83 FR 1529 - Airworthiness Directives; The Boeing Company Airplanes
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration Federal Register Volume 83, Issue 9 (January 12, 2018)
Federal Aviation Administration
Federal Register Volume 83, Issue 9 (January 12, 2018)
| Page Range | 1529-1532 | |
| FR Document | 2018-00256 |
[Federal Register Volume 83, Number 9 (Friday, January 12, 2018)] [Rules and Regulations] [Pages 1529-1532] From the Federal Register Online [www.thefederalregister.org] [FR Doc No: 2018-00256] ----------------------------------------------------------------------- DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA-2017-0629; Product Identifier 2016-NM-184-AD; Amendment 39-19149; AD 2018-01-08] RIN 2120-AA64 Airworthiness Directives; The Boeing Company Airplanes AGENCY: Federal Aviation Administration (FAA), DOT. ACTION: Final rule. ----------------------------------------------------------------------- SUMMARY: We are adopting a new airworthiness directive (AD) for all The Boeing Company Model 737-100, -200, -200C, -300, -400, and -500 series airplanes. This AD was prompted by reports of fatigue cracking in the frame outboard chord and in the radius of the auxiliary chord at a certain area. This AD requires inspections to detect this cracking, and corrective action if necessary. We are issuing this AD to address the unsafe condition on these products. DATES: This AD is effective February 16, 2018 . The Director of the Federal Register approved the incorporation by reference of a certain publication listed in this AD as of December 26, 2012 (77 FR 69747, November 21, 2012). 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; telephone 562-797-1717; internet https://www.myboeingfleet.com. You may view this service information at the FAA, Transport Standards Branch, 1601 Lind Avenue SW, Renton, WA. For information on the availability of this material at the FAA, call 425-227-1221. It is also available on the internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2017-0629. Examining the AD Docket You may examine the AD docket on the internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2017- 0629; 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 final rule, the regulatory evaluation, any comments received, and other information. The address for the Docket Office (phone: 800-647-5527) is Docket Management Facility, 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: George Garrido, Aerospace Engineer, Airframe Section, FAA, Los Angeles ACO Branch, 3960 Paramount Boulevard, Lakewood, CA 90712-4137; phone: 562-627-5232; fax: 562-627- 5210; email: george.garrido@faa.gov. SUPPLEMENTARY INFORMATION: Discussion We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 by adding an AD that would apply to all The Boeing Company Model 737-100, -200, -200C, -300, -400, and -500 series airplanes. The NPRM published in the Federal Register on June 30, 2017 (82 FR 29792). The NPRM was prompted by reports of fatigue cracking in the frame outboard chord and in the radius of the auxiliary chord at a certain area. The NPRM proposed to require inspections to detect this cracking, and corrective action if necessary. We are issuing this AD to detect and correct fatigue cracking of the outboard and auxiliary chords, which could result in reduced structural integrity of the outboard chord and consequent rapid decompression of the airplane. Comments We gave the public the opportunity to participate in developing this final rule. The following presents the comments [[Page 1530]] 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 Supplemental Type Certificate (STC) ST01219SE does not affect the ability to accomplish the actions specified in the NPRM. We agree with the commenter. We have redesignated paragraph (c) of the proposed AD as (c)(1) 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 methods of compliance (AMOC) approval request is not necessary to comply with the requirements of 14 CFR 39.17. Request To Remove Certain Language in Paragraph (i) of the Proposed AD Boeing asked that the language ``and repair'' be removed from paragraph (i) of the proposed AD. Boeing stated that the language in paragraph (i) refers to a section in Part 6 of Boeing Alert Service Bulletin 737-53A1166, Revision 2, dated May 25, 2006, which is to determine if the modification should be classified as interim or permanent. Boeing noted that the additional language ``and repair'' is not part of that section, and suggested it be deleted. We agree with the commenter's request for the reason provided. We have deleted ``and repair'' from paragraph (i) of this AD. Request To Clarify Certain Language Swiftair S.A. stated that the language describing the requirements in paragraph (h) of the proposed AD is confusing. Swiftair asked that the effectivity and the requirements identified in paragraph (h) of the proposed AD be clarified in some way due to extensive sub-paragraphs. Swiftair recommended that the ``and'' in the sentence be emphasized. We acknowledge the commenter's concern. However, we cannot emphasize or highlight specific text in an AD. The affected airplanes in paragraph (h) of the AD are those that meet all of the criteria specified in the sub-paragraphs. We have not changed this AD in this regard. Swiftair S.A. also stated that the language describing the requirements in paragraph (j) of the proposed AD is confusing. Swiftair added that the pre-regulatory text in the NPRM refers to actions from AD 2012-23-04, Amendment 39-17260 (77 FR 