Airworthiness Directives; The Boeing Company Airplanes, 34252-34256 [2015-14174]

Download as PDF 34252 Federal Register / Vol. 80, No. 115 / Tuesday, June 16, 2015 / Rules and Regulations asabaliauskas on DSK5VPTVN1PROD with RULES the requirements of paragraph (g) of this AD for Model A300–600 airplanes. (i) Where the tables in paragraph 1.E.(2), ‘‘Accomplishment Timescale,’’ of Airbus Service Bulletin A300–57–6029, Revision 08, dated April 25, 2013, specify a grace period for doing the actions for airplanes that have exceeded the thresholds, this AD requires, for all airplanes, that the actions be done within the specified grace period after the effective date of this AD or before the specified thresholds, whichever occurs later. (ii) Where Airbus Service Bulletin A300– 57–6029, Revision 08, dated April 25, 2013, specifies to ‘‘contact Airbus’’ before further flight, this AD requires repairing using a method approved by the Manager, International Branch, ANM–116, Transport Airplane Directorate, FAA; or European Aviation Safety Agency (EASA); or Airbus’s EASA Design Organization Approval (DOA); and accomplishing those actions before further flight. If approved by the DOA, the approval must include the DOA-authorized signature. (2) If, during any inspection as required by paragraph (h)(1) of this AD, discrepancies are detected, before next flight, accomplish the applicable corrective actions, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A300–57–6029, Revision 08, dated April 25, 2013. (3) Corrective actions, as required by paragraph (h)(2) of this AD, do not constitute terminating action for the repetitive inspection requirements of paragraph (h)(1) of this AD. (i) Credit for Previous Actions (1) This paragraph provides credit for actions required by paragraph (g) of this AD, if those actions were performed before April 23, 2008 (the effective date of AD 2008–06– 18, Amendment 39–15430 (73 FR 14670, March 19, 2008)), using the applicable service information identified in paragraphs (i)(1)(i) through (i)(1)(iv) of this AD, which are not incorporated by reference by this AD. (i) Airbus Service Bulletin A300–57–0177, Revision 03, dated May 29, 2006 (for Model A300 series airplanes). (ii) Airbus Service Bulletin A300–57–0177, Revision 04, dated January 5, 2007 (for Model A300 series airplanes). (iii) Airbus Service Bulletin A300–57– 6029, Revision 04, dated May 29, 2006 (for Model A300–600 series airplanes). (iv) Airbus Service Bulletin A300–57– 6029, Revision 05, dated October 23, 2006 (for Model A300–600 series airplanes). (2) This paragraph provides credit for actions required by paragraph (g) or (h) of this AD, if those actions were performed before the effective date of this AD, using Airbus Service Bulletin A300–57–6029, Revision 07, dated June 6, 2011 (for Model A300–600 series airplanes), which is not incorporated by reference by this AD. (j) 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 VerDate Sep<11>2014 16:14 Jun 15, 2015 Jkt 235001 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: Dan Rodina, Aerospace Engineer, International Branch, ANM–116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057–3356; telephone 425–227–2125; fax 425–227–1149. Information may be emailed to: 9-ANM-116AMOC-REQUESTS@faa.gov. (i) 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. The AMOC approval letter must specifically reference this AD. (ii) AMOCs approved previously for AD 2008–06–18, Amendment 39–15430 (73 FR 14670, March 19, 2008), are approved as AMOCs for the corresponding requirements of this AD. (2) Contacting the Manufacturer: As of the effective date of this AD, 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) Reporting Requirements: A federal agency may not conduct or sponsor, and a person is not required to respond to, nor shall a person be subject to a penalty for failure to comply with a collection of information subject to the requirements of the Paperwork Reduction Act unless that collection of information displays a current valid OMB Control Number. The OMB Control Number for this information collection is 2120–0056. Public reporting for this collection of information is estimated to be approximately 5 minutes per response, including the time for reviewing instructions, completing and reviewing the collection of information. All responses to this collection of information are mandatory. Comments concerning the accuracy of this burden and suggestions for reducing the burden should be directed to the FAA at: 800 Independence