FORM: 2391 DRAWING NO: ICA-560XL Cessna Aircraft Company P.O Box 7704 WICHITA, KS 67277

Transcription

1 FORM: 2391 DRAWING NO: ICA-560XL Cessna Aircraft Company P.O Box 7704 WICHITA, KS ENGINEERING DRAWING AND PART LIST SIGNATURE AUTHORIZATION Originals Electronically Signed in the VPM System ================================================================================ REVISION: ICA-560XL ICA --- PKG: ================================================================================ ORIGINATOR (DRM) Michael Bean (APPROVE 03/22/ :15:31) MAINTENANCE_ENG (ALL) Stephen Taylor (APPROVE 03/12/ :32:24) ICA_COORDINATOR (ALL) Brice Logan (APPROVE 03/13/ :47:15) GROUP (560XL) Scott Hendrix (APPROVE 03/13/ :20:18) ODA ICA admin (ALL) Doug Carpenter (APPROVE 03/13/ :22:01) ODA_admin (ALL) Aaron Heiman (NOT REQUIRED 03/14/ :42:17) PROJECT (560XL) Aaron Heiman (APPROVE 03/14/ :42:17) TC ODA Project admin (ALL) Bob Stuever (APPROVE 03/14/ :58:26) ICA_COORDINATOR (ALL) Jason Peterson (APPROVE 03/22/ :40:54) RELEASE (ALL) Stephanie Haymond (APPROVE 03/22/ :13:32)

2 TEXTRON AVIATION INC. AIRCRAFT DIVISION WICHITA, KANSAS GH-3000/3900 ELECTRONIC STANDBY INSTRUMENT SYSTEM UPDATE ICA Supplement MODEL NO: 560XL SUPPLEMENT NO: ICA-560XL SUPPLEMENT DATE: 3/22/2018 TEXTRON AVIATION INC. Form 2261 Rev 1

3 TEXTRON AVIATION INC. AIRCRAFT DIVISION WICHITA, KANSAS REVISIONS ICA-560XL Rev: - Date: Mar 22/2018 ICA Summary Pages 1-6 Manuals Affected Description Title Maintenance Manual pages pages pages pages pages pages pages INSTRUMENT PANEL - MAINTENANCE PRACTICES AIR DATA SYSTEMS - INSPECTION/CHECK (Airplanes thru -6000) COLLINS ATTITUDE HEADING REFERENCE SYSTEM (AHRS) - ADJUSTMENT/TEST GH-3000/3900 ELECTRONIC STANDBY INSTRUMENT SYSTEM - DESCRIPTION AND OPERATION (Airplanes and On) GH-3000/3900 ELECTRONIC STANDBY INSTRUMENT SYSTEM - TROUBLESHOOTING (Airplanes and On) GH-3000/3900 ELECTRONIC STANDBY INSTRUMENT SYSTEM - MAINTENANCE PRACTICES (Airplanes and On) GH-3000/3900 ELECTRONIC STANDBY INSTRUMENT SYSTEM - ADJUSTMENT/TEST (Airplanes and On) page 1 STANDBY ELECTRONIC HORIZONTAL SITUATION INDICATOR (EHSI-4000) - DESCRIPTION AND OPERATION page pages pages STANDBY ELECTRONIC HORIZONTAL SITUATION INDICATOR (EHSI-4000) - ADJUSTMENT/TEST PITOT STATIC SYSTEMS - INSPECTION/CHECK (Airplanes and On) TAILCONE STINGER - MAINTENANCE PRACTICES The GH-3000 has been superseded by the GH-3900 because of part obsolescence beginning with Airplanes and On. The GH-3900 shares the same location, ref des and function as the original Electronic Standby Instrument. Appendix A: Illustrated Parts Catalog 1. Export Compliance See Appendix A See Attached Parts Table A. This publication contains technical data and is subject to U.S. export regulations. This information has been exported from the United States in accordance with export administration regulations. Diversion contrary to U.S. law is prohibited. ECCN: 9E991 Page 1 of 6 Mar 22/2018 TEXTRON AVIATION INC.

4 TEXTRON AVIATION INC. AIRCRAFT DIVISION WICHITA, KANSAS Revision Bars A. Revision bars in this ICA supplement identify new ICAs and/or changes to the current ICAs in the released maintenance manual. New ICAs that are not in the current maintenance manual will have a revision bar from top to bottom along the left margin. ICAs that are in the current maintenance manual and have information added, deleted or revised will have a revision bar(s) in the left margin adjacent to the added, deleted or revised information. New or changed illustrations will have a change bar for the entire length of the page. 3. Page Numbering A. The page number system for ICA included in this supplement have three-element numbers that are separated by dashes. The three-element number is found at the bottom right corner of the page, left of the page number. The date is found below the page number. B. When the chapter/system element number is followed with zeros in the section/subsystem and subject/unit element number ( ), the information is applicable to the entire system. C. When the section/subsystem element number is followed with zeros in the subject/unit element number ( ), the information is applicable to the subsystems in the system. D. The subject/unit element number is used to identify information applicable to units in the subsystems. The subject/unit element number continues in sequence from the number -01- with the number of subsystem units in which maintenance information is necessary. E. All system/subsystem/unit (chapter/section/subject) maintenance data is separated into speciied types of information: Description and Operation, Troubleshooting, Maintenance Practices, etc. Blocks of page numbers that are in sequence are used to identify the type of information: (1) Description and Operation or Troubleshooting information may not be included if the procedure is easy. When subtopics are short, they may be put together into the Maintenance Practices section. Maintenance Practices can have a mix of subtopics that includes information to service, remove, install, adjust, test, clean, paint or do approved repairs. (2) Longer procedures that are not as easy to do may be included in a speciied section. Page 1 through 99 - Description and Operation Page 101 through Troubleshooting Page 201 through Maintenance Practices Page 301 through Servicing Page 401 through Removal/Installation Page 501 through Adjustment/Test Page 601 through Inspection/Check Page 701 through Cleaning/Painting Page 801 through Approved Repairs F. A typical page number: Page 2 of 6 Mar 22/2018 TEXTRON AVIATION INC.

