SERVICE BULLETIN MANDATORY

BEECHCRAFT Bonanza Series Maintenance Manual, P/N 36-590001-9A20 or subsequent revision, Chapter 20-00 and 25-00. BEECHCRAFT Baron 58 Series Maintenance Manual, P/N 102-590000-5A23 or subsequent revision, Chapter 20-00 and 25-00. K. Publications Affected None. L. Interchangeability of Parts Not applicable. M. Warranty Credit Warranty coverage for this Service Bulletin expired May, 2001. 2. Material Information A. Materials - Price and Availability Contact a Raytheon Aircraft Authorized Service Center for information. B. Industry Support Not applicable. C. Airplanes The following parts required for this modification may be ordered through a Raytheon Aircraft Authorized Service Center or RAPID: * The rivet length X is to be determined in the field. + Acceptable alternative blind rivets, for use if access to opposite side of skin is limited. Part Number Description Quantity Per Airplane *MS20470AD4-X Rivet, Solid, Universal Head, 9 + *NAS1398B4-X Rivet, Blind (Cherrylock-style) 9 + *132269B4-X Rivet, Blind (Cherrymax-style) 9 SB 53-3341, Rev. 2 4 of 9 SERVICE BULLETIN MANDATORY Issued: September, 1999 Revised: October, 2002 Raytheon Aircraft Company expressly reserves the right to supersede, cancel and/or declare obsolete, without prior notice, any parts or publications that may be referenced in this Service Bulletin. The following materials may be obtained locally: D. Spares Not applicable. E. Reidentified Parts None. F. Tooling - Price and Availability Not applicable. 3. Accomplishment Instructions This Service Bulletin shall be accomplished as follows: NOTE Should any difficulty be encountered in accomplishing this Service Bulletin, contact Raytheon Aircraft Company at 1-800-429-5372 or 316-676-3140. Part Number Description Quantity Per Airplane A-A-1491, CCC-C-40, or equivalent Cotton Cheesecloth As Required A-A-2758 or equivalent Marking Pen, Felt Tip or equivalent As Required A-A-58054 (Scotchbrite or equivalent) Abrasive Pad As Required MIL-C-81706, Alodine 1200, or equivalent Chemical Conversion Coating As Required MIL-P-23377 or equivalent Epoxy Polyamide Primer As Required Methyl Propyl Ketone As Required TT-N-95, Type II or equivalent Aliphatic Naphtha As Required P-D-680, Type III or equivalent Dry Cleaning Solvent As Required SB 53-3341, Rev. 2 5 of 9 SERVICE BULLETIN MANDATORY Issued: September, 1999 Revised: October, 2002 A. Airplane Observe all Warnings and Cautions contained in the aircraft manuals referred to in this Service Bulletin. Whenever any part of this system is dismantled, adjusted, repaired or renewed, detailed investigation must be made on completion to make sure that distortion, tools, rags or any other loose articles or foreign matter that could impede the free movement and safe operation of the system are not present, and that the systems and installations in the work area are clean. NOTE If any airplane has five, six, or seven rivets installed along the horizontal rivet line just aft of the aft web flange of the front spar upper fitting cutout instead of six, this is an acceptable condition. (1) Refer to Figure 1 and inspect for rivets between F.S. 83.00 and F.S. 91.00 at W.L. 90.3. Universal (round) head or flush head blind rivets may have been installed along this rivet line. If rivets are installed in the noted locations, no further action is necessary. If rivets are not present, proceed to step 2. (2) Remove all power from the airplane and disconnect the battery. Display warning notices prohibiting reconnection of airplane electrical power. (3) Open cabin or passenger door to gain access to airplane interior. Refer to airplane Maintenance Manual. (4) Remove passenger seats, as required, to gain access to the RH Side Panel. Refer to airplane Maintenance Manual. (5) Remove RH Side Panel. (6) Remove and retain interior insulation from areas above the floorboards and between the forward and aft spars, 9.70 inches below W.L. 100.00 (approximately W.L. 90.3). It may be necessary to move aside or remove the wing fairing rubber extrusion to gain access to the area where two missing forward rivets are to be installed. Use care to prevent damage to the extrusion during removal or drilling operations. (7) Locate the lower right hand fuselage panel assembly, P/N 002-430040-181 for Model A36 Bonanza airplanes, P/N 002-430040-175 for Model B36TC Bonanza airplanes, and P/N 002-430040-133 for Model 58 Baron airplanes. Mark a horizontal line for installation of P/N MS20470AD4-X or equivalent rivets using a suitable marking pen or pencil. SB 