SERVICE BULLETIN TITLE AIR CONDITIONING - R134A AIR CONDITIONER SYSTEM INSTALLATION FOR AIRPLANES EQUIPPED WITH G1000 AND 867 SHP ENGINE

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1 TITLE AIR CONDITIONING - R134A AIR CONDITIONER SYSTEM INSTALLATION FOR AIRPLANES EQUIPPED WITH G1000 AND 867 SHP ENGINE EFFECTIVITY DESCRIPTION MODEL 208B SERIAL NUMBERS 208B5000 and On To provide parts and instructions to install the R134A Air Conditioner System on airplanes equipped with G1000 Avionics and the 867 SHP Engine. COMPLIANCE OPTIONAL. This service bulletin can be accomplished at the discretion of the owner. A service bulletin published by Textron Aviation may be recorded as completed in an aircraft log only when the following requirements are satisfied: 1) The mechanic must complete all of the instructions in the service bulletin, including the intent therein. 2) The mechanic must correctly use and install all applicable parts supplied with the service bulletin kit. Only with written authorization from Textron Aviation can substitute parts or rebuilt parts be used to replace new parts. 3) The mechanic or airplane owner must use the technical data in the service bulletin only as approved and published. 4) The mechanic or airplane owner must apply the information in the service bulletin only to aircraft serial numbers identified in the Effectivity section of the bulletin. 5) The mechanic or airplane owner must use maintenance practices that are identified as acceptable standard practices in the aviation industry and governmental regulations. No individual or corporate organization other than Textron Aviation is authorized to make or apply any changes to a Textron Aviation-issued service bulletin, service letter, or flight manual supplement without prior written consent from Textron Aviation. Textron Aviation is not responsible for the quality of maintenance performed to comply with this document, unless the maintenance is accomplished at a Textron Aviation-owned Service Center. APPROVAL Textron Aviation received FAA approval for the technical data in this publication that changes the airplane type design. Textron Aviation received EASA approval for the technical data in this publication that changes the airplane type design. FLIGHT CREW OPERATIONS No Changes CONSUMABLE MATERIAL You must use the consumable materials that follow, or their equivalent, to complete this service bulletin. June 1, 2017 Page 1 of 59 Textron Aviation Customer Service, P.O. Box 7706, Wichita, KS 67277, U.S.A 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 2017

2 NAME NUMBER MANUFACTURER USE Sealant (6 oz Semkit) U Sealant (3.5 oz Semkit) Corrosion Resistant Primer Color Chem Film Treatment Adhesive (1 quart can) U K U U Textron Aviation Textron Aviation Parts Distribution 5800 East Pawnee PO Box 1521 Wichita, KS Textron Aviation Textron Aviation Parts Distribution 5800 East Pawnee PO Box 1521 Wichita, KS Textron Aviation Parts Distribution 7121 Southwest Boulevard Wichita, KS Textron Aviation Textron Aviation Parts Distribution 5800 East Pawnee PO Box 1521 Wichita, KS Textron Aviation Textron Aviation Parts Distribution 5800 East Pawnee PO Box 1521 Wichita, KS Sealant (2 oz tube) U Textron Aviation Textron Aviation Parts Distribution 5800 East Pawnee PO Box 1521 Wichita, KS Sealant U074031S Textron Aviation Textron Aviation Parts Distribution 5800 East Pawnee PO Box 1521 Wichita, KS Fay sealing To apply to doubler To apply to bare metal To apply to bare metal Various adhesive uses Air duct sealant Air duct sealant Flat Black Paint Enamel Available locally To paint substrate material REFERENCES Cessna Model 208/208B Maintenance Manual Cessna Model 208 Illustrated Parts Catalog Cessna Model SHP Garmin FAA Approved Airplane Flight Manual PUBLICATIONS AFFECTED None WEIGHT AND BALANCE INFORMATION MODEL 208B WEIGHT CHANGE ARM RESULTANT MOMENT MOMENT/ inches inch-pounds inch-pounds Page 2 June 1, 2017

3 ACCOMPLISHMENT INSTRUCTIONS NOTE: Read and understand these instructions before you begin the installation of the air conditioning system. 1. Prepare the airplane for maintenance. A. Make sure that the airplane is electrically grounded. B. Make sure that all switches are in the OFF/NORM position. C. Disconnect electrical power from the airplane. (1) Disconnect the airplane battery. (2) Disconnect external electrical power. D. 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. Put a tail stand in position under the tail of the airplane. 3. Remove and keep the following interior components and furnishings and hardware that attaches them. (Refer to applicable sections of the Model 208/208B Maintenance Manual and Illustrated Parts Catalog.) A. Crew seats. B. Passenger seats. C. Floor covering material. D. Pilot's and copilot's scuff plates and control column cover assemblies. E. The Left Substrate Forward Wall, if applicable. F. The trim actuator chain guard from the left side of the throttle quadrant pedestal assembly. G. All window trim panels and sidewall panels and the avionics cover assembly. H. The headliner from the windshield to the rear spar. Roll and stow the headliner at the rear spar area. I. The left, right, and center aft cabin wall assemblies. J. Floorboard access panels as necessary. K. The floorboard heater plenums between approximately FS and FS to get access for refrigerant hose routings. L. Remove the left side flexible heater duct under the floorboard for access to route refrigerant hoses. M. Existing overhead cockpit ventilation plenum assembly. As necessary, discard the flexible ducts from the main plenum assembly. N. The crew steps from the left and right side. O. The headliner from the aft partition upper wall. P. Remove the aft upper partition assembly. Q. All other components as necessary. 4. (Refer to Figure 7.) Install three S Circuit Breakers. A. Remove the circuit breaker panel assembly. (Refer to the Model 208/208B Maintenance Manual, Chapter 24, Electrical Distribution - Maintenance Practices.) NOTE: It is not necessary to disturb the pitot static system to remove the circuit breaker panel assembly. If the pitot system is disturbed the pitot static system test will have to be performed. (1) Keep all the attaching hardware. June 1, 2017 Page 3

