81 FR 29508 - Airworthiness Directives; The Boeing Company Airplanes
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration Federal Register Volume 81, Issue 92 (May 12, 2016)
Federal Aviation Administration
Federal Register Volume 81, Issue 92 (May 12, 2016)
| Page Range | 29508-29511 | |
| FR Document | 2016-11168 |
[Federal Register Volume 81, Number 92 (Thursday, May 12, 2016)] [Proposed Rules] [Pages 29508-29511] From the Federal Register Online [www.thefederalregister.org] [FR Doc No: 2016-11168] ----------------------------------------------------------------------- DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA-2016-6669; Directorate Identifier 2015-NM-191-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) 2006-20- 11, which applies to certain The Boeing Company Model 757-200, -200CB, and -200PF series airplanes. AD 2006-20-11 currently requires initial and repetitive detailed or high frequency eddy current (HFEC) inspections for cracks around the rivets at the upper fastener row of the skin lap splice of the fuselage, and repairing any crack found. Since we issued AD 2006-20-11, an evaluation done by the design approval holder (DAH) indicated that the fuselage skin lap splice is subject to widespread fatigue damage (WFD). This proposed AD would no longer allow the detailed inspections and would instead require repetitive external HFEC inspections for cracking of the skin lap splices of the fuselage, and repair if necessary. We are proposing this AD to detect and correct fatigue cracking at certain skin lap splice locations of the fuselage, which could result in reduced structural integrity and rapid decompression of the airplane. DATES: We must receive comments on this proposed AD by June 27, 2016. 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: Data & Services Management, 3855 Lakewood Boulevard, MC D800-0019, Long Beach, CA 90846-0001; telephone: 206-544-5000, extension 2; fax: 206-766-5683; Internet https://www.myboeingfleet.com. You may view this referenced service information at the FAA, Transport Airplane Directorate, 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-2016- 6669. 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-2016- 6669; 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: Eric Schrieber, Aerospace Engineer, Airframe Branch, ANM-120L, FAA, Los Angeles Aircraft Certification Office (ACO), 3960 Paramount Boulevard, Lakewood, CA 90712-4137; phone: 562-627-5348; 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-2016-6669; Directorate Identifier 2015-NM-191-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://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 September 22, 2006, we issued AD 2006-20-11, Amendment 39-14781 (71 FR 58485, October 4, 2006) (``AD 2006-20-11''), for certain The Boeing Company Model 757-200, -200CB, and -200PF series airplanes. AD 2006-20-11 requires initial and repetitive detailed or HFEC inspections for cracks around the rivets at the upper fastener row of the skin lap splice of the fuselage, and repairing any crack found. AD 2006-20-11 resulted from reports of cracking in the fuselage skin of the crown skin panel. We issued AD 2006-20-11 to detect and correct premature fatigue cracking at certain skin lap splice locations of the fuselage, and consequent rapid decompression of the airplane. Structural fatigue damage is progressive. It begins as minute cracks, and those cracks grow under the action of repeated stresses. This can happen because of normal operational conditions and design attributes, or [[Page 29509]] because of isolated situations or incidents such as material defects, poor fabrication quality, or corrosion pits, dings, or scratches. Fatigue damage can occur locally, in small areas or structural design details, or globally. Global fatigue damage is general degradation of large areas of structure with similar structural details and stress levels. Multiple-site damage is global damage that occurs in a large structural element such as a single rivet line of a lap splice joining two large skin panels. Global damage can also occur in multiple elements such as adjacent frames or stringers. Multiple-site-damage and multiple-element-damage cracks are typically too small initially to be reliably detected with normal inspection methods. Without intervention, these cracks will grow, and eventually compromise the structural integrity of the airplane, in a condition known as WFD. As an airplane ages, WFD will likely occur, and will certainly occur if the airplane is operated long enough without any intervention. The FAA's WFD final rule (75 FR 69746, November 15, 2010) became effective on January 14, 2011. The WFD rule requires certain actions to prevent structural failure due to WFD throughout the operational life of certain existing transport category airplanes and all of these airplanes that will be certificated in the future. For existing and future airplanes subject to the WFD rule, the rule requires that DAHs establish a limit of validity (LOV) of the engineering data that support the structural maintenance program. Operators affected by the WFD rule may not fly an airplane beyond its LOV, unless an extended LOV is approved. The WFD rule (75 FR 69746, November 15, 2010) does not require identifying and developing maintenance actions if the DAHs can show that such actions are not necessary to prevent WFD before the airplane reaches the LOV. Many LOVs, however, do depend on accomplishment of future maintenance actions. As stated in the WFD rule, any maintenance actions necessary to reach the LOV will be mandated by airworthiness directives through separate rulemaking actions. In the context of WFD, this action is necessary to enable DAHs to propose LOVs that allow operators the longest operational lives for their