83 FR 48527 - Airworthiness Directives; The Boeing Company Airplanes
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration Federal Register Volume 83, Issue 187 (September 26, 2018)
Federal Aviation Administration
Federal Register Volume 83, Issue 187 (September 26, 2018)
| Page Range | 48527-48530 | |
| FR Document | 2018-20358 |
[Federal Register Volume 83, Number 187 (Wednesday, September 26, 2018)] [Rules and Regulations] [Pages 48527-48530] From the Federal Register Online [www.thefederalregister.org] [FR Doc No: 2018-20358] ----------------------------------------------------------------------- DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA-2018-0412; Product Identifier 2017-NM-180-AD; Amendment 39-19420; AD 2018-19-20] RIN 2120-AA64 Airworthiness Directives; The Boeing Company Airplanes AGENCY: Federal Aviation Administration (FAA), DOT. ACTION: Final rule. ----------------------------------------------------------------------- SUMMARY: We are superseding Airworthiness Directive (AD) 2010-25-06, which applied to certain The Boeing Company Model 737-200, -300, -400, and -500 series airplanes. AD 2010-25-06 required repetitive inspections for cracking of certain fuselage frames and stub beams, and corrective actions if necessary. AD 2010-25-06 also provided for an optional repair, which terminated the repetitive inspections. For airplanes on which a certain repair was done, AD 2010-25-06 also required repetitive inspections for cracking of certain fuselage frames and stub beams, and corrective actions if necessary. This AD retains the actions required by AD 2010-25-06 and expands the inspection area. This AD was prompted by additional cracking found in areas not covered by the inspections in AD 2010-25-06. We are issuing this AD to address the unsafe condition on these products. DATES: This AD is effective October 31, 2018. The Director of the Federal Register approved the incorporation by reference of a certain publication listed in this AD as of October 31, 2018. ADDRESSES: For service information identified in this final rule, contact Boeing Commercial Airplanes, Attention: Contractual & Data Services (C&DS), 2600 Westminster Blvd., MC 110-SK57, Seal Beach, CA 90740-5600; telephone 562-797-1717; internet https://www.myboeingfleet.com. You may view this service information at the FAA, Transport Standards Branch, 2200 South 216th St., Des Moines, WA. For information on the availability of this material at the FAA, call 206-231-3195. It is also available on the internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2018- 0412. 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-2018- 0412; or in person at Docket Operations between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this final rule, the regulatory evaluation, any comments received, and other information. The address for Docket Operations (phone: 800-647- 5527) is U.S. Department of Transportation, Docket Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New Jersey Avenue SE, Washington, DC 20590. FOR FURTHER INFORMATION CONTACT: Galib Abumeri, Aerospace Engineer, Airframe Section, Los Angeles ACO Branch, FAA, 3960 Paramount Boulevard, Lakewood, CA 90712-4137; phone: 562-627-5324; fax: 562-627- 5210; email: [email protected]. SUPPLEMENTARY INFORMATION: Discussion We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 to supersede AD 2010-25-06, Amendment 39-16539 (75 FR 81409, December 28, 2010) (``AD 2010-25-06''). AD 2010-25-06 applied to certain Model 737-200, -300, -400, and -500 series airplanes. The NPRM published in the Federal Register on May 15, 2018 (83 FR 22422). The NPRM was prompted by additional cracking found in areas not covered by the inspections in AD 2010-25-06. The NPRM proposed to retain the actions required by AD 2010-25-06 and expand the inspection area. We are issuing this AD [[Page 48528]] to address fatigue cracking of certain fuselage frames and stub beams and possible severed frames, which could result in reduced structural integrity of the frames. This reduced structural integrity can increase loading in the fuselage skin, which will accelerate skin crack growth and could result in rapid decompression of the fuselage. Comments We gave the public the opportunity to participate in developing this AD. The following presents the comments received on the NPRM and the FAA's response to each comment. Effect of Winglets on Accomplishment of the Proposed Actions Aviation Partners Boeing stated that accomplishing the supplemental type certificate (STC) ST01219SE does not affect the actions specified in the NPRM. We agree with the commenter. We have redesignated paragraph (c) of the proposed AD as paragraph (c)(1) of this AD and added paragraph (c)(2) to this AD to state that installation of STC ST01219SE does not affect the ability to accomplish the actions required by this AD. Therefore, for airplanes on which STC ST01219SE is installed, a ``change in product'' alternative method of compliance (AMOC) approval request is not necessary to comply with the requirements of 14 CFR 39.17. Request To Clarify Compliance Language Boeing asked that the compliance language in paragraphs (g), (h), (i), (j) and (k) of the proposed AD be changed since there are multiple conditions and compliance times specified in paragraph 1.E., ``Compliance'' of the referenced service information. Boeing asked that the wording in these paragraphs be changed from ``at the applicable time'' specified in tables 1, 2, 3, 4, 5, and 9, respectively, to ``at the applicable condition and time'' specified in tables 1, 2, 3, 4, 5, and 9, respectively. Boeing stated that these changes would provide clarification. Although we do not agree to revise this AD as requested by the commenter, we agree to clarify the compliance language. The phrase ``at the applicable time'' means the compliance time associated with a given condition, as specified in the applicable table in paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin 737-53A1254, Revision 3, dated November 13, 2017. We have not changed this AD in this