53-3341, Rev. 2 6 of 9 SERVICE BULLETIN MANDATORY Issued: September, 1999 Revised: October, 2002 If the installer opts to install blind rivets in lieu of MS20470AD4-X rivets, use a suitable stop drill or otherwise take care to avoid drilling damage to plumbing and electrical lines, structural parts, etc., in the airplane interior. Personal injury or damage to equipment could result. When drilling rivet holes, look inside at the P/N 002-430043-19 gusset to make sure that an edge distance of at least two times the rivet diameter is maintained between the edge of the material and the center of each fastener hole. Maintain rivet spacing at least three times rivet diameter (center-to-center) distance between each new fastener hole. (8) Drill pilot holes for missing P/N MS20470AD4-X or equivalent rivets in locations as follows (see Figures 1 and 2): (a) Drill three holes through the skin and P/N 002-430043-19 gusset just above the upper wing bolt attach fitting cutout. (b) Drill six holes through the skin and the edge of the P/N 002-430043-19 gusset just aft of the aft web flange on the front spar. (9) Drill 0.125 + 0.0035 inch diameter holes for installation of P/N MS20470AD4-X or equivalent rivets. Insure "foreign object elimination" by vacuuming or wiping up all metal shavings and other drilling or cleaning debris. (10) Deburr rivet holes and vacuum or wipe up any drilling debris using clean cotton cheesecloth or clean wiping rag. Solvents, primers, and paints are flammable and toxic to skin, eyes, and respiratory tract. Skin and eye protection is required. Avoid repeated or prolonged contact. Keep away from flames or sources of heat. Use in a well- ventilated area or respiratory protection equipment may be required. Chemical conversion coating may affect skin, eyes, and respiratory tract. Chemical goggles and neoprene gloves will be worn. Use in a well- ventilated area. SB 53-3341, Rev. 2 7 of 9 SERVICE BULLETIN MANDATORY Issued: September, 1999 Revised: October, 2002 (11) Use abrasive pads to dress out drilled hole areas. Clean the area with clean cotton cheesecloth or clean wiping rag dampened with appropriate solvent. Repeat solvent wipe cleaning, as necessary. Wipe surfaces dry with clean cotton cheesecloth. (12) Apply chemical conversion coating to bare metal surfaces of both interior and exterior locations. Allow adequate drying time following application of chemical conversion coating. (13) Refer to Figure 1 and Figure 2 and install P/N MS20470AD4-X or equivalent rivets in hole locations drilled in step 9. Dip each rivet shank in epoxy polyamide primer and install wet. Use an appropriate size rivet gun and bucking bar to install rivets. (14) Prime both interior and exterior surfaces in the repair area with epoxy polyamide primer. (15) Allow adequate drying time for epoxy polyamide primer, then touch up the exterior top coat paint to match exterior paint color. Refer to airplane Maintenance Manual for methods and paint color. (16) Install wing fairing rubber extrusion (if removed to facilitate drilling and rivet installation operations). (17) Install insulation retained from step 6. (18) Install RH Side Panel. (19) Install passenger seats which were removed to gain access to the RH Side Panel. Refer to airplane Maintenance Manual. (20) Reconnect the airplane battery, remove warning notices and restore power. (21) Ensure all work areas are clean and clear of tools and miscellaneous items of equipment. (22) Return airplane to service. B. Spares Not applicable. C. Record of Compliance Upon completion of this Service Bulletin, make an appropriate maintenance record entry. SB 53-3341, Rev. 2 8 of 9 SERVICE BULLETIN MANDATORY Issued: September, 1999 Revised: October, 2002 B334101.AI FWD F.S. 91.00 W.L. 90.3 WING BOLT ATTACH POINT VIEW OF RH FUSELAGE ON BONANZA MODEL (TYPICAL), WING AND WING FAIRING RUBBER EXTRUSION NOT SHOWN THESE 9 RIVETS WERE NOT INSTALLED ON SOME AIRPLANES. F.S. 83.00 Inspection/Installation of Missing Rivets in RH Fuselage Figure 1 SB 53-3341, Rev. 2 9 of 9 SERVICE BULLETIN MANDATORY Issued: September, 1999 Revised: October, 2002 B324802.AI FWD DRILL HOLES AND INSTALL MISSING RIVETS IN 9 PLACES, MAINTAIN EDGE DISTANCE OF AT LEAST TWO TIMES RIVET DIAMETER, MAINTAIN RIVET SPACING AT LEAST THREE TIMES RIVET DIAMETER. W.L. 90.3 F.S. 83.00 F.S. 91.00 FRONT SPAR UPPER FITTING (WING BOLT NOT INSTALLED) RH CABIN DOOR THRESHOLD VIEW LOOKING OUTBOARD AT RH FUSELAGE ON BONANZA MODEL (TYPICAL) P/N 002-430043-19 GUSSET Installation of Missing Rivets in RH Fuselage Figure 2