81 FR 72511 - Airworthiness Directives; The Boeing Company Airplanes
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration Federal Register Volume 81, Issue 203 (October 20, 2016)
Federal Aviation Administration
Federal Register Volume 81, Issue 203 (October 20, 2016)
| Page Range | 72511-72515 | |
| FR Document | 2016-23078 |
[Federal Register Volume 81, Number 203 (Thursday, October 20, 2016)] [Rules and Regulations] [Pages 72511-72515] From the Federal Register Online [www.thefederalregister.org] [FR Doc No: 2016-23078] ----------------------------------------------------------------------- DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA-2015-6538; Directorate Identifier 2015-NM-031-AD; Amendment 39-18668; AD 2016-20-02] 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 certain The Boeing Company Model 737-300, -400, and -500 series airplanes. This AD was prompted by an evaluation by the design approval holder (DAH) indicating that the aft pressure bulkhead is subject to widespread fatigue damage (WFD). This AD requires repetitive inspections of the aft pressure bulkhead web for any cracking, incorrectly drilled fastener holes, and elongated fastener holes; and related investigative and corrective actions, if necessary. We are issuing this AD to detect and correct fatigue cracking of the aft pressure bulkhead web at the ``Y''-chord, which could result in reduced structural [[Page 72512]] integrity of the airplane and rapid decompression of the fuselage. DATES: This AD is effective November 25, 2016. The Director of the Federal Register approved the incorporation by reference of a certain publication listed in this AD as of November 25, 2016. ADDRESSES: For service information identified in this final rule, contact Boeing Commercial Airplanes, Attention: Data & Services Management, P.O. Box 3707, MC 2H-65, Seattle, WA 98124-2207; telephone 206-544-5000, extension 1; fax 206-766-5680; Internet https://www.myboeingfleet.com. You may view this referenced service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For information on the availability of this material at the FAA, call 425-227-1221. It is also available on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2015- 6538. 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-2015- 6538; 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 AD, 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: Payman Soltani, Aerospace Engineer, Airframe Branch, ANM-120L, FAA, Los Angeles Aircraft Certification Office, 3960 Paramount Boulevard, Lakewood, CA 90712-4137; telephone: 562-627-5313; fax: 562-627-5210; email: [email protected]. 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 certain The Boeing Company Model 737-100, -200, -200C, -300, -400, and -500 series airplanes. The NPRM published in the Federal Register on November 30, 2015 (80 FR 74731) (``the NPRM''). The NPRM was prompted by an evaluation by the DAH indicating that the aft pressure bulkhead is subject to WFD. The NPRM proposed to require repetitive inspections of the aft pressure bulkhead web for any cracking, incorrectly drilled fastener holes, and elongated fastener holes, and related investigative and corrective actions, if necessary. We are issuing this AD to detect and correct fatigue cracking of the aft pressure bulkhead web at the ``Y''-chord, which could result in reduced structural integrity of the airplane and rapid decompression of the fuselage. Comments We gave the public the opportunity to participate in developing this AD. The following presents the comments received on the NPRM and the FAA's response to each comment. Effect of Winglets on Accomplishment of the Proposed Actions Aviation Partners Boeing stated that the installation of winglets per supplemental type certificate (STC) ST01219SE does not affect the accomplishment of the manufacturer's service instructions. We agree with the commenter. We have redesignated paragraph (c) of the NPRM as paragraph (c)(1) in this final rule and added a new paragraph (c)(2) to state that STC ST01219SE does not affect the mitigating action or accomplishment of the actions required by this final rule. 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 39.71. Request To Clarify the Proposed Requirements of the NPRM Mr. Cas Lausberg stated that the subject of the NPRM is addressed in AD 99-08-23, Amendment 39-11132 (64 FR 19879, April 23, 1999) (``AD 99-08-23''), which was superseded by AD 2012-18-13 R1, Amendment 39- 17429 (78 FR 27020, May 9, 2013) (``AD 2012-18-13 R1''). The commenter questioned the need for the new NPRM. We agree to provide clarification. As stated in the ``Discussion'' section of the NPRM, this final rule is being issued as part of the overall joint effort by Boeing and the FAA to satisfy requirements of the FAA's WFD final rule (75 FR 69746, November 15, 2010), which became effective on January 14, 2011. The inspections required by AD 99-08-23 and AD 2012-18-13 R1 do not address WFD concerns. However, Boeing Alert Service Bulletin 737-53A1214, Revision 5, dated January 30, 2015, addresses WFD with new inspection requirements, which incorporate a compliance time (threshold) corresponding to the WFD inspection start point (ISP) and shorter repetitive intervals where indicated. These requirements are included in this AD. We have not changed this AD in this regard. Request To Revise the Term ``Global Fatigue Damage'' Boeing requested that the term ``global fatigue damage'' be changed to ``widespread fatigue damage'' in the NPRM. Boeing stated that this is the first time it has seen the term ``global'' used to describe WFD. Boeing commented that it is better not to introduce a new term. We agree with the commenter. Although the ``Discussion'' section of the proposed rule is not carried over into the final rule, we agree that the term ``global fatigue damage'' should not be introduced as a new term. We have not changed this AD in this regard. Request To Correct Reference to Group 1 LOV (Limit of Validity) Boeing requested that we change the wording in the ``Differences Between This Proposed AD and the Service Information'' paragraph of the NPRM, which referred to WFD-based inspections specified in certain tables of Boeing Alert Service Bulletin 737-53A1214, Revision 5, dated January 30, 2015. The NPRM stated that the WFD-based inspections would affect only Group 2 airplanes because Group 1 airplanes will reach their LOV before the compliance times specified ``in tables 9, 10, and 11'' of Boeing Alert Service Bulletin 737-53A1214, Revision 5, dated January 30, 2015. Boeing stated that the inspections listed in tables 9, 10, and 11 of Boeing Alert Service Bulletin 737-53A1214, Revision 5, dated January 30, 2015, also include non-WFD inspections that are required prior to the ISP threshold of 76,000 cycles. Boeing stated that, therefore, it is not true to say that Group 1 airplanes will reach their limit of validity before the compliance times specified in tables 9, 10 and 11. We partially agree with the commenter. Although the ``Differences Between This Proposed AD and the Service Information'' paragraph of the proposed rule is not carried over into the final rule, we agree to provide clarification. Since AD 2012-18-13 R1 was issued, Boeing issued Alert Service Bulletin 737-53A1214, Revision 5, dated January 30, 2015. Affected airplanes are now divided into two groups: Group 1, line numbers 1 through 2565 inclusive; and Group 2, line numbers 2566 through [[Page 72513]] 3132 inclusive. Boeing's evaluation determined that inspections to address WFD concerns are required for the aft pressure bulkhead web at the ``Y'' chord at an ISP of 76,000 total flight cycles. Since Group 1 airplanes will reach their LOV of 75,000 total flight cycles (34,000 total flight cycles for line numbers 1 through 291 inclusive), which is prior to this ISP, no WFD inspections are provided for those airplanes. For Group 2 airplanes, which have an LOV of 85,000 total flight cycles, new tables 9, 10, and 11 of Boeing Alert Service Bulletin 737-53A1214, Revision 5, dated January 30, 2015, include inspections to address WFD. We have not changed this AD in this regard. Request To Clarify the Applicability Boeing requested that we clarify the applicability of the proposed AD. Boeing stated that Model 737-100, -200, and -200C airplanes should be removed from the ``Applicability'' paragraph. Boeing stated that the Group 2 airplanes only include Model 737-300, -400, and -500 airplanes. We agree with the commenter's request for the reasons stated above. We have revised the applicability in paragraph (c) of this AD to remove Model 737-100, -200, and -200C series airplanes and revised the SUMMARY section to specify certain Model 737-300, -400, and -500 series airplanes. Request To Clarify Airplanes Affected by Terminating Action Provisions Boeing requested that we change the wording for the terminating action in paragraph (j) of the proposed AD. Boeing stated that the paragraph should specify that the terminating action applies only to Group 2 airplanes. Boeing stated that specifying Group 2 airplanes clearly states the intent of the terminating action. We agree with the commenter's request for the reasons stated above. We have expanded the structure of paragraph (j) of this AD accordingly. In addition, we have clarified that the terminating action does not apply to stringer S-5L to S-7L and stringer S-5R to S-9R, as specified in AD 2012-18-13 R1 and Boeing Alert Service Bulletin 737-53A1214, Revision 5, dated January 30, 2015. Request To Revise the Inspections for Group 2 Airplanes All Nippon Airways (ANA) requested that we revise the inspection requirements in the proposed AD for Group 2 airplanes. ANA requested that we either mandate the inspections in tables 10 and 11 of Boeing Alert Service Bulletin 737-53A1214, Revision 5, dated January 30, 2015, for only Group 2 airplanes with 76,000 flight cycles and more, or create a new NPRM to supersede AD 2012-18-13 R1 to mandate all inspection requirements using Boeing Alert Service Bulletin 737- 53A1214, Revision 5, dated January 30, 2015. ANA stated that if a new proposed rule is created, it requests that credit be given for any previously approved AMOCs to AD 2012-18-13 R1, to reduce additional burden for operators and the FAA. We agree with the commenter's request for the reasons stated by the commenter. The intent of this final rule is to address the WFD concerns in accordance with the FAA's WFD final rule (75 FR 69746, November 15, 2010). We have revised paragraphs (g), (h), and (l) of this AD accordingly. Additional Changes to This AD In paragraphs (g) and (h) of this AD, we have clarified the compliance times by explicitly stating the compliance times instead of referring to the compliance tables in paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin 737-53A1214, Revision 5, dated January 30, 2015. The actions in paragraph (h) of the proposed AD states to do detailed and eddy current inspections of the aft pressure bulkhead web from the forward or aft side of the bulkhead for any cracking, incorrectly drilled fastener hole, and elongated fastener hole. In this AD, we have clarified the actions by providing the operators the option of doing detailed and LFEC inspections from the aft side of the aft pressure bulkhead, or doing a detailed and HFEC inspections from the forward side of the aft pressure bulkhead, for any cracking, incorrectly drilled fastener hole, and elongated fastener hole. Conclusion We reviewed the relevant data, considered the comments received, and determined that air safety and the public interest require adopting this AD with the changes