SERVICE BULLETIN MANDATORY SB 28-4131

M. Warranty Credit Warranty credit for labor and parts obtained from Beechcraft Corporation or Hawker Beechcraft Services, to the extent noted under MANPOWER and MATERIAL, will be allowed on all airplanes meeting all the following criteria: (1) Airplane owners must have active Standard Warranty coverage and/or an active Beechcraft Maintenance program with applicable Service Bulletin coverage for the subject airplane when the Service Bulletin is issued. (2) Standard Warranty coverage and/or Beechcraft Maintenance Program must be active for the subject airplane on the day the work is accomplished. (3) The work shall be accomplished in accordance with the criteria defined in Paragraph 1.D., COMPLIANCE. (4) The work shall be accomplished in accordance with criteria defined in Paragraph 3, ACCOMPLISHMENT INSTRUCTIONS. (5) The work shall be accomplished at Hawker Beechcraft Services or an Authorized Service Center (ASC) rated to perform maintenance on the specific model of Beechcraft airplane. (6) While work shall be accomplished in accordance with the criteria defined in Paragraph 1.D, COMPLIANCE, warranty coverage offered in this Service Bulletin will expire 12 months from the last day of the month this Service Bulletin is issued. After this date, the owner/operator assumes the responsibility for compliance cost. (7) Claims for compliance with this Service Bulletin (SB) are to be filed as a W4-type claim against SB 28-4131. (8) After the Service Bulletin has been accomplished, a warranty claim must be submitted to HBC within 60 days of the Service Bulletin completion date. Beechcraft Corporation (BC) reserves the right to void continued airplane warranty coverage in the area affected by this Service Bulletin until the date the Service Bulletin is accomplished. The owner/operator should contact Hawker Beechcraft Services or an ASC to schedule the warranty work to be accomplished. Hawker Beechcraft Services or an ASC must submit the appropriate paperwork directly to the Beechcraft Warranty Department for warranty consideration. 2. Material Information A. Materials - Price and Availability Contact information: Hawker Beechcraft Parts & Distribution (HBP&D) 10511 East Central Avenue Wichita, KS 67206 USA Phone: 316-676-3100 or 1-888-727-4344 Fax: 316-676-3222 or 316-676-3327 E-mail: parts@beechcraft.com SERVICE BULLETIN Issued: November, 2013 5 of 11 SB 28-4131 MANDATORY B. Industry Support Not applicable. C. Airplanes (1) The following parts required for accomplishment of this Service Bulletin may be ordered through Hawker Beechcraft Services, an ASC, or HBP&D: Beechcraft Corporation 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. (2) The following materials may be obtained locally: Part Number Description Quantity Per Airplane 60-921046-1 Leading Edge Outboard Fuel Cell, Left As Required 60-921046-2 Leading Edge Outboard Fuel Cell, Right As Required 002-920034-1 Leading Edge Inboard Fuel Cell, Left As Required 002-920034-2 Leading Edge Inboard Fuel Cell, Right As Required 58-380003-5 Center Tank Fuel Cell, Left As Required 58-380003-6 Center Tank Fuel Cell, Right As Required WWD82 Clamp As Required NAS1924-114 or WWD114 Clamp As Required 52KS3 or 4852SS305 Clamp As Required 002-920020-1 Gasket As Required 35-921502 Gasket As Required Part Number Description Quantity Per Airplane Polyken 231 or ASTM- D5486, Type IV, Class I Tape, Pressure-Sensitive As Required SERVICE BULLETIN Issued: November, 2013 SB 28-4131 6 of 11 MANDATORY 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 Beechcraft Corporation at 1-800-429-5372 or 316-676-3140. Observe all Warnings and Cautions contained in the airplane 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. A. Airplane (1) Perform the following Steps (1)(a) through (1)(f) to inspect part numbers of all six fuel cells in accordance with Table 1 below. Fuel Cell part numbers that are listed in the Fuel Cell P/N to be Removed column shall be replaced by part numbers in the Fuel Cell P/N to be Installed column. Table 1 Fuel Cell P/N to be Removed Fuel Cell P/N to be Installed P/N 60-921046-5, Leading Edge Outboard Fuel Cell, Left P/N 60-921046-1, Leading Edge Outboard Fuel Cell, Left P/N 60-921046-6, Leading Edge Outboard Fuel Cell, Right P/N 60-921046-2, Leading Edge Outboard Fuel Cell, Right P/N 002-920034-9, Leading Edge Inboard Fuel Cell, Left P/N 002-920034-1, Leading Edge Inboard Fuel Cell, Left SERVICE BULLETIN Issued: November, 2013 7 of 11 SB 28-4131 MANDATORY At all locations during the incorporation of this Service Bulletin, inspect for the existence of and damage from foreign objects (FOD). All foreign objects shall be removed and any damage shall be addressed in accordance with the applicable Baron Maintenance Manual or Shop Manual. (a) Remove all power from the airplane and disconnect the battery. Display warning notices prohibiting reconnection of airplane electrical power. Review fuel handling and fuel cell maintenance procedures warnings and cautions contained in Baron Maintenance Manual or Shop Manual. (b) Defuel the airplane in accordance with the applicable chapter/section of the appropriate Maintenance Manual or Shop Manual. (c) Remove lower and upper access panels to enable replacement of the inboard, outboard and center section fuel cells. Refer to Figure 1. (d) Remove the respective fuel cell doors to gain access to the fuel cells. These doors are located behind access panels removed in Step (1)(c). (e) Remove the exhaust heat shields to enable access to fuel cells. Refer to Figure 1. (f) Use an explosion proof flashlight and mirror as needed to inspect the top and middle of all existing fuel cells to determine which part numbers have been installed. Fuel Cell part numbers that are listed in the Fuel Cell P/N to be Removed column of Table 1 shall be replaced by part numbers in the Fuel Cell P/N to be Installed column. (2) Remove the applicable fuel cell(s), as defined in Step (1), in accordance with the applicable chapter/section of the appropriate Maintenance Manual or Shop Manual. (3) Along all areas of the fuel bay liners, verify that tape is installed over rivets and sheet metal edges, and that no foreign objects are present. If any foreign objects exist or tape is found to be missing from edges, remove the foreign objects and install tape over defined areas. P/N 002-920034-10, Leading Edge Inboard Fuel Cell, Right P/N 002-920034-2, Leading Edge Inboard Fuel Cell, Right P/N 58-380003-13, Center Tank Fuel Cell, Left P/N 58-380003-5, Center Tank Fuel Cell, Left P/N 58-380003-14, Center Tank Fuel Cell, Right P/N 58-380003-6, Center Tank Fuel Cell, Right Table 1 Fuel Cell P/N to be Removed Fuel Cell P/N to be Installed SERVICE BULLETIN Issued: November, 2013 SB 28-4131 8 of 11 MANDATORY (4) Install the applicable new fuel cell(s), as defined in Step (1), in accordance with guidelines provided in the applicable chapter/section of the appropriate Maintenance Manual or Shop Manual, in conjunction with the following Steps (4)(a) through (4)(f): NOTE Verify interconnect tube position relative to the spar. If the interconnect tube is not correctly positioned, unintended loads could be induced on the fuel cell. (a) Apply forward pressure to the aft side of each interconnect tube. If the interconnect tube(s) are installed correctly the tube bead should come against the spar and not continue to the leading edge fuel cell area (Refer to Figure 3). If the interconnect tube is not installed correctly remove the interconnect tube and install correctly per Figure 3. If the