Application Revisions Next Assy Used On Rev. Description Date Approved Approved 9K-88130-1 9K-88130-1 1 Initial Release per EC 14344 6/13/19 DB

PROPRIETARY THE RIGHTS OF INNOVATIVE SOLUTIONS & SUPPORT INC. ARE INCLUDED IN THE INFORMATION DISCLOSED HEREIN. THIS DRAWING AND/OR DOCUMENT SHALL NOT BE REPRODUCED OR TRANSFERRED TO OTHER DOCUMENTS OR USED OR DISCLOSED TO OTHERS FOR MANUFACTURING OR FOR ANY PURPOSE EXCEPT AS SPECIFICALLY AUTHORIZED IN WRITING BY INNOVATIVE SOLUTIONS & SUPPORT INC.

PILOTS GUIDE

Integrated Stand-By Unit with (ISU A/T) P/N: 9K-88130-1 for B-200 King Air – Pro Line 21

Contract Number:

Contractor:

Written By: D. Kemper Date: 5/24/19 PILOTS GUIDE Checker: Date: Integrated Stand-by Unit (ISU)

Engineer: D. Kemper Date: 6/13/19 with AutoThrottle (A/T)

Document Approval: D. Babe Date: 6/13/19 CAGE CODE

QA Approval: B. Urbanski Date: 6/13/19 0EUW0 1D-13714

Design Approval: M. Knopf Date: 6/13/19 Form# 07315-372 Rev - SHEET 1 of 50

REVISION HISTORY

Rev 1 Initial Release of document

TITLE CAGE CODE PILOTS GUIDE Integrated Standby Unit with Autothrottle 0EUW0 1D-13714

Use & disclosure is governed by the statement on the document cover page. REVISION LEVEL 1 SHEET 2 of 50

TABLE OF CONTENTS

1.0 INTRODUCTION ...... 9 1.1 DESCRIPTION ...... 9 1.2 PURPOSE ...... 9 1.3 ABBREVIATIONS ...... 10

2.0 OPERATING THEORY ...... 11 2.1 AUTOTHROTTLE ...... 11 2.2 INTEGRATED STANDBY UNIT ...... 11 2.3 INITIALIZATION ...... 12 2.3.1 Autothrottle Friction Test ...... 13 2.4 AUTOTHROTTLE MODES OF OPERATION ...... 14 2.4.1 TORQUE Mode ...... 14 2.4.2 (TORQUE) Mode ...... 15 2.4.3 GO-AROUND (TORQUE) Mode ...... 15 2.4.4 OUT Mode (VMC Protection) ...... 16 2.4.5 (TORQUE) Mode ...... 16 2.4.6 Mode ...... 16 2.4.7 TURBULENCE (SPEED) Mode ...... 18 2.4.8 Changing Autothrottle Modes ...... 18 2.5 PROTECTION MODES ...... 19 2.5.1 Temperature Protection ...... 19 2.5.2 Over / Under-Speed Protection ...... 19

3.0 SYSTEM DESCRIPTION ...... 20 3.1 AUTOTHROTTLE ...... 20 3.1.1 A/T Actuators ...... 20 3.1.2 A/T ENGAGED Annunciator ...... 21 3.1.3 ISU With Autothrottle ...... 21 3.2 INTEGRATED STANDBY UNIT (ISU) ...... 21 3.2.1 Tile 1 – Left Side of ISU ...... 22 3.2.1.1 ...... 22 3.2.1.1.1 Airspeed Color Band ...... 22 3.2.1.1.2 Mach Display...... 23 3.2.1.1.3 Airspeed Failure Warning Flag ...... 23 3.2.1.2 Attitude Direction Indicator (ADI) ...... 23 3.2.1.2.1 Attitude Alignment ...... 23 3.2.1.2.2 Pitch Ladder ...... 24 3.2.1.2.3 Roll Indicator ...... 24 3.2.1.2.4 ADI Failure Warning Flag ...... 25 3.2.1.3 ...... 25

TITLE CAGE CODE PILOTS GUIDE Integrated Standby Unit with Autothrottle 0EUW0 1D-13714

Use & disclosure is governed by the statement on the document cover page. REVISION LEVEL 1 SHEET 3 of 50

TABLE OF CONTENTS 3.2.1.3.1 Barometric Correction ...... 25 3.2.1.3.2 Altimeter Failure Warning Flag ...... 26 3.2.1.3.3 External Baro Sync (Optional) ...... 26 3.2.1.4 Vertical Speed ...... 26 3.2.2 Tile 2 – Right Side of ISU ...... 26 3.2.2.1 Horizontal Situation Indicator (HSI) ...... 26 3.2.2.2 Heading Source ...... 27 3.2.2.2.1 Heading Failure Flag ...... 28 3.2.2.3 NAV Source ...... 28 3.2.3 ISU Failure Flags ...... 30 3.2.4 Tile 3 – Autothrottle Display Parameters ...... 31 3.2.4.1 Autothrottle Mode ...... 31 3.2.4.2 Autothrottle Annunciations ...... 31 3.2.5 Modifiable Parameters ...... 32 3.2.5.1 BARO CORRECTION ...... 33 3.2.5.2 A/T SETPOINT ...... 33 3.2.5.3 HDG SLEW ...... 33 3.2.5.4 COURSE ...... 33 3.2.6 ISU Bezel Button Controls ...... 34 3.2.6.1 A/T Status LED ...... 35 3.2.7 Power Lever Controls ...... 35 3.3 MAIN MENU ...... 36 3.3.1 Initializing Gross Takeoff Weight ...... 36 3.3.2 Adjust Gross Weight ...... 37 3.3.3 Display Brightness ...... 38 3.3.4 Service Mode ...... 38 3.3.5 ISU CONFIG Menu ...... 39 3.4 SERVICE MODE ...... 41 3.4.1 Service Menu ...... 41 3.4.2 A/T STATUS Page ...... 42 3.4.3 A/T CONFIG Page ...... 42 3.4.4 DATALOAD Page ...... 43 3.4.5 EVENT LOG Page ...... 43 3.4.6 CALIBRATION Page ...... 44

4.0 FAULT DETECTION ...... 45 4.1 SYSTEM FAULTS ...... 45 4.2 FRICTION CALIBRATION ...... 48

5.0 TROUBLESHOOTING ...... 49

TITLE CAGE CODE PILOTS GUIDE Integrated Standby Unit with Autothrottle 0EUW0 1D-13714

Use & disclosure is governed by the statement on the document cover page. REVISION LEVEL 1 SHEET 4 of 50

TABLE OF CONTENTS 6.0 SOFTWARE LOADING ...... 50

TITLE CAGE CODE PILOTS GUIDE Integrated Standby Unit with Autothrottle 0EUW0 1D-13714

Use & disclosure is governed by the statement on the document cover page. REVISION LEVEL 1 SHEET 5 of 50

LIST OF TABLES Table / Title Page

Table 3-1 Airspeed Color Bar ...... 22 Table 3-2 Bearing Pointer Display Formats ...... 28 Table 3-3 ISU Failure Flags ...... 30 Table 3-4 Autothrottle Annunciations ...... 31 Table 4-1 Autothrottle System Faults ...... 45

TITLE CAGE CODE PILOTS GUIDE Integrated Standby Unit with Autothrottle 0EUW0 1D-13714

Use & disclosure is governed by the statement on the document cover page. REVISION LEVEL 1 SHEET 6 of 50

