81 FR 34871 - Airworthiness Directives; The Boeing Company Airplanes
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration Federal Register Volume 81, Issue 105 (June 1, 2016)
Federal Aviation Administration
Federal Register Volume 81, Issue 105 (June 1, 2016)
| Page Range | 34871-34876 | |
| FR Document | 2016-12329 |
[Federal Register Volume 81, Number 105 (Wednesday, June 1, 2016)] [Rules and Regulations] [Pages 34871-34876] From the Federal Register Online [www.thefederalregister.org] [FR Doc No: 2016-12329] ----------------------------------------------------------------------- DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA-2015-5812; Directorate Identifier 2015-NM-077-AD; Amendment 39-18531; AD 2016-11-04] 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) 2011-23-05 for all The Boeing Company Model 737-300, -400, and -500 series airplanes. AD 2011-23-05 required repetitive inspections for cracking of the 1.04- inch nominal diameter wire penetration hole, and applicable related investigative and corrective actions. This new AD adds new inspection areas, a modification that terminates certain inspections, post- modification inspections, and repair if necessary. This AD was prompted by an evaluation by the design approval holder (DAH) that indicates the fuselage frames and frame reinforcements are subject to widespread fatigue damage (WFD). We are issuing this AD to detect and correct fatigue cracking of the fuselage frames and frame reinforcements that could [[Page 34872]] result in reduced structural integrity of the airplane. DATES: This AD is effective July 6, 2016. The Director of the Federal Register approved the incorporation by reference of a certain publication listed in this AD as of July 6, 2016. The Director of the Federal Register approved the incorporation by reference of a certain other publication listed in this AD as of November 16, 2011 (76 FR 67343, November 1, 2011). ADDRESSES: For service information identified in this final rule, contact Boeing Commercial Airplanes, Attention: Data & Services Management, P.O. Box 3707, MC 2H-65, Seattle, WA 98124-2207; telephone 206-544-5000, extension 1; fax 206-766-5680; Internet https://www.myboeingfleet.com. You may view this referenced service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For information on the availability of this material at the FAA, call 425-227-1221. It is also available on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2015- 5812. Examining the AD Docket You may examine the AD docket on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2015- 5812; 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: Galib Abumeri, Aerospace Engineer, Airframe Branch, ANM-120L, FAA, Los Angeles Aircraft Certification Office (ACO), 3960 Paramount Boulevard, Lakewood, CA 90712-4137; phone: 562-627-5324; 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 2011-23-05, Amendment 39-16856 (76 FR 67343, November 1, 2011) (``AD 2011-23-05''). AD 2011-23-05 applied to certain Model 737-300, -400, and -500 series airplanes. The NPRM published in the Federal Register on November 27, 2015 (80 FR 74047) (``the NPRM''). The NPRM was prompted by an evaluation by the DAH that indicates the fuselage frames and frame reinforcements are subject to WFD. The NPRM proposed to continue to require repetitive inspections for cracking of the 1.04-inch nominal diameter wire penetration hole, and applicable related investigative and corrective actions. The NPRM also proposed to add new inspection areas, a modification that terminates certain inspections, post-modification inspections, and repair if necessary. We are issuing this AD to detect and correct fatigue cracking of the fuselage frames and frame reinforcements that 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. Effect of Winglets on Accomplishment of the Proposed Actions Aviation Partners Boeing stated that accomplishing the supplemental type certificate (STC) ST01219SE (http://rgl.faa.gov/ Regulatory_and_Guidance_Library/rgstc.nsf/0/ ebd1cec7b301293e86257cb30045557a/$FILE/ST01219SE.pdf) does not affect the actions specified in the NPRM. We agree with the commenter. We have redesignated paragraph (c) of the proposed AD as paragraph (c)(1) and added a new paragraph (c)(2) to this AD to state that installation of STC ST01219SE (http:// rgl.faa.gov/Regulatory_and_Guidance_Library/rgstc.nsf/0/ ebd1cec7b301293e86257cb30045557a/$FILE/ST01219SE.pdf) does not affect the ability to accomplish the actions required by this AD. Therefore, for airplanes on which STC ST01219SE is installed, a ``change in product'' alternative method of compliance (AMOC) approval request is not necessary to comply with the requirements of 14 CFR 39.17. Request To Revise Applicability Boeing requested that we change the applicability to ``all'' airplanes instead of airplanes referenced in Boeing Alert Service Bulletin 737-53A1279, Revision 2, dated April 21, 2015. Boeing stated that Boeing Alert Service Bulletin 737-53A1279, Revision 2, dated April 21, 2015, specifies the effectivity as ``all'' airplanes. We agree with the commenter's request. In the NPRM we referred to Boeing Alert Service Bulletin 737-53A1279, Revision 2, dated April 21, 2015, which specifies an effectivity of all Model 737-300, -400, and - 500 series airplanes. For clarity, we have revised the SUMMARY section and paragraph (c)(1) of this AD to specify ``all'' airplanes. Request To Revise Compliance Time Southwest Airlines (SWA) requested that we revise paragraph (t) of the proposed AD to clearly state all inspections required by paragraph (n) of the proposed AD will be due at the later of 30,000 total flight cycles or 4,500 flight cycles from the effective date of the AD. SWA stated that, for airplanes which have previously accomplished the inspections specified in Boeing Alert Service Bulletin 737-53A1279, Revision 1, dated September 2, 2011, paragraph (n) of the proposed AD and table 1 of paragraph 1.E., ``Compliance,'' in Boeing Alert Service Bulletin 737-53A1279, Revision 2, dated April 21, 2015, currently requires inspections 4,500 flight cycles from the last inspection and do not specifically take into account those airplanes already doing the repetitive inspections. We do not agree with the commenter's request. AD 2011-23-05 required inspections on airplanes with less than 40,000 total flight cycles to begin prior to 30,000 total flight cycles or within 90 days from November 16, 2011 (the effective date of AD 2011-23-05), whichever occurs later. The repetitive inspection intervals of 4,500 flight cycles are not changed. The new WFD requirement lowers the initial airplane applicability total flight cycles from 40,000 to 30,000. Paragraph (n) of this AD addresses airplanes with more than 30,000 total flight cycles as of the effective date of the AD, and all airplanes that have already accomplished the initial inspection or a repetitive inspection. These airplanes are to continue the repetitive inspections at intervals not to exceed 4,500 flight cycles from the last inspection. The commenter's requested change would reset the time to the next inspection from the effective date of this AD instead of from the last inspection. This would result in a one-time increase in the repetitive interval, which would not meet the WFD requirements. We have not changed this AD in this regard. Request To Clarify Inspections in Paragraphs (m) and (n) of the Proposed AD Boeing requested that we clarify the inspections required in paragraph (m) [[Page 34873]] and (n) of the proposed AD. Boeing stated that the words ``an inspection'' is not specific enough to ensure the required inspections will be accomplished. We agree with the commenter's request. The wording ``an inspection'' could be interpreted incorrectly, and the Part 2 or Part 4 inspections specified in Boeing Alert Service Bulletin 737-53A1279, Revision 2, dated April 21, 2015, may not be accomplished prior to installation of the preventive modification. We have revised paragraph (m) of this AD to state in part, ``before further flight after accomplishing the Part 2 or Part 4 inspections specified in this paragraph, and no cracking was found, do ``Part 5-- Preventative Modification'' as specified in the Accomplishment Instructions of