Document ID: chunk:federal_register_of_legislation:F2007L02145:body:0:p3
Version: federal_register_of_legislation:F2007L02145
Segment Type: other
Provision Reference: 
Character Range: 6790–9817

S-22 to 34.
   BS 240,                                                   from S-34L to 34R, underside.
   BS 320,                                                   from S-34 to nose gear wheel well.
   2E.  Before exceeding 19,000 flights, inspect locations:
   BS 140 to 520,                                            all pressure shell structure.

   Repeat the '2E.' inspection at intervals not to exceed 3000 flights, until 20,000 flights.  Then inspect at 20,000 flights or within 2000 flights since last inspected, whichever occurs later.  Thereafter inspect at intervals not to exceed 2000 flights.

      3. Conduct additional internal and external close visual inspections one frame bay and one stringer each side of any frame crack.  If the frame crack exceeds one half of the frame cross section, extend the inspection area to 6 stringer spacings each side of the frame crack.

      4. Inspect any fuselage skin lap splices in the vicinity of any frame or floor beam crack longer than 25mm, for 500mm fore and aft of the cracked member.  Inspect in accordance with Boeing NDT Manual D6-7170, Part 6 Subject 53-30-00 Figure 2.

   Note 2:  FAA AD 2005-08-01 and Boeing SB 747-53A2265 (various revisions as applicable) refer.

   Note 3:  Crew escape hatches, crew doors, and main entry doors are excluded from the inspection requirements of this AD.

   New Requirements introduced by previous amendment (Amendment 6)

   Note 4:  These additional requirements are the new requirements introduced by FAA AD 2005-08-01.  There may be some overlap between the existing and the new requirements.  Boeing Service Bulletin 747-53A2265 Revision 9 contains detailed accomplishment instructions for the new requirements introduced at this amendment.

   Note 5:  The term "existing requirement" and "new requirement" are used to denote pre and post FAA AD 2005-08-01 requirements respectively.

      5. For Group 1 through 11 airplanes, conduct an internal detailed inspection for cracks of the left and right side body frames and adjacent skin between BS 420 and 460 inclusive and between stringers S-8 and S-12 inclusive, in accordance with the Figures 11 through 16 (BSB 747-53A2265 Revision 9).

   Note 6:  Accomplishment of the 10,000 total flight-cycle (flight limit) inspection required by existing requirement 2 and new requirement 6 of this AD, or the initial inspection required by new requirement 8 of this AD, as applicable, is considered acceptable for compliance with the requirements of this paragraph.

   Note 7:  For Groups 1, 3 through 6, and 8 through 11 airplanes, the 8,000 total flight-cycle detailed inspection in new requirement 5 of this AD is a new flight limit inspection in addition to those inspections specified in existing requirement 2 of this AD.  For Groups 2 and 7 airplanes, the 7,000 total flight cycle inspection in new requirement 5 of this AD is an addition to the existing 7,000 total flight-cycle (flight limit) inspection.

      6. For Group 1 through 11 airplanes,