Ave. SW., Washington, DC 20591, Attn: Information Collection Clearance Officer, AES–200. (k) Related Information (1) Refer to Mandatory Continuing Airworthiness Information (MCAI) EASA Airworthiness Directive 2012–0203, dated October 1, 2012, for related information. This MCAI may be found in the AD docket on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA– 2014–0618. (2) Service information identified in this AD that is not incorporated by reference is available at the addresses specified in paragraphs (l)(5) and (l)(6) of this AD. (l) Material Incorporated by Reference (1) The Director of the Federal Register approved the incorporation by reference PO 00000 Frm 00014 Fmt 4700 Sfmt 4700 (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. (3) The following service information was approved for IBR on July 21, 2015. (i) Airbus Service Bulletin A300–57–6029, Revision 08, dated April 25, 2013. (ii) Reserved. (4) The following service information was approved for IBR on April 23, 2008 (73 FR 14670, March 19, 2008). (i) Airbus Service Bulletin A300–57–0177, Revision 05, dated March 23, 2007. (ii) Airbus Service Bulletin A300–57–6029, Revision 06, dated March 23, 2007. (5) For service information identified in this AD, contact Airbus SAS Airworthiness Office—EAW, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 93 44 51; email account.airworth-eas@ airbus.com; Internet http://www.airbus.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 June 3, 2015. Michael Kaszycki, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2015–14283 Filed 6–15–15; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2014–0485; Directorate Identifier 2014–NM–093–AD; Amendment 39–18176; AD 2015–12–03] RIN 2120–AA64 Airworthiness Directives; The Boeing Company Airplanes Federal Aviation Administration (FAA), DOT. ACTION: Final rule. AGENCY: We are superseding Airworthiness Directive (AD) 2007–13– 05 for all The Boeing Company Model 777–200, –200LR, –300, and –300ER series airplanes. AD 2007–13–05 required repetitive measurements of the freeplay of the right and left elevators, rudder, and rudder tab, and related SUMMARY: E:\FR\FM\16JNR1.SGM 16JNR1 Federal Register / Vol. 80, No. 115 / Tuesday, June 16, 2015 / Rules and Regulations asabaliauskas on DSK5VPTVN1PROD with RULES investigative and corrective actions if necessary. This new AD requires repetitive freeplay inspections and lubrication of the right and left elevators, rudder, and rudder tab, and related investigative and corrective actions if necessary. This AD was prompted by the manufacturer’s determination that the procedure for the rudder freeplay inspection does not properly detect excessive freeplay in the rudder control load loop. We are issuing this AD to detect and correct excessive wear in the load loop components of the control surfaces, which could lead to excessive freeplay of the control surfaces, flutter, and consequent loss of control of the airplane. DATES: This AD is effective July 21, 2015. The Director of the Federal Register approved the incorporation by reference of a certain publication listed in this AD as of July 21, 2015. ADDRESSES: For service information identified in this AD, contact Boeing Commercial Airplanes, Attention: Data & Services Management, P. O. Box 3707, MC 2H–65, Seattle, WA 98124–2207; telephone 206–544–5000, extension 1; fax 206–766–5680; Internet https:// www.myboeingfleet.com. You may view this referenced service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For information on the availability of this material at the FAA, call 425–227–1221. It is also available on the Internet at http:// www.regulations.gov by searching for and locating Docket No. FAA–2014– 0485. Examining the AD Docket You may examine the AD docket on the Internet at http:// www.regulations.gov by searching for and locating Docket No. FAA–2014– 0485; 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: Haytham Alaidy, Aerospace Engineer, Airframe Branch, ANM–120S, FAA, Seattle Aircraft Certification Office (ACO), 1601 Lind Avenue SW., Renton, WA 98057–3356; phone: 425–917–6573; VerDate Sep<11>2014 16:14 Jun 15, 2015 Jkt 235001 fax: 425–917–6590; email: Haytham.Alaidy@faa.gov. SUPPLEMENTARY INFORMATION: Discussion We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 to supersede AD 2007–13–05, Amendment 39–15109 (72 FR 33856, June 20, 2007). AD 2007–13–05 applied to all The Boeing Company Model 777– 200, –200LR, –300, and –300ER series airplanes. The NPRM published in the Federal Register on July 29, 2014 (79 FR 