MODIFICATION KIT. 400 (LC41-550FG) 41034, thru 41650, thru 41580, thru 41800,

Transcription

1 Single Engine MODIFICATION KIT MK TITLE WAAS UPGRADE FOR GARMIN EQUIPPED AIRPLANES EFFECTIVITY Model Serial Numbers 350 (LC42-550FG) thru 42558, thru 42569, (LC41-550FG) 41034, thru 41650, thru 41580, thru 41800, DESCRIPTION This modification kit provides instructions and parts to install Wide Area Augmentation System (WAAS) capability. APPROVAL FAA approval has been obtained on all technical data in this Modification Kit that affects type design. REFERENCE SB CHANGE IN WEIGHT AND BALANCE MODEL: 350, 400 WEIGHT CHANGE: Negligible Page 1 of 43 To obtain satisfactory results, procedures specified in this publication must be accomplished in accordance with accepted methods and prevailing government regulations. Cessna Aircraft Company cannot be responsible for the quality of work performed in accomplishing the requirements of this publication. Cessna Aircraft Company, Customer Service, P.O. Box 7706, Wichita, Kansas 67277, U.S.A. (316) Facsimile (316) COPYRIGHT 2009

2 MATERIAL INFORMATION MK contains the parts required to accomplish this Modification Kit. PART NUMBER DESCRIPTION QUANTITY MK Kit, consisting of the following 1 parts: Antenna, GA 35, GPS/WAAS, Garmin Antenna, GA 37, GPS/WAAS + XM, GARMIN 1 LB Rev OR (use as supplied) LB Rev A Antenna Wedge Block, WAAS., Machined OR (use as supplied) Antenna Wedge Block, WAAS, Molded Garmin GDU 1044 Multi Function Display with AFCS, VNV Garmin GIA 63W Integrated Avionics Unit, WAAS 1 2 TY242M Wire Tie, Metal Insert 30 TM1A-C Cable Tie Mount, Small V86/1EA Mark 5 Mix Nozzles 1 AN970-3 Washer, Large Area #10 1 MS21083-C08 Nut, Self Locking, Low Height, NAS1149FN832P Washer, #6 1 MS Screw, Machine HD, 8-32 x 1.5 inch 1 MS Screw, Machine HD, 8-32 x 1.0 inch 1 LB Rev Braid Assembly, Exterior WAAS Antenna A197 Screw, 82deg Oval HD, Recessed 8-32 x 3/4 Inch 4 TMS130-1 Straight TNC connector, TFLX TMR Degree, TNC connector, TFLX AMP Straight TNC connector 1 MK Page 2

3 PART NUMBER DESCRIPTION QUANTITY AMP 90 TNC connector 1 Mixed Filler 6.4 Mixed Dry Fillers 1 MS21083-C3 Nut, Self Locking, Non Metallic, NAS1149CO363R Washer, Cres, #10 4 MS24893-C276 Screw, Machine, flat head, Cres, x In addition to MK , the following materials are necessary: NAME NUMBER QUANTITY MANUFACTURER USE Silicone Caulk, White MIL-A Jeffco Resin System 5 fl oz RTV 162 (White) or equivalent Jeffco Pack 5 1 ea 1 ea Cessna Aircraft Company Cessna Parts Distribution 5800 East Pawnee PO Box1521 Wichita, KS Cessna Aircraft Company Cessna Parts Distribution 5800 East Pawnee PO Box1521 Wichita, KS To install antenna To install antenna Stabilant 22 Electrical Contact Enhancer (0.5 ml) Alclad Aluminum Devcon Plastic Welder II, 47 ml Dev Pak MLS 2024-T3 or S V86 1 ea As necessary 2 ea Cessna Aircraft Company Cessna Parts Distribution 5800 East Pawnee PO Box1521 Wichita, KS Purchase locally or purchase from: Cessna Aircraft Company Cessna Parts Distribution 5800 East Pawnee PO Box1521 Wichita, KS Cessna Aircraft Company Cessna Parts Distribution 5800 East Pawnee PO Box1521 Wichita, KS To install antenna To make antenna template To install antenna MK Page 3

4 NAME NUMBER QUANTITY MANUFACTURER USE Application Gun (for 47/50 ml Devcon cartridges) 14280V86 (or equivalent) 1 Cessna Aircraft Company Cessna Parts Distribution 5800 East Pawnee PO Box1521 Wichita, KS To install antenna Plastic Mixing Cup Evercoat E -cup (1 quart size) (or equivalent) 1 Procure locally To Mix Filler Isopropyl Alcohol TT-I-735 Grade B (1 quart size) (or equivalent) As required Procure locally To clean surfaces 3 M Masking Tape 3 M Masking Tape (1 inch wide) (or equivalent) As required Procure locally To Mask off work area Sandpaper Grit As required Procure locally To remove paint REFERENCE DOCUMENTS The following documents (or latest revisions) are available from Cessna: Document Number Revision Description RC M Cessna 400 Airplane Maintenance Manual RB L Cessna 350 Airplane Maintenance Manual SB Cessna Service Bulletin G1000 System Software Upgrade to GDU 8.10 SB Cessna Service Bulletin Pilots Operating Handbook Revisions The following documents (or latest revisions) are available from the Garmin Website: Document Number Revision Description E Garmin G1000 System Maintenance Manual, Cessna 350, G1000 v8.xx Software Loading and Post Installation Checkout, Cessna 350,400 MK Page 4

5 ACCOMPLISHMENT INSTRUCTIONS NOTE: Wiring Changes. There are no associated changes required to the avionics wiring or configuration of the existing installation, except for the GPS antennas and coax cables addressed later. The GIA 63W units and the GDU 1044 MFD are installed as slide in replacements for the original units. 1. Revise the POH as follows: If not previously accomplished, refer to Cessna Service Bulletin SB Pilots Operating Handbook Revisions and update the Pilot s Operating Handbook (POH) to the latest POH revision. 2. Determine the installed software level and perform a pre-functional operational test of the G1000 Avionics as follows: NOTE: The following operational checks should be accomplished with the airplane outside the hangar and in an unobstructed area to ensure reliable radio and GPS satellite communication. A. Determine the installed software part number as follows: 1. Make sure that all necessary circuit breakers are pushed in for normal mode startup of the Garmin G1000 system. 2. Connect a 28-volt ground power unit to the external power receptacle and turn on the ground power unit. 3. On the overhead console, put the LEFT and RIGHT BATTERY MASTER, CROSSTIE, and AVIONICS MASTER switches to the ON position and allow the system to power up. 4. Using the large FMS knob on the MFD, highlight the AUX group page, then rotate the small inner FMS knob to view the AUX-SYSTEM STATUS page. 5. Record the System Software Version which is viewable at the top right corner of the airframe field on the MFD. Determine whether Service Bulletin SB has been complied with by looking at the airplane logbooks and maintenance entries. 6. If is not displayed as the System Software Version, then SB G1000 System Software Upgrade to GDU 8.10 Version (or later software revision) has not been complied with, proceed as follows: a. If SB has not been complied with, contact Cessna Customer Service Telephone , Fax and obtain Service Bulletin SB G1000 System Software Upgrade to GDU 8.10 Version (or later approved software revision). SB must be complied with later in this document. 7. If is displayed as the system software version, then SB may have been complied with. Proceed as follows: MK Page 5

