Innovative Solutions & Support Document No.: 1D-13466 1500 District Avenue Revision: IR Burlington, MA 01803

FAA APPROVED

AIRPLANE FLIGHT MANUAL SUPPLEMENT

TO THE

PILATUS PC-12 SERIES AIRPLANE FLIGHT MANUAL

FOR

INTEGRATED STANDBY UNIT WITH

Registration No.: ______

Serial No.: ______

This supplement must be attached to the FAA approved Airplane Flight Manual when the Innovative Solutions & Support (IS&S) Integrated Standby Unit with Autothrottle is installed in accordance with technical data approved by the USA FAA STC # SA00381BO.

The information contained in this document supplements or supersedes the basic manual only in those areas listed herein. For Limitations, Procedures, and Performance information not contained in this Supplement, consult the basic Airplane Flight Manual.

FAA Approved:

Date William P. Witzig Manager, Northeast Flight Test Section, AIR-711 Federal Aviation Administration 1200 District Avenue Burlington, MA 01803-5299

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FAA Approved: 2/14/2019 Innovative Solutions & Support Document No.: 1D-13466 1500 District Avenue Revision: IR Burlington, MA 01803

EFFECTED REV DESCRIPTION FAA APPROVAL PAGES

IR Initial Release ALL 2/14/2019

W. Witzig

AIR-711

NOTE: All changes are indicated by a black vertical line along the left margin.

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FAA Approved: 2/14/2019 Innovative Solutions & Support Document No.: 1D-13068 1500 District Avenue Revision: IR Burlington, MA 01803

1.0 SECTION 1 - GENERAL ...... 5 GENERAL ...... 5 ELECTRICAL / AVIONICS ABBREVIATIONS ...... 6

2.0 SECTION 2 - LIMITATIONS ...... 7 SYSTEMS AND EQUIPMENT LIMITS ...... 7 ISU WITH AUTOTHROTTLE (ISU A/T) SYSTEM ...... 7

3.0 SECTION 3 - EMERGENCY PROCEDURES ...... 8 3.23 INTEGRATED STANDBY UNIT (ISU) FAILURES ...... 8 3.23.1 General ...... 8 3.23.1.1 Legacy PC-12 Configuration ...... 8 3.23.1.2 PC-12 NG Configuration ...... 8 3.23.2 Magnetic Heading Input Failure on ISU ...... 8 3.23.3 ISU Attitude or Heading Failure ...... 8 3.23.4 ISU Air Data Failure ...... 8 3.23.5 ISU CONFIGURATION – ON GROUND ONLY ...... 9 3.24 AUTOTHROTTLE FUNCTION FAILURES ...... 10 3.24.1 Autothrottle (All PC-12) ...... 10 3.24.2 Autothrottle Malfunction (A/T FAIL) ...... 10 3.24.3 Autothrottle Malfunction ...... 11 3.24.4 External ADC Input Failure ...... 11

4.0 SECTION 4 - NORMAL PROCEDURES ...... 12 4.1 GENERAL ...... 12 4.3 PREFLIGHT INSPECTION ...... 12 4.3.8 Cockpit ...... 12 4.4 BEFORE STARTING ENGINE ...... 12 4.6 BEFORE TAXING ...... 13 4.8 BEFORE ...... 14 4.8.1 BEFORE DEPARTURE ...... 14 4.9 TAKEOFF ...... 14 Page 3 of 22

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4.11 ...... 15 4.12 ...... 15 4.13 ...... 15 4.14 BEFORE ...... 16 4.14.1 APPROACH CHECK ...... 16 4.14.2 FINAL CHECK ...... 16 4.15 BALKED LANDING (GO-AROUND) ...... 16

