WINGTIP LED LIGHTING UPDATE ICA Supplement

TEXTRON AVIATION INC. AIRCRAFT DIVISION WICHITA, KANSAS 67277

MODEL NO: 525B

SUPPLEMENT NO: ICA-525B-33-00002 SUPPLEMENT DATE: 9/14/2018

REVISIONS

ICA-525B-33-00002 Rev: - Date: Sep 14/2018 ICA Summary Pages 1-6 Manuals Affected Description Title 33-40-00 Pages Exterior Lighting - Description and Operation 1-2 33-40-00 Pages Exterior Lighting - Maintenance Practices 201-215 Maintenance Manual 33-40-01 Page Exterior LED Lighting - Troubleshooting 101 33-40-01 Pages Exterior LED Lighting - Maintenance Practices 201-211 • Adds in description of LED Anti Collision Light Modification/Service Bulletin and covers troubleshooting/maintenance of the modification. Appendix A: Illustrated Parts NOT USED Catalog Appendix B: Model 525B 33-40-01 Figure (Serials -0001 thru -0056 02 Pages 0-3 Navigation and Anti Collision Light Mod and -0058 thru -0134) Wiring Diagram Manual Appendix B: Model 525B 33-40-02 Figure (Serials -0057 and -0135 and 03 Pages 0-3 Navigation and Anti Collision Light Mod On) Wiring Diagram Manual

1. Export Compliance 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

2. 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.

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B. When the chapter/system element number is followed with zeros in the section/subsystem and subject/unit element number (28-00-00), 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 (28-21-00), 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 specified 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 specified section. Page 1 through 99 - Description and Operation Page 101 through 199 - Troubleshooting Page 201 through 299 - Maintenance Practices Page 301 through 399 - Servicing Page 401 through 499 - Removal/Installation Page 501 through 599 - Adjustment/Test Page 601 through 699 - Inspection/Check Page 701 through 799 - Cleaning/Painting Page 801 through 899 - Approved Repairs F. A typical page number:

G. Illustrations use the same figure numbers as the page block in which they appear. For example, Figure 202 would be the second figure in a Maintenance Practices section.

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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 identified 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

NOTE: 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.

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INTRODUCTION

1. Purpose 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 WINGTIP LED LIGHTING UPDATE on the Cessna Model 525B 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 23.1529 "Instructions for Continued Airworthiness" associated with this installation. This document is a supplement to the Model 525B Wiring Diagram 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.

NOTE: This document must be placed with the aircraft operator's Technical Library CD-ROM or Model 525B 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 Airplanes -0001 Thru -0293 Incorporating 525B SB525B-33-07

3. Complete ICA Documents A. The following document(s), in conjunction with this supplement, constitute the Instructions for Continued Airworthiness for the WINGTIP LED LIGHTING UPDATE. All items must be available to the operator at initial delivery. (1) Model 525B Maintenance Manual (2) Model 525B (Serials -0001 thru -0056 and -0058 thru -0134) Wiring Diagram Manual (3) Model 525B (Serials -0057 and -0135 and On) Wiring Diagram Manual

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LIST OF INSTRUCTIONS FOR CONTINUED AIRWORTHINESS

1. Model 525B Maintenance Manual A. Chapter 33, Lights (1) ATA 33-40-00, Exterior Lighting - Description and Operation (2) ATA 33-40-00, Exterior Lighting - Maintenance Practices (3) ATA 33-40-01, Exterior LED Lighting - Troubleshooting (4) ATA 33-40-01, Exterior LED Lighting - Maintenance Practices

2. Model 525B (Serials -0001 thru -0056 and -0058 thru -0134) Wiring Diagram Manual A. Chapter 33, Lights (1) ATA 33-40-01, Figure 02, Navigation and Anti Collision Light Mod

3. Model 525B (Serials -0057 and -0135 and On) Wiring Diagram Manual A. Chapter 33, Lights (1) ATA 33-40-02, Figure 03, Navigation and Anti Collision Light Mod

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INSPECTION PROGRAM AND AIRWORTHINESS LIMITATIONS

1. Continuous Inspection Program A. This ICA Supplement does not affect the current inspection program.

2. Airworthiness Limitations A. Cessna Aircraft Company Model 525B Maintenance Manual, Chapter 4, Airworthiness Limitations, contains the system and airframe limitations for the Model 525B.

NOTE: The Airworthiness Limitations section is FAA-approved and specifies maintenance required under Section 43.16 and 91.403 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.

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EXTERIOR LIGHTING - DESCRIPTION AND OPERATION

1. General A. The exterior lighting system contains the landing/taxi lights, navigation lights, anti-collision lights, the left wing inspection light, the optional right wing inspection light, and the ground recognition beacon. It is possible that optional tail floodlights are installed. On Airplanes -0057, -0263, and -0294 and On, LED exterior lights are installed. For Airplanes -0057 and -0451 and On, some of the exterior lights are controlled by one of the two the Garmin GTC 570 Touchscreen Control Units. Service Bulletin SB525B-33-07 (Airplanes -0001 thru -0293) is available to convert the anti-collision lights to the LED format, the LED format does not require a power supply. The exterior lighting system gives sufficient light for airplane operation during the day or night.

2. Description A. The landing/taxi lights are installed in the fuselage fairing, immediately forward of the forward wing spar. When the LANDING light switches are in the RECOG/TAXI position, the lights operate as taxi lights during ground operation, and as recognition lights while in the air. When the LANDING light switches are in the LANDING position, the lights operate as landing lights. B. Navigation lights include the red and green lights installed in the wing tips and the white light installed in the tail at the top of the vertical stabilizer. The left wing tip contains a red navigation light and the right wing tip contains a green navigation light. C. Anti-collision lights are the white, flashing lights installed in the wing tips. The anti-collision lights use the same mount base as the navigation lights. D. The ground recognition beacon is a red light installed at the top of the vertical stabilizer that flashes. E. A wing inspection light is installed in the fuselage, on the left side, forward of the wing leading edge. On Airplanes -0213 and On, it is possible to have an optional wing inspection light installed on the right side of the fuselage. The installation of the right and left wing inspection lights are typical. The function of the lights is to let the pilot visually examine the wing leading edge for ice conditions. F. Optional tail flood lights, if installed, are found below the left and right horizontal stabilizers. When activated, the lights show the vertical tail surface.

3. Operation A. Landing/taxi lights are controlled by manual LANDING L and R switches (SI065 left, SI066 right) found on the left instrument panel. When the switches are in the L or R position, two relays on each side of the airplane (KL001 and KZ001 left, KR001 and KZ002 right) engage and the light assembly receives 28 VDC at 17.8 amps. When the switch is moved to the RECOG/TAXI position, one relay on each side (KL001 and KR001) disengages and electrical power is sent through a resistor that causes the current to be reduced which causes the light output to decrease. B. Navigation lights are controlled as follows: (1) For Airplanes -0001 thru -0056 and -0058 thru -0450, by a single manual navigation light switch (SI055) on the left switch panel. This switch controls 28 VDC to the navigation lights. (2) For Airplanes -0057 and -0451 and On, by one of the two the Garmin GTC 570 Touchscreen Control Units. For a general overview of the GTC 570 refer to Chapter 34, Garmin G3000 Integrated Avionics System - Description and Operation, Garmin GTC 570 Touchscreen Control Unit. C. Anti-collision lights are controlled by a single manual anti-collision light switch (SI056) on the left switch panel. The switch controls 28 VDC electrical power to the anti-collision light power supplies (UL020 left, UR020 right). Each light has its own power supply. When DC electrical power is applied to the power supply, an on and off current is sent to the anti-collision light and the light flashes. Airplanes -0001 thru -0293 incorporating SB525B-33-07 and Airplanes -0294 and On utilize LED anti-collision lights and do not have power supplies.

