82 FR 29792 - Airworthiness Directives; The Boeing Company Airplanes
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration Federal Register Volume 82, Issue 125 (June 30, 2017)
Federal Aviation Administration
Federal Register Volume 82, Issue 125 (June 30, 2017)
| Page Range | 29792-29795 | |
| FR Document | 2017-13773 |
[Federal Register Volume 82, Number 125 (Friday, June 30, 2017)] [Proposed Rules] [Pages 29792-29795] From the Federal Register Online [www.thefederalregister.org] [FR Doc No: 2017-13773] ----------------------------------------------------------------------- DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA-2017-0629; Directorate Identifier 2016-NM-184-AD] RIN 2120-AA64 Airworthiness Directives; The Boeing Company Airplanes AGENCY: Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). ----------------------------------------------------------------------- SUMMARY: We propose to adopt a new airworthiness directive (AD) for all The Boeing Company Model 737-100, -200, -200C, -300, -400, and -500 series airplanes. This proposed 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 proposed AD would require inspections to detect this cracking, and corrective action if necessary. We are proposing this AD to address the unsafe condition on these products. DATES: We must receive comments on this proposed AD by August 14, 2017. ADDRESSES: You may send comments, using the procedures found in 14 CFR 11.43 and 11.45, by any of the following methods:Federal eRulemaking Portal: Go to http://www.regulations.gov. Follow the instructions for submitting comments. Fax: 202-493-2251. Mail: U.S. Department of Transportation, Docket Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New Jersey Avenue SE., Washington, DC 20590. Hand Delivery: Deliver to Mail address above between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. For service information identified in this NPRM, contact Boeing Commercial Airplanes, Attention: Contractual & Data Services (C&DS), 2600 Westminster Blvd., MC 110-SK57, Seal Beach, CA 90740; telephone 562-797-1717; Internet https://www.myboeingfleet.com. You may view this referenced service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For information on the availability of this material at the FAA, call 425-227-1221. It is also available on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-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 proposed AD, the regulatory evaluation, any comments received, and other information. The street address for the Docket Office (phone: 800-647-5527) is in the ADDRESSES section. Comments will be available in the AD docket shortly after receipt. FOR FURTHER INFORMATION CONTACT: Alan Pohl, Aerospace Engineer, Airframe Branch, ANM-120S, FAA, Seattle Aircraft Certification Office, 1601 Lind Avenue SW., Renton, Washington 98057-3356; phone: (425) 917- 6450; fax: (425) 917-6590; email: [email protected]. SUPPLEMENTARY INFORMATION: Comments Invited We invite you to send any written relevant data, views, or arguments about this proposal. Send your comments to an address listed under the ADDRESSES section. Include ``Docket No. FAA-2017-0629; Directorate Identifier 2016-NM-184-AD'' at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of this proposed AD. We will consider all comments received by the closing date and may amend this proposed AD because of those comments. We will post all comments we receive, without change, to http://www.regulations.gov, including any personal information you provide. We will also post a report summarizing each substantive verbal contact we receive about this proposed AD. Discussion We have received reports indicating that fatigue cracking was found in the frame outboard chord at BS 727 and in the radius of the auxiliary chord at BS 727 and S-18A on certain airplanes. Cracks in the outboard chord were found on airplanes having between 20,000 and 85,000 flight cycles, and between 27,000 and 74,000 flight hours. Cracks in the radius of the auxiliary chord were found on airplanes having between 46,000 and 85,000 flight cycles, and between 41,000 and 64,000 flight hours. The cracks were caused by fatigue, and, for certain airplanes, the fretting of adjacent parts contributed to the initiation of the fatigue damage. This condition, if not corrected, could result in reduced structural integrity of the outboard chord and consequent rapid decompression of the airplane. Related Rulemaking On October 16, 2012, we issued AD 2012-23-04, Amendment 39-17260 (77 FR 69747, November 21, 2012) (``AD 2012-23-04''), applicable to all The Boeing Company Model 737-100, -200, -200C, -300, -400, and -500 series airplanes. That AD requires various inspections for cracks in the outboard chord of the frame at BS 727. That AD also requires inspections for cracks in the BS 727 frame outboard chord and the radius of the auxiliary chord, for certain airplanes. That AD was prompted by several reports of fatigue cracking in the frame outboard chord at BS 727 and in the radius of the auxiliary chord. The actions required by that AD are intended 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. [[Page 29793]] Since issuance of AD 2012-23-04, the FAA has found discrepancies in the requirements of that AD, as follows: The optional terminating action specified in paragraph (r) of AD 2012-23-04 allows terminating action if the preventive modification is installed. However, Boeing Alert Service Bulletin 737- 53A1166, Revision 2, dated May 25, 2006, allows terminating action only if both the BS 727 outboard chord is replaced and the preventive modification is installed. Consequently, for airplanes having line numbers 1 through 999 inclusive on which the preventive modification may have been installed, the