tube is installed correctly proceed to the next step. (b) The purpose of this step is to verify that the fuel cell is positioned tight against the spar. If the fuel cell is not tight against and supported by the spar, unintended loads could be induced on the fuel cell. Hold forward pressure on the aft side of the interconnect tube(s), access the forward side of the interconnect tubes in the inboard and outboard leading edge fuel cells and ensure that the leading edge inboard and outboard fuel cells, at each interconnect tube, are tight against the forward side of the spar. If not tight, reposition nipple, ensuring it is tight against the forward face of the spar. (c) Reinstall center tank nipples to interconnect tubes and ensure that the fuel cell is tight against the aft face of the fuel bay liner. (d) Install new clamps, P/N WWD82, as applicable, to interconnect tube, P/N 002-920012-53. Ensure that the clamps are torqued to 30-35 inch-pounds. Install new clamps, P/N WWD114 (or equivalent P/N NAS1924-114), as applicable, to interconnect tube, P/N 002-920012-51. Ensure that the clamps are torqued to 35-40 inch-pounds. (e) When assembling wet wing interconnect tube P/N 60-921047-1 into leading edge outboard fuel cell, use new clamp, P/N 52KS3 or P/N 4852SS305, as needed. Torque to 20-25 inch-pounds. (f) Ensure that the hanger snap clips are properly fastened on the top of each fuel cell. (5) Install the respective fuel cell doors, using new gaskets, P/N 002-920020-1 (As Required) and P/N 35-921502 (As Required). Install fuel access panels. Install any other access panels that were removed to gain access to the applicable fuel cells. (6) Install exhaust heat shields. (7) Reconnect the airplane battery, remove warning notices, and restore power. (8) Fully fuel the airplane in accordance with guidelines provided in the applicable chapter/section of the appropriate Maintenance Manual or Shop Manual. A minimum of four hours after fueling the airplane, check for leaks. (9) Ensure all work areas are clean and clear of tools and miscellaneous items of equipment. (10) Return airplane to service. B. Spares Review fuel cell configuration as defined in Paragraph 1.A.(2) of this Service Bulletin. C. Record of Compliance Upon completion of this Service Bulletin, make an appropriate maintenance record entry. SERVICE BULLETIN Issued: November, 2013 9 of 11 SB 28-4131 MANDATORY B413103.AI LOWER ACCESS PANELS UPPER ACCESS PANEL LOCATIONS HEAT SHIELD SHOWN REMOVED FUEL ACCESS Access Panel Locations Figure 1 SERVICE BULLETIN Issued: November, 2013 SB 28-4131 10 of 11 MANDATORY B413101.AI CENTER TANK FUEL CELL WET WING INTERCONNECT TUBE P/N 60-921047-1 LEADING EDGE OUTBOARD FUEL CELL LEADING EDGE INBOARD FUEL CELL WET WING CLAMP P/N 52KS3 OR P/N 4852SS305, (1 EACH - LEFT AND RIGHT) P/N 002-920012-53 INBOARD INTERCONNECT TUBE WWD82 CLAMP (4 EACH - LEFT AND RIGHT) P/N 002-920012-51 OUTBOARD INTERCONNECT TUBE WWD114 OR NAS1924-114 CLAMP (2 EACH - LEFT AND RIGHT) (LEFT WING SHOWN, RIGHT OPPOSITE) Fuel Cells Figure 2 SERVICE BULLETIN Issued: November, 2013 11 of 11 SB 28-4131 MANDATORY B413102.AI THE MIDDLE BEAD OF THE INTERCONNECT TUBE SHOULD BE ON THE AFT SIDE OF THE SPAR. THE INTERCONNECT TUBE SHOULD BE STICKING OUT OF THE NIPPLE ON BOTH SIDES FOR THE MID-BOARD AND INBOARD TUBES. THE OUTBOARD TUBE SHOULD BE FLUSH OR SLIGHTLY IN OR OUT DEPENDING ON TOLERANCES. VIEW SHOWING THE MIDDLE BEAD OF THE P/N 002-920012-51 OR -53 INTERCONNECT TUBE LOCATED ON THE AFT SIDE OF THE SPAR. BEAD SHOULD BE LOCATED FIRMLY AGAINST SPAR TO ALLOW PROPER FIT AT FUEL CELL INSTALLATION. FWD A B B A FOR THE -51 2.60 INCHES FOR THE -53 3.00 INCHES FOR THE -51 2.90 INCHES FOR THE -53 4.80 INCHES SPAR FUEL BAY LINER (REFERENCE DIMENSIONS ONLY) Fuel Cell Installation Requirements Figure 3