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D. The ground recognition beacon is controlled as follows: (1) For Airplanes -0001 thru -0056 and -0058 thru -0450, by the beacon light switch (SI024) on the left switch panel. When the switch is put in the BEACON position the red strobe light assembly will operate at a rate of 45 to 55 flashes-per-minute. (2) For Airplanes -0057 and -0451 and On, by one of the two the Garmin GTC 570 Touchscreen Control Units. The beacon light is protected by the 5 ampere GROUND RECOG BEACON (HZ060) circuit breaker on the aft J-Box. For a general overview of the GTC 570 refer to Chapter 34, Garmin G3000 Integrated Avionics System - Description and Operation, Garmin GTC 570 Touchscreen Control Unit. E. The wing inspection light is controlled by the wing inspection light switch (SI025) on the left switch panel. When the switch is put in the WING INSP position the wing inspection light comes on. F. Optional tail flood lights are controlled as follows: (1) For Airplanes -0001 thru -0056 and -0058 thru -0450, by the TAIL FLOOD switch (SI109) on the lighting control panel. When the switch is in the FLOOD position the lights on the vertical tail surface come on. (2) For Airplanes -0057 and -0451 and On, by one of the two the Garmin GTC 570 Touchscreen Control Units. The tail food light is protected by the 5 ampere TAIL FLOOD LIGHTS (HZ062) circuit breaker on the aft J-Box. For a general overview of the GTC 570 refer to Chapter 34, Garmin G3000 Integrated Avionics System - Description and Operation, Garmin GTC 570 Touchscreen Control Unit.

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EXTERIOR LIGHTING - MAINTENANCE PRACTICES

1. General A. This section contains the data that is necessary to complete maintenance procedures on the exterior lights. The exterior lights include the landing/taxi lights, the navigation lights, the anti-collision lights, the ground recognition lights, the left wing inspection light and the optional right wing inspection light. It is possible optional tail floodlights are installed. For a description of each of the lighting systems, refer to Exterior Lighting - Description and Operation.

2. Tools and Equipment A. For a list of tools and equipment refer to Lighting - General.

3. Navigation Light Removal/Installation

NOTE: The removal and installation procedure for the left and right navigation lights is typical. A. Remove the Navigation Light Assembly (Refer to Figure 201). (1) Open the aft baggage compartment door. (2) Open access panel 321CC to get access to the aft circuit breaker panel, installed in the aft power J-Box. Refer to Chapter 6, Access Plates and Panels Identification - Description and Operation. (3) Disengage the NAV LIGHTS circuit breaker on the aft circuit breaker panel. Refer to Chapter 24, DC Electrical Load Distribution - Description and Operation. (4) Remove the screws that attach the retainers, clear lens, and gasket to the mounting base. (5) Remove the retainers and the clear lens from the mounting base. (6) Remove the gasket from the mounting base. (7) Remove the screws that attach the colored lens, lamp holder (FL001 left, FR001 right), and gasket to the mounting base. (8) Disconnect the electrical wires from the navigation lamp holder at the splices (AL028 and AL029 left, AR023 and AR024 right). (9) Remove the navigation lamp holder from the airplane. B. Install the Navigation Light Assembly (Refer to Figure 201). (1) Push the navigation light wires through the mounting base. (2) Connect the electrical wires to the navigation lamp holder (FL001 left, FR001 right) at the splices (AL028 and AL029 left, AR023 and AR024 right). (3) Use the screws to install the gasket, navigation lamp holder, and colored lens on the mounting base. (4) Use the screws to install the retainers and clear lens on the mounting base. (5) Engage the NAV LIGHTS circuit breaker on the aft circuit-breaker panel. Refer to Chapter 24, DC Electrical Load Distribution - Description and Operation.

4. Anti-Collision Light Removal/ Installation (Airplanes -0001 thru -0056 and Airplanes -058 thru -0262 and Airplanes -0264 thru -0293 Not Incorporating SB525B-33-07)

NOTE: The removal and installation procedures for the left or right anti-collision lights are typical. A. Remove the Anti-Collision Light (Refer to Figure 201). (1) Open the aft baggage compartment door. (2) Open access panel 321CC to get access to the aft circuit breaker panel, installed in the aft power J-Box. Refer to Chapter 6, Access Plates and Panels Identification - Description and Operation. (3) Disengage the ANTI-COLLISION LIGHT circuit breaker on the aft circuit breaker panel. Refer to Chapter 24, DC Electrical Load Distribution - Description and Operation. (4) Remove the screws that attach the retainer, clear lens, and gasket to the mounting base. (5) Remove the retainers, clear lens, and gasket from the mounting base. (6) Remove the screws that attach the anti-collision light (FL002 left, FR002 right) to the mounting base. (7) Disconnect the electrical connector (PL021 left, PR035 right) from the anti-collision light. (8) Remove the anti-collision light from the airplane.

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Navigation and Anti-Collision Light Installation Figure 201 (Sheet 1)

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B. Install the Anti-Collision Light (Refer to Figure 201). (1) Connect the electrical connector (PL021 left, PR035 right) to the anti-collision light (FL002 left, FR002 right). (2) Use the screws to attach the anti-collision light assembly to the mounting base. (3) Use the screws to install the gasket, clear lens, and retainers on the mounting base. (4) Engage the ANTI-COLLISION LIGHT circuit breaker on the aft circuit breaker panel. Refer to Chapter 24, DC Electrical Load Distribution - Description and Operation. (5) Close access panel 321CC. Refer to Chapter 6, Access Plates and Panel Identification - Description and Operation. (6) Close the aft baggage compartment door.

5. Anti-Collision Light Power Supply Removal/Installation (Airplanes -0001 thru -0056 and Airplanes -058 thru -0262 and Airplanes -0264 thru -0293 Not Incorporating SB525B-33-07 A. Remove the Anti-Collision Light Power Supply (Refer to Figure 201). (1) Open the aft baggage compartment door. (2) Open access panel 321CC to get access to the aft circuit breaker panel, installed in the aft power J-Box. Refer to Chapter 6, Access Plates and Panels Identification - Description and Operation. (3) Disengage the ANTI-COLLISION LIGHT circuit breaker on the aft circuit breaker panel. Refer to Chapter 24, DC Electrical Load Distribution - Description and Operation. (4) Remove wing access panel 542GB left, or 642GB right to get access to the anti-collision power supply (UL006 left, UR006 right). Refer to Chapter 6, Access Plates and Panels Identification - Description and Operation. (5) Withdraw access panel sufficiently to get access to anti-collision power supply electrical connectors. (6) Disconnect the electrical connectors (PL006 and PL007 left, PR006 and PR007 right) from the anti-collision power supply. (7) Remove the screws that attach the anti-collision power supply to the access panel. B. Install the Anti-Collision Power Supply (Refer to Figure 201). (1) Use the screws to attach the anti-collision power supply (UL006 left, UR006 right) to access panel 542GB left, or 642GB right. (2) Connect the electrical connectors (PL006 and PL007 left, PR006 and PR007 right) to the anti- collision power supply. (3) Install the access panel and power supply assembly to the wing. Refer to Chapter 6, Access Plates and Panels Identification - Description and Operation. (4) Engage the ANTI-COLLISION LIGHT circuit breaker on the aft circuit breaker panel. Refer to Chapter 24, DC Electrical Load Distribution - Description and Operation. (5) Close access panel 321CC. Refer to Chapter 6, Access Plates and Panel Identification - Description and Operation. (6) Close the aft baggage compartment door.

