81 FR 59541 - Airworthiness Directives; The Boeing Company Airplanes
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration Federal Register Volume 81, Issue 168 (August 30, 2016)
Federal Aviation Administration
Federal Register Volume 81, Issue 168 (August 30, 2016)
| Page Range | 59541-59543 | |
| FR Document | 2016-20673 |
[Federal Register Volume 81, Number 168 (Tuesday, August 30, 2016)] [Proposed Rules] [Pages 59541-59543] From the Federal Register Online [www.thefederalregister.org] [FR Doc No: 2016-20673] [[Page 59541]] ----------------------------------------------------------------------- DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA-2016-8848; Directorate Identifier 2016-NM-054-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 adopt a new airworthiness directive (AD) for certain The Boeing Company Model 737-300, -400, and -500 series airplanes. This proposed AD was prompted by an evaluation by the design approval holder (DAH) indicating that the fuselage skin is subject to widespread fatigue damage (WFD). This proposed AD would require modification of the lap joint, including related investigative actions and corrective actions if necessary. This proposed AD also would require repetitive post-modification inspections for cracking of the skin at critical fastener rows, and corrective actions if necessary. We are proposing this AD to detect and correct cracks at the lap joint skin that could link up and result in rapid decompression and loss of structural integrity of the airplane. DATES: We must receive comments on this proposed AD by October 14, 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, P.O. Box 3707, MC 2H-65, Seattle, WA 98124-2207; telephone: 206-544-5000, extension 1; fax: 206-766-5680; 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- 8848. 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- 8848; 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: Wade Sullivan, Aerospace Engineer, Airframe Branch, ANM-120S, FAA, Seattle Aircraft Certification Office (ACO), 1601 Lind Avenue SW., Renton, WA 98057-3356; phone: 425-917- 6430, fax: 425-917-6590; email: [email protected]. SUPPLEMENTARY INFORMATION: Comments Invited We invite you to send any written relevant data, views, or arguments about this proposal. Send your comments to an address listed under the ADDRESSES section. Include ``Docket No. FAA-2016-8848; Directorate Identifier 2016-NM-054-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 Fatigue damage can occur locally, in small areas or structural design details, or globally, in widespread areas. Multiple-site damage is widespread damage that occurs in a large structural element such as a single rivet line of a lap splice joining two large skin panels. Widespread 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. This condition is known as widespread fatigue damage. It is associated with general degradation of large areas of structure with similar structural details and stress levels. 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 have received a report indicating that a Model 737-300 series airplane with 20-inch spaced tear strap crown skin configuration experienced a rapid decompression when the lap joint at stringer S-4L between station (STA) 664 and STA 727 cracked and opened up. Investigation shows that the cracks were [[Page 59542]] caused by fatigue cracks in the lower skin at the lower row of fasteners in the S-4L lap joint. The airplane had accumulated 39,781 total flight cycles and 48,740 total flight hours. This condition, if not corrected, could result in rapid decompression and loss of structural integrity. Related Service Information Under 1 CFR Part 51 We reviewed Boeing Alert Service Bulletin 737-53A1343, dated March 25, 2016. The service information describes procedures for modification of the lap joint, including related investigative actions and corrective actions if necessary. The service information also describes procedures for post-modification inspections for cracking of the skin at critical fastener rows, and corrective actions if necessary. 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, except as discussed under ``Differences Between this Proposed AD and the Service Information.'' 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-2016-8848. The phrase ``related investigative actions'' is used in this proposed AD. Related investigative actions are follow-on actions that (1) are related to the primary action, and (2) further investigate the nature of any condition found. Related investigative actions in an AD could include, for example, inspections. The phrase ``corrective actions'' is used in this proposed AD. Corrective actions correct or address any condition found. Corrective actions in an AD could include, for example, repairs. Differences Between This Proposed AD and the Service Information Boeing Alert Service Bulletin 737-53A1343, date March 25, 2016, specifies to contact the manufacturer for certain instructions, but this proposed AD would require accomplishment