4 NORMAL PROCEDURES 4.13 DESCENT Ice Protection system AS REQUIRED Power Control Lever SET to desired torque Cabin Pressure Controller SET to field elevation + 500 ft Windshield Heat AS REQUIRED 4.14 BEFORE LANDING 4.14.1 APPROACH CHECK 1. Ice Protection system AS REQUIRED 2. SECTION 4 NORMAL PROCEDURES 4.14.2 FINAL CHECK 1. Landing Gear 3 Green Lights 2. Flaps AS REQUIRED - With residual airframe ice SET maximum 15° - Boot failure Maintain at 0° 3. Speed Reduce to AOA centered and stabilized Boot failure 130 KIAS AOA Deice or 105 KIAS... SECTION 4 NORMAL PROCEDURES 4.15 BALKED LANDING (GO-AROUND) Go Around switch (if autopilot engaged) PRESS Power Control Lever (According to the Balked Landing Torque chart in Section 5) Climb airspeed 84 KIAS Flaps - Normal SET 15° (max 163 KIAS) - With residual airframe ice Maintain at 15°... SECTION 4 NORMAL PROCEDURES 4.16 LANDING 4.16.1 NORMAL 1. TOUCH DOWN MAIN WHEELS FIRST. 2. DO NOT FLARE WITH HIGH PITCH ANGLE. 3. Power Control Lever IDLE 4. Condition Lever GROUND IDLE 5. Braking AS REQUIRED 4.16.2 SHORT FIELD 1. TOUCH DOWN MAIN WHEELS FIRST. 2. SECTION 4 NORMAL PROCEDURES 4.18 SHUTDOWN WARNING INDICATION ENGINE FIRE AFTER SHUTDOWN, IMMEDIATELY DO DRY MOTORING RUN PROCEDURE. NOTES Allow ITT to stabilize at least two minutes at ground idle. Monitor compressor deceleration after shutdown for possible engine damage. Power Control Lever IDLE DETENT Parking Brake SET/PEDALS PUSH... SECTION 4 NORMAL PROCEDURES 4.19 PARKING Flight Control Lock INSTALLED Passenger door REMOVE thermal blanket (if installed) Wheel chocks AS REQUIRED Tail stand AS REQUIRED NOTE Install the tail stand when the aircraft is parked outside and wet snow fall is expected. Tie downs AS REQUIRED CAUTION... SECTION 4 NORMAL PROCEDURES 4.20 OXYGEN SYSTEM Oxygen Pressure Gauge NOTE READING Outside Air Temperature NOTE READING Percentage of Full Bottle DETERMINE from the " Oxygen Available with Partially Full Bottle " graph, Figure 4-1. COMPUTE Oxygen Duration in minutes: a. Page 243 SECTION 4 NORMAL PROCEDURES No. of Oxygen Duration Oxygen Duration Pax Oxygen Pax plus Pax plus Masks 1 Crew Mask on 2 Crew Masks on Connected Diluter/ 100 % Diluter/ 100 % Demand Demand (min) (min) (min) (min) Figure 4-2. Oxygen Duration with Full Bottle (Standard Oxygen System) (Sheet 1 of 2) Issued: March 30, 2001 Report No: 02211... Page 244 SECTION 4 NORMAL PROCEDURES No. of Oxygen Duration Oxygen Duration Pax Oxygen Pax plus Pax plus Masks 1 Crew Mask on 2 Crew Masks on Connected Diluter/ 100 % Diluter/ 100 % Demand Demand (min) (min) (min) (min) Figure 4-2. Oxygen Duration with a Full Bottle (Larger Capacity Oxygen System) (Sheet 2 of 2) Report No: 02211 Issued: March 30, 2001... SECTION 4 NORMAL PROCEDURES 4.21 AUTOPILOT 4.21.1 AUTOPILOT OPERATION SUMMARY WARNINGS THE PILOT IN COMMAND MUST CONTINUOUSLY MONITOR THE AUTOPILOT WHEN IT IS ENGAGED, PREPARED DISCONNECT AUTOPILOT AND TAKE IMMEDIATE CORRECTIVE ACTION - INCLUDING MANUAL CONTROL OF THE AIRPLANE AND/OR PERFORMANCE EMERGENCY PROCEDURES... Page 246 SECTION 4 NORMAL PROCEDURES Inflight Autopilot Engagement (Verify the airplane is in a trimmed condition prior to autopilot engagement.) a. AP Button - PRESS. Note AP and FD annunciators ON. If no other flight director modes are selected at the time of autopilot engagement the mode of operation will be flight director wings level and pitch attitude hold. Page 247 SECTION 4 NORMAL PROCEDURES Altitude Hold a. ALT Mode Selector Button - PRESS. Note ALT mode annunciator ON. Autopilot will maintain the pressure altitude. NOTE In accordance with FAA recommendation(ACOO- 24B), use of basic "PITCH ATTITUDE HOLD" mode recommended during operation severe turbulence. Page 248 SECTION 4 NORMAL PROCEDURES Vertical speed and Altitude Preselect Operation NOTE The altitude alert annunciator is illuminated 1000 ± 50 feet prior to the selected altitude, goes out 200 ± 50 feet prior to the selected altitude and illuminates momentarily when the selected altitude is reached. Once selected altitude... Page 249 SECTION 4 NORMAL PROCEDURES CAUTION ENGAGING GO AROUND WILL CANCEL ALT ARM. PILOT EFFORT SUCH AS RESELECTING THE DESIRED ALTITUDE, OR PUSHING THE ARM BUTTON, IS REQUIRED TO ARM ALTITUDE HOLD IN GO AROUND. 4) Airplane - ESTABLISH ATTITUDE to intercept the selected altitude. Page 250 SECTION 4 NORMAL PROCEDURES c. Changing Vertical Speed 1) Using CWS a) CWS button - PRESS and HOLD. b) Airplane - Establish desired vertical speed. c) CWS button - RELEASE. 2) Using Vertical Trim Control VERTICAL TRIM CONTROL - PRESS either up or down to increase or decrease the vertical speed. Page 251 SECTION 4 NORMAL PROCEDURES Indicated Airspeed Hold a. IAS Mode Selector button - PRESS. Note the IAS mode annunciator ON. The autopilot will maintain the current indicated airspeed. b. Change Selected Indicated Airspeed. 1) Using CWS (recommended for airspeed changes of 10 KIAS or greater). Page 252 SECTION 4 NORMAL PROCEDURES Roll Attitude Hold (HDG Mode Off) a. CWS button - PRESS and hold while manually banking the airplane to any desired angle between 6° and the maximum autopilot limit of 25° ± 4°. b. CWS button - RELEASE. Roll attitude hold will maintain the desired bank angle. Page 253 SECTION 4 NORMAL PROCEDURES NAV Coupling a. Course Bearing Pointer - SET to desired course. b. Heading Selector Knob - SET BUG to provide desired intercept angle. c. NAV Mode Selector Button - PRESS. 1) If the Course Deviation Bar is greater than 40% to 60% of full scale from center: the aircraft will continue in HDG mode (or wings level if HDG not selected) with the NAV ARM annunciated;... Page 254 THE AUTOPILOT MUST BE DISENGAGED WHEN THE AIRPLANE IS BELOW 1000 FT AGL IN COUPLED ILS APPROACH MODE, WHEN THE AIRPLANE EQUIPPED WITH FUNCTIONING PILATUS OPTION RADAR ALTIMETER. BC Approach Coupling a. Course Bearing Pointer - SET to the ILS front course inbound heading. Page 255 SECTION 4 NORMAL PROCEDURES Glideslope Coupling NOTE Glideslope coupling is inhibited when operating in NAV or APR BC modes. Glideslope coupling occurs automatically in the APR mode. a. APR Mode - ENGAGED. NOTE Autopilot can capture glideslope from below or slightly above the beam while operating in either PITCH ATTITUDE HOLD, IAS HOLD, VS HOLD, or ALT HOLD modes. Page 256 SECTION 4 NORMAL PROCEDURES Missed Approach a. Power Lever GA Switch - PRESS to engage the go-around mode. This will provide a wings level, pitch up command. Note GA mode annunciator ON. Forward PCL to the required setting. b. Activate A/P modes as desired. CAUTION ENGAGING GO AROUND WILL CANCEL ALL MODES. Page 257 SECTION 4 NORMAL PROCEDURES 4.21.2 FLIGHT DIRECTOR OPERATION NOTE The Flight Director modes of operation are the same as those used for autopilot operations except the autopilot is not engaged and the pilot must maneuver the aircraft to satisfy the Flight Director commands. No autotrim functions are provided by the autopilot. Page 258 SECTION 4 NORMAL PROCEDURES AMPLIFIED PROCEDURES 4.23 CROSSWIND OPERATION The maximum demonstrated crosswind for takeoff and landing for all flap configurations is shown in para 4.2. CAUTION ON RUNWAYS WITH POOLS OF STANDING WATER AND/OR POOR BRAKING ACTION IT MAY NOT BE POSSIBLE TO MAINTAIN THE CENTERLINE AND/OR THE CORRECT ALIGNMENT OF THE AIRCRAFT ON THE RUNWAY IN CONDITIONS OF STRONG CROSSWIND. Page 259 SECTION 4 NORMAL PROCEDURES 4.24 FLIGHT IN ICING CONDITIONS Icing conditions can exist when: The Outside Air Temperature (OAT) on the ground and for takeoff, or Total Air Temperature (TAT) in flight, is 10°C or colder, and visible moisture in any form is present (such as clouds, fog or mist with visibility of one mile or less, rain snow, sleet and ice crystals). Page 260 SECTION 4 NORMAL PROCEDURES During all icing encounters or times with visible ice accretion on any part of the airframe the flaps must not be extended beyond certain limits. These limits eliminate the possibility of tailplane stall which results in an uncontrolled aircraft pitch down moment. Page 261 SECTION 4 NORMAL PROCEDURES The LH side and RH side windshield deice is activated from the overhead DE ICING switch panel by two switches labeled LH WSH and RH WSH respectively, being pushed to ON and the HEAVY/LIGHT switch pushed to either LIGHT or HEAVY depending on the severity of the icing encounter. Page 262 SECTION 4 NORMAL PROCEDURES The emergency procedures, concerning failure of the ice protection systems during flight in icing conditions, are provided in Section 3. On departure from icing conditions the inertial separator (INERT SEP) and the propeller deice system (PROP DE ICE) should be kept OPEN and ON respectively until all visible and unprotected areas of the aircraft are observed as being free of ice. Page 263 SECTION 4 NORMAL PROCEDURES CAWS STATUS System Setting System System Functional Failed BOOTS 1MIN DE ICE BOOTS DE ICE BOOTS GREEN off 3MIN GREEN on with DE ICE AMBER on PROP PROP DE ICE AMBER on INERT OPEN INERT SEP AMBER on LH or RH HEAVY WSHLD HEAT AMBER on... Page 264 SECTION 4 NORMAL PROCEDURES 4.25 SEVERE ICING CONDITIONS Severe icing may result from environmental conditions outside of those for which the airplane is certificated. Flight in freezing rain, freezing drizzle, or mixed icing conditions (supercooled liquid water and ice crystals) may result in ice build-up on protected surfaces exceeding the capability of the ice protection system, or may result in ice forming aft of the protected surfaces. Page 265 SECTION 4 NORMAL PROCEDURES 4.26 PREVENTING OF FROZEN/LOCKED BRAKES (IF CARBON BRAKES INSTALLED) Frozen brakes could occur when fully saturated with water and operated at or below +41° F (+5° C). The following procedures will help to prevent frozen brakes: TAXI BEFORE TAKEOFF •... Page 266 SECTION 4 NORMAL PROCEDURES THIS PAGE INTENTIONALLY LEFT BLANK Report No: 02211 Issued: March 30, 2001 4-52... Page 267 SECTION 5 PERFORMANCE SECTION 5 PERFORMANCE TABLE OF CONTENTS Subject Page GENERAL STANDARD TABLES FIG. 5-1, FAHRENHEIT TO CELSIUS TEMPERATURE CONVERSION FIG. 5-2, INDICATED OAT CORRECTION FIG. 5-3, ISA CONVERSION FIG. 5-4, U.S. GALLONS TO LITERS CONVERSION FIG. 5-5, FEET TO METERS CONVERSION FIG. Page 268 SECTION 5 PERFORMANCE Subject Page TAKEOFF PERFORMANCE FIG. 5-16, STATIC TAKEOFF TORQUE 5-17 FIG. 5-17. ACCELERATE-STOP DISTANCE - FLAPS 30° (STANDARD UNITS) 5-18 FIG. 5-18. ACCELERATE-STOP DISTANCE - FLAPS 30° (METRIC UNITS) 5-19 FIG. 5-19. TAKEOFF GROUND ROLL - FLAPS 30° (STANDARD UNITS) 5-20 FIG. Page 269 SECTION 5 PERFORMANCE Subject Page DESCENT PERFORMANCE FIG. 5-54. TIME TO DESCEND 5-74 FIG. 5-55. FUEL USED TO DESCEND (STANDARD UNITS) 5-75 FIG. 5-56. FUEL USED TO DESCEND (METRIC UNITS) 5-76 FIG. 5-57. DISTANCE TO DESCEND 5-77 FIG. 5-58. POWER-OFF GLIDE TIME (STANDARD UNITS) 5-78 FIG. Page 270 SECTION 5 PERFORMANCE INTENTIONALLY LEFT BLANK Report No: 02211 Issued: March 30, 2001 5-iv Revision 13: Oct 06, 2017... Page 271 SECTION 5 PERFORMANCE GENERAL This section contains all of the required and complementary performance data for airplane operation. PC-12/45 operation with this POH is limited in the performance charts to an aircraft Maximum Takeoff Weight of 9921 lb (4500 kg). Aircraft performance associated with optional equipment and systems which require supplements is provided in Section 9, Supplements. Page 272 SECTION 5 PERFORMANCE Figure 5-1. Fahrenheit to Celsius Conversion Report No: 02211 Issued: March 30, 2001 Revision 3: October 28, 2005... Page 273 SECTION 5 PERFORMANCE Figure 5-2. Indicated OAT Correction Issued: March 30, 2001 Report No: 02211 Revision 3: October 28, 2005... Page 274 SECTION 5 PERFORMANCE Figure 5-3. ISA Conversion Report No: 02211 Issued: March 30, 2001 Revision 3: October 28, 2005... Page 275 SECTION 5 PERFORMANCE Figure 5-4. U.S. Gallons to Liters Conversion Issued: March 30, 2001 Report No: 02211 Revision 3: October 28, 2005... Page 276 SECTION 5 PERFORMANCE Figure 5-5. Feet to Meters Conversion Report No: 02211 Issued: March 30, 2001 Revision 3: October 28, 2005... Page 277 SECTION 5 PERFORMANCE Figure 5-6. Pounds to Kilograms Conversion Issued: March 30, 2001 Report No: 02211 Revision 3: October 28, 2005... Page 278 SECTION 5 PERFORMANCE Figure 5-7. Inches to Millimeters Conversion Report No: 02211 Issued: March 30, 2001 Revision 3: October 28, 2005... Page 279 SECTION 5 PERFORMANCE Figure 5-8. Wind Components Issued: March 30, 2001 Report No: 02211 Revision 3: October 28, 2005... Page 280 SECTION 5 PERFORMANCE Figure 5- 9. Airspeed Calibration - Flaps Retracted Report No: 02211 Issued: March 30, 2001 5-10 Revision 3: October 28, 2005... Page 281 SECTION 5 PERFORMANCE Figure 5-10. Airspeed Calibration - Flaps Extended Issued: March 30, 2001 Report No: 02211 Revision 3: October 28, 2005 5-11... Page 282 SECTION 5 PERFORMANCE Figure 5-11. Altimeter Correction Report No: 02211 Issued: March 30, 2001 5-12 Revision 3: October 28, 2005... Page 283 SECTION 5 PERFORMANCE See FLIGHT IN ICING CONDITIONS para for info on effect of icing Figure 5-12. Stall Speeds KIAS - Flight Idle Power (standard units) Issued: March 30, 2001 Report No: 02211 Revision 3: October 28, 2005 5- 13... Page 284 SECTION 5 PERFORMANCE See FLIGHT IN ICING CONDITIONS para for info on effect of icing Figure 5-13. Stall Speeds KIAS - Flight Idle Power (metric units) Report No: 02211 Issued: March 30, 2001 5-14 Revision 3: October 28, 2005... Page 285 SECTION 5 PERFORMANCE See FLIGHT IN ICING CONDITIONS para for info on effect of icing Figure 5-14. Stall Speeds KCAS - Flight Idle Power (standard units) Issued: March 30, 2001 Report No: 02211 Revision 3: October 28, 2005 5-15... Page 286 SECTION 5 PERFORMANCE See FLIGHT IN ICING CONDITIONS para for info on effect of icing Figure 5-15. Stall Speeds KCAS - Flight Idle Power (metric units) Report No: 02211 Issued: March 30, 2001 5-16 Revision 3: October 28, 2005... Page 287 SECTION 5 PERFORMANCE Figure 5-16. Static Takeoff Torque Issued: March 30, 2001 Report No: 02211 Revision 3: October 28, 2005 5-17... Page 288 SECTION 5 PERFORMANCE See FLIGHT IN ICING CONDITIONS para for info on effect of icing Figure 5-17. Accelerate - Stop Distance - Flaps 30° (standard units) Report No: 02211 Issued: March 30, 2001 5-18 Revision 3: October 28, 2005... Page 289 SECTION 5 PERFORMANCE See FLIGHT IN ICING CONDITIONS para for info on effect of icing Figure 5-18. Accelerate - Stop Distance - Flaps 30° (metric units) Issued: March 30, 2001 Report No: 02211 Revision 3: October 28, 2005 5-19... Page 290 SECTION 5 PERFORMANCE See FLIGHT IN ICING CONDITIONS para for info on effect of icing Figure 5-19. Takeoff Ground Roll - Flaps 30° (standard units) Report No: 02211 Issued: March 30, 2001 5-20 Revision 3: October 28, 2005... Page 291 SECTION 5 PERFORMANCE See FLIGHT IN ICING CONDITIONS para for info on effect of icing Figure 5-20. Takeoff Ground Roll - Flaps 30° (metric units) Issued: March 30, 2001 Report No: 02211 Revision 3: October 28, 2005 5-21... Page 292 SECTION 5 PERFORMANCE See FLIGHT IN ICING CONDITIONS para for info on effect of icing Figure 5-21. Takeoff Total Distance - Flaps 30° (standard units) Report No: 02211 Issued: March 30, 2001 5-22 Revision 3: October 28, 2005... Page 293 SECTION 5 PERFORMANCE See FLIGHT IN ICING CONDITIONS para for info on effect of icing Figure 5-22. Takeoff Total Distance - Flaps 30° (metric units) Issued: March 30, 2001 Report No: 02211 Revision 3: October 28, 2005 5-23... Page 294 SECTION 5 PERFORMANCE See FLIGHT IN ICING CONDITIONS para for info on effect of icing Figure 5-23. Accelerate - Stop Distance - Flaps 15° (standard units) Report No: 02211 Issued: March 30, 2001 5-24 Revision 3: October 28, 2005... Page 295 SECTION 5 PERFORMANCE See FLIGHT IN ICING CONDITIONS para for info on effect of icing Figure 5-24. Accelerate - Stop Distance - Flaps 15° (metric units) Issued: March 30, 2001 Report No: 02211 Revision 3: October 28, 2005 5-25... Page 296 SECTION 5 PERFORMANCE See FLIGHT IN ICING CONDITIONS para for info on effect of icing Figure 5-25. Takeoff Ground Roll - Flaps 15° (standard units) Report No: 02211 Issued: March 30, 2001 5-26 Revision 3: October 28, 2005... Page 297 SECTION 5 PERFORMANCE See FLIGHT IN ICING CONDITIONS para for info on effect of icing Figure 5-26. Takeoff Ground Roll - Flaps 15° (metric units) Issued: March 30, 2001 Report No: 02211 Revision 3: October 28, 2005 5-27... Page 298 SECTION 5 PERFORMANCE See FLIGHT IN ICING CONDITIONS para for info on effect of icing Figure 5-27. Takeoff Total Distance - Flaps 15° (standard units) Report No: 02211 Issued: March 30, 2001 5-28 Revision 3: October 28, 2005... Page 299 SECTION 5 PERFORMANCE See FLIGHT IN ICING CONDITIONS para for info on effect of icing Figure 5-28. Takeoff Total Distance - Flaps 15° (metric units) Issued: March 30, 2001 Report No: 02211 Revision 3: October 28, 2005 5-29... Page 300 SECTION 5 PERFORMANCE Figure 5-29. Maximum Climb Torque Report No: 02211 Issued: March 30, 2001 5-30 Revision 3: October 28, 2005... Page 301 SECTION 5 PERFORMANCE Figure 5-30. Maximum Rate of Climb - Flaps 30° (standard units) Issued: March 30, 2001 Report No: 02211 Revision 3: October 28, 2005 5-31... Page 302 SECTION 5 PERFORMANCE Figure 5-31. Maximum Rate of Climb - Flaps 30° (metric units) Report No: 02211 Issued: March 30, 2001 5-32 Revision 3: October 28, 2005... Page 303 SECTION 5 PERFORMANCE Figure 5-32. Maximum Rate of Climb - Flaps 15° (standard units) Issued: March 30, 2001 Report No: 02211 Revision 3: October 28, 2005 5-33... Page 304 SECTION 5 PERFORMANCE Figure 5- 33. Maximum Rate of Climb - Flaps 15° (metric units) Report No: 02211 Issued: March 30, 2001 5-34 Revision 3: October 28, 2005... Page 305 SECTION 5 PERFORMANCE See FLIGHT IN ICING CONDITIONS para for info on effect of icing Figure 5-34. Maximum Rate of Climb - Flaps 0° (standard units) Issued: March 30, 2001 Report No: 02211 Revision 3: October 28, 2005 5-35... Page 306 SECTION 5 PERFORMANCE See FLIGHT IN ICING CONDITIONS para for info on effect of icing Figure 5-35. Maximum Rate of Climb - Flaps 0° (metric units) Report No: 02211 Issued: March 30, 2001 5-36 Revision 3: October 28, 2005... Page 307 SECTION 5 PERFORMANCE CRUISE CLIMB AIRSPEED SCHEDULE ASSOCIATED CONDITIONS: PROPELLER SPEED 1700 RPM INERTIAL SEPARATOR CLOSED ISA Altitude IOAT ISA Altitude IOAT (°C) (ft) (°C) (°C) (kt) (kt) (°C) (ft) (°C) (°C) (kt) (kt) 5000 5000 10000 10000 15000 15000 20000 20000 25000... Page 308 SECTION 5 PERFORMANCE Figure 5-37. Rate of Climb - Cruise Climb (standard units) Report No: 02211 Issued: March 30, 2001 5-38 Revision 3: October 28, 2005... Page 309 SECTION 5 PERFORMANCE Figure 5-38. Rate of Climb - Cruise Climb (metric units) Issued: March 30, 2001 Report No: 02211 Revision 3: October 28, 2005 5-39... Page 310 SECTION 5 PERFORMANCE Figure 5-39. Time to Climb - Cruise Climb (standard units) Report No: 02211 Issued: March 30, 2001 5-40 Revision 3: October 28, 2005... Page 311 SECTION 5 PERFORMANCE Figure 5-40. Time to Climb - Cruise Climb (metric units) Issued: March 30, 2001 Report No: 02211 Revision 3: October 28, 2005 5-41... Page 312 SECTION 5 PERFORMANCE Figure 5-41. Fuel Used to Climb - Cruise Climb (standard units) Report No: 02211 Issued: March 30, 2001 5-42 Revision 3: October 28, 2005... Page 313 SECTION 5 PERFORMANCE Figure 5-42. Fuel Used to Climb - Cruise Climb (metric units) Issued: March 30, 2001 Report No: 02211 Revision 3: October 28, 2005 5-43... Page 314 SECTION 5 PERFORMANCE Figure 5-43. Distance to Climb - Cruise Climb (standard units) Report No: 02211 Issued: March 30, 2001 5-44 Revision 3: October 28, 2005... Page 315 SECTION 5 PERFORMANCE Figure 5-44. Distance to Climb - Cruise Climb (metric units) Issued: March 30, 2001 Report No: 02211 Revision 3: October 28, 2005 5-45... Page 316 SECTION 5 PERFORMANCE Figure 5-45. Maximum Cruise Power (Sheet 1 of 4) Report No: 02211 Issued: March 30, 2001 5-46 Revision 8: December 01, 2012... Page 317 SECTION 5 PERFORMANCE Figure 5-45. Maximum Cruise Power (Sheet 2 of 4) Issued: March 30, 2001 Report No: 02211 Revision 8: December 01, 2012 5-47... Page 318 SECTION 5 PERFORMANCE Figure 5-45. Maximum Cruise Power (Sheet 3 of 4) Report No: 02211 Issued: March 30, 2001 5-48 Revision 8: December 01, 2012... Page 319 SECTION 5 PERFORMANCE Figure 5-45. Maximum Cruise Power (Sheet 4 of 4) Issued: March 30, 2001 Report No: 02211 Revision 8: December 01, 2012 5-49... Page 320 SECTION 5 PERFORMANCE Figure 5-46. Long Range Cruise (Sheet 1 of 4) Report No: 02211 Issued: March 30, 2001 5-50 Revision 3: October 28, 2005... Page 321 SECTION 5 PERFORMANCE Figure 5-46. Long Range Cruise (Sheet 2 of 4) Issued: March 30, 2001 Report No: 02211 Revision 3: October 28, 2005 5-51... Page 322 SECTION 5 PERFORMANCE Figure 5-46 Long Range Cruise (Sheet 3 of 4) Report No: 02211 Issued: March 30, 2001 5-52 Revision 3: October 28, 2005... Page 323 SECTION 5 PERFORMANCE Figure 5-46 Long Range Cruise (Sheet 4 of 4) Issued: March 30, 2001 Report No: 02211 Revision 3: October 28, 2005 5-53... Page 324 SECTION 5 PERFORMANCE Figure 5-47 Maximum Endurance Cruise (Sheet 1 of 4) Report No: 02211 Issued: March 30, 2001 5-54 Revision 6: Jun 30, 2010... Page 325 SECTION 5 PERFORMANCE Figure 5-47 Maximum Endurance Cruise (Sheet 2 of 4) Issued: March 30, 2001 Report No: 02211 Revision 6: Jun 30, 2010 5-55... Page 326 SECTION 5 PERFORMANCE Figure 5-47 Maximum Endurance Cruise (Sheet 3 of 4) Report No: 02211 Issued: March 30, 2001 5-56 Revision 6: Jun 30, 2010... Page 327 SECTION 5 PERFORMANCE Figure 5-47 Maximum Endurance Cruise (Sheet 4 of 4) Issued: March 30, 2001 Report No: 02211 Revision 6: Jun 30, 2010 5-57... Page 328 SECTION 5 PERFORMANCE Figure 5-48 Specific Air Range - 7000 lb (Sheet 1 of 3) Report No: 02211 Issued: March 30, 2001 5-58 Revision 3: October 28, 2005... Page 329 SECTION 5 PERFORMANCE Figure 5-48 Specific Air Range - 7000 lb (Sheet 2 of 3) Issued: March 30, 2001 Report No: 02211 Revision 3: October 28, 2005 5-59... Page 330 SECTION 5 PERFORMANCE Figure 5-48 Specific Air Range - 7000 lb (Sheet 3 of 3) Report No: 02211 Issued: March 30, 2001 5-60 Revision 3: October 28, 2005... Page 331 SECTION 5 PERFORMANCE Figure 5-49 Specific Air Range - 8000 lb (Sheet 1 of 3) Issued: March 30, 2001 Report No: 02211 Revision 3: October 28, 2005 5-61... Page 332 SECTION 5 PERFORMANCE Figure 5-49 Specific Air Range - 8000 lb (Sheet 2 of 3) Report No: 02211 Issued: March 30, 2001 5-62 Revision 3: October 28, 2005... Page 333 SECTION 5 PERFORMANCE Figure 5-49 Specific Air Range - 8000 lb (Sheet 3 of 3) Issued: March 30, 2001 Report No: 02211 Revision 3: October 28, 2005 5-63... Page 334 SECTION 5 PERFORMANCE Figure 5-50 Specific Air Range - 9000 lb (Sheet 1 of 3) Report No: 02211 Issued: March 30, 2001 5-64 Revision 3: October 28, 2005... Page 335 SECTION 5 PERFORMANCE Figure 5-50 Specific Air Range - 9000 lb (Sheet 2 of 3) Issued: March 30, 2001 Report No: 02211 Revision 3: October 28, 2005 5-65... Page 336 SECTION 5 PERFORMANCE Figure 5-50 Specific Air Range - 9000 lb (Sheet 3 of 3) Report No: 02211 Issued: March 30, 2001 5-66 Revision 3: October 28, 2005... Page 337 SECTION 5 PERFORMANCE Figure 5-51 Specific Air Range - 10000 lb (Sheet 1 of 3) Issued: March 30, 2001 Report No: 02211 Revision 3: October 28, 2005 5-67... Page 338 SECTION 5 PERFORMANCE Figure 5-51 Specific Air Range - 10000 lb (Sheet 2 of 3) Report No: 02211 Issued: March 30, 2001 5-68 Revision 3: October 28, 2005... Page 339 SECTION 5 PERFORMANCE Figure 5-51 Specific Air Range - 10000 lb (Sheet 3 of 3) Issued: March 30, 2001 Report No: 02211 Revision 3: October 28, 2005 5-69... Page 340 SECTION 5 PERFORMANCE Figure 5-52 Specific Air Range - 10400 lb (Sheet 1 of 3) Report No: 02211 Issued: March 30, 2001 5-70 Revision 3: October 28, 2005... Page 341 SECTION 5 PERFORMANCE Issued: March 30, 2001 Report No: 02211 Revision 3: October 28, 2005 5-71... Page 342 SECTION 5 PERFORMANCE Figure 5-52 Specific Air Range - 10400 lb (Sheet 3 of 3) Report No: 02211 Issued: March 30, 2001 5-72 Revision 3: October 28, 2005... Page 343 SECTION 5 PERFORMANCE See FLIGHT IN ICING CONDITIONS para for info on effect of icing Figure 5-53 Holding Time and Fuel Issued: March 30, 2001 Report No: 02211 Revision 3: October 28, 2005 5-73... Page 344 SECTION 5 PERFORMANCE Figure 5-54 Time to Descend Report No: 02211 Issued: March 30, 2001 5-74 Revision 3: October 28, 2005... Page 345 SECTION 5 PERFORMANCE Figure 5-55 Fuel Used to Descend (standard units) Issued: March 30, 2001 Report No: 02211 Revision 3: October 28, 2005 5-75... Page 346 SECTION 5 PERFORMANCE Figure 5-56 Fuel Used to Descend (metric units) Report No: 02211 Issued: March 30, 2001 5-76 Revision 3: October 28, 2005... Page 347 SECTION 5 PERFORMANCE Figure 5-57 Distance to Descend Issued: March 30, 2001 Report No: 02211 Revision 3: October 28, 2005 5-77... Page 348 SECTION 5 PERFORMANCE Figure 5-58 Power-off Glide Time (standard units) Report No: 02211 Issued: March 30, 2001 5-78 Revision 3: October 28, 2005... Page 349 SECTION 5 PERFORMANCE Figure 5-59 Power-off Glide Time (metric units) Issued: March 30, 2001 Report No: 02211 Revision 3: October 28, 2005 5-79... Page 350 SECTION 5 PERFORMANCE Figure 5-60 Power-off Glide Distance Report No: 02211 Issued: March 30, 2001 5-80 Revision 3: October 28, 2005... Page 351 SECTION 5 PERFORMANCE Figure 5-61 Balked Landing Torque Issued: March 30, 2001 Report No: 02211 Revision 3: October 28, 2005 5-81... Page 352 SECTION 5 PERFORMANCE See FLIGHT IN ICING CONDITIONS para for info on effect of icing Figure 5-62 Rate of Climb - Balked Landing (standard units) Report No: 02211 Issued: March 30, 2001 5-82 Revision 3: October 28, 2005... Page 353 SECTION 5 PERFORMANCE See FLIGHT IN ICING CONDITIONS para for info on effect of icing Figure 5-63 Rate of Climb - Balked Landing (metric units) Issued: March 30, 2001 Report No: 02211 Revision 3: October 28, 2005 5-83... Page 354 SECTION 5 PERFORMANCE See FLIGHT IN ICING CONDITIONS para for info on effect of icing Figure 5-64 Landing Total Distance - Flaps 40° (standard units) Report No: 02211 Issued: March 30, 2001 5-84 Revision 3: October 28, 2005... Page 355 SECTION 5 PERFORMANCE See FLIGHT IN ICING CONDITIONS para for info on effect of icing Figure 5-65 Landing Total Distance - Flaps 40° (metric units) Issued: March 30, 2001 Report No: 02211 Revision 3: October 28, 2005 5-85... Page 356 SECTION 5 PERFORMANCE See FLIGHT IN ICING CONDITIONS para for info on effect of icing Figure 5-66 Landing Ground Roll - Flaps 40° (standard units) Report No: 02211 Issued: March 30, 2001 5-86 Revision 3: October 28, 2005... Page 357 SECTION 5 PERFORMANCE See FLIGHT IN ICING CONDITIONS para for info on effect of icing Figure 5-67 Landing Ground Roll - Flaps 40° (metric units) Issued: March 30, 2001 Report No: 02211 Revision 3: October 28, 2005 5-87... Page 358 SECTION 5 PERFORMANCE See FLIGHT IN ICING CONDITIONS para for info on effect of icing Figure 5-68 Landing Total Distance with the use of Reverse Thrust - Flaps 40° (standard units) Report No: 02211 Issued: March 30, 2001 5-88 Revision 3: October 28, 2005... Page 359 SECTION 5 PERFORMANCE See FLIGHT IN ICING CONDITIONS para for info on effect of icing Figure 5-69 Landing Total Distance with the use of Reverse Thrust - Flaps 40° (metric units) Issued: March 30, 2001 Report No: 02211 Revision 3: October 28, 2005 5-89... Page 360 SECTION 5 PERFORMANCE See FLIGHT IN ICING CONDITIONS para for info on effect of icing Figure 5-70 Landing Ground Roll with the use of Reverse Thrust - Flaps 40° (standard units) Report No: 02211 Issued: March 30, 2001 5-90 Revision 3: October 28, 2005... Page 361 SECTION 5 PERFORMANCE See FLIGHT IN ICING CONDITIONS para for info on effect of icing Figure 5-71 Landing Ground Roll with the use of Reverse Thrust - Flaps 40° (metric units) Issued: March 30, 2001 Report No: 02211 Revision 3: October 28, 2005 5-91... Page 362 SECTION 5 PERFORMANCE FLIGHT IN ICING CONDITIONS The following section presents performance information related to the operation in or into known icing conditions. This information was derived analytically from actual wind tunnel tests with natural ice. The following cases are considered: •... Page 363 SECTION 5 PERFORMANCE ENGINE TORQUE When the engine inlet inertial separator is open during flight at altitudes above 5000 ft, the maximum torque available can be reduced by up to 1.2 psi in non icing conditions, and up to 2.1 psi in icing conditions. Page 364 SECTION 5 PERFORMANCE The total takeoff distance is calculated by first computing the total takeoff distance in non-icing conditions from Figure 5-27 (standard units) or Figure 5-28 (metric units) and then correcting that distance for takeoff in or into known icing conditions by using the corrections in Table 2. Table 2 - Icing Corrections to Takeoff Total Distance TABLE A TAKEOFF WEIGHT - KG... Page 365 SECTION 5 PERFORMANCE Analogically, the takeoff ground roll is derived correcting the distances obtained from Figure 5- 25 (standard units) or Figure 5-26 (metric units) by using Table 3. Table 3 - Icing Corrections to Takeoff Ground Roll TABLE A TAKEOFF WEIGHT - KG ALTITUDE 2900... Page 366 SECTION 5 PERFORMANCE Example: Pressure Altitude 6000 ft Outside Air Temperature 18°C Weight 3500 kg Headwind Component 8 kt Uphill Component 1% Takeoff Ground Roll 450 m (from Figure 5-26) Icing Correction (A + B +C) = 28.5% + 1.6% + 0.5% = 30.6% ... Page 367 SECTION 5 PERFORMANCE Table 4 - Icing Corrections to Accelerate Stop Distance TABLE A TAKEOFF WEIGHT - KG ALTITUDE CORRECTION (%) 2900 3300 3700 4100 4500 POWER CHOP SPEED (KIAS) 0 FT 2000 FT 4000 FT 6000 FT 8000 FT 10000 FT 12000 FT 14000 FT... Page 368 SECTION 5 PERFORMANCE MAXIMUM RATE OF CLIMB The use of Flaps 30° is prohibited in or into known icing conditions. After icing encounters, and with visible ice accretion on the airframe, a climb is performed with the flaps retracted and a climb speed based on the schedule below. Page 369 SECTION 5 PERFORMANCE Table 7 - Icing Corrections to Maximum Rate of Climb with Pneumatic De-ice Boots Inoperative RATE OF CLIMB CORRECTION (FEET PER MINUTE) TAKEOFF WEIGHT - KG ALTITUDE - FT 2900 3500 4500 -1510 -1270 -980 5000 -1640 -1370 -1050 10000... Page 370 SECTION 5 PERFORMANCE Table 9 - Icing Corrections to Holding Fuel Flow with Pneumatic De-ice Boots Inoperative FUEL FLOW CORRECTION (%) AIRCRAFT WEIGHT - KG ALTITUDE - FT 2900 - 4500 0 FT 5000 FT 10000 FT 15000 FT 6393 - 9921 ALTITUDE - FT AIRCRAFT WEIGHT - LB BALKED RATE OF CLIMB... Page 371 SECTION 5 PERFORMANCE After failure of the airframe pneumatic boots in icing conditions, a balked landing climb is performed with Flaps 0° and a climb speed of 130 KIAS. The total climb performance is calculated by first computing the Rate of Climb in non-icing conditions from Figure 5-62 (standard units) or Figure 5-63 (metric units) and then correcting the Rate of Climb in or into known icing conditions by using the corrections in the Table 11. Page 372 SECTION 5 PERFORMANCE LANDING PERFORMANCE The flaps must be set to 15° for landing. The use of Flaps 30° or 40° for landing is prohibited. With pneumatic de-ice boots failed; a flaps-up-landing must be performed. For both flap configurations, the landing reference speed must be adjusted to the values indicated by the corresponding correction table. Page 373 SECTION 5 PERFORMANCE Table 13 - Icing Corrections to Landing Total Distance – Flaps 15° - No Reverse Thrust TABLE A LANDING WEIGHT - KG ALTITUDE CORRECTION (%) 2900 3300 3700 4100 4500 (KIAS) 0 FT 2000 FT 4000 FT 6000 FT 8000 FT 10000 FT... Page 374 SECTION 5 PERFORMANCE Table 14- Icing Corrections to Landing Ground Roll – Flaps 15° - No Reverse Thrust TABLE A LANDING WEIGHT - KG ALTITUDE CORRECTION (%) 2900 3300 3700 4100 4500 (KIAS) 0 FT 2000 FT 4000 FT 6000 FT 8000 FT 10000 FT 12000 FT... Page 375 SECTION 5 PERFORMANCE Table 15 - Icing Corrections to Landing Total Distance – Flaps 0° - No Reverse Thrust TABLE A LANDING WEIGHT - KG ALTITUDE CORRECTION (%) 2900 3300 3700 4100 4500 (KIAS) 0 FT +103 +107 2000 FT +101 +105 +109... Page 376 SECTION 5 PERFORMANCE Table 16 - Icing Corrections to Landing Ground Roll – Flaps 0° - No Reverse Thrust TABLE A LANDING WEIGHT - KG ALTITUDE CORRECTION (%) 2900 3300 3700 4100 4500 (KIAS) 0 FT +103 +115 +117 +113 +114 2000 FT +105... Page 377 SECTION 5 PERFORMANCE Table 17 - Icing Corrections to Landing Total Distance – Flaps 15° - With Reverse Thrust TABLE A LANDING WEIGHT - KG ALTITUDE CORRECTION (%) 2900 3300 3700 4100 4500 (KIAS) 0 FT 2000 FT 4000 FT 6000 FT 8000 FT 10000 FT... Page 378 SECTION 5 PERFORMANCE Table 18 - Icing Corrections to Landing Ground Roll – Flaps 15° - With Reverse Thrust TABLE A LANDING WEIGHT - KG ALTITUDE CORRECTION (%) 2900 3300 3700 4100 4500 (KIAS) 0 FT 2000 FT 4000 FT 6000 FT 8000 FT 10000 FT... Page 379 SECTION 5 PERFORMANCE Table 19 - Icing Corrections to Landing Total Distance – Flaps 0° - With Reverse Thrust TABLE A LANDING WEIGHT - KG ALTITUDE CORRECTION (%) 2900 3300 3700 4100 4500 (KIAS) 0 FT 2000 FT 4000 FT +101 6000 FT +100... Page 380 SECTION 5 PERFORMANCE Table 20 - Icing Corrections to Landing Ground Roll – Flaps 0° - With Reverse Thrust TABLE A LANDING WEIGHT - KG ALTITUDE CORRECTION (%) 2900 3300 3700 4100 4500 (KIAS) 0 FT +102 +103 2000 FT +103 +101 4000 FT... Page 381 SECTION 5 PERFORMANCE FLIGHT PLANNING EXAMPLE GENERAL Before performance calculations can begin, it will be necessary to determine the aircraft loading. Refer to Section 6, Weight and Balance to calculate the actual aircraft loading. For this flight planning example, the sample aircraft loading in Section 6, Fig. 6-8, will be used. Aircraft Configuration: Total Trip Distance 765 nm... Page 382 SECTION 5 PERFORMANCE CLIMB NOTE The climb performance chart assumes a no wind condition. The pilot must consider the effect of the winds aloft when computing time, fuel, and distance to climb. The fuel to climb includes the fuel consumed during the takeoff run. Apply the cruise conditions of pressure altitude and temperature (respectively 28000 ft and ISA + 10°C in this case) to the appropriate chart to determine the time, fuel, and distance to climb from sea level to the cruise altitude at the specified takeoff weight (8798 lb in this case). Page 383 SECTION 5 PERFORMANCE Takeoff weight - Usable fuel + Fuel reserve* + Allowance for = Weight at descent beginning of descent 8798 lb - 1650 lb + 300 lb + 100 lb = 7548 lb *As required by operating regulations; here a reserve corresponding to 45 min hold at 5000 ft is assumed. Page 384 SECTION 5 PERFORMANCE Cruise Speed +/- Headwind Component = Ground Speed 250 KTAS -10 kt 240 KTAS Cruise Distance / Ground Speed = Cruise Time 632 nm / 240 kt = 2.63 hr (2hr 38 min) Cruise Time x Fuel Flow = Cruise Fuel 2.63 hr x 325 lb/hr... Page 385 SECTION 5 PERFORMANCE TOTAL FLIGHT TIME The total flight time is the sum of the time to climb, descent, and cruise. Climb Time + Descent Time + Cruise Time = Total Time 23 min + 13 min + 2 hr 38 min 3 hr 14 min TOTAL FUEL REQUIRED The total fuel required is the sum of the fuel consumed during engine start and ground... Page 386 SECTION 5 PERFORMANCE INTENTIONALLY LEFT BLANK Report No: 02211 Issued: March 30, 2001 5-116 Revision 13: Oct 06, 2017... Page 387 SECTION 6 WEIGHT AND BALANCE SECTION 6 WEIGHT AND BALANCE TABLE OF CONTENTS Subject Page GENERAL AIRPLANE WEIGHING PREPARATION WEIGHING PROCEDURE WITH LOAD PLATES WEIGHING PROCEDURE WITH JACKS AND LOAD CELLS 6-6A WEIGHT AND BALANCE RECORD GENERAL LOADING RECOMMENDATIONS 6-11 CARGO 6-11 HAZARDOUS MATERIALS... Page 388 SECTION 6 WEIGHT AND BALANCE THIS PAGE INTENTIONALLY LEFT BLANK Report No: 02211 Issued: March 30, 2001 6-ii... Page 389 SECTION 6 WEIGHT AND BALANCE GENERAL This section contains the information required to determine the Basic Empty Weight and Moment of the aircraft, adjust the B.E.W. & M as equipment is added or removed, and calculate aircraft loading for various flight operations. Sample loading forms are provided. To achieve the performance designed for the aircraft it must be flown with approved weight and center of gravity limits. Page 390 SECTION 6 WEIGHT AND BALANCE AIRPLANE WEIGHING PREPARATION Make sure that all applicable items listed on the airplane equipment list are installed in their proper locations. Clean airplane. Remove dirt, excessive grease, water, and foreign items. Completely defuel the fuel tanks. Use the wing fuel drain ports for the completion of the task. Page 391 SECTION 6 WEIGHT AND BALANCE WEIGHING PROCEDURE WITH LOAD PLATES LEVELING Open the cargo door and place a level across the seat tracks. Adjust the main gear tire pressure until the airplane is laterally level. Place the level along the top of the inboard seat track and adjust the nose tire pressure until the airplane is longitudinally level. Page 392 SECTION 6 WEIGHT AND BALANCE Figure 6-1A. Airplane Weighing Form (Sheet 1 of 3) Report No: 02211 Issued: March 30, 2001 Revision 2: February 28, 2005... Page 393 SECTION 6 WEIGHT AND BALANCE Dimension Average (b) Landing Symbol Gear in (mm) Nose Left Main Right Main (L+R) / 2 NOSE GEAR Dimension (mm) (in) (mm) 111.90 2842 111.82 2840 111.74 2838 111.62 2835 111.54 2833 111.46 2831 111.34 2828 111.27 2826... Page 394 SECTION 6 WEIGHT AND BALANCE MAIN GEAR ARM Dimension (mm) (in) (mm) 254.78 6471 254.46 6463 254.07 6453 253.60 6441 253.04 6427 252.41 6411 251.71 6393 250.88 6372 249.97 6349 248.91 6322 247.73 6292 Dimension (b) is strut extension Calculate the airplane C.G. arm as weighed: C.G. Page 395 SECTION 6 WEIGHT AND BALANCE WEIGHING PROCEDURE WITH JACKS AND LOAD CELLS LEVELING Put the jacks in position below the wing and tail jacking points. The fuselage jacking points must not be used. Refer to the manufacturers instructions for the use of the load cell equipment. Page 396 SECTION 6 WEIGHT AND BALANCE 463.38 in (11770 mm) 216.75 in (5505.5 mm) LEFT MAIN JACKING POINT RIGHT MAIN JACKING POINT TAIL JACKING POINT Scale Scale Position Symbol Reading lb (kg) Tail Jacking Point Left Main Jacking Point Right Main Jacking Point TOTAL AIRCRAFT WEIGHT Figure 6-1B. Page 397 SECTION 6 WEIGHT AND BALANCE Model: Serial No.: Registration No.: Date: Item Weight C.G. Arm Moment lb (kg) in (m) lb-in (mkg) 1. Airplane Weight, C.G. arm, and moment. (As weighed in Figure 6-1) 2. Unusable Fuel 32.9 (14.9) 225.6 (5.73) 7422 (87.38) 3. Page 398 SECTION 6 WEIGHT AND BALANCE WEIGHT AND BALANCE RECORD Figure 6-3. Weight and Balance Record is a log of the modifications that occurred after the airplane was licensed at the factory. Any change to the permanently installed equipment or airplane modifications which effect the airplane Basic Empty Weight or Total Moment must be entered in Figure 6-3. Page 399 SECTION 6 WEIGHT AND BALANCE Figure 6-3. Weight and Balance Record (Sheet 1 of 2) Issued: March 30, 2001 Report No: 02211... Page 400 SECTION 6 WEIGHT AND BALANCE Figure 6-3. Weight and Balance Record (Sheet 2 of 2) Report No: 02211 Issued: March 30, 2001 6-10... Page 401 SECTION 6 WEIGHT AND BALANCE GENERAL LOADING RECOMMENDATIONS The following general loading recommendation is intended as only a guide. Refer to Section 2 for Seating and Cargo Limitations. The pilot in command must refer to the appropriate moment charts, loading form, and the C.G. Envelope to determine that the airplane is properly loaded. Fuel load may be limited by maximum weight. Page 402 SECTION 6 WEIGHT AND BALANCE HAZARDOUS MATERIALS Protection against the damaging effects of leakage of hazardous materials has not been provided in the cargo area. Provisions should be made for protection if carriage of these materials is planned. In addition to the pilot in command, other personnel used for loading and unloading should be properly trained concerning the handling, storage, loading and unloading of hazardous materials if they are to be carried. Page 403 SECTION 6 WEIGHT AND BALANCE Figure 6-4. Loading Areas Issued: March 30, 2001 Report No: 02211 Revision 15: Dec 12, 2019 6-13... Page 404 SECTION 6 WEIGHT AND BALANCE MAXIMUM ALLOWABLE WEIGHT PER SINGLE CONTAINER ( WITHOUT SPECIAL EQUIPMENT ) The maximum allowable weight is based on the package dimensions, vertical c.g. and the number of seat rails used to secure the fore-aft tie-down straps. The flowcharts below can be used to determine whether the weight of a cargo item is acceptable, which Restraint Bars are to be used, and how the cargo is to be loaded. Page 405 20% of Width? The Cargo Tie-Down Is the cargo lateral Configuration Charts are not c.g. within centre valid: contact Pilatus for advice 20% of width? Max 67% 1. Place the cargo in the cabin with the height heavier end to the rear. Page 406 SECTION 6 WEIGHT AND BALANCE MAXIMUM ALLOWABLE WEIGHT PER SINGLE CONTAINER ( WITHOUT SPECIAL EQUIPMENT ) Step Two Choose the correct Restraint Bar(s) based on the cargo width Cargo width between 14 ½” and 15 ¾” (between 370mm and 400mm) Use a single, short Restraint Bar (525.25.12.072 or 525.25.12.171 or... Page 407 SECTION 6 WEIGHT AND BALANCE MAXIMUM ALLOWABLE WEIGHT PER SINGLE CONTAINER ( WITHOUT SPECIAL EQUIPMENT ) Step Three Figure 6-8. Determine Correct Cargo Tie-Down Chart & Curve Issued: March 30, 2001 Report No: 02211 Revision 6: Jun 30, 2010 6-17... Page 408 1.25? The Cargo Tie-Down Configuration Charts are not Use Height/Length ratio to enter the Cargo valid: contact Pilatus for Tie-Down Configuration Chart determined in advice Flowchart Two (Figures 6-11 through 6-14). Determine allowable cargo weight. Page 409 SECTION 6 WEIGHT AND BALANCE MAXIMUM ALLOWABLE WEIGHT PER SINGLE CONTAINER (WITHOUT SPECIAL EQUIPMENT) RESTRAIN CARGO IN CABIN Fit the Restraint Bars and the Load Carrier Assemblies to the aircraft. If there is more than one cargo item, try to place the heavier items forward of the lighter ones. Place cargo in cabin: ensure cargo is firmly against Restraint Bar(s) Restrain cargo with straps attached to the seat rails. Page 410 SECTION 6 WEIGHT AND BALANCE MAXIMUM ALLOWABLE WEIGHT PER SINGLE CONTAINER (WITHOUT SPECIAL EQUIPMENT) EXAMPLE The cargo to be transported is shown below. Looking down, the c.g. is roughly in the centre of the box, but its height is unknown. Weight 200 lb (90kg) 18”... Page 411 SECTION 6 WEIGHT AND BALANCE Step 3: Determine the correct cargo tie-down configuration chart and curve 3a. The front stop is attached to 4 seat rails, but cargo tie down straps can only be fitted to the inner seat tracks. This cargo straddles 2 seat rails. The restraining Bars are angle shaped (not “T”-section) and thus Figure 6-11 is used. Page 412 SECTION 6 WEIGHT AND BALANCE MAXIMUM ALLOWABLE WEIGHT PER SINGLE CONTAINER (WITHOUT SPECIAL EQUIPMENT) Figure 6-11. Cargo straddling two (2) seat rails: Angle Restraining Bar Figure 6-12. Cargo straddling four (4) seat rails: Angle Restraining Bar Report No: 02211 Issued: March 30, 2001 6-22 Revision 6: Jun 30, 2010... Page 413 SECTION 6 WEIGHT AND BALANCE MAXIMUM ALLOWABLE WEIGHT PER SINGLE CONTAINER (WITHOUT SPECIAL EQUIPMENT) Figure 6-13. Cargo straddling two (2) seat rails: “T” Restraining Bar Figure 6-14. Cargo straddling four (4) seat rails: “T” Restraining Bar Issued: March 30, 2001 Report No: 02211 Revision 6: Jun 30, 2010 6-23... Page 414 SECTION 6 WEIGHT AND BALANCE INSTALLATION OF A CARGO NET FORWARD OF CARGO IS RECOMMENDED IF PASSENGERS ARE IN CABIN CARGO NET FRAME 24 FRAME 27 EXTENDABLE FRAME 32 LUGGAGE NET LUGGAGE NET FRAME 34 ANCHOR PLATE STRAP NET FLOOR STRAP EXTENDED ATTACHMENT... Page 415 SECTION 6 WEIGHT AND BALANCE WEIGHT AND BALANCE DETERMINATION FOR FLIGHT This section contains the crew seats, baggage, fuel load moments charts and C of G envelopes in LB-IN and MKG. Refer to the Interior Configurations section for the passenger seat moments. Find the correct Moment Chart for the Interior Code No. Page 416 SECTION 6 WEIGHT AND BALANCE Subtract the weight and moment of the fuel allowance for engine start and ground operations to determine Takeoff Weight and Moment. Divide the moment by the weight to determine the C.G. arm. Nose and main landing gear retraction or extension and flap retraction or extension weight and balance effects need not be considered by the pilot for the weight and balance calculation. Page 417 SECTION 6 WEIGHT AND BALANCE • Calculate the cargo moment as follows: Locate one of the luggage net floor attachment points at frame 34. Measure distance from the attachment point to the center of the cargo i.e.35 in (0,889 m). The fuselage station dimension at the luggage net attachment point is 361.15 in (9,170 m) The arm of the cargo is the fuselage station dimension of the net attachment point minus... Page 418 SECTION 6 WEIGHT AND BALANCE CREW OCCUPANT MOMENTS ( LB - IN ) ARM 160.27 IN* WEIGHT MOMENT WEIGHT MOMENT WEIGHT MOMENT WEIGHT MOMENT lb - in* lb - in* lb - in* lb - in* 8014 16027 24040 32054 9616 17630 25643... Page 419 SECTION 6 WEIGHT AND BALANCE REAR BAGGAGE AREA MOMENTS ( LB - IN ) STANDARD NET AT FRAME 34 - ARM 371.0 IN WEIGHT MOMENT WEIGHT MOMENT WEIGHT MOMENT WEIGHT MOMENT lb - in lb - in lb - in lb - in 3,710 40,810... Page 420 SECTION 6 WEIGHT AND BALANCE REAR BAGGAGE AREA MOMENTS ( LB - IN ) EXTENDABLE NET AT FRAME 32 - ARM 361.0 IN WEIGHT MOMENT WEIGHT MOMENT WEIGHT MOMENT WEIGHT MOMENT lb - in lb - in lb - in lb - in 3610 50543... Page 421 SECTION 6 WEIGHT AND BALANCE FUEL LOAD MOMENTS (LB - IN) WEIGHT MOMENT WEIGHT MOMENT WEIGHT MOMENT WEIGHT MOMENT lb - in lb - in lb - in lb - in 22572 183555 1500 347656 2200 511463 45161 207111 1600 371079 2300 534839... Page 422 SECTION 6 WEIGHT AND BALANCE PC-12/45 EXAMPLE LOADING FORM INTERIOR CODE: STD-9S ITEM WEIGHT ARM AFT OF MOMENT DATUM in (m) lb-in 1. Basic Empty Weight 5613 225.16 (5.719) 1263823 2. Combi Interior Conversion 3. Pilot 160.27 (4.071) 27246 4. Copilot (Right Seat Passenger) 160.27 (4.071) 27246 5. Page 423 SECTION 6 WEIGHT AND BALANCE PC-12/45 LOADING FORM INTERIOR CODE: ITEM WEIGHT ARM AFT OF MOMENT lb (kg) DATUM in (m) lb-in (kg-m) 1. Basic Empty Weight 2. Combi Interior Conversion 3. Pilot 160.27 (4.071) 4. Copilot (Right Seat Passenger) 160.27 (4.071) 5. Page 424 SECTION 6 WEIGHT AND BALANCE Figure 6-18. C. G. Envelope (Sheet 1 of 2) Report No: 02211 Issued: March 30, 2001 6-34 Revision 6: Jun 30, 2010... Page 425 SECTION 6 WEIGHT AND BALANCE Figure 6-18. C. G. Envelope (Sheet 2 of 2) Issued: March 30, 2001 Report No: 02211 Revision 6: Jun 30, 2010 6-35... Page 426 WEIGHT AND BALANCE EQUIPMENT LIST Refer to Pilatus Report No. 02047, Airplane equipment List, attached to the back of this report. The equipment list itemizes the installed equipment included in the Basic Empty Weight indicated in Figure 6-2 of this Airplane Flight Manual. Page 427 Before making any changes to the interior configuration, contact Pilatus to make sure that any modification work or SB’s are identified for embodiment. The placard must then be changed to show the correct code for the new configuration. Page 428 SECTION 6 WEIGHT AND BALANCE THIS PAGE INTENTIONALLY LEFT BLANK Report No: 02211 Issued: March 30, 2001 6-38 Revision 6: Jun 30, 2010... Page 429 SECTION 6 WEIGHT AND BALANCE CORPORATE COMMUTER INTERIOR CODE STD-9S GENERAL The basic Corporate Commuter Interior consisting of 9 standard passenger seats. The section contains the following information: • passenger seat location chart • permitted passenger seat Part Nos. that can be installed •... Page 430 SECTION 6 WEIGHT AND BALANCE Report No: 02211 Issued: March 30, 2001 Interior Code STD-9S. Page 6-01-2 Revision 15: Dec 12, 2019... Page 431 SECTION 6 WEIGHT AND BALANCE CORPORATE COMMUTER INTERIOR CODE STD-9S PERMITTED PASSENGER SEAT PART Nos. THAT CAN BE INSTALLED SEAT TYPE I PC-12 PC-12/45 AND PC-12/47 SEAT FIXED REMOVABLE FIXED REMOVABLE CUSHIONS CUSHIONS CUSHIONS CUSHIONS 1,3,5,7 959.30.01.501 525.22.12.011 959.30.01.511 525.22.12.011 959.30.01.503 959.30.01.513 959.30.01.505... Page 432 SECTION 6 WEIGHT AND BALANCE CORPORATE COMMUTER INTERIOR CODE STD-9S PASSENGER SEATS AND FURNISHINGS WEIGHT AND MOMENT CHART SEAT TYPE I SEAT TYPE II ITEM WEIGHT MOMENT WEIGHT MOMENT LB (KG) LB-IN (KG-M) LB (KG) LB-IN (KG-M) PASS SEAT 1 29.10 (13.2) 6358 (73.25) 31.60 (14.3) Page 433 SECTION 6 WEIGHT AND BALANCE CORPORATE COMMUTER INTERIOR CODE STD-9S PASSENGER SEAT OCCUPANT MOMENT CHART PASSENGER SEAT TYPE I & II OCCUPANT MOMENTS ( LB - IN ) WEIGHT PAX 1 PAX 2 PAX 3 PAX 4 PAX 5 PAX 6 PAX 7 PAX 8 PAX 9... Page 434 SECTION 6 WEIGHT AND BALANCE CORPORATE COMMUTER INTERIOR CODE STD-9S PASSENGER SEAT OCCUPANT MOMENT CHART PASSENGER SEAT TYPE I & II OCCUPANT MOMENTS ( KG - M ) WEIGHT PAX 1 PAX 2 PAX 3 PAX 4 PAX 5 PAX 6 PAX 7 PAX 8 PAX 9... Page 435 SECTION 6 WEIGHT AND BALANCE CORPORATE COMMUTER INTERIOR CODE STD-6S-3B GENERAL This configuration is a variation of the basic Corporate Commuter interior and consists of 6 standard passenger seats and a 3 seat bench. It is the operator's responsibility to check before using this configuration whether they require authorization by their regulatory authority. Page 436 SECTION 6 WEIGHT AND BALANCE CORPORATE COMMUTER INTERIOR CODE STD-6S-3B SEAT LOCATIONS 179.88" 211.17" 244.17" 277.17" FUSELAGE STATION 4.569 m 5.364 m 6.202 m 7.040 m DISTANCE FROM 0" 31.28" 64.28" 97.28" DIVIDER AFT SURFACE 0.795 m 1.633 m 2.471 m PAX 2 PAX 4 PAX 6... Page 437 SECTION 6 WEIGHT AND BALANCE CORPORATE COMMUTER INTERIOR CODE STD-6S-3B PERMITTED PASSENGER SEAT PART Nos. THAT CAN BE INSTALLED PC-12 PC-12/45 SEAT FIXED REMOVABLE FIXED REMOVABLE CUSHIONS CUSHIONS CUSHIONS CUSHIONS 1,3,5 959.30.01.501 525.22.12.011 959.30.01.511 525.22.12.011 959.30.01.503 959.30.01.513 959.30.01.505 959.30.01.515 959.30.01.507 959.30.01.517 959.30.01.509 959.30.01.519... Page 438 SECTION 6 WEIGHT AND BALANCE CORPORATE COMMUTER INTERIOR CODE STD-6S-3B PASSENGER SEATS AND FURNISHINGS WEIGHT AND MOMENT CHART ITEM WEIGHT LB (KG) MOMENT LB-IN (KG-M) PASS SEAT 1 29.10 (13.2) 6299 (72.57) PASS SEAT 2 29.10 (13.2) 6271 (72.25) PASS SEAT 3 29.10 (13.2) 7260 (83.64) PASS SEAT 4... Page 439 SECTION 6 WEIGHT AND BALANCE CORPORATE COMMUTER INTERIOR CODE STD-6S-3B PASSENGER SEAT OCCUPANT MOMENT CHART PASSENGER SEAT OCCUPANT MOMENTS ( LB - IN ) WEIG 213.0 212.0 246.0 245.0 279.0 278.0 321.1 321.1 321.1 10650 10602 12300 12252 13950 13902 16056 16056 16056... Page 440 SECTION 6 WEIGHT AND BALANCE CORPORATE COMMUTER INTERIOR CODE STD-6S-3B PASSENGER SEAT OCCUPANT MOMENT CHART PASSENGER SEAT OCCUPANT MOMENTS ( KG - M ) WEIGHT 5.410 5.386 6.248 6.224 7.087 7.061 8.156 8.156 8.156 135.25 134.64 156.21 155.60 177.16 176.55 203.91 203.91 203.91... Page 441 SECTION 6 WEIGHT AND BALANCE EXECUTIVE INTERIOR CODE EX 6S-2 GENERAL The basic Executive Interior consisting of 6 executive passenger seats. The section contains the following information: • passenger seat location chart • permitted passenger seat Part Nos. that can be installed •... Page 442 SECTION 6 WEIGHT AND BALANCE EXECUTIVE INTERIOR CODE EX-6S-2 SEAT LOCATIONS CD PLAYER TOILET PAX 6 CABINET (OPTIONAL) DISTANCE FROM 0" 10.05" 31.89" 31.30" 147.18" DIVIDER AFT SURFACE 0.255 m 0.810 m 0.795 m 3.738 m 179.95" 190.00" 211.85" 211.19" 327.13"... Page 443 SECTION 6 WEIGHT AND BALANCE EXECUTIVE INTERIOR CODE EX-6S-2 PERMITTED PASSENGER PART Nos. THAT CAN BE INSTALLED PC-12, PC-12/45 AND PC-12/47 SEAT PACIFIC SCIENTIFIC RESTRAINT SCHROTH RESTRAINT 959.30.01.601 959.30.01.613 959.30.01.625 959.30.01.617 959.30.01.627 959.30.01.619 959.30.01.629 959.30.01.621 959.30.01.631 959.30.01.623 959.30.01.815 959.30.01.817 959.30.01.819 959.30.01.821 959.30.01.602 959.30.01.614... Page 444 SECTION 6 WEIGHT AND BALANCE EXECUTIVE INTERIOR CODE EX-6S-2 PASSENGER SEATS AND FURNISHINGS WEIGHT AND MOMENT CHART ITEM WEIGHT LB (KG) MOMENT LB-IN (KG-M) PASS SEAT 1 OR 2 44.1 (20.0) 10143.4 (116.87) PASS SEAT 3 OR 4 48.61 (22.05) 13570.5 (156.35) PASS SEAT 5 48.61 (22.05) Page 445 SECTION 6 WEIGHT AND BALANCE EXECUTIVE INTERIOR CODE EX-6S-2 PASSENGER SEAT OCCUPANT MOMENT CHART PASSENGER SEAT OCCUPANT MOMENTS ( LB - IN ) WEIGHT 234.09 276.12 322.13 334.12 11705 13806 16107 16706 14046 16567 19328 20047 16387 19329 22549 23388 18728 22090 25771... Page 446 SECTION 6 WEIGHT AND BALANCE EXECUTIVE INTERIOR CODE EX-6S-2 PASSENGER SEAT OCCUPANT MOMENT CHART EXECUTIVE INTERIOR CODE EX 6S-2 PASSENGER SEAT OCCUPANT MOMENTS ( KG - M) WEIGHT 5.946 7.014 8.182 8.487 148.65 175.34 204.55 212.16 178.38 210.41 245.46 254.60 208.11 245.47 286.38... Page 447 SECTION 6 WEIGHT AND BALANCE EXECUTIVE INTERIOR CODE EX-8S GENERAL This configuration is a variation of the basic executive interior and consists of 8 executive passenger seats. It is the operator's responsibility to check before using this configuration whether they require authorization by their regulatory authority. The following information is given: ... Page 448 SECTION 6 WEIGHT AND BALANCE EXECUTIVE INTERIOR CODE EX-8S SEAT LOCATIONS CD PLAYER TOILET CABINET (OPTIONAL) DISTANCE FROM 0" 10.05" 31.89" 31.30" DIVIDER AFT SURFACE 0.255 m 0.810 m 0.795 m 179.95" 190.00" 211.85" 211.19" FUSELAGE STATION 4.571 m 4.826 m 5.381 m 5.364 m ARRESTING... Page 449 SECTION 6 WEIGHT AND BALANCE EXECUTIVE INTERIOR CODE EX-8S PERMITTED PASSENGER SEAT PART Nos. THAT CAN BE INSTALLED SEAT NO. PC-12, PC-12/45 AND PC-12/47 959.30.01.613 959.30.01.625 959.30.01.617 959.30.01.627 959.30.01.619 959.30.01.629 959.30.01.621 959.30.01.631 959.30.01.623 959.30.01.815 959.30.01.817 959.30.01.819 959.30.01.821 959.30.01.614 959.30.01.626 959.30.01.618 959.30.01.628 959.30.01.620 959.30.01.630... Page 450 SECTION 6 WEIGHT AND BALANCE EXECUTIVE INTERIOR CODE EX-8S PASSENGER SEATS AND FURNISHINGS WEIGHT AND MOMENT CHART ITEM WEIGHT LB (KG) MOMENT LB-IN (KG-M) PASS SEAT 1 OR 2 44.1 (20.0) 10143.4 (116.87) PASS SEAT 3 OR 4 48.61 (22.05) 13570.5 (156.35) PASS SEAT 5 OR 6 48.61 (22.05) Page 451 SECTION 6 WEIGHT AND BALANCE EXECUTIVE INTERIOR CODE EX-8S PASSENGER SEAT OCCUPANT MOMENT CHART PASSENGER SEAT OCCUPANT MOMENTS ( LB - IN ) WEIGHT 234.09 276.12 308.12 340.12 11705 13806 15406 17006 14046 16567 18487 20407 16387 19329 21569 23809 18728 22090 24650... Page 452 SECTION 6 WEIGHT AND BALANCE EXECUTIVE INTERIOR CODE EX-8S PASSENGER SEAT OCCUPANT MOMENT CHART CREW AND PASSENGER SEAT OCCUPANT MOMENTS ( KG - M ) WEIGHT 5.946 7.014 7.826 8.639 148.65 175.34 195.66 215.98 178.38 210.41 234.79 259.17 208.11 245.47 