outboard chord may not have been replaced. Additionally, paragraph (r)(2) of AD 2012-23-04 specifies replacing only a cracked outboard chord; however, the intent was to require replacement of the outboard chord whether it was cracked or not. In light of these factors, there could be cracking in the auxiliary chord combined with cracking in the outboard chord. This cracking could progress undetected and result in the identified unsafe condition. Boeing Alert Service Bulletin 737-53A1166, Revision 2, dated May 25, 2006, contains instructions to determine whether the modification should be classified as interim or permanent; a one-time inspection is specified after the interim modification is done. The instructions specified in the previous service information did not contain this stipulation during installation of the preventive modification. Therefore, the modification could have resulted in edge margins in the frame outboard chord that would have been classified as interim had the modification been done in accordance with Boeing Alert Service Bulletin 737-53A1166, Revision 2, dated May 25, 2006. Since neither Boeing Alert Service Bulletin 737-53A1166, Revision 2, dated May 25, 2006, nor AD 2012-23-04 contained instructions to measure edge margins, it is possible that an edge margin condition exists, so the one-time follow-on inspection must be done. Paragraph (r) of AD 2012-23-04 terminates the one-time inspection specified in Part 8 of the Accomplishment Instructions of Boeing Alert Service Bulletin 737-53A1166, Revision 2, dated May 25, 2006, for airplanes that have the interim preventive modification installed. This inspection is referenced in paragraph (o) of AD 2012- 23-04, and should not have been terminated. Paragraph (o) of AD 2012- 23-04 was incorrectly included in the list of paragraphs with inspections that are terminated after accomplishing paragraph (r) of that AD. Therefore, since the discrepancies described previously provide inadvertent relief to operators, we find it necessary to issue additional, new AD rulemaking to provide additional inspection requirements. We have confirmed that the requirements of this AD correct those discrepancies and do not conflict with other requirements of AD 2012-23-04. 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 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. FAA's Determination We are proposing this AD because we evaluated all the relevant information and determined the unsafe condition described previously is likely to exist or develop in other products of these same type designs. Proposed AD Requirements This proposed AD would require accomplishing the actions specified in the service information described previously. This AD corrects discrepancies in the requirements for certain airplanes identified in AD 2012-23-04. The FAA has considered that fact in determining whether to issue a new AD action or to supersede AD 2012-23-04. We have determined that a less burdensome approach is to issue a separate AD action applicable to the airplanes on which the discrepancies could have occurred. This proposed AD would not supersede AD 2012-23-04, and compliance with the requirements must continue for airplanes listed in the applicability of AD 2012-23-04. This proposed AD is a separate AD action, applicable only to the airplanes identified in paragraph (c) of this AD. Costs of Compliance We estimate the following costs to comply with this proposed AD: Estimated Costs -------------------------------------------------------------------------------------------------------------------------------------------------------- Affected airplanes Cost per Action Labor cost of U.S. product Cost on U.S. operators registry -------------------------------------------------------------------------------------------------------------------------------------------------------- Detailed and High Frequency Eddy Current 6 work-hours x $85 per hour 5 $510 $2,550 per inspection cycle. (HFEC) inspections. = $510 per inspection cycle. One-time follow-on HFEC inspection....... 9 work-hours x $85 per hour 5 765 $3,825. = $765. HFEC inspection.......................... 9 work-hours x $85 per hour 150 765 $114,750. = $765. -------------------------------------------------------------------------------------------------------------------------------------------------------- We estimate the following costs to do any necessary repairs that would be required based on the results of the inspections. We have no way of determining the number of aircraft that might need these repairs: On-Condition Costs ---------------------------------------------------------------------------------------------------------------- Cost per Action Labor cost Parts cost product ---------------------------------------------------------------------------------------------------------------- Repair of cracking of the outboard chord frame 514 work-hours x $85 per hour = $13,586 $57,276 $43,690. Repair of cracking of the outboard chord...... 