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
Textron Aviation Customer Service, P.O. Box 7706, Wichita, KS 67277, U.S.A. 1-316-517-5800
COPYRIGHT © 2015
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.)

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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.

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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.

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(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.

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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.

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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.

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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.)

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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.

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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.

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(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.

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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.

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(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.

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

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

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Figure 2. Aft Shelf Assembly Installation (Sheet 1)

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Figure 2. Aft Shelf Assembly Installation (Sheet 2)

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

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

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

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

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Figure 4. CVR Microphone Installation (Sheet 1)

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Figure 5. CVR Adapter Installation (Sheet 1)

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Figure 5. CVR Adapter Installation (Sheet 2)

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Figure 5. CVR Adapter Installation (Sheet 3)

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Figure 6. Accelerometer Installation (Sheet 1)

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Figure 6. Accelerometer Installation (Sheet 2)

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Figure 6. Accelerometer Installation (Sheet 3)

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Figure 7. FDR Potentiometer Installation (Sheet 1)

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Figure 7. FDR Potentiometer Installation (Sheet 2)

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Figure 7. FDR Potentiometer Installation (Sheet 3)

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Figure 8. Circuit Breaker Installation (Sheet 1)

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Figure 9. FDR Parameter Test Procedure (Sheet 1)

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Figure 9. FDR Parameter Test Procedure (Sheet 2)

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Figure 9. FDR Parameter Test Procedure (Sheet 3)

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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

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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

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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

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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
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