Service Bulletin Cab-31-01

Caravan SERVICE BULLETIN CAB-31-01

REVISION TRANSMITTAL

This sheet transmits Revision 1 to CAB-31-01, which: A. Separates the Cockpit Voice and Data Recorder from the CAB-31-01 Kit for HAZMAT handling purposes. NOTE: This revision replaces the original issue of CAB-31-01 in its entirety.

REVISION COMPLIANCE NO EFFECT. Airplanes previously modified by CAB-31-01 are not affected by this revision.

LOG OF REVISIONS Original Issue October 21, 2015 Revision 1 August 14, 2017

Original Issue - October 21, 2015 CAB-31-01 Revision 1 - August 14, 2017 Page 1 of 1

Caravan SERVICE BULLETIN CAB-31-01

TITLE INDICATING/RECORDING SYSTEMS - CVDR INSTALLATION

EFFECTIVITY MODEL SERIAL NUMBERS 208B 5000 and On

NOTE: This service bulletin is not applicable to aircraft that have the Dual GMA1347 Audio Panel Option.

REASON To provide a modification to install the Cockpit Voice and Data Recorder (CVDR) on 208B EX model airplanes not equipped with CVDR from the factory.

DESCRIPTION This service bulletin provides parts and instructions to install CVDR on airplanes not previously equipped with the option from the factory.

COMPLIANCE OPTIONAL. This service bulletin can be accomplished at the discretion of the owner.

APPROVAL Cessna received FAA approval for the technical data in this publication that changes the airplane type design.

CONSUMABLE MATERIAL You may need the consumable materials that follow, or their equivalent, to complete this service bulletin.

NAME NUMBER MANUFACTURER USE Alodine U074093 Textron Aviation To apply to bare metal Textron Aviation Parts and Distribution 5800 East Pawnee, PO Box 1521 Wichita, KS 67218 Clear Polyurethane Commercially Available To apply over the ground stud Paint identifier

WEIGHT AND BALANCE INFORMATION

MODEL Fitted with KHF 1050 (Aft shelf) WEIGHT CHANGE +18.96 pounds RESULTANT MOMENT +6095.68 inch-pounds MOMENT/1000 +6.10 inch-pounds

Original Issue - October 21, 2015 CAB-31-01 Revision 1 - August 14, 2017 Page 1 of 38

Textron Aviation Customer Service, P.O. Box 7706, Wichita, KS 67277, U.S.A. 1-316-517-5800 This document 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 COPYRIGHT © 2015 Caravan SERVICE BULLETIN CAB-31-01

MODEL Not Fitted with KHF 1050 (Aft shelf) WEIGHT CHANGE +22.40 pounds RESULTANT MOMENT +7396.57 inch-pounds MOMENT/1000 +7.40 inch-pounds

REFERENCES Cessna Model 208 Maintenance Manual.

ICA-208-31-00001 - L-3 Communications FA2100 CVDR ICA Supplement.

ACCOMPLISHMENT INSTRUCTIONS 1. Prepare the airplane for maintenance. A. Make sure that the airplane is electrically grounded. B. Retract the flaps. (1) Connect the external power unit to the airplane. (2) Set the external power switch to the BUS position. (3) Set the battery switch to the ON position. (4) Fully retract the flaps. (5) set the battery switch to the OFF position. (6) Set the external power switch to the OFF position. (7) Remove the external electrical power unit from the airplane. C. Make sure that all switches are in the OFF/NORM position. D. Disconnect electrical power from the airplane. (1) Disconnect external electrical power. (2) Disconnect the airplane battery. E. Attach maintenance warning tags to the battery and external power receptacle that have "DO NOT CONNECT ELECTRICAL POWER - MAINTENANCE IN PROGRESS" written on them. 2. (Refer to Figure 8, Detail B.) Install the DCU S1232-502 Circuit Breaker (HI027) in the avionics circuit breaker panel. Fabricate 12-gauge jumper wire long enough to extend to the closest circuit breaker and to the 2-amp circuit breaker noted as "DCU." Use two S1367-3-8 ring terminal for the jumper side. Use one S1367-1-8 ring terminal on the ship side with 2HI027-11PI900 wire. Engage "DCU" circuit breaker. (Refer to the Model 208 Maintenance Manual, Chapter 24, Electrical Distribution System - Maintenance Practices and Model 208 Wiring Diagram Manual, Chapter 24, Electrical Distribution System - Maintenance Practices.) 3. (Refer to Figure 8, Detail A.) Install the CVDR S1232-505 Circuit Breaker (HC046) in the left circuit breaker panel. Connect circuit breaker to existing bus bar. Use one S1367-1-8 ring terminal on the ship side with 2HC046-PJC011 wire. Engage CVDR circuit breaker. (Refer to the Model 208 Maintenance Manual, Chapter 24, Electrical Distribution System - Maintenance Practices and Model 208 Wiring Diagram Manual, Chapter 24, Electrical Distribution System - Maintenance Practices.) 4. (Refer to Figure 1.) Do the modification of the 2614070-6 Avionics Shelf as follows: A. Remove the rear compartment wall. (Refer to the Model 208 Maintenance Manual, Chapter 25, Rear Compartment Wall - Maintenance Practices.)

