SERVICE BULLETIN Recurring Inspection MANDATORY AP-1260 M

Service Bulletin revision requires that the cracks must be repaired by installation of the applicable P/N 58- 4008 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 flight hours. D. Compliance Airworthiness Directive AD 90-08-14 was issued on the matter covered by the prior release of this Service Bulletin (SB No. 2269, Rev. 1). A new or revised Airworthiness Directive is anticipated to be issued as a result of this FAA directed revision. (1) Civil Airplanes 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 flight 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 flight hour intervals thereafter. If cracks are found, the applicable P/N 58-4008 Kit(s) must be installed. Any airplane with known crack(s) in compliance with prior releases of this Service Bulletin (SB No. 2269) which allowed cracks must install the applicable P/N 58-4008 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. SERVICE BULLETIN Issued: August, 1989 Revised: June, 2004 SB 53-2269, REV. 2 3 of 9 MANDATORY Any of the areas shown in Figure 1 that are modified by the installation of a doubler need not be inspected until 1500 flight hours after the installation of that particular doubler. If no cracks are found in the doubler, repeat the inspection of the doubler every 500 flight hours thereafter. (2) Military Airplanes For compliance information on military airplanes affected by this Service Bulletin, contact the appropriate headquarters. E. Approval The engineering data contained in this Service Bulletin is FAA approved. 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-hour 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. 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. 53-2269, Rev. 2" be made in the following: Beechcraft Travel Air 95 B95, B95A, D95A and E95 Illustrated Parts Catalog, P/N 95-590018B3 or subsequent, Figure 8; Raytheon Aircraft Beech Baron B55, E55, and 58 (58A) Illustrated Parts Catalog, P/N 58-590000-19E10 or subsequent, Chapter 53-10; MANDATORY SERVICE BULLETIN Issued: August, 1989 Revised: June, 2004 SB 53-2269, REV. 2 4 of 9 Raytheon Aircraft Beech Baron 56TC and A56TC Illustrated Parts Catalog, P/N 96-590003-7B2 or subsequent, Figure 101; Raytheon Aircraft Beech Baron 55, A55, B55 (B55A), C55 (C55A), D55 (D55A) and E55 (E55A) Illustrated Parts Catalog, P/N 96-590010-13B3 or subsequent, Chapter 53-17. The appropriate Section(s) or Chapter(s) of the applicable airplane Illustrated Parts Catalog and/or Illustrated Parts Catalog Supplement. 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 Travel Air - Model 95, B95, B95A, D95A and E95, Serials TD-1 through TD-721; Beech Baron - Model 95-55, 95-A55, 95-B55 and 95-B55A, Serials TC-1 through TC-1525 except TC-350 and TC-1471; Model 95-C55, 95-C55A, D55, D55A, E55 and E55A, Serials TC-350, TE-1 through TE-896; Model 56TC and A56TC, Serials TG-1 through TG-94; Model 95-B55B (T42A), Serials TF-1 through TF-70. 58-4008-1 S Kit Information - Front Spar Carry-Thru Structure Reinforcement (Forward Frame) 1 required SERVICE BULLETIN Issued: August, 1989 Revised: June, 2004 SB 53-2269, REV. 2 5 of 9 MANDATORY 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. Beech Travel Air - Model 95, B95, B95A, D95A and E95, Serials TD-1 through TD-721; Beech Baron - Model 95-55, 95-A55, 95-B55 and 95-B55A, Serials TC-1 through TC-1525 except TC-350 and TC-1471; Model 95-C55, 95-C55A, D55, D55A, E55 and E55A, Serials TC-350, TE-1 through TE-896; Model 56TC and A56TC, Serials TG-1 through TG-94; Model 95-B55B (T42A), Serials TF-1 through TF-70. 58-4008-3 S Kit Information - Front Spar Carry-Thru Structure Reinforcement (Rear Frame) 1 required Beech Baron - Model 58, 58A, Serials TH-1 through TH-303, except TH-255. 58-4008-5 S Kit Information - Front Spar Carry-Thru Structure Reinforcement (Forward Frame) 1 required Beech Baron - Model 58, 58A, Serials (TH-1 through TH-303, except TH-255. 58-4008-7 S Kit Information - Front Spar Carry-Thru Structure Reinforcement (Rear Frame) 1 required Beech Baron - Model 95-B55, Serials TC-1471, TC-1526 through TC-2456; Model E55, Serials TE-897 through TE-1201; Model 58, 58A, Serials TH-255, TH-304 through TH-1475. 58-4008-9 S Kit Information - Front Spar Carry-Thru Structure Reinforcement (Forward Frame) 1 required Beech Baron - Model 95-B55, Serials TC-1471, TC-1526 through TC-2456; Model E55, Serials TE-897 through TE-1201; Model 58, 58A, Serials TH-255, TH-304 through TH-1475. 58-4008-11 S Kit Information - Front Spar Carry-Thru Structure Reinforcement (Rear Frame) 1 required Model/Serial Part Number Description Quantity Per Airplane MANDATORY SERVICE BULLETIN Issued: August, 1989 Revised: June, 2004 SB 53-2269, REV. 2 6 of 9 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 for commercial aircraft, and appropriate headquarters for military aircraft. A. Airplane 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. SERVICE BULLETIN Issued: August, 1989 Revised: June, 2004 SB 53-2269, REV. 2 7 of 9 MANDATORY (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 hours. NOTE Any of the shaded areas shown in Figure 1 that are modified by the installation of 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 doubler 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, determine the methods 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) 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 P/N 58-4008 Kit(s) within the next 100 flight hours, 12 calendar months or the next scheduled inspection whichever occurs first. Caution must be used during the stop drilling operation. Do not drill into spar cap, skin, or any other structure. A thin steel plate may be used to prevent damaging adjacent structure. (ii) A crack exceeding 4.0 inches in length shall be repaired PRIOR TO FURTHER FLIGHT per the applicable P/N 58-4008 Kit(s). MANDATORY SERVICE BULLETIN Issued: August, 1989 Revised: June, 2004 SB 53-2269, REV. 2 8 of 9 (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 P/N 58-4008 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 P/N 58- 4008 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 P/N 58-4008 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 forward and aft frames on the same side of the airplane, in either the web face and/or 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 forward and aft frames on the same side of the airplane, in either the web face and/or the bend radius, and all of the cracks are less than 1.0 inch long, a repair shall be made per the applicable P/N 58-4008 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 forward carry-thru fitting, an external skin doubler may be required. Contact Raytheon Aircraft Company for further instructions. (7) Repair all cracks per the applicable P/N 58-4008 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. SERVICE BULLETIN Issued: August, 1989 Revised: June, 2004 SB 53-2269, REV. 2 9 of 9 MANDATORY Inspection for Cracks in the Wing Forward Spar Carry-Thru Structure Forward and Aft Frames Figure 1 B226901A.AI 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 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 FORWARD WEB