69747, November 21, 2012) (``AD 2012-23-04'') and the combination of that rulemaking and the actions in the proposed AD is confusing. Swiftair also stated that paragraph (r) of AD 2012-23-04 should be explained in the current requirements and not in the pre-regulatory text. We agree that some clarification is necessary. Concerning the request to include the current requirements of AD 2012-23-04 in this AD, we would have had to issue different rulemaking. Instead of a stand-alone AD, the alternative would have been to supersede AD 2012- 23-04, which would have resulted in a single but considerably more complex AD. All operators identified in AD 2012-23-04 would then have to show compliance with the new supersedure AD. Our experience with similar complex ADs, and with operator feedback, is that it is preferable to leave the existing AD as is and issue a related but stand-alone AD such as this one. To clarify the criteria in paragraph (h)(3) of this AD, we have added Note 1 to paragraph (h)(3) of this AD to reference the optional terminating action specified in paragraph (r) of AD 2012-23-04. Conclusion We reviewed the relevant data, considered the comments received, and determined that air safety and the public interest require adopting this final rule 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 correcting 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 final rule. Related Service Information Under 1 CFR Part 51 We reviewed Boeing Alert Service Bulletin 737-53A1166, Revision 2, dated May 25, 2006. The service information describes procedures for inspections for cracks of the body station (BS) 727 frame outboard chord and in the radius of the auxiliary chord, and repair or replacement 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. Costs of Compliance We estimate that this AD affects 160 airplanes of U.S. registry. We estimate the following costs to comply with this AD: Estimated Costs ---------------------------------------------------------------------------------------------------------------- Affected Action Labor cost airplanes of Cost per Cost on U.S. operators U.S. registry product ---------------------------------------------------------------------------------------------------------------- Detailed and High Frequency 6 work-hours x $85 per 5 $510 $2,550 per inspection Eddy Current (HFEC) hour = $510 per cycle. inspections. inspection cycle. One-time follow-on HFEC 9 work-hours x $85 per 5 765 $3,825. inspection. hour = $765. HFEC inspection............... 9 work-hours x $85 per 150 765 $114,750. hour = $765. ---------------------------------------------------------------------------------------------------------------- We estimate the following costs to do any necessary repairs that are required based on the results of the inspections. We have no way of determining the number of aircraft that might need these repairs: [[Page 1531]] On-Condition Costs ---------------------------------------------------------------------------------------------------------------- Cost per Action Labor cost Parts cost product ---------------------------------------------------------------------------------------------------------------- Repair of cracking of the outboard chord 514 work-hours x $85 per hour = $13,586 $57,276. frame. $43,690. Repair of cracking of the outboard chord... 49 work-hours x $85 per hour = 4,255 8,420. $4,165. ---------------------------------------------------------------------------------------------------------------- Authority for This Rulemaking Title 49 of the United States Code specifies the FAA's authority to issue rules on aviation safety. Subtitle I, section 106, describes the authority of the FAA Administrator. Subtitle VII: Aviation Programs, describes in more detail the scope of the Agency's authority. We are issuing this rulemaking under the authority described in Subtitle VII, Part A, Subpart III, Section 44701: ``General requirements.'' Under that section, Congress charges the FAA with promoting safe flight of civil aircraft in air commerce by prescribing regulations for practices, methods, and procedures the Administrator finds necessary for safety in air commerce. This regulation is within the scope of that authority because it addresses an unsafe condition that is likely to exist or develop on products identified in this rulemaking action. This AD is issued in accordance with authority delegated by the Executive Director, Aircraft Certification Service, as authorized by FAA Order 8000.51C. In accordance with that order, issuance of ADs is normally a function of the Compliance and Airworthiness Division, but during this transition period, the Executive Director has delegated the authority to issue ADs applicable to transport category airplanes to the Director of the System Oversight Division. Regulatory Findings 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 adding the following new airworthiness directive (AD): 2018-01-08 The Boeing Company: Amendment 39-19149; Docket No. FAA- 2017-0629; Product Identifier 2016-NM-184-AD. (a) Effective Date This AD is effective February 16, 2018. (b) Affected ADs None. (c) Applicability (1) This AD applies to all The Boeing Company Model 737-100, - 200, -200C, -300, -400, and -500 series airplanes, certificated in any category. (2) Installation of Supplemental Type Certificate (STC) ST01219SE (http://rgl.faa.gov/Regulatory_and_Guidance_Library/rgstc.nsf/0/EBD1CEC7B301293E86257CB30045557A?OpenDocument&Highlight=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. (d) Subject Air Transport Association (ATA) of America Code 53, Fuselage. (e) Unsafe Condition This AD was prompted by reports of fatigue cracking in the frame outboard chord and in the radius of the auxiliary chord at body station (BS) 727 and stringer (S) 18A. We are issuing this AD to detect and correct fatigue cracking of the outboard and auxiliary chords, which could result in reduced structural integrity of the outboard chord and consequent rapid decompression of the airplane. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Repetitive Inspections and Corrective Action For airplanes identified in paragraph (h) of this AD: Within 4,500 flight cycles or 24 months after the effective date of this AD, whichever occurs first, do internal detailed and High Frequency Eddy Current (HFEC) inspections to detect cracks in the auxiliary chord radius, in accordance with Part 1 of the Accomplishment Instructions of Boeing Alert Service Bulletin 737-53A1166, Revision 2, dated May 25, 2006. If any crack is found during any inspection required by this paragraph, before further flight, repair using a method approved in accordance with the procedures specified in paragraph (l) of this AD. Repeat the inspections thereafter at intervals not to exceed 15,000 flight cycles. Replacement of the outboard chord of the frame at BS 727 concurrently with the installation of the preventive modification of the outboard chord in accordance with Part 6 of the Accomplishment Instructions of Boeing Alert Service Bulletin 737-53A1166, Revision 2, dated May 25, 2006, terminates the repetitive inspections required by this paragraph. (h) Airplanes for Actions Specified in Paragraph (g) of This AD The actions specified in paragraph (g) of this AD are required for airplanes that meet the criteria of paragraphs (h)(1), (h)(2), (h)(3), and (h)(4) of this AD. (1) Model 737-100, -200, and -200C series airplanes, line numbers 1 through 999 inclusive. (2) Airplanes identified as Groups 1, 2, and 3 in Boeing Alert Service Bulletin 737-53A1166, Revision 2, dated May 25, 2006. (3) Airplanes on which a preventive modification has been installed in accordance with the method specified in paragraph (h)(3)(i), (h)(3)(ii), or (h)(3)(iii) of this AD. Note 1 to paragraph (h)(3) of this AD: The modification identified in paragraph (h)(3) of this AD is also specified in paragraph (r) of AD 2012-23-04, Amendment 39-17260 (77 FR 69747, November 21, 2012), as optional terminating action. (i) Part 6 of the Accomplishment Instructions of Boeing Alert Service Bulletin 737-53A1166, Revision 2, dated May 25, 2006. [[Page 1532]] (ii) Part II of the Accomplishment Instructions of Boeing Alert Service Bulletin 737-53A1166, Revision 1, dated May 25, 1995. (iii) Part II of the Accomplishment Instructions of Boeing Alert Service Bulletin 737-53A1166, dated June 30, 1994. (4) Airplanes on which the outboard chord has not been replaced in accordance with the method specified in paragraph (h)(4)(i), (h)(4)(ii), or (h)(4)(iii) of this AD. (i) Part 3 of the Accomplishment Instructions of Boeing Alert Service Bulletin 737-53A1166, Revision 2, dated May 25, 2006. (ii) Part I of the Accomplishment Instructions of Boeing Alert Service Bulletin 737-53A1166, Revision 1, dated May 25, 1995. (iii) Part I of the Accomplishment Instructions of Boeing Alert Service Bulletin 737-53A1166, dated June 30, 1994. (i) Edge Margin Measurement, Related Investigative Actions, and Repair For Model 737-100, -200, and -200C series airplanes having line numbers 1 through 999 inclusive, identified as Groups 1 through 3 in Boeing Alert Service Bulletin 737-53A1166, Revision 2, dated May 25, 2006, on which the preventive modification has been installed in accordance with Boeing Alert Service Bulletin 737-53A1166, dated June 30, 1994; or Boeing Alert Service Bulletin 737-53A1166, Revision 1, dated May 25, 1995: Within 60,000 flight cycles after accomplishing the preventive modification, determine if the modification is classified as interim or permanent by using the edge margin measurement classification specified in part 6 of the Accomplishment Instructions of Boeing Alert Service Bulletin 737- 53A1166, Revision 2, dated May 25, 2006. In lieu of measuring on the airplane, a review of engineering documentation may be used to classify the modification if the engineering documentation was completed at the time of the modification and has the edge margins recorded. (1) If the modification is classified as permanent, no further action is required by paragraph (i) of this AD. (2) If the modification is classified as interim: Within 60,000 flight cycles after accomplishment of the interim modification of the outboard chord of the frame at BS 727 at S-18A, but no earlier than 50,000 flight cycles after accomplishment of the modification, do a one-time follow-on open-hole eddy current inspection to detect cracks in the modified chord, in accordance with part 8 of the Accomplishment Instructions of Boeing Alert Service Bulletin 737- 53A1166, Revision 2, dated May 25, 2006. If any crack is found, before further flight, repair in accordance with part 3 or part 4, as applicable, of the Accomplishment Instructions of Boeing Alert Service Bulletin 737-53A1166, Revision 2, dated May 25, 2006; except, if the repairs cannot be installed using the identified procedures, repair before further flight using a method approved in accordance with the procedures specified in paragraph (l) of this AD. (j) Follow-On Inspection for Interim Modification and Repair For airplanes