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# SERVICE BULLETIN MANDATORY

SB 28-4131 Issued: November, 2013 The export of these commodities, technology or software are subject to the U.S. Export Administration Regulations. Diversion contrary to U.S. law is prohibited. For guidance on export control requirements, contact the Commerce Department's Bureau of Export Administration at http://www.bis.doc.gov. Beechcraft Corporation (BC) issues Service Information for the benefit of owners and fixed base operators in the form of two classes of Service Bulletins. The first class, Mandatory Service Bulletins (red border) includes changes, inspection and modifications that could affect safety or crashworthiness. BC also issues Service Bulletins with no red border which are designated as either recommended or optional in the compliance section within the bulletin. In the case of recommended Service Bulletins, BC feels the changes, modifications, improvements or inspections will benefit the owner/operator and although highly recommended, Recommended Service Bulletins are not considered mandatory at the time of issuance. In the case of Optional Service Bulletins, compliance with the changes, modifications, improvements or inspection s is at the owner/operator's discretion. Both classes are available on the web at http://pubs.beechcraft.com and mailed to: (a) Owners of record on the FAA Aircraft Registration Branch List and the BC Safety of Flight Information (SOFI) List. (b) Those having a publications subscription. Information on Safety of Flight Information (SOFI) or subscription can be obtained through the Beechcraft Corporation Technical Manual Distribution Center (TMDC). As Mandatory Service Bulletins and Service Bulletins are issued, the Service Bulletin Master Index will be updated and available online at http://pubs.beechcraft.com. Warranty will be allowed only when specifically defined in the Service Bulletin and in accordance with BC Warranty Policy. Unless otherwise designated, BC Mandatory Service Bulletins, Service Bulletins and BC Kits are approved for installation on BC airplanes in original or BC modified configurations only. BC Mandatory Service Bulletins, Service Bulletins and Kits may not be compatible with airplanes modified by STC installations or modifications other than BC approved kits. 

### 1. Planning Information A. Effectivity (1) Airplanes Model G58 Baron, Serials TH-2356 through TH-2378. If you are no longer in possession of the airplane, please forward this information to the present owner. (2) Spares The following fuel cells are suspect if ordered from Beechcraft (HBP&D) between January 2012 and November 2013 on Baron Model 95, B95, B95A, D95A, E95, 95-55, 95-A55, 95-B55, 95-B55A, 95-B55B (T-42), 95-C55, 95-C55A, D55, D55A, E55, E55A, 56TC, A56TC, 58, 58A, and G58: TITLE : FUEL - INSPECTION/REPLACEMENT OF FUEL CELLS

Part Number Description 60-921046-5 Leading Edge Outboard Fuel Cell, Left
60-921046-6 Leading Edge Outboard Fuel Cell, Right
002-920034-9 Leading Edge Inboard Fuel Cell, Left
002-920034-10 Leading Edge Inboard Fuel Cell, Right
58-380003-13 Center Tank Fuel Cell, Left

58-380003-14 Cente r Tank Fuel Cell, Right

# SERVICE BULLETIN

Issued: November, 2013 

# SB 28-4131 2 of 11 

# MANDATORY

B. Reason This Service Bulletin is being issued to address poten tial fuel leaks in defined fuel cells installed in the wings. C. Description This Service Bulletin provides instructions to remove and replace suspect fuel cells with new fuel cells, in accordance with definitions provided in Table 1 of Paragraph 3.A. D. Compliance An Airworthiness Directive will be requested on the matter covered by this Service Bulletin. Beechcraft Corporation consid ers this to be a Mandatory Service Bulle tin. Airplanes with 150 or more flight hours shall remove a nd replace applicable fuel cells at the nextannual inspection or 100 flight hours, whichever occurs first. Airplanes wit h less than 150 flight hours shall remove and repla ce applicable fuel cells within 20 flight hours from issuance of this Service Bulletin. NOTE Until such time as this Service Bulletin has been complied with, reference Safety Communique 332. E. Approval The engineering data contained in thisService Bulletin is FAA approved. Prior to accomplishment, owners/operators of airplanes registered in countries other than the United States shall consult with their local Aviation Regulatory Authority. Incorporation of this Service Bulletin restores the airplane to original Type Design. F. Manpower The following information is for planning purposes only: Estimated man-hours for inspection: 12 hours Suggested number of technicians for inspection: 1 Estimated man-hours for modification: 16 ho urs per fuel cell, not to exceed 96 hours Suggested number of technicians: 2 The above is an estimate based on experienced, properly equipped tec hnicians complying with this Service Bulletin. Occasionally, after work has started, conditions may be foun d that could result in additional man-hours.