of repair methods, modification deviations, and alteration deviations in one of the following ways: In accordance with a method that we approve; or Using data that meet the certification basis of the airplane, and that have been approved by the Boeing Commercial Airplanes Organization Designation Authorization (ODA) whom we have authorized to make those findings. Explanation of Compliance Time The compliance time for the modification specified in this proposed AD for addressing WFD was established to ensure that discrepant structure is modified before WFD develops in airplanes. Standard inspection techniques cannot be relied on to detect WFD before it becomes a hazard to flight. We will not grant any extensions of the compliance time to complete any AD-mandated service bulletin related to WFD without new data that would substantiate and clearly warrant such an extension. Costs of Compliance We estimate that this proposed AD affects 115 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 ---------------------------------------------------------------------------------------------------------------- Lap joint skin modification...... 2,142 work-hours x $12,500 $194,570........... $22,375,550. $85 per hour = $182,070 per modification. Post-Modification inspection..... 102 work-hours x $0 $8,670 per $997,050 per $85 per hour = inspection cycle. inspection cycle. $8,670 per inspection cycle. ---------------------------------------------------------------------------------------------------------------- We have received no definitive data that would enable us to provide cost estimates for the on-condition 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. Regulatory Findings We 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 this 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. [[Page 59543]] 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 adding the following new airworthiness directive (AD): The Boeing Company: Docket No. FAA-2016-8848; Directorate Identifier 2016-NM-054-AD. (a) Comments Due Date We must receive comments by October 14, 2016. (b) Affected ADs This AD affects AD 2015-16-08, Amendment 39-18233 (80 FR 51450, August 25, 2015) (``AD 2015-16-08''). (c) Applicability This AD applies to The Boeing Company Model 737-300, -400, and - 500 series airplanes, certificated in any category, as identified in Boeing Alert Service Bulletin 737-53A1343, dated March 25, 2016; except for Group 5 airplanes identified in Boeing Alert Service Bulletin 737-53A1343, dated March 25, 2016. (d) Subject Air Transport Association (ATA) of America Code 53, Fuselage. (e) Unsafe Condition This AD was prompted by an evaluation by the design approval holder (DAH) indicating that the fuselage skin is subject to widespread fatigue damage (WFD). We are issuing this AD to detect and correct cracks at the lap joint skin that could link up and result in rapid decompression and loss of structural integrity of the airplane. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Lap Joint Skin Modification Before the accumulation of 50,000 total flight cycles, or within 3,000 flight cycles after the effective date of this AD, whichever occurs later: Modify the lap joint skin, including doing all applicable related investigative and corrective actions, in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 737-53A1343, dated March 25, 2016, except as required by paragraph (i) of this AD. Do all applicable related investigative and corrective actions before further flight. (h) Inspection of the Critical Fastener Rows Within 38,000 flight cycles after modifying the lap joint skin as required by paragraph (g) of this AD: Inspect the skin at critical fastener rows by doing the actions specified in paragraph (h)(1) or (h)(2) of this AD, in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 737-53A1343, dated March 25, 2016. If any crack is found during any inspection, repair before further flight using a method approved in accordance with the procedures specified in paragraph (l) of this AD. Repeat the inspection thereafter at intervals not to exceed 2,000 flight cycles in unrepaired areas. (1) From the inside of the airplane: Do a low frequency eddy current (LFEC) inspection for any crack in the skin at the critical fastener row, and a medium frequency eddy current (MFEC) inspection for any crack in the skin at the critical fastener row. (2) From the outside of the airplane: Do a LFEC inspection for any crack in the fuselage skin. (i) Exception to Service Information Specifications Although Boeing Alert Service Bulletin 737-53A1343, dated March 25, 2016, specifies to contact Boeing for repair instructions, and specifies that action as ``RC'' (Required for Compliance), this AD requires repair before further flight using a method approved in accordance with the procedures specified in paragraph (l) of this AD. (j) AD Provisions for Part 26 Supplemental Inspections Table 5 of paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin 737-53A1343, dated March 25, 2016, specifies post- modification