43981). The NPRM was prompted by a determination by the manufacturer that, after AD 2007–13–05 was issued, the procedure for the rudder freeplay inspection did not properly detect excessive freeplay in the rudder control load loop. The NPRM proposed to continue to require repetitive freeplay inspections and lubrication of the right and left elevators, rudder, and rudder tab; and related investigative and corrective actions if necessary. We are issuing this AD to detect and correct excessive wear in the load loop components of the control surfaces, which could lead to excessive freeplay of the control surfaces, flutter, and consequent loss of control of the airplane. Comments We gave the public the opportunity to participate in developing this AD. The following presents the comments received on the NPRM (79 FR 43981, July 29, 2014) and the FAA’s response to each comment. A4A, on behalf of American Airlines (AA), stated that AA is already in compliance with the requirements proposed in the NPRM (79 FR 43981, July 29, 2014). Request To Exclude Certain Airplanes Boeing requested that the airplanes referenced in the SUMMARY section and Discussion paragraph of the NPRM (79 FR 43981, July 29, 2014) be changed from ‘‘all The Boeing Company Model 777 airplanes’’ to ‘‘most of The Boeing Company Model 777 airplanes.’’ Boeing stated that Model 777–200F airplanes are not affected by the NPRM. We agree to change the phrase ‘‘all The Boeing Company Model 777 airplanes’’ for clarity. This final rule supersedes AD 2007–13–05, Amendment 39–15109 (72 FR 33856, June 20, 2007), which was applicable to all Boeing Model 777–200, –200LR, –300, and –300ER series airplanes. At the time AD 2007–13–05 was published, all Model 777–200, –200LR, –300, and –300ER series airplanes were referred to as ‘‘all The Boeing Company Model 777 PO 00000 Frm 00015 Fmt 4700 Sfmt 4700 34253 airplanes.’’ Since then, Model 777F has been added to the U.S. type certificate data sheet. We have revised the SUMMARY section of this final rule to specify all The Boeing Company Model 777–200, –200LR, –300, and –300ER series airplanes. The Discussion paragraph of the NPRM (79 FR 43981, July 29, 2014) is not restated in this final rule. Request To Clarify the Unsafe Condition Boeing requested that we clarify the unsafe condition specified in the SUMMARY section, Discussion paragraph, and paragraph (e) of the NPRM. Boeing stated that the repetitive freeplay inspections of the right and left elevators, rudder, and rudder tab proposed in the NPRM (79 FR 43981, July 29, 2014) would not prevent, detect, or correct flutter; the proposed freeplay inspections would detect excessive wear in the load loop components of the control surfaces. Boeing pointed out that excessive wear could lead to excessive freeplay of the control surfaces, which could cause unacceptable airframe vibration during flight. Based on the explanation provided by the commenter, we agree to clarify the unsafe condition that is the basis for issuing this final rule. However, we will not replace the word ‘‘flutter’’ with ‘‘unacceptable airframe vibration’’ because the unsafe condition is flutter, not vibration. We have revised the unsafe condition statement as follows, ‘‘We are issuing this AD to detect and correct excessive wear in the load loop components of the control surfaces, which could lead to excessive freeplay of the control surfaces, flutter, and consequent loss of control of the airplane.’’ This revision appears in the SUMMARY section and Discussion paragraph of the SUPPLEMENTARY INFORMATION section of this final rule, as well as paragraph (e) of this AD. Request To Clarify the Requirements of Paragraph (g) of the Proposed AD (79 FR 43981, July 29, 2014) Boeing requested that we revise paragraph (g) of the proposed AD (79 FR 43981, July 29, 2014) by deleting ‘‘rudder’’ from the following sentence: ‘‘If during any inspection required by this paragraph, the rudder freeplay exceeds any applicable measurement . . . .’’ Boeing explained that this statement is incorrect because it is not just the rudder freeplay, but if any elevator, rudder, or rudder tab freeplay exceeds any applicable measurement specified in the service information, the E:\FR\FM\16JNR1.SGM 16JNR1 34254 Federal Register / Vol. 80, No. 115 / Tuesday, June 16, 2015 / Rules and Regulations applicable corrective actions need to be accomplished before further flight. We agree to revise the specified sentence in paragraph (g) of this AD, because corrective actions before further flight are needed for any elevator, rudder, or rudder tab freeplay that exceeds any applicable measurement specified in Boeing Special Attention Service Bulletin 777–27–0062, Revision 2, dated January 27, 2014. Requests To Correct Errors in the Service Information Japan Airlines (JAL) and United Airlines noted that there are typographical errors in Appendix B and Appendix C of Boeing Special Attention Service Bulletin 777–27–0062, Revision 2, dated January 27, 2014. JAL requested that the FAA issue an AD to mandate the incorporation of the next revision (Revision 3) of Boeing Special Attention Service Bulletin 777–27–0062, or provide an exception to these typographical errors in this AD. United Airlines requested that the FAA issue a global alternative method of compliance (AMOC) to correct the errors identified in Boeing Special Attention Service Bulletin 777–27–0062, Revision 2, dated January 27, 2014. We agree that Appendix B and Appendix C of Boeing Special Attention Service Bulletin 777–27–0062, Revision 2, dated January 27, 2014, contain typographical errors. However, we do not consider that delaying this action until after the release of the manufacturer’s planned service bulletin revision is warranted. Because some of these typographical errors affect the procedures for correctly measuring the freeplay of the rudder tab surface, we have provided the corrections for those errors in paragraph (i) of this AD instead of issuing an AMOC. Paragraph (i) of the proposed AD (79 FR 43981, July 29, 2014) has been redesignated as paragraph (i)(1) in this AD, and new paragraphs (i)(2), (i)(3), and (i)(4) have been added to this AD. We have also revised paragraph (g) of this AD to refer to paragraphs (i)(1) through (i)(4) of this AD. Additional Changes to This Final Rule Paragraph (k)(4) of the NPRM (79 FR 43981, July 29, 2014) stated that AMOCs approved previously for AD 2007–13– 05, Amendment 39–15109 (72 FR 33856, June 20, 2007), are not approved as AMOCS for the requirements of this AD. We have now determined that AMOCs for certain actions required by AD 2007–13–05 are acceptable for the corresponding requirements of this AD. We have revised paragraph (k)(4) of this AD and added new paragraphs (k)(5) and (k)(6) to this AD to include this information. Conclusion We reviewed the relevant data, considered the comments received, and determined that air safety and the public interest require adopting this AD with the changes described previously, and minor editorial changes. We have determined that these minor changes: • Are consistent with the intent that was proposed in the NPRM (79 FR 43981, July 29, 2014) for correcting the unsafe condition; and • Do not add any additional burden upon the public than was already proposed in the NPRM (79 FR 43981, July 29, 2014). 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 Special Attention Service Bulletin 777–27– 0062, Revision 2, dated January 27, 2014. The service information describes procedures for repetitive freeplay inspections and lubrication of the right and left elevators, rudder, and rudder tab, and related investigative and corrective actions. This service information is reasonably available because the interested parties have access to it through their normal course of business or by the means identified in the ADDRESSES section of this AD. Costs of Compliance We estimate that this AD affects 142 airplanes of U.S. registry. The new actions of this AD would add no additional economic burden to that imposed by AD 2007–13–05, Amendment 39–15109 (72 FR 33856, June 20, 2007). The current costs for this AD are repeated for the convenience of affected operators, as follows: ESTIMATED COSTS Action Labor cost Measurement (inspection), elevator. 4 work-hours × $85 per hour = $340 per measurement (inspection) cycle. 17 work-hours × $85 per hour = $1,445 per lubrication cycle. 4 work-hours × $85 per hour = $340 per measurement (inspection) cycle. 7 work-hours × $85 per hour = $595 per lubrication cycle. 3 work-hours × $85 per hour = $255 per measurement (inspection) cycle. 5 work-hours × $85 per hour = $425 per lubrication cycle. Lubrication, elevator ............... Measurement (inspection), rudder. Lubrication, rudder ................. Measurement (inspection), rudder tab. asabaliauskas on DSK5VPTVN1PROD with RULES Lubrication, rudder tab ........... We have received no definitive data that would enable us to provide cost estimates for the on-condition corrective actions specified in this AD. VerDate Sep<11>2014 16:14 Jun 15, 2015 Jkt 235001 Parts cost Cost per product $0 $340 per measurement (inspection) cycle. $48,280 per measurement (inspection) cycle. 