5.0 SECTION 5 - PERFORMANCE ...... 17

6.0 SECTION 6 - WEIGHT AND BALANCE ...... 18

7.0 SECTION 7 - AIRPLANE AND SYSTEM DESCRIPTION ...... 19

8.0 SECTION 8 - HANDLING, SERVICING AND MAINTENANCE ...... 20

9.0 SECTION 9 - SUPPLEMENTS ...... 21

10.0 SECTION 10 - SAFETY AND OPERATIONAL TIPS ...... 22

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1.0 SECTION 1 - GENERAL

GENERAL This supplement supplies the information necessary for the operation of the airplane when the IS&S Integrated Standby Unit with Autothrottle system is installed in accordance with STC Project Number SA02208BO-A There are two configurations of the Integrated Standby Unit with Autothrottle system. The configurations cover the requirements of the legacy PC-12 (PC-12, PC-12/45, PC-12/47) and the PC-12-47E NG. One configuration is referred to as the legacy PC-12 configuration (MSN up to 1000). When installed in the legacy PC-12, the ISU replaces the existing Radio Magnetic Indicator on the Pilot's instrument panel. The second configuration is covering the PC-12/47E NG (MSN 1001 and up). When installed in the PC-12 NG, the ISU replaces the existing Electronic Standby Instrument System (ESIS) on the Pilot's instrument panel. The differences between the configurations are mainly due to the existing power bus structure and existing equipment differences in the legacy PC-12 and PC-12 NG. The ISU Autothrottle equipment is the similar for both configurations except for the mounting procedure of the A/T kit. An Installation Configuration Module (ICM) and the installation kit provide for differences in specific configurations.

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ELECTRICAL / AVIONICS ABBREVIATIONS

ACK Acknowledge ADAHRS Air Data Attitude Heading Reference System ADC Air Data Computer AFM Airplane Flight Manual AHRS Attitude Heading Reference System ALT Altitude AT or A/T Autothrottle ATT Attitude BARO Barometric BATT Battery CAS Crew Alerting System CONFIG Configuration DG Directional Gyro EPS Emergency Power System ESIS Electronic Standby Instrument System GA Go Around DH Decision Height DISC or Disconnect DISCON HDG Heading IN Inches ISU Integrated Standby Display ITT Inter Turbine Temperature LBS Pounds MEN Menu MDA Minimum Decision Altitude MSN Manufacturer Serial Number NG Next Generation PFD Primary Flight Display PRESS Pressure RVSM Reduced Vertical Separation Minimums SPD Speed TO Take-Off TRQ Torque

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2.0 SECTION 2 - LIMITATIONS

SYSTEMS AND EQUIPMENT LIMITS

ISU WITH AUTOTHROTTLE (ISU A/T) SYSTEM A copy of the ISU with Autothrottle Pilot’s Guide, 1D-13470, Revision 5, or later appropriate revisions, must be available for access by the flight crew when operating the ISU with Autothrottle system.  The Integrated Standby Unit (ISU) standby instrument functionality is not certified for RVSM operations.  DG mode must be used in locations outside 65° North to 40° South in Latitude. Operating the ISU in magnetic mode near the Earth’s magnetic poles can lead to erroneous readings. Extended Geographical Limits can be achieved when magnetic heading is provided by an IRU/AHRS rated to operate at latitudes outside the 65° North to 40° South limitation.  Caution must be used while navigating in areas of high magnetic declination usually seen in latitudes outside the 65° N to 40° S, as the ISU displays Magnetic heading not True heading.  During approach, the Autothrottle must be disengaged when airplane is at or below Minimum Descend Altitude (MDA) or Decision Altitude (DA).  Continued Autothrottle operation is prohibited following abnormal operation or malfunction prior to corrective maintenance.  Autothrottle operation is limited to use by the left seat pilot.  The use of polarized sunglasses by a flight crew member is prohibited.

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3.0 SECTION 3 - EMERGENCY PROCEDURES

3.23 INTEGRATED STANDBY UNIT (ISU) FAILURES

3.23.1 General

3.23.1.1 Legacy PC-12 Configuration Change references to the second (Standby) Attitude Indicator and the second (Standby) Altimeter, to the Integrated Standby Unit (ISU).

3.23.1.2 PC-12 NG Configuration Change references to the Electronic Standby Instrument System (ESIS) to the Integrated Standby Unit (ISU).

3.23.2 Magnetic Heading Input Failure on ISU Indication: Amber “DG” displayed on ISU.

NOTE

The ISU is only interfaced with AHRS 1 (Legacy PC-12) or ADAHRS 1 (PC-12 NG). Failure of the AHRS 1 or ADAHRS 1 will cause ISU to automatically select directional gyro mode of operation.

If primary flight displays and CAS system do not indicate any heading failures: 1. Heading Use primary flight displays.

If primary flight displays and CAS system indicate only heading failures: 1. ISU Manually set HDG input based on Magnetic Compass.

3.23.3 ISU Attitude or Heading Failure Indication: Red "ATT" and/or “HDG” displayed on ISU during normal operation. 1. ISU Do not use for remainder of flight

3.23.4 ISU Air Data Failure Indication: Red “ALT” and/or “SPD” displayed on ISU during normal operation. 1. ISU Do not use for remainder of flight

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3.23.5 ISU CONFIGURATION – ON GROUND ONLY Indication: Amber “CONFIG” displayed on ISU during normal operation.