described previously and minor editorial changes. We have determined that these minor changes:Are consistent with the intent that was proposed in the NPRM for 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 AD. Related Service Information Under 1 CFR Part 51 We reviewed Boeing Alert Service Bulletin 737-53A1214, Revision 5, dated January 30, 2015. The service information describes procedures for, among other actions, repetitive inspections of the aft pressure bulkhead web for any cracking, incorrectly drilled fastener holes, and elongated fastener holes; and related investigative and corrective actions. This service information is reasonably available because the interested parties have access to it through their normal course of business or by the means identified in the ADDRESSES section. Costs of Compliance We estimate that this AD affects 122 airplanes of U.S. registry. We estimate the following costs to comply with this AD: Estimated Costs ---------------------------------------------------------------------------------------------------------------- Cost on U.S. Action Labor cost Parts cost Cost per product operators ---------------------------------------------------------------------------------------------------------------- Inspections of the web at the Up to 60 work-hours x $0 Up to $5,100 per Up to $622,200 ``Y''-chord. $85 per hour = Up to inspection cycle. per inspection $5,100 per inspection cycle. cycle. ---------------------------------------------------------------------------------------------------------------- We have received no definitive data that will enable us to provide cost estimates for the on-condition actions specified in this AD. Authority for This Rulemaking Title 49 of the United States Code specifies the FAA's authority to issue rules on aviation safety. Subtitle I, section 106, describes the authority of the FAA Administrator. Subtitle VII: Aviation Programs, describes in more detail the scope of the Agency's authority. We are issuing this rulemaking under the authority described in Subtitle VII, Part A, Subpart III, Section 44701: [[Page 72514]] ``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 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): 2016-20-02 The Boeing Company: Amendment 39-18668; Docket No. FAA- 2015-6538; Directorate Identifier 2015-NM-031-AD. (a) Effective Date This AD is effective November 25, 2016. (b) Affected ADs This AD affects AD 2012-18-13 R1, Amendment 39-17429 (78 FR 27020, May 9, 2013) (``AD 2012-18-13 R1''). (c) Applicability (1) This AD applies to The Boeing Company Model 737-300, -400, and -500 series airplanes, certificated in any category, identified as Group 2 in Boeing Alert Service Bulletin 737-53A1214, Revision 5, dated January 30, 2015. (2) Installation of Supplemental Type Certificate (STC) ST01219SE (http://rgl.faa.gov/Regulatory_and_Guidance_Library/rgstc.nsf/0/EBD1CEC7B301293E86257CB30045557A?OpenDocument&Highlight=st01219s) 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 an evaluation by the design approval holder indicating that the aft pressure bulkhead is subject to widespread fatigue damage. We are issuing this AD to detect and correct fatigue cracking of the aft pressure bulkhead web at the ``Y''-chord, which could result in reduced structural integrity of the airplane and rapid decompression of the fuselage. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Repetitive Inspections of the Aft Pressure Bulkhead Web at the ``Y''-Chord Upper Bulkhead Within 76,000 total flight cycles, or within 4,500 flight cycles since the most recent low frequency eddy current (LFEC) inspection accomplished in accordance with AD 2012-18-13 R1, or within 9,500 flight cycles since the most recent high frequency eddy current (HFEC) inspection accomplished in accordance with AD 2012-18-13 R1, whichever occurs latest: Do detailed and LFEC inspections from the aft side of the aft pressure bulkhead web, or do detailed and HFEC inspections from the forward side of the aft pressure bulkhead web, for any cracking, incorrectly drilled fastener hole, and elongated fastener hole, and do all applicable related investigative and corrective actions, in accordance with Part I of the Accomplishment Instructions of Boeing Alert Service Bulletin 737-53A1214, Revision 5, dated January 30, 2015, except as required by paragraph (i) of this AD. Do all related investigative and corrective actions before further flight. If any cracking, incorrectly drilled fastener hole, or elongated fastener hole is found, before further flight, repair the aft pressure bulkhead web using a method approved in accordance with the procedures specified in paragraph (l) of this AD. Thereafter, repeat the inspections at the applicable times specified in table 10 of paragraph 1.E., ``Compliance'' of Boeing Alert Service Bulletin 737-53A1214, Revision 5, dated January 30, 2015. (h) Repetitive Inspections of the Aft Pressure Bulkhead Web at the ``Y''-Chord Below S-15 Within 76,000 total flight cycles, or within 4,500 flight cycles since the most recent LFEC inspection accomplished in accordance with AD 2012-18-13 R1, or within 9,500 flight cycles since the most recent HFEC inspection accomplished in accordance with AD 2012-18-13 R1, whichever occurs latest: Do detailed and LFEC inspections from the aft side of the aft pressure bulkhead, or do detailed and HFEC inspections from the forward side of the aft pressure bulkhead, for any cracking, incorrectly drilled fastener hole, and elongated fastener hole, and do all applicable corrective actions, in accordance with Part III of the Accomplishment Instructions of Boeing Alert Service Bulletin 737-53A1214, Revision 5, dated January 30, 2015, except as required by paragraph (i) of this AD. Do all corrective actions before further flight. If any cracking, incorrectly