82 FR 38637 - Airworthiness Directives; The Boeing Company Airplanes
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration Federal Register Volume 82, Issue 156 (August 15, 2017)
Federal Aviation Administration
Federal Register Volume 82, Issue 156 (August 15, 2017)
| Page Range | 38637-38641 | |
| FR Document | 2017-16776 |
[Federal Register Volume 82, Number 156 (Tuesday, August 15, 2017)] [Proposed Rules] [Pages 38637-38641] From the Federal Register Online [www.thefederalregister.org] [FR Doc No: 2017-16776] ----------------------------------------------------------------------- DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA-2017-0774; Product Identifier 2017-NM-036-AD] RIN 2120-AA64 Airworthiness Directives; The Boeing Company Airplanes AGENCY: Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). ----------------------------------------------------------------------- SUMMARY: We propose to supersede Airworthiness Directive (AD) 2012-12- 05, which applies to all The Boeing Company Model 737-100, -200, -200C, -300, -400, and -500 series airplanes. AD 2012-12-05 currently requires repetitive inspections for cracking under the stop fittings and intercostal flanges and for cracking of the intercostal web, attachment clips, stringer splice channels, frame, reinforcement angle, shear web, frame outer chord and inner chord; a one-time inspection to detect missing fasteners; repetitive inspections of the cargo barrier net fitting for cracking; repetitive inspections for cracking of the stringer S-15L aft intercostal; and repair or corrective action if necessary. Since we issued AD 2012-12-05, we have received reports of additional cracking in locations not covered by the inspections in that AD. For certain airplanes, this proposed AD would add new repetitive inspections of certain areas of the frame inner chord, and applicable on-condition actions. We are proposing this AD to address the unsafe condition on these products. DATES: We must receive comments on this proposed AD by September 29, 2017. ADDRESSES: You may send comments, using the procedures found in 14 CFR 11.43 and 11.45, by any of the following methods:Federal eRulemaking Portal: Go to http://www.regulations.gov. Follow the instructions for submitting comments. Fax: 202-493-2251. Mail: U.S. Department of Transportation, Docket Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New Jersey Avenue SE., Washington, DC 20590. Hand Delivery: Deliver to Mail address above between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. For service information identified in this NPRM, contact Boeing Commercial Airplanes, Attention: Contractual & Data Services (C&DS), 2600 Westminster Blvd., MC 110-SK57, Seal Beach, CA 90740; telephone 562-797-1717; Internet https://www.myboeingfleet.com. You may view this referenced service information at the FAA, Transport Standards Branch, 1601 Lind Avenue SW., Renton, WA. For information on the availability of this material at the FAA, call 425-227-1221. It is also available on the internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2017-0774. Examining the AD Docket You may examine the AD docket on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2017- 0774; or in person at the Docket Management Facility between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this proposed AD, the regulatory evaluation, any comments received, and other information. The street address for the Docket Office (phone: 800-647-5527) is in the ADDRESSES section. Comments will be available in the AD docket shortly after receipt. FOR FURTHER INFORMATION CONTACT: Galib Abumeri, Aerospace Engineer, Airframe Section, FAA, Los Angeles Aircraft Certification Office (ACO) Branch, 3960 Paramount Boulevard, Lakewood, CA 90712-4137; phone: 562- 627-5324; fax: 562-627-5210; email: [email protected]. SUPPLEMENTARY INFORMATION: Comments Invited 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 ADDRESSES section. Include ``Docket No. FAA-2017-0774; Product Identifier 2017-NM-036-AD'' at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of this proposed AD. We will consider all comments received by the closing date and may amend this proposed AD because of those comments. We will post all comments we receive, without change, to http:// [[Page 38638]] www.regulations.gov, including any personal information you provide. We will also post a report summarizing each substantive verbal contact we receive about this proposed AD. Discussion On June 4, 2012, we issued AD 2012-12-05, Amendment 39-17084 (77 FR 36139, June 18, 2012) (``AD 2012-12-05''), for all The Boeing Company Model 737-100, -200, -200C, -300, -400, and -500 series airplanes. AD 2012-12-05 superseded AD 2004-09-09, Amendment 39-13598 (69 FR 23646, April 30, 2004); and AD 2009-16-14, Amendment 39-15987 (74 FR 38901, August 5, 2009). AD 2012-12-05 requires repetitive inspections for cracking under the stop fittings and intercostal flanges and for cracking of the intercostal web, attachment clips, stringer splice channels, frame, reinforcement angle, shear web, frame outer chord and inner chord; a one-time inspection to detect missing fasteners; repetitive inspections of the cargo barrier net fitting for cracking; repetitive inspections for cracking of the stringer S-15L aft intercostal; and repair or corrective action if necessary. AD 2012-12- 05 resulted from reports of cracking of the station (STA) 348.2 frame above the two outboard fasteners attaching the frame inner chord and door stop fittings, and in the outboard chord at stringer S-16L. AD 2012-12-05 also resulted from reports of missing fasteners in the STA 348.2 frame inner chord. We issued AD 2012-12-05 to detect and correct fatigue cracking of the intercostals on the forward and aft sides of the forward entry door cutout, which could result in loss of the forward entry door and rapid decompression of the airplane. Actions Since AD 2012-12-05 Was Issued Since we issued AD 2012-12-05, we have received reports of additional cracking in the STA 351.2 frame inner chord at stringer S- 17L, at the fastener hole location common to the frame inner chord, door sill, and shear web. The cracks were reported on Model 737-300 and -500 airplanes that had accumulated between 40,600 and 65,500 total flight cycles. The STA 351.2 frame inner chord at stringer S-17L is hidden under the shear web and the door sill; therefore, any cracking at this location cannot be visually detected. Related Service Information Under 1 CFR Part 51 We reviewed Boeing Alert Service Bulletin 737-53A1240, Revision 2, dated November 2, 2016. The service information describes procedures for, among other actions, repetitive inspections of the fastener holes in the STA 351.2 frame inner chord at stringer 17L, and applicable on- condition actions. This service information is reasonably available because the interested parties have access to it through their normal course of business or by the means identified in the ADDRESSES section. FAA's Determination 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. Proposed AD Requirements This proposed AD would retain all requirements of AD 2012-12-05. Although this proposed AD does not explicitly