80 FR 51450 - Airworthiness Directives; The Boeing Company Airplanes
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration Federal Register Volume 80, Issue 164 (August 25, 2015)
Federal Aviation Administration
Federal Register Volume 80, Issue 164 (August 25, 2015)
| Page Range | 51450-51454 | |
| FR Document | 2015-20372 |
[Federal Register Volume 80, Number 164 (Tuesday, August 25, 2015)] [Rules and Regulations] [Pages 51450-51454] From the Federal Register Online [www.thefederalregister.org] [FR Doc No: 2015-20372] ----------------------------------------------------------------------- DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA-2014-0772; Directorate Identifier 2014-NM-090-AD; Amendment 39-18233; AD 2015-16-08] RIN 2120-AA64 Airworthiness Directives; The Boeing Company Airplanes AGENCY: Federal Aviation Administration (FAA), DOT. ACTION: Final rule. ----------------------------------------------------------------------- SUMMARY: We are superseding Airworthiness Directive (AD) 2011-08-51 for certain The Boeing Company Model 737-300, -400, and -500 series airplanes. AD 2011-08-51 required repetitive inspections of the lap joint at certain stringers along the entire length from certain body stations. This new AD expands the inspection area, requires additional inspections for cracks and open pockets, requires corrective actions if necessary, and revises the compliance times. This AD was prompted by an evaluation by the design approval holder (DAH) that has determined that the lower fastener holes in the lower skin of the fuselage lap splice are subject to widespread fatigue damage (WFD). We are issuing this AD to detect and correct fatigue cracking of the lower fastener holes in the lower skin of the fuselage lap splice, which could result in reduced structural integrity of the airplane. DATES: This AD is effective September 29, 2015. The Director of the Federal Register approved the incorporation by reference of a certain publication listed in this AD as of September 29, 2015. ADDRESSES: For service information identified in this AD, contact Boeing Commercial Airplanes, Attention: Data & Services Management, P.O. Box 3707, MC 2H-65, Seattle, WA 98124-2207; telephone 206-544- 5000, extension 1; fax 206-766-5680; Internet https://www.myboeingfleet.com. You may view this referenced service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For information on the availability of this material at the FAA, call 425-227-1221. It is also available on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA 2014- 0772. 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-2014- 0772; 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: Jennifer Tsakoumakis, Aerospace Engineer, Airframe Branch, ANM-120L, FAA, Los Angeles Aircraft Certification Office (ACO), 3960 Paramount Boulevard, Lakewood, CA 90712-4137; phone: 562-627-5264; fax: 562-627-5210; email: [email protected]. SUPPLEMENTARY INFORMATION: Discussion We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 to supersede AD 2011-08-51, Amendment 39-16701 (76 FR 28632, May 18, 2011). AD 2011-08-51 applied to certain The Boeing Company Model 737-300, -400, and -500 series airplanes. The NPRM published in the Federal Register on November 17, 2014 (79 FR 68381). The NPRM was prompted by an evaluation by the DAH that has determined that the lower fastener holes in the lower skin of the fuselage lap splice are subject to WFD. The NPRM proposed to continue to require repetitive inspections of the lap joint at certain stringers along the entire length from certain body stations. The NPRM also proposed to expand the inspection area, require additional inspections for cracks and open pockets, require corrective actions if necessary, and revise the compliance times. We are issuing this AD to detect and correct fatigue cracking of the lower fastener holes in the lower skin of the fuselage lap splice, which could result in reduced structural integrity of the airplane. Comments We gave the public the opportunity to participate in developing this AD. The following presents the comments received on the NPRM (79 FR 68381, November 17, 2014) and the FAA's response to each comment. Request To Revise Wording Boeing requested that we revise the last sentence in paragraph (k) of the proposed AD (79 FR 68381, November 17, 2014) to clarify that the on-condition actions may be ``inspection or repair'' rather than ``inspection and repair.'' Boeing stated that condition 10 in table 6 of Boeing Alert Service Bulletin 737-53A1319, Revision 2, dated April 4, 2014, describes obtaining inspection or repair instructions. Boeing explained that, depending on the configuration details identified, repetitive inspections alone may be an appropriate action, or a repair may be the appropriate action. We agree with the commenter's request. Varying detail configurations and the total flight cycles at the time of the finding are used to determine if an inspection program is adequate to address the unsafe condition or if installation of a repair is required. We have revised the wording in paragraph (k) of this AD to require inspection or repair. Request To Clarify Paragraph Heading Southwest Airlines (SWA) stated that the heading ``Repetitive Inspections for Crack Indications at Stringers S-4R and S-4L, Body Station (BS) 360 to BS 908,'' of paragraph (g) of the proposed AD (79 FR 68381, November 17, 2014) is misleading. SWA explained that the heading is confusing since the paragraph contains both an initial inspection and repetitive inspections. We agree to clarify the terminology used in the heading. When the term ``repetitive'' is used, it does not necessarily exclude the initial action. Many existing ADs use the term ``repetitive'' in the headers for paragraphs that contain both the initial action and repetitive actions. We find that no change to this AD is necessary regarding this issue. [[Page 51451]] Request To Add Clarifying Note SWA requested that we add a note in paragraph (g) and paragraph (h) of the proposed AD (79 FR 68381, November 17, 2014) specifying that Group 3 airplanes do not require inspection between BS 540 and BS 727E. SWA stated that Boeing Alert Service Bulletin 737-53A1319, Revision 2, dated April 4, 2014, specifies no inspections to be accomplished from BS 540 to BS 727E on Group 3 airplanes. SWA stated that, since paragraphs (g) and (h) of the proposed AD and tables 1, 2, and 3 of Boeing Alert Service Bulletin 737-53A1319, Revision 2, dated April 4, 2014, define the inspection area as stringers 4L and 4R from BS 360 to BS 908 for all airplanes, it could be interpreted that the proposed AD would require an increased inspection area for Group 3 airplanes. We partially agree with the commenter's request. We disagree to add a note in paragraph (g) and paragraph (h) of this AD. The Accomplishment Instructions of Boeing Alert Service Bulletin 737- 53A1319, Revision 2, dated April 4, 2014, are clear regarding which areas must be inspected. The SUMMARY section of this final rule does specify that the inspection area is increased. However, we have added ``as applicable'' to paragraphs (g) and paragraph (h) of this AD to provide clarification