drilled fastener hole, or elongated fastener hole is found, before further flight, repair the aft pressure bulkhead web using a method approved in accordance with the procedures specified in paragraph (l) of this AD. Thereafter, repeat the inspections at the applicable times specified in table 11 of paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin 737-53A1214, Revision 5, dated January 30, 2015. (i) Exception to the Service Information Where Boeing Alert Service Bulletin 737-53A1214, Revision 5, dated January 30, 2015, specifies to contact Boeing for repair instructions: Before further flight, repair using a method approved in accordance with the procedures specified in paragraph (l) of this AD. (j) Terminating Action for Other Rulemaking (1) For Group 2 airplanes specified in Boeing Alert Service Bulletin 737-53A1214, Revision 5, dated January 30, 2015: Accomplishing the actions required by paragraph (g) of this AD terminates the inspections required by paragraph (k) of AD 2012-18- 13 R1, except for stringer S-5L to S-7L and stringer S-5R to S-9R. (2) For Group 2 airplanes specified in Boeing Alert Service Bulletin 737-53A1214, Revision 5, dated January 30, 2015: Accomplishing the actions required by paragraph (h) of this AD terminates the inspections required by paragraph (l) of AD 2012-18- 13 R1. (k) Credit for Previous Actions This paragraph provides credit for the actions required by paragraphs (g) and (h) of this AD, if the actions were performed before the effective date of this AD using Boeing Alert Service Bulletin 737-53A1214, Revision 4, dated December 16, 2011. [[Page 72515]] (l) Alternative Methods of Compliance (AMOCs) (1) The Manager, Los Angeles Aircraft Certification Office (ACO), FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. In accordance with 14 CFR 39.19, send your request to your principal inspector or local Flight Standards District Office, as appropriate. If sending information directly to the manager of the ACO, send it to the attention of the person identified in paragraph (m)(1) of this AD. Information may be emailed to: [email protected]. (2) Before using any approved AMOC, notify your appropriate principal inspector, or lacking a principal inspector, the manager of the local flight standards district office/certificate holding district office. (3) An AMOC that provides an acceptable level of safety may be used for any repair, modification, or alteration required by this AD if it is approved by the Boeing Commercial Airplanes Organization Designation Authorization (ODA) that has been authorized by the Manager, Los Angeles ACO, to make those findings. To be approved, the repair method, modification deviation, or alteration deviation must meet the certification basis of the airplane, and the approval must specifically refer to this AD. (4) AMOCs approved previously for AD 2012-18-13 R1, Amendment 39-17429 (78 FR 27020, May 9, 2013), are approved as AMOCs for the corresponding provisions of this AD. (m) Related Information (1) For more information about this AD, contact Payman Soltani, Aerospace Engineer, Airframe Branch, ANM-120L, FAA, Los Angeles ACO, 3960 Paramount Boulevard, Lakewood CA 90712-4137; telephone: 562- 627-5313; fax: 562-627-5210; email: [email protected]. (2) Service information identified in this AD that is not incorporated by reference is available at the addresses specified in paragraphs (n)(3) and (n)(4) of this AD. (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. (i) Boeing Alert Service Bulletin 737-53A1214, Revision 5, dated January 30, 2015. (ii) Reserved. (3) For service information identified in this AD, contact Boeing Commercial Airplanes, Attention: Data & Services Management, P.O. Box 3707, MC 2H-65, Seattle, WA 98124-2207; telephone 206-544- 5000, extension 1; fax 206-766-5680; Internet https://www.myboeingfleet.com. (4) You may view this 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. (5) You may view this service information that is incorporated by reference at the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, call 202-741-6030, or go to: http://www.archives.gov/federal-register/cfr/ibr-locations.html. Issued in Renton, Washington, on September 16, 2016. Thomas Groves, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2016-23078 Filed 10-19-16; 8:45 am] BILLING CODE 4910-13-P
![Federal Register / Vol. 81, No. 203 / Thursday, October 20, 2016 / Rules and Regulations 72511
TABLE 1 TO PARAGRAPH (j)(4) OF THIS Sanjay Ralhan, Aerospace Engineer, (6) The following service information was
International Branch, ANM–116, Transport approved for IBR on August 28, 2007 (72 FR
AD—ASM REPLACEMENT—Continued 40222, July 24, 2007).
Airplane Directorate, FAA, 1601 Lind
Avenue SW., Renton, WA 98057–3356; (i) Airbus A318/A319/A320/A321 Fuel
Affected airplane Airworthiness Limitations, Document
ASM part No. telephone 425–227–1405; fax 425–227–1149.
configuration
Information may be emailed to: 9-ANM-116- 95A.1931/05, Issue 1, dated December 19,
Post-Airbus Service Bulletin AMOC-REQUESTS@faa.gov. 2005.
A320–47–1011 .................. 2060017–102 (i) Before using any approved AMOC, (ii) Reserved.
notify your appropriate principal inspector, (7) For service information identified in
or lacking a principal inspector, the manager this AD, contact Airbus, Airworthiness
(k) Retained Requirement: No Alternative
of the local flight standards district office/ Office—EIAS, 1 Rond Point Maurice
Actions, Intervals, and/or CDCCLs, With No
certificate holding district office. The AMOC Bellonte, 31707 Blagnac Cedex, France;
Changes
approval letter must specifically reference telephone +33 5 61 93 36 96; fax +33 5 61
This paragraph restates the requirements of 93 44 51; email account.airworth-eas@
this AD.
paragraph (k) of AD 2012–20–07, with no airbus.com; Internet http://www.airbus.com.
