82 FR 44504 - Airworthiness Directives; The Boeing Company Airplanes
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration Federal Register Volume 82, Issue 184 (September 25, 2017)
Federal Aviation Administration
Federal Register Volume 82, Issue 184 (September 25, 2017)
| Page Range | 44504-44509 | |
| FR Document | 2017-20114 |
[Federal Register Volume 82, Number 184 (Monday, September 25, 2017)] [Rules and Regulations] [Pages 44504-44509] From the Federal Register Online [www.thefederalregister.org] [FR Doc No: 2017-20114] ----------------------------------------------------------------------- DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA-2016-9301; Product Identifier 2015-NM-193-AD; Amendment 39-19056; AD 2017-19-26] RIN 2120-AA64 Airworthiness Directives; The Boeing Company Airplanes AGENCY: Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule. ----------------------------------------------------------------------- SUMMARY: We are superseding Airworthiness Directive (AD) 2008-12-04, which applied to certain The Boeing Company Model 737-600, -700, -700C, -800, and -900 series airplanes. AD 2008-12-04 required various repetitive inspections to detect cracks along the chem-milled steps of the fuselage skin, and to detect missing or loose fasteners in the area of a certain preventive modification or repairs; replacement of the time-limited repair with a permanent repair, if applicable; and applicable corrective actions which would end certain repetitive inspections. This AD reduces the post-modification inspection compliance times, limits installation of the preventive modification to airplanes with fewer than 30,000 total flight cycles, and adds repetitive inspections for modified airplanes. This AD was prompted by an evaluation by the design approval holder (DAH) that indicated that the upper skin panel at the chem-milled step above the lap joint is subject to widespread fatigue damage (WFD) if the modification was installed after 30,000 total flight cycles. We are issuing this AD to address the unsafe condition on these products. DATES: This AD is effective October 30, 2017. [[Page 44505]] The Director of the Federal Register approved the incorporation by reference of a certain publication listed in this AD as of October 30, 2017. ADDRESSES: For service information identified in this final rule, contact Boeing Commercial Airplanes, Attention: Contractual & Data Services (C&DS), 2600 Westminster Blvd., MC 110-SK57, Seal Beach, CA 90740; telephone 562-797-1717; Internet https://www.myboeingfleet.com. You may view this referenced service information at the FAA, Transport Standards Branch, 1601 Lind Avenue SW., Renton, WA. For information on the availability of this material at the FAA, call 425-227-1221. It is also available on the internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2016-9301. 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-2016- 9301; 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: Alan Pohl, Aerospace Engineer, Airframe Section, FAA, Seattle ACO Branch, 1601 Lind Avenue SW., Renton, WA 98057-3356; phone: 425-917-6450; fax: 425-917-6590; email: [email protected]. SUPPLEMENTARY INFORMATION: Discussion We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 to supersede AD 2008-12-04, Amendment 39-15547 (73 FR 32991, June 11, 2008) (``AD 2008-12-04''). AD 2008-12-04 applied to certain The Boeing Company Model 737-600, -700, -700C, -800, and -900 series airplanes. The NPRM published in the Federal Register on November 22, 2016 (81 FR 83745) (``the NPRM''). The NPRM was prompted by an evaluation by the DAH that indicated that the upper skin panel at the chem-milled step above the lap joint is subject to WFD if the modification was installed after 30,000 total flight cycles. The NPRM proposed to continue to require various repetitive inspections to detect cracks along the chem-milled steps of the fuselage skin, and to detect missing or loose fasteners in the area of the preventive modification or repairs; replacement of the time-limited repair with a permanent repair, if applicable; and applicable corrective actions which would end certain repetitive inspections. The NPRM also proposed to reduce the post-modification inspection compliance times, limit installation of the preventive modification to airplanes with fewer than 30,000 total flight cycles, and add repetitive inspections for modified airplanes. We are issuing this AD to detect and correct cracking of the upper skin panel at the chem-milled step above the lap joint, 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 and the FAA's response to each comment. Support for the NPRM Boeing and United Airlines supported the NPRM. Effect of Winglets on Accomplishment of the Proposed Actions Aviation Partners Boeing stated that installation of winglets, as provided in Supplemental Type Certificate (STC) ST00830SE, does not affect the ability to accomplish the actions proposed in the NPRM. We agree with the commenter. We have redesignated paragraph (c) of the proposed AD as (c)(1) and added paragraph (c)(2) to this AD to state that installation of STC ST00830SE does not affect the ability to accomplish the actions required by this AD. Therefore, for airplanes on which STC ST00830SE is installed, a ``change in product'' alternative method of compliance (AMOC) approval request is not necessary to comply with the requirements of 14 CFR 39.17. Request To Revise Certain Compliance Time Provisions Southwest Airlines (SWA) asked that we revise certain compliance language in paragraph (p)(4) of the proposed AD, which stipulated that post-repair or post-mod inspections be done at the time specified in the service information or at the time specified in the previously approved AMOC, ``whichever occurs first.'' SWA stated that previously approved AMOCs for post-repair or post-modification supplemental inspections that comply with certain regulations may contain unique damage tolerance inspection programs that demonstrate a level of safety equivalent to that of AD 2008-12-04. SWA added that altering those supplemental inspections to post-repair or post-modification inspections as specified in Boeing Alert Service Bulletin 737-53A1232, Revision 3, dated July 27, 2015, when those are done first, could result in incorrect inspection methods to geometrical structure that does not conform to the repair or modification definitions specified in Revisions 1 and 3 of that service information. We partially agree with the commenter's request. We have determined that repairs and preventive modifications should be handled separately. Fleet experience and subsequent analysis of Model 737-200, -200C, -300, -400, and -500 airplanes, which have similar chem-milled step details, have shown that certain post-preventative modification inspection programs may not adequately address the unsafe condition. Therefore, paragraph (p)(4) of this AD has been changed to remove the language ``preventative modifications'' and remove the reference to the service information and ``whichever occurs first'' from the compliance time specified. In addition, we have