AD 2009-02-06 R1

We are revising an existing airworthiness directive (AD) that applies to certain Boeing Model 737-300, -400, and -500 series airplanes. That AD currently requires repetitive high frequency eddy current inspections for cracking of the 1.04-inch nominal diameter wire penetration hole in the frame and frame reinforcement, between stringers S-20 and S-21, on both the left and right sides of the airplane, and related investigative and corrective actions if necessary. This new AD clarifies certain compliance requirements. This AD results from reports of cracking in the frame, or in the frame and frame reinforcement, common to the 1.04-inch nominal diameter wire penetration hole intended for wire routing. We are issuing this AD to detect and correct cracking in the fuselage frames and frame reinforcements, which could reduce the structural capability of the frames to sustain limit loads, and result in cracking in the fuselage skin and subsequent rapid depressurization of the airplane. \n\n\nDATES: This AD is effective September 23, 2009. \n\tThe Director of the Federal Register approved the incorporation by reference of a certain publication listed in the AD as of April 15, 2009 (74 FR 10469, March 11, 2009). \n\tWe must receive comments on this AD by November 9, 2009.

Final rule; request for comments.

2009-02-06 R1 Boeing: Amendment 39-16015. Docket No. FAA-2009-0787; Directorate Identifier 2009-NM-090-AD. \n\nEffective Date \n\n\t(a) This airworthiness directive (AD) is effective September 23, 2009. \n\nAffected ADs \n\n\t(b) This AD revises AD 2009-02-06. \n\nApplicability \n\n\t(c) This AD applies to Boeing Model 737-300, -400, and -500 series airplanes, certificated in any category; as identified in Boeing Alert Service Bulletin 737-53A1279, dated December 18, 2007. \n\nSubject \n\n\t(d) Air Transport Association (ATA) of America Code 53: Fuselage. \n\nUnsafe Condition \n\n\t(e) This AD results from reports of cracking in the frame, or in the frame and frame reinforcement, common to the 1.04-inch nominal diameter wire penetration hole intended for wire routing. We are issuing this AD to detect and correct cracking in the fuselage frames and frame reinforcements, which could reduce the structural capability of the frames to sustain limit loads, and result in cracking in the fuselageskin and subsequent rapid depressurization of the airplane. \n\nCompliance \n\n\t(f) You are responsible for having the actions required by this AD performed within the compliance times specified, unless the actions have already been done. \n\nRestatement of Requirements of AD 2009-02-06 With Clarifications of Compliance Requirements \n\nService Bulletin Reference Paragraph \n\n\t(g) The term "service bulletin,'' as used in this AD, means Boeing Alert Service Bulletin 737-53A1279, dated December 18, 2007. \n\t(1) Where the service bulletin specifies a compliance time after the date on the service bulletin, this AD requires compliance within the specified compliance time after the effective date of this AD. \n\t(2) The "Condition'' column of paragraph 1.E., "Compliance,'' of Boeing Alert Service Bulletin 737-53A1279, dated December 18, 2007, refers to total flight cycles "at the date given on this service bulletin.'' However, this AD applies to the airplanes with the specified total flightcycles as of April 15, 2009 (the effective date of AD 2009-02-06). \n\t(3) Where the service bulletin specifies to contact Boeing for instructions for removing damage and repairing cracking: Before further flight, remove the damage or repair the cracking using a method approved in accordance with the procedures specified in paragraph (j) of this AD. \n\t(4) Although the service bulletin referenced in this AD specifies to submit information to the manufacturer, this AD does not include that requirement. \n\nInspections, Related Investigative Actions, and Corrective Actions \n\n\t(h) At the applicable time specified in paragraph 1.E., "Compliance,'' of the service bulletin, except as specified by paragraph (g)(1) of this AD: Do a high frequency eddy current (HFEC) surface inspection or an HFEC hole/edge inspection for cracking of the 1.04-inch nominal diameter wire penetration hole in the frame and frame reinforcement, between stringer S-20 and S-21; and do all applicable related investigative and corrective actions by accomplishing all the actions specified in the Accomplishment Instructions of the service bulletin, except as specified by paragraphs (g)(3) and (g)(4) of this AD. Do all applicable related investigative and corrective actions before further flight. Thereafter, repeat the inspections at the applicable intervals specified in paragraph 1.E., "Compliance,'' of the service bulletin. \n\nTerminating Action \n\n\t(i) Doing the repair in Part 3 or the preventative modification in Part 5 of the Accomplishment Instructions of the service bulletin terminates the repetitive inspection requirements of this AD. \n\nAlternative Methods of Compliance (AMOCs) \n\n\t(j)(1) The Manager, Seattle Aircraft Certification Office (ACO), FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. Send information to Attn: Wayne Lockett, Aerospace Engineer, Airframe Branch, ANM-120S, 1601 Lind Avenue, SW., Renton, Washington 98057-3356; telephone (425) 917-6447; fax (425) 917-6590. Or, e-mail information to 9-ANM- Seattle-ACO-AMOC-Requests@faa.gov. \n\t(2) To request a different method of compliance or a different compliance time for this AD, follow the procedures in 14 CFR 39.19. Before using any approved AMOC on any airplane to which the AMOC applies, notify your principal maintenance inspector (PMI) or principal avionics inspector (PAI), as appropriate, or lacking a principal inspector, your local Flight Standards District Office. The AMOC approval letter must specifically reference this AD. \n\t(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 an Authorized Representative for the Boeing Commercial Airplanes Delegation Option Authorization Organization who has been authorized by the Manager, Seattle ACO, to make those findings. For a repair method to be approved, the repair must meet the certification basis of the airplane and the approvalmust specifically refer to this AD. \n\nMaterial Incorporated by Reference \n\n\t(k) You must use Boeing Alert Service Bulletin 737-53A1279, dated December 18, 2007, to do the actions required by this AD, unless the AD specifies otherwise. \n\t(1) The Director of the Federal Register previously approved the incorporation by reference of Boeing Alert Service Bulletin 737- 53A1279, dated December 18, 2007, on April 15, 2009 (74 FR 10469, March 11, 2009). \n\t(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; e-mail me.boecom@boeing.com; Internet https://www.myboeingfleet.com. \n\t(3) You may review copies of the service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington. For information on the availability of this material at the FAA, call 425-227-1221 or 425-227-1152. \n\t(4) You may also review copies of the service information that is incorporated by reference at the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, call 202-741-6030, or go to: http:// www.archives.gov/federal_register/code_of_federal_regulations/ ibr_locations.html.