CAB-31-01 Page 2 Revision 1 - August 14, 2017 Caravan SERVICE BULLETIN CAB-31-01

B. Loosen the mounting tray hold-down knobs/nuts and move the avionics boxes off of the 2614070-6 Avionics Shelf, but do not unplug the cable assemblies from the avionics boxes. (Refer to the application sections of Chapter 34 of the Model 208 Maintenance Manual.) NOTE: The 2614070-6 Avionics Shelf may have avionics boxes for KTA-870 TAS, Stormscope, and KRA 405B Rad Alt installed. C. Use protective plastic to cover the avionics boxes that you have moved to protect them from debris as you do the modification. D. Remove the 2614070-6 Avionics Shelf from the structure. Note: If WX500 Stormscope is installed, remove the Stormscope mounting tray from the avionics shelf. Keep the attachment hardware. E. Use protective plastic to cover the surfaces of the 2614070-6 Avionics Shelf that are adjacent to the hole that you will drill. F. (Refer to Figure1, View A-A.) Match drill four 0.203-inch diameter holes from the mounting tray to the 2614070-6 Avionics Shelf. G. Drill and countersink eight Number 40 (0.098-inch diameter) holes for the rivets that will attach the four MS21075L08N Nutplates. H. Deburr and apply Alodine to bare metal. I. With eight MS20426AD3-3 Rivets, install the four MS21075L08N Nutplates to the 2614070-6 Avionics Shelf. J. (Refer to Figure 1, View B-B.) With the four MS35206-245 Screws, install the 115-00658-00 Remote Mount Rack and the 011-00796-01 Backplate (Part of the 3929307-802-1) to the 2614070-6 Avionics Shelf. K. Clean, electrically bond, and make sure that the electrical resistance value between the rack and the shelf is within the allowable maximum limit of 0.0025 Ohms. (Refer to the Model 208 Maintenance Manual, Chapter 20, Electrical Bonding - Maintenance Practices.) L. Connect the 3929307-2 Wiring Assembly GSD 41 Adapter (Part of the 3929307-802-1). Connect adapter plug JT307 into PT307 of the airplane harness. (Refer to the Model 208 Wiring Diagram Manual, Chapter 23, 23-20-01 Figure 03, GSD 41 DCU.) M. (Refer to Figure 1, View C-C and View D-D.) Install the 011-01457-00 GSD 41 Data Concentrator Unit (DCU) on the 115-00658-00 Remote Mount Rack on the 2614070-6 Avionics Shelf. N. Remove the protective plastic from the avionics boxes and the 2614070-6 Avionics Shelf. O. With the kept attachment hardware, install the 2614070-6 Avionics Shelf to the structure. P. Put the avionics boxes that you moved from the 2614070-6 Avionics Shelf in installation position and tighten the mounting tray hold-down knobs to install them on the 2614070-6 Avionics Shelf. (Refer to the application sections of Chapter 34 of the Model 208 Maintenance Manual.) 5. (Airplanes that are not equipped with the optional KHF 1050 Communication System) (Refer to Figure 2.) Install the 2601014-31 Aft Shelf Assembly and CVDR as follows: NOTE: Airplanes that are equipped with the optional KHF 1050 Communication System will already have the 2601014-31 Aft Shelf Assembly installed, and can skip to Step 6. A. (Refer to Figure 2, View A-A.) Put the 2601014-31 Aft Shelf Assembly in installation position. Corners of support 2601014-34 may be trimmed as needed to fit, up to 45 degrees. B. Match drill four Number 21 (0.159-inch diameter) holes in the 2612051 Bulkhead on the left side of the airplane and then match drill four Number 21 (0.159-inch diameter) holes in the 2612051 Bulkhead on the right side of the airplane. C. (Refer to Figure 2, View C-C.) Match drill four Number 21 (0.159-inch diameter) holes in the 2601014-34 Support Assembly on the left side of the airplane and then match drill four Number 21 (0.159-inch diameter) holes in the 2601014-34 Support Assembly on the right side of the airplane.

CAB-31-01 Revision 1 - August 14, 2017 Page 3 Caravan SERVICE BULLETIN CAB-31-01

D. (Refer to Figure 2, View B-B.) Match drill 10 Number 30 (0.128-inch diameter) holes in the 2612000 Airplane Skin on the left side of the airplane and then match drill 10 Number 30 (0.128-inch diameter) holes in the 2612000 Airplane Skin on the right side of the airplane. E. Deburr and apply Alodine to bare metal. F. Install the 3940005-4 CVDR Bracket Assembly on the 2601014-31 Aft Shelf Assembly as follows: (1) (Refer to Figure 3, View A-A and View B-B.) From the 2601014-31 Aft Shelf Assembly, remove the two rivets shown that are next to RBL 8.20. (2) Put the 3940005-4 CVDR Bracket Assembly in installation position on the 2601014-31 Aft Shelf Assembly. (3) Make marks for and drill two number 30 (0.128-inch diameter) holes in the 3940005-4 CVDR Bracket Assembly common to the holes in the 2601014-31 Aft Shelf Assembly where rivets were removed from the position next to RBL 8.20. (4) Make marks for and drill 17 Number 30 (0.128-inch diameter) holes in the 3940005-4 CVDR Bracket Assembly and the 2601014-31 Aft Shelf Assembly. (5) Deburr and apply Alodine to bare metal. G. (Refer to Figure 3, View C-C and View F-F.) Install the 6318104-2 Ground Stud on the 2601014-31 Aft Shelf Assembly as follows: (1) Make a mark for and drill one 0.203-inch diameter hole in the 2601014-31 Aft Shaft Assembly. (2) Deburr and apply Alodine to bare metal. (3) Install the 6318104-2 Ground Stud on the 2601014-31 Aft Shelf Assembly. Make sure that you install the hardware in the order shown in the Model 208 Maintenance reference that follows. (Refer to Model 208 Maintenance Manual, Chapter 20, Electrical Bonding - Maintenance Practices, Figure 211: Electrical Bonding - CVDR Ground Stud Installation.) (4) Clean, electrically bond, and make sure that the electrical resistance value between the ground stud and the shelf is within the allowable maximum limit of 0.0025 Ohms. (Refer to Model 208 Maintenance Manual, Chapter 20, Electrical Bonding - Maintenance Practices.) (5) Use one of the following methods to identify the newly installed 6318104-2 Ground Stud with the label "GT907." (a) Use a rubber stamp with black ink to stamp "GT907" on the structure next to the hole where the 6318104-2 Ground Stud is installed. Then apply clear polyurethane over the ink. (b) Use a label maker to make a label with "GT907" written on it and attach the label to the structure next to the hole where the 6318104-2 Ground Stud is installed. (c) With Scotchcal Silkscreen Tape, make a decal with "GT907" written on it and attach the label to the structure next to the hole where the 6318104-2 Ground Stud is installed. H. (Refer to Figure 3, View C-C and View D-D.) Install the 6895-D-2-X-5-5 Impact Switch on the 2601014-31 Aft Shelf Assembly as follows: (1) Using the impact switch, match drill four 0.203-inch diameter holes in the 2601014-31 Aft Shelf Assembly. (2) Drill and countersink eight number 40 (0.098-inch diameter) holes for the rivets that will attach the four MS21075L3N Nutplates. (3) Deburr and apply Alodine to bare metal. (4) With eight MS20426AD3-3A Rivets, install the four MS21075L3N Nutplates to the 2601014-31 Aft Shelf Assembly.