added paragraph (p)(5) to this AD to address only the preventive modifications without change to the service information and ``whichever occurs first'' language. Request To Retain Certain Exceptions Additionally, SWA asked that paragraphs (j) and (k) of AD 2008-12- 04 be included in the proposed AD. Paragraph (j) of AD 2008-12-04 provides an allowance for repairs that are FAA-approved and that have a minimum of three rows of fasteners above and below the chem-milled step. SWA stated that paragraph (k) of AD 2008-12-04 provides a means of inspections without an AMOC when an external repair is covering the chem-milled step, but that the doubler does not span the step by a minimum of three rows of fasteners above and below the chem-milled step. SWA added that both paragraphs (j) and (k) of AD 2008-12-04 are missing from the proposed AD and should be added, with certain clarifications, to paragraph (j) of the proposed AD. First, the repair is an external doubler repair. Second, in lieu of the doing the post- repair supplemental inspections in accordance with table 2 of paragraph 1.E., [[Page 44506]] ``Compliance,'' of Boeing Alert Service Bulletin 737-53A1232, Revision 3, dated July 27, 2015, the inspections should be done in accordance with 14 CFR 121.1109(c)(2) or 14 CFR 129.109(b)(2) supplemental inspection requirements, or in accordance with FAA-approved damage tolerance inspection requirements. SWA also stated that if paragraphs (j) and (k) of AD 2008-12-04 are not restated for compliance with existing FAA-approved repairs, operators will be required to seek AMOC approvals for such existing repairs prior to the inspection threshold or repeat interval of table 1 of paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin 737-53A1232, Revision 3, dated July 27, 2015. SWA stated that not including the exceptions in paragraphs (j) and (k) of AD 2008-12-04 could potentially lead to disruption of operations if it is necessary to request AMOC approvals during repair discovery, or could burden operators with records research to identify these repairs for AMOC approvals prior to the required compliance times. We agree that an allowance can be made for repairs that meet the criteria specified in paragraph (j) of AD 2008-12-04. These repairs address the unsafe condition identified in this AD. Therefore, we have added paragraph (l)(3) to this AD to include the provision of paragraph (j) of AD 2008-12-04 for repairs that were accomplished before the effective date of this AD. We disagree that post-repair inspections for these repairs should be done in accordance with 14 CFR 121.1109(c)(2) or 14 CFR 129.109(b)(2) supplemental inspection requirements. Post-repair inspections for repairs that meet the criteria of paragraph (j) of this AD are to be accomplished in accordance with table 2 of paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin 737-53A1232, Revision 3, dated July 27, 2015. This is consistent with the DAH's current recommendation as well as the requirements of paragraph (j) of AD 2008- 12-04. Paragraph (l)(3) of this AD reflects these provisions. We also disagree with the commenter's request to change the word ``repair'' to ``external doubler repair'' in paragraph (l)(3) of this AD because we are retaining the provisions of paragraph (j) of AD 2008- 12-04. We also agree to add certain provisions of paragraph (k) of AD 2008-12-04 to this AD. We have added paragraph (l)(4) to this AD to address certain repairs as defined in paragraph (k) of AD 2008-12-04. However, paragraph (l)(4) of this AD does not include a reference to Boeing Model 737 Non-destructive Test (NDT) Manual, Part 6, Subject 53- 30-20, and instead requires that the inspection be done using FAA- approved procedures. We have also added Note 1 to paragraph (l)(4) of this AD to specify that guidance on the inspection specified in paragraph (l)(4) of this AD can be found in Boeing Model 737 NDT Manual, Part 6, Subject 53-30-20. Clarification of Paragraph (i)(1) of This AD We have revised the language in paragraph (i)(1) of this AD to clarify which modifications are exempt from the actions required by paragraph (i)(1) of this AD. 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 737-53A1232, Revision 3, dated July 27, 2015. This service information describes procedures for an external detailed inspection and an external nondestructive inspection (NDI) for cracks in the fuselage skin at chem-milled steps. Corrective actions include a permanent or time-limited repair, a preventive modification, and replacement of loose and missing fasteners. Related investigative actions include internal and external detailed inspections of the repair area. 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 376 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................. Up to 25 work-hours x $0 Up to $2,125 per Up to $799,000 per $85 per hour = inspection cycle. inspection cycle. $2,125 per inspection cycle. ---------------------------------------------------------------------------------------------------------------- We estimate the following costs to do any necessary repairs and replacements that would be required based on the results of the inspections. We have no way of determining the number of aircraft that might need these replacements: On-Condition Costs ---------------------------------------------------------------------------------------------------------------- Cost per Action Labor cost Parts cost product ---------------------------------------------------------------------------------------------------------------- Fastener replacement.................. Up to 1 work-hour x $85 per Minimal.................. $85 hour = $85. ---------------------------------------------------------------------------------------------------------------- [[Page 44507]] We have received no definitive data that would enable us to provide cost estimates for the related investigative actions, certain repairs, and other applicable 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. This AD is issued in accordance with authority delegated by the Executive Director, Aircraft Certification Service, as authorized by FAA Order 8000.51C. In accordance with that order, issuance of ADs is normally a function of the Compliance and Airworthiness Division, but during this transition period, the Executive Director has delegated the authority to issue ADs applicable to transport category airplanes to the Director of the System Oversight Division. Regulatory Findings We have determined that this AD will not have federalism implications under Executive Order 13132. This AD will not have a substantial direct effect on the States, on the relationship between the national government and the States, or on the distribution of power and responsibilities among the various levels of government. For the reasons discussed above, I certify that this AD: (1) Is not a ``significant regulatory action'' under Executive Order 12866, (2) Is not a ``significant rule'' under DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979), (3) Will not affect intrastate aviation in Alaska, and (4) Will not