airplanes, and still ensure that WFD will not occur. This approach allows for an implementation strategy that provides flexibility to DAHs in determining the timing of service information development (with FAA approval), while providing operators with certainty regarding the LOV applicable to their airplanes. We are proposing this AD to detect and correct fatigue cracking at certain skin lap splice locations of the fuselage, which could result in reduced structural integrity and rapid decompression of the airplane. Actions Since AD 2006-20-11 Was Issued Since issuance of AD 2006-20-11, an evaluation done by the DAH indicated that the fuselage skin lap splice is subject to WFD. We have determined that the detailed inspection that is allowed as an option in AD 2006-20-11, does not adequately address the identified unsafe condition. Only HFEC inspections are adequate to address the identified unsafe condition. Related Service Information Under 1 CFR Part 51 We reviewed Boeing Special Attention Service Bulletin 757-53-0090, Revision 1, dated November 19, 2015. The service information describes procedures for repetitive external HFEC inspections for cracking of the skin lap splices of the fuselage. 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 require accomplishing the actions specified in the service information described previously. For information on the procedures and compliance times, see this service information at http://www.regulations.gov by searching for and locating Docket No. FAA-2016- 6669. Costs of Compliance We estimate that this proposed AD affects 572 airplanes of U.S. registry. We estimate the following costs to comply with this proposed AD: Estimated Costs ---------------------------------------------------------------------------------------------------------------- Cost on U.S. Action Labor cost Parts cost Cost per product operators ---------------------------------------------------------------------------------------------------------------- Inspections [retained actions Up to 20 work-hours x $0 Up to $1,700 per Up to $972,400 per from AD 2006-20-11]. $85 per hour = up to inspection cycle. inspection cycle. $1,700 per inspection cycle. New proposed inspections....... Up to 20 work-hours x 0 Up to $1,700 per Up to $972,400 per $85 per hour = up to inspection cycle. inspection cycle. $1,700 per inspection cycle. ---------------------------------------------------------------------------------------------------------------- We have received no definitive data that would enable us to provide a cost estimate for the on-condition repairs 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. 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. [[Page 29510]] 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) 2006-20-11, Amendment 39-14781 (71 FR 58485, October 4, 2006), and adding the following new AD: The Boeing Company: Docket No. FAA-2016-6669; Directorate Identifier 2015-NM-191-AD. (a) Comments Due Date The FAA must receive comments on this AD action by June 27, 2016. (b) Affected ADs This AD replaces AD 2006-20-11, Amendment 39-14781 (71 FR 58485, October 4, 2006) (``AD 2006-20-11''). This AD affects AD 2006-11-11, Amendment 39-14615 (71 FR 30278, May 26, 2006) (``AD 2006-11-11''). (c) Applicability (c) This AD applies to The Boeing Company Model 757-200, -200CB, and -200PF series airplanes, certificated in any category, as identified in Boeing Special Attention Service Bulletin 757-53-0090, Revision 1, dated November 19, 2015. (d) Subject Air Transport Association (ATA) of America Code 53, Fuselage. (e) Unsafe Condition This AD was prompted by an evaluation done by the design approval holder which indicated that the fuselage skin lap splice is subject to widespread fatigue damage. We are issuing this AD to detect and correct fatigue cracking at certain skin lap splice locations of the fuselage, which could result in reduced structural integrity and rapid decompression of the airplane. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Retained Initial and Repetitive Inspections With Terminating Action This paragraph restates the requirements of paragraph (f) of AD 2006-20-11, with terminating action. Do initial and repetitive detailed or high frequency eddy current (HFEC) inspections for cracking around the rivets at the upper fastener row of the skin lap splice of the fuselage by doing all the actions in accordance with the Accomplishment Instructions of Boeing Special Attention Service Bulletin 757-53-0090, dated June 2, 2005, except as provided by paragraphs (h) and (i) of this AD. Do the inspections at the applicable times specified in Paragraph 1.E., ``Compliance,'' of Boeing Special Attention Service Bulletin 757-53-0090, dated June 2, 2005; except where Boeing Special Attention Service Bulletin 757-53- 0090, dated June 2, 2005, specifies a compliance time ``after the original release date of this service bulletin,'' this AD requires compliance after November 8, 2006 (the effective date of AD 2006-20- 11). Accomplishing an inspection required by paragraph (j) of this AD terminates the inspections required by this paragraph. (h) Retained Repair With No Changes This paragraph restates the requirements of paragraph (g) of AD 2006-20-11, with no changes. If any crack is found during any inspection required by paragraph (g) of this AD: Before further flight, repair the crack using a method approved in accordance with the procedures specified in paragraph (m) of this AD. (i) Retained No Reporting Required With No Changes This paragraph restates the provision specified in paragraph (h) of AD 2006-20-11, with no changes. Although Boeing Special Attention Service Bulletin 757-53-0090, dated June 2, 2005, recommends that inspection results be reported to the manufacturer, this AD does