Application Revisions Next Assy Used On Rev. Description Date Approved Approved 9K-88126-1 9K-88126-1 1 Initial Release per EC 14012 6/22/18 DB 9K-88126-3 9K-88126-3 2 Revised per EC 14069 7/24/18 DB 3 Revised per EC 14119 9/12/18 DB 4 Revised per EC 14128 9/21/18 DB 5 Revised per EC 14167 11/2/18 DB 6 Revised per EC 14167 11/20/18 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 STANDBY UNIT (ISU) with AUTOTHROTTLE (A/T) P/N: 9D-88126-1 (Legacy PC-12) P/N: 9D-88126-3 (PC-12 NG)
Contract Number:
Contractor:
Written By: M. Rudy Date: 6/21/18 PILOTS GUIDE Checker: Date: INTEGRATED STANDBY UNIT (ISU)
Engineer: M. Rudy Date: 6/21/18 with AUTOTHROTTLE (A/T)
Document Approval: D. Babe Date: 6/22/18 CAGE CODE
QA Approval: B. Urbanski Date: 6/22/18 0EUW0 1D-13470
Design Approval: M. Knopf Date: 6/22/18 Form# 07315-372 Rev - SHEET 1 of 40
REVISION HISTORY
Rev 6 Par 2.1: Modified to remove engine start mode with voltage monitoring and temperature protection. Removed Par 2.2 "Engine Start Mode" and all associated subparagraphs. Par 2.2: Changed from Par 2.3 and corrected spelling issue in header Par 2.2.1: Removed reference to engine start mode
Rev 5 Added descriptions of Hot Start and Low Voltage Protection in Section 2.0. Added A/T Initialization and Friction Test to Section 2.3.
Rev 4 Updated Override test
Rev 3 Removed ATCP. Updated Figure 2-18
Rev 2 Updates to calibration procedure
Rev 1 Initial Release of document
TITLE CAGE CODE PILOTS GUIDE INTEGRATED STANDBY UNIT (ISU) with Autothrottle 0EUW0 1D-13470 (A/T)
Use & disclosure is governed by the statement on the document cover page. REVISION LEVEL 6 SHEET 2 of 40
TABLE OF CONTENTS
1.0 INTRODUCTION ...... 7 1.1 ISU WITH A/T DESCRIPTION ...... 7 1.2 PURPOSE ...... 7
2.0 OPERATIONAL SPECIFICATIONS ...... 8 2.1 ISU A/T OVERVIEW ...... 8 2.2 ISU INITIALIZATION ...... 9 2.2.1 A/T Initialization ...... 11 2.2.2 Friction Test ...... 11 2.3 ISU BEZEL BUTTON CONTROLS...... 12 2.4 ISU DISPLAY ...... 16 2.4.1 TILE 1 ...... 16 2.4.1.1 Airspeed Indicator ...... 16 2.4.1.1.1 Airspeed Color bar (When configured to be displayed) ...... 16 2.4.1.1.2 Airspeed Failure Warning Flag ...... 17 2.4.1.2 Mach Display ...... 17 2.4.1.3 Selected Airspeed ...... 17 2.4.1.4 Attitude Direction indicator (ADI) ...... 17 2.4.1.4.1 Startup...... 18 2.4.1.4.2 Pitch Ladder ...... 18 2.4.1.4.3 Roll Indicator ...... 18 2.4.1.4.4 ADI Failure Warning Flag ...... 19 2.4.1.5 Altimeter ...... 19 2.4.1.5.1 Altimeter Failure Warning Flag ...... 19 2.4.2 Tile 2 ...... 20 2.4.2.1 Horizontal Situation Indicator (HSI) ...... 20 2.4.2.2 HSI Source ...... 20 2.4.2.3 Vertical Speed Indicator (VSI) ...... 21 2.4.2.3.1 VSI Failure Warning Flag ...... 21 2.4.3 Warning Flags ...... 22 2.4.4 In-Air ISU Reset ...... 22 2.5 ADJUSTMENT MODES ISU ...... 23 2.5.1 BRT ...... 23 2.5.2 HDG ...... 24 2.5.3 BARO ...... 24 2.5.4 NAV 1 (Configuration Option) ...... 25 2.5.5 TRQ or SPD SEL ...... 26 2.5.6 AT MODE ...... 26 2.6 A/T ANNUNCIATIONS ...... 27 2.7 MAIN MENU ...... 28 TITLE CAGE CODE PILOTS GUIDE INTEGRATED STANDBY UNIT (ISU) with Autothrottle 0EUW0 1D-13470 (A/T)
Use & disclosure is governed by the statement on the document cover page. REVISION LEVEL 6 SHEET 3 of 40
TABLE OF CONTENTS 2.8 AUTOTHROTTLE MAIN MENU ...... 28 2.9 AUTOTHROTTLE STATUS PAGE...... 28 2.10 AUTOTHROTTLE SETUP MENU ...... 29 2.11 CONFIG MENU ...... 30 2.11.1 Standard Baro ...... 31 2.11.2 Metric Display ...... 31 2.11.3 Directional Gyro (DG) Mode ...... 31 2.11.4 Baro Set Units ...... 32 2.11.5 Latitude ...... 32 2.11.6 Service Mode ...... 33
3.0 FAULT DETECTION ...... 34 3.1 SYSTEM FAULTS ...... 34 3.2 AUTOTHROTTLE FAULT ANNUNCIATIONS ...... 35
4.0 CALIBRATION ...... 36 4.1 ISU REQUIRED EQUIPMENT FOR CALIBRATION ...... 36 4.2 REQUIRED INFORMATION FOR CALIBRATION ...... 36 4.3 SYSTEM CONFIGURATION DURING CALIBRATION ...... 37 4.4 ENTERING SERVICE MODE...... 37 4.5 SETTING THE AIRCRAFT PITCH OFFSET ...... 38 4.6 AUTOTHROTTLE CALIBRATION ISU ...... 38
5.0 TROUBLESHOOTING ...... 39
6.0 DATA LOADING ...... 40
TITLE CAGE CODE PILOTS GUIDE INTEGRATED STANDBY UNIT (ISU) with Autothrottle 0EUW0 1D-13470 (A/T)
Use & disclosure is governed by the statement on the document cover page. REVISION LEVEL 6 SHEET 4 of 40
LIST OF TABLES Table / Title Page
Table 2-1 ISU Bezel Button Applicability ...... 12 Table 2-2 Airspeed Color Bar ...... 16 Table 2-3 HSI Source Indications ...... 21 Table 3-1 ISU System Fault Table ...... 34 Table 3-2 A/T Fault Annunciation Table ...... 35 Table 4-1 Calibration Equipment ...... 36 Table 4-2 Magnetic Field Calculator Details ...... 37
TITLE CAGE CODE PILOTS GUIDE INTEGRATED STANDBY UNIT (ISU) with Autothrottle 0EUW0 1D-13470 (A/T)
Use & disclosure is governed by the statement on the document cover page. REVISION LEVEL 6 SHEET 5 of 40
LIST OF FIGURES Figure / Title Page