have a significant economic impact, positive or negative, on a substantial number of small entities under the criteria of the Regulatory Flexibility Act. List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. Adoption of the Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA amends 14 CFR part 39 as follows: PART 39--AIRWORTHINESS DIRECTIVES 0 1. The authority citation for part 39 continues to read as follows: Authority: 49 U.S.C. 106(g), 40113, 44701. Sec. 39.13 [Amended] 0 2. The FAA amends Sec. 39.13 by removing Airworthiness Directive (AD) 2008-12-04, Amendment 39-15547 (73 FR 32991, June 11, 2008), and adding the following new AD: 2017-19-26 The Boeing Company: Amendment 39-19056; Docket No. FAA- 2016-9301; Product Identifier 2015-NM-193-AD. (a) Effective Date This AD is effective October 30, 2017. (b) Affected ADs This AD replaces AD 2008-12-04, Amendment 39-15547 (73 FR 32991, June 11, 2008) (``AD 2008-12-04''). (c) Applicability (1) This AD applies to The Boeing Company Model 737-600, -700, - 700C, -800, and -900 series airplanes, certificated in any category, as identified in Boeing Alert Service Bulletin 737-53A1232, Revision 3, dated July 27, 2015. (2) Installation of Supplemental Type Certificate (STC) ST00830SE [http://rgl.faa.gov/Regulatory_and_Guidance_Library/rgstc.nsf/0/184DE9A71EC3FA5586257EAE00707DA6?OpenDocument&Highlight=st00830se] does not affect the ability to accomplish the actions required by this AD. Therefore, for airplanes on which STC ST00830SE 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 a fatigue test that revealed numerous cracks in the upper skin panel at the chem-milled step above the lap joint, followed by an evaluation by the design approval holder (DAH) that indicated that location is subject to widespread fatigue damage (WFD) on airplanes on which a certain modification was installed after 30,000 total flight cycles. We are issuing this AD to detect and correct cracking of the upper skin panel at the chem-milled step above the lap joint, 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) Inspections at Locations Without the Preventive Modification, Time- Limited Repair, or Permanent Repair Installed At locations where a preventive modification, time-limited repair, or permanent repair has not been installed as specified in Boeing Service Bulletin 737-53A1232: At the applicable time specified in paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin 737-53A1232, Revision 3, dated July 27, 2015, do an external detailed inspection and an inspection specified in either paragraph (g)(1) or (g)(2) of this AD, for any crack in the fuselage skin at the chem-milled steps at specified locations, in accordance with Accomplishment Instructions of Boeing Alert Service Bulletin 737-53A1232, Revision 3, dated July 27, 2015. Do all applicable related investigative and corrective actions before further flight in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 737-53A1232, Revision 3, dated July 27, 2015, except as required by paragraph (l)(1) of this AD, and except as provided in paragraphs (l)(3) and (l)(4) of this AD. Repeat the inspections thereafter at the applicable time specified in paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin 737-53A1232, Revision 3, dated July 27, 2015. (1) Do an external medium frequency eddy current (MFEC), or magneto optic imager (MOI), or C-Scan inspection. (2) Do an external ultrasonic phased array (UTPA) inspection. (h) Repetitive Post-Modification Inspections and Repair at Any Location With the Preventive Modification But No Time-Limited or Permanent Repair At any location with a preventive modification installed as specified in Boeing Service Bulletin 737-53A1232: At the applicable time specified in paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin 737-53A1232, Revision 3, dated July 27, 2015, except as required by paragraph (l)(2) of this AD, do the actions specified in paragraphs (h)(1) and (h)(2) of this AD. (1) Do external detailed and external high frequency and medium frequency eddy current inspections for any crack, in accordance with Part 7 of the Accomplishment Instructions of Boeing Alert Service Bulletin 737-53A1232, Revision 3, dated July 27, 2015. If no crack is found during the inspection, repeat the inspections thereafter at the applicable time specified in paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin 737-53A1232, Revision 3, dated July 27, 2015. If any crack is found during any inspection required by this paragraph, repair before further flight, in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 737- 53A1232, Revision 3, dated July 27, [[Page 44508]] 2015, except as required by paragraph (l)(1) of this AD. (2) Do a detailed inspection for any crack and any loose or missing fasteners, in accordance with Part 7 of the Accomplishment Instructions of Boeing Alert Service Bulletin 737-53A1232, Revision 3, dated July 27, 2015. Repeat the inspections thereafter at applicable time specified in paragraph 1.E, ``Compliance,'' of Boeing Alert Service Bulletin 737-53A1232, Revision 3, dated July 27, 2015. If any crack is found during any inspection, or any loose or missing fastener is found, before further flight, do all applicable corrective actions, in accordance with Part V of the Accomplishment Instructions of Boeing Alert Service Bulletin 737- 53A1232, Revision 3, dated July 27, 2015, except as specified in paragraph (l)(1) of this AD. (i) Additional Actions for Modified Airplanes (1) At any location where a preventive modification as specified in Boeing Service Bulletin 737-53A1232 was installed after the accumulation of 30,000 total flight cycles, at the applicable time specified in paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin 737-53A1232, Revision 3, dated July 27, 2015, except as required by paragraph (l)(2) of this AD, do all applicable investigative and corrective actions using a method approved in accordance with the procedures specified in paragraph (p) of this AD. For preventive modifications installed on airplanes listed in Appendix A of Boeing Alert Service Bulletin 737-53A1232, Revision 3, dated July 27, 2015, at the specified total flight cycles: The actions specified in this paragraph are not required. (2) For airplanes which have installed STC ST01697SE (http:// rgl.faa.gov/Regulatory_and_Guidance_Library/rgstc.nsf/0/ 0812969a86af879b8625766400600105/$FILE/ST01697SE.pdf) and the preventive modification has been installed after 15,000 total flight cycles: Before the accumulation of 25,000 total flight cycles, do all applicable investigative and corrective actions using a method approved in accordance with the procedures specified in paragraph (p) of this AD. (j) Inspections and Repair at Locations With the Permanent Chem-Milled Step Repair Installed At any location where a permanent repair has been installed as specified in Boeing Service Bulletin 737-53A1232: At the applicable time specified in paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin 737-53A1232, Revision 3, dated July 27, 2015, do the inspections specified in paragraph (j)(1) or (j)(2) of this