restate the actions in Boeing Alert Service Bulletin 737-53A1240, Revision 1, dated June 29, 2010, that are part of the requirements of AD 2012-12-05, this proposed AD would retain those requirements. Those requirements are referenced in the service information identified previously, which, in turn, is referenced in paragraph (p) of this proposed AD. Paragraph (p) of this proposed AD would require accomplishment of the actions identified as ``RC'' (required for compliance) in the Accomplishment Instructions of Boeing Alert Service Bulletin 737-53A1240, Revision 2, dated November 2, 2016, except for any differences identified as exceptions in the regulatory text of this proposed AD. For information on the procedures and compliance times for Boeing Alert Service Bulletin 737-53A1240, Revision 2, dated November 2, 2016, see this service information at http://www.regulations.gov by searching for and locating Docket No. FAA-2017-0774. Costs of Compliance We estimate that this proposed AD affects 411 airplanes of U.S. registry. We estimate the following costs to comply with this proposed AD: Estimated Costs ---------------------------------------------------------------------------------------------------------------- Action Labor cost Parts cost Cost per product Cost on U.S. operators ---------------------------------------------------------------------------------------------------------------- Inspections for cracking 18 work-hours x $85 $0 $1,530 per $628,830 per inspection under the stop fittings and per hour = $1,530 inspection cycle. intercostal flanges per inspection cycle. cycle. [retained actions from AD 2012-12-05] (411 airplanes). Inspection of areas forward 2 work-hours x $85 0 $170 per $69,870 per inspection of the aft entry door per hour = $170 per inspection cycle. [retained actions from AD inspection cycle. cycle. 2012-12-05] (411 airplanes). Inspection of areas aft of 1 work-hour x $85 per 0 $85 per $34,935 per inspection the forward entry door hour = $85 per inspection cycle. [retained actions from AD inspection cycle. cycle. 2012-12-05] (411 airplanes). Inspection for missing 1 work-hour x $85 per 476 $561............ $230,571. fasteners [retained actions hour = $85. from AD 2012-12-05] (411 airplanes). Inspection of fastener holes 27 work[dash]hours x 0 $2,295 per $367,200 per inspection (new proposed action) (160 $85 per hour = inspection cycle. airplanes). $2,295 per cycle. inspection cycle. ---------------------------------------------------------------------------------------------------------------- We estimate the following costs to do any necessary repairs that would be required based on the results of the inspections. We have no way of determining the number of aircraft that might need these repairs: [[Page 38639]] On-Condition Costs ---------------------------------------------------------------------------------------------------------------- Cost per Action Labor cost Parts cost product ---------------------------------------------------------------------------------------------------------------- Repair of cracking done in accordance with 24 work-hours x $85 per hour = $11,856 $13,896 Boeing Alert Service Bulletin 737-53A1240. $2,040. ---------------------------------------------------------------------------------------------------------------- We have received no definitive data that would enable us to provide cost estimates for the other on-condition corrective actions specified in this proposed AD. Authority for This Rulemaking 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. This proposed AD is issued in accordance with authority delegated by the Executive Director, Aircraft Certification Service, as authorized by FAA Order 8000.51C. In accordance with that order, issuance of ADs is normally a function of the Compliance and Airworthiness Division, but during this transition period, the Executive Director has delegated the authority to issue ADs applicable to transport category airplanes to the Director of the System Oversight Division. Regulatory Findings 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. List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. The Proposed Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA proposes to amend 14 CFR part 39 as follows: PART 39--AIRWORTHINESS DIRECTIVES 0 1. The authority citation for part 39 continues to read as follows: Authority: 49 U.S.C. 106(g), 40113, 44701. Sec. 39.13 [Amended] 0 2. The FAA amends Sec. 39.13 by removing Airworthiness Directive (AD) 2012-12-05, Amendment 39-17084 (77 FR 36139, June 18, 2012), and adding the following new AD: The Boeing Company: Docket No. FAA-2017-0774; Product Identifier 2017-NM-036-AD. (a) Comments Due Date The FAA must receive comments on this AD action by September 29, 2017. (b) Affected ADs This AD replaces AD 2012-12-05, Amendment 39-17084 (77 FR 36139, June 18, 2012) (``AD 2012-12-05''). (c) Applicability This AD applies to all The Boeing Company Model 737-100, -200, - 200C, -300, -400, and -500 series airplanes, certificated in any category. (d) Subject (d) Air Transport Association (ATA) of America Code 53, Fuselage. (e) Unsafe Condition This AD was prompted by reports of cracking of the station (STA) 348.2 frame above the two outboard fasteners attaching the frame inner chord and door stop fittings, and in the outboard chord at stringer S-16L; missing fasteners in the STA 348.2 frame inner chord; and additional cracking in locations not covered by the inspections in AD 2012-12-05. We are issuing this AD to detect and correct fatigue cracking of the intercostals on the forward and aft sides of the forward entry door cutout, which could result in loss of the forward entry door and rapid decompression of the airplane. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Retained Initial Compliance Time for Model 737-100, -200, -200C, - 300, -400, and -500 Series Airplanes, With No Changes This paragraph restates the requirements of paragraph (i) of AD 2012-12-05, with no changes. For all Model 737-100, -200, -200C, - 300, -400, and -500 series airplanes, as identified in Boeing Alert Service Bulletin 737-53A1204, Revision 1, dated March 26, 2007: Before the accumulation of 15,000 total flight cycles, or within 4,500 flight cycles after November 1, 2005 (the effective date of AD 2005-20-03, Amendment 39-14296 (70 FR 56361, September 27, 2005) (``AD 2005-20-03'')), whichever occurs later: Do the inspections required by paragraphs (i) and (j) of this AD. (h) Retained Initial Compliance Time for Model 737-200C Series Airplanes, With No Changes This paragraph restates the requirements of paragraph (j) of AD 2012-12-05, with no changes. For all Model 737-200C series airplanes, as identified in Boeing Alert Service Bulletin 737- 53A1204, Revision 1, dated March 26, 2007: Before the accumulation of 15,000 total flight cycles, or within 4,500 flight cycles after September 9, 2009 (the effective date of AD 2009-16-14, Amendment 39-15987 (74 FR 38901, August 5, 2009) (``AD 2009-16-14'')), whichever occurs later, do the inspection required by paragraph (k) of this AD. (i) Retained Initial Inspection for Group 1 Configuration Airplanes, With No Changes This