not include that requirement. (j) New Repetitive Inspections At the applicable time specified in table 1 of paragraph 1.E., ``Compliance,'' of Boeing Special Attention Service Bulletin 757-53- 0090, Revision 1, dated November 19, 2015, except as provided by paragraph (l)(1) of this AD: Do an external high frequency eddy current (HFEC) inspection for cracking of the skin lap splices of the fuselage, in accordance with the Accomplishment Instructions of Boeing Special Attention Service Bulletin 757-53-0090, Revision 1, dated November 19, 2015. Repeat the inspection thereafter at the applicable times specified in table 1 of paragraph 1.E., ``Compliance,'' of Boeing Special Attention Service Bulletin 757-53- 0090, Revision 1, dated November 19, 2015. Doing an inspection required by this paragraph terminates the inspections required by paragraph (g) of this AD. (k) Repair for Cracking Found During Inspections Required by Paragraph (j) of This AD If any cracking is found during any inspection required by paragraph (j) of this AD, repair before further flight using a method approved in accordance with the procedures specified in paragraph (m) of this AD. (l) Exceptions to Service Information (1) Where Boeing Special Attention Service Bulletin 757-53-0090, Revision 1, dated November 19, 2015, specifies a compliance time ``after the Revision 1 date of this service bulletin,'' this AD requires compliance within the specified compliance time after the effective date of this AD. (2) Although Boeing Special Attention Service Bulletin 757-53- 0090, Revision 1, dated November 19, 2015, specifies to contact Boeing for repair instructions, and specifies that action as ``RC'' (Required for Compliance), paragraph (k) of this AD requires repair before further flight using a method approved in accordance with the procedures specified in paragraph (m) of this AD. (m) Alternative Methods of Compliance (AMOCs) (1) The Manager, Los Angeles 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. 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 ACO, send it to the attention of the person identified in paragraph (n)(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, 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) AMOCs approved for AD 2006-20-11, are approved as AMOCs for the corresponding provisions of paragraphs (g) and (j) of this AD. (5) Except as required by paragraph (l)(2) of this AD: For service information that contains steps that are labeled as Required for Compliance (RC), the provisions of paragraphs (m)(5)(i) and (m)(5)(ii) apply. (i) The steps labeled as RC, including substeps under an RC step and any figures [[Page 29511]] identified in an RC step, must be done to comply with the AD. 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. (6) The inspections specified in paragraph (g) of this AD are approved as an AMOC to paragraph (h) of AD 2006-11-11 for the inspections of Significant Structural Items (SSI) 53-30-07 and 53- 60-07 (fuselage lap splices, left and right upper fastener row) listed in the May 2003 or June 2005 revision of the Boeing 757 Maintenance Planning Data (MPD) Document D622N001-9. This AMOC applies only to the common areas identified in paragraphs (m)(6)(i) and (m)(6)(ii) of this AD. All provisions of AD 2006-11-11 that are not specifically referenced in the above statements remain fully applicable and must be complied with as specified in AD 2006-11-11. Operators may revise their FAA-approved maintenance or inspection program with these alternative inspections for common areas. (i) Common areas inspected before the effective date of this AD in accordance with the Accomplishment Instructions of Boeing Special Attention Service Bulletin 757-53-0090, dated June 2, 2005. (ii) Common areas inspected in accordance with the Accomplishment Instructions of Boeing Special Attention Service Bulletin 757-53-0090, Revision 1, dated November 19, 2015. (n) Related Information (1) For more information about this AD, contact Eric Schrieber, Aerospace Engineer, Airframe Branch, ANM-120L, FAA, Los Angeles Aircraft Certification Office (ACO), 3960 Paramount Boulevard, Lakewood, CA 90712-4137; phone: 562-627-5348; fax: 562-627-5210; email: [email protected]. (2) For service information identified in this AD, contact Boeing Commercial Airplanes, Attention: Data & Services Management, 3855 Lakewood Boulevard, MC D800-0019, Long Beach, CA 90846-0001; telephone: 206-544-5000, extension 2; fax: 206-766-5683; Internet https://www.myboeingfleet.com. You may view this referenced service information at the FAA, Transport Airplane Directorate, 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 May 5, 2016. Michael Kaszycki, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2016-11168 Filed 5-11-16; 8:45 am] BILLING CODE 4910-13-P
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(4) AMOCs approved previously for the eddy current (HFEC) inspections for contains this proposed AD, the
optional preventive modification installed in cracks around the rivets at the upper regulatory evaluation, any comments
accordance with paragraph (h) of AD 2013– fastener row of the skin lap splice of the received, and other information. The
19–04, and AMOCs approved previously for fuselage, and repairing any crack found. street address for the Docket Office
repairs for AD 2013–19–04, are approved as
AMOCs for the corresponding provisions of
Since we issued AD 2006–20–11, an (phone: 800–647–5527) is in the
this AD, provided that such modification or evaluation done by the design approval ADDRESSES section. Comments will be
repair included installation of the splice holder (DAH) indicated that the fuselage available in the AD docket shortly after
plate as specified in Boeing Special Attention skin lap splice is subject to widespread receipt.