4 B. Remove the circuit breaker guards, if installed. C. Remove the LED Panel. Discard the screws. (Refer to Model 208/208B Maintenance Manual, Chapter 33, Left Circuit Breaker Assembly LED Panels - Removal/Installation.) D. Remove and discard the 15-Amp circuit breakers at the Left Vent Blower (HC050) and Right Vent Blower (HC060) locations on the left circuit breaker panel. E. Cut off the terminals of the 14-gage wires that were connected to the 15-amp circuit breakers you discarded. F. Cap and stow these two 14-gage wires. G. Install the three S Circuit Breakers at the (HC049, HC050, HC060) locations in the circuit breaker panel. H. Remove the cap from the 2HC049-NJC011 (16) Wire. I. Install the Terminal to the 2HC049-NJC011 (16) wire at the HC049 circuit breaker. J. Connect the 2HC049-NJC011 (16) wire to the S (HC049) Circuit Breaker. K. Remove the cap from the 2HC050-EEJC005 (16) Wire. L. Install the Terminal to the 2HC050-EEJC005 (16) Wire next to the HC050 circuit breaker. M. Connect the 2HC050-EEJC005 (16) wire to the S (HC050) Circuit Breaker. N. Remove the cap from the 2HC060-*RJC005 (16) Wire. O. Install the Terminal on the 2HC060-*RJC005 (16) Wire located next to the S (HC060) Circuit Breaker. P. Connect the 2HC060-*RJC005 (16) Wire to the S (HC060) Circuit Breaker. 5. (Refer to Figure 7.) Install one S Circuit Breaker (HC039). A. Install the S Circuit Breaker in the circuit breaker panel at HC039. (Refer to the Model 208/208B Maintenance Manual, Chapter 24, Electrical Distribution - Maintenance Practices.) B. Remove the cap from the 2HC039-*SJC005 (20) Wire. C. Install the Terminal to the 2HC039-*SJC005 (20) Wire at the HC039 circuit breaker. D. Connect the 2HC039-*SJC005 (20) Wire to the S (HC039) Circuit Breaker. E. Install the kept LED Panel. (Refer to the Model 208/208B Maintenance Manual, Chapter 33, Left Circuit Breaker Panels- Removal/Installation.) F. Install the kept circuit breaker guards. G. Install the kept circuit breaker electrical panel assembly. (Refer to the Model 208/208B Maintenance Manual, Chapter 24, Electrical Distribution System - Maintenance Practices.) 6. (Refer to Figure 1, Sheet 7 through 21.) Install the refrigerant hose assemblies to the air conditioner components. (Refer to the Model 208/208B Maintenance Manual, Chapter 21, R134A Air Conditioning System - Maintenance Practices.) A. Cut the S Grommets to length and install around lightening holes as shown with EC1300LP Adhesive as shown. (Refer to the Model 208/208B Maintenance Manual Chapter 20, Adhesive and Solvent Bonding - Maintenance Practices.) B. Attach the hoses in place with clamps and tie straps as shown. Do not fully tighten tie straps until after a leak test has been completed when all components are installed. C. Add a drop of refrigerant oil to the threaded connections to assist in tightening. D. Keep the hose ends covered when routing to keep them from getting contaminated. Page 4 June 1, 2017

5 E. Do a visual inspection of all hoses after routing to make sure the connections are tight and that the hoses will not be chafed on any other structure or components. 7. Install the tailcone evaporator. A. (Refer to Figure 4, Detail A and Detail D.) Install the Aft Evaporator Assembly. (1) Measure and mark the upper attachment hole on the Plate. (2) Put the Plate on the left bulkhead. (3) Make sure that the notch in the Plate centers in the stringer on the left bulkhead. (4) Drill a Number 10 (0.193 inch-diameter) in the left bulkhead to match the lowest attachment hole in the Plate. (5) Drill the Number 10 (0.193 inch-diameter) hole through the hole location that was marked on the Plate and the left bulkhead. (6) Remove the Plate from the left bulkhead. (7) Deburr the holes that were drilled. (8) With the AN3-3A Bolts, temporarily assemble the F Duct Assembly to the Bracket, Bracket Assembly, and Attach Angle. (9) Install the above assembly into the airplane and locate the unit by installing one AN525-8R6 Screw in the lowest attachment hole in the Plate and aligning with the existing nutplate on the left bulkhead. NOTE: This fastener will be temporary, only to locate the unit. This hole will be used to also keep the aft partition in the airplane when the installation is complete. (10) Put the Bracket on the cabin skin and level the evaporator in place. (11) Match drill the 10 holes through the Bracket common to the tailcone sidewall skin. (a) (b) (c) Drill the holes that are accessible. Disassemble and attach the bracket with temporary sheet metal fasteners. Drill the remainder of the holes. (12) Match drill the eight holes through the Bracket common to the tailcone sidewall skin. (a) (b) (c) Drill the holes that are accessible. Disassemble and attach the bracket with temporary sheet metal fasteners. Drill the remainder of the holes. (13) Locate the two nutplate locations on the aft side of the left bulkhead to match the two upper fastener hole locations on the Plate. (14) Remove the Aft Evaporator Assembly and attach the Bracket and the Bracket Assembly to the structure with four MS20470AD4-4 Rivets. (15) Drill and install the two MS21069L3 Nutplates on the aft side of the bulkhead typical with the existing bulkhead nutplate. (16) Reinstall the Aft Evaporator Assembly with the third lowest hole. Install AN525-10R6 Screws through the top two holes in the Plate and bulkhead. Leave the lowest hole open to install the aft partition. (17) (Refer to Figure 4, Detail B and View B-B.) Drill a 0.81 diameter hole in the lower left tailcone skin for the Tube Assembly and install one MS Grommet. (18) Install the Tube Assembly from the Aft Evaporator Assembly to the drain hole and attach with a S Clamp on the evaporator. June 1, 2017 Page 5