paragraph restates the requirements of paragraph (k) of AD 2012-12-05, with no changes. For Group 1 airplanes identified in Boeing Alert Service Bulletin 737-53A1204, Revision 1, dated March 26, 2007: Perform a detailed inspection for cracking of the intercostal web, attachment clips, and stringer splice channels; and a high frequency eddy current (HFEC) inspection for cracking of the stringer splice channels located forward and aft of the forward entry door; and do all applicable corrective actions before further flight; in accordance with Parts [[Page 38640]] 1 and 2 of the Work Instructions of Boeing Special Attention Service Bulletin 737-53-1204, dated June 19, 2003, or Boeing Alert Service Bulletin 737-53A1204, Revision 1, dated March 26, 2007; or in accordance with Parts 1, 2, 4, and 5 of the Work Instructions of Boeing Alert Service Bulletin 737-53A1204, Revision 2, dated June 24, 2010. After September 9, 2009 (the effective date of AD 2009-16- 14), and until July 23, 2012 (the effective date of AD 2012-12-05), Boeing Alert Service Bulletin 737-53A1204, Revision 1, dated March 26, 2007; or Boeing Alert Service Bulletin 737-53A1204, Revision 2, dated June 24, 2010; may be used to accomplish the actions required by this paragraph. As of July 23, 2012, only Boeing Alert Service Bulletin 737-53A1204, Revision 2, dated June 24, 2010, may be used to accomplish the actions required by this paragraph. (j) Retained Initial Inspection for Cargo Configuration Airplanes (Forward of the Forward Entry Door), With No Changes This paragraph restates the requirements of paragraph (l) of AD 2012-12-05, with no changes. For Group 2 cargo airplanes identified in Boeing Alert Service Bulletin 737-53A1204, Revision 1, dated March 26, 2007: Perform a detailed inspection for cracking of the intercostal webs and attachment clips located forward of the forward entry door, and do all applicable corrective actions before further flight, in accordance with Part 3 of the Work Instructions of Boeing Special Attention Service Bulletin 737-53-1204, dated June 19, 2003, or Boeing Alert Service Bulletin 737-53A1204, Revision 1, dated March 26, 2007; or in accordance with Part 3 of Boeing Alert Service Bulletin 737-53A1204, Revision 2, dated June 24, 2010. After September 9, 2009 (the effective date of AD 2009-16-14), and until July 23, 2012 (the effective date of AD 2012-12-05), Boeing Alert Service Bulletin 737-53A1204, Revision 1, dated March 26, 2007; or Boeing Alert Service Bulletin 737-53A1204, Revision 2, dated June 24, 2010; may be used to accomplish the actions required by this paragraph. As of July 23, 2012, only Boeing Alert Service Bulletin 737-53A1204, Revision 2, dated June 24, 2010, may be used to accomplish the actions required by this paragraph. (k) Retained Initial Inspection for Cargo Configuration Airplanes (Aft of the Forward Entry Door), With No Changes This paragraph restates the requirements of paragraph (m) of AD 2012-12-05, with no changes. For Group 2 cargo airplanes identified in Boeing Alert Service Bulletin 737-53A1204, Revision 1, dated March 26, 2007: Perform a detailed inspection for cracking of the intercostal webs and attachment clips located aft of the forward entry door, and do all applicable corrective actions before further flight, in accordance with Part 4 of the Work Instructions of Boeing Alert Service Bulletin 737-53A1204, Revision 1, dated March 26, 2007; or in accordance with Part 3 of Boeing Alert Service Bulletin 737-53A1204, Revision 2, dated June 24, 2010. As of July 23, 2012 (the effective date of AD 2012-12-05), only Boeing Alert Service Bulletin 737-53A1204, Revision 2, dated June 24, 2010, may be used to accomplish the actions required by this paragraph. (l) Retained Repetitive Inspections, With No Changes This paragraph restates the requirements of paragraph (n) of AD 2012-12-05, with no changes. Repeat the inspections required by paragraphs (i), (j), and (k) of this AD thereafter at intervals not to exceed 6,000 flight cycles after the previous inspection, or within 3,000 flight cycles after September 9, 2009, whichever occurs later. (m) Retained Exceptions to Boeing Special Attention Service Bulletin 737-53-1204, With No Changes This paragraph restates the requirements of paragraph (o) of AD 2012-12-05, with no changes. Do the actions required by paragraphs (g), (h), (i), (j), (k), and (l) of this AD by accomplishing all the applicable actions specified in the Accomplishment Instructions of Boeing Special Attention Service Bulletin 737-53-1204, dated June 19, 2003; Boeing Alert Service Bulletin 737-53A1204, Revision 1, dated March 26, 2007; or Boeing Alert Service Bulletin 737-53A1204, Revision 2, dated June 24, 2010; except as provided by paragraphs (m)(1) and (m)(2) of this AD. After September 9, 2009 (the effective date of AD 2009-16-14), and until July 23, 2012 (the effective date of AD 2012-12-05), Boeing Alert Service Bulletin 737-53A1204, Revision 1, dated March 26, 2007; or Boeing Alert Service Bulletin 737-53A1204, Revision 2, dated June 24, 2010; may be used to accomplish the actions required by this paragraph. As of July 23, 2012, only Boeing Alert Service Bulletin 737-53A1204, Revision 2, dated June 24, 2010, may be used to accomplish the actions required by this paragraph. (1) Where Boeing Special Attention Service Bulletin 737-53-1204, dated June 19, 2003; Boeing Alert Service Bulletin 737-53A1204, Revision 1, dated March 26, 2007; or Boeing Alert Service Bulletin 737-53A1204, Revision 2, dated June 24, 2010, specifies to contact Boeing for repair instructions: Before further flight, repair using a method approved in accordance with the procedures specified in paragraph (s) of this AD. (2) Where Boeing Special Attention Service Bulletin 737-53-1204, dated June 19, 2003; or Boeing Alert Service Bulletin 737-53A1204, Revision 1, dated March 26, 2007; specifies a compliance time relative to the date of a service bulletin, this AD requires compliance relative to September 9, 2009 (the effective date of AD 2009-16-14). Where Boeing Special Attention Service Bulletin 737-53- 1204, dated June 19, 2003; or Boeing Alert Service Bulletin 737- 53A1204, Revision 1, dated March 26, 2007; specifies a compliance time relative to the date of the initial release of a service bulletin, this AD requires compliance relative to November 1, 2005 (the effective date of AD 2005-20-03). (n) Retained Exceptions to Boeing Alert Service Bulletin 737-53A1204, With No Changes This paragraph restates exceptions to Boeing Alert Service Bulletin 737-53A1204 specified in paragraph (r) of AD 2012-12-05, with no changes. (1) The access and restoration instructions identified in the Work Instructions of Boeing Alert Service Bulletin 737-53A1204, Revision 2, dated June 24, 2010, are not required by this AD. Operators may perform those actions in accordance with approved maintenance procedures. (2) The use of Boeing Drawing 65-88700 is not allowed when accomplishing the actions required by this AD in accordance with the Work Instructions of Boeing Alert Service Bulletin 737-53A1204, Revision 2, dated June 24, 2010. (o) Retained Initial and Repetitive Inspections of the S-15L Aft Intercostal