0 $1,445 per lubrication cycle ... $205,190 per lubrication cycle. 0 $340 per measurement (inspection) cycle. $48,280 per measurement (inspection) cycle. 0 $595 per lubrication cycle ...... $84,490 per lubrication cycle. 0 $255 per measurement (inspection) cycle. $36,210 per measurement (inspection) cycle. 0 $425 per lubrication cycle ...... $60,350 per lubrication cycle. 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, PO 00000 Frm 00016 Cost on U.S. operators Fmt 4700 Sfmt 4700 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 E:\FR\FM\16JNR1.SGM 16JNR1 Federal Register / Vol. 80, No. 115 / Tuesday, June 16, 2015 / Rules and Regulations 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 1. The authority citation for part 39 continues to read as follows: ■ Authority: 49 U.S.C. 106(g), 40113, 44701. § 39.13 [Amended] 2. The FAA amends § 39.13 by removing Airworthiness Directive (AD) 2007–13–05, Amendment 39–15109 (72 FR 33856, June 20, 2007), and adding the following new AD: asabaliauskas on DSK5VPTVN1PROD with RULES ■ 2015–12–03 The Boeing Company: Amendment 39–18176 ; Docket No. FAA–2014–0485; Directorate Identifier 2014–NM–093–AD. (a) Effective Date This AD is effective July 21, 2015. VerDate Sep<11>2014 16:14 Jun 15, 2015 Jkt 235001 (b) Affected ADs This AD replaces AD 2007–13–05, Amendment 39–15109 (72 FR 33856, June 20, 2007). (c) Applicability This AD applies to The Boeing Company Model 777–200, –200LR, –300, and –300ER series airplanes, certificated in any category, as identified in paragraphs (c)(1) and (c)(2) of this AD. (1) Airplanes having a Variable Number identified in paragraph 1.A., ‘‘Effectivity,’’ of Boeing Special Attention Service Bulletin 777–27–0062, Revision 2, dated January 27, 2014. (2) Airplanes having a date of issuance of the original airworthiness certificate or date of issuance of the original export certificate of airworthiness on or after January 27, 2014. (d) Subject Air Transport Association (ATA) of America Code 27, Flight Controls. (e) Unsafe Condition This AD was prompted by the manufacturer’s determination that the procedure for the rudder freeplay inspection does not properly detect excessive freeplay in the rudder control load loop. We are issuing this AD to detect and correct excessive wear in the load loop components of the control surfaces, which could lead to excessive freeplay of the control surfaces, flutter, and consequent loss of control of the airplane. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Repetitive Inspections of Elevators, Rudder, and Rudder Tab At the applicable times specified in tables 1, 2, and 3 of paragraph 1.E., ‘‘Compliance,’’ of Boeing Special Attention Service Bulletin 777–27–0062, Revision 2, dated January 27, 2014, except as provided by paragraph (i)(1) of this AD: Inspect the freeplay of the right and left elevators, rudder, and rudder tab by accomplishing all of the actions specified in Parts 1, 3, and 5 of the Accomplishment Instructions of Boeing Special Attention Service Bulletin 777–27–0062, Revision 2, dated January 27, 2014, except as provided by paragraphs (i)(2) through (i)(4) of this AD. Repeat the inspections thereafter at the intervals specified in tables 1, 2, and 3 of paragraph 1.E., ‘‘Compliance,’’ of Boeing Special Attention Service Bulletin 777–27– 0062, Revision 2, dated January 27, 2014. If, during any inspection required by this paragraph, the freeplay exceeds any applicable measurement specified in Part 1, 3, and 5, as applicable, of the Accomplishment Instructions of Boeing Special Attention Service Bulletin 777–27– 0062, Revision 2, dated January 27, 2014, before further flight, do the applicable corrective actions in accordance with Part 1, 3, and 5 of the Accomplishment Instructions of Boeing Special Attention Service Bulletin 777–27–0062, Revision 2, dated January 27, 2014. PO 00000 Frm 00017 Fmt 4700 Sfmt 4700 34255 (h) Repetitive Lubrication At the applicable times specified in tables 1, 2, and 3 of paragraph 1.E., ‘‘Compliance,’’ of Boeing Special Attention Service Bulletin 777–27–0062, Revision 2, dated January 27, 2014, except as provided by paragraph (i)(1) of this AD: Lubricate the elevator components, rudder components, and rudder tab components, by accomplishing all of the actions specified in Parts 2, 4, and 6 of the Accomplishment Instructions of Boeing Special Attention Service Bulletin 777–27– 0062, Revision 2, dated January 27, 