CAB-31-01 Page 4 Revision 1 - August 14, 2017 Caravan SERVICE BULLETIN CAB-31-01

(5) With the four MS35207-265 Screws and four NAS43DD3-8FC Spacers, install the 6895-D-2-X-5-5 Impact Switch on the 2601014-31 Aft Shelf Assembly. (6) Clean, electrically bond, and make sure that the electrical resistance value between the impact switch and the shelf is within the allowable maximum limit of 0.0025 Ohms. (Refer to Model 208 Maintenance Manual, Chapter 20, Electrical Bonding - Maintenance Practices.) (7) With 15 MS20470AD4-4A Rivets and four MS20470AD4-4A5 Rivets, install the 3940005-4 CVDR Bracket Assembly on the 2601014-31 Aft Shelf Assembly. I. (Refer to Figure 3, View C-C and View E-E.) With the four MS24694-S5 Screws, install the 178E0919-00 SSCVR Mount. J. Refer to Figure 3, View D-D.) With the four MS24693-S6 Screws and four MS21044N04 Nuts, install the 3929306-7 CVDR Adapter. Connect 3 shields of harness to MS24693-S6 with S1367-1-6 Terminal. Install PT305 to impact switch. (Refer to the Instructions for Continued Airworthiness - 208B ICA-208-31-00001 - L-3 Communications FA2100 CVDR ICA Supplement. K. Install ground wires labeled "GT907" on ground stud GT907 (MS25036-103 Terminal). L. Install PT306 to JT306 on airplane side of harness. M. Install JT311 to PT311 on airplane side of harness. N. Secure harness as required with existing harnesses. O. (Refer to Figure 2, View A-A.) With four MS20470AD5-4A-5 Rivets, attach the 2601014-31 Aft Shelf Assembly via the 2601014-37 Support to the 2612051 Bulkhead on the left side of the airplane. With four MS20470AD5-4A-5 Rivets, attach the 2601014-31 Aft Shelf Assembly via the 2601014-37 Support to the 2612051 Bulkhead on the right side of the airplane. P. (Refer to Figure 2, View C-C.) With four MS20470AD5-4A-5 Rivets, respectively, attach the 2601014-31 Aft Shelf Assembly via the 2601014-34 Support Assembly to the 2612052 Bulkhead on the left and right side of the airplane. Q. (Refer to Figure 2, View B-B.) With 10 MS20470AD4-4A Rivets, attach the 2601014-31 Aft Shelf Assembly via the 2601014-8 Support to the 2612000 Airplane Skin on the left side of the airplane. With 10 MS20470AD4-4A Rivets, attach the 2601014-31 via the 2601014-9 Aft Shelf Assembly to the 2612000 Airplane Skin on the right side of the airplane. R. Place S2562-1 tubing, as required, around wire harness between anchors. S. Clean, electrically bond, and make sure that the electrical resistance value between the shelf and the airplane structure is within the allowable maximum limit of 0.0025 Ohms. (Refer to Model 208 Maintenance Manual, Chapter 20, Electrical Bonding - Maintenance Practices.) T. Go to step 7. 6. (Airplanes that are equipped with the optional KHF 1050 Communication System.) (Refer to Figure 3.) Do the modification of the 2601014-31 Aft Shelf Assembly and the installation of the CVDR as follows: A. Install the 3940005-4 CVDR Bracket Assembly on the 2601014-31 Aft Shelf Assembly as follows: (1) (Refer to Figure 3, View A-A and View B-B.) From the 2601014-31 Aft Shelf Assembly, remove the two rivets shown that are adjacent to RBL 8.20. (2) Put the 3940005-4 CVDR Bracket Assembly in installation position on the 2601014-31 Aft Shelf Assembly. (3) Make marks for and drill two Number 30 (0.128-inch diameter) holes in the 3940005-4 CVDR Bracket Assembly common to the holes in the 2601014-31 Aft Shelf Assembly where you removed the two rivets that are adjacent to RBL 8.20. (4) Make marks for and drill 17 Number 30 (0.128-inch diameter) holes in the 3940005-4 CVDR Bracket Assembly and the 2601014-31 Aft Shelf Assembly. (5) Deburr and apply Alodine to bare metal.

CAB-31-01 Revision 1 - August 14, 2017 Page 5 Caravan SERVICE BULLETIN CAB-31-01

B. (Refer to Figure 3, View C-C and View F-F.) Install the 6318104-2 Ground Stud on the 2601014-31 Aft Shelf Assembly as follows: (1) Make a mark for and drill one 0.203-inch diameter hole in the 2601014-31 Aft Shelf Assembly. (2) Deburr and apply Alodine to bare metal. (3) Install the 6318104-2 Ground Stud on the 2601014-31 Aft Shelf Assembly. Make sure that you install the hardware in the order shown in the Model 208 Maintenance Manual reference that follows. (Refer to the Model 208 Maintenance Manual, Chapter 20, Electrical Bonding - Maintenance Practices, Figure 211: Electrical Bonding - CVDR Ground Stud Installation.) (4) Clean, electrically bond, and make sure that the electrical resistance value between the ground stud and the structure is within the allowable maximum limit of 0.0025 Ohms. (Refer to the Model 208 Maintenance Manual, Chapter 20, Electrical Bonding - Maintenance Practices.) (5) Use one of the methods that follow to identify the newly installed 6318104-2 Ground Stud with the label "GT907". (a) Use a rubber stamp with black ink to stamp GT907 on the structure adjacent to the hole where the 6318104-2 Ground Stud is installed. Then apply clear polyurethane over the ink. (b) Use a label maker to make a label with GT907 written on it and attach the label to the structure adjacent to the hole where the 6318104-2 Ground Stud is installed. (c) With Scotchcal Silkscreen Tape, make a decal with GT907 written on it and attach the label to the structure adjacent to the hole where the 6318104-2 Ground Stud is installed. C. (Refer to Figure 3, View C-C and View D-D.) Install the 6895-D-2-X-5-5 Impact Switch on the 2601014-31 Aft Shelf Assembly as follows: (1) Using the impact switch, match drill four 0.203-inch diameter holes in the 2601014-31 Aft Shelf Assembly. (2) Drill and countersink eight Number 40 (0.098-inch diameter) holes for the rivets that will attach the four MS21075L3N Nutplates. (3) Deburr and apply Alodine to bare metal. (4) With eight MS20426AD3-3A Rivets, install the four MS21075L3N Nutplates to the 2601014-31 Aft Shelf Assembly. (5) With the four MS35207-265 Screws and four NAS43DD3-8FC Spacers, install the 6895-D-2-X-5-5 Impact Switch on the 2601014-31 Aft Shelf Assembly. (6) Clean, electrically bond, and make sure that the electrical resistance value between the impact switch and the structure is within the allowable maximum limit of 0.0025 Ohms. (Refer to the Model 208 Maintenance Manual, Chapter 20, Electrical Bonding - Maintenance Practices.) (7) With 15 MS20470AD4-4A Rivets and four MS20470AD4-4A5 Rivets, install the 3940005-4 CVDR Bracket Assembly on the 2601014-31 Aft Shelf Assembly. D. (Refer to Figure 3, View C-C and View E-E.) With the four MS24694-S5 Screws, install the 178E0919-00 SSCVR Mount. E. (Refer to Figure 3, View D-D.) With the four MS24693-S6 Screws and four MS21044N04 Nuts, install the 3929306-7 CVDR Adapter. Connect 3 shields of harness to MS24693-S6 with S1367-1-6 Terminal. Install PT305 to impact switch. (Refer to the Instructions for Continued Airworthiness - 208B ICA-208-31-00001 - L-3 Communications FA2100 CVDR ICA Supplement.) F. Install ground wires labeled "GT907" on ground stud GT907 (MS25036-103 Terminal). G. Install PT306 to JT306 on airplane side of harness. H. Install JT311 to PT311 on airplane side of harness.