LIST OF FIGURES Figure / Title Page

Figure 2-1 ISU - Aligning Flag ...... 12 Figure 2-2 Integrated Standby Unit ...... 13 Figure 2-3 ISU – TORQUE Mode ...... 14 Figure 2-4 ISU – TAKEOFF / GO AROUND Mode ...... 15 Figure 2-5 ISU – AIRSPEED Mode ...... 17 Figure 2-6 ISU – Zoomed Selected Airspeed ...... 18 Figure 3-1 ISU A/T Installed Panel Locations ...... 20 Figure 3-2 A/T Engaged Annunciator ...... 21 Figure 3-3 ISU Display Tiles ...... 21 Figure 3-4 ISU Display Elements ...... 22 Figure 3-5 Airspeed Color Bar ...... 23 Figure 3-6 ALIGNING Flag ...... 24 Figure 3-7 Pitch Ladder ...... 24 Figure 3-8 Roll Indicator ...... 24 Figure 3-9 Altimeter Normal and Metric Display ...... 25 Figure 3-10 Baro Correction ...... 26 Figure 3-11 Horizontal Situation Indicator (HSI) ...... 27 Figure 3-12 CDI and Bearing Pointer Display ...... 29 Figure 3-13 Selected Course - Zoomed ...... 29 Figure 3-14 Glide Slope/Localizer Display ...... 29 Figure 3-15 ISU Invalid Parameter Flags ...... 30 Figure 3-16 Autothrottle Window ...... 31 Figure 3-17 ISU Control Features ...... 34 Figure 3-18 A/T Power Lever Controls ...... 35 Figure 3-19 ISU - MAIN MENU ...... 36 Figure 3-20 Gross Takeoff Weight Entry ...... 37 Figure 3-21 MAIN MENU - Gross Weight ...... 37 Figure 3-22 MAIN MENU – Brightness Adjustment ...... 38 Figure 3-23 MAIN MENU – Service Mode ...... 38 Figure 3-24 ISU CONFIG MENU ...... 39 Figure 3-25 ISU – Service Menu ...... 41 Figure 3-26 Service Mode – Autothrottle Status Page ...... 42

TITLE CAGE CODE PILOTS GUIDE Integrated Standby Unit with Autothrottle 0EUW0 1D-13714

Use & disclosure is governed by the statement on the document cover page. REVISION LEVEL 1 SHEET 7 of 50

LIST OF FIGURES Figure / Title Page Figure 3-27 Service Mode – Autothrottle Configuration Page ...... 42 Figure 3-28 Service Mode – Dataload Page ...... 43 Figure 3-29 Service Mode – Event Log Page ...... 43 Figure 3-30 Service Mode – Calibration Page ...... 44

TITLE CAGE CODE PILOTS GUIDE Integrated Standby Unit with Autothrottle 0EUW0 1D-13714

Use & disclosure is governed by the statement on the document cover page. REVISION LEVEL 1 SHEET 8 of 50

1.0 INTRODUCTION

1.1 DESCRIPTION

The Integrated Standby Unit with ThrustSenseTM Autothrottle is manufactured by Innovative Solutions and Support, located in Exton, PA. It is designed to meet the performance requirements of IS&S specification 1R-84176.

The autothrottle system provides automatic control of each engine’s power to maintain the selected torque or airspeed. The autothrottle also offers advanced alerting and protection against inadvertent excursions into unsafe engine operating conditions, including temperature and torque, as well as unsafe . Control of the autothrottle is provided by the installation of the IS&S Integrated Stand-by Unit (ISU).

The ISU uses internal standalone sensors to calculate and display the following data:  Attitude (Roll, Bank, and /Skid)  Unusual Attitude Chevrons  Heading (360 degree HSI perspective)  Airspeed / Mach (with Color Band Speed Cues)  Pressure and Corrected (InHg and HPA)  Vertical Speed

In addition to the basic standby display functions of Attitude, Airspeed, Altitude, and Heading, the ISU supports the display of the following configurable items:  Lateral and Vertical Navigation Deviation Scales and Pointers  VOR / ILS / FMS Bearing pointers

1.2 PURPOSE This document is intended to provide a detailed description of the functions and features of the IS&S Integrated Standby Unit (ISU) with ThrustSenseTM Autothrottle, Part Number 9D-94176-1 when installed in King Air aircraft. Functionality of that are not directly affected by the installation of this system are not included in this document.

TITLE CAGE CODE PILOTS GUIDE Integrated Standby Unit with Autothrottle 0EUW0 1D-13714

Use & disclosure is governed by the statement on the document cover page. REVISION LEVEL 1 SHEET 9 of 50

1.3 ABBREVIATIONS

ACK Acknowledge ADC Air Data AFM Flight Manual AHRS Attitude Heading Reference System ALT Altitude 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 FGP Flight Guidance Panel FLC Change Mode GA Go Around DH Decision Height DISC or Disconnect DISCON HDG Heading IN Inches ISU Integrated Standby Display Unit ISU A/T Integrated Standby Unit with Autothrottle ITT Inter Turbine Temperature LBS Pounds MENU Menu MDA Minimum Decision Altitude MFK Multi-Function Knob MSN Manufacturer Serial Number NG Next Generation PCL Power Control Lever PFD PRESS Pressure RVSM Reduced Vertical Separation Minimums SPD Speed TO Take-Off TRQ Torque

TITLE CAGE CODE PILOTS GUIDE Integrated Standby Unit with Autothrottle 0EUW0 1D-13714

Use & disclosure is governed by the statement on the document cover page. REVISION LEVEL 1 SHEET 10 of 50

2.0 OPERATING THEORY

2.1 AUTOTHROTTLE

The autothrottle system controls engine power by moving each engine’s power lever using a pair of motorized actuator assemblies installed within the aircraft’s center pedestal. The actuators incorporate a clutchless drive shaft mechanism, which can easily be over-ridden with a nominal amount of pressure. CAUTION: The pilot must ensure the Controls are adjusted to maintain a safe propeller speed (Np) for the power (Torque) being set by the autothrottle.

The autothrottle operates in one of two primary modes, TORQUE or AIRSPEED. In TORQUE mode, the autothrottle controls engine power to maintain a specific engine torque. In AIRSPEED mode, the autothrottle controls engine power to maintain a specific airspeed. The autothrottle receives performance parameters (Torque, RPM, Oil Pressure, and ITT) from each engine, Airspeed from the (ADC), and Selected Airspeed from the Flight Guidance Panel (FGP).

2.2 INTEGRATED STANDBY UNIT The Integrated Standby Unit is a standalone display and data processing unit designed to provide an independent standby reference for primary flight parameters. It incorporates internal gyros and accelerometers to determine aircraft attitude and accelerations. The ISU also has integral pressure transducers to integrate with the copilot’s Pitot/Static system to calculate air data parameters such as Altitude, Airspeed, and Vertical Speed. The ISU receives data from the remotely mounted standby Magnetic Sensor Unit to determine Magnetic Heading. All standby data is displayed on the ISU’s integrated color AMLCD display.

To improve data accuracy, availability, and usability, the ISU is capable of receiving Air Data from the primary ADC, and Heading reference from the AHRS systems. This allows the autothrottle functions to synchronize with the same input data that is being shown on the primary displays.

TITLE CAGE CODE PILOTS GUIDE Integrated Standby Unit with Autothrottle 0EUW0 1D-13714

Use & disclosure is governed by the statement on the document cover page. REVISION LEVEL 1 SHEET 11 of 50

To improve emergency availability, the ISU is normally powered by a battery backed power supply. This allows the ISU to operate either from one of the primary power busses, or to run independent of the engine generators or aircraft battery for at least 30 minutes. When operating on the battery backup, the autothrottle capabilities are not available. ISU power is controlled by a separate (ESIS) toggle switch located on the lower left side of the instrument panel.

2.3 INITIALIZATION The ISU powers up in the normal operating mode seconds after power is applied to the system. Initialization of attitude takes approximately 60 seconds after power up. During this period, the ISU displays the Aligning warning flag as shown in Figure 2-1. The indicated attitude should not be used during alignment. The Airspeed Indicator, Altimeter, and the Vertical Speed Indicator (VSI) will be displayed as soon as valid air data is computed by the internal pressure sensors. Magnetic Heading will be displayed as soon as magnetic sensor data is available.

Note: The aircraft should be kept stable during the alignment period.

Figure 2-1 ISU - Aligning Flag

After Alignment, the ISU will display the normal operational display as shown in Figure 2-2. Each feature of the ISU display is described in subsequent sections. The bottom of the ISU display is reserved for autothrottle indications.