regarding the inspection area. Request To Clarify Compliance Times SWA requested that we revise paragraph (g) of the proposed AD (79 FR 68381, November 17, 2014) to clarify the compliance times. SWA recommended splitting the paragraph requirements into three separate paragraphs to address three different airplane groups. SWA stated that table 1 of paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin 737-53A1319, Revision 2, dated April 4, 2014, does not account for airplanes that were inspected previously using either Boeing Alert Service Bulletin 737-53A1319, dated April 4, 2011, or Boeing Alert Service Bulletin 737-53A1319, Revision 1, dated April 8, 2011. SWA stated that it is unclear how to apply the compliance times in table 1 for these airplanes, and as a result, airplanes with more than 30,000 total flight cycles that were not inspected previously using Boeing Alert Service Bulletin 737-53A1319, Revision 2, dated April 4, 2014, will have exceeded the compliance times in table 1 upon the effective date of the AD. SWA stated that since paragraph (n) of the proposed AD (79 FR 68381, November 17, 2014) provides credit for actions required by paragraph (g) of the proposed AD that were performed prior to the effective date of the AD using either Boeing Alert Service Bulletin 737-53A1319, dated April 4, 2011, or Boeing Alert Service Bulletin 737- 53A1319, Revision 1, dated April 8, 2011, SWA assumes that the intent of paragraph (g) of the proposed AD is for the operator to accomplish the first inspection in accordance with Boeing Alert Service Bulletin 737-53A1319, Revision 2, dated April 4, 2014, within 500 cycles from the last inspection accomplished previously in accordance with either the Boeing Alert Service Bulletin, dated April 4, 2011, or Revision 1, dated April 8, 2011. We do not agree with the commenter's request to revise paragraph (g) of this AD. However, we do agree to clarify the compliance times. For airplanes that were inspected previously using either Boeing Alert Service Bulletin 737-53A1319, dated April 4, 2011, or Boeing Alert Service Bulletin 737-53A1319, Revision 1, dated April 8, 2011, the next inspection must be done within 500 cycles from the last inspection accomplished previously in accordance with either the Boeing Alert Service Bulletin, dated April 4, 2011, or Revision 1, dated April 8, 2011, except as provided by table 2 of paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin 737-53A1319, Revision 2, dated April 4, 2014. Table 2 of paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin 737-53A1319, Revision 2, dated April 4, 2014, provides optional inspections that may be used after inspections in table 1 of paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin 737- 53A1319, Revision 2, dated April 4, 2014, have been accomplished. For airplanes that were not inspected previously using either Boeing Alert Service Bulletin 737-53A1319, dated April 4, 2011, or Boeing Alert Service Bulletin 737-53A1319, Revision 1, dated April 8, 2011, the initial inspection must be done within the applicable compliance times specified in table 1 of paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin 737-53A1319, Revision 2, dated April 4, 2014. We have not changed this AD in this regard. Request To Clarify Inspection Requirements SWA requested that we provide clarification regarding the applicability of table 2 of paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin 737-53A1319, Revision 2, dated April 4, 2014, for accomplishing the repetitive inspections required by paragraph (g) of the proposed AD (79 FR 68381, November 17, 2014). SWA stated that the inspection intervals defined in table 2 are dependent on the total flight cycles of airplanes that meet condition 1 (no crack found), and that operators of airplanes that meet condition 2 (any crack found) should contact Boeing for repair instructions prior to further flight. SWA stated that the alternative repetitive inspection intervals apply only to aircraft that meet condition 1 each time the aircraft is inspected. SWA explained that it is unclear whether or not the operator is able to continue utilizing the table 2 inspection intervals if condition 2 is found during any repetitive inspection on an airplane, or if the operator must revert back to the table 1 repetitive inspection interval from that point forward for that airplane. We agree that clarification is necessary. Paragraph (l) of this AD requires a repair if any crack is found. Accomplishment of the repair terminates the repetitive inspections required by paragraphs (g) and (j) of this AD in the repaired area only. Repetitive inspections must be done on all unrepaired areas at the times specified in table 1 or table 2, as applicable. We find that no change to this AD is necessary regarding this issue. Requests for Credit and Exception to Inspection Requirements SWA requested that we include a provision in paragraph (n) of the proposed AD (79 FR 68381, November 17, 2014) to provide credit for the general visual inspection required by paragraph (k) of the proposed AD for skin panels that were replaced using the procedures specified in Figure 35 of Boeing Service Bulletin 737-53-1306, provided that the corrective action for Condition 9 is followed. SWA also requested that we add an exception in paragraph (m) of the proposed AD (79 FR 68381, November 17, 2014) that allows the operator to omit the inspection required by paragraph (k) of the proposed AD if the corrective action for Condition 9 is followed and the operator's records show the part number of the skin assembly installed on the airplane. To justify its requests, SWA stated that its airplanes, defined as Group 1 in Boeing Alert Service Bulletin 737-53A1319, Revision 2, dated April 4, 2014, on which the crown skin panel replacement was accomplished as described previously in Figure 35 of Boeing Service Bulletin 737-53-1306, were inspected previously to determine if the existing skin assembly was an ``MPN 65C35798-1 (open pockets [[Page 51452]] adjacent to the STR 4R lap joint)'' or an ``MPN 65C35798-8 (closed pockets adjacent to the STR 4R lap joint).'' SWA stated that the existing skin panel was then replaced with a new skin panel of the same configuration as the removed production panel. SWA explained that if an operator's records show the part number of the skin panel assembly installed, the operator will be able to determine if the panel is configured with Condition 9 or Condition 10 and, therefore, SWA does not need to do the inspection required by paragraph (k) of the proposed AD. We disagree with the commenter's requests. The fuselage crown skin replacements described in Boeing Service Bulletin 737-53-1306 are a part of a SWA-specific modification program. We do not consider it appropriate to include various provisions in an AD that are applicable only to a single operator's unique use of an affected airplane. However, an operator may request approval of an alternative method of compliance under the provisions of paragraph (o) of this AD if sufficient data are submitted to substantiate that the fuselage crown skin replacements would provide an acceptable level of safety. We have not changed this AD in this regard. 