Airworthiness Directives; The Boeing Company Airplanes, 80242-80247 [2015-30881]

Download as PDF 80242 Federal Register / Vol. 80, No. 247 / Thursday, December 24, 2015 / Rules and Regulations modification Number 55128S18242; or P/N F2511373420000, post-modification Number 55128S18242) of the cockpit instrument panel does not constitute terminating action for the repetitive inspections required by paragraph (g) of this AD. (ii) If, during the inspection required by paragraph (h)(2) of this AD, any cracking is found in bracket No. 7 of the cockpit instrument panel: Although Airbus Service Bulletin A330–25–3538, Revision 02, dated April 24, 2014; and Airbus Service Bulletin A340–25–4351, Revision 01, dated January 31, 2014; specify to contact Airbus for repair instructions, and specify that action as ‘‘RC’’ (Required for Compliance), repair the cracking before further flight using a repair method approved by the Manager, International Branch, ANM–116, Transport Airplane Directorate, FAA; or the European Aviation Safety Agency (EASA); or Airbus’s EASA Design Organization Approval (DOA). (i) Optional Terminating Modification for Paragraph (g) of This AD Modifying an airplane by replacing bracket No. 6 of the cockpit instrument panel with a new, reinforced bracket, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A330–25–3548, dated October 31, 2013; or Airbus Service Bulletin A340–25–4354, dated October 31, 2013; as applicable; terminates the repetitive inspections required by paragraph (g) of this AD. tkelley on DSK3SPTVN1PROD with RULES (j) Credit for Previous Actions This paragraph provides credit for actions required by paragraphs (g) and (h) of this AD, if those actions were performed before the effective date of this AD using the service information identified in paragraph (j)(1), (j)(2), or (j)(3) of this AD, which is not incorporated by reference in this AD. (1) Airbus Service Bulletin A330–25–3538, dated September 10, 2013. (2) Airbus Service Bulletin A330–25–3538, Revision 01, dated April 24, 2014. (3) Airbus Service Bulletin A340–25–4351, dated September 10, 2014. (k) Other FAA AD Provisions The following provisions also apply to this AD: (1) Alternative Methods of Compliance (AMOCs): The Manager, International Branch, ANM–116, Transport Airplane Directorate, 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 International Branch, send it to ATTN: Vladimir Ulyanov, Aerospace Engineer, International Branch, ANM–116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057–3356; telephone 425–227–1138; fax 425–227–1149. Information may be emailed to: 9-ANM-116AMOC-REQUESTS@faa.gov. 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 VerDate Sep<11>2014 17:12 Dec 23, 2015 Jkt 238001 district office. The AMOC approval letter must specifically reference this AD. (2) Contacting the Manufacturer: For any requirement in this AD to obtain corrective actions from a manufacturer, the action must be accomplished using a method approved by the Manager, International Branch, ANM– 116, Transport Airplane Directorate, FAA; or the EASA; or Airbus’s EASA DOA. If approved by the DOA, the approval must include the DOA-authorized signature. (3) Required for Compliance (RC): Except as required by paragraph (h)(2)(ii) of this AD, if Airbus Service Bulletin A330–25–3538, Revision 02, dated April 24, 2014; or Airbus Service Bulletin A340–25–4351, Revision 01, dated January 31, 2014; contain procedures or tests that are identified as RC, those procedures and tests must be done to comply with this AD; any procedures and tests that are not identified as RC are recommended. Those procedures and tests that are not identified as RC may be deviated from, using accepted methods in accordance with the operators maintenance or inspection program without obtaining approval of an AMOC, provided the procedures and tests identified as RC can be done and the airplane can be put back in an airworthy condition. Any substitutions or changes to procedures or tests identified as RC require approval of an AMOC. (l) Related Information (1) Refer to Mandatory Continuing Airworthiness Information (MCAI) EASA Airworthiness Directive 2014–0127, dated May 15, 2014, for related information. This MCAI may be found in the AD docket on the Internet at http://www.regulations.gov/ #!documentDetail;D=FAA-2015-0083-0002. (2) Service information identified in this AD that is not incorporated by reference is available at the addresses specified in paragraphs (m)(3) and (m)(4) of this AD. (m) 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 this AD specifies otherwise. (i) Airbus Service Bulletin A330–25–3538, Revision 02, dated April 24, 2014. (ii) Airbus Service Bulletin A330–25–3548, dated October 31, 2013. (iii) Airbus Service Bulletin A340–25– 4351, Revision 01, dated January 31, 2014. (iv) Airbus Service Bulletin A340–25– 4354, dated October 31, 2013. (3) For service information identified in this AD, contact Airbus SAS, Airworthiness Office—EAL, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 93 45 80; email airworthiness.A330-A340@airbus.com; Internet http://www.airbus.com. (4) You may view this service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For information on the availability of this material at the FAA, call 425–227–1221. (5) You may view this service information that is incorporated by reference at the PO 00000 Frm 00036 Fmt 4700 Sfmt 4700 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/ibrlocations.html. Issued in Renton, Washington, on December 9, 2015. Michael Kaszycki, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2015–31714 Filed 12–23–15; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2015–0828; Directorate Identifier 2014–NM–146–AD; Amendment 39–18341; AD 2015–25–03] RIN 2120–AA64 Airworthiness Directives; The Boeing Company Airplanes Federal Aviation Administration (FAA), DOT. ACTION: Final rule. AGENCY: We are superseding Airworthiness Directive (AD) 2013–23– 03, which applies to certain The Boeing Company Model 747–100, 747–100B, 747–100B SUD, 747–200B, 747–200C, 747–200F, 747–300, 747–400, 747– 400D, 747–400F, and 747SR series airplanes. AD 2013–23–03 required a detailed inspection of certain attach fittings for a cylindrical defect, and replacement if necessary. For certain airplanes, this new AD requires new inspections of the inboard actuator attach fittings for machining defects, and overhaul or replacement if necessary. This new AD also limits the compliance time for doing the replacement for certain other airplanes. This AD was prompted by a report that a machining defect was also found on some of the actuator assemblies inspected during manufacture. This defect could lead to fatigue cracking and subsequent fracture. We are issuing this AD to detect and correct defective inboard actuator attach fittings which, combined with loss of the outboard actuator load path, could result in uncontrolled retraction of the outboard flap, damage to flight control systems, and consequent reduced controllability of the airplane. DATES: This AD is effective January 28, 2016. The Director of the Federal Register approved the incorporation by reference SUMMARY: E:\FR\FM\24DER1.SGM 24DER1 Federal Register / Vol. 80, No. 247 / Thursday, December 24, 2015 / Rules and Regulations of a certain publication listed in this AD as of January 28, 2016. The Director of the Federal Register approved the incorporation by reference of a certain other publication listed in this AD as of November 29, 2013 (78 FR 68345, November 14, 2013). ADDRESSES: For service information identified in this AD, contact Boeing Commercial Airplanes, Attention: Data & Services Management, P.O. Box 3707, MC 2H–65, Seattle, WA 98124–2207; telephone 206–544–5000, extension 1; fax 206–766–5680; Internet https:// www.myboeingfleet.com. You may view this referenced service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For information on the availability of this material at the FAA, call 425–227–1221. It is also available on the Internet at https:// www.regulations.gov by searching for and locating Docket No. FAA–2015– 0828. Examining the AD Docket You may examine the AD docket on the Internet at http:// www.regulations.govby searching for and locating Docket No. FAA–2015– 0828; 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: Nathan Weigand, Aerospace Engineer, Airframe Branch, ANM–120S, FAA, Seattle Aircraft Certification Office, 1601 Lind Avenue SW., Renton, WA 98057–3356; phone: 425–917–6428; fax: 425–917–6590; email: nathan.p.weigand@faa.gov. SUPPLEMENTARY INFORMATION: 20178). The NPRM was prompted by a report that a machining defect was also found on some of the actuator assemblies inspected during manufacture. The NPRM proposed to continue to require doing a detailed inspection of certain attach fittings for a cylindrical defect and replacing if necessary. This defect could lead to fatigue cracking and subsequent fracture. For certain airplanes, the NPRM proposed to mandate new inspections of the inboard actuator attach fittings for machining defects, and overhaul or replacement, if necessary. The NPRM also proposed to limit the compliance time for doing the replacement for certain other airplanes. We are issuing this AD to detect and correct defective inboard actuator attach fittings which, combined with loss of the outboard actuator load path, could result in uncontrolled retraction of the outboard flap, damage to flight control systems, and consequent reduced controllability 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 (80 FR 20178, April 15, 2015) and the FAA’s response to each comment. tkelley on DSK3SPTVN1PROD with RULES Discussion Request to Add Terminating Action Boeing asked that we revise the NPRM (80 FR 20178, April 15, 2015) to specify that no additional action is required for a wall thickness of 0.140 inch or greater with no machining defect present, as also provided in Table 1 of Boeing Alert Service Bulletin 747– 57A2443, Revision 1, dated June 23, 2014. We agree with the commenter that no additional action is required for a wall thickness of 0.140 inch or greater with no machining defect present. However, we do not agree with the request to revise the AD because if this condition exists, no action is required by this AD. Only actions that are required to address the identified unsafe condition are specified in this AD. We have made no change to the AD in this regard. We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 to supersede AD 2013–23–03, Amendment 39–17658 (78 FR 68345, November 14, 2013). AD 2013–23–03 applied to certain The Boeing Company Model 747–100, 747–100B, 747–100B SUD, 747–200B, 747–200C, 747–200F, 747–300, 747–400, 747–400D, 747– 400F, and 747SR series airplanes. The NPRM published in the Federal Register on April 15, 2015 (80 FR Request to Revise Certain Requirements Paragraph (k) of the proposed AD (80 FR 20178, April 15, 2015) would have affected certain inboard actuator attach fittings that were inspected using Boeing Alert Service Bulletin 747– 57A2443, dated September 12, 2013. United Airlines (UAL) requested that we remove this inspection criterion. UAL noted that there was no requirement to identify the actuators; therefore, operators would not be likely to VerDate Sep<11>2014 17:12 Dec 23, 2015 Jkt 238001 PO 00000 Frm 00037 Fmt 4700 Sfmt 4700 80243 positively identify them. UAL added that actuators are not likely to be tracked in position, and could have been moved between airplanes as a result of maintenance. UAL also stated that, in general, it would be better if the AD as a whole was worded not to depend on a record of previous inspection accomplishment, but rather on parts identification. We acknowledge the commenter’s concerns. We realize that paragraph (k) of this AD is predicated on the fact that operators kept records from the inspection specified in Boeing Alert Service Bulletin 747–57A2443, dated September 12, 2013. The intent of this AD is to either replace inboard actuator attach fittings having part number (P/N) 65B08564–7, or to inspect P/N 65B08564–7 for cylindrical defects, machining defects, and wall thickness, and accomplish applicable corrective actions. For that reason we have changed the introductory text of paragraph (k) of this AD so that it applies to airplanes on which doing the detailed inspection required by paragraph (h)(1) of this AD was done before the effective date of this AD and a cylindrical defect was found but a replacement was not done. We have also revised paragraph (k)(1) of this AD to require an ultrasonic inspection to determine the minimum thickness or mechanically determine the minimum thickness and to allow a records review for the inspections. This change ensures all inspections are done on airplanes with P/N 65B08564–7 that did not replace P/N 65B08564–7 after complying with AD 2013–23–03, Amendment 39–17658 (78 FR 68345, November 14, 2013). To address airplanes on which inboard actuator attach fittings were replaced after complying with paragraph (h)(1) of AD 2013–23–03, Amendment 39–17658 (78 FR 68345, November 14, 2013), we have added new paragraph (m) to this AD, which specifies that for airplanes on which the detailed inspection required by paragraph (h)(1) of this AD is done before the effective date of this AD and the inboard actuator attach fitting has been replaced since that inspection, the inspection to determine the part number specified in paragraph (g) of this AD must be done within 90 days after the effective date of this AD, and the applicable actions specified in paragraphs (h), (i), and (j) of this AD must be done within the applicable times specified in paragraphs (h), (i), and (j) of this AD. We have also added a records review as an option if records are available that can conclusively determine the part number. We E:\FR\FM\24DER1.SGM 24DER1 80244 Federal Register / Vol. 80, No. 247 / Thursday, December 24, 2015 / Rules and Regulations redesignated subsequent paragraphs accordingly. Request to Add Inspection UAL stated that the actions specified in paragraph (l) of the proposed AD (80 FR 20178, April 15, 2015) would also depend on the record of findings from inspections made in accordance with AD 2013–23–03, Amendment 39–17658 (78 FR 68345, November 14, 2013). UAL added that there was no AD requirement to record these findings. UAL noted that operators conducted the inspections and took actions that were required. UAL stated that it would be better to call out a new inspection in the AD to determine which condition the actuator is in, and then take action as appropriate. We acknowledge the commenter’s concerns. We have revised paragraph (l) of this AD to specify that no actuator attach fitting having P/N 65B08564–7 may be installed on any airplane unless the inspection specified in paragraph (h)(1) of this AD is done prior to installation and the applicable actions specified in paragraphs (i) and (j) of this AD are done within the applicable times specified in paragraphs (i) and (j) of this AD. We have also added a records review as an option if records are available that can conclusively determine if the actions have been done. Change to Paragraph (h)(2) of the Proposed AD ((80 FR 20178, April 15, 2015) We have revised paragraph (h)(2) of this AD by referring to Boeing Alert Service Bulletin 747–57A2443, Revision 1, dated June 23, 2014, as an appropriate source of service information for accomplishing the required actions. 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 change described previously and minor editorial changes. We have determined that these minor changes: • Are consistent with the intent that was proposed in the NPRM (80 FR 20178, April 15, 2015) for correcting the unsafe condition; and • Do not add any additional burden upon the public than was already proposed in the NPRM (80 FR 20178, April 15, 2015). We also determined that this change 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 747–57A2443, dated September 12, 2013; and Boeing Alert Service Bulletin 747–57A2443, Revision 1, dated June 23, 2014. The service information describes procedures for new inspections of the inboard actuator attach fittings for machining defects, and overhaul or replacement, if necessary. This service information is reasonably available because the interested parties have access to it through their normal course of business or by the means identified in the ADDRESSES section. Costs of Compliance We estimate that this AD affects 184 airplanes of U.S. registry. We estimate the following costs to comply with this AD: ESTIMATED COSTS Cost per product Labor cost Retained inspection for part number in AD 2013-23–03, Amendment 39-17658 (78 FR 68345, November 14, 2013). New proposed inspections for machining defect. Replacement for airplanes without any defect 7 work-hours × $85 per hour = $595 ............. $0 $595 $109,480 8 work-hours × $85 per hour = $680 ............. 0 680 $125,120 6 work-hours × $85 per hour = $510 ............. 13,720 14,230 tkelley on DSK3SPTVN1PROD with RULES 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 17:12 Dec 23, 2015 Jkt 238001 $14,230 per airplane 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. We have received no definitive data that would enable us to provide a cost estimate for the on-condition actions specified in this AD. VerDate Sep<11>2014 Parts cost Cost on U.S. operators Action (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. 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 List of Subjects in 14 CFR Part 39 PO 00000 Frm 00038 Fmt 4700 Sfmt 4700 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 1. The authority citation for part 39 continues to read as follows: ■ Authority: 49 U.S.C. 106(g), 40113, 44701. E:\FR\FM\24DER1.SGM 24DER1 Federal Register / Vol. 80, No. 247 / Thursday, December 24, 2015 / Rules and Regulations § 39.13 [Amended] 2. The FAA amends § 39.13 by removing Airworthiness Directive (AD) 2013–23–03, Amendment 39–17658 (78 FR 68345, November 14, 2013), and adding the following new AD: ■ 2015–25–03 The Boeing Company: Amendment 39–18341; Docket No. FAA–2015–0828; Directorate Identifier 2014–NM–146–AD. (a) Effective Date This AD is effective January 28, 2016. (b) Affected ADs This AD replaces AD 2013–23–03, Amendment 39–17658 (78 FR 68345, November 14, 2013). (c) Applicability This AD applies to The Boeing Company Model 747–100, 747–100B, 747–100B SUD, 747–200B, 747–200C, 747–200F, 747–300, 747–400, 747–400D, 747–400F, and 747SR series airplanes, certificated in any category, as identified in Boeing Alert Service Bulletin 747–57A2443, Revision 1, dated June 23, 2014. (d) Subject Air Transport Association (ATA) of America Code 57, Wings. (e) Unsafe Condition This AD was prompted by a report of the fracture of an inboard actuator attach fitting of the outboard flap. An inspection of the attach fitting revealed that it was incorrectly machined with a cylindrical profile instead of a conical profile, resulting in reduced wall thickness. A machining defect was also found on some actuator assemblies inspected during manufacture at the point where the tapered machining transitioned to the hemispherical machining at the top of the inner surface. This defect could lead to fatigue cracking and subsequent fracture. We are issuing this AD to detect and correct defective inboard actuator attach fittings which, combined with loss of the outboard actuator load path, could result in uncontrolled retraction of the outboard flap, damage to flight control systems, and consequent reduced controllability of the airplane. tkelley on DSK3SPTVN1PROD with RULES (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Retained Part Number Inspection With Revised Service Information This paragraph restates the requirements of paragraph (g) of AD 2013–23–03, Amendment 39–17658 (78 FR 68345, November 14, 2013), with revised service information. Within 90 days after November 29, 2013 (the effective date of AD 2013–23– 03): Inspect to determine the part number of the inboard actuator attach fittings of the outboard flaps, in accordance with Part 1 of the Accomplishment Instructions of Boeing Alert Service Bulletin 747–57A2443, dated September 12, 2013; or Boeing Alert Service Bulletin 747–57A2443, Revision 1, dated VerDate Sep<11>2014 17:12 Dec 23, 2015 Jkt 238001 June 23, 2014. As of the effective date of this AD, only Boeing Alert Service Bulletin 747– 57A2443, Revision 1, dated June 23, 2014, may be used. (h) Retained Actions for Certain Attach Fittings With Revised Service Information This paragraph restates the requirements of paragraph (h) of AD 2013–23–03, Amendment 39–17658 (78 FR 68345, November 14, 2013), with revised service information. If, during the inspection required by paragraph (g) of this AD, any inboard actuator attach fitting having part number (P/N) 65B08564–7 is found, before further flight, do the actions specified in paragraph (h)(1) or (h)(2) of this AD. (1) Do a detailed inspection of the inboard actuator attach fitting for a cylindrical defect, in accordance with Part 2 of the Accomplishment Instructions of Boeing Alert Service Bulletin 747–57A2443, dated September 12, 2013; or Boeing Alert Service Bulletin 747–57A2443, Revision 1, dated June 23, 2014. As of the effective date of this AD, only Boeing Alert Service Bulletin 747– 57A2443, Revision 1, dated June 23, 2014, may be used. For airplanes on which the detailed inspection is done before the effective date of this AD: If any cylindrical defect is found, before further flight, do the actions specified in paragraph (h)(1)(i) or (h)(1)(ii) of this AD. (i) Do a minimum thickness inspection of the inboard actuator attach fitting to determine minimum wall thickness of the actuator fitting assembly, in accordance with Part 3 of the Accomplishment Instructions of Boeing Alert Service Bulletin 747–57A2443, dated September 12, 2013; or Boeing Alert Service Bulletin 747–57A2443, Revision 1, dated June 23, 2014. If the minimum thickness of the wall is less than 0.130 inch: Before further flight, replace the inboard actuator attach fitting of the outboard flap, in accordance with Part 4 of the Accomplishment Instructions of Boeing Alert Service Bulletin 747–57A2443, dated September 12, 2013. (ii) Replace the inboard actuator attach fitting of the outboard flap, in accordance with Part 4 of the Accomplishment Instructions of Boeing Alert Service Bulletin 747–57A2443, dated September 12, 2013. (2) Replace the inboard actuator attach fitting of the outboard flap, in accordance with Part 4 of the Accomplishment Instructions of Boeing Alert Service Bulletin 747–57A2443, dated September 12, 2013; or Boeing Alert Service Bulletin 747–57A2443, Revision 1, dated June 23, 2014. As of the effective date of this AD, only Boeing Alert Service Bulletin 747–57A2443, Revision 1, dated June 23, 2014, may be used. (i) New Actions for Certain Airplanes on Which Any Cylindrical Defect Is Found For airplanes on which the detailed inspection required by paragraph (h)(1) of this AD is done on or after the effective date of this AD: If any cylindrical defect is found during any inspection required by paragraph (h)(1) of this AD, before further flight, do the actions specified in paragraph (i)(1) or (i)(2) of this AD. (1) Determine the minimum wall thickness of the actuator attach fitting either by doing PO 00000 Frm 00039 Fmt 4700 Sfmt 4700 80245 an ultrasonic inspection or by mechanically measuring the thickness and do a detailed inspection of the inner conical section to determine if the machining defect is present, in accordance with Part 3 of the Accomplishment Instructions of Boeing Alert Service Bulletin 747–57A2443, Revision 1, dated June 23, 2014. (i) If the minimum thickness of the wall is less than 0.130 inch: Before further flight, replace the inboard actuator attach fitting of the outboard flap, in accordance with Part 4 of the Accomplishment Instructions of Boeing Alert Service Bulletin 747–57A2443, Revision 1, dated June 23, 2014. (ii) If the minimum thickness of the wall is 0.140 inch or greater and the machining defect is present, before further flight, do the actions specified in paragraph (i)(1)(ii)(A) or (i)(1)(ii)(B) of this AD. (A) Overhaul the inboard actuator attach fitting of the outboard flap, in accordance with Part 5 of the Accomplishment Instructions of Boeing Alert Service Bulletin 747–57A2443, Revision 1, dated June 23, 2014. (B) Replace the inboard actuator attach fitting of the outboard flap, in accordance with Part 4 of the Accomplishment Instructions of Boeing Alert Service Bulletin 747–57A2443, Revision 1, dated June 23, 2014. (iii) If the minimum thickness of the wall is 0.130 inch or greater and less than 0.140 inch and the machining defect is not present, within 48 months or 3,000 flight cycles after the effective date of this AD, whichever occurs first, replace the inboard actuator attach fitting of the outboard flap, in accordance with Part 4 of the Accomplishment Instructions of Boeing Alert Service Bulletin 747–57A2443, Revision 1, dated June 23, 2014. (iv) If the minimum thickness of the wall is 0.130 inch or greater and less than 0.140 inch and the machining defect is present, before further flight, replace the inboard actuator attach fitting of the outboard flap, in accordance with Part 4 of the Accomplishment Instructions of Boeing Alert Service Bulletin 747–57A2443, Revision 1, dated June 23, 2014. (2) Replace the inboard actuator attach fitting of the outboard flap, in accordance with Part 4 of the Accomplishment Instructions of Boeing Alert Service Bulletin 747–57A2443, Revision 1, dated June 23, 2014. (j) New Actions for Airplanes on Which No Cylindrical Defects Are Found If no cylindrical defect is found during any inspection required by paragraph (h)(1) of this AD, within 24 months after the effective date of this AD, do the actions specified in paragraph (j)(1) or (j)(2) of this AD. (1) Determine the minimum wall thickness of the actuator attach fitting either by doing an ultrasonic inspection or by mechanically measuring the thickness and do a detailed inspection of the inner conical section to determine if the machining defect is present, in accordance with Part 3 of the Accomplishment Instructions of Boeing Alert Service Bulletin 747–57A2443, Revision 1, dated June 23, 2014. E:\FR\FM\24DER1.SGM 24DER1 80246 Federal Register / Vol. 80, No. 247 / Thursday, December 24, 2015 / Rules and Regulations tkelley on DSK3SPTVN1PROD with RULES (i) If the minimum thickness of the wall is less than 0.130 inch: Before further flight, replace the inboard actuator attach fitting of the outboard flap, in accordance with Part 4 of the Accomplishment Instructions of Boeing Alert Service Bulletin 747 57A2443, Revision 1, dated June 23, 2014. (ii) If the minimum thickness of the wall is 0.140 inch or greater and the machining defect is present, before further flight, do the actions specified in paragraph (j)(1)(ii)(A) or (j)(1)(ii)(B) of this AD. (A) Overhaul the inboard actuator attach fitting of the outboard flap, in accordance with Part 5 of the Accomplishment Instructions of Boeing Alert Service Bulletin 747–57A2443, Revision 1, dated June 23, 2014. (B) Replace the inboard actuator attach fitting of the outboard flap, in accordance with Part 4 of the Accomplishment Instructions of Boeing Alert Service Bulletin 747–57A2443, Revision 1, dated June 23, 2014. (iii) If the minimum thickness of the wall is 0.130 inch or greater and less than 0.140 inch and the machining defect is not present, within 48 months or 3,000 flight cycles after the effective date of this AD, whichever occurs first, replace the inboard actuator attach fitting of the outboard flap, in accordance with Part 4 of the Accomplishment Instructions of Boeing Alert Service Bulletin 747–57A2443, Revision 1, dated June 23, 2014. (iv) If the minimum thickness of the wall is 0.130 inch or greater and less than 0.140 inch and the machining defect is present, before further flight, replace the inboard actuator attach fitting of the outboard flap, in accordance with Part 4 of the Accomplishment Instructions of Boeing Alert Service Bulletin 747–57A2443, Revision 1, dated June 23, 2014 (2) Replace the inboard actuator attach fitting of the outboard flap, in accordance with Part 4 of the Accomplishment Instructions of Boeing Alert Service Bulletin 747–57A2443, Revision 1, dated June 23, 2014. (k) New Inspection or Replacement for Certain Fittings That Were Previously Inspected For airplanes on which the detailed inspection required by paragraph (h)(1) of this AD is done before the effective date of this AD, except as required by paragraph (m) of this AD: If any cylindrical defect is found during any inspection required by paragraph (h)(1) of this AD and the replacement of the inboard actuator attach fitting of the outboard flap was not done as specified in Part 4 of the Accomplishment Instructions of Boeing Alert Service Bulletin 747–57A2443, within 24 months after the effective date of this AD, do the actions specified in paragraph (k)(1) or (k)(2) of this AD. (1) Do a detailed inspection of the inner conical section for machining defects and do an ultrasonic inspection to determine the minimum thickness or mechanically determine the minimum thickness, in accordance with Part 3 of the Accomplishment Instructions of Boeing Alert Service Bulletin 747–57A2443, Revision 1, VerDate Sep<11>2014 17:12 Dec 23, 2015 Jkt 238001 dated June 23, 2014. A review of airplane maintenance records, if available, is acceptable to determine the wall thickness and to determine if there are machining defects, provided wall thickness and machining defects can be positively determined from the records review. (i) If any machining defect is found and the minimum thickness of the wall is 0.140 inch or greater: Before further flight, do the actions specified in paragraph (k)(1)(i)(A) or (k)(1)(i)(B) of this AD. (A) Overhaul the inboard actuator attach fitting of the outboard flap, in accordance with Part 5 of the Accomplishment Instructions of Boeing Alert Service Bulletin 747–57A2443, Revision 1, dated June 23, 2014. (B) Replace the inboard actuator attach fitting of the outboard flap, in accordance with Part 4 of the Accomplishment Instructions of Boeing Alert Service Bulletin 747–57A2443, Revision 1, dated June 23, 2014. (ii) If any machining defect is found and the minimum thickness of the wall is 0.130 inch or greater and less than 0.140 inch: Before further flight, replace the inboard actuator attach fitting of the outboard flap, in accordance with Part 4 of the Accomplishment Instructions of Boeing Alert Service Bulletin 747–57A2443, Revision 1, dated June 23, 2014. (iii) If no machining defect is found and the minimum thickness of the wall is 0.130 inch or greater and less than 0.140 inch: Within 48 months or 3,000 flight cycles after the effective date of this AD, whichever occurs first, replace the inboard actuator attach fitting of the outboard flap, in accordance with Part 4 of the Accomplishment Instructions of Boeing Alert Service Bulletin 747–57A2443, Revision 1, dated June 23, 2014. (iv) If a machining defect is or is not found and the minimum thickness of the wall is less than 0.130 inch: Before further flight, replace the inboard actuator attach fitting of the outboard flap, in accordance with Part 4 of the Accomplishment Instructions of Boeing Alert Service Bulletin 747–57A2443, Revision 1, dated June 23, 2014. (2) Replace the inboard actuator attach fitting of the outboard flap, in accordance with Part 4 of the Accomplishment Instructions of Boeing Alert Service Bulletin 747–57A2443, Revision 1, dated June 23, 2014. (l) Parts Installation Limitation As of the effective date of this AD, no actuator attach fitting having P/N 65B08564– 7 may be installed on any airplane unless the inspection specified in paragraph (h)(1) of this AD is done prior to installation and the applicable actions specified in paragraphs (i) and (j) of this AD are done within the applicable times specified in paragraphs (i) and (j) of this AD. A review of airplane maintenance records, if available, is acceptable to determine if the inspection and applicable actions have been done, provided the inspection and actions can be positively determined from the records review. PO 00000 Frm 00040 Fmt 4700 Sfmt 4700 (m) Action for Parts Installed After AD 2013–23–03, Amendment 39–17658 (78 FR 68345, November 14, 2013) Was Accomplished For airplanes on which the detailed inspection required by paragraph (h)(1) of this AD is done before the effective date of this AD and the inboard actuator attach fitting was replaced since that inspection: Within 90 days after the effective date of this AD, inspect to determine the part number of the inboard actuator attach fittings of the outboard flaps and, for inboard actuator attach fittings having P/N 65B08564–7, do the applicable actions specified in paragraphs (h), (i), and (j) of this AD within the applicable times specified in paragraphs (h), (i), and (j) of this AD. A review of airplane maintenance records, if available, is acceptable to determine the part number, provided the part number can be positively determined from the records review. (n) Alternative Methods of Compliance (AMOCs) (1) The Manager, Seattle Aircraft Certification Office (ACO), FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. In accordance with 14 CFR 39.19, send your request to your principal inspector or local Flight Standards District Office, as appropriate. If sending information directly to the manager of the ACO, send it to the attention of the person identified in paragraph (o) of this AD. Information may be emailed to: 9-ANM-Seattle-ACO-AMOCRequests@faa.gov. (2) Before using any approved AMOC, notify your appropriate principal inspector, or lacking a principal inspector, the manager of the local flight standards district office/ certificate holding district office. (3) An AMOC that provides an acceptable level of safety may be used for any repair required by this AD if it is approved by the Boeing Commercial Airplanes Organization Designation Authorization (ODA) that has been authorized by the Manager, Seattle ACO, to make those findings. For a repair method to be approved, the repair must meet the certification basis of the airplane, and the approval must specifically refer to this AD. (4) If any service information contains steps that are identified as RC (Required for Compliance), those steps must be done to comply with this AD; any steps that are not identified as RC are recommended. Those steps that are not identified as RC may be deviated from using accepted methods in accordance with the operator’s maintenance or inspection program without obtaining approval of an AMOC provided the steps identified as RC can be done and the airplane can be put back in an airworthy condition. Any substitutions or changes to steps identified as RC require approval of an AMOC. (5) AMOCs approved for AD 2013–23–03, Amendment 39–17658 (78 FR 68345, November 14, 2013) are approved as AMOCs for the corresponding provisions of this AD. (o) Related Information For more information about this AD, contact Nathan Weigand, Aerospace E:\FR\FM\24DER1.SGM 24DER1 Federal Register / Vol. 80, No. 247 / Thursday, December 24, 2015 / Rules and Regulations Engineer, Airframe Branch, ANM–120S, FAA, Seattle Aircraft Certification Office, 1601 Lind Avenue SW., Renton, WA 98057– 3356; phone: 425–917–6428; fax: 425–917– 6590; email: nathan.p.weigand@faa.gov. (p) 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 January 28, 2016. (i) Boeing Alert Service Bulletin 747– 57A2443, Revision 1, dated June 23, 2014. (ii) Reserved. (4) The following service information was approved for IBR on November 29, 2013 (78 FR 68345, November 14, 2013). (i) Boeing Alert Service Bulletin 747– 57A2443, dated September 12, 2013. (ii) Reserved. (5) For service information identified in this AD, contact Boeing Commercial Airplanes, Attention: Data & Services Management, P. O. Box 3707, MC 2H–65, Seattle, WA 98124–2207; telephone 206– 544–5000, extension 1; fax 206–766–5680; Internet https://www.myboeingfleet.com. (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/ibrlocations.html. Issued in Renton, Washington, on November 24, 2015. Jeffrey E. Duven, Manager, Transport Airplane Directorate,Aircraft Certification Service. [FR Doc. 2015–30881 Filed 12–23–15; 8:45 am] BILLING CODE 4910–13–P COMMODITY FUTURES TRADING COMMISSION 17 CFR Part 1 RIN 3038–AE23 Records of Commodity Interest and Related Cash or Forward Transactions Commodity Futures Trading Commission. ACTION: Final rule. tkelley on DSK3SPTVN1PROD with RULES AGENCY: The Commodity Futures Trading Commission (the ‘‘Commission’’ or ‘‘CFTC’’) is amending Commission Regulation 1.35(a) to: Provide that all records required to be SUMMARY: VerDate Sep<11>2014 17:12 Dec 23, 2015 Jkt 238001 maintained under this regulation must be maintained in a form and manner which permits prompt, accurate and reliable location, access, and retrieval of any particular record, data, or information; clarify that all records, except records of oral and written communications leading to the execution of a commodity interest transaction and related cash or forward transactions, must be kept in a form and manner that allows for identification of a particular transaction; exclude members of designated contract markets (‘‘DCMs’’) and of swap execution facilities (‘‘SEFs’’) that are not registered or required to register with the Commission (‘‘Unregistered Members’’) from the requirements to keep written communications that lead to the execution of a commodity interest transaction and related cash or forward transactions, keep text messages, and keep records in a particular form and manner; and exclude commodity trading advisors (‘‘CTAs’’) from the oral recordkeeping requirement (‘‘Final Rule’’). DATES: Effective December 24, 2015. FOR FURTHER INFORMATION CONTACT: Katherine Driscoll, Associate Chief Counsel, (202) 418–5544, kdriscoll@ cftc.gov; August A. Imholtz III, Special Counsel, (202) 418–5140, aimholtz@ cftc.gov; or Lauren Bennett, Special Counsel, (202) 418–5290, lbennett@ cftc.gov, Division of Swap Dealer and Intermediary Oversight, Commodity Futures Trading Commission, 1155 21st Street NW., Washington, DC 20581. SUPPLEMENTARY INFORMATION: I. Background The Commission amended Regulation 1.35(a) in December 2012 as part of a series of rulemakings intended to integrate certain existing Commission rules more fully with the framework created by the Dodd-Frank Wall Street Reform and Consumer Protection Act for swap dealers and major swap participants (the ‘‘2012 Amendment’’).1 Regulation 1.35(a) requires each futures commission merchant (‘‘FCM’’), retail foreign exchange dealer (‘‘RFED’’), introducing broker (‘‘IB’’), and member of a DCM or of a SEF to keep full, complete, and systematic records of all transactions relating to its business of dealing in commodity interest and related cash or forward transactions.2 The Commodity Exchange Act (‘‘CEA’’) defines ‘‘member’’ as an individual, 1 See Adaptation of Regulations to Incorporate Swaps—Records of Transactions, 77 FR 75523 (December 21, 2012) (‘‘2012 Amendment Adopting Release’’). 2 17 CFR 1.35(a)(1). PO 00000 Frm 00041 Fmt 4700 Sfmt 4700 80247 association, partnership, corporation, or trust—(i) owning or holding membership in, or admitted to membership representation on, the registered entity 3 or derivatives transaction execution facility; or (ii) having trading privileges on the registered entity or derivatives transaction execution facility.4 Regulation 1.35(a) requires FCMs, RFEDs, IBs, and members of a DCM or of a SEF to keep records of written communications that lead to the execution of a commodity interest transaction and related cash or forward transactions. Additionally, Regulation 1.35(a) includes a requirement to keep records of certain oral communications, which applies to each FCM, RFED, large IB (defined as an IB that has generated over $5 million in aggregate gross revenues over the preceding three years from its activities as an IB), and member of a DCM or of a SEF that is registered or required to register with the Commission as a floor broker (‘‘FB’’) (only with regard to acting as an agent for a non-affiliated client) or as a CTA.5 Unlike the written recordkeeping requirement that applies to both commodity interest transactions and related cash or forward transactions, the oral recordkeeping requirement is limited to commodity interest transactions.6 The scope of records covered by Regulation 1.35(a) includes communications by telephone, voicemail, facsimile, instant messaging, chat rooms, electronic mail, mobile device, or other digital or electronic media.7 These communications include text messages. Regulation 1.35(a) also mandates that all records be kept in a form and manner identifiable and searchable by transaction. 3 The term ‘‘registered entity’’ is defined in CEA section 1a(40) to include both DCMs and SEFs. See CEA sections 1a(40)(A) (DCMs) and (D) (SEFs). 4 7 U.S.C. 1a(34). 5 As stated in the 2012 Amendment, the oral recordkeeping requirement in Regulation 1.35(a) does not apply to: (i) Oral communications that lead solely to the execution of a related cash or forward transaction; (ii) oral communications provided or received by a floor broker that do not lead to the purchase or sale for any person other than the floor broker of any commodity for future delivery, security futures product, swap, or commodity option authorized under section 4c of the Commodity Exchange Act; (iii) an introducing broker that has generated over the preceding three years $5 million or less in aggregate gross revenues from its activities as an introducing broker; (iv) a floor trader; (v) a commodity pool operator; (vi) a swap dealer; (vii) a major swap participant; or (viii) a member of a DCM or SEF that is not registered or required to be registered with the Commission in any capacity. 17 CFR 1.35(a)(1). 6 17 CFR 1.35(a)(1). 7 Id. E:\FR\FM\24DER1.SGM 24DER1

Agencies

[Federal Register Volume 80, Number 247 (Thursday, December 24, 2015)]
[Rules and Regulations]
[Pages 80242-80247]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2015-30881]


-----------------------------------------------------------------------

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2015-0828; Directorate Identifier 2014-NM-146-AD; 
Amendment 39-18341; AD 2015-25-03]
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) 2013-23-03, 
which applies to certain The Boeing Company Model 747-100, 747-100B, 
747-100B SUD, 747-200B, 747-200C, 747-200F, 747-300, 747-400, 747-400D, 
747-400F, and 747SR series airplanes. AD 2013-23-03 required a detailed 
inspection of certain attach fittings for a cylindrical defect, and 
replacement if necessary. For certain airplanes, this new AD requires 
new inspections of the inboard actuator attach fittings for machining 
defects, and overhaul or replacement if necessary. This new AD also 
limits the compliance time for doing the replacement for certain other 
airplanes. This AD was prompted by a report that a machining defect was 
also found on some of the actuator assemblies inspected during 
manufacture. This defect could lead to fatigue cracking and subsequent 
fracture. We are issuing this AD to detect and correct defective 
inboard actuator attach fittings which, combined with loss of the 
outboard actuator load path, could result in uncontrolled retraction of 
the outboard flap, damage to flight control systems, and consequent 
reduced controllability of the airplane.

DATES: This AD is effective January 28, 2016.
    The Director of the Federal Register approved the incorporation by 
reference

[[Page 80243]]

of a certain publication listed in this AD as of January 28, 2016.
    The Director of the Federal Register approved the incorporation by 
reference of a certain other publication listed in this AD as of 
November 29, 2013 (78 FR 68345, November 14, 2013).

ADDRESSES: For service information identified in this AD, contact 
Boeing Commercial Airplanes, Attention: Data & Services Management, 
P.O. Box 3707, MC 2H-65, Seattle, WA 98124-2207; telephone 206-544-
5000, extension 1; fax 206-766-5680; Internet https://www.myboeingfleet.com. You may view this referenced service information 
at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., 
Renton, WA. For information on the availability of this material at the 
FAA, call 425-227-1221. It is also available on the Internet at https://www.regulations.gov by searching for and locating Docket No. FAA-2015-
0828.

Examining the AD Docket

    You may examine the AD docket on the Internet at http://www.regulations.govby searching for and locating Docket No. FAA-2015-
0828; 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: Nathan Weigand, Aerospace Engineer, 
Airframe Branch, ANM-120S, FAA, Seattle Aircraft Certification Office, 
1601 Lind Avenue SW., Renton, WA 98057-3356; phone: 425-917-6428; fax: 
425-917-6590; email: nathan.p.weigand@faa.gov.

SUPPLEMENTARY INFORMATION: 

Discussion

    We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR 
part 39 to supersede AD 2013-23-03, Amendment 39-17658 (78 FR 68345, 
November 14, 2013). AD 2013-23-03 applied to certain The Boeing Company 
Model 747-100, 747-100B, 747-100B SUD, 747-200B, 747-200C, 747-200F, 
747-300, 747-400, 747-400D, 747-400F, and 747SR series airplanes. The 
NPRM published in the Federal Register on April 15, 2015 (80 FR 20178). 
The NPRM was prompted by a report that a machining defect was also 
found on some of the actuator assemblies inspected during manufacture. 
The NPRM proposed to continue to require doing a detailed inspection of 
certain attach fittings for a cylindrical defect and replacing if 
necessary. This defect could lead to fatigue cracking and subsequent 
fracture. For certain airplanes, the NPRM proposed to mandate new 
inspections of the inboard actuator attach fittings for machining 
defects, and overhaul or replacement, if necessary. The NPRM also 
proposed to limit the compliance time for doing the replacement for 
certain other airplanes. We are issuing this AD to detect and correct 
defective inboard actuator attach fittings which, combined with loss of 
the outboard actuator load path, could result in uncontrolled 
retraction of the outboard flap, damage to flight control systems, and 
consequent reduced controllability 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 (80 
FR 20178, April 15, 2015) and the FAA's response to each comment.

Request to Add Terminating Action

    Boeing asked that we revise the NPRM (80 FR 20178, April 15, 2015) 
to specify that no additional action is required for a wall thickness 
of 0.140 inch or greater with no machining defect present, as also 
provided in Table 1 of Boeing Alert Service Bulletin 747-57A2443, 
Revision 1, dated June 23, 2014.
    We agree with the commenter that no additional action is required 
for a wall thickness of 0.140 inch or greater with no machining defect 
present. However, we do not agree with the request to revise the AD 
because if this condition exists, no action is required by this AD. 
Only actions that are required to address the identified unsafe 
condition are specified in this AD. We have made no change to the AD in 
this regard.

Request to Revise Certain Requirements

    Paragraph (k) of the proposed AD (80 FR 20178, April 15, 2015) 
would have affected certain inboard actuator attach fittings that were 
inspected using Boeing Alert Service Bulletin 747-57A2443, dated 
September 12, 2013. United Airlines (UAL) requested that we remove this 
inspection criterion. UAL noted that there was no requirement to 
identify the actuators; therefore, operators would not be likely to 
positively identify them. UAL added that actuators are not likely to be 
tracked in position, and could have been moved between airplanes as a 
result of maintenance. UAL also stated that, in general, it would be 
better if the AD as a whole was worded not to depend on a record of 
previous inspection accomplishment, but rather on parts identification.
    We acknowledge the commenter's concerns. We realize that paragraph 
(k) of this AD is predicated on the fact that operators kept records 
from the inspection specified in Boeing Alert Service Bulletin 747-
57A2443, dated September 12, 2013. The intent of this AD is to either 
replace inboard actuator attach fittings having part number (P/N) 
65B08564-7, or to inspect P/N 65B08564-7 for cylindrical defects, 
machining defects, and wall thickness, and accomplish applicable 
corrective actions. For that reason we have changed the introductory 
text of paragraph (k) of this AD so that it applies to airplanes on 
which doing the detailed inspection required by paragraph (h)(1) of 
this AD was done before the effective date of this AD and a cylindrical 
defect was found but a replacement was not done. We have also revised 
paragraph (k)(1) of this AD to require an ultrasonic inspection to 
determine the minimum thickness or mechanically determine the minimum 
thickness and to allow a records review for the inspections. This 
change ensures all inspections are done on airplanes with P/N 65B08564-
7 that did not replace P/N 65B08564-7 after complying with AD 2013-23-
03, Amendment 39-17658 (78 FR 68345, November 14, 2013).
    To address airplanes on which inboard actuator attach fittings were 
replaced after complying with paragraph (h)(1) of AD 2013-23-03, 
Amendment 39-17658 (78 FR 68345, November 14, 2013), we have added new 
paragraph (m) to this AD, which specifies that for airplanes on which 
the detailed inspection required by paragraph (h)(1) of this AD is done 
before the effective date of this AD and the inboard actuator attach 
fitting has been replaced since that inspection, the inspection to 
determine the part number specified in paragraph (g) of this AD must be 
done within 90 days after the effective date of this AD, and the 
applicable actions specified in paragraphs (h), (i), and (j) of this AD 
must be done within the applicable times specified in paragraphs (h), 
(i), and (j) of this AD. We have also added a records review as an 
option if records are available that can conclusively determine the 
part number. We

[[Page 80244]]

redesignated subsequent paragraphs accordingly.

Request to Add Inspection

    UAL stated that the actions specified in paragraph (l) of the 
proposed AD (80 FR 20178, April 15, 2015) would also depend on the 
record of findings from inspections made in accordance with AD 2013-23-
03, Amendment 39-17658 (78 FR 68345, November 14, 2013). UAL added that 
there was no AD requirement to record these findings. UAL noted that 
operators conducted the inspections and took actions that were 
required. UAL stated that it would be better to call out a new 
inspection in the AD to determine which condition the actuator is in, 
and then take action as appropriate.
    We acknowledge the commenter's concerns. We have revised paragraph 
(l) of this AD to specify that no actuator attach fitting having P/N 
65B08564-7 may be installed on any airplane unless the inspection 
specified in paragraph (h)(1) of this AD is done prior to installation 
and the applicable actions specified in paragraphs (i) and (j) of this 
AD are done within the applicable times specified in paragraphs (i) and 
(j) of this AD. We have also added a records review as an option if 
records are available that can conclusively determine if the actions 
have been done.

Change to Paragraph (h)(2) of the Proposed AD ((80 FR 20178, April 15, 
2015)

    We have revised paragraph (h)(2) of this AD by referring to Boeing 
Alert Service Bulletin 747-57A2443, Revision 1, dated June 23, 2014, as 
an appropriate source of service information for accomplishing the 
required actions.

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 change described previously and minor editorial 
changes. We have determined that these minor changes:
     Are consistent with the intent that was proposed in the 
NPRM (80 FR 20178, April 15, 2015) for correcting the unsafe condition; 
and
     Do not add any additional burden upon the public than was 
already proposed in the NPRM (80 FR 20178, April 15, 2015).
    We also determined that this change 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 747-57A2443, dated 
September 12, 2013; and Boeing Alert Service Bulletin 747-57A2443, 
Revision 1, dated June 23, 2014. The service information describes 
procedures for new inspections of the inboard actuator attach fittings 
for machining defects, and overhaul or replacement, if necessary. This 
service information is reasonably available because the interested 
parties have access to it through their normal course of business or by 
the means identified in the ADDRESSES section.

Costs of Compliance

    We estimate that this AD affects 184 airplanes of U.S. registry.
    We estimate the following costs to comply with this AD:

                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                                                            Cost per
              Action                    Labor cost         Parts cost        product      Cost on U.S. operators
----------------------------------------------------------------------------------------------------------------
Retained inspection for part       7 work-hours x $85                $0            $595  $109,480
 number in AD 2013[dash]23-03,      per hour = $595.
 Amendment 39[dash]17658 (78 FR
 68345, November 14, 2013).
New proposed inspections for       8 work-hours x $85                 0             680  $125,120
 machining defect.                  per hour = $680.
Replacement for airplanes without  6 work-hours x $85            13,720          14,230  $14,230 per airplane
 any defect.                        per hour = $510.
----------------------------------------------------------------------------------------------------------------

    We have received no definitive data that would enable us to provide 
a cost estimate for the on-condition actions specified in this AD.

Authority for This Rulemaking

    Title 49 of the United States Code specifies the FAA's authority to 
issue rules on aviation safety. Subtitle I, Section 106, describes the 
authority of the FAA Administrator. Subtitle VII, Aviation Programs, 
describes in more detail the scope of the Agency's authority.
    We are issuing this rulemaking under the authority described in 
Subtitle VII, Part A, Subpart III, Section 44701, ``General 
requirements.'' Under that section, Congress charges the FAA with 
promoting safe flight of civil aircraft in air commerce by prescribing 
regulations for practices, methods, and procedures the Administrator 
finds necessary for safety in air commerce. This regulation is within 
the scope of that authority because it addresses an unsafe condition 
that is likely to exist or develop on products identified in this 
rulemaking action.

Regulatory Findings

    We have determined that this AD will not have federalism 
implications under Executive Order 13132. This AD will not have a 
substantial direct effect on the States, on the relationship between 
the national government and the States, or on the distribution of power 
and responsibilities among the various levels of government.
    For the reasons discussed above, I certify that this AD:
    (1) Is not a ``significant regulatory action'' under Executive 
Order 12866,
    (2) Is not a ``significant rule'' under DOT Regulatory Policies and 
Procedures (44 FR 11034, February 26, 1979),
    (3) Will not affect intrastate aviation in Alaska, and
    (4) Will not have a significant economic impact, positive or 
negative, on a substantial number of small entities under the criteria 
of the Regulatory Flexibility Act.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Incorporation by 
reference, Safety.

Adoption of the Amendment

    Accordingly, under the authority delegated to me by the 
Administrator, the FAA amends 14 CFR part 39 as follows:

PART 39--AIRWORTHINESS DIRECTIVES

0
1. The authority citation for part 39 continues to read as follows:

    Authority: 49 U.S.C. 106(g), 40113, 44701.

[[Page 80245]]

Sec.  39.13  [Amended]

0
2. The FAA amends Sec.  39.13 by removing Airworthiness Directive (AD) 
2013-23-03, Amendment 39-17658 (78 FR 68345, November 14, 2013), and 
adding the following new AD:
2015-25-03 The Boeing Company: Amendment 39-18341; Docket No. FAA-
2015-0828; Directorate Identifier 2014-NM-146-AD.

(a) Effective Date

    This AD is effective January 28, 2016.

(b) Affected ADs

    This AD replaces AD 2013-23-03, Amendment 39-17658 (78 FR 68345, 
November 14, 2013).

(c) Applicability

    This AD applies to The Boeing Company Model 747-100, 747-100B, 
747-100B SUD, 747-200B, 747-200C, 747-200F, 747-300, 747-400, 747-
400D, 747-400F, and 747SR series airplanes, certificated in any 
category, as identified in Boeing Alert Service Bulletin 747-
57A2443, Revision 1, dated June 23, 2014.

(d) Subject

    Air Transport Association (ATA) of America Code 57, Wings.

(e) Unsafe Condition

    This AD was prompted by a report of the fracture of an inboard 
actuator attach fitting of the outboard flap. An inspection of the 
attach fitting revealed that it was incorrectly machined with a 
cylindrical profile instead of a conical profile, resulting in 
reduced wall thickness. A machining defect was also found on some 
actuator assemblies inspected during manufacture at the point where 
the tapered machining transitioned to the hemispherical machining at 
the top of the inner surface. This defect could lead to fatigue 
cracking and subsequent fracture. We are issuing this AD to detect 
and correct defective inboard actuator attach fittings which, 
combined with loss of the outboard actuator load path, could result 
in uncontrolled retraction of the outboard flap, damage to flight 
control systems, and consequent reduced controllability of the 
airplane.

(f) Compliance

    Comply with this AD within the compliance times specified, 
unless already done.

(g) Retained Part Number Inspection With Revised Service Information

    This paragraph restates the requirements of paragraph (g) of AD 
2013-23-03, Amendment 39-17658 (78 FR 68345, November 14, 2013), 
with revised service information. Within 90 days after November 29, 
2013 (the effective date of AD 2013-23-03): Inspect to determine the 
part number of the inboard actuator attach fittings of the outboard 
flaps, in accordance with Part 1 of the Accomplishment Instructions 
of Boeing Alert Service Bulletin 747-57A2443, dated September 12, 
2013; or Boeing Alert Service Bulletin 747-57A2443, Revision 1, 
dated June 23, 2014. As of the effective date of this AD, only 
Boeing Alert Service Bulletin 747-57A2443, Revision 1, dated June 
23, 2014, may be used.

(h) Retained Actions for Certain Attach Fittings With Revised Service 
Information

    This paragraph restates the requirements of paragraph (h) of AD 
2013-23-03, Amendment 39-17658 (78 FR 68345, November 14, 2013), 
with revised service information. If, during the inspection required 
by paragraph (g) of this AD, any inboard actuator attach fitting 
having part number (P/N) 65B08564-7 is found, before further flight, 
do the actions specified in paragraph (h)(1) or (h)(2) of this AD.
    (1) Do a detailed inspection of the inboard actuator attach 
fitting for a cylindrical defect, in accordance with Part 2 of the 
Accomplishment Instructions of Boeing Alert Service Bulletin 747-
57A2443, dated September 12, 2013; or Boeing Alert Service Bulletin 
747-57A2443, Revision 1, dated June 23, 2014. As of the effective 
date of this AD, only Boeing Alert Service Bulletin 747-57A2443, 
Revision 1, dated June 23, 2014, may be used. For airplanes on which 
the detailed inspection is done before the effective date of this 
AD: If any cylindrical defect is found, before further flight, do 
the actions specified in paragraph (h)(1)(i) or (h)(1)(ii) of this 
AD.
    (i) Do a minimum thickness inspection of the inboard actuator 
attach fitting to determine minimum wall thickness of the actuator 
fitting assembly, in accordance with Part 3 of the Accomplishment 
Instructions of Boeing Alert Service Bulletin 747-57A2443, dated 
September 12, 2013; or Boeing Alert Service Bulletin 747-57A2443, 
Revision 1, dated June 23, 2014. If the minimum thickness of the 
wall is less than 0.130 inch: Before further flight, replace the 
inboard actuator attach fitting of the outboard flap, in accordance 
with Part 4 of the Accomplishment Instructions of Boeing Alert 
Service Bulletin 747-57A2443, dated September 12, 2013.
    (ii) Replace the inboard actuator attach fitting of the outboard 
flap, in accordance with Part 4 of the Accomplishment Instructions 
of Boeing Alert Service Bulletin 747-57A2443, dated September 12, 
2013.
    (2) Replace the inboard actuator attach fitting of the outboard 
flap, in accordance with Part 4 of the Accomplishment Instructions 
of Boeing Alert Service Bulletin 747-57A2443, dated September 12, 
2013; or Boeing Alert Service Bulletin 747-57A2443, Revision 1, 
dated June 23, 2014. As of the effective date of this AD, only 
Boeing Alert Service Bulletin 747-57A2443, Revision 1, dated June 
23, 2014, may be used.

(i) New Actions for Certain Airplanes on Which Any Cylindrical Defect 
Is Found

    For airplanes on which the detailed inspection required by 
paragraph (h)(1) of this AD is done on or after the effective date 
of this AD: If any cylindrical defect is found during any inspection 
required by paragraph (h)(1) of this AD, before further flight, do 
the actions specified in paragraph (i)(1) or (i)(2) of this AD.
    (1) Determine the minimum wall thickness of the actuator attach 
fitting either by doing an ultrasonic inspection or by mechanically 
measuring the thickness and do a detailed inspection of the inner 
conical section to determine if the machining defect is present, in 
accordance with Part 3 of the Accomplishment Instructions of Boeing 
Alert Service Bulletin 747-57A2443, Revision 1, dated June 23, 2014.
    (i) If the minimum thickness of the wall is less than 0.130 
inch: Before further flight, replace the inboard actuator attach 
fitting of the outboard flap, in accordance with Part 4 of the 
Accomplishment Instructions of Boeing Alert Service Bulletin 747-
57A2443, Revision 1, dated June 23, 2014.
    (ii) If the minimum thickness of the wall is 0.140 inch or 
greater and the machining defect is present, before further flight, 
do the actions specified in paragraph (i)(1)(ii)(A) or (i)(1)(ii)(B) 
of this AD.
    (A) Overhaul the inboard actuator attach fitting of the outboard 
flap, in accordance with Part 5 of the Accomplishment Instructions 
of Boeing Alert Service Bulletin 747-57A2443, Revision 1, dated June 
23, 2014.
    (B) Replace the inboard actuator attach fitting of the outboard 
flap, in accordance with Part 4 of the Accomplishment Instructions 
of Boeing Alert Service Bulletin 747-57A2443, Revision 1, dated June 
23, 2014.
    (iii) If the minimum thickness of the wall is 0.130 inch or 
greater and less than 0.140 inch and the machining defect is not 
present, within 48 months or 3,000 flight cycles after the effective 
date of this AD, whichever occurs first, replace the inboard 
actuator attach fitting of the outboard flap, in accordance with 
Part 4 of the Accomplishment Instructions of Boeing Alert Service 
Bulletin 747-57A2443, Revision 1, dated June 23, 2014.
    (iv) If the minimum thickness of the wall is 0.130 inch or 
greater and less than 0.140 inch and the machining defect is 
present, before further flight, replace the inboard actuator attach 
fitting of the outboard flap, in accordance with Part 4 of the 
Accomplishment Instructions of Boeing Alert Service Bulletin 747-
57A2443, Revision 1, dated June 23, 2014.
    (2) Replace the inboard actuator attach fitting of the outboard 
flap, in accordance with Part 4 of the Accomplishment Instructions 
of Boeing Alert Service Bulletin 747-57A2443, Revision 1, dated June 
23, 2014.

(j) New Actions for Airplanes on Which No Cylindrical Defects Are Found

    If no cylindrical defect is found during any inspection required 
by paragraph (h)(1) of this AD, within 24 months after the effective 
date of this AD, do the actions specified in paragraph (j)(1) or 
(j)(2) of this AD.
    (1) Determine the minimum wall thickness of the actuator attach 
fitting either by doing an ultrasonic inspection or by mechanically 
measuring the thickness and do a detailed inspection of the inner 
conical section to determine if the machining defect is present, in 
accordance with Part 3 of the Accomplishment Instructions of Boeing 
Alert Service Bulletin 747-57A2443, Revision 1, dated June 23, 2014.

[[Page 80246]]

    (i) If the minimum thickness of the wall is less than 0.130 
inch: Before further flight, replace the inboard actuator attach 
fitting of the outboard flap, in accordance with Part 4 of the 
Accomplishment Instructions of Boeing Alert Service Bulletin 747 
57A2443, Revision 1, dated June 23, 2014.
    (ii) If the minimum thickness of the wall is 0.140 inch or 
greater and the machining defect is present, before further flight, 
do the actions specified in paragraph (j)(1)(ii)(A) or (j)(1)(ii)(B) 
of this AD.
    (A) Overhaul the inboard actuator attach fitting of the outboard 
flap, in accordance with Part 5 of the Accomplishment Instructions 
of Boeing Alert Service Bulletin 747-57A2443, Revision 1, dated June 
23, 2014.
    (B) Replace the inboard actuator attach fitting of the outboard 
flap, in accordance with Part 4 of the Accomplishment Instructions 
of Boeing Alert Service Bulletin 747-57A2443, Revision 1, dated June 
23, 2014.
    (iii) If the minimum thickness of the wall is 0.130 inch or 
greater and less than 0.140 inch and the machining defect is not 
present, within 48 months or 3,000 flight cycles after the effective 
date of this AD, whichever occurs first, replace the inboard 
actuator attach fitting of the outboard flap, in accordance with 
Part 4 of the Accomplishment Instructions of Boeing Alert Service 
Bulletin 747-57A2443, Revision 1, dated June 23, 2014.
    (iv) If the minimum thickness of the wall is 0.130 inch or 
greater and less than 0.140 inch and the machining defect is 
present, before further flight, replace the inboard actuator attach 
fitting of the outboard flap, in accordance with Part 4 of the 
Accomplishment Instructions of Boeing Alert Service Bulletin 747-
57A2443, Revision 1, dated June 23, 2014
    (2) Replace the inboard actuator attach fitting of the outboard 
flap, in accordance with Part 4 of the Accomplishment Instructions 
of Boeing Alert Service Bulletin 747-57A2443, Revision 1, dated June 
23, 2014.

(k) New Inspection or Replacement for Certain Fittings That Were 
Previously Inspected

    For airplanes on which the detailed inspection required by 
paragraph (h)(1) of this AD is done before the effective date of 
this AD, except as required by paragraph (m) of this AD: If any 
cylindrical defect is found during any inspection required by 
paragraph (h)(1) of this AD and the replacement of the inboard 
actuator attach fitting of the outboard flap was not done as 
specified in Part 4 of the Accomplishment Instructions of Boeing 
Alert Service Bulletin 747-57A2443, within 24 months after the 
effective date of this AD, do the actions specified in paragraph 
(k)(1) or (k)(2) of this AD.
    (1) Do a detailed inspection of the inner conical section for 
machining defects and do an ultrasonic inspection to determine the 
minimum thickness or mechanically determine the minimum thickness, 
in accordance with Part 3 of the Accomplishment Instructions of 
Boeing Alert Service Bulletin 747-57A2443, Revision 1, dated June 
23, 2014. A review of airplane maintenance records, if available, is 
acceptable to determine the wall thickness and to determine if there 
are machining defects, provided wall thickness and machining defects 
can be positively determined from the records review.
    (i) If any machining defect is found and the minimum thickness 
of the wall is 0.140 inch or greater: Before further flight, do the 
actions specified in paragraph (k)(1)(i)(A) or (k)(1)(i)(B) of this 
AD.
    (A) Overhaul the inboard actuator attach fitting of the outboard 
flap, in accordance with Part 5 of the Accomplishment Instructions 
of Boeing Alert Service Bulletin 747-57A2443, Revision 1, dated June 
23, 2014.
    (B) Replace the inboard actuator attach fitting of the outboard 
flap, in accordance with Part 4 of the Accomplishment Instructions 
of Boeing Alert Service Bulletin 747-57A2443, Revision 1, dated June 
23, 2014.
    (ii) If any machining defect is found and the minimum thickness 
of the wall is 0.130 inch or greater and less than 0.140 inch: 
Before further flight, replace the inboard actuator attach fitting 
of the outboard flap, in accordance with Part 4 of the 
Accomplishment Instructions of Boeing Alert Service Bulletin 747-
57A2443, Revision 1, dated June 23, 2014.
    (iii) If no machining defect is found and the minimum thickness 
of the wall is 0.130 inch or greater and less than 0.140 inch: 
Within 48 months or 3,000 flight cycles after the effective date of 
this AD, whichever occurs first, replace the inboard actuator attach 
fitting of the outboard flap, in accordance with Part 4 of the 
Accomplishment Instructions of Boeing Alert Service Bulletin 747-
57A2443, Revision 1, dated June 23, 2014.
    (iv) If a machining defect is or is not found and the minimum 
thickness of the wall is less than 0.130 inch: Before further 
flight, replace the inboard actuator attach fitting of the outboard 
flap, in accordance with Part 4 of the Accomplishment Instructions 
of Boeing Alert Service Bulletin 747-57A2443, Revision 1, dated June 
23, 2014.
    (2) Replace the inboard actuator attach fitting of the outboard 
flap, in accordance with Part 4 of the Accomplishment Instructions 
of Boeing Alert Service Bulletin 747-57A2443, Revision 1, dated June 
23, 2014.

(l) Parts Installation Limitation

    As of the effective date of this AD, no actuator attach fitting 
having P/N 65B08564-7 may be installed on any airplane unless the 
inspection specified in paragraph (h)(1) of this AD is done prior to 
installation and the applicable actions specified in paragraphs (i) 
and (j) of this AD are done within the applicable times specified in 
paragraphs (i) and (j) of this AD. A review of airplane maintenance 
records, if available, is acceptable to determine if the inspection 
and applicable actions have been done, provided the inspection and 
actions can be positively determined from the records review.

(m) Action for Parts Installed After AD 2013-23-03, Amendment 39-17658 
(78 FR 68345, November 14, 2013) Was Accomplished

    For airplanes on which the detailed inspection required by 
paragraph (h)(1) of this AD is done before the effective date of 
this AD and the inboard actuator attach fitting was replaced since 
that inspection: Within 90 days after the effective date of this AD, 
inspect to determine the part number of the inboard actuator attach 
fittings of the outboard flaps and, for inboard actuator attach 
fittings having P/N 65B08564-7, do the applicable actions specified 
in paragraphs (h), (i), and (j) of this AD within the applicable 
times specified in paragraphs (h), (i), and (j) of this AD. A review 
of airplane maintenance records, if available, is acceptable to 
determine the part number, provided the part number can be 
positively determined from the records review.

(n) Alternative Methods of Compliance (AMOCs)

    (1) The Manager, Seattle Aircraft Certification Office (ACO), 
FAA, has the authority to approve AMOCs for this AD, if requested 
using the procedures found in 14 CFR 39.19. In accordance with 14 
CFR 39.19, send your request to your principal inspector or local 
Flight Standards District Office, as appropriate. If sending 
information directly to the manager of the ACO, send it to the 
attention of the person identified in paragraph (o) of this AD. 
Information may be emailed to: 9-ANM-Seattle-ACO-AMOC-Requests@faa.gov.
    (2) Before using any approved AMOC, notify your appropriate 
principal inspector, or lacking a principal inspector, the manager 
of the local flight standards district office/certificate holding 
district office.
    (3) An AMOC that provides an acceptable level of safety may be 
used for any repair required by this AD if it is approved by the 
Boeing Commercial Airplanes Organization Designation Authorization 
(ODA) that has been authorized by the Manager, Seattle ACO, to make 
those findings. For a repair method to be approved, the repair must 
meet the certification basis of the airplane, and the approval must 
specifically refer to this AD.
    (4) If any service information contains steps that are 
identified as RC (Required for Compliance), those steps must be done 
to comply with this AD; any steps that are not identified as RC are 
recommended. Those steps that are not identified as RC may be 
deviated from using accepted methods in accordance with the 
operator's maintenance or inspection program without obtaining 
approval of an AMOC provided the steps identified as RC can be done 
and the airplane can be put back in an airworthy condition. Any 
substitutions or changes to steps identified as RC require approval 
of an AMOC.
    (5) AMOCs approved for AD 2013-23-03, Amendment 39-17658 (78 FR 
68345, November 14, 2013) are approved as AMOCs for the 
corresponding provisions of this AD.

(o) Related Information

    For more information about this AD, contact Nathan Weigand, 
Aerospace

[[Page 80247]]

Engineer, Airframe Branch, ANM-120S, FAA, Seattle Aircraft 
Certification Office, 1601 Lind Avenue SW., Renton, WA 98057-3356; 
phone: 425-917-6428; fax: 425-917-6590; email: 
nathan.p.weigand@faa.gov.

(p) 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 
January 28, 2016.
    (i) Boeing Alert Service Bulletin 747-57A2443, Revision 1, dated 
June 23, 2014.
    (ii) Reserved.
    (4) The following service information was approved for IBR on 
November 29, 2013 (78 FR 68345, November 14, 2013).
    (i) Boeing Alert Service Bulletin 747-57A2443, dated September 
12, 2013.
    (ii) Reserved.
    (5) For service information identified in this AD, contact 
Boeing Commercial Airplanes, Attention: Data & Services Management, 
P. O. Box 3707, MC 2H-65, Seattle, WA 98124-2207; telephone 206-544-
5000, extension 1; fax 206-766-5680; Internet https://www.myboeingfleet.com.
    (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 November 24, 2015.
Jeffrey E. Duven,
Manager, Transport Airplane Directorate,Aircraft Certification Service.
[FR Doc. 2015-30881 Filed 12-23-15; 8:45 am]
 BILLING CODE 4910-13-P