and Cargo Barrier Net Fitting for Model 737-200C Series Airplanes, With No Changes This paragraph restates the requirements of paragraph (s) of AD 2012-12-05, with no changes. For Group 2 airplanes identified in Boeing Alert Service Bulletin 737-53A1204, Revision 2, dated June 24, 2010: Before the accumulation of 15,000 total flight cycles, or within 4,500 flight cycles after July 23, 2012 (the effective date of AD 2012-12-05), whichever occurs later, do initial detailed and HFEC inspections for cracking of the S-15L aft intercostal between BS 348.2 and BS 360, and do a detailed inspection of the cargo barrier net fitting at the intercostal, in accordance with Figure 3 of the Accomplishment Instructions of Boeing Alert Service Bulletin 737-53A1204, Revision 2, dated June 24, 2010. If any cracking is found, before further flight, repair using a method approved in accordance with the procedures specified in paragraph (s) of this AD. Repeat the inspections thereafter at intervals not to exceed 6,000 flight cycles. (p) Actions for Boeing Alert Service Bulletin 737-53A1240, Including New Repetitive Inspections of Certain Fastener Holes (1) For airplanes identified as Group 1 and Group 3 in Boeing Alert Service Bulletin 737-53A1240, Revision 2, dated November 2, 2016: Except as required by paragraph (q) of this AD, at the applicable times specified in paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin 737-53A1240, Revision 2, dated November 2, 2016, do all applicable actions identified as ``RC'' (required for compliance) in, and in accordance with, the Accomplishment Instructions of Boeing Alert Service Bulletin 737- 53A1240, Revision 2, dated November 2, 2016. (2) For airplanes identified as Group 2 in Boeing Alert Service Bulletin 737-53A1240, Revision 2, dated November 2, 2016: Within 120 days after the effective date of this AD, do actions to correct the unsafe condition using a method approved in accordance with the procedures specified in paragraph (s) of this AD. (q) Exceptions to Service Information Specifications (1) Where Boeing Alert Service Bulletin 737-53A1240, Revision 2, dated November 2, 2016, uses the phrase ``after the Revision 2 date of this service bulletin,'' for purposes of determining compliance with the [[Page 38641]] requirements of this AD, the phrase ``after the effective date of this AD'' must be used. (2) Where Boeing Alert Service Bulletin 737-53A1240, Revision 2, dated November 2, 2016, specifies contacting Boeing, and specifies that action as RC: This AD requires using a method approved in accordance with the procedures specified in paragraph (s) of this AD. (r) Credit for Previous Actions This paragraph provides credit for the actions specified in paragraph (p) of this AD, if those actions were performed before the effective date of this AD using Boeing Alert Service Bulletin 737- 53A1240, Revision 1, dated June 29, 2010, provided the conditions specified in paragraphs (r)(1) and (r)(2) of this AD are met and except as provided by paragraph (r)(3) of this AD. Boeing Alert Service Bulletin 737-53A1240, Revision 1, dated June 29, 2010, was incorporated by reference in AD 2012-12-05. (1) Note 1 of paragraph 3.A of the Accomplishment Instructions of Boeing Alert Service Bulletin 737-53A1240, Revision 1, dated June 29, 2010, was disregarded when accomplishing the actions. (2) Boeing Drawing 65-88700 was not used when accomplishing the actions in accordance with the Work Instructions of Boeing Alert Service Bulletin 737-53A1240, Revision 1, dated June 29, 2010. (3) The access and restoration instructions identified in the Work Instructions of Boeing Alert Service Bulletin 737-53A1240, Revision 1, dated June 29, 2010, are not required. Operators are allowed to perform those actions in accordance with approved maintenance procedures. (s) Alternative Methods of Compliance (AMOCs) (1) The Manager, Los Angeles Aircraft Certification Office (ACO) Branch, 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 directly to the manager of the certification office, send it to the attention of the person identified in paragraph (t)(1) of this AD. Information may be emailed to: [email protected]. (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, modification, or alteration required by this AD if it is approved by the Boeing Commercial Airplanes Organization Designation Authorization (ODA) that has been authorized by the Manager, Los Angeles ACO Branch, to make those findings. To be approved, the repair method, modification deviation, or alteration deviation must meet the certification basis of the airplane, and the approval must specifically refer to this AD. (4) Except as required by paragraph (q)(2) of this AD: For service information that contains steps that are labeled as Required for Compliance (RC), the provisions of paragraphs (s)(4)(i) and (s)(4)(ii) of this AD apply. (i) The steps labeled as RC, including substeps under an RC step and any figures identified in an RC step, must be done to comply with the AD. If a step or substep is labeled ``RC Exempt,'' then the RC requirement is removed from that step or substep. An AMOC is required for any deviations to RC steps, including substeps and identified figures. (ii) Steps not labeled as RC may be deviated from using accepted methods in accordance with the operator's maintenance or inspection program without obtaining approval of an AMOC, provided the RC steps, including substeps and identified figures, can still be done as specified, and the airplane can be put back in an airworthy condition. (t) Related Information (1) For more information about this AD, contact Galib Abumeri, Aerospace Engineer, Airframe Branch, ANM-120L, FAA, Los Angeles Aircraft Certification Office (ACO) Branch, 3960 Paramount Boulevard, Lakewood, CA 90712-4137; phone: 562-627-5324; fax: 562- 627-5210; email: [email protected]. (2) For service information identified in this AD, contact Boeing Commercial Airplanes, Attention: Contractual & Data Services (C&DS), 2600 Westminster Blvd., MC 110-SK57, Seal Beach, CA 90740; telephone 562-797-1717; Internet https://www.myboeingfleet.com. You may view this referenced service information at the FAA, Transport Standards Branch, 1601 Lind Avenue SW., Renton, WA. For information on the availability of this material at the FAA, call 425-227-1221. Issued in Renton, Washington, on August 2, 2017. Jeffrey E. Duven, Director, System Oversight Division, Aircraft Certification Service. [FR Doc. 2017-16776 Filed 8-14-17; 8:45 am] BILLING CODE 4910-13-P
![Federal Register / Vol. 82, No. 156 / Tuesday, August 15, 2017 / Proposed Rules 38637
for this AD, if requested using the procedures Issued in Renton, Washington, on July 28, W12–140, 1200 New Jersey Avenue SE.,
found in 14 CFR 39.19. In accordance with 2017. Washington, DC 20590.
14 CFR 39.19, send your request to your John P. Piccola, Jr., • Hand Delivery: Deliver to Mail
principal inspector or local Flight Standards Acting Director, System Oversight Division, address above between 9 a.m. and 5
District Office, as appropriate. If sending Aircraft Certification Service. p.m., Monday through Friday, except
information directly to the manager of the Federal holidays.