AD, in accordance with Accomplishment Instructions of Boeing Alert Service Bulletin 737-53A1232, Revision 3, dated July 27, 2015. Repeat the inspections thereafter at the applicable time specified in paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin 737-53A1232, Revision 3, dated July 27, 2015. Do all applicable related investigative and corrective actions before further flight in accordance with Boeing Alert Service Bulletin 737-53A1232, Revision 3, dated July 27, 2015, except as required by paragraph (l)(1) of this AD. (1) Do an external low frequency eddy current (LFEC) inspection for any crack, and doubler external LFEC and external detailed inspections for any crack and loose or missing fasteners. (2) Do an external LFEC inspection for any crack, a doubler external LFEC and external detailed inspections for any crack and loose or missing fasteners, and an internal MFEC for any crack. (k) Inspection and Replacement at Locations With a Chem-Milled Time- Limited Repair Installed At any location where a chem-milled time-limited repair is installed, do the actions specified in paragraphs (k)(1) and (k)(2) of this AD, at the applicable time specified in 1.E. ``Compliance,'' of Boeing Alert Service Bulletin 737-53A1232, Revision 3, dated July 27, 2015. (1) Do internal and external detailed inspections of the time- limited repair for any crack, or loose or missing fasteners, in accordance with Part IV of the Accomplishment Instructions of Boeing Alert Service Bulletin 737-53A1232, Revision 3, dated July 27, 2015. Repeat the inspections thereafter at the applicable time specified in paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin 737-53A1232, Revision 3, dated July 27, 2015. If any crack is found during any inspection, or if any loose or missing fastener is found, before further flight, do all applicable corrective actions, in accordance with Part IV of the Accomplishment Instructions of Boeing Alert Service Bulletin 737-53A1232, Revision 3, dated July 27, 2015, except as specified in paragraph (l)(1) of this AD. (2) Replace the time-limited repair with the permanent repair, in accordance with Part IV of the Accomplishment Instructions of Boeing Alert Service Bulletin 737-53A1232, Revision 3, dated July 27, 2015. (l) Exceptions to Service Information Specifications (1) Where Boeing Alert Service Bulletin 737-53A1232, Revision 3, dated July 27, 2015, specifies to contact Boeing for repair instructions, this AD requires repair before further flight using a method approved in accordance with the procedures specified in paragraph (p) of this AD. (2) Where paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin 737-53A1232, Revision 3, dated July 27, 2015, specifies a compliance time ``after the date of Revision 2 of this service bulletin,'' this AD requires compliance within the specified compliance time after the effective date of this AD. (3) For airplanes on which the actions specified in paragraph (g) of this AD are required: Inspections specified in table 1 of paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin 737-53A1232, Revision 3, dated July 27, 2015, are not required in areas that are spanned by an FAA-approved repair that has a minimum of 3 rows of fasteners above and below the chem-milled step, provided that the repair was installed before the effective date of this AD. Operators must accomplish post-repair inspections at the applicable time specified in table 2 of paragraph 1.E, ``Compliance,'' of Boeing Alert Service Bulletin 737-53A1232, Revision 3, dated July 27, 2015. (4) For any airplane that has an external doubler covering the chem-milled step, but the doubler does not span the step by a minimum of 3 rows of fasteners above and below the chem-milled step and the doubler was installed before the effective date of this AD: One method of compliance with the inspection requirement of paragraph (g) of this AD is to inspect all chem-milled steps covered by the repair using non-destructive test (NDT) methods approved in accordance with the procedures specified in paragraph (p) of this AD. These repairs are to be considered time-limited and are subject to the post-repair supplemental inspections and replacement at the times specified in table 3 of paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin 737-53A1232, Revision 3, dated July 27, 2015. Note 1 to paragraph (l)(4) of this AD: Guidance for the procedures for the alternative inspection specified in paragraph (l)(4) of this AD can be found in the Boeing 737 NDT Manual, Part 6, Subject 53-30-20. (m) Optional Terminating Action (1) For airplanes that have accumulated 30,000 total flight cycles or fewer, or for airplanes on which STC ST01697SE was installed and that have accumulated 15,000 total flight cycles or fewer, accomplishment of the preventive modification specified in Part V of Boeing Alert Service Bulletin 737-53A1232, Revision 3, dated July 27, 2015, terminates the inspections required by paragraph (g) of this AD in the modified areas only. (2) Installation of a permanent repair as specified in Part III of Boeing Alert Service Bulletin 737-53A1232, Revision 3, dated July 27, 2015, or a time-limited repair as specified in Part IV of Boeing Alert Service Bulletin 737-53A1232, Revision 3, dated July 27, 2015, terminates the inspections required by paragraph (g) of this AD in the repaired areas only. (n) Installation Limitations of Preventive Modification As of the effective date of this AD, installation of the preventive modification specified in Boeing Service Bulletin 737- 53A1232 is prohibited on the airplanes identified in paragraphs (n)(1) and (n)(2) of this AD. (1) Airplanes that have accumulated more than 30,000 total flight cycles. (2) Airplanes which have installed STC ST01697SE and that have accumulated more than 15,000 total flight cycles. (o) Credit for Previous Actions This paragraph provides credit for the corresponding actions specified in paragraphs (g), (h), (i), (j), (k), and (m) of this AD, if those actions were performed before the effective date of this AD using the service information identified in paragraph (o)(1), (o)(2), or (o)(3) of this AD. (1) Boeing Special Attention Service Bulletin 737-53A1232, dated April 2, 2007. [[Page 44509]] (2) Boeing Special Attention Service Bulletin 737-53A1232, Revision 1, dated May 18, 2012. (3) Boeing Special Attention Service Bulletin 737-53A1232, Revision 2, dated July 26, 2013. (p) Alternative Methods of Compliance (AMOCs) (1) The Manager, Seattle ACO Branch, FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. In accordance with 14 CFR 39.19, send your request to your principal inspector or local Flight Standards District Office, as appropriate. If sending information directly to the manager of the certification office, send it to the attention of the person identified in paragraph (q)(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, Seattle ACO, to make those findings. To be approved, the repair method, modification deviation, or alteration deviation must meet the certification basis of the airplane, and the approval must specifically refer to this AD. (4) AMOCs