273.92 302.37 237.84... Page 453 SECTION 6 WEIGHT AND BALANCE EXECUTIVE INTERIOR CODE EX-4S-3B GENERAL This configuration is a variation of the basic Executive interior and consists of 4 executive passenger seats and a 3 seat bench. It is the operator's responsibility to check before using this configuration whether they require authorization by their regulatory authority. Page 454 SECTION 6 WEIGHT AND BALANCE EXECUTIVE INTERIOR CODE EX-4S-3B SEAT LOCATIONS CD PLAYER TOILET CABINET (OPTIONAL) DISTANCE FROM 0" 10.05" 31.89" 31.30" DIVIDER AFT SURFACE 0.255 m 0.810 m 0.795 m 179.95" 190.00" 211.85" 211.19" FUSELAGE STATION 4.571 m 4.826 m 5.381 m 5.364 m ARRESTING... Page 455 SECTION 6 WEIGHT AND BALANCE EXECUTIVE INTERIOR CODE EX-4S-3B PERMITTED PASSENGER SEAT PART Nos. THAT CAN BE INSTALLED PC-12 AND PC-12/45 SEAT PACIFIC SCIENTIFIC RESTRAINT SCHROTH RESTRAINT 959.30.01.601 959.30.01.613 959.30.01.625 959.30.01.617 959.30.01.627 959.30.01.619 959.30.01.629 959.30.01.621 959.30.01.631 959.30.01.623 959.30.01.815 959.30.01.817 959.30.01.819 959.30.01.821 959.30.01.602 959.30.01.614... Page 456 SECTION 6 WEIGHT AND BALANCE 5, 6, 7 959.30.01.801 959.30.01.804 959.30.01.802 959.30.01.805 959.30.01.803 (Bench Seat) NOTES: The extendable baggage net can be used with this interior. A bulkhead plus curtain Part No. 525.24.12.023 can be installed at frame 32. EXECUTIVE INTERIOR CODE EX-4S-3B PASSENGER SEATS AND FURNISHINGS WEIGHT AND MOMENT CHART PC-12 AND PC-12/45 ITEM... Page 457 SECTION 6 WEIGHT AND BALANCE EXECUTIVE INTERIOR CODE EX-4S-3B PASSENGER SEAT OCCUPANT MOMENTS PASSENGER SEAT OCCUPANT MOMENTS ( LB - IN ) WEIGHT 5/6/7 234.09 276.12 320.12 11705 13806 16006 14046 16567 19207 16387 19329 22409 18728 22090 25610 21068 24851 28811 23409... Page 458 SECTION 6 WEIGHT AND BALANCE EXECUTIVE INTERIOR CODE EX-4S-3B PASSENGER SEAT OCCUPANT MOMENTS PASSENGER SEAT OCCUPANT MOMENTS ( KGM ) WEIGHT 5/6/7 5.946 7.014 8.131 148.65 175.34 203.28 178.38 210.41 243.93 208.11 245.47 284.59 237.84 280.54 325.25 267.57 315.61 365.90 297.30 350.68 406.56... Page 459 SECTION 6 WEIGHT AND BALANCE EXECUTIVE INTERIOR CODE EX-6S-STD-2S GENERAL This configuration is a variation of the basic Executive interior and consists of 6 executive passenger seats and 2 standard seats. It is the operator's responsibility to check before using this configuration whether they require authorization by their regulatory authority. Page 460 SECTION 6 WEIGHT AND BALANCE Report No: 02211 Issued: March 30, 2001 Interior Code EX-6S-STD-2S. Page 6-06-2 Revision 15: Dec 12, 2019... Page 461 SECTION 6 WEIGHT AND BALANCE EXECUTIVE INTERIOR CODE EX-6S-STD-2S PERMITTED PASSENGER SEAT PART Nos. THAT CAN BE INSTALLED SEAT NO. PC-12, PC-12/45 AND PC-12/47 959.30.01.613 959.30.01.625 959.30.01.617 959.30.01.627 959.30.01.619 959.30.01.629 959.30.01.621 959.30.01.631 959.30.01.623 959.30.01.815 959.30.01.817 959.30.01.819 959.30.01.821 959.30.01.614 959.30.01.626 959.30.01.618 959.30.01.628 959.30.01.620 959.30.01.630... Page 462 SECTION 6 WEIGHT AND BALANCE PC-12, PC-12/45 AND PC-12/47 SEAT NO. SEAT TYPE I SEAT TYPE II 525.22.12.011 959.30.01.445 959.30.01.447 525.22.12.012 959.30.01.446 959.30.01.448 NOTE: The lap belt extension Part No. 959.30.01.588 or Part No. 959.30.01.590 can be installed on TYPE I seats 7 and 8 only. NOTE: It is not allowed to install TYPE I and II seats behind each other. Page 463 SECTION 6 WEIGHT AND BALANCE EXECUTIVE INTERIOR CODE EX-6S-STD-2S PASSENGER SEAT OCCUPANT MOMENT CHART PASSENGER SEAT TYPE I & II OCCUPANT MOMENTS ( LB - IN ) WEIGHT 234.09 276.12 308.12 341.00 11705 13806 15406 17050 14046 16567 18487 20460 16387 19329 21569... Page 464 SECTION 6 WEIGHT AND BALANCE EXECUTIVE INTERIOR CODE EX-6S-STD-2S PASSENGER SEAT OCCUPANT MOMENT CHART PASSENGER SEAT TYPE I & II OCCUPANT MOMENTS ( KG - M ) WEIGHT 5.946 7.014 7.826 8.661 148.65 175.34 195.66 216.54 178.38 210.41 234.79 259.84 208.11 245.47 273.92... Page 465 SECTION 6 WEIGHT AND BALANCE EXECUTIVE INTERIOR CODE EX-4S-STD-4S GENERAL This configuration is a variation of the basic Executive interior and consists of 4 executive passenger seats and 4 standard seats. It is the operator's responsibility to check before using this configuration whether they require authorization by their regulatory authority. Page 466 SECTION 6 WEIGHT AND BALANCE Report No: 02211 Issued: March 30, 2001 Interior Code EX-4S-STD-4S. Page 6-07-2 Revision 15: Dec 12, 2019... Page 467 SECTION 6 WEIGHT AND BALANCE EXECUTIVE INTERIOR CODE EX-4S-STD-4S PERMITTED PASSENGER SEAT PART Nos. THAT CAN BE INSTALLED SEAT NO. PC-12, PC-12/45 AND PC-12/47 959.30.01.613 959.30.01.625 959.30.01.617 959.30.01.627 959.30.01.619 959.30.01.629 959.30.01.621 959.30.01.631 959.30.01.623 959.30.01.815 959.30.01.817 959.30.01.819 959.30.01.821 959.30.01.614 959.30.01.626 959.30.01.618 959.30.01.628 959.30.01.620 959.30.01.630... Page 468 SECTION 6 WEIGHT AND BALANCE PC-12, PC-12/45 AND PC-12/47 SEAT NO. SEAT TYPE I SEAT TYPE II 5, 7 525.22.12.011 959.30.01.445 959.30.01.447 6, 8 525.22.12.012 959.30.01.446 959.30.01.448 NOTE: The lap belt extension Part No. 959.30.01.588 and Part No. 959.30.01.590 can be installed on TYPE I seats 5 through 8 only. NOTE: It is not allowed to install TYPE I and II seats behind each other. Page 469 SECTION 6 WEIGHT AND BALANCE EXECUTIVE INTERIOR CODE EX-4S-STD-4S PASSENGER SEATS AND FURNISHINGS WEIGHT AND MOMENT CHART PC-12, PC-12/45 AND PC-12/47 ITEM WEIGHT MOMENT LB (KG) LB-IN (KG-M) PASS SEAT 1 OR 2 44.1 (20.0) 10143.4 (116.87) PASS SEAT 3 OR 4 48.61 (22.05) 13570.5 (156.35) SEAT TYPE I... Page 470 SECTION 6 WEIGHT AND BALANCE EXECUTIVE INTERIOR CODE EX-4S-STD-4S PASSENGER SEAT OCCUPANT MOMENT CHART PASSENGER SEAT TYPE I & II OCCUPANT MOMENTS ( LB - IN ) WEIGHT 234.09 276.12 310.00 343.00 11705 13806 15500 17150 14046 16567 18600 20580 16387 19329 21700... Page 471 SECTION 6 WEIGHT AND BALANCE EXECUTIVE INTERIOR CODE EX-4S-STD-4S PASSENGER SEAT OCCUPANT MOMENT CHART PASSENGER SEAT TYPE I & II OCCUPANT MOMENTS ( KG - M ) WEIGHT 5.9460 7.0135 7.8740 8. 7122 148.65 175.34 196.85 217.81 178.38 210.41 236.22 261.37 208.11 245.47... Page 472 SECTION 6 WEIGHT AND BALANCE INTENTIONALLY LEFT BLANK Report No: 02211 Issued: March 30, 2001 Interior Code EX-4S-STD-4S. Page 6-07-8 Revision 15: Dec 12, 2019... Page 473 VOLUME 2 PILOT'S OPERATING HANDBOOK EASA APPROVED AIRPLANE FLIGHT MANUAL PC-12 SERIES MSN 321, 401-544 AND 546-888 Report No. 02211 Manufacturer's Serial No. - ____________________ Registration No. - ___________________________ EASA Type Certificate No: EASA.A.089 FAA Type Certificate No: A78EU PILATUS AIRCRAFT LTD. Page 475 SECTION 7-1 AIRPLANE AND SYSTEMS DESCRIPTION GENERAL Section 7 of this Pilot's Operating Handbook contains information related to the detailed description and operation of the airplane and its systems. SECTION CONTENTS GENERAL AIRFRAME FLIGHT CONTROLS LANDING GEAR BAGGAGE COMPARTMENT CARGO TIE-DOWNS SEATS / RESTRAINT SYSTEMS DOORS, WINDOWS, AND EXITS CONTROL LOCKS... Page 476 SECTION 7-1 AIRPLANE AND SYSTEMS DESCRIPTION SECTION CONTENTS 7-20 CABIN PRESSURIZATION CONTROL SYSTEM 7-21 OXYGEN SYSTEM 7-22 COCKPIT ARRANGEMENT 7-23 CENTRAL ADVISORY AND WARNING SYSTEM (CAWS) 7-24 PITOT STATIC SYSTEMS 7-25 STALL WARNING / STICK PUSHER SYSTEM 7-26 PNEUMATIC WING DEICE SYSTEM 7-27 COMFORT FEATURES 7-28... Page 477 SECTION 7-2 AIRPLANE AND SYSTEMS DESCRIPTION AIRFRAME GENERAL The airplane is a low wing, T-tail, single engine, retractable landing gear type designed to transport passengers, cargo, or various combinations of both passengers and cargo. Construction is conventional semimonocoque, primarily incorporating aluminum alloy, but composite structures are used in certain areas. Page 478 SECTION 7-2 AIRPLANE AND SYSTEMS DESCRIPTION EMPENNAGE The empennage is a T-tail design with the horizontal stabilizer mounted on top of the vertical stabilizer. The aft fuselage is attached to the cabin at the aft pressure bulkhead. The vertical and horizontal stabilizer assemblies are conventional aluminum construction. Page 479 SECTION 7-3 AIRPLANE AND SYSTEMS DESCRIPTION FLIGHT CONTROLS GENERAL The flight control system is conventional using push-pull rods and carbon steel cables. Electric trim systems are provided for the aileron, rudder, and elevator. All trim systems can be disconnected in the event of a runaway condition. An aileron/rudder interconnect system is installed to improve lateral stability and turn coordination. Page 480 SECTION 7-3 AIRPLANE AND SYSTEMS DESCRIPTION TRIM The aileron, horizontal stabilizer and rudder trim are electrically operated. Aileron and horizontal stabilizer trim operation are controlled by a switch on the outboard horn of each control wheel while rudder trim operation is controlled by a switch located on the Engine Power Control Lever. Page 481 SECTION 7-3 AIRPLANE AND SYSTEMS DESCRIPTION A rotation sensor is installed on each of the outer flap screw actuators. These sense the rotation of the flexible shafts and give signals to the FCWU. The FCWU monitors these signals for asymmetrical flexible shaft rotation of more than 20 rotations (caused by a broken inner flap drive shaft). Page 482 SECTION 7-3 AIRPLANE AND SYSTEMS DESCRIPTION A FLAP GROUND RESET switch is installed on the maintenance test panel (right sidewall behind the co-pilot seat). The FLAP GROUND RESET switch is only operational on the ground for maintenance purposes. INDICATION / WARNING A three-axis trim position indicator is located on the center console. Page 483 SECTION 7-3 AIRPLANE AND SYSTEMS DESCRIPTION Fig 7-3-1. Flap System Issued: March 30, 2001 Report No: 02211 Revision 13: Oct 06, 2017 7-3-5... Page 484 SECTION 7-3 AIRPLANE AND SYSTEMS DESCRIPTION INTENTIONALLY LEFT BLANK Report No: 02211 Issued: March 30, 2001 7-3-6 Revision 13: Oct 06, 2017... Page 485 SECTION 7-4 AIRPLANE AND SYSTEMS DESCRIPTION LANDING GEAR GENERAL Refer to Figure 7-4-1, Landing Gear System, for system operation. The landing gear is a conventional tricycle configuration that is extended and retracted using hydraulic pressure produced by an electrically powered hydraulic pump. Landing gear extension and retraction is the only function of the hydraulic system and landing gear operation is completely automatic upon pilot gear selection. Page 486 SECTION 7-4 AIRPLANE AND SYSTEMS DESCRIPTION Nose wheel steering is accomplished using the rudder pedals which are mechanically connected to the nosewheel. Additional nosewheel steering is done through differential braking. Use of rudder pedal only will turn the nosewheel ± 12 degrees from center while differential braking will turn the nosewheel ±... Page 487 SECTION 7-4 AIRPLANE AND SYSTEMS DESCRIPTION HYDRAULIC SYSTEM DESCRIPTION The main hydraulic system comprises a power pack located in the hydraulic service bay in the left wing root behind the main spar, a nitrogen charged accumulator in the same location, a landing gear selector valve mounted in the cockpit mechanically linked to the pilots control panel selector handle by a push/pull rod and three actuators, one for each landing gear leg. Page 488 SECTION 7-4 AIRPLANE AND SYSTEMS DESCRIPTION Cockpit controls consist of the following - A landing gear selector handle is located on the pilot's lower right panel and facilitates extension or retraction of the landing gear. It acts directly, via a rod, on the landing gear selector valve. Page 489 SECTION 7-4 AIRPLANE AND SYSTEMS DESCRIPTION Figure 7-4-1. Landing Gear System (Sheet 1 of 4) Issued: March 30, 2001 Report No: 02211 Revision 13: Oct 06, 2017 7-4-5... Page 490 SECTION 7-4 AIRPLANE AND SYSTEMS DESCRIPTION Figure 7-4-1. Landing Gear System (Sheet 2 of 4) Report No: 02211 Issued: March 30, 2001 7-4-6 Revision 8: December 01, 2012... Page 491 SECTION 7-4 AIRPLANE AND SYSTEMS DESCRIPTION Figure 7-4-1. Landing Gear System (Sheet 3 of 4) Issued: March 30, 2001 Report No: 02211 Revision 13: Oct 06, 2017 7-4-7... Page 492 SECTION 7-4 AIRPLANE AND SYSTEMS DESCRIPTION Figure 7-4-1. Landing Gear System (Sheet 4 of 4) Report No: 02211 Issued: March 30, 2001 7-4-8 Revision 13: Oct 06, 2017... Page 493 SECTION 7-4 AIRPLANE AND SYSTEMS DESCRIPTION INDICATION/WARNING Extended position indication is provided by micro switches internal to the main landing gear actuators and a proximity switch on the nose landing gear drag link. Retraction position indication is provided by proximity switches on the landing gear doors. Landing gear position is indicated in the cockpit by three dual-indication lights (one for each leg), located to the left of the landing gear selector handle. Page 494 SECTION 7-4 AIRPLANE AND SYSTEMS DESCRIPTION EMERGENCY EXTENSION SYSTEM The emergency extension system is required to ensure that the landing gear can be extended and locked after a failure of the main system. This is accomplished by releasing the hydraulic pressure in the actuators by selecting landing gear DOWN via the selector handle. Page 495 SECTION 7-4 AIRPLANE AND SYSTEMS DESCRIPTION AIR / GROUND SYSTEM The airplane is equipped with independent weight on wheel detectors, one on each main landing gear. Each weight on wheel signal is generated by a proximity switch. Each proximity switch controls a relay that provides the AIR/GND signal to the different systems. Page 496 SECTION 7-4 AIRPLANE AND SYSTEMS DESCRIPTION Failure of a weight on wheel signal, while the airplane is in the air (GND signal provided), will have the following effects on the systems: LH and RH Stick Pusher Stick Pusher is inoperative. Stick Shaker and aural stall Computers warning still operative from the other computer Cabin Pressurization... Page 497 SECTION 7-4 AIRPLANE AND SYSTEMS DESCRIPTION BRAKES Refer to Figure 7-4-2, Brake System, for system operation. Aircraft braking is provided by two brake assemblies, one bolted to each main landing gear axle. The brakes are controlled by toe pedals attached to each rudder pedal assembly. Page 498 SECTION 7-4 AIRPLANE AND SYSTEMS DESCRIPTION WHEELS AND TIRES The wheels are split-hub type, the main wheels have three fusible plugs which melt when there is too much heat from the brakes. Tubeless tires are installed on the wheels and each wheel has a tire inflation valve and an overinflation safety plug. The main wheels have fairings on the outer hubs which make the wheels aerodynamically smooth when the landing gear is retracted. Page 499 SECTION 7-4 AIRPLANE AND SYSTEMS DESCRIPTION Figure 7-4-2. Brake System Issued: March 30, 2001 Report No: 02211 Revision 13: Oct 06, 2017 7-4-15... Page 500 SECTION 7-4 AIRPLANE AND SYSTEMS DESCRIPTION INTENTIONALLY BLANK Report No: 02211 Issued: March 30, 2001 7-4-16 Revision 13: Oct 06, 2017... Page 501 SECTION 7-5 AIRPLANE AND SYSTEMS DESCRIPTION BAGGAGE COMPARTMENT A baggage compartment is provided at the rear of the cabin and is accessible during flight. A standard luggage net is secured at twelve attachment points to secure the baggage. An extendible baggage net can be installed instead of the standard net, to secure baggage in front of and in the baggage compartment. Page 502 SECTION 7-5 AIRPLANE AND SYSTEMS DESCRIPTION INTENTIONALLY BLANK Report No: 02211 Issued: March 30, 2001 7-5-2 Revision 7: Jul 20, 2011... Page 503 SECTION 7-6 AIRPLANE AND SYSTEMS DESCRIPTION CARGO TIE-DOWNS Tie-down anchor points fit into the seat rails and lock into place by an over-center lever. Tie-down straps can be secured to these anchor points. Issued: March 30, 2001 Report No: 02211 Revision 7: Jul 20, 2011 7-6-1... Page 504 SECTION 7-6 AIRPLANE AND SYSTEMS DESCRIPTION INTENTIONALLY BLANK Report No: 02211 Issued: March 30, 2001 7-6-2 Revision 7: Jul 20, 2011... Page 505 SECTION 7-7 AIRPLANE AND SYSTEMS DESCRIPTION SEATS/RESTRAINT SYSTEMS SEATS For aircraft MSN 321, 401-544 and 546-660 Pre SB 25-050: The crew seats are adjustable both fore and aft and vertically. The fore and aft adjustment handle is under the front and the up and down adjustment handle is at the rear of the seat. All armrests can be moved upwards. Page 506 SECTION 7-7 AIRPLANE AND SYSTEMS DESCRIPTION Figure 7-7-1. Crew Seat Controls (MSN 321, 401-544 and 546-660 - Pre SB 25-050) (Sheet 1 of 2) Report No: 02211 Issued: March 30, 2001 7-7-2 Revision 16: December 18, 2020... Page 507 SECTION 7-7 AIRPLANE AND SYSTEMS DESCRIPTION Figure 7-7-1. Crew Seat Controls (MSN 321, 401-544 and 546-660 - Post SB 25-050 and MSN 661 and up) (Sheet 2 of 2) Issued: March 30, 2001 Report No: 02211 Revision 16: December 18, 2020 7-7-3... Page 508 SECTION 7-7 AIRPLANE AND SYSTEMS DESCRIPTION INTENTIONALLY LEFT BLANK Report No: 02211 Issued: March 30, 2001 7-7-4 Revision 13: Oct 06, 2017... Page 509 SECTION 7-8 AIRPLANE AND SYSTEMS DESCRIPTION DOORS, WINDOWS, AND EXITS PASSENGER DOOR The passenger door is located in the front left fuselage, immediately aft of the cockpit, and is 4 ft 5 in (1.35 m) high by 2 ft 0 in (0.61 m) wide. The door can be opened or closed from either side and is secured by six locking pins. Page 510 SECTION 7-8 AIRPLANE AND SYSTEMS DESCRIPTION The CAWS warning CAR DOOR annunciator will illuminate and a voice callout “Warning Cargo Door” will be heard when the door is not properly closed and locked. WINDOWS A two-piece windshield and two side windows provide cockpit visibility. Both pilot and copilot windshields are laminated twin-layer mineral glass with an embedded polyvinyl butyrol (PVB) layer. Page 511 SECTION 7-8 AIRPLANE AND SYSTEMS DESCRIPTION Figure 7-8-1. Emergency Exit Issued: March 30, 2001 Report No: 02211 Revision 7: Jul 20, 2011 7-8-3... Page 512 SECTION 7-8 AIRPLANE AND SYSTEMS DESCRIPTION INTENTIONALLY BLANK Report No: 02211 Issued: March 30, 2001 7-8-4 Revision 7: Jul 20, 2011... Page 513 SECTION 7-9 AIRPLANE AND SYSTEMS DESCRIPTION CONTROL LOCKS The elevator and ailerons can be secured by placing a control lock through the hole in the collar and control column when the elevator is full down and the ailerons are neutral. For flight the control lock is stowed in a stowage point located on the cockpit left sidewall to the rear of the pilots seat. Page 514 SECTION 7-9 AIRPLANE AND SYSTEMS DESCRIPTION INTENTIONALLY BLANK Report No: 02211 Issued: March 30, 2001 7-9-2 Revision 7: Jul 20, 2011... Page 515 SECTION 7-10 AIRPLANE AND SYSTEMS DESCRIPTION ENGINE DESCRIPTION AND OPERATION Refer to Figure 7-10-1, PT6A-67B Engine, for engine configuration. This airplane is powered by the Pratt & Whitney PT6A-67B, which is a light weight, reverse flow, free turbine engine. In addition to the gas generator section, the PT6A-67B incorporates a power section with the power turbine and propeller reduction gearbox, an integral oil system, and an accessory gearbox for mountings for various accessories. Page 516 SECTION 7-10 AIRPLANE AND SYSTEMS DESCRIPTION Figure 7-10-1. PT6A-67B Engine Report No: 02211 Issued: March 30, 2001 7-10-2 Revision 7: Jul 20, 2011... Page 517 SECTION 7-10 AIRPLANE AND SYSTEMS DESCRIPTION AIR INDUCTION The air induction system is integrated into the front and rear lower cowlings and comprises of an air inlet and inlet duct, a plenum, and an inertial separator. The air inlet consists of a crescent shaped metal leading edge through which hot exhaust is passed to prevent ice accumulation. Page 518 SECTION 7-10 AIRPLANE AND SYSTEMS DESCRIPTION Figure 7-10-2. Inertial Separator Report No: 02211 Issued: March 30, 2001 7-10-4 Revision 7: Jul 20, 2011... Page 519 SECTION 7-10 AIRPLANE AND SYSTEMS DESCRIPTION CONTROLS Refer to Figure 7-10-3, Engine and Propeller Controls / Indication. Engine power is controlled by POWER CONTROL, CONDITION, and MANUAL OVERRIDE levers located on the center console. POWER CONTROL LEVER The POWER CONTROL lever (PCL) selects the required engine power (N g) and in certain conditions it directly controls the propeller pitch. Page 520 SECTION 7-10 AIRPLANE AND SYSTEMS DESCRIPTION Figure 7-10-3. Engine and Propeller Controls / Indications Report No: 02211 Issued: March 30, 2001 7-10-6 Revision 7: Jul 20, 2011... Page 521 SECTION 7-10 AIRPLANE AND SYSTEMS DESCRIPTION MANUAL OVERRIDE LEVER Description The MANUAL OVERRIDE lever (MOR) is located on the center console to the left of PCL. The MOR controls the engine power in case of a pneumatic failure of the engine fuel control or in case of a PCL system failure. Page 522 SECTION 7-10 AIRPLANE AND SYSTEMS DESCRIPTION WARNING PCL OPERATION AFT OF THE IDLE DETENT IS NOT PERMITTED WHEN ENGINE OPERATION CONTROLLED BY THE MANUAL OVERRIDE LEVER. CAUTION THE MOR LEVER MUST BE IN THE OFF POSITION PRIOR TO ENGINE START TO PREVENT A HOT START. Page 523 SECTION 7-10 AIRPLANE AND SYSTEMS DESCRIPTION CONDITION LEVER The Condition Lever has three positions and is used to select the gas generator idle speed, shut down the engine, and feather the propeller. The GROUND IDLE position (G.I.) is for ground operation only. This setting ensures that the propeller speed remains above the prohibited range (350 rpm to 950 rpm) for ambient conditions up to a temperature of approximately 45°C. Page 524 SECTION 7-10 AIRPLANE AND SYSTEMS DESCRIPTION ENGINE FUEL Refer to Figure 7-10-4, Engine Fuel System, for system configuration. For airplane fuel storage and distribution, refer to Fuel system, this section. The engine fuel system consists of an oil to fuel heat exchanger, a high pressure engine driven fuel pump, a fuel control unit, a fuel flow transducer, a fuel flow divider and dump valve, and the fuel nozzles. Page 525 SECTION 7-10 AIRPLANE AND SYSTEMS DESCRIPTION Refer to Figure 7-10-5, Engine Oil System, for system configuration. The engine oil system consists of pressure, scavenge, and breather systems with the oil tank being an integral part of the engine compressor inlet case. Oil is supplied to the engine bearings, reduction gears, accessory drives, torquemeter, and propeller governor. Page 526 SECTION 7-10 AIRPLANE AND SYSTEMS DESCRIPTION OIL DEBRIS MONITORING (ODM) (MSN 534-999 PRE SB 79-006) A sensor module is installed in the oil pipeline to the oil cooler. The sensor module detects metal particles above a certain size that pass through it. A signal conditioner connected to the sensor converts a detected metal particle into a pulse signal. Page 527 SECTION 7-10 AIRPLANE AND SYSTEMS DESCRIPTION Figure 7-10-5. Engine Oil System Issued: March 30, 2001 Report No: 02211 Revision 7: Jul 20, 2011 7-10-13... Page 528 SECTION 7-10 AIRPLANE AND SYSTEMS DESCRIPTION INDICATION/WARNING Engine indication for normal operation is displayed on the Engine Instrument System (EIS). Generator 1 and generator 2 voltages and currents are displayed on two of the EIS displays (GEN 1 and GEN 2). Continuous monitoring of the voltages and currents for close to limit cautions and out of limit warnings is provided by the EIS. Page 529 SECTION 7-10 AIRPLANE AND SYSTEMS DESCRIPTION STARTING Starting is provided by a combination starter/generator unit. Starter function is controlled by the STARTER switch on the pilot's overhead panel. When the STARTER switch is pressed to ON for more than 2 seconds, the green ON annunciator in the switch is illuminated, and the EIS energizes the Starting Control Relay which through the Starter Relay energizes the starter. Page 530 SECTION 7-10 AIRPLANE AND SYSTEMS DESCRIPTION FIRE DETECTION The system is composed of a sensor element and a responder. The sensor is a stainless steel capillary tube filled with helium and containing a central hydrogen- charged core which readily releases hydrogen gas when heated above a temperature threshold. Page 531 SECTION 7-11 AIRPLANE AND SYSTEMS DESCRIPTION ENGINE INSTRUMENT SYSTEM (EIS) GENERAL The Engine Instrument System (EIS) is a computer controlled system which receives input from the sensors. It displays engine and other system information and provides warnings when certain parameter limits are exceeded (Figure 7-11-1). The EIS has two independent Acquisition and Processing Units (APU) and a Display Unit (DU) combined into a single unit. Page 532 SECTION 7-11 AIRPLANE AND SYSTEMS DESCRIPTION Within the EIS display is a fuel totalizer function. The digital display indicates total fuel remaining, fuel flow, fuel used and endurance. The fuel QTY indicates the total computed fuel quantity in the wings. The fuel USED indicates fuel consumed based on fuel flow vs time (FL/H) of engine operation. Page 533 SECTION 7-11 AIRPLANE AND SYSTEMS DESCRIPTION OPERATION When electrical power is supplied to the EIS, the acquisition and display unit does a self test. If the self test is satisfactory the displays will come on. The system test is activated by momentarily pressing the test switch on the EIS panel. The EIS test progressively activates all of the LCD display segments, illuminates the caution and warning lights, and checks the APUs and power supplies for serviceability. Page 534 SECTION 7-11 AIRPLANE AND SYSTEMS DESCRIPTION ENGINE CONDITION MONITORING SYSTEM General The Engine Condition Monitoring system (ECMS) monitors the health of the engine and detects engine deterioration, thus enabling planned corrective and /or preventative maintenance actions. The ECMS periodically records the engine data and corrects the reading to correspond to ambient conditions (air data). Page 535 SECTION 7-11 AIRPLANE AND SYSTEMS DESCRIPTION Engine Run recording Engine run condition is when the fuel flow is more 50 lbs/h or the Np is more than 1000 RPM. The ECMS stores the engine start and stop times and all maximum parameters values. Page 536 SECTION 7-11 AIRPLANE AND SYSTEMS DESCRIPTION OIL DEBRIS MONITORING (ODM) SYSTEM (MSN 534-999 PRE SB 79-006) General The ODM system counts metal particles in the engine oil flow. It makes the CHIP caution on the EIS come on if the number of particles within a fixed time exceeds predefined limits. Page 537 SECTION 7-11 AIRPLANE AND SYSTEMS DESCRIPTION CAUTIONS AND WARNINGS PARAMETER CAUTION RANGE WARNING RANGE (Digits blink 40/min) (Digits blink 80/min) Torque 44.4 to 61.0 psi 44.4 to 61 psi (after 20 sec. delay). above 61 psi 800 to 870° C 800 to 870°... Page 538 SECTION 7-11 AIRPLANE AND SYSTEMS DESCRIPTION CAUTIONS AND WARNINGS (CONT'D) PARAMETER CAUTION RANGE WARNING RANGE (Digits blink 40/min) (Digits blink 80/min) below 950 (on ground, after 5 sec. if unfeather delay) (Note 1 & 2) below 1640 (after 5 sec. delay) above 1760 to 1870 1760 to 1870 rpm (after 20... Page 539 SECTION 7-11 AIRPLANE AND SYSTEMS DESCRIPTION Figure 7-11-1. Engine Instrument System (Sheet 1 of 2) Issued: March 30, 2001 Report No: 02211 Revision 7: Jul 20, 2011 7-11-9... Page 540 SECTION 7-11 AIRPLANE AND SYSTEMS DESCRIPTION Figure 7-11-1. Engine Instrument System (Sheet 2 of 2) Report No: 02211 Issued: March 30, 2001 7-11-10 Revision 7: Jul 20, 2011... Page 541 SECTION 7-11 AIRPLANE AND SYSTEMS DESCRIPTION EIS FAILURE CODES To assist with preliminary troubleshooting, help maintenance personnel and avoid unnecessary EIS replacements, if the following fault codes appear flight crew may cycle EIS power and verify if the fault code remains. One EIS power cycle consists of: EIS 1 circuit breaker OPEN... Page 542 SECTION 7-11 AIRPLANE AND SYSTEMS DESCRIPTION INTENTIONALLY LEFT BLANK Report No: 02211 Issued: March 30, 2001 7-11-12 Revision 7: Jul 20, 2011... Page 543 SECTION 7-12 AIRPLANE AND SYSTEMS DESCRIPTION PROPELLER GENERAL Refer to Figure 7-10-3, Engine Controls/ Indications and Figure 7-12-1, Propeller Pitch Mechanism. The airplane is equipped with a Hartzell 105 in (2.67 m), four blade, variable pitch, full feathering propeller which is driven by the engine power turbine through a reduction gearing. Page 544 SECTION 7-12 AIRPLANE AND SYSTEMS DESCRIPTION Figure 7-12-1. Propeller Pitch Mechanism Report No: 02211 Issued: March 30, 2001 7-12-2 Revision 7: Jul 20, 2011... Page 545 SECTION 7-12 AIRPLANE AND SYSTEMS DESCRIPTION OPERATION Refer to Figure 7-12-1, Propeller Pitch Mechanism. In normal operation the propeller unfeathers after the condition lever is moved to Ground Idle and the engine is accelerating to idle Ng during engine start. On the ground at idle power the propeller rotates at approximately 1060 rpm. Page 546 SECTION 7-12 AIRPLANE AND SYSTEMS DESCRIPTION The above cycles are repeated until the DE ICING PROP switch is set to OFF. OAT sensing is by a sensor mounted under the left hand wing. This sensor is termed the controller and presents the principal control signal. A second sensor is mounted in an identical position under the right hand wing. Page 547 SECTION 7-13 AIRPLANE AND SYSTEMS DESCRIPTION FUEL GENERAL Refer to Figure 7-13-1, Fuel System for system schematics and equipment layout. Fuel is contained in two integral wing tanks and is supplied to the engine in excess of that required for all ground and flight operations. Each wing tank contains drain valves. The transfer and delivery of fuel is achieved using a motive flow jet pump system and two engine driven pumps (low pressure pump and the FCU high pressure pump). Page 548 SECTION 7-13 AIRPLANE AND SYSTEMS DESCRIPTION OPERATION During normal operation with the engine running, fuel is transferred from the wings to the engine by a motive flow system. Fuel under pressure from the low pressure engine driven pump is returned to the wings to provide motive flow through the transfer ejector pump and the delivery ejector pump. Page 549 SECTION 7-13 AIRPLANE AND SYSTEMS DESCRIPTION Normal system operation is indicated by the left and right fuel quantity gauges remaining within 2 LCD segments of each other. (When a difference of 3 LCD segments is observed, the fuel boost pump for the tank with the higher quantity should be turned ON until the quantities are even. Page 550 SECTION 7-13 AIRPLANE AND SYSTEMS DESCRIPTION Figure 7-13-1. Fuel System (Sheet 1 of 4) Report No: 02211 Issued: March 30, 2001 7-13-4 Revision 15: Dec 12, 2019... Page 551 SECTION 7-13 AIRPLANE AND SYSTEMS DESCRIPTION Figure 7-13-1. Fuel System (Sheet 2 of 4) Issued: March 30, 2001 Report No: 02211 Revision 7: Jul 20, 2011 7-13-5... Page 552 SECTION 7-13 AIRPLANE AND SYSTEMS DESCRIPTION Figure 7-13-1. Fuel System (Sheet 3 of 4) Report No: 02211 Issued: March 30, 2001 7-13-6 Revision 7: Jul 20, 2011... Page 553 SECTION 7-13 AIRPLANE AND SYSTEMS DESCRIPTION Figure 7-13-1. Fuel System (Sheet 4 of 4) Issued: March 30, 2001 Report No: 02211 Revision 7: Jul 20, 2011 7-13-7... Page 554 SECTION 7-13 AIRPLANE AND SYSTEMS DESCRIPTION INTENTIONALLY BLANK Report No: 02211 Issued: March 30, 2001 7-13-8 Revision 7: Jul 20, 2011... Page 555 SECTION 7-14 AIRPLANE AND SYSTEMS DESCRIPTION ELECTRICAL GENERAL Refer to Figure 7-14-1, Power Generation Distribution System (PGDS) for system schematics and equipment layout. The electrical 28 VDC system, consists of the following power sources: GEN 1 system: a main generator 28 V, 300 A or a 28 V 400 A option ... Page 556 SECTION 7-14 AIRPLANE AND SYSTEMS DESCRIPTION illuminated. An external power control unit is installed which will disconnect the external power unit if the output voltage goes above 29.5 VDC or below 23 VDC. CAUTION THE GPU MUST BE CAPABLE OF PROVIDING A MINIMUM OF 500 AMPS FOR ALL SYSTEMS TO BE OPERATED CONTINUOUSLY AND 1,000 AMPS IF ENGINE STARTER OPERATION IS REQUIRED. Page 557 SECTION 7-14 AIRPLANE AND SYSTEMS DESCRIPTION BUS TIE INTERLOCK To permit both generators to charge the battery (two batteries - if installed) and supply all electrical services, GEN 1 is connected to the BAT BUS via the BUS TIE and GEN 2 to the BAT BUS via the GEN 2 TIE. Page 558 SECTION 7-14 AIRPLANE AND SYSTEMS DESCRIPTION CIRCUIT BREAKERS The COOLING, ELECTRICAL HEATING, HYDRAULIC and FLAP systems are all high current consuming systems which are connected directly to the main battery line. The electrical power circuit breakers for these systems are not accessible to the pilot (under cabin floor). Page 559 SECTION 7-14 AIRPLANE AND SYSTEMS DESCRIPTION CONTROLS AND INDICATORS Overhead Panel The electrical system is controlled from the ELECTRICAL POWER MANAGEMENT section of the overhead panel. The overhead panel has: • Control relay circuit breakers for BUS TIE and GEN 2 TIE •... Page 560 SECTION 7-14 AIRPLANE AND SYSTEMS DESCRIPTION The INV switch is a two position switch GEN 1 or BATT. When the switch is set to GEN 1 the 26 VAC 400 Hz is supplied by the No 1 Inverter, when the switch is set to BATT the 26 VAC 400 Hz is supplied from the No 2 inverter. Page 561 SECTION 7-14 AIRPLANE AND SYSTEMS DESCRIPTION Figure 7-14-1. Electrical Power System – Single Battery (Sheet 1 of 7) Issued: March 30, 2001 Report No: 02211 Revision 7: Jul 20, 2011 7-14-7... Page 562 SECTION 7-14 AIRPLANE AND SYSTEMS DESCRIPTION Figure 7-14-1. Electrical Power System - Dual Batteries (Sheet 2 of 7) Report No: 02211 Issued: March 30, 2001 7-14-8 Revision 7: Jul 20, 2011... Page 563 SECTION 7-14 AIRPLANE AND SYSTEMS DESCRIPTION Figure 7-14-1. Electrical Power System – Master Power Switch (Sheet 3 of 7) Issued: March 30, 2001 Report No: 02211 Revision 7: Jul 20, 2011 7-14-9... Page 564 SECTION 7-14 AIRPLANE AND SYSTEMS DESCRIPTION Figure 7-14-1. Electrical Power System (Typical Overhead Panel) (Sheet 4 of 7) Report No: 02211 Issued: March 30, 2001 7-14-10 Revision 7: Jul 20, 2011... Page 565 SECTION 7-14 AIRPLANE AND SYSTEMS DESCRIPTION Figure 7-14-1. Electrical Power System (Typical Left Circuit Breaker Panels) (Sheet 5 of 7) Issued: March 30, 2001 Report No: 02211 Revision 7: Jul 20, 2011 7-14-11... Page 566 SECTION 7-14 AIRPLANE AND SYSTEMS DESCRIPTION Figure 7-14-1. Electrical Power System (Typical Right Circuit Breaker Panels) (Sheet 6 of 7) Report No: 02211 Issued: March 30, 2001 7-14-12 Revision 7: Jul 20, 2011... Page 567 SECTION 7-14 AIRPLANE AND SYSTEMS DESCRIPTION Figure 7-14-1. Electrical Power System (AC Power) (Sheet 7 of 7) Issued: March 30, 2001 Report No: 02211 Revision 7: Jul 20, 2011 7-14-13... Page 568 SECTION 7-14 AIRPLANE AND SYSTEMS DESCRIPTION OPERATION Before applying electrical power to the aircraft, set the STBY BUS switch to the STBY BUS position and check the overhead panel switch positions to ensure that all electrical services are off, the NON ESS bus selector is set to AUTO, and the red bus status indicators are illuminated to show that no busbars are powered. Page 569 SECTION 7-14 AIRPLANE AND SYSTEMS DESCRIPTION Selecting AV 1 and 2 switches to ON applies power to the AVIONICS busses and extinguishes their red status indicators. It is not significant which inverter is selected, as long as the amber INVERTER caption on the CAWS is not illuminated. At this time the STBY BUS switch should be set to the off position. Page 570 SECTION 7-14 AIRPLANE AND SYSTEMS DESCRIPTION RED WARNING ESNTL BUS Indicates voltage on BAT, GEN 1 or GEN 2 Busses is below 22 V. Voice callout “Warning Essential Bus, Generator 1” or “Warning Essential Bus, Generator 2” or “Warning Essential Bus, Battery”... Page 571 SECTION 7-15 AIRPLANE AND SYSTEMS DESCRIPTION LIGHTING INTERIOR Cockpit lighting consists of internally lit cockpit instruments, glareshield mounted floodlights, control wheel reading lights, and a dome light. Light intensity is controlled by switches and rheostats located at the aft end of the center console. Separate intensity control of the pilot, copilot, and center console panels is provided. Page 572 SECTION 7-15 AIRPLANE AND SYSTEMS DESCRIPTION RECOGNITION LIGHTS Optional recognition lights and power supply units are installed in the left and right forward outer flap fairings. They provide forward illumination during taxiing and enhance the conspicuity of the aircraft in the traffic pattern or enroute. The lights are controlled by a switch located on the EXTERNAL LIGHTS section of the overhead panel. Page 573 SECTION 7-16 AIRPLANE AND SYSTEMS DESCRIPTION ENVIRONMENTAL CONTROL SYSTEM GENERAL Refer to Figure 7-16-1, Environmental Control System, for system layout. The Environmental Control System (ECS) is designed to take engine bleed air, reduce its temperature to that desired, and deliver it to the cabin air distribution system for pressurization and ventilation. Page 574 SECTION 7-16 AIRPLANE AND SYSTEMS DESCRIPTION A Firewall Shutoff Valve enables isolation of the system in emergency conditions such as an engine fire. Operation of the Firewall Shutoff Valve also opens a ram air scoop on the right fuselage underside which introduces ambient ventilation air through the distribution system. Page 575 SECTION 7-16 AIRPLANE AND SYSTEMS DESCRIPTION The Temperature Control System has two modes of operation as selected on the Auto/Manual switch. In the Auto mode, TCV operation is controlled by electrical signals from a cabin temperature sensor, located on the cabin headliner, to maintain the selected temperature between 18°C and 30°C. Page 576 SECTION 7-16 AIRPLANE AND SYSTEMS DESCRIPTION Figure 7-16-1. Environmental Control System (Sheet 1 of 3) Report No: 02211 Issued: March 30, 2001 7- 16-4 Revision 7: Jul 20, 2011... Page 577 SECTION 7-16 AIRPLANE AND SYSTEMS DESCRIPTION Figure 7-16-1. Environmental Control System (Sheet 2 of 3) Issued: March 30, 2001 Report No: 02211 Revision 7: Jul 20, 2011 7-16-5... Page 578 SECTION 7-16 AIRPLANE AND SYSTEMS DESCRIPTION Figure 7-16-1. Environmental Control System (Sheet 3 of 3) Report No: 02211 Issued: March 30, 2001 7-16-6 Revision 7: Jul 20, 2011... Page 579 SECTION 7-17 AIRPLANE AND SYSTEMS DESCRIPTION HEATING SYSTEM GENERAL Refer to Figure 7-16-1, Environmental Control System, for the system layout. The PC12 is equipped with an auxiliary electrical heating system, which is used to supplement the air cycle system during prolonged low temperature operations such as cruise at high altitude. Page 580 SECTION 7-17 AIRPLANE AND SYSTEMS DESCRIPTION The function of the power inhibits are fully automatic and require no pilot input. Thermal protection, once tripped, will require pilot action to reset. OPERATION The Auxiliary heating system is controlled by a combination of the ECS switch, situated on the co-pilot’s lower left panel to the left of the pilots control yoke and the CABIN switch on the HEATING section of the overhead panel. Page 581 SECTION 7-18 AIRPLANE AND SYSTEMS DESCRIPTION FOOT WARMER SYSTEM (OPTIONAL) DESCRIPTION The foot warmer system (when installed) comprises a 28 VDC 1kW heater installed forward above the cockpit floor. Ducting connects the heater to foot outlets at the pilot and copilot position. A FOOT heater switch is installed on the HEATING section of the overhead panel. Page 582 SECTION 7-18 AIRPLANE AND SYSTEMS DESCRIPTION INTENTIONALLY BLANK Report No: 02211 Issued: March 30, 2001 7-18-2 Revision 7: Jul 20, 2011... Page 583 SECTION 7-19 AIRPLANE AND SYSTEMS DESCRIPTION COOLING SYSTEM (OPTIONAL) GENERAL The Vapor Cycle Cooling System (VCCS) (when installed) is designed to operate on the ground from a 28 VDC power cart or aircraft electrical power when the engine is operating. The electric motor driven system provides a means of precooling cockpit and cabin areas prior to and during passenger boarding, providing comfort prior to engine start. Page 584 SECTION 7-19 AIRPLANE AND SYSTEMS DESCRIPTION OPERATION When the system is activated, an electric motor drives the compressor at constant speed and capacity which compresses the refrigerant gas to high pressure. The hot, high pressure gas then passes through the condenser coil where it is cooled and condensed into a warm liquid at constant pressure. Page 585 SECTION 7-19 AIRPLANE AND SYSTEMS DESCRIPTION Figure 7-19-1. Vapor Cycle Cooling System Issued: March 30, 2001 Report No: 02211 Revision 7: Jul 20, 2011 7-19-3... Page 586 SECTION 7-19 AIRPLANE AND SYSTEMS DESCRIPTION INTENTIONALLY BLANK Report No: 02211 Issued: March 30, 2001 7-19-4 Revision 7: Jul 20, 2011... Page 587 SECTION 7-20 AIRPLANE AND SYSTEMS DESCRIPTION CABIN PRESSURIZATION CONTROL SYSTEM GENERAL Refer to Figure 7-20-1, Cabin Pressurization Control system, for controls and functional diagram. Control of the cabin pressure is obtained by regulating the rate of exhaust of the outflow air that is provided for pressurization and ventilation of the airplane cabin. Page 588 SECTION 7-20 AIRPLANE AND SYSTEMS DESCRIPTION Figure 7-20-1. Cabin Pressurization (Sheet 1 of 2) Report No: 02211 Issued: March 30, 2001 7-20-2 Revision 7: Jul 20, 2011... Page 589 SECTION 7-20 AIRPLANE AND SYSTEMS DESCRIPTION Figure 7-20-1. Cabin Pressurization (Sheet 2 of 2) Issued: March 30, 2001 Report No: 02211 Revision 7: Jul 20, 2011 7-20-3... Page 590 SECTION 7-20 AIRPLANE AND SYSTEMS DESCRIPTION Low pressure needed for operation of the controller is provided by the ejector valve, which is connected to the controller VACUUM port through a check valve. The ejector valve is also connected to the safety valve through a normally closed solenoid valve to provide the low pressure to operate the valve for inflight depressurization and unpressurized ground operation. Page 591 SECTION 7-20 AIRPLANE AND SYSTEMS DESCRIPTION OPERATION During normal ground operation with the pressurization switch in AUTO and the condition lever in the Ground Idle position, the solenoid valve will open when electrical power is applied to the system. The airplane will be unpressurized. Before selecting the ECS on, set the desired cabin rate of climb and set the outflow controller to 500 feet above the airplane cruise altitude. Page 592 SECTION 7-20 AIRPLANE AND SYSTEMS DESCRIPTION Repressurizing the airplane cabin after depressurization is accomplished by setting the pressurization switch to AUTO to remove electrical power from the solenoid valve. The solenoid valve closes and removes the vacuum from the safety valve, causing the valve to close. Page 593 SECTION 7-21 AIRPLANE AND SYSTEMS DESCRIPTION OXYGEN SYSTEM GENERAL The aircraft is equipped with an emergency oxygen system for use by the crew and passengers in the event of contaminated air being introduced into the cabin or a loss of pressurization with a rapid descent to lower altitudes. Page 594 SECTION 7-21 AIRPLANE AND SYSTEMS DESCRIPTION Two crew full-face masks of the diluter demand type are located in boxes on the front of the cockpit bulkhead behind each crew member. They are permanently connected to outlets in the cockpit sidewalls. Each mask which is of the diluter-demand type, is equipped with a microphone and an ON/OFF - AIRMIX/100% selector valve. Page 595 SECTION 7-21 AIRPLANE AND SYSTEMS DESCRIPTION OPERATION WARNING PREVENT POSSIBLE FREEZING MALFUNCTIONING OF SYSTEM, MAKE SURE THAT THE SYSTEM IS ONLY SERVICED WITH APPROVED, AVIATION GRADE OXYGEN. TO PREVENT POSSIBLE EXPLOSION AND/OR FIRE, MAKE SURE ALL OIL AND GREASE IS KEPT AWAY FROM OXYGEN SYSTEM COMPONENTS. Page 596 SECTION 7-21 AIRPLANE AND SYSTEMS DESCRIPTION The ON position will be selected by the pilot, in the event of smoke or fumes being present in the cabin, and also to test the passengers masks on the ground before passenger boarding. The OFF position will be selected if the aircraft is being flown without passengers or is taken out of service for an extended time in order to conserve oxygen. Page 597 SECTION 7-21 AIRPLANE AND SYSTEMS DESCRIPTION REAR RIGHT SIDE The right side larger capacity oxygen system has the same operation and components as the left side. The following components have a different location. The oxygen cylinder is installed in the top right side of the rear fuselage compartment. The oxygen replenishment point comprising a charging valve and a system pressure gauge is installed at the bottom right of the rear fuselage compartment. Page 598 SECTION 7-21 AIRPLANE AND SYSTEMS DESCRIPTION INTENTIONALLY BLANK Report No: 02211 Issued: March 30, 2001 7-21-6 Revision 7: Jul 20, 2011... Page 599 SECTION 7-22 AIRPLANE AND SYSTEMS DESCRIPTION COCKPIT ARRANGEMENT GENERAL Refer to Figure 7-22-1, for the Cockpit Layout. The cockpit is of a conventional layout in that all of controls, switches, and instruments are readily accessible to the pilot for single pilot operation. The overhead panel contains the switches to control the electrical bus distribution, external lighting de-icing, starting and cabin heating systems. Page 600 SECTION 7-22 AIRPLANE AND SYSTEMS DESCRIPTION The left side of the instrument panel contains the flight instruments for the pilot. These include the airspeed, attitude, directional, altitude, and rate of climb instruments. The airspeed indicator provides data for various system control inputs and has a variable M mo needle for the constant Mach maximum airspeed limit above 15,200 feet. Page 601 SECTION 7-22 AIRPLANE AND SYSTEMS DESCRIPTION Figure 7-22-1. Typical Cockpit Layout Issued: March 30, 2001 Report No: 02211 Revision 7: Jul 20, 2011 7-22-3... Page 602 SECTION 7-22 AIRPLANE AND SYSTEMS DESCRIPTION INTENTIONALLY BLANK Report No: 02211 Issued: March 30, 2001 7-22-4 Revision 7: Jul 20, 2011... Page 603 SECTION 7-23 AIRPLANE AND SYSTEMS DESCRIPTION CENTRAL ADVISORY AND WARNING SYSTEM (CAWS) GENERAL Refer to Figure 7-23-1, Central Advisory and Warning System (CAWS), for more information on the warning/caution/advisory lights and voice callouts. DESCRIPTION The Central Advisory and Warning System (CAWS) integrates the control and display functions of aircraft systems status into a single unit. Page 604 SECTION 7-23 AIRPLANE AND SYSTEMS DESCRIPTION OPERATION The CAWS must be tested when the aircraft is on the ground before takeoff. Pressing the TEST LAMP switch on the overhead panel will check the system and make all the annunciator LED’s and the master WARNING and CAUTION lights illuminate. Pressing the TEST LAMP switch in the air will only make all the CAWS annunciator LED’s illuminate. Page 605 SECTION 7-23 AIRPLANE AND SYSTEMS DESCRIPTION WARNING / CAUTION AND ADVISORY INDICATIONS Voice Caption Color Description Callout PASS DOOR Warning Indicates passenger door and/or handle Passenger are not locked. Door CAR DOOR Warning Indicates cargo door and/or handle are not Cargo Door locked. Page 606 SECTION 7-23 AIRPLANE AND SYSTEMS DESCRIPTION WARNING / CAUTION AND ADVISORY INDICATIONS (CONT’D) Voice Caption Color Description Callout GEN 2 Amber None Indicates that generator 2 is off-line. BUS TIE Amber None Indicates generator 1 bus tie isolation relay is open. Page 607 SECTION 7-23 AIRPLANE AND SYSTEMS DESCRIPTION WARNING / CAUTION AND ADVISORY INDICATIONS (CONT’D) Voice Caption Color Description Callout FUEL PRESS Amber None Indicates fuel system pressure is less then 2 psi (0.14 bar). Light goes off when fuel system pressure is greater than 3.5 psi (0.24 bar). Page 608 SECTION 7-23 AIRPLANE AND SYSTEMS DESCRIPTION WARNING / CAUTION AND ADVISORY INDICATIONS (CONT’D) Voice Caption Color Description Callout R FUEL Amber None Indicates fuel quantity in right wing tank has reached 20 US gal (75 liters). BATTERY Amber None Indicates a battery over voltage or over current condition OIL QTY Amber... Page 609 SECTION 7-23 AIRPLANE AND SYSTEMS DESCRIPTION Figure 7-23-1. Central Advisory and Warning System (CAWS) Annunciator Panel Issued: March 30, 2001 Report No: 02211 Revision 7: Jul 20, 2011 7-23-7... Page 610 SECTION 7-23 AIRPLANE AND SYSTEMS DESCRIPTION INTENTIONALLY BLANK Report No: 02211 Issued: March 30, 2001 7-23-8 Revision 7: Jul 20, 2011... Page 611 SECTION 7-24 AIRPLANE AND SYSTEMS DESCRIPTION PITOT STATIC SYSTEMS GENERAL The pitot static systems obtain dynamic and static pressure to operate instruments for the pilot and copilot flight information. DESCRIPTION Pitot pressure, for the pilot’s airspeed indicator is sensed by a heated pitot head which is installed on the bottom of the right wing and is carried through lines within the wing and fuselage to the gauge on the pilot’s instrument panel. Page 612 SECTION 7-24 AIRPLANE AND SYSTEMS DESCRIPTION INDICATION / WARNING There are three amber caution annunciators on the CAWS for the pitot and static systems, which are accompanied by a gong. If the gong is heard and the CAWS PITOT 1 annunciator is on, this indicates a failure of the right pitot head heating circuit which supplies the pilot’s instruments. Page 613 SECTION 7-24 AIRPLANE AND SYSTEMS DESCRIPTION Figure 7-19. Pitot and Static Systems Issued: March 30, 2001 Report No: 02211 Revision 7: Jul 20, 2011 7-24-3... Page 614 SECTION 7-24 AIRPLANE AND SYSTEMS DESCRIPTION INTENTIONALLY BLANK Report No: 02211 Issued: March 30, 2001 7-24-4 Revision 7: Jul 20, 2011... Page 615 SECTION 7-25 AIRPLANE AND SYSTEMS DESCRIPTION STALL WARNING / STICK PUSHER SYSTEM GENERAL The airplane is equipped with a stick shaker-pusher system to improve aircraft handling in the low speed flight regime by preventing the airplane from inadvertently entering a stall condition. Page 616 SECTION 7-25 AIRPLANE AND SYSTEMS DESCRIPTION When operated in PUSHER ICE MODE (to provide protection in icing conditions), all the shaker and pusher actuating points, measured by the angle of attack vanes, are reduced by 8°. The pusher ICE mode is set when the propeller de-icing system is switched ON and the inertial separator is set to OPEN. Page 617 SECTION 7-25 AIRPLANE AND SYSTEMS DESCRIPTION OPERATION The vane attached to the AOA probe aligns itself with the relative airflow. As it moves, it positions a wiper unit in the probe. This wiper unit adjusts the electrical output to its respective pusher computer. Page 618 SECTION 7-25 AIRPLANE AND SYSTEMS DESCRIPTION INDICATION / WARNING A digital serial output, from the left hand computer, provides the data for the FAST/SLOW pointer on the EFIS EADI. (Refer to EFIS section for more information). In the instance of disparity between the LH and RH weight-on-wheels inputs, the Central Advisory and Warning System annunciator AIR/GND and PUSHER are activated to warn the pilot of the malfunction. Page 619 SECTION 7-25 AIRPLANE AND SYSTEMS DESCRIPTION Figure 7-25-1. Stall Warning/Stick Pusher System (Sheet 1 of 3) Issued: March 30, 2001 Report No: 02211 Revision 7: Jul 20, 2011 7-25-5... Page 620 SECTION 7-25 AIRPLANE AND SYSTEMS DESCRIPTION Figure 7-25-1. Stall Warning/Stick Pusher System (Sheet 2 of 3) Report No: 02211 Issued: March 30, 2001 7-25-6 Revision 7: Jul 20, 2011... Page 621 SECTION 7-25 AIRPLANE AND SYSTEMS DESCRIPTION Figure 7-25-1. Stall Warning/Stick Pusher System (Sheet 3 of 3) Issued: March 30, 2001 Report No: 02211 Revision 7: Jul 20, 2011 7-25-7... Page 622 SECTION 7-25 AIRPLANE AND SYSTEMS DESCRIPTION INTENTIONALLY BLANK Report No: 02211 Issued: March 30, 2001 7-25-8 Revision 7: Jul 20, 2011... Page 623 SECTION 7-26 AIRPLANE AND SYSTEMS DESCRIPTION PNEUMATIC WING DEICE SYSTEM GENERAL Inflatable neoprene boots are installed on the leading edges of the wings and horizontal tail surfaces. Their purpose is to inflate and dispense any ice which may accrete on their surface during flight in atmospheric icing conditions. Page 624 SECTION 7-26 AIRPLANE AND SYSTEMS DESCRIPTION OPERATION Refer to Figure 7-26-1, Pneumatic Wing Deice System. In the off mode the system applies a continuous vacuum to the de-ice boots while the engine is running. The system is initiated by pressing the switch labeled BOOTS on the DE-ICING section of the overhead panel. Page 625 SECTION 7-26 AIRPLANE AND SYSTEMS DESCRIPTION Figure 7-26-1. Deicing System (Sheet 1 of 2) Issued: March 30, 2001 Report No: 02211 Revision 7: Jul 20, 2011 7-26-3... Page 626 SECTION 7-26 AIRPLANE AND SYSTEMS DESCRIPTION Figure 7-26-1. Deicing System (Sheet 2 of 2) Report No: 02211 Issued: March 30, 2001 7-26-4 Revision 7: Jul 20, 2011... Page 627 SECTION 7-27 AIRPLANE AND SYSTEMS DESCRIPTION COMFORT FEATURES GENERAL Extra comfort for the pilot and copilot can be provided by optional equipment installed at build. For colder climates a foot warmer system can be installed, refer to the Foot Warmer System description and operation for more information. Noise canceling headsets can be installed in place of the normal headsets. Page 628 SECTION 7-27 AIRPLANE AND SYSTEMS DESCRIPTION INTENTIONALLY BLANK Report No: 02211 Issued: March 30, 2001 7-27-2 Revision 7: Jul 20, 2011... Page 629 SECTION 7-28 AIRPLANE AND SYSTEMS DESCRIPTION CABIN FEATURES GENERAL The PC-12 has a large cabin that offers a flexible interior configuration for passenger and cargo loading. There are two basic cabin configurations, a Corporate Commuter and an Executive interior. Variations to the two basic configurations are continually being developed, refer to Section 2 for the variations that have been approved. Page 630 SECTION 7-28 AIRPLANE AND SYSTEMS DESCRIPTION A toilet compartment is installed in the front right hand side of the aircraft. The forward wall of the toilet compartment forms the cabin divider. Left and right storage cabinets are installed, the left cabinet fits against a small divider behind the passenger door and the right cabinet fits against the toilet compartment rear wall. Page 631 SECTION 7-29 AIRPLANE AND SYSTEMS DESCRIPTION GENERAL AVIONICS INSTALLATION AUDIO PANEL GENERAL The audio panel provides the capability to select transmitter and audio either though the cockpit speakers or headphones. Crew intercom and cabin PA are also available. Aural warnings can be heard in the headphone audio and loudspeakers. An optional second audio control panel can be installed in the copilot’s instrument panel. Page 632 SECTION 7-29 AIRPLANE AND SYSTEMS DESCRIPTION Figure 7-29-1. Typical Avionics Report No: 02211 Issued: March 30, 2001 7-29-2 Revision 7: Jul 20, 2011... Page 633 SECTION 7-30 AIRPLANE AND SYSTEMS DESCRIPTION ATTITUDE AND HEADING REFERENCE SYSTEM GENERAL The Attitude and Heading Reference System (AHRS) supplies pitch, roll, heading and turn rate information to the EFIS EADI and EHSI and the Radio Magnetic Indicator (RMI). The system maintains accurate indications in all aircraft attitudes. The AHRS is installed in the avionics bay and the magnetic sensing unit is within the right wing. Page 634 SECTION 7-30 AIRPLANE AND SYSTEMS DESCRIPTION Two switches AHRS 1 on the pilot's lower right panel control the source of heading information displayed. The DG/SLAVE switch selects a free gyro mode when set to DG or AHRS heading information when the switch is set to SLAVE. The CW/CCW switch slews the heading card clockwise (CW) or counterclockwise (CCW) when the DG/SLAVE switch is set to DG. Page 635 SECTION 7-30 AIRPLANE AND SYSTEMS DESCRIPTION If the AHRS selection is changed the autopilot will automatically disconnect. It can be re- engaged