Service Bulletin 737–53–1294, except as fatigue damage (WFD). This proposed FOR FURTHER INFORMATION CONTACT: Eric
provided by paragraph (l)(5) of this AD. AD would no longer allow the detailed Schrieber, Aerospace Engineer,
(5) The time-limited repair approved as inspections and would instead require Airframe Branch, ANM–120L, FAA, Los
specified in FAA Letter 120S–15–140, dated repetitive external HFEC inspections for
June 3, 2015, is approved as an AMOC to the
Angeles Aircraft Certification Office
cracking of the skin lap splices of the (ACO), 3960 Paramount Boulevard,
corresponding requirements of this AD.
fuselage, and repair if necessary. We are Lakewood, CA 90712–4137; phone:
(m) Related Information proposing this AD to detect and correct 562–627–5348; fax: 562–627–5210;
(1) For more information about this AD, fatigue cracking at certain skin lap email: eric.schrieber@faa.gov.
contact Alan Pohl, Aerospace Engineer, splice locations of the fuselage, which SUPPLEMENTARY INFORMATION:
Airframe Branch, ANM–120S, FAA, Seattle could result in reduced structural
Aircraft Certification Office, 1601 Lind integrity and rapid decompression of Comments Invited
Avenue SW., Renton, WA 98057–3356; the airplane.
phone: 425–917–6450; fax: 425–917–6590; We invite you to send any written
email: alan.pohl@faa.gov. DATES: We must receive comments on relevant data, views, or arguments about
(2) For service information identified in this proposed AD by June 27, 2016. this proposed AD. Send your comments
this AD, contact Boeing Commercial ADDRESSES: You may send comments, to an address listed under the
Airplanes, Attention: Data & Services using the procedures found in 14 CFR ADDRESSES section. Include ‘‘Docket No.
Management, P.O. Box 3707, MC 2H–65, 11.43 and 11.45, by any of the following FAA–2016–6669; Directorate Identifier
Seattle, WA 98124–2207; telephone 206– methods: 2015–NM–191–AD’’ at the beginning of
544–5000, extension 1; fax 206–766–5680;
• Federal eRulemaking Portal: Go to your comments. We specifically invite
Internet https://www.myboeingfleet.com. You
may view this referenced service information http://www.regulations.gov. Follow the comments on the overall regulatory,
at the FAA, Transport Airplane Directorate, instructions for submitting comments. economic, environmental, and energy
1601 Lind Avenue SW., Renton, WA. You • Fax: 202–493–2251. aspects of this proposed AD. We will
may view this referenced service information • Mail: U.S. Department of consider all comments received by the
at the FAA, Transport Airplane Directorate, Transportation, Docket Operations, M– closing date and may amend this
1601 Lind Avenue SW., Renton, WA. For 30, West Building Ground Floor, Room proposed AD because of those
information on the availability of this W12–140, 1200 New Jersey Avenue SE., comments.
material at the FAA, call 425–227–1221. Washington, DC 20590. We will post all comments we
Issued in Renton, Washington, on May 5, • Hand Delivery: Deliver to Mail receive, without change, to http://
2016. address above between 9 a.m. and 5 www.regulations.gov, including any
Michael Kaszycki, p.m., Monday through Friday, except personal information you provide. We
Acting Manager, Transport Airplane Federal holidays. will also post a report summarizing each
Directorate, Aircraft Certification Service. For service information identified in substantive verbal contact we receive
[FR Doc. 2016–11167 Filed 5–11–16; 8:45 am] this NPRM, contact Boeing Commercial about this proposed AD.
BILLING CODE 4910–13–P Airplanes, Attention: Data & Services
Discussion
Management, 3855 Lakewood
Boulevard, MC D800–0019, Long Beach, On September 22, 2006, we issued AD
DEPARTMENT OF TRANSPORTATION CA 90846–0001; telephone: 206–544– 2006–20–11, Amendment 39–14781 (71
5000, extension 2; fax: 206–766–5683; FR 58485, October 4, 2006) (‘‘AD 2006–
Federal Aviation Administration Internet https:// 20–11’’), for certain The Boeing
www.myboeingfleet.com. You may view Company Model 757–200, –200CB, and
14 CFR Part 39 this referenced service information at –200PF series airplanes. AD 2006–20–
[Docket No. FAA–2016–6669; Directorate the FAA, Transport Airplane 11 requires initial and repetitive
Identifier 2015–NM–191–AD] Directorate, 1601 Lind Avenue SW., detailed or HFEC inspections for cracks
Renton, WA. For information on the around the rivets at the upper fastener
RIN 2120–AA64 availability of this material at the FAA, row of the skin lap splice of the
call 425–227–1221. It is also available fuselage, and repairing any crack found.
Airworthiness Directives; The Boeing
on the Internet at http:// AD 2006–20–11 resulted from reports of
Company Airplanes
www.regulations.gov by searching for cracking in the fuselage skin of the
AGENCY: Federal Aviation and locating Docket No. FAA–2016– crown skin panel. We issued AD 2006–
Administration (FAA), DOT. 6669. 20–11 to detect and correct premature
ACTION: Notice of proposed rulemaking fatigue cracking at certain skin lap
Examining the AD Docket splice locations of the fuselage, and
jstallworth on DSK7TPTVN1PROD with PROPOSALS
(NPRM).
You may examine the AD docket on consequent rapid decompression of the
SUMMARY: We propose to supersede the Internet at http:// airplane.