1. ISU Check with maintenance for dispatch capability. 2. ISU Autothrottle Autothrottle prohibited for flight

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3.24 AUTOTHROTTLE FUNCTION FAILURES

3.24.1 Autothrottle (All PC-12) NOTE The pilot can disengage the Autothrottle (A/T) by pressing the “A/T DISCON” button on the throttle lever. The pilot can override the A/T by manually controlling the throttle lever and turning off the A/T power by toggling the "A/T PWR" button on the ISU bezel to disengage the A/T.

A loss of power to the ISU or to equipment required by the ISU for the A/T function would cause the A/T to disengage and go to the A/T OFF state.

The ISU is on Battery Bus Power or EPS Bus power and provides power to the A/T Assembly.

The A/T automatically disengages when the ISU does not receive the required engine data for ITT and/or Torque.

3.24.2 Autothrottle Malfunction (A/T FAIL) Indication: Amber “A/T FAIL” displayed on ISU.

1. Throttle Lever Manually control 2. Autothrottle Acknowledge disconnect

WARNING

DO NOT ATTEMPT TO RE-ENGAGE THE AUTOTHROTTLE FOLLOWING AN AUTOTHROTTLE MALFUNCTION FOR THE DURATION OF THE FLIGHT.

3. Aircraft Continue flight without Autothrottle

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3.24.3 Autothrottle Malfunction Indication: Inadvertent or abrupt movement of throttle lever while the Autothrottle is engaged (autopilot may be engaged or not engaged).

1. Throttle Lever Manually override 2. ISU Autothrottle Set to OFF

WARNING

DO NOT ATTEMPT TO RE-ENGAGE THE AUTOTHROTTLE FOLLOWING AN AUTOTHROTTLE MALFUNCTION FOR THE DURATION OF THE FLIGHT. 3.Aircraft Continue flight without Autothrottle

3.24.4 External ADC Input Failure Indication: Amber “EXT ADC FAIL” displayed on ISU.

NOTE Operation of the Autothrottle is not available for takeoff and go-around. A/T function reverts to internal air data parameters for A/T control.

1. Aircraft Continue flight

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4.0 SECTION 4 - NORMAL PROCEDURES

4.1 GENERAL Normal operating procedures are described in the IS&S Pilot's Guide for ISU with Autothrottle System, 1D-13470. The Pilot(s) should be familiar with the operation of the ISU and Autothrottle before using them in flight.

4.3 PREFLIGHT INSPECTION

4.3.8 Cockpit Add: 35. Autothrottle Confirm OFF

4.4 BEFORE STARTING ENGINE For PC-12 NG configuration Change step 8d: 8.d ESIS ALIGNING To the following: 8.d ISU ALIGNING

and

Change step 23: 23. Radios/Avionics SET as required, ESIS aligned To the following: 23. Radios/Avionics SET as required, ISU aligned

For Legacy PC-12 configuration Change step 4: 4. BATT 1 switch ON BATT 2 switch ON (if 2nd battery installed) To the following: 4. BATT 1 switch ON BATT 2 switch ON (if 2nd battery installed) Page 12 of 22

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ISU ALIGNING

and

Add new step 16: 16. ISU ISU aligned

4.6 BEFORE TAXING For PC-12 NG configuration only Change step 7: 7. PFD, MFD CAS, ESIS No flags or red warning captions, all aligned

To the following: 7. PFD, MFD CAS, ISU No flags or red warning captions, all aligned

For all PC-12 configurations Add at the end of the “BEFORE TAXIING” procedure: 8. Autothrottle Test: a) Friction Lock Adjust open b) ISU Autothrottle Select A/T Setup, Select Friction Test: RUN

NOTE

The throttle lever must move freely forward and aft during the test and the reported value on the ISU A/T setup page should be less than 20,000 (unit-less counts).

c) A/T Override Test Perform manually

NOTE

The pilot must be able to manually move the throttle lever during this test without having to use excessive force. Page 13 of 22

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d) If test successful A/T can be used

CAUTION

IF EITHER OF THE AUTOTHROTTLE PRE-FLIGHT TESTS (FRICTION OR OVERRIDE) DO NOT PASS, THE AUTOTHROTTLE SHOULD NOT BE USED DURING FLIGHT UNTIL MAINTENANCE IS PERFORMED ON THE AUTOTHROTTLE SO THAT IT SUCCESSFULLY PASSES THE PRE-FLIGHT TESTS. SEE THE ISU A/T SYSTEM PILOT’S GUIDE OR INSTALLATION MANUAL FOR THE PROCEDURES FOR THESE TESTS.