6 (19) Make a 45 angle cut at the end of the tube where it is outside of the airplane. Make sure that the open hole on the scarf is aft. (20) (Refer to Figure 4, Detail B.) Find the stowed connector (PT002) and connect it to the aft evaporator assembly connector. (21) (Refer to Figure 1, Views JJ-JJ and KK-KK.) Attach the refrigerant hoses to the Aft Evaporator Assembly. B. Install the aft upper substrate wall. (1) (Refer to Figure 4, View A-A.) Pull back the insulating material from the top and bottom of the Substrate Assembly approximately one inch from the top edge and bottom edge of the panel to fit over the flange on the cross support panel and to clear the bulkhead. (2) Temporarily install the Upper Substrate Aft Wall Panel. Locate the substrate panel with the two holes in the bulkhead common to the left and right outboard upper return air grill cover screw holes. (3) Match drill the remaining Number 10 (0.193-inch diameter) holes in the substrate panel from the existing holes in the bulkhead. (4) Match drill the lower return air grill cover Number 10 (0.193-inch diameter) holes in the existing Cross Support Panel below the outboard return air ducts. (5) Remove the substrate panel. (6) With a rotary file, trim the Cross Support Panel to match the lower circular cutout of the left and right elbow duct holes in the substrate panel. Deburr the cutout and apply U Color Chem Film Treatment and K Corrosion Resistant Primer. (7) (Refer to Figure 4, Detail A.) Trim and fit the forward corner's points on the Duct Assembly to fit the aft upper substrate panel. (a) Trim the rectangular openings in the substrate panel to fit the wye duct. (8) (Refer to Figure 4, Detail A.) Temporarily install the Elbow Assembly (left) and Elbow Assembly (right) to the aft side of the aft upper substrate panel with three AN525-10R12 Screws until the adhesive drys. (9) Remove the three AN525-10R12 Screws. (10) (Refer to Figure 4, View A-A.) Locate and drill a Number 10 (0.193-inch diameter) hole and install the MS21047L3 Nutplate on the forward side of the Cross Support as shown. (11) Apply U Color Chem Film Treatment and K Corrosion Resistant Primer to all bare metal edges. (12) Mask and paint the interior of the outboard circular air duct openings in the substrate material with flat black to reduce visibility of the substrate material. (13) Reinstall the substrate panel with the elbow assemblies attached. (14) (Refer to Figure 4, Detail A.) Install the Duct Assembly to the aft side of the aft upper substrate panel with four each AN R16 Screws and S Washers. (15) Install the three flexible duct tubes from the evaporator to the return and supply ducts installed on the upper substrate panel. Install the F and two each F Ducts (cut to length) with four S S Clamps and two S S Clamps. (16) (Refer to Figure 4, Detail C.) Attach the return air duct from the upper substrate wall assembly to the Hanger with one each AN525-10R6 Screw, MS21044N3 Nut and MS21919DG58 Clamp. Attach the Hanger to the cross support panel with one AN525-10R6 Screw. (17) Install the fabric headliner and attach the lower edge in place along both sidewalls and the aft wall Cross Support Panel. Page 6 June 1, 2017