5 TEXTRON AVIATION INC. AIRCRAFT DIVISION WICHITA, KANSAS G. Illustrations use the same igure numbers as the page block in which they appear. For example, Figure 202 would be the second igure in a Maintenance Practices section. 4. Supplement Revisions A. Revisions to this supplement may be accomplished if changes to this supplement are required after release of the original issue and prior to incorporation into the manuals listed in the REVISIONS table. B. All revisions to this supplement will have changes identiied in detail in the revision block(s) above. C. All pages in this ICA supplement will have the same date and are valid as of the date shown. 5. ICA Incorporation into Applicable Manuals Most ICA supplements will be incorporated in the next available revision to the manuals listed above and should be used in conjunction with those manuals until the next available revision is released. A. The ICA Supplement List located in the Introduction section of each manual listed in the REVISIONS table will indicate the incorporation status as of the release date of the published revision. B. The manual revision level of the supplement incorporation will be listed in the "Manual Incorporation Status" column in the ICA Supplement List, when those ICAs associated with that manual have been incorporated. After ICAs are incorporated, the manual that they are incorporated in must now be used for those ICAs instead of the supplement. Based on revision cycle times for the affected manuals, MM ICAs, WDM ICAs, etc. in this supplement may be incorporated in the manuals at different times. There will not be a revision to this supplement to indicate incorporation in the manuals. Users are required to check the ICA Supplement List for each manual affected to determine incorporation status. C. This supplement will be completely superseded by the manuals listed in the REVISIONS table when it has been incorporated in all of the manuals. Page 3 of 6 Mar 22/2018 TEXTRON AVIATION INC.

6 TEXTRON AVIATION INC. AIRCRAFT DIVISION WICHITA, KANSAS Purpose INTRODUCTION A. The purpose of this Supplement is to provide the maintenance technician with the information necessary to ensure the correct functionality and performance of the GH-3000/3900 ELECTRONIC STANDBY INSTRUMENT SYSTEM on the Cessna Model 560XL until this information gets incorporated into the next revision to the manuals listed in the "REVISIONS" section of this supplement. B. This ICA supplement is designed to satisfy the requirements of 14 CFR "Instructions for Continued Airworthiness" associated with this installation. This document is a supplement to the Model 560XL Maintenance Manual and will be incorporated in the next revision to the manual. C. When this information is incorporated in the next revision to the manuals listed in the "REVISIONS" section, those manuals shall take precedence over this supplemental document. Refer to the "ICA Supplement List" in the "Introduction" section of the respective manual for the status of all applicable ICA Supplements. D. Revisions to this supplement may occur if there is a change to any of the ICAs in this supplement prior to incorporation into all of the affected manuals. This document must be placed with the aircraft operator's Technical Library CD-ROM or Model 560XL Maintenance Manual and incorporated into the operator's scheduled maintenance program. 2. Effectivity A. These Instructions for Continued Airworthiness (ICA) are effective for the following aircraft model and serialization. Model Beginning Effectivity Ending Effectivity 560XL and On 3. Complete ICA Documents A. The following document(s), in conjunction with this supplement, constitute the Instructions for Continued Airworthiness for the GH-3000/3900 ELECTRONIC STANDBY INSTRUMENT SYSTEM on the Cessna Model 560XL. All items must be available to the operator at initial delivery. (1) Model 560XL Maintenance Manual Page 4 of 6 Mar 22/2018 TEXTRON AVIATION INC.

7 TEXTRON AVIATION INC. AIRCRAFT DIVISION WICHITA, KANSAS Model 560XL Maintenance Manual LIST OF INSTRUCTIONS FOR CONTINUED AIRWORTHINESS A. Chapter 34 Navigation (1) Refer to ATA Instrument Panel - Maintenance Practices. (2) Refer to ATA Air Data Systems - Inspection/Check. (3) Refer to ATA Collins Attitude Heading Reference System (AHRS) - Adjustment/Test. (4) Refer to ATA GH-3000/3900 Electronic Standby Instrument System - Description/ Operation. (5) Refer to ATA GH-3000/3900 Electronic Standby Instrument System - Troubleshooting. (6) Refer to ATA GH-3000/3900 Electronic Standby Instrument System - Maintenance Practices. (7) Refer to ATA GH-3000/3900 Electronic Standby Instrument System - Adjustment/Test. (8) Refer to ATA Standby Electronic Horizontal Situation Indicator (EHSI-4000) - Description and Operation. (9) Refer to ATA Standby Electronic Horizontal Situation Indicator (EHSI-4000) - Adjustment/Test. (10) Refer to ATA Pitot Static Systems - Inspection/Check (Airplanes and On) (11) Refer to ATA Tailcone Stinger - Maintenance Practices. Page 5 of 6 Mar 22/2018 TEXTRON AVIATION INC.

8 TEXTRON AVIATION INC. AIRCRAFT DIVISION WICHITA, KANSAS Continuous Inspection Program INSPECTION PROGRAM AND AIRWORTHINESS LIMITATIONS A. This ICA Supplement does not affect the current inspection program. 2. Airworthiness Limitations A. Cessna Aircraft Company Model 560XL Maintenance Manual, Chapter 4, Airworthiness Limitations, contains the system and airframe limitations for the Model 560XL. The Airworthiness Limitations section is FAA-approved and speciies maintenance required under Section and of Title 14 Code of Federal Regulations, unless an alternative program has been FAA approved. (1) There are no new (or additional) airworthiness limitations associated with this equipment and/or installation. Page 6 of 6 Mar 22/2018 TEXTRON AVIATION INC.