49 work-hours x $85 per hour = 4,255 8,420 $4,165. ---------------------------------------------------------------------------------------------------------------- [[Page 29794]] Authority for This Rulemaking Title 49 of the United States Code specifies the FAA's authority to issue rules on aviation safety. Subtitle I, section 106, describes the authority of the FAA Administrator. Subtitle VII: Aviation Programs, describes in more detail the scope of the Agency's authority. We are issuing this rulemaking under the authority described in Subtitle VII, Part A, Subpart III, Section 44701: ``General requirements.'' Under that section, Congress charges the FAA with promoting safe flight of civil aircraft in air commerce by prescribing regulations for practices, methods, and procedures the Administrator finds necessary for safety in air commerce. This regulation is within the scope of that authority because it addresses an unsafe condition that is likely to exist or develop on products identified in this rulemaking action. Regulatory Findings We determined that this proposed AD would not have federalism implications under Executive Order 13132. This proposed AD would not have a substantial direct effect on the States, on the relationship between the national Government and the States, or on the distribution of power and responsibilities among the various levels of government. For the reasons discussed above, I certify this proposed regulation: (1) Is not a ``significant regulatory action'' under Executive Order 12866, (2) Is not a ``significant rule'' under the DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979), (3) Will not affect intrastate aviation in Alaska, and (4) Will not have a significant economic impact, positive or negative, on a substantial number of small entities under the criteria of the Regulatory Flexibility Act. List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. The Proposed Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA proposes to amend 14 CFR part 39 as follows: PART 39--AIRWORTHINESS DIRECTIVES 0 1. The authority citation for part 39 continues to read as follows: Authority: 49 U.S.C. 106(g), 40113, 44701. Sec. 39.13 [Amended] 0 2. The FAA amends Sec. 39.13 by adding the following new airworthiness directive (AD): The Boeing Company: Docket No. FAA-2017-0629; Directorate Identifier 2016-NM-184-AD. (a) Comments Due Date We must receive comments by August 14, 2017. (b) Affected ADs None. (c) Applicability This AD applies to all The Boeing Company Model 737-100, -200, - 200C, -300, -400, and -500 series airplanes, certificated in any category. (d) Subject 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. (i) Part 6 of the Accomplishment Instructions of Boeing Alert Service Bulletin 737-53A1166, Revision 2, dated May 25, 2006. (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 and repair 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 [[Page 29795]] 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, Seattle Aircraft Certification Office (ACO), FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. In accordance with 14 CFR 39.19, send your request to your principal inspector or local Flight Standards District Office, as appropriate. If sending information directly to the manager of the ACO, send it to the attention of the person identified in paragraph (m)(1) of this AD. Information may be emailed to: 9-ANM[email protected]. (2) Before using any approved AMOC, notify your appropriate principal inspector, or lacking a principal inspector, the manager of the local flight standards district office/certificate holding district office. (3) An AMOC that provides an acceptable level of safety may be used for any repair, modification, or alteration required by this AD if it is approved by the Boeing Commercial Airplanes Organization Designation Authorization (ODA) that has been authorized by the Manager, Seattle ACO, to make those findings. To be approved, the repair method, modification deviation, or alteration deviation must meet the certification basis of the airplane, and the approval must specifically refer to this AD. (m) Related Information (1) For more information about this AD, contact Alan Pohl, Aerospace Engineer, Airframe Branch, ANM-120S, FAA, Seattle Aircraft Certification Office, 1601 Lind Avenue SW., Renton, Washington 98057-3356; phone: (425) 917-6450; fax: (425) 917-6590; email: [email protected]. (2) For service information identified in this AD, contact Boeing Commercial Airplanes, Attention: Contractual & Data Services (C&DS), 2600 Westminster Blvd., MC 110-SK57, Seal Beach, CA 90740; telephone 562-797-1717; Internet https://www.myboeingfleet.com. You may view this referenced service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For information on the availability of this material at the FAA, call 425-227-1221. Issued in Renton, Washington, on June 22, 2017. John P. Piccola, Jr., Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2017-13773 Filed 6-29-17; 8:45 am] BILLING CODE 4910-13-P
![29792 Federal Register / Vol. 82, No. 125 / Friday, June 30, 2017 / Proposed Rules
116, Transport Airplane Directorate, FAA; or DATES: We must receive comments on this proposal. Send your comments to
the European Aviation Safety Agency this proposed AD by August 14, 2017. an address listed under the ADDRESSES
(EASA); or Airbus’s EASA Design section. Include ‘‘Docket No. FAA–
ADDRESSES: You may send comments,
Organization Approval (DOA). If approved by
using the procedures found in 14 CFR 2017–0629; Directorate Identifier 2016–
the DOA, the approval must include the
DOA-authorized signature. 11.43 and 11.45, by any of the following NM–184–AD’’ at the beginning of your
methods: comments. We specifically invite
(k) Related Information
• Federal eRulemaking Portal: Go to comments on the overall regulatory,
(1) Refer to Mandatory Continuing http://www.regulations.gov. Follow the economic, environmental, and energy
Airworthiness Information (MCAI) EASA AD instructions for submitting comments. aspects of this proposed AD. We will
2016–0217, dated November 2, 2016, for
• Fax: 202–493–2251. consider all comments received by the
related information. This MCAI may be
found in the AD docket on the Internet at • Mail: U.S. Department of closing date and may amend this
http://www.regulations.gov by searching for Transportation, Docket Operations, M– proposed AD because of those
and locating Docket No. FAA–2017–0628. 30, West Building Ground Floor, Room comments.