having line numbers 1 through 3132 inclusive, on which an interim modification of the BS 727 outboard chord as defined in part 6 of the Accomplishment Instructions of Boeing Alert Service Bulletin 737-53A1166, Revision 2, dated May 25, 2006, has been accomplished: Within 60,000 flight cycles after accomplishment of the interim modification of the outboard chord of the frame at BS 727 at S-18A, but no earlier than 50,000 flight cycles after accomplishment of the modification, do a one-time follow-on open- hole eddy current inspection to detect cracks in the modified chord, in accordance with part 8 of the Accomplishment Instructions of Boeing Alert Service Bulletin 737-53A1166, Revision 2, dated May 25, 2006. If any crack is found during the inspection required by this paragraph, before further flight, repair in accordance with part 3 or part 4, as applicable, of the Accomplishment Instructions of Boeing Alert Service Bulletin 737-53A1166, Revision 2, dated May 25, 2006; except, where the repairs cannot be installed using the procedures identified in this service bulletin, repair before further flight using a method approved in accordance with the procedures specified in paragraph (l) of this AD. (k) Exception to the Service Information Access and restoration procedures specified in the Accomplishment Instructions of Boeing Alert Service Bulletin 737- 53A1166, Revision 2, dated May 25, 2006, are not required by this AD. Operators may do those actions following their approved maintenance procedures. (l) 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 (m) of this AD. Information may be emailed to: 9-ANM-LAACO-AMOC-Requests@faa.gov. (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. (m) Related Information For more information about this AD, contact George Garrido, Aerospace Engineer, Airframe Section, FAA, Los Angeles ACO Branch, 3960 Paramount Boulevard, Lakewood, CA 90712-4137; phone: 562-627- 5232; fax: 562-627-5210; email: george.garrido@faa.gov. (n) 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. (3) The following service information was approved for IBR on December 26, 2012 (77 FR 69747, November 21, 2012). (i) Boeing Alert Service Bulletin 737-53A1166, Revision 2, dated May 25, 2006. (ii) Reserved. (4) For service information identified in this AD, contact Boeing Commercial Airplanes, Attention: Contractual & Data Services (C&DS), 2600 Westminster Blvd., MC 110-SK57, Seal Beach, CA 90740; telephone 562-797-1717; internet https://www.myboeingfleet.com. (5) You may view this service information at the FAA, Transport Standards Branch, 1601 Lind Avenue SW, Renton, WA. For information on the availability of this material at the FAA, call 425-227-1221. (6) 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 Renton, Washington, on January 2, 2018. Michael Kaszycki, Acting Director, System Oversight Division, Aircraft Certification Service. [FR Doc. 2018-00256 Filed 1-11-18; 8:45 am] BILLING CODE 4910-13-P
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Authority: 49 U.S.C. 106(g), 40113, 44701. inspector, the manager of the local flight (C&DS), 2600 Westminster Blvd., MC
standards district office/certificate holding 110–SK57, Seal Beach, CA 90740;
§ 39.13 [Amended] district office. telephone 562–797–1717; internet
■ 2. The FAA amends § 39.13 by adding (i) Related Information https://www.myboeingfleet.com. You
the following new airworthiness may view this service information at the
(1) Refer to MCAI EASA AD 2014–0045,
directive (AD): dated February 25, 2014; corrected March 4, FAA, Transport Standards Branch, 1601
2018–01–11 Airbus: Amendment 39–19152; 2014, for related information. You may Lind Avenue SW, Renton, WA. For
Docket No. FAA–2017–1244; Product examine the MCAI on the internet at http:// information on the availability of this
Identifier 2013–NM–145–AD. www.regulations.gov by searching for and material at the FAA, call 425–227–1221.
locating Docket No. FAA–2017–1244. It is also available on the internet at
(a) Effective Date
(2) For more information about this AD, http://www.regulations.gov by searching
This AD becomes effective January 29, contact Sanjay Ralhan, Aerospace Engineer, for and locating Docket No. FAA–2017–
2018. International Section, Transport Standards 0629.
(b) Affected ADs Branch, FAA, 1601 Lind Avenue SW,
Renton, WA 98057–3356; telephone: 425– Examining the AD Docket
None. 227–1405; fax: 425–227–1149.
You may examine the AD docket on
(c) Applicability (j) Material Incorporated by Reference the internet at http://
This AD applies to Airbus Model A319– None. www.regulations.gov by searching for
115 and A319–133 airplanes, certificated in and locating Docket No. FAA–2017–
any category, all manufacturer serial Issued in Renton, Washington, on January
2, 2018. 0629; or in person at the Docket
numbers, having received in production
Airbus modification 33125 (installation of
Management Facility between 9 a.m.
Michael Kaszycki,
Gaseous Oxygen System (GOS) for and 5 p.m., Monday through Friday,
Acting Director, System Oversight Division,
passengers), except those on which Airbus except Federal holidays. The AD docket
Aircraft Certification Service.
modification 153555 and 155860 have been contains this final rule, the regulatory
[FR Doc. 2018–00343 Filed 1–11–18; 8:45 am]
embodied in production. evaluation, any comments received, and
BILLING CODE 4910–13–P other information. The address for the
(d) Subject
Docket Office (phone: 800–647–5527) is
Air Transport Association (ATA) of Docket Management Facility, U.S.