9 1. General INSTRUMENT PANEL - MAINTENANCE PRACTICES A. The instrument panels are mounted to the instrument panel structure by screws. The panel assembly consists of a panel, attaching hardware and panel components. B. The following procedures are typical for removal/installation of the panel assembly. For maintenance of the individual system components. Refer to the applicable system. 2. Tools and Equipment A. For a list of required tools and equipment, Refer to Indicating/Recording Systems - General. 3. Center Panel Assembly Removal/Installation Airplanes thru A. Remove Center Panel Assembly (Refer to Figure 201). (1) Open the battery compartment access door to get access to the battery (UY006). (2) Disconnect the battery connector (PY010). (a) Put a maintenance warning tag on the battery that reads: "DO NOT CONNECT THE BATTERY. MAINTENANCE IN PROGRESS." (3) Remove RMU 1, RMU 2, and the Standby Nav/Com control unit. Refer to Chapter 23, Honeywell Primus II SRZ-850 Integrated Radio System - Maintenance Practices. (4) Remove the fuel low indicator. Refer to Instruments - Maintenance Practices, or Chapter 77, Integrated Engine Instruments - Maintenance Practices. (5) Remove the engine tachometer/fan speed/itt indicator. Refer to Chapter 77, Integrated Engine Instruments - Maintenance Practices, or Instruments - Maintenance Practices. (6) Remove the annunciator panel. Refer to Master Warning and Annunciator Panel Lights System - Maintenance Practices. (7) Remove the landing gear control handle. Refer to Chapter 32, Landing Gear Control Handle - Removal/Installation. (8) Remove the engine turbine speed/oil system indicator. Refer to Chapter 77, Integrated Engine Instruments - Maintenance Practices, or Instruments - Maintenance Practices. (9) Remove the DU-870 multifunction display and MC-800 display controller. Refer to Chapter 34, Honeywell Primus 1000 Electronic Flight Instrument System (EFIS) - Maintenance Practices. (10) Remove the MS-560 mode selector. Refer to Chapter 34, Honeywell Primus 1000 Electronic Flight Instrument System (EFIS) - Maintenance Practices. (11) Remove the fuel quantity and fuel temperature gage. Refer to Chapter 28, Fuel Quantity Gauging Components - Removal/Installation and Fuel Temperature Components - Removal/Installation. (12) Remove the Horizontal Situation Indicator. Refer to Chapter 34, Aeronetics HSI-315 Standby Horizontal Situation Indicator (HSI) - Maintenance Practices. (13) Remove the Secondary Flight Display. Refer to Chapter 34, Meggitt Secondary Flight Display - Maintenance Practices. (14) Remove the Ram Air Temperature (RAT) indicator. Refer to Instruments - Maintenance Practices. (15) Remove the Throttle Detent Position Indicator. Refer to Chapter 77, Throttle Detent Position Indicator - Maintenance Practices. (16) Remove the screws that attach the center panel and remove the center panel. (17) Remove the center panel from the airplane. B. Install Center Panel Assembly (Refer to Figure 201). (1) Put the center panel in airplane and secure with screws. (2) Install the RMU 1, the RMU 2, and the Standby Nav/Com control unit. Refer to Chapter 23, Honeywell Primus II SRZ-850 Integrated Radio System. (3) Install the fuel low indicator. Refer to Chapter 73, Engine Fuel Indicating - Maintenance Practices. (4) Install the engine tachometer/fan speed/itt indicator. Refer to Chapter 77, Fan Speed Indicator - Maintenance Practices and Turbine Speed Indicator - Maintenance Practices Page 201

10 Pilot's and Copilot's Instrument Panel Installation Figure 201 (Sheet 1) Page 202

11 Pilot's and Copilot's Instrument Panel Installation Figure 201 (Sheet 2) Page 203

12 Pilot's and Copilot's Instrument Panel Installation Figure 201 (Sheet 3) Page 204

13 Pilot's and Copilot's Instrument Panel Installation Figure 201 (Sheet 4) Page 205

14 Pilot's and Copilot's Instrument Panel Installation Figure 201 (Sheet 5) Page 206

15 (5) Install the annunciator panel. Refer to Master Warning and Annunciator Panel Lights System - Maintenance Practices. (6) Install the landing gear control handle. Refer to Chapter 32, Landing Gear Control Handle Removal/Installation. (7) Install the engine turbine speed/oil system indicator. Refer to Chapter 77, Engine Indicating. (8) Install the DU-870 multifunction display and MC-800 display controller. Refer to Chapter 34, Honeywell Primus 1000 Electronic Flight Instrument System (EFIS) - Maintenance Practices. (9) Install MS-560 mode selector. Refer to Chapter 34, Honeywell Primus 1000 Electronic Flight Instrument System (EFIS) - Maintenance Practices. (10) Install the fuel quantity and the fuel temperature gage. Refer to Chapter 28, Fuel Quantity Gauging Components and Fuel Temperature Components - Maintenance Practices. (11) Install the Horizontal Situation Indicator. Refer to Chapter 34, Aeronetics HSI-315 Standby Horizontal Situation Indicator (HSI) - Maintenance Practices. (12) Install the Secondary Flight Display indicator. Refer to Chapter 34, Meggitt Secondary Flight Display - Maintenance Practices. (13) Install the RAT Ram Air Temperature indicator. Refer to Chapter 34, Ram Outside Air Temperature - Maintenance Practices (14) Install the Throttle Detent Position Indicator. Refer to Chapter 77, Throttle Detent Position Indicator - Maintenance Practices. (15) Remove the maintenance warning tag from battery (UY009). (16) Connect the battery connector (PY010) to battery (UY009). (17) Close the battery compartment access door. (18) Do the light functional tests on internally lighted instruments, the post lights and the electroluminescent panels. Refer to Chapter 33, Flight Compartment Primary Lights - Maintenance Practices. 4. Center Panel Assembly Removal/Installation (Airplanes thru -6000) A. Remove Center Panel Assembly (Refer to Figure 201). (1) Open the battery compartment access door to get access to the battery (UY006). (2) Disconnect the battery connector (PY010). (a) Put a maintenance warning tag on the battery that reads: "DO NOT CONNECT THE BATTERY. MAINTENANCE IN PROGRESS." (3) Remove the RMU 1, the RMU 2, and the Standby Nav/Com control unit. Refer to Chapter 23, Honeywell Primus II SRZ-850 Integrated Radio System - Maintenance Practices. (4) Remove the Engine Indicating System-Active Matrix Liquid Crystal Display. Refer to Chapter 77, Integrated Engine Instruments - Maintenance Practices. (5) Remove the annunciator panel. Refer to Master Warning and Annunciator Panel Lights System - Maintenance Practices. (6) Remove the landing gear control handle. Refer to Chapter 32, Landing Gear Control Handle - Removal/Installation. (7) Remove the DU-870 multifunction display and the MC-800 display controller. Refer to Chapter 34, Honeywell Primus 1000 Electronic Flight Instrument System (EFIS) - Maintenance Practices. (8) Remove MS-560 mode selector. Refer to Chapter 34, Honeywell Primus 1000 Electronic Flight Instrument System (EFIS) - Maintenance Practices. (9) Remove the Horizontal Situation Indicator. Refer to Chapter 34, Aeronetics HSI-315 Standby Horizontal Situation Indicator (HSI) - Maintenance Practices. (10) Remove the Secondary Flight Display. Refer to Chapter 34, Meggitt Secondary Flight Display - Maintenance Practices. (11) Remove the screws securing center panel and remove center panel. (12) Remove the center panel from airplane. B. Install Center Panel Assembly (Refer to Figure 201). (1) Put the center panel in airplane and secure with screws. (2) Install the RMU 1, RMU 2, and the Standby Nav/Com control unit. Refer to Chapter 23, Honeywell Primus II SRZ-850 Integrated Radio System. (3) Install the Engine Indicating System-Active Matrix Liquid Crystal Display. Refer to Chapter 77, Integrated Engine Instruments - Maintenance Practices Page 207

