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AD/TAYLORCRAFT/1 Amdt 1 - Wing Struts
Taylorcraft Series AeroplanesTaylorcraft Series Aeroplanes
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Taylorcraft Series Aeroplanes
| AD/TAYLORCRAFT/1 Amdt 1 | Wing Struts | 4/2008 |
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| Applicability: | Models A, BC, BCS, BC-65, BCS-65, BC12-65 (Army L-2H), BCS12-65, BC12-D, BCS12-D, BC12-D1, BCS12-D1, BC12D-85, BCS12D-85, BC12D-4-85,BCS12D-4-85, BF (Army L-2G), BFS, BF-60, BFS-60, BF-65, BF12-65 (Army L-2K), BFS-65, BL, BLS, BL-65 (Army L-2F), BLS-65, BL12-65 (Army L-2J), BLS12-65, 19, F19, F21, F21A, F21B, F22, F22A, F22B, and F22C aircraft; all serial numbers, and,The affected models do not incorporate sealed front lift struts part number MA-A815, Univair part number UA-A815, or FAA-approved equivalent part number, and sealed aft lift struts, part number MA-A854, Univair part number UA-854, or FAA-approved equivalent part number, for all struts.Note 1: This Directive applies to all Taylorcraft models listed above, including those not listed in Taylorcraft Aviation, LLC Service Bulletin No.2007-001 Revision B, dated 15 October 2007. If there are any other differences between the requirements of this Directive and the above service bulletin, this Directive takes precedence.Note 2: For the purposes of this Directive, a used strut that has been inspected using the ultrasound or radiograph inspection method, meets the Acceptance/Rejection Criteria specified in Taylorcraft Aviation, LLC Service Bulletin No.2007-001 Revision B, dated 15 October 2007, and is treated with internal corrosion protection, is considered a new strut. |
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| Requirement: | 1. Visually inspect the left and right wing front and aft lift struts, part number A-A815 and A-A854, or FAA-approved equivalent part numbers, along the entire bottom 12-inches of each strut for cracks and corrosion in accordance with Part 1 of the Instructions in Taylorcraft Aviation, LLC Service Bulletin (SB) No. 2007-001 Revision A, or SB No. 2007-001 Revision B, or later FAA approved revision.2. If any cracks are found during the Requirement 1 visual inspection, replace the cracked strut in accordance with SB No. 2007-001 Revision B, with the following applicable strut: |
| a. A sealed front lift strut, part number MA-A815, Univair part number UA-A815, or FAA-approved equivalent part number, a sealed aft lift strut, part number MA-A854, Univair part number UA-854, or FAA-approved equivalent part number. Installing these lift struts terminates the repetitive inspections required by this Directive for that strut and no further action is required.b. A new vented front lift strut, part number A-A815, a new vented aft lift strut, part number A-A854, or FAA-approved equivalent part numbers, that is treated with internal corrosion protection specified in SB No. 2007-001 Revision B, or later FAA approved revision. Installing one of these lift struts is subject to the repetitive inspections required in Requirement 4.3. If corrosion is found during the Requirement 1 visual inspection, accomplish an ultrasound or radiograph inspection to determine if the corrosion exceeds the Acceptance/Rejection Criteria specified in SB No. 2007-001 Revision B.4. If no corrosion or cracks are found during the Requirement 1 visual inspection, or if the Requirement 3 inspection reveals that the corrosion does not exceed the Acceptance/Rejection Criteria specified in SB No. 2007-001 Revision B, repetitively inspect thereafter in accordance with Part 2 of SB No. 2002-001 Revision B, using the ultrasound or radiograph inspection method and treat with internal corrosion protection until all struts are replaced with the sealed struts specified in Requirement 2.a. If any cracks are found or corrosion is found that exceeds the Acceptance/Rejection Criteria specified in SB No. 2007-001 Revision B, during any of the repetitive inspections required by this Directive, take the necessary corrective actions as applicable in Requirement 5.5. If, during any Requirement 3 or Requirement 4 inspection any cracks are found or it is determined that the corrosion exceeds the Acceptance/Rejection Criteria specified in SB No. 2007-001 Revision B, replace the lift strut with the applicable lift strut specified in Requirement 2.a. or 2.b.6. Do not install lift strut part numbers A-A815 or A-A854, or FAA-approved equivalent part number, unless:a. Within the last 48 months it has been inspected using the ultrasound or radiograph method;b. It meets the Acceptance/Rejection Criteria; and,c. It is treated with internal corrosion protection as specified in SB No. 2007-001 Revision B. |
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