7 (18) Trim the two outboard circular openings in the fabric headliner material approximately inch smaller in diameter than the circular duct opening in the substrate panel assembly. (19) Split the fabric headliner from corner to corner at the two rectangular duct openings so that the fabric material can be folded out and glued onto the male extensions of the Duct Assembly. Trim the ends of the fabric to length and attach to the Duct with EC1300LP Adhesive. (Refer to the Model 208/208B Maintenance Manual, Chapter 20, Adhesive and Solvent Bonding - Maintenance Practices.) (20) (Refer to Figure 4, Detail A.) Install the Louver Assemblies on the (left) and (right) Duct Assemblies as shown. (21) Use a punch to locate the nutplates on the bulkhead through the headliner material. (22) Match drill four inch diameter holes through the forward mounting tabs on the duct assemblies. (23) Install the two (left) and (right) Duct Assemblies in the aft upper cabin area with four MS Screws. (24) Trim the aft end of the (left) and (right) Duct Assemblies to get edge distance on the mounting tabs on the forward end of the duct assemblies. (25) (Refer to Figure 4, Detail A and View C-C.) Install the Grill Assemblies with six AN525-10R12 Screws, four MS24694-S53 Screws, and two AN525-10R6 Screws at the upper outboard location with the wire pattern in position. Put the grills in a position to make sure that there is no direct view into the duct through the louver from a seated position. 8. (Refer to Figure 3.) Install the (right) (left) Wing Mounted Evaporator. A. Remove access panels 511AB and 611AB. B. Remove the courtesy lights from the wing. (Refer to the Model 208/208B Maintenance Manual, Chapter 33, Courtesy Lights - Maintenance Practices.) C. Remove and discard the Elbow Assembly and the hardware that attaches it to the left hand ventilation system. D. Remove and discard the 33E83-2 Blower Assembly. Keep the hardware that attaches it. (Refer to the Model 208 Illustrated Parts Catalog, Cabin Air Ventilation System.) E. Remove sealant, sound deadening material and fiberglass insulation material from the interior and exterior area where the duct penetrates the cabin. Keep the sound dampening material to use as a template. F. Remove and keep the TKS line and fitting, deice tubes, and the bulkhead fitting from the wing root rib if installed. Cover the tube openings to prevent contamination. G. (Refer to Figure 3, View C-C.) Install the Doubler. (1) Put the Doubler in position as shown and make a mark around it. (2) Remove rivets from the area where the Doubler will be installed. (3) Match drill from the root rib to the Doubler, and from the Doubler to the root rib. (4) Put the (left) or (right) Check Valve Assembly on the lower forward most hole of the doubler. June 1, 2017 Page 7

8 CAUTION: EXERCISE CAUTION WHEN DRILLING OUT THE RIVETS ON RIGHT SIDE BECAUSE OF ELECTRICAL WIRES IN THE AREA BEHIND THE ROW OF RIVETS. (5) Drill out the existing vertical row of rivets at approximately FS NOTE: Leave the lowest existing rivet in the vertical row because it will not be common to the doubler. (6) Match drill the existing holes from the cabin to the Doubler. (7) Match drill the deice bulkhead fitting penetration holes and the 3.55-inch diameter air return duct hole. (8) Measure and drill the two inch diameter refrigerant line bulkhead penetration holes. (9) Locate the (left) or (right) Check Valve Assembly on the doubler lower forward most hole. (a) (b) (c) Locate the duct assembly with the Number 10 (0.193-inch diameter) hole on the upper aft side of the duct assembly. Center the inside diameter of the duct assembly on the hole in the cabin with the louvers positioned vertically. Make sure the louvers are free to rotate full motion. (10) (Refer to Figure 3, View D-D.) Make sure the Duct Assembly is free to fit through the hole in the cabin and doubler. (11) Remove the Doubler and deburr holes, clean the mating surfaces, and apply U Color Chem Film Treatment to all bare edges. (12) Apply U074031S Sealant to the large end of the Duct Assembly on the outer diameter of the duct and install it in the cabin plenum with the small diameter end facing out. Rotate the unit until the smaller tube is located at the lowest point. (13) Apply U Sealant to the doubler and attach it to the airplane cabin skin with temporary sheet metal fasteners. The Duct Assembly should be rotated until it is centered in the opening. Temporarily keep its location centered in the opening by shimming with wooden shims (popsicle sticks or tongue depressors). (14) (Refer to Figure 3, View C-C.) Install the 29 MS20470AD4-4 Rivets common to the Doubler and the cabin skin. NOTE: It is permissible to use S Rivets (blind), or to install the rivets in either direction for ease of installation. H. Cut the P Dampening Material to match the kept material, and install it in same place as the removed dampening material. I. Install the insulation that you kept. J. Reinstall the TKS line and fitting (if installed), deice bulkhead fitting, and deice wing tubing through the existing hole in the cabin and cabin skin. K. (Refer to Figure 3, Detail A.) Install the (left) or (right) Check Valve Assembly and the Seal with four MS Screws through the cabin sidewall into the nutplates on the Duct Assembly (left) or Duct Assembly (right). L. (Refer to Figure 1, View L-L and M-M.) Install the refrigerant bulkhead fittings and hardware through the cabin sidewall. M. (Refer to Figure 3, Detail A.) Install the Grills with the MS Screws. Page 8 June 1, 2017