Figure 2-1 ISU Warning Flag Display ...... 9 Figure 2-2 ISU Operational Display During Alignment Phase ...... 10 Figure 2-3 ISU Normal Operational Display ...... 10 Figure 2-4 ISU Display and Control Features ...... 11 Figure 2-5 ISU Main Menu ...... 12 Figure 2-6 ISU A/T Main Menu ...... 13 Figure 2-7 ISU Config Menu Display ...... 14 Figure 2-8 Airspeed Color Bar ...... 17 Figure 2-9 Alignment Flag ...... 18 Figure 2-10 Pitch Ladder ...... 18 Figure 2-11 Roll Indicator ...... 19 Figure 2-12 Altimeter Normal and Metric Display ...... 19 Figure 2-13 Horizontal Situation Indicator (HSI) ...... 20 Figure 2-14 Vertical Speed Indicator (VSI) ...... 21 Figure 2-15 Warning Flags ...... 22 Figure 2-16 In-Air Reset Prompt ...... 23 Figure 2-17 Adjustment Mode Options ...... 23 Figure 2-18 Adjustment Mode Options ...... 24 Figure 2-19 Baro Correction ...... 24 Figure 2-20 Bearing Pointer Display ...... 25 Figure 2-21 Glide Slope/Localizer Display ...... 26 Figure 2-22 A/T Status Page ...... 28 Figure 2-23 ISU A/T Setup Menu Display ...... 29 Figure 2-24 Menu Options ...... 30 Figure 2-25 DG Mode Selection ...... 31 Figure 2-26 Baro Set Units ...... 32 Figure 2-27 Service Mode Confirmation and Software Part Numbers ...... 33
TITLE CAGE CODE PILOTS GUIDE INTEGRATED STANDBY UNIT (ISU) with Autothrottle 0EUW0 1D-13470 (A/T)
Use & disclosure is governed by the statement on the document cover page. REVISION LEVEL 6 SHEET 6 of 40
1.0 INTRODUCTION
1.1 ISU WITH A/T DESCRIPTION The Integrated Standby Unit with Autothrottle is manufactured by Innovative Solutions and Support (IS&S) (CAGE code: 0EUW0), located in Exton, PA. The system is designed to meet the performance requirements of IS&S specification 1R-88126. The ISU displays the following information: Attitude Heading (360-degree HSI perspective) Airspeed Mach Altitude (InHg and HPA) Vertical Speed Vertical and glide slope deviations Roll and Bank Indication Unusual Attitude Chevrons Zooming Autothrottle State Information The ISU displays the following configurable items: Airspeed Color bar Indications VOR / ILS / FMS Bearing pointers Selected Torque (Autothrottle Configurations) Selected Airspeed (Autothrottle Configurations)
1.2 PURPOSE This document is intended to supplement the approved Airplane Flight Manual Supplement (AFMS) for aircraft equipped with the IS&S Integrated Standby Unit (ISU) with Autothrottle functionality, Part Number 9D-88126-1 (Legacy PC-12) and 9D-88126-3 (PC-12 NG). Functionality of existing systems not affected by this installation is not included in this Pilots Guide.
TITLE CAGE CODE PILOTS GUIDE INTEGRATED STANDBY UNIT (ISU) 0EUW0 1D-13470
Use & disclosure is governed by the statement on the document cover page. REVISION LEVEL 6 SHEET 7 of 40
2.0 OPERATIONAL SPECIFICATIONS
2.1 ISU A/T OVERVIEW When first powered up, the ISU Autothrottle begins initialization. It takes approximately 60 seconds for the ISU to fully initialize aircraft attitude and heading. If the ISU resets while in air then the unit will re-initialize after acknowledging through the multi-function push button that the aircraft is in straight and level flight to support in-flight alignment.
TITLE CAGE CODE PILOTS GUIDE INTEGRATED STANDBY UNIT (ISU) 0EUW0 1D-13470
Use & disclosure is governed by the statement on the document cover page. REVISION LEVEL 6 SHEET 8 of 40
2.2 ISU INITIALIZATION During initialization the “ALIGNING” flag as shown in Figure 2-2 is displayed to advise the pilots that the attitude and heading data is unavailable. 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. In the case that valid air data cannot be computed the ISU will display the warnings flags for airspeed, altitude and vertical speed as appropriate. In general, the ISU will display the warning flag for any gauge when data has been detected to be invalidated. Figure 2-1 shows the warning flags for each instrument in the corresponding position.
Figure 2-1 ISU Warning Flag Display Note: The aircraft should be kept stable during the initialization period.
After approximately 1 minute and 30 seconds of initialization the ISU warning flags will be replaced by the normal operational display as shown in Figure 2-3. Each portion of the operational display, as identified in Figure 2-4, will be described in subsequent sections.
TITLE CAGE CODE PILOTS GUIDE INTEGRATED STANDBY UNIT (ISU) 0EUW0 1D-13470
Use & disclosure is governed by the statement on the document cover page. REVISION LEVEL 6 SHEET 9 of 40
Figure 2-2 ISU Operational Display During Alignment Phase
Figure 2-3 ISU Normal Operational Display
TITLE CAGE CODE PILOTS GUIDE INTEGRATED STANDBY UNIT (ISU) 0EUW0 1D-13470
Use & disclosure is governed by the statement on the document cover page. REVISION LEVEL 6 SHEET 10 of 40
2.2.1 A/T Initialization When first powered on, the ISU A/T performs tests to verify the integrity of the autothrottle system components. If these tests determine a critical fault, the autothrottle will be disabled and “A/T FAIL” will be annunciated in amber text at the bottom of the ISU display.
2.2.2 Friction Test When the ISU A/T is initializing while the aircraft is on the ground and the engine is not running, it will perform an automated friction test to verify the force required to drive the Power Lever through its full range of motion. When this is occurring, the power lever advances to full power position then retards to the idle position and disconnects. This test will not occur if the engine is running. If this test determines that the friction level is too high, the test will stop and “A/T CAL REQD” will be annunciated at the bottom of the display. If the Friction Test fails, loosen the friction locks on the Power Lever and press the Multi- Function Knob to clear the error. If the fault recurs, follow the Autothrottle Friction Calibration procedures outlined in the Installation and Operations Manual, 1D-88126.