6. Landing Light Assembly Removal/Installation A. Remove the Landing Light Assembly (Refer to Figure 202). (1) Open the aft baggage compartment door. (2) Open access panel 321CC to get access to the aft circuit breaker panel, installed in the aft power J-Box. Refer to Chapter 6, Access Plates and Panels Identification - Description and Operation. (3) Disengage the LH LANDING/RECOGNITION LIGHT or the RH LANDING/RECOGNITION LIGHT circuit breaker installed on the aft circuit breaker panel. Refer to Chapter 24, DC Load Distribution - Description and Operation. (4) Remove the screws that attach the landing light assembly (FL003 left, FR003 right) to the forward fairing.

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Landing Light Installation Figure 202 (Sheet 1)

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Landing Light Installation Figure 202 (Sheet 2)

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WARNING: Make sure the landing lights have had time to cool before they are removed. The lights operate at very high temperatures and can cause severe burns.

(5) On Airplanes -0180 and On and Airplanes -0001 thru -0179 incorporating SB525B-33-01 do the steps that follow: (a) Disconnect the electrical wires from the lamp. (b) Disconnect the bonding jumper from the landing light assembly. (6) On Airplanes -0001 thru -0179 not incorporating SB525B-33-01 do the steps that follow: (a) Disconnect the electrical wires from the lamp. (b) Disconnect the lanyard from the landing light assembly. (7) Remove the landing light assembly from the airplane. B. Install the Landing Light Assembly (Refer to Figure 202). (1) On Airplanes -0180 and On and Airplanes -0001 thru -0179 incorporating SB525B-33-01 do the steps that follow: (a) Connect the bonding jumper from the landing light assembly. (b) Connect the electrical wires to the lamp. (2) On Airplanes -0001 thru -0179 not incorporating SB525B-33-01 do the steps that follow: (a) Connect the lanyard from the fuselage. (b) Connect the electrical wires from the lamp. (3) Use the screws to attach the landing light assembly (FL003 left, FR003 right) to the forward fairing. (4) Engage the LH LANDING/RECOGNITION LIGHT or the RH LANDING/RECOGNITION LIGHT circuit breaker installed on the aft circuit breaker panel. Refer to Chapter 24, DC Load Distribution - Description and Operation. (5) Close access panel 321CC. Refer to Chapter 6, Access Plates and Panels Identification - Description and Operation. (6) Close the aft baggage compartment door.

7. Landing Light Assembly Lamp Removal/Installation A. Remove the Landing Light Assembly Lamp (Refer to Figure 202). (1) Remove the landing light assembly (FL003 left, FR003 right) from the forward fairing. Refer to Landing Light Assembly Removal/Installation. (2) Disconnect the safety lanyard from the retainer clamp. (3) Loosen the screw on the retainer clamp to remove the lamp and the cuff. B. Install the Landing Light Assembly Lamp (Refer to Figure 202). (1) Clean the cuff and apply a thin layer of DC4 High Temperature Silicone Compound to the inside of the cuff. Refer to the Citation Standard Practices Manual, Chapter 20, Fuel, Weather, Pressure, and High-Temperature Sealing - Maintenance Practices. (2) Install the landing light lamp and the cuff in the retainer clamp. (3) Tighten the screw on the retainer clamp. (4) Attach the safety lanyard to the retainer clamp. (5) Install the landing light assembly (FL003 left, FR003 right) on the airplane. Refer to Landing Light Assembly Removal/Installation.

8. Landing Light Power Control Assembly and Components Removal/Installation (Airplanes -0001 thru -0262 and Airplanes -0264 thru -0293)

NOTE: The removal and installation procedures for the left and right landing light power control assembly and components are typical. A. Remove Landing Light Power Control Assembly. Refer to Figure 202. (1) Open the aft baggage compartment door. (2) Open access panel 321CC to get access to the aft circuit breaker panel installed in the aft power J-Box. Refer to Chapter 6, Access Plates and Panels Identification - Description and Operation.

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(3) Disengage the LH LANDING/RECOGNITION LIGHT or RH LANDING/RECOGNITION LIGHT circuit breaker on the aft circuit breaker panel. Refer to Chapter 24, DC Electrical Load Distribution - Description and Operation. (4) Remove panel 192A. (5) Identify and tag the wiring connected to the relay and to the resistor. (6) Disconnect the wiring connected to the relay and to the resistor. (7) For Airplanes -0109 thru -0262 and Airplanes -0264 thru -0293 and Airplanes -0001 thru -0108, Incorporating Service Bulletin SB525B-33-03, remove the three screws that attach the mounting plate to the fairing frame. (8) For Airplanes -0001 thru -0108 not incorporating SB525B-33-03, remove the four screws that attach the landing light power control assembly mounting plate to the fairing frame. (9) Remove the landing light power control assembly from the airplane. B. Install Landing Light Power Control Assembly. Refer to Figure 202. (1) Put the landing light power control assembly in the correct position. (2) For Airplanes -0109 thru -0262 and Airplanes -0264 thru -0293 and Airplanes -0001 thru -0108, Incorporating Service Bulletin SB525B-33-03, install the three screws that attach the mounting plate to the fairing frame. (3) For Airplanes -0001 thru -0108 not incorporating SB525B-33-03, install the four screws that attach the landing light power control assembly mounting plate to the fairing frame. (4) Connect the wiring to the relay and to the resistor. (5) Do a test of the Landing and Recognition Lights. Refer to Exterior Lighting - Adjustment/Test. (6) Install panel 192A. C. Remove Landing Light Power Controller Assembly Resistor. Refer to Figure 202. (1) Open the aft baggage compartment door. (2) Open access panel 321CC to get access to the aft circuit breaker panel installed in the aft power J-Box. Refer to Chapter 6, Access Plates and Panels Identification - Description and Operation. (3) Disengage the LH LANDING/RECOGNITION LIGHT or RH LANDING/RECOGNITION LIGHT circuit breaker on the aft circuit breaker panel. Refer to Chapter 24, DC Electrical Load Distribution - Description and Operation. (4) Remove panel 192A. (5) Identify and tag the wiring connected to the resistor. (6) Disconnect the wiring connected to the resistor. (7) Remove the nut, washer and bolt that attaches the resistor to the landing light power controller assembly mount. (8) Remove the resistor from the airplane. D. Install Landing Light Power Controller Assembly Resistor. Refer to Figure 202. (1) Put the resistor in the correct position on the landing light power controller assembly mount. (2) Install the bolt, washer and nut to attach the resistor to the landing light power controller assembly mount. (3) Connect the wiring to the resistor. (4) Do a test of the Landing and Recognition Lights. Refer to Exterior Lighting - Adjustment/Test. (5) Install panel 192A. E. Remove Landing Light Power Controller Assembly Relay. Refer to Figure 202. (1) Open the aft baggage compartment door. (2) Open access panel 321CC to get access to the aft circuit breaker panel installed in the aft power J-Box. Refer to Chapter 6, Access Plates and Panels Identification - Description and Operation. (3) Disengage the LH LANDING/RECOGNITION LIGHT or RH LANDING/RECOGNITION LIGHT circuit breaker on the aft circuit breaker panel. Refer to Chapter 24, DC Electrical Load Distribution - Description and Operation. (4) Remove panel 192A. (5) Identify and tag the wiring connected to the relay. (6) Disconnect the wiring connected to the relay. (7) Remove the two screws that attaches the relay to the landing light power controller assembly mount. (8) Remove the relay from the airplane.