9 N. (Refer to Figure 3, Detail A, View A-A and Detail C.) Drill a 0.44-inch diameter hole and eight Number 40 (0.098-inch diameter) holes through the lower wing skin just aft of the large evaporator access hole in the lower wing surface. O. Install the Tube Assembly with eight MS20426AD3-4 Rivets. P. Use the ventilation fan motors as a drill template and match drill the two Number 10 (0.193-inch diameter) holes in the ( ) Duct Assembly. Q. Mount the ( ) Duct Assembly in the wing root rib area with the existing hardware from the ventilation fan installation that was removed. R. (Refer to Figure 3, Details A and B and Figure 6.) Find the stowed connectors (PR005 and PL005) and connect them to the vendor connectors on the evaporators. S. (Refer to Figure 3, View B-B.) Assemble the and Brackets to the evaporator as shown. T. Install the evaporator assembly in the wing root rib area and attach it to the ( ) Duct Assembly with existing hardware. U. Drill four Number 10 (0.193-inch diameter) holes in the structure as necessary. NOTE: The airplane may already have the Number 10 (0.193-inch) diameter holes, or have pilot holes that need to be drilled to Number 10 holes. V. Attach the (left) and (right) Brackets with four each AN3-4A Bolts, MS21044N3 Nut and NAS1149F0363P Washers. W. (Refer to Figure 3, Detail A.) Install the air supply and air return flexible ducts from the wing evaporator assembly to the cabin with F and F Hoses (cut to length) and two each S S and S S Clamps. X. Install the high pressure (supply) and low pressure (suction) refrigerant lines to the wing evaporator assembly with the AE Hose Assembly and the AE Hose Assembly to connect the unit to the cabin bulkhead fittings. Use a drop of refrigerant oil on the threaded connections prior to tightening. Y. Install the P Tube (cut to length) from the evaporator assembly to the Tube Assembly with two S Clamps. Z. Inspect the installation for secure fittings, fasteners, and hardware installation. AA. Install the removed Courtesy Light Assembly with kept hardware. (Refer to the Model 208/208B Maintenance Manual, Chapter 33, Courtesy Lights - Maintenance Practices.) AB. Install access panels 511AB and 611AB with the kept hardware. (Refer to the Model 208/208B Maintenance Manual, Chapter 6, Access Plates and Panels Identification - Description and Operation.) 9. (Refer to Figure 2, Detail A.) Lower cowling modification and receiver/dryer, compressor and condenser installation. A. Remove the nose landing gear fairing. B. Remove the upper and lower engine cowlings. (Refer to the Model 208/208B Maintenance Manual, Chapter 71, Engine Cowling and Nose Cap - Maintenance Practices.) C. Transfer the cowl prop rod, prop rod holder, latch restraints, and any other hardware from the existing cowling to the new Lower Cowl Assembly (left). Install a new Placard at the same location as the existing cowling. D. (Refer to Figure 6, Detail C.) Install a Placard at the position shown. E. Install a Placard at the position shown. F. Trim the new Lower Cowl Assembly to fit. June 1, 2017 Page 9

10 G. Discard the existing lower left cowling. H. Trim and bevel the forward and aft ends of the three longitudinal hat sections to clear the existing forward bulkhead and firewall assembly. Also trim around the drain petcocks and drain tubes. Trim as necessary at the centerline to fit the existing cowling assembly. Touch up bare metal surfaces with U Color Chem Film Treatment and as necessary. I. Reinstall the upper left cowling assembly. (Refer to the 208/208B Maintenance Manual, Chapter 71, Engine Cowling and Nose Cap - Maintenance Practices.) J. Hand fit the new Lower Cowl Assembly (left) and make sure it latches correctly with the upper left cowling assembly. K. Remove the Lower Cowl Assembly (left). L. Paint the Lower Cowl Assembly (left) to match the airplane. M. Remove the upper left cowling assembly. (Refer to the Model 208/208B Maintenance Manual, Chapter 71, Engine Cowling and Nose Cap - Maintenance Practices.) N. Get access to the aft left and right side of the engine firewall from the cabin interior through the floorboard access holes. O. Remove the pilot's and copilot's floorboard flexible heater duct from the heater control box. (1) Move the right side out of the area of the refrigerant hose penetration point. (2) Move the left side out of the area of the condenser bracket attachment point. P. If installed, remove the Cover from the lower right hand forward side of the firewall to get access to the refrigerant hose penetration points. Q. (Refer to Figure 1, View F-F.) Match drill, ream, or measure and drill and inch diameter holes in the firewall as applicable. Deburr the holes and apply U Color Chem Film Treatment and K Corrosion Resistant Primer to the bare metal. R. If necessary, cut two small vertical slits in the engine firewall blanket on the left and right sides. S. Pull the blanket from the firewall and attach the flap out of the way to work on the firewall. T. (Refer to Figure 1, Views A-A and B-B.) Install the 1936T100-9 Air Conditioner Receiver Dryer. (Refer to the Model 208/208B Maintenance Manual, Chapter 21, R134A Air Conditioning System - Maintenance Practices.) U. (Refer to Figure 2, View A-A.) Install the condenser bracket assembly on the left side of the firewall. (1) Drill out existing rivets in the firewall. (2) Install the with bolts and washers as shown. V. Reinstall the left and right heater ducts to the control box. W. (Refer to Figure 2, Details A, B and C.) Install the Condenser Coil. (Refer to the Model 208/208B Maintenance Manual, Chapter 21, R134A Air Conditioning System - Maintenance Practices.) X. (Refer to Figure 1, Detail C and Detail D.) Install the Air Conditioner Compressor and brackets. (Refer to the Model 208/208B Series Maintenance Manual, Chapter 21, R134A Air Conditioning System - Maintenance Practices.) Y. Remove the cover plate and gasket on the left aft side of the engine by removing the four bolts to get access to the air conditioner drive pad. Z. (Refer to Figure 1, View D-D and Figure 6, Sheet 3.) Install connector JN050 on the green wire that is attached to the compressor using a S Pin crimped to the end of the wire. (1) If there is an automotive-style connector attached to the green wire, cut it off, and install it in the connector using a S Pin crimped to the end of the wire. Page 10 June 1, 2017