America Code 35, Oxygen. DEPARTMENT OF TRANSPORTATION Department of Transportation, Docket
(e) Reason
Federal Aviation Administration Operations, M–30, West Building
This AD was prompted by a fire during a Ground Floor, Room W12–140, 1200
flight, in the vicinity of the GOS for 14 CFR Part 39 New Jersey Avenue SE, Washington, DC
passengers. We are issuing this AD to prevent 20590.
an uncontrolled fire in the vicinity of the [Docket No. FAA–2017–0629; Product FOR FURTHER INFORMATION CONTACT:
GOS for passengers, near the cargo area, Identifier 2016–NM–184–AD; Amendment George Garrido, Aerospace Engineer,
which could result in loss of the airplane. 39–19149; AD 2018–01–08]
Airframe Section, FAA, Los Angeles
(f) Compliance RIN 2120–AA64 ACO Branch, 3960 Paramount
Comply with this AD within the Boulevard, Lakewood, CA 90712–4137;
compliance times specified, unless already Airworthiness Directives; The Boeing phone: 562–627–5232; fax: 562–627–
done. Company Airplanes 5210; email: george.garrido@faa.gov.
(g) Required Action(s) AGENCY: Federal Aviation SUPPLEMENTARY INFORMATION:
Within 30 days after the effective date of Administration (FAA), DOT. Discussion
this AD, request instructions from the ACTION: Final rule.
We issued a notice of proposed
Manager, International Section, Transport
Standards Branch, FAA, to address the SUMMARY: We are adopting a new rulemaking (NPRM) to amend 14 CFR
unsafe condition specified in paragraph (e) of airworthiness directive (AD) for all The part 39 by adding an AD that would
this AD; and accomplish the actions at the Boeing Company Model 737–100, –200, apply to all The Boeing Company Model
times specified in, and in accordance with, –200C, –300, –400, and –500 series 737–100, –200, –200C, –300, –400, and
those instructions. Guidance can be found in airplanes. This AD was prompted by –500 series airplanes. The NPRM
Mandatory Continuing Airworthiness reports of fatigue cracking in the frame published in the Federal Register on
Information (MCAI) European Aviation June 30, 2017 (82 FR 29792). The NPRM
Safety Agency (EASA) AD 2014–0045, dated
outboard chord and in the radius of the
auxiliary chord at a certain area. This was prompted by reports of fatigue
February 25, 2014; corrected March 4, 2014. cracking in the frame outboard chord
AD requires inspections to detect this
(h) Alternative Methods of Compliance cracking, and corrective action if and in the radius of the auxiliary chord
(AMOCs) necessary. We are issuing this AD to at a certain area. The NPRM proposed
The Manager, International Section, address the unsafe condition on these to require inspections to detect this
Transport Standards Branch, FAA, has the products. cracking, and corrective action if
authority to approve AMOCs for this AD, if necessary. We are issuing this AD to
requested using the procedures found in 14 DATES: This AD is effective February 16, detect and correct fatigue cracking of the
CFR 39.19. In accordance with 14 CFR 39.19, 2018 . outboard and auxiliary chords, which
send your request to your principal inspector The Director of the Federal Register could result in reduced structural
or local Flight Standards District Office, as approved the incorporation by reference integrity of the outboard chord and
sradovich on DSK3GMQ082PROD with RULES
appropriate. If sending information directly of a certain publication listed in this AD
to the International Section, send it to the consequent rapid decompression of the
as of December 26, 2012 (77 FR 69747, airplane.
attention of the person identified in November 21, 2012).
paragraph (i)(2) of this AD. Information may Comments
be emailed to: 9-ANM-116-AMOC- ADDRESSES: For service information
REQUESTS@faa.gov. Before using any identified in this final rule, contact We gave the public the opportunity to
approved AMOC, notify your appropriate Boeing Commercial Airplanes, participate in developing this final rule.
principal inspector, or lacking a principal Attention: Contractual & Data Services The following presents the comments
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ON-CONDITION COSTS
Cost per
Action Labor cost Parts cost product
Repair of cracking of the outboard chord frame .......... 514 work-hours × $85 per hour = $43,690 .................. $13,586 $57,276.
Repair of cracking of the outboard chord .................... 49 work-hours × $85 per hour = $4,165 ...................... 4,255 8,420.