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 (79 FR 68381, November 17, 2014) for correcting the unsafe condition; and Do not add any additional burden upon the public than was already proposed in the NPRM (79 FR 68381, November 17, 2014). We also determined that these changes will not increase the economic burden on any operator or increase the scope of this AD. Interim Action We consider this AD interim action. An investigation is ongoing, and no terminating action has been developed. Once terminating action is developed, approved, and available, we might consider additional rulemaking. Related Service Information Under 1 CFR Part 51 We reviewed Boeing Alert Service Bulletin 737-53A1319, Revision 2, dated April 4, 2014. The service information describes procedures for inspections for crack indications at certain stringers, an inspection for open pockets of the lower skin panel at stringer S-4R, and repairs. 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 of this AD. Costs of Compliance We estimate that this AD affects 130 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 ---------------------------------------------------------------------------------------------------------------- Repetitive inspections 6 or 4,270 None.............. $510 or $362,950 $66,300 or [actions retained from AD work[dash]hours per inspection $47,183,500 per 2011-08-51, Amendment 39- (depending on cycle. inspection 16701 (76 FR 28632, May 18, inspection method) x cycle. 2011)]. $85 per work-hour = $510 or $362,950 per inspection cycle. Repetitive inspections [new 4 or 550 None.............. $340 or $46,750 $44,200 or action]. work[dash]hours per inspection $6,077,500 per (depending on cycle. inspection inspection method) x cycle. $85 per hour = $340 or $46,750 per inspection cycle. One-time inspections [new 5,370 work[dash]hours None.............. $456,450......... $59,338,500. action]. x $85 per hour = $456,450. ---------------------------------------------------------------------------------------------------------------- We have received no definitive data that would enable us to provide a cost estimate 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, ``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 have determined that this AD will not have federalism implications under Executive Order 13132. This AD will not have a substantial direct effect on the States, on the relationship between the national government and the States, or on the distribution of power and responsibilities among the various levels of government. For the reasons discussed above, I certify that this AD: (1) Is not a ``significant regulatory action'' under Executive Order 12866, (2) Is not a ``significant rule'' under DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979), (3) Will not affect intrastate aviation in Alaska, and (4) Will not have a significant economic impact, positive or negative, on a substantial number of small entities under the criteria of the Regulatory Flexibility Act. List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. Adoption of the Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA amends 14 CFR part 39 as follows: PART 39--AIRWORTHINESS DIRECTIVES 0 1. The authority citation for part 39 continues to read as follows: [[Page 51453]] Authority: 49 U.S.C. 106(g), 40113, 44701. Sec. 39.13 [Amended] 0 2. The FAA amends Sec. 39.13 by removing Airworthiness Directive (AD) 2011-08-51, Amendment 39-16701 (76 FR 28632, May 18, 2011), and adding the following new AD: 2015-16-08 The Boeing Company: Amendment 39-18233; Docket No. FAA- 2014-0772; Directorate Identifier 2014-NM-090-AD. (a) Effective Date This AD is effective September 29, 2015. (b) Affected ADs This AD replaces AD 2011-08-51, Amendment 39-16701 (76 FR 28632, May 18, 2011). (c) Applicability This AD applies to The Boeing Company Model 737-300, -400, and - 500 series airplanes, certificated in any category, as identified in Boeing Alert Service Bulletin 737-53A1319, Revision 2, dated April 4, 2014. (d) Subject Air Transport Association (ATA) of America Code 53: Fuselage. (e) Unsafe Condition This AD was prompted by an evaluation by the design approval holder (DAH) that has determined that the lower fastener holes in the lower skin of the fuselage lap splice are subject to widespread fatigue damage (WFD). We are issuing this AD to detect and correct fatigue cracking of the lower fastener holes in the lower skin of the fuselage lap splice, which could result in reduced structural integrity of the airplane. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Repetitive Inspections for Crack Indications at Stringers S-4R and S-4L, Body Station (BS) 360 to BS 908 At the applicable time specified in table 1 of paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin 737-53A1319, Revision 2, dated April 4, 2014: Do an external eddy current inspection, or internal eddy current and detailed inspections, for crack indications at stringers S-4R and S-4L, from BS 360 to BS 908, as applicable, except as provided by paragraph (h) of this AD, in accordance with Part 1 of the Accomplishment Instructions of Boeing Alert Service Bulletin 737-53A1319, Revision 2, dated April 4, 2014. Repeat the inspection(s) thereafter at the applicable intervals specified in table 1 or table 2, as applicable, of paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin 737-53A1319, Revision 2, dated April 4, 2014. Either inspection option may be used at any repetitive inspection cycle. (h) One-Time Inspections for Cracks at Stringers S-4L and S-4R, BS 360 to BS 908 At the applicable time specified in table 3 of paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin 737-53A1319, Revision 2, dated April 4, 2014, except as required by paragraph (m) of this AD: Do one-time internal detailed and eddy current inspections for cracks at stringers S-4R and S-4L, from BS 360 to BS 908, as applicable, in accordance with Part 2 of the Accomplishment Instructions of Boeing Alert Service Bulletin 737-53A1319, Revision 2, dated April 4, 2014. Accomplishment of the inspections required by this paragraph does not terminate the repetitive inspections required by paragraph (g) of this AD. (i) One-Time Inspections for Cracks at Stringer S-4R, BS 908 to BS 1016 For airplanes identified as Group 2, 3, 5, and 7 in Boeing Alert Service Bulletin 737-53A1319, Revision 2, dated April 4, 2014: At the applicable time specified in table 4 of paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin 737-53A1319, Revision 2, dated April 4, 2014, except as required by paragraph (m) of this AD, do one-time internal detailed and eddy current inspections for cracks at stringer S-4R, from BS 908 to BS 1016, in accordance with Part 3 of the Accomplishment Instructions of Boeing Alert Service Bulletin 737-53A1319, Revision 2, dated April 4, 2014. (j) Repetitive Inspections for Cracks at Stringer S-4R, BS 908 to BS 1016 For airplanes identified as Group 2, 3, 5, and 7 in Boeing Alert Service Bulletin 737-53A1319, Revision 2, dated April 4, 2014: At the applicable time specified in table 5 of paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin 737-53A1319, Revision 2, dated April 4, 2014, except as required by paragraph (m) of this AD, do external eddy current inspections, or internal eddy current and detailed inspections, for cracks at stringer S-4R, from BS 908 to BS 1016, in accordance with Part 4 of the Accomplishment Instructions of Boeing Alert Service Bulletin 737-53A1319, Revision 2, dated April 4, 2014. Repeat the inspection(s) thereafter at the applicable intervals specified in table 5 of paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin 737-53A1319, Revision 2, dated April 4, 2014. Either inspection option may be used at any repetitive inspection cycle. (k) General Visual Inspection for Open Pockets at Stringer S-4R, BS 908 to BS 1016 For airplanes identified as Group 1, 4, and 6 in Boeing Alert Service Bulletin 737-53A1319, Revision 2, dated April 4, 2014: At the applicable time specified in table 6 of paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin 737-53A1319, Revision 2, dated April 4, 2014, except as required by paragraph (m) of this AD, do a general visual inspection for open pockets of the lower skin panel at stringer S-4R, from BS 908 to BS 1016, in accordance with Part 5 of the Accomplishment Instructions of Boeing Alert Service Bulletin 737-53A1319, Revision 2, dated April 4, 2014. If any open pocket is found, before further flight, inspect or repair using a method approved in accordance with the procedures specified in paragraph (o) of this AD. (l) Corrective Action If any crack is found during any inspection required by this AD: Before further flight, repair using a method approved in accordance with the procedures specified in paragraph (o) of this AD. Accomplishment of repairs approved in accordance with the procedures specified in paragraph (o) of this AD terminates the repetitive inspections specified in paragraphs (g) and (j) of this AD in the repaired areas only. (m) Service Information Exception Where Boeing Alert Service Bulletin 737-53A1319, Revision 2, dated April 4, 2014, specifies a compliance time ``after the Revision 2 date of this service bulletin,'' this AD requires compliance within the specified compliance time after the effective date of this AD. (n) Credit for Previous Actions This paragraph provides credit for actions required by paragraph (g) of this AD, if those actions were performed before the effective date of this AD using Boeing Alert Service Bulletin 737-53A1319, dated April 4, 2011; or Boeing Alert Service Bulletin 737-53A1319, Revision 1, dated April 8, 2011. Boeing Alert Service Bulletin 737- 53A1319, dated April 4, 2011, was incorporated by reference in AD 2011-08-51, Amendment 39-16701 (76 FR 28632, May 18, 2011). Boeing Alert Service Bulletin 737-53A1319, Revision 1, dated April 8, is not incorporated by reference in this AD. (o) 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 (p)(1) of this AD. (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 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. For a repair method to be approved, the repair must meet the certification basis of the airplane, and the approval must specifically refer to this AD. (4) AMOCs approved for AD 2011-08-51, Amendment 39-16701 (76 FR 28632, May 18, 2011), are approved as AMOCs for the corresponding provisions of paragraphs (g) and (l) of this AD. [[Page 51454]] (p) Related Information (1) For more information about this AD, contact Jennifer Tsakoumakis, Aerospace Engineer, Airframe Branch, ANM-120L, FAA, Los Angeles Aircraft Certification Office (ACO), 3960 Paramount Boulevard, Lakewood, CA 90712-4137; phone: 562-627-5264; 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 (q)(4) and (q)(5) of this AD. (q) Material Incorporated by Reference (1) The Director of the Federal Register approved the incorporation by reference (IBR) of the service information listed in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51. (2) You must use this service information as applicable to do the actions required by this AD, unless the AD specifies otherwise. (3) The following service information was approved for IBR on September 29, 2015. (i) Boeing Alert Service Bulletin 737-53A1319, Revision 2, dated April 4, 2014. (ii) Reserved. (4) For Boeing 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. (5) 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. (6) You may view this service information that is incorporated by reference at the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, call 202-741-6030, or go to: http://www.archives.gov/federal-register/cfr/ibr-locations.html. Issued in Renton, Washington, on August 7, 2015. Jeffrey E. Duven, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2015-20372 Filed 8-24-15; 8:45 am] BILLING CODE 4910-13-P
![51450 Federal Register / Vol. 80, No. 164 / Tuesday, August 25, 2015 / Rules and Regulations
1601 Lind Avenue SW., Renton, WA. For Commercial Airplanes, Attention: Data inspections for cracks and open pockets,
information on the availability of this & Services Management, P.O. Box 3707, require corrective actions if necessary,
material at the FAA, call 425–227–1221. MC 2H–65, Seattle, WA 98124–2207; and revise the compliance times. We are
(5) You may view this service information telephone 206–544–5000, extension 1;
that is incorporated by reference at the
issuing this AD to detect and correct
National Archives and Records
fax 206–766–5680; Internet https:// fatigue cracking of the lower fastener
Administration (NARA). For information on www.myboeingfleet.com. You may view holes in the lower skin of the fuselage
the availability of this material at NARA, call this referenced service information at lap splice, which could result in
202–741–6030, or go to: http:// the FAA, Transport Airplane reduced structural integrity of the
www.archives.gov/federal-register/cfr/ibr- Directorate, 1601 Lind Avenue SW., airplane.
locations.html. Renton, WA. For information on the
availability of this material at the FAA, Comments
Issued in Renton, Washington, on August
10, 2015. call 425–227–1221. It is also available
We gave the public the opportunity to
Michael Kaszycki, on the Internet at http://
participate in developing this AD. The
Acting Manager, Transport Airplane www.regulations.gov by searching for
following presents the comments
Directorate, Aircraft Certification Service. and locating Docket No. FAA 2014–
received on the NPRM (79 FR 68381,
[FR Doc. 2015–20585 Filed 8–24–15; 8:45 am] 0772.
November 17, 2014) and the FAA’s
BILLING CODE 4910–13–P Examining the AD Docket response to each comment.
You may examine the AD docket on Request To Revise Wording
DEPARTMENT OF TRANSPORTATION the Internet at http://
www.regulations.gov by searching for Boeing requested that we revise the
Federal Aviation Administration and locating Docket No. FAA–2014– last sentence in paragraph (k) of the
0772; or in person at the Docket proposed AD (79 FR 68381, November
14 CFR Part 39 Management Facility between 9 a.m. 17, 2014) to clarify that the on-condition
and 5 p.m., Monday through Friday, actions may be ‘‘inspection or repair’’
[Docket No. FAA–2014–0772; Directorate except Federal holidays. The AD docket rather than ‘‘inspection and repair.’’