6 a. If SB has been complied with, locate the software installation CD ROM 350GSW00-00 (Model 350) or 400GSW00-00 (Model 400) that was required in the referenced Service Bulletin. The CD-ROM should be located in the blue sleeve at the back of the Pilot s Operating Handbook. The CD will be used later in this document when configuring the software for WAAS. B. Do basic pre-functional operational checks of the following functions (Refer to Model 350/400 Airplane Maintenance Manual as applicable, or the Garmin G1000 System Line Maintenance Manual for the Cessna 350 / 400 for more information): NOTE: These basic operational checks are to ensure that there are no pre-existing conditions or issues prior to installation of G1000 WAAS. A failure of any Line Replacement Unit (LRU) or system indication should be troubleshot and repaired prior to continuing with this installation. 1. Verify the Line Replacement Units (LRUs) status as follows: a. With the system power on, turn the large FMS knob on the MFD to go to the AUX group page. b. Turn the small FMS knob on the MFD to go to the AUX-SYSTEM STATUS page. c. Push the LRU soft key, then press the small FMS knob to activate the cursor in the LRU INFO field. d. Scroll down and verify that there is a green check in the STATUS column for each LRU item. If any of the LRU items shows a red X in the STATUS column, you must first correct the cause of the red X condition before continuing with this Service Document. 2. Communication Radios, COM 1 and COM 2: Tune the COM 1 Radio to a local VHF COM frequency, select COM 1 on the GMA 1347 Audio panel. Verify the receiver output produces a clear and understandable audio output. Verify the transmitter functions properly by contacting another station and getting a report of reliable communications. Repeat the procedure for the COM 2 Radio. 3. NAV 1 and NAV 2, NAV Audio: Tune an active VOR or ILS frequency on the NAV 1 and NAV 2 Navigation Receivers. Press the CDI button on the PFD to select the VOR 1, then turn the CRS knob to center the CDI indication on the HSI on a selected course. Verify that there are no navigation flags on the HSI (CDI needle will disappear when there is an active flag). Select the NAV 1 button on the GMA 1347 Audio Panel and listen for the presence of the VOR audio and ident. Repeat the procedure for the NAV 2 receiver. 4. GPS operation: With the airplane outside and in view of the satellites, verify that the GPS system is properly receiving and that the G1000 system has received a proper position fix. Turn the large FMS knob on the MFD to the AUX group page, then turn the small FMS knob until reaching the AUX 1 page. Press the GPS 1 button and make sure that the GPS 1 is properly receiving 5-8 satellites. Press the GPS 2 button and verify that the GPS 2 is also properly receiving the satellites. MK Page 6

7 5. GFC 700 Autopilot System (AFCS) check: a. After the G1000 system has been powered up, verify that there are no Autopilot Error (AFCS) messages. b. With the G1000 system actively receiving satellites, press the AP and FD button on the GDU 1042 MFD. Verify that the autopilot engages in the Pitch and Roll modes. c. Press the HDG button on the MFD and turn the HDG knob to move the Heading Bug to the left and right of the airplane heading. The autopilot roll mode should follow. d. Press the VS button on the MFD, then press the NOSE UP and NOSE DOWN button on the MFD. Verify that the pitch movement of the stick follows the operation of the buttons. e. Press the AP DISC button on the control stick and verify that the autopilot disconnects and that an aural tone is heard. 6. GDL 69A XM Weather / Datalink: Verify that the XM Datalink system is properly receiving both XM Weather and Entertainment Audio. a. Bring the airplane to an area on the ramp with as few obstacles to lineof-sight viewing of the southern horizon as possible. Turn the large FMS knob on the MFD until reaching the AUX group of pages. Then turn the small FMS knob until reaching the AUX-XM Information page. Press the INFO key and the page will display the 8-character XM DATA RADIO ID and the 8-Character AUDIO RADIO ID numbers. b. If the broadcast receiver is working and the airplane is in view of at least one XM satellite, the Data and Audio Signal Strength should be Good or Marginal. If the signal strength is reported as Weak or None, reposition the airplane as required. Check the signal strength of both the Data Signal and Audio Signal. 7. Transponder operation: Verify that there are no failure messages associated with the operation of the GTX 33 Transponder. 8. Avidyne TAS620 Traffic System Interface Check: a. Move the airplane outside and verify that the traffic system displays local traffic. The Avidyne traffic systems should show traffic in the vicinity of the airport and in the appropriate quadrants on the MFD and PFD displays. Refer to the Pilots Operating Handbook to determine proper operation of the Avidyne TAS620 traffic systems. b. Make sure that local traffic is displayed on the Traffic pages of both the MFD and the inset page of the PFD. 9. Oxygen system (Model 400 only): Check the display on the MFD Engine page by pressing the SYSTEM soft-key and the OXYGEN soft key on the engine page of the MFD. When the OXYGEN button is pressed, the manifold on the oxygen bottle should be heard to engage. Press the OXYGEN soft-key again to disengage the oxygen flow. MK Page 7

8 10. Carbon Monoxide Detector: Verify that there are no failure messages associated with the operation of the Carbon Monoxide Detector. 11. G1000 System and Airframe Error Messages: Test to make sure that there are no failure messages displayed on the G1000 Avionics system. Some initial startup messages will inherently appear and must be acknowledged. Clear all initial messages before determining the validity of persistent displayed error messages. 3. Disassembly. Perform the following disassembly steps per the detailed instructions contained in the applicable Cessna 350 or 400 Airplane Maintenance Manual (AMM). A. Install a suitable tail-stand to support the airplane tail during maintenance. B. Remove the baggage netting that divides the baggage compartment from the aft baggage shelf. C. Remove the cushion from the aft bulkhead and remove the padded carpeting in the aft baggage shelf. D. Prepare the airplane for maintenance and make sure that all switches are in the OFF/NORM position: 1. Electrically ground the airplane. 2. Disconnect electrical power from the airplane. 3. Disconnect external electrical power 4. Disconnect the airplane batteries. 5. Attach maintenance warning tags to the batteries and external power receptacle that have DO NOT CONNECT ELECTRICAL POWER MAINTENANCE IN PROGRESS written on them. E. Remove and store the pins holding the rear seat backs to the rear seat back bar. Store the pins in a secure location. Remove the seat back bar from the airplane. F. Remove the rear seat back and the bottom seat cushions from the rear seat positions and store them in a location where they will not be damaged. G. Remove the copilot seat from the airplane. Store in a secure location. H. Remove the right door tread and hardware. I. Remove the aft interior upholstery panel along the right side of the airplane near the passenger s seats and remove the elevator push tube cover along the right side of the baggage compartment. J. Remove the retaining hardware from the forward overhead console assembly. Lower the overhead just enough to gain suitable access to the aft end of the console and support it with wire ties to the top of the fuselage. MK Page 8

9 NOTE: It is not necessary to disconnect the oxygen hose and/or wiring harnesses when lowering the overhead console. K. Remove the aft overhead console from over the baggage compartment. NOTE: Do not remove the overhead air-conditioning duct. L. Remove the aft door surround upholstery panel around the right passenger door frame and right aft passenger window. M. If installed, remove the air-conditioning evaporator cover located in the baggage compartment area. N. Remove the black pitch servo access panel located on the floor of the aft baggage shelf. O. Remove the ELT access panel located on the aft bulkhead. P. Disconnect the BNC and remote switch connectors on the ELT. Remove the ELT from the mount behind the baggage bulkhead. Turn the ELT to the OFF position or leave the ELT in the ARM position if there is no OFF position. Q. Unbolt and remove the ELT support bracket from the antenna shelf at the aft end of the airplane. Retain the hardware. 4. (Figure 11.) Remove the Garmin GDU 1042 Multi-Function Display (MFD) and Garmin GIA 63 units as follows: NOTE: The existing Garmin GDU 1042 Multi-Function Display will be replaced with a new Garmin GDU 1044 Multi-Function Display, which has an added VNAV button in the AFCS control section. The VNAV button is required as part of the WAAS upgrade in order to allow the full vertical navigation function of the GFC 700 autopilot to operate during an LPV type approach. Both of the Garmin GIA 63 Integrated Avionics Units require replacement with GIA 63W WAAS approved Integrated Avionics Units. A. (Figure 11.) Using a 3/32 inch Allen-hex handle, loosen the 4 locking cam-locks on the 4 corners of the Garmin GDU 1042 MFD. Remove the existing GDU 1042 MFD from the right side of the instrument panel. Use the quick release tabs and disconnect the DSUB connector on the back. Be sure to record the old serial numbers and remove all data cards from the equipment. B. (Figure 11.) Remove both the #1 and #2 GIA 63 Integrated Avionics units from their trays in the radio rack. The GIA units are the large LRU units that are mounted directly behind where the GDU 1042 MFD was mounted on the right side of the instrument panel. Use a #2 Phillips screwdriver to release the bail. Raise the bails and remove each unit from the airplane. Be sure to record the old serial numbers. C. Return the original GDU 1042 display and both the original GIA 63 Integrated Avionics Units to Cessna for a core credit. 5. Remove the original GPS antennas and the GPS #2 BNC Connector as follows: A. Disconnect the GPS 1 and GPS 2 coax cables from the two Garmin GA56 GPS antennas. MK Page 9