(2) For more information about this AD, W12–140, 1200 New Jersey Avenue SE., We will post all comments we
contact Dan Rodina, Aerospace Engineer, Washington, DC 20590. receive, without change, to http://
International Branch, ANM–116, Transport • Hand Delivery: Deliver to Mail www.regulations.gov, including any
Airplane Directorate, FAA, 1601 Lind address above between 9 a.m. and 5 personal information you provide. We
Avenue SW., Renton, WA 98057–3356; p.m., Monday through Friday, except will also post a report summarizing each
telephone 425–227–2125; fax 425–227–1149.
(3) For service information identified in Federal holidays. substantive verbal contact we receive
this AD, contact Airbus SAS, Airworthiness For service information identified in about this proposed AD.
Office—EAW, 1 Rond Point Maurice this NPRM, contact Boeing Commercial
Airplanes, Attention: Contractual & Data Discussion
Bellonte, 31707 Blagnac Cedex, France;
telephone +33 5 61 93 36 96; fax +33 5 61 Services (C&DS), 2600 Westminster We have received reports indicating
93 44 51; email account.airworth-eas@ Blvd., MC 110–SK57, Seal Beach, CA that fatigue cracking was found in the
airbus.com; Internet http://www.airbus.com. 90740; telephone 562–797–1717; frame outboard chord at BS 727 and in
You may view this service information at the Internet https://
FAA, Transport Airplane Directorate, 1601
the radius of the auxiliary chord at BS
Lind Avenue SW., Renton, WA. For
www.myboeingfleet.com. You may view 727 and S–18A on certain airplanes.
information on the availability of this this referenced service information at Cracks in the outboard chord were
material at the FAA, call 425–227–1221. the FAA, Transport Airplane found on airplanes having between
Directorate, 1601 Lind Avenue SW., 20,000 and 85,000 flight cycles, and
Issued in Renton, Washington, on June 22,
2017. Renton, WA. For information on the between 27,000 and 74,000 flight hours.
availability of this material at the FAA, Cracks in the radius of the auxiliary
John P. Piccola, Jr.,
call 425–227–1221. It is also available chord were found on airplanes having
Acting Manager, Transport Airplane
on the Internet at http:// between 46,000 and 85,000 flight cycles,
Directorate, Aircraft Certification Service.
www.regulations.gov by searching for and between 41,000 and 64,000 flight
[FR Doc. 2017–13755 Filed 6–29–17; 8:45 am]
and locating Docket No. FAA–2017– hours. The cracks were caused by
BILLING CODE 4910–13–P
0629. fatigue, and, for certain airplanes, the
Examining the AD Docket fretting of adjacent parts contributed to
DEPARTMENT OF TRANSPORTATION the initiation of the fatigue damage. This
You may examine the AD docket on condition, if not corrected, could result
Federal Aviation Administration the Internet at http:// in reduced structural integrity of the
www.regulations.gov by searching for outboard chord and consequent rapid
14 CFR Part 39 and locating Docket No. FAA–2017– decompression of the airplane.
0629; or in person at the Docket
[Docket No. FAA–2017–0629; Directorate Management Facility between 9 a.m. Related Rulemaking
Identifier 2016–NM–184–AD] and 5 p.m., Monday through Friday, On October 16, 2012, we issued AD
RIN 2120–AA64 except Federal holidays. The AD docket 2012–23–04, Amendment 39–17260 (77
contains this proposed AD, the FR 69747, November 21, 2012) (‘‘AD
Airworthiness Directives; The Boeing regulatory evaluation, any comments 2012–23–04’’), applicable to all The
Company Airplanes received, and other information. The Boeing Company Model 737–100, –200,
street address for the Docket Office –200C, –300, –400, and –500 series
AGENCY: Federal Aviation
(phone: 800–647–5527) is in the airplanes. That AD requires various
Administration (FAA), DOT.