Airworthiness Directive (AD) 2006–20– www.regulations.gov by searching for Structural fatigue damage is
11, which applies to certain The Boeing and locating Docket No. FAA–2016– progressive. It begins as minute cracks,
Company Model 757–200, –200CB, and 6669; or in person at the Docket and those cracks grow under the action
–200PF series airplanes. AD 2006–20– Management Facility between 9 a.m. of repeated stresses. This can happen
11 currently requires initial and and 5 p.m., Monday through Friday, because of normal operational
repetitive detailed or high frequency except Federal holidays. The AD docket conditions and design attributes, or
VerDate Sep<11>2014 13:23 May 11, 2016 Jkt 238001 PO 00000 Frm 00004 Fmt 4702 Sfmt 4702 E:\FR\FM\12MYP1.SGM 12MYP1](https://thefederalregister.org/doc/81_FR_29600/page/1.svg)
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because of isolated situations or not fly an airplane beyond its LOV, address the identified unsafe condition.
incidents such as material defects, poor unless an extended LOV is approved. Only HFEC inspections are adequate to
fabrication quality, or corrosion pits, The WFD rule (75 FR 69746, address the identified unsafe condition.
dings, or scratches. Fatigue damage can November 15, 2010) does not require
identifying and developing maintenance Related Service Information Under 1
occur locally, in small areas or
actions if the DAHs can show that such CFR Part 51
structural design details, or globally.
Global fatigue damage is general actions are not necessary to prevent We reviewed Boeing Special
degradation of large areas of structure WFD before the airplane reaches the Attention Service Bulletin 757–53–
with similar structural details and stress LOV. Many LOVs, however, do depend 0090, Revision 1, dated November 19,
levels. Multiple-site damage is global on accomplishment of future 2015. The service information describes
damage that occurs in a large structural maintenance actions. As stated in the procedures for repetitive external HFEC
element such as a single rivet line of a WFD rule, any maintenance actions inspections for cracking of the skin lap
lap splice joining two large skin panels. necessary to reach the LOV will be splices of the fuselage. This service
Global damage can also occur in mandated by airworthiness directives information is reasonably available
multiple elements such as adjacent through separate rulemaking actions. because the interested parties have
frames or stringers. Multiple-site- In the context of WFD, this action is access to it through their normal course
damage and multiple-element-damage necessary to enable DAHs to propose of business or by the means identified
cracks are typically too small initially to LOVs that allow operators the longest in the ADDRESSES section.
be reliably detected with normal operational lives for their airplanes, and
still ensure that WFD will not occur. FAA’s Determination
inspection methods. Without
intervention, these cracks will grow, This approach allows for an We are proposing this AD because we
and eventually compromise the implementation strategy that provides evaluated all the relevant information
structural integrity of the airplane, in a flexibility to DAHs in determining the and determined the unsafe condition
condition known as WFD. As an timing of service information described previously is likely to exist or
airplane ages, WFD will likely occur, development (with FAA approval), develop in other products of the same
and will certainly occur if the airplane while providing operators with certainty type design.
is operated long enough without any regarding the LOV applicable to their
airplanes. Proposed AD Requirements
intervention.
We are proposing this AD to detect
The FAA’s WFD final rule (75 FR and correct fatigue cracking at certain This proposed AD would require
69746, November 15, 2010) became skin lap splice locations of the fuselage, accomplishing the actions specified in
effective on January 14, 2011. The WFD which could result in reduced structural the service information described
rule requires certain actions to prevent integrity and rapid decompression of previously. For information on the
structural failure due to WFD the airplane. procedures and compliance times, see
throughout the operational life of this service information at http://
certain existing transport category Actions Since AD 2006–20–11 Was www.regulations.gov by searching for
airplanes and all of these airplanes that Issued and locating Docket No. FAA–2016–
will be certificated in the future. For Since issuance of AD 2006–20–11, an 6669.
existing and future airplanes subject to evaluation done by the DAH indicated Costs of Compliance
the WFD rule, the rule requires that that the fuselage skin lap splice is
DAHs establish a limit of validity (LOV) subject to WFD. We estimate that this proposed AD
of the engineering data that support the We have determined that the detailed affects 572 airplanes of U.S. registry.
structural maintenance program. inspection that is allowed as an option We estimate the following costs to
Operators affected by the WFD rule may in AD 2006–20–11, does not adequately comply with this proposed AD:
ESTIMATED COSTS
Cost on U.S.
Action Labor cost Parts cost Cost per product operators
Inspections [retained actions from AD Up to 20 work-hours × $85 per hour = $0 Up to $1,700 per in- Up to $972,400 per
2006–20–11]. up to $1,700 per inspection cycle. spection cycle. inspection cycle.
New proposed inspections ..................... Up to 20 work-hours × $85 per hour = 0 Up to $1,700 per in- Up to $972,400 per
up to $1,700 per inspection cycle. spection cycle. inspection cycle.
We have received no definitive data We are issuing this rulemaking under products identified in this rulemaking
that would enable us to provide a cost the authority described in Subtitle VII, action.
estimate for the on-condition repairs Part A, Subpart III, Section 44701, Regulatory Findings
specified in this proposed AD. ‘‘General requirements.’’ Under that
section, Congress charges the FAA with We have determined that this
Authority for This Rulemaking proposed AD would not have federalism
jstallworth on DSK7TPTVN1PROD with PROPOSALS
promoting safe flight of civil aircraft in
Title 49 of the United States Code implications under Executive Order
air commerce by prescribing regulations
specifies the FAA’s authority to issue 13132. This proposed AD would not
for practices, methods, and procedures
rules on aviation safety. Subtitle I, have a substantial direct effect on the
the Administrator finds necessary for
Section 106, describes the authority of States, on the relationship between the
the FAA Administrator. Subtitle VII, safety in air commerce. This regulation national Government and the States, or
Aviation Programs, describes in more is within the scope of that authority on the distribution of power and
detail the scope of the Agency’s because it addresses an unsafe condition responsibilities among the various
authority. that is likely to exist or develop on levels of government.