Figure 2-4 ISU Display and Control Features
TITLE CAGE CODE PILOTS GUIDE INTEGRATED STANDBY UNIT (ISU) 0EUW0 1D-13470
Use & disclosure is governed by the statement on the document cover page. REVISION LEVEL 6 SHEET 11 of 40
2.3 ISU BEZEL BUTTON CONTROLS The Bezel controls consist of three basic control functions. These functions are the A/T On/Off selection, MENU key and the Multi-function control knob. The ISU will use a combination of button press and encoder control steps, as the data entry method for a given control function. Variations of the ISU control functions are listed in Table 2-1. The push buttons are implemented as normally open momentary switches that register a true or asserted condition when pressed. The encoder knob, which also has an integrated push button, serves as the up/increase function with clockwise rotations and the down/decrease function with counter clockwise rotations. The encoder knob functionality legend is displayed in the lower right corner. Pushing the encoder knob is linked to the selection function or to accept an entered value. Table 2-1 ISU Bezel Button Applicability
Integrated Standby Unit Part 9D-84176-() Part Number Descriptions 9D-84176-9 2 Pushbuttons (A/T PWR, MENU) and Rotary Encoder Input Method 9D-84176-11 2 Pushbuttons (A/T PWR, MENU) and Rotary Encoder Input Method 1. Main Menu –The ISU Main Menu controls the ISU display. Selection of the Menu bezel button results in the display of the below image in Tile 2, the bottom of ISU display where Horizontal Situation Indicator and the Vertical Speed Indicator are located.
Figure 2-5 ISU Main Menu
SEL TRQ: Select the SEL TRQ option and adjust to the desirable value using the Up/Down Functions To save the SEL TRQ, use the Select Function or Menu push button SEL SPD: Select the SEL SPD option and adjust to the desirable value using the Up/Down Functions To save the SEL SPD, use the Select Function or Menu push button A/T: Selection changes the Main Menu to the Autothrottle Menu.
TITLE CAGE CODE PILOTS GUIDE INTEGRATED STANDBY UNIT (ISU) 0EUW0 1D-13470
Use & disclosure is governed by the statement on the document cover page. REVISION LEVEL 6 SHEET 12 of 40
CONFIG: Selection changes the Main Menu to the Config Menu
2. A/T Menu – The ISU A/T Menu controls the ISU display. Selection of the A/T: item in the above Main Menu results in the display of the below image in Tile 2, the bottom of the ISU display where HSI and VSI are located.
Figure 2-6 ISU A/T Main Menu
A/T Status… Selection changes the Autothrottle Menu to the Autothrottle Status Page.
A/T Setup… Selection changes the Autothrottle Menu to the Autothrottle Setup Page.
A/T ASPD SRC: Select the A/T ASPD SRC option and adjust to the desirable airspeed source to external (EXT) or internal (INT). EXT selects the A/T control setting for airspeed to follow the primary air data settings. INT selects the ISU internally calculated airspeed value. EXT should be the default source.
3. A/T Status Page – The ISU A/T Status Page controls the ISU display. Selection of the A/T Status… item in the above Autothrottle Main Menu results in the display of the below image in Tile 2, the bottom of ISU display where HSI and VSI are located. Details on the A/T status page can be found in paragraph 2.9.
4. A/T Setup Menu – The ISU A/T Setup Menu controls the ISU display. Selection of the A/T Setup… item in the above Autothrottle Main Menu results in the display of the below image in Tile 2. Details on the A/T status page can be found in paragraph 2.10.
5. Config Menu – The ISU Config Menu controls the ISU display. Selection of the Config: item in the above Main Menu results in the display of the below image in Tile 2, the bottom of ISU display where HSI and VSI are located.
TITLE CAGE CODE PILOTS GUIDE INTEGRATED STANDBY UNIT (ISU) 0EUW0 1D-13470
Use & disclosure is governed by the statement on the document cover page. REVISION LEVEL 6 SHEET 13 of 40
Figure 2-7 ISU Config Menu Display
Standard Baro Selection clears any applied pressure corrections and returns the Baro adjustment to standard pressure.
Metric Display Toggles the metric display of the ISU. “ON” displays the altitude in meters above the normal display of feet on the altimeter
Baro Set Units Toggles the Baro Correction units between Inches of Mercury (InHg) and Hecto Pascals (HPA)
DG Mode Indicates whether or not the ISU is using its internal gyroscopes (ON) for heading or the external Heading Source/IRUs (OFF)
Latitude Latitude should be adjusted whenever there is an appreciable change in latitude Select the Latitude option and adjust to the desirable value using the Up/Down Functions To save the Latitude, use the Select Function To return to the previous Latitude, press the MEN button Service Mode (only Selection of service mode is available. available if airspeed ≤ Upon selection, the ISU shall present a confirm / cancel 21 kts and within 30 prompt sec. of power up. Confirmation enters service mode and the ISU P/Ns are displayed. Cancelation returns the ISU to the main menu.
6. Up Function
TITLE CAGE CODE PILOTS GUIDE INTEGRATED STANDBY UNIT (ISU) 0EUW0 1D-13470
Use & disclosure is governed by the statement on the document cover page. REVISION LEVEL 6 SHEET 14 of 40
Clockwise Rotation of Encoder Used to scroll through menus and control adjustable settings 7. Down Function Counterclockwise Rotation of Encoder Used to scroll through menus and control adjustable settings 8. Select Function SEL Button or Integrated Encoder Push Button Used to select the currently highlighted field in the menu Used to scroll through adjustable options when not in the menu
TITLE CAGE CODE PILOTS GUIDE INTEGRATED STANDBY UNIT (ISU) 0EUW0 1D-13470
Use & disclosure is governed by the statement on the document cover page. REVISION LEVEL 6 SHEET 15 of 40
2.4 ISU DISPLAY The ISU display is broken into two (2) Tiles. The upper portion of the display is considered Tile 1 and the lower portion of the display is considered Tile 2. Tile 1 displays the Airspeed, Attitude Altitude, Mach and Localizer and Glideslope Deviation Scales. Tile 2 displays the Heading, Vertical Speed Indicator, Baro Correction, Adjustable Settings and Menu. Refer to Figure 2-4 for instrument depictions and locations.
2.4.1 TILE 1
2.4.1.1 Airspeed Indicator The Airspeed indicator tape is displayed on the left side of Tile 1. The Indicated Airspeed (IAS) data is computed directly from pressure measurements taken from the Pitot Static System of the aircraft and is in the units of knots.