10 NOTE: The GA 56 antennas are the two outboard antennas on the antenna shelf, behind the aft baggage bulkhead, aft of the ELT mount. B. If not already identified, label both the GPS 1 and GPS 2 coax cables. NOTE: On a standard installation, the GPS 1 antenna will be mounted on the right side of the antenna shelf, and the GPS 2 antenna will be mounted on the left side. C. (Figure 11.) Use an ohmmeter and check the end-to-end continuity of the center conductor of each coax cable from the antenna connector end to the GPS RF connector on the GIA 63 LRU trays. Verify that the GPS 1 coax cable is correctly identified, that the GPS 1 coax cable is actually going to the GPS 1 radio tray, and that the GPS 2 coax cable is actually going to the GPS 2 radio tray. NOTE: (Figure 11.) The word GPS is stamped near the RF connectors on the inside of each GIA 63 radio tray, to help locate the proper coax connectors for the continuity check. The #1 GIA 63 is the position on the Left (inboard), and the #2 GIA 63 unit is the tray position on the Right (outboard) behind where the MFD was located. D. Cut the BNC connector off the antenna end of the GPS 1 coax cable. Pull the antenna end of the GPS 1 coax cable out of the wire bundle along the right side of the fuselage, only until reaching the point just below the right aft door frame. Let the end of this cable that was pulled out of the harness hang loose for the moment. Leave the remaining section of this coax cable that goes to the GIA 63 #1 radio tray in place. E. Leave the GPS 2 coax cable in place. Cut the BNC connector off the antenna end of the GPS 2 coax cable as close to the connector as possible. F. There are two Garmin GA 56 antennas located on the aft antenna shelf just aft of where the ELT was mounted. Remove both of the Garmin GA 56 GPS antennas and all associated hardware from the antenna shelf. Discard the hardware. 6. Remove the XM antenna as follows: A. Disconnect the XM Datalink coaxial cable from the Garmin GA 55 XM Antenna on the antenna shelf. Label this coax as XM DATALINK. Leave the XM coax cable in place. Do not cut the connector off the end of this coax. NOTE: The GA 55 XM antenna is centered between the GA 56 GPS antennas that were located on the same shelf. B. Remove the GA 55 XM antenna and associated hardware from the aft antenna shelf. Discard the hardware. 7. (Figures 5, 6 and 7.) Modify the Antenna Shelf as follows: A. (Figure 6.) Create a template out of a piece of aluminum sheet as shown. NOTE: The template will be used as the guide for drilling the new holes in the antenna shelf. The elongated hole shown in Figure 6 will not be elongated in the drill template. See note on Figure 6. NOTE: Make sure that holes in the drill template match the hole locations on the GA 37 Antenna. MK Page 10

11 B. (Figures 5 and 6.) Put the drill template on the antenna shelf over the original center GA 55 XM antenna mount location. Position the drill template to best align the aft mounting holes as closely as possible. C. (Figure 5 and 6.) Temporarily tape the drill template in place. D. Using the drill template, drill the four mounting holes using a inch diameter drill bit. NOTE: Due to the restricted access at the antenna shelf, a compact right angle drill head, or equivalent may be necessary to drill the holes on the antenna shelf. E. Using the drill template, drill the two large holes for the two coax connectors using a inch diameter drill bit. Alternatively, these two large holes may be made using a small tungsten carbide rotary grinding tool attached to a rotary type hand-held tool or equivalent. F. Remove the drill template. G. (Figure 6.) After the two holes have been drilled, the inch diameter hole on the forward end of the elongated hole pattern must be blended with the original aft large hole on the shelf. Using a marking pen, draw lines connecting the two holes as shown, to create one elongated hole. H. (Figure 6.) Use a rotary type hand-held or equivalent tool and carefully remove the material along the lines between the new and original large holes. I. Vacuum out any debris from the antenna shelf and the surrounding area, including the belly of the airplane. 8. Mount the GA 37 Antenna and install the GPS 1 TNC Connector as follows: A. (Figure 7) Mount the GA 37 ( ) antenna on the antenna shelf as shown. NOTE: Install the GA 37 antenna so that the blue banded TNC connector is located forward when mounted. NOTE: Two different types of coax cable may be installed. Either RG-400 or TFLX cable coax cable may be in the airplane. The RG 400 is a larger gold colored coax cable, while the TFLX is a small diameter green coax cable. Both types of coax cable are acceptable for this installation. The replacement connector ends for both types of coax cables are supplied with this kit. Discard the two connectors that are not used. The part numbers for the TFLX connector ends are identified in parentheses in the following steps. B. Locate the antenna ends of the existing XM and GPS 2 coax cables. Cut off any excess length from the cables. Make sure the labels remain attached to the coax. C. (Figures 2 and 4A.) Using a (TMS130-1) TNC connector, install the connector onto the antenna end antenna end of the GPS 2 coax cable. CAUTION: Use extra care when assembling and crimping coax connectors. Please refer to Figure 4A for information on how to properly assemble coax connectors. MK Page 11

12 D. Using an ohmmeter, do a continuity check between the center pin and the connector body of the newly installed GPS 2 coax connector. If there is continuity, the connector was improperly installed (shorted), and must be cut off and replaced with a new connector. E. (Figures 1, and 2.) Connect the GPS 2 coax cable and the XM coax cable to the GA 37 Antenna. NOTE: The GPS 2 coax cable connects to the forward blue banded connector. The XM coax cable connects to the aft yellow banded connector. F. (Figures 1 and 3.) Inspect the aft compartment of the airplane. If there are coax cables contacting the elevator push tube below the antennas, secure the XM and GPS 2 coax cables in place with the wire bundles along the right side of the fuselage, keep only minimal slack in the GPS and XM coax cables near the antennas. Use TY242M tiewraps as required. 9. (Figures 8, 9, and 10) Install the Antenna Wedge Block as follows: NOTE: The installation of the Garmin GA 35 GPS / WAAS (GPS 1) Antenna, which will be mounted above the baggage door on top of the fuselage, requires the installation of a 14 degree antenna wedge block (LB or LB , as supplied). The purpose of this block is to level the antenna with respect to the horizon during flight so that the GPS / WAAS antenna has a good view angle of the satellites. A. Make sure that the interior of the airplane and exposed floor equipment is covered with plastic or similar material to avoid damage to the upholstery and equipment. B. (Figure 13, 14 and 15.) Use masking tape to mask off the top of the fuselage as shown. C. (Figure 16.) Locate the two air-conditioning duct brackets on the interior side of the fuselage at approximately FS D. (Figures 8 and 16.) On the centerline of the interior side of the fuselage, locate and mark the center between the forward and aft air conditioning duct brackets for the antenna connector hole. The location of this hole will be at approximately FS E. (Figure 16.) From the fuselage interior, use a #40 (0.098 inch) size drill bit and drill a pilot hole between the two air-conditioning duct brackets as marked in the previous step. F. (Figures 8, 14, and 16.) Drill a 1.25 inch hole through the top of the fuselage at the location where the #40 (0.098 inch) pilot hole was drilled. G. (Figures 8 and 15.) Drill a #13 (0.184 inch) hole on the fuselage centerline approximately 1.8 inches aft of the center of the 1.25 inch hole. H. (Figures 13 and 14.) Temporarily position the wedge block on top of the 1.25 inch hole that was drilled, and mark a footprint outline around the base of the wedge block onto the masking tape. NOTE: Position the antenna wedge block slightly forward so that the 1.25 inch hole in the fuselage is aligned towards the aft side of the larger opening in the wedge block, MK Page 12