ADDRESSES section. Comments will be inspections for cracks in the outboard
ACTION: Notice of proposed rulemaking
available in the AD docket shortly after chord of the frame at BS 727. That AD
(NPRM). receipt. also requires inspections for cracks in
SUMMARY: We propose to adopt a new FOR FURTHER INFORMATION CONTACT: the BS 727 frame outboard chord and
airworthiness directive (AD) for all The Alan Pohl, Aerospace Engineer, the radius of the auxiliary chord, for
Boeing Company Model 737–100, –200, Airframe Branch, ANM–120S, FAA, certain airplanes. That AD was
–200C, –300, –400, and –500 series Seattle Aircraft Certification Office, prompted by several reports of fatigue
airplanes. This proposed AD was 1601 Lind Avenue SW., Renton, cracking in the frame outboard chord at
mstockstill on DSK30JT082PROD with PROPOSALS
prompted by reports of fatigue cracking Washington 98057–3356; phone: (425) BS 727 and in the radius of the auxiliary
in the frame outboard chord and in the 917–6450; fax: (425) 917–6590; email: chord. The actions required by that AD
radius of the auxiliary chord at a certain alan.pohl@faa.gov. are intended to detect and correct
area. This proposed AD would require SUPPLEMENTARY INFORMATION: fatigue cracking of the outboard and
inspections to detect this cracking, and auxiliary chords, which could result in
corrective action if necessary. We are Comments Invited reduced structural integrity of the
proposing this AD to address the unsafe We invite you to send any written outboard chord and consequent rapid
condition on these products. relevant data, views, or arguments about decompression of the airplane.
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Authority for This Rulemaking § 39.13 [Amended] (1) Model 737–100, –200, and –200C series
■ 2. The FAA amends § 39.13 by adding airplanes, line numbers 1 through 999
Title 49 of the United States Code inclusive.
specifies the FAA’s authority to issue the following new airworthiness
(2) Airplanes identified as Groups 1, 2, and
rules on aviation safety. Subtitle I, directive (AD): 3 in Boeing Alert Service Bulletin 737–
section 106, describes the authority of The Boeing Company: Docket No. FAA– 53A1166, Revision 2, dated May 25, 2006.
the FAA Administrator. Subtitle VII: 2017–0629; Directorate Identifier 2016– (3) Airplanes on which a preventive
Aviation Programs, describes in more NM–184–AD. modification has been installed in
detail the scope of the Agency’s accordance with the method specified in
(a) Comments Due Date
paragraph (h)(3)(i), (h)(3)(ii), or (h)(3)(iii) of
authority. We must receive comments by August 14, this AD.
We are issuing this rulemaking under 2017. (i) Part 6 of the Accomplishment
the authority described in Subtitle VII, Instructions of Boeing Alert Service Bulletin
Part A, Subpart III, Section 44701: (b) Affected ADs
737–53A1166, Revision 2, dated May 25,
‘‘General requirements.’’ Under that None. 2006.
section, Congress charges the FAA with (c) Applicability (ii) Part II of the Accomplishment
promoting safe flight of civil aircraft in Instructions of Boeing Alert Service Bulletin
This AD applies to all The Boeing 737–53A1166, Revision 1, dated May 25,
air commerce by prescribing regulations Company Model 737–100, –200, –200C,
for practices, methods, and procedures 1995.
–300, –400, and –500 series airplanes, (iii) Part II of the Accomplishment
the Administrator finds necessary for certificated in any category.
Instructions of Boeing Alert Service Bulletin
safety in air commerce. This regulation 737–53A1166, dated June 30, 1994.