regard. Addition of Omitted Word We inadvertently omitted the word ``in'' prior to the word ``table'' in the phrase ``. . . the applicable time specified table . . .'' in certain sentences in paragraphs (g), (h), (i), and (j) of the proposed AD. We have revised the applicable sentences in paragraphs (g), (h), (i), and (j) of this AD to read ``. . . the applicable time specified in table. . . .'' Conclusion We reviewed the relevant data, considered the comments received, and determined that air safety and the public interest require adopting this AD with the changes described previously, and minor editorial changes. We have determined that these minor changes:Are consistent with the intent that was proposed in the NPRM for addressing the unsafe condition; and Do not add any additional burden upon the public than was already proposed in the NPRM. We also determined that these changes will not increase the economic burden on any operator or increase the scope of this AD. Related Service Information Under 1 CFR Part 51 We reviewed Boeing Alert Service Bulletin 737-53A1254, Revision 3, dated November 13, 2017. This service information describes procedures for detailed and eddy current inspections of the fuselage frame and over wing stub beam at body station (BS) 616, BS 639, and BS 597 or BS 601, and buttock line (BL) 45.5 floor beam web at the BS 639 stub beam attachment, and related investigative and corrective 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. Costs of Compliance We estimate that this AD affects 67 airplanes of U.S. registry. We estimate the following costs to comply with this AD: Estimated Costs for Required Actions ---------------------------------------------------------------------------------------------------------------- Cost on U.S. Action Labor cost Parts cost Cost per product operators ---------------------------------------------------------------------------------------------------------------- Inspections..................... Up to 67 work-hours $0 Up to $5,695 per Up to $381,565 per x $85 per hour = inspection cycle. inspection cycle. $5,695 per inspection cycle. ---------------------------------------------------------------------------------------------------------------- We estimate the following costs to do certain necessary repairs/ replacements 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/replacements: On-Condition Costs ---------------------------------------------------------------------------------------------------------------- Action ** Labor cost Parts cost Cost per product ---------------------------------------------------------------------------------------------------------------- Repairs/replacements.................. Up to 76 work-hours x * Up to $6,460. $85 per hour = $6,460. ---------------------------------------------------------------------------------------------------------------- * All required parts are supplied by the operator. This cost is minimal, and we have no way to determine what an operator would pay for these parts. ** We have received no definitive data that would enable us to provide cost estimates for certain other repairs specified in this 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. [[Page 48529]] 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 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 and associated appliances to the Director of the System Oversight Division. Regulatory Findings We have determined that this AD will not have federalism implications under Executive Order 13132. This AD will not have a substantial direct effect on the States, on the relationship between the national government and the States, or on the distribution of power and responsibilities among the various levels of government. For the reasons discussed above, I certify that this AD: (1) Is not a ``significant regulatory action'' under Executive Order 12866, (2) Is not a ``significant rule'' under 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. Adoption of the Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA amends 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) 2010-25-06, Amendment 39-16539 (75 FR 81409, December 28, 2010), and adding the following new AD: 2018-19-20 The Boeing Company: Amendment 39-19420; Docket No. FAA- 2018-0412; Product Identifier 2017-NM-180-AD. (a) Effective Date This AD is effective October 31, 2018. (b) Affected ADs This AD replaces AD 2010-25-06, Amendment 39-16539 (75 FR 81409, December 28, 2010) (``AD 2010-25-06''). (c) Applicability (1) This AD applies to The Boeing Company Model 737-200, -300, - 400, and -500 series airplanes, certificated in any category, as identified in Boeing Alert Service Bulletin 737-53A1254, Revision 3, dated November 13, 2017. (2) Installation of Supplemental Type Certificate (STC) ST01219SE (http://rgl.faa.gov/Regulatory_and_Guidance_Library/ rgstc.nsf/0/ebd1cec7b301293e86257cb30045557a/$FILE/ST01219SE.pdf) does not affect the ability to accomplish the actions required by this AD. Therefore, for airplanes on which STC ST01219SE is installed, a ``change in product'' alternative method of compliance (AMOC) approval request is not necessary to comply with the requirements of 14 CFR 39.17. (d) Subject Air Transport Association (ATA) of America Code 53, Fuselage. (e) Unsafe Condition This AD was prompted by the detection of fatigue cracks at certain frame sections, in addition to stub beam cracking, caused by high flight cycle stresses from both pressurization and maneuver loads and additional cracking found in areas not covered by the inspections in AD 2010-25-06. We are issuing this AD to address fatigue cracking of certain fuselage frames and stub beams and possible severed frames, which could result in reduced structural integrity of the frames. This reduced structural integrity can increase loading in the fuselage skin, which will accelerate skin crack growth and could result in rapid decompression of the fuselage. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Repetitive Inspections of Body Stations 616 and 639 Frames and Stub Beams and Corrective Actions At the applicable time specified in table 1 of paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin 737-53A1254, Revision 3, dated November 13, 2017: Do a detailed or high frequency eddy current (HFEC) inspection for cracking of the body station (BS) 616 and 639 frames and stub beams and do all applicable related investigative and corrective actions, in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 737- 53A1254, Revision 3, dated November 13, 2017, except as required by paragraph (m)(1) of this AD. Do all applicable related investigative and corrective actions before further flight. Thereafter, repeat the inspection at the applicable time specified in table 1 of paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin 737-53A1254, Revision 3, dated November 13, 2017. (h) Repetitive Post-Repair Inspections of Body Stations 616 and 639 Frames and Integral Stub Beams and Corrective Actions At the applicable time specified in table 2 of paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin 737-53A1254, Revision 3, dated November 13, 2017: Do the inspections required by paragraphs (h)(1) and (h)(2) of this AD; or the inspection required by paragraph (h)(3) of this AD; as applicable, in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 737-53A1254, Revision 3, dated November 13, 2017, except as required by paragraph (m)(1) of this AD. Do all applicable related investigative and corrective actions before further flight. Thereafter, repeat the inspection at the applicable time specified in table 2 of paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin 737-53A1254, Revision 3, dated November 13, 2017. (1) Do a low frequency eddy current (LFEC) inspection of the web, and an HFEC inspection of the inner and outer chord common to the upper end fastener rows of the web splice doubler for cracking. (2) Do the inspection specified in paragraph (h)(2)(i) or (h)(2)(ii) of this AD. (i) Do a detailed inspection of the replacement frame section for cracking. (ii) Do an HFEC and LFEC inspection of the replacement frame section for cracking. (3) Do a detailed or HFEC inspection of the replacement stub beam for cracking. (i) Repetitive Inspections of Buttock Line 45.5 Longitudinal Floor Beam Web at Body Station 639 Stub Beam Attachment and Corrective Actions For Group 1 and Group 2 airplanes as identified in Boeing Alert Service Bulletin 737-53A1254, Revision 3, dated November 13, 2017, at the time specified in table 3 or table 4, as applicable, of paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin 737-53A1254, Revision 3, dated November 13, 2017, except as required by paragraph (m)(2) of this AD: Do the inspections required by paragraph (i)(1) and (i)(2) of this AD and all applicable corrective actions, in accordance with the Accomplishment Instructions of Boeing Alert [[Page 48530]] Service Bulletin 737-53A1254, Revision 3, dated November 13, 2017, except as required by paragraph (m)(1) of this AD. Do all applicable corrective actions before further flight. Thereafter, repeat the inspections at the time specified in table 3 or table 4, as applicable, of paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin 737-53A1254, Revision 3, dated November 13, 2017. (1) Do an open-hole HFEC inspection for cracking of the buttock line (BL) 45.5 longitudinal floor beam web at each fastener hole common to the stub beam attachment angle. (2) Do an HFEC surface inspection for cracking of the BL 45.5 longitudinal floor beam web around the fastener head/tail at each fastener location common to the backup strap. (j) Repetitive Post-Repair Inspections of Buttock Line 45.5 Longitudinal Floor Beam Web at Body Station 639 and Corrective Actions For Group 2 airplanes as identified in Boeing Alert Service Bulletin 737-53A1254, Revision 3, dated November 13, 2017, at the applicable time specified in table 5 of paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin 737-53A1254, Revision 3, dated November 13, 2017, except as required by paragraph (m)(2) of this AD: Do the inspections required by paragraphs (j)(1) and (j)(2) of this AD and all applicable corrective actions, in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 737-53A1254, Revision 3, dated November 13, 2017, except as required by paragraph (m)(1) of this AD. Do all applicable corrective actions before further flight. Thereafter, repeat the inspections at the applicable time specified in table 5 of paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin 737-53A1254, Revision 3, dated November 13, 2017. (1) Do an open-hole HFEC inspection for cracking of the BL 45.5 longitudinal floor beam web filler at each fastener hole common to the stub beam attachment angle. (2) Do an HFEC surface inspection for cracking of the BL 45.5 longitudinal floor beam web filler around the fastener head/tail at each fastener location common to the backup strap. (k) Repetitive Inspections for Cracking of BS 616 Machined Stub Beam Upper Chord and Corrective Actions For Group 2 and Group 3 airplanes as identified in Boeing Alert Service Bulletin 737-53A1254, Revision 3, dated November 13, 2017, at the applicable time specified in table 9 of paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin 737-53A1254, Revision 3, dated November 13, 2017, except as required by paragraph (m)(2) of this AD; do detailed and medium frequency eddy current subsurface inspections for cracking of the BS 616 machined stub beam upper chord, and all applicable corrective actions, except as required by paragraph (m)(1) of this AD. Do all applicable corrective actions before further flight. Thereafter, repeat the inspections at the applicable time specified in table 9 of paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin 737-53A1254, Revision 3, dated November 13, 2017. (l) Credit for Previous Actions (1) This paragraph provides credit for actions required by paragraph (g) of this AD, if those actions were performed before the effective date of this AD, using Boeing Alert Service Bulletin 737- 53A1254, Revision 1, dated July 9, 2009; or