11 AA. AB. (Refer to Figure 1, View D-D and Figure 6, Sheet 3) Find the stowed wire (1PN020-1PN050) in the convoluted tubing, attach the S Socket and install in the S Plug (PN050). Connect the S Plug (PN050) and the compressor connector (JN050). AC. (Refer to Figure 1, View B-B and Figure 6, Sheet 3.) Find the two stowed wires (1PN020-IPN050 and 11PI021-2PN020) in the convoluted tubing, attach the S Sockets, and install the stowed wires into the S Plug (PN020). AD. Connect PN020 and the pressure switch connector (JN020). AE. AF. (Refer to Figure 1, Detail C and Detail E.) Install the Compressor Drive Assembly. (Refer to the Model 208/208 Maintenance Manual Chapter 21, R134A Air Conditioning System - Maintenance Practices.) (Refer to Figure 2.) Attach the Lower Cowl Assembly (left). (1) Install the two sets of Air Conditioner Louvered Panels and with AN525-10R8 Screws. (Refer to the Model 208 Illustrated Parts Catalog, Chapter 71, Cowl Assembly - Lower LH.) (2) Stow the and Winter Panels for winter use only. (3) Install all removed cowl assemblies. (Refer to the Model 208/208B Maintenance Manual, Chapter 71, Cowling - Maintenance Practices.) (4) Install the nose landing gear fairing. 10. (Refer to Figure 5, Views A-A and B-B.) Install the overhead ducts. A. Drill out four CR Rivets and remove the air valve to get access to install the rivets for the (left) and (right) Bracket Assemblies. B. Match drill eight Number 30 (0.128-inch diameter) holes through the (left) and (right) Bracket Assemblies. C. Attach the (left) and (right) Bracket Assemblies with eight NAS1097AD4-4 Rivets. D. Install two Ducts from the main plenum assembly at the forward wing-to-fuselage carry-thru to the outlets. E. Attach the ducts in place with six MS Tie Straps. Seal the ducts to the main plenum and vents with RTV-102 Sealant at the main plenum. (Refer to the Model 208/208B Maintenance Manual, Chapter 20, Adhesive and Solvent Bonding - Maintenance Practices.) F. Install two AV Air Valves with eight MS Screws. 11. Remove maintenance warning tags and connect the airplane battery. 12. Do a leak check of the air conditioning system. (Refer to the Model 208/208B Maintenance Manual, Chapter 12, R134A Air Conditioning - Servicing.) 13. Charge the air conditioning system and add oil to the compressor. (Refer to the Model 208/208B Maintenance Manual, Chapter 12, R134A Air Conditioning - Servicing.) 14. Tighten all hoses in place with tie straps. 15. Start the engine. (Refer to the Model SHP Garmin G1000 Airplane Flight Manual.) 16. Do an air conditioning system operational test. (Refer to the Model 208/208B Maintenance Manual, Chapter 21, R134A Air Conditioning System - Maintenance Practices (PT6A-140)). 17. Operate the air conditioning system to make sure that cool air is coming out of all vents. 18. If TKS is installed, do a purge of all lines in the TKS system that you had to disconnect for access. (Refer to the Model 208/208B Maintenance Manual, Chapter 30, Ice and Rain Protection.) June 1, 2017 Page 11

12 19. Do a leak check and functional test of the TKS system. (Refer to the applicable sections of the Model 208/208B Maintenance Manual, Chapter 30, Ice and Rain Protection.) 20. Stop the engine. (Refer to the Model SHP Garmin G1000 Airplane Flight Manual.) 21. Reinstall the following components with the kept hardware. (Refer to applicable sections of the Model 208/208B Maintenance Manual and Illustrated Parts Catalog.) A. Crew seats. B. Passenger seats. C. Floor covering material. D. Pilot's and copilot's scuff plates and control column cover assemblies. E. The Left Substrate Forward Wall. F. The trim actuator chain guard from the left side of the throttle quadrant pedestal assembly. G. All window trim panels and sidewall panels and the avionics cover assembly. H. The Brace if removed from the left and right side of the upper wing-to-fuselage carry-thru area. I. The headliner from the rear spar to the windshield. J. The left, right, center and upper aft wall assemblies. K. The heater plenums and heater ducts. L. Floorboard access panels as necessary. M. The crew steps from the left and right side. N. All other components as necessary. 22. Make an entry in the airplane logbook stating this service bulletin has been installed. Page 12 June 1, 2017