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![29510 Federal Register / Vol. 81, No. 92 / Thursday, May 12, 2016 / Proposed Rules
For the reasons discussed above, I subject to widespread fatigue damage. We are 0090, Revision 1, dated November 19, 2015.
certify that the proposed regulation: issuing this AD to detect and correct fatigue Doing an inspection required by this
(1) Is not a ‘‘significant regulatory cracking at certain skin lap splice locations paragraph terminates the inspections
of the fuselage, which could result in required by paragraph (g) of this AD.
action’’ under Executive Order 12866,
reduced structural integrity and rapid
(2) Is not a ‘‘significant rule’’ under (k) Repair for Cracking Found During
decompression of the airplane.
the DOT Regulatory Policies and Inspections Required by Paragraph (j) of
Procedures (44 FR 11034, February 26, (f) Compliance This AD
1979), Comply with this AD within the If any cracking is found during any
(3) Will not affect intrastate aviation compliance times specified, unless already inspection required by paragraph (j) of this
in Alaska, and done. AD, repair before further flight using a
method approved in accordance with the
(4) Will not have a significant (g) Retained Initial and Repetitive procedures specified in paragraph (m) of this
economic impact, positive or negative, Inspections With Terminating Action AD.
on a substantial number of small entities This paragraph restates the requirements of
under the criteria of the Regulatory (l) Exceptions to Service Information
paragraph (f) of AD 2006–20–11, with
Flexibility Act. terminating action. Do initial and repetitive (1) Where Boeing Special Attention Service
detailed or high frequency eddy current Bulletin 757–53–0090, Revision 1, dated
List of Subjects in 14 CFR Part 39 (HFEC) inspections for cracking around the November 19, 2015, specifies a compliance
Air transportation, Aircraft, Aviation rivets at the upper fastener row of the skin time ‘‘after the Revision 1 date of this service
lap splice of the fuselage by doing all the bulletin,’’ this AD requires compliance
safety, Incorporation by reference, within the specified compliance time after
actions in accordance with the
Safety. Accomplishment Instructions of Boeing the effective date of this AD.
The Proposed Amendment Special Attention Service Bulletin 757–53– (2) Although Boeing Special Attention
0090, dated June 2, 2005, except as provided Service Bulletin 757–53–0090, Revision 1,
Accordingly, under the authority by paragraphs (h) and (i) of this AD. Do the dated November 19, 2015, specifies to
delegated to me by the Administrator, inspections at the applicable times specified contact Boeing for repair instructions, and
the FAA proposes to amend 14 CFR part in Paragraph 1.E., ‘‘Compliance,’’ of Boeing specifies that action as ‘‘RC’’ (Required for
39 as follows: Special Attention Service Bulletin 757–53– Compliance), paragraph (k) of this AD
0090, dated June 2, 2005; except where requires repair before further flight using a
PART 39—AIRWORTHINESS Boeing Special Attention Service Bulletin method approved in accordance with the
757–53–0090, dated June 2, 2005, specifies a procedures specified in paragraph (m) of this
DIRECTIVES
compliance time ‘‘after the original release AD.
■ 1. The authority citation for part 39 date of this service bulletin,’’ this AD (m) Alternative Methods of Compliance
requires compliance after November 8, 2006
continues to read as follows: (AMOCs)
(the effective date of AD 2006–20–11).
Authority: 49 U.S.C. 106(g), 40113, 44701. Accomplishing an inspection required by (1) The Manager, Los Angeles Aircraft
paragraph (j) of this AD terminates the Certification Office (ACO), FAA, has the
§ 39.13 [Amended] inspections required by this paragraph. authority to approve AMOCs for this AD, if
■ 2. The FAA amends § 39.13 by requested using the procedures found in 14
(h) Retained Repair With No Changes CFR 39.19. In accordance with 14 CFR 39.19,
removing Airworthiness Directive (AD)
This paragraph restates the requirements of send your request to your principal inspector
2006–20–11, Amendment 39–14781 (71 or local Flight Standards District Office, as
paragraph (g) of AD 2006–20–11, with no
FR 58485, October 4, 2006), and adding changes. If any crack is found during any appropriate. If sending information directly
the following new AD: inspection required by paragraph (g) of this to the manager of the ACO, send it to the
The Boeing Company: Docket No. FAA– AD: Before further flight, repair the crack attention of the person identified in
2016–6669; Directorate Identifier 2015– using a method approved in accordance with paragraph (n)(1) of this AD. Information may
NM–191–AD. the procedures specified in paragraph (m) of be emailed to: 9-ANM-LAACO-AMOC-
this AD. Requests@faa.gov.
(a) Comments Due Date (2) Before using any approved AMOC,
(i) Retained No Reporting Required With No notify your appropriate principal inspector,
The FAA must receive comments on this
Changes or lacking a principal inspector, the manager
AD action by June 27, 2016.