CAB-31-01 Page 6 Revision 1 - August 14, 2017 Caravan SERVICE BULLETIN CAB-31-01

I. Secure harness as required with existing harnesses. J. Place S2562-1 tubing, as required, around wire harness between anchors. 7. (Refer to Figure 4.) Do the installation of the S056-0048-00 Cockpit Voice Recorder (CVR) Microphone as follows: A. Remove the pilot's and co-pilot's control column cover assembly. (Refer to the Model 208 Maintenance Manual, Chapter 25, Cabin Upholstery - Maintenance Practices.) B. Remove the PFD and MFD Garmin Display Units (GDU) as necessary for access to install the S056-0048-00 CVR Microphone. (Refer to the Model 208 Maintenance Manual, Chapter 34, Garmin Display Units (GDU) - Maintenance Practices.) C. Remove the audio panel as necessary for access to install the S056-0048-00 CVR Microphone. (Refer to the Model 208 Maintenance Manual, Chapter 23, Garmin GMA 1347 Audio Panel System Components - Maintenance Practices.) D. Remove the instrument display panel as necessary for access to install the S056-0048-00 CVR Microphone. (Refer to the Model 208 Maintenance Manual, Chapter 31, Instrument and Control Panels - Maintenance Practices.) E. (Refer to Figure 4, View A-A.) Drill one 0.540-inch diameter hole in the 2613471 Sub Panel Assembly. Note: If hole is already on the sub assembly, enlarge to 0.540-inch. F. If necessary, install CM3018-92 shim(s) between the cockpit voice recorder microphone and the mounting bracket. G. Deburr and apply Alodine to bare metal. H. (Refer to Figure 4, View B-B.) With the two MS35206-227 Screws, install the S056-0048-00 CVR Microphone to the structure (part of the 3929306-803). I. Connect the 3929306-3 Area Mic Wiring Assembly (part of the 3929306-803). (Refer to the Instructions for Continued Airworthiness - 208B ICA-208-31-00001 - L-3 Communications FA2100 CVDR ICA Supplement.) J. Install the GDUs, audio panel, and instrument display panel, that you removed for access to install the S056-0048-00 CVR Microphone. (Refer to the Model 208 Maintenance Manual, Chapter 34, Garmin Display Units (GDU) - Maintenance Practices, Chapter 23, Garmin GMA 1347 Audio Panel System Components - Maintenance Practices, and Chapter 31, Instrument and Control Panels - Maintenance Practices.) 8. (Refer to Figure 5.) Install the CVR adapter as follows: A. (Refer to Figure 5, View A-A and View B-B.) Match drill six Number 21 (0.159-inch diameter) holes in the pedestal structure for the rivets that attach the 2601495-15 Adapter Bracket Assembly. B. Deburr and apply Alodine to bare metal. C. With the six S2906-5-2 Rivets, attach the 2601495-15 Adapters Bracket Assembly to the pedestal structure. If nut plates are installed on the pedestal, use 6 AN525-832R9 screws to install the bracket assembly. D. (Refer to Figure 5, View C-C and View D-D.) In each of the two M1090 CVR Adapters, match drill to enlarge the four holes to 0.147-inch in diameter. E. Deburr and apply Alodine to bare metal. F. Attach the two M1090 CVR Adapters to the 2601495-15 Adapters Bracket Assembly with the eight MS35206-228 Screws and the eight NAS1149FN632P Washers. G. Clean, electrically bond, and make sure that the electrical resistance value between the CVR adapters and structure is within the allowable maximum limit of 0.0025 Ohms. (Refer to the Model 208 Maintenance Manual, Chapter 20, Electrical Bonding - Maintenance Practices.) H. Attach connector PI529 to right CVR adapter.