TITLE CAGE CODE PILOTS GUIDE Integrated Standby Unit with Autothrottle 0EUW0 1D-13714

Use & disclosure is governed by the statement on the document cover page. REVISION LEVEL 1 SHEET 12 of 50

Figure 2-2 Integrated Standby Unit

2.3.1 Autothrottle Friction Test

Part of the ISU initialization includes an automated test to verify autothrottle functionality and power lever friction. If these tests determine a critical fault, the autothrottle functionality will be disabled. The autothrottle Friction Test is only run if the aircraft is on the ground and the engine is not running. This test verifies the ability of the autothrottle to drive the Power Control Levers through their full range of motion. When the test is running, each power control lever will individually advance to full power position and then retard to the idle position before disconnecting control. Each lever will advance forward and backward twice. If this test determines that the friction level within the range of motion is too high, the test will stop and “A/T CAL REQ” will be annunciated at the bottom of the ISU display. If calibration is required, the pilot should perform the Friction Calibration Procedure described in Section 4.2 before attempting to use the autothrottle.

TITLE CAGE CODE PILOTS GUIDE Integrated Standby Unit with Autothrottle 0EUW0 1D-13714

Use & disclosure is governed by the statement on the document cover page. REVISION LEVEL 1 SHEET 13 of 50

2.4 AUTOTHROTTLE MODES OF OPERATION

The autothrottle functions in various operating modes. All of the operating modes function by regulating engine power to maintain either a target TORQUE or AIRSPEED. The sub-modes differ by using a target value appropriate for the intended functionality.

2.4.1 TORQUE Mode

In TORQUE mode the autothrottle controls the power of each engine to the selected target torque as indicated on the ISU display. In manual TORQUE mode, the target torque is selected by rotating the MFK knob to set a desired torque value. Other Torque sub-modes command predetermined torque levels including: TAKEOFF, CLIMB, GO-AROUND, and ITT PROTECTION modes.

Figure 2-3 ISU – TORQUE Mode

TORQUE mode is indicated by the “A/T TORQUE” annunciation that displays the current target torque value (ft-lbs). Rotating the ISU knob will adjust the target torque, and the torque value will zoom up in size with a white border while it is being adjusted for easier readability. When adjustment is complete, the value will zoom back down. If the target torque is adjusted while the autothrottle is engaged in torque mode, the new target is effective immediately.

TITLE CAGE CODE PILOTS GUIDE Integrated Standby Unit with Autothrottle 0EUW0 1D-13714

Use & disclosure is governed by the statement on the document cover page. REVISION LEVEL 1 SHEET 14 of 50

2.4.2 TAKEOFF (TORQUE) Mode

In TAKEOFF mode the autothrottle controls the power of each engine to output the recommended maximum takeoff torque. TAKEOFF mode is a Torque sub-mode, and is the only autothrottle mode available for engagement when the aircraft is on ground. Adjusting the target torque while in Takeoff Mode will cause the active mode to revert to manual Torque mode. TAKEOFF mode is armed by pressing the GA button, located on the left power control lever (see Figure 3-18). When TAKEOFF mode is armed “A/T TAKEOFF” (magenta) will be annunciated on the ISU. After pre-takeoff checks are complete and the aircraft is lined up on the , autothrottle assisted takeoff is initiated by pressing the A/T PWR key on the ISU to engage the autothrottle. Takeoff torque will be maintained until the power is automatically reduced to CLIMB power after 2 ½ minutes, unless the target torque is manually adjusted, or a different mode is selected.

Figure 2-4 ISU – TAKEOFF / GO AROUND Mode

2.4.3 GO-AROUND (TORQUE) Mode If the GA button is pressed while airborne, the autothrottle will enter GO-AROUND mode. GO- AROUND mode is a Torque sub-mode. In GO-AROUND mode, the autothrottle controls the power of each engine to output maximum torque. GO-AROUND mode is selected by pressing the GA button while in the air. When selected, the target torque is automatically set to the maximum torque value and displayed in magenta. If the TITLE CAGE CODE PILOTS GUIDE Integrated Standby Unit with Autothrottle 0EUW0 1D-13714

Use & disclosure is governed by the statement on the document cover page. REVISION LEVEL 1 SHEET 15 of 50

autothrottle is not already active, pressing the A/T PWR key will activate the autothrottle. When GO-AROUND mode is active “GO-AROUND” will be annunciated in magenta on the ISU. Like Takeoff mode, maximum torque will be maintained until the power is automatically reduced to CLIMB power after 2 ½ minutes (unless the target torque is manually adjusted or a different mode is selected).

2.4.4 ENGINE OUT Mode (VMC Protection)

In most modes, if the autothrottle detects an engine failure it will automatically disconnect. However, if TAKEOFF or GO-AROUND modes are active, the autothrottle will enter ENGINE OUT protection mode. This protection mode will target the maximum available torque on the operating engine. The pilot will be able to adjust the target torque setting as long as the airspeed is above VMCA. If the airspeed falls below VMC, the autothrottle will reduce the torque as needed to avoid over powering authority. Below minimum controllable airspeed, the target torque value will be blacked out and cannot be manually adjusted using the ISU A/T.

2.4.5 CLIMB (TORQUE) Mode In CLIMB mode the autothrottle controls the power of each engine to the recommended climb torque. CLIMB mode is a Torque sub-mode, and is entered automatically when the are at or near maximum power 2 ½ minutes after Takeoff or Go-Around mode is initiated. In CLIMB mode, the target torque is reduced to climb power which is displayed in magenta. Climb torque is maintained until the target torque is adjusted manually or another mode is selected.

2.4.6 AIRSPEED Mode In AIRSPEED mode the autothrottle controls the power of each engine to maintain the target airspeed indicated on the ISU A/T display. Other Airspeed sub-modes command predetermined airspeeds including: AIRSPEED and TURBULENCE modes.

TITLE CAGE CODE PILOTS GUIDE Integrated Standby Unit with Autothrottle 0EUW0 1D-13714

Use & disclosure is governed by the statement on the document cover page. REVISION LEVEL 1 SHEET 16 of 50

Figure 2-5 ISU – AIRSPEED Mode

Airspeed mode is indicated by the “A/T SPEED:” annunciation that displays the current target airspeed value (knots). The target airspeed is displayed in cyan text. The target airspeed is synchronized with the Selected Airspeed set using the Flight Guidance Panel (FGP). In some configurations, the target airspeed is adjusted by rotating the Multifunction Knob (as shown in Figure 3-17) after “A/T SPEED:” is selected. Pressing the knob will highlight the selected parameter, indicating its value can be adjusted. While being adjusted, the target airspeed values displayed on the ISU A/T will zoom up in size as shown in Figure 2-6.

Target airspeed is always limited between Speed and Maximum Operating Airspeed based on aircraft configuration. The autothrottle will automatically adjust the minimum and maximum selectable airspeed based on: Gross Weight, Position, De-Icing activation, and MMO speeds.

CAUTION: The autothrottle AIRSPEED mode is not compatible with the Flight Level Change (FLC) mode and they must not be activated at the same time. In FLC mode, the autopilot will adjust aircraft pitch to control airspeed. In AIRSPEED mode, the autothrottle will adjust engine power to control airspeed. These modes will be in conflict and may result in undesirable aircraft performance.

TITLE CAGE CODE PILOTS GUIDE Integrated Standby Unit with Autothrottle 0EUW0 1D-13714

Use & disclosure is governed by the statement on the document cover page. REVISION LEVEL 1 SHEET 17 of 50

Figure 2-6 ISU – Zoomed Selected Airspeed

2.4.7 TURBULENCE (SPEED) Mode In TURBULENCE mode, the autothrottle controls the power of each engine to maintain Turbulence Penetration Speed. TURBULENCE mode is an Airspeed sub-mode. TURBULENCE mode is selected from the Main Menu. When selected, the autothrottle is switched into AIRSPEED mode and the target airspeed is automatically set to the recommended Turbulent Air Penetration Speed. If the autothrottle is not already active, pressing the A/T PWR key will activate the autothrottle.