Boeing Alert Service Bulletin 737-53A1254, Revision 2, dated February 22, 2012. (2) This paragraph provides credit for actions required by paragraph (h) of this AD, if those actions were performed before the effective date of this AD, using Boeing Alert Service Bulletin 737- 53A1254, Revision 2, dated February 22, 2012. (m) Exceptions to Service Information Specifications (1) Where Boeing Alert Service Bulletin 737-53A1254, Revision 3, dated November 13, 2017, specifies to contact Boeing for repair instructions: Before further flight, do the repair using a method approved in accordance with the procedures specified in paragraph (n) of this AD. (2) Where Paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin 737-53A1254, Revision 3, dated November 13, 2017, specifies a compliance time ``after the Revision 3 date of this service bulletin,'' this AD requires compliance within the specified compliance time after the effective date of this AD. (n) Alternative Methods of Compliance (AMOCs) (1) The Manager, Los Angeles 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 (o)(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) AMOCs approved previously for AD 2010-25-06 are approved as AMOCs for the corresponding provisions of Boeing Alert Service Bulletin 737-53A1254, Revision 3, dated November 13, 2017, that are required by paragraphs (g) and (h) of this AD. (o) Related Information (1) For information about this AD, contact Galib Abumeri, Aerospace Engineer, Airframe Section, Los Angeles ACO Branch, FAA, 3960 Paramount Boulevard, Lakewood, CA 90712-4137; phone: 562-627- 5324; fax: 562-627-5210; email: [email protected]. (2) Service information identified in this AD that is not incorporated by reference is available at the addresses specified in paragraphs (p)(3) and (p)(4) of this AD. (p) Material Incorporated by Reference (1) The Director of the Federal Register approved the incorporation by reference (IBR) of the service information listed in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51. (2) You must use this service information as applicable to do the actions required by this AD, unless the AD specifies otherwise. (i) Boeing Alert Service Bulletin 737-53A1254, Revision 3, dated November 13, 2017. (ii) Reserved. (3) 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- 5600; telephone 562-797-1717; internet https://www.myboeingfleet.com. (4) You may view this service information at the FAA, Transport Standards Branch, 2200 South 216th St., Des Moines, WA. For information on the availability of this material at the FAA, call 206-231-3195. (5) You may view this service information that is incorporated by reference at the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, call 202-741-6030, or go to: http://www.archives.gov/federal-register/cfr/ibr-locations.html. Issued in Des Moines, Washington, on September 10, 2018. Michael Kaszycki, Acting Director, System Oversight Division, Aircraft Certification Service. [FR Doc. 2018-20358 Filed 9-25-18; 8:45 am] BILLING CODE 4910-13-P
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328–55–557, Revision 1, dated February 1, (3) For service information identified in DATES: This AD is effective October 31,
2018 (for Model 328–100 airplanes); or 328 this AD, contact 328 Support Services GmbH, 2018.
Support Services GmbH Service Bulletin SB– Global Support Center, P.O. Box 1252, D– The Director of the Federal Register
328J–55–324, dated September 1, 2017; or 82231 Wessling, Federal Republic of
Germany; telephone +49 8153 88111 6666;
approved the incorporation by reference
328 Support Services GmbH Service Bulletin
SB–328J–55–324, Revision 1, dated February fax +49 8153 88111 6565; email gsc.op@ of a certain publication listed in this AD
1, 2018 (for Model 328–300 airplanes). 328support.de; internet http:// as of October 31, 2018.
www.328support.de. ADDRESSES: For service information
(k) Other FAA AD Provisions (4) You may view this service information identified in this final rule, contact
The following provisions also apply to this at the FAA, Transport Standards Branch, Boeing Commercial Airplanes,
AD: 2200 South 216th St., Des Moines, WA. For
(1) Alternative Methods of Compliance information on the availability of this
Attention: Contractual & Data Services
(AMOCs): The Manager, International material at the FAA, call 206–231–3195. (C&DS), 2600 Westminster Blvd., MC
Section, Transport Standards Branch, FAA, (5) You may view this service information 110–SK57, Seal Beach, CA 90740–5600;
has the authority to approve AMOCs for this that is incorporated by reference at the telephone 562–797–1717; internet
AD, if requested using the procedures found National Archives and Records https://www.myboeingfleet.com. You
in 14 CFR 39.19. In accordance with 14 CFR Administration (NARA). For information on may view this service information at the
39.19, send your request to your principal the availability of this material at NARA, call FAA, Transport Standards Branch, 2200
inspector or local Flight Standards District 202–741–6030, or go to: http://
South 216th St., Des Moines, WA. For
Office, as appropriate. If sending information www.archives.gov/federal-register/cfr/ibr-
directly to the International Section, send it locations.html. information on the availability of this
to the attention of the person identified in material at the FAA, call 206–231–3195.
Issued in Des Moines, Washington, on It is also available on the internet at
paragraph (l)(2) of this AD. Information may September 7, 2018.
be emailed to: 9-ANM-116-AMOC- http://www.regulations.gov by searching
Michael Kaszycki,
REQUESTS@faa.gov. Before using any for and locating Docket No. FAA–2018–
approved AMOC, notify your appropriate Acting Director, System Oversight Division, 0412.
principal inspector, or lacking a principal Aircraft Certification Service.
inspector, the manager of the local flight [FR Doc. 2018–20357 Filed 9–25–18; 8:45 am] Examining the AD Docket
standards district office/certificate holding BILLING CODE 4910–13–P You may examine the AD docket on
district office.