Authority for This Rulemaking under the criteria of the Regulatory We are issuing this AD to detect and correct
Flexibility Act. fatigue cracking of the outboard and auxiliary
Title 49 of the United States Code chords, which could result in reduced
specifies the FAA’s authority to issue List of Subjects in 14 CFR Part 39 structural integrity of the outboard chord and
rules on aviation safety. Subtitle I, consequent rapid decompression of the
Air transportation, Aircraft, Aviation
section 106, describes the authority of airplane.
the FAA Administrator. Subtitle VII: safety, Incorporation by reference,
Safety. (f) Compliance
Aviation Programs, describes in more
detail the scope of the Agency’s Comply with this AD within the
Adoption of the Amendment
compliance times specified, unless already
authority. Accordingly, under the authority done.
We are issuing this rulemaking under
delegated to me by the Administrator,
the authority described in Subtitle VII, (g) Repetitive Inspections and Corrective
the FAA amends 14 CFR part 39 as Action
Part A, Subpart III, Section 44701:
follows:
‘‘General requirements.’’ Under that For airplanes identified in paragraph (h) of
section, Congress charges the FAA with PART 39—AIRWORTHINESS this AD: Within 4,500 flight cycles or 24
promoting safe flight of civil aircraft in months after the effective date of this AD,
DIRECTIVES whichever occurs first, do internal detailed
air commerce by prescribing regulations
and High Frequency Eddy Current (HFEC)
for practices, methods, and procedures ■ 1. The authority citation for part 39 inspections to detect cracks in the auxiliary
the Administrator finds necessary for continues to read as follows: chord radius, in accordance with Part 1 of the
safety in air commerce. This regulation Authority: 49 U.S.C. 106(g), 40113, 44701. Accomplishment Instructions of Boeing Alert
is within the scope of that authority Service Bulletin 737–53A1166, Revision 2,
because it addresses an unsafe condition § 39.13 [Amended] dated May 25, 2006. If any crack is found
that is likely to exist or develop on ■ 2. The FAA amends § 39.13 by adding during any inspection required by this
products identified in this rulemaking paragraph, before further flight, repair using
the following new airworthiness a method approved in accordance with the
action. directive (AD):
This AD is issued in accordance with procedures specified in paragraph (l) of this
2018–01–08 The Boeing Company: AD. Repeat the inspections thereafter at
authority delegated by the Executive
Amendment 39–19149; Docket No. intervals not to exceed 15,000 flight cycles.
Director, Aircraft Certification Service, Replacement of the outboard chord of the
FAA–2017–0629; Product Identifier
as authorized by FAA Order 8000.51C. 2016–NM–184–AD. frame at BS 727 concurrently with the
In accordance with that order, issuance installation of the preventive modification of
of ADs is normally a function of the (a) Effective Date the outboard chord in accordance with Part
Compliance and Airworthiness This AD is effective February 16, 2018. 6 of the Accomplishment Instructions of
Division, but during this transition Boeing Alert Service Bulletin 737–53A1166,
(b) Affected ADs Revision 2, dated May 25, 2006, terminates
period, the Executive Director has
None. the repetitive inspections required by this
delegated the authority to issue ADs
paragraph.
applicable to transport category (c) Applicability
airplanes to the Director of the System (1) This AD applies to all The Boeing (h) Airplanes for Actions Specified in
Oversight Division. Company Model 737–100, –200, –200C, Paragraph (g) of This AD
–300, –400, and –500 series airplanes, The actions specified in paragraph (g) of
Regulatory Findings certificated in any category. this AD are required for airplanes that meet
This AD will not have federalism (2) Installation of Supplemental Type the criteria of paragraphs (h)(1), (h)(2), (h)(3),
implications under Executive Order Certificate (STC) ST01219SE (http:// and (h)(4) of this AD.
13132. This AD will not have a rgl.faa.gov/Regulatory_and_Guidance_ (1) Model 737–100, –200, and –200C series
Library/rgstc.nsf/0/EBD1CEC7B301293 airplanes, line numbers 1 through 999
substantial direct effect on the States, on
E86257CB30045557A?OpenDocument inclusive.
the relationship between the national (2) Airplanes identified as Groups 1, 2, and
&Highlight=st01219se) does not affect the
government and the States, or on the ability to accomplish the actions required by 3 in Boeing Alert Service Bulletin 737–
distribution of power and this AD. Therefore, for airplanes on which 53A1166, Revision 2, dated May 25, 2006.
responsibilities among the various STC ST01219SE is installed, a ‘‘change in (3) Airplanes on which a preventive
levels of government. product’’ alternative method of compliance modification has been installed in
For the reasons discussed above, I (AMOC) approval request is not necessary to accordance with the method specified in
certify that this AD: comply with the requirements of 14 CFR paragraph (h)(3)(i), (h)(3)(ii), or (h)(3)(iii) of
(1) Is not a ‘‘significant regulatory 39.17. this AD.
action’’ under Executive Order 12866, Note 1 to paragraph (h)(3) of this AD: The
(d) Subject modification identified in paragraph (h)(3) of
(2) Is not a ‘‘significant rule’’ under
sradovich on DSK3GMQ082PROD with RULES
Air Transport Association (ATA) of this AD is also specified in paragraph (r) of
DOT Regulatory Policies and Procedures AD 2012–23–04, Amendment 39–17260 (77
America Code 53, Fuselage.