2.4.8 Changing Autothrottle Modes

The autothrottle mode can be changed from TORQUE to AIRSPEED, or AIRSPEED to TORQUE by pressing and the ISU MFK knob for 2 seconds. The mode can be changed while the autothrottle is engaged or disengaged. AIRSPEED mode is not available while on the ground. When one of the sub-modes is active (e.g. TAKEOFF, CLIMB, GO-AROUND, TURBULENCE), adjusting the target torque or airspeed will revert the mode to the primary mode.

TITLE CAGE CODE PILOTS GUIDE Integrated Standby Unit with Autothrottle 0EUW0 1D-13714

Use & disclosure is governed by the statement on the document cover page. REVISION LEVEL 1 SHEET 18 of 50

2.5 PROTECTION MODES

2.5.1 Temperature Protection

If the Interstage-Turbine Temperature (ITT) for either engine reaches the defined limit (slightly less than the maximum), the autothrottle’s temperature protection logic will activate to protect the engine from potential over-temperature damage. The temperature limits are slightly higher for TAKEOFF and GO-AROUND modes.

If the maximum operating temperature is reached with the autothrottle engaged, the autothrottle will automatically switch to ITT Protection (TORQUE) mode and gradually decrease the target torque (from the current torque value) in an attempt to remain within temperature limits. The target torque will be blacked out and cannot be adjusted until the temperature is reduced below the ITT limit. CAUTION: The automatic reduction in engine power alone may not be sufficient to decrease engine temperature. The pilot should also consider decreasing aircraft pitch attitude and increasing airspeed as appropriate to maximize engine cooling.

2.5.2 Over / Under-Speed Protection

When the autothrottle is engaged in TORQUE mode, the airspeed protection logic protects against inadvertent under-speed or over-speed conditions. The autothrottle continuously monitors airspeed data to ensure it remains within a safe envelope. The autothrottle uses aircraft Gross Weight, Attitude, Flap Position and De-Ice Protection to determine the minimum and maximum safe airspeed limits. If the airspeed approaches the minimum or maximum safe airspeed, the autothrottle will automatically switch into AIRSPEED mode with the target speed set to a value within the upper and lower limits. The target speed will be blacked out and cannot be adjusted until the airspeed has decreased or increased within the safe limits. If the target speed that is selected becomes too high or too low based on changes in aircraft configuration that effect maximum or minimum airspeeds, the autothrottle will automatically adjust the selected speed to the new maximum or minimum airspeed.

TITLE CAGE CODE PILOTS GUIDE Integrated Standby Unit with Autothrottle 0EUW0 1D-13714

Use & disclosure is governed by the statement on the document cover page. REVISION LEVEL 1 SHEET 19 of 50

3.0 SYSTEM DESCRIPTION

3.1 AUTOTHROTTLE

The autothrottle system consists of the Integrated Stand-by Unit (ISU), the left and right Actuators which are attached to the Power Levers within the center pedestal, the A/T Engaged (A/T ENG) Annunciator on the instrument panel, and the A/T DISC button attached to the right Power Lever. The microprocessor within the ISU processes aircraft and engine performance signals from the ADC, AHRS, and the each engine to control each of the A/T Actuators to achieve the desired performance.

3.1.1 A/T Actuators

The autothrottle system employs a gearless driveshaft mechanism without the need for a physical clutch. Each of the Power Levers is controlled by its own actuator/driveshaft assembly. When the autothrottle is disconnected, it remains physically connected to the Power Lever mechanism. The autothrottle “disconnect” is a transition into a state where the actuator motors become passive and will not drive the Power Levers. When disconnected, the autothrottle mechanism imposes a slight amount of friction from the driveshaft when the Power Levers are moved. When engaged, the autothrottle may easily be over-ridden by applying the nominal force required to cause the driveshaft to slip.

Figure 3-1 ISU A/T Installed Panel Locations

TITLE CAGE CODE PILOTS GUIDE Integrated Standby Unit with Autothrottle 0EUW0 1D-13714

Use & disclosure is governed by the statement on the document cover page. REVISION LEVEL 1 SHEET 20 of 50

3.1.2 A/T ENGAGED Annunciator

The autothrottle system includes an annunciator located on the instrument panel to the right of the pilot’s primary flight display, as indicated in Figure 3-1. The annunciator text “A/T ENG” is illuminated (green) to indicate when the autothrottle is engaged.

Figure 3-2 A/T Engaged Annunciator

3.1.3 ISU With Autothrottle

The ISU contains the A/T Processor, Color LCD Display, and UI Controls. The ISU is mounted near the center of the instrument panel. The ISU LCD displays primary flight as well as autothrottle parameters. The bottom of the ISU display (Tile 3) is reserved to display autothrottle information. When active, it displays: the autothrottle mode, Target Torque or Airspeed, Protection Mode, and A/T Annunciations.

Figure 3-3 ISU Display Tiles

3.2 INTEGRATED STANDBY UNIT (ISU)

The ISU display is broken into three (3) sections. The left portion of the display is considered Tile 1 and the right portion of the display is considered Tile 2. The lower portion of the display (Tile 3) is reserved for autothrottle indications. Tile 1 displays the Airspeed, Attitude Altitude, Vertical Speed, Baro Correction, Mach, and Localizer and Glideslope Deviation Scales. Tile 2

TITLE CAGE CODE PILOTS GUIDE Integrated Standby Unit with Autothrottle 0EUW0 1D-13714

Use & disclosure is governed by the statement on the document cover page. REVISION LEVEL 1 SHEET 21 of 50

displays the Heading, Nav Source, Adjustable Settings and the Menu. Refer to Figure 3-5 for instrument depictions and locations.

Figure 3-4 ISU Display Elements

3.2.1 Tile 1 – Left Side of ISU

3.2.1.1 Airspeed Indicator

The Airspeed indicator tape is displayed on the left side of Tile 1. The (IAS) data is computed directly from pressure measurements taken from the Pitot Static System of the aircraft and is in the units of knots.

3.2.1.1.1 Airspeed Color Band

The airspeed color band is located to the right side of the Airspeed tape. The color band can provide fast recognition of operating airspeed ranges that are critical for safe flight.

Table 3-1 Airspeed Color Bar

Color Bar Minimum (kts) Maximum (kts) Low Speed Awareness Range Red Min IAS 73 Stall Speed Range White 73 95 Safe Flap Operating Range Green/White 95 140 Normal Operating Range Green 140 Vmo/Mmo High Speed Awareness Range Red Vmo/Mmo Max IAS

TITLE CAGE CODE PILOTS GUIDE Integrated Standby Unit with Autothrottle 0EUW0 1D-13714

Use & disclosure is governed by the statement on the document cover page. REVISION LEVEL 1 SHEET 22 of 50

Figure 3-5 Airspeed Color Bar

3.2.1.1.2 Mach Display The ISU includes a display of the at the bottom of the Airspeed Tape in Tile 1. The Mach number is displayed in the format of 0.XXX as shown in Figure 3-5. Mach will be displayed if above 0.400 to a limit of 0.999 and will be removed from the display if it decreases under 0.380.

3.2.1.1.3 Airspeed Failure Warning Flag

If the airspeed data from the internal Piot/ transducers is invalid the Airspeed Tape indicator will be replaced with a red SPD warning flag. Refer to Figure 3-15 for ISU failure flags.

3.2.1.2 Attitude Direction Indicator (ADI) The ADI is displayed in the center of Tile 1 and provides the necessary Pitch and Roll information. The /Ground depiction is representative of what is seen from the pilot’s perspective looking out of the which provides a quick reference of attitude. For any pitch between ±85° a portion of the sky and ground will always be visible for quick attitude determination.

