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

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FAA APPROVED

AIRPLANE FLIGHT MANUAL SUPPLEMENT

TO THE

PILATUS PC-12 SERIES AIRPLANE FLIGHT MANUAL

FOR

INTEGRATED STANDBY UNIT WITH AUTOTHROTTLE

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

FAA Approved: 2/14/2019


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REV DESCRIPTION EFFECTED

PAGES FAA APPROVAL

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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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 TAKEOFF ................................................................................................... 14

4.8.1 BEFORE DEPARTURE ....................................................................................... 14

4.9 TAKEOFF ................................................................................................................... 14



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4.11 CLIMB ......................................................................................................................... 15

4.12 CRUISE ...................................................................................................................... 15

4.13 DESCENT .................................................................................................................. 15

4.14 BEFORE LANDING .................................................................................................... 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

aircraft 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 DISCON

Disconnect

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

DO NOT ATTEMPT TO RE-ENGAGE THE AUTOTHROTTLE FOLLOWING AN

AUTOTHROTTLE MALFUNCTION FOR THE DURATION OF THE FLIGHT.

3. Aircraft Continue flight without Autothrottle

WARNING



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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

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

WARNING



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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)



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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.



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d) If test successful A/T can be used

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):

“A/T PWR” LINE SELECT KEY SELECTION RESULTS IN IMMEDIATE THROTTLE LEVER

ADJUSTMENT FOR TAKEOFF. PILOT MUST MONITOR OPERATION OF THE

AUTOTHROTTLE DURING TAKEOFF.

CAUTION

CAUTION



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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



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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 OR MSN 1271 and up)

225.13 5614.18 1263935.90



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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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