CAB-31-01 Revision 1 - August 14, 2017 Page 7 Caravan SERVICE BULLETIN CAB-31-01

I. Attach connector PI528 to left CVR adapter. J. Install wiring assembly at the connectors. K. Install the control column cover assembly. (Refer to the Model 208 Maintenance Manual, Chapter 25, Cabin Upholstery - Maintenance Practices.) 9. (Refer to Figure 6.) Install the accelerometer as follows: A. Remove the strap fairing assembly, if applicable, at the left wing root. B. If applicable, remove the left lower wing panel 511AB. (Refer to the Model 208, Chapter 6, Access Plates and Panels Identification - Description and Operation.) C. Remove headliner in accordance with Model 208 Maintenance Manual, Chapter 25, Cabin Upholstery - Maintenance Practices. D. Remove bracket 2601247-69. E. (Refer to Figure 6, View A-A.) Remove and discard the three existing rivets. NOTE: Airplanes with 3940005-13 Angle and 3940005-11 Accelerometer Bracket Assembly already installed should go to step 9.L. F. Put the 3940005-13 Angle and the 3940005-11 Accelerometer Bracket Assembly in installation position. G. (Refer to Figure 6, View A-A and View B-B.) Drill the holes that follow: (1) Match drill one Number 30 (0.128-inch diameter) hole in the 3940005-13 Angle to align with the existing hole in the 2611221-5 Left Fuselage Root Rib Assembly. (2) Match drill two Number 21 (0.159-inch diameter) holes in the 3940005-11 Accelerometer Bracket Assembly to align with the existing holes in the 2611221-5 Left Fuselage Root Rib Assembly. (3) Make marks for and drill six Number 30 (0.128-inch diameter) holes in the 2611221-5 Left Fuselage Root Rib Assembly and the 3940005-13 Angle. (4) Make marks for and drill two Number 30 (0.128-inch diameter) holes in the 2611221-5 Left Fuselage Root Rib Assembly, 3940005-13 Angle, and 3940005-11 Accelerometer Bracket Assembly. H. Deburr and apply Alodine to bare metal. I. With seven MS20470AD4-4A5 Rivets, attach the 3940005-13 Angle to the 2611221-5 Left Fuselage Root Rib Assembly. NOTE: You can install the rivets with the heads of the rivets facing toward the center line of the airplane and the tails of the rivets facing toward the left wing. J. With two MS20470AD4-5A Rivets, attach the 3940005-13 Angle and the 3940005-11 Accelerometer Bracket Assembly to the 2611221-5 Left Fuselage Root Rib Assembly. NOTE: You can install the rivets with the heads of the rivets facing toward the center line of the airplane and the tails of the rivets facing toward the left wing. K. With two MS20470AD5-5A5 Rivets, attach the 3940005-11 Accelerometer Bracket Assembly to the 2611221-5 Left Fuselage Root Rib Assembly. NOTE: You can install the rivets with the heads of the rivets facing toward the center line of the airplane and the tails of the rivets facing toward the left wing. L. Clean, electrically bond, and make sure that the electrical resistance value is within the allowable maximum limit of 0.0025 Ohms at the ground stud GC900 on the 3940005-11 Accelerometer Bracket Assembly. (Refer to the Model 208 Maintenance Manual, Chapter 20, Electrical Bonding - Maintenance Practices.)

CAB-31-01 Page 8 Revision 1 - August 14, 2017 Caravan SERVICE BULLETIN CAB-31-01

M. (Refer to Figure 6, Detail A.) With the three MS35207-263 Screws, attach the 3001-01-111 3-Axis Accelerometer to the 3940005-11 Accelerometer Bracket Assembly. N. If applicable, use one of the methods that follow to identify the ground stud with the label "GC900". (1) Use a rubber stamp with black ink to stamp GC900 on the structure adjacent to the hole where the ground stud is installed. Then apply clear polyurethane over the ink. (2) Use a label maker to make a label with GC900 written on it and attach the label to the structure adjacent to the hole where the ground stud is installed. (3) With Scotchcal Silkscreen Tape, make a decal with GC900 written on it and attach the label to the structure adjacent to the hole where the ground stud is installed. O. Attach connector PC302 to accelerometer. P. If applicable, attach ground wire GC900 to ground stud. Q. If applicable, install the strap fairing assembly at the left wing root. R. If applicable, install the left lower wing panel 511AB. (Refer to the Model 208, Chapter 6, Access Plates and Panels Identification - Description and Operation.) 10. (Refer to Figure 7.) Do the installation of the FDR potentiometer as follows: NOTE: 2601495-3 Potentiometer Bracket Assembly and 2601495-23 Accelerometer Bracket may already be installed. Accomplish the following steps 10.A thru 10.D as applicable. A. (Refer to Figure 7, Sheet 1 View A-A and Sheet 2 View A-A.) Put the 2601495-23 Accelerometer Bracket and the 2601495-3 Potentiometer Bracket in installation position. B. Drill the holes that follow: (1) Drill two Number 30 (0.128-inch diameter) holes in the 2611118 Bulkhead Assembly and the 2601495-23 Accelerometer Bracket. (2) Drill two Number 30 (0.128-inch diameter) holes in the 2611022 Bulkhead Assembly and the 2601495-23 Accelerometer Bracket. (3) Drill six Number 30 (0.128-inch diameter) holes in the 2601495-23 Accelerometer Bracket and the 2601495-3 Potentiometer Bracket Assembly. C. Deburr and apply Alodine to bare metal. D. With three MS20470AD4-5A5 Rivets, two MS20470AD4-5A Rivets, and five MS20470AD4-4A Rivets, attach the 2601495-23 Accelerometer Bracket and the 2601495-3 Potentiometer Bracket Assembly to the airplane structure. E. Clean, electrically bond, and make sure that the electrical resistance value between the brackets and the airplane structure is within the allowable maximum limit of 0.0025 Ohms. (Refer to the Model 208 Maintenance Manual, Chapter 20, Electrical Bonding - Maintenance Practices.) F. Remove supplied screws from the three L3-7 mount cleats and install three MS35206-217 screws. G. (Refer to Figure 7, View B-B.) With the three L3-7 Mount Cleats and the three MS35206-217 Screws, attach the V200639 Potentiometer (part of the 3929306-4) to the 2601495-3 Potentiometer Bracket Assembly. H. Turn the potentiometer shaft fully counterclockwise. I. (Refer to Figure 7, Sheet 1 View A-A.) Install the 2601495-7 Lever Assembly, MS21322-11 Clamp, and 2601495-10 Rod Assembly with the two AN3-6 Bolts, two NAS1149F0332P Washers, two S1450-3-10-032 Washers, two AN310-3 Nuts, and two MS24665-172 Cotter Pins. J. (Refer to Figure 7, View C-C.) Install and tighten the two AN565D4H3 Set Screws.