3.2.1.2.1 Attitude Alignment

At startup the ISU will display an amber ALIGNING flag on the ADI. The flag indicates the ISU is initializing. Once initialization is complete, the flag will be removed indicating the ISU is ready for use. Flight crew should wait for the ISU to complete initialization and the flag is removed before use.

TITLE CAGE CODE PILOTS GUIDE Integrated Standby Unit with Autothrottle 0EUW0 1D-13714

Use & disclosure is governed by the statement on the document cover page. REVISION LEVEL 1 SHEET 23 of 50

Figure 3-6 ALIGNING Flag

3.2.1.2.2 Pitch Ladder

The pitch ladder shows the pitch of the aircraft and gives warnings for extreme pitch. The Sky/Ground depiction is separated by 0° pitch. Red chevrons are displayed when the pitch angle is either too high or low as shown in Figure 3-7.

Figure 3-7 Pitch Ladder

3.2.1.2.3 Roll Indicator

The Roll indicator (see Figure 3-8) provides the Roll angle for the aircraft and gives a warning when the roll angle exceeds 35° by changing to amber. The Roll indicator displays gradations for every 10° of roll between ±30°.

Figure 3-8 Roll Indicator

TITLE CAGE CODE PILOTS GUIDE Integrated Standby Unit with Autothrottle 0EUW0 1D-13714

Use & disclosure is governed by the statement on the document cover page. REVISION LEVEL 1 SHEET 24 of 50

3.2.1.2.4 ADI Failure Warning Flag

If the data from the internal sensors are invalid the will be replaced with a red ATT warning flag. Refer to Figure 3-15 for ISU failure flags.

3.2.1.3 Altimeter

The ISU provides an Altitude Tape that is located on the right side of Tile 1. It displays the altitude in feet above mean (MSL). It can also display the altitude in meters if the “METRIC DISPLAY” option is enabled in the ISU configuration menu.

Figure 3-9 Altimeter Normal and Metric Display

3.2.1.3.1 Barometric Correction

The Barometric Correction indicates the Barometric Altitude Correction value. The default Baro Correction is 29.92 InHg/1013 HPa. Baro Correction is adjusted by rotating the ISU MFK knob. Rotating the knob CW increases the value and Rotating the knob CCW decreases the value. When the Baro Correction value is being adjusted the displayed value will zoom up in size.

TITLE CAGE CODE PILOTS GUIDE Integrated Standby Unit with Autothrottle 0EUW0 1D-13714

Use & disclosure is governed by the statement on the document cover page. REVISION LEVEL 1 SHEET 25 of 50

Figure 3-10 Baro Correction

3.2.1.3.2 Altimeter Failure Warning Flag

If the data from the internal Static Air pressure sensor is invalid the Altitude Tape indicator will be replaced with a red ALT warning flag. Refer to Figure 3-15 for ISU failure flags.

3.2.1.3.3 External Baro Sync (Optional)

If external Baro Correction is configured, the ISU Baro Correction will be synchronized to the pilot’s PFD and manual adjustment on the ISU will be disabled. If the external Baro Correction is not received, the ISU will allow manual adjustment of the Baro Correction.

3.2.1.4 Vertical Speed

The Vertical Speed is displayed numerically above the altitude tape. This will be a digital value with an arrow to indicate the direction.

If the data from the internal Static Air pressure sensor is invalid the Vertical Speed indication will be replaced with a red VERT warning flag. Refer to Figure 3-15 for ISU failure flags.

3.2.2 Tile 2 – Right Side of ISU

3.2.2.1 Horizontal Situation Indicator (HSI)

Aircraft Heading is displayed as a Horizontal Situation Indicator (HSI) with 360 rose in the center of Tile 2. It displays heading numerically and as compass orientation with gradations of 10° and labels every 30° with cardinal headings labeled as ‘N’, ‘S’, ‘E’, and ‘W’ respectively.

TITLE CAGE CODE PILOTS GUIDE Integrated Standby Unit with Autothrottle 0EUW0 1D-13714

Use & disclosure is governed by the statement on the document cover page. REVISION LEVEL 1 SHEET 26 of 50

Figure 3-11 Horizontal Situation Indicator (HSI)

3.2.2.2 Heading Source

The heading reference for the HSI is indicated next to the numeric heading display. The default source for heading is the external magnetic sensor which is represented by a green ‘M’ indication. Directional Gyro (DG) mode is selectable within the menu and is represented by a white ‘DG’ indication.

Note: DG mode is not available until the internal gyro sensors have finished alignment.

If the magnetic heading source is invalid, the HSI source will automatically switch to DG mode and an amber ‘DG’ heading source indication will be displayed.

CAUTION! Since the ISU displays Magnetic Heading, IS&S recommends the use of DG mode when operating near the Earth’s magnetic poles where the Earth’s magnetic variation can cause erroneous indications.

HEADING SOURCE INDICATIONS

INDICATION COLOR MODE HDG SOURCE DETAILS

Green Magnetic External Magnetic Default Sensor Unit

White DG Internal User selected option

TITLE CAGE CODE PILOTS GUIDE Integrated Standby Unit with Autothrottle 0EUW0 1D-13714

Use & disclosure is governed by the statement on the document cover page. REVISION LEVEL 1 SHEET 27 of 50

Amber DG Internal Gyroscope Fault detected with the Magnetic Sensor Unit. Forced DG mode.

3.2.2.2.1 Heading Failure Flag

If magnetic heading data from the magnetic sensor is invalid and the internal gyros have not completed alignment, the Heading indication (HIS) will be replaced with a red HDG warning flag. Refer to Figure 3-15 for ISU failure flags.

3.2.2.3 NAV Source

The NAV configuration is used to select the display of the navigation source, Bearing Pointers, Localizer and Glide Slope CDIs and the Course indicator. The Navigation source data is received on ARINC 429 channels. Depending on the configuration and data validity, the ISU can display VOR, ADF or FMS bearing pointers on the HSI and glide slope/localizer deviations on the ADI.

Table 3-2 Bearing Pointer Display Formats

BEARING POINTERS SOURCE COLOR DISPLAY FORMAT ADF-1 Cyan Single Needle Image ADF-2 Cyan Dual Needle Image VOR-1 Green Single Needle Image VOR-2 Green Dual Needle Image FMS Magenta Dual Needle Image

The Bearing Pointers can be seen in Figure 3-12. The associated navigation data that pertains to a given bearing pointer is displayed to the left of the HSI and takes on the same color as the pointer indicator. The NAV1 bearing pointer is a single needle and the NAV2 bearing pointer is a double needle. This functionality can be turned off either by configuration or menu option.

TITLE CAGE CODE PILOTS GUIDE Integrated Standby Unit with Autothrottle 0EUW0 1D-13714

Use & disclosure is governed by the statement on the document cover page. REVISION LEVEL 1 SHEET 28 of 50

Figure 3-12 CDI and Bearing Pointer Display

Figure 3-13 Selected Course - Zoomed

Figure 3-14 shows the glide slope and localizer displays. These displays are enabled when the ILS Navigation source is selected for one of the 2 Navigation data sources.

Figure 3-14 Glide Slope/Localizer Display

TITLE CAGE CODE PILOTS GUIDE Integrated Standby Unit with Autothrottle 0EUW0 1D-13714

Use & disclosure is governed by the statement on the document cover page. REVISION LEVEL 1 SHEET 29 of 50

3.2.3 ISU Failure Flags In the case that any of the primary flight parameters become invalid, each of the respective display features will be removed and replaced with a boxed red failure flag. Figure 3-15 shows the warning flags and their respective position for each invalid parameter.