2.4.1.1.1 Airspeed Color bar (When configured to be displayed) The airspeed color bar is located to the right side of the Airspeed tape. The color bar can provide fast recognition of airspeed ranges that are critical for safe flight. The minimum and maximum settings for the color bars are configured in the configuration module customized for the aircraft (type). Table 2-2 Airspeed Color Bar
Color Bar Minimum (kts) Maximum (kts) Low Speed Awareness Range Red 21 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 900
TITLE CAGE CODE PILOTS GUIDE INTEGRATED STANDBY UNIT (ISU) 0EUW0 1D-13470
Use & disclosure is governed by the statement on the document cover page. REVISION LEVEL 6 SHEET 16 of 40
Figure 2-8 Airspeed Color Bar
2.4.1.1.2 Airspeed Failure Warning Flag If the data from the internal air data computation is invalidated by the ISU internal fault processing, the Airspeed indicator displays a red warning flag. Refer to Section 2.4.3 for Airspeed indicator warning flag figure.
2.4.1.2 Mach Display The ISU includes a display of the Mach number on the bottom of the Airspeed Tape in Tile 1. The Mach number is displayed in the format of 0.XXX as shown in Figure 2-8. 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.
2.4.1.3 Selected Airspeed The ISU includes a display of the Selected Airspeed number on the top of the Airspeed Tape in Tile 1. The Selected Airspeed number is displayed in the format of XXX as shown in Figure 2- 4. Selected Airspeed will only be displayed while the Autothrottle is engaged. Adjusting the selected airspeed will cause the selected airspeed display to zoom up.
2.4.1.4 Attitude Direction indicator (ADI) The ADI is displayed in the center of Tile 1 and provides the necessary Pitch and Roll information. The Sky/Ground depiction is representative of what is seen from the pilot’s perspective looking out of the cockpit 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.
TITLE CAGE CODE PILOTS GUIDE INTEGRATED STANDBY UNIT (ISU) 0EUW0 1D-13470
Use & disclosure is governed by the statement on the document cover page. REVISION LEVEL 6 SHEET 17 of 40
2.4.1.4.1 Startup 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 moving the aircraft. Excessive movement during the alignment period may extend the alignment time.
Figure 2-9 Alignment Flag
2.4.1.4.2 Pitch Ladder The pitch ladder shows the pitch of the aircraft and gives warnings for extreme pitch. The Sky/Ground depiction is separated by a 0° pitch line. Red chevrons are displayed when the pitch angle is either too high or low as shown in Figure 2-10.
Figure 2-10 Pitch Ladder
2.4.1.4.3 Roll Indicator The Roll indicator, see Figure 2-11, 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 graduations for every 10° of roll between ±30°.
TITLE CAGE CODE PILOTS GUIDE INTEGRATED STANDBY UNIT (ISU) 0EUW0 1D-13470
Use & disclosure is governed by the statement on the document cover page. REVISION LEVEL 6 SHEET 18 of 40
Figure 2-11 Roll Indicator
2.4.1.4.4 ADI Failure Warning Flag If the data from the internal sensor is either invalid or not received the Airspeed indicator shall display a red warning flag. Refer to Section 2.4.3 for the ADI warning flag figure.
2.4.1.5 Altimeter The ISU provides an altimeter that is located on the right side of Tile 1. It displays the altitude in feet above mean sea level (MSL). It can also display the altitude in meters if the metric option is set in the Menu, see Figure 2-12. Refer to Section 2.11.2 for metric display option and Section 2.5.3 for Baro Correction description.
Figure 2-12 Altimeter Normal and Metric Display
2.4.1.5.1 Altimeter Failure Warning Flag If the data from the Pitot Static is either invalid or not received the Altimeter displays a red warning flag. Refer to Section 2.4.3 for Altimeter warning flag figure.
TITLE CAGE CODE PILOTS GUIDE INTEGRATED STANDBY UNIT (ISU) 0EUW0 1D-13470
Use & disclosure is governed by the statement on the document cover page. REVISION LEVEL 6 SHEET 19 of 40
2.4.2 Tile 2
2.4.2.1 Horizontal Situation Indicator (HSI) The 360 HSI, see Figure 2-13, is displayed in the center of Tile 2. It displays heading in degrees with gradations of 10° and labels every 30° with North, South, East, and West labeled N, S, E, and W respectively.
Figure 2-13 Horizontal Situation Indicator (HSI)
2.4.2.2 HSI Source The heading source for the HSI is shown next to the heading numeral display. The default source for the HSI is the external magnet heading source which is represented by a green ‘M’ indication. Directional Gyro (DG) mode is also selectable within the menu and is represented by a white ‘DG’ indication. Refer to Figure 2-25 for DG mode menu option depiction. Note: DG mode is not available while aligning. After alignment is complete, if the external heading source data is either invalid or not received the HSI source will automatically switch to DG mode and an amber ‘DG’ heading source indication will be displayed next to the heading numeral display. During alignment, if the external heading source data is either invalid or not received the HSI source will display a red “HDG” flag head indication which represents that the ISU is in magnetic mode but is no longer using current external heading source data. Refer to Table 2-3 for HSI source indication depictions and causes.
TITLE CAGE CODE PILOTS GUIDE INTEGRATED STANDBY UNIT (ISU) 0EUW0 1D-13470
Use & disclosure is governed by the statement on the document cover page. REVISION LEVEL 6 SHEET 20 of 40
Table 2-3 HSI Source Indications
Indication Color Mode HSI Source Cause
Green Magnetic External Magnetic Default Heading Source
White DG Internal Gyroscope User selected option
Amber DG Internal Gyroscope Fault detected with the external heading source. Forced DG mode.
IS&S recommends the use of DG mode in locations where the Earth’s magnetic inclination can cause erroneous readings. This occurs near the Earth’s magnetic poles. CAUTION! Operating the ISU in magnetic mode near the Earth’s magnetic poles can lead to erroneous readings. DG mode should be used in locations with high magnetic inclination.
CAUTION! The HSI displays Magnetic heading not True heading. Caution should be used while navigating in areas of high magnetic declination.
2.4.2.3 Vertical Speed Indicator (VSI) The Vertical Speed Indicator (VSI), Figure 2-14, is located on the right side of Tile 2. Each minor gradation represents 500 feet per minute (fpm). Each major gradation (1, 2, or 3) represents 1,000 fpm.
Figure 2-14 Vertical Speed Indicator (VSI)
2.4.2.3.1 VSI Failure Warning Flag If the data from the Pitot Static is either invalid or not received the Altimeter displays a red warning flag. If the Altimeter is either invalid or not received the VSI will display the VSI warning flag. Refer to Section 2.4.3 for Altimeter warning flag figure.