manually. YAW RATE SENSOR INSTALLATION (OPTIONAL) An optional remote mounted sensor when installed, provides angular rate information, displayed independent of AHRS function on the EFIS EHSI display unit(s). Issued: March 30, 2001 Report No: 02211 Revision 7: Jul 20, 2011... Page 636 SECTION 7-30 AIRPLANE AND SYSTEMS DESCRIPTION INTENTIONALLY BLANK Report No: 02211 Issued: March 30, 2001 7-30-4 Revision 7: Jul 20, 2011... Page 637 SECTION 7-31 AIRPLANE AND SYSTEMS DESCRIPTION STANDBY ATTITUDE INDICATOR GENERAL A second attitude indicator gyro is located on the instrument panel to the left of the airspeed indicator. DESCRIPTION The attitude gyro provides a second source of pitch and roll information. This attitude gyro is a self contained vertical axis gyroscope, mounted in a pitch gimbal, which is mounted in a roll gimbal. Page 638 SECTION 7-31 AIRPLANE AND SYSTEMS DESCRIPTION INTENTIONALLY BLANK Report No: 02211 Issued: March 30, 2001 7-31-2 Revision 7: Jul 20, 2011... Page 639 SECTION 7-32 AIRPLANE AND SYSTEMS DESCRIPTION EMERGENCY LOCATOR TRANSMITTER DESCRIPTION An Emergency Locator Transmitter (ELT) is installed in the rear fuselage. It is connected to an antenna which is installed on the top of the fuselage below the dorsal fairing and has a battery pack that must be replaced after a specified time. The ELT 121 AF transmits on the international distress frequencies of 121.5 and 243.0 MHz. Page 640 SECTION 7-32 AIRPLANE AND SYSTEMS DESCRIPTION INTENTIONALLY BLANK Report No: 02211 Issued: March 30, 2001 7-32-2 Revision 7: Jul 20, 2011... SECTION 7-33 AIRPLANE AND SYSTEMS DESCRIPTION ELECTRONIC FLIGHT INSTRUMENTATION SYSTEM EFS 40/50 GENERAL The Bendix King Electronic Flight Instrumentation System (EFIS) is an electronic navigation display system. The system receives data from the AHRS, angle of attack, and navigation systems. The data is displayed to the pilot on two multimode color displays. Page 642 SECTION 7-33 AIRPLANE AND SYSTEMS DESCRIPTION ELECTRONIC ATTITUDE DIRECTOR INDICATOR The Electronic Attitude Director Indicator (EADI) displays aircraft flight attitude from roll, pitch, yaw and heading data provided by the AHRS. Refer to Figure 7-33-1, EADI. Airplane Symbol: An airplane symbol in the center of the display is used as a reference point. Page 643 SECTION 7-33 AIRPLANE AND SYSTEMS DESCRIPTION In the lower right corner of the display, a green alphanumeric field displays the selected DH. This field is active only when the DH set knob is active or when the radar altimeter is providing valid height data. To the right and above center of the display, a yellow DH alert is displayed in a black box outlined in yellow. Page 644 SECTION 7-33 AIRPLANE AND SYSTEMS DESCRIPTION Figure 7-33-1. EADI Report No: 02211 Issued: March 30, 2001 7-33-4 Revision 7: Jul 20, 2011... Page 645 SECTION 7-33 AIRPLANE AND SYSTEMS DESCRIPTION Wind Speed The full time wind vectoring indicating approximate wind and Vector direction and speed is displayed on the EHSI display in white in the upper left corner below the selected course. Wind vector information will be available only when valid data is provided by the LNAV. Page 646 SECTION 7-33 AIRPLANE AND SYSTEMS DESCRIPTION Figure 7-33-2. EHSI (Sheet 1 of 2) Report No: 02211 Issued: March 30, 2001 7-33-6 Revision 7: Jul 20, 2011... Page 647 SECTION 7-33 AIRPLANE AND SYSTEMS DESCRIPTION Figure 7-33-2. EHSI (Sheet 2 of 2) Issued: March 30, 2001 Report No: 02211 Revision 7: Jul 20, 2011 7-33-7... Page 648 SECTION 7-33 AIRPLANE AND SYSTEMS DESCRIPTION Heading Select Bug: An orange heading bug is manually rotated around the compass scale by the heading select knob on the control panel. A digital readout of the selected heading is displayed in the lower right hand corner. Once set, the heading bug rotates with the compass card. Page 649 SECTION 7-33 AIRPLANE AND SYSTEMS DESCRIPTION To/From Indicator: A white arrow head is displayed near the center of the (not illus. in Fig. 7-33-3) EHSI with head pointing toward the course pointer (TO) or toward the tail or the course pointer (FROM). indicates the selected course is to or from the station or waypoint. Page 650 SECTION 7-33 AIRPLANE AND SYSTEMS DESCRIPTION Course Annunciation: Magnetic course is automatically displayed in VOR/LOC, GPS, and ADF. Glide Slope Display: If the selected primary sensor is an ILS, the vertical scale will appear on the right side when the selected inboard course is within 105 degrees of the aircraft heading. Page 651 SECTION 7-33 AIRPLANE AND SYSTEMS DESCRIPTION Selected Course The alphanumeric course select readout in the upper Display: left corner of the display functions the same in the map mode as in the standard EHSI mode. The standard EHSI selected course is removed from the center of the display. Page 652 SECTION 7-33 AIRPLANE AND SYSTEMS DESCRIPTION Figure 7-33-3. Map Mode Display Report No: 02211 Issued: March 30, 2001 7-33-12 Revision 7: Jul 20, 2011... Page 653 SECTION 7-33 AIRPLANE AND SYSTEMS DESCRIPTION ARC Display The expanded ( ARC ) format provides an enlarged display for increased resolution to NAV data due to the enlarged compass scale presentation. Refer to Figure 7-33-4, Arc Display. The following will address only those areas of the EHSI ARC Mode which are different from the standard compass presentations previously described. Page 654 SECTION 7-33 AIRPLANE AND SYSTEMS DESCRIPTION Figure 7-33-4. Arc Display Report No: 02211 Issued: March 30, 2001 7-33-14 Revision 7: Jul 20, 2011... Page 655 SECTION 7-33 AIRPLANE AND SYSTEMS DESCRIPTION EFIS CONTROL PANEL Refer to Figure 7-33-5, EFIS Control Panel. The EFIS Control Panel is located on the center console and provide the following functions. NAV SENSOR During installation, the system was programmed with the type and SELECT: quantity of each piece of interfacing equipment. Page 656 SECTION 7-33 AIRPLANE AND SYSTEMS DESCRIPTION NUMBER 2 SYSTEM The bearing pointer select button works similar to the NAV BEARING POINTER sensor select button and the Number 1 Bearing Pointer Select SELECT: button. A press of the bearing pointer button sequentially selects the next available sensor. Page 657 SECTION 7-33 AIRPLANE AND SYSTEMS DESCRIPTION RANGE SELECTION: RANGE DOWN - A press of the RANGE DOWN button selects the next lower range to be displayed while in the NAV MAP mode of operation. Once the lowest selectable range is reached, the RANGE UP button button must be used for a range change. Page 658 SECTION 7-33 AIRPLANE AND SYSTEMS DESCRIPTION HEADING SELECT Rotation of the HEADING SELECT knob allows the heading KNOB: bug on the EHSI to be rotated to the desired heading. The Control Panel provides a HEADING SYNC feature. Pulling the Control Panel HEADING SELECT knob will cause the heading bug on the EHSI to slew to the present aircraft heading (lubber line). Page 659 SECTION 7-33 AIRPLANE AND SYSTEMS DESCRIPTION Figure 7-33-5. EFIS Control Panel Issued: March 30, 2001 Report No: 02211 Revision 7: Jul 20, 2011 7-33-19... Page 660 SECTION 7-33 AIRPLANE AND SYSTEMS DESCRIPTION MULTI-FUNCTION DISPLAY (KMD 850) The KMD 850 Multi-function display (MFD) is an independent Liquid crystal display (LCD) which shows: A moving map display Weather radar data (if installed) Terrain data (if EGPWS or TAWS is installed) ... Page 661 SECTION 7-33 AIRPLANE AND SYSTEMS DESCRIPTION Control keys The control keys are used to manipulate the page that is currently displayed. Either a soft label on the LCD on the left side of the key or the control key annunciator on the right side of the control key indicates the functionality of each key. Page 662 SECTION 7-33 AIRPLANE AND SYSTEMS DESCRIPTION TRFC (TCAS if installed) TERR (Terrain if EGPWS or TAWS is installed) AUX (Set-up pages) When a function select key is pushed, the indicator above the key is illuminated to show that the function has been selected for display. Page 663 SECTION 7-33 AIRPLANE AND SYSTEMS DESCRIPTION Figure 7- 33-6. Multifunction Display Control Panel Issued: March 30, 2001 Report No: 02211 Revision 7: Jul 20, 2011 7-33-23... SECTION 7-33 AIRPLANE AND SYSTEMS DESCRIPTION WEATHER RADAR (IF INSTALLED) Display Weather radar information may be displayed with or without navigation data presentation on the EFIS or the MFD. When selected, a vertical view of the weather return along the Track Line may be displayed on the MFD. Page 665 SECTION 7-33 AIRPLANE AND SYSTEMS DESCRIPTION Figure 7-33-7. MFD Weather Radar Display (Sheet 1 of 2) Issued: March 30, 2001 Report No: 02211 Revision 7: Jul 20, 2011 7-33-25... Page 666 SECTION 7-33 AIRPLANE AND SYSTEMS DESCRIPTION Figure 7-33-7. MFD Weather Radar Display (Sheet 2 of 2) Report No: 02211 Issued: March 30, 2001 7-33-26 Revision 7: Jul 20, 2011... Page 667 SECTION 7-33 AIRPLANE AND SYSTEMS DESCRIPTION Control Panel Weather radar display is controlled by a panel located on the center lower panel of the cockpit. Refer to Figure 7-33-8, Radar Control Panel. The Radar Control Panel provides the following functions. Radar Function Rotary switch selects the desired operating condition. Page 668 SECTION 7-33 AIRPLANE AND SYSTEMS DESCRIPTION Figure 7-33-8. Radar Control Panel Report No: 02211 Issued: March 30, 2001 7-33-28 Revision 7: Jul 20, 2011... Page 669 SECTION 7-33 AIRPLANE AND SYSTEMS DESCRIPTION TRK Buttons: When pressed provides a yellow azimuth line and a digital display of the azimuth line placement left or right of the airplane nose. For vertical profile (VP) operations, the track buttons perform the two functions: Prior to engaging VP, the appropriate button (left or right) is used to place the track line at the desired azimuth angle to be vertically scanned... Page 670 SECTION 7-33 AIRPLANE AND SYSTEMS DESCRIPTION With lightning mode ON, up to 63 grey colored lightning cell symbols can be displayed on the EFIS. There are three lightning cell symbols to show the different levels of lightning intensity. The level 1 (lowest rate of discharge) symbol is a lightning bolt with no arrowheads. Page 671 SECTION 7-33 AIRPLANE AND SYSTEMS DESCRIPTION Figure 7-33-9. Composite Display - Approach Issued: March 30, 2001 Report No: 02211 Revision 7: Jul 20, 2011 7-33-31... Page 672 SECTION 7-33 AIRPLANE AND SYSTEMS DESCRIPTION Figure 7-33-10. Composite Display - Enroute Report No: 02211 Issued: March 30, 2001 7-33-32 Revision 7: Jul 20, 2011... Page 673 SECTION 7-1 AIRPLANE AND SYSTEMS DESCRIPTION INDICATION / WARNING During normal operation the following faults may be detected and displayed automatically. SG ( Red ): EFIS information in general is unreliable. Revert to backup instruments. CP ( Red ): EFIS control panel switch stuck for more than 10 seconds. Page 674 SECTION 7-33 AIRPLANE AND SYSTEMS DESCRIPTION INTENTIONALLY BLANK Report No: 02211 Issued: March 30, 2001 7-33-34 Revision 7: Jul 20, 2011... Page 675 SECTION 7-34 AIRPLANE AND SYSTEMS DESCRIPTION AUTOPILOT GENERAL The autopilot installed in the PC-12 aircraft is the Bendix/King KFC 325 Digital Automatic Flight Control System (AFCS). The limitations presented in Section 2 of this Handbook are pertinent to the operation of the KFC 325 AFCS as installed. The Automatic Flight Control System must be operated within the limitations specified. Page 676 SECTION 7-34 AIRPLANE AND SYSTEMS DESCRIPTION navigation receiver based on the EHSI selected primary navigation source. Glideslope coupling is inhibited in the NAV mode. APR: Alternately engages and disengages the Approach mode. Depressing APR will activate the Flight Director. APR mode will capture and track selected EHSI primary navigation sensor with approach accuracy. Page 677 SECTION 7-34 AIRPLANE AND SYSTEMS DESCRIPTION Figure 7-34-1. Autopilot Mode Annunciations ALT: Alternately engages and disengages the Altitude Hold mode. Altitude Hold commands the aircraft to maintain the pressure altitude existing at the moment of selection. The pilot must correct for altimeter changes during flight to insure barometrically corrected altitude. Page 678 SECTION 7-34 AIRPLANE AND SYSTEMS DESCRIPTION The AP annunciator will flash for approximately six seconds upon successful completion of the Preflight Test. An aural tone accompanies the flashing AP annunciation. The Autopilot mode will not be enabled until the Preflight Test has been successfully passed. ALTITUDE / VERTICAL SPEED PRESELECT The KAS 297C operation is controlled by a Controller located in the pilot's instrument panel. Page 679 SECTION 7-34 AIRPLANE AND SYSTEMS DESCRIPTION OPERATION AUTOPILOT Emergency and Normal Procedures are detailed in Sections 3 and 4 of this Handbook. The following conditions will cause the autopilot to automatically disengage: Pilot related input Roll rates in excess of 10° per second will cause the autopilot to disengage except when the CWS switch is held depressed. Page 680 SECTION 7-34 AIRPLANE AND SYSTEMS DESCRIPTION ALTITUDE / VERTICAL SPEED PRESELECT Emergency and Normal Procedures are detailed in Sections 3 and 4 of this Handbook. CONTROL WHEEL STEERING Mounted on each inboard control wheel horn is the Control Wheel Steering (CWS) switch. Page 681 SECTION 7-34 AIRPLANE AND SYSTEMS DESCRIPTION INDICATION / WARNING AUTOPILOT The engaged and armed autopilot modes are annunciated on the Mode Controller and in the upper area of the EADI. Refer to Figure 7-34-2, Autopilot Mode Annunciations. The following annunciations are illuminated on the Mode Controller (EADI annunciations are shown in Figure 7-34-2). Page 682 SECTION 7-34 AIRPLANE AND SYSTEMS DESCRIPTION IAS: Illuminates when the Airspeed Hold mode is engaged by depressing the IAS pushbutton. Illuminates when the FD pushbutton is depressed or by default when any Flight Director mode is engaged. The Flight Director mode is Wings Level and Pitch Attitude Hold. Page 683 SECTION 7-34 AIRPLANE AND SYSTEMS DESCRIPTION Figure 7-34-2. Autopilot Mode Annunciations Issued: March 30, 2001 Report No: 02211 Revision 7: Jul 20, 2011 7-34-9... Page 684 SECTION 7-34 AIRPLANE AND SYSTEMS DESCRIPTION ALTITUDE / VERTICAL SPEED PRESELECT The engaged and armed modes are annunciated on the Controller and in the upper area of the EADI. Refer to Figure 7-34-3, Altitude / Vertical Speed Preselect Annunciations. The following annunciations are illuminated on the Controller ( EADI annunciations are shown in Figure 7-34-2. Page 685 SECTION 7-34 AIRPLANE AND SYSTEMS DESCRIPTION Figure 7-34-3. Altitude / Vertical Speed Preselect Annunciations CAPT: Illuminates when the KAS 297C has switched the Flight Director from the active Pitch mode to Altitude Capture (CAPT) mode. The Altitude Capture mode occurs prior to the point the Flight Director engages Altitude Hold. Page 686 SECTION 7-34 AIRPLANE AND SYSTEMS DESCRIPTION INTENTIONALLY BLANK Report No: 02211 Issued: March 30, 2001 7-34-12 Revision 7: Jul 20, 2011... Page 687 SECTION 8 HANDLING, SERVICING, AND MAINTENANCE SECTION 8 HANDLING, SERVICING AND MAINTENANCE TABLE OF CONTENTS Subject Page GENERAL IDENTIFICATION PLATE AIRPLANE INSPECTIONS AIRPLANE INSPECTION PERIODS AIRPLANE SCHEDULED INSPECTIONS COMPONENT LIFE POLICY PREVENTIVE MAINTENANCE MODIFICATIONS OR REPAIRS SERVICE BULLETINS AND SERVICE LETTERS GROUND HANDLING TOWING PARKING... Page 688 SECTION 8 HANDLING, SERVICING, AND MAINTENANCE Subject Page SERVICING (CONT'D) ENGINE OIL 8-15 Oil Replenishment Procedure 8-17 Complete Oil System Replenishment 8-17 FUEL SYSTEM 8-18 Refueling Precautions 8-18 Fueling Procedure 8-19 Fuel Contamination 8-20 Fuel Anti-Icing Additive 8-21 LANDING GEAR - TIRES 8-23 LANDING GEAR - BRAKES 8-23... Fax: 41-41-619 7311 eMail: SupportPC12@pilatus-aircraft.com Pilatus Aircraft Ltd. cannot accept responsibility for continued airworthiness of any airplane not maintained in accordance with the information contained within this section or the Airplane Maintenance Manual (AMM). IDENTIFICATION PLATE An identification plate is located on the lower left side of the fuselage aft of the cargo door. Page 690 AMM. Reference is made to the topics in this manual and Pilatus issued Service Bulletins for inspection, repair, removal and installation procedures called for in the inspection sheets. It is the responsibility of the owner or operator to make sure that mechanics inspecting the airplane have access to these documents as well as the inspection sheets. Pilatus Aircraft Ltd should be contacted for further information, or for the required maintenance which must be accomplished by appropriately licensed personnel. All other maintenance required on the airplane should be accomplished by the appropriately licensed personnel. SERVICE BULLETINS AND SERVICE LETTERS Pilatus Aircraft will issue Service Bulletins and Service Letters from time to time which will be sent to owners, service centers and distributors. Service Bulletins should be complied with promtly and depending on their nature material and labor allowances may apply, this aspect will be addressed in the Planning Information section of the bulletin. Page 693 SECTION 8 HANDLING, SERVICING, AND MAINTENANCE Figure 8-1. Aircraft Towing Issued: March 30, 2001 Report No: 02211... Page 694 SECTION 8 HANDLING, SERVICING, AND MAINTENANCE PARKING In normal weather conditions, the airplane can be parked on any firm surface, headed into wind (if possible) and the parking brake applied, or wheel chocks in place, or both. The tail stand should be installed any time the aircraft is parked outside and wet snow fall is expected. Page 695 SECTION 8 HANDLING, SERVICING, AND MAINTENANCE Figure 8-2. Blanks and Covers (Existing Standard) (Sheet 1 of 2) Issued: March 30, 2001 Report No: 02211 Revision 8: December 01, 2012... Page 696 SECTION 8 HANDLING, SERVICING, AND MAINTENANCE Figure 8-2. Blanks and Covers (Existing Standard) (Sheet 2 of 2) Report No: 02211 Issued: March 30, 2001 Revision 8: December 01, 2012... Page 697 SECTION 8 HANDLING, SERVICING, AND MAINTENANCE Figure 8-3. Blanks and Covers (New Standard) Issued: March 30, 2001 Report No: 02211 Revision 8: December 01, 2012... Page 698 SECTION 8 HANDLING, SERVICING, AND MAINTENANCE MOORING The airplane should be moored for immovability, security and protection. The following procedures should be used for the proper mooring of the airplane (Ref. Figs. 8-2, 8-3 and 8-4): Head the airplane into wind, where possible. Retract the flaps. Page 699 SECTION 8 HANDLING, SERVICING, AND MAINTENANCE Figure 8-4. Airplane Mooring Issued: March 30, 2001 Report No: 02211 Revision 8: December 01, 2012 8-11... SECTION 8 HANDLING, SERVICING, AND MAINTENANCE JACKING SINGLE WHEEL JACKING To assist in wheel and brake maintenance, both the two main wheels and the nose wheel can be jacked, independently, using a bottle jack and an adapter (Ref. Fig. 8-5). The adapters are shaped to accept the piston of a bottle jack. Page 701 SECTION 8 HANDLING, SERVICING, AND MAINTENANCE Figure 8-5. Single Wheel Jacking Issued: March 30, 2001 Report No: 02211 Revision 8: December 01, 2012 8-13... Page 702 SECTION 8 HANDLING, SERVICING, AND MAINTENANCE Figure 8-6. Main Jacking Points Report No: 02211 Issued: March 30, 2001 8-14 Revision 8: December 01, 2012... SECTION 8 HANDLING, SERVICING, AND MAINTENANCE PASSENGER SEAT REMOVAL AND INSTALLATION Pilots may remove and install passenger seats in accordance with the information given in Section 6 – Weight and Balance. SERVICING In addition to the inspection periods (detailed in Airplane Inspection) and the pre-flight inspections provided in Section 4 of this Handbook, complete servicing instructions are detailed in the AMM Chapter 12-00-00. Page 704 SECTION 8 HANDLING, SERVICING, AND MAINTENANCE A visual sight gauge is provided to allow the oil level to be checked without removing the dipstick. If the oil level is below the green band on the sight gauge the oil level has to be checked with the dipstick. Page 705 SECTION 8 HANDLING, SERVICING, AND MAINTENANCE OIL REPLENISHMENT PROCEDURE Open the left engine access panel and secure open with the struts. Use a ladder for better access to the filler cap/dipstick. Disconnect the electrical cannon plug. Release the locking mechanism and remove the filler cap/dipstick assembly from the filler neck on the filler neck on the accessory gearbox. Page 706 SECTION 8 HANDLING, SERVICING, AND MAINTENANCE FUEL SYSTEM The left and right wing fuel tanks are gravity filled through openings on the upper surface. The tanks should always be kept full between flights to reduce explosive vapor space and condensation. Allowance should be made for expansion to minimize venting of fuel if ambient temperature is expected to rise markedly. Page 707 SECTION 8 HANDLING, SERVICING, AND MAINTENANCE High frequency pulse transmissions in the vicinity of the airplane represents a fire hazard. During all refueling/defueling operations, fire fighting equipment must be available. FUELING PROCEDURE Make sure the fuel supplied is checked for type, grade and freedom from contamination. Page 708 SECTION 8 HANDLING, SERVICING, AND MAINTENANCE FUEL CONTAMINATION Fuel contamination is usually the result of foreign material present in the fuel system. This foreign material can take many forms, i.e. water, sand, dirt, microbes or bacterial growth. In addition, additives that are not compatible with the fuel used can cause the fuel to become contaminated. Page 709 SECTION 8 HANDLING, SERVICING, AND MAINTENANCE FUEL ANTI-ICING ADDITIVE WARNING OPERATING IN AMBIENT TEMPERATURES LESS THAN 0°C WITHOUT FOLLOWING THE PROCEDURE TO ADD ANTI-ICING ADDITIVES MAY LEAD TO ICE IN THE FUEL SYSTEM, WHICH MAY EVENTUALLY BLOCK DELIVERY LINES AND COMPONENTS OF THE FUEL SYSTEM, INCLUDING THE FUEL FILTER, SUBSEQUENTLY RESTRICTING OR STOPPING THE FLOW OF FUEL TO THE ENGINE. Page 710 SECTION 8 HANDLING, SERVICING, AND MAINTENANCE WARNING FUEL SYSTEM ANTI-ICING ADDITIVES CONTAIN ETHYLENE GLYCOL MONOMETHYL ETHER (EGME) DIETHYLENE GLYCOL MONOMETHYL ETHER (DIEGME), WHICH ARE HIGHLY TOXIC. THESE PRODUCTS MUST BE HANDLED WITH EXTREME CARE. AVOID ALL DIRECT CONTACT WITH SKIN AND CLOTHING. ANY CLOTHING ACCIDENTLY CONTAMINATED... Page 711 SECTION 8 HANDLING, SERVICING, AND MAINTENANCE LANDING GEAR - TIRES For maximum service, keep tires inflated to the proper pressures. All wheels and tires are balanced before original installation, and the relationship to tire and wheel should be maintained upon reinstallation. Unbalanced wheels can cause extreme vibration in the landing gear;... Page 712 SECTION 8 HANDLING, SERVICING, AND MAINTENANCE HYDRAULIC SYSTEM With the cargo door open, the hydraulic fluid level can be checked on the visual indicator installed on the hydraulic pressure tank in the wing root. Servicing of the hydraulic system should only be performed by approved personnel with the correct maintenance equipment in accordance with procedures in the AMM. Page 713 SECTION 8 HANDLING, SERVICING, AND MAINTENANCE OXYGEN SYSTEM The standard oxygen system replenishment is carried out at a hinged service panel (11BR) on the right side of the fuselage, forward of the wing leading edge. The service panel is fitted with an oxygen replenishment valve and a system pressure gage. The gage is marked from 0 to 2000 psi, with a red zone from 1850 to 2000 psi. Page 714 SECTION 8 HANDLING, SERVICING, AND MAINTENANCE CAUTION REPLENISHMENT OXYGEN SYSTEM SHOULD ONLY BE CARRIED OUT BY QUALIFIED PERSONNEL. Obtain the outside air temperature. (OAT). A fully charged cylinder has a pressure of 1841 psi at a temperature of 20°C. Filling pressures will vary depending upon the ambient temperature in the service bay and the temperature rise due to the compression of the oxygen. Page 715 SECTION 8 HANDLING, SERVICING, AND MAINTENANCE Temp (°C) Press (psig) 2419 2375 2331 2287 2242 2198 2153 2108 2063 2018 1974 1930 1885 1850 1841 1798 1755 1712 1669 1628 1586 1545 1505 1466 1426 1388 1351 1313 1275 1239 Figure 8-7. Page 716 SECTION 8 HANDLING, SERVICING, AND MAINTENANCE CLEANING AND CARE WINDSHIELD/SIDE WINDOWS CAUTION REMOVE WRIST-WATCHES, RINGS AND OTHER JEWELRY FROM HANDS AND WRISTS BEFORE CLEANING THE SIDE WINDOWS. WINDSHIELDS WINDOWS EASILY DAMAGED IMPROPER HANDLING CLEANING TECHNIQUES. DO NOT USE SOLVENTS, FUELS, DETERGENTS, ALCOHOL, ACETONE OR THINNERS TO CLEAN THE SIDE WINDOWS. Page 717 SECTION 8 HANDLING, SERVICING, AND MAINTENANCE Windshield (Glass) Place the airplane inside a hanger or in a shaded area and allow to cool from the heat of the sun's rays. Using clean (preferably running) water, flood the surface. Use bare clean hands, with no jewelry, to feel and dislodge any dirt or abrasive materials. Page 718 SECTION 8 HANDLING, SERVICING, AND MAINTENANCE EXTERIOR PAINT SURFACES The airplane should be washed with a mild soap and water solution. Harsh abrasives or alkaline soaps or detergents could make scratches on painted or plastic surfaces or cause corrosion of metal. Cover areas where cleaning solutions could cause damage. Exterior Recommended Cleaning Agents: ... Page 719 SECTION 8 HANDLING, SERVICING, AND MAINTENANCE DEICING BOOT CARE The wings, T-tail, and propeller deicing boots have a special electrical-conductive coating to bleed off static charges which cause radio interference and may perforate the boots. Fuelling and other servicing practices should be done carefully to avoid damaging the conductive coating or tearing of the boots. Page 720 SECTION 8 HANDLING, SERVICING, AND MAINTENANCE DEICING BOOT CARE The wings, T-tail, and propeller deicing boots have a special electrical-conductive coating to bleed off static charges which cause radio interference and may perforate the boots. Fueling and other servicing practices should be done carefully to avoid damaging the conductive coating or tearing of the boots. Page 721 SECTION 8 HANDLING, SERVICING, AND MAINTENANCE CAUTION AGE MASTER NO 1 STAINS SKIN, CLOTHING AND OTHER SURFACES. WEAR PLASTIC OR RUBBER GLOVES AND PROTECT SURROUNDING AREAS WHEN USING IT. USE WATERLESS HAND CLEANER TO REMOVE STAINING. IT IS NOT SUITABLE FOR THE USE ON ESTANE DE-ICERS AS IT WILL NOT BE ABSORBED BY THE DE-ICER, CAUSING RUN BACK AND STAINING ON THE AIRCRAFT SURFACE. Page 722 SECTION 8 HANDLING, SERVICING, AND MAINTENANCE PROPELLER CARE Propeller care consists of checking the propeller area for leaks and damage, this also includes any damage to the propeller hub and deicing boots. Inspect the visible hub parts daily for surface damage. Look for evidence of grease and or oil leaks. Inspect the propeller blades, daily, for scratches and gouges in the leading or trailing edge, or on the blade face and camber surfaces. Page 723 SECTION 8 HANDLING, SERVICING, AND MAINTENANCE ENGINE CARE The engine exterior and compartment may be cleaned, using a suitable solvent. Most efficient cleaning is done using a spry-type cleaner. Before spry cleaning, make sure the protection is afforded for components which might be adversely affected by the solvent. Refer to the AMM for proper lubrication of controls and components after engine cleaning. Page 724 SECTION 8 HANDLING, SERVICING, AND MAINTENANCE EXTENDED STORAGE Prolonged out-of-service care applies to all airplane which will not be flown for an indefinite period (less than 60 days) but which are to be kept