(ii) AMOCs approved previously for AD
changes. Except as required by paragraph (l) (8) You may view this service information
of this AD, after accomplishing the revisions 2012–20–07 are approved as AMOCs for the
corresponding provisions of this AD. at the FAA, Transport Airplane Directorate,
required by paragraph (j) of this AD, no 1601 Lind Avenue SW., Renton, WA. For
alternative actions (e.g., inspections), (2) Contacting the Manufacturer: As of the
effective date of this AD, for any requirement information on the availability of this
intervals, and/or CDCCLs may be used other material at the FAA, call 425–227–1221.
than those specified in Airbus A318/A319/ in this AD to obtain corrective actions from
(9) You may view this service information
A320/A321 ALS Part 5—Fuel Airworthiness a manufacturer, the action must be
that is incorporated by reference at the
Limitations, dated February 28, 2006, as accomplished using a method approved by
National Archives and Records
defined in Airbus A318/A319/A320/A321 the Manager, International Branch, ANM–
Administration (NARA). For information on
Fuel Airworthiness Limitations, Document 116, Transport Airplane Directorate, FAA; or
the availability of this material at NARA, call
95A.1931/05, Issue 4, dated August 26, 2010, EASA; or Airbus’s EASA DOA. If approved
202–741–6030, or go to: http://www.archives.
unless the actions, intervals, and/or CDCCLs by the DOA, the approval must include the
gov/federal-register/cfr/ibr-locations.html.
are approved as an alternative method of DOA-authorized signature.
compliance (AMOC) in accordance with the Issued in Renton, Washington, on
(o) Related Information September 28, 2016.
procedures specified in paragraph (n)(1) of
this AD. (1) Refer to Mandatory Continuing Dionne Palermo,
Airworthiness Information (MCAI) EASA
(l) New Requirement of This AD: Revise the Acting Manager, Transport Airplane
Airworthiness Directive 2014–0260, dated
Maintenance or Inspection Program Directorate, Aircraft Certification Service.
December 5, 2014, for related information.
Within 60 days after the effective date of This MCAI may be found in the AD docket [FR Doc. 2016–24078 Filed 10–19–16; 8:45 am]
this AD, revise the maintenance or inspection on the Internet at http://www.regulations.gov BILLING CODE 4910–13–P
program, as applicable, by incorporating the by searching for and locating Docket No.
fuel airworthiness limitations (e.g., life FAA–2016–5589.
limits, tasks, and CDCCLs, and associated (2) Service information identified in this DEPARTMENT OF TRANSPORTATION
thresholds and intervals) described in Airbus AD that is not incorporated by reference is
A318/A319/A320/A321 ALS Part 5, Fuel available at the addresses specified in Federal Aviation Administration
Airworthiness Limitations, Revision 01, paragraphs (p)(7) and (p)(8) of this AD.
dated July 9, 2014. The initial compliance 14 CFR Part 39
times for the tasks are at the times specified (p) Material Incorporated by Reference
in Airbus A318/A319/A320/A321 ALS Part (1) The Director of the Federal Register [Docket No. FAA–2015–6538; Directorate
5, Fuel Airworthiness Limitations, Revision approved the incorporation by reference Identifier 2015–NM–031–AD; Amendment
01, dated July 9, 2014, or within 60 days after (IBR) of the service information listed in this 39–18668; AD 2016–20–02]
the effective date of this AD, whichever paragraph under 5 U.S.C. 552(a) and 1 CFR
occurs later. Incorporating the requirements RIN 2120–AA64
part 51.
of this paragraph terminates the requirements (2) You must use this service information
of paragraphs (g) through (k) of this AD. Airworthiness Directives; The Boeing
as applicable to do the actions required by
this AD, unless this AD specifies otherwise.
Company Airplanes
(m) New Requirement of This AD: No
Alternative Actions, Intervals, or CDCCLs (3) The following service information was AGENCY: Federal Aviation
approved for IBR on November 25, 2016. Administration (FAA), DOT.
After the maintenance or inspection (i) Airbus A318/A319/A320/A321
program has been revised as required by ACTION: Final rule.
Airworthiness Limitations Section (ALS) Part
paragraph (l) of this AD, no alternative
5, Fuel Airworthiness Limitations, Revision SUMMARY: We are adopting a new
actions (e.g., inspections), intervals, or
01, dated July 9, 2014. The title page of this
CDCCLs may be used unless the actions, airworthiness directive (AD) for certain
document does not contain the revision date.
intervals, or CDCCLs are approved as an The Boeing Company Model 737–300,
AMOC in accordance with the procedures The remaining pages of this document do not
include the revision level. –400, and –500 series airplanes. This
specified in paragraph (n)(1) of this AD. AD was prompted by an evaluation by
(ii) Reserved.
(n) Other FAA AD Provisions (4) The following service information was the design approval holder (DAH)
The following provisions also apply to this approved for IBR on November 21, 2012 (77 indicating that the aft pressure bulkhead
AD: FR 63716, October 17, 2012). is subject to widespread fatigue damage
(1) Alternative Methods of Compliance (i) Airbus A318/A319/A320/A321 Fuel (WFD). This AD requires repetitive
(AMOCs): The Manager, International Airworthiness Limitations, Document inspections of the aft pressure bulkhead
asabaliauskas on DSK3SPTVN1PROD with RULES
Branch, ANM–116, Transport Airplane 95A.1931/05, Issue 4, dated August 26, 2010. web for any cracking, incorrectly drilled
Directorate, FAA, has the authority to (ii) Reserved.
fastener holes, and elongated fastener
approve AMOCs for this AD, if requested (5) The following service information was
approved for IBR on December 14, 2009 (74
holes; and related investigative and
using the procedures found in 14 CFR 39.19.