(44 FR 11034, February 26, 1979), FR 69747, November 21, 2012), as optional
(3) Will not affect intrastate aviation (e) Unsafe Condition terminating action.
in Alaska, and This AD was prompted by reports of (i) Part 6 of the Accomplishment
(4) Will not have a significant fatigue cracking in the frame outboard chord Instructions of Boeing Alert Service Bulletin
economic impact, positive or negative, and in the radius of the auxiliary chord at 737–53A1166, Revision 2, dated May 25,
on a substantial number of small entities body station (BS) 727 and stringer (S) 18A. 2006.
VerDate Sep<11>2014 17:21 Jan 11, 2018 Jkt 244001 PO 00000 Frm 00017 Fmt 4700 Sfmt 4700 E:\FR\FM\12JAR1.SGM 12JAR1](https://thefederalregister.org/doc/83_FR_1538/page/3.svg)
![1532 Federal Register / Vol. 83, No. 9 / Friday, January 12, 2018 / Rules and Regulations
(ii) Part II of the Accomplishment (j) Follow-On Inspection for Interim Airframe Section, FAA, Los Angeles ACO
Instructions of Boeing Alert Service Bulletin Modification and Repair Branch, 3960 Paramount Boulevard,
737–53A1166, Revision 1, dated May 25, For airplanes having line numbers 1 Lakewood, CA 90712–4137; phone: 562–627–
1995. through 3132 inclusive, on which an interim 5232; fax: 562–627–5210; email:
(iii) Part II of the Accomplishment modification of the BS 727 outboard chord as george.garrido@faa.gov.
Instructions of Boeing Alert Service Bulletin defined in part 6 of the Accomplishment (n) Material Incorporated by Reference
737–53A1166, dated June 30, 1994. Instructions of Boeing Alert Service Bulletin
(4) Airplanes on which the outboard chord 737–53A1166, Revision 2, dated May 25, (1) The Director of the Federal Register
has not been replaced in accordance with the 2006, has been accomplished: Within 60,000 approved the incorporation by reference
method specified in paragraph (h)(4)(i), flight cycles after accomplishment of the (IBR) of the service information listed in this
interim modification of the outboard chord of paragraph under 5 U.S.C. 552(a) and 1 CFR
(h)(4)(ii), or (h)(4)(iii) of this AD.
the frame at BS 727 at S–18A, but no earlier part 51.
(i) Part 3 of the Accomplishment
than 50,000 flight cycles after (2) You must use this service information
Instructions of Boeing Alert Service Bulletin
accomplishment of the modification, do a as applicable to do the actions required by
737–53A1166, Revision 2, dated May 25,
one-time follow-on open-hole eddy current this AD, unless the AD specifies otherwise.
2006. (3) The following service information was
inspection to detect cracks in the modified
(ii) Part I of the Accomplishment approved for IBR on December 26, 2012 (77
chord, in accordance with part 8 of the
Instructions of Boeing Alert Service Bulletin FR 69747, November 21, 2012).
Accomplishment Instructions of Boeing Alert
737–53A1166, Revision 1, dated May 25, Service Bulletin 737–53A1166, Revision 2, (i) Boeing Alert Service Bulletin 737–
1995. dated May 25, 2006. If any crack is found 53A1166, Revision 2, dated May 25, 2006.
(iii) Part I of the Accomplishment during the inspection required by this (ii) Reserved.
Instructions of Boeing Alert Service Bulletin paragraph, before further flight, repair in (4) For service information identified in
737–53A1166, dated June 30, 1994. accordance with part 3 or part 4, as this AD, contact Boeing Commercial
(i) Edge Margin Measurement, Related applicable, of the Accomplishment Airplanes, Attention: Contractual & Data
Instructions of Boeing Alert Service Bulletin Services (C&DS), 2600 Westminster Blvd.,
Investigative Actions, and Repair
737–53A1166, Revision 2, dated May 25, MC 110–SK57, Seal Beach, CA 90740;
For Model 737–100, –200, and –200C 2006; except, where the repairs cannot be telephone 562–797–1717; internet https://
series airplanes having line numbers 1 installed using the procedures identified in www.myboeingfleet.com.
through 999 inclusive, identified as Groups this service bulletin, repair before further (5) You may view this service information
1 through 3 in Boeing Alert Service Bulletin flight using a method approved in at the FAA, Transport Standards Branch,
737–53A1166, Revision 2, dated May 25, accordance with the procedures specified in 1601 Lind Avenue SW, Renton, WA. For
2006, on which the preventive modification paragraph (l) of this AD. information on the availability of this
has been installed in accordance with Boeing (k) Exception to the Service Information material at the FAA, call 425–227–1221.