16 (4) Install the annunciator panel. Refer to Master Warning and Annunciator Panel Lights System - Maintenance Practices. (5) Install the landing gear control handle. Refer to Chapter 32, Landing Gear Control Handle Removal/Installation. (6) Install the DU-870 multifunction display and MC-800 display controller. Refer to Chapter 34, Honeywell Primus 1000 Electronic Flight Instrument System (EFIS) - Maintenance Practices. (7) Install MS-560 mode selector. Refer to Chapter 34, Honeywell Primus 1000 Electronic Flight Instrument System (EFIS) - Maintenance Practices. (8) Install the Horizontal Situation Indicator. Refer to Chapter 34, Aeronetics HSI-315 Standby Horizontal Situation Indicator (HSI) - Maintenance Practices. (9) Install the Secondary Flight Display indicator. Refer to Chapter 34, Meggitt Secondary Flight Display - Maintenance Practices. (10) Remove the maintenance warning tag from battery (UY009). (11) Connect the battery connector (PY010) to battery (UY009). (12) Close the battery compartment access door. (13) Do the light functional tests on internally lighted instruments, the post lights and the electroluminescent panels. Refer to Chapter 33, Flight Compartment Primary Lights - Maintenance Practices. 5. Center Instrument Panel Assembly Removal/Installation (Airplanes And On) A. Remove the Center Instrument Panel Assembly. Refer to Figure 202. (1) Make sure that the ELECTRICAL BATT ON/OFF switch/light on the left tilt panel is in the OFF position. (2) Open the battery compartment access door to get access to the battery (UY006). (3) Disconnect the electrical connector (PY010) from the battery. (a) Put a maintenance warning tag on the battery that reads: "DO NOT CONNECT THE BATTERY. MAINTENANCE IN PROGRESS." (4) Remove the ire tray. Refer to Chapter 26, Engine Fire Tray Assembly - Maintenance Practices. (5) Remove the MFDs. Refer to Chapter 34, Collins Electronic Flight Instrument System (EFIS) - Maintenance Practices. (a) Remove the screws to release the MFD mounts from the center instrument panel. (6) Remove the Electronic Standby Attitude Indicator (ESAI). Refer to Chapter 34, GH-3000/3900 Electronic Standby Instrument System - Maintenance Practices. (a) Remove the mounting clamp from the center instrument panel. (7) Remove the Standby Electronic Horizontal Situation Indicator (EHSI). Refer to Chapter 34, Standby Electronic Horizontal Situation Indicator (EHSI-4000) - Maintenance Practices. (a) Remove the mounting clamp from the center instrument panel. (8) Remove the Standby Engine Indicator. Refer to Chapter 77, Integrated Engine Instruments - Maintenance Practices. (a) Remove the mounting clamp from the center instrument panel. (9) Remove the TAWS switch/lights. Refer to Chapter 31, Switch/Lights - Maintenance Practices. (10) Remove the screws to release the center instrument panel from the support structure. (11) Remove the center instrument panel from the airplane. B. Install the Center Instrument Panel Assembly. Refer to Figure 202. (1) Put the center instrument panel into position in the airplane. (2) Install the screws to attach the center instrument panel to the support structure. (3) Install the TAWS switch/lights. Refer to Chapter 31, Switch/Lights - Maintenance Practices. (4) Install the Standby Engine Indicator. Refer to Chapter 77, Integrated Engine Instruments - Maintenance Practices. (5) Install the Standby Electronic Horizontal Situation Indicator (EHSI). Refer to Chapter 34, Standby Electronic Horizontal Situation Indicator (EHSI-4000) - Maintenance Practices. (6) Install the Electronic Standby Attitude Indicator (ESAI). Refer to Chapter 34, GH-3000/3900 Electronic Standby Instrument System - Maintenance Practices. (7) Install the MFDs. Refer to Chapter 34, Collins Electronic Flight Instrument System (EFIS) - Maintenance Practices. (8) Install the ire tray. Refer to Chapter 26, Engine Fire Tray Assembly - Maintenance Practices. (9) Remove the maintenance warning tag from the battery (UY009) Page 208