13 for clearance of the TNC connector. Refer to Figure 19 for an example of proper wedge offset. I. Remove the wedge block and carefully cut through the tape along the footprint of the wedge block with a razor blade or utility type knife. Do not damage the lightning protection mesh underneath the paint. J. (Figure 15.) Remove the tape from the footprint area of the antenna wedge only, leaving the surrounding area masked off. CAUTION: Do not sand into or through the metallic lightning protection mesh. The mesh layer is very thin and extreme care must be taken to sand only until the bare metal of the mesh is exposed. K. (Figures 17 and 18.) Use a Scotch-Brite sanding disk attached to a rotary tool or manually hand sand and remove the paint and primer of the footprint area until at least 90% of the metallic lightning protection mesh in the footprint area is exposed. The exposed mesh should have a glossy sheen to it when completed. Be particularly careful not to damage or remove the mesh around the smaller hole, as this will be used later for grounding the antenna bond strap. See Figure 18 for an example of the completed sanding job. NOTE: Minor damage to the mesh is acceptable only as long as it does not exceed approximately 10% of the surface area of the footprint. If greater damage occurs, perform a mesh repair of the area per Chapter 51 of the 350 or 400 Airplane Maintenance Manual. L. Using grit paper or equivalent sanding material, surface prep (scuff) the mating face of the antenna wedge block that will be mounted against the skin of the fuselage. M. Clean all the dust and debris away from the sanded areas. Use Isopropyl Alcohol and a lint free cloth to thoroughly clean the exterior side of the fuselage that was sanded. Use the clean side of the lint free cloth for each wipe until the area is thoroughly clean of all contaminants. N. Temporarily locate the antenna wedge block in position. With the wedge block held in position, mask the fuselage surface all the way around the wedge block, leaving a inch gap between the wedge block and the masking tape. Set the wedge block aside. O. To prevent accidental contamination of nearby fuselage surfaces with resin while bonding the antenna wedge block in place, apply additional masking to protect the larger area on the fuselage around the antenna wedge block. P. (Figure 19.) Use a 0.75 inch diameter piece of masking tape to mask off the lightning mesh around the #13 (0.185 inch) size drilled antenna ground hole. The masking tape will prevent bonding adhesive from contaminating the exposed lightning protection mesh. Q. Mix the contents of one Jeffco Pack 5 resin kit together. Reserve 1 fl oz of mixed resin (without filler) to use in the following step for wetting out the mating surfaces of the wedge and fuselage. Pour 4 fl oz of the mixed resin into a container and add one Mixed Filler 6.4 dry filler pack. Thoroughly mix the resin and fillers together to create an adhesive paste. MK Page 13

14 R. Wet out the mating surfaces of the wedge and fuselage with the mixed resin (without fillers) that was reserved in the previous step. S. Apply the Jeffco and Filler Mix adhesive paste to the antenna wedge block. There should be enough Jeffco and Filler Mix adhesive paste between the antenna wedge block and the fuselage to completely fill the gap between the two components. When applying the Jeffco and Filler Mix Adhesive paste to the antenna wedge block, spread the paste down with a stir stick or spatula to help prevent voids in the Jeffco and Filler Mix adhesive once the antenna wedge block is positioned in place on the fuselage. NOTE: Avoid getting mixed filler into the antenna mount screw holes on the wedge block. Use a temporarily installed screw if required to keep the Jeffco adhesive paste out of the threaded insert holes on the wedge block. T. (Figures 10 and 19.) Mount the antenna wedge block onto the fuselage as shown. U. (Figure 19.) Allow the Jeffco and Filler Mix adhesive paste to squeeze out as shown. Make sure that the wedge is aligned in the same position where it was marked at and that the wedge centerline is aligned with the fuselage centerline. NOTE: In order to maintain clearance of the TNC connector, position the antenna wedge block slightly forward so that the 1.25 inch hole in the fuselage is aligned towards the aft side of the larger opening in the wedge block. Refer to Figure 19. V. Firmly hold the wedge block in place use a second person if required. Use a wooden stir stick or a small piece of plastic to remove the excess paste, creating a radiused fillet around the outside of the base of the wedge. W. Gently clean all excess Jeffco and Filler Mix Adhesive from in and around the antenna wedge block using a clean, lint free cloth moistened with isopropyl alcohol. X. Carefully remove the 0.75 inch circular piece of tape from the antenna ground hole, so as not to pull the metallic lightning protection mesh away from the airplane skin. Y. Recheck the wedge position and securely tape the wedge block down in several directions across the top of the fuselage to prevent any movement of the block during the cure cycle. NOTE: Make sure that the masking tape that is on the fuselage is not between the fuselage and the antenna wedge block. Remove the tape as required. Z. Apply a small weight of 1 to 2 pounds to the top of the antenna wedge block. AA. Allow the antenna wedge block installation to pre-cure for at least three hours at room temperature not less than 77 Fahrenheit. NOTE: If the room temperature is below 77 Fahrenheit, then shop heaters or heat lamps may be placed in the room nearby to raise the ambient temperature to at least 77 Fahrenheit, but should not be placed in close proximity to the repair area. Excessive external heat applied to the repair area during the pre-cure could cause the resin to have an exothermic reaction (become extremely hot and possibly cause a fire). BB. After the minimum three hour pre-cure is completed, perform the final cure of the adhesive on the wedge block at 77 Fahrenheit for seven days or at 212 Fahrenheit for two hours. MK Page 14

15 CC. Once fully cured, remove the weight, and all other protective tape and material. 10. Install the new GPS 1 TNC connector and reroute the existing coax cable as follows: NOTE: Two different types of coax cable may be installed. Either RG-400 or TFLX cable coax cable may be in the airplane. The RG 400 is a larger gold colored coax cable, and the TFLX is a small diameter green coax cable. Both types of coax cable are acceptable for this installation. The replacement connector ends for both types of coax cables are supplied with this kit. Discard the two unused connectors. The part numbers for the TFLX connector ends are identified in parentheses in the following steps. A. (Figures 2, 4A or 4B.) Using (TMR130-1) 90 TNC Connector, install the connector onto the antenna end of the GPS 1 coax. Label this end of coax cable as GPS 1. CAUTION: Use extra care when assembling and crimping coax connectors. Please refer to Figure 4A or 4B for information on how to properly assemble coax connectors. NOTE: It is not necessary to cut excess length off of the GPS 1 coax cable. The extra length may be used as a service loop. B. Using an ohmmeter, do a continuity check between the center pin of the newly installed GPS 1 coax connector and the connector body. If there is continuity, the connector was improperly installed (shorted), and must be cut off and replaced with a new connector. C. (Figure 1.) Route the coax cable from where it is hanging loose near the right door frame, up the right aft side of the door frame to the center of the overhead, then aft along the left side of the overhead air-conditioning duct, and then along the center of the overhead area to the location where the GA 35 antenna and wedge block has been installed. D. (Figure 1.) Install the TM1A-C Tie Blocks anywhere as necessary to keep the GPS 1 coax cable secure. They should be placed 6-8 inches apart. Mark the areas where the TM1A-C Tie-Blocks will be placed. Use grit sand paper to surface prep the areas on the fuselage and the left side of the overhead air-conditioning duct where the TM1A-C Tie-blocks will be located. Use grit sand paper to surface prep the base of the TM1A-C Tie-block. E. Clean the surface prepared areas with a clean lint-free rag and Isopropyl Alcohol. F. Use 14340V86 Devcon Plastic Welder II, 14285V86 Mark 5 Mix Nozzles, and 14280V86 Devcon Application Gun to secure the TM1A-C Tie Blocks to the fuselage and to the left side of the air-conditioning duct. G. Tape the TM1A-C Tie-blocks in place until the 14340V86 Devcon Plastic Welder II adhesive cures. Remove the tape after the adhesive is cured. Allow to cure for at least 30 minutes. H. (Figure 3.) Use TY242M tie-wraps as necessary to secure the coax cable to existing wire bundles and to the TM1A-C Wire Tie Blocks. Make a service loop with a bend radius of three quarters of an inch with the remaining length of the GPS 1 coax cable near the GA35 antenna location. MK Page 15