airworthiness limitation inspections in compliance with 14 CFR 25.571(a)(3) at the modified locations, which support compliance with 14 CFR 121.1109(c)(2) or 129.109(b)(2). As airworthiness limitations, these inspections are required by maintenance and operational rules. It is therefore unnecessary to mandate them in this AD. Deviations from these inspections require FAA approval, but do not require an alternative method of compliance. (k) Terminating Action for AD 2015-16-08 Accomplishing the modification required by paragraph (g) of this AD terminates the inspections required by paragraphs (g), (h), (i), (j), and (k) of AD 2015-16-08 for the modified area only. (l) Alternative Methods of Compliance (AMOCs) (1) The Manager, Seattle Aircraft Certification Office (ACO), FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. 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 (m)(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, Seattle 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) Except as required by paragraph (i) of this AD: For service information that contains steps that are labeled as Required for Compliance (RC), the provisions of paragraphs (l)(4)(i) and (l)(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. 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. (m) Related Information (1) For more information about this AD, contact Wade Sullivan, Aerospace Engineer, Airframe Branch, ANM-120S, FAA, Seattle ACO, 1601 Lind Avenue SW., Renton, WA 98057-3356; phone: 425-917-6430, fax: 425-917-6590; email: [email protected]. (2) For service information identified in this AD, contact Boeing Commercial Airplanes, Attention: Data & Services Management, P.O. Box 3707, MC 2H-65, Seattle, WA 98124-2207; telephone: 206-544- 5000, extension 1; fax: 206-766-5680; 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 August 16, 2016. Dorr M. Anderson, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2016-20673 Filed 8-29-16; 8:45 am] BILLING CODE 4910-13-P
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DEPARTMENT OF TRANSPORTATION Directorate, 1601 Lind Avenue SW., multiple elements such as adjacent
Renton, WA. For information on the frames or stringers. Multiple-site
Federal Aviation Administration availability of this material at the FAA, damage and multiple-element damage
call 425–227–1221. It is also available cracks are typically too small initially to
14 CFR Part 39 on the internet at http:// be reliably detected with normal
[Docket No. FAA–2016–8848; Directorate www.regulations.gov by searching for inspection methods. Without
Identifier 2016–NM–054–AD] and locating Docket No. FAA–2016– intervention, these cracks will grow,
8848. and eventually compromise the
RIN 2120–AA64 structural integrity of the airplane. This
Examining the AD Docket
condition is known as widespread
Airworthiness Directives; The Boeing You may examine the AD docket on fatigue damage. It is associated with
Company Airplanes the Internet at http:// general degradation of large areas of
AGENCY: Federal Aviation www.regulations.gov by searching for structure with similar structural details
Administration (FAA), DOT. and locating Docket No. FAA–2016– and stress levels. As an airplane ages,
8848; or in person at the Docket WFD will likely occur, and will
ACTION: Notice of proposed rulemaking
Management Facility between 9 a.m. certainly occur if the airplane is
(NPRM). and 5 p.m., Monday through Friday, operated long enough without any
SUMMARY: We propose to adopt a new except Federal holidays. The AD docket intervention.
airworthiness directive (AD) for certain contains this proposed AD, the The FAA’s WFD final rule (75 FR
The Boeing Company Model 737–300, regulatory evaluation, any comments 69746, November 15, 2010) became
–400, and –500 series airplanes. This received, and other information. The effective on January 14, 2011. The WFD
proposed AD was prompted by an street address for the Docket Office rule requires certain actions to prevent
evaluation by the design approval (phone: 800–647–5527) is in the structural failure due to WFD
holder (DAH) indicating that the ADDRESSES section. Comments will be throughout the operational life of
fuselage skin is subject to widespread available in the AD docket shortly after certain existing transport category
fatigue damage (WFD). This proposed receipt. airplanes and all of these airplanes that
AD would require modification of the FOR FURTHER INFORMATION CONTACT: will be certificated in the future. For
lap joint, including related investigative Wade Sullivan, Aerospace Engineer, existing and future airplanes subject to
actions and corrective actions if Airframe Branch, ANM–120S, FAA, the WFD rule, the rule requires that
necessary. This proposed AD also Seattle Aircraft Certification Office DAHs establish a limit of validity (LOV)
would require repetitive post- (ACO), 1601 Lind Avenue SW., Renton, of the engineering data that support the
modification inspections for cracking of WA 98057–3356; phone: 425–917–6430, structural maintenance program.