13 Figure 1. Receiver/Dryer and Hose Routing Installation (Sheet 1) June 1, 2017 Page 13

14 Figure 1. Receiver/Dryer and Hose Routing Installation (Sheet 2) Page 14 June 1, 2017

15 Figure 1. Receiver/Dryer and Hose Routing Installation (Sheet 3) June 1, 2017 Page 15

16 Figure 1. Receiver/Dryer and Hose Routing Installation (Sheet 4) Page 16 June 1, 2017

17 Figure 1. Receiver/Dryer and Hose Routing Installation (Sheet 5) June 1, 2017 Page 17

18 Figure 1. Receiver/Dryer and Hose Routing Installation (Sheet 6) Page 18 June 1, 2017

19 Figure 1. Receiver/Dryer and Hose Routing Installation (Sheet 7) June 1, 2017 Page 19

20 Figure 1. Receiver/Dryer and Hose Routing Installation (Sheet 8) Page 20 June 1, 2017

21 Figure 1. Receiver/Dryer and Hose Routing Installation (Sheet 9) June 1, 2017 Page 21

22 Figure 1. Receiver/Dryer and Hose Routing Installation (Sheet 10) Page 22 June 1, 2017

23 Figure 1. Receiver/Dryer and Hose Routing Installation (Sheet 11) June 1, 2017 Page 23

24 Figure 1. Receiver/Dryer and Hose Routing Installation (Sheet 12) Page 24 June 1, 2017

25 Figure 1. Receiver/Dryer and Hose Routing Installation (Sheet 13) June 1, 2017 Page 25

26 Figure 1. Receiver/Dryer and Hose Routing Installation (Sheet 14) Page 26 June 1, 2017

27 Figure 1. Receiver/Dryer and Hose Routing Installation (Sheet 15) June 1, 2017 Page 27

28 Figure 1. Receiver/Dryer and Hose Routing Installation (Sheet 16) Page 28 June 1, 2017

29 Figure 1. Receiver/Dryer and Hose Routing Installation (Sheet 17) June 1, 2017 Page 29

30 Figure 1. Receiver/Dryer and Hose Routing Installation (Sheet 18) Page 30 June 1, 2017

31 Figure 1. Receiver/Dryer and Hose Routing Installation (Sheet 19) June 1, 2017 Page 31

32 Figure 1. Receiver/Dryer and Hose Routing Installation (Sheet 20) Page 32 June 1, 2017

33 Figure 1. Receiver/Dryer and Hose Routing Installation (Sheet 21) June 1, 2017 Page 33

34 Figure 1. Receiver/Dryer and Hose Routing Installation (Sheet 22) Page 34 June 1, 2017

35 Figure 1. Receiver/Dryer and Hose Routing Installation (Sheet 23) June 1, 2017 Page 35

36 Figure 2. Condenser Installation (Sheet 1) Page 36 June 1, 2017

37 Figure 2. Condenser Installation (Sheet 2) June 1, 2017 Page 37

38 Figure 3. Wing Evaporator Installation (Sheet 1) Page 38 June 1, 2017

39 Figure 3. Wing Evaporator Installation (Sheet 2) June 1, 2017 Page 39

40 Figure 3. Wing Evaporator Installation (Sheet 3) Page 40 June 1, 2017

41 Figure 3. Wing Evaporator Installation (Sheet 4) June 1, 2017 Page 41

42 Figure 4. Aft Evaporator Installation (Sheet 1) Page 42 June 1, 2017

43 Figure 4. Aft Evaporator Installation (Sheet 2) June 1, 2017 Page 43

44 Figure 4. Aft Evaporator Installation (Sheet 3) Page 44 June 1, 2017

45 Figure 4. Aft Evaporator Installation (Sheet 4) June 1, 2017 Page 45

46 Figure 4. Aft Evaporator Installation (Sheet 5) Page 46 June 1, 2017

47 Figure 4. Aft Evaporator Installation (Sheet 6) June 1, 2017 Page 47

48 Figure 5. Air Outlet Installation (Sheet 1) Page 48 June 1, 2017

49 Figure 6. Instrument Panel Switch and Placard Installation (Sheet 1) June 1, 2017 Page 49

50 Figure 6. Instrument Panel Switch and Placard Installation (Sheet 2) Page 50 June 1, 2017

51 Figure 6. Instrument Panel Switch and Placard Installation (Sheet 3) June 1, 2017 Page 51

52 Figure 7. Circuit Breaker Installation (Sheet 1) Page 52 June 1, 2017

53 MATERIAL INFORMATION Order the kit below to install this modification. NEW P/N QUAN- TITY 1 KEY WORD OLD P/N INSTRUCTIONS/ DISPOSITION Kit, consisting of the following parts: AE Hose Assembly AE Hose Assembly AE Hose Assembly AE Hose Assembly AE Hose Assembly AE Hose Assembly AE Hose Assembly AE Hose Assembly AE Hose Assembly AE Hose Assembly AE Hose Assembly AE Hose Assembly AE Hose Assembly AE Hose Assembly AE Hose Assembly AE Hose Assembly AN3-3A 2 Bolt AN3-4A 32 Bolt AN3-5A 8 Bolt AN3-6A 3 Bolt AN4C12A 3 Bolt AN4C5A 4 Bolt AN4C6A 3 Bolt AN4-16A 1 Bolt AN4-17A 1 Bolt AN4-41A 1 Bolt AN525-10R6 6 Screw AN525-10R7 8 Screw AN525-10R12 10 Screw June 1, 2017 Page 53

54 NEW P/N QUAN- TITY AN R16 4 Screw AN6C10A 1 Bolt AN6C12A 4 Bolt AN6C16A 1 Bolt AN815-8D 1 Nut AN818-12D 1 Nut AN821-8D 2 Elbow AN824-6D 1 Tee AN832-8J 1 Union AN832-12J 1 Union AN838-4D 1 Elbow AN833-8D 4 Elbow AN919-2D 2 Reducer AN Reducer AN919-12D 2 Reducer AN919-19D 4 Reducer AN924-12J 1 Nut AN924-4D 1 Nut AN924-8D 4 Nut AN924-8J 1 Nut AS5174D Union AV Air Valve B C 12 inches Sleeving CM3687D Tee CM3687D Tee CM3687D Tee C B 4 Clip CR Rivet CR Rivet F feet Duct F feet Duct F feet Duct F feet Duct F feet Duct F V-Belt KEY WORD OLD P/N INSTRUCTIONS/ DISPOSITION Page 54 June 1, 2017