16 11. Mount the GA 35 GPS 1 Antenna as follows: A. (Figure 9.) Use MLS Stabilant 22 Contact Enhancer to treat the exposed area of the exterior fuselage Lightning Protection Mesh inside the aft hole of the wedge block. Treat the terminal ends of the LB Ground Braid Assembly and treat the hardware that will be used to mount the Ground Braid. Treat the spot-faced area of the GA 35 antenna that is located around the forward RH mounting hole. NOTE: MLS Stabilant 22 Electrical Contact Enhancer is to be added to terminated connections to enhance conductivity. Ensure the terminals are clean before applying Stabilant 22. Apply Stabilant 22 on the terminals of connectors by coating each terminal. The supplied brush can be used for application. Ensure connectors and receptacles are free from moisture. If necessary, dry the connectors using a heat gun. B. (Figure 9 and 19.) Install the LB Ground Braid. Using MS or MS Screws (use whichever one will give at least two threads protrusion through the nut on the other side), AN970-3 Large area washer, NAS1149FN832P Washer, and MS21083C08 Self Locking Nut, attach the components as shown. Make sure that the AN970-3 Large Area Washer has metal to metal contact with the lightning protection mesh at the small hole. C. (Figures 9 and 19.) The opposite end of the LB Ground Braid will be mounted in the spot-faced area at the forward right corner of the antenna wedge block. First install the 91802A197 screw through the forward right mounting hole of the GA 35 antenna. Place the ring terminal end of the ground strap onto the screw, and place the GA 35 antenna onto the antenna wedge block. CAUTION: Do not use the screws included with the antenna to mount the GA 35 antenna. They are too long and could damage the fuselage when installed. D. Use an ohmmeter to check the resistance between the GA 35 antenna base and the Lightning Protection Mesh or a suitable grounding point on the fuselage of the airplane. The total resistance should be less than 25 milliohms. E. Mount the GA 35 antenna to the antenna wedge block using the remaining three 91802A197 screws. Torque the screws in-lbs. Do not over torque, as damage may occur to the antenna wedge block. F. Apply a thin bead of the RTV-162 (white) over the head of the four mounting screws of the GA 35 antenna. Do not apply excessive amounts of RTV-162. Smooth out the RTV-162 when finished. G. Mask off any areas where the RTV is not to be used, and apply a thin bead of RTV-162 around the perimeter of the seam, between the GA 35 antenna and the antenna wedge block. Allow the RTV-162 to cure and then remove the masking tape. H. Mask off any areas where the RTV should not be applied, and apply a thin bead of RTV-162 silicone around the base of the antenna wedge block, where it meets the fuselage skin. I. Use a wooden stir stick or a plastic handle to create a radiused fillet in the RTV-162 around the base of the antenna wedge block. Apply enough RTV to cover up the residue from the bonding paste. Allow the RTV-162 to cure and remove any masking tape. MK Page 16

17 J. Route the TNC connector on the GPS 1 coax cable through the hole in the fuselage and connect it to the GA 35 antenna. NOTE: A long needle nose pliers may be required to turn the threaded TNC barrel nut onto the connector of the GA 35 antenna. 12. Reassemble the Airplane as follows: A. At this point the installation and relocation of the antennas is complete. Inspect the installation of the antennas and coax cables. Inspect for security of the installations, security of cables and wiring, and inspect all the areas of the airplane for FOD material. Ensure that no cables or wiring interferes with the free movement of the flight control systems. NOTE: Perform all the steps of the reassembly process in accordance with the instructions contained in the applicable 350 or 400 Airplane Maintenance Manual. B. Vacuum out all the compartments of the airplane that were opened. C. (Figure 11.) Install two of the new Garmin GIA 63W WAAS Integrated Avionics Units into the tray positions that were previously used by the GIA 63 Units. Record the serial numbers and gently slide the units into their tray positions. Lower the bails and secure them with a number 2 Phillips screw driver. CAUTION: Be careful when connecting the GDU display connectors together as the pins inside these connectors can easily be damaged if the connector is forced together. D. (Figure 11.) Install the new Garmin GDU 1044 MFD into the instrument panel. Connect the high-density DSUB connector on the back of the unit and make sure that the connector is firmly latched. Use a 3/32 inch Allen wrench to secure the Cam-Locks on the four corners of the unit. E. Reconnect the airplane batteries and airplane electrical power: 1. Remove the maintenance warning tags from the batteries and the ground power receptacle. 2. Reconnect both the left and right airplane batteries to the electrical system. (Refer to the appropriate 350 or 400 AMM for further details.) NOTE: Be careful that both batteries are connected to the proper polarity cables. 3. Reinstall the battery cover access panel. F. Reinstall the ELT mounting bracket back onto the antenna shelf using the original kept hardware. G. Reinstall the ELT onto the mounting bracket and secure in place using the latch or Velcro on the mounting bracket. Reconnect the Antenna BNC connector and the remote switch connector on the ELT unit. Place the ELT switch in the ARM position. MK Page 17

18 H. Install the ELT access panel. Install the four screws, using the original hardware. I. Reinstall the pitch servo access panel located on floor of the aft baggage shelf. If equipped with the air-conditioning evaporator, make sure the screws and the leading edge of the access cover are attached to the nut-plates on top of the evaporator assembly. J. If equipped, reinstall the air-conditioning evaporator cover located in the baggage compartment area. K. Install the padded carpeting in the aft baggage shelf. Tuck any loose edges of the padded carpeting underneath the edge of the Oxygen fill port surround. L. Reinstall the aft interior cushion against the aft bulkhead. M. Reinstall the baggage netting that divides the baggage compartment from the aft baggage shelf. Tighten the two bolts that secure this net to the floor. N. Install the aft overhead console upholstery above the baggage compartment. O. Install the door surround upholstery panel around the right passenger door frame and right aft passenger window. P. Cut the wire ties holding the forward overhead console up and reinstall the forward overhead console assembly. Q. Reinstall the interior upholstery panels along the right side of the airplane, including the aft section near the rear passenger s seat and the elevator push tube cover in the baggage compartment. R. Reinstall the right door tread and hardware. S. Reinstall the co-pilot seat. T. Reinstall the rear seat back bar and the snap pins into their positions on the outboard ends. There are 2 square washer plates mounted between the bar and the fuselage attach points. Reinstall the rear seat backs and the 4 remaining snap pins into the seat back bar. U. Reinstall the bottom seat cushions in the rear seat positions. V. Reinstall the cargo net on the floor of the baggage compartment. 13. Configure the G1000 Software for the WAAS installation as follows: NOTE: If more information is desired on the operation of the G1000 Avionics systems, the installer may refer to the Garmin G1000 Line Maintenance Manual for the Cessna 350,400, Garmin P/N Rev E (or latest revision), the Pilots Operating Handbook, or the G1000 Cockpit Reference Guide for the Cessna 350 / 400. A. The G1000 System Software must now be configured for Wide Area Augmentation System (WAAS) capability, per Cessna Service Bulletin SB G1000 System Software Upgrade to GDU 8.10 Version (or later approved software revision.). MK Page 18