the skin at critical fastener rows, and fax: 425–917–6590; email: Operators affected by the WFD rule may
corrective actions if necessary. We are wade.sullivan@faa.gov. not fly an airplane beyond its LOV,
proposing this AD to detect and correct SUPPLEMENTARY INFORMATION: unless an extended LOV is approved.
cracks at the lap joint skin that could The WFD rule (75 FR 69746,
Comments Invited November 15, 2010) does not require
link up and result in rapid
We invite you to send any written identifying and developing maintenance
decompression and loss of structural
relevant data, views, or arguments about actions if the DAHs can show that such
integrity of the airplane.
this proposal. Send your comments to actions are not necessary to prevent
DATES: We must receive comments on WFD before the airplane reaches the
an address listed under the ADDRESSES
this proposed AD by October 14, 2016. section. Include ‘‘Docket No. FAA– LOV. Many LOVs, however, do depend
ADDRESSES: You may send comments, 2016–8848; Directorate Identifier 2016– on accomplishment of future
using the procedures found in 14 CFR NM–054–AD’’ at the beginning of your maintenance actions. As stated in the
11.43 and 11.45, by any of the following comments. We specifically invite WFD rule, any maintenance actions
methods: comments on the overall regulatory, necessary to reach the LOV will be
• Federal eRulemaking Portal: Go to economic, environmental, and energy mandated by airworthiness directives
http://www.regulations.gov. Follow the aspects of this proposed AD. We will through separate rulemaking actions.
instructions for submitting comments. consider all comments received by the In the context of WFD, this action is
• Fax: 202–493–2251. closing date and may amend this necessary to enable DAHs to propose
• Mail: U.S. Department of proposed AD because of those LOVs that allow operators the longest
Transportation, Docket Operations, M– comments. operational lives for their airplanes, and
30, West Building Ground Floor, Room We will post all comments we still ensure that WFD will not occur.
W12–140, 1200 New Jersey Avenue SE., receive, without change, to http:// This approach allows for an
Washington, DC 20590. www.regulations.gov, including any implementation strategy that provides
• Hand Delivery: Deliver to Mail personal information you provide. We flexibility to DAHs in determining the
address above between 9 a.m. and 5 will also post a report summarizing each timing of service information
p.m., Monday through Friday, except substantive verbal contact we receive development (with FAA approval),
Federal holidays. about this proposed AD. while providing operators with certainty
For service information identified in regarding the LOV applicable to their
this NPRM, contact Boeing Commercial Discussion airplanes.
mstockstill on DSK3G9T082PROD with PROPOSALS
Airplanes, Attention: Data & Services Fatigue damage can occur locally, in We have received a report indicating
Management, P.O. Box 3707, MC 2H–65, small areas or structural design details, that a Model 737–300 series airplane
Seattle, WA 98124–2207; telephone: or globally, in widespread areas. with 20-inch spaced tear strap crown
206–544–5000, extension 1; fax: 206– Multiple-site damage is widespread skin configuration experienced a rapid
766–5680; Internet: https:// damage that occurs in a large structural decompression when the lap joint at
www.myboeingfleet.com. You may view element such as a single rivet line of a stringer S–4L between station (STA) 664
this referenced service information at lap splice joining two large skin panels. and STA 727 cracked and opened up.
the FAA, Transport Airplane Widespread damage can also occur in Investigation shows that the cracks were
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![Federal Register / Vol. 81, No. 168 / Tuesday, August 30, 2016 / Proposed Rules 59543
The Proposed Amendment (h) Inspection of the Critical Fastener Rows be emailed to: 9–ANM-Seattle-ACO-AMOC-
Within 38,000 flight cycles after modifying Requests@faa.gov.