(d) Subject
is within the scope of that authority (4) Airplanes on which the outboard chord
because it addresses an unsafe condition Air Transport Association (ATA) of
America Code 53, Fuselage. has not been replaced in accordance with the
that is likely to exist or develop on method specified in paragraph (h)(4)(i),
products identified in this rulemaking (e) Unsafe Condition (h)(4)(ii), or (h)(4)(iii) of this AD.
action. This AD was prompted by reports of (i) Part 3 of the Accomplishment
fatigue cracking in the frame outboard chord Instructions of Boeing Alert Service Bulletin
Regulatory Findings 737–53A1166, Revision 2, dated May 25,
and in the radius of the auxiliary chord at
We determined that this proposed AD body station (BS) 727 and stringer (S) 18A. 2006.
would not have federalism implications We are issuing this AD to detect and correct (ii) Part I of the Accomplishment
under Executive Order 13132. This fatigue cracking of the outboard and auxiliary Instructions of Boeing Alert Service Bulletin
chords, which could result in reduced 737–53A1166, Revision 1, dated May 25,
proposed AD would not have a 1995.
substantial direct effect on the States, on structural integrity of the outboard chord and
consequent rapid decompression of the (iii) Part I of the Accomplishment
the relationship between the national airplane. Instructions of Boeing Alert Service Bulletin
Government and the States, or on the 737–53A1166, dated June 30, 1994.
distribution of power and (f) Compliance
(i) Edge Margin Measurement, Related
responsibilities among the various Comply with this AD within the Investigative Actions, and Repair
levels of government. compliance times specified, unless already
For the reasons discussed above, I done. For Model 737–100, –200, and –200C
certify this proposed regulation: series airplanes having line numbers 1
(g) Repetitive Inspections and Corrective through 999 inclusive, identified as Groups
(1) Is not a ‘‘significant regulatory Action 1 through 3 in Boeing Alert Service Bulletin
action’’ under Executive Order 12866, 737–53A1166, Revision 2, dated May 25,
For airplanes identified in paragraph (h) of
(2) Is not a ‘‘significant rule’’ under this AD: Within 4,500 flight cycles or 24 2006, on which the preventive modification
the DOT Regulatory Policies and months after the effective date of this AD, has been installed in accordance with Boeing
Procedures (44 FR 11034, February 26, whichever occurs first, do internal detailed Alert Service Bulletin 737–53A1166, dated
1979), and High Frequency Eddy Current (HFEC) June 30, 1994; or Boeing Alert Service
(3) Will not affect intrastate aviation inspections to detect cracks in the auxiliary Bulletin 737–53A1166, Revision 1, dated
in Alaska, and chord radius, in accordance with Part 1 of the May 25, 1995: Within 60,000 flight cycles
(4) Will not have a significant Accomplishment Instructions of Boeing Alert after accomplishing the preventive
economic impact, positive or negative, Service Bulletin 737–53A1166, Revision 2, modification, determine if the modification is
on a substantial number of small entities dated May 25, 2006. If any crack is found classified as interim or permanent by using
during any inspection required by this the edge margin measurement and repair
under the criteria of the Regulatory
paragraph, before further flight, repair using classification specified in Part 6 of the
Flexibility Act. Accomplishment Instructions of Boeing Alert
a method approved in accordance with the
List of Subjects in 14 CFR Part 39 procedures specified in paragraph (l) of this Service Bulletin 737–53A1166, Revision 2,
AD. Repeat the inspections thereafter at dated May 25, 2006. In lieu of measuring on
Air transportation, Aircraft, Aviation intervals not to exceed 15,000 flight cycles. the airplane, a review of engineering
safety, Incorporation by reference, Replacement of the outboard chord of the documentation may be used to classify the
Safety. frame at BS 727 concurrently with the modification if the engineering
installation of the preventive modification of documentation was completed at the time of
The Proposed Amendment the modification and has the edge margins
the outboard chord in accordance with Part
Accordingly, under the authority 6 of the Accomplishment Instructions of recorded.
delegated to me by the Administrator, Boeing Alert Service Bulletin 737–53A1166, (1) If the modification is classified as
the FAA proposes to amend 14 CFR part Revision 2, dated May 25, 2006, terminates permanent, no further action is required by
mstockstill on DSK30JT082PROD with PROPOSALS
39 as follows: the repetitive inspections required by this paragraph (i) of this AD.