approved previously for repairs for AD 2008-12-04 are approved as AMOCs for the installation of the repair specified in this AD, provided all post-repair inspections are done at the applicable times specified in the AMOC. (5) AMOCs approved previously for preventive modifications for AD 2008-12-04 are approved as AMOCs for the installation of the preventive modification specified in this AD, provided all post- modification inspections are done at the applicable times specified in the AMOC, or in tables 1a and 1b of paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin 737-53A1232, Revision 3, dated July 27, 2015, whichever occurs first. The AMOC must include all of the inspections specified in Tables 1a and 1b of Boeing Alert Service Bulletin 737-53A1232, Revision 3, dated July 27, 2015. (q) Related Information (1) For more information about this AD, contact Alan Pohl, Aerospace Engineer, Airframe Section, FAA, Seattle ACO Branch, 1601 Lind Avenue SW., Renton, WA 98057-3356; phone: 425-917-6577; fax: 425-917-6450; email: [email protected]. (2) Service information identified in this AD that is not incorporated by reference is available at the addresses specified in paragraphs (r)(3) and (r)(4) of this AD. (r) 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 737-53A1232, Revision 3, dated July 27, 2015. (ii) Reserved. (3) For service information identified in this AD, contact Boeing Commercial Airplanes, Attention: Contractual & Data Services (C&DS), 2600 Westminster Blvd., MC 110-SK57, Seal Beach, CA 90740; telephone 562-797-1717; Internet https://www.myboeingfleet.com. (4) You may view this service information at the FAA, Transport Standards Branch, 1601 Lind Avenue SW., Renton, WA. For information on the availability of this material at the FAA, call 425-227-1221. (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 14, 2017. Jeffrey E. Duven, Director, System Oversight Division, Aircraft Certification Service. [FR Doc. 2017-20114 Filed 9-22-17; 8:45 am] BILLING CODE 4910-13-P
![44504 Federal Register / Vol. 82, No. 184 / Monday, September 25, 2017 / Rules and Regulations
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structure, the main spar joint, and the engine Agency (EASA), or BAE Systems the availability of this material at NARA, call
support attachment bolts, which could lead (Operations) Limited’s EASA DOA. If 202–741–6030, or go to: http://
to reduced structural integrity with approved by the DOA, the approval must www.archives.gov/federal-register/cfr/ibr-
consequent loss of control. include the DOA-authorized signature. locations.html.
(3) Reporting Requirements: For any
(f) Actions and Compliance Issued in Kansas City, Missouri, on
reporting requirement in this AD, a federal
Comply with paragraphs (f)(1) through (3) September 14, 2017.
agency may not conduct or sponsor, and a
of this AD within the compliance times person is not required to respond to, nor Pat Mullen,
specified, unless already done: shall a person be subject to a penalty for Acting Deputy Director, Policy & Innovation
(1) Before further flight after October 30, failure to comply with a collection of Division, Aircraft Certification Service.
2017 (the effective date of this AD), information subject to the requirements of [FR Doc. 2017–20047 Filed 9–22–17; 8:45 am]
incorporate BAE Systems (Operations) the Paperwork Reduction Act unless that BILLING CODE 4910–13–P
Limited Jetstream Series 3100 & 3200 collection of information displays a current
Corrosion Prevention and Control valid OMB Control Number. The OMB
Programme, Manual Ref. JS/CPCP/01, Control Number for this information
Revision 8, dated October 15, 2016, into the DEPARTMENT OF TRANSPORTATION
collection is 2120–0056. Public reporting for
Limitations of your FAA-approved this collection of information is estimated to
maintenance program (instructions for Federal Aviation Administration
be approximately 5 minutes per response,
continued airworthiness) on the basis of including the time for reviewing instructions,
which the operator or the owner ensures the completing and reviewing the collection of 14 CFR Part 39
continuing airworthiness of each operated information. All responses to this collection
airplane, as applicable to the airplane model. of information are mandatory. Comments [Docket No. FAA–2016–9301; Product
(2) Do all tasks in the BAE Systems concerning the accuracy of this burden and Identifier 2015–NM–193–AD; Amendment
(Operations) Limited Jetstream Series 3100 & suggestions for reducing the burden should 39–19056; AD 2017–19–26]
3200 Corrosion Prevention and Control be directed to the FAA at: 800 Independence
Programme, Manual Ref. JS/CPCP/01, Ave. SW., Washington, DC 20591, Attn: RIN 2120–AA64
Revision 8, dated October 15, 2016, at the Information Collection Clearance Officer,
compliance times specified in the manual, or AES–200. Airworthiness Directives; The Boeing
within the next 12 months after October 30, Company Airplanes
2017 (the effective date of this AD), (h) Related Information
whichever occurs later; except for the Refer to MCAI European Aviation Safety AGENCY: Federal Aviation
following tasks, which must be done within Agency 2017–0073, dated April 27, 2017. Administration (FAA), Department of
12 months after October 30, 2017 (the The MCAI can be found in the AD docket on Transportation (DOT).
effective date of this AD): 52–11–002 C1, the Internet at: https://www.regulations.gov/ ACTION: Final rule.
200/EX/01 C2, 500/IN/02 C1, 600/IN/04 C1, document?D=FAA-2017-0639-0002.
and 700/IN/04 C1. SUMMARY: We are superseding
(3) If any discrepancy, particularly (i) Material Incorporated by Reference
Airworthiness Directive (AD) 2008–12–
corrosion, is found during any inspections or (1) The Director of the Federal Register 04, which applied to certain The Boeing
tasks required by paragraphs (f)(1) or (2) of approved the incorporation by reference
(IBR) of the service information listed in this
Company Model 737–600, –700, –700C,
this AD, within the compliance time
specified, repair or replace, as applicable, all paragraph under 5 U.S.C. 552(a) and 1 CFR –800, and –900 series airplanes. AD
damaged structural parts and components part 51. 2008–12–04 required various repetitive
and do the maintenance procedures for (2) You must use this service information inspections to detect cracks along the
corrective action following BAE Systems as applicable to do the actions required by chem-milled steps of the fuselage skin,
(Operations) Limited Jetstream Series 3100 & this AD, unless the AD specifies otherwise. and to detect missing or loose fasteners
3200 Corrosion Prevention and Control (i) BAE Systems (Operations) Limited in the area of a certain preventive
Programme, Manual Ref. JS/CPCP/01, Jetstream Series 3100 & 3200 Corrosion modification or repairs; replacement of
Revision 8, dated October 15, 2016. If no Prevention and Control Programme, Manual the time-limited repair with a
compliance time is defined, do the applicable Ref. JS/CPCP/01, Revision 8, dated October
15, 2016.
permanent repair, if applicable; and
corrective action before further flight.