[FR Doc. 2017–16578 Filed 8–14–17; 8:45 am]
certification office, send it to the attention of For service information identified in
BILLING CODE 4910–13–P
the person identified in paragraph (k)(1) of this NPRM, contact Boeing Commercial
this AD. Information may be emailed to: 9-
Airplanes, Attention: Contractual & Data
ANM-Seattle-ACO-AMOC-Requests@faa.gov.
(2) Before using any approved AMOC, DEPARTMENT OF TRANSPORTATION Services (C&DS), 2600 Westminster
notify your appropriate principal inspector, Blvd., MC 110–SK57, Seal Beach, CA
or lacking a principal inspector, the manager Federal Aviation Administration 90740; telephone 562–797–1717;
of the local flight standards district office/ Internet https://
certificate holding district office. 14 CFR Part 39 www.myboeingfleet.com. You may view
(3) An AMOC that provides an acceptable this referenced service information at
[Docket No. FAA–2017–0774; Product
level of safety may be used for any repair, Identifier 2017–NM–036–AD] the FAA, Transport Standards Branch,
modification, or alteration required by this 1601 Lind Avenue SW., Renton, WA.
AD if it is approved by the Boeing RIN 2120–AA64 For information on the availability of
Commercial Airplanes Organization this material at the FAA, call 425–227–
Designation Authorization (ODA) that has Airworthiness Directives; The Boeing 1221. It is also available on the internet
been authorized by the Manager, Seattle ACO Company Airplanes at http://www.regulations.gov by
Branch, to make those findings. To be searching for and locating Docket No.
approved, the repair method, modification
AGENCY: Federal Aviation
Administration (FAA), DOT. FAA–2017–0774.
deviation, or alteration deviation must meet
the certification basis of the airplane, and the ACTION: Notice of proposed rulemaking Examining the AD Docket
approval must specifically refer to this AD. (NPRM). You may examine the AD docket on
(4) AMOCs approved previously for AD
SUMMARY: We propose to supersede the Internet at http://
2015–19–12 are approved as AMOCs for the
corresponding provisions of paragraph (g) of Airworthiness Directive (AD) 2012–12– www.regulations.gov by searching for
this AD. 05, which applies to all The Boeing and locating Docket No. FAA–2017–
(5) Except as required by paragraph (h)(1) Company Model 737–100, –200, –200C, 0774; or in person at the Docket
of this AD: For service information that –300, –400, and –500 series airplanes. Management Facility between 9 a.m.
contains steps that are labeled as Required AD 2012–12–05 currently requires and 5 p.m., Monday through Friday,
for Compliance (RC), the provisions of repetitive inspections for cracking under except Federal holidays. The AD docket
paragraphs (j)(5)(i) and (j)(5)(ii) of this AD the stop fittings and intercostal flanges contains this proposed AD, the
apply.
and for cracking of the intercostal web, regulatory evaluation, any comments
(i) The steps labeled as RC, including received, and other information. The
substeps under an RC step and any figures attachment clips, stringer splice
channels, frame, reinforcement angle, street address for the Docket Office
identified in an RC step, must be done to (phone: 800–647–5527) is in the
comply with the AD. If a step or substep is shear web, frame outer chord and inner
ADDRESSES section. Comments will be
labeled ‘‘RC Exempt,’’ then the RC chord; a one-time inspection to detect
missing fasteners; repetitive inspections available in the AD docket shortly after
requirement is removed from that step or
receipt.
substep. An AMOC is required for any of the cargo barrier net fitting for
deviations to RC steps, including substeps cracking; repetitive inspections for FOR FURTHER INFORMATION CONTACT:
and identified figures. cracking of the stringer S–15L aft Galib Abumeri, Aerospace Engineer,
(ii) Steps not labeled as RC may be intercostal; and repair or corrective Airframe Section, FAA, Los Angeles
deviated from using accepted methods in action if necessary. Since we issued AD Aircraft Certification Office (ACO)
accordance with the operator’s maintenance
2012–12–05, we have received reports Branch, 3960 Paramount Boulevard,
or inspection program without obtaining Lakewood, CA 90712–4137; phone:
approval of an AMOC, provided the RC steps,
of additional cracking in locations not
covered by the inspections in that AD. 562–627–5324; fax: 562–627–5210;
including substeps and identified figures, can email: galib.abumeri@faa.gov.
still be done as specified, and the airplane For certain airplanes, this proposed AD
would add new repetitive inspections of SUPPLEMENTARY INFORMATION:
can be put back in an airworthy condition.
certain areas of the frame inner chord, Comments Invited
(k) Related Information and applicable on-condition actions. We
(1) For more information about this AD, We invite you to send any written
are proposing this AD to address the
contact Wayne Lockett, Aerospace Engineer, relevant data, views, or arguments about
unsafe condition on these products.
Airframe Section, FAA, Seattle ACO Branch, this proposed AD. Send your comments
DATES: We must receive comments on to an address listed under the
1601 Lind Avenue SW., Renton, WA 98057–
3356; phone: 425–917–6447; fax: 425–917– this proposed AD by September 29, ADDRESSES section. Include ‘‘Docket No.
6590; email: wayne.lockett@faa.gov. 2017. FAA–2017–0774; Product Identifier
(2) For service information identified in ADDRESSES: You may send comments, 2017–NM–036–AD’’ at the beginning of
this AD, contact Boeing Commercial using the procedures found in 14 CFR your comments. We specifically invite
Airplanes, Attention: Contractual & Data 11.43 and 11.45, by any of the following comments on the overall regulatory,
mstockstill on DSK30JT082PROD with PROPOSALS
Services (C&DS), 2600 Westminster Blvd.,
methods: economic, environmental, and energy
MC 110–SK57, Seal Beach, CA 90740–5600;
telephone 562–797–1717; Internet https://
• Federal eRulemaking Portal: Go to aspects of this proposed AD. We will
www.myboeingfleet.com. You may view this http://www.regulations.gov. Follow the consider all comments received by the
referenced service information at the FAA, instructions for submitting comments. closing date and may amend this
Transport Standards Branch, 1601 Lind • Fax: 202–493–2251. proposed AD because of those
Avenue SW., Renton, WA. For information • Mail: U.S. Department of comments.
on the availability of this material at the Transportation, Docket Operations, M– We will post all comments we
FAA, call 425–227–1221. 30, West Building Ground Floor, Room receive, without change, to http://
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![38638 Federal Register / Vol. 82, No. 156 / Tuesday, August 15, 2017 / Proposed Rules
www.regulations.gov, including any entry door cutout, which could result in described previously is likely to exist or
personal information you provide. We loss of the forward entry door and rapid develop in other products of the same
will also post a report summarizing each decompression of the airplane. type design.
substantive verbal contact we receive
Actions Since AD 2012–12–05 Was Proposed AD Requirements
about this proposed AD.