In accordance with 14 CFR 39.19, send your FR 62219, November 27, 2009). corrective actions, if necessary. We are
request to your principal inspector or local (i) Airbus A318/A319/A320/A321 Fuel issuing this AD to detect and correct
Flight Standards District Office, as Airworthiness Limitations, Document fatigue cracking of the aft pressure
appropriate. If sending information directly 95A.1931/05, Issue 2, dated July 8, 2008. bulkhead web at the ‘‘Y’’-chord, which
to the International Branch, send it to ATTN: (ii) Reserved. could result in reduced structural
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![72514 Federal Register / Vol. 81, No. 203 / Thursday, October 20, 2016 / Rules and Regulations
‘‘General requirements.’’ Under that (b) Affected ADs procedures specified in paragraph (l) of this
section, Congress charges the FAA with This AD affects AD 2012–18–13 R1, AD. Thereafter, repeat the inspections at the
promoting safe flight of civil aircraft in Amendment 39–17429 (78 FR 27020, May 9, applicable times specified in table 10 of
air commerce by prescribing regulations 2013) (‘‘AD 2012–18–13 R1’’). paragraph 1.E., ‘‘Compliance’’ of Boeing Alert
for practices, methods, and procedures Service Bulletin 737–53A1214, Revision 5,
(c) Applicability dated January 30, 2015.
the Administrator finds necessary for
(1) This AD applies to The Boeing
safety in air commerce. This regulation Company Model 737–300, –400, and –500 (h) Repetitive Inspections of the Aft Pressure
is within the scope of that authority series airplanes, certificated in any category, Bulkhead Web at the ‘‘Y’’-Chord Below S–15
because it addresses an unsafe condition identified as Group 2 in Boeing Alert Service Within 76,000 total flight cycles, or within
that is likely to exist or develop on Bulletin 737–53A1214, Revision 5, dated 4,500 flight cycles since the most recent
products identified in this rulemaking January 30, 2015. LFEC inspection accomplished in accordance
action. (2) Installation of Supplemental Type with AD 2012–18–13 R1, or within 9,500
Certificate (STC) ST01219SE (http:// flight cycles since the most recent HFEC
Regulatory Findings rgl.faa.gov/Regulatory_and_Guidance_ inspection accomplished in accordance with
Library/rgstc.nsf/0/EBD1CEC7B301293E8625 AD 2012–18–13 R1, whichever occurs latest:
This AD will not have federalism 7CB30045557A?
implications under Executive Order Do detailed and LFEC inspections from the
OpenDocument&Highlight=st01219s) does
13132. This AD will not have a aft side of the aft pressure bulkhead, or do
not affect the ability to accomplish the
substantial direct effect on the States, on detailed and HFEC inspections from the
actions required by this AD. Therefore, for
the relationship between the national airplanes on which STC ST01219SE is forward side of the aft pressure bulkhead, for
installed, a ‘‘change in product’’ alternative any cracking, incorrectly drilled fastener
government and the States, or on the
method of compliance (AMOC) approval hole, and elongated fastener hole, and do all
distribution of power and
request is not necessary to comply with the applicable corrective actions, in accordance
responsibilities among the various with Part III of the Accomplishment
levels of government. requirements of 14 CFR 39.17.
Instructions of Boeing Alert Service Bulletin
For the reasons discussed above, I (d) Subject 737–53A1214, Revision 5, dated January 30,
certify that this AD: Air Transport Association (ATA) of 2015, except as required by paragraph (i) of
(1) Is not a ‘‘significant regulatory America Code 53, Fuselage. this AD. Do all corrective actions before
action’’ under Executive Order 12866, (e) Unsafe Condition further flight. If any cracking, incorrectly
drilled fastener hole, or elongated fastener
(2) Is not a ‘‘significant rule’’ under This AD was prompted by an evaluation by hole is found, before further flight, repair the
DOT Regulatory Policies and Procedures the design approval holder indicating that aft pressure bulkhead web using a method
(44 FR 11034, February 26, 1979), the aft pressure bulkhead is subject to
approved in accordance with the procedures
(3) Will not affect intrastate aviation widespread fatigue damage. We are issuing
specified in paragraph (l) of this AD.
this AD to detect and correct fatigue cracking
in Alaska, and of the aft pressure bulkhead web at the ‘‘Y’’-
Thereafter, repeat the inspections at the
(4) Will not have a significant chord, which could result in reduced applicable times specified in table 11 of
economic impact, positive or negative, structural integrity of the airplane and rapid paragraph 1.E., ‘‘Compliance,’’ of Boeing
on a substantial number of small entities decompression of the fuselage. Alert Service Bulletin 737–53A1214,
Revision 5, dated January 30, 2015.
under the criteria of the Regulatory (f) Compliance
Flexibility Act. (i) Exception to the Service Information
Comply with this AD within the
List of Subjects in 14 CFR Part 39 compliance times specified, unless already Where Boeing Alert Service Bulletin 737–
done. 53A1214, Revision 5, dated January 30, 2015,
Air transportation, Aircraft, Aviation specifies to contact Boeing for repair
safety, Incorporation by reference, (g) Repetitive Inspections of the Aft Pressure instructions: Before further flight, repair
Bulkhead Web at the ‘‘Y’’-Chord Upper using a method approved in accordance with
Safety. Bulkhead
the procedures specified in paragraph (l) of
Adoption of the Amendment Within 76,000 total flight cycles, or within this AD.
