MANDATORY SERVICE BULLETIN

4004 Kit(s) within the compliance times specified under ACCOMPLISHMENT INSTRUCTIONS in this Service Bulletin. If no cracks are discovered, this Service Bulletin revision requires re-inspection of the wing forward spar carry-thru structure forward and aft frames every 500 fiight hours. D. Compliance Raytheon Aircraft Company considers this to be a mandatory inspection/modification and it must be accomplished as soon as possible after receipt of this Service Bulletin, but no later than the first 1500 fiight hours. If an airplane has over 1500 flight hours, it is to be accomplished at the next scheduled inspection. If no cracks are found, it should be repeated at 500 ftight hour intervals thereafter. If cracks are found, the applicable PIN 36-4004 Kit(s) must be installed. Any airplane with known crack(s) in compliance with the original release of this Service Bulletin (SB No. 2360) which allowed cracks must install the applicable PIN 36-4004 Kit(s). Compliance times for installation of the appropriate kits vary depending on length and location of cracks and are specified under ACCOMPLISHMENT INSTRUCTIONS in this Service Bulletin. If the airplane must be moved to another location for repairs to be accomplished, a ferry permit may be obtained in accordance with 14 CFR Part 21.197 (a)(1) and 14 CFR 21.199 by contacting the FAA. Any of the areas shown in Figure 1 that are modified by the installation of a doubler need not be inspected until 1500 ftight hours after the installation of that particular doubler. If no cracks are found, repeat the inspection of the doubler every 500 flight hours thereafter. Airworthiness Directive AD 95-04-03 (which superseded AD 92-08-07 and AD 91-14-13) was issued on the matter covered by the original release of this Service Bulletin (SB No. 2360). A new or revised Airworthiness Directive is anticipated to be issued as a result of this FAA directed revision. E. Approval The engineering data contained in this Service Bulletin is FAA approved. Issued: November, 1990 Revised: June, 2004 58 53-2360, REV. 1 2 019 Raytheon Aircraft Company I MANDATORY SERVICE BULLETIN F. Manpower The following information is for planning purposes only: Estimated man-hours for visual and dye-penetrant inspection: 4 hours (if accomplished in conjunction with an annual or routine inspection). Estimated man-hours for modification: The man-hours determination will be based upon the findings of the inspection. Contact Raytheon Aircraft Company at 1-800-429-5372 or 316-676-3140 for assistance. I Suggested number of men: 1 man. The above is an estimate based on experienced, properly equipped personnel complying with this Service Bulletin. Occasionally, after work has started, conditions may be found which could result in additional man-hours. G. Weight and Balance The weight and balance information for each airplane modified in accordance with this Service Bulletin must be adjusted in accordance with the kit drawing. It is the responsibility of the owner/operator to maintain compliance with the applicable Airworthiness Regulations. H. Electrical Load Data Not changed. I. Software Accomplishment Summary Not applicable. J. References The appropriate Section(s) or Chapter(s) of the applicable airplane Shop Manual. Maintenance Manual. Shop Manual Supplement and/or Maintenance Manual Supplement. K. Publications Affected It is recommended that a note "See Service Bulletin No. 53-2360, Rev. 1" be made in the following: Beechcraft Debonair/Bonanza 33, A33, B33, C33, C33A, D33, E33 and E33A Illustrated Parts Catalog, PIN 33-590011-3E or subsequent, Figure 6; Beechcraft Bonanza F33, G33, F33A and F33C Illustrated Parts Catalog, PIN 33-590010-7F3 or subsequent, Figures 101 and 101A; Beechcraft Bonanza H35, J35, K35, M35, N35, P35, S35, V35, V35TC, V35A and V35A-TC Illustrated Parts Catalog, PIN 35-590015-9C5 or subsequent, Figure 7; Beechcraft Bonanza V35B and V35B-TC Illustrated Parts Catalog, PIN 35-590102-5E4 or subsequent, Figures 101 and 101A; Raytheon Aircraft Beech Bonanza 36, A36, A36TC and B36TC Illustrated Parts Catalog, PIN 36-590001- 1G16 or subsequent, Figures 101 and 101A; The appropriate Section(s) or Chapter(s) of the applicable airplane Illustrated Parts Catalog and/or Illustrated Parts Catalog Supplement. I Issued: November, 1990 Revised: June, 2004 5853-2360, REV. 1 3019 I I I I I I I Raytheon Aircraft Company I MANDATORY SERVICE BULLETIN 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 or RAPID for information. B. Industry Support Not applicable. C. Airplanes The following kits required for this modification may be ordered through a Raytheon Aircraft