19 If SB has not been previously complied with, proceed to Step B. If SB has already been complied with, proceed to Step C. B. Perform SB (or later approved software revision) in its entirety. When selecting the Baseline software option in Step 6 (G1000 Software Load) of SB , select the WAAS Baseline option. Perform the remainder of SB as written. After SB is completed, proceed to Step 14. C. The G1000 System Software must be reloaded and configured for WAAS capability. The CD-ROM necessary for software installation should be located in the blue sleeve at the back of the Pilot s Operating Handbook. Return the CD-ROM to the blue sleeve in the POH after completing the software loading and configuration. Complete the software load portion of SB in its entirety. When selecting the Baseline software option in Step 6 (G1000 Software Load) of SB , select the WAAS Baseline option, and perform the remainder of SB as it is written. Proceed to Step Perform Operational Ground Checks as follows: NOTE: If more information is desired on the installation of the software, or the operation of the G1000 Avionics systems, the installer may refer to the G1000 v8.10 Software Loading and Post Installation Checkout, Cessna 350,400 Garmin P/N Rev 02 (or latest revision), or the Garmin G1000 Line Maintenance Manual for the Cessna 350,400; Garmin P/N Rev E (or latest revision). A. After SB has been complied with, do an operational check of the airplane avionics as follows: NOTE: The following operational checks should be accomplished with the airplane outside the hangar and in an unobstructed area to ensure reliable radio and GPS satellite communication. B. Make sure that all necessary circuit breakers are pushed in for normal mode startup of the Garmin G1000 system. C. Connect a 28-volt ground power unit to the external power receptacle and turn on the ground power unit. D. On the overhead console, put the LEFT and RIGHT BATTERY MASTER, CROSSTIE, and AVIONICS MASTER switches to the ON position and allow the system to power up in normal operation. E. LRU Status check: 1. Using the large FMS knob on the MFD, highlight the AUX group page, then rotate the small inner FMS knob to view the AUX-SYSTEM STATUS page. 2. Press the LRU soft key at the bottom of the MFD, then press the small FMS knob to activate the cursor in the LRU Info field on the MFD. 3. Using the small FMS knob, scroll through the list of LRUs and verify that each LRU has a green check mark displayed in status. If any LRU has a red X displayed in status, that system must be troubleshot and corrected. MK Page 19

20 4. Verify that the cross talk between the PFD and the MFD is working. This can be checked by tuning a frequency on one GDU display and verifying that the frequency changes on the opposite display. F. G1000 System and Airframe Error Messages: Test to make sure that there are no failure messages displayed on the PFD. Some initial startup messages will inherently appear and must be acknowledged. Clear all initial messages before determining the validity of displayed error messages. G. Engine Instrumentation: To test the engine instrumentation, press the SYSTEM soft key at the bottom left of the MFD. The engine page will display. Verify that the ambient manifold pressure is correctly displayed and that the page is displaying the correct voltages for the left and right buses. Observe that there are no engine instruments displaying red X s. H. Receiver / Transmitter Operation, COM 1 and COM 2: Tune the #1 Comm Radio to a local VHF COM frequency, select COM 1 on the GMA 1347 Audio panel. Verify the receiver output produces a clear and understandable audio output. Verify the transmitter functions properly by contacting another station and getting a report of reliable communications. Repeat the procedure for the #2 Comm Radio. I. ELT: Check the ELT remote switch function. Tune the VHF COM to MHz, then briefly set the ELT remote switch located in the right side of the instrument panel to the ON position. Listen through the cabin speaker or the headsets for 3 audible sweeps of the ELT and verify that the red light flashes on the remote switch. Immediately thereafter, turn the remote switch back to the ARM position. NOTE: Per FCC regulations, the ELT system should only be checked during the first five (5) minutes of the hour. J. VOR/LOC, Glide-slope check: 1. Check the VOR, ILS, and glide slope functions with ramp test equipment. Operate the equipment according to the test equipment manufacturer s instructions. Adjust the RF signal to a level adequate to perform the test. Select the appropriate HSI source by using the CDI soft key. 2. Simulate a VOR signal on radial 000 with a course-width of 20. Verify full scale deflection of the CDI while applying a 10 deviation signal. Exercise the CDI with both right and left deviations for both NAV 1 and NAV 2 VHF navigation receivers. Exercise the glide-slope deviation indicator with up and down deviation indications. NOTE: The PFD HSI does not show a course deviation bar unless a valid VHF NAV frequency is tuned. Navigation system flags cause the CDI needle to disappear. Red X s will not be displayed for the Navigation system. 3. With an active VOR/LOC navigation frequency tuned on the NAV 1 receiver, press the NAV 1 button on the GMA1347 Audio Panel and verify that the NAV Audio and Ident are being received in the headsets or over the speaker. 4. Repeat step 14.J.1 through 14.J.3 for the NAV 2 receiver. MK Page 20

21 K. GPS Signal Acquisition Check: 1. Turn the large FMS knob on MFD until reaching the AUX group, and then turn the small FMS knob until reaching the AUX GPS STATUS page. Press the GPS 1 soft key at the bottom of the screen. Verify that the GPS 1 unit is displaying a 5-8 of satellites. The GPS SOLUTION should indicate 3D Differential for the type of Navigation quality that the selected GPS is receiving and should ideally have 6-8 satellites in view, which are displayed as filled status bars. 2. Press the GPS 2 soft key at the bottom of the page and repeat step 14.K.1 for the GPS If the unit is unable to acquire satellites, relocate the airplane away from any obstructions that might be shading GPS reception. If the reception does not improve, check the GPS antenna installations. NOTE: After turning on the Avionics Master switch with GIA63W units newly installed, the initial acquisition of position can take up to 20 minutes. Subsequent acquisitions should not take more than 2 or 3 minutes. 4. On the position page or Map page, verify that the displayed latitude / longitude information agrees with a known reference position. L. VHF COM Interference Check: 1. The following tests should be conducted with all installed avionics turned on. Once the Signal Acquisition Test has been completed successfully, test the COM 1 and COM 2 radios to make sure that the communication radio transmissions do not adversely interfere with the reception and performance of the GPS navigation systems and that there is no harmful interference with the installed IFR avionics systems during radio transmissions. 2. Enter a valid GPS waypoint into the flight plan of the Garmin G For each GIA unit, view the AUX - GPS Status Page and verify that at least 6-8 satellites have been acquired and that the GPS is displaying the current position. 4. Verify that the GPS units are sending valid data to the HSI indication on the PFD and that the CDI indication of the HSI is properly displayed when the CDI button on the PFD is selected to the GPS mode. 5. Select MHz on the COM 1 transceiver. Set the CDI button on the PFD to GPS. Set the Audio Panel to COM Transmit for a period of 30 seconds by pressing and holding the MIC key. 7. Verify that the GPS CDI indication on the PFD does not move or disappear during the transmission. Verify that the displayed satellites on the AUX GPS STATUS page do not completely disappear and that the G1000 system does MK Page 21

22 not completely lose its position fix. There may however, be some reduction in signal strength during this test, which is acceptable. 8. Repeat steps 14.L. 3 through 14.L. 7 for the following frequencies, then repeat all 14.L steps for the COM 2 Transceiver: MHz MHz MHz MHz MHz MHz MHz MHz MHz MHz MHz MHz 9. If the GPS CDI display repeatedly flags (CDI needle disappears on the HSI) during any of these tests, check all coax for continuity, and all connectors for proper connection. M. GDL 69A XM Weather / Datalink: Verify that the XM Datalink system is properly receiving both XM Weather and Entertainment Audio. 1. Bring the airplane to an area on the ramp with as few obstacles to line-of-sight viewing of the southern horizon as possible. Turn the large FMS knob on the MFD until reaching the AUX group of pages. Then turn the small FMS knob until reaching the AUX-XM Information page. Press the INFO key and the page will display the 8-character XM DATA RADIO ID and AUDIO RADIO ID numbers. 2. If the broadcast receiver is working and the airplane is in view of at least one XM satellite, the Data and Audio Signal Strength should be Good or Marginal. If the signal strength is reported as Weak or None, reposition the airplane as required. Check the signal strength of both the Data Signal and Audio Signal. 3. Go to the AUX XM INFORMATION page and press the RADIO soft key at the bottom of the screen. 4. Plug a set of headphones into one of the pilot stations and verify that you can hear the XM radio playing in both left and right channels. 5. Using the volume control located in the cabin, verify that you can increase and decrease the XM radio volume. N. Transponder Operation Check: The operation of the GTX 33 Mode-S Transponder is accomplished using the G1000 PFD. Refer to Garmin G1000 Cockpit Reference Guide for the Cessna 350/400 for basic operation. Perform a basic operational check on the transponder. Any discrepancies or anomalies should be corrected before proceeding. Verify that there are no system error messages associated with the operation of the GTX 33 Transponder. Use appropriate test equipment if available to test the operation of the Transponder. O. Avidyne TAS620 Traffic System Interface Check: MK Page 22