Identifier 2014–NM–090–AD; Amendment
39–18233; AD 2015–16–08]
contains this AD, the regulatory Boeing stated that condition 10 in table
evaluation, any comments received, and 6 of Boeing Alert Service Bulletin 737–
RIN 2120–AA64 other information. The address for the 53A1319, Revision 2, dated April 4,
Docket Office (phone: 800–647–5527) is 2014, describes obtaining inspection or
Airworthiness Directives; The Boeing Docket Management Facility, U.S. repair instructions. Boeing explained
Company Airplanes Department of Transportation, Docket that, depending on the configuration
AGENCY: Federal Aviation Operations, M–30, West Building details identified, repetitive inspections
Administration (FAA), DOT. Ground Floor, Room W12–140, 1200 alone may be an appropriate action, or
ACTION: Final rule.
New Jersey Avenue SE., Washington, a repair may be the appropriate action.
DC 20590.
We agree with the commenter’s
SUMMARY: We are superseding FOR FURTHER INFORMATION CONTACT: request. Varying detail configurations
Airworthiness Directive (AD) 2011–08– Jennifer Tsakoumakis, Aerospace and the total flight cycles at the time of
51 for certain The Boeing Company Engineer, Airframe Branch, ANM–120L, the finding are used to determine if an
Model 737–300, –400, and –500 series FAA, Los Angeles Aircraft Certification inspection program is adequate to
airplanes. AD 2011–08–51 required Office (ACO), 3960 Paramount address the unsafe condition or if
repetitive inspections of the lap joint at Boulevard, Lakewood, CA 90712–4137; installation of a repair is required. We
certain stringers along the entire length phone: 562–627–5264; fax: 562–627– have revised the wording in paragraph
from certain body stations. This new AD 5210; email: jennifer.tsakoumakis@ (k) of this AD to require inspection or
expands the inspection area, requires faa.gov. repair.
additional inspections for cracks and SUPPLEMENTARY INFORMATION:
open pockets, requires corrective Request To Clarify Paragraph Heading
actions if necessary, and revises the Discussion
compliance times. This AD was Southwest Airlines (SWA) stated that
We issued a notice of proposed
prompted by an evaluation by the the heading ‘‘Repetitive Inspections for
rulemaking (NPRM) to amend 14 CFR
design approval holder (DAH) that has Crack Indications at Stringers S–4R and
part 39 to supersede AD 2011–08–51,
determined that the lower fastener holes S–4L, Body Station (BS) 360 to BS 908,’’
Amendment 39–16701 (76 FR 28632,
in the lower skin of the fuselage lap of paragraph (g) of the proposed AD (79
May 18, 2011). AD 2011–08–51 applied
splice are subject to widespread fatigue FR 68381, November 17, 2014) is
to certain The Boeing Company Model
damage (WFD). We are issuing this AD 737–300, –400, and –500 series misleading. SWA explained that the
to detect and correct fatigue cracking of airplanes. The NPRM published in the heading is confusing since the
the lower fastener holes in the lower Federal Register on November 17, 2014 paragraph contains both an initial
skin of the fuselage lap splice, which (79 FR 68381). The NPRM was inspection and repetitive inspections.
could result in reduced structural prompted by an evaluation by the DAH We agree to clarify the terminology
integrity of the airplane. that has determined that the lower used in the heading. When the term
DATES: This AD is effective September fastener holes in the lower skin of the ‘‘repetitive’’ is used, it does not
29, 2015. fuselage lap splice are subject to WFD. necessarily exclude the initial action.
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The Director of the Federal Register The NPRM proposed to continue to Many existing ADs use the term
approved the incorporation by reference require repetitive inspections of the lap ‘‘repetitive’’ in the headers for
of a certain publication listed in this AD joint at certain stringers along the entire paragraphs that contain both the initial
as of September 29, 2015. length from certain body stations. The action and repetitive actions. We find
ADDRESSES: For service information NPRM also proposed to expand the that no change to this AD is necessary
identified in this AD, contact Boeing inspection area, require additional regarding this issue.
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![51452 Federal Register / Vol. 80, No. 164 / Tuesday, August 25, 2015 / Rules and Regulations
adjacent to the STR 4R lap joint)’’ or an substantiate that the fuselage crown skin terminating action has been developed.
‘‘MPN 65C35798–8 (closed pockets replacements would provide an Once terminating action is developed,
adjacent to the STR 4R lap joint).’’ SWA acceptable level of safety. We have not approved, and available, we might
stated that the existing skin panel was changed this AD in this regard. consider additional rulemaking.
then replaced with a new skin panel of
Conclusion Related Service Information Under 1
the same configuration as the removed
production panel. SWA explained that We reviewed the relevant data, CFR Part 51
if an operator’s records show the part considered the comments received, and
determined that air safety and the We reviewed Boeing Alert Service
number of the skin panel assembly
installed, the operator will be able to public interest require adopting this AD Bulletin 737–53A1319, Revision 2,
determine if the panel is configured with the changes described previously dated April 4, 2014. The service
with Condition 9 or Condition 10 and, and minor editorial changes. We have information describes procedures for
therefore, SWA does not need to do the determined that these minor changes: inspections for crack indications at
inspection required by paragraph (k) of • Are consistent with the intent that certain stringers, an inspection for open
the proposed AD. was proposed in the NPRM (79 FR pockets of the lower skin panel at
We disagree with the commenter’s 68381, November 17, 2014) for stringer S–4R, and repairs. This service
requests. The fuselage crown skin correcting the unsafe condition; and information is reasonably available
replacements described in Boeing • Do not add any additional burden because the interested parties have
Service Bulletin 737–53–1306 are a part upon the public than was already access to it through their normal course
of a SWA-specific modification proposed in the NPRM (79 FR 68381, of business or by the means identified
program. We do not consider it November 17, 2014). in the ADDRESSES section of this AD.
appropriate to include various We also determined that these
provisions in an AD that are applicable changes will not increase the economic Costs of Compliance
only to a single operator’s unique use of burden on any operator or increase the We estimate that this AD affects 130
an affected airplane. However, an scope of this AD.
operator may request approval of an airplanes of U.S. registry.
alternative method of compliance under Interim Action We estimate the following costs to
the provisions of paragraph (o) of this We consider this AD interim action. comply with this AD:
AD if sufficient data are submitted to An investigation is ongoing, and no
ESTIMATED COSTS
Cost on U.S.