(2) Contacting the Manufacturer: For any
the internet at http://
requirement in this AD to obtain corrective www.regulations.gov by searching for
DEPARTMENT OF TRANSPORTATION and locating Docket No. FAA–2018–
actions from a manufacturer, the action must
be accomplished using a method approved 0412; or in person at Docket Operations
Federal Aviation Administration
by the Manager, International Section, between 9 a.m. and 5 p.m., Monday
Transport Standards Branch, FAA; or the through Friday, except Federal holidays.
European Aviation Safety Agency (EASA); or 14 CFR Part 39
The AD docket contains this final rule,
328 Support Services GmbH’s EASA Design [Docket No. FAA–2018–0412; Product the regulatory evaluation, any
Organization Approval (DOA). If approved by Identifier 2017–NM–180–AD; Amendment comments received, and other
the DOA, the approval must include the 39–19420; AD 2018–19–20]
DOA-authorized signature. information. The address for Docket
RIN 2120–AA64 Operations (phone: 800–647–5527) is
(l) Related Information U.S. Department of Transportation,
(1) Refer to Mandatory Continuing Airworthiness Directives; The Boeing Docket Operations, M–30, West
Airworthiness Information (MCAI) EASA Company Airplanes Building Ground Floor, Room W12–140,
Airworthiness Directive 2017–0239, dated 1200 New Jersey Avenue SE,
November 30, 2017, for related information. AGENCY: Federal Aviation
Washington, DC 20590.
This MCAI may be found in the AD docket Administration (FAA), DOT.
on the internet at http://www.regulations.gov FOR FURTHER INFORMATION CONTACT:
ACTION: Final rule.
by searching for and locating Docket No. Galib Abumeri, Aerospace Engineer,
FAA–2018–0503. SUMMARY: We are superseding Airframe Section, Los Angeles ACO
(2) For more information about this AD, Airworthiness Directive (AD) 2010–25– Branch, FAA, 3960 Paramount
contact Todd Thompson, Aerospace 06, which applied to certain The Boeing Boulevard, Lakewood, CA 90712–4137;
Engineer, International Section, Transport Company Model 737–200, –300, –400, phone: 562–627–5324; fax: 562–627–
Standards Branch, FAA, 2200 South 216th
Street, Des Moines, WA 98198; telephone and –500 series airplanes. AD 2010–25– 5210; email: galib.abumeri@faa.gov.
and fax 206–231–3228. 06 required repetitive inspections for SUPPLEMENTARY INFORMATION:
(3) Service information identified in this cracking of certain fuselage frames and
AD that is not incorporated by reference is stub beams, and corrective actions if Discussion
available at the addresses specified in necessary. AD 2010–25–06 also We issued a notice of proposed
paragraphs (m)(3) and (m)(4) of this AD. provided for an optional repair, which rulemaking (NPRM) to amend 14 CFR
(m) Material Incorporated by Reference terminated the repetitive inspections. part 39 to supersede AD 2010–25–06,
(1) The Director of the Federal Register
For airplanes on which a certain repair Amendment 39–16539 (75 FR 81409,
approved the incorporation by reference was done, AD 2010–25–06 also required December 28, 2010) (‘‘AD 2010–25–
(IBR) of the service information listed in this repetitive inspections for cracking of 06’’). AD 2010–25–06 applied to certain
paragraph under 5 U.S.C. 552(a) and 1 CFR certain fuselage frames and stub beams, Model 737–200, –300, –400, and –500
part 51. and corrective actions if necessary. This series airplanes. The NPRM published
(2) You must use this service information AD retains the actions required by AD in the Federal Register on May 15, 2018
as applicable to do the actions required by 2010–25–06 and expands the inspection (83 FR 22422). The NPRM was
daltland on DSKBBV9HB2PROD with RULES
this AD, unless this AD specifies otherwise. area. This AD was prompted by prompted by additional cracking found
(i) 328 Support Services GmbH Service
Bulletin SB–328–55–557, Revision 2, dated
additional cracking found in areas not in areas not covered by the inspections
May 24, 2018. covered by the inspections in AD 2010– in AD 2010–25–06. The NPRM
(ii) 328 Support Services GmbH Service 25–06. We are issuing this AD to proposed to retain the actions required
Bulletin SB–328J–55–324, Revision 2, dated address the unsafe condition on these by AD 2010–25–06 and expand the
May 24, 2018. products. inspection area. We are issuing this AD
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We are issuing this rulemaking under PART 39—AIRWORTHINESS (g) Repetitive Inspections of Body Stations
the authority described in Subtitle VII, DIRECTIVES 616 and 639 Frames and Stub Beams and
Part A, Subpart III, Section 44701, Corrective Actions
‘‘General requirements.’’ Under that ■ 1. The authority citation for part 39 At the applicable time specified in table 1
section, Congress charges the FAA with of paragraph 1.E., ‘‘Compliance,’’ of Boeing
continues to read as follows:
promoting safe flight of civil aircraft in Alert Service Bulletin 737–53A1254,
Authority: 49 U.S.C. 106(g), 40113, 44701. Revision 3, dated November 13, 2017: Do a