Table 3-3 ISU Failure Flags

FAILURE FLAG INVALID FEATURE SPD Airspeed Tape ATT Attitude (ADI) ALT Altitude Tape HDG Heading (HSI) VERT Vertical Speed

Figure 3-15 ISU Invalid Parameter Flags

TITLE CAGE CODE PILOTS GUIDE Integrated Standby Unit with Autothrottle 0EUW0 1D-13714

Use & disclosure is governed by the statement on the document cover page. REVISION LEVEL 1 SHEET 30 of 50

3.2.4 Tile 3 – Autothrottle Display Parameters

3.2.4.1 Autothrottle Mode

The ISU will display the basic autothrottle mode as “A/T SPEED” or “A/T TORQUE” on the left side of Tile 3 at the bottom of the ISU A/T display. The Target Torque value (magenta if engaged) or the Target Airspeed value (cyan if engaged) is displayed next to the mode. When the target setpoint is being adjusted it will zoom up in size for several seconds. Any autothrottle annunciation will also zoom up for 3 seconds when first displayed. Annunciations, Sub-modes, Protection Modes and Limits are displayed on the right side of Tile 3.

Figure 3-16 Autothrottle Window

3.2.4.2 Autothrottle Annunciations

The autothrottle control window will display the following annunciations. All annunciations will zoom up for 3 seconds when they first become active as long as the A/T selected value, baro correction, or selected course are not zoomed up as well.

Table 3-4 Autothrottle Annunciations

A/T MESSAGE COLOR DESCRIPTION A/T SPEED white The autothrottle is in AIRSPEED mode A/T TORQUE white The autothrottle is in TORQUE mode ENTER T/O GW: white Aircraft Takeoff Gross Weight must be entered A/T TAKEOFF magenta The autothrottle is operating in TAKEOFF mode A/T GO-AROUND magenta The autothrottle is operating in GO-AROUND mode A/T CLIMB magenta The autothrottle is operating in CLIMB mode UNDERSPEED white The autothrottle is in UNDERSPEED Protection mode OVERSPEED white The autothrottle is in OVERSPEED Protection mode ITT white The autothrottle is in TEMPERATURE Protection mode VMO white Target Airspeed is limited by VMO ICE white Target Airspeed is limited by De-Icing Activation FLAP white Target Airspeed is limited by Flap Position

TITLE CAGE CODE PILOTS GUIDE Integrated Standby Unit with Autothrottle 0EUW0 1D-13714

Use & disclosure is governed by the statement on the document cover page. REVISION LEVEL 1 SHEET 31 of 50

A/T MESSAGE COLOR DESCRIPTION Autopilot vertical SPD mode activate. AP SPD white (only displayed for 3 seconds after activation) Autopilot vertical MACH mode active. AP MACH white (only displayed for 3 seconds after activation) The autothrottle is using ISU derived airspeeds because EXT ADC amber the ADC data is not available The autothrottle has disconnected, and cannot be used ACK DISCONNECT amber until acknowledged by pressing the MFK knob on the ISU Autopilot FLC mode activation has caused autothrottle to AP ASPD HOLD amber disconnect. The autothrottle cannot be re-engaged until acknowledged by pressing the MFK knob on the ISU. The autothrottle self-test has determined that the Power A/T CAL REQ amber Control Lever friction must be adjusted and recalibrated The autothrottle has disconnected due to an excessive TRQ MISMATCH amber difference in left/right engine Torque The autothrottle has detected an inoperative engine and is A/T ENGINE OUT amber operating in ENGINE OUT mode

3.2.5 Modifiable Parameters

The Multi-Function Knob (MFK) on the ISU is used to adjust several parameters and to navigate the MENU. When the menu is not displayed, pressing the MFK button will cycle through the adjustable selections. The current selection will zoom up to indicate the active selection. After 5 seconds (if the value is not adjusted) the selection will revert to the default (usually BARO). The selected parameter will remain zoomed up in size while being adjusted. The selection follows the sequence indicated below, but will vary depending on the current mode and configuration.

1) BARO CORRECTION Default (unless Baro Correction Sync is enabled) 2) A/T SETPOINT Target Torque or Target Speed (depending on A/T mode) 3) HDG SLEW Only available when in DG Heading mode 4) SELECTED COURSE Only available when NAV Input is enabled

TITLE CAGE CODE PILOTS GUIDE Integrated Standby Unit with Autothrottle 0EUW0 1D-13714

Use & disclosure is governed by the statement on the document cover page. REVISION LEVEL 1 SHEET 32 of 50

3.2.5.1 BARO CORRECTION

BARO is used to enter the local Barometric pressure correction to convert the sensed static air pressure into Barometric Altitude. Normally, the barometric correction will be synchronized with the setting applied to the pilot’s PFD. If Baro Sync is not configured or the baro correction data is not received, this parameter will be included as the default MFK function.

3.2.5.2 A/T SETPOINT

Depending on the autothrottle mode, this menu item will allow for the adjustment of either Target Torque (ft-lbs), or Target Airspeed (knots). Target Airspeed is not adjustable on the ISU if the autothrottle is configured for Airspeed Sync (with the FGP).

3.2.5.3 HDG SLEW

The “HDG” adjustment slews the displayed Heading while in DG mode. Rotating the encoder CW increases the displayed heading (which rotates the compass rose CCW). Holding the MENU button for more than 2 seconds will reset the applied heading offset to zero.

3.2.5.4 COURSE

The “CRS” adjustment is used to select the Course used to calculate lateral deviation for the selected navigation source.

TITLE CAGE CODE PILOTS GUIDE Integrated Standby Unit with Autothrottle 0EUW0 1D-13714

Use & disclosure is governed by the statement on the document cover page. REVISION LEVEL 1 SHEET 33 of 50

3.2.6 ISU Bezel Button Controls

The ISU incorporates three user controls. These are the:

 A/T PWR Key - Engages or Disengages the autothrottle system

 MENU Key - Activates the Main Menu or navigates to the previous menu level

 Multi-Function Knob (MFK) - Rotate to adjust the selected parameter. Press to edit or accept selected parameter.

Figure 3-17 ISU Control Features

The ISU uses a combination of button presses and the encoder to control the functionality provided by the autothrottle. The A/T PWR and MENU Keys are momentary push buttons. Pressing the AT PWR Key, Engages or Disengages (deactivates) the autothrottle System. Pressing the MENU Key activates the Main Menu, or navigates back to the previous menu level if the menu is currently active.

Rotating the Multi-Function Knob controls a rotary encoder used to increment or decrement a selected value. The Multi-Function Knob also has an integrated button, activated by pressing on the knob. Pressing the MFK button serves to accept, edit, or activate the selected parameter.

TITLE CAGE CODE PILOTS GUIDE Integrated Standby Unit with Autothrottle 0EUW0 1D-13714

Use & disclosure is governed by the statement on the document cover page. REVISION LEVEL 1 SHEET 34 of 50

3.2.6.1 A/T Status LED

The A/T Status LED is used to quickly convey the state of the autothrottle system. It is located on the ISU A/T bezel. It supports the following states:

 Steady GREEN – Autothrottle is engaged

 Flashing AMBER – Autothrottle has disconnected

 Steady AMBER – A/T Disconnect must be acknowledged

3.2.7 Power Lever Controls

The autothrottle system adds a second button to the Power Levers, in addition to the GA button. The A/T DISC button is attached to the right Power Lever. This button is used to facilitate quickly disconnecting the autothrottle control without the need to remove your hand from the Power Levers.

The GA button is used by the autothrottle to select TAKEOFF mode (on ground) or GO- AROUND mode (airborne).

Figure 3-18 A/T Power Lever Controls

TITLE CAGE CODE PILOTS GUIDE Integrated Standby Unit with Autothrottle 0EUW0 1D-13714

Use & disclosure is governed by the statement on the document cover page. REVISION LEVEL 1 SHEET 35 of 50

3.3 MAIN MENU

The autothrottle’s main menu can be entered by pressing the MENU key when the aircraft is stationary on the ground. The main menu offers the following functions:  GWT – Adjust the Aircraft Gross Weight entry  BRT – Adjust the LCD Display Brightness  TURBULENCE – Select AIRSPEED mode at Turbulent Air Penetration Speed (in air only)  ISU CONFIG - Access the ISU CONFIG Menu.  SERV MODE – Access ISU SERVICE Mode (ground only)

Figure 3-19 ISU - MAIN MENU

When the MAIN MENU is active, the MFK knob may be rotated to select an item in the menu, where the current selection is highlighted. Pressing the MFK knob activates the selected function or mode. Pressing the MENU key again de-activates the menu or navigates up.