CAB-31-01 Revision 1 - August 14, 2017 Page 9 Caravan SERVICE BULLETIN CAB-31-01

K. (Refer to Figure 7, View B-B.) Connect the 3929306-4 Flap Potentiometer Wiring Assembly. (Refer to the Model 208 Wiring Diagram Manual, Chapter 31, Section 31-31-01, Figure 3, FA2100 Cockpit Voice/Data Recorder System.) 11. Do the CVDR configuration as follows: A. Remove the database SD cards from the bottom slots of the PFD1, PFD2, and MFD displays, mark the SD Cards as "PFD1", "PFD2", or "MFD" as you remove them, and store them in a safe place for later installation. B. Pull the "START CONT" C/B in LH C/B Panel to disable the fuel alarm. C. Remove the maintenance warning tags and connect the airplane battery. Apply external power if necessary. D. Disengage the PFD1, PFD2, and the MFD circuit breakers. E. Place the "Battery" switch in the "ON" position. F. Place the "Avionics" switches to the "ON" position. G. Push and hold the ENT key on PFD2 while you engage the PFD2 circuit breaker. H. Release the ENT key when the message INITIALIZING SYSTEM shows on the PFD2. I. Push and hold the ENT key on the MFD while you engage the MFD circuit breaker. J. Release the ENT key when the message INITIALIZING SYSTEM shows on the MFD. K. Install the 010-00681-15 (or latest revision) G1000 Software Loader Card in the top SD slot of the PFD1. NOTE: The G1000 Software Loader Card is in the SD card holder in the Pilot's Operating Handbook. If you cannot find the G1000 Software Loader Card, contact Cessna. L. Push and hold the ENT key on PFD1 while you engage the PFD1 circuit breaker. M. Release the ENT key when the message INITIALIZING SYSTEM shows on the PFD1. N. Push the NO soft key when the message DO YOU WANT TO UPDATE USER SETTINGS? shows. O. Turn the small FMS knob on the PFD1 to go to the SYSTEM group SYSTEM UPLOAD page. P. Push the small FMS knob on the PFD1 to start the cursor. Q. Turn the small FMS knob to highlight INSTALLATION OPTIONS in the AIRFRAME field and push the ENT key. NOTE: With some loader cards, INSTALLATION OPTIONS - GENERAL may be shown rather than INSTALLATION OPTIONS. R. Turn the small FMS knob to highlight CESSNA CARAVAN - FDR/CVR Installation Option in the option list of the FILE field and push the ENT key. NOTE: If the CESSNA CARAVAN - FDR/CVR Installation Option is not found in the INSTALLATION OPTIONS - GENERAL group, highlight and select the INSTALLATION OPTIONS - PT6A-114A ONLY group. The FDR/CVR Option found there is also valid for airplanes equipped with the PT6A-140 engine. S. Push the LOAD soft key. T. Monitor the upload status. (1) If the upload fails, push the ENT key when the Upload Failed message is shown, and then push the LOAD soft key to begin the upload again.

CAB-31-01 Page 10 Revision 1 - August 14, 2017 Caravan SERVICE BULLETIN CAB-31-01

(2) If the upload completes successfully, push the ENT key when the Upload Complete message is shown. NOTE: You can attempt to upload for a maximum of five times because of a failed or cancelled upload prompt message. If the system does not upload after the fifth attempt, refer to the 190-00869-00 Garmin Line Maintenance Manual, Revision E or later, Appendix B.3 Software / Configuration Troubleshooting. If the system still does not upload, contact Cessna Customer Service: Telephone 316-517-5800. U. Push the UPDT CFG and the ENT soft keys to update the PFD1 configuration module. V. Monitor the update status. (1) If the update fails, push the ENT key when the Update Failed message is shown, and then push the UPDT CFG and the ENT soft keys to begin the update again. (2) If the update completes successfully, push the ENT key when the Update Config Complete message is shown. NOTE: You can attempt to update for a maximum of five times because of a failed or cancelled update config prompt message. If the system does not update after the fifth attempt, refer to the 190-00869-00 Garmin Line Maintenance Manual, Revision E or later, Appendix B.3 Software / Configuration Troubleshooting. If the system still does not update, contact Cessna Customer Service: Telephone 316-517-5800. W. Put the AVIONICS 1 and 2 switches in the OFF position and remove the 010-00681-15 (or latest revision) G1000 Software Loader Card from the top slot of the PFD1. X. Insert the database SD cards into the bottom slots of the PFD1, PFD2, and MFD displays from which you removed them. Y. Engage "START CONT" circuit breaker. Z. Put the AVIONICS 1 and 2 switches to the ON position and let the system power on in normal mode. 12. Calibrate flap potentiometer as follows: A. Ensure that flaps have been rigged in accordance with 208 Maintenance Manual Chapter 27-50-02 before starting this configuration. B. Attach an inclinometer to either flap on the trailing edge rib at W.S. 68.00, approximately 34 inches from the inboard edge of the flap. C. Power on avionics in normal mode and verify system software version 767.15 or later is installed. D. Pull out the PFD1 circuit breaker. E. Set inclinometer to 0 degrees in the flaps up position. F. Set the flaps selector lever to 15 degrees. G. Press and hold the "ENT" button on the PDF1 display while pushing in the PFD1 circuit breaker. The "ENT" button may be released when the "Intitializing System" message appears. H. Use the outer FMS knob to scroll to the "GEA" page. I. Use the inner FMS knob to scroll to the "GEA Status" page. J. Press the "ANLG In" softkey. K. Locate the channel 3A "Flaps Position" Field. The value of this field is the flaps position as indicated by the flap potentiometer. L. Loosen the flap potentiometer cleats. M. Slowly rotate the potentiometer until the "Flaps Position" field on PFD1 matches the inclinometer(+/- 0.3"). N. Carefully tighten the potentiometer cleats ensuring the potentiometer does not rotate.

CAB-31-01 Revision 1 - August 14, 2017 Page 11 Caravan SERVICE BULLETIN CAB-31-01