Alert Service Bulletin 737–53A1166, dated (6) You may view this service information
June 30, 1994; or Boeing Alert Service Access and restoration procedures that is incorporated by reference at the
Bulletin 737–53A1166, Revision 1, dated specified in the Accomplishment National Archives and Records
Instructions of Boeing Alert Service Bulletin Administration (NARA). For information on
May 25, 1995: Within 60,000 flight cycles
737–53A1166, Revision 2, dated May 25, the availability of this material at NARA, call
after accomplishing the preventive
2006, are not required by this AD. Operators
modification, determine if the modification is 202–741–6030, or go to: http://
may do those actions following their
classified as interim or permanent by using www.archives.gov/federal-register/cfr/ibr-
approved maintenance procedures.
the edge margin measurement classification locations.html.
specified in part 6 of the Accomplishment (l) Alternative Methods of Compliance Issued in Renton, Washington, on January
Instructions of Boeing Alert Service Bulletin (AMOCs) 2, 2018.
737–53A1166, Revision 2, dated May 25, (1) The Manager, Los Angeles ACO Branch, Michael Kaszycki,
2006. In lieu of measuring on the airplane, FAA, has the authority to approve AMOCs
a review of engineering documentation may Acting Director, System Oversight Division,
for this AD, if requested using the procedures
be used to classify the modification if the found in 14 CFR 39.19. In accordance with Aircraft Certification Service.
engineering documentation was completed at 14 CFR 39.19, send your request to your [FR Doc. 2018–00256 Filed 1–11–18; 8:45 am]
the time of the modification and has the edge principal inspector or local Flight Standards BILLING CODE 4910–13–P
margins recorded. District Office, as appropriate. If sending
(1) If the modification is classified as information directly to the manager of the
permanent, no further action is required by certification office, send it to the attention of DEPARTMENT OF TRANSPORTATION
paragraph (i) of this AD. the person identified in paragraph (m) of this
(2) If the modification is classified as AD. Information may be emailed to: 9-ANM- Federal Aviation Administration
interim: Within 60,000 flight cycles after LAACO-AMOC-Requests@faa.gov.
accomplishment of the interim modification (2) Before using any approved AMOC,
14 CFR Part 39
of the outboard chord of the frame at BS 727 notify your appropriate principal inspector,
at S–18A, but no earlier than 50,000 flight or lacking a principal inspector, the manager [Docket No. FAA–2017–1242; Product
cycles after accomplishment of the of the local flight standards district office/ Identifier 2013–NM–043–AD; Amendment
modification, do a one-time follow-on open- certificate holding district office. 39–19150; AD 2018–01–09]
hole eddy current inspection to detect cracks (3) An AMOC that provides an acceptable
level of safety may be used for any repair, RIN 2120–AA64
in the modified chord, in accordance with
modification, or alteration required by this
part 8 of the Accomplishment Instructions of
AD if it is approved by the Boeing Airworthiness Directives; Fokker
Boeing Alert Service Bulletin 737–53A1166,
Commercial Airplanes Organization Services B.V. Airplanes
Revision 2, dated May 25, 2006. If any crack Designation Authorization (ODA) that has
is found, before further flight, repair in been authorized by the Manager, Los Angeles AGENCY: Federal Aviation
accordance with part 3 or part 4, as ACO Branch, to make those findings. To be Administration (FAA), DOT.
sradovich on DSK3GMQ082PROD with RULES
applicable, of the Accomplishment approved, the repair method, modification
Instructions of Boeing Alert Service Bulletin ACTION: Final rule; request for
deviation, or alteration deviation must meet
737–53A1166, Revision 2, dated May 25, the certification basis of the airplane, and the comments.
2006; except, if the repairs cannot be approval must specifically refer to this AD.
installed using the identified procedures, SUMMARY: We are superseding
repair before further flight using a method (m) Related Information Airworthiness Directive (AD) 95–25–02,
approved in accordance with the procedures For more information about this AD, which applied to certain Fokker
specified in paragraph (l) of this AD. contact George Garrido, Aerospace Engineer, Services B.V. Model F28 Mark 0100
VerDate Sep<11>2014 15:52 Jan 11, 2018 Jkt 244001 PO 00000 Frm 00018 Fmt 4700 Sfmt 4700 E:\FR\FM\12JAR1.SGM 12JAR1](https://thefederalregister.org/doc/83_FR_1538/page/4.svg)
Document Created: 2018-10-26 09:51:50
Document Modified: 2018-10-26 09:51:50
| 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 February 16, 2018 . | |
| Contact | George Garrido, Aerospace Engineer, Airframe Section, FAA, Los Angeles ACO Branch, 3960 Paramount Boulevard, Lakewood, CA 90712-4137; phone: 562-627-5232; fax: 562-627- 5210; email: [email protected] | |
| FR Citation | 83 FR 1529 | |
| RIN Number | 2120-AA64 | |
| CFR Associated | Air Transportation; Aircraft; Aviation Safety; Incorporation by Reference and Safety |
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