3.3.1 Initializing Gross Takeoff Weight

The autothrottle logic requires aircraft Gross Weight (GWT) to accurately compute airspeed performance limitations. The Gross Takeoff Weight (GTOW) is required to be entered when the ISU is first powered on, and is maintained automatically by reducing the weight as fuel is burned.

TITLE CAGE CODE PILOTS GUIDE Integrated Standby Unit with Autothrottle 0EUW0 1D-13714

Use & disclosure is governed by the statement on the document cover page. REVISION LEVEL 1 SHEET 36 of 50

Figure 3-20 Gross Takeoff Weight Entry

When the ISU is powered on, the display initially prompts for the entry of Gross Takeoff Weight (see Figure 3-20). The value is adjusted by rotating the MFK knob to the initial GWT value then entered by pressing the MFK button. The GWT value will decrease by the weight of fuel burned when the engines are running. All other autothrottle functions are inhibited until the initial GTOW has been entered.

3.3.2 Adjust Gross Weight After the initialization, the GWT value may be reviewed and adjusted if necessary through the MAIN MENU, which is accessed by pressing the MENU key. When the GWT line is highlighted, pressing the MFK knob button activates the GWT value for editing – indicated by inverted text box. The value may be adjusted by rotating the MFK knob. The modified GWT must be accepted by pressing the MFK button again.

Figure 3-21 MAIN MENU - Gross Weight

To adjust aircraft Gross Weight: 1. Press the MENU Key to access the MAIN MENU 2. Rotate the MFK knob to highlight the “GWT” menu item 3. Press the MFK knob to activate GWT for editing 4. Rotate the MFK knob to adjust the Gross Weight value (pounds) 5. Press the MFK knob to accept the new value

TITLE CAGE CODE PILOTS GUIDE Integrated Standby Unit with Autothrottle 0EUW0 1D-13714

Use & disclosure is governed by the statement on the document cover page. REVISION LEVEL 1 SHEET 37 of 50

3.3.3 Display Brightness

The brightness of the LCD display backlighting, autothrottle status LED, and ISU button brightness is controlled by adjusting the display brightness (BRT) setting in the Main Menu. The brightness will also automatically react proportionately to changes in the ambient cockpit lighting (decreasing lighting as ambient light decreases). The display brightness is adjustable on a scale from 1 (lowest) to 100 (brightest). This relative setting is applied to the automatic brightness setting, which is proportionate to the existing ambient light.

Figure 3-22 MAIN MENU – Brightness Adjustment

To adjust the Brightness; press the MENU key to access the MAIN MENU, rotate the MFK knob to highlight the “BRT” entry, and press the MFK knob to edit the field. Rotate the MFK knob to adjust the BRT value ( 1 – 100%) then press the MFK knob to accept the new setting.

3.3.4 Service Mode Service Mode provides additional functionality that is not needed for normal autothrottle operation. When the ISU is operating in Service Mode, normal autothrottle functionality is not supported. Service Mode may only be selected while on the ground within thirty seconds of applying power. Service Mode is entered by selecting the SVC MODE line from the Main Menu (see Figure 3-23). The SVC MODE line is removed from the menu while in flight or if the autothrottle system has been powered up for more than thirty seconds.

Figure 3-23 MAIN MENU – Service Mode

TITLE CAGE CODE PILOTS GUIDE Integrated Standby Unit with Autothrottle 0EUW0 1D-13714

Use & disclosure is governed by the statement on the document cover page. REVISION LEVEL 1 SHEET 38 of 50

To Activate Service Mode: 1. Press MENU key to access MAIN MENU 2. Rotate the MFK knob to highlight the SERV MODE menu item 3. Press the MFK button, pull/push the ISU circuit breaker to restart the ISU in Service Mode

3.3.5 ISU CONFIG Menu

The ISU CONFIG Menu provides configuration control of the ISU display. Selection of the ISU CONFIG Main Menu item results in the display of the ISU CONFIG Menu in Tile 2.

Figure 3-24 ISU CONFIG MENU

TITLE CAGE CODE PILOTS GUIDE Integrated Standby Unit with Autothrottle 0EUW0 1D-13714

Use & disclosure is governed by the statement on the document cover page. REVISION LEVEL 1 SHEET 39 of 50

ISU CONFIG Menu

STD Baro… Resets the Baro Correction to (ISA) standard pressure.

Metric: ON/OFF Toggles the display of Altitude in Meters. “ON” displays the altitude in meters above the normal display of feet on the Altitude Tape

Baro U: InHg/HP Toggles the display of Baro Correction units between Inches of Mercury (InHg) and HectoPascals (HPA)

DG: ON/OFF Toggles DG Heading Mode ON (ISU uses internal ) or OFF (ISU displays mag heading from Magnetic Sensor Unit)

Lat: Allows user to enter the Latitude where the aircraft is located. Initializing the Latitude will improve DG Heading mode performance and should be updated to the approximate Latitude anytime prolonged use of DG mode is anticipated. The Latitude value is adjusted using the MFK knob.

Nav: ON/OFF Toggles the display of Navigation data on the ISU. “ON” displays the Nav data on the ADI and HSI. “OFF” will remove Nav data from the display.

TITLE CAGE CODE PILOTS GUIDE Integrated Standby Unit with Autothrottle 0EUW0 1D-13714

Use & disclosure is governed by the statement on the document cover page. REVISION LEVEL 1 SHEET 40 of 50

3.4 SERVICE MODE Service Mode provides the operator a menu of maintenance related functions to support the continued operation of the autothrottle. These functions include: configuration, calibration, and status reporting. The autothrottle’s current software configuration is displayed when “Dataload” is the highlighted option in the menu. autothrottle configuration and setup information is displayed when “A/T Config” is selected, and the autothrottle event log and hours of operation are displayed when “Unit Log” is selected. Service Mode functionality is entirely separate from the primary autothrottle functionality, and can only be accessed while on the ground.

Figure 3-25 ISU – Service Menu

3.4.1 Service Menu When the ISU is operating in Service Mode, the MFK knob is turned to highlight a desired function, and then pressed to enter the selected submenu. Pressing the MENU key will return to the main menu. The SERVICE MENU includes the following items:  A/T CONFIG provides an interface to review and calibrate the autothrottle friction  DATALOAD supports the upload of new software and configuration files  UNIT LOG displays a timeline of system events recorded by the autothrottle  CALIBRATION supports the calibration of ISU lighting and brightness  STATUS PAGE pages displays the status of the ISU and autothrottle interfaces

When the SERVICE MENU is active, the MFK knob may be rotated to select the highlighted item. Pressing the MFK button activates the selected service function or page. Pressing the MENU key while one of the sub-pages is active, navigates back to the SERVICE MENU.

TITLE CAGE CODE PILOTS GUIDE Integrated Standby Unit with Autothrottle 0EUW0 1D-13714

Use & disclosure is governed by the statement on the document cover page. REVISION LEVEL 1 SHEET 41 of 50

3.4.2 A/T STATUS Page The Autothrottle Status Page (STATUS PAGE) displays the status of the various autothrottle data interfaces. Failures are indicated by a ‘FAIL’ annunciation in RED. Pressing the MENU key will exit the Status Page once active.

Figure 3-26 Service Mode – Autothrottle Status Page

3.4.3 A/T CONFIG Page The Autothrottle Configuration Service Page displays the Power Lever actuator friction coefficients and facilitates the calibration of the autothrottle.

Figure 3-27 Service Mode – Autothrottle Configuration Page

TITLE CAGE CODE PILOTS GUIDE Integrated Standby Unit with Autothrottle 0EUW0 1D-13714

Use & disclosure is governed by the statement on the document cover page. REVISION LEVEL 1 SHEET 42 of 50

3.4.4 DATALOAD Page The Dataload page is used to update the installed autothrottle software, firmware, or configuration files. It also can be accessed to retrieve (upload) Data files that have been logged by the ISU.