17 Instrument Panel Assembly Installation Figure 202 (Sheet 1) Page 209

18 Instrument Panel Assembly Installation Figure 202 (Sheet 2) Page 210

19 Instrument Panel Assembly Installation Figure 202 (Sheet 3) Page 211

20 Instrument Panel Assembly Installation Figure 202 (Sheet 4) Page 212

21 Instrument Panel Assembly Installation Figure 202 (Sheet 5) Page 213

22 Instrument Panel Assembly Installation Figure 202 (Sheet 6) Page 214

23 (10) Connect the electrical connector (PY010) to the battery. (11) Close the battery compartment access door. 6. Left Panel Assembly Removal/Installation (Airplanes Thru -6000) A. Remove Left Panel Assembly (Refer to Figure 201). (1) Open the battery compartment access door to get access to the battery (UY006). (2) Disconnect the battery connector (PY010). (a) Put a maintenance warning tag on the battery that reads: "DO NOT CONNECT THE BATTERY. MAINTENANCE IN PROGRESS." (3) Remove the DU-870 primary light display and DC-550 display controller. Refer to Chapter 34, Honeywell Primus 1000 Display and Flight Guidance System - Maintenance Practices. (4) Remove the audio control panel. Refer to Chapter 23, Audio Integrating System - Maintenance Practices. (5) Remove the digital clock. Refer to Digital Clock - Maintenance Practices. (6) Remove the angle-of-attack indicator. Refer to Chapter 34, Angle-of-Attack System - Removal/ Installation. (7) Remove the MASTER WARNING RESET switch and the MASTER CAUTION RESET switch. Refer to Master Warning and Annunciator Panel Lights System - Maintenance Practices. (8) Remove the DME 1 Indicator. Refer to Chapter 34, DME - Maintenance Practices. (9) Remove the A/P OFF and the Y/D OFF switch. Refer to Aerospace Optics Switches - Maintenance Practices. (10) Remove the electroluminescent panels. Refer to Chapter 33, Flight Compartment Primary Lighting - Maintenance Practices. (11) Remove the volt and amp meters. (12) Remove screws attaching the left panel to the structure. Move the panel forward enough to access backside of panel. (13) Remove the remaining switches and relays from panel. Tag disconnected wires for later installation. (14) Remove the left panel from the airplane. B. Install Left Panel Assembly (Refer to Figure 201). (1) Install all the switches and relays that were removed. (2) Put the left panel in airplane and secure with screws. (3) Install the volt and amp meters. (4) Install the electroluminescent panels. Refer to Chapter 33, Flight Compartment Primary Lights - Maintenance Practices. (5) Install the A/P OFF and the Y/D OFF switch. Refer to Aerospace Optics Switches - Maintenance Practices. (6) Install the MASTER WARNING RESET switch and the MASTER CAUTION RESET switch. Refer to Master Warning and Annunciator Panel Lights System - Maintenance Practices. (7) Install the DME 1 Indicator. Refer to Chapter 34, DME - Maintenance Practices. (8) Install the angle-of-attack indicator. Refer to Chapter 34, Angle-of- Attack System - Removal/ Installation. (9) Install the digital clock. Refer to Digital Clock - Maintenance Practices. (10) Install the audio control panel. Refer to Chapter 23, Honeywell Audio Control System - Maintenance Practices. (11) Install the DU-870 primary light display and the DC-550 display controller. Refer to Chapter 34, Honeywell Primus 1000 Display and Flight Guidance System - Maintenance Practices. (12) Remove the maintenance warning tag from battery (UY009). (13) Connect the battery connector (PY010) to battery (UY009). (14) Close the battery compartment access door. (15) Perform the illumination check on internally lighted instruments, post lights and electroluminescent panels. Refer to Chapter 33, Flight Compartment Primary Lights - Maintenance Practices Page 215

24 7. Left Instrument Panel Assembly Removal/Installation (Airplanes And On) A. Remove the Left Instrument Panel Assembly. Refer to Figure 202. (1) Make sure that the ELECTRICAL BATT ON/OFF switch/light on the left tilt panel is in the OFF position. (2) Open the battery compartment access door to get access to the battery (UY006). (3) Disconnect the electrical connector (PY010) from the battery. (a) Put a maintenance warning tag on the battery that reads: "DO NOT CONNECT THE BATTERY. MAINTENANCE IN PROGRESS." (4) Remove the PFD. Refer to Chapter 34, Collins Electronic Flight Instrument System (EFIS) - Maintenance Practices. (a) Remove the screws to release the PFD mount from the left instrument panel. (5) Remove the Display Control Panel. Refer to Chapter 34, Collins Electronic Flight Instrument System (EFIS) - Maintenance Practices. (6) Remove the Audio Control Panel. Refer to Chapter 23, Collins Dual Audio System - Maintenance Practices. (7) Remove the digital clock. Refer to Digital Clock - Maintenance Practices. (8) Remove the battery temperature indicator. Refer to Chapter 24, Battery Temperature Gage - Removal/Installation. (9) Remove the MASTER WARNING RESET and MASTER CAUTION RESET switch/lights. Refer to Master Warning and Annunciator Panel Lights System - Maintenance Practices. (10) Remove the screws to release the left instrument panel from the support structure. (11) Remove the left instrument panel from the airplane. B. Install the Left Instrument Panel Assembly. Refer to Figure 202. (1) Put the left instrument panel into position in the airplane. (2) Install the screws to attach the left instrument panel to the support structure. (3) Install the MASTER WARNING RESET and MASTER CAUTION RESET switch/lights. Refer to Master Warning and Annunciator Panel Lights System - Maintenance Practices. (4) Install the battery temperature indicator. Refer to Chapter 24, Battery Temperature Gage - Removal/Installation. (5) Install the digital clock. Refer to Digital Clock - Maintenance Practices. (6) Install the Audio Control Panel. Refer to Chapter 23, Collins Dual Audio System - Maintenance Practices. (7) Install the Display Control Panel. Refer to Chapter 34, Collins Electronic Flight Instrument System (EFIS) - Maintenance Practices. (8) Install the PFD. Refer to Chapter 34, Collins Electronic Flight Instrument System (EFIS) - Maintenance Practices. (9) Remove the maintenance warning tag from the battery (UY009). (10) Connect the electrical connector (PY010) to the battery. (11) Close the battery compartment access door. 8. Right Panel Assembly Removal/Installation (Airplanes Thru -6000) A. Remove Right Panel Assembly (Refer to Figure 201). (1) Open the battery compartment access door to get access to the battery (UY006). (2) Disconnect the battery connector (PY010). (a) Put a maintenance warning tag on the battery that reads: "DO NOT CONNECT THE BATTERY. MAINTENANCE IN PROGRESS." (3) Remove the DU- 870 primary light display and the DC-550 display controller. Refer to Chapter 34, Honeywell Primus 1000 Display and Flight Guidance System - Maintenance Practices. (4) Remove the audio control panel. Refer to Chapter 23, Honeywell Audio Control System - Maintenance Practices. (5) Remove the digital clock. Refer to Digital Clock - Maintenance Practices. (6) Remove the DME 2 Indicator. Refer to Chapter 34, DME - Maintenance Practices. (7) Remove the oxygen pressure indicator. Refer to Chapter 35, Oxygen Pressure Gauge- Removal/Installation. (8) Remove the MASTER WARNING RESET switch and the MASTER CAUTION RESET switch. Refer to Master Warning and Annunciator Panel Lights System - Maintenance Practices Page 216