air commerce by prescribing regulations detailed or high frequency eddy current
for practices, methods, and procedures § 39.13 [Amended] (HFEC) inspection for cracking of the body
the Administrator finds necessary for station (BS) 616 and 639 frames and stub
safety in air commerce. This regulation ■ 2. The FAA amends § 39.13 by beams and do all applicable related
is within the scope of that authority removing Airworthiness Directive (AD) investigative and corrective actions, in
because it addresses an unsafe condition 2010–25–06, Amendment 39–16539 (75 accordance with the Accomplishment
that is likely to exist or develop on FR 81409, December 28, 2010), and Instructions of Boeing Alert Service Bulletin
adding the following new AD: 737–53A1254, Revision 3, dated November
products identified in this rulemaking
13, 2017, except as required by paragraph
action. 2018–19–20 The Boeing Company: (m)(1) of this AD. Do all applicable related
This AD is issued in accordance with Amendment 39–19420; Docket No. investigative and corrective actions before
authority delegated by the Executive FAA–2018–0412; Product Identifier further flight. Thereafter, repeat the
2017–NM–180–AD. inspection at the applicable time specified in
Director, Aircraft Certification Service,
table 1 of paragraph 1.E., ‘‘Compliance,’’ of
as authorized by FAA Order 8000.51C. (a) Effective Date
Boeing Alert Service Bulletin 737–53A1254,
In accordance with that order, issuance This AD is effective October 31, 2018. Revision 3, dated November 13, 2017.
of ADs is normally a function of the
(b) Affected ADs (h) Repetitive Post-Repair Inspections of
Compliance and Airworthiness
This AD replaces AD 2010–25–06, Body Stations 616 and 639 Frames and
Division, but during this transition
Amendment 39–16539 (75 FR 81409, Integral Stub Beams and Corrective Actions
period, the Executive Director has
delegated the authority to issue ADs December 28, 2010) (‘‘AD 2010–25–06’’). At the applicable time specified in table 2
of paragraph 1.E., ‘‘Compliance,’’ of Boeing
applicable to transport category (c) Applicability Alert Service Bulletin 737–53A1254,
airplanes and associated appliances to (1) This AD applies to The Boeing Revision 3, dated November 13, 2017: Do the
the Director of the System Oversight Company Model 737–200, –300, –400, and inspections required by paragraphs (h)(1) and
Division. –500 series airplanes, certificated in any (h)(2) of this AD; or the inspection required
category, as identified in Boeing Alert by paragraph (h)(3) of this AD; as applicable,
Regulatory Findings Service Bulletin 737–53A1254, Revision 3, in accordance with the Accomplishment
dated November 13, 2017. Instructions of Boeing Alert Service Bulletin
We have determined that this AD will 737–53A1254, Revision 3, dated November
(2) Installation of Supplemental Type
not have federalism implications under 13, 2017, except as required by paragraph
Certificate (STC) ST01219SE (http://
Executive Order 13132. This AD will rgl.faa.gov/Regulatory_and_Guidance_ (m)(1) of this AD. Do all applicable related
not have a substantial direct effect on Library/rgstc.nsf/0/ebd1cec7b301293e86257 investigative and corrective actions before
the States, on the relationship between cb30045557a/$FILE/ST01219SE.pdf) does further flight. Thereafter, repeat the
the national government and the States, not affect the ability to accomplish the inspection at the applicable time specified in
or on the distribution of power and table 2 of paragraph 1.E., ‘‘Compliance,’’ of
actions required by this AD. Therefore, for
Boeing Alert Service Bulletin 737–53A1254,
responsibilities among the various airplanes on which STC ST01219SE is
Revision 3, dated November 13, 2017.
levels of government. installed, a ‘‘change in product’’ alternative
(1) Do a low frequency eddy current (LFEC)
method of compliance (AMOC) approval inspection of the web, and an HFEC
For the reasons discussed above, I
request is not necessary to comply with the inspection of the inner and outer chord
certify that this AD: requirements of 14 CFR 39.17. common to the upper end fastener rows of
(1) Is not a ‘‘significant regulatory the web splice doubler for cracking.
(d) Subject
action’’ under Executive Order 12866, (2) Do the inspection specified in
Air Transport Association (ATA) of paragraph (h)(2)(i) or (h)(2)(ii) of this AD.
(2) Is not a ‘‘significant rule’’ under America Code 53, Fuselage.
DOT Regulatory Policies and Procedures (i) Do a detailed inspection of the
(e) Unsafe Condition replacement frame section for cracking.
(44 FR 11034, February 26, 1979), (ii) Do an HFEC and LFEC inspection of the
(3) Will not affect intrastate aviation This AD was prompted by the detection of replacement frame section for cracking.
fatigue cracks at certain frame sections, in
in Alaska, and (3) Do a detailed or HFEC inspection of the
addition to stub beam cracking, caused by replacement stub beam for cracking.