2014, as applicable. Repeat the lubrication thereafter at the interval specified in tables 1, 2, and 3 of paragraph 1.E., ‘‘Compliance,’’ of Boeing Special Attention Service Bulletin 777–27– 0062, Revision 2, dated January 27, 2014, as applicable. (i) Exception to Service Information Specifications (1) Where Boeing Special Attention Service Bulletin 777–27–0062, Revision 2, dated January 27, 2014, specifies a compliance time ‘‘after the original issue date on this service bulletin,’’ this AD requires compliance within the specified compliance time after July 25, 2007 (the effective date of AD 2007– 13–05, Amendment 39–15109 (72 FR 33856, June 20, 2007)). (2) Where Appendix B, paragraph 1.f., ‘‘Freeplay Inspection,’’ step (8), of Boeing Special Attention Service Bulletin 777–27– 0062, Revision 2, dated January 27, 2014, specifies that the center of the pad must be within 1.0 inch (13 millimeters) of the center line of the rib rivets in the rudder tab, this AD requires that the center of the tab must be within 1.0 inch (25 millimeters) of the center line of the rib rivets in the rudder tab. (3) Where Appendix C, paragraph 1.e., ‘‘Rudder Tab Surface Freeplay—Inspection,’’ step (2) and step (6), of Boeing Special Attention Service Bulletin 777–27–0062, Revision 2, dated January 27, 2014, specify that the placement of the force gage and pad should be within one inch of the centerline line of the middle rudder PCU rib and at 12 +/¥1 inch (305 +/¥72 millimeters) forward of the rudder tab trailing edge, this AD requires placement of the force gage and pad within one inch of the centerline line of the middle rudder PCU rib and at 12 +/¥1 inch (305 +/¥25 millimeters) forward of the rudder tab trailing edge. (4) Where Appendix C, paragraph 1.e., ‘‘Rudder Tab Surface Freeplay—Inspection,’’ step (3), of Boeing Special Attention Service Bulletin 777–27–0062, Revision 2, dated January 27, 2014, specifies to apply a 30 +/ ¥pound (133 +/¥14 newton) force, this AD requires applying a 30 +/¥3 pound force (133 +/¥14 newton) force. (j) Credit for Previous Actions This paragraph provides credit for the 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 specified in paragraph (j)(1) or (j)(2) of this AD. (1) Boeing Special Attention Service Bulletin 777–27–0062, dated July 18, 2006, which was incorporated by reference in AD 2007–13–05, Amendment 39–15109 (72 FR 33856, June 20, 2007). E:\FR\FM\16JNR1.SGM 16JNR1 34256 Federal Register / Vol. 80, No. 115 / Tuesday, June 16, 2015 / Rules and Regulations (2) Boeing Special Attention Service Bulletin 777–27–0062, Revision 1, dated October 1, 2009, which is not incorporated by reference in this AD. (k) 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 (l)(1) 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) AMOCs approved previously for the freeplay measurements of the right and left elevators and rudder tab required by paragraph (f) of AD 2007–13–05, Amendment 39–15109 (72 FR 33856, June 20, 2007), are approved as AMOCs for the corresponding requirements of this AD. (5) AMOCs approved previously for the freeplay measurements of the rudder required by paragraph (f) of AD 2007–13–05, Amendment 39–15109 (72 FR 33856, June 20, 2007), are not approved as AMOCs for the corresponding requirements of this AD. We are not aware of any such AMOCs. (6) AMOCs approved previously for the repetitive lubrications required by paragraph (g) of AD 2007–13–05, Amendment 39–15109 (72 FR 33856, June 20, 2007), are approved as AMOCs for the corresponding requirements of this AD. asabaliauskas on DSK5VPTVN1PROD with RULES (l) Related Information (1) For more information about this AD, contact Haytham Alaidy, Aerospace Engineer, Airframe Branch, ANM–120S, FAA, Seattle Aircraft Certification Office (ACO), 1601 Lind Avenue SW., Renton, WA 98057–3356; phone: 425–917–6573; fax: 425– 917–6590; email: Haytham.Alaidy@faa.gov. (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. VerDate Sep<11>2014 16:14 Jun 15, 2015 Jkt 235001 (2) You must use this service information as applicable to do the actions required by this AD, unless the AD specifies otherwise. (i) Boeing Special Attention Service Bulletin 777–27–0062, Revision 2, dated January 27, 2014. (ii) Reserved. (3) For service information identified in this AD, contact Boeing Commercial Airplanes, Attention: Data & Services Management, P. O. Box 3707, MC 2H–65, Seattle, WA 98124–2207; telephone 206– 544–5000, extension 1; fax 206–766–5680; Internet https://www.myboeingfleet.com. (4) You may view this service