25 (9) Remove the A/P OFF and the Y/D OFF switch. Refer to Aerospace Optics Switches - Maintenance Practices. (10) Remove the electroluminescent panels. Refer to Chapter 33, Flight Compartment Primary Lights - Maintenance Practices. (11) Remove the cockpit voice recorder control panel. Refer to Chapter 23, Fairchild A200S Cockpit Voice Recorder - Maintenance Practices. (12) Remove the battery temperature gage. Refer to Chapter 24, Battery Temperature Gage - Maintenance Practices. (13) Remove the screws securing right panel to structure. Carefully withdraw panel to allow access to switches and connectors. (14) Remove all remaining switches from panel. Tag all disconnected wires for later reassembly. B. Install Right Panel Assembly (Refer to Figure 201). (1) Install all the switches that were removed. (2) Put the right panel in airplane and secure with screws. (3) Install the battery temperature gage. Refer to Chapter 24, Battery Temperature Gage - Maintenance Practices. (4) Install the cockpit voice recorder control panel. Refer to Chapter 23, Fairchild A200S Cockpit Voice Recorder - Maintenance Practices. (5) Install the electroluminescent panels. Refer to Chapter 33, Flight Compartment Primary Lights - Maintenance Practices. (6) Install the AP OFF and the Y/D OFF annunciator. Refer to Aerospace Optics Switches - Maintenance Practices. (7) Install the MASTER WARNING RESET switch and the MASTER CAUTION RESET switch. Refer to Master Warning and Annunciator Panel Lights System - Maintenance Practices. (8) Install the oxygen pressure indicator. Refer to Chapter 35, Crew Oxygen - Maintenance Practices. (9) Install the DME 2 Indicator. Refer to Chapter 34, DME - Maintenance Practices. (10) Install the digital clock. Refer to Digital Clock - Maintenance Practices. (11) Install the audio control panel. Refer to Chapter 23, Honeywell Audio Control System - Maintenance Practices. (12) Install the DU-870 primary light display and the DC-550 display controller. Refer to Chapter 34, Honeywell Primus 1000 Display and Flight Guidance System - Maintenance Practices. (13) Remove the maintenance warning tag from the battery (UY009). (14) Connect battery connector (PY010) to battery (UY009). (15) Close the battery compartment access door. (16) Do the light functional test on internally lighted instruments, the post lights and the electroluminescent panels. Refer to Chapter 33, Flight Compartment Primary Lights - Maintenance Practices. 9. Right Instrument Panel Assembly Removal/Installation (Airplanes And On) A. Remove the Right Instrument Panel Assembly. Refer to Figure 202. (1) Make sure that the ELECTRICAL BATT ON/OFF switch/light on the left tilt panel is in the OFF position. (2) Open the battery compartment access door to get access to the battery (UY006). (3) Disconnect the electrical connector (PY010) from the battery. (a) Put a maintenance warning tag on the battery that reads: "DO NOT CONNECT THE BATTERY. MAINTENANCE IN PROGRESS." (4) Remove the PFD. Refer to Chapter 34, Collins Electronic Flight Instrument System (EFIS) - Maintenance Practices. (a) Remove the screws to release the PFD mount from the left instrument panel. (5) Remove the Display Control Panel. Refer to Chapter 34, Collins Electronic Flight Instrument System (EFIS) - Maintenance Practices. (6) Remove the Audio Control Panel. Refer to Chapter 23, Collins Dual Audio System - Maintenance Practices. (7) Remove the MASTER WARNING RESET and MASTER CAUTION RESET switch/lights. Refer to Master Warning and Annunciator Panel Lights System - Maintenance Practices Page 217

26 (8) Remove the APU FIRE PUSH Switch/Light. Refer to Chapter 49, Auxiliary Power Unit Indicating - Maintenance Practices. (9) Remove the APU RELAY ENGAGE/APU FAIL Indicator. Refer to Chapter 49, Auxiliary Power Unit Indicating - Maintenance Practices. (10) Remove the APU Ammeter. Refer to Chapter 49, Auxiliary Power Unit Indicating - Maintenance Practices. (11) Remove the screws to release the right instrument panel from the support structure. (12) Remove the right instrument panel from the airplane. B. Install the Right Instrument Panel Assembly. Refer to Figure 202. (1) Put the right instrument panel into position in the airplane. (2) Install the screws to attach the right instrument panel to the support structure. (3) Install the APU Ammeter. Refer to Chapter 49, Auxiliary Power Unit Indicating - Maintenance Practices. (4) Install the APU RELAY ENGAGE/APU FAIL Indicator. Refer to Chapter 49, Auxiliary Power Unit Indicating - Maintenance Practices. (5) Install the APU FIRE PUSH Switch/Light. Refer to Chapter 49, Auxiliary Power Unit Indicating - Maintenance Practices. (6) Install the MASTER WARNING RESET and MASTER CAUTION RESET switch/lights. Refer to Master Warning and Annunciator Panel Lights System - Maintenance Practices. (7) Install the Audio Control Panel. Refer to Chapter 23, Collins Dual Audio System - Maintenance Practices. (8) Install the Display Control Panel. Refer to Chapter 34, Collins Electronic Flight Instrument System (EFIS) - Maintenance Practices. (9) Install the PFD. Refer to Chapter 34, Collins Electronic Flight Instrument System (EFIS) - Maintenance Practices. (10) Remove the maintenance warning tag from the battery (UY009). (11) Connect the electrical connector (PY010) to the battery. (12) Close the battery compartment access door. 10. Tilt Panel Assembly Removal/Installation (Airplanes Thru -6000) A. Remove Tilt Panel Assembly (Refer to Figure 201). (1) Open the battery compartment access door to get access to the battery (UY006). (2) Disconnect the battery connector (PY010). (a) Put a maintenance warning tag on the battery that reads: "DO NOT CONNECT THE BATTERY. MAINTENANCE IN PROGRESS." (3) Put the maintenance warning tag on airplane, stating "DO NOT CONNECT ELECTRICAL POWER". (4) Remove the BLEED AIR SELECT knob. (5) Remove the electroluminescent panel (EL panel) from tilt panel. Refer to Chapter 33, Flight Compartment Primary Lighting - Maintenance Practices. (6) Remove the Temperature Controller from tilt panel. Refer to Chapter 21, Cabin/Cockpit Temperature Control System - Maintenance Practices. (7) Remove the cabin altitude controller. Refer to Chapter 21, Pressurization Control - Maintenance Practices. (8) Remove the Cabin Pressurization Controller from the tilt panel. Refer to Chapter 21, Pressurization Control - Maintenance Practices. (9) Remove the Cabin Altitude Controller. Refer to Chapter 21, Pressurization Control - Maintenance Practices. (10) Remove the Cabin Differential Pressure Gage. Refer to Chapter 21, Pressurization Control - Maintenance Practices. (11) Remove the Manual Pressurization Toggle Valve. Refer to Chapter 21, Pressurization Control - Maintenance Practices. (12) Disconnect the tilt panel plugs (PI006) and (PI004) from the connectors (JI006) and (JI004). (13) Remove the screws attaching the tilt panel to the center panel structure. (14) Remove the tilt panel from the airplane. B. Install Tilt Panel Assembly (Refer to Figure 201). (1) Connect the plugs (PI006 and PI004) to the tilt panel connectors (JI006 and JI004) Page 218