4.8 BEFORE TAKEOFF For Legacy PC-12 configuration Add the following step: 24. ISU Autothrottle: a) Throttle Lever Select GA (verify command bars in view) b) ISU Autothrottle Verify A/T Take Off torque displayed in magenta

For PC-12 NG configuration

4.8.1 BEFORE DEPARTURE Add the following step: 11. ISU Autothrottle: a) Throttle Lever Select GA (verify command bars in view) b) ISU Autothrottle Verify A/T Take Off torque displayed in magenta

4.9 TAKEOFF For an ISU Autothrottle take-off, change step 3 (Legacy PC-12) or step 2 (PC-12 NG):

CAUTION

“A/T PWR” LINE SELECT KEY SELECTION RESULTS IN IMMEDIATE THROTTLE LEVER ADJUSTMENT FOR TAKEOFF. PILOT MUST MONITOR OPERATION OF THE AUTOTHROTTLE DURING TAKEOFF.

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3. or 2. ISU Autothrottle Press ISU Line Select Key #1 “A/T PWR”

NOTE

The torque limiter assists the pilot in protecting the engine from exceeding engine power limits. The pilot is responsible for verifying the proper selected (calculated) torque value. The pilot needs to monitor proper power advancement of the engaged Autothrottle and take manual control of the throttle if power does not develop sufficiently for takeoff.

Also, add the following note after last step (all PC-12 configurations):

NOTE

After 2.5 minutes in engaged Autothrottle takeoff or go-around mode, the A/T will automatically switch from TO/GA sub mode to climb sub mode over a 10 second transition period.

4.11 CLIMB Change step 3: In order to use Autothrottle for climb: a) ISU Autothrottle Set Climb Torque b) ISU Autothrottle Press ISU LSK #1 “A/T PWR” (not required for an ISU Autothrottle take-off)

4.12 CRUISE Change step 4 (Legacy PC-12) or step 2 (PC-12 NG): 4 or 2. In order to use Autothrottle for cruise: a) ISU Autothrottle Select A/T TRQ or SPD mode b) ISU Autothrottle Press ISU LSK #1 “A/T PWR”

4.13 DESCENT Page 15 of 22

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Change step 2 (Legacy PC-12) or step 3 (PC-12 NG): 2 or 3. In order to use Autothrottle for descent: a) ISU Autothrottle Select A/T TRQ or SPD mode b) ISU Autothrottle Press ISU LSK #2 “A/T ON”

4.14 BEFORE LANDING

4.14.1 APPROACH CHECK Add the following step for all PC-12 configurations: 11. ISU Autothrottle AS DESIRED

NOTE

Airspeed mode is recommended for approaches.

4.14.2 FINAL CHECK Add the following step for all PC-12 configurations: 7. ISU Autothrottle A/T OFF at or below minimums

4.15 BALKED LANDING (GO-AROUND) For all PC-12 configurations, when ISU Autothrottle is ON, change steps 1 and 2: 1. Go Around Switch PRESS 2. THROTTLE LEVER MONITOR (According to Balked Landing Torque chart in Section 5)

NOTE

The torque limiter assists the pilot in protecting the engine from exceeding engine power limits. The pilot is responsible for verifying the proper selected (calculated) torque value. The pilot needs to monitor proper power advancement of the engaged Autothrottle and take manual control of the throttle if power does not develop sufficiently after go-around initiation.

4.17 AFTER LANDING For all PC-12 configurations, add the following step at the end of the procedure: 7. ISU Autothrottle Confirm OFF

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5.0 SECTION 5 - PERFORMANCE No change.

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6.0 SECTION 6 - WEIGHT AND BALANCE Addition of the ISU with Autothrottle kit changes the base aircraft Weight and Balance as follows:

Aircraft Configuration Body Arm (in) Total Weight (lbs) Moment (lbs-in) Legacy PC-12 (PC-12/41/45/47) 225.17 5612.39 1263765.70 PC-12 NG (MSN 1001-1270 and Pre-SB 34-042) 225.17 5612.70 1263806.00 PC-12 NG (MSN 1001-1270 and Post-SB 34-042 225.13 5614.18 1263935.90 OR MSN 1271 and up)

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7.0 SECTION 7 - AIRPLANE AND SYSTEM DESCRIPTION Refer to the ISU with Autothrottle Pilot’s Guide, document number 1D-13470, Revision 5, or later appropriate revision.

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8.0 SECTION 8 - HANDLING, SERVICING AND MAINTENANCE No change.

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9.0 SECTION 9 - SUPPLEMENTS No change.

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10.0 SECTION 10 - SAFETY AND OPERATIONAL TIPS No change.

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