Action Labor cost Parts cost Cost per product operators
Repetitive inspections [actions retained 6 or 4,270 work-hours (depending on in- None ........... $510 or $362,950 $66,300 or
from AD 2011–08–51, Amendment spection method) × $85 per work-hour per inspection $47,183,500 per
39–16701 (76 FR 28632, May 18, = $510 or $362,950 per inspection cycle. inspection cycle.
2011)]. cycle.
Repetitive inspections [new action] ........ 4 or 550 work-hours (depending on in- None ........... $340 or $46,750 per $44,200 or
spection method) × $85 per hour = inspection cycle. $6,077,500 per
$340 or $46,750 per inspection cycle. inspection cycle.
One-time inspections [new action] .......... 5,370 work-hours × $85 per hour = None ........... $456,450 ................ $59,338,500.
$456,450.
We have received no definitive data is within the scope of that authority (3) Will not affect intrastate aviation
that would enable us to provide a cost because it addresses an unsafe condition in Alaska, and
estimate for the on-condition actions that is likely to exist or develop on (4) Will not have a significant
specified in this AD. products identified in this rulemaking economic impact, positive or negative,
action. on a substantial number of small entities
Authority for This Rulemaking
Regulatory Findings under the criteria of the Regulatory
Title 49 of the United States Code Flexibility Act.
specifies the FAA’s authority to issue We have determined that this AD will
rules on aviation safety. Subtitle I, List of Subjects in 14 CFR Part 39
not have federalism implications under
Section 106, describes the authority of Executive Order 13132. This AD will Air transportation, Aircraft, Aviation
the FAA Administrator. Subtitle VII, not have a substantial direct effect on safety, Incorporation by reference,
Aviation Programs, describes in more the States, on the relationship between Safety.
detail the scope of the Agency’s the national government and the States,
authority. Adoption of the Amendment
or on the distribution of power and
We are issuing this rulemaking under responsibilities among the various Accordingly, under the authority
the authority described in Subtitle VII, levels of government. delegated to me by the Administrator,
Part A, Subpart III, Section 44701, the FAA amends 14 CFR part 39 as
‘‘General requirements.’’ Under that For the reasons discussed above, I
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certify that this AD: follows:
section, Congress charges the FAA with
promoting safe flight of civil aircraft in (1) Is not a ‘‘significant regulatory PART 39—AIRWORTHINESS
air commerce by prescribing regulations action’’ under Executive Order 12866, DIRECTIVES
for practices, methods, and procedures (2) Is not a ‘‘significant rule’’ under
the Administrator finds necessary for DOT Regulatory Policies and Procedures ■ 1. The authority citation for part 39
safety in air commerce. This regulation (44 FR 11034, February 26, 1979), continues to read as follows:
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![Federal Register / Vol. 80, No. 164 / Tuesday, August 25, 2015 / Rules and Regulations 51453
Authority: 49 U.S.C. 106(g), 40113, 44701. (h) One-Time Inspections for Cracks at or repair using a method approved in
Stringers S–4L and S–4R, BS 360 to BS 908 accordance with the procedures specified in
§ 39.13 [Amended] paragraph (o) of this AD.
At the applicable time specified in table 3
■ 2. The FAA amends § 39.13 by of paragraph 1.E., ‘‘Compliance,’’ of Boeing (l) Corrective Action
Alert Service Bulletin 737–53A1319,
removing Airworthiness Directive (AD) Revision 2, dated April 4, 2014, except as If any crack is found during any inspection
2011–08–51, Amendment 39–16701 (76 required by paragraph (m) of this AD: Do required by this AD: Before further flight,
FR 28632, May 18, 2011), and adding one-time internal detailed and eddy current repair using a method approved in
the following new AD: inspections for cracks at stringers S–4R and accordance with the procedures specified in
S–4L, from BS 360 to BS 908, as applicable, paragraph (o) of this AD. Accomplishment of
2015–16–08 The Boeing Company:
in accordance with Part 2 of the repairs approved in accordance with the
Amendment 39–18233; Docket No.
Accomplishment Instructions of Boeing Alert procedures specified in paragraph (o) of this
FAA–2014–0772; Directorate Identifier
Service Bulletin 737–53A1319, Revision 2, AD terminates the repetitive inspections
2014–NM–090–AD. dated April 4, 2014. Accomplishment of the specified in paragraphs (g) and (j) of this AD
(a) Effective Date inspections required by this paragraph does in the repaired areas only.
not terminate the repetitive inspections
This AD is effective September 29, 2015. required by paragraph (g) of this AD. (m) Service Information Exception
(b) Affected ADs (i) One-Time Inspections for Cracks at Where Boeing Alert Service Bulletin 737–
This AD replaces AD 2011–08–51, Stringer S–4R, BS 908 to BS 1016 53A1319, Revision 2, dated April 4, 2014,
Amendment 39–16701 (76 FR 28632, May 18, specifies a compliance time ‘‘after the
For airplanes identified as Group 2, 3, 5, Revision 2 date of this service bulletin,’’ this
2011). and 7 in Boeing Alert Service Bulletin 737– AD requires compliance within the specified
(c) Applicability 53A1319, Revision 2, dated April 4, 2014: At compliance time after the effective date of
the applicable time specified in table 4 of
This AD applies to The Boeing Company this AD.
paragraph 1.E., ‘‘Compliance,’’ of Boeing
Model 737–300, –400, and –500 series Alert Service Bulletin 737–53A1319, (n) Credit for Previous Actions
airplanes, certificated in any category, as Revision 2, dated April 4, 2014, except as
identified in Boeing Alert Service Bulletin This paragraph provides credit for actions
required by paragraph (m) of this AD, do one-
737–53A1319, Revision 2, dated April 4, required by paragraph (g) of this AD, if those
time internal detailed and eddy current
2014. actions were performed before the effective
inspections for cracks at stringer S–4R, from
date of this AD using Boeing Alert Service
BS 908 to BS 1016, in accordance with Part
(d) Subject Bulletin 737–53A1319, dated April 4, 2011;
3 of the Accomplishment Instructions of
Air Transport Association (ATA) of Boeing Alert Service Bulletin 737–53A1319, or Boeing Alert Service Bulletin 737–
America Code 53: Fuselage. Revision 2, dated April 4, 2014. 53A1319, Revision 1, dated April 8, 2011.