(4) Will not have a significant high flight cycle stresses from both
economic impact, positive or negative, pressurization and maneuver loads and (i) Repetitive Inspections of Buttock Line
on a substantial number of small entities additional cracking found in areas not 45.5 Longitudinal Floor Beam Web at Body
under the criteria of the Regulatory covered by the inspections in AD 2010–25– Station 639 Stub Beam Attachment and
Flexibility Act. 06. We are issuing this AD to address fatigue Corrective Actions
cracking of certain fuselage frames and stub For Group 1 and Group 2 airplanes as
List of Subjects in 14 CFR Part 39 beams and possible severed frames, which identified in Boeing Alert Service Bulletin
could result in reduced structural integrity of 737–53A1254, Revision 3, dated November
Air transportation, Aircraft, Aviation the frames. This reduced structural integrity 13, 2017, at the time specified in table 3 or
safety, Incorporation by reference, can increase loading in the fuselage skin, table 4, as applicable, of paragraph 1.E.,
Safety. which will accelerate skin crack growth and ‘‘Compliance,’’ of Boeing Alert Service
daltland on DSKBBV9HB2PROD with RULES
could result in rapid decompression of the Bulletin 737–53A1254, Revision 3, dated
Adoption of the Amendment fuselage. November 13, 2017, except as required by
paragraph (m)(2) of this AD: Do the
Accordingly, under the authority (f) Compliance inspections required by paragraph (i)(1) and
delegated to me by the Administrator, Comply with this AD within the (i)(2) of this AD and all applicable corrective
the FAA amends 14 CFR part 39 as compliance times specified, unless already actions, in accordance with the
follows: done. Accomplishment Instructions of Boeing Alert
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![48530 Federal Register / Vol. 83, No. 187 / Wednesday, September 26, 2018 / Rules and Regulations
Service Bulletin 737–53A1254, Revision 3, of Boeing Alert Service Bulletin 737– (o) Related Information
dated November 13, 2017, except as required 53A1254, Revision 3, dated November 13, (1) For information about this AD, contact
by paragraph (m)(1) of this AD. Do all 2017. Galib Abumeri, Aerospace Engineer,
applicable corrective actions before further Airframe Section, Los Angeles ACO Branch,
flight. Thereafter, repeat the inspections at (l) Credit for Previous Actions
FAA, 3960 Paramount Boulevard, Lakewood,
the time specified in table 3 or table 4, as (1) This paragraph provides credit for CA 90712–4137; phone: 562–627–5324; fax:
applicable, of paragraph 1.E., ‘‘Compliance,’’ actions required by paragraph (g) of this AD, 562–627–5210; email: galib.abumeri@faa.gov.
of Boeing Alert Service Bulletin 737– if those actions were performed before the (2) Service information identified in this
53A1254, Revision 3, dated November 13, effective date of this AD, using Boeing Alert AD that is not incorporated by reference is
2017. Service Bulletin 737–53A1254, Revision 1, available at the addresses specified in
(1) Do an open-hole HFEC inspection for dated July 9, 2009; or Boeing Alert Service paragraphs (p)(3) and (p)(4) of this AD.
cracking of the buttock line (BL) 45.5 Bulletin 737–53A1254, Revision 2, dated
longitudinal floor beam web at each fastener February 22, 2012. (p) Material Incorporated by Reference
hole common to the stub beam attachment (2) This paragraph provides credit for (1) The Director of the Federal Register
angle. actions required by paragraph (h) of this AD, approved the incorporation by reference
(2) Do an HFEC surface inspection for if those actions were performed before the (IBR) of the service information listed in this
cracking of the BL 45.5 longitudinal floor effective date of this AD, using Boeing Alert paragraph under 5 U.S.C. 552(a) and 1 CFR
beam web around the fastener head/tail at Service Bulletin 737–53A1254, Revision 2, part 51.
each fastener location common to the backup dated February 22, 2012. (2) You must use this service information
strap. as applicable to do the actions required by
(m) Exceptions to Service Information this AD, unless the AD specifies otherwise.
(j) Repetitive Post-Repair Inspections of Specifications
Buttock Line 45.5 Longitudinal Floor Beam (i) Boeing Alert Service Bulletin 737–
Web at Body Station 639 and Corrective (1) Where Boeing Alert Service Bulletin 53A1254, Revision 3, dated November 13,
Actions 737–53A1254, Revision 3, dated November 2017.
13, 2017, specifies to contact Boeing for (ii) Reserved.
For Group 2 airplanes as identified in repair instructions: Before further flight, do (3) For service information identified in
Boeing Alert Service Bulletin 737–53A1254, the repair using a method approved in this AD, contact Boeing Commercial
Revision 3, dated November 13, 2017, at the accordance with the procedures specified in Airplanes, Attention: Contractual & Data
applicable time specified in table 5 of Services (C&DS), 2600 Westminster Blvd.,
paragraph (n) of this AD.
paragraph 1.E., ‘‘Compliance,’’ of Boeing MC 110–SK57, Seal Beach, CA 90740–5600;
(2) Where Paragraph 1.E., ‘‘Compliance,’’ of
Alert Service Bulletin 737–53A1254, telephone 562–797–1717; internet https://
Boeing Alert Service Bulletin 737–53A1254,
Revision 3, dated November 13, 2017, except www.myboeingfleet.com.