Authorized Service Center or RAPID: Model/Serial Part Number Description Quantity Per Airplane Beech Debonair/Bonanza - 36-4004-1 S Kit Information - 1 Required Model 35-33, 35-A33, 35-B33, 35-C33, Front Spar Carry-Thru E33, F33 and G33, Serials CD-1 through Structure Reinforcement CD-1304; (Forward Frame) Beech Bonanza - Model 35-C33A, E33A and F33A, Serials CE-1 through CE-400; Model E33C and F33C, Serials CJ-1 through CJ-30; Model H35, J35, K35, M35, N35, P35, S35, V35, V35A and V35B, Serials 0-4866 through 0-9414, except 0-9379; Model 36, Serials E-1 through E-184; Model A36, Serials E-185 through E-379, except E-356. Beech Bonanza - 36-4004-3 S Kit Information - 1 Required Model 36, Serials E-1 through E-184; Front Spar Carry-Thru Model A36, Serials E-185 through E-379, Structure Reinforcement except E-356. (Rear Frame) Issued: November, 1990 Revised: June, 2004 S8 53-2360, REV. 1 4 of 9 Raytheon Aircraft Company I MANDATORY SERVICE BULLETIN Model/Serial Part Number Description Quantity Per Airplane Beech Bonanza - 36-4004-5 S Kit Information - 1 Required Model F33A, Serials CE-401 through Front Spar Carry-Thru CE-1192; Structure Reinforcement Model F33C, Serials CJ-31 through ! (Forward Frame) CJ-179; Model V35B, Serials 0-9379, 0-9415 through 0-10403; Model A36, Serials E-356, E-380 through E-2397; Model A36TC, Serials EA-1 through EA-241, EA-243 through EA-272. Beech Bonanza - 36-4004-7 S Kit Information - 1 Required Model F33A, Serials CE-401 through Front Spar Carry-Thru CE-1192; Structure Reinforcement Model F33C, Serials CJ-31 through (Rear Frame) CJ-179; Model V35B, Serials 0-9379, 0-9415 through 0-10403; Model A36, Serials E-356, E-380 through E-2397; Model A36TC, Serials EA-1 through EA-241. EA-243 through EA-272. Beech Bonanza - 36-4004-9 S Kit Information - 1 Required Model B36TC, Serials EA-242, EA-273 Front Spar Carry-Thru through EA-471. Structure Reinforcement (Forward Frame) Beech Bonanza - 36-4004-11 S Kit Information - 1 Required Model B36TC, Serials EA-242, EA-273 Front Spar Carry-Thru through EA-471. Structure Reinforcement (Rear Frame) Beech Debonair/Bonanza - 36-4004-13 S Kit Information - 1 Required Model 35-33, 35-A33, 35-B33, 35-C33, Front Spar Carry-Thru E33, F33 and G33, Serials CO-1 through Structure Reinforcement CO-1304; (Rear Frame) Beech Bonanza - Model 35-C33A, E33A and F33A, Serials CE-1 through CE-400; Model E33C and F33C, Serials CJ-1 through CJ-30; Model H35, J35, K35, M35, N35, P35, S35, V35, V35A and V35B, Serials D-4866 through 0-9414, except 0-9379; Raytheon Aircraft Company expressly reserves the right to supersede, cancel and/or declare obsolete, without prior notice, any kits, parts, or publications that may be referenced in this Service Bulletin. I I I I I I I I I I I I I I I Issued: November, 1990 Revised; June, 2004 5853-2360, REV. 1 5 of 9 I I Raytheon Aircraft Company I MANDATORY SERVICE BULLETIN I CAUTION 1 All Raytheon Aircraft approved kits, unless otherwise designated, are approved for installation on Raytheon Aircraft airplanes in original or Raytheon Aircraft approved modified configurations only. Raytheon Aircraft approved kits may not be compatible with airplanes modified by STC installations or modifications other than Raytheon Aircraft approved kits. D. Spares Not applicable. E. Reidentified Parts None. F. Tooling - Price and Availability None. 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. A. Airplane I WARNING I Observe all Warnings and Cautions contained in the aircraft manuals referenced 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 Refer to the appropriate Section(s) or Chapter(s) of the applicable airplane Shop Manual, Maintenance Manual, Shop Manual Supplement and/or Maintenance Manual Supplement when accomplishing this Service Bulletin. (1) Remove all power from the airplane and disconnect the battery. Display warning notices prohibiting reconnection of airplane electrical power. Issued: November, 1990 Revised: June. 2004 5853-2360, REV. 1 6 of 9 Raytheon Aircraft Company I MANDATORY SERVICE BULLETIN (2) Remove the pilot's and copilot's seats and the carry-thru cover to obtain access to the front spar carry-thru structure. (3) Thoroughly clean the forward and aft frames (webs) of the front spar carry-thru structure in the shaded areas shown in Figure 1. (4) Perform a visual inspection of the area cleaned in step 3 for evidence of cracks. (5) Perform a dye-penetrant inspection, using visible dyes, of the area cleaned in step 3 for evidence of cracks. NOTE The first inspection must be performed no later than the first 1500 flight hours. If an airplane has over 1500 flight hours, the inspection is to be