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F. Install Landing Light Power Controller Assembly Relay. Refer to Figure 202. (1) Put the relay in the correct position on the landing light power controller assembly mount. (2) Install the two screws to attach the relay to the landing light power Controller assembly mount. (3) Connect the wiring to the relay. (4) Do a test of the Landing and Recognition Lights. Refer to Exterior Lighting - Adjustment/Test. (5) Install panel 192A.

9. Beacon Light Removal/Installation A. Remove the Beacon Light (Refer to Figure 203). (1) Open the aft baggage compartment door. (2) Open access panel 321CC to get access to the aft circuit breaker panel, installed in the aft power J-Box. Refer to Chapter 6, Access Plates and Panels Identification - Description and Operation. (3) Disengage the GND REC BEACON on the aft circuit breaker panel. (4) Loosen the screw on the clamp that attaches the lens to the flasher assembly (FV002). (5) Remove the lens from the flasher assembly. (6) Push down on the lamp and turn it counterclockwise to remove it from the flasher assembly. (7) Remove the screws that attach the flasher assembly to the airplane. (8) Disconnect the electrical wires from the flasher assembly at the splices (AV001, AV002). (9) Remove the flasher assembly from the airplane. B. Install the Beacon Light (Refer to Figure 203). (1) Connect the electrical wires to the flasher assembly (FV002) at the splices (AV001, AV002). (2) Put the flasher assembly in position on the airplane. (3) Use the screws to attach the flasher assembly to the airplane. (4) Push down on the lamp and turn it clockwise to install it in the flasher assembly. (5) Put the lens in position on the flasher assembly. (6) Install the clamp and tighten the screw to assemble the lens and flasher assembly. (7) Engage the GND REC BEACON on the aft circuit breaker panel. (8) Close access panel 321CC. Refer to Chapter 6, Access Plates and Panels Identification - Description and Operation. (9) Close the aft baggage compartment door.

10. Navigation Tail Light Assembly Removal/Installation A. Remove Navigation Tail Light Assembly (FV001) (Refer to Figure 204). (1) Disengage the NAVIGATION LIGHTS circuit breaker. Refer to Chapter 24, DC Electrical Load Distribution - Description and Operation. (2) Open the aft baggage compartment door. (3) Open access panel 321CC to get access to the aft circuit breaker panel, installed in the aft power junction box (J-Box). Refer to Chapter 6, Access Plates and Panels Identification - Description and Operation. (4) Disengage the NAVIGATION LIGHTS circuit breaker on the aft circuit breaker panel. (5) Remove the screws and O-rings that attach the lens retainer, lens, gasket and navigation tail light assembly (FV001) to the bullet fairing. (6) Remove the lens retainer, lens and gasket from the navigation tail light assembly. (7) Remove the lamp from the navigation tail light assembly by pushing in and turning counterclockwise. (8) Disconnect the electrical wires from the navigation tail light assembly by removing screws. (9) Remove the navigation tail light assembly from the airplane. B. Install Navigation Tail Light Assembly (Refer to Figure 204). (1) Connect electrical wires to the navigation tail light assembly (FV001) using screws. (2) Install the lamp in navigation tail light assembly by pushing in and turning clockwise. (3) Position the navigation tail light assembly in its correct position in the bullet fairing. (4) Place the gasket and lens on the lamp holder and install lens retainer. (5) Attach the lens retainer with the screws and O-rings. (6) Engage the NAVIGATION LIGHTS circuit breaker. Refer to Chapter 24, DC Electrical Load Distribution - Description and Operation.

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Beacon Light Installation Figure 203 (Sheet 1)

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Navigation Tail Light Installation Figure 204 (Sheet 1)

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(7) Close access panel 321CC. Refer to Chapter 6, Access Plates and Panels Identification - Description and Operation. (8) Close the aft baggage compartment door.

11. Wing Inspection Light Removal/Installation A. Remove the Wing Inspection Light Assembly (Refer to Figure 205).

NOTE: The removal procedures do not include removal of the light housing.

NOTE: On Airplanes -0213 and On, it is possible an optional right wing inspection light is installed. The removal and/or installation for the two lights are typical.

(1) Open the aft baggage compartment door. (2) Open access panel 321CC to get access to the aft circuit breaker panel, installed in the aft power J-Box. Refer to Chapter 6, Access Plates and Panels Identification - Description and Operation. (3) Disengage the WING INSPECTION LIGHT circuit breaker on the aft circuit breaker panel. Refer to Chapter 24, DC Electrical Load Distribution - Description and Operation. (4) Remove the screws that attach the lens and retainer assembly to the housing. (5) Remove the nut to disconnect the lanyard from the lens and retainer assembly. (6) Push in on the lamp and turn it counterclockwise to remove lamp it from the lamp holder assembly (FC002). (7) Loosen the nuts to remove the lamp holder assembly from the housing. (8) Disconnect the electrical wires at the splice (AC020) and the ground point. (9) Remove the lamp holder assembly from the airplane. B. Install the Wing Inspection Light (Refer to Figure 205). (1) Connect the electrical wires to the lamp holder assembly (FC002) at the splice (AC020) and the ground point. (2) Use the nuts to install the lamp holder assembly to the housing. (3) Push in on the lamp and turn clockwise to install it in the lamp holder assembly. (4) Use the nut to attach the lanyard to the lens and retainer assembly. (5) Use the screws to attach the lens and retainer assembly to the housing. (a) Make sure the lens and retainer assembly drain hole is at the bottom of the assembly. (6) Engage the WING INSPECTION LIGHT circuit breaker on the aft circuit breaker panel. (7) Make sure that the wing inspection light is adjusted correctly. Refer to Exterior Lighting, Adjustment/Test. (8) Close access panel 321CC. Refer to Chapter 6, Access Plates and Panel Identification - Description and Operation. (9) Close the aft baggage compartment door. (10) Close access panel 321CC. Refer to Chapter 6, Access Plates and Panel Identification - Description and Operation. (11) Close the aft baggage compartment door.

12. Optional Pulse Light Controller Removal/Installation A. Remove the Optional Pulse Light Controller (Refer to Figure 206).

NOTE: The pulse light controller is under the aft baggage compartment floor at FS 432.00 and WL 106.94.

(1) Disengage the PULSE circuit breaker on the left circuit breaker panel. (2) Remove the screws that attach the pulse light controller to the brackets. (3) Disconnect the electrical connectors (PT061 and PT062) from the pulse light controller. (4) Remove the pulse light controller from the airplane. B. Install the Pulse Light Controller (Refer to Figure 206). (1) Connect the electrical connectors (PT061 and PT062) to the pulse light controller (UT031). (2) Put the pulse light controller in position between the brackets at FS 432.00 and WL 106.94. (3) Use the screws to attach the pulse light controller to the brackets.

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Wing Inspection Light Installation Figure 205 (Sheet 1)

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Pulse Light Controller Installation Figure 206 (Sheet 1)

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(4) Install access panel 321DB. Refer to Chapter 6, Access Plates and Panels Identification - Description and Operation. (5) Close the aft baggage compartment door. (6) Engage the PULSE circuit breaker on the left circuit breaker panel.

13. Optional Tail Floodlight Removal/Installation

NOTE: The optional tail floodlights are installed below the left and right horizontal stabilizers. A TAIL FLOOD switch, (SI109) is installed on the left instrument panel to control the two lights.