TITLE CAGE CODE PILOTS GUIDE INTEGRATED STANDBY UNIT (ISU) 0EUW0 1D-13470
Use & disclosure is governed by the statement on the document cover page. REVISION LEVEL 6 SHEET 21 of 40
2.4.3 Warning Flags When the data from either the pitot static or the external magnetic heading source is invalid or not received a warning flag will be presented in place of the corresponding instrument display, see Figure 2-15.
Figure 2-15 Warning Flags
2.4.4 In-Air ISU Reset If the ISU detects a fault or temporarily loses power in flight it will reset. When the airspeed is greater than 50 kts and the ISU starts, a prompt will be displayed that will indicate to the pilot to ‘Maintain a level attitude and a steady course, press SEL to reinitialize’. During the initialization time the airplane should be flown as straight and level as is achievable. Figure 2-16 shows the prompt that is displayed when the ISU is reset in flight.
TITLE CAGE CODE PILOTS GUIDE INTEGRATED STANDBY UNIT (ISU) 0EUW0 1D-13470
Use & disclosure is governed by the statement on the document cover page. REVISION LEVEL 6 SHEET 22 of 40
Figure 2-16 In-Air Reset Prompt
2.5 ADJUSTMENT MODES ISU When the menu is not displayed pressing the SEL button will cause one (1) of the seven (7) indications shown in Figure 2-17 to appear in the lower right corner of Tile 2. The indication shown will be the active adjustment mode for further interactions. Detailed descriptions for each of the settings can be found in Sections 2.5.1 through 2.4.7 of this document. Holding the MEN button for more than 2 seconds will cause a reset of the active adjustment and return the adjustment value back to its default. “ACK” annunciator will only be displayed when the autothrottle is disconnected for any reason.
Figure 2-17 Adjustment Mode Options
2.5.1 BRT The BRT adjustment mode adjusts the brightness of the display. This is an offset and the Ambient Light Sensor (ALS) will still automatically adjust the brightness. When the brightness is being manually adjusted, a brightness bar appears at the bottom of Tile 2, refer to Figure 2-18.
TITLE CAGE CODE PILOTS GUIDE INTEGRATED STANDBY UNIT (ISU) 0EUW0 1D-13470
Use & disclosure is governed by the statement on the document cover page. REVISION LEVEL 6 SHEET 23 of 40
Figure 2-18 Adjustment Mode Options
2.5.2 HDG The “HDG” adjustment mode adjusts the Heading. This heading adjustment adds an offset to the heading and is used during DG mode flight. Pressing the UP arrow button or rotating the encoder CW rotates the HSI CCW. Pressing the Down arrow button or rotating the encoder CCW rotates the HSI CW. When the heading is being adjusted the HSI numeral display will expand up to a 200 percent increase in size to show a zoomed view of the adjustment. Holding the MEN button for more than 2 seconds will reset the applied heading offset to zero.
2.5.3 BARO The “Baro” adjustment mode adjusts the Baro Correction value. The default Baro Correction is 29.92 InHg/1013 HPa. Rotating the encoder CW increases the value and rotating the encoder CCW decreases the value. When the Baro correction value is being adjusted the Baro set display will expand up to a 200 percent increase in size to show a zoomed view of the adjustment. When the altimeter transitions from below 18,000ft to above 18,000ft the Baro Correction will automatically set to the default value (29.92 InHg) and expand to show the automatic adjustment, Figure 2-19.
Figure 2-19 Baro Correction
TITLE CAGE CODE PILOTS GUIDE INTEGRATED STANDBY UNIT (ISU) 0EUW0 1D-13470
Use & disclosure is governed by the statement on the document cover page. REVISION LEVEL 6 SHEET 24 of 40
2.5.4 NAV 1 (Configuration Option) The “NAV 1” adjustments are used to select the desired navigation source for the bearing pointers and display of the localizer and/or glide slope deviation. The Navigation source data is received on ARINC 429 channels by the ISU. Depending on the validity status of the received data and the selection made through this menu feature, the pilot/crew can display VOR bearing pointers on the HSI and glide slope/localizer deviations on the ADI. The Bearing Pointers can be seen in Figure 2-20. 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 availability of frequency and distance information is dependent on the data information provided by the NAV radios on their respective data busses. The NAV1 bearing pointer is a single needle. The legacy PC-12 ISU configuration replaces the RMI and therefore displays bearing needle data when a valid VOR station has been detected by the NAV receiver. The frequency and distance information are not available from the NAV converter in the legacy PC-12. The PC-12 NG is not configured to display Nav data on the standby display.
Figure 2-20 Bearing Pointer Display
Figure 2-21 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.
TITLE CAGE CODE PILOTS GUIDE INTEGRATED STANDBY UNIT (ISU) 0EUW0 1D-13470
Use & disclosure is governed by the statement on the document cover page. REVISION LEVEL 6 SHEET 25 of 40
Figure 2-21 Glide Slope/Localizer Display
2.5.5 TRQ or SPD SEL The “TRQ SEL” or “SPD SEL” adjustment mode adjusts the selected target speed or torque through the bezel encoder. This mode will display and allow changes to the currently selected autothrottle target setting. Rotate the encoder knob to adjust the values. Note: Values will be clamped to configurable min and max values. Airspeed is adjusted in 1 knot and torque in 0.1 psi resolution. Airspeed cannot be selected below the VS0 plus 10 knots, which is an added safety margin. When the ISU detects an Icing condition (inertial separator open and propeller heat ON) another 20 knots are added to the minimum speed setting. The maximum selectable speed is below VMO. Torque is limited on max adjustment side. The controller limits to lower end to stay above 5 psi.
2.5.6 AT MODE The “AT MODE” adjustment mode toggles the autothrottle hold mode between torque and speed hold. Rotating the encoder knob when AT MODE is displayed next to the encoder will switch between torque and speed A/T control. Note: Speed control is only available when in air when valid airspeed is available.
TITLE CAGE CODE PILOTS GUIDE INTEGRATED STANDBY UNIT (ISU) 0EUW0 1D-13470
Use & disclosure is governed by the statement on the document cover page. REVISION LEVEL 6 SHEET 26 of 40
On ground, only A/T Takeoff Mode can be selected, which is armed through the GA switch. The G/A switch when used in air will initiate the A/T Go-Around function driving the throttle towards maximum go-around speed. The take-off and go-around speed are calculated based on density altitude and outside air temperature following the configured PC-12 Aircraft Flight Manual settings.