4,500 flight cycles since the most recent low
Accordingly, under the authority frequency eddy current (LFEC) inspection (j) Terminating Action for Other Rulemaking
delegated to me by the Administrator, accomplished in accordance with AD 2012– (1) For Group 2 airplanes specified in
the FAA amends 14 CFR part 39 as 18–13 R1, or within 9,500 flight cycles since Boeing Alert Service Bulletin 737–53A1214,
follows: the most recent high frequency eddy current Revision 5, dated January 30, 2015:
(HFEC) inspection accomplished in Accomplishing the actions required by
PART 39—AIRWORTHINESS accordance with AD 2012–18–13 R1, paragraph (g) of this AD terminates the
DIRECTIVES whichever occurs latest: Do detailed and inspections required by paragraph (k) of AD
LFEC inspections from the aft side of the aft 2012–18–13 R1, except for stringer S–5L to
■ 1. The authority citation for part 39 pressure bulkhead web, or do detailed and
S–7L and stringer S–5R to S–9R.
continues to read as follows: HFEC inspections from the forward side of
(2) For Group 2 airplanes specified in
the aft pressure bulkhead web, for any
Authority: 49 U.S.C. 106(g), 40113, 44701. cracking, incorrectly drilled fastener hole, Boeing Alert Service Bulletin 737–53A1214,
and elongated fastener hole, and do all Revision 5, dated January 30, 2015:
§ 39.13 [Amended] applicable related investigative and Accomplishing the actions required by
corrective actions, in accordance with Part I paragraph (h) of this AD terminates the
■ 2. The FAA amends § 39.13 by adding inspections required by paragraph (l) of AD
of the Accomplishment Instructions of
the following new airworthiness
asabaliauskas on DSK3SPTVN1PROD with RULES
Boeing Alert Service Bulletin 737–53A1214, 2012–18–13 R1.
directive (AD): Revision 5, dated January 30, 2015, except as (k) Credit for Previous Actions
2016–20–02 The Boeing Company: required by paragraph (i) of this AD. Do all
Amendment 39–18668; Docket No. related investigative and corrective actions This paragraph provides credit for the
FAA–2015–6538; Directorate Identifier before further flight. If any cracking, actions required by paragraphs (g) and (h) of
2015–NM–031–AD. incorrectly drilled fastener hole, or elongated this AD, if the actions were performed before
fastener hole is found, before further flight, the effective date of this AD using Boeing
(a) Effective Date repair the aft pressure bulkhead web using a Alert Service Bulletin 737–53A1214,
This AD is effective November 25, 2016. method approved in accordance with the Revision 4, dated December 16, 2011.
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![Federal Register / Vol. 81, No. 203 / Thursday, October 20, 2016 / Rules and Regulations 72515
(l) Alternative Methods of Compliance National Archives and Records FAA, Transport Airplane Directorate,
(AMOCs) Administration (NARA). For information on 1601 Lind Avenue SW., Renton, WA.
(1) The Manager, Los Angeles Aircraft the availability of this material at NARA, call For information on the availability of
Certification Office (ACO), FAA, has the 202–741–6030, or go to: http://
this material at the FAA, call 425–227–
authority to approve AMOCs for this AD, if www.archives.gov/federal-register/cfr/ibr-
locations.html. 1221. It is also available on the Internet
requested using the procedures found in 14 at http://www.regulations.gov by
CFR 39.19. In accordance with 14 CFR 39.19, Issued in Renton, Washington, on
send your request to your principal inspector searching for and locating Docket No.
September 16, 2016.
or local Flight Standards District Office, as FAA–2016–0465.
Thomas Groves,
appropriate. If sending information directly Examining the AD Docket
to the manager of the ACO, send it to the Acting Manager, Transport Airplane
attention of the person identified in Directorate, Aircraft Certification Service. You may examine the AD docket on
paragraph (m)(1) of this AD. Information may [FR Doc. 2016–23078 Filed 10–19–16; 8:45 am] the Internet at http://
be emailed to: 9-ANM-LAACO-AMOC- BILLING CODE 4910–13–P www.regulations.gov by searching for
Requests@faa.gov. and locating Docket No. FAA–2016–
(2) Before using any approved AMOC,
notify your appropriate principal inspector,
0465; or in person at the Docket
DEPARTMENT OF TRANSPORTATION Management Facility between 9 a.m.
or lacking a principal inspector, the manager
of the local flight standards district office/ and 5 p.m., Monday through Friday,
certificate holding district office.