Accordingly, under the authority the lap joint skin as required by paragraph (g) (2) Before using any approved AMOC,
delegated to me by the Administrator, of this AD: Inspect the skin at critical fastener notify your appropriate principal inspector,
the FAA proposes to amend 14 CFR part rows by doing the actions specified in or lacking a principal inspector, the manager
39 as follows: paragraph (h)(1) or (h)(2) of this AD, in of the local flight standards district office/
accordance with the Accomplishment certificate holding district office.
PART 39—AIRWORTHINESS Instructions of Boeing Alert Service Bulletin (3) An AMOC that provides an acceptable
DIRECTIVES 737–53A1343, dated March 25, 2016. If any
level of safety may be used for any repair,
crack is found during any inspection, repair
before further flight using a method approved modification, or alteration required by this
■ 1. The authority citation for part 39 in accordance with the procedures specified AD if it is approved by the Boeing
continues to read as follows: in paragraph (l) of this AD. Repeat the Commercial Airplanes Organization
Authority: 49 U.S.C. 106(g), 40113, 44701. inspection thereafter at intervals not to Designation Authorization (ODA) that has
exceed 2,000 flight cycles in unrepaired been authorized by the Manager, Seattle
§ 39.13 [Amended] areas. ACO, to make those findings. To be
(1) From the inside of the airplane: Do a approved, the repair method, modification
■ 2. The FAA amends § 39.13 by adding low frequency eddy current (LFEC) deviation, or alteration deviation must meet
the following new airworthiness inspection for any crack in the skin at the the certification basis of the airplane, and the
directive (AD): critical fastener row, and a medium approval must specifically refer to this AD.
The Boeing Company: Docket No. FAA– frequency eddy current (MFEC) inspection
(4) Except as required by paragraph (i) of
2016–8848; Directorate Identifier 2016– for any crack in the skin at the critical
fastener row. this AD: For service information that
NM–054–AD. contains steps that are labeled as Required
(2) From the outside of the airplane: Do a
(a) Comments Due Date LFEC inspection for any crack in the fuselage for Compliance (RC), the provisions of
skin. paragraphs (l)(4)(i) and (l)(4)(ii) of this AD
We must receive comments by October 14,
apply.
2016. (i) Exception to Service Information
(i) The steps labeled as RC, including
(b) Affected ADs Specifications
substeps under an RC step and any figures
This AD affects AD 2015–16–08, Although Boeing Alert Service Bulletin identified in an RC step, must be done to
737–53A1343, dated March 25, 2016, comply with the AD. An AMOC is required
Amendment 39–18233 (80 FR 51450, August
specifies to contact Boeing for repair
25, 2015) (‘‘AD 2015–16–08’’). for any deviations to RC steps, including
instructions, and specifies that action as
‘‘RC’’ (Required for Compliance), this AD substeps and identified figures.
(c) Applicability
requires repair before further flight using a (ii) Steps not labeled as RC may be
This AD applies to The Boeing Company deviated from using accepted methods in
Model 737–300, –400, and –500 series method approved in accordance with the
procedures specified in paragraph (l) of this accordance with the operator’s maintenance
airplanes, certificated in any category, as
AD. or inspection program without obtaining
identified in Boeing Alert Service Bulletin
approval of an AMOC, provided the RC steps,
737–53A1343, dated March 25, 2016; except (j) AD Provisions for Part 26 Supplemental
for Group 5 airplanes identified in Boeing including substeps and identified figures, can
Inspections
Alert Service Bulletin 737–53A1343, dated still be done as specified, and the airplane
Table 5 of paragraph 1.E., ‘‘Compliance,’’ can be put back in an airworthy condition.