Issued
Discussion This proposed AD would retain all
Since we issued AD 2012–12–05, we requirements of AD 2012–12–05.
On June 4, 2012, we issued AD 2012– have received reports of additional Although this proposed AD does not
12–05, Amendment 39–17084 (77 FR cracking in the STA 351.2 frame inner explicitly restate the actions in Boeing
36139, June 18, 2012) (‘‘AD 2012–12– chord at stringer S–17L, at the fastener Alert Service Bulletin 737–53A1240,
05’’), for all The Boeing Company Model hole location common to the frame Revision 1, dated June 29, 2010, that are
737–100, –200, –200C, –300, –400, and inner chord, door sill, and shear web. part of the requirements of AD 2012–
–500 series airplanes. AD 2012–12–05 The cracks were reported on Model 12–05, this proposed AD would retain
superseded AD 2004–09–09, 737–300 and –500 airplanes that had those requirements. Those requirements
Amendment 39–13598 (69 FR 23646, accumulated between 40,600 and 65,500 are referenced in the service information
April 30, 2004); and AD 2009–16–14, total flight cycles. The STA 351.2 frame identified previously, which, in turn, is
Amendment 39–15987 (74 FR 38901, inner chord at stringer S–17L is hidden referenced in paragraph (p) of this
August 5, 2009). AD 2012–12–05 under the shear web and the door sill; proposed AD. Paragraph (p) of this
requires repetitive inspections for therefore, any cracking at this location proposed AD would require
cracking under the stop fittings and cannot be visually detected. accomplishment of the actions
intercostal flanges and for cracking of
Related Service Information Under 1 identified as ‘‘RC’’ (required for
the intercostal web, attachment clips,
CFR Part 51 compliance) in the Accomplishment
stringer splice channels, frame,
Instructions of Boeing Alert Service
reinforcement angle, shear web, frame We reviewed Boeing Alert Service
Bulletin 737–53A1240, Revision 2,
outer chord and inner chord; a one-time Bulletin 737–53A1240, Revision 2,
inspection to detect missing fasteners; dated November 2, 2016, except for any
dated November 2, 2016. The service
repetitive inspections of the cargo differences identified as exceptions in
information describes procedures for,
barrier net fitting for cracking; repetitive the regulatory text of this proposed AD.
among other actions, repetitive
inspections for cracking of the stringer inspections of the fastener holes in the For information on the procedures
S–15L aft intercostal; and repair or STA 351.2 frame inner chord at stringer and compliance times for Boeing Alert
corrective action if necessary. AD 2012– 17L, and applicable on-condition Service Bulletin 737–53A1240, Revision
12–05 resulted from reports of cracking actions. This service information is 2, dated November 2, 2016, see this
of the station (STA) 348.2 frame above reasonably available because the service information at http://
the two outboard fasteners attaching the interested parties have access to it www.regulations.gov by searching for
frame inner chord and door stop fittings, through their normal course of business and locating Docket No. FAA–2017–
and in the outboard chord at stringer S– or by the means identified in the 0774.
16L. AD 2012–12–05 also resulted from ADDRESSES section. Costs of Compliance
reports of missing fasteners in the STA
348.2 frame inner chord. We issued AD FAA’s Determination We estimate that this proposed AD
2012–12–05 to detect and correct fatigue We are proposing this AD because we affects 411 airplanes of U.S. registry. We
cracking of the intercostals on the evaluated all the relevant information estimate the following costs to comply
forward and aft sides of the forward and determined the unsafe condition with this proposed AD:
ESTIMATED COSTS
Action Labor cost Parts cost Cost per product Cost on U.S.
operators
Inspections for cracking under the stop 18 work-hours × $85 per hour = $1,530 $0 $1,530 per inspec- $628,830 per in-
fittings and intercostal flanges [re- per inspection cycle. tion cycle. spection cycle.
tained actions from AD 2012–12–05]
(411 airplanes).
Inspection of areas forward of the aft 2 work-hours × $85 per hour = $170 0 $170 per inspection $69,870 per in-
entry door [retained actions from AD per inspection cycle. cycle. spection cycle.
2012–12–05] (411 airplanes).
Inspection of areas aft of the forward 1 work-hour × $85 per hour = $85 per 0 $85 per inspection $34,935 per in-
entry door [retained actions from AD inspection cycle. cycle. spection cycle.
2012–12–05] (411 airplanes).
Inspection for missing fasteners [re- 1 work-hour × $85 per hour = $85 ........ 476 $561 ....................... $230,571.
tained actions from AD 2012–12–05]
(411 airplanes).
Inspection of fastener holes (new pro- 27 work-hours × $85 per hour = $2,295 0 $2,295 per inspec- $367,200 per in-
posed action) (160 airplanes). per inspection cycle. tion cycle. spection cycle.
mstockstill on DSK30JT082PROD with PROPOSALS
We estimate the following costs to do required based on the results of the determining the number of aircraft that
any necessary repairs that would be inspections. We have no way of might need these repairs:
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![Federal Register / Vol. 82, No. 156 / Tuesday, August 15, 2017 / Proposed Rules 38639
ON-CONDITION COSTS
Cost per
Action Labor cost Parts cost product
Repair of cracking done in accordance with Boeing 24 work-hours × $85 per hour = $2,040 ...................... $11,856 $13,896
Alert Service Bulletin 737–53A1240.
We have received no definitive data (2) Is not a ‘‘significant rule’’ under the frame inner chord and door stop fittings,
that would enable us to provide cost the DOT Regulatory Policies and and in the outboard chord at stringer S–16L;
estimates for the other on-condition Procedures (44 FR 11034, February 26, missing fasteners in the STA 348.2 frame
inner chord; and additional cracking in
corrective actions specified in this 1979),
locations not covered by the inspections in
proposed AD. (3) Will not affect intrastate aviation AD 2012–12–05. We are issuing this AD to
in Alaska, and detect and correct fatigue cracking of the
Authority for This Rulemaking (4) Will not have a significant intercostals on the forward and aft sides of
Title 49 of the United States Code economic impact, positive or negative, the forward entry door cutout, which could
specifies the FAA’s authority to issue on a substantial number of small entities result in loss of the forward entry door and
rules on aviation safety. Subtitle I, under the criteria of the Regulatory rapid decompression of the airplane.