2.6 A/T ANNUNCIATIONS The selected A/T Mode is displayed in the upper left corner of tile 2. Active A/T modes are annunciated as A/T SPEED or A/T TORQUE. The A/T status LED is will be lit in GREEN when the A/T is active. The A/T can or will be disconnected through the following actions: A/T PWR button on the bezel A/T Disconnect button on the throttle handle A/P IAS HOLD mode selection Exceedances (IAS or TRQ minimums/maximums) that cannot be resolved within five seconds
The “ACK DISCONNECT” mode will be displayed in the lower status field any time the autothrottle is disconnected. This mode will not be available by cycling through the encoder selections. ACK needs to be acknowledged via the encoder push button by the operator before a new mode can be selected. Other A/T annunciations are displayed in the lower status field of the ISU. The following messages may appear: A/T TAKEOFF MODE: Takeoff mode (TRQ) selection on ground via Go-Around switch A/T GO AROUND MODE: Go Around Mode (TRQ) selection in air via Go-Around switch. A/T CLIMB MODE: Climb mode (TRQ) transition after 2.5 minutes coming out of the Take-off or Go-Around mode.
OVERSPD DETECTED: Exceedance control mode entered when IAS exceeds VFE or VMO. When VMO is entered while in TRQ mode, the A/T mode switches into A/T SPEED mode if the exceedance cannot be resolved within three seconds. The speed target will switch to VMO minus three knots. OVERTRQ DETECTED: Exceedance control mode entered when Torque enters caution range. UNDERTRQ DETECTED: Exceedance control mode entered when Torque goes below 5 psi.
TITLE CAGE CODE PILOTS GUIDE INTEGRATED STANDBY UNIT (ISU) 0EUW0 1D-13470
Use & disclosure is governed by the statement on the document cover page. REVISION LEVEL 6 SHEET 27 of 40
OVERTEMP DETECTED: Exceedance control mode entered when ITT goes above the configured maximum ITT value. During A/T take-off the go-around mode, the ITT is allowed to go up to the ITT warning limit before OVERTEMP mode is entered.
2.7 MAIN MENU The Main Menu can be entered by pressing the “MENU” button. The Main Menu offers the options to change selected airspeed, selected torque, enter the Autothrottle Menu and enter the Config Menu. To select the currently highlighted menu option, use the select function.
2.8 AUTOTHROTTLE MAIN MENU The Autothrottle Menu can be entered by pressing the “MEN” button and then selected A/T. The Autothrottle Menu offers the options to enter the Autothrottle Status page, enter the Autothrottle Setup page or change the selected airspeed input from external to internal (This option will only be available if configured for external airspeed).
2.9 AUTOTHROTTLE STATUS PAGE The Autothrottle Status page can be entered by pressing the “MEN” button, selecting A/T and then selecting A/T Status. The Autothrottle status menu will display relevant status information required for proper Autothrottle operation.
Figure 2-22 A/T Status Page
The A/T status page is primarily a maintenance display but can be utilized to verify the A/T functional status. The parameters displayed are as follows: A/P: Provides a FAIL or PASS annunciation if the autopilot data bus is properly read. The data is used to detect if the IAS HOLD mode is selected on the autopilot, which will disconnect the Autothrottle or not allow it to be enabled. AP IAS Hold mode is mutually exclusive with the operation of the Autothrottle. TITLE CAGE CODE PILOTS GUIDE INTEGRATED STANDBY UNIT (ISU) 0EUW0 1D-13470
Use & disclosure is governed by the statement on the document cover page. REVISION LEVEL 6 SHEET 28 of 40
A/T: Provides a FAIL or PASS annunciation if the motor communication is established. OAT: Provides a FAIL or value indication in degrees C if the temperature information is available. Torque: Provides a FAIL or value indication in PSI if the torque signal is read from the engine sensor. ITT: Provides a FAIL or temperature indication in degrees C if the thermocouple is read from the engine sensor. Flaps: Provides a FAIL or flap setting in degrees if the flap position sensor is properly read. ADC: Provides a FAIL or PASS annunciation if the primary air data bus is properly read. The primary indicated airspeed is the one being used for airspeed control unless the ISU IAS is selected. IAS-H: Provides an ON/OFF indication if the Autopilot is in Indicated Airspeed Hold mode. IAS: Provides the read value in knots for the Indicated Airspeed from the primary air data computer. POS: Provides an indication of the throttle position as read by the A/T position sensor.
2.10 AUTOTHROTTLE SETUP MENU The Autothrottle Setup Menu can be entered by pressing the “MEN” button, selecting A/T and then selecting A/T Setup. The Autothrottle Setup menu offers the options to Calibrate the A/T position sensor, run the left or right throttle friction test, manually set the min position value, manually set the max position value, and turn on the override test.
Figure 2-23 ISU A/T Setup Menu Display
TITLE CAGE CODE PILOTS GUIDE INTEGRATED STANDBY UNIT (ISU) 0EUW0 1D-13470
Use & disclosure is governed by the statement on the document cover page. REVISION LEVEL 6 SHEET 29 of 40
Friction Test: Selection will run the friction test for the throttle. The value returned should be less than 20,000 counts. Greater values would indicate that either the throttle brake is set or that the A/T mechanism is not sufficiently adjusted. Forward Pos: Selection will attempt to set the max throttle position manually. Throttle should be moved to the max position before selected. Back Pos: Selection will attempt to set the min throttle position manually. Throttle should be moved to the min position before selected. Override Test: This test will lock the throttle in place at its maximum movement power to allow testing of manual pilot override. If excessive force is needed to override the throttle hold then the Autothrottle installation should be checked.
2.11 CONFIG MENU The Config Menu, Figure 2-24, can be entered by pressing the ‘MEN’ button and then selecting Config. The Menu offers the options for Metric Display, Baro Set Units, DG Mode, and Service Mode. When it is displayed the menu covers the HSI and VSI in Tile 2. Use the rotary encoder to scroll through the menu options. To select the currently highlighted menu option, use the encoder push button select function.
Figure 2-24 Menu Options
TITLE CAGE CODE PILOTS GUIDE INTEGRATED STANDBY UNIT (ISU) 0EUW0 1D-13470
Use & disclosure is governed by the statement on the document cover page. REVISION LEVEL 6 SHEET 30 of 40
2.11.1 Standard Baro The Standard Baro option provides an accessible method to clear any applied pressure corrections and returns the Baro adjustment setting to standard pressure. Pushing the SEL button Standard Baro is highlighted will remove the menu and set the baro correction to standard pressure.
2.11.2 Metric Display The metric display option provides a metric display on the Altimeter. The altitude is displayed in meters above the standard unit display on the altimeter.