paragraph. (2) If the modification is classified as
PART 39—AIRWORTHINESS interim: Within 60,000 flight cycles after
(h) Airplanes for Actions Specified in accomplishment of the interim modification
DIRECTIVES Paragraph (g) of This AD of the outboard chord of the frame at BS 727
The actions specified in paragraph (g) of at S–18A, but no earlier than 50,000 flight
■ 1. The authority citation for part 39
this AD are required for airplanes that meet cycles after accomplishment of the
continues to read as follows: the criteria of paragraphs (h)(1), (h)(2), (h)(3), modification, do a one-time follow-on open-
Authority: 49 U.S.C. 106(g), 40113, 44701. and (h)(4) of this AD. hole eddy current inspection to detect cracks
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![Federal Register / Vol. 82, No. 125 / Friday, June 30, 2017 / Proposed Rules 29795
in the modified chord, in accordance with (3) An AMOC that provides an acceptable THSA upper attachments and no-back
Part 8 of the Accomplishment Instructions of level of safety may be used for any repair, housing. We are proposing this AD to
Boeing Alert Service Bulletin 737–53A1166, modification, or alteration required by this address the unsafe condition on these
Revision 2, dated May 25, 2006. If any crack AD if it is approved by the Boeing
is found, before further flight, repair in Commercial Airplanes Organization
products.
accordance with Part 3 or Part 4, as Designation Authorization (ODA) that has DATES: We must receive comments on
applicable, of the Accomplishment been authorized by the Manager, Seattle this proposed AD by August 14, 2017.
Instructions of Boeing Alert Service Bulletin ACO, to make those findings. To be ADDRESSES: You may send comments,
737–53A1166, Revision 2, dated May 25, approved, the repair method, modification
2006; except, if the repairs cannot be deviation, or alteration deviation must meet
using the procedures found in 14 CFR
installed using the identified procedures, the certification basis of the airplane, and the 11.43 and 11.45, by any of the following
repair before further flight using a method approval must specifically refer to this AD. methods:
approved in accordance with the procedures • Federal eRulemaking Portal: Go to
specified in paragraph (l) of this AD. (m) Related Information http://www.regulations.gov. Follow the
(1) For more information about this AD, instructions for submitting comments.
(j) Follow-On Inspection for Interim
Modification and Repair
contact Alan Pohl, Aerospace Engineer, • Fax: 202–493–2251.
Airframe Branch, ANM–120S, FAA, Seattle • Mail: U.S. Department of
For airplanes having line numbers 1 Aircraft Certification Office, 1601 Lind
through 3132 inclusive, on which an interim
Transportation, Docket Operations, M–
Avenue SW., Renton, Washington 98057–
modification of the BS 727 outboard chord as 3356; phone: (425) 917–6450; fax: (425) 917– 30, West Building Ground Floor, Room
defined in Part 6 of the Accomplishment 6590; email: alan.pohl@faa.gov. W12–140, 1200 New Jersey Avenue SE.,
Instructions of Boeing Alert Service Bulletin (2) For service information identified in Washington, DC 20590.
737–53A1166, Revision 2, dated May 25, this AD, contact Boeing Commercial • Hand Delivery: Deliver to Mail
2006, has been accomplished: Within 60,000 Airplanes, Attention: Contractual & Data address above between 9 a.m. and 5
flight cycles after accomplishment of the Services (C&DS), 2600 Westminster Blvd., p.m., Monday through Friday, except
interim modification of the outboard chord of MC 110–SK57, Seal Beach, CA 90740; Federal holidays.
the frame at BS 727 at S–18A, but no earlier telephone 562–797–1717; Internet https:// For service information identified in
than 50,000 flight cycles after www.myboeingfleet.com. You may view this
accomplishment of the modification, do a
this NPRM, contact Airbus SAS,
referenced service information at the FAA,
one-time follow-on open-hole eddy current Transport Airplane Directorate, 1601 Lind Airworthiness Office—EAL, 1 Rond
inspection to detect cracks in the modified Avenue SW., Renton, WA. For information Point Maurice Bellonte, 31707 Blagnac
chord, in accordance with Part 8 of the on the availability of this material at the Cedex, France; telephone +33 5 61 93 36
Accomplishment Instructions of Boeing Alert FAA, call 425–227–1221. 96; fax +33 5 61 93 45 80; email
Service Bulletin 737–53A1166, Revision 2, airworthiness.A330-A340@airbus.com;
Issued in Renton, Washington, on June 22,
dated May 25, 2006. If any crack is found Internet http://www.airbus.com. You
2017.