55 NEW P/N QUAN- TITY S feet Grommet KEY WORD OLD P/N INSTRUCTIONS/ DISPOSITION MS20426AD Rivet None MS20427M4-5 2 Rivet None MS20470AD3-4 2 Rivet None MS20470AD Rivet None MS21042L4 2 Nut None MS21042L6 6 Nut None MS21044N3 13 Nut None MS21047L3 1 Nutplate None MS21051L08 4 Nutplate None MS21069L3 2 Nutplate None MS21083N3 8 Nut None MS21251B5S 1 Locking Turnbuckle Body None MS RS 1 Clevis End Turnbuckle None MS LL 1 Eye End Turnbuckle MS Clip MS21919DG18 1 Clamp MS21919DG58 1 Clamp MS24694-S53 4 Screw MS24694-S55 4 Screw None MS Retainer None MS O-Ring MS Strap MS Screw MS Screw MS Screw MS Screw MS Grommet NAS1097AD Rivet None NAS1149C0432R 12 Washer NAS1149C0663R 6 Washer NAS1149D0363K 40 Washer NAS1149D0463K 2 Washer NAS1149F0363P 8 Washer NAS1149F0432P 1 Washer June 1, 2017 Page 55

56 NEW P/N QUAN- TITY NAS1149F0463P 1 Washer NAS1149F1290P 10 Washer NAS1149F1790P 2 Washer NAS1564D Reducer NAS43DD Spacer NAS43DD4-15FC 1 Spacer NAS43DD4-7FC 1 Spacer NAS557-18A 1 Grommet NAS557-24A 1 Grommet P inches Tube P inches Tube S1021Z Screw S Grommet S Circuit Breaker S Circuit Breaker S Washer S Clamp S Pin S Socket S Cap Housing S Cap Housing S Anchor S S 4 Clamp S S 8 Clamp S S 4 Clamp S Mount S Plug S Tie Strap S Clamp S Hose S Insulation Tube S Tee S3278A3 1 O-Ring S3278A6 1 O-Ring S Gasket KEY WORD OLD P/N INSTRUCTIONS/ DISPOSITION Page 56 June 1, 2017

57 NEW P/N QUAN- TITY S Washer S O-Ring S O-Ring Aft Evaporator Assembly Condenser Coil KEY WORD OLD P/N INSTRUCTIONS/ DISPOSITION Right Evaporator Module Assembly Left Evaporator Module Assembly 1936T Receiver Dryer Valve Valve Bushing Fitting Bushing S O-Ring O-Ring Valve Valve Tube Reducer Duct Assembly Duct Assembly Duct Assembly Left Duct Assembly Right Duct Assembly Duct Assembly Duct Assembly Bracket Bracket Bracket Bracket Assembly Attach Angle Doubler Tube Assembly Support Bracket Assembly June 1, 2017 Page 57

58 NEW P/N QUAN- TITY Clamp Bolt Inlet Duct Assembly Winter Panel KEY WORD OLD P/N INSTRUCTIONS/ DISPOSITION Winter Panel None Left Check Valve Assembly Right Check Valve Assembly Seal Duct Assembly Duct Assembly Grill Assembly Left Elbow Assembly Right Elbow Assembly Hangar Forward Seal Assembly Aft Seal Assembly Outboard Seal Assembly Inboard Seal Assembly Bracket Assembly Pressure Switch Assembly Clamp Weld Assembly Clamp Weld Assembly Support Tensioner Support Shim Compressor Mount Assembly Compressor Drive Assembly Forward Compressor Mount Compressor Assembly Placard Placard-867 SHP Engine Louver Assembly Bracket Assembly Bracket Assembly Cover Assembly Trim Page 58 June 1, 2017

59 NEW P/N QUAN- TITY Substrate Assembly Cowl Assembly KEY WORD OLD P/N INSTRUCTIONS/ DISPOSITION Continuity Switches Wire Bundle Assembly Duct-Pilot/Copilot 1 Instructions Based on availability and lead times, parts may require advanced scheduling. June 1, 2017 Page 59

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61 OWNER ADVISORY TITLE NAVIGATION - R134A AIR CONDITIONER SYSTEM INSTALLATION FOR AIRPLANES EQUIPPED WITH G1000 AND 867 SHP ENGINE TO: Cessna Aircraft Owner REASON This owner advisory is to inform you that has been issued. provides parts and instructions to install the R134A Air Conditioner System on airplanes equipped with G1000 Avionics and the 867 SHP Engine. COMPLIANCE OPTIONAL. This service bulletin can be accomplished at the discretion of the owner. LABOR HOURS WORK PHASE Modification MAN-HOURS As Required MATERIAL AVAILABILITY PART NUMBER AVAILABILITY COST * * * Please contact Textron Aviation Parts Distribution for current cost and availability of parts listed in this service document. Phone at (Domestic) or (International). Send to: parts@txtav.com. Based on availability and lead times, parts may require advanced scheduling. WARRANTY Not Applicable Please contact a Textron Aviation Authorized Service Facility for detailed information and arrange to have Textron Aviation service bulletin 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 Access" link at to register. June 1, 2017 Page 1 of 1 Textron Aviation Customer Service, P.O. Box 7706, Wichita, KS 67277, U.S.A 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 2017

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