2.11.3 Directional Gyro (DG) Mode The heading is determined from the spin of internal gyroscopes when Directional Gyro (DG) mode is enabled. DG mode provides the ability to navigate in areas of high magnetic inclination such as those found near the magnetic poles. The DG mode menu item may be displayed with the ON or OFF text colored in amber. The selection will be displayed amber OFF during the alignment phase to indicate that the DG mode is unavailable during the alignment phase. The amber ON will be displayed in the event that the ISU has lost the external magnetic heading source and is forced to stay in DG mode (ON) due to the unavailable magnetic heading signal. Note: The background behind the DG Mode selection text will turn amber if the user highlights the DG Mode menu item when it is unavailable.
Figure 2-25 DG Mode Selection
TITLE CAGE CODE PILOTS GUIDE INTEGRATED STANDBY UNIT (ISU) 0EUW0 1D-13470
Use & disclosure is governed by the statement on the document cover page. REVISION LEVEL 6 SHEET 31 of 40
2.11.4 Baro Set Units The Baro Set Units option provides the ability to select metric or standard units for the barometric pressure. The options are InHg (Inches of Mercury), or HPA (hectopascal), see Figure 2-26. To change the Barometric units, press select when the ‘Baro Set Units’ menu option is selected.
Figure 2-26 Baro Set Units
2.11.5 Latitude Within the Menu there is a latitude selection field that should be adjusted at startup and whenever DG mode is used or whenever there is an appreciable change in latitude. To adjust the latitude, enter the Menu and select the “Latitude” option. The latitude numeral will be highlighted and is adjustable via the arrow buttons or the rotary encoder. To save the adjusted latitude, use the select function. To return to the previous Latitude press the MEN button. When the region of operation for the aircraft undergoes an appreciable change in latitude (greater than twenty degrees) the latitude should be adjusted to reflect the new latitude.
CAUTION! Failure to adjust or incorrect adjustment of the latitude can result in a DG mode heading accuracy that is outside of the specified accuracy of the instrument.
TITLE CAGE CODE PILOTS GUIDE INTEGRATED STANDBY UNIT (ISU) 0EUW0 1D-13470
Use & disclosure is governed by the statement on the document cover page. REVISION LEVEL 6 SHEET 32 of 40
2.11.6 Service Mode Service mode offers the ability to calibrate the ISU. It is only available within 30 seconds of startup and not in flight. When the service mode menu option is selected a confirmation page, Figure 2-27, is displayed that shows all of the software part numbers (OFP, Service Mode, Boot Strap).
Figure 2-27 Service Mode Confirmation and Software Part Numbers
NOTE: The software versions shown above are for informational purposes only and may not represent the most up to date software revisions. Actual SW versions are covered in the IS&S Operations and Installation Manual 1D-88126.
TITLE CAGE CODE PILOTS GUIDE INTEGRATED STANDBY UNIT (ISU) 0EUW0 1D-13470
Use & disclosure is governed by the statement on the document cover page. REVISION LEVEL 6 SHEET 33 of 40
3.0 FAULT DETECTION The ISU annunciates system faults as outlined below. The ISU processor performs power-on and continuous automatic Built In Tests (BITs) of the operation of the assemblies and circuits. Each ISU carrying an identical part number is identical and interchangeable, troubleshooting procedures for diagnosing ISU problems should include swapping ISUs and performing functional tests. If the problem follows the ISU, then the ISU may be faulty. If the fault indication stays in the same mounting position (left or right), the problem may be the aircraft interface or connected component.
3.1 SYSTEM FAULTS Table 3-1 lists the indication displayed on the ISU for the failure of various display functions along with potential sources for the problem. Refer to Figure 2-15 for warning flag depictions.
Table 3-1 ISU System Fault Table
Display Failure Possible Source Function Indication
Airspeed SPD Pitot Static Connection Leak / Failure Attitude ATT Magnetic Heading Source Failure Altitude ALT Pitot Static Connection Leak / Failure Vertical Speed VERT Pitot Static Connection Leak / Failure (No Altitude Data)
Heading HDG Magnetic Heading Source Interface Failure All Blank Screen No power to displays or internal lighting failure Internal hardware failure Software has been incorrectly loaded or corrupted All CONFIG ISU could not read its configuration file. Limit annunciations are not available and A/T functionality is disabled.
TITLE CAGE CODE PILOTS GUIDE INTEGRATED STANDBY UNIT (ISU) 0EUW0 1D-13470
Use & disclosure is governed by the statement on the document cover page. REVISION LEVEL 6 SHEET 34 of 40
3.2 AUTOTHROTTLE FAULT ANNUNCIATIONS Table 3-2 lists the indications displayed on the ISU for failures that are associated or affect the operation of the Autothrottle. The annunciation is provided along the bottom of the ISU display. Table 3-2 A/T Fault Annunciation Table
Failure Indication Possible Source INVALID FLAPS Flaps position input reads an invalid value. Autothrottle operation is not available. EXT ADC FAIL The primary air data input has failed. The ISU will utilize the internal data value. Loss of temperature information will prohibit the availability of the Takeoff or Go-Around mode capability. A/T FAIL A/T Fail will be displayed under the following conditions: - Airspeed Invalid - Torque is out of configured range or invalid - ITT is out of range or invalid - Power loop back is not received - Go around or Disconnect switch is stuck. A/T COMM FAIL The Autothrottle communication between the ISU and the A/T motor has failed. Autothrottle operation is not available. A/T CAL REQUIRED The Autothrottle system has not been calibrated or the calibration has been erased. Autothrottle operation is not available. See paragraph 2.10 for details on how to perform A/T calibration. A/T INIT The A/T INIT flag will be displayed if the ISU failed to send the setup commands to the motor and receive and acknowledgement from the Autothrottle. POSITION INPUT INVALID The position sensor reads a value outside of the calibrated range. Autothrottle operation is not available. See paragraph 2.10 for details on how to perform A/T calibration. MOTOR OVERTEMP If the motor temperature exceeds the max rated limit the Autothrottle will disconnect and the motor temp fault message will be displayed.
MOTOR FAULT If the motor reports errors in the error register this flag will be displayed.
TITLE CAGE CODE PILOTS GUIDE INTEGRATED STANDBY UNIT (ISU) 0EUW0 1D-13470
Use & disclosure is governed by the statement on the document cover page. REVISION LEVEL 6 SHEET 35 of 40
4.0 CALIBRATION The ISU contains internal Accelerometers and Gyroscopes that are used to provide reliable situational awareness. To adjust for the positioning of the ISU, a calibration routine must be performed. To run the calibration routine, it is necessary to have a compass rose on a level surface that depicts at least magnetic North, South, East and West. The calibration routine also requires an aircraft pitch offset which is the difference between the aircrafts attitude on the ground versus in flight. To perform an aircraft pitch offset calibration, follow the procedures contained in Section 4.5. The ISU requires throttle calibration be performed that can be run through the A/T status menu, see Section 5.6.