Revision 3, dated November 13, 2017,
as required by paragraph (m)(2) of this AD: (4) You may view this service information
specifies a compliance time ‘‘after the
Do the inspections required by paragraphs at the FAA, Transport Standards Branch,
Revision 3 date of this service bulletin,’’ this
(j)(1) and (j)(2) of this AD and all applicable 2200 South 216th St., Des Moines, WA. For
corrective actions, in accordance with the AD requires compliance within the specified
compliance time after the effective date of information on the availability of this
Accomplishment Instructions of Boeing Alert material at the FAA, call 206–231–3195.
Service Bulletin 737–53A1254, Revision 3, this AD.
(5) You may view this service information
dated November 13, 2017, except as required (n) Alternative Methods of Compliance that is incorporated by reference at the
by paragraph (m)(1) of this AD. Do all (AMOCs) National Archives and Records
applicable corrective actions before further Administration (NARA). For information on
(1) The Manager, Los Angeles ACO Branch,
flight. Thereafter, repeat the inspections at the availability of this material at NARA, call
FAA, has the authority to approve AMOCs
the applicable time specified in table 5 of 202–741–6030, or go to: http://
for this AD, if requested using the procedures
paragraph 1.E., ‘‘Compliance,’’ of Boeing www.archives.gov/federal-register/cfr/ibr-
found in 14 CFR 39.19. In accordance with
Alert Service Bulletin 737–53A1254, locations.html.
14 CFR 39.19, send your request to your
Revision 3, dated November 13, 2017.
(1) Do an open-hole HFEC inspection for principal inspector or local Flight Standards Issued in Des Moines, Washington, on
cracking of the BL 45.5 longitudinal floor District Office, as appropriate. If sending September 10, 2018.
beam web filler at each fastener hole information directly to the manager of the Michael Kaszycki,
common to the stub beam attachment angle. certification office, send it to the attention of
the person identified in paragraph (o)(1) of Acting Director, System Oversight Division,
(2) Do an HFEC surface inspection for Aircraft Certification Service.
cracking of the BL 45.5 longitudinal floor this AD. Information may be emailed to: 9-
ANM-LAACO-AMOC-Requests@faa.gov. [FR Doc. 2018–20358 Filed 9–25–18; 8:45 am]
beam web filler around the fastener head/tail
at each fastener location common to the (2) Before using any approved AMOC, BILLING CODE 4910–13–P
backup strap. notify your appropriate principal inspector,
or lacking a principal inspector, the manager
(k) Repetitive Inspections for Cracking of BS of the local flight standards district office/ DEPARTMENT OF TRANSPORTATION
616 Machined Stub Beam Upper Chord and certificate holding district office.
Corrective Actions (3) An AMOC that provides an acceptable Federal Aviation Administration
For Group 2 and Group 3 airplanes as level of safety may be used for any repair,
identified in Boeing Alert Service Bulletin modification, or alteration required by this 14 CFR Part 71
737–53A1254, Revision 3, dated November AD if it is approved by the Boeing
13, 2017, at the applicable time specified in Commercial Airplanes Organization [Docket No. FAA–2018–0312; Airspace
table 9 of paragraph 1.E., ‘‘Compliance,’’ of Designation Authorization (ODA) that has Docket No. 18–AGL–07]
Boeing Alert Service Bulletin 737–53A1254, been authorized by the Manager, Los Angeles
Revision 3, dated November 13, 2017, except ACO Branch, to make those findings. To be RIN 2120–AA66
as required by paragraph (m)(2) of this AD; approved, the repair method, modification
do detailed and medium frequency eddy deviation, or alteration deviation must meet Establishment of Class E Airspace;
current subsurface inspections for cracking of the certification basis of the airplane, and the Glen Ullin, ND
daltland on DSKBBV9HB2PROD with RULES
the BS 616 machined stub beam upper chord, approval must specifically refer to this AD.
and all applicable corrective actions, except (4) AMOCs approved previously for AD AGENCY: Federal Aviation
as required by paragraph (m)(1) of this AD. 2010–25–06 are approved as AMOCs for the Administration (FAA), DOT.
Do all applicable corrective actions before corresponding provisions of Boeing Alert ACTION: Final rule.
further flight. Thereafter, repeat the Service Bulletin 737–53A1254, Revision 3,
inspections at the applicable time specified dated November 13, 2017, that are required SUMMARY: This action establishes Class
in table 9 of paragraph 1.E., ‘‘Compliance,’’ by paragraphs (g) and (h) of this AD. E airspace extending upward from 700
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Document Created: 2018-09-26 00:47:30
Document Modified: 2018-09-26 00:47:30
| 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 | Rules and Regulations | |
| Action | Final rule. | |
| Dates | This AD is effective October 31, 2018. | |
| Contact | Galib Abumeri, Aerospace Engineer, Airframe Section, Los Angeles ACO Branch, FAA, 3960 Paramount Boulevard, Lakewood, CA 90712-4137; phone: 562-627-5324; fax: 562-627- 5210; email: [email protected] | |
| FR Citation | 83 FR 48527 | |
| RIN Number | 2120-AA64 | |
| CFR Associated | Air Transportation; Aircraft; Aviation Safety; Incorporation by Reference and Safety |
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