This paragraph restates the provision of the local flight standards district office/
(b) Affected ADs specified in paragraph (h) of AD 2006–20–11, certificate holding district office.
This AD replaces AD 2006–20–11, with no changes. Although Boeing Special (3) An AMOC that provides an acceptable
Amendment 39–14781 (71 FR 58485, October Attention Service Bulletin 757–53–0090, level of safety may be used for any repair,
4, 2006) (‘‘AD 2006–20–11’’). This AD affects dated June 2, 2005, recommends that modification, or alteration required by this
AD 2006–11–11, Amendment 39–14615 (71 inspection results be reported to the AD if it is approved by the Boeing
FR 30278, May 26, 2006) (‘‘AD 2006–11– manufacturer, this AD does not include that Commercial Airplanes Organization
11’’). requirement. Designation Authorization (ODA) that has
been authorized by the Manager, Los Angeles
(c) Applicability (j) New Repetitive Inspections ACO, to make those findings. To be approved
(c) This AD applies to The Boeing At the applicable time specified in table 1 the repair method, modification deviation, or
Company Model 757–200, –200CB, and of paragraph 1.E., ‘‘Compliance,’’ of Boeing alteration deviation must meet the
–200PF series airplanes, certificated in any Special Attention Service Bulletin 757–53– certification basis of the airplane and the
category, as identified in Boeing Special 0090, Revision 1, dated November 19, 2015, approval must specifically refer to this AD.
Attention Service Bulletin 757–53–0090, except as provided by paragraph (l)(1) of this (4) AMOCs approved for AD 2006–20–11,
Revision 1, dated November 19, 2015. AD: Do an external high frequency eddy are approved as AMOCs for the
jstallworth on DSK7TPTVN1PROD with PROPOSALS
current (HFEC) inspection for cracking of the corresponding provisions of paragraphs (g)
(d) Subject skin lap splices of the fuselage, in accordance and (j) of this AD.
Air Transport Association (ATA) of with the Accomplishment Instructions of (5) Except as required by paragraph (l)(2)
America Code 53, Fuselage. Boeing Special Attention Service Bulletin of this AD: For service information that
757–53–0090, Revision 1, dated November contains steps that are labeled as Required
(e) Unsafe Condition 19, 2015. Repeat the inspection thereafter at for Compliance (RC), the provisions of
This AD was prompted by an evaluation the applicable times specified in table 1 of paragraphs (m)(5)(i) and (m)(5)(ii) apply.
done by the design approval holder which paragraph 1.E., ‘‘Compliance,’’ of Boeing (i) The steps labeled as RC, including
indicated that the fuselage skin lap splice is Special Attention Service Bulletin 757–53– substeps under an RC step and any figures
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![Federal Register / Vol. 81, No. 92 / Thursday, May 12, 2016 / Proposed Rules 29511
identified in an RC step, must be done to DEPARTMENT OF TRANSPORTATION 30, West Building Ground Floor, Room
comply with the AD. An AMOC is required W12–140, 1200 New Jersey Avenue SE.,
for any deviations to RC steps, including Federal Aviation Administration Washington, DC 20590.
substeps and identified figures. • Hand Delivery: U.S. Department of
(ii) Steps not labeled as RC may be 14 CFR Part 39 Transportation, Docket Operations, M–
deviated from using accepted methods in 30, West Building Ground Floor, Room
[Docket No. FAA–2015–0077; Directorate
accordance with the operator’s maintenance W12–140, 1200 New Jersey Avenue SE.,
Identifier 2013–NM–254–AD]
or inspection program without obtaining Washington, DC, between 9 a.m. and 5
approval of an AMOC, provided the RC steps, RIN 2120–AA64 p.m., Monday through Friday, except
including substeps and identified figures, can Federal holidays.
still be done as specified, and the airplane Airworthiness Directives; ATR—GIE
Avions de Transport Régional For service information identified in
can be put back in an airworthy condition.
Airplanes this SNPRM, contact ATR—GIE Avions
(6) The inspections specified in paragraph
de Transport Régional, 1, Allée Pierre
(g) of this AD are approved as an AMOC to AGENCY: Federal Aviation Nadot, 31712 Blagnac Cedex, France;
paragraph (h) of AD 2006–11–11 for the
Administration (FAA), DOT. telephone +33 (0) 5 62 21 62 21; fax +33
inspections of Significant Structural Items
(SSI) 53–30–07 and 53–60–07 (fuselage lap ACTION: Supplemental notice of (0) 5 62 21 67 18; email
splices, left and right upper fastener row) proposed rulemaking (NPRM); continued.airworthiness@atr.fr; Internet
listed in the May 2003 or June 2005 revision reopening of comment period. http://www.aerochain.com. You may
of the Boeing 757 Maintenance Planning Data view this referenced service information
SUMMARY: We are revising an earlier at the FAA, Transport Airplane
(MPD) Document D622N001–9. This AMOC proposed airworthiness directive (AD)
applies only to the common areas identified Directorate, 1601 Lind Avenue SW.,
for certain ATR—GIE Avions de Renton, WA. For information on the
in paragraphs (m)(6)(i) and (m)(6)(ii) of this
Transport Régional Model ATR42–500 availability of this material at the FAA,
AD. All provisions of AD 2006–11–11 that
and Model ATR72–212A airplanes. The call 425–227–1221.