ready-to-fly, with the least possible preparation. If the airplane is to be stored temporarily, or indefinitely, reference must be made to the AMM for the proper storage procedures, which are all time related and classified as follows: Stage 1... Page 725 The training must be given to the corrosion inspection procedures as detailed in the AMM. The inspection must be recorded in the aircrafts flight log book. If corrosion is evident or suspected, you must contact a Pilatus service center for further instructions. GEOGRAPHICAL LOCATION AND ENVIRONMENT... Page 726 SECTION 8 HANDLING, SERVICING, AND MAINTENANCE Moisture is in the air as a gas, water vapor or as finely divided droplets of liquid. These forms of moisture contain chemicals such as chlorides, sulfates and nitrates. When the moisture evaporates the chemicals remain on the surfaces. The moisture and the chemicals can be trapped in joints. Page 727 SECTION 9 SUPPLEMENTS SECTION 9 SUPPLEMENTS TABLE OF CONTENTS GENERAL 9-00-1 Mark X If Supp Subject Report No. INSTALLED Not applicable Not applicable Bendix/King KHF 950 Communications System 01973-001/9-3 Bendix/King KLN 90B GPS Navigation System 01973-001/9-4 Argus 5000 Electronic RMI/Moving Map Display 01973-001/9-5 Bendix / King Traffic Collision and Avoidance 01973-001/9-6... Page 728 SECTION 9 SUPPLEMENTS Mark X If Supp Subject Report No. INSTALLED Not applicable Not applicable Emergency Power System 01973-001/9-22 Multifunction Display (KMD 850) 01973-001/9-23 Enhanced Ground Proximity Warning System 01973-001/9-24 (EGPWS) PC-12 (4100 kg MTOW variant) 02211/9-25 Multi Hazard Awareness Processor KMH 820 02211/9-26 TAWS/TAS BF Goodrich WX-500 Stormscope System... Page 729 SECTION 9 SUPPLEMENTS GENERAL This section provides information in the form of supplements for the operation of the airplane when equipped with optional equipment or systems which are not installed on the standard airplane. All of the supplements are FOCA Approved and those that are applicable are part of this Handbook. Page 730 SECTION 9 SUPPLEMENTS INTENTIONALLY LEFT BLANK Report No: 02211 Issued: March 30, 2001 9-00-2 Revision 1: February 28, 2005... Page 732 This supplement supplies the information necessary for the operation of the airplane when the BENDIX/KING KHF 950 Communications System is installed in accordance with FOCA Approved Pilatus drawings. SECTION 2 - LIMITATIONS The KHF 950 Pilot's Guide (KPN 006-08343-0002 or 006-18038-0000 or laterr revisionss) must be immediately available to the pilot whenever this HF Communication System is used. Page 733 SECTION 9 SUPPLEMENT 3 SECTION 5 - PERFORMANCE No change. SECTION 6 - WEIGHT AND BALANCE Factory installed optional equipment is included in the licensed weight and balance data in Section 6 of the basic Pilot's Operating Handbook and FOCA approved Airplane Flight Manual. SECTION 7 - DESCRIPTION The High Frequency (HF) communication system gives long-distance voice communication between aircraft and a ground station. Page 734 SECTION 9 SUPPLEMENT 3 THIS PAGE INTENTIONALLY LEFT BLANK Report No: 01973-001 Issued: January 31, 1995 9-03-4 4 of 4 Revision 1: February 28, 2005... Page 735 This supplement must be attached to the Pilot's Operating Handbook and FOCA Approved Airplane Flight Manual when the Bendix/King KLN 90B Global Positioning System (GPS) is installed in accordance with Pilatus Drawings. The information contained herein supplements or supersedes the information in the basic Pilot's Operating Handbook and FOCA Approved Airplane Flight Manual only in those areas listed. Page 736 SECTION 9 SUPPLEMENT 4 INTENTIONALLY LEFT BLANK Report No: 01973-001 Issued: Mar 13, 1995 9-04-2 Revision 3: Sep 09, 2016... Page 737 SECTION 9 SUPPLEMENT 4 LIST OF EFFECTIVE PAGES Page No Rev No. 9-04-1 Title 9-04-2 thru 9-04-18 Issued: Mar 13, 1995 Report No: 01973-001 Revision 3: Sep 09, 2016 9-04-3... Page 738 SECTION 9 SUPPLEMENT 4 INTENTIONALLY LEFT BLANK Report No: 01973-001 Issued: Mar 13, 1995 9-04-4 Revision 3: Sep 09, 2016... Page 739 SECTION 9 SUPPLEMENT 4 LOG OF REVISIONS Revision Page Number Number Description and Date Sep 09, 2016 9-04-2 thru Introduction of List of Effective Pages and Log of Revisions. 9-04-6 9-04-9 Updated required software versions for B-RNAV to include later versions. Page 740 SECTION 9 SUPPLEMENT 4 INTENTIONALLY LEFT BLANK Report No: 01973-001 Issued: Mar 13, 1995 9-04-6 Revision 3: Sep 09, 2016... Page 741 SECTION 9 SUPPLEMENT 4 SECTION 1 - GENERAL This supplement supplies the information necessary for the operation of the airplane when the BENDIX/KING KLN 90B GPS Navigation System is installed in accordance with Modification Approval Sheet PIL 12/34/009. Issued: Mar 13, 1995 Report No: 01973-001 Revision 3: Sep 09, 2016 9-04-7... Page 742 SECTION 9 SUPPLEMENT 4 SECTION 2 - LIMITATIONS The KLN 90B GPS Pilot’s Guide, P/N 006-08773-0000, dated December, 1994 (or later applicable revision) must be immediately available to the flight crew whenever navigation is predicated on the use of the system. The Operational Revision Status (ORS) of the Pilot’s Guide must match the ORS level annunciated on the Self-Test page. Page 743 SECTION 9 SUPPLEMENT 4 The KLN 90B can only be used for approach guidance if the reference co-ordinate datum system for the instrument approach is WGS-84 or NAD-83. (All approaches in the KLN 90B data base use the WGS-84 or the NAD-83 geodetic datum.) The use of the KLN 90B to perform Basic RNAV (B-RNAV) operations in the designated European airspace is limited as follows:... Page 744 SECTION 9 SUPPLEMENT 4 If a “RAIM NOT AVAILABLE” message is displayed during B-RNAV operation, navigation may continue using KLN 90B provided cross-check with VOR, DME and NDB information shows adequate airplane positioning performance (RNP5). Otherwise, revert to an alternative means of navigation Refer to the KLN 90B Pilot’s Guide, Appendices B and C, for appropriate pilot actions to be accomplished in response to annunciated messages. Page 745 SECTION 9 SUPPLEMENT 4 The waypoint (WPT) annunciation on the EFIS display, will be activated prior to reaching a waypoint in the active flight plan. The KLN 90B GPS will provide navigation along a curved path segment to ensure a smooth transition between two adjacent legs in the flight plan. Page 746 SECTION 9 SUPPLEMENT 4 GPS approach (APR ARM/ACT) switch/annunciator - Used to a) manually select or deselect approach ARM (or deselect approach ACT) and b) annunciate the stage of approach operation either armed (ARM) or activated (ACT). Sequential button pushes if in ACT would first result in approach ARM and then approach arm cancelled. Page 747 SECTION 9 SUPPLEMENT 4 NOTE Using the right hand outer knob, select the ACT (Active Flight Plan Waypoints) pages. Pull the right hand inner knob out and scroll to the destination airport, then push the inner knob in and select the ACT 7 or ACT 8 page. To delete or replace a SID, STAR or approach, select FPL 0 page. Page 748 SECTION 9 SUPPLEMENT 4 NOTE Select HDG mode for DME arc intercepts. NAV or APR coupled DME arc intercepts can result in excessive overshoots (aggravated by high ground speeds and/or intercepts from inside the arc). WARNING FLYING FINAL OUTBOUND FROM AN OFF-AIRPORT VORTAC ON AN OVERLAY APPROACH;... Page 749 SECTION 9 SUPPLEMENT 4 NOTE There is no automatic LEG sequencing at the MAP. After climbing in accordance with the published missed approach procedure, press , verify or change the desired holding fix and press ENT. GENERAL NOTES • The data base must be up to date for non-precision instrument approach operation. Page 750 SECTION 9 SUPPLEMENT 4 • The DME arc IAF (arc intercept waypoint) will be: (a) On your present position radial off the arc VOR when you load the IAF into the flight plan. (b) The beginning of the arc if currently on a radial beyond the arc limit. Page 751 SECTION 9 SUPPLEMENT 4 • Flagged navigation inside the FAF may usually be restored (not guaranteed) by pressing the GPS APR button changing from ACT to ARM. Fly the missed approach. • The instrument approach using the KLN 90B may be essentially automatic starting 30 NM out (with a manual barometer setting update) or it may require judicious selection of the OBS and LEG modes. Page 752 SECTION 9 SUPPLEMENT 4 SECTION 7 DESCRIPTION The KLN 90B GPS panel mounted unit contains the GPS sensor, the navigation computer, a CRT display, and all controls required to operate the unit. It also houses the data base cartridge which plugs directly into the back of the unit. The data base cartridge is an electronic memory containing information on airports, navaids, intersections, SID’s, STAR’s, instrument approaches, special use airspace, and other items of value to the pilot. Page 775 SECTION 9 SUPPLEMENT 10 PILOT'S OPERATING HANDBOOK FOCA APPROVED AIRPLANE FLIGHT MANUAL SUPPLEMENT NO. 10 OPERATIONS IN COLD CONDITIONS This supplement must be attached to the Pilot's Operating Handbook and FOCA Approved Airplane Flight Manual when operating the PC-12, PC-12/45 and PC-12/47 in cold conditions with SB 25-002 modifications installed. Page 776 SECTION 9 SUPPLEMENT 10 THIS PAGE INTENTIONALLY LEFT BLANK Report No: 01973-001 Issued: Nov 20, 1996 9-10-2 Revision 2: September 05, 2016... Page 777 SECTION 9 SUPPLEMENT 10 LIST OF EFFECTIVE PAGES Page No Rev No. Page No. Rev No. 9-10-1 9-10-2 9- 10-3 9-10-4 thru 9-10-6 9-10-7 9-10-8 thru 9-10-12 9-10-13 9-10-14 Issued: Nov 20, 1996 Report No: 01973-001 Revision 3: December 18, 2020 9-10-3... Page 778 SECTION 9 SUPPLEMENT 10 THIS PAGE INTENTIONALLY LEFT BLANK Report No: 01973-001 Issued: Nov 20, 1996 9-10-4 Revision 2: September 05, 2016... Page 779 SECTION 9 SUPPLEMENT 10 LOG OF TEMPORARY REVISIONS The incorporation of temporary revisions into this supplement are to be recorded on the sheet below. Instructions for the removal of temporary revisions will be given in the instruction sheet issued with revisions. DATE OF CANCELLED TEMPORARY REVISION TITLE... Page 780 SECTION 9 SUPPLEMENT 10 THIS PAGE INTENTIONALLY LEFT BLANK Report No: 01973-001 Issued: Nov 20, 1996 9-10-6 Revision 2: September 05, 2016... Page 781 SECTION 9 SUPPLEMENT 10 LOG OF REVISIONS Revision Page Number Number Description and Date Supplement updated to new format: added LOEP, 05.09.2016 LOTR and LOR. Editorial and layout changes. 9-10-9 thru 9-10-14 115V Cold weather kit (SB 25-040) incorporated. The Revision Number 2 to AFM Supplement No. 10 is approved under the authority of DOA ref. Page 782 SECTION 9 SUPPLEMENT 10 THIS PAGE INTENTIONALLY LEFT BLANK Report No: 01973-001 Issued: Nov 20, 1996 9-10-8 Revision 2: September 05, 2016... Page 783 SECTION 9 SUPPLEMENT 10 SECTION 1 - GENERAL This supplement provides the information necessary to operate the PC-12, PC-12/45 and PC-12/47 aircraft in cold temperatures with a battery and an engine heater system installed (Post SB 25-002 and Post SB 25-040). SECTION 2 - LIMITATIONS OTHER LIMITATIONS OPERATIONS IN COLD CONDITIONS... Page 784 SECTION 9 SUPPLEMENT 10 SECTION 4 - NORMAL PROCEDURES GENERAL If the aircraft is to be parked outside for a period of time and the ambient ground temperature is expected to be: 0 to -15° C connect a 110/115 VAC ground power supply to the battery heater connector. Page 785 SECTION 9 SUPPLEMENT 10 SECTION 7 - SYSTEM DESCRIPTION BATTERY HEATER SYSTEM Description A belt type 110/115 VAC heating element is wrapped around the outside of the battery. A temperature sensor is attached to the aircraft skin and a wiring harness connects the temperature sensor to the battery heating element and the external power receptacle. Page 786 SECTION 9 SUPPLEMENT 10 SUPPLEMENTARY HEATER Supplementary ceramic element safety heater of 1500 Watts is placed in the center of the aircraft cabin to provide heating. The cabin heater is connected to the connector on the battery heating element wiring harness. CAUTIONS FOR A 110/115 VAC SYSTEM, THE CABIN HEATER CONNECTOR IS LIMITED TO A MAXIMUM OF... Page 787 SECTION 9 SUPPLEMENT 10 AIRPLANE EQUIPMENT LIST This list itemizes the equipment installed and required for operations in cold weather conditions. Mark ‘X’ ITEM PILATUS MASS Code PART NO. installed SERVICING Cold weather kit (110 VAC) Battery heater installation Tanis TAS200-03... Page 788 SECTION 9 SUPPLEMENT 10 THIS PAGE INTENTIONALLY LEFT BLANK Report No: 01973-001 Issued: Nov 20, 1996 9-10-14 Revision 2: September 05, 2016... Page 790 SECTION 9 SUPPLEMENT 11 INTENTIONALLY BLANK Report No: 01973-001 Issued: 9-11-1A Revision 7: May 08, 2012... Page 791 SECTION 9 SUPPLEMENT 11 LIST OF EFFECTIVE PAGES Page No. Rev No. 9-11-1 Title 9-11-1A 9-11-1B 9-11-1C thru 9-11-1E 9-11-1F 9-11-2 thru 9-11-6 9-11-7 thru 9-11-16 Issued: Report No: 01973-001 Revision 8: November 14, 2016 9-11-1B... Page 792 SECTION 9 SUPPLEMENT 11 INTENTIONALLY BLANK Report No: 01973-001 Issued: 9-11-1C Revision 7: May 08, 2012... Page 793 SECTION 9 SUPPLEMENT 11 LOG OF TEMPORARY REVISIONS The incorporation of temporary revisions into this supplement are to be recorded on the sheet below. Instructions for the removal of temporary revisions will be given in the instruction sheet issued with revisions. DATE CANCELLED TEMPORARY REVISION TITLE... Page 794 SECTION 9 SUPPLEMENT 11 INTENTIONALLY BLANK Report No: 01973-001 Issued: 9-11-1E Revision 7: May 08, 2012... Page 795 SECTION 9 SUPPLEMENT 11 LOG OF REVISIONS Revision Page Number Number Description and Date May 08, 2012 Pages 1A thru 1F issued. 9-11-7 Interior codes updated. 9-11-14 thru Page references updated. 9- 11-16 Approved under DOA No. EASA.21J.357 Nov 14, 2016 9-11-1B LOEP updated 9-11-1F... Page 796 SECTION 9 SUPPLEMENT 11 SECTION 2 - LIMITATIONS Service Bulletin 04-002 lists the aircraft tasks which must be done prior to the registration of the aircraft and the use of this Supplement in Canada. PC-12 CENTER OF GRAVITY LIMITS Weight Forward Limit Aft Limit Pounds (kilograms) Page 801 SECTION 9 SUPPLEMENT 11 SECTION 3 - EMERGENCY PROCEDURES 3.15 ELECTRICAL SYSTEM FAILURES For POH 01973-001: 3.15.1. ESNTL BUS A. Battery Bus Failure The following system remains operative: • Low airspeed warning For POH 02211: 3.15.2. ESNTL BUS A. Battery Bus Failure The following system remains operative: •... Page 802 SECTION 9 SUPPLEMENT 11 SECTION 6 - WEIGHT AND BALANCE Refer to POH Section 6, Interior Configurations and then to the applicable Interior Code No. for seat locations, permitted seat Part Nos. that can be installed, seat weight and moment charts and seat occupant moment charts. The following Interior Configurations are approved for PC-12, PC-12/45 and PC-12/47 use in Canada: Corporate Commuter Interior Code STD-9S (9 single seats) Page 803 SECTION 9 SUPPLEMENT 11 SECTION 6 - PC-12 WEIGHT AND BALANCE Figure 6-9. C. G. Envelope (9039 lb) (Sheet 1 of 2) Issued: March 5, 1997 Report No: 01973-001 Revision 8: November 14, 2016 9-11-9... Page 804 SECTION 9 SUPPLEMENT 11 Figure 6-9. C. G. Envelope (4100 kg) (Sheet 2 of 2) Report No: 01973-001 Issued: March 5, 1997 9-11-10 Revision 8: November 14, 2016... Page 805 SECTION 9 SUPPLEMENT 11 SECTION 6 - PC-12/45 WEIGHT AND BALANCE Figure 6-9. C. G. Envelope (9921 lb) (Sheet 1 of 2) Issued: March 5, 1997 Report No: 01973-001 Revision 8: November 14, 2016 9-11- 11... Page 806 SECTION 9 SUPPLEMENT 11 Figure 6-9. C. G. Envelope (4500 kg) (Sheet 2 of 2) Report No: 01973-001 Issued: March 5, 1997 9-11-12 Revision 8: November 14, 2016... Page 807 SECTION 9 SUPPLEMENT 11 SECTION 6 - PC-12/47 WEIGHT AND BALANCE Figure 6-9. C. G. Envelope (10450 lb) (Sheet 1 of 2) Issued: March 5, 1997 Report No: 01973-001 Revision 8: November 14, 2016 9-11-13... Page 808 SECTION 9 SUPPLEMENT 11 Figure 6-9. C. G. Envelope (4740 kg) (Sheet 2 of 2) Report No: 01973-001 Issued: March 5, 1997 9-11-14 Revision 8: November 14, 2016... Page 809 SECTION 9 SUPPLEMENT 11 SECTION 7 - AIRPLANE AND SYSTEMS DESCRIPTION SECTION 7-3 FLIGHT CONTROLS INDICATION / WARNING SYSTEM Page 7-3-5 The Central Advisory and Warning System (CAWS) annunciator panel includes a STAB TRIM warning light. The illumination of this warning caption will illuminate when the aircraft is on the ground for more than 60 seconds and the trim position is unsafe for takeoff. Page 810 SECTION 9 SUPPLEMENT 11 SECTION 7-34 AUTOPILOT INDICATION / WARNING Page 7-34-8 A/P DISENG caution is delayed 3 seconds in order to prevent aural warning conflict with the autopilot system. The caution will go off after 30 seconds. Report No: 01973-001 Issued: March 5, 1997 9-11-16 Revision 8: November 14, 2016... Page 816 SECTION 9 SUPPLEMENT 14 LIST OF EFFECTIVE PAGES Page No Rev No. 9-14-1 Title 9-14-1A 9-14-1B 9-14-2 9-14-3 Report No: 01973-001 Issued: Jul 20, 2011 9-14-1A... Page 817 SECTION 9 SUPPLEMENT 14 LOG OF REVISIONS Revision Page Number Number Description and Date Jul 20, 2011 9-14-1A and Page issued 9-14-1B 9-14-2 Documentary change - Bendix King document number removed. Approved under the Authority of DOA ref. EASA.21J.357 Issued: Jul 20, 2011 Report No: 01973-001 9-14-1B... Page 818 SECTION 9 SUPPLEMENT 14 SECTION 1 - GENERAL This supplement supplies the information necessary for the operation of the airplane when the dual system BENDIX/KING KT70 Mode S Air Traffic Control (ATC) transponder system is installed in accordance with Modification Approval Sheet PIL 12/34/040. Page 819 SECTION 9 SUPPLEMENT 14 SECTION 7 DESCRIPTION Two BENDIX/KING KT70 Mode S ATC transponder systems are installed in the aircraft. One is used as the main system, the other is used as a standby. A push-switch installed on the center instrument panel is used to select the ‘active’ transponder system. Page 836 SECTION 9 SUPPLEMENT 18 THIS PAGE INTENTIONALLY LEFT BLANK Report No: 01973-001 Issued: October 29, 1999 9-18-2 Revision 2: September 01, 2014... Page 837 SECTION 9 SUPPLEMENT 18 LIST OF EFFECTIVE PAGES Page No Rev No. Page No. Rev No. 9-18-1 9-18-2 9-18-3 9-18-4 thru 9-18-6 9-18-7 9-18-8 and 9-18-9 9-18-10 9-18-11 and 9-18-12 9-18-13 and 9-18-14 9-18-15 9-18-16 9-18-17 9-18-18 Issued: October 29, 1999 Report No: 01973-001 Revision 04: Dec 12, 2019 9-18-3... Page 838 SECTION 9 SUPPLEMENT 18 THIS PAGE INTENTIONALLY LEFT BLANK Report No: 01973-001 Issued: October 29, 1999 9-18-4 Revision 2: September 01, 2014... Page 839 SECTION 9 SUPPLEMENT 18 LOG OF TEMPORARY REVISIONS The incorporation of temporary revisions into this supplement are to be recorded on the sheet below. Instructions for the removal of temporary revisions will be given in the instruction sheet issued with revisions. DATE OF CANCELLED TEMPORARY REVISION TITLE... Page 840 SECTION 9 SUPPLEMENT 18 THIS PAGE INTENTIONALLY LEFT BLANK Report No: 01973-001 Issued: October 29, 1999 9-18-6 Revision 2: September 01, 2014... Page 841 SECTION 9 SUPPLEMENT 18 LOG OF REVISIONS Revision Page Number Number Description and Date 9-18-2 thru 9-18-18 Alternate placards added. Structure completely 01.09.2014 9-18-18 revised. New LOEP, LOTR and LOR. Editorial and layout changes. The Revision Number 2 to AFM Supplement No. 18 is approved under the authority of DOA ref. Page 842 SECTION 9 SUPPLEMENT 18 THIS PAGE INTENTIONALLY LEFT BLANK Report No: 01973-001 Issued: October 29, 1999 9-18-8 Revision 2: September 01, 2014... Page 843 SECTION 9 SUPPLEMENT 18 SECTION 1 - GENERAL This Airplane Flight Manual Supplement gives the information and lists the specifics necessary for the operation of the airplane on the French register in accordance with the requirements of the French DGAC. Issued: October 29, 1999 Report No: 01973-001 Revision 2: September 01, 2014... Page 844 SECTION 9 SUPPLEMENT 18 SECTION 2 – LIMITATIONS Service Bulletin 04-005 lists the modifications (tasks) that must be done before registration of the airplane in France and before use of this supplement. The three French DGAC-approved pages (Ref: Report 01973-001-FR, MANUEL DE VOL) must be attached to the original Swiss FOCA- approved Airplane Flight Manual (AFM) (Ref. Page 845 SECTION 9 SUPPLEMENT 18 On the cargo door: TIRER POUR OUVRIR (Accompanied by a downward pointing arrow) APPUYER ICI POUR OUVRIR LA PORTE TIRER LA POIGNÉE ET TIRER LA PORTE VERS L`EXTERIEUR NE PAS OUVRIR LA PORTE LORSQUE LE MOTEUR TOURNE SAUF EN CAS D`URGENCE On each side of the rudder, on the top surface of each aileron and three places on the top surface of each flap (total ten places):... Page 846 SECTION 9 SUPPLEMENT 18 On the rear of one of the nine passenger seats: LE MASQUE À OXYGÈNE SE TROUVE SOUS LE SIÈGE AVANT On the rear of the nine passenger seats: POUR LE DECOLLAGE ET L`ATTERRISSAGE - CEINTURE ATTACHÉE - DOSSIER EN POSITION VERTICALE FOR TAKEOFF AND LANDING - FASTEN SEAT BELT... Page 847 SECTION 9 SUPPLEMENT 18 On the left cockpit/cabin divider wall (continued): L`EXTINCTEUR EST SITUÉ SUR LE COTÉ DROIT DU COCKPIT DERRIÈRE LE SIÈGE DU CO- PILOTE FIRE EXTINGUISHER LOCATED ON COCKPIT SIDE R.H. BULK- HEAD BEHIND CO-PILOT SEAT (Accompanied by an arrow pointing to the right) On the emergency exit: TIRER / PULL (white letters, transparent background) SORTIE / EXIT... Page 848 SECTION 9 SUPPLEMENT 18 Interior Placards – Executive Configuration: On the passenger door: SORTIE / EXIT NE PAS OUVRIR EN VOL DO NOT OPERATE IN FLIGHT POUR OUVRIR LA PORTE LEVER LA POIGNÉE ET TOURNER TO OPEN LIFT LATCH ROTATE HANDLE OUVERT OPEN FERMÉ... Page 849 SECTION 9 SUPPLEMENT 18 Near each of six passenger seats: NE PAS FUMER LORS DE L`UTILISATION DE L`OXYGÈNE DO NOT SMOKE WHILE OXYGEN IS IN USE POUR LE DECOLLAGE ET L`ATTERRISSAGE - LE SIEGE DOIT ÊTRE COMPLÈTEMENT REDRESSÉ COMPLÈTEMENT EN ARRIÈRE COMPLÈTEMENT À... Page 850 SECTION 9 SUPPLEMENT 18 On the left cockpit/cabin divider wall: L`EXTINCTEUR EST SITUÉ SUR LE COTÉ DROIT DU COCKPIT DERRIÈRE LE SIÈGE DU CO-PILOTE FIRE EXTINGUISHER LOCATED ON COCKPIT SIDE R.H. BULK- HEAD BEHIND CO-PILOT SEAT (accompanied by an arrow pointing to the right) Report No: 01973-001 EASA Approved Issued: October 29, 1999... Page 851 SECTION 9 SUPPLEMENT 18 SECTION 7 – AIRPLANE AND SYSTEMS DESCRIPTION In the POH on page 7-34-3 the following Note is added after the HALF BANK paragraph: NOTE: Depending on course changes, Half Bank mode may lead to wide turns exceeding RNP-5 volumes. Page 852 SECTION 9 SUPPLEMENT 18 SECTION 9 – SUPPLEMENTS At the date of issue of this supplement, these are the FOCA-approved supplements (to the Airplane Flight Manual) that are also accepted by the DGAC for French registered airplanes: Original Subject Supp. Bendix/King RDS 82 VP Weather Radar Bendix/King KHF 950 Communications System Bendix/King KLN 90B GPS Navigation System... Page 893 SECTION 9 SUPPLEMENT 25 PILOT'S OPERATING HANDBOOK FOCA APPROVED AIRPLANE FLIGHT MANUAL SUPPLEMENT NO. 25 PC-12 (4100 KG MTOW VARIANT) FROM MSN 401 UPWARDS This supplement must be attached to the Pilot's Operating Handbook and FOCA Approved Airplane Flight Manual when operating the PC-12 at a weight of 4100 kg. Page 894 SECTION 9 SUPPLEMENT 25 INTENTIONALLY LEFT BLANK Report No: 02211-25 Issued: March 30, 2001 9-25-2 Revision 3: July 12, 2016... Page 895 SECTION 9 SUPPLEMENT 25 LIST OF EFFECTIVE PAGES Page No Rev No. 9-25-1 Title 9-25-2 9-25-3 thru 9-25-6 9-25-7 thru 9-25-10 9-25-11 thru 9-25-38 Issued: March 30, 2001 Report No: 02211-25 Revision 4: Oct 06, 2017 9- 25-3... Page 896 SECTION 9 SUPPLEMENT 25 INTENTIONALLY LEFT BLANK Report No: 02211-25 Issued: March 30, 2001 9-25-4 Revision 4: Oct 06, 2017... Page 897 SECTION 9 SUPPLEMENT 25 LOG OF REVISIONS Revision Page Number Number Description and Date Jul 12, 2016 9-25-2 thru Introduction of List of Effective Pages and Log of Revisions. 