27 (2) Install the Cabin Altitude Controller Gage. Refer to Chapter 21, Pressurization Control - Maintenance Practices. (3) Install the Manual Pressurization Valve toggle. Refer to Chapter 21, Pressurization Control - Maintenance Practices. (4) Install the Cabin Differential Gage. Refer to Chapter 21, Pressurization Control - Maintenance Practices. (5) Install the Cabin Pressurization Controller. Refer to Chapter 21, Pressurization Control - Maintenance Practices. (6) Put the tilt panel in the airplane and attach with screws. (7) Install the electroluminescent panel (EL panel) on tilt panel. Refer to Chapter 33, Flight Compartment Primary Lighting - Maintenance Practices. (8) Install the BLEED AIR SELECT knob. (9) Install the Temperature Controller. Refer to Chapter 21, Cabin/Cockpit Temperature Control System - Maintenance Practices. (10) Remove the maintenance warning tag from battery (UY009). (11) Connect the battery connector (PY010) to the battery (UY009). (12) Close the battery compartment access door. (13) Do a check of all the related systems that were removed and installed with the tilt panel installation to make sure that all the systems operate correctly. (a) Make sure the pressure system operates correctly with the BLEED AIR SELECT knob positions. 11. Left Tilt Panel Assembly Removal/Installation (Airplanes and On) A. Remove the Left Tilt Panel Assembly. Refer to Figure 202. (1) Make sure that the ELECTRICAL BATT ON/OFF switch/light on the left tilt panel is in the OFF position. (2) Open the battery compartment access door to get access to the battery (UY006). (3) Disconnect the electrical connector (PY010) from the battery. (a) Put a maintenance warning tag on the battery that reads: "DO NOT CONNECT THE BATTERY. MAINTENANCE IN PROGRESS." (4) Remove the oxygen pressure gage from the left switch tilt EL panel. Refer to Chapter 35, Oxygen Pressure Gage - Removal/Installation. (5) Remove the MIC SEL HEADSET/MASK, COCKPIT SPEAKERS, AHRS REV, and ADC REV switch/lights from the left switch tilt EL panel. Refer to Switch/Lights - Maintenance Practices. (6) Remove the two L AHRS SLAVE switches from the left switch tilt EL panel. (7) Remove the knob from the passenger oxygen control valve on the left switch tilt EL panel. (8) Remove the left switch tilt EL panel. Refer to Chapter 33, Flight Compartment Primary Lighting - Maintenance Practices. (9) Remove the passenger oxygen control valve from the structure. Refer to Chapter 35, Passenger Oxygen Controls - Removal/Installation. (10) Remove the knob from the FUEL CROSSFEED switch on the FUEL ENGINE tilt EL panel. (11) Remove the FUEL BOOST L, FUEL BOOST R, IGNITION L, IGNITION R, FADEC RESET L, and FADEC RESET R switch/lights from the FUEL ENGINE tilt EL panel. Refer to Switch/Lights - Maintenance Practices. (12) Remove the FUEL ENGINE tilt EL panel. Refer to Chapter 33, Flight Compartment Primary Lighting - Maintenance Practices. (13) Remove the FUEL CROSSFEED switch from the structure. (14) Remove the control lock tilt EL panel. Refer to Chapter 33, Flight Compartment Primary Lighting - Maintenance Practices. (15) Remove the BATT, NORM/EMER, AVIONICS, GROUND DISPATCH, and INTERIOR switch/ lights from the ELECTRICAL tilt EL panel. Refer to Switch/Lights - Maintenance Practices. (16) Remove the L GEN, R GEN, STBY PWR, and EMER LTS switches from the ELECTRICAL tilt EL panel. (17) Remove the ELECTRICAL tilt EL panel. Refer to Chapter 33, Flight Compartment Primary Lighting - Maintenance Practices. (18) Remove the screws to release the left tilt panel assembly from the support structure. (19) Remove the left tilt panel assembly from the airplane Page 219

