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Innovative Solutions & Support Document No.: 1D-13466 1500 District Avenue Revision: IR Burlington, MA 01803
Page 1 of 22
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
Innovative Solutions & Support Document No.: 1D-13466 1500 District Avenue Revision: IR Burlington, MA 01803
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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.
FAA Approved: 2/14/2019
Innovative Solutions & Support Document No.: 1D-13068 1500 District Avenue Revision: IR Burlington, MA 01803
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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
FAA Approved: 2/14/2019
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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
FAA Approved: 2/14/2019
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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.
FAA Approved: 2/14/2019
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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
FAA Approved: 2/14/2019
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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.
FAA Approved: 2/14/2019
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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
FAA Approved: 2/14/2019
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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
FAA Approved: 2/14/2019
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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
FAA Approved: 2/14/2019
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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
FAA Approved: 2/14/2019
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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
FAA Approved: 2/14/2019
Innovative Solutions & Support Document No.: 1D-13466 1500 District Avenue Revision: IR Burlington, MA 01803
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5.0 SECTION 5 - PERFORMANCE
No change.
FAA Approved: 2/14/2019
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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
FAA Approved: 2/14/2019
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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.
FAA Approved: 2/14/2019
Innovative Solutions & Support Document No.: 1D-13466 1500 District Avenue Revision: IR Burlington, MA 01803
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8.0 SECTION 8 - HANDLING, SERVICING AND MAINTENANCE
No change.
FAA Approved: 2/14/2019
Innovative Solutions & Support Document No.: 1D-13466 1500 District Avenue Revision: IR Burlington, MA 01803
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9.0 SECTION 9 - SUPPLEMENTS
No change.
FAA Approved: 2/14/2019
Innovative Solutions & Support Document No.: 1D-13466 1500 District Avenue Revision: IR Burlington, MA 01803
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10.0 SECTION 10 - SAFETY AND OPERATIONAL TIPS
No change.
FAA Approved: 2/14/2019