O. Cycle the flaps to ensure that the flap system operates without binding or iterference. P. Check to make sure that the GEA1 "Flaps Position" readout matches the flap position according to the inclinometer (+/- 1.0") at the following flap lever positions: ~0 Degrees or up ~15 Degrees or To/APR ~30 Degrees or land Q. Remove inclinometer from the wing. R. Power down avionics and aircraft. S. Flap potentiometer configuration complete. NOTE: When accomplishing adjustment test in the following step 13, use information from Table 502 of 208 Maintenance Manual Chapter 27-50-02 in lieu of information from Table 502 in 208 Maintenance Manual Chapter 31, L-3 that is referenced below. 13. Do an operational test of the system, including the FDR Parameter Test Procedure in the entirety of the following step 13.A. (Refer to the Model 208 Maintenance Manual, Chapter 31, L-3 Communications FA2100 Cockpit Voice/Data Recorder System- Adjustment/Test.) A. FDR Parameter Test Procedure. NOTE: This FDR Parameter Test Procedure shall be worked in lieu of Paragraph G - FDR Parameter Test - Chapter 31, L-3 Communications FA2100 Cockpit Voice/Data Recorder System- Adjustment/Test. (1) Ensure the recorder power is OFF. (2) (Refer to Figure 9, Sheet 1.) Make connection between RAU and CICC/3 using Ethernet cable as shown. (3) Make connection between the recorder and GSE connector. (4) Open ROSE and Log in. NOTE: The default ROSE Administrator password is "ROSE". (5) Apply aircraft power to the recorder. (6) Click Select Aircraft Configuration on the ROSE main menu and select the appropriate aircraft configuration; "Cessna 208-208B Caravan". Click OK when finished. (7) Click the Recorder Interface button. Select CICC/3 and click on Connect button. (8) Click the Test Flight Recorder button on the ROSE main menu. (9) (Refer to Figure 9, Sheet 2.) Check that the recorder status is being displayed to verify that the recorder has been connected successfully. The status should be FAULT NOT RECORDING as shown. (10) Click the Start Recording button to issue a start recording command to the connected recorder. (11) (Refer to Figure 9, Sheet 3.) Check that the recorder status changes to OK RECORDING as shown. (12) Click the "Set Memory Marker" button to apply a memory marker pointer to the recorder. NOTE: Take note of the memory marker number assigned by the recorder. (13) Record data for at least 30 seconds. (14) Click the Stop Recording button to terminate data recording on the connected recorder. (15) Click the Close button to return to ROSE main menu. (16) Click the Import/Export Flight Data button from the ROSE Main menu.

CAB-31-01 Page 12 Revision 1 - August 14, 2017 Caravan SERVICE BULLETIN CAB-31-01

(17) Click the Import New Data button on the Flight Data File Control menu. (18) Enter a file name for the flight data file to be created on the local disk. Select ROSE raw frame type under New File Type field. (19) Select Recorder for the Source of Data option. (20) Under Data Dump Options, select Dump Data From Memory Mark and select the memory mark number from step 13.A(12). (21) Click "OK" to import New Data file. (22) Select Report/Display/Analyze on ROSE main menu. (23) Select 208-208B Production under Select a Report Name. (24) Select Alphanumeric comma delimited export file under Report Description and click OK. (25) Select Local File Data on Report Setup page. (26) Select the file name entered on step 13.A(18) under Source of Data. Click OK. (27) Select a file name and location and save the file. (28) Open the comma delimited file in Excel and review data for accuracy. 14. Do the Flight Data Recorder Underwater Locator Beacon Functional Check. (Refer to the Model 208 Maintenance Manual, Chapter 31, L-3 Communications FA2100 Cockpit Voice/Data Recorder System- Inspection/Check.) 15. Install the rear compartment wall. (Refer to the Model 208 Maintenance Manual, Chapter 25, Rear Compartment Wall - Maintenance Practices.) 16. Install the headliner. (Refer to the Model 208 Maintenance Manual, Chapter 25, Cabin Upholstery - Maintenance Practices.) 17. Make an entry in the airplane logbook that states compliance and method of compliance with this service bulletin.

CAB-31-01 Revision 1 - August 14, 2017 Page 13 Caravan SERVICE BULLETIN CAB-31-01

Figure 1. 2614070-6 Avionics Shelf Modification and GSD 41 Data Concentrator Installation (Sheet 1)

CAB-31-01 Page 14 Revision 1 - August 14, 2017 Caravan SERVICE BULLETIN CAB-31-01

Figure 1. 2614070-6 Avionics Shelf Modification and GSD 41 Data Concentrator Installation (Sheet 2)

CAB-31-01 Revision 1 - August 14, 2017 Page 15 Caravan SERVICE BULLETIN CAB-31-01

Figure 2. Aft Shelf Assembly Installation (Sheet 1)

CAB-31-01 Page 16 Revision 1 - August 14, 2017 Caravan SERVICE BULLETIN CAB-31-01

Figure 2. Aft Shelf Assembly Installation (Sheet 2)

CAB-31-01 Revision 1 - August 14, 2017 Page 17 Caravan SERVICE BULLETIN CAB-31-01

Figure 3. 2601014-31 Aft Shelf Assembly Modification and CVDR Installation (Sheet 1)

CAB-31-01 Page 18 Revision 1 - August 14, 2017 Caravan SERVICE BULLETIN CAB-31-01

Figure 3. 2601014-31 Aft Shelf Assembly Modification and CVDR Installation (Sheet 2)

CAB-31-01 Revision 1 - August 14, 2017 Page 19 Caravan SERVICE BULLETIN CAB-31-01

Figure 3. 2601014-31 Aft Shelf Assembly Modification and CVDR Installation (Sheet 3)

CAB-31-01 Page 20 Revision 1 - August 14, 2017 Caravan SERVICE BULLETIN CAB-31-01

Figure 3. 2601014-31 Aft Shelf Assembly Modification and CVDR Installation (Sheet 4)

CAB-31-01 Revision 1 - August 14, 2017 Page 21 Caravan SERVICE BULLETIN CAB-31-01

Figure 4. CVR Microphone Installation (Sheet 1)

CAB-31-01 Page 22 Revision 1 - August 14, 2017 Caravan SERVICE BULLETIN CAB-31-01

Figure 5. CVR Adapter Installation (Sheet 1)

CAB-31-01 Revision 1 - August 14, 2017 Page 23 Caravan SERVICE BULLETIN CAB-31-01

Figure 5. CVR Adapter Installation (Sheet 2)

CAB-31-01 Page 24 Revision 1 - August 14, 2017 Caravan SERVICE BULLETIN CAB-31-01

Figure 5. CVR Adapter Installation (Sheet 3)

CAB-31-01 Revision 1 - August 14, 2017 Page 25 Caravan SERVICE BULLETIN CAB-31-01

Figure 6. Accelerometer Installation (Sheet 1)

CAB-31-01 Page 26 Revision 1 - August 14, 2017 Caravan SERVICE BULLETIN CAB-31-01

Figure 6. Accelerometer Installation (Sheet 2)

CAB-31-01 Revision 1 - August 14, 2017 Page 27 Caravan SERVICE BULLETIN CAB-31-01

Figure 6. Accelerometer Installation (Sheet 3)

CAB-31-01 Page 28 Revision 1 - August 14, 2017 Caravan SERVICE BULLETIN CAB-31-01

Figure 7. FDR Potentiometer Installation (Sheet 1)