March 25, 2016. of Boeing Alert Service Bulletin 737–
(d) Subject 53A1343, dated March 25, 2016, specifies (m) Related Information
post-modification airworthiness limitation
Air Transport Association (ATA) of (1) For more information about this AD,
inspections in compliance with 14 CFR
America Code 53, Fuselage. contact Wade Sullivan, Aerospace Engineer,
25.571(a)(3) at the modified locations, which
support compliance with 14 CFR Airframe Branch, ANM–120S, FAA, Seattle
(e) Unsafe Condition
121.1109(c)(2) or 129.109(b)(2). As ACO, 1601 Lind Avenue SW., Renton, WA
This AD was prompted by an evaluation by airworthiness limitations, these inspections 98057–3356; phone: 425–917–6430, fax: 425–
the design approval holder (DAH) indicating are required by maintenance and operational 917–6590; email: wade.sullivan@faa.gov.
that the fuselage skin is subject to rules. It is therefore unnecessary to mandate (2) For service information identified in
widespread fatigue damage (WFD). We are them in this AD. Deviations from these this AD, contact Boeing Commercial
issuing this AD to detect and correct cracks inspections require FAA approval, but do not Airplanes, Attention: Data & Services
at the lap joint skin that could link up and require an alternative method of compliance. Management, P.O. Box 3707, MC 2H–65,
result in rapid decompression and loss of
structural integrity of the airplane. (k) Terminating Action for AD 2015–16–08 Seattle, WA 98124–2207; telephone: 206–
544–5000, extension 1; fax: 206–766–5680;
(f) Compliance Accomplishing the modification required
by paragraph (g) of this AD terminates the Internet: https://www.myboeingfleet.com.
Comply with this AD within the inspections required by paragraphs (g), (h), You may view this referenced service
compliance times specified, unless already (i), (j), and (k) of AD 2015–16–08 for the information at the FAA, Transport Airplane
done. modified area only. Directorate, 1601 Lind Avenue SW., Renton,
(g) Lap Joint Skin Modification WA. For information on the availability of
(l) Alternative Methods of Compliance
this material at the FAA, call 425–227–1221.
Before the accumulation of 50,000 total (AMOCs)
flight cycles, or within 3,000 flight cycles (1) The Manager, Seattle Aircraft Issued in Renton, Washington, on August
after the effective date of this AD, whichever Certification Office (ACO), FAA, has the 16, 2016.
mstockstill on DSK3G9T082PROD with PROPOSALS
occurs later: Modify the lap joint skin, authority to approve AMOCs for this AD, if Dorr M. Anderson,
including doing all applicable related requested using the procedures found in 14 Acting Manager, Transport Airplane
investigative and corrective actions, in CFR 39.19. In accordance with 14 CFR 39.19,
Directorate, Aircraft Certification Service.
accordance with the Accomplishment send your request to your principal inspector
Instructions of Boeing Alert Service Bulletin or local Flight Standards District Office, as [FR Doc. 2016–20673 Filed 8–29–16; 8:45 am]
737–53A1343, dated March 25, 2016, except appropriate. If sending information directly BILLING CODE 4910–13–P
as required by paragraph (i) of this AD. Do to the manager of the ACO, send it to the
all applicable related investigative and attention of the person identified in
corrective actions before further flight. paragraph (m)(1) of this AD. Information may
VerDate Sep<11>2014 17:56 Aug 29, 2016 Jkt 238001 PO 00000 Frm 00026 Fmt 4702 Sfmt 9990 E:\FR\FM\30AUP1.SGM 30AUP1](https://thefederalregister.org/doc/81_FR_59709/page/3.svg)
Document Created: 2018-02-09 11:42:07
Document Modified: 2018-02-09 11:42:07
| 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 October 14, 2016. | |
| Contact | Wade Sullivan, Aerospace Engineer, Airframe Branch, ANM-120S, FAA, Seattle Aircraft Certification Office (ACO), 1601 Lind Avenue SW., Renton, WA 98057-3356; phone: 425-917- 6430, fax: 425-917-6590; email: [email protected] | |
| FR Citation | 81 FR 59541 | |
| RIN Number | 2120-AA64 | |
| CFR Associated | Air Transportation; Aircraft; Aviation Safety; Incorporation by Reference and Safety |
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