NOTE: The removal and installation procedures for the left and right tail floodlights are typical. A. Remove the Optional Tail Floodlight (Refer to Figure 207). (1) Open the aft baggage compartment door. (2) Open access panel 321CC to get access to the aft circuit breaker panel installed in the aft power J-Box. Refer to Chapter 6, Access Plates and Panels Identification - Description and Operation. (3) Disengage the TAIL FLOODLIGHTS circuit breaker installed on the aft circuit breaker panel. Refer to Chapter 24, DC Load Distribution - Description and Operation. (4) Remove the screws that attach the tail floodlight assembly (FT005 left, FT006 right) to the horizontal stabilizer. (5) Disconnect the electrical wires at the splices (AT089 and AT090 left, AT097 and AT098 right). (6) Remove the screw that connects the lanyard to the rib in the horizontal stabilizer. (7) Remove the tail floodlight assembly from the airplane. B. Install the Optional Tail Floodlight (Refer to Figure 207). (1) Hold the tail floodlight assembly (FT005 left, FT006 right) in position near the opening in the horizontal stabilizer. (2) Use the screw to connect the lanyard to the rib in the horizontal stabilizer. (3) Connect the electrical wires at the splices (AT089 and AT090 left, AT097 and AT098 right). (4) Put the tail floodlight assembly in position on the horizontal stabilizer. (5) Install the screws that attach the tail floodlight assembly to the horizontal stabilizer. (6) Engage the TAIL FLOODLIGHTS circuit breaker installed on the aft circuit breaker panel. Refer to Chapter 24, DC Load Distribution - Description and Operation. (7) Close access panel 321CC. Refer to Chapter 6, Access Plates and Panel Identification - Description and Operation. (8) Close the aft baggage compartment door.

14. Optional Tail Floodlight Lamp Removal/Installation

NOTE: Each tail floodlight assembly contains two DA27 lamps. The removal and installation procedures for any of the lamps in the assembly are typical. A. Remove the Optional Tail Floodlight Lamp (Refer to Figure 207). (1) Remove the tail floodlight assembly from the airplane. Refer to Optional Tail Floodlight Removal/ Installation. (2) Push in on the lamp and turn it counterclockwise. (3) Remove the lamp from the tail floodlight assembly. B. Install the Optional Tail Floodlight Lamp (Refer to Figure 207). (1) Put the lamp in position in the tail floodlight assembly. (2) Push in on the lamp and turn it clockwise to install it in the tail floodlight assembly. (3) Install the tail floodlight assembly on the airplane. Refer to Optional Tail Floodlight Removal/ Installation.

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Optional Tail Floodlight Installation Figure 207 (Sheet 1)

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EXTERIOR LED LIGHTING - TROUBLESHOOTING

1. General A. This section gives troubleshooting procedures for the Exterior LED Lighting System.

2. Tools and Equipment A. For tools and equipment, refer to Lighting - General.

3. Troubleshooting A. It is necessary to understand the system before troubleshooting the Exterior LED Lighting system. Become familiar with the system components, assemblies, and mechanical functions before you do any of the troubleshooting procedures. B. Wingtip Anti-Collision Light Fails to Operate.(Airplanes -0001 thru -0293 Incorporating SB525B-33-07) (1) Make sure that the ANTI COLL circuit breaker (HZ054) on the aft circuit breaker panel is engaged.

NOTE: Once a discrepancy has been found and repaired, it is not necessary to do the remainder of the procedure.

(2) Make sure that the ANTI COLL switch (SI056) is in the ON position. (3) If Anti-Collision Light(s) still fail to operate, do the following: (a) If both the left and right Anti-Collision lights fail to operate, check for proper ground at the ANTI COLL switch (SI056). If found, repair open ground as necessary then do the Anti- Collision Lights Functional Test, Refer to Chapter 33, Exterior Lighting - Adjustment/Test 1 Check for proper power (28VDC) on the ANTI COLL switch (SI056). If found, repair open circuit as necessary then do the Anti-Collision Lights Functional Test, Refer to Chapter 33, Exterior Lighting - Adjustment/Test. (b) If both the left and right Anti-Collision Lights fail to operate, check the ANTI COLL circuit breaker (HZ054) for correct operation. Repair/replace bad circuit breaker as necessary, then do the Anti-Collision Lights Functional Test, Refer to Chapter 33, Exterior Lighting - Adjustment/Test. (c) Check for proper ground on Pin D, JL053/PL054 (Left Wing) and JR053/PR054 (Right Wing). If found, repair open ground as necessary then do the Anti-Collision Lights Functional Test, Refer to Chapter 33, Exterior Lighting - Adjustment/Test. (d) Check for proper power (28VDC) on Pin B, JL053/PL054 (Left Wing) and JR053/PR054 (Right Wing). If found, repair open circuit as necessary then do the Anti-Collision Lights Functional Test, Refer to Chapter 33, Exterior Lighting - Adjustment/Test. (e) If the Anti Collision Light has good power and ground, replace the light assembly. Refer to Chapter 33, Exterior LED Lighting - Maintenance Practices.

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EXTERIOR LED LIGHTING - MAINTENANCE PRACTICES Airplanes -0057, -0263 and -294 and On)

1. General A. This section contains the data that is necessary to complete maintenance procedures on the exterior lights. The exterior lights include the landing/taxi lights, the navigation lights, the anti-collision lights, the ground recognition lights, the left wing inspection light, the optional right inspection light, and the tail flood lights. For a description of each of the lighting systems, refer to Exterior Lighting - Description and Operation.

2. Tools and Equipment A. For a list of tools and equipment refer to Lighting - General.

3. Navigation and Anti-Collision Light Removal/Installation (Airplanes -0001 thru -0058, -0058 thru -0262, and -0264 thru -0293 Incorporating SB525B-33-07)

NOTE: The removal and installation procedure for the left and right navigation lights is typical. A. Remove the Navigation and Anti-Collision Light Assembly (Refer to Figure 201). (1) Open the aft baggage compartment door. (2) Open access panel 321CC to get access to the aft circuit breaker panel installed in the aft power J-Box. Refer to Chapter 6, Access Plates and Panels Identification - Description and Operation. (3) Disengage the ANTI-COLLISION LIGHT and NAV LIGHTS circuit breakers on the aft circuit breaker panel. Refer to Chapter 24, DC Electrical Load Distribution - Description and Operation. (4) Remove the screws from the light (FL005 left, FR005 right). (5) Pull the light away from the wing tip to get access to the electrical connector (PL054 left, PR054 right). (6) Disconnect the electrical connector. (7) Remove the light assembly from the airplane. B. Install the Navigation and Anti-Collision Light Assembly (Refer to Figure 201). (1) Put the light in position at the wing tip. (2) Connect the electrical connector. (3) Install the screws. (4) Engage the ANTI-COLLISION LIGHT and NAV LIGHTS circuit breaker on the aft circuit breaker panel. Refer to Chapter 24, DC Electrical Load Distribution - Description and Operation. (5) Close access panel 321CC. Refer to Chapter 6, Access Plates and Panels Identification - Description and Operation. (6) Close the aft baggage compartment door. (7) Do the Navigation and Anti-Collision Lights Functional Test. Refer to Exterior Lighting - Adjustment/Test.

4. Navigation and Anti-Collision Light Removal/Installation (Airplanes -0263 and -0294 thru -0450)

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Navigation and Anti-Collision Light Installation Figure 201 (Sheet 1)

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B. Install the Navigation and Anti-Collision Light Assembly (Refer to Figure 201). (1) Put the light in position at the wing tip. (2) Connect the electrical connector. (3) Install the screws. (4) Engage the ANTI-COLLISION LIGHT and NAV LIGHTS circuit breaker on the aft circuit breaker panel. Refer to Chapter 24, DC Electrical Load Distribution - Description and Operation. (5) Close access panel 321CC. Refer to Chapter 6, Access Plates and Panels Identification - Description and Operation. (6) Close the aft baggage compartment door. (7) Do the Navigation and Anti-Collision Lights Functional Test. Refer to Exterior Lighting - Adjustment/Test.