Section 106, describes the authority of Flexibility Act. (f) Compliance
the FAA Administrator. Subtitle VII, List of Subjects in 14 CFR Part 39 Comply with this AD within the
Aviation Programs, describes in more compliance times specified, unless already
detail the scope of the Agency’s Air transportation, Aircraft, Aviation done.
authority. safety, Incorporation by reference,
Safety. (g) Retained Initial Compliance Time for
We are issuing this rulemaking under Model 737–100, –200, –200C, –300, –400, and
the authority described in Subtitle VII, The Proposed Amendment –500 Series Airplanes, With No Changes
Part A, Subpart III, Section 44701, This paragraph restates the requirements of
Accordingly, under the authority
‘‘General requirements.’’ Under that paragraph (i) of AD 2012–12–05, with no
delegated to me by the Administrator,
section, Congress charges the FAA with changes. For all Model 737–100, –200,
the FAA proposes to amend 14 CFR part
promoting safe flight of civil aircraft in –200C, –300, –400, and –500 series airplanes,
39 as follows:
air commerce by prescribing regulations as identified in Boeing Alert Service Bulletin
for practices, methods, and procedures 737–53A1204, Revision 1, dated March 26,
PART 39—AIRWORTHINESS 2007: Before the accumulation of 15,000 total
the Administrator finds necessary for DIRECTIVES
safety in air commerce. This regulation flight cycles, or within 4,500 flight cycles
after November 1, 2005 (the effective date of
is within the scope of that authority ■ 1. The authority citation for part 39 AD 2005–20–03, Amendment 39–14296 (70
because it addresses an unsafe condition continues to read as follows: FR 56361, September 27, 2005) (‘‘AD 2005–
that is likely to exist or develop on Authority: 49 U.S.C. 106(g), 40113, 44701. 20–03’’)), whichever occurs later: Do the
products identified in this rulemaking inspections required by paragraphs (i) and (j)
action. § 39.13 [Amended] of this AD.
This proposed AD is issued in ■ 2. The FAA amends § 39.13 by (h) Retained Initial Compliance Time for
accordance with authority delegated by removing Airworthiness Directive (AD) Model 737–200C Series Airplanes, With No
the Executive Director, Aircraft 2012–12–05, Amendment 39–17084 (77 Changes
Certification Service, as authorized by FR 36139, June 18, 2012), and adding This paragraph restates the requirements of
FAA Order 8000.51C. In accordance the following new AD: paragraph (j) of AD 2012–12–05, with no
with that order, issuance of ADs is The Boeing Company: Docket No. FAA– changes. For all Model 737–200C series
normally a function of the Compliance 2017–0774; Product Identifier 2017– airplanes, as identified in Boeing Alert
and Airworthiness Division, but during NM–036–AD. Service Bulletin 737–53A1204, Revision 1,
this transition period, the Executive dated March 26, 2007: Before the
(a) Comments Due Date accumulation of 15,000 total flight cycles, or
Director has delegated the authority to
The FAA must receive comments on this within 4,500 flight cycles after September 9,
issue ADs applicable to transport 2009 (the effective date of AD 2009–16–14,
category airplanes to the Director of the AD action by September 29, 2017.
Amendment 39–15987 (74 FR 38901, August
System Oversight Division. (b) Affected ADs 5, 2009) (‘‘AD 2009–16–14’’)), whichever
This AD replaces AD 2012–12–05, occurs later, do the inspection required by
Regulatory Findings paragraph (k) of this AD.
Amendment 39–17084 (77 FR 36139, June
We have determined that this 18, 2012) (‘‘AD 2012–12–05’’). (i) Retained Initial Inspection for Group 1
proposed AD would not have federalism (c) Applicability Configuration Airplanes, With No Changes
implications under Executive Order This paragraph restates the requirements of
13132. This proposed AD would not This AD applies to all The Boeing
Company Model 737–100, –200, –200C, paragraph (k) of AD 2012–12–05, with no
have a substantial direct effect on the –300, –400, and –500 series airplanes, changes. For Group 1 airplanes identified in
States, on the relationship between the certificated in any category. Boeing Alert Service Bulletin 737–53A1204,
mstockstill on DSK30JT082PROD with PROPOSALS
national Government and the States, or Revision 1, dated March 26, 2007: Perform a
on the distribution of power and (d) Subject detailed inspection for cracking of the
responsibilities among the various (d) Air Transport Association (ATA) of intercostal web, attachment clips, and
levels of government. America Code 53, Fuselage. stringer splice channels; and a high
frequency eddy current (HFEC) inspection for
For the reasons discussed above, I (e) Unsafe Condition cracking of the stringer splice channels
certify that the proposed regulation: This AD was prompted by reports of located forward and aft of the forward entry
(1) Is not a ‘‘significant regulatory cracking of the station (STA) 348.2 frame door; and do all applicable corrective actions
action’’ under Executive Order 12866, above the two outboard fasteners attaching before further flight; in accordance with Parts
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![Federal Register / Vol. 82, No. 156 / Tuesday, August 15, 2017 / Proposed Rules 38641
requirements of this AD, the phrase ‘‘after the for Compliance (RC), the provisions of airplanes. This proposed AD was
effective date of this AD’’ must be used. paragraphs (s)(4)(i) and (s)(4)(ii) of this ADprompted by reports of cracks found in
(2) Where Boeing Alert Service Bulletin apply. the lower chord of the left wing rear
737–53A1240, Revision 2, dated November 2, (i) The steps labeled as RC, including spar. This proposed AD would require
2016, specifies contacting Boeing, and substeps under an RC step and any figures
specifies that action as RC: This AD requires identified in an RC step, must be done to
repetitive inspections for cracking of the
using a method approved in accordance with comply with the AD. If a step or substep is lower chord of the rear spar and lower
the procedures specified in paragraph (s) of labeled ‘‘RC Exempt,’’ then the RC aft skin at wing buttock line (WBL) 157
this AD. requirement is removed from that step or and applicable on-condition actions. We
substep. An AMOC is required for any are proposing this AD to address the
(r) Credit for Previous Actions
deviations to RC steps, including substeps unsafe condition on these products.
This paragraph provides credit for the and identified figures. DATES: We must receive comments on
actions specified in paragraph (p) of this AD, (ii) Steps not labeled as RC may be
if those actions were performed before the this proposed AD by September 29,
deviated from using accepted methods in
effective date of this AD using Boeing Alert accordance with the operator’s maintenance 2017.
Service Bulletin 737–53A1240, Revision 1, or inspection program without obtaining ADDRESSES: You may send comments,
dated June 29, 2010, provided the conditions approval of an AMOC, provided the RC steps, using the procedures found in 14 CFR
specified in paragraphs (r)(1) and (r)(2) of this including substeps and identified figures, can11.43 and 11.45, by any of the following
AD are met and except as provided by still be done as specified, and the airplane
paragraph (r)(3) of this AD. Boeing Alert
methods:
can be put back in an airworthy condition.
