Federal Aviation Administration (FAA), DOT.
Notice of proposed rulemaking (NPRM).
We propose to supersede an existing airworthiness directive (AD) that applies to certain The Boeing Company Model 767 airplanes. The existing AD currently requires revising the Airworthiness Limitations Section of the maintenance planning data (MPD) document. Since we issued that AD, a re-evaluation of certain doors and flaps was done based on their fatigue-critical nature. This proposed AD would revise the maintenance program to incorporate an additional limitation, and would add airplanes to the applicability. We are proposing this AD to detect and correct fatigue cracking of the principal structural element (PSEs), which could adversely affect the structural integrity of the airplane.
We must receive comments on this proposed AD by April 9, 2012.
You may send comments, using the procedures found in 14 CFR 11.43 and 11.45, by any of the following methods:
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For service information identified in this AD, contact Boeing Commercial Airplanes, Attention: Data & Services Management, P.O. Box 3707, MC 2H–65, Seattle, Washington 98124–2207; telephone 206–544–5000, extension 1; fax 206–766–5680; email
You may examine the AD docket on the Internet at
Berhane Alazar, Aerospace Engineer, Airframe Branch, ANM–120S, FAA, Seattle Aircraft Certification Office, 1601 Lind Avenue SW., Renton, Washington 98057–3356; phone: 425–917–6577; fax: 425–917–6590; email:
We invite you to send any written relevant data, views, or arguments about this proposed AD. Send your comments to an address listed under the
We will post all comments we receive, without change, to
On September 4, 2003, we issued AD 2003–18–10, amendment 39–13301 (68 FR 53503, September 11, 2003), for certain The Boeing Company Model 767–200, –300, –300F, and –400ER series airplanes. That AD requires revising Subsection B, Section 9, of Boeing 767 Maintenance Planning Data (MPD) Document D622T001–9, titled “Airworthiness Limitations (AWLs) and Certification Maintenance Requirements (CMRs),” to incorporate Revision October 2002; and Appendix B of Boeing 767 MPD Document D622T001, Revision December 2002. That AD resulted from analysis of data that identified specific initial inspection thresholds and repetitive inspection intervals for certain principal structural elements (PSEs) to be added to the airworthiness limitation instructions (ALI). We issued that AD to ensure that fatigue cracking of various PSEs is detected and corrected; such fatigue cracking could adversely affect the structural integrity of these airplanes.
Since we issued AD 2003–18–10 (68 FR 53503, September 11, 2003), a re-evaluation of certain doors and flaps was done based on their fatigue-critical nature. These items were classified as PSEs and have been included in the revised MPD Document.
We reviewed Subsection B, Airworthiness Limitations—Structural Inspections, of Section 9, Airworthiness Limitations (AWLs) and Certification Maintenance Requirements (CMRs), D622T001–9, Revision July 2011, of the Boeing 767 Maintenance Planning Data (MPD) Document. This service information describes procedures for an additional critical fatigue inspection.
We are proposing this AD because we evaluated all the relevant information and determined the unsafe condition described previously is likely to exist or develop in other products of the same type design.
This proposed AD would retain certain requirements of AD 2003–18–10 (68 FR 53503, September 11, 2003). This proposed AD would revise the Airworthiness Limitations Section of the Maintenance Planning Data (MPD) Document 767 Airworthiness Limitations Instructions (ALI) which adds a critical fatigue inspection and revises the applicability to include additional airplane line numbers.
This proposed AD would retain certain requirements of AD 2003–18–10 (68 FR 53503, September 11, 2003). Since AD 2003–18–10 was issued, the AD format has been revised, and certain paragraphs have been rearranged. As a result, the corresponding paragraph identifiers have changed in this proposed AD, as listed in the following table:
We estimate that this proposed AD affects 417 airplanes of U.S. registry.
We estimate the following costs to comply with this proposed AD:
Title 49 of the United States Code specifies the FAA's authority to issue rules on aviation safety. Subtitle I, Section 106, describes the authority of the FAA Administrator. Subtitle VII, Aviation Programs, describes in more detail the scope of the Agency's authority.
We are issuing this rulemaking under the authority described in Subtitle VII, Part A, Subpart III, Section 44701, “General requirements.” Under that section, Congress charges the FAA with promoting safe flight of civil aircraft in air commerce by prescribing regulations for practices, methods, and procedures the Administrator finds necessary for safety in air commerce. This regulation is within the scope of that authority because it addresses an unsafe condition that is likely to exist or develop on products identified in this rulemaking action.
We have determined that this proposed AD would not have federalism implications under Executive Order 13132. This proposed AD would not have a substantial direct effect on the States, on the relationship between the national Government and the States, or on the distribution of power and responsibilities among the various levels of government.
For the reasons discussed above, I certify that the proposed regulation:
(1) Is not a “significant regulatory action” under Executive Order 12866,
(2) Is not a “significant rule” under the DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979),
(3) Will not affect intrastate aviation in Alaska, and
(4) Will not have a significant economic impact, positive or negative, on a substantial number of small entities under the criteria of the Regulatory Flexibility Act.
Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety.