Boeing Alert Service Bulletin 737–53A1319,
(e) Unsafe Condition (j) Repetitive Inspections for Cracks at dated April 4, 2011, was incorporated by
This AD was prompted by an evaluation by Stringer S–4R, BS 908 to BS 1016 reference in AD 2011–08–51, Amendment
the design approval holder (DAH) that has For airplanes identified as Group 2, 3, 5, 39–16701 (76 FR 28632, May 18, 2011).
determined that the lower fastener holes in and 7 in Boeing Alert Service Bulletin 737– Boeing Alert Service Bulletin 737–53A1319,
the lower skin of the fuselage lap splice are 53A1319, Revision 2, dated April 4, 2014: At Revision 1, dated April 8, is not incorporated
subject to widespread fatigue damage (WFD). the applicable time specified in table 5 of by reference in this AD.
We are issuing this AD to detect and correct paragraph 1.E., ‘‘Compliance,’’ of Boeing
Alert Service Bulletin 737–53A1319, (o) Alternative Methods of Compliance
fatigue cracking of the lower fastener holes in (AMOCs)
the lower skin of the fuselage lap splice, Revision 2, dated April 4, 2014, except as
which could result in reduced structural required by paragraph (m) of this AD, do (1) The Manager, Los Angeles Aircraft
integrity of the airplane. external eddy current inspections, or internal Certification Office (ACO), FAA, has the
eddy current and detailed inspections, for authority to approve AMOCs for this AD, if
(f) Compliance cracks at stringer S–4R, from BS 908 to BS requested using the procedures found in 14
Comply with this AD within the 1016, in accordance with Part 4 of the CFR 39.19. In accordance with 14 CFR 39.19,
compliance times specified, unless already Accomplishment Instructions of Boeing Alert send your request to your principal inspector
done. Service Bulletin 737–53A1319, Revision 2, or local Flight Standards District Office, as
dated April 4, 2014. Repeat the inspection(s) appropriate. If sending information directly
(g) Repetitive Inspections for Crack thereafter at the applicable intervals specified to the manager of the ACO, send it to the
Indications at Stringers S–4R and S–4L, in table 5 of paragraph 1.E., ‘‘Compliance,’’ attention of the person identified in
Body Station (BS) 360 to BS 908 of Boeing Alert Service Bulletin 737– paragraph (p)(1) of this AD.
At the applicable time specified in table 1 53A1319, Revision 2, dated April 4, 2014. (2) Before using any approved AMOC,
of paragraph 1.E., ‘‘Compliance,’’ of Boeing Either inspection option may be used at any notify your appropriate principal inspector,
Alert Service Bulletin 737–53A1319, repetitive inspection cycle. or lacking a principal inspector, the manager
Revision 2, dated April 4, 2014: Do an (k) General Visual Inspection for Open of the local flight standards district office/
external eddy current inspection, or internal Pockets at Stringer S–4R, BS 908 to BS 1016 certificate holding district office.
eddy current and detailed inspections, for (3) An AMOC that provides an acceptable
For airplanes identified as Group 1, 4, and
crack indications at stringers S–4R and S–4L, 6 in Boeing Alert Service Bulletin 737– level of safety may be used for any repair
from BS 360 to BS 908, as applicable, except 53A1319, Revision 2, dated April 4, 2014: At required by this AD if it is approved by the
as provided by paragraph (h) of this AD, in the applicable time specified in table 6 of Boeing Commercial Airplanes Organization
accordance with Part 1 of the paragraph 1.E., ‘‘Compliance,’’ of Boeing Designation Authorization (ODA) that has
Accomplishment Instructions of Boeing Alert Alert Service Bulletin 737–53A1319, been authorized by the Manager, Los Angeles
Service Bulletin 737–53A1319, Revision 2, Revision 2, dated April 4, 2014, except as ACO, to make those findings. For a repair
dated April 4, 2014. Repeat the inspection(s) required by paragraph (m) of this AD, do a method to be approved, the repair must meet
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thereafter at the applicable intervals specified general visual inspection for open pockets of the certification basis of the airplane, and the
in table 1 or table 2, as applicable, of the lower skin panel at stringer S–4R, from approval must specifically refer to this AD.
paragraph 1.E., ‘‘Compliance,’’ of Boeing BS 908 to BS 1016, in accordance with Part (4) AMOCs approved for AD 2011–08–51,
Alert Service Bulletin 737–53A1319, 5 of the Accomplishment Instructions of Amendment 39–16701 (76 FR 28632, May 18,
Revision 2, dated April 4, 2014. Either Boeing Alert Service Bulletin 737–53A1319, 2011), are approved as AMOCs for the
inspection option may be used at any Revision 2, dated April 4, 2014. If any open corresponding provisions of paragraphs (g)
repetitive inspection cycle. pocket is found, before further flight, inspect and (l) of this AD.
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![51454 Federal Register / Vol. 80, No. 164 / Tuesday, August 25, 2015 / Rules and Regulations
(p) Related Information ACTION: Final rule. SUPPLEMENTARY INFORMATION:
(1) For more information about this AD, Discussion
contact Jennifer Tsakoumakis, Aerospace SUMMARY: We are adopting a new
Engineer, Airframe Branch, ANM–120L, airworthiness directive (AD) for Airbus On March 27, 2015, at 80 FR 16325,
FAA, Los Angeles Aircraft Certification Helicopters Model AS350B, AS350BA, the Federal Register published our
Office (ACO), 3960 Paramount Boulevard, AS350B1, AS350B2, AS350B3, AS350C, notice of proposed rulemaking (NPRM),
Lakewood, CA 90712–4137; phone: 562–627– AS350D, AS350D1, AS355E, AS355F, which proposed to amend 14 CFR part
5264; fax: 562–627–5210; email: AS355F1, AS355F2, AS355N, AS355NP, 39 by adding an AD that would apply
jennifer.tsakoumakis@faa.gov.