(ii) Reserved. applicable corrective actions which
(g) Other FAA AD Provisions (3) For British Aerospace Jetstream Series would end certain repetitive
The following provisions also apply to this 3100 and 3200 service information related to inspections. This AD reduces the post-
AD: this AD, contact BAE Systems (Operations) modification inspection compliance
(1) Alternative Methods of Compliance Limited, Customer Information Department, times, limits installation of the
(AMOCs): The Manager, Small Airplane Prestwick International Airport, Ayrshire, preventive modification to airplanes
Standards Branch, FAA, has the authority to KA9 2RW, Scotland, United Kingdom; with fewer than 30,000 total flight
approve AMOCs for this AD, if requested telephone: +44 1292 675207; fax: +44 1292 cycles, and adds repetitive inspections
using the procedures found in 14 CFR 39.19. 675704; email: RApublications@
Send information to ATTN: Doug Rudolph, baesystems.com; Internet: http://
for modified airplanes. This AD was
Aerospace Engineer, FAA, Small Airplane www.baesystems.com/Businesses/ prompted by an evaluation by the
Standards Branch, 901 Locust, Room 301, RegionalAircraft/. design approval holder (DAH) that
Kansas City, Missouri 64106; telephone: (4) You may review copies of the indicated that the upper skin panel at
asabaliauskas on DSKBBXCHB2PROD with RULES
(816) 329–4059; fax: (816) 329–4090; email: referenced service information at the FAA, the chem-milled step above the lap joint
doug.rudolph@faa.gov. Before using any Policy and Innovation Division, 901 Locust, is subject to widespread fatigue damage
approved AMOC on any airplane to which Kansas City, Missouri 64106. For information (WFD) if the modification was installed
the AMOC applies, notify your appropriate on the availability of this material at the after 30,000 total flight cycles. We are
principal inspector (PI) in the FAA Flight FAA, call (816) 329–4148. In addition, you issuing this AD to address the unsafe
Standards District Office (FSDO), or lacking can access this service information on the
a PI, your local FSDO. Internet at http://www.regulations.gov by
condition on these products.
(2) Contacting the Manufacturer: For any searching for and locating Docket No. FAA– DATES: This AD is effective October 30,
requirement in this AD to obtain corrective 2017–0639. 2017.
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![Federal Register / Vol. 82, No. 184 / Monday, September 25, 2017 / Rules and Regulations 44507
We have received no definitive data List of Subjects in 14 CFR Part 39 upper skin panel at the chem-milled step
that would enable us to provide cost above the lap joint, which could result in
Air transportation, Aircraft, Aviation reduced structural integrity of the airplane.
estimates for the related investigative safety, Incorporation by reference,
actions, certain repairs, and other Safety. (f) Compliance
applicable actions specified in this AD. Comply with this AD within the
Adoption of the Amendment compliance times specified, unless already
Authority for This Rulemaking
Accordingly, under the authority done.
Title 49 of the United States Code delegated to me by the Administrator,
specifies the FAA’s authority to issue (g) Inspections at Locations Without the
the FAA amends 14 CFR part 39 as Preventive Modification, Time-Limited
rules on aviation safety. Subtitle I, follows: Repair, or Permanent Repair Installed
Section 106, describes the authority of
the FAA Administrator. Subtitle VII, At locations where a preventive
PART 39—AIRWORTHINESS modification, time-limited repair, or
Aviation Programs, describes in more DIRECTIVES permanent repair has not been installed as
detail the scope of the Agency’s specified in Boeing Service Bulletin 737–
authority. ■ 1. The authority citation for part 39 53A1232: At the applicable time specified in
We are issuing this rulemaking under continues to read as follows: paragraph 1.E., ‘‘Compliance,’’ of Boeing
the authority described in Subtitle VII, Authority: 49 U.S.C. 106(g), 40113, 44701. Alert Service Bulletin 737–53A1232,
Part A, Subpart III, Section 44701, Revision 3, dated July 27, 2015, do an
‘‘General requirements.’’ Under that § 39.13 [Amended] external detailed inspection and an
section, Congress charges the FAA with inspection specified in either paragraph (g)(1)
■ 2. The FAA amends § 39.13 by or (g)(2) of this AD, for any crack in the
promoting safe flight of civil aircraft in removing Airworthiness Directive (AD) fuselage skin at the chem-milled steps at
air commerce by prescribing regulations 2008–12–04, Amendment 39–15547 (73 specified locations, in accordance with
for practices, methods, and procedures FR 32991, June 11, 2008), and adding Accomplishment Instructions of Boeing Alert
the Administrator finds necessary for the following new AD: Service Bulletin 737–53A1232, Revision 3,
safety in air commerce. This regulation dated July 27, 2015. Do all applicable related
2017–19–26 The Boeing Company:
is within the scope of that authority Amendment 39–19056; Docket No.
investigative and corrective actions before
because it addresses an unsafe condition further flight in accordance with the
FAA–2016–9301; Product Identifier
that is likely to exist or develop on Accomplishment Instructions of Boeing Alert
2015–NM–193–AD.
products identified in this rulemaking Service Bulletin 737–53A1232, Revision 3,
(a) Effective Date dated July 27, 2015, except as required by
action.
This AD is effective October 30, 2017. paragraph (l)(1) of this AD, and except as
This AD is issued in accordance with provided in paragraphs (l)(3) and (l)(4) of this
authority delegated by the Executive (b) Affected ADs AD. Repeat the inspections thereafter at the
Director, Aircraft Certification Service, This AD replaces AD 2008–12–04, applicable time specified in paragraph 1.E.,
as authorized by FAA Order 8000.51C. Amendment 39–15547 (73 FR 32991, June ‘‘Compliance,’’ of Boeing Alert Service
In accordance with that order, issuance 11, 2008) (‘‘AD 2008–12–04’’). Bulletin 737–53A1232, Revision 3, dated July
of ADs is normally a function of the 27, 2015.