accomplished at the next scheduled inspection. If no cracks are found repeat the inspection every 500 flight hour. I NOTE Any of the shaded areas shown in Figure 1 that are modified by the installation of I a doubler need not be dye-penetrant inspected until 1500 flight hours after the installation of that particular doubler. If no cracks are found, repeat the inspection every 500 flight hours. Cracks found in the shaded areas of Figure 1 that have not been modified by a Idoubler must be repaired as indicated in this Service Bulletin on an individual basis. (6) If cracks are discovered or if any cracks are known to still be present from a previous inspection, Idetermine the method of repair according to the following criteria: NOTE The extent of repair is limited to cracking in the radius of the web flange and cracks in the web flat areas at the fasteners of the lower front spar cap. (a) For cracks in the bend radius: i CAU~I?N ! Caution must be used during the stop drilling operation. Do not drill into the spar cap, skin, or any other structure. A thin steel plate may be used to prevent damaging adjacent structure. (i) A crack up to 4.0 inches in length shall be stop drilled at the ends using a #30 drill bit. The area is to be repaired per the applicable PIN 36-4004 Kit(s) within the next 100 flight hours, 12 calendar months or the next scheduled inspection whichever occurs first. (ii) A crack exceeding 4.0 inches in length shall be repaired PRIOR TO FURTHER FLIGHT per the applicable PIN 36-4004 Kit(s). Issued: November, 1990 Revised: June, 2004 5853-2360, REV. 1 7 of 0 II I I Raytheon Aircraft Company I MANDATORY SERVICE BULLETIN (b) For cracks in the web face, in the area of the huckbolt fasteners: (i) A crack emanating from one fastener in two directions is considered to be one crack. Do not stop drill, due to the possibility of damaging structure behind web face. (ii) Any crack shall be repaired per the applicable PIN 36-4004 Kit(s), within the next 25 flight hours, 12 calendar months or the next scheduled inspection whichever occurs first. (iii) A crack passing through two fasteners and extending beyond for more than 0.5 inch on either end shall be repaired PRIOR TO FURTHER FLIGHT, per the applicable PIN 36- 4004 Kit(s). (iv) A crack passing through two fasteners and extending beyond for less than 0.5 inch on both ends shall be repaired per the applicable PIN 36-4004 Kit(s), within the next 25 flight hours, 12 calendar months or the next scheduled inspection whichever occurs first. (c) If cracks are found in both the fOlWard and aft frames on the same side of the airplane, in either the web face andlor the bend radius, and any of the cracks are more than 1.0 inch long, a repair shall be made PRIOR TO FURTHER FLIGHT. (d) If cracks are found in both the fOlWard and aft frames on the same side of the airplane, in either the web face andlor the bend radius, and all of the cracks are less than 1.0 inch long, a repair shall be made per the applicable PIN 36-4004 Kit(s) within the next 25 flight hours, 12 calendar months or the next scheduled inspection whichever occurs first. (e) If a fuselage skin crack is discovered around the opening for the lower fOlWard carry-thru fitting, an external skin doubler may be required. Contact Raytheon Aircraft Company for further instructions. (7) Repair all cracks per the applicable PIN 36-4004 Kit(s). (8) Reinstall the carry-thru cover and the pilot's and copilot's seats. (9) Reconnect the airplane battery, remove warning notices and restore power. (10) Ensure all work areas are clean and clear of tools and miscellaneous items of equipment. (11) Return airplane to service. B. Spares Not applicable. C. Record of Compliance Upon completion of this Service Bulletin, make an appropriate maintenance record entry specifying the kit identification number and the kit serial number. It is recommended that the parts list contained in the kit be filed for future reference until the listing of parts has been incorporated into the Parts Catalog. Issued: November, 1990 Revised: June, 2004 58 53-2360, REV. 1 8 of9 Raytheon Aircraft Company I MANDATORY SERVICE BULLETIN B23GOO1A,AI FORWARD WEB INSPECT FOR CRACKS AROUND HUCKBOLTS AND BETWEEN HUCKBOLTS AND ALONG THE RADIUS OF THE CARRY-THRU WEB AS INDICATED BY THE SHADED AREAS OF THE ILLUSTRATION AFT WEB INSPECT FOR CRACKS AROUND HUCKBOLTS AND BETWEEN HUCKBOLTS AND ALONG THE RADIUS OF THE CARRY-THRU WEB AS INDICATED BY THE SHADED AREAS OF THE ILLUSTRATION Inspection for Cracks in the Wing Forward Spar Carry-Thru Structure Forward and Aft Frames I Figure 1 Issued: November, 1990 Revised: June, 2004 5853-2360, REV. 1 9 of 9