Document ID: chunk:federal_register_of_legislation:F2008L00719:body:0:p2
Version: federal_register_of_legislation:F2008L00719
Segment Type: other
Provision Reference: 
Character Range: 2855–5945

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.

             As a terminating action for the repetitive inspections required by this Directive, all vented lift struts, part numbers A-A815, A-A854, and FAA-approved equivalent part numbers, may be replaced with sealed lift struts part numbers MA-A815, UA-A815, MA-A854, UA-854, or FAA-approved equivalent part numbers.

             Note:  FAA AD 2008-04-09 Amdt 39-15381 refers.
Compliance:     1. Within 5 hours time in service after 20 August 2007, unless one of the following conditions is met:

                   1. The struts have been replaced with