Important! The calibration routine must be completed before the aircraft pitch offset procedures.
4.1 ISU REQUIRED EQUIPMENT FOR CALIBRATION The following table contains the equipment that is required for the calibration procedures contained herein. Table 4-1 Calibration Equipment
Equipment Quantity Comments Aircraft Jacks (Optional) 1 Set Used for leveling the aircraft. Inclinometer 2 Provides a level reference. Calibrated Handheld Magnetic 1 Provides a precise magnetic heading source. Compass
4.2 REQUIRED INFORMATION FOR CALIBRATION The Latitude, Longitude and Elevation must be known in order to find the magnetic field data for the specific location of the calibration. On a computer with internet access navigate to the following National Oceanic and Atmospheric Administration (NOAA) website to find the specific magnetic field data necessary for calibration.
TITLE CAGE CODE PILOTS GUIDE INTEGRATED STANDBY UNIT (ISU) 0EUW0 1D-13470
Use & disclosure is governed by the statement on the document cover page. REVISION LEVEL 6 SHEET 36 of 40
NOAA website for magnetic field data - http://www.ngdc.noaa.gov/geomag-web/#igrfwmm
Table 4-2 Magnetic Field Calculator Details
Field Parameter Value Comments Latitude Latitude of calibration Location Longitude Longitude of calibration Elevation Elevation of calibration If a more current magnetic field model Model Model IGRF 11 is available it should be used. Start Date Current Date Date range End Date Current Date These are the default values. Step Size 1 Result Result Format HTML When all of the data is entered press the ‘Calculate’ button and a new window will appear with the magnetic field information at the calibration site.
Important! Print or record the magnetic field information.
4.3 SYSTEM CONFIGURATION DURING CALIBRATION During calibration any aircraft equipment that produces a significant magnetic field should be turned off and if possible disconnected via ECBs. Devices that produce significant magnetic fields include but are not limited to: Deice Manifold Heaters, Pitot Heaters, Static Heaters, Windshield Heaters, Air Conditioners, etc. The calibration should be performed outside in an area of low magnetic influence away from buildings, fences, vehicles or any other large metal objects. The calibration should be performed using internal aircraft battery only. Do not use any external power, including power pack battery set, or ground power. If a tug is used to tow the aircraft into position during the calibration, use a hitch-type tug with a long aluminum tow bar. In each position, while the ISU is gathering data, the tug should be powered down.
4.4 ENTERING SERVICE MODE To begin calibration, select the menu key and scroll down to the Service Mode option within the first 30 seconds of power-up. This cannot be done in flight and the airspeed must be less than 50 knots. Once the service mode menu option has been selected the unit will display a prompt to cycle power to enter service mode. Cycle power. When the unit powers up it will display a Calibration option.
TITLE CAGE CODE PILOTS GUIDE INTEGRATED STANDBY UNIT (ISU) 0EUW0 1D-13470
Use & disclosure is governed by the statement on the document cover page. REVISION LEVEL 6 SHEET 37 of 40
4.5 SETTING THE AIRCRAFT PITCH OFFSET The aircraft pitch offset procedures provide the ability to level the ISU’s ADI to the aircrafts in-flight attitude characteristics. The aircraft pitch offset procedure only needs to be performed at the initial installation of the LRU. All calibration information is maintained in non-volatile memory within the LRU. 1. Level the aircraft by adjusting the aircraft roll attitude to 0.0° and the pitch attitude to 0.0°. Measurement of level can be performed by placing a digital inclinometer on the aft cabin floor. Pitch should be measured by placing the digital inclinometer parallel to the centerline of the aircraft. Roll should be measured by placing the digital inclinometer perpendicular to the centerline of the aircraft. 2. Enter Service Mode as described in Section 4.4 and select the ‘Pitch Offset’ option. 3. A confirmation page will be displayed. Verify that the aircraft is level in both pitch and roll. If any of these requirements have not been met do not proceed. 4. If the preceding requirements have been met select the ‘OK’ option to continue. 5. The ISU will display an ‘ACQUIRING DATA’ indication. Ensure that the aircraft is stationary during the calibration period.
Caution! The aircraft should remain stationary while calibrating the pitch offset. Movement of the aircraft can lead to erroneous pitch offset calibration.
6. After the calibration period the ISU will display either a ‘PITCH OFFSET CALIBRATION SUCCEEDED’ or a ‘PITCH OFFSET CALIBRATION FAILED’ indication. If the calibration failed, repeat the Aircraft Pitch Offset calibration contained herein. If the calibration is successful select ‘OK’ and cycle power to the ISU.
4.6 AUTOTHROTTLE CALIBRATION ISU An automatic throttle friction test procedure will be performed by the ISU upon power on if the engine is not running and a valid calibration is detected. If no valid calibration is detected the “A/T Cal Required” message will be displayed along the bottom of the HSI. This friction test will confirm the total range of motion for the autothrottle in the ISU. If the friction test detects a slippage of more than 20,000 the “A/T Cal Required” message will be displayed along the bottom of the HSI. Forward and Back position set points can also be set manually by moving the throttle to the min or max position and selecting the appropriate selection from the A/T setup menu. (See paragraph 2.10) The Forward and Back positions must be set before the friction test and autothrottle functionality are used.
TITLE CAGE CODE PILOTS GUIDE INTEGRATED STANDBY UNIT (ISU) 0EUW0 1D-13470
Use & disclosure is governed by the statement on the document cover page. REVISION LEVEL 6 SHEET 38 of 40
5.0 TROUBLESHOOTING All ISU issues that cannot be troubleshot using this Pilots Guide or the AFMS require factory repair and must be returned to IS&S. For more information, reference the Operations and Installation Manual, 1D-88126.
TITLE CAGE CODE PILOTS GUIDE INTEGRATED STANDBY UNIT (ISU) 0EUW0 1D-13470
Use & disclosure is governed by the statement on the document cover page. REVISION LEVEL 6 SHEET 39 of 40
6.0 DATA LOADING Reference IS&S ISU with A/T Operations and Installation Manual, 1D-88126, for specifics regarding data loading procedures.
TITLE CAGE CODE PILOTS GUIDE INTEGRATED STANDBY UNIT (ISU) 0EUW0 1D-13470
Use & disclosure is governed by the statement on the document cover page. REVISION LEVEL 6 SHEET 40 of 40