Airworthiness directives › 2012-10-03
AD 2012-10-03 Airworthiness Directives; The Boeing Company Airplanes
Models named: 747-100, 747-100B, 747-200B, 747-200C, 747-200F, 747-300, 747SR, 747SP series. Read the applicability below — it usually turns on serial or part numbers too.
Applicability*9
This AD applies to The Boeing Company Model 747-100, 747-100B, 747-200B, 747-200C, 747-200F, 747-300, 747SR, and 747SP series airplanes, certificated in any category, as identified in Boeing Service Bulletin 747-53A2303, Revision 2, dated October 1, 2009.
Compliance
You are responsible for having the actions required by this AD performed within the compliance times specified, unless the actions have already been done.
Required actions
This paragraph restates the requirements of paragraph A. of AD 90-21-17, Amendment 39-6768 (55 FR 41510, October 12, 1990), with revised service information, reduced inspection interval, and added subparagraph. Conduct a close visual or detailed inspection, and a high frequency eddy current (HFEC) inspection, of the fuselage skin lap splice between BS 400 and BS 520, at stringers S-6L and S-6R, for cracking, in accordance with Boeing Alert Service Bulletin 747-53A2303, dated June 2, 1988, or Revision 1, dated March 29, 1990; or Boeing Service Bulletin 747-53A2303, Revision 2, dated October 1, 2009; at the times specified in paragraph (g)(1), (g)(2), or (g)(3) of this AD. After the effective date of this AD, only Boeing Service Bulletin 747-53A2303, Revision 2, dated October 1, 2009, may be used. Adequate lighting must be used for this inspection. The eddy current inspections may be conducted without removal of the paint, provided the paint does not interfere with the inspections. Paint must be removed, using an approved chemical stripper, in any situation where the inspector determines that the paint is interfering with the proper functioning of the inspection instrument. (1) Within the next 100 landings after March 31, 1989 (the effective date of AD 89-05-03, Amendment 39-6146 (54 FR 7397, February 21, 1989), which was superseded by AD 90-21-17, Amendment 39-6768 (55 FR 41510, October 12, 1990)), for airplanes that have accumulated 16,000 or more landings as of March 31, 1989, unless previously accomplished within the last 4,900 landings. (2) Within the next 1,000 landings after March 31, 1989, or prior to the accumulation of 16,000 landings, whichever occurs first, for airplanes that have accumulated between 12,000 and 16,000 landings, as of March 31, 1989 (the effective date of AD 89-05-03, Amendment 39-6146 (54 FR 7397, February 21, 1989), which was superseded by AD 90-21-17, Amendment 39-6768 (55 FR 41510, October 12, 1990)), unless previously accomplished within the last 4,000 landings. (3) Prior to the accumulation of 13,000 landings for airplanes that have accumulated 12,000 or fewer landings as of March 31, 1989 (the effective date of AD 89-05-03, Amendment 39-6146 (54 FR 7397, February 21, 1989), which was superseded by AD 90-21-17, Amendment 39-6768 (55 FR 41510, October 12, 1990)), unless previously accomplished within the last 5,000 landings. (4) For the purposes of this AD, a detailed inspection is: “An intensive examination of a specific item, installation, or assembly to detect damage, failure, or irregularity. Available lighting is normally supplemented with a direct source of good lighting at an intensity deemed appropriate. Inspection aids such as mirror, magnifying lenses, etc., may be necessary. Surface cleaning and elaborate procedures may be required.”
Unsafe condition
This AD was prompted by from reports of multiple adjacent cracks on an airplane, and a recent fleet-wide evaluation of widespread fatigue damage of skin lap joints, which indicated the need for revised procedures and reduced compliance times. The Federal Aviation Administration is issuing this AD to detect and correct cracking of the fuselage skin lap splice between body station (BS) 400 and BS 520, at stringers S-6L and S-6R. Such cracking could result in sudden loss of cabin pressurization and the inability of the fuselage to withstand fail-safe loads.
Affected ADs
This AD supersedes AD 90-21-17, Amendment 39-6768 (55 FR 41510, October 12, 1990).
Read the original on the Federal Register →
You just looked this one up by hand
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The directive text above is reproduced from the Federal Register, a work of the United States government and in the public domain. The separation into applicability, compliance and required actions is TrackAD's.*1