(c) Applicability (1) Do an external medium frequency eddy
Compliance and Airworthiness
Division, but during this transition (1) This AD applies to The Boeing current (MFEC), or magneto optic imager
Company Model 737–600, –700, –700C, (MOI), or C-Scan inspection.
period, the Executive Director has (2) Do an external ultrasonic phased array
–800, and –900 series airplanes, certificated
delegated the authority to issue ADs (UTPA) inspection.
in any category, as identified in Boeing Alert
applicable to transport category Service Bulletin 737–53A1232, Revision 3,
airplanes to the Director of the System (h) Repetitive Post-Modification Inspections
dated July 27, 2015. and Repair at Any Location With the
Oversight Division. (2) Installation of Supplemental Type Preventive Modification But No Time-
Certificate (STC) ST00830SE [http://rgl.faa.
Regulatory Findings Limited or Permanent Repair
gov/Regulatory_and_Guidance_Library/rgstc.
We have determined that this AD will nsf/0/184DE9A71EC3FA5586257EAE00 At any location with a preventive
707DA6?OpenDocument&Highlight= modification installed as specified in Boeing
not have federalism implications under
st00830se] does not affect the ability to Service Bulletin 737–53A1232: At the
Executive Order 13132. This AD will applicable time specified in paragraph 1.E.,
not have a substantial direct effect on accomplish the actions required by this AD.
Therefore, for airplanes on which STC ‘‘Compliance,’’ of Boeing Alert Service
the States, on the relationship between ST00830SE is installed, a ‘‘change in Bulletin 737–53A1232, Revision 3, dated July
the national government and the States, product’’ alternative method of compliance 27, 2015, except as required by paragraph
or on the distribution of power and (AMOC) approval request is not necessary to (l)(2) of this AD, do the actions specified in
responsibilities among the various comply with the requirements of 14 CFR paragraphs (h)(1) and (h)(2) of this AD.
levels of government. 39.17. (1) Do external detailed and external high
For the reasons discussed above, I frequency and medium frequency eddy
(d) Subject current inspections for any crack, in
certify that this AD:
Air Transport Association (ATA) of accordance with Part 7 of the
(1) Is not a ‘‘significant regulatory America Code 53, Fuselage. Accomplishment Instructions of Boeing Alert
action’’ under Executive Order 12866, Service Bulletin 737–53A1232, Revision 3,
(2) Is not a ‘‘significant rule’’ under (e) Unsafe Condition dated July 27, 2015. If no crack is found
DOT Regulatory Policies and Procedures This AD was prompted by a fatigue test during the inspection, repeat the inspections
asabaliauskas on DSKBBXCHB2PROD with RULES
(44 FR 11034, February 26, 1979), that revealed numerous cracks in the upper thereafter at the applicable time specified in
(3) Will not affect intrastate aviation skin panel at the chem-milled step above the paragraph 1.E., ‘‘Compliance,’’ of Boeing
in Alaska, and lap joint, followed by an evaluation by the Alert Service Bulletin 737–53A1232,
design approval holder (DAH) that indicated Revision 3, dated July 27, 2015. If any crack
(4) Will not have a significant that location is subject to widespread fatigue is found during any inspection required by
economic impact, positive or negative, damage (WFD) on airplanes on which a this paragraph, repair before further flight, in
on a substantial number of small entities certain modification was installed after accordance with the Accomplishment
under the criteria of the Regulatory 30,000 total flight cycles. We are issuing this Instructions of Boeing Alert Service Bulletin
Flexibility Act. AD to detect and correct cracking of the 737–53A1232, Revision 3, dated July 27,
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![Federal Register / Vol. 82, No. 184 / Monday, September 25, 2017 / Rules and Regulations 44509
(2) Boeing Special Attention Service (2) You must use this service information Airbus Helicopters, 2701 N Forum
Bulletin 737–53A1232, Revision 1, dated as applicable to do the actions required by Drive, Grand Prairie, TX 75052;
May 18, 2012. this AD, unless the AD specifies otherwise. telephone (972) 641–0000 or (800) 232–
(3) Boeing Special Attention Service (i) Boeing Alert Service Bulletin 737– 0323; fax (972) 641–3775; or at http://
Bulletin 737–53A1232, Revision 2, dated July 53A1232, Revision 3, dated July 27, 2015.
26, 2013. (ii) Reserved.
www.airbushelicopters.com/techpub.
(3) For service information identified in You may review the referenced
(p) Alternative Methods of Compliance service information at the FAA, Office
this AD, contact Boeing Commercial
(AMOCs) of the Regional Counsel, Southwest
Airplanes, Attention: Contractual & Data
(1) The Manager, Seattle ACO Branch, Services (C&DS), 2600 Westminster Blvd., Region, 10101 Hillwood Pkwy., Room
FAA, has the authority to approve AMOCs MC 110–SK57, Seal Beach, CA 90740; 6N–321, Fort Worth, TX 76177.
for this AD, if requested using the procedures telephone 562–797–1717; Internet https://
found in 14 CFR 39.19. In accordance with www.myboeingfleet.com. Examining the AD Docket
14 CFR 39.19, send your request to your (4) You may view this service information You may examine the AD docket on
principal inspector or local Flight Standards at the FAA, Transport Standards Branch, the Internet at http://
District Office, as appropriate. If sending 1601 Lind Avenue SW., Renton, WA. For
information directly to the manager of the www.regulations.gov by searching for
information on the availability of this and locating Docket No. FAA–2016–
certification office, send it to the attention of material at the FAA, call 425–227–1221.