Boeing Alert Service Bulletin 737-53A1279, Revision 2, dated April 21, 2015.'' We have revised paragraph (n) of this AD to state in part, ``before further flight after accomplishing the Part 4 inspection specified in this paragraph, and no cracking was found, do ``Part 5--Preventative Modification'' as specified in the Accomplishment Instructions of Boeing Alert Service Bulletin 737-53A1279, Revision 2, dated April 21, 2015.'' Request To Remove a Certain Low Frequency Eddy Current (LFEC) Inspection Boeing requested that we remove the LFEC inspection in paragraph (s) of the proposed AD. Boeing stated that paragraph (s) of the proposed AD is applicable to Groups 4 through 6 as identified in Boeing Alert Service Bulletin 737-53A1279, Revision 2, dated April 21, 2015, and that LFEC inspections are not required for Groups 4 through 6. We agree with the commenter's request. We have revised paragraph (s) of this AD by removing the LFEC inspection requirement. Request To Clarify Service Information Description Boeing requested that we include ``0.50 inch diameter holes'' in the first bullet under the Related Service Information Under 1 CFR part 51 section. Boeing stated that the 0.50 inch hole was one of the main updates of Boeing Alert Service Bulletin 737-53A1279, Revision 2, dated April 21, 2015. We agree with commenter's request and have revised this final rule accordingly. Request To Revise Responsible FAA ACO Boeing requested that we revise paragraph (u)(3) of the proposed AD to reference the Los Angeles ACO instead of the Seattle ACO. We agree with the commenter's request. In July 2014, the Los Angeles ACO assumed responsibility for the out-of-production Model 737 airplanes. We have revised paragraph (u)(3) of this AD and the engineer contact information accordingly. 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 737-53A1279, Revision 2, dated April 21, 2015. The service information describes procedures for the following actions. Inspections of wire penetration holes, 0.50 inch diameter holes, standoff/tooling holes, and the production fastener holes for cracking in the forward cargo compartment frames and frame reinforcements, between stringer (S) S-19 and S-22, on both left and right sides of the airplane. A preventive modification of frames between S-19 and S-22. Post-modification inspections. 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. Costs of Compliance We estimate that this AD affects 605 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 [retained actions 16 work-hours x $85 per $0 $1,360 per $822,800 per from AD 2011-23-05]. hour = $1,360 per inspection cycle. inspection cycle. inspection cycle. Inspections [new action]....... 32 work-hours x $85 per 0 $2,720 per $1,645,600 per hour = $2,720 per inspection cycle. inspection cycle. inspection cycle. Modification [new action]...... 32 work-hours x $85 per 0 $2,720............ $1,645,600 hour = $2,720. ---------------------------------------------------------------------------------------------------------------- We estimate the following costs to do any necessary repairs that would be required based on the results of the inspection. We have no way of determining the number of aircraft that might need these repairs: On-Condition Costs ---------------------------------------------------------------------------------------------------------------- Cost per Action Labor cost Parts cost product ---------------------------------------------------------------------------------------------------------------- Repair.................................... 18 work-hours x $85 per hour = $0 $1,530 $1,530. ---------------------------------------------------------------------------------------------------------------- [[Page 34874]] 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: 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) 2011-23-05, Amendment 39-16856 (76 FR 67343, November 1, 2011), and adding the following new AD: 2016-11-04 The Boeing Company: Amendment 39-18531; Docket No. FAA- 2015-5812; Directorate Identifier 2015-NM-077-AD. (a) Effective Date This AD is effective July 6, 2016. (b) Affected ADs This AD replaces AD 2011-23-05, Amendment 39-16856 (76 FR 67343, November 1, 2011) (``AD 2011-23-05''). (c) Applicability (1) This AD applies to all The Boeing Company Model 737-300, - 400, and -500 series airplanes; certificated in any category. (2) Installation of Supplemental Type Certificate (STC) ST01219SE (http://rgl.faa.gov/Regulatory_and_Guidance_Library/ rgstc.nsf/0/ebd1cec7b301293e86257cb30045557a/$FILE/ST01219SE.pdf) does not affect the ability to accomplish the actions required by this AD. Therefore, for airplanes on which STC ST01219SE is installed, a ``change in product'' alternative method of compliance (AMOC) approval request is not necessary to comply with the requirements of 14 CFR 39.17. (d) Subject Air Transport Association (ATA) of America Code 53, Fuselage. (e) Unsafe Condition This AD was prompted by an evaluation by the design approval holder (DAH) that indicates the fuselage frames and frame reinforcements are subject to widespread fatigue damage (WFD). We are issuing this AD to detect and correct fatigue cracking of the fuselage frames and frame reinforcements, 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) Retained Inspection, With References to Terminating Actions This paragraph restates the requirements of paragraph (g) of AD 2011-23-05, with references to terminating actions. At the applicable time specified in paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin 737-53A1279, Revision 1, dated September 2, 2011, except as required by paragraphs (k)(1), (k)(2), and (k)(4) of this AD: Do a high frequency eddy current (HFEC) surface or HFEC hole/edge inspection for any cracking of the 1.04- inch nominal diameter wire penetration hole in the frame and frame reinforcement between stringer (S) S-20 and S-21, in accordance with Part 2 of the Accomplishment Instructions of Boeing Alert Service Bulletin 737-53A1279, Revision 1, dated September 2, 2011. Accomplishment of the applicable inspections required by paragraphs (m) and (n) of this AD terminates the inspections required by this paragraph. Accomplishment of the modification required by paragraph (p) of this AD terminates the inspections required by this paragraph for the modified area only. (h) Retained Repetitive Inspections, With References to Terminating Actions This paragraph restates the requirements of paragraph (h) of AD 2011-23-05, with references to terminating actions. Within 4,500 flight cycles after accomplishment of the most recent inspection specified in Part 2 or Part 4 of the Accomplishment Instructions of Boeing Alert Service Bulletin 737-53A1279, Revision 1, dated September 2, 2011, or within 90 days after November 16, 2011 (the effective date of AD 2011-23-05), whichever occurs later: Do an HFEC hole/edge inspection for cracking of the 1.04-inch nominal diameter wire penetration hole in the frame and frame reinforcement between S-20 and S-21, in accordance with Part 4 of the Accomplishment Instructions of Boeing Alert Service Bulletin 737-53A1279, Revision 1, dated September 2, 2011. Repeat the inspection thereafter at intervals not to exceed 4,500 flight cycles. Accomplishment of the applicable inspections required by paragraphs (m) and (n) of this AD, terminates the inspections required by this paragraph. Accomplishment of the modification specified in paragraph (j) or (p) of this AD terminates the repetitive inspections required by this paragraph for the modified area only. Accomplishment of the repair specified in paragraph (i) of this AD terminates the repetitive inspections required by this paragraph for the repaired area only. (i) Retained Repair, With No Changes This paragraph restates the requirements of paragraph (i) of AD 2011-23-05, with no changes. If any cracking is found during any inspection required by paragraph (g) or (h) of this AD: Before further flight, repair the crack including doing all applicable related investigative and corrective actions, in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 737- 53A1279, Revision 1, dated September 2, 2011, except as required by paragraph (k)(3) of this AD. All applicable related investigative and corrective actions must be done before further flight. Accomplishment of the requirements of this paragraph terminates the repetitive inspection requirements of paragraph (h) of this AD for the repaired location of that frame. (j) Retained Optional Terminating Action, With New Limitation This paragraph restates the optional action provided in paragraph (j) of AD 2011-23-05, with a new limitation. Accomplishment of the preventive modification before the effective date of this AD, including doing all related investigative and applicable corrective actions, specified in Part 5 of the Accomplishment Instructions of Boeing Alert Service Bulletin 737- 53A1279, Revision 1, dated September 2, 2011, except as required by paragraph (k)(3) of this AD, terminates the repetitive inspection requirements of paragraph (h) of this AD for the modified [[Page 34875]] location of that frame, provided the modification is done before further flight after an inspection required by paragraph (g) or (h) of this AD has been done, and no cracking was found on that frame location during that inspection. (k) Retained Exceptions to Service Information Specifications, With No Changes This paragraph restates the requirements of paragraph (k) of AD 2011-23-05, with no changes. The following exceptions apply as specified in paragraphs (g), (i), and (j) of this AD. (1) Where paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin 737-53A1279, Revision 1, dated September 2, 2011, refers to a compliance time ``from date on Revision 1 of this service bulletin,'' this AD requires compliance within the specified compliance time after November 16, 2011 (the effective date of AD 2011-23-05). (2) For airplanes meeting all of the criteria specified in paragraphs (k)(2)(i), (k)(2)(ii), and (k)(2)(iii) of this AD: The compliance time for the initial inspection specified in Part 2 of the Accomplishment Instructions of Boeing Alert Service Bulletin 737-53A1279, Revision 1, dated September 2, 2011, and required by paragraph (g) of this AD, may be extended to 90 days after November 16, 2011 (the effective date of AD 2011-23-05). (i) Model 737-300 series airplanes in Group 1, line numbers 1001 through 2565 inclusive; (ii) Airplanes that have accumulated 40,000 or more total flight cycles as of November 16, 2011 (the effective date of AD 2011-23- 05); and (iii) Airplanes on which the modification specified in Boeing Service Bulletin 737-53-1273, dated September 20, 2006; Revision 1, dated December 21, 2006; Revision 2, dated June 4, 2007; Revision 3, dated December 7, 2009; or Revision 4, dated July 23, 2010; has been done, including any configuration or deviation that has been approved as an AMOC during accomplishment of these service bulletins, by the Boeing Commercial Airplanes Organization Designation Authorization (ODA) that has been authorized by the Manager, Seattle Aircraft Certification Office (ACO) or Los Angeles ACO to make those findings. (3) Where Boeing Alert Service Bulletin 737-53A1279, Revision 1, dated September 2, 2011, specifies to contact Boeing for appropriate repair instructions: Before further flight, repair the crack using a method approved in accordance with the procedures specified in paragraph (u) of this AD. (4) The ``Condition'' column of paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin 737-53A1279, Revision 1, dated September 2, 2011, refers to total flight cycles ``at the date of/on this service bulletin.'' However, this AD applies to the airplanes with the specified total flight cycles as of November 16, 2011 (the effective date of AD 2011-23-05). (l) Retained Credit for Previous Actions, With No Changes This paragraph restates the requirements of paragraph (l) of AD 2011-23-05, with no changes. Actions done in accordance with Boeing Alert Service Bulletin 737-53A1279, dated December 18, 2007, before November 16, 2011 (the effective date of AD 2011-23-05), are acceptable for compliance with the corresponding actions required by paragraphs (g), (h), (i), and (j) of this AD. (m) New Requirement of This AD: Inspections of Frames and Frame Reinforcements Between S-19 and S-22 for Certain Airplanes on Which Certain Inspections Have Not Been Accomplished For airplanes identified as Groups 1 through 6, Configuration 3, in Boeing Alert Service Bulletin 737-53A1279, Revision 2, dated April 21, 2015, with 30,000 total flight cycles or fewer as of the effective date of this AD, on which any inspections specified in Boeing Alert Service Bulletin 737-53A1279, Revision 1, dated September 2, 2011, have not been accomplished: Except as required by paragraphs (t)(1) and (t)(2) of this AD, at the applicable time specified in table 1 of paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin 737-53A1279, Revision 2, dated April 21, 2015, or within 4,500 flight cycles after the effective date of this AD, whichever occurs later, do inspections for cracking at certain locations in the frames and frame reinforcements in accordance with ``Part 2--Initial Detail and HFEC Inspection'' of the Accomplishment Instructions of Boeing Alert Service Bulletin 737-53A1279, Revision 2, dated April 21, 2015. Repeat the inspections for cracking at certain locations in the frames and frame reinforcements as specified in ``Part 4--Repeat Detail and HFEC Inspections'' of the Accomplishment Instructions of Boeing Alert Service Bulletin 737- 53A1279, Revision 2, dated April 21, 2015, thereafter at the applicable interval specified in paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin 737-53A1279, Revision 2, dated April 21, 2015; or, before further flight after accomplishing the Part 2 or Part 4 inspections specified in this paragraph, and no cracking was found, do ``Part 5--Preventative Modification'' as specified in the Accomplishment Instructions of Boeing Alert Service Bulletin 737-53A1279, Revision 2, dated April 21, 2015. Accomplishment of the preventive modification specified in this paragraph terminates the repetitive inspections required by this paragraph for the modified area only. Do all actions specified in this paragraph in accordance with Accomplishment Instructions of Boeing Alert Service Bulletin 737-53A1279, Revision 2, dated April 21, 2015. (n) New Requirement of This AD: Inspections of Frames and Frame Reinforcements Between S-19 and S-22 for Groups 1-6, Configuration 3, Airplanes For airplanes identified as Groups 1 through 6, Configuration 3, in Boeing Alert Service Bulletin 737-53A1279, Revision 2, dated April 21, 2015, with more than 30,000 total flight cycles as of the effective date of this AD, or that have been inspected as specified in Boeing Alert Service Bulletin 737-53A1279, Revision 1, dated September 2, 2011: Except as required by paragraphs (t)(1) and (t)(2) of this AD, at the applicable time specified in table 1 of paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin 737-53A1279, Revision 2, dated April 21, 2015, do inspections for cracking at certain locations of the frames and frame reinforcements in accordance with ``Part 4--Repeat Detail and HFEC Inspections'' of the Accomplishment Instructions of Boeing Alert Service Bulletin 737-53A1279, Revision 2, dated April 21, 2015. Repeat the inspections thereafter at the applicable interval specified in paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin 737-53A1279, Revision 2, dated April 21, 2015; or, before further flight after accomplishing the Part 4 inspection specified in this paragraph, and no cracking was found, do ``Part 5--Preventative Modification'' as specified in the Accomplishment Instructions of Boeing Alert Service Bulletin 737-53A1279, Revision 2, dated April 21, 2015. Accomplishment of the preventive modification specified in this paragraph terminates the repetitive inspections required by this paragraph for the modified area only. (o) New Requirement of This AD: Repairs If any crack is found during any inspection required by paragraph (m) or (n) of this AD: Before further flight, repair, in accordance with ``Part 3--Repair'' of the Accomplishment Instructions of Boeing Alert Service Bulletin 737-53A1279, Revision 2, dated April 21, 2015, except where Boeing Alert Service Bulletin 737-53A1279, Revision 2, dated April 21, 2015, specifies to contact Boeing for damage removal and repair instructions, repair before further flight using a method approved in accordance with the procedures specified in paragraph (u) of this AD. Accomplishing a repair terminates the inspections required by paragraphs (m) and (n) of this AD in the repaired area only. Accomplishment of a repair terminates the modification required by paragraph (p) of this AD at the repaired location only. (p) New Requirement of This AD: Preventative Modification of the Frames Between S-19 and S-22 For airplanes identified as Groups 1 through 6, Configuration 3, in Boeing Alert Service Bulletin 737-53A1279, Revision 2, dated April 21, 2015: Except as required by paragraphs (t)(1) and (t)(2) of this AD, at the applicable time specified in table 2 of paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin 737-53A1279, Revision 2, dated April 21, 2015, do the preventive modification of the frames between S-19 and S-22, in accordance with ``Part 5-- Preventative Modification'' of the Accomplishment Instructions of Boeing Alert Service Bulletin 737-53A1279, Revision 2, dated April 21, 2015. Accomplishment of the modification required by this paragraph terminates the requirements of paragraphs (g), (h), (m), and (n) of this AD for the modified location only. (q) New Requirement of This AD: Inspections of Preventive Modification for Groups 1-3, Configuration 1, Airplanes For airplanes identified as Groups 1 through 3, Configuration 1, in Boeing Alert [[Page 34876]] Service Bulletin 737-53A1279, Revision 2, dated April 21, 2015: Except as required by paragraph (t)(1) of this AD, at the applicable time specified in table 3 of paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin 737-53A1279, Revision 2, dated April 21, 2015, do HFEC, LFEC, and detailed inspections for cracking in accordance with ``Part 7--INSPECTION OF PREVENTATIVE MODIFICATION'' of the Accomplishment Instructions of Boeing Alert Service Bulletin 737-53A1279, Revision 2, dated April 21, 2015. Repeat the inspections thereafter at the applicable interval specified in paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin 737-53A1279, Revision 2, dated April 21, 2015. If any cracking is found during any inspection required by this paragraph, before further flight, repair using a method approved in accordance with the procedures specified in paragraph (u) of this AD. (r) New Requirement of This AD: Inspections of Preventive Modification for Groups 1-6, Configuration 2, Airplanes For airplanes identified as Groups 1 through 6, Configuration 2, in Boeing Alert Service Bulletin 737-53A1279, Revision 2, dated April 21, 2015: Except as required by paragraph (t)(1) of this AD, at the applicable time specified in table 4 or table 6 of paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin 737-53A1279, Revision 2, dated April 21, 2015, do HFEC, LFEC, and detailed inspections for cracking in accordance with ``Part 8--INSPECTION OF PREVENTATIVE MODIFICATION'' of the Accomplishment Instructions of Boeing Alert Service Bulletin 737-53A1279, Revision 2, dated April 21, 2015. Repeat the inspections thereafter at the applicable interval specified in table 4 or table 6 of paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin 737-53A1279, Revision 2, dated April 21, 2015. If any cracking is found during any inspection required by this paragraph, before further flight, repair using a method approved in accordance with the procedures specified in paragraph (u) of this AD. (s) New Requirement of This AD: Inspections of Preventive Modification for Groups 4-6, Configuration 1, Airplanes For airplanes identified as Groups 4 through 6, Configuration 1, in Boeing Alert Service Bulletin 737-53A1279, Revision 2, dated April 21, 2015: At the applicable time specified in table 5 of paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin 737-53A1279, Revision 2, dated April 21, 2015, except as required by paragraph (t)(1) of this AD: Do HFEC and detailed inspections for cracking in accordance with ``Part 7--INSPECTION OF PREVENTATIVE MODIFICATION'' of the Accomplishment Instructions of Boeing Alert Service Bulletin 737-53A1279, Revision 2, dated April 21, 2015. Repeat the inspections thereafter at the applicable time specified in paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin 737-53A1279, Revision 2, dated April 21, 2015. If any cracking is found during any inspection required by this paragraph, before further flight, repair using a method approved in accordance with the procedures specified in paragraph (u) of this AD. (t) New Requirement of This AD: Exceptions to Service Bulletin Specifications (1) Where paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin 737-53A1279, Revision 2, dated April 21, 2015, refers to 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. (2) The ``Condition'' column in table 1 and table 2 of paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin 737-53A1279, Revision 2, dated April 21, 2015, refers to total flight cycles ``at the Revision 2 date of this service bulletin.'' However, this AD applies to the airplanes with the specified total flight cycles as of the effective date of this AD. (u) Alternative Methods of Compliance (AMOCs) (1) The Manager, Los Angeles 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 (v)(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 ODA that has been authorized by the Manager, Los Angeles ACO, to make those findings. To be approved, the repair method, modification deviation, or alteration deviation must meet the certification basis of the airplane and the approval must specifically refer to this AD. (4) AMOCs approved for the ADs in paragraphs (u)(4)(i) through (u)(4)(iii) of this AD are approved as AMOCs for the corresponding provisions of this AD. (i) AD 2009-02-06, Amendment 39-15796 (74 FR 10469, March 11, 2009). (ii) AD 2009-02-06 R1, Amendment 39-16015 (74 FR 45979, September 8, 2009). (iii) AD 2011-23-05. (v) Related Information (1) For more information about this AD, contact Galib Abumeri, Aerospace Engineer, Airframe Branch, ANM-120L, FAA, Los Angeles ACO, 3960 Paramount Boulevard, Lakewood, CA 90712-4137; phone: 562-627- 5324; 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 (w)(5) and (w)(6) of this AD. (w) 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 July 6, 2016. (i) Boeing Alert Service Bulletin 737-53A1279, Revision 2, dated April 21, 2015. (ii) Reserved. (4) The following service information was approved for IBR on November 16, 2011 (76 FR 67343, November 1, 2011). (i) Boeing Alert Service Bulletin 737-53A1279, Revision 1, dated September 2, 2011. (ii) Reserved. (5) 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. (6) You may view this service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For information on the availability of this material at the FAA, call 425-227-1221. (7) 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 May 18, 2016. Dionne Palermo, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2016-12329 Filed 5-31-16; 8:45 am] BILLING CODE 4910-13-P
![Federal Register / Vol. 81, No. 105 / Wednesday, June 1, 2016 / Rules and Regulations 34871
Service Bulletin 777–28–0078, Revision 1, be emailed to: 9-ANM-Seattle-ACO-AMOC- 2H–65, Seattle, WA 98124–2207; telephone
dated April 27, 2015, concurrently with Requests@faa.gov. 206–544–5000, extension 1; fax 206–766–
accomplishing the actions required by (2) Before using any approved AMOC, 5680; Internet https://
paragraph (g) of this AD, install a new P301 notify your appropriate principal inspector, www.myboeingfleet.com.
panel on the left side of the airplane, install or lacking a principal inspector, the manager (4) For GE Aviation service information
a new P302 panel on the right side of the of the local flight standards district office/ identified in this AD, contact GE Aviation
airplane, and change the wiring; or perform certificate holding district office. Fleet Support, 1 Neumann Way, Cincinnati,
bonding resistance measurements and rework (3) An AMOC that provides an acceptable OH 45215; telephone 513–552–3272; email:
the airplane installations; as applicable; in level of safety may be used for any repair, aviation.fleetsupport@ge.com; Internet http://
accordance with the Accomplishment modification, or alteration required by this www.geaviation.com.
Instructions of Boeing Service Bulletin 777– AD if it is approved by the Boeing (5) You may view this service information
28A0047, Revision 5, dated September 20, Commercial Airplanes Organization at the FAA, Transport Airplane Directorate,
2010; or Boeing Service Bulletin 777– Designation Authorization (ODA) that has 1601 Lind Avenue SW., Renton, WA. For
28A0047, Revision 6, dated July 11, 2013. been authorized by the Manager, Seattle information on the availability of this
(2) For airplanes identified in Boeing ACO, to make those findings. To be material at the FAA, call 425–227–1221.
Special Attention Service Bulletin 777–28– approved, the repair method, modification (6) You may view this service information
0078, Revision 1, dated April 27, 2015, deviation, or alteration deviation must meet that is incorporated by reference at the
except for Group 10 airplanes on which the the certification basis of the airplane and the National Archives and Records
actions described in Boeing Service Bulletin approval must specifically refer to this AD. Administration (NARA). For information on
777–28–0060; or Work Package 2 of the (4) For service information that contains the availability of this material at NARA, call
Accomplishment Instructions of Boeing steps that are labeled as Required for 202–741–6030, or go to: http://
Service Bulletin 777–28–0062, have not been Compliance (RC), the provisions of www.archives.gov/federal-register/cfr/ibr-
accomplished: Concurrently with paragraphs (k)(4)(i) and (k)(4)(ii) of this AD locations.html.
accomplishing the requirements of paragraph apply.
Issued in Renton, Washington, on May 18,
(g) of this AD, do wiring changes in the P110 (i) The steps labeled as RC, including
2016.
and P210 panels, in accordance with the substeps under an RC step and any figures
applicable Accomplishment Instructions of identified in an RC step, must be done to Dionne Palermo,
GE Aviation Service bulletin 5000ELM–28– comply with the AD. An AMOC is required Acting Manager, Transport Airplane
075, Revision 1, dated August 5, 2014; and for any deviations to RC steps, including Directorate, Aircraft Certification Service.
GE Aviation Service Bulletin 6000ELM–28– substeps and identified figures. [FR Doc. 2016–12443 Filed 5–31–16; 8:45 am]
076, Revision 1, dated August 5, 2014. (ii) Steps not labeled as RC may be BILLING CODE 4910–13–P
deviated from using accepted methods in
(i) Parts Installation Prohibition accordance with the operator’s maintenance
For Group 10 airplanes, as identified in or inspection program without obtaining
DEPARTMENT OF TRANSPORTATION
Boeing Special Attention Service Bulletin approval of an AMOC, provided the RC steps,
777–28–0078, Revision 1, dated April 27, including substeps and identified figures, can
Federal Aviation Administration
2015, after completion of the actions required still be done as specified, and the airplane
by paragraph (g) of this AD, no person may can be put back in an airworthy condition.
install an auxiliary fuel tank on any Group 14 CFR Part 39
10 airplane. (l) Related Information
(1) For more information about this AD, [Docket No. FAA–2015–5812; Directorate
(j) Credit for Previous Actions contact Sue Lucier, Aerospace Engineer, Identifier 2015–NM–077–AD; Amendment
(1) This paragraph provides credit for Propulsion Branch, ANM–140S, FAA, Seattle 39–18531; AD 2016–11–04]
actions required by paragraph (h)(1) of this ACO, 1601 Lind Avenue SW., Renton, WA RIN 2120–AA64
AD, if those actions were performed before 98057–3356; phone: 425–917–6438; fax: 425–
May 26, 2011 (the effective date of AD 2011– 917–6590; email: suzanne.lucier@faa.gov. Airworthiness Directives; The Boeing
09–05, Amendment 39–16667 (77 FR 22305, (2) Boeing service information identified in
April 21, 2011)), using a service bulletin this AD that is not incorporated by reference
Company Airplanes
identified in paragraph (j)(1)(i) or (j)(1)(ii) of is available at the addresses specified in AGENCY: Federal Aviation
this AD, which are not incorporated by paragraphs (m)(3) and (m)(5) of this AD. Administration (FAA), DOT.
reference in this AD.
(i) Boeing Service Bulletin 777–28A0047, (m) Material Incorporated by Reference ACTION: Final rule.
Revision 3, dated June 11, 2009. (1) The Director of the Federal Register
(ii) Boeing Service Bulletin 777–28A0047, approved the incorporation by reference SUMMARY: We are superseding
Revision 4, dated May 20, 2010. (IBR) of the service information listed in this Airworthiness Directive (AD) 2011–23–
(2) This paragraph provides credit for paragraph under 5 U.S.C. 552(a) and 1 CFR 05 for all The Boeing Company Model
actions required by paragraph (g) of this AD, part 51. 737–300, –400, and –500 series
if those actions were performed before the (2) You must use this service information airplanes. AD 2011–23–05 required
effective date of this AD using Boeing Special as applicable to do the actions required by repetitive inspections for cracking of the
Attention Service Bulletin 777–28–0078, this AD, unless the AD specifies otherwise.
1.04-inch nominal diameter wire
dated September 4, 2014, which is not (i) Boeing Service Bulletin 777–28A0047,
Revision 5, dated September 20, 2010. penetration hole, and applicable related
incorporated by reference in this AD.
(ii) Boeing Service Bulletin 777–28A0047, investigative and corrective actions.
(k) Alternative Methods of Compliance Revision 6, dated July 11, 2013. This new AD adds new inspection
(AMOCs) (iii) Boeing Special Attention Service areas, a modification that terminates
(1) The Manager, Seattle Aircraft Bulletin 777–28–0078, Revision 1, dated certain inspections, post-modification
Certification Office (ACO), FAA, has the April 27, 2015. inspections, and repair if necessary.
authority to approve AMOCs for this AD, if (iv) GE Aviation Service Bulletin This AD was prompted by an evaluation
sradovich on DSK3TPTVN1PROD with RULES
requested using the procedures found in 14 5000ELM–28–075, Revision 1, dated August by the design approval holder (DAH)
CFR 39.19. In accordance with 14 CFR 39.19, 5, 2014.
that indicates the fuselage frames and
send your request to your principal inspector (v) GE Aviation Service Bulletin 6000ELM–
or local Flight Standards District Office, as 28–076, Revision 1, dated August 5, 2014. frame reinforcements are subject to
appropriate. If sending information directly (3) For Boeing service information widespread fatigue damage (WFD). We
to the manager of the ACO, send it to the identified in this AD, contact Boeing are issuing this AD to detect and correct
attention of the person identified in Commercial Airplanes, Attention: Data & fatigue cracking of the fuselage frames
paragraph (l)(1) of this AD. Information may Services Management, P.O. Box 3707, MC and frame reinforcements that could
VerDate Sep<11>2014 16:11 May 31, 2016 Jkt 238001 PO 00000 Frm 00011 Fmt 4700 Sfmt 4700 E:\FR\FM\01JNR1.SGM 01JNR1](https://thefederalregister.org/doc/81_FR_34976/page/1.svg)
![Federal Register / Vol. 81, No. 105 / Wednesday, June 1, 2016 / Rules and Regulations 34873
and (n) of the proposed AD. Boeing Bulletin 737–53A1279, Revision 2, and minor editorial changes. We have
stated that the words ‘‘an inspection’’ is dated April 21, 2015, and that LFEC determined that these minor changes:
not specific enough to ensure the inspections are not required for Groups • Are consistent with the intent that
required inspections will be 4 through 6. was proposed in the NPRM for
accomplished. We agree with the commenter’s correcting the unsafe condition; and
We agree with the commenter’s request. We have revised paragraph (s) • Do not add any additional burden
request. The wording ‘‘an inspection’’ of this AD by removing the LFEC upon the public than was already
could be interpreted incorrectly, and the inspection requirement. proposed in the NPRM.
Part 2 or Part 4 inspections specified in We also determined that these
Boeing Alert Service Bulletin 737– Request To Clarify Service Information
Description changes will not increase the economic
53A1279, Revision 2, dated April 21, burden on any operator or increase the
2015, may not be accomplished prior to Boeing requested that we include scope of this AD.
installation of the preventive ‘‘0.50 inch diameter holes’’ in the first
modification. bullet under the Related Service Related Service Information Under 1
We have revised paragraph (m) of this Information Under 1 CFR part 51 CFR Part 51
AD to state in part, ‘‘before further flight section. Boeing stated that the 0.50 inch We reviewed Boeing Alert Service
after accomplishing the Part 2 or Part 4 hole was one of the main updates of Bulletin 737–53A1279, Revision 2,
inspections specified in this paragraph, Boeing Alert Service Bulletin 737– dated April 21, 2015. The service
and no cracking was found, do ‘‘Part 5— 53A1279, Revision 2, dated April 21, information describes procedures for the
Preventative Modification’’ as specified 2015. following actions.
in the Accomplishment Instructions of We agree with commenter’s request • Inspections of wire penetration
Boeing Alert Service Bulletin 737– and have revised this final rule holes, 0.50 inch diameter holes,
53A1279, Revision 2, dated April 21, accordingly. standoff/tooling holes, and the
2015.’’
We have revised paragraph (n) of this Request To Revise Responsible FAA production fastener holes for cracking in
AD to state in part, ‘‘before further flight ACO the forward cargo compartment frames
after accomplishing the Part 4 Boeing requested that we revise and frame reinforcements, between
inspection specified in this paragraph, paragraph (u)(3) of the proposed AD to stringer (S) S–19 and S–22, on both left
and no cracking was found, do ‘‘Part 5— reference the Los Angeles ACO instead and right sides of the airplane.
Preventative Modification’’ as specified of the Seattle ACO. • A preventive modification of frames
in the Accomplishment Instructions of We agree with the commenter’s between S–19 and S–22.
Boeing Alert Service Bulletin 737– request. In July 2014, the Los Angeles • Post-modification inspections.
53A1279, Revision 2, dated April 21, ACO assumed responsibility for the out- • Repairs.
2015.’’ of-production Model 737 airplanes. We This service information is reasonably
have revised paragraph (u)(3) of this AD available because the interested parties
Request To Remove a Certain Low have access to it through their normal
and the engineer contact information
Frequency Eddy Current (LFEC) course of business or by the means
accordingly.
Inspection identified in the ADDRESSES section.
Boeing requested that we remove the Conclusion
Costs of Compliance
LFEC inspection in paragraph (s) of the We reviewed the relevant data,
proposed AD. Boeing stated that considered the comments received, and We estimate that this AD affects 605
paragraph (s) of the proposed AD is determined that air safety and the airplanes of U.S. registry.
applicable to Groups 4 through 6 as public interest require adopting this AD We estimate the following costs to
identified in Boeing Alert Service with the changes described previously, comply with this AD:
ESTIMATED COSTS
Cost on U.S.
Action Labor cost Parts cost Cost per product operators
Inspections [retained actions from AD 16 work-hours × $85 per hour = $1,360 $0 $1,360 per inspec- $822,800 per in-
2011–23–05]. per inspection cycle. tion cycle. spection cycle.
Inspections [new action] ......................... 32 work-hours × $85 per hour = $2,720 0 $2,720 per inspec- $1,645,600 per in-
per inspection cycle. tion cycle. spection cycle.
Modification [new action] ........................ 32 work-hours × $85 per hour = $2,720 0 $2,720 .................... $1,645,600
We estimate the following costs to do required based on the results of the determining the number of aircraft that
any necessary repairs that would be inspection. We have no way of might need these repairs:
ON-CONDITION COSTS
Cost per
Action Labor cost Parts cost
sradovich on DSK3TPTVN1PROD with RULES
product
Repair .............................................. 18 work-hours × $85 per hour = $1,530 ................................................... $0 $1,530
VerDate Sep<11>2014 16:11 May 31, 2016 Jkt 238001 PO 00000 Frm 00013 Fmt 4700 Sfmt 4700 E:\FR\FM\01JNR1.SGM 01JNR1](https://thefederalregister.org/doc/81_FR_34976/page/3.svg)
![34874 Federal Register / Vol. 81, No. 105 / Wednesday, June 1, 2016 / Rules and Regulations
Authority for This Rulemaking § 39.13 [Amended] the applicable inspections required by
paragraphs (m) and (n) of this AD terminates
Title 49 of the United States Code ■ 2. The FAA amends § 39.13 by the inspections required by this paragraph.
specifies the FAA’s authority to issue removing Airworthiness Directive (AD) Accomplishment of the modification
rules on aviation safety. Subtitle I, 2011–23–05, Amendment 39–16856 (76 required by paragraph (p) of this AD
Section 106, describes the authority of FR 67343, November 1, 2011), and terminates the inspections required by this
the FAA Administrator. Subtitle VII, adding the following new AD: paragraph for the modified area only.
Aviation Programs, describes in more 2016–11–04 The Boeing Company: (h) Retained Repetitive Inspections, With
detail the scope of the Agency’s Amendment 39–18531; Docket No. References to Terminating Actions
authority. FAA–2015–5812; Directorate Identifier This paragraph restates the requirements of
2015–NM–077–AD. paragraph (h) of AD 2011–23–05, with
We are issuing this rulemaking under
the authority described in Subtitle VII, (a) Effective Date references to terminating actions. Within
Part A, Subpart III, Section 44701, 4,500 flight cycles after accomplishment of
This AD is effective July 6, 2016.
the most recent inspection specified in Part
‘‘General requirements.’’ Under that 2 or Part 4 of the Accomplishment
(b) Affected ADs
section, Congress charges the FAA with Instructions of Boeing Alert Service Bulletin
promoting safe flight of civil aircraft in This AD replaces AD 2011–23–05,
Amendment 39–16856 (76 FR 67343, 737–53A1279, Revision 1, dated September
air commerce by prescribing regulations November 1, 2011) (‘‘AD 2011–23–05’’). 2, 2011, or within 90 days after November 16,
for practices, methods, and procedures 2011 (the effective date of AD 2011–23–05),
the Administrator finds necessary for (c) Applicability whichever occurs later: Do an HFEC hole/
safety in air commerce. This regulation (1) This AD applies to all The Boeing edge inspection for cracking of the 1.04-inch
is within the scope of that authority Company Model 737–300, –400, and –500 nominal diameter wire penetration hole in
series airplanes; certificated in any category. the frame and frame reinforcement between
because it addresses an unsafe condition S–20 and S–21, in accordance with Part 4 of
that is likely to exist or develop on (2) Installation of Supplemental Type
Certificate (STC) ST01219SE (http:// the Accomplishment Instructions of Boeing
products identified in this rulemaking rgl.faa.gov/Regulatory_and_Guidance_ Alert Service Bulletin 737–53A1279,
action. Library/rgstc.nsf/0/ Revision 1, dated September 2, 2011. Repeat
ebd1cec7b301293e86257cb30045557a/$FILE/ the inspection thereafter at intervals not to
Regulatory Findings exceed 4,500 flight cycles. Accomplishment
ST01219SE.pdf) does not affect the ability to
We have determined that this AD will accomplish the actions required by this AD. of the applicable inspections required by
not have federalism implications under Therefore, for airplanes on which STC paragraphs (m) and (n) of this AD, terminates
ST01219SE is installed, a ‘‘change in the inspections required by this paragraph.
Executive Order 13132. This AD will Accomplishment of the modification
not have a substantial direct effect on product’’ alternative method of compliance
(AMOC) approval request is not necessary to specified in paragraph (j) or (p) of this AD
the States, on the relationship between comply with the requirements of 14 CFR terminates the repetitive inspections required
the national government and the States, 39.17. by this paragraph for the modified area only.
or on the distribution of power and Accomplishment of the repair specified in
responsibilities among the various (d) Subject paragraph (i) of this AD terminates the
levels of government. Air Transport Association (ATA) of repetitive inspections required by this
America Code 53, Fuselage. paragraph for the repaired area only.
For the reasons discussed above, I
certify that this AD: (e) Unsafe Condition (i) Retained Repair, With No Changes
(1) Is not a ‘‘significant regulatory This AD was prompted by an evaluation by This paragraph restates the requirements of
action’’ under Executive Order 12866, the design approval holder (DAH) that paragraph (i) of AD 2011–23–05, with no
(2) Is not a ‘‘significant rule’’ under indicates the fuselage frames and frame changes. If any cracking is found during any
reinforcements are subject to widespread inspection required by paragraph (g) or (h) of
DOT Regulatory Policies and Procedures
fatigue damage (WFD). We are issuing this this AD: Before further flight, repair the crack
(44 FR 11034, February 26, 1979), including doing all applicable related
AD to detect and correct fatigue cracking of
(3) Will not affect intrastate aviation the fuselage frames and frame investigative and corrective actions, in
in Alaska, and reinforcements, which could result in accordance with the Accomplishment
(4) Will not have a significant reduced structural integrity of the airplane. Instructions of Boeing Alert Service Bulletin
economic impact, positive or negative, 737–53A1279, Revision 1, dated September
(f) Compliance 2, 2011, except as required by paragraph
on a substantial number of small entities
Comply with this AD within the (k)(3) of this AD. All applicable related
under the criteria of the Regulatory compliance times specified, unless already investigative and corrective actions must be
Flexibility Act. done. done before further flight. Accomplishment
List of Subjects in 14 CFR Part 39 of the requirements of this paragraph
(g) Retained Inspection, With References to terminates the repetitive inspection
Terminating Actions
Air transportation, Aircraft, Aviation requirements of paragraph (h) of this AD for
safety, Incorporation by reference, This paragraph restates the requirements of the repaired location of that frame.
Safety. paragraph (g) of AD 2011–23–05, with
references to terminating actions. At the (j) Retained Optional Terminating Action,
Adoption of the Amendment applicable time specified in paragraph 1.E., With New Limitation
‘‘Compliance,’’ of Boeing Alert Service This paragraph restates the optional action
Accordingly, under the authority Bulletin 737–53A1279, Revision 1, dated provided in paragraph (j) of AD 2011–23–05,
delegated to me by the Administrator, September 2, 2011, except as required by with a new limitation. Accomplishment of
the FAA amends 14 CFR part 39 as paragraphs (k)(1), (k)(2), and (k)(4) of this AD: the preventive modification before the
follows: Do a high frequency eddy current (HFEC) effective date of this AD, including doing all
sradovich on DSK3TPTVN1PROD with RULES
surface or HFEC hole/edge inspection for any related investigative and applicable
PART 39—AIRWORTHINESS cracking of the 1.04-inch nominal diameter corrective actions, specified in Part 5 of the
DIRECTIVES wire penetration hole in the frame and frame Accomplishment Instructions of Boeing Alert
reinforcement between stringer (S) S–20 and Service Bulletin 737–53A1279, Revision 1,
S–21, in accordance with Part 2 of the dated September 2, 2011, except as required
■ 1. The authority citation for part 39
Accomplishment Instructions of Boeing Alert by paragraph (k)(3) of this AD, terminates the
continues to read as follows: Service Bulletin 737–53A1279, Revision 1, repetitive inspection requirements of
Authority: 49 U.S.C. 106(g), 40113, 44701. dated September 2, 2011. Accomplishment of paragraph (h) of this AD for the modified
VerDate Sep<11>2014 16:11 May 31, 2016 Jkt 238001 PO 00000 Frm 00014 Fmt 4700 Sfmt 4700 E:\FR\FM\01JNR1.SGM 01JNR1](https://thefederalregister.org/doc/81_FR_34976/page/4.svg)
![34876 Federal Register / Vol. 81, No. 105 / Wednesday, June 1, 2016 / Rules and Regulations
Service Bulletin 737–53A1279, Revision 2, flight, repair using a method approved in (w) Material Incorporated by Reference
dated April 21, 2015: Except as required by accordance with the procedures specified in (1) The Director of the Federal Register
paragraph (t)(1) of this AD, at the applicable paragraph (u) of this AD. approved the incorporation by reference
time specified in table 3 of paragraph 1.E., (IBR) of the service information listed in this
‘‘Compliance,’’ of Boeing Alert Service (t) New Requirement of This AD: Exceptions
to Service Bulletin Specifications paragraph under 5 U.S.C. 552(a) and 1 CFR
Bulletin 737–53A1279, Revision 2, dated part 51.
April 21, 2015, do HFEC, LFEC, and detailed (1) Where paragraph 1.E., ‘‘Compliance,’’ of (2) You must use this service information
inspections for cracking in accordance with Boeing Alert Service Bulletin 737–53A1279, as applicable to do the actions required by
‘‘Part 7—INSPECTION OF PREVENTATIVE Revision 2, dated April 21, 2015, refers to a this AD, unless the AD specifies otherwise.
MODIFICATION’’ of the Accomplishment compliance time ‘‘after the Revision 2 date of (3) The following service information was
Instructions of Boeing Alert Service Bulletin this service bulletin,’’ this AD requires approved for IBR on July 6, 2016.
737–53A1279, Revision 2, dated April 21, compliance within the specified compliance (i) Boeing Alert Service Bulletin 737–
2015. Repeat the inspections thereafter at the time after the effective date of this AD. 53A1279, Revision 2, dated April 21, 2015.
applicable interval specified in paragraph (2) The ‘‘Condition’’ column in table 1 and (ii) Reserved.
1.E., ‘‘Compliance,’’ of Boeing Alert Service table 2 of paragraph 1.E., ‘‘Compliance,’’ of (4) The following service information was
Bulletin 737–53A1279, Revision 2, dated Boeing Alert Service Bulletin 737–53A1279, approved for IBR on November 16, 2011 (76
April 21, 2015. If any cracking is found Revision 2, dated April 21, 2015, refers to FR 67343, November 1, 2011).
during any inspection required by this total flight cycles ‘‘at the Revision 2 date of (i) Boeing Alert Service Bulletin 737–
paragraph, before further flight, repair using this service bulletin.’’ However, this AD 53A1279, Revision 1, dated September 2,
a method approved in accordance with the applies to the airplanes with the specified 2011.
procedures specified in paragraph (u) of this total flight cycles as of the effective date of (ii) Reserved.
AD. (5) For Boeing service information
this AD.
identified in this AD, contact Boeing
(r) New Requirement of This AD: Inspections (u) Alternative Methods of Compliance Commercial Airplanes, Attention: Data &
of Preventive Modification for Groups 1–6, (AMOCs) Services Management, P. O. Box 3707, MC
Configuration 2, Airplanes 2H–65, Seattle, WA 98124–2207; telephone
(1) The Manager, Los Angeles ACO, FAA,
For airplanes identified as Groups 1 206–544–5000, extension 1; fax 206–766–
has the authority to approve AMOCs for this
through 6, Configuration 2, in Boeing Alert 5680; Internet https://
AD, if requested using the procedures found www.myboeingfleet.com.
Service Bulletin 737–53A1279, Revision 2, in 14 CFR 39.19. In accordance with 14 CFR
dated April 21, 2015: Except as required by (6) You may view this service information
39.19, send your request to your principal at the FAA, Transport Airplane Directorate,
paragraph (t)(1) of this AD, at the applicable
inspector or local Flight Standards District 1601 Lind Avenue SW., Renton, WA. For
time specified in table 4 or table 6 of
Office, as appropriate. If sending information information on the availability of this
paragraph 1.E., ‘‘Compliance,’’ of Boeing
directly to the manager of the ACO, send it material at the FAA, call 425–227–1221.
Alert Service Bulletin 737–53A1279,
to the attention of the person identified in (7) You may view this service information
Revision 2, dated April 21, 2015, do HFEC,
paragraph (v)(1) of this AD. Information may that is incorporated by reference at the
LFEC, and detailed inspections for cracking
in accordance with ‘‘Part 8—INSPECTION be emailed to: 9-ANM-LAACO-AMOC- National Archives and Records
OF PREVENTATIVE MODIFICATION’’ of the Requests@faa.gov. Administration (NARA). For information on
Accomplishment Instructions of Boeing Alert (2) Before using any approved AMOC, the availability of this material at NARA, call
Service Bulletin 737–53A1279, Revision 2, notify your appropriate principal inspector, 202–741–6030, or go to: http://
dated April 21, 2015. Repeat the inspections or lacking a principal inspector, the manager www.archives.gov/federal-register/cfr/ibr-
thereafter at the applicable interval specified of the local flight standards district office/ locations.html.
in table 4 or table 6 of paragraph 1.E., certificate holding district office. Issued in Renton, Washington, on May 18,
‘‘Compliance,’’ of Boeing Alert Service (3) An AMOC that provides an acceptable 2016.
Bulletin 737–53A1279, Revision 2, dated level of safety may be used for any repair, Dionne Palermo,
April 21, 2015. If any cracking is found modification, or alteration required by this
AD if it is approved by the Boeing Acting Manager, Transport Airplane
during any inspection required by this Directorate, Aircraft Certification Service.
paragraph, before further flight, repair using Commercial Airplanes ODA that has been
a method approved in accordance with the authorized by the Manager, Los Angeles [FR Doc. 2016–12329 Filed 5–31–16; 8:45 am]
procedures specified in paragraph (u) of this ACO, to make those findings. To be BILLING CODE 4910–13–P
AD. approved, the repair method, modification
deviation, or alteration deviation must meet
(s) New Requirement of This AD: Inspections the certification basis of the airplane and the
of Preventive Modification for Groups 4–6,
DEPARTMENT OF TRANSPORTATION
approval must specifically refer to this AD.
Configuration 1, Airplanes (4) AMOCs approved for the ADs in Federal Aviation Administration
For airplanes identified as Groups 4 paragraphs (u)(4)(i) through (u)(4)(iii) of this
through 6, Configuration 1, in Boeing Alert AD are approved as AMOCs for the
14 CFR Part 39
Service Bulletin 737–53A1279, Revision 2, corresponding provisions of this AD.
dated April 21, 2015: At the applicable time (i) AD 2009–02–06, Amendment 39–15796 [Docket No. FAA–2015–8465; Directorate
specified in table 5 of paragraph 1.E., (74 FR 10469, March 11, 2009). Identifier 2014–NM–239–AD; Amendment
‘‘Compliance,’’ of Boeing Alert Service (ii) AD 2009–02–06 R1, Amendment 39– 39–18535; AD 2016–11–08]
Bulletin 737–53A1279, Revision 2, dated 16015 (74 FR 45979, September 8, 2009).
April 21, 2015, except as required by (iii) AD 2011–23–05. RIN 2120–AA64
paragraph (t)(1) of this AD: Do HFEC and
detailed inspections for cracking in
(v) Related Information Airworthiness Directives; Airbus
accordance with ‘‘Part 7—INSPECTION OF (1) For more information about this AD, Defense and Space S.A. (Formerly
PREVENTATIVE MODIFICATION’’ of the contact Galib Abumeri, Aerospace Engineer, Known as Construcciones
Accomplishment Instructions of Boeing Alert Airframe Branch, ANM–120L, FAA, Los Aeronauticas, S.A.)
Angeles ACO, 3960 Paramount Boulevard,
sradovich on DSK3TPTVN1PROD with RULES
Service Bulletin 737–53A1279, Revision 2,
dated April 21, 2015. Repeat the inspections Lakewood, CA 90712–4137; phone: 562–627– AGENCY: Federal Aviation
thereafter at the applicable time specified in 5324; fax: 562–627–5210; email: Administration (FAA), Department of
paragraph 1.E., ‘‘Compliance,’’ of Boeing galib.abumeri@faa.gov. Transportation (DOT).
Alert Service Bulletin 737–53A1279, (2) Service information identified in this ACTION: Final rule.
Revision 2, dated April 21, 2015. If any AD that is not incorporated by reference is
cracking is found during any inspection available at the addresses specified in SUMMARY: We are superseding
required by this paragraph, before further paragraphs (w)(5) and (w)(6) of this AD. Airworthiness Directive (AD) 2001–12–
VerDate Sep<11>2014 16:11 May 31, 2016 Jkt 238001 PO 00000 Frm 00016 Fmt 4700 Sfmt 4700 E:\FR\FM\01JNR1.SGM 01JNR1](https://thefederalregister.org/doc/81_FR_34976/page/6.svg)
Document Created: 2018-02-08 07:26:51
Document Modified: 2018-02-08 07:26:51
| 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 July 6, 2016. | |
| Contact | Galib Abumeri, Aerospace Engineer, Airframe Branch, ANM-120L, FAA, Los Angeles Aircraft Certification Office (ACO), 3960 Paramount Boulevard, Lakewood, CA 90712-4137; phone: 562-627-5324; fax: 562-627-5210; email: [email protected] | |
| FR Citation | 81 FR 34871 | |
| RIN Number | 2120-AA64 | |
| CFR Associated | Air Transportation; Aircraft; Aviation Safety; Incorporation by Reference and Safety |
2025 Federal Register | Disclaimer | Privacy Policy
USC | CFR | eCFR