# SERVICE BULLETIN

Issued: November, 2013 3 of 11 

# SB 28-4131 MANDATORY

G. Weight and Balance Negligible. It is the responsibility of the owner/operator tomaintain compliance with the applicable Airworthiness Regulations. H. Electrical Load Data No change. I. Software Accomplishment Summary Not applicable. J. References Baron 55 and 58 Maintenance Manual, P/N 55-590000-13G5, Chapter 28; Beechcraft Baron 56TC and A56TC Turbo-Baro n Shop Manual, P/N 96-590003-5B, Revision 96-590003-5B5, Section 8; Beechcraft Travel Air 95 Series Shop Manual, P/ N 95-590001-1C, Revision 95-590001-1C5, Section 4; Beech Baron 58P and 58TC Maintenance Manual, P/N 102-590000-5A, Revision A25, Chapter 28; Safety Communique 332. K. Publications Affected It is recommended that a note, “See Service Bulletin 28-4131,” be madein the appropriat e chapter of the Illustrated Parts Catalog. L. Interchangeability of Parts Not applicable.

# SERVICE BULLETIN

Issued: November, 2013 

# SB 28-4131 4 of 11 

# MANDATORY

M. Warranty Credit Warranty credit for labor and parts obtained from Beechcraft Corporat ion 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 Bulle tin coverage for the su bject 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 accord ance with criteria defi ned in Paragraph 3, ACCOMPLISHMENT INSTRUCTIONS. (5) The work shall be accomplished at Hawker Beechcraft Services or an Authorized Service Center (ASC) rated to perform maint enance on the specific model of Beechcraft airplane. (6) While work shall be accomplished in accordance with the criteria define d 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 owne r/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 Bulle tin 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 vo id continued airplane warra nty coverage in the area affected by this Service Bulletin until t he date the Service Bulletin is accomplished. The owner/operator should contact Hawker Beechcraft Services or an ASC to schedule th e warranty work to be accomplished. Hawker Beechcraft Services or an ASC must submit the appropriate paperwork directly to the Beechcraft Warranty De partment 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 orde red through Hawker Beechcraft Services, an ASC, or HBP&D:

Beechcraft Corporation expressly re serves the right to supersede, cancel and/or declare obsolete, without prior notice, any parts or publications that may be refere nced 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 Outboa rd Fuel Cell, Right As Required

002-920034-1 Leadin g Edge Inboard Fuel Cell, Left As Required

002-920034-2 Leadin g Edge Inboard Fuel Cell, Right As Required

58-380003-5 Center Tank Fu el Cell, Left As Required

58-380003-6 Center Tank Fu el Cell, Right As Required
WWD82 Clamp As Required NAS1924-114 or WWD114 Clamp As Required 52KS3 or 4852SS305 Clamp As Required 002-920020-1 Gas ket As Required 35-921502 Gasket As Required

Part Number Description Quantity Per AirplanePolyken 231 or ASTMD5486, 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 partnumbers 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, Leadin g Edge Outboard Fuel Cell, Left P/N 60-921046-6, Leading Edge Outboard Fuel Cell, Right P/N 60-921046-2, Leadin g 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 Maintenanc e 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 accord ance with the applic able chapter/section of the appropriate Maintenance Manual or Shop Manual. (c) Remove lower and upper access panels to enab le replacement of the inboard, outboard and center section fuel cells. Refer to Figure 1. (d) Remove the respective fuel ce ll doors to gain access to the fu el cells. These doors are located behind access panels removed in Step (1)(c). (e) Remove the exhaust heat sh ields to enable access to fuel cells. Refer to Figure 1. (f) Use an explosion proof flash light and mirror as needed to in spect 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 in stalled over rivets and sheet metal edges, and that no foreign objects are present. If any fo reign objects exist or tapeis 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 St eps (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 ea ch interconnect tube. If th e interconnecttube(s) are installed correctly the tube bead should come against the spar and not continue to the leading edge fuel cell area (Refer to Fi gure 3). If the interconnect tube is not installed correctly remove the interconnect tube and install correctly per Figu re 3. If the tube is installed correctly proceed to the next step. (b) The purpose of this step is to ve rify that the fuel cell is position ed tight against th e spar. If the fuel cell is not tight against and supported by the sp ar, unintended loads could be induced on the fuel cell. Hold forward pressure on the aft side of the interconnect tube(s), ac cess 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 to rqued 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 torq ued 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 4852SS 305, as needed. Torq ue to 20-25 inch-pounds. (f) Ensure that the hanger snap clips are prop erly fastened on the top of each fuel cell. (5) Install the respective fuel cell doors, using new gaskets, P/N 002-9200 20-1 (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 clea n 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, ma ke an appropriate ma intenance 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