5. Navigation and Anti-Collision Light Removal/Installation (Airplanes -0057 and -0451 and On)

NOTE: The removal and installation procedure for the left and right navigation lights is typical. A. Remove the Navigation and Anti-Collision Light Assembly (Refer to Figure 201). (1) Open the aft baggage compartment door. (2) Open access panel 321CC to get access to the aft circuit breaker panel installed in the aft power J-Box. Refer to Chapter 6, Access Plates and Panels Identification - Description and Operation. (3) Disengage the ANTI-COLLISION LIGHT and NAV LIGHTS circuit breakers on the aft circuit breaker panel. Refer to Chapter 24, DC Electrical Load Distribution - Description and Operation. (4) Remove the screws from the light (FL001 left, FR001 right) (5) Pull the light away from the wing tip to get access to the electrical connector (PL051 left, PR051 right). (6) Disconnect the electrical connector. (7) Remove the light from the airplane. B. Install the Navigation and Anti-Collision Light Assembly (Refer to Figure 201). (1) If necessary, put the spacer in its position on the wing tip with the thick side up. (2) Use Type I, Class B sealant and apply a fillet seal fully around the base of the spacer where it installs on the wing tip. Refer to the Citation Standard Practices Manual, Chapter 20, Fuel, Weather, Pressure, and High-Temperature Sealing - Maintenance Practices. (3) Make sure that the fillet seal fills the gap between the spacer and the wing tip. (4) Put the light in position at the wing tip. (5) Connect the electrical connector. (6) Install the screws. (7) Do an electrical bond check (Type 1) from the screws to the structure. Refer to the Citation Standard Practices Manual, Chapter 20, Electrical Bonding and Grounding - Maintenance Practices. (8) Engage the ANTI-COLLISION LIGHT and NAV LIGHTS circuit breaker on the aft circuit breaker panel. Refer to Chapter 24, DC Electrical Load Distribution - Description and Operation. (9) Close access panel 321CC. Refer to Chapter 6, Access Plates and Panels Identification - Description and Operation. (10) Close the aft baggage compartment door. (11) Do the Navigation and Anti-Collision Lights Functional Test. Refer to Exterior Lighting - Adjustment/Test.

6. Landing Light Assembly Removal/Installation A. Remove the Landing Light Assembly (Refer to Figure 202). (1) Open the aft baggage compartment door. (2) Open access panel 321CC to get access to the aft circuit breaker panel installed in the aft power J-Box. Refer to Chapter 6, Access Plates and Panels Identification - Description and Operation. (3) Disengage the LH LANDING/RECOGNITION LIGHT or RH LANDING/RECOGNITION LIGHT circuit breaker on the aft circuit breaker panel. Refer to Chapter 24, DC Electrical Load Distribution - Description and Operation. (4) Remove the screws that attach the landing light assembly (FL003 left, FR003 right) to the forward fairing.

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Landing Light Installation Figure 202 (Sheet 1)

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WARNING: Make sure that the landing lights are cool before you remove them. The lights operate at very high temperatures and can cause bad burns.

(5) Pull the light away from the forward fairing to get access to the electrical connector (PL027 left, PR027 right). (6) Disconnect the ground straps (GR006 and GL005). (7) Remove the landing light assembly from the airplane. B. Install the Landing Light Assembly (Refer to Figure 202). (1) Put the light in position at the forward fairing. (2) Connect the electrical connector (PL050 left, PR050 right). (3) Connect the ground straps (GR006 and GL005). (4) Use the screws to attach the landing light assembly (FL003 left, FR003 right) to the forward fairing. (5) Engage the LH LANDING/RECOGNITION LIGHT or RH LANDING/RECOGNITION LIGHT circuit breaker on the aft circuit breaker panel. Refer to Chapter 24, DC Electrical Load Distribution - Description and Operation. (6) Do a test of the Landing and Recognition Lights. Refer to Exterior Lighting - Adjustment/Test. (7) Close access panel 321CC. Refer to Chapter 6, Access Plates and Panels Identification - Description and Operation. (8) Close the aft baggage compartment door.

7. Beacon Light Removal/Installation A. Remove the Beacon Light (Refer to Figure 203). (1) Open the aft baggage compartment door. (2) Open access panel 321CC to get access to the aft circuit breaker panel installed in the aft power J-Box. Refer to Chapter 6, Access Plates and Panels Identification - Description and Operation. (3) Disengage the GND REC BEACON circuit breaker on the aft circuit breaker panel. Refer to Chapter 24, DC Electrical Load Distribution - Description and Operation. (4) Remove the screws from the light (FV002). (5) Pull the light away from the fairing on the vertical stabilizer to get access to the electrical connector (PV007). (6) Disconnect the electrical connector. (7) Remove the light from the airplane. B. Install the Beacon Light (Refer to Figure 203). (1) Put the light in position at the fairing. (2) Connect the electrical connector (PV007). (3) Install the screws. (4) Do a test of the Ground Recognition Beacon. Refer to Exterior Lighting - Adjustment/Test. (5) Engage the GND REC BEACON circuit breaker on the aft circuit breaker panel. Refer to Chapter 24, DC Electrical Load Distribution - Description and Operation. (6) Close access panel 321CC. Refer to Chapter 6, Access Plates and Panels Identification - Description and Operation. (7) Close the aft baggage compartment door.

8. Wing Inspection Light Removal/Installation A. Remove the Wing Inspection Light Assembly (Refer to Figure 204).

NOTE: On Airplanes -0213 and On, it is possible an optional right wing inspection light is installed. The removal/installation for the two lights are typical.

(1) Disengage the WING INSPECTION LIGHT circuit breaker on the aft circuit breaker panel installed in the aft power J-Box. Refer to Chapter 24, DC Electrical Load Distribution - Description and Operation. (2) Remove the screws from the light (FC002)

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Beacon Light Installation Figure 203 (Sheet 1)

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Wing Inspection Light Installation Figure 204 (Sheet 1)

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(3) Pull the light away from the airplane to get access to the electrical connectors (PC079 and JC080). (4) Disconnect the electrical connectors. (5) Remove the light from the airplane. B. Install the Wing Inspection Light (Refer to Figure 204). (1) Put the light in position at the airplane. (2) Connect the electrical connectors (PC079 and JC080). (3) Install the screws. (4) Engage the WING INSPECTION LIGHT circuit breaker on the aft circuit breaker panel. Refer to Chapter 24, DC Electrical Load Distribution - Description and Operation. (5) Do a test of the Wing Inspection Light. Refer to Exterior Lighting - Adjustment/Test.

9. Tail Flood Light Removal/Installation

NOTE: The tail flood lights are installed below the left and right horizontal stabilizers. A TAIL FLOOD switch, (SI109) is installed on the left instrument panel to control the two lights. On Airplanes -0312 and On the tail flood light assemblies that are installed have an aluminum body and acrylic lens. On Airplane -0263 and Airplanes -0294 thru -0311 the tail flood light assemblies that are installed have a polycarbonate body and a clear polycarbonate lens.