CAB-31-01 Revision 1 - August 14, 2017 Page 29 Caravan SERVICE BULLETIN CAB-31-01

Figure 7. FDR Potentiometer Installation (Sheet 2)

CAB-31-01 Page 30 Revision 1 - August 14, 2017 Caravan SERVICE BULLETIN CAB-31-01

Figure 7. FDR Potentiometer Installation (Sheet 3)

CAB-31-01 Revision 1 - August 14, 2017 Page 31 Caravan SERVICE BULLETIN CAB-31-01

Figure 8. Circuit Breaker Installation (Sheet 1)

CAB-31-01 Page 32 Revision 1 - August 14, 2017 Caravan SERVICE BULLETIN CAB-31-01

Figure 9. FDR Parameter Test Procedure (Sheet 1)

CAB-31-01 Revision 1 - August 14, 2017 Page 33 Caravan SERVICE BULLETIN CAB-31-01

Figure 9. FDR Parameter Test Procedure (Sheet 2)

CAB-31-01 Page 34 Revision 1 - August 14, 2017 Caravan SERVICE BULLETIN CAB-31-01

Figure 9. FDR Parameter Test Procedure (Sheet 3)

CAB-31-01 Revision 1 - August 14, 2017 Page 35 Caravan SERVICE BULLETIN CAB-31-01

MATERIAL INFORMATION

Order the kit below to install this modification.

NEW P/N QUAN- KEY WORD OLD P/N INSTRUCTIONS/ TITY DISPOSITION CAB-31-01 1 Kit, consisting of the following parts: AN3-6 2 Bolt None AN310-3 2 Nut None AN565D4H3 2 Set Screw None L3-7 3 Mount Cleat None MS20426AD3-3A 8 Rivet None MS20426AD3-3 8 Rivet None MS20470AD4-4A 20 Rivet None MS20470AD4-4A5 11 Rivet None MS20470AD4-5A 4 Rivet None MS20470AD4-5A5 3 Rivet None MS20470AD5-5A5 2 Rivet None MS21044N04 4 Nut None MS21075L08N 4 Nutplate None MS21075L3N 4 Nutplate None MS21322-11 1 Clamp None MS24665-172 2 Cotter Pin None MS24693-S6 4 Screw None MS24694-S5 4 Screw None MS35206-217 3 Screw None MS35206-227 2 Screw None MS35206-228 8 Screw None MS35206-245 4 Screw None MS35207-263 3 Screw None MS35207-265 4 Screw None M1090 2 CVR Adapter None NAS1149F0332P 2 Washer None NAS1149FN632P 8 Washer None NAS43DD3-8FC 4 Spacer None S1232-502 1 Circuit Breaker None

CAB-31-01 Page 36 Revision 1 - August 14, 2017 Caravan SERVICE BULLETIN CAB-31-01

NEW P/N QUAN- KEY WORD OLD P/N INSTRUCTIONS/ TITY DISPOSITION S1232-505 1 Circuit Breaker None S1450-3-10-032 2 Washer None S2906-5-2 6 Rivet None V200639 1 Potentiometer None 011-01457-01 1 GSD 41 Data Concentrator None 115-00658-00 1 Remote Mount Rack None 178E0919-00 1 SS CVR Mount None 2601495-10 1 Rod Assembly None 2601495-15 1 Adapters Bracket Assembly None 2601495-3 1 Potentiometer Bracket None Assembly 2601495-5 1 Accelerometer Bracket None Assembly 2601495-7 1 Lever Assembly None 3001-01-111 1 3-Axis Accelerometer None 3929306-3 (part of 1 Area Mic Wiring Assembly None 3929306-803) 3929306-4 1 Flap Potentiometer Wiring None Assembly 3929307-2 (part of 1 GSD 41 Adapter Wiring None 3929307-802-1) Assembly 3940005-11 1 Accelerator Bracket None Assembly 3940005-13 1 Angle None 3940005-4 1 CVDR Bracket Assembly None S1367-1-8 3 Ring Terminal None S1367-3-8 2 Ring Terminal None S1367-1-6 2 Terminal None S2562-1 X 3 ft Convoluted Tubing None 6318104-2 2 Ground Stud Assembly None 6895-D-2-X-5-5 1 Impact Switch 1 CM3018-92 2 Shim None AN525-832R9 6 Screw None MS25036-103 1 Terminal None CAB-31-01 1 Instructions

CAB-31-01 Revision 1 - August 14, 2017 Page 37 Caravan SERVICE BULLETIN CAB-31-01

The part listed below is required but not included in the kit above for HAZMAT handling purposes.

NEW P/N QUAN- KEY WORD OLD P/N INSTRUCTIONS/ TITY DISPOSITION 2100-3083-51 1 Cockpit Voice and Data None Recorder

Airplanes that are not equipped with the optional KHF 1050 Communication System must also order the parts that follow:

NEW P/N QUAN- KEY WORD OLD P/N INSTRUCTIONS/ TITY DISPOSITION MS20470AD4-4A 20 Rivet None MS20470AD5-4A-5 16 Rivet None 2601014-31 1 Shelf Assembly None 3929306-7 1 CVDR Adapter Wiring None Assembly

CAB-31-01 Page 38 Revision 1 - August 14, 2017 Caravan OWNER ADVISORY CAB-31-01

TITLE INDICATING/RECORDING SYSTEMS - CVDR INSTALLATION

TO: Cessna 208B EX Owner

NOTE: This service bulletin is not applicable to aircraft that have the Dual GMA1347 Audio Panel Option.

REASON This owner advisory is to inform you that CAB-31-01 has been issued to announce the availability of a modification to install the Cockpit Voice and Data Recorder (CVDR ) on 208B EX model airplanes not equipped with CVDR from the factory.

DESCRIPTION CAB-31-01 provides parts and instructions to install CVDR on airplanes not previously equipped with the option from the factory.

COMPLIANCE OPTIONAL. This service bulletin can be accomplished at the discretion of the owner.

WARRANTY Not Applicable.

Please contact a Cessna Caravan Authorized Service Facility for detailed information and arrange to have Cessna service bulletin CAB-31-01 accomplished on your airplane.

NOTE: As a convenience, service documents are now available online to all our customers through a simple, free-of-charge registration process. If you would like to sign up, please visit the "Customer Support Login" link at www.txtavsupport.com to register.

CAB-31-01 October 21, 2015 Page 1 of 1