are not specifically referenced in the above
NPRM proposed to require measuring
statements remain fully applicable and must
the gap between the Type III Emergency Examining the AD Docket
be complied with as specified in AD 2006–
11–11. Operators may revise their FAA-
Exit doors and certain overhead stowage You may examine the AD docket on
approved maintenance or inspection program compartment fittings; removing certain the Internet at http://
with these alternative inspections for fittings from the overhead stowage www.regulations.gov by searching for
common areas. compartments and measuring the gap and locating Docket No. FAA–2015–
(i) Common areas inspected before the between the Type III Emergency Exit 0077; or in person at the Docket
effective date of this AD in accordance with doors and the overhead stowage Management Facility between 9 a.m.
the Accomplishment Instructions of Boeing compartment hooks, if necessary; and and 5 p.m., Monday through Friday,
Special Attention Service Bulletin 757–53– re-installing or repairing, as applicable, except Federal holidays. The AD docket
0090, dated June 2, 2005. the Type III Emergency Exit doors. The contains this proposed AD, the
(ii) Common areas inspected in accordance NPRM was prompted by a report regulatory evaluation, any comments
with the Accomplishment Instructions of indicating that interference occurred received, and other information. The
Boeing Special Attention Service Bulletin between a Type III Emergency Exit door
street address for the Docket Office
757–53–0090, Revision 1, dated November and the surrounding passenger cabin
(telephone: 800–647–5527) is in the
19, 2015. furnishing during a production check.
ADDRESSES section. Comments will be
This action revises the NPRM by adding
(n) Related Information available in the AD docket shortly after
new proposed requirements for
(1) For more information about this AD, receipt.
modifying the overhead stowage
contact Eric Schrieber, Aerospace Engineer, compartments. We are proposing this FOR FURTHER INFORMATION CONTACT: Tom
Airframe Branch, ANM–120L, FAA, Los supplemental NPRM (SNPRM) to Rodriguez, Aerospace Engineer,
Angeles Aircraft Certification Office (ACO), prevent interference between a Type III International Branch, ANM–116,
3960 Paramount Boulevard, Lakewood, CA Emergency Exit door and the overhead Transport Airplane Directorate, FAA,
90712–4137; phone: 562–627–5348; fax: 562– stowage compartment fitting installed 1601 Lind Avenue SW., Renton, WA
627–5210; email: eric.schrieber@faa.gov. 98057–3356; telephone 425–227–1137;
on the rail; which could result in
(2) For service information identified in fax: 425–227–1149.
obstructed opening of a Type III
this AD, contact Boeing Commercial
Emergency Exit door during an SUPPLEMENTARY INFORMATION:
Airplanes, Attention: Data & Services
emergency evacuation. Since these
Management, 3855 Lakewood Boulevard, MC Comments Invited
D800–0019, Long Beach, CA 90846–0001;
actions impose an additional burden
over those proposed in the NPRM, we We invite you to send any written
telephone: 206–544–5000, extension 2; fax:
206–766–5683; Internet https:// are reopening the comment period to relevant data, views, or arguments about
www.myboeingfleet.com. You may view this allow the public the chance to comment this proposed AD. Send your comments
referenced service information at the FAA, on these proposed changes. to an address listed under the
Transport Airplane Directorate, 1601 Lind DATES: We must receive comments on ADDRESSES section. Include ‘‘Docket No.
Avenue SW., Renton, WA. For information this SNPRM by June 27, 2016. FAA–2015–0077; Directorate Identifier
on the availability of this material at the ADDRESSES: You may send comments, 2013–NM–254–AD’’ at the beginning of
your comments. We specifically invite
jstallworth on DSK7TPTVN1PROD with PROPOSALS
FAA, call 425–227–1221. using the procedures found in 14 CFR
11.43 and 11.45, by any of the following comments on the overall regulatory,
Issued in Renton, Washington, on May 5,
methods: economic, environmental, and energy
2016.
• Federal eRulemaking Portal: Go to aspects of this proposed AD. We will
Michael Kaszycki, consider all comments received by the
http://www.regulations.gov. Follow the
Acting Manager, Transport Airplane instructions for submitting comments. closing date and may amend this
Directorate, Aircraft Certification Service. • Fax: 202–493–2251. proposed AD based on those comments.
[FR Doc. 2016–11168 Filed 5–11–16; 8:45 am] • Mail: U.S. Department of We will post all comments we
BILLING CODE 4910–13–P Transportation, Docket Operations, M– receive, without change, to http://
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Document Created: 2016-05-12 01:07:55
Document Modified: 2016-05-12 01:07:55
| 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 June 27, 2016. | |
| Contact | Eric Schrieber, Aerospace Engineer, Airframe Branch, ANM-120L, FAA, Los Angeles Aircraft Certification Office (ACO), 3960 Paramount Boulevard, Lakewood, CA 90712-4137; phone: 562-627-5348; fax: 562-627-5210; email: [email protected] | |
| FR Citation | 81 FR 29508 | |
| RIN Number | 2120-AA64 | |
| CFR Associated | Air Transportation; Aircraft; Aviation Safety; Incorporation by Reference and Safety |
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