NOTE: The removal/installation procedures for the left and right tail flood lights are typical. A. Remove the Tail Flood Light (Refer to Figure 205). (1) Open the aft baggage compartment door. (2) Open the access panel 321CC to get access to the aft circuit breaker panel installed in the aft power J-Box. Refer to Chapter 6, Access Plates and Panels Identification - Description and Operation. (3) Disengage the TAIL FLOOD LIGHTS circuit breaker on the aft-power J-Box circuit-breaker panel. Refer to Chapter 24, DC Electrical Load Distribution - Description and Operation. (4) Remove the screws that attach the tail flood light assembly (FT005 left, FT006 right) to the horizontal stabilizer. (5) Disconnect the electrical connectors (JT904 and PT903 left, JT905 and PT906 right). (6) Remove the tail flood light assembly from the horizontal stabilizer. (7) Remove the screws that connect the light to the adapter plate. B. Install the Tail Flood Light (Refer to Figure 205). (1) Put the light on the lens and align the screw holes. (2) Install the screws that connect the light to the adapter plate. (3) Put the tail flood light assembly (FT005 left, FT006 right) in position at the horizontal stabilizer. (4) Connect the electrical connectors (JT904 and PT903 left, JT905 and PT906 right). (5) Install the screws that attach the tail flood light assembly to the horizontal stabilizer. (6) Engage the TAIL FLOOD LIGHTS circuit breaker on the aft circuit breaker panel. Refer to Chapter 24, DC Electrical Load Distribution - Description and Operation. (7) Do a test of the Tail Flood Light. Refer to Exterior Lighting - Adjustment/Test. (8) Close the access panel 321CC. Refer to Chapter 6, Access Plates and Panel Identification - Description and Operation. (9) Close the aft baggage compartment door.

10. LED Tail Light Assembly Removal/Installation A. Remove the LED Tail Light Assembly (Refer to Figure 206). (1) Open the aft baggage compartment door. (2) Open access panel 321CC to get access to the aft circuit breaker panel, installed in the aft power J-Box. Refer to Chapter 6, Access Plates and Panels Identification - Description and Operation. (3) Disengage the NAV LIGHTS circuit breaker on the aft circuit breaker panel. Refer to Chapter 24, DC Electrical Load Distribution - Description and Operation. (4) Remove the screws that attach the lens and LED tail light assembly (FV001) to the bullet assembly. (5) Remove lens from the LED tail light assembly.

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Tail Flood Light Installation Figure 205 (Sheet 1)

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Navigation Tail Light Installation Figure 206 (Sheet 1)

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(6) Disconnect the electrical wires from the LED tail light assembly at the splices (AV003, AV004). (7) Remove the LED tail light assembly from the airplane. B. Install the LED Tail Light Assembly (Refer to Figure 206). (1) Connect the electrical wires to the LED tail light assembly (FV001) at the splices (AV003, AV004). (2) Put the LED tail light assembly in position on the bullet fairing. (3) Use the screws to attach the lens and LED tail light assembly to the bullet fairing. (4) Engage the NAV LIGHTS circuit breaker on the aft circuit breaker panel. Refer to Chapter 24, DC Electrical Load Distribution - Description and Operation. (5) Close access panel 321CC. Refer to Chapter 6, Access Plates and Panel Identification - Description and Operation. (6) Close the aft baggage compartment door.

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SUPPLEMENT NO: ICA-525B-33-00002 APPENDIX A: ILLUSTRATED PARTS CATALOG

NOT APPLICABLE

SUPPLEMENT NO: ICA-525B-33-00002 APPENDIX B: WIRING DIAGRAM MANUAL

NAVIGATION AND ANTI COLLISION LIGHT MOD Figure 02 (Sheet 1)

Figure 02 Page 0 © TEXTRON AVIATION INC. 33-40-01 Sep 14/2018 CESSNA® MODEL 525B (SERIALS -0001 THRU -0056 AND -0058 THRU -0134) WIRING DIAGRAM MANUAL

FIG UNITS REF PART NUMBER NOMENCLATURE EFFECTIVITY PER DES 1 2 3 4 5 6 7 FROM TO ASSY

02 NAVIGATION AND ANTI COLLISION LIGHT MOD JL053 M39029/57-358 . CONTACT SOCKET ...... V81349 01 R - SJS840410 . . PLUG 4-PIN V58982 01 R JR053 M39029/57-358 . CONTACT SOCKET ...... V81349 01 R - SJS840410 . . PLUG 4-PIN V58982 01 R PL054 M39029/57-357 . CONTACT SOCKET ...... V81349 01 R - MS27484E10F5S . . CONNECTOR V96906 01 R - S3627-10 . . BACKSHELL V71379 01 R PR054 M39029/57-357 . CONTACT SOCKET ...... V81349 01 R - MS27484E10F5S . . CONNECTOR V96906 01 R - S3627-10 . . BACKSHELL V71379 01 R

- ITEM NOT ILLUSTRATED Figure 02 Page 1 © TEXTRON AVIATION INC. 33-40-01 Sep 14/2018 CESSNA® MODEL 525B (SERIALS -0001 THRU -0056 AND -0058 THRU -0134) WIRING DIAGRAM MANUAL

NAVIGATION AND ANTI COLLISION LIGHT MOD Figure 02 (Sheet 2)

Figure 02 Page 2 © TEXTRON AVIATION INC. 33-40-01 Sep 14/2018 CESSNA® MODEL 525B (SERIALS -0001 THRU -0056 AND -0058 THRU -0134) WIRING DIAGRAM MANUAL

FIG UNITS REF PART NUMBER NOMENCLATURE EFFECTIVITY PER DES 1 2 3 4 5 6 7 FROM TO ASSY

02 NAVIGATION AND ANTI COLLISION LIGHT MOD AL028 M81714/65-16-1 . SPLICE LEFT WING NAVIGATION (ZONE 541)...... 01 R AL029 M81714/65-16-1 . SPLICE LEFT WING NAVIGATION (ZONE 541)...... 01 R AR023 M81714/65-16-1 . SPLICE ...... 01 R AR024 M81714/65-16-1 . SPLICE ...... 01 R FL001 03-1302-1003 . LIGHT ASSEMBLY ...... VS5289 RF- R 01 FR001 03-1302-1004 . LIGHT ASSEMBLY ...... VS5289 01 R GR002 6328006-2 . GROUND STUD (ZONE 612) ...... 01 R GR004 6328006-2 . GROUND STUD (ZONE 642) ...... 01 R JL053 M39029/57-358 . CONTACT SOCKET ...... V81349 01 R - SJS840410 . . PLUG 4-PIN V58982 01 R JM003 MS3474L22-41S . CONNECTOR LEFT WING FEEDTHRU (ZONE 311) ...... 01 R - M85049/51-1-22N . . BACKSHELL 01 R JR053 M39029/57-358 . CONTACT SOCKET ...... V81349 01 R - SJS840410 . . PLUG 4-PIN V58982 01 R JS003 MS3474L22-41S . CONNECTOR RIGHT WING FEEDTHRU (ZONE 312) ...... 01 R - M85049/51-1-22N . . BACKSHELL 01 R PL006 MS3459L10SL3P . CONNECTOR LEFT WING STROBE LIGHT POWER SUPPLY 01 R (ZONE 541) ...... - S3744-10-90 . . BACKSHELL 01 R PL007 MS3456L10SL3S . CONNECTOR LEFT WING STROBE LIGHT POWER SUPPLY 01 R (ZONE 541) ...... - M85049/55-10A . . BACKSHELL 01 R PL021 MS3459L10SL3S . CONNECTOR LEFT WING LIGHT (ZONE 541) ...... 01 R - S3744-10 . . BACKSHELL 01 R PL053 M39029/58-364 . PIN ...... V81349 01 R - SJS840400 . . RECEPTACLE 4-PIN V58982 01 R PL054 M39029/57-357 . CONTACT SOCKET ...... V81349 01 R - MS27484E10F5S . . CONNECTOR V96906 01 R - S3627-10 . . BACKSHELL V71379 01 R PM003 MS3475L22-41P . CONNECTOR LEFT TAIL/WING DISCONNECT (ZONE 512) . . . . . 01 R - M85049/51-1-22N . . BACKSHELL 01 R PR006 MS3459L10SL3P . CONNECTOR (ZONE 641/642)...... 01 R - S3744-10-90 . . BACKSHELL 01 R PR007 MS3456L10SL3S . CONNECTOR (ZONE 641/642)...... 01 R - M85049/55-10A . . BACKSHELL 01 R PR035 MS3459L10SL3S . CONNECTOR (ZONE 641/642)...... 01 R - S3744-10 . . BACKSHELL 01 R PR053 M39029/58-364 . PIN ...... V81349 01 R - SJS840400 . . RECEPTACLE 4-PIN V58982 01 R PR054 M39029/57-357 . CONTACT SOCKET ...... V81349 01 R - MS27484E10F5S . . CONNECTOR V96906 01 R - S3627-10 . . BACKSHELL V71379 01 R PS003 MS3475L22-41P . CONNECTOR RIGHT WING/TAIL DISCONNECT (ZONE 612). . . . 01 R - M85049/51-1-22N . . BACKSHELL 01 R UL020 . POWER SUPPLY LEFT WING ...... RF R UR020 . POWER SUPPLY RIGHT WING ...... RF R