the person identified in paragraph (q)(1) of 9143; or in person at the Docket
(5) You may view this service information
this AD. Information may be emailed to: 9- that is incorporated by reference at the Operations Office between 9 a.m. and 5
ANM-Seattle-ACO-AMOC-Requests@faa.gov. National Archives and Records p.m., Monday through Friday, except
(2) Before using any approved AMOC, Administration (NARA). For information on Federal holidays. The AD docket
notify your appropriate principal inspector, the availability of this material at NARA, call contains this AD, the European Aviation
or lacking a principal inspector, the manager 202–741–6030, or go to: http://www.archives. Safety Agency (EASA) AD, any
of the local flight standards district office/
certificate holding district office.
gov/federal-register/cfr/ibr-locations.html. incorporated-by-reference service
(3) An AMOC that provides an acceptable Issued in Renton, Washington, on information, the economic evaluation,
level of safety may be used for any repair, September 14, 2017. any comments received, and other
modification, or alteration required by this Jeffrey E. Duven, information. The street address for the
AD if it is approved by the Boeing Director, System Oversight Division, Aircraft Docket Operations Office (phone: 800–
Commercial Airplanes Organization Certification Service. 647–5527) is U.S. Department of
Designation Authorization (ODA) that has Transportation, Docket Operations
been authorized by the Manager, Seattle [FR Doc. 2017–20114 Filed 9–22–17; 8:45 am]
Office, M–30, West Building Ground
ACO, to make those findings. To be BILLING CODE 4910–13–P
Floor, Room W12–140, 1200 New Jersey
approved, the repair method, modification
deviation, or alteration deviation must meet
Avenue SE., Washington, DC 20590.
the certification basis of the airplane, and the DEPARTMENT OF TRANSPORTATION FOR FURTHER INFORMATION CONTACT: Rao
approval must specifically refer to this AD. Edupuganti, Aviation Safety Engineer,
(4) AMOCs approved previously for repairs Federal Aviation Administration Regulations & Policy Section, Rotorcraft
for AD 2008–12–04 are approved as AMOCs Standards Branch, FAA, 10101
for the installation of the repair specified in 14 CFR Part 39 Hillwood Pkwy., Fort Worth, Texas
this AD, provided all post-repair inspections 76177; telephone (817) 222–5110; email
are done at the applicable times specified in [Docket No. FAA–2016–9143; Product rao.edupuganti@faa.gov.
the AMOC. Identifier 2013–SW–037–AD; Amendment
(5) AMOCs approved previously for 39–19051; AD 2017–19–21] SUPPLEMENTARY INFORMATION:
preventive modifications for AD 2008–12–04 Discussion
are approved as AMOCs for the installation RIN 2120–AA64
of the preventive modification specified in On March 14, 2017, at 82 FR 13565,
this AD, provided all post-modification Airworthiness Directives; Airbus the Federal Register published our
inspections are done at the applicable times Helicopters notice of proposed rulemaking (NPRM),
specified in the AMOC, or in tables 1a and which proposed to amend 14 CFR part
1b of paragraph 1.E., ‘‘Compliance,’’ of AGENCY: Federal Aviation
39 by adding an AD that would apply
Boeing Alert Service Bulletin 737–53A1232, Administration (FAA), DOT.
to Airbus Helicopters (formerly
Revision 3, dated July 27, 2015, whichever ACTION: Final rule.
occurs first. The AMOC must include all of
Eurocopter France) Model EC225LP
the inspections specified in Tables 1a and 1b SUMMARY: We are adopting a new helicopters. The NPRM proposed to
of Boeing Alert Service Bulletin 737– airworthiness directive (AD) for Airbus require replacing the EMLUB glycol
53A1232, Revision 3, dated July 27, 2015. pump, the air and glycol pressure
Helicopters Model EC225LP helicopters.
switches, and the MGB lubrication card,
(q) Related Information This AD requires modifying the
and modifying and re-identifying the
(1) For more information about this AD, emergency lubrication system (EMLUB).
helicopter wiring harness. The NPRM
contact Alan Pohl, Aerospace Engineer, This AD was prompted by two incidents
also proposed testing the function of the
Airframe Section, FAA, Seattle ACO Branch, of emergency ditching after there was a
1601 Lind Avenue SW., Renton, WA 98057–
EMLUB and electrical systems and
warning of a loss of oil pressure and a
3356; phone: 425–917–6577; fax: 425–917– revising the Emergency Procedures
false EMLUB failure. The actions of this
6450; email: alan.pohl@faa.gov. section of the RFM. Lastly, the NPRM
AD are intended to address an unsafe
(2) Service information identified in this proposed to prohibit installing certain
condition on these products.
AD that is not incorporated by reference is part-numbered EMLUB glycol pumps,
asabaliauskas on DSKBBXCHB2PROD with RULES
available at the addresses specified in DATES: This AD is effective October 30, air-pressure switches, glycol pressure
paragraphs (r)(3) and (r)(4) of this AD. 2017. switches and electronic boards on any
(r) Material Incorporated by Reference
The Director of the Federal Register helicopter. The proposed requirements
approved the incorporation by reference were intended to prevent a false EMLUB
(1) The Director of the Federal Register of a certain document listed in this AD
approved the incorporation by reference warning. This condition when
(IBR) of the service information listed in this as of October 30, 2017. associated with a loss of the MGB oil
paragraph under 5 U.S.C. 552(a) and 1 CFR ADDRESSES: For service information pressure could result in an unnecessary
part 51. identified in this final rule, contact emergency landing or ditching.
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Document Created: 2018-10-24 14:43:48
Document Modified: 2018-10-24 14:43:48
| Category | Regulatory Information | |
| Collection | Federal Register | |
| sudoc Class | AE 2.7: GS 4.107: AE 2.106: | |
| Publisher | Office of the Federal Register, National Archives and Records Administration | |
| Section | Rules and Regulations | |
| Action | Final rule. | |
| Dates | This AD is effective October 30, 2017. | |
| Contact | Alan Pohl, Aerospace Engineer, Airframe Section, FAA, Seattle ACO Branch, 1601 Lind Avenue SW., Renton, WA 98057-3356; phone: 425-917-6450; fax: 425-917-6590; email: [email protected] | |
| FR Citation | 82 FR 44504 | |
| RIN Number | 2120-AA64 | |
| CFR Associated | Air Transportation; Aircraft; Aviation Safety; Incorporation by Reference and Safety |
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