28 B. Install the Left Tilt Panel Assembly. Refer to Figure 202. (1) Put the left tilt panel assembly into position in the airplane. (2) Install the screws to attach the left tilt panel assembly to the support structure. (3) Install the ELECTRICAL tilt EL panel. Refer to Chapter 33, Flight Compartment Primary Lighting - Maintenance Practices. (4) Install the L GEN, R GEN, STBY PWR, and EMER LTS switches in the ELECTRICAL tilt EL panel. (5) Install the BATT, NORM/EMER, AVIONICS, GROUND DISPATCH, and INTERIOR switch/lights in the ELECTRICAL tilt EL panel. Refer to Switch/Lights - Maintenance Practices. (6) Install the control lock tilt EL panel. Refer to Chapter 33, Flight Compartment Primary Lighting - Maintenance Practices. (7) Attach the FUEL CROSSFEED switch to the structure with the screws. (8) Install the FUEL ENGINE tilt EL panel. Refer to Chapter 33, Flight Compartment Primary Lighting - Maintenance Practices. (9) Install the FUEL BOOST L, FUEL BOOST R, IGNITION L, IGNITION R, FADEC RESET L, and FADEC RESET R switch/lights in the FUEL ENGINE tilt EL panel. Refer to Switch/Lights - Maintenance Practices. (10) Install the knob on the FUEL CROSSFEED switch in the FUEL ENGINE tilt EL panel. (11) Install the passenger oxygen control valve to the structure. Refer to Chapter 35, Passenger Oxygen Controls - Removal/Installation. (12) Install the left switch tilt EL panel. Refer to Chapter 33, Flight Compartment Primary Lighting - Maintenance Practices. (13) Install the knob on the passenger oxygen control valve in the left switch tilt EL panel. (14) Install the two L AHRS SLAVE switches in the left switch tilt EL panel. (15) Install the MIC SEL HEADSET/MASK, COCKPIT SPEAKERS, AHRS REV, and ADC REV switch/lights in the left switch tilt EL panel. Refer to Switch/Lights - Maintenance Practices. (16) Install the oxygen pressure gage in the left switch tilt EL panel. Refer to Chapter 35, Oxygen Pressure Gage - Removal/Installation. (17) Remove the maintenance warning tag from the battery (UY009). (18) Connect the electrical connector (PY010) to the battery. (19) Close the battery compartment access door. (20) Do a check of all the related systems that you removed and installed on the left tilt panel assembly to make sure that all the systems operate correctly. 12. Right Tilt Panel Assembly Removal/Installation (Airplanes and On) A. Remove the Right Tilt Panel Assembly. Refer to Figure 202. (1) Make sure that the ELECTRICAL BATT ON/OFF switch/light on the left tilt panel is in the OFF position. (2) Open the battery compartment access door to get access to the battery (UY006). (3) Disconnect the electrical connector (PY010) from the battery. (a) Put a maintenance warning tag on the battery that reads: "DO NOT CONNECT THE BATTERY. MAINTENANCE IN PROGRESS." (4) Remove the landing gear control EL panel. Refer to Chapter 33, Flight Compartment Primary Lighting - Maintenance Practices. (5) Remove the landing gear control. Refer to Chapter 32, Landing Gear Control Unit - Maintenance Practices. (6) Remove the PITOT/STATIC, W/S FAN, WING XFLOW, and WING INSP LTS switch/lights from the ANTI-ICE tilt EL panel. Refer to Switch/Lights - Maintenance Practices. (7) Remove the WING/ENGINE and TAIL switches from the ANTI-ICE tilt EL panel. (8) Remove the ANTI-ICE tilt EL panel. Refer to Chapter 33, Flight Compartment Primary Lighting - Maintenance Practices. (9) Remove the PRESS SOURCE knob from the PRESSURIZATION tilt EL panel. (10) Remove the CABIN PRESS MODE, CABIN DUMP, and CABIN TEMP CTL switch/lights from the PRESSURIZATION tilt EL panel. Refer to Switch/Lights - Maintenance Practices. (11) Remove the MANUAL and CKPT RECIRC switches from the PRESSURIZATION tilt EL panel. (12) Remove the PRESSURIZATION tilt EL panel. Refer to Chapter 33, Flight Compartment Primary Lighting - Maintenance Practices. (13) Remove the PRESS SOURCE select switch from the structure Page 220

29 (14) Remove the cockpit/cabin temperature controller. Refer to Chapter 21, Cabin/Cockpit Temperature Control System - Maintenance Practices. (15) Remove the ADC REV, AHRS REV, COCKPIT SPEAKERS, and MIC SEL HEADSET/MASK switch/lights from the right switch tilt EL panel. Refer to Switch/Lights - Maintenance Practices. (16) Remove the two R AHRS SLAVE switches from the right switch tilt EL panel. (17) Remove the right switch tilt EL panel. Refer to Chapter 33, Flight Compartment Primary Lighting - Maintenance Practices. (18) Remove the cabin altitude controller. Refer to Chapter 21, Pressurization Control - Maintenance Practices. (19) Remove the cabin differential pressure gage. Refer to Chapter 21, Pressurization Control - Maintenance Practices. (20) Remove the screws to release the right tilt panel assembly from the support structure. (21) Remove the right tilt panel assembly from the airplane. B. Install the Right Tilt Panel Assembly. Refer to Figure 202. (1) Put the right tilt panel assembly into position in the airplane. (2) Install the screws to attach the right tilt panel assembly to the support structure. (3) Install the cabin differential pressure gage. Refer to Chapter 21, Pressurization Control - Maintenance Practices. (4) Install the cabin altitude controller. Refer to Chapter 21, Pressurization Control - Maintenance Practices. (5) Install the right switch tilt EL panel. Refer to Chapter 33, Flight Compartment Primary Lighting - Maintenance Practices. (6) Install the two R AHRS SLAVE switches in the right switch tilt EL panel. (7) Install the ADC REV, AHRS REV, COCKPIT SPEAKERS, and MIC SEL HEADSET/MASK switch/lights in the right switch tilt EL panel. Refer to Switch/Lights - Maintenance Practices. (8) Install the cockpit/cabin temperature controller. Refer to Chapter 21, Cabin/Cockpit Temperature Control System - Maintenance Practices. (9) Install the PRESS SOURCE select switch to the structure. (10) Install the PRESSURIZATION tilt EL panel. Refer to Chapter 33, Flight Compartment Primary Lighting - Maintenance Practices. (11) Install the MANUAL and CKPT RECIRC switches in the PRESSURIZATION tilt EL panel. (12) Install the CABIN PRESS MODE, CABIN DUMP, and CABIN TEMP CTL switch/lights in the PRESSURIZATION tilt EL panel. Refer to Switch/Lights - Maintenance Practices. (13) Install the PRESS SOURCE knob in the PRESSURIZATION tilt EL panel. (14) Install the ANTI-ICE tilt EL panel. Refer to Chapter 33, Flight Compartment Primary Lighting - Maintenance Practices. (15) Install the WING/ENGINE and TAIL switches in the ANTI-ICE tilt EL panel. (16) Install the PITOT/STATIC, W/S FAN, WING XFLOW, and WING INSP LTS switch/lights in the ANTI-ICE tilt EL panel. Refer to Switch/Lights - Maintenance Practices. (17) Install the landing gear control. Refer to Chapter 32, Landing Gear Control Unit - Maintenance Practices. (18) Install the landing gear control EL panel. Refer to Chapter 33, Flight Compartment Primary Lighting - Maintenance Practices. (19) Remove the maintenance warning tag from the battery (UY009). (20) Connect the electrical connector (PY010) to the battery. (21) Close the battery compartment access door. (22) Do a check of all the related systems that you removed and installed on the left tilt panel assembly to make sure that all the systems operate correctly. Task Instrument Panel Area Inspection A. Access. (1) Remove pilot and copilot seats. B. Inspection. (1) Visually examine the face of all of the instrument panels Page 221

30 (2) Examine all gages and display units for security of installation, evidence of damage and legibility of markings and placards. (3) From under instrument panel, visually examine all of the components and structures for security of installation and evidence of damage. (a) Examine the visible portion of aft side of the forward pressure bulkhead for security of component attachment, evidence of damage and general condition. (b) Comply with general electrical wiring inspection per task and hose and line inspection per Task Pay particular attention to wiring which may have become loose and may become entangled with the rudder pedals, torque tube or interfere with the crew's feet. (4) Restore access as required. End of task Page 222