- ITEM NOT ILLUSTRATED Figure 02 Page 3 © TEXTRON AVIATION INC. 33-40-01 Sep 14/2018 CESSNA® MODEL 525B (SERIALS -0057 AND -0135 AND ON) WIRING DIAGRAM MANUAL

NAVIGATION AND ANTI COLLISION LIGHT MOD Figure 03 (Sheet 1)

Figure 03 Page 0 © TEXTRON AVIATION INC. 33-40-02 Sep 14/2018 CESSNA® MODEL 525B (SERIALS -0057 AND -0135 AND ON) WIRING DIAGRAM MANUAL

FIG UNITS REF PART NUMBER NOMENCLATURE EFFECTIVITY PER DES 1 2 3 4 5 6 7 FROM TO ASSY

03 NAVIGATION AND ANTI COLLISION LIGHT MOD JL053 M39029/57-358 . CONTACT SOCKET ...... V81349 01 R - SJS840410 . . PLUG 4-PIN V 58982 01 R JR053 M39029/57-358 . CONTACT SOCKET ...... V81349 01 R - SJS840410 . . PLUG 4-PIN V58982 01 R PL054 M39029/57-357 . CONTACT SOCKET ...... V81349 01 R - MS27484E10F5S . . CONNECTOR V96906 01 R - S3627-10 . . BACKSHELL V71379 01 R PR054 M39029/57-357 . CONTACT SOCKET ...... V81349 01 R - MS27484E10F5S . . CONNECTOR V96906 01 R - S3627-10 . . BACKSHELL V71379 01 R

- ITEM NOT ILLUSTRATED Figure 03 Page 1 © TEXTRON AVIATION INC. 33-40-02 Sep 14/2018 CESSNA® MODEL 525B (SERIALS -0057 AND -0135 AND ON) WIRING DIAGRAM MANUAL

NAVIGATION AND ANTI COLLISION LIGHT MOD Figure 03 (Sheet 2)

Figure 03 Page 2 © TEXTRON AVIATION INC. 33-40-02 Sep 14/2018 CESSNA® MODEL 525B (SERIALS -0057 AND -0135 AND ON) WIRING DIAGRAM MANUAL

FIG UNITS REF PART NUMBER NOMENCLATURE EFFECTIVITY PER DES 1 2 3 4 5 6 7 FROM TO ASSY

03 NAVIGATION AND ANTI COLLISION LIGHT MOD AL028 M81714/65-16-1 . SPLICE ...... 01 R AL029 M81714/65-16-1 . SPLICE ...... 01 R AR023 M81714/65-16-1 . SPLICE ...... 01 R AR024 M81714/65-16-1 . SPLICE ...... 01 R FL001 03-1302-1003 . LH NAV LIGHT ...... 01 R FR001 03-1302-1004 . RH NAV LIGHT ...... 01 R GL002 6328006-2 . GROUND STUD ASSEMBLY ...... 01 R - MS35207-266 . . SCREW 01 R - MS35338-157 . . LOCK WASHER 02 R - MS35650-305T . . NUT 02 R - NAS1149D0316H . . WASHER 04 R GR004 6328006-2 . GROUND STUD ASSEMBLY ...... 01 R - MS35338-157 . . LOCK WASHER 02 R - MS35360-305T . . NUT 02 R - MS35650-305T . . SCREW 01 R - NAS1149D0316H . . WASHER 04 R JL053 M39029/57-358 . CONTACT SOCKET ...... V81349 01 R - SJS840410 . . PLUG 4-PIN V 58982 01 R JM003 MS3474L22-41S . CONNECTOR ...... V96906 0057 0057 01 R 0135 & ON - M85049/51-1-22N . . STRAIN RELIEF V81349 01 R JR053 M39029/57-358 . CONTACT SOCKET ...... V81349 01 R - SJS840410 . . PLUG 4-PIN V58982 01 R JS003 MS3474L22-41S . CONNECTOR ...... V96906 0057 0057 01 R 0135 & ON - M85049/51-1-22N . . STRAIN RELIEF V81349 01 R PL006 MS3459L10SL3P . CONNECTOR ...... 01 R - S3744-10-90 . . BACKSHELL 01 R PL007 MS3456L10SL3S . CONNECTOR ...... 01 R - M85049/55-10A . . BACKSHELL 01 R PL021 MS3459L10SL3S . CONNECTOR ...... 01 R - S3744-10 . . BACKSHELL 01 R PL053 M39029/58-364 . PIN ...... V81349 01 R - SJS840400 . . RECEPTACLE 4-PIN V58982 01 R PL054 M39029/57-357 . CONTACT SOCKET ...... V81349 01 R - MS27484E10F5S . . CONNECTOR V96906 01 R - S3627-10 . . BACKSHELL V71379 01 R PM003 MS3475L22-41P . CONNECTOR ...... V96906 0057 0057 01 R 0135 & ON - M85049/51-1-22N . . STRAIN RELIEF V81349 01 R PR006 MS3459L10SL3P . CONNECTOR ...... V96906 01 R - S3744-10-90 . . BACKSHELL V71379 01 R PR007 MS3456L10SL3S . CONNECTOR ...... 01 R - M85049/55-10A . . BACKSHELL 01 R PR035 MS3459L10SL3S . CONNECTOR ...... 01 R - S3744-10 . . BACKSHELL 01 R PR053 M39029/58-364 . PIN ...... V81349 01 R - SJS840400 . . RECEPTACLE, 4-PIN V58982 01 R PR054 M39029/57-357 . CONTACT SOCKET ...... V81349 01 R - MS27484E10F5S . . CONNECTOR V96906 01 R - S3627-10 . . BACKSHELL V71379 01 R PS003 MS3475L22-41P . CONNECTOR ...... V96906 0057 0057 01 R 0135 & ON - M85049/51-1-22N . . STRAIN RELIEF V81349 01 R UL020 . POWER SUPPLY LH ANTI COLLISION LIGHT ...... RF R UR020 . POWER SUPPLY RH ANTI COLLISION LIGHT ...... RF R