EC130B4, and EC130T2 helicopters. to Airbus Helicopters Model AS350B,
(2) Service information identified in this
AD that is not incorporated by reference is This AD requires inspecting the AS350BA, AS350B1, AS350B2,
available at the addresses specified in swashplate assembly rotating star to AS350B3, AS350C, AS350D, AS350D1,
paragraphs (q)(4) and (q)(5) of this AD. determine whether a ferrule was AS355E, AS355F, AS355F1, AS355F2,
installed. If a ferrule exists, this AD AS355N, AS355NP, EC130B4, and
(q) Material Incorporated by Reference
requires inspecting the rotating star for EC130T2 helicopters with a swashplate
(1) The Director of the Federal Register a crack and removing any cracked assembly with rotating star, part number
approved the incorporation by reference rotating star. This AD was prompted by (P/N) 350A371003–04, 350A371003–05,
(IBR) of the service information listed in this
paragraph under 5 U.S.C. 552(a) and 1 CFR
a report that reconditioning the rotating 350A371003–06, 350A371003–07, or
part 51. swashplate per a certain repair 350A371003–08. The NPRM proposed
(2) You must use this service information procedure could result in the rotating to require inspecting the swashplate
as applicable to do the actions required by star cracking. The actions of this AD are assembly rotating star to determine
this AD, unless the AD specifies otherwise. intended to detect a crack in the rotating whether a ferrule was installed. If a
(3) The following service information was star and prevent failure of the rotating ferrule exists, this proposed AD would
approved for IBR on September 29, 2015. star and subsequent loss of control of require inspecting the rotating star for a
(i) Boeing Alert Service Bulletin 737– the helicopter. crack and removing any cracked rotating
53A1319, Revision 2, dated April 4, 2014.
DATES: This AD is effective September star. The proposed requirements were
(ii) Reserved.
(4) For Boeing service information 29, 2015. intended to detect a crack in the rotating
identified in this AD, contact Boeing The Director of the Federal Register star and prevent failure of the rotating
Commercial Airplanes, Attention: Data & approved the incorporation by reference star and subsequent loss of control of
Services Management, P.O. Box 3707, MC of certain documents listed in this AD the helicopter.
2H–65, Seattle, WA 98124–2207; telephone as of September 29, 2015. The NPRM was prompted by AD No.
206–544–5000, extension 1; fax 206–766– 2014–0132R1, dated June 2, 2014,
5680; Internet https:// ADDRESSES: For service information
issued by EASA, which is the Technical
www.myboeingfleet.com. identified in this AD, contact Airbus
Agent for the Member States of the
(5) You may view this referenced service Helicopters, Inc., 2701 N. Forum Drive,
European Union. EASA AD No. 2014–
information at the FAA, Transport Airplane Grand Prairie, TX 75052; telephone
0132R1 corrects an unsafe condition for
Directorate, 1601 Lind Avenue SW., Renton, (972) 641–0000 or (800) 232–0323; fax
WA. For information on the availability of Airbus Helicopters (previously
(972) 641–3775; or at http://
this material at the FAA, call 425–227–1221. Eurocopter France) Model AS 350 B,
www.airbushelicopters.com/techpub.
(6) You may view this service information BA, BB, B1, B2, B3, D, AS 355 E, F, F1,
You may review the referenced service
that is incorporated by reference at the F2, N, NP, EC 130 B4, and T2
information at the FAA, Office of the
National Archives and Records helicopters if equipped with a
Administration (NARA). For information on Regional Counsel, Southwest Region,
swashplate assembly with a rotating
the availability of this material at NARA, call 10101 Hillwood Pkwy., Room 6N–321,
star, P/N 350A371003–04, P/N
202–741–6030, or go to: http:// Fort Worth, Texas 76177.
350A371003–05, P/N 350A371003–06,
www.archives.gov/federal-register/cfr/ibr-
Examining the AD Docket P/N 350A371003–07, or P/N
locations.html.
You may examine the AD docket on 350A371003–08. EASA advises that
Issued in Renton, Washington, on August during a repair of a helicopter, it was
7, 2015. the Internet at http://
www.regulations.gov or in person at the discovered that rotating swashplates
Jeffrey E. Duven, reconditioned in accordance with a
Docket Operations Office between 9
Manager, Transport Airplane Directorate, certain repair procedure could
Aircraft Certification Service. a.m. and 5 p.m., Monday through
Friday, except Federal holidays. The AD experience a high stress level. This
[FR Doc. 2015–20372 Filed 8–24–15; 8:45 am]
docket contains this AD, the European condition, if not corrected, could affect
BILLING CODE 4910–13–P
Aviation Safety Agency (EASA) AD, any the service life of the part. To address
incorporated-by-reference service this unsafe condition, EASA AD No.
information, the economic evaluation, 2014–0132R1 requires repetitive
DEPARTMENT OF TRANSPORTATION inspections and replacement of the
any comments received, and other
information. The street address for the rotating star.
Federal Aviation Administration
Docket Operations Office (phone: 800– Comments
14 CFR Part 39 647–5527) is U.S. Department of We gave the public the opportunity to
Transportation, Docket Operations participate in developing this AD, but
[Docket No. FAA–2015–0673; Directorate Office, M–30, West Building Ground
Identifier 2014–SW–034–AD; Amendment we received no comments on the NPRM
39–18244; AD 2015–17–11]
Floor, Room W12–140, 1200 New Jersey (80 FR 16325, March 27, 2015).
Avenue SE., Washington, DC 20590.
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RIN 2120–AA64 FOR FURTHER INFORMATION CONTACT: FAA’s Determination
Robert Grant, Aviation Safety Engineer, These helicopters have been approved
Airworthiness Directives; Airbus
Safety Management Group, FAA, 10101 by the aviation authority of France and
Helicopters
Hillwood Pkwy., Fort Worth, Texas are approved for operation in the United
AGENCY:Federal Aviation 76177; telephone (817) 222–5110; email: States. Pursuant to our bilateral
Administration (FAA), DOT. robert.grant@faa.gov. agreement with France, EASA, its
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Document Created: 2018-02-23 11:03:08
Document Modified: 2018-02-23 11:03:08
| 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 September 29, 2015. | |
| Contact | Jennifer Tsakoumakis, Aerospace Engineer, Airframe Branch, ANM-120L, FAA, Los Angeles Aircraft Certification Office (ACO), 3960 Paramount Boulevard, Lakewood, CA 90712-4137; phone: 562-627-5264; fax: 562-627-5210; email: [email protected] | |
| FR Citation | 80 FR 51450 | |
| RIN Number | 2120-AA64 | |
| CFR Associated | Air Transportation; Aircraft; Aviation Safety; Incorporation by Reference and Safety |
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