9-25-6 9-15-13 and Updated paragraph numbers due to introduction of new 9-15-14 paragraph 4.19 in POH 02211 resulting in renumbering of subsequent paragraphs (editorial change). Page 898 SECTION 9 SUPPLEMENT 25 Revision Page Number Number Description and Date 9-25-34 thru Text run on (editorial). Oct 06, 2017 9-25-38 (Continued) This revision 4 of AFM SUPPLEMENT 25 is approved under the Authority of DOA ref. EASA.21J.357 Date of Approval: 06 Oct, 2017 Report No: 02211-25 Issued: March 30, 2001 9-25-6... Page 899 SECTION 9 SUPPLEMENT 25 SECTION 1 - GENERAL MAXIMUM WEIGHTS Maximum Ramp Weight 9,083 lb (4,120 kg) Maximum Takeoff Weight 9,039 lb (4,100 kg) Maximum Landing Weight 9,039 lb (4,100 kg) Maximum Zero Fuel Weight 8,160 lb (3,700 kg) Maximum Cargo Weight Baggage Area 400 lb (180 kg) Cabin Area... Page 900 SECTION 9 SUPPLEMENT 25 SECTION 2 - LIMITATIONS AIRSPEED INDICATOR MARKINGS MARKING KIAS VALUE REMARKS OR RANGE Normal operating range. Lower limit is Green Arc 86 to 236 maximum weight stall speed in the clean configuration (V ). Upper limit is the maximum operating speed (V White Arc 59 to 130... Page 901 SECTION 9 SUPPLEMENT 25 CENTER OF GRAVITY LIMITS Weight Forward Limit Aft Limit Pounds (kilograms) A.O.D.: In. / M A.O.D.: In. / M 9083 (4120) 230.49 / 5.854 241.57 / 6.136 9039 (4100) 230.18 / 5.847 241.63 / 6.137 8160 (3700) 223.99 / 5.689 242.73 / 6.163 7938 (3600) Page 902 SECTION 9 SUPPLEMENT 25 PLACARDS On the main landing gear doors: TYRE PRESSURE 55 PSI On the instrument panel: (4100 KG) KIAS (2600 KG) KIAS KIAS 0.48 On the left and right cargo door frame: MAX FREIGHT LOAD = 1000 kg / 2200 lb Max Load on Max Load on Seat Rails... Page 903 SECTION 9 SUPPLEMENT 25 SECTION 3 - EMERGENCY PROCEDURES AIRSPEEDS FOR EMERGENCY OPERATIONS All airspeeds shown are with airplane in clean configuration under ISA conditions. Landing Approach Speeds with ice accretion on the airframe: After failure of: Minimum Approach Speed: Pneumatic Deice Boots (flap position limit 0°) 124 KIAS... Page 904 SECTION 9 SUPPLEMENT 25 EMERGENCY LANDING 3.9.1 GLIDE DISTANCE AND SPEED 4. Best glide speed 110 KIAS for 9039 lb (4100 kg) (for best glide speed see para 3.2.B) 3.9.2 FORCED LANDING (ENGINE CUT-OFF/FEATHER) 6. Best glide speed 110 KIAS for 9039 lb (4100 kg) (for best glide speed see para 3.2.B) 13. Page 905 SECTION 9 SUPPLEMENT 25 SECTION 4 - NORMAL PROCEDURES AIRSPEEDS FOR NORMAL OPERATIONS Airspeeds for normal operations are listed below. Unless otherwise noted, all airspeeds are based on a maximum takeoff weight of 9039 lb (4100 kg) at sea level under ISA standard day conditions. Takeoff (V Flaps 15°... Page 906 SECTION 9 SUPPLEMENT 25 4.24 FLIGHT IN ICING CONDITIONS The minimum recommended speeds for icing encounters and with residual ice on the airframe are: Climb, Flaps 0°, Pusher Ice Mode = 135 KIAS Holding Pattern, Flaps 0° = 140 KIAS to 170 KIAS Landing Approach, Flaps 15°, Pusher Ice Mode = 100 KIAS Landing Approach, Flaps 0°, Boot Failure Pusher Ice Mode... Page 907 SECTION 9 SUPPLEMENT 25 SECTION 5 - PERFORMANCE GENERAL The performance information presented in Section 5 of this POH can be used for aircraft operation but is limited to an aircraft Maximum Takeoff Weight of 4100 kg (9039 lb). FLIGHT IN ICING CONDITIONS The following section presents performance information related to the operation in or into known icing conditions. Page 908 SECTION 9 SUPPLEMENT 25 STALL SPEEDS When operating in STICK PUSHER ICE MODE the stick pusher computer automatically reduces the shaker and pusher settings, as measured by the angle of attack vanes, by 8°. With operational pneumatic de-ice boots, this results in an increase of the stall speed at the maximum takeoff weight of 12 kts with flaps set to 0°... Page 909 SECTION 9 SUPPLEMENT 25 The total takeoff distance is calculated by first computing the total takeoff distance in non- icing conditions from Figure 5-27 (standard units) or Figure 5-28 (metric units) and then correcting that distance for takeoff in or into known icöing conditions by using the corrections in Table 2. Page 910 SECTION 9 SUPPLEMENT 25 Analogically, the takeoff ground roll is derived correcting the distances obtained from Figure 5-25 (standard units) or Figure 5-26 (metric units) by using Table 3. Table 3 - Icing Corrections to Takeoff Ground Roll TABLE A TAKEOFF WEIGHT - KG ALTITUDE CORRECTION (%) 2900... Page 911 SECTION 9 SUPPLEMENT 25 Example: • Pressure Altitude 6000 ft • Outside Air Temperature 18°C • Weight 3500 kg • Headwind Component 8 kt • Uphill Component Takeoff Ground Roll 450 m (from Figure 5-26) • • Icing Correction (A + B +C) = 28.5% + 1.6% + 0.5% = 30.6% •... Page 912 SECTION 9 SUPPLEMENT 25 Table 4 - Icing Corrections to Accelerate Stop Distance TABLE A TAKEOFF WEIGHT - KG ALTITUDE CORRECTION (%) 2900 3300 3700 4100 POWER CHOP SPEED (KIAS) 0 FT 2000 FT 4000 FT 6000 FT 8000 FT 10000 FT 12000 FT 14000 FT... Page 913 SECTION 9 SUPPLEMENT 25 MAXIMUM RATE OF CLIMB The use of Flaps 30° is prohibited in or into known icing conditions. After icing encounters, and with visible ice accretion on the airframe, a climb is performed with the flaps retracted and a climb speed based on the schedule below. Page 914 SECTION 9 SUPPLEMENT 25 Table 7 - Icing Corrections to Maximum Rate of Climb with Pneumatic De-ice Boots Inoperative RATE OF CLIMB CORRECTION (FEET PER MINUTE) TAKEOFF WEIGHT - KG ALTITUDE - FT 2900 3500 4100 -1510 -1270 -1090 5000 -1640 -1370 -1180... Page 915 SECTION 9 SUPPLEMENT 25 Table 9 - Icing Corrections to Holding Fuel Flow with Pneumatic De-ice Boots Inoperative FUEL FLOW CORRECTION (%) AIRCRAFT WEIGHT - KG ALTITUDE - FT 2900 - 4100 0 FT 5000 FT 10000 FT 15000 FT 6393 - 9039 ALTITUDE - FT AIRCRAFT WEIGHT - LB... Page 916 SECTION 9 SUPPLEMENT 25 After failure of the airframe pneumatic boots in icing conditions, a balked landing climb is performed with Flaps 0° and a climb speed of 130 KIAS. The total climb performance is calculated by first computing the Rate of Climb in non-icing conditions from Figure 5- 62 (standard units) or Figure 5-63 (metric units) and then correcting the Rate of Climb in or into known icing conditions by using the corrections in the Table 11. Page 917 SECTION 9 SUPPLEMENT 25 LANDING PERFORMANCE The flaps must be set to 15° for landing. The use of Flaps 30° or 40° for landing is prohibited. With pneumatic de-ice boots failed; a flaps-up-landing must be performed. For both flap configurations, the landing reference speed must be adjusted to the values indicated by the corresponding correction table. Page 918 SECTION 9 SUPPLEMENT 25 Table 13 - Icing Corrections to Landing Total Distance – Flaps 15° - No Reverse Thrust TABLE A LANDING WEIGHT - KG ALTITUDE CORRECTION (%) 2900 3300 3700 4100 (KIAS) 0 FT 2000 FT 4000 FT 6000 FT 8000 FT 10000 FT... Page 919 SECTION 9 SUPPLEMENT 25 Table 14- Icing Corrections to Landing Ground Roll – Flaps 15° - No Reverse Thrust TABLE A LANDING WEIGHT - KG ALTITUDE CORRECTION (%) 2900 3300 3700 4100 (KIAS) 0 FT 2000 FT 4000 FT 6000 FT 8000 FT 10000 FT 12000 FT... Page 920 SECTION 9 SUPPLEMENT 25 Table 15 - Icing Corrections to Landing Total Distance – Flaps 0° - No Reverse Thrust TABLE A LANDING WEIGHT - KG ALTITUDE CORRECTION (%) 2900 3300 3700 4100 (KIAS) 0 FT +103 2000 FT +101 +105 4000 FT +100... Page 921 SECTION 9 SUPPLEMENT 25 Table 16 - Icing Corrections to Landing Ground Roll – Flaps 0° - No Reverse Thrust TABLE A LANDING WEIGHT - KG ALTITUDE CORRECTION (%) 2900 3300 3700 4100 (KIAS) 0 FT +103 +115 +117 +113 2000 FT +105 +116... Page 922 SECTION 9 SUPPLEMENT 25 Table 17 - Icing Corrections to Landing Total Distance – Flaps 15° - With Reverse Thrust TABLE A LANDING WEIGHT - KG ALTITUDE CORRECTION (%) 2900 3300 3700 4100 (KIAS) 0 FT 2000 FT 4000 FT 6000 FT 8000 FT 10000 FT... Page 923 SECTION 9 SUPPLEMENT 25 Table 18 - Icing Corrections to Landing Ground Roll – Flaps 15° - With Reverse Thrust TABLE A LANDING WEIGHT - KG ALTITUDE CORRECTION (%) 2900 3300 3700 4100 (KIAS) 0 FT 2000 FT 4000 FT 6000 FT 8000 FT 10000 FT... Page 924 SECTION 9 SUPPLEMENT 25 Table 19 - Icing Corrections to Landing Total Distance – Flaps 0° - With Reverse Thrust TABLE A LANDING WEIGHT - KG ALTITUDE CORRECTION (%) 2900 3300 3700 4100 (KIAS) 0 FT 2000 FT 4000 FT 6000 FT +100 8000 FT... Page 925 SECTION 9 SUPPLEMENT 25 Table 20 - Icing Corrections to Landing Ground Roll – Flaps 0° - With Reverse Thrust TABLE A LANDING WEIGHT - KG ALTITUDE CORRECTION (%) 2900 3300 3700 4100 (KIAS) 0 FT +102 +103 2000 FT +103 +101 4000 FT... Page 926 SECTION 9 SUPPLEMENT 25 SECTION 6 - WEIGHT AND BALANCE PC-12 EXAMPLE LOADING FORM INTERIOR CODE: STD-9S ITEM WEIGHT ARM AFT OF MOMENT DATUM in (m) lb-in 5613 225.16 (5.719) 1263823 1. Basic Empty Weight 2. Combi Interior Conversion 3. Pilot 160.27 (4.071) 27246 4. Page 927 SECTION 9 SUPPLEMENT 25 PC-12 LOADING FORM INTERIOR CODE: ITEM WEIGHT ARM AFT OF MOMENT lb (kg) DATUM in (m) lb-in (kg-m) 1. Basic Empty Weight 2. Combi Interior Conversion 3. Pilot 160.27 (4.071) 4. Copilot (Right Seat Passenger) 160.27 (4.071) 5. Page 928 SECTION 9 SUPPLEMENT 25 Figure 6-9. C. G. Envelope (Sheet 1 of 2) Report No: 02211-25 Issued: March 30, 2001 9-25-36 EASA Approved Revision 4: Oct 06, 2017... Page 929 SECTION 9 SUPPLEMENT 25 Figure 6-9. C. G. Envelope (Sheet 2 of 2) Issued: March 30, 2001 Report No: 02211-25 Revision 4: Oct 06, 2017 EASA Approved 9- 25-37... Page 930 SECTION 9 SUPPLEMENT 25 SECTION 8 HANDLING, SERVICING AND MAINTENANCE LANDING GEAR - TIRES Main Wheel Tires Wheel type - BFG PN3-1543 Tire type - 8.50-10, 10PR, TL (160 mph) Tire pressure - 55 + 3 - 0 psi (3.8 + 0.2 - 0 bar) Report No: 02211-25 Issued: March 30, 2001 9-25-38... Page 932 SECTION 9 SUPPLEMENT 26 SECTION 1 - GENERAL This supplement supplies the information necessary for the operation of the airplane when the Multi Hazard Awareness Processor (KMH 820) is installed in accordance with Modification Approval Sheet PIL 12/34/123. The KMH 820 Multi Hazard Awareness Processor provides Terrain Awareness and Warning (TAWS) and Traffic Advisory (TAS) functions combined within the same processor. Page 933 SECTION 9 SUPPLEMENT 26 NOTE The Terrain Awareness Display is intended to serve as a situational awareness tool only. It may not provide either the accuracy and/or fidelity on which to solely base terrain or obstacle avoidance maneuvering decisions. SECTION 3 – EMERGENCY PROCEDURES For ditching or other off-airport landings, inhibit the TAWS aural alert functions by selecting the TERR INHIBIT switch on the pilots instrument panel to ON (annunciated). Page 934 SECTION 9 SUPPLEMENT 26 INDICATORS AND CONTROLS All TAS indication and control is via the MFD option. Refer to the Bendix/King KTA870/KMH880 Traffic Advisory System/Multi Hazard Awareness System Pilot’s Guide, Honeywell part number 006-18265-0000 Revision 0, dated 03/2001, or later revision. Also refer to the KMD 550/850 Traffic Avoidance Function (TCAS/TAS) Pilots Guide Addendum, Honeywell part number 006- 18238-0000, Revision 0, dated April/2001, or later revision. Page 935 SECTION 9 SUPPLEMENT 26 i.e. runways shorter than 2000 feet. The terrain inhibit switch should not be operated for normal flight operations. The TERR P/TEST / TERR INOP switch annunciator is a momentary action switch with a horizontally split screen annunciator, which is installed in the line of sight. When not illuminated, the upper TERR P/TEST legend consists of white letters on a black background. Page 936 SECTION 9 SUPPLEMENT 26 RESPONSE TO ALERTS TAS ALERTS Traffic Advisory annunciations (TA) are shown in the following table. Aural Visual Pilot Response TRAFFIC, TRAFFIC A filled yellow circle on the Conduct a visual search for traffic display. the intruder. If successful, maintain visual acquisition to ensure safe operation NOTE... Page 937 SECTION 9 SUPPLEMENT 26 NOTES Traffic Advisories can be expected to occur during normal flight operation. Generally TA’s will occur more frequently in terminal areas during arrival, and less frequently during departure and enroute operations. In the vast majority of these cases, the aircraft displayed will be safely separated and there will be no need for pilots to initiate any avoidance maneuvers. Page 938 SECTION 9 SUPPLEMENT 26 TAWS ALERTS Respond to TAWS alerts as follows: WARNING ALERT When an aural PULL UP warning TERRAIN TERRAIN PULL UP or OBSTACLE OBSTACLE PULL UP occurs, the following procedure should be followed: Level the wings, simultaneously adding maximum power. Smoothly pitch up at a rate of 2 to 3 degrees per second towards an initial target pitch attitude of 15 degrees nose up. Page 939 SECTION 9 SUPPLEMENT 26 CAUTION ALERT When an aural CAUTION TERRAIN or a CAUTION OBSTACLE alert occurs, take positive action until the alert ceases. Stop descending, or initiate a climb and/or turn as necessary, based on the analysis of all available instruments and information. Selecting other display pages does not disable the terrain function as evidenced by the black on gray terrain icon displayed on the icon bar. Page 940 SECTION 9 SUPPLEMENT 26 • An aural TAWS SYSTEM OK message is given over the cockpit speaker • The red TERR warning light extinguishes and amber TERR caution light illuminates • A terrain self-test pattern appears on the MFD • The terrain self-test pattern disappears after several sweeps of the terrain display •... Page 941 SECTION 9 SUPPLEMENT 26 SECTION 7 - SYSTEM DESCRIPTION MULTI-HAZARD AWARENESS SYSTEM (KMH 820) Ref. Fig 7-1 The KMH 820 Multi Hazard Awareness Processor (TAWS/TAS) consists of a processor, two directional Antennas (Upper and Lower), a dedicated GPS antenna (Upper) and a configuration Module. Page 942 SECTION 9 SUPPLEMENT 26 GPS ANTENNA TAS ANTENNA TOP 28 VDC TAWS/ 28 VDC I/P GPS ANT I/P SUPPRESSION 28 VDC RTN TRANSPONDER CHASSIS GND CONFIG MODULE SUPPRESSION SUPPRESSION I/O A/C FLIGHT A/C CONFIGURATION I/P PARAMETERS CAWS AHRS 1 AUDIO AUDIO INHIBIT O/P INHIBIT I/P A429 Tx... Page 943 SECTION 9 SUPPLEMENT 26 The TAS is capable of surveillance of aircraft equipped with transponders (i.e. Mode S and Mode C) able to reply to ATCRBS Mode C interrogations in their operational environments. The TAS system is unable to detect any intruding aircraft without an operating transponder. The TAS portion of the KMH 820 processor provides the flight crew with situational awareness and position information for transponder equipped aircraft in proximity to their own aircraft. Page 944 SECTION 9 SUPPLEMENT 26 aircraft sensors and processed to determine if the aircraft is in danger. The TAWS is uniquely configured for operation in the PC-12 by programming a system configuration module with PC- 12 specific parameters. The TAWS portion of the KMH 820 comprises the following functions; •... Page 945 SECTION 9 SUPPLEMENT 26 When the TAWS initiates an aural alert an audio inhibit discrete ground is output to the CAWS system, which suppresses any aural callout initiated by the CAWS for the duration of the TAWS aural alert. The TAWS is internally configured to suppress any TAS aural alerts for the duration of any TAWS aural alerts. Page 946 SECTION 9 SUPPLEMENT 26 When the TAWS initiates an aural alert an audio inhibit discrete ground is output to the CAWS system, which suppresses any aural callout initiated by the CAWS for the duration of the TAWS aural alert. The TAWS is internally configured to suppress any TAS aural alerts for the duration of any TAWS aural alerts. Page 948 SECTION 9 SUPPLEMENT 27 SECTION 1 - GENERAL This supplement supplies the information necessary for the operation of the airplane when the BFGOODRICH WX500 Stormscope System is installed in accordance with Modification 02- 0089. SECTION 2 - LIMITATIONS No change. SECTION 3 - EMERGENCY PROCEDURES No change. Page 949 SECTION 9 SUPPLEMENT 27 SECTION 7 – DESCRIPTION DESCRIPTION The Stormscope System detects lightning activity 360 degrees around the aircraft up to a distance of 200 nautical miles. The stormscope antenna installed on the bottom of the fuselage detects intra-cloud, inter-cloud or cloud-to-ground electrical discharges and sends the resulting discharge signals to the processor. Page 950 SECTION 9 SUPPLEMENT 27 Strike Display Mode In the strike display mode a X symbol (discharge point) is shown on the MFD when the strormscope system detects a discharge within the selected range and view. The strike display mode shows the discharge points on the MFD in relation to where the discharges are actually detected instead of close to an associated group as is done in the cell display mode. Page 952 SECTION 9 SUPPLEMENT 28 SECTION 1 - GENERAL This supplement supplies the information necessary for the operation of the airplane when DC-DC Converter and 12V DC power outlets are installed. SECTION 2 - LIMITATIONS The cabin placards: Near each 12 VDC power outlet: MAX 5 A DO NOT USE DURING... Page 953 SECTION 9 SUPPLEMENT 28 SECTION 5 - PERFORMANCE No change. SECTION 6 - WEIGHT AND BALANCE Converter weight and moment PC-12/45 ITEM WEIGHT LB (KG) MOMENT LB/IN (KG/M) Converter RG 40 (1.6) 1084.449 (12.592) SECTION 7 - SYSTEM DESCRIPTION The DC-DC converter and the six 12V DC power outlets give the facility for passengers to operate portable electronic equipment in the cabin. Page 954 SECTION 9 SUPPLEMENT 28 SECTION 5 - PERFORMANCE No change. SECTION 6 - WEIGHT AND BALANCE Converter weight and moment PC-12/45 ITEM WEIGHT LB (KG) MOMENT LB/IN (KG/M) Converter RG 40 (1.6) 1084.449 (12.592) SECTION 7 - SYSTEM DESCRIPTION The DC-DC converter and the six 12V DC power outlets give the facility for passengers to operate portable electronic equipment in the cabin. Page 972 SECTION 9 SUPPLEMENT 33 THIS PAGE INTENTIONALLY LEFT BLANK Report No: 02211 Issued: November 8, 2005 9-33-2 Revision 3: September 01, 2014... Page 973 SECTION 9 SUPPLEMENT 33 LIST OF EFFECTIVE PAGES Page No Rev No. Page No. Rev No. 9-33-1 9-33-2 9-33-3 9-33-4 9-33-5 and 9-33-6 9-33-7 9-33-8 9-33-9 thru 9-33-13 9-33-14 thru 9-33-21 9-33-22 9-33-23 thru 9-33-40 Issued: November 8, 2005 Report No: 02211 Revision 6: December 18, 2020 9-33-3... Page 974 SECTION 9 SUPPLEMENT 33 INTENTIONALLY LEFT BLANK Report No: 02211 Issued: November 8, 2005 9-33-4 Revision 5: Oct 06, 2017... Page 975 SECTION 9 SUPPLEMENT 33 LOG OF TEMPORARY REVISIONS The incorporation of temporary revisions into this supplement are to be recorded on the sheet below. Instructions for the removal of temporary revisions will be given in the instruction sheet issued with revisions. DATE OF CANCELLED TEMPORARY REVISION TITLE... Page 976 SECTION 9 SUPPLEMENT 33 THIS PAGE INTENTIONALLY LEFT BLANK Report No: 02211 Issued: November 8, 2005 9-33-6 Revision 3: September 01, 2014... Page 977 SECTION 9 SUPPLEMENT 33 LOG OF REVISIONS Revision Page Number Number Description and Date 9-33-2 thru 9-33-22 Arm value correction. MTOW and Loading form values 01.09.2014 corrected. New LOEP, LOTR and LOR. Editorial and layout changes. The Revision Number 3 to AFM Supplement No. 33 is approved under the authority of DOA ref. Page 978 SECTION 9 SUPPLEMENT 33 Revision Page Number Number Description and Date 9-33-16 17058 - Paragraph 3.13 added which details PC-12/47 06.10.2017 flap settings and speeds during an inadvertent (Continued) pusher/shaker operation situation. 17188 - Minimum landing approach speed updated at paragraph 3.19.2 17301 - (MTOW) reference added to paragraphs 3.9.8 and 3.9.9... Page 979 SECTION 9 SUPPLEMENT 33 SECTION 1 - GENERAL MAXIMUM WEIGHTS Maximum Ramp Weight 10495 lb (4760 kg) Maximum Takeoff Weight 10450 lb (4740 kg) Maximum Landing Weight 9921 lb (4500 kg) TYPICAL AIRPLANE WEIGHTS Useful Load 4982 lb (2260 kg) SPECIFIC LOADINGS Wing Loading 37.6 lb/sq ft (183.7 kg/sq m) Page 980 SECTION 9 SUPPLEMENT 33 Figure 1-1. Airplane Three View and Dimensions Report No: 02211 Issued: November 8, 2005 9-33-10 Revision 3: September 01, 2014... Page 981 SECTION 9 SUPPLEMENT 33 SECTION 2 - LIMITATIONS AIRSPEED LIMITATIONS AIRSPEED KCAS KIAS SIGNIFICANCE Maximum Operating Do not make full or abrupt control Maneuvering Speed - V movements above this speed. 10450 lb (4740 kg) AIRSPEED INDICATOR MARKINGS MARKING KIAS VALUE REMARKS OR RANGE Normal operating range. Page 982 SECTION 9 SUPPLEMENT 33 CENTER OF GRAVITY LIMITS Weight Forward Limit Aft Limit Pounds (kilograms) A.O.D.: In. / M A.O.D.: In. / M 10450 (4740) 232.20 / 5.898 240.43 / 6.107 9921 (4500) 232.20 / 5.898 240.94 / 6.120 8158 (3700) 224.13 / 5.693 7938 (3600) 242.99 / 6.172... Page 983 SECTION 9 SUPPLEMENT 33 OTHER LIMITATIONS PC-12/47 AIRCRAFT The aircraft must be operated in accordance with this Supplement when the Identification Plate installed on the lower left side of the fuselage aft of the cargo door defines the Model Designation as PC-12/47. CREW SEATS Pilot crew seat Part No. Page 984 SECTION 9 SUPPLEMENT 33 SECTION 3 - EMERGENCY PROCEDURES AIRSPEEDS FOR EMERGENCY OPERATIONS All airspeeds shown are with airplane in clean configuration under ISA conditions. Operating Maneuvering Speed (V 10450 lb (4740 kg) 163 KIAS Best Glide (Propeller feathered): 10450 lb (4740 kg) 116 KIAS Landing Approach Speeds with ice accretion on the airframe (based on Maximum Landing Weight (MLW) of 9921 lb / 4500 kg):... Page 985 SECTION 9 SUPPLEMENT 33 EMERGENCY DESCENT 3.8.2 MAXIMUM RANGE DESCENT - AFTER ENGINE FAIL – SINGLE BATTERY 4. Speed 116 KIAS for 10450 lb (4740 kg) (for lighter aircraft weights refer POH, Sect 3, para 3.2.B) (in icing conditions 140 KIAS) 3.8.3 MAXIMUM RANGE DESCENT - AFTER ENGINE FAIL –... Page 986 SECTION 9 SUPPLEMENT 33 3.9.8 LANDING WITHOUT FLAPS 3. Final approach speed 121 KIAS for 10450 lb (4740 kg) (MTOW) 3.9.9 DITCHING 4. Final approach speed 86 KIAS for 10450 lb (4740 kg) (MTOW) 3.12 STICK PUSHER FAILURE IN FLIGHT: 3. Page 987 SECTION 9 SUPPLEMENT 33 3.19.5 AOA PROBE DEICE FAILURE IN ICING CONDITIONS 9. Landing approach Keep minimum landing approach for 9921 lb (4500 kg) (MLW) speed above 105 KIAS or shaker activation speed, whichever is highest. 3.19.7 PUSHER ICE MODE FAILURE IN ICING CONDITIONS 9. Page 988 SECTION 9 SUPPLEMENT 33 FLIGHT IN ICING CONDITIONS The following section presents performance information related to the operation in or into known icing conditions. This information was derived analytically from actual wind tunnel tests with natural ice. The following cases are considered: •... Page 989 SECTION 9 SUPPLEMENT 33 ENGINE TORQUE When the engine inlet inertial separator is open and during flight, the maximum torque available can be reduced by up to 2.2 psi in non-icing conditions, and up to 3.0 psi in icing conditions. TAKEOFF PERFORMANCE The flaps must be set to 15°... Page 990 SECTION 9 SUPPLEMENT 33 The total takeoff distance is calculated by first computing the total takeoff distance in non-icing conditions from Figure 5-27 (standard units) or Figure 5-28 (metric units) and then correcting that distance for takeoff in or into known icing conditions by using the corrections in Table 2. Page 991 SECTION 9 SUPPLEMENT 33 Analogically, the takeoff ground roll is derived correcting the distances obtained from Figure 5- 25 (standard units) or Figure 5-26 (metric units) by using Table 3. Table 3 - Icing Corrections to Takeoff Ground Roll TABLE A TAKEOFF WEIGHT - KG ALTITUDE 2900... Page 992 SECTION 9 SUPPLEMENT 33 Example: Pressure Altitude 6000 ft Outside Air Temperature 18°C Weight 3500 kg Headwind Component 8 kt Uphill Component Takeoff Ground Roll 450 m (from Figure 5-26) Icing Correction (A + B +C) = 28.5% + 1.6% + 0.5% = 30.6% ... Page 993 SECTION 9 SUPPLEMENT 33 Table 4 - Icing Corrections to Accelerate Stop Distance TABLE A TAKEOFF WEIGHT - KG ALTITUDE CORRECTION (%) 2900 3300 3700 4100 4500 4740 POWER CHOP SPEED (KIAS) 0 FT 2000 FT 4000 FT 6000 FT 8000 FT 10000 FT 12000 FT... Page 994 SECTION 9 SUPPLEMENT 33 MAXIMUM RATE OF CLIMB The use of Flaps 30° is prohibited in or into known icing conditions. After icing encounters, and with visible ice accretion on the airframe, a climb is performed with the flaps retracted and a climb speed based on the schedule below. Table 5 - Climb Speed in Icing Conditions PNEUMATIC DE-ICE FLAPS UP... Page 995 SECTION 9 SUPPLEMENT 33 Table 7 - Icing Corrections to Maximum Rate of Climb with Pneumatic De-ice Boots Inoperative RATE OF CLIMB CORRECTION (FEET PER MINUTE) TAKEOFF WEIGHT - KG ALTITUDE - FT 2900 3500 4500 4740 -1510 -1270 -980 -920 -1640 -1370... Page 996 SECTION 9 SUPPLEMENT 33 Table 9 - Icing Corrections to Holding Fuel Flow with Pneumatic De-ice Boots Inoperative FUEL FLOW CORRECTION (%) AIRCRAFT WEIGHT - KG ALTITUDE - FT 2900 - 4740 0 FT 5000 FT 10000 FT 15000 FT 6393 - 10450 ALTITUDE - FT AIRCRAFT WEIGHT - LB... Page 997 SECTION 9 SUPPLEMENT 33 After failure of the airframe pneumatic boots in icing conditions, a balked landing climb is performed with Flaps 0° and a climb speed of 130 KIAS. The total climb performance is calculated by first computing the Rate of Climb in non-icing conditions from Figure 5- 62 (standard units) or Figure 5-63 (metric units) and then correcting the Rate of Climb in or into known icing conditions by using the corrections in the Table 11. Page 998 SECTION 9 SUPPLEMENT 33 LANDING PERFORMANCE The flaps must be set to 15° for landing. The use of Flaps 30° or 40° for landing is prohibited. With pneumatic de-ice boots failed, a flaps-up-landing must be performed. For both flap configurations, the landing reference speed must be adjusted to the values indicated by the corresponding correction table. Page 999 SECTION 9 SUPPLEMENT 33 Table 13 - Icing Corrections to Landing Total Distance – Flaps 15° - No Reverse Thrust TABLE A LANDING WEIGHT - KG ALTITUDE CORRECTION (%) 2900 3300 3700 4100 4500 (KIAS) 0 FT 2000 FT 4000 FT 6000 FT 8000 FT 10000 FT... Page 1000 SECTION 9 SUPPLEMENT 33 Table 14- Icing Corrections to Landing Ground Roll – Flaps 15° - No Reverse Thrust TABLE A LANDING WEIGHT - KG ALTITUDE CORRECTION (%) 2900 3300 3700 4100 4500 (KIAS) 0 FT 2000 FT 4000 FT 6000 FT 8000 FT 10000 FT... Page 1001 SECTION 9 SUPPLEMENT 33 Table 15 - Icing Corrections to Landing Total Distance – Flaps 0° - No Reverse Thrust TABLE A LANDING WEIGHT - KG ALTITUDE CORRECTION (%) 2900 3300 3700 4100 4500 (KIAS) +103 +107 0 FT 2000 FT +101 +105 +109... Page 1002 SECTION 9 SUPPLEMENT 33 Table 16 - Icing Corrections to Landing Ground Roll – Flaps 0° - No Reverse Thrust TABLE A LANDING WEIGHT - KG ALTITUDE CORRECTION (%) 2900 3300 3700 4100 4500 (KIAS) 0 FT +103 +115 +117 +113 +114 2000 FT... Page 1003 SECTION 9 SUPPLEMENT 33 Table 17 - Icing Corrections to Landing Total Distance – Flaps 15° - With Reverse Thrust TABLE A LANDING WEIGHT - KG ALTITUDE CORRECTION (%) 2900 3300 3700 4100 4500 (KIAS) 0 FT 2000 FT 4000 FT 6000 FT 8000 FT 10000 FT... Page 1004 SECTION 9 SUPPLEMENT 33 Table 18 - Icing Corrections to Landing Ground Roll – Flaps 15° - With Reverse Thrust TABLE A LANDING WEIGHT - KG ALTITUDE CORRECTION (%) 2900 3300 3700 4100 4500 (KIAS) 0 FT 2000 FT 4000 FT 6000 FT 8000 FT 10000 FT... Page 1005 SECTION 9 SUPPLEMENT 33 Table 19 - Icing Corrections to Landing Total Distance – Flaps 0° - With Reverse Thrust TABLE A LANDING WEIGHT - KG ALTITUDE CORRECTION (%) 2900 3300 3700 4100 4500 (KIAS) 0 FT 2000 FT 4000 FT +101 +100 +103... Page 1006 SECTION 9 SUPPLEMENT 33 Table 20 - Icing Corrections to Landing Ground Roll – Flaps 0° - With Reverse Thrust TABLE A LANDING WEIGHT - KG ALTITUDE CORRECTION (%) 2900 3300 3700 4100 4500 (KIAS) 0 FT +102 +103 2000 FT +103 +101 4000 FT... Page 1007 SECTION 9 SUPPLEMENT 33 SECTION 6 - WEIGHT AND BALANCE PC-12/47 EXAMPLE LOADING FORM INTERIOR CODE: STD-9S ITEM WEIGHT ARM AFT OF MOMENT lb (kg) DATUM in (m) lb-in (kg-m) 1. Basic Empty Weight 5613 225.16 (5.719) 1263823 2. Combi Interior Conversion 3. Page 1008 SECTION 9 SUPPLEMENT 33 PC-12/47 EXAMPLE LOADING FORM INTERIOR CODE: ITEM WEIGHT ARM AFT OF MOMENT lb (kg) DATUM in (m) lb-in (kg-m) 1. Basic Empty Weight 2. Combi Interior Conversion 3. Pilot 160.27 (4.071) 4. Copilot (Right Seat Passenger) 160.27 (4.071) 5. Page 1009 SECTION 9 SUPPLEMENT 33 Figure 6-9. C. G. Envelope (Sheet 1 of 2) Issued: November 8, 2005 EASA Approved Report No: 02211 Revision 5: Oct 06, 2017 9-33-39... Page 1010 SECTION 9 SUPPLEMENT 33 Figure 6-9. C. G. Envelope (Sheet 2 of 2) Report No: 02211 EASA Approved Issued: November 8, 2005 9-33-40 Revision 5: Oct 06, 2017... Page 1012 SECTION 9 SUPPLEMENT 34 THIS PAGE INTENTIONALLY LEFT BLANK Report No: 02211 EASA Approved Issued: 1 September, 2009 9-34-2 Revision 1: September 01, 2014... Page 1013 SECTION 9 SUPPLEMENT 34 LIST OF EFFECTIVE PAGES Page No Rev No. Page No. Rev No. 9-34-1 9-34-2 thru 9-34-22 9-34-3 9-34-4 thru 9-34-6 9-34-7 9-34-8 and 9-34-9 9-34-10 9-34-11 9-34-12 9-34-13 thru 9-34-22 Issued: 1 September, 2009 Report No: 02211 Revision 02: Dec 12, 2019 9-34-3... Page 1014 SECTION 9 SUPPLEMENT 34 THIS PAGE INTENTIONALLY LEFT BLANK Report No: 02211 Issued: 1 September, 2009 9-34-4 Revision 1: September 01, 2014... Page 1015 SECTION 9 SUPPLEMENT 34 LOG OF TEMPORARY REVISIONS The incorporation of temporary revisions into this supplement are to be recorded on the sheet below. Instructions for the removal of temporary revisions will be given in the instruction sheet issued with revisions. DATE OF CANCELLED TEMPORARY REVISION TITLE... Page 1016 SECTION 9 SUPPLEMENT 34 THIS PAGE INTENTIONALLY LEFT BLANK Report No: 02211 Issued: 1 September, 2009 9-34-6 Revision 1: September 01, 2014... Page 1017 SECTION 9 SUPPLEMENT 34 LOG OF REVISIONS Page Revision Number Number Description and Date 9-34-2 thru 9-34-22 Alternate placards added. Structure completely revised. 