Federal Aviation Administration except Federal holidays. The AD docket
(3) An AMOC that provides an acceptable contains this AD, the regulatory
level of safety may be used for any repair, 14 CFR Part 39 evaluation, any comments received, and
modification, or alteration required by this other information. The street address for
[Docket No. FAA–2016–0465; Directorate
AD if it is approved by the Boeing
Commercial Airplanes Organization
Identifier 2015–NM–096–AD; Amendment the Docket Office (telephone: 800–647–
39–18679; AD 2016–20–13] 5527) is Docket Management Facility,
Designation Authorization (ODA) that has
been authorized by the Manager, Los Angeles RIN 2120–AA64 U.S. Department of Transportation,
ACO, to make those findings. To be Docket Operations, M–30, West
approved, the repair method, modification Airworthiness Directives; Airbus Building Ground Floor, Room W12–140,
deviation, or alteration deviation must meet Airplanes 1200 New Jersey Avenue SE.,
the certification basis of the airplane, and the Washington, DC 20590.
approval must specifically refer to this AD. AGENCY: Federal Aviation
(4) AMOCs approved previously for AD FOR FURTHER INFORMATION CONTACT:
Administration (FAA), Department of Vladimir Ulyanov, Aerospace Engineer,
2012–18–13 R1, Amendment 39–17429 (78
Transportation (DOT). International Branch, ANM–116,
FR 27020, May 9, 2013), are approved as
AMOCs for the corresponding provisions of ACTION: Final rule. Transport Airplane Directorate, FAA,
this AD. 1601 Lind Avenue SW., Renton, WA
SUMMARY: We are adopting a new
(m) Related Information 98057–3356; telephone: 425–227–1138;
airworthiness directive (AD) for certain
(1) For more information about this AD, fax: 425–227–1149.
Airbus Model A330–200 and –300 series
contact Payman Soltani, Aerospace Engineer, airplanes; and Model A340–200 and SUPPLEMENTARY INFORMATION:
Airframe Branch, ANM–120L, FAA, Los –300 series airplanes. This AD was
Angeles ACO, 3960 Paramount Boulevard, Discussion
Lakewood CA 90712–4137; telephone: 562– prompted by a determination that the
compliance times for certain post-repair We issued a notice of proposed
627–5313; fax: 562–627–5210; email: rulemaking (NPRM) to amend 14 CFR
payman.soltani@faa.gov. inspections and certain allowable
(2) Service information identified in this damage limits (ADLs) must be reduced part 39 by adding an AD that would
AD that is not incorporated by reference is in order to address fatigue. This AD apply to certain Airbus Model A330–
available at the addresses specified in requires identifying any repairs and 200 and –300 series airplanes; and
paragraphs (n)(3) and (n)(4) of this AD. ADLs used to assess or control any Model A340–200 and –300 series
(n) Material Incorporated by Reference structural damage on certain structural airplanes. The NPRM published in the
areas, and corrective action if necessary. Federal Register on February 18, 2016
(1) The Director of the Federal Register (81 FR 8160) (‘‘the NPRM’’). The NPRM
approved the incorporation by reference We are issuing this AD to prevent
(IBR) of the service information listed in this fatigue damage on primary structure and was prompted by a determination that
paragraph under 5 U.S.C. 552(a) and 1 CFR structural repairs, which could result in the compliance times for certain post-
part 51. reduced structural integrity of the repair inspections and certain ADLs
(2) You must use this service information airplane. must be reduced in order to address
as applicable to do the actions required by fatigue. The NPRM proposed to require
this AD, unless the AD specifies otherwise. DATES: This AD is effective November identifying any repairs and ADLs used
(i) Boeing Alert Service Bulletin 737– 25, 2016. to assess or control any structural
53A1214, Revision 5, dated January 30, 2015. The Director of the Federal Register damage on certain structural areas, and
(ii) Reserved. approved the incorporation by reference
(3) For service information identified in
corrective action if necessary. We are
of certain publications listed in this AD issuing this AD to prevent fatigue
this AD, contact Boeing Commercial
Airplanes, Attention: Data & Services
as of November 25, 2016. damage on primary structure and
Management, P.O. Box 3707, MC 2H–65, ADDRESSES: For service information structural repairs, which could result in
Seattle, WA 98124–2207; telephone 206– identified in this final rule, contact reduced structural integrity of the
asabaliauskas on DSK3SPTVN1PROD with RULES
544–5000, extension 1; fax 206–766–5680; Airbus, Airworthiness Office—EIAS, 1 airplane.
Internet https://www.myboeingfleet.com. Rond Point Maurice Bellonte, 31707 The European Aviation Safety Agency
(4) You may view this service information Blagnac Cedex, France; telephone: +33 5 (EASA), which is the Technical Agent
at the FAA, Transport Airplane Directorate,
1601 Lind Avenue SW., Renton, WA. For
61 93 36 96; fax: +33 5 61 93 44 51; for the Member States of the European
information on the availability of this email: account.airworth-eas@ Union, has issued EASA AD 2015–
material at the FAA, call 425–227–1221. airbus.com; Internet: http:// 0101R1, dated June 12, 2015 (referred to
(5) You may view this service information www.airbus.com. You may view this after this as the Mandatory Continuing
that is incorporated by reference at the referenced service information at the Airworthiness Information, or ‘‘the
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Document Created: 2016-10-21 09:58:59
Document Modified: 2016-10-21 09:58:59
| 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 November 25, 2016. | |
| Contact | Payman Soltani, Aerospace Engineer, Airframe Branch, ANM-120L, FAA, Los Angeles Aircraft Certification Office, 3960 Paramount Boulevard, Lakewood, CA 90712-4137; telephone: 562-627-5313; fax: 562-627-5210; email: [email protected] | |
| FR Citation | 81 FR 72511 | |
| RIN Number | 2120-AA64 | |
| CFR Associated | Air Transportation; Aircraft; Aviation Safety; Incorporation by Reference and Safety |
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