Service Bulletin 737–53A1240, Revision 1, • Federal eRulemaking Portal: Go to
dated June 29, 2010, was incorporated by (t) Related Information http://www.regulations.gov. Follow the
reference in AD 2012–12–05. (1) For more information about this AD, instructions for submitting comments.
(1) Note 1 of paragraph 3.A of the contact Galib Abumeri, Aerospace Engineer, • Fax: 202–493–2251.
Accomplishment Instructions of Boeing Alert Airframe Branch, ANM–120L, FAA, Los • Mail: U.S. Department of
Service Bulletin 737–53A1240, Revision 1, Angeles Aircraft Certification Office (ACO) Transportation, Docket Operations, M–
dated June 29, 2010, was disregarded when Branch, 3960 Paramount Boulevard, 30, West Building Ground Floor, Room
accomplishing the actions. Lakewood, CA 90712–4137; phone: 562–627– W12–140, 1200 New Jersey Avenue SE.,
(2) Boeing Drawing 65–88700 was not used 5324; fax: 562–627–5210; email: Washington, DC 20590.
when accomplishing the actions in galib.abumeri@faa.gov. • Hand Delivery: Deliver to Mail
accordance with the Work Instructions of (2) For service information identified in
address above between 9 a.m. and 5
Boeing Alert Service Bulletin 737–53A1240, this AD, contact Boeing Commercial
Revision 1, dated June 29, 2010. Airplanes, Attention: Contractual & Data p.m., Monday through Friday, except
(3) The access and restoration instructions Services (C&DS), 2600 Westminster Blvd., Federal holidays.
identified in the Work Instructions of Boeing MC 110–SK57, Seal Beach, CA 90740; For service information identified in
Alert Service Bulletin 737–53A1240, telephone 562–797–1717; Internet https:// this NPRM, contact Boeing Commercial
Revision 1, dated June 29, 2010, are not www.myboeingfleet.com. You may view this Airplanes, Attention: Contractual & Data
required. Operators are allowed to perform referenced service information at the FAA, Services (C&DS), 2600 Westminster
those actions in accordance with approved Transport Standards Branch, 1601 Lind Blvd., MC 110–SK57, Seal Beach, CA
maintenance procedures. Avenue SW., Renton, WA. For information 90740–5600; telephone 562–797–1717;
on the availability of this material at the Internet https://
(s) Alternative Methods of Compliance
FAA, call 425–227–1221.
(AMOCs) www.myboeingfleet.com. You may view
(1) The Manager, Los Angeles Aircraft Issued in Renton, Washington, on August this referenced service information at
Certification Office (ACO) Branch, FAA, has 2, 2017. the FAA, Transport Standards Branch,
the authority to approve AMOCs for this AD, Jeffrey E. Duven, 1601 Lind Avenue SW., Renton, WA.
if requested using the procedures found in 14 Director, System Oversight Division, Aircraft For information on the availability of
CFR 39.19. In accordance with 14 CFR 39.19, Certification Service. this material at the FAA, call 425–227–
send your request to your principal inspector [FR Doc. 2017–16776 Filed 8–14–17; 8:45 am] 1221. It is also available on the Internet
or local Flight Standards District Office, as BILLING CODE 4910–13–P at http://www.regulations.gov by
appropriate. If sending information directly
to the manager of the certification office,
searching for and locating Docket No.
send it to the attention of the person FAA–2017–0773.
identified in paragraph (t)(1) of this AD. DEPARTMENT OF TRANSPORTATION
Examining the AD Docket
Information may be emailed to: 9-ANM-
LAACO-AMOC-Requests@faa.gov. Federal Aviation Administration You may examine the AD docket on
(2) Before using any approved AMOC, the Internet at http://
notify your appropriate principal inspector, 14 CFR Part 39 www.regulations.gov by searching for
or lacking a principal inspector, the manager and locating Docket No. FAA–2017–
[Docket No. FAA–2017–0773; Product
of the local flight standards district office/ 0773; or in person at the Docket
Identifier 2017–NM–067–AD]
certificate holding district office. Management Facility between 9 a.m.
(3) An AMOC that provides an acceptable RIN 2120–AA64 and 5 p.m., Monday through Friday,
level of safety may be used for any repair,
modification, or alteration required by this except Federal holidays. The AD docket
Airworthiness Directives; The Boeing contains this NPRM, the regulatory
AD if it is approved by the Boeing Company Airplanes
Commercial Airplanes Organization evaluation, any comments received, and
Designation Authorization (ODA) that has AGENCY: Federal Aviation other information. The street address for
mstockstill on DSK30JT082PROD with PROPOSALS
been authorized by the Manager, Los Angeles Administration (FAA), DOT. the Docket Office (phone: 800–647–
ACO Branch, to make those findings. To be 5527) is in the ADDRESSES section.
approved, the repair method, modification ACTION: Notice of proposed rulemaking
(NPRM). Comments will be available in the AD
deviation, or alteration deviation must meet docket shortly after receipt.
the certification basis of the airplane, and the
approval must specifically refer to this AD. SUMMARY: We propose to adopt a new FOR FURTHER INFORMATION CONTACT:
(4) Except as required by paragraph (q)(2) airworthiness directive (AD) for all The Payman Soltani, Aerospace Engineer,
of this AD: For service information that Boeing Company Model 737–100, –200, Airframe Section, FAA, Los Angeles
contains steps that are labeled as Required –200C, –300, –400, and –500 series Aircraft Certification Office (ACO)
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Document Created: 2017-08-15 01:13:00
Document Modified: 2017-08-15 01:13:00
| Category | Regulatory Information | |
| Collection | Federal Register | |
| sudoc Class | AE 2.7: GS 4.107: AE 2.106: | |
| Publisher | Office of the Federal Register, National Archives and Records Administration | |
| Section | Proposed Rules | |
| Action | Notice of proposed rulemaking (NPRM). | |
| Dates | We must receive comments on this proposed AD by September 29, 2017. | |
| Contact | Galib Abumeri, Aerospace Engineer, Airframe Section, FAA, Los Angeles Aircraft Certification Office (ACO) Branch, 3960 Paramount Boulevard, Lakewood, CA 90712-4137; phone: 562- 627-5324; fax: 562-627-5210; email: [email protected] | |
| FR Citation | 82 FR 38637 | |
| RIN Number | 2120-AA64 | |
| CFR Associated | Air Transportation; Aircraft; Aviation Safety; Incorporation by Reference and Safety |
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