23 1. Verify that when the Avionics Master switch is turned on, an aural warning for the Traffic System is announced that says Ground Mode. 2. With the airplane outside, verify that the traffic system displays local traffic. The Avidyne TAS 620 Traffic system should show traffic in the vicinity of the airport and in the appropriate quadrants on the MFD and PFD displays. Refer to the Pilots Operating Handbook to determine proper operation of the Avidyne TAS 620 traffic system. 3. Make sure that local traffic is displayed on the Traffic pages of both the MFD and the inset page of the PFD. 4. Verify that there are no persistent error messages associated with the operation of the Avidyne TAS 620 traffic system after a period of 10 minutes. P. Operation of the Oxygen system (model 400 only). Check the operation of the Oxygen system on the MFD Engine page by pressing the SYSTEM soft-key and the OXYGEN soft key on the engine page of the MFD. When the Oxygen button is pressed, the manifold on the oxygen bottle should be heard to engage. Press the OXYGEN soft-key again to disengage the oxygen flow. Verify that the Oxygen Quantity pressure correctly displays on the engine page of the MFD. Q. Autopilot Pre-Flight Test. 1. Turn on the G1000 system in normal mode. Ensure that the A/P TRIM master switch in the overhead panel is ON. 2. A red AFCS (Auto Flight Control System) annunciation will appear in the upper left side of the PFD until the attitude comes up. 3. Verify that once the Attitude display and GPS systems are active and that the red AFCS annunciation changes to a white PFT annunciation. NOTE: If the red AFCS annunciation remains on the PFD after the attitude indication comes up and never switches to a white PFT annunciation, this indicates there is a failure in the autopilot system preventing the preflight test from continuing. 4. Upon successful completion of the pre-flight test, an aural alert will sound and the PFT annunciation will clear. Continue to the AFCS Switch Checks. NOTE: If the white PFT annunciation turns red, the test has failed and additional troubleshooting will have to be performed prior to continuing with the test. 5. If the aural alert is not heard, but pre-flight testing passed, engage the Autopilot by pressing the AP key on the MFD and disengage the Autopilot by pressing the AP key again. Visual and aural disconnect alerting should occur. R. AFCS Switch Checks. To verify that the AFCS system buttons and switches are operating correctly, perform the following checks: 1. Actuate the Manual Electric Trim (MET) hat switch forward / aft on the pilot s control stick. The pitch trim should engage and run in the selected direction. Check operation in both directions. MK Page 23

24 2. While actuating the pilot s MET switch in the pitch axis, press and hold the A/P DISC button on the pilot s control stick. The pitch trim should stop running and the pitch trim indication should stop moving. The pitch trim will not run for as long as the A/P DISC button is pressed. 3. Release the pilot s A/P DISC button. The trim should resume running. Release the MET switch. 4. Actuate the MET switch forward/aft on the copilot s control stick. The pitch trim should engage and the run in the selected direction. Check operation in both directions. 5. While actuating the copilot s MET switch in the pitch axis, press and hold the A/P DISC button on the copilot s control stick. The pitch trim should stop running and the pitch trim indication should stop moving. The pitch trim will not run for as long as the A/P DISC button is pressed. 6. Release the copilot s A/P DISC button. The trim should resume running. Release the MET switch. 7. Engage the Autopilot by pressing the AP key on the MFD. The pitch and roll clutches should engage, resisting movement of the control stick. 8. Press and hold the CWS switch on the pilot s control stick. CWS should be annunciated on the PFD and the control stick should now move freely when moved manually. 9. Release the CWS switch. CWS should be removed from the PFD and the autopilot should hold the control stick in its present attitude. 10. Press the A/P DISC switch. The Autopilot should command a normal disengagement. A single disconnect tone will be heard and a flashing amber AP will be visible on the PFD for approximately five seconds. 11. Verify that the control stick is free in pitch and roll axes. 12. Engage the Autopilot. 13. Pull the AUTOPILOT circuit breaker. The Autopilot should command an abnormal disconnect, consisting of a continuous disconnect tone and flashing red AP. No AFCS annunciations (e.g. AFCS, PFT, and Mis-trim) should remain across the top of the PFD. 14. Press the AP key on the MFD to silence the autopilot abnormal disconnects tone, then reset the AUTOPILOT breaker. 15. Wait for the pre-flight test sequence to successfully complete again. 16. Press the Go Around button on the flap control panel. GA should be annunciated on the PFD for both pitch and roll modes and the command bars should indicate a wings-level climb to 7 degrees. NOTE: The GA ENGAGED legend on the Go Around button will not illuminate, since it is not supported in the current version of software. MK Page 24

25 17. Press the FD key on the MFD twice to deactivate the Go Around mode and reset the Flight Director. Green PIT and ROL annunciations will be visible on the PFD. 18. Center the pitch trim. 19. Engage the Autopilot. 20. Press the CWS button and verify there is no residual force on the control stick for the pitch axis. 21. Extend the flaps to approach position. The trim should immediately run in the NOSE DOWN direction (this can be seen by observing the pitch trim indication on the MFD). 22. Retract the flaps. The trim should immediately run in the NOSE UP direction. 23. Disengage the Autopilot by pressing the A/P DISC switch. S. Autopilot Operation Checks. 1. Push the HDG knob in to synchronize the heading bug to the present airplane heading on the HSI. 2. Engage the Autopilot. 3. Select Heading mode by pressing the HDG key on the MFD. The command bars should be level and the control stick should be stationary (very slow movement is acceptable due to the airplane not being perfectly level). 4. Turn the HDG knob to the left and verify that the command bars move to the left and the control stick moves to the left. 5. Turn the HDG knob to the right and verify that the command bars move to the right and the control stick moves to the right. 6. Push the HDG knob in to synchronize the heading bug to the present airplane heading on the HSI. 7. Push the CWS button and pull the control stick or yoke to the middle of the pitch control range. 8. Release the CWS button. Verify that the Autopilot clutches re-engage and hold the control stick stationary. 9. Holding the control stick lightly, press the NOSE UP key on the MFD twice to increase the pitch reference. Verify that the command bars move up approximately one degree and the control stick begins moving aft. 10. Hold the control stick or yoke and press the CWS button, re-synchronizing the pitch reference and re-centering the control stick. 11. Release the CWS button and verify that servo clutches re-engage before releasing the control stick. MK Page 25

26 12. Press the NOSE DN key on the MFD twice. Verify that the command bars command down and the control stick begins moving forward. 13. Hold the controls and press CWS to re-center the command bars and stop control stick or yoke movement. 14. With the Autopilot still engaged and the CWS button pressed, move the control stick or yoke to its aft limit. 15. Release the CWS button and apply continuous forward pressure without overpowering the control stick. After 1 or 2 seconds, the trim should begin moving in a trim up direction. Verify that the Pitch Trim indicator on the PFD or MFD follows the operation of the trim motor. 16. Grip the control stick and press the CWS button. Trim motion should stop. 17. Move the control stick to the forward limit and release the CWS button. 18. Slowly pull back on the control stick. After a similar delay, the trim should begin to trim down. 19. Relieve pressure on the control stick and the trim motion should stop. 20. Operate the Trim Switch on the stick and test the left-right movement of the Aileron Trim motor. Verify that the Aileron Trim indication on the PFD or MFD follows the operation of the Aileron Trim motor. 21. Hold the control stick and press the A/P DISC switch to disconnect the Autopilot. 22. Engage VS mode by pressing the VS key on the MFD. Verify the PFD displays VS in green and indicates a pitch reference of 0 FPM. 23. Press the FLC key on the MFD and verify that FLC is annunciated on the PFD in green. It should show a reference of 80 KTS (This is the minimum speed reference for this airplane). 24. Press the ALT key on the MFD and verify that the ALT annunciation is displayed in green on the PFD with an altitude reference equal to the aircraft altitude. 25. Press the FD key and verify that the mode annunciations and command bars are removed from the display. 26. While holding the stick, press the AP DISC key. MK Page 26

27 T. GIA Failure Test. This final checkout tests various secondary communications paths to ensure that the paths function correctly. Perform the steps per Table 1 and verify the results of each test. TABLE 1 Step Single GIA Failure Conditions: 1. Remove power from GIA 1 by pulling INTEG AVION 1 and COM 1 breakers. 2. Restore power to GIA 1. Allow to reacquire satellites. Desired Result GIA 1 Failure - For a GIA 1 failure, only the following shall flag invalid: COM/NAV 1 field. NAV 1 CDI loses deviation bar. TAWS FAIL AFCS 3. Remove power from GIA 2 by pulling INTEG AVION 2 and COM 2 breakers. 4. Restore power to GIA 2. Dual GIA Failure Conditions: 1. Remove power from both GIA units. 2. Restore power to both GIA units. GIA 2 Power Failure - For a GIA 2 failure, only the following shall flag invalid: COM/NAV 2 field. NAV 2 CDI loses deviation bar. TAWS FAIL AFCS CO Detector Fail TCAD Altitude Invalid (if installed) Dual GIA Failure - For a dual GIA failure, only the following shall occur: COM/NAV 1 & COM/NAV 2 fields flag invalid. GPS CDI flags INTEG on PFD. NAV 1, 2 CDI loses deviation bar. XPDR field flags invalid on PFD. Engine Instrument field flags invalid on MFD. TAWS FAIL AFCS fail CO Detector Fail TCAD Altitude Invalid (if installed) GMA 1 Fail (annunciation only) AHRS 1 Not Receiving GPS Info alert MK Page 27

28 U. Display Failure Test. Perform the steps per Table 2 and verify the results of each test. Step MFD Display Failure Conditions: 1. Remove power from MFD. 2. Restore power to MFD. PFD Display Failure Conditions: 1. Remove power from PFD. 2. Replace power to PFD. TABLE 2 Desired Result The following shall occur when power is removed from the MFD: PFD switches to reversion mode. Attitude and Heading remain valid from AHRS. Airspeed, Altitude, Vertical Speed, and OAT remain valid from Air Data Computer. Engine Instrumentation appears on PFD. COM/NAV 2 fields flag invalid. TAWS N/A The following shall occur when power is removed from the PFD: MFD switches to reversion mode. Attitude and Heading remain valid from AHRS. Airspeed, Altitude, Vertical Speed, and OAT remain valid from Air Data Computer. MFD retains engine instrumentation. COM/NAV 1 fields flag invalid. TAWS N/A V. AHRS/ADC Backup Path Test. Perform the steps per Table 3 and verify the results of each test. Step Secondary AHRS/ADC path check: 1. Remove power from PFD. 2. Remove power from GIA2. 3. Check for desired results. 4. Restore power to the PFD and GIA2. TABLE 3 Desired Result The following shall occur on the MFD when power is removed from the PFD and GIA2: MFD switches to reversion mode. Attitude and Heading remain valid from AHRS. Airspeed, Altitude, Vertical Speed, and OAT remain valid from Air Data Computer. Engine Instrumentation flags invalid. All COM & NAV fields flag invalid. MK Page 28

29 W. On the overhead console, put the LEFT and RIGHT BATTERY MASTER, CROSSTIE, and AVIONICS MASTER switches to the OFF position. X. Remove external power from the airplane. 15. Return to Service. A. Make a logbook entry in the airplane maintenance records that describes the work performed, making notations that: The WAAS installation was accomplished per this Service Bulletin/Modification Kit. Installed Equipment List was updated to reflect the equipment changes. The Garmin G1000 system software was configured for WAAS operation per Cessna Service Bulletin SB G1000 System Software Upgrade to GDU 8.10 Version (or latest revision.) A Post Installation checkout was performed per the functional test requirements in this Service Bulletin and SB (or latest revision). MK Page 29

30 Figure 1 GA 37 and GA 35 Antenna Coax Routing MK Page 30

31 MK Figure 2 Coax Cable Modifications Page 31

32 Figure 3 - Tie Block Mounting Detail MK Page 32

33 FOR RG-400 COAX FOR TFLX COAX CABLE 1. Slide on any heat shrink labels if used, the black adhesive heat shrink, and then the crimp tube. 2. Strip the cable per the dimensions shown. Remove the materials. 3. Install the cable insulator onto the center conductor, butting it up against the cable di-electric. 4. Tin the center conductor, and then solder the contact onto the center conductor, butting the contact up against the cable insulator, leaving no gaps. Caution: do not overheat the contact and swell the dielectric and / or the insulator. 5. Flare the outer shield braid by gently rotating the contact and dielectric, then finish to flare out, not disturbing the inner foil shield. Do not remove the aluminum Mylar foil inner shield from the dielectric. 6. Insert the contact into the rear of the connector body, the inner shield being inside of the connector body and the braid shield outside, until the contact snaps into place. Slide the crimp tube up over the braid and up against the connector body. Crimp using M22520/5.01 (Daniels HX4 or equivalent) crimping tool with appropriate die. 7. Slide the Black Adhesive Heat Shrink up over the rear end of the connector body, and Heat Shrink. * NOTE: Use the Silver Crimp Tube (Outer Ferrule) Supplied with the connector. MK Page 33

34 Figure 4A Coax Connector Assembly Instructions TMR130-1 RIGHT ANGLE TNC CONNECTOR ASSEMBLY INSTRUCTIONS 1. Slide on any heat shrink labels if used, then the black adhesive heat shrink, and then the crimp tube over the coax. 2. Strip the cable per the dimensions shown. Be careful not to nick the center conductor or the shield braid. Remove the materials. Do not remove the inner foil shield from the dielectric. 3. Install the cable insulator onto the center conductor, butting it up against the cable dielectric. 4. Tin the center conductor. Flare the outer shield braid by gently rotating the center conductor and dielectric, then finish to flare out, not disturbing the inner foil shield. Do not remove the inner foil shield from the dielectric. 5. Insert the cable into the rear of the connector body, the inner foil shield being inside of the connector body and the braid shield over the outside, inserting the center conductor into the slot of the contact, until the cable insulator butts against the contact. 6. Solder the center conductor onto the contact. CAUTION: Do not overheat the contact and swell the dielectric and / or the cable insulator. 7. Slide the crimp tube up over the braid and up against the connector body. Crimp using M22520/5-01 (Daniels HX4 or equivalent) crimping tool with appropriate die. 8. Add the O-ring to the access cap, then thread on cap and tighten. Install and heat shrink the black adhesive heat shrink onto the connector, completely covering the crimp tube and rear part of the connector body if possible. * NOTE: Use the Silver Crimp Tube (Outer Ferrule) Supplied with the connector. MK Figure 4B Coax Connector Assembly Instructions - Continued Page 34

35 MK Page 35

36 Figure 5 - Antenna Box Modification MK Page 36

37 Figure 6 - Drill Template for Antenna Box MK Page 37

38 Figure 7 - GA 37 Antenna Installations MK Page 38

39 Figure 8 - Wedge Location Detail MK Page 39

40 Figure 9 - Wedge Block and GA 35 Assembly Detail. MK Page 40

41 MK Page 41

42 Figure 11 - GIA and GDU Equipment Locations. Figure Degree Wedge Block. Figure 13 Masked off, and Marking Foot print on masking. Figure 14 Footprint of Wedge Marked on Masking. Figure 15 Masking Removed only under Footprint. FIGURE 16 NOTE: The location of the brackets may vary. The connector hole may need to be repositioned slightly. Once the fore and aft position of the hole location is determined, mark the hole location on the inside of the fuselage, as close to the lateral centerline as possible. Drill the pilot hole from inside the MK Page 42 fuselage. Be aware that the bond seam that connects the two fuselage halves together inside the cabin is not

43 Figure 16 Location of air-conditioning duct brackets and center connector hole. Figure 17 Removal of the paint, under the footprint to expose lightning mesh Figure 18 - Appearance of mesh exposed down to bare metal with a glossy appearance. Figure 19 Wedge Block bonded on with Jeffco Adhesive. Notice Adhesive Squeeze out. MK Page 43