Figure 3-28 Service Mode – Dataload Page

3.4.5 EVENT LOG Page The UNIT LOG page displays a chronological listing of autothrottle faults and events detected by the ISU. Each event includes a timestamp (hours of ISU operation) and the Event or Fault description. The most recent events are displayed at the top of the list. Rotating the MFK knob, scrolls through the event log to access earlier events.

Figure 3-29 Service Mode – Event Log Page

TITLE CAGE CODE PILOTS GUIDE Integrated Standby Unit with Autothrottle 0EUW0 1D-13714

Use & disclosure is governed by the statement on the document cover page. REVISION LEVEL 1 SHEET 43 of 50

3.4.6 CALIBRATION Page The Calibration Page provides the interface to adjust the ISU’s brightness levels to calibrate its lighting to match the cockpit’s lighting characteristics. There are separate adjustments available for the LCD backlighting, the bezel buttons, LED status light and the calibration.

Figure 3-30 Service Mode – Calibration Page

TITLE CAGE CODE PILOTS GUIDE Integrated Standby Unit with Autothrottle 0EUW0 1D-13714

Use & disclosure is governed by the statement on the document cover page. REVISION LEVEL 1 SHEET 44 of 50

4.0 FAULT DETECTION

The ISU detects and records autothrottle faults and events as outlined below. The ISU processor performs power-on and continuous automatic Built In Tests (BIT) of the autothrottle assemblies and circuits. All detected Faults will be captured in an Event Log that can be reviewed in Service Mode. The Event Log stores the latest (62) events in a ring-buffer in non- volatile memory. Each logged event has an associated time stamp that can reviewed against the current hours of operation. When the Event Log is full, new events will over-write the oldest event.

4.1 SYSTEM FAULTS

If any critical autothrottle fault is detected, the autothrottle will immediately disconnect with the accompanying cautionary light illuminating amber and the audible tone. If the fault is persistent all autothrottle functionality will be disabled.

Table 4-1 Autothrottle System Faults

Event / Fault Possible Source INVALID FLAPS Flaps position input reads an invalid value. Autothrottle operation is not available. SPD INVALID The Indicated Airspeed parameter from the air data input has failed or is missing. Autothrottle operation is not available. OAT INVALID The Outside Air Temperature parameter from the air data input has failed or is missing. Loss of temperature information from the ADC will prevent the Take-Off and Go-Around functions. TRQ INVALID The left or right engine torque value is invalid. The autothrottle would disconnect and the A/T operation is not available. ITT INVALID The left or right engine Inlet Turbine Temperature value is invalid. The autothrottle would disconnect and the A/T operation is not available. DISC INVALID The A/T Disconnect discrete input has been detected to be active for more than five seconds. Autothrottle operation is not available. GA INVALID The Go-Around discrete input has been detected to be active for more than five seconds. Autothrottle operation is not available. NOT ENABLED The power loop feedback has not been received after commanding the relays to provide power to the motors. Autothrottle operation is

TITLE CAGE CODE PILOTS GUIDE Integrated Standby Unit with Autothrottle 0EUW0 1D-13714

Use & disclosure is governed by the statement on the document cover page. REVISION LEVEL 1 SHEET 45 of 50

Event / Fault Possible Source not available. A/T COMM FAIL The serial between the ISU and the A/T motor has failed. Autothrottle operation is not available. A/T CALIBRATION The autothrottle failed its calibration or the calibration record could REQUIRED not be retrieved. Autothrottle operation is not available. A/T INIT The A/T INIT will be captured if the setup commands fail to be acknowledged by the motor on startup. Autothrottle operation is not available. MOTOR OVERTEMP Recorded if the motor temperature exceeds an internal temperature limit. The autothrottle will disconnect and A/T operation is no longer available. MOTOR FAULT Recorded if the motor reports an error bit in its error register. The autothrottle will disconnect and A/T operation is no longer available. ENGINE FAIL This event will be logged and will cause the A/T to switch into ENGINE OUT mode if the event occurred while in TAKEOFF or GO AROUND mode. Otherwise this will cause the A/T to disengage. TRQ MISMATCH This event will be logged if the A/T is engaged and the TRQ offset between the left and right engine exceeds 500 ft-lbs for more than 5 seconds. OVERSPEED This event will be logged if the VMO or MMO is exceeded for more than 5 seconds. The autothrottle will disconnect and A/T operation is no longer available until the airspeed is back in a valid range. UNDERSPEED This event will be logged if the airspeed goes below the minimum airspeed for more than 5 seconds. The autothrottle will disconnect and A/T operation is no longer available until the airspeed is back in a valid range. LEFT ENG TRQ EXC This event will be logged if the left engine torques is exceeded for more than 5 seconds. The autothrottle will disconnect and A/T operation is no longer available until the airspeed is back in a valid range.

TITLE CAGE CODE PILOTS GUIDE Integrated Standby Unit with Autothrottle 0EUW0 1D-13714

Use & disclosure is governed by the statement on the document cover page. REVISION LEVEL 1 SHEET 46 of 50

Event / Fault Possible Source RIGHT ENG TRQ This event will be logged if the right engine torques is EXC exceeded for more than 5 seconds. The autothrottle will disconnect and A/T operation is no longer available until the airspeed is back in a valid range. LEFT ENG ITT EXC This event will be logged if the left engine ITT is exceeded for more than 5 seconds. The autothrottle will disconnect and A/T operation is no longer available until the airspeed is back in a valid range. RIGHT ENG ITT This event will be logged if the right engine torques is EXC exceeded for more than 5 seconds. The autothrottle will disconnect and A/T operation is no longer available until the airspeed is back in a valid range.

TITLE CAGE CODE PILOTS GUIDE Integrated Standby Unit with Autothrottle 0EUW0 1D-13714

Use & disclosure is governed by the statement on the document cover page. REVISION LEVEL 1 SHEET 47 of 50

4.2 FRICTION CALIBRATION

The autothrottle actuators are able to overcome a reasonable amount of friction to move the Power Levers. The required force is limited to avoid using excessive force to over-power failed or stuck linkage. As part of the power-on self tests, the autothrottle drives the Power Levers through their full range of motion to verify the force required to move them. This test is performed before the engines are started. This test may be affected by excessive tightening of the friction knob on the power console.

If the Friction Test fails, as indicated by “A/T CAL REQ” being annunciated on the ISU, the power lever friction knob should be loosened and the power levers moved by hand through their full range of motion to determine if something is interfering with their free movement.

If there is nothing obstructing the movement of the power levers, the Friction Test should be repeated by cycling power to the ISU (while on the ground). If the Friction Test fails again, the Friction Calibration procedures should be performed prior to using the autothrottle system. The Friction Calibration procedures are described in the ISU A/T Operations and Installation Manual, 1D-88130.

TITLE CAGE CODE PILOTS GUIDE Integrated Standby Unit with Autothrottle 0EUW0 1D-13714

Use & disclosure is governed by the statement on the document cover page. REVISION LEVEL 1 SHEET 48 of 50

5.0 TROUBLESHOOTING

All autothrottle issues that cannot be resolved or diagnosed using this Pilots Guide or the Operations and Installation Manual, 1D-88130, may require factory repair and must be returned to IS&S.

TITLE CAGE CODE PILOTS GUIDE Integrated Standby Unit with Autothrottle 0EUW0 1D-13714

Use & disclosure is governed by the statement on the document cover page. REVISION LEVEL 1 SHEET 49 of 50

6.0 SOFTWARE LOADING

Reference the IS&S ISU Operations and Installation Manual, 1D-88130, for detailed software data loading procedures.

TITLE CAGE CODE PILOTS GUIDE Integrated Standby Unit with Autothrottle 0EUW0 1D-13714

Use & disclosure is governed by the statement on the document cover page. REVISION LEVEL 1 SHEET 50 of 50