Accordingly, under the authority delegated to me by the Administrator, the FAA proposes to amend 14 CFR part 39 as follows:
1. The authority citation for part 39 continues to read as follows:
49 U.S.C. 106(g), 40113, 44701.
2. The FAA amends § 39.13 by removing airworthiness directive (AD) 2003–18–10, Amendment 39–13301 (68 FR 53503, September 11, 2003), and adding the following new AD:
The FAA must receive comments on this AD action by April 9, 2012.
This AD supersedes AD 2003–18–10, Amendment 39–13301 (68 FR 53503, September 11, 2003).
This AD applies to The Boeing Company Model 767–200, –300, –300F, and –400ER series airplanes; certificated in any category; line numbers 1 through 997 inclusive.
This AD requires revisions to certain operator maintenance documents to include new inspections. Compliance with these inspections is required by 14 CFR 91.403(c). For airplanes that have been previously modified, altered, or repaired in the areas addressed by these inspections, the operator may not be able to accomplish the inspections described in the revisions. In this situation, to comply with 14 CFR 91.403(c), the operator must request approval for an alternative method of compliance according to paragraph (k) of this AD. The request should include a description of changes to the required inspections that will ensure the continued damage tolerance of the affected structure. The FAA has provided guidance for this determination in Advisory Circular (AC) 25.1529–1A.
Joint Aircraft System Component (JASC)/Air Transport Association (ATA) of America Code 51, Standard Practices/Structures; 52, Doors; 53, Fuselage structure; 54, Nacelle/Pylons; 55, Stabilizers; 56, Windows; and 57, Wings.
This AD was prompted by a re-evaluation of certain doors and flaps based on their fatigue-critical nature. We are issuing this AD to detect and correct fatigue cracking of the principal structural elements (PSEs), which could adversely affect the structural integrity of the airplane.
Comply with this AD within the compliance times specified, unless already done.
For Model 767–200, –300, –300F, and –400ER series airplanes having line numbers 1 through 895 inclusive: Within 18 months after October 16, 2003 (the effective date AD 2003–18–10, (68 FR 53503, September 11, 2003)), revise Subsection B, Section 9, of Boeing 767 MPD Document D622T001–9, entitled “Airworthiness Limitations and Certification Maintenance Requirements,” to incorporate Revision October 2002; and Appendix B of Boeing 767 MPD Document D622T001, Revision December 2002; or Subsection B, Airworthiness Limitations—Structural Limitations, of Section 9, Airworthiness Limitations (AWLs) and Certification Maintenance Requirements (CMRs), D622T001–9, Revision July 2011, of the Boeing 767 MPD Document.
Except as provided by paragraphs (i) and (k) of this AD: After the actions required by paragraph (g) of this AD have been accomplished, no alternative inspections or inspection intervals shall be approved for the structural significant items (SSIs) contained in Section 9 of Boeing 767 MPD Document D622T001–9, Revision October 2002.
Within 18 months after the effective date of this AD, revise the maintenance program to incorporate the limitations section in Subsection B, Airworthiness Limitations—Structural Inspections, of Section 9, Airworthiness Limitations (AWLs) and Certification Maintenance Requirements (CMRs), D622T001–9, Revision July 2011, of the Boeing 767 MPD Document. Doing this revision terminates the requirements of paragraph (g) of this AD.
For the purposes of this AD, the terms principal structural elements (PSEs) as used in this AD, and SSIs as used in Subsection B, Airworthiness Limitations—Structural Inspections, of Section 9, Airworthiness Limitations (AWLs) and Certification Maintenance Requirements (CMRs), D622T001–9, Revision July 2011, of the Boeing 767 MPD Document, are considered to be interchangeable.
Except as provided by paragraph (k) of this AD: After the actions required by paragraph (i) of this AD have been accomplished, no alternative inspections or inspection intervals shall be approved for the SSIs contained in Subsection B, Airworthiness Limitations—Structural Inspections, of Section 9, Airworthiness Limitations (AWLs) and Certification Maintenance Requirements (CMRs), D622T001–9, Revision July 2011, of the Boeing 767 MPD Document.
(1) The Manager, Seattle Aircraft Certification Office (ACO), ANM–120S, FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. In accordance with 14 CFR 39.19, send your request to your principal inspector or local Flight Standards District Office, as appropriate. If sending information
(2) Before using any approved AMOC, notify your appropriate principal inspector, or lacking a principal inspector, the manager of the local flight standards district office/certificate holding district office.
(3) An AMOC that provides an acceptable level of safety may be used for any repair required by this AD if it is approved by the Boeing Commercial Airplanes Organization Designation Authorization (ODA) that has been authorized by the Manager, Seattle Aircraft Certification Office (ACO) to make those findings. For a repair method to be approved, the repair must meet the certification basis of the airplane and 14 CFR 25.571, Amendment 45, and the approval must specifically refer to this AD.
(1) For more information about this AD, contact Berhane Alazar, Aerospace Engineer, Airframe Branch, ANM–120S, FAA, Seattle Aircraft Certification Office, 1601 Lind Avenue SW., Renton, Washington 98057–3356; phone: 425–917–6577; fax: 425–917–6590; email:
(2) For service information identified in this AD, contact Boeing Commercial Airplanes, Attention: Data & Services Management, P.O. Box 3707, MC 2H–65, Seattle, Washington 98124–2207; telephone 206–544–5000, extension 1; fax 206–766–5680; email