Discussion \n\n\tOn January 9, 2009, we issued AD 2009-02-06, amendment 39-15796 (74 FR 10469, March 11, 2009), for certain Boeing Model 737-300, -400, and -500 series airplanes. That AD requires repetitive high frequency eddy current inspections for cracking of the 1.04-inch nominal diameter wire penetration hole in the frame and frame reinforcement, between stringers S-20 and S-21, on both the left and right sides of the airplane, and related investigative and corrective actions if necessary. That AD resulted from reports of cracking in the frame, or in the frame and frame reinforcement, common to the 1.04-inch nominal diameter wire penetration hole intended for wire routing. We issued that AD to detect and correct cracking in the fuselage frames and frame reinforcements, which could reduce the structural capability of the frames to sustain limit loads, and result in cracking in the fuselage skin and subsequent rapid depressurization of the airplane.Actions Since Existing AD Was Issued \n\n\tSince we issued AD 2009-02-06, January 9, 2009, amendment 39-15796 (74 FR 10469, March 11, 2009), we have determined that we need to clarify certain compliance requirements in the existing AD, as follows: \n\n\tWe have inserted a new paragraph (g)(1) in this AD to state that while the service bulletin specifies compliance times in terms of the "date on this service bulletin,'' this AD requires compliance within the specified compliance time "after the effective date of this AD.'' This paragraph appeared in the original NPRM, but was inadvertently removed from AD 2009-02-06. \n\tWe removed the reference to the "Accomplishment Instructions'' of Boeing Alert Service Bulletin 737-53A1279, dated December 18, 2007, from paragraph (g) of this AD. Paragraphs (g)(1) through (g)(4) of this AD do not all refer to text located in the service bulletin Accomplishment Instructions. \n\tWe added a reference to the Accomplishment Instructions of Boeing Alert Service Bulletin 737-53A1279, dated December 18, 2007, to paragraph (i) of this AD to provide the locations of "Part 3'' and "Part 5,'' as referenced in that paragraph of the AD. \n\nChanges to Existing AD \n\n\tThis AD retains all the requirements of AD 2009-02-06. Since AD 2009-02-06 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 AD, as listed in the following table: \n\n\tRevised Paragraph Identifiers\n\n\nRequirement in AD 2009-02-06\nCorresponding requirement in this AD\nparagraph (d)\nparagraph (e)\nparagraph (e)\nparagraph (f)\nparagraph (f)\nparagraph (g)\nparagraph (g)\nparagraph (h)\nparagraph (h)\nparagraph (i)\nparagraph (i)\nparagraph (j)\nparagraph (j)\nparagraph (k)\n\n\nFAA's Determination and Requirements of This AD \n\n\tWe are issuing this AD because the unsafe condition described previously is likely to exist or develop on other products of these same type designs that could be registered in the United States in the future. This AD revises AD 2009-02-06. This AD retains the requirements of the existing AD and clarifies certain compliance requirements. Since no new airplanes are affected by this AD and there are no new required actions, notice and opportunity for public comment before issuing this AD are unnecessary. \n\nComments Invited \n\n\tThis AD is a final rule that involves requirements affecting flight safety, and we did not provide you with notice and an opportunity to provide your comments before it becomes effective. However, we invite you to send any written data, views, or arguments about this AD. Send your comments to an address listed under the ADDRESSES section. Include "Docket No. FAA-2009-0787; Directorate Identifier 2009-NM-090-AD'' at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of this AD. We will consider all comments received by the closing date and may amend this AD because of those comments. \n\tWe will post all comments we receive, without change, to http:// www.regulations.gov, including any personal information you provide. We will also post a report summarizing each substantive verbal contact we receive about this AD. \n\nAuthority for This Rulemaking \n\n\tTitle 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. \n\tWe 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. \n\nRegulatory Findings \n\n\tThis AD will not have federalism implications under Executive Order 13132. This AD will 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. \n\tFor the reasons discussed above, I certify that this AD: \n\t(1) Is not a "significant regulatory action'' under Executive Order 12866, \n\t(2) Is not a "significant rule'' under DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979), and \n\t(3) 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. \n\tYou can find our regulatory evaluation and the estimated costs of compliance in the AD docket. \n\nList of Subjects in 14 CFR Part 39 \n\n\tAir transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. \n\nAdoption of the Amendment \n\nAccordingly, under the authority delegated to me by the Administrator, the FAA amends 14 CFR part 39 as follows: \n\nPART 39--AIRWORTHINESS DIRECTIVES \n\n 1. The authority citation for part 39 continues to read as follows: \n\n\tAuthority: 49 U.S.C. 106(g), 40113, 44701. \n\nSec. 39.13 (Amended) \n\n2. The FAA amends Sec. 39.13 by removing amendment 39-15796 (74 FR 10469, March 11, 2009) and adding the following new AD: