SERVICE BULLETIN MANDATORY

FAA Aircraft Inspection and Repair Manual, P/N AC43.13-1A, Paragraph 300; Model 35 Shop Manual, P/N 35-590096B18 or subsequent, Section 3; Bonanza 33, 35, 36 Series Maintenance Manual, P/N 36590001-9A17 or subsequent, Chapter 27-21; Bonanza Illustrated Parts Catalog for Models H35 through V35A-TC, P/N 35-590015C5 or subsequent; Bonanza Illustrated Parts Catalog for Models 35 through G35, P/N 35-590028B4 or subsequent; Bonanza Illustrated Parts Catalog for Models V35B, P/N 35-590102E4 or subsequent. K. Publications Affected It is recommended that a note "See Service Bulletin No. 2668, Rev. 2" be made in the following: Model 35 Shop Manual, P/N 35-590096B18 or subsequent, Section 3; Bonanza 33, 35, 36 Series Maintenance Manual, P/N 36590001-9A17 or subsequent, Chapter 27-21; Bonanza Illustrated Parts Catalog for Models H35 through V35A-TC, P/N 35-590015C5 or subsequent; Bonanza Illustrated Parts Catalog for Models 35 through G35, P/N 35-590028B4 or subsequent; Bonanza Illustrated Parts Catalog for Models V35B, P/N 35-590102E4 or subsequent. L. Interchangeability of Parts Not applicable. M. Warranty Credit None. 2. Material Information A. Materials - Price and Availability Contact a Raytheon Aircraft Authorized Service Center for information. B. Industry Support Not applicable. SB 2668, Rev. 2 4 of 9 SERVICE BULLETIN MANDATORY Issued: September, 1996 Revised, December, 1998 C. Airplanes (1) The following parts required for this modification may be ordered through a Raytheon Aircraft Authorized Service Center. Some of the materials may be obtained locally. (*) Serials D-1 through D-5725. (**) Serials D-5726 through D-10403, D-15001, and D-15002. (***) It is permissible to mix or match P/N 131765-8M and P/N 35-524106-9 rod ends on the same differential tail control rod assembly. (2) The following materials may be obtained locally: Part Number Description Quantity Per Airplane 35-524106-11 (*) or 35-524106-13 (**) Differential Tail Control Rod Assembly As Required 35-524106-2 (*) or 35-524106-6 (**) Tube As Required 131765-8M (***) or 35-524106-9 (***) Rod End As Required AN316-6R Nut As Required Part Number Description Quantity Per Airplane MIL-S-8802, Class B Sealant (i.e. PR-1440, Pro Seal 890 B-1/2, MC 236) As Required MIL-C-38736 or equivalent (****) Solvent As Required MIL-C-16173, Grade 2 Corrosion Preventative Compound (i.e. Braycote 137) As Required MIL-C-22750 (FED-STD- 595, Color No. 12246) or equivalent Orange Epoxy, Enamel, or Polyurethane Paint As Required MIL-G-23827 Grease (i.e. Aeroshell 7) As Required SB 2668, Rev. 2 5 of 9 SERVICE BULLETIN MANDATORY Issued: September, 1996 Revised, December, 1998 (****) MEK or MPK may be used as an alternative. D. Spares (1) The following materials may be obtained locally: (****) MEK or MPK may be used as an alternative. 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. E. Tooling - Price and Availability Not applicable. MIL-P-23377 Epoxy Polyamide Primer As Required TT-N-95, Type II Naptha (Aliphatic) As Required P-D-680, Type I Mineral Spirits As Required MIL-C-5541 Alodine 1200 As Required Part Number Description Quantity Per Airplane MIL-S-8802, Class B Sealant (i.e. PR-1440, Pro Seal 890 B-1/2, MC 236) As Required MIL-C-38736 or equivalent (****) Solvent As Required MIL-C-16173, Grade 2 Corrosion Preventative Compound (i.e. Braycote 137) As Required MIL-C-22750 (FED-STD- 595, Color No. 12246) or equivalent Orange Epoxy, Enamel, or Polyurethane Paint As Required MIL-G-23827 Grease (i.e. Aeroshell 7) As Required MIL-P-23377 Epoxy Polyamide Primer As Required TT-N-95, Type II Naptha (Aliphatic) As Required P-D-680, Type I Mineral Spirits As Required MIL-C-5541 Alodine 1200 As Required Part Number Description Quantity Per Airplane SB 2668, Rev. 2 6 of 9 SERVICE BULLETIN MANDATORY Issued: September, 1996 Revised, December, 1998 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 1-800-625-7043 or 316-676-4556 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. (1) Remove all power from the airplane and disconnect the battery. Display warning notices prohibiting reconnection of airplane electrical power. (2) Accomplish the following using Figure 1 for reference. (3) Remove the tail cone and any access covers/panels required to gain access to the two ruddervator differential tail control rod assemblies. (4) Inspect all four (4) rod ends for P/N identification and refer to the following note. NOTE It is not necessary to modify P/N 131765-8M, P/N 35-524106-9 rod ends (that have a sealed shaft) or P/N AHM4-1006 rod ends (which have a solid shaft) that have been installed on either differential control rod assembly. However, they will need to be inspected for cracks and corrosion in accordance with step 10. Proceed with the following steps for other parts affected. (5) Identify by left and right location and remove the existing P/N 35-524106 or P/N 35-524106-8 differential tail control rod assemblies. (6) Accurately measure and record the length of each rod assembly. The measurement is taken from the center of one rod end bolt hole to the center of the other rod end bolt hole. (7) Loosen the nuts and remove the rod ends from each rod assembly. (8) Remove the nuts from the rod ends. (9) Thoroughly clean the rod ends, nuts, and the interior and exterior of the rod assembly tubes with P/N MIL-S-38736 solvent and allow to dry. SB 2668, Rev. 2 7 of 9 SERVICE BULLETIN MANDATORY Issued: September, 1996 Revised, December, 1998 (10) Inspect the rod ends, nut, and tubes for cracks and corrosion in accordance with the dye penetrant procedures listed in the P/N AC43. 13-1A FAA Aircraft Inspection and Repair Manual, paragraph 300. (11) Smooth any minor nicks, dents, and scratches that are less than 0.010 inch deep. Apply P/N MIL-C- 5541 Alodine 1200 to any areas of bare metal and prime with P/N MIL-P-23377D, Type I epoxy polyamide primer. (12) If cracks or corrosion are found or the threads are damaged, reference the MATERIAL section and replace the affected part. NOTE If a complete rod assembly is required, obtain the new assembly (listed in the MATERIAL section) and adjust the rod ends to obtain the length of the original rod assembly (step 6). Tighten the nuts to secure the rod ends and proceed to step 20 to complete the instructions for the new rod assembly. NOTE It is permissible to mix or match P/N AHM4-1006, P/N 131765-8M and P/N 35- 524106-9 rod ends on the same differential tail control rod assembly. (13) If no cracks or corrosion are found in the tubes, perform the following: (a) Blow clean, dry, filtered shop air through each tube to remove all moisture. (b) Fill the interior of each tube with P/N MIL-C-16173, Grade 2 corrosion preventative compound diluted with enough P/N TT-N-95, Type II aliphatic naphtha or P/N P-D-680 mineral spirits to allow flowability. Drain off the excess solution and allow to dry. (14) If no cracks or corrosion are found in the rod ends perform the following steps using Detail C for reference: (a) Clean the hollow shaft in each rod end with solvent and allow to dry. (b) Fill the hollow shaft with P/N MIL-S-8802, Class B sealant and allow to cure. (c) After the sealant has cured, lubricate the ball and groove in the rod end insert with P/N MIL-G- 23827 grease. (d) Reidentify the modified rod end as P/N 35-524106-9 using an indelible marker. (15) Apply P/N MIL-C-22750 orange epoxy, enamel, or polyurethane paint to the first two inches of each tube end and allow to dry. If corrosion preventative compound is present when the paint is to be applied, remove it with P/N MIL-C-38736 solvent before painting. NOTE The application of orange paint to the rod assembly tube provides a readily identifiable indication that the tube has been treated with corrosion preventative compound and that the rod ends have been sealed. (16) Install the nuts on the rod ends. SB 2668, Rev. 2 8 of 9 SERVICE BULLETIN MANDATORY Issued: September, 1996 Revised, December, 1998 (17) Lubricate the rod end threads with corrosion preventative compound and install the rod ends in the rod assembly tube. In order to insure adequate thread engagement, be sure that the rod end threads are visible in the rod assembly tube inspection holes (located at both ends of the tube) after the rod ends have been adjusted to obtain the recorded length. If the inspection holes are not present, be sure that the engaged rod end does not extend more than 1 5/8 inches past the end of the tube (distance is measured from the end of the tube to the center of the rod end insert). (18) Adjust the rod ends until the rod assembly is the same length recorded in step 6. (19) Tighten the nuts to secure the rod ends. (20) Reidentify the modified rod assemblies using an indelible marker as follows: (a) The modified P/N 35-524106 rod assemblies become P/N 35-524106-11 rod assemblies. (b) The modified P/N 35-524106-8 rod assemblies become P/N 35-524106-13 rod assemblies. (21) Install the rod assemblies per the left and right identification established in step 5. (22) Operate the ruddervator controls to insure proper operation of the differential tail control rod assemblies and the ruddervator. (23) Install the tail cone and any access panels/covers that were removed to facilitate this Service Bulletin. (24) Reconnect the airplane battery, remove warning notices and restore power. (25) Ensure all work areas are clean and clear of tools and miscellaneous items of equipment. (26) Return airplane to service. B. Spares Remove all P/N 131765-3M rod ends from stock. Modify and reidentify the rod ends in accordance with step 13 of the Accomplishment Instructions. Refer to Figure 1 as required. Return the reidentified rod ends to stock. If Rod End P/N AHM4-1006 is found in stock, modification to it is not necessary. Remove all P/N 35-524306 and P/N 35-524306-8 differential tail control rod assemblies from stock. Modify and reidentify the rod assemblies in accordance with steps 6 through 9 and steps 13 through 20 of the Accomplishment Instructions. Refer to Figure 1 as required. Return the reidentified rod assemblies to stock. C. Record of Compliance Upon completion of this Service Bulletin, make an appropriate maintenance record entry. SB 2668, Rev. 2 9 of 9 SERVICE BULLETIN MANDATORY Issued: September, 1996 Revised, December, 1998 C DETAIL C RUDDERVATOR DIFFERENTIAL TAIL CONTROL ROD ASSEMBLIES B A ROD END NUT INSPECTION HOLE PAINT BOTH ENDS OF TUBE WITH ORANGE PAINT TO INDICATE THAT THE ASSEMBLY HAS BEEN MODIFIED IN ACCORDANCE WITH THIS SERVICE BULLETIN TUBE FILL THE ENTIRE HOLLOW SHAFT THROUGH THIS OPENING WITH SEALANT HOLLOW SHAFT IN ROD END ROD END INSPECTION HOLE NUT ROD END OPENING IN HOLLOW SHAFT ROD END INSERT SB266802 Ruddervator Differential Tail Control Rod Assembly Figure 1 C DETAIL DETAIL DETAIL A A