01.09.2014 New LOEP, LOTR and LOR. Editorial and layout changes. The Revision Number 1 to AFM Supplement No. 34 is approved under the authority of DOA ref. Page 1018 SECTION 9 SUPPLEMENT 34 THIS PAGE INTENTIONALLY LEFT BLANK Report No: 02211 Issued: 1 September, 2009 9-34-8 Revision 1: September 01, 2014... Page 1019 SECTION 9 SUPPLEMENT 34 SECTION 1 – GENERAL This supplement provides the information necessary to operate the PC-12, PC-12/45 and PC12/47 aircraft in the Republic of Argentina. Issued: 1 September, 2009 Report No: 02211 Revision 1: September 01, 2014 9-34-9... Page 1020 SECTION 9 SUPPLEMENT 34 SECTION 2 – LIMITATIONS On airplanes registered in the Republic of Argentina, the necessary equipment for the different kinds of operations must comply with the applicable Argentine Regulations. GLOBAL POSITIONING SYSTEM The pilot is not authorized to use the Global Positioning System (GPS) for precision approach and landing. Page 1021 SECTION 9 SUPPLEMENT 34 On interior emergency exit: SALIDA DE EMERGENCIA EMPUJE EMPUJE HACIA ADENTRO DESPUES DE SOLTAR Issued: 1 September, 2009 EASA Approved Report No: 02211 Revision 1: September 01, 2014 9-34-11... Page 1022 SECTION 9 SUPPLEMENT 34 CABIN PLACARDS The following placards are installed in all aircraft. On interior of passenger door: SALIDA/EXIT NO UTILIZAR EN VUELO DO NOT OPERATE IN FLIGHT NO ABRIR LA PUERTA CON EL MOTOR EN MARCHA EXCEPTO EN EMERGENCIA CERRADO DO NOT OPEN DOOR WHEN ENGINE CLOSED... Page 1023 SECTION 9 SUPPLEMENT 34 On interior cargo door handle cover: NO QUITAR LA CUBIERTA EN VUELO DO NOT REMOVE COVER IN FLIGHT On interior cargo door handle: LEVANTAR LA PALANCA DE CIERRE, TIRAR DE LA PALANCA Y EMPUJAR LA PUERTA HACIA AFUERA LIFT LOCKING LEVER AND PULL HANDLE PUSH DOOR OUT On interior of cargo door:... Page 1024 SECTION 9 SUPPLEMENT 34 On lower cargo door frame: INSTALAR EL SOPORTE DE COLA ANTES DE CARGAR EL AVION On lower cargo door frame: INSTALL TAIL SUPPORT STAND BEFORE LOADING CARGO On cabin to baggage area step: MANTENGA LIBRE LA REJILLA KEEP GRILL CLEAR Above the baggage area: MAXIMA CARGA DE EQUIPAJE = 70 kg / 155 lb... Page 1025 SECTION 9 SUPPLEMENT 34 Issued: 1 September, 2009 EASA Approved Report No: 02211 Revision 1: September 01, 2014 9-34-15... Page 1026 SECTION 9 SUPPLEMENT 34 Report No: 02211 EASA Approved Issued: 1 September, 2009 9-34-16 Revision 1: September 01, 2014... Page 1027 SECTION 9 SUPPLEMENT 34 6 SEAT EXECUTIVE (Interior Code EX-6S-2) The cabin placards plus the following additional placards are those required for this interior. On the inside of the lavatory doors: - NO FUMAR EN EL LAVABO - NO SMOKING IN LAVATORY - NO OCUPAR EL LAVABO DURANTE DESPEGUE / ATERRIZAJE Y TURBULENCIA - TOILET COMPARTMENT NOT TO BE OCCUPIED DURING... Page 1028 SECTION 9 SUPPLEMENT 34 On the inside of the optional wardrobe: MANTENER LAS PUERTAS CERREDAS DURANTE DESPEGUE / ATERRIZAJE DOORS MUST BE CLOSED DURING TAKEOFF / LANDING EL EQUIPAJE NO DEBE SOBREPASAR EL BORDE. MANTENER CERRADA LA RED DURANTE EL VUELO. NO BAGGAGE ALLOWED ABOVE EDGE NET MUST BE CLOSED FOR FLIGHT PESO LIMITE... Page 1029 SECTION 9 SUPPLEMENT 34 Issued: 1 September, 2009 EASA Approved Report No: 02211 Revision 1: September 01, 2014 9-34-19... Page 1030 SECTION 9 SUPPLEMENT 34 Near the optional coat rail in the baggage compartment: MAX PESO A COLGAR 5 KG / 11 LB. MAX COAT RAIL 5 KG / 11 LB. 8 SEAT EXECUTIVE (Interior Code EX-8S) and a 6 SEAT EXECUTIVE AND 2 SEAT CORPORATE COMMUTER (Interior Code EX-6S-STD-2S) The cabin placards, the 6 seat executive placards and the following replacement / additional placards are required for this interior:... Page 1031 SECTION 9 SUPPLEMENT 34 PLACARDS – 4 SEAT EXECUTIVE AND 4 SEAT CORPORATE COMMUTER (Interior Code EX4S-STD-4S) On the armrest near passenger oxygen mask for seats 7 and 8: TIRE DE LA CINTA PARA TIRE DE LA CINTA PARA LA MASCARA DE OXIGENO LA MASCARA DE OXIGENO PULL TAPE FOR PULL TAPE FOR... Page 1032 SECTION 9 SUPPLEMENT 34 Report No: 02211 EASA Approved Issued: 1 September, 2009 9-34-22 Revision 1: September 01, 2014... Page 1034 SECTION 9 SUPPLEMENT 35 INTENTIONALLY BLANK Report No: 02211 DGAC Approved Issued: Aug 01, 2012 9-35-2... Page 1035 SECTION 9 SUPPLEMENT 35 LIST OF EFFECTIVE PAGES Page No Rev No. 9-35-1 and 9-35-2 9-35-3 9-35-4 thru 9-35-6 9-35-7 9-35-8 and 9-35-9 9-35-10 and 9-35-11 9-35-12 and 9-35-13 9-35-14 and 9-35-15 9-35-16 thru 9-35-18 9-35-19 9-35-20 and 9-35-21 9-35-22 Issued: Aug 01, 2012 Report No: 02211 Revision 02: Dec 12, 2019... Page 1036 SECTION 9 SUPPLEMENT 35 INTENTIONALLY BLANK Report No: 02211 Issued: Aug 01, 2012 9-35-4 Revision 1: September 01, 2014... Page 1037 SECTION 9 SUPPLEMENT 35 LOG OF TEMPORARY REVISIONS The incorporation of temporary revisions into this supplement are to be recorded on the sheet below. Instructions for the removal of temporary revisions will be given in the instruction sheet issued with revisions. DATE CANCELLED TEMPORARY REVISION TITLE... Page 1038 SECTION 9 SUPPLEMENT 35 INTENTIONALLY BLANK Report No: 02211 Issued: Aug 01, 2012 9-35-6 Revision 1: September 01, 2014... Page 1039 SECTION 9 SUPPLEMENT 35 LOG OF REVISIONS Revision Page Number Number Description and Date Revision 1 9-35-3 thru 9-35-10 LOEP & LOR Updated to reflect Revision 1. Editorial 01.09.2014 changes to footers. Structure change. 9-35-14 and 9-35-15 Additional placards added. 9-35-19 Additional placards added. Page 1040 SECTION 9 SUPPLEMENT 35 INTENTIONALLY BLANK Report No: 02211 Issued: Aug 01, 2012 9-35-8 Revision 1: September 01, 2014... Page 1041 SECTION 9 SUPPLEMENT 35 SECTION 1 – GENERAL This supplement provides the information necessary to operate the PC-12, PC-12/45 and PC12/47 aircraft in the Republic of Chile. Issued: Aug 01, 2012 Report No: 02211 Revision 1: September 01, 2014 9-35-9... Page 1042 SECTION 9 SUPPLEMENT 35 SECTION 2 – LIMITATIONS On airplanes registered in the Republic of Chile, the necessary equipment for the different kinds of operations must comply with the applicable Chilean Regulations. EXTERNAL PLACARDS On exterior of passenger door: TIRE DE LA MANILLA Y GIRE PARA ABRIR NO ABRIR LA PUERTA CON EL MOTOR EN MARCHA... Page 1043 SECTION 9 SUPPLEMENT 35 CABIN PLACARDS The following placards are installed in all aircraft. On interior of passenger door: SALIDA/EXIT NO UTILIZAR EN VUELO DO NOT OPERATE IN FLIGHT NO ABRIR LA PUERTA CON EL MOTOR EN MARCHA EXCEPTO EN EMERGENCIA CERRADO DO NOT OPEN DOOR WHEN ENGINE CLOSED... Page 1044 SECTION 9 SUPPLEMENT 35 On interior cargo door handle cover: NO QUITAR LA CUBIERTA EN VUELO DO NOT REMOVE COVER IN FLIGHT On interior cargo door handle: LEVANTAR EL SEGURO, TIRAR LA PALANCA Y EMPUJAR LA PUERTA HACIA AFUERA LIFT LOCKING LEVER AND PULL HANDLE PUSH DOOR OUT On interior of cargo door: NO ABRIR LA PUERTA... Page 1045 SECTION 9 SUPPLEMENT 35 On lower cargo door frame: INSTALAR EL SOPORTE DE COLA ANTES DE CARGAR EL AVION On lower cargo door frame: INSTALL TAIL SUPPORT STAND BEFORE LOADING CARGO On cabin to baggage area step: MANTENGA LIBRE LA REJILLA KEEP GRILL CLEAR Above the baggage area: MAXIMA CARGA DE EQUIPAJE = 70 kg / 155 lb... Page 1046 SECTION 9 SUPPLEMENT 35 Report No: 02211 DGAC Approved Issued: Aug 01, 2012 9-35-14 Revision 1: September 01, 2014... Page 1047 SECTION 9 SUPPLEMENT 35 Issued: Aug 01, 2012 DGAC Approved Report No: 02211 Revision 1: September 01, 2014 9-35-15... Page 1048 SECTION 9 SUPPLEMENT 35 6 SEAT EXECUTIVE (Interior Code EX-6S-2) The cabin placards plus the following additional placards are those required for this interior. On the inside of the lavatory doors: On the toilet door #1: - NO FUMAR EN EL BAÑO - NO SMOKING IN LAVATORY - NO OCUPAR EL BAÑO DURANTE DESPEGUE / ATERRIZAJE Y TURBULENCIA... Page 1049 SECTION 9 SUPPLEMENT 35 On the oxygen mask box: MASCARA DE OXIGENO EN EL INTERIOR OXYGEN MASK INSIDE Below the oxygen mask box: TIRE DE LA CINTA PARA LA MASCA DE OXIGENO PULL TAPE FOR OXYGEN MASK Near the toilet seat: PRESIONE PARA VACIAR PUSH TO FLUSH LUZ DEL BAÑO... Page 1050 SECTION 9 SUPPLEMENT 35 On the inside of the left and right cabinet drawers: On the left upper drawer PESO LIMITE WEIGHT LIMIT 10 lb / 4.5kg On the left lower drawer PESO LIMITE WEIGHT LIMIT 25 lb / 11.3kg On the right upper drawer PESO LIMITE WEIGHT LIMIT 5 lb / 2.3kg... Page 1051 SECTION 9 SUPPLEMENT 35 Issued: Aug 01, 2012 DGAC Approved Report No: 02211 Revision 1: September 01, 2014 9-35-19... Page 1052 SECTION 9 SUPPLEMENT 35 Near the optional coat rail in the baggage compartment: MAX PESO A COLGAR 5 KG / 11 LB. MAX COAT RAIL 5 KG / 11 LB. 8 SEAT EXECUTIVE (Interior Code EX-8S) and a 6 SEAT EXECUTIVE AND 2 SEAT CORPORATE COMMUTER (Interior Code EX-6S-STD-2S) The cabin placards, the 6 seat executive placards and the following replacement / additional placards are required for this interior:... Page 1053 SECTION 9 SUPPLEMENT 35 PLACARDS – 4 SEAT EXECUTIVE AND 4 SEAT CORPORATE COMMUTER (Interior Code EX4S-STD-4S) On the armrest near passenger oxygen mask for seats 7 and 8: TIRE DE LA CINTA PARA TIRE DE LA CINTA PARA LA MASCARA DE OXIGENO LA MASCARA DE OXIGENO PULL TAPE FOR PULL TAPE FOR... Page 1054 SECTION 9 SUPPLEMENT 35 Report No: 02211 DGAC Approved Issued: Aug 01, 2012 9-35-22 Revision 1: September 01, 2014... Page 1055 SECTION 9 PC-12 SUPPLEMENT PILOT'S OPERATING HANDBOOK EASA APPROVED AIRPLANE FLIGHT MANUAL SUPPLEMENT REPORT NO. 02474 GERMAN PLACARDS This supplement must be attached to the Pilot's Operating Handbook and EASA Approved Airplane Flight Manual for t h e E A S A certified PC-12 airplanes. Page 1056 SECTION 9 PC-12 SUPPLEMENT This Page Intentionally Left Blank Report No: 02474 Pilot's Operating Handbook Supplement Issue date: Nov 21, 2019... Page 1057 Table of Contents Front Matter Table of Contents Section Subject Page List of Effective Data Modules FM-1-1 Log of Revisions FM-3-1 Issue 001 - Revision 00 - Dated: 21 November 2019 FM-3-1 Log of Temporary Revisions FM-4-1 Pilot's Operating Handbook Supplement Report No: 02474 Issue date: Nov 21, 2019 Page FM-0-1... Page 1058 Table of Contents This Page Intentionally Left Blank Pilot's Operating Handbook Supplement Report No: 02474 Issue date: Nov 21, 2019 Page FM-0-2... Page 1059 List of Effective Data Modules List of Effective Data Modules All DMC are preceded with PC-12-C but for clarity this has been left out C = Changed data module N = New data module Data module code (DMC) Document title Issue date A15-00-2474-00A-002A-A List of Effective Data Modules... Page 1060 List of Effective Data Modules This Page Intentionally Left Blank Pilot's Operating Handbook Supplement Report No: 02474 Issue date: Nov 21, 2019 Page FM-1-2... Page 1061 Log of Revisions Log of Revisions Issue 001 - Revision 00 - Dated: 21 November 2019 Initial Issue of the PC-12 AFM Supplement 02474. The Issue 001 Revision 00 of the AFM Supplement ref. 02474 is approved under the authority of DOA No. EASA.21J.357. Approval date: 21.11.2019 Table 1: Issue 001 - Revision 00 - List of changes Section... Page 1062 Issue 001 - Revision 00 - Dated: 21 November 2019 This Page Intentionally Left Blank Pilot's Operating Handbook Supplement Report No: 02474 Issue date: Nov 21, 2019 Page FM-3-2... Page 1063 Log of Temporary Revisions Log of Temporary Revisions Temporary Revision Title Date of Issue Cancelled by Pilot's Operating Handbook Supplement Report No: 02474 Issue date: Nov 21, 2019 Page FM-4-1... Page 1064 Log of Temporary Revisions Temporary Revision Title Date of Issue Cancelled by Pilot's Operating Handbook Supplement Report No: 02474 Issue date: Nov 21, 2019 Page FM-4-2... Page 1065 Section 1 - General Table of Contents SECTION 1 General Table of Contents Section Subject Page General 1-1-1 General 1-1-1 Pilot's Operating Handbook Supplement Report No: 02474 Issue date: Nov 21, 2019 Page 1-0-1... Page 1066 Section 1 - General Table of Contents This Page Intentionally Left Blank Pilot's Operating Handbook Supplement Report No: 02474 Issue date: Nov 21, 2019 Page 1-0-2... Page 1067 Section 1 - General General General General This supplement provides the information necessary to operate the PC-12 aircraft with placards in the German language installed. This Supplement must be attached to Pilot’s Operating Handbook Report No.: − 01973-001 − 02211 −... Page 1068 Section 1 - General General This Page Intentionally Left Blank Pilot's Operating Handbook Supplement Report No: 02474 Issue date: Nov 21, 2019 Page 1-1-2... Page 1069 Section 2 - Limitations (EASA Approved) Table of Contents SECTION 2 Limitations (EASA Approved) Table of Contents Section Subject Page Limitations 2-1-1 Pilot's Operating Handbook Supplement Report No: 02474 Issue date: Nov 21, 2019 Page 2-0-1... Page 1070 Section 2 - Limitations (EASA Approved) Table of Contents This Page Intentionally Left Blank Pilot's Operating Handbook Supplement Report No: 02474 Issue date: Nov 21, 2019 Page 2-0-2... Page 1071 Section 2 - Limitations (EASA Approved) Limitations Limitations CABIN PLACARDS The following placards are installed in all aircraft. On interior of cabin door: On interior of emergency exit: On interior of emergency exit handle: On interior of cargo door handle cover: On interior of cargo door: On the rear of the left cockpit bulkhead: 12-C-A150223-A-S4080-00402-A-001-01... Page 1072 Section 2 - Limitations (EASA Approved) Limitations 9 SEAT CORPORATE COMMUTER INTERIOR (Interior Code STD-9S) The cabin placards plus the following are those required for the interior. Near each passenger oxygen outlet: On the rear of the left cockpit bulkhead: On the rear of the left cockpit bulkhead: On the rear of the right cockpit bulkhead: On the back of the standard passenger seat (except seat 5):... Page 1073 Section 2 - Limitations (EASA Approved) Limitations 6 SEAT EXECUTIVE INTERIOR (Interior Code EX-6S-2) The cabin placards plus the following are those required for the interior. On each oxygen mask pocket: On the armrest near each passenger oxygen mask: Near each executive seat: 12-C-A150223-A-S4080-00404-A-001-01 Figure 2-3: Placards - Cabin - 6 Seat executive (Interior code EX-6S-2) - German Pilot's Operating Handbook Supplement... Page 1074 Section 2 - Limitations (EASA Approved) Limitations 8 SEAT EXECUTIVE INTERIOR (Interior Code EX-8S) The cabin placards, the 6 seat executive and the following replacement/additional placards are required for this interior. Rear of executive passenger seat No. 5, 6, 7 and 8: or or 12-C-A150223-A-S4080-00405-A-001-01 Figure 2-4: Placards - Cabin - 8 Seat executive (Interior code EX-8S) - German... Page 1075 Section 2 - Limitations (EASA Approved) Limitations TOILET PLACARDS The toilet placards are installed in all executive interiors. On the toilet door #1: On the toilet door #3: Near the toilet seat: On the oxygen mask box: Below the oxygen mask box: 12-C-A150223-A-S4080-00406-A-001-01 Figure 2-5: Placards - Cabin - Toilet - German Pilot's Operating Handbook Supplement... Page 1076 Section 2 - Limitations (EASA Approved) Limitations This Page Intentionally Left Blank Pilot's Operating Handbook Supplement Report No: 02474 Issue date: Nov 21, 2019 Page 2-1-6... Page 1077 SECTION 10 SAFETY AND OPERATIONAL TIPS SECTION 10 SAFETY AND OPERATIONAL TIPS TABLE OF CONTENTS Subject Page GENERAL 10-1 SAFETY TIPS 10-1 OPERATIONAL TIPS 10-1 ANTI-COLLISION LIGHTS 10-1 CROSSWIND OPERATION 10-1 FLAMMABLE MATERIALS, PRESSURE VESSELS AND 10-3 EQUIPMENT LOCATIONS REMOVAL OF SNOW, ICE AND FROST FROM THE 10-4 AIRCRAFT OPERATIONS FROM PREPARED UNPAVED SURFACES... Page 1078 SECTION 10 SAFETY AND OPERATIONAL TIPS THIS PAGE INTENTIONALLY LEFT BLANK Report No: 02211 Issued: March 30, 2001 10-ii... Page 1079 SECTION 10 SAFETY AND OPERATIONAL TIPS GENERAL This section provides information for the operation of the airplane. SAFETY TIPS Pilots who fly above 10,000 feet should be aware of the need for physiological training. It is recommended that this training be taken before flying above 10,000 feet and receive refresher training every two or three years. Page 1080 SECTION 10 SAFETY AND OPERATIONAL TIPS and put on bank in the opposite direction to maintain the runway centerline. The aircraft is then flown in a sideslip to touch down initially on one wheel. As soon as one wheel touches, lower the other two to the runway and immediately select either the condition lever to ground idle or the PCL to beta or reverse. Page 1081 SECTION 10 SAFETY AND OPERATIONAL TIPS FLAMMABLE MATERIALS, PRESSURE VESSELS AND EQUIPMENT LOCATIONS Refer to Figure 10-1 for the location of these items. Figure 10-1. Flammable Materials, Pressure Vessels and Equipment Locations Issued: March 30, 2001 Report No: 02211 10-3... Page 1082 FAA and Transport Canada Holdover Timetables Pilatus recommend that ground de-icing/anti-icing is done with the engine shutdown to minimize fluid ingestion into the engine and bleed air ducting. The ECS switch must remain set to OFF for approximately five minutes after the de- icing/anti-icing procedure has been completed. Page 1083 Various de-icing fluids are commercially available. Clariant fluids were rigorously tested on PC-12 aircraft with no detrimental effect identified. Clariant fluids are therefore recommended by Pilatus for use on PC-12 aircraft. NOTE For de-icing the temperature of all heated fluids should be at least 60°C (140°F) at the nozzle. Page 1084 SECTION 10 SAFETY AND OPERATIONAL TIPS HEALTH EFFECTS Pilots must be aware of the potential health problems of de-icing/anti-icing fluids to ensure the correct precautions are taken when a de-icing/anti-icing procedure is done, and to better ensure the wellbeing of the passengers and crew. PRE-FLIGHT CHECKS FOR ICE, SLUSH, SNOW OR FROST THAT ADHERES TO THE AIRCRAFT To establish the need for aircraft de-icing, a pre-flight check is required to identify any... Page 1085 SECTION 10 SAFETY AND OPERATIONAL TIPS START Do Pre-Flight Checks (Para 3) Do freezing precipitation conditions De-Icing/Anti-Icing Is it possible to do a Do Two-Step exist, or is a Holdover required (Para 6) Two-Step procedure? procedure (Para 6.B) time required? Do One-Step procedure (Para 6.A) Page 1086 SECTION 10 SAFETY AND OPERATIONAL TIPS DE-ICING ONLY PROCEDURE To reduce the quantity of de-icing fluid required, a manual method can be used as a pre- step process, before the de-icing process, in order to remove large amounts of frozen contamination, for example, snow, slush or ice Ice, slush, snow or frost may be removed from aircraft surfaces by manual methods or fluids. Page 1087 SECTION 10 SAFETY AND OPERATIONAL TIPS 6. DE-ICING/ANTI-ICING CAUTION THE APPLICATION OF TYPE II, III OR IV FLUIDS, MAY CAUSE RESIDUES TO COLLECT IN AERODYNAMICALLY QUIET AREAS, CAVITIES AND GAPS. DRIED RESIDUES MAY REHYDRATE AND FREEZE FOLLOWING A PERIOD OF HIGH HUMIDITY AND/OR RAIN CONDITIONS. Page 1088 SECTION 10 SAFETY AND OPERATIONAL TIPS APPLICATION OF DE-ICING/ANTI-ICING FLUID A. GENERAL Flight crew should supervise the de-icing and anti-icing of the aircraft to ensure proper application of the fluid. When ice, snow or slush is removed from aircraft surfaces, care must be taken to prevent entry and accumulation of the ice, snow or slush in intakes or control surface hinge areas. Page 1089 SECTION 10 SAFETY AND OPERATIONAL TIPS DE-ICING/ANTI-ICING THE WINGS, TAIL AND FUSELAGE The wings are the main lifting surfaces of the aircraft and must be free of snow and ice to operate efficiently. De-icing/anti-icing of the wings should begin at the leading edge wing tip with the flaps retracted, sweeping in the aft and inboard direction. Page 1090 SECTION 10 SAFETY AND OPERATIONAL TIPS LANDING GEAR AND WHEEL BAYS DE-ICING The application of de-icing fluid in this area must be kept to a minimum. De-icing fluid must not be directed onto the brakes and wheels. Landing gear and wheel bays must be kept free from a buildup of slush, ice or accumulation of blown snow. Page 1091 SECTION 10 SAFETY AND OPERATIONAL TIPS NOTE Any forward area from which fluid may blow back onto the windscreen during taxi or take-off must be free of fluid residues prior to departure. Figure 10-3 Essential Aircraft De-Icing Areas Issued: March 30, 2001 Report No: 02211 Revision 8: December 01, 2012 10-13... Page 1092 SECTION 10 SAFETY AND OPERATIONAL TIPS Figure 10-4 Essential Aircraft Anti-Icing Areas Report No: 02211 Issued: March 30, 2001 10-14 Revision 8: December 01, 2012... Page 1093 SECTION 10 SAFETY AND OPERATIONAL TIPS 8. SPRAYING TECHNIQUE ONE STEP DE-ICING/ANTI-ICING Heated water and/or heated fluid must be sprayed on the aircraft in a manner which minimizes heat loss on the aircraft. If spraying is carried out with the engine running, the engine must be at Idle with all engine bleed air turned off. Page 1094 SECTION 10 SAFETY AND OPERATIONAL TIPS POST DE-ICING/ANTI-ICING PROCEDURE CAUTION AIRCRAFT OPERATORS ARE SOLELY RESPONSIBLE FOR ENSURING HOLDOVER TIMETABLES CONTAIN CURRENT DATA. TABLES ARE FOR USE IN DEPARTURE PLANNING ONLY AND MUST BE USED IN CONJUNCTION WITH PRE TAKE-OFF CONTAMINATION PROCEDURES. POST DE-ICING/ANTI-ICING CHECK The areas that follow must be checked for any contamination that may still remain after the de-icing/anti-icing procedure has been done:... Page 1095 SECTION 10 SAFETY AND OPERATIONAL TIPS PRE-TAKEOFF CONTAMINATION CHECK CAUTION UNDER NO CIRCUMSTANCES SHALL AN AIRCRAFT THAT HAS BEEN ANTI-ICED RECEIVE A FURTHER COATING OF ANTI-ICING FLUID DIRECTLY ON TOP OF THE CONTAMINATED FILM. IF AN ADDITIONAL TREATMENT IS REQUIRED BEFORE FLIGHT, A COMPLETE DE-ICING/ANTI-ICING PROCEDURE MUST BE PERFORMED. Page 1096 SECTION 10 SAFETY AND OPERATIONAL TIPS 11. TAKE-OFF PERFORMANCE – SAE TYPE II, TYPE III AND TYPE IV FLUIDS CAUTION ANTICIPATE A HEAVIER THAN NORMAL ELEVATOR FORCE AT ROTATION. EVEN WITH THE INCREASED PULL FORCE, THE AIRCRAFT MAY ROTATE SLOWER THEN NORMAL. Page 1097 SECTION 10 SAFETY AND OPERATIONAL TIPS OPERATIONS FROM PREPARED UNPAVED SURFACES The aircraft is constructed for operations from prepared unpaved surfaces. Prepared unpaved surfaces are taxi-ways and runways that are prepared and approved for aircraft operations with a surface other than tarmac or concrete. CAUTION PREPARED UNPAVED SURFACES SUITABLE FOR AIRCRAFT OPERATIONS VARY GREATLY AND SOME... Page 1098 SECTION 10 SAFETY AND OPERATIONAL TIPS On sandy or dusty surfaces, or where loose grass is present, reverse thrust can cause a loss of forward visibility and particles ingested into the air intake can cause increased engine wear. INERTIAL SEPARATOR When operating from any surface where there is a risk of dust, sand or other material entering the engine intake, it is recommended to open the inertial separator. Page 1099 SECTION 10 SAFETY AND OPERATIONAL TIPS PASSENGER BRIEFINGS GENERAL In Sections 3 and 4 there are procedural actions that call for the pilot to brief the passengers. They fall into two categories those forming part of an emergency procedure and the more regular type ones for taxiing prior to takeoff and before landing. Tips for passenger briefings during an emergency cannot be specified as each situation will place a different demand on the pilot. Page 1100 SECTION 10 SAFETY AND OPERATIONAL TIPS BEFORE LANDING (Section 4, para 4-14) For aircraft with a standard cabin interior: Stow hand baggage under the seats Put the seat back in the upright position Position the seat headrest to support the head ... Page 1101 SECTION 10 SAFETY AND OPERATIONAL TIPS ENGINE INSTRUMENT SYSTEM FAULT CODES The flight crew are permitted to reset the following EIS fault codes using a maximum of three EIS power cycles. 1, 2, 3, 4, 5, 6, 10, 11, 12, 13, 14, 15, 16, 17, 18, 19, 23, 24, 25, 35, 38, 39, 43, 47, 59, 65, 66, 69, 70, 71, 72, 74, 75, 76, 79, 88, 89, 90 and EIS unit caution light flashing (fault with the EIS internal self-test). Page 1102 SECTION 10 SAFETY AND OPERATIONAL TIPS THIS PAGE INTENTIONALLY BLANK Report No: 02211 Issued: March 30, 2001 10-24 Revision 8: December 01, 2012... Aldo Wicki / Pilatus Aircraft Noch ist völlig unklar, warum am Sonntag in Mailand ein Pilatus-Flugzeug drei Minuten nach dem Start vom Flughafen Milano-Linate in ein leerstehendes Bürogebäude abgestürzt ist. Augenzeugen wollen gesehen haben, dass der Motor, also die Propellerturbine, brannte. Laut Medienberichten ist angeblich bereits ein Flugschreiber gefunden worden. Diese Meldung ist aber wohl mit Vorsicht zu geniessen. Denn der PC-12 hat üblicherweise keine sogenannte Blackbox und auch keinen Cockpit-Voice-Recorder an Bord, wie es bei grossen Passagiermaschinen der Fall ist. Deren aufgezeichnete Daten oder Gespräche helfen sonst bei der Aufklärung von Absturzursachen. Fest steht: Der Flugzeugtyp Pilatus PC-12 gilt als sicher. Seine Propellerturbine vom Typ PT6 des Herstellers Pratt & Whitney zählt sogar zu den zuverlässigsten Antrieben weltweit. Allerdings wird der mit bis zu zehn Sitzen ausgestattete PC-12 nur von einer einzigen Turbine angetrieben. Fällt diese aus, muss der Pilot anders als etwa in einer zweimotorigen Maschine unmittelbar eine Notlandung einleiten. Diese ist umso gefährlicher, je tiefer das Fleugzeug ist: Es fehlt die Zeit zum Suchen einer geeigneten Notlandefläche, auf der das Flugzeug im Segelflug aufsetzen könnte. Brand erschwert Ursachenforschung Diese Systeme sind aber bei kleinen Turbopropflugzeugen wie dem PC-12 bis anhin nicht vorgeschrieben. Zudem könnten auch der wohl grosse Zerstörungsgrad und ein nach dem Crash ausgebrochener Brand an der Absturzstelle die Suche nach den Ursachen erschweren. Der Pilot war offenbar ein bekannter deutsch-rumänischer Bauunternehmer und Millionär. Das Flugzeug war in Rumänien registriert. Für den PC-12 ist nur ein Pilot vorgeschrieben, keine Zweiercrew wie etwa in Airlinern. Die Turbopropmaschine gilt seit drei Jahrzehnten als sicheres Flugzeug. Bereits am 31. Mai 1991 hebt erstmals ein PC-12 vom Pilatus-Werkflugplatz in Buochs ab. Ob der zu jener Zeit riskante Plan, ein Reiseflugzeug mit lediglich einer Propellerturbine anzubieten, aufgeht, weiss damals niemand. Denn alle anderen Hersteller setzen auf mindestens zwei Motoren. Aufgrund der legendär hohen Zuverlässigkeit der verwendeten Propellerturbine PT6 sind die Verantwortlichen bei Pilatus aber überzeugt davon, dass ein Triebwerk genügt, was zu wesentlich geringeren Betriebskosten führt. Der Erfolg gibt ihnen recht. Denn mittlerweile sind bis Oktober dieses Jahres mehr als 1800 Exemplare ausgeliefert worden. Einen direkten Wettbewerber in diesem Flugzeugsegment gibt es bis jetzt noch nicht, auch wenn Cessna/Beechcraft ein ebenfalls einmotoriges Konkurrenzmodell mit Namen Beechcraft Denali entwickelt haben, das kurz vor dem Erstflug steht. In Stans ist der PC-12 durch stetige Evolution mittlerweile zur Version PC-12 NGX weiterentwickelt worden. Es gibt ihn auch in einer Variante als Ambulanzflugzeug. Vor allem in Australien beim Royal Flying Doctor Service ist er gefragt. Denn im Outback muss die robuste Turboprop auf unbefestigten Schotterpisten starten und landen können. Vom Porter zum PC-24 Grundstein der zivilen Flugzeuge von Pilatus ist eine ungemein vielseitige Maschine, der PC-6 Porter. Schon am 4. Mai 1959 hebt ein Porter erstmals ab, zunächst mit einem Kolbenmotor, später mit einer Propellerturbine. Vor mehr als 62 Jahren ist er als robustes Flugzeug in Metallbauweise konzipiert. Damals passen bis zu sieben Passagiere oder eine Tonne Fracht hinein. Fast 600 Porter und Turbo Porter entstehen. Die Karriere endet erst 2019 nach 60-jähriger Erfolgsgeschichte. Um mehr Kapazität für den Businessjet PC-24 zu haben, wurde der Bau des Porter vor zwei Jahren eingestellt. Einige seiner bewährten Eigenschaften – etwa das buschpistentaugliche Fahrwerk, eine grosse Frachttüre und nur eine Propellerturbine als Antrieb – bildeten auch die DNA für die Entwicklung des PC-12 vor mehr als dreissig Jahren. Dieser ist aber anders als ein Porter dank seinem Einziehfahrwerk mit mehr als 500 km/h deutlich schneller. Zudem hat der PC-12 eine sogenannte Druckkabine und kann damit oberhalb des Wettergeschehens fliegen. Von 129 Flugzeugen, die Pilatus 2020 auslieferte, sind 82 Exemplare vom Typ PC-12. Die zivile Turbopropmaschine ist damit der unangefochtene Bestseller des Flugzeugbauers aus Stans. News und Hintergründe aus den Sparten Automobil, Motorrad, Velo, öffentlicher Verkehr, Luftfahrt und Schifffahrt. Hier kostenlos anmelden.