during the inspection required by this may view this referenced service
paragraph, before further flight, repair in John P. Piccola, Jr.,
Acting Manager, Transport Airplane
information at the FAA, Transport
accordance with Part 3 or Part 4, as
applicable, of the Accomplishment Directorate, Aircraft Certification Service. Airplane Directorate, 1601 Lind Avenue
Instructions of Boeing Alert Service Bulletin SW., Renton, WA. For information on
[FR Doc. 2017–13773 Filed 6–29–17; 8:45 am]
737–53A1166, Revision 2, dated May 25, the availability of this material at the
BILLING CODE 4910–13–P
2006; except, where the repairs cannot be FAA, call 425–227–1221.
installed using the procedures identified in
this service bulletin, repair before further Examining the AD Docket
flight using a method approved in DEPARTMENT OF TRANSPORTATION
You may examine the AD docket on
accordance with the procedures specified in the Internet at http://
paragraph (l) of this AD. Federal Aviation Administration
www.regulations.gov by searching for
(k) Exception to the Service Information 14 CFR Part 39 and locating Docket No. FAA–2017–
Access and restoration procedures 0627; or in person at the Docket
specified in the Accomplishment [Docket No. FAA–2017–0627; Directorate Management Facility between 9 a.m.
Instructions of Boeing Alert Service Bulletin Identifier 2017–NM–037–AD] and 5 p.m., Monday through Friday,
737–53A1166, Revision 2, dated May 25, RIN 2120–AA64 except Federal holidays. The AD docket
2006, are not required by this AD. Operators contains this proposed AD, the
may do those actions following their Airworthiness Directives; Airbus regulatory evaluation, any comments
approved maintenance procedures. Airplanes received, and other information. The
(l) Alternative Methods of Compliance street address for the Docket Operations
(AMOCs)
AGENCY: Federal Aviation
Administration (FAA), DOT. office (telephone 800–647–5527) is in
(1) The Manager, Seattle Aircraft the ADDRESSES section. Comments will
ACTION: Notice of proposed rulemaking
Certification Office (ACO), FAA, has the be available in the AD docket shortly
authority to approve AMOCs for this AD, if (NPRM).
after receipt.
requested using the procedures found in 14
CFR 39.19. In accordance with 14 CFR 39.19,
SUMMARY: We propose to adopt a new FOR FURTHER INFORMATION CONTACT:
send your request to your principal inspector airworthiness directive (AD) for all Vladimir Ulyanov, Aerospace Engineer,
or local Flight Standards District Office, as Airbus Model A330–200 Freighter, International Branch, ANM–116,
appropriate. If sending information directly –200, and –300 series airplanes; and Transport Airplane Directorate, FAA,
to the manager of the ACO, send it to the Airbus Model A340–200, –300, –500, 1601 Lind Avenue SW., Renton, WA
mstockstill on DSK30JT082PROD with PROPOSALS
attention of the person identified in and –600 series airplanes. This 98057–3356; telephone 425–227–1138;
paragraph (m)(1) of this AD. Information may proposed AD was prompted by a report fax 425–227–1149.
be emailed to: 9-ANM-Seattle-ACO-AMOC- that the trimmable horizontal stabilizer SUPPLEMENTARY INFORMATION:
Requests@faa.gov.
(2) Before using any approved AMOC,
actuator (THSA) might not function as
intended after failure of the primary Comments Invited
notify your appropriate principal inspector,
or lacking a principal inspector, the manager load path. This proposed AD would We invite you to send any written
of the local flight standards district office/ require repetitive detailed visual relevant data, views, or arguments about
certificate holding district office. inspections for discrepancies of the this proposed AD. Send your comments
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Document Created: 2017-06-30 06:02:06
Document Modified: 2017-06-30 06:02:06
| Category | Regulatory Information | |
| Collection | Federal Register | |
| sudoc Class | AE 2.7: GS 4.107: AE 2.106: | |
| Publisher | Office of the Federal Register, National Archives and Records Administration | |
| Section | Proposed Rules | |
| Action | Notice of proposed rulemaking (NPRM). | |
| Dates | We must receive comments on this proposed AD by August 14, 2017. | |
| Contact | Alan Pohl, Aerospace Engineer, Airframe Branch, ANM-120S, FAA, Seattle Aircraft Certification Office, 1601 Lind Avenue SW., Renton, Washington 98057-3356; phone: (425) 917- 6450; fax: (425) 917-6590; email: [email protected] | |
| FR Citation | 82 FR 29792 | |
| RIN Number | 2120-AA64 | |
| CFR Associated | Air Transportation; Aircraft; Aviation Safety; Incorporation by Reference and Safety |
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