information at FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For information on the availability of this material at the FAA, call 425–227–1221. (5) You may view this service information that is incorporated by reference at the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, call 202–741–6030, or go to: http:// www.archives.gov/federal-register/cfr/ibrlocations.html. Issued in Renton, Washington, on June 3, 2015. Jeffrey E. Duven, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2015–14174 Filed 6–15–15; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration incorporating an operational limitation into the Limitations section of the airplane flight manual (AFM) or airplane flight manual supplement (AFMS). This AD was prompted by reports of Avidyne IFDs displaying incorrect course deviation indication information during GPS approaches (incorrect display of lateral deviations). We are issuing this AD to correct the unsafe condition on these products. DATES: This AD is effective July 1, 2015 to all persons except those persons to whom it was made immediately effective by Emergency AD 2015–10–51, issued on May 18, 2015, which contained the requirements of this amendment. We must receive comments on this AD by July 31, 2015. ADDRESSES: You may send comments, using the procedures found in 14 CFR 11.43 and 11.45, by any of the following methods: • Federal eRulemaking Portal: Go to http://www.regulations.gov. Follow the instructions for submitting comments. • Fax: 202–493–2251. • Mail: U.S. Department of Transportation, Docket Operations, M– 30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE., Washington, DC 20590. • Hand Delivery: Deliver to Mail address above between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. 14 CFR Part 39 Examining the AD Docket [Docket No. FAA–2015–2191; Directorate Identifier 2015–CE–019–AD; Amendment 39–18183; AD 2015–10–51] You may examine the AD docket on the Internet at http:// www.regulations.gov by searching for and locating Docket No. FAA–2015– 2191; or in person at the Docket Operations Office 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 street address for the Docket Operations Office (phone: 800–647–5527) is in the ADDRESSES section. Comments will be available in the AD docket shortly after receipt. FOR FURTHER INFORMATION CONTACT: Anthony Pigott, Aerospace Engineer, Boston Aircraft Certification Office, FAA, 12 New England Executive Park, Burlington, MA 01803; phone: (781) 238–7158; fax: (781) 238–7199; email: anthony.pigott@faa.gov. SUPPLEMENTARY INFORMATION: RIN 2120–AA64 Airworthiness Directives; Avidyne Corporation Integrated Flight Displays Federal Aviation Administration (FAA), DOT. ACTION: Final rule; request for comments. AGENCY: We are adopting a new airworthiness directive (AD) for Avidyne Corporation (Avidyne) Integrated Flight Displays (IFDs) part number (P/N) 700–00083–() loaded with software release 9.3.1.0 or earlier release (referred to as Model R9—10 inch), P/ N 700–00171–() loaded with software release 9.2.5.0 or earlier release (referred to as Model R9—12 inch), and P/N 700– 00182–() loaded with software release 10.0.3.0 or earlier release (referred to as Model IFD540). This emergency AD was sent previously to all known U.S. owners and operators of all aircraft that incorporate the above referenced Avidyne IFDs. This AD requires SUMMARY: PO 00000 Frm 00018 Fmt 4700 Sfmt 4700 Discussion On May 18, 2015, we issued Emergency AD 2015–10–51, which requires incorporating an operational limitation into the Limitations section of E:\FR\FM\16JNR1.SGM 16JNR1

Agencies

[Federal Register Volume 80, Number 115 (Tuesday, June 16, 2015)]
[Rules and Regulations]
[Pages 34252-34256]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2015-14174]


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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2014-0485; Directorate Identifier 2014-NM-093-AD; 
Amendment 39-18176; AD 2015-12-03]
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) 2007-13-05 for 
all The Boeing Company Model 777-200, -200LR, -300, and -300ER series 
airplanes. AD 2007-13-05 required repetitive measurements of the 
freeplay of the right and left elevators, rudder, and rudder tab, and 
related

[[Page 34253]]

investigative and corrective actions if necessary. This new AD requires 
repetitive freeplay inspections and lubrication of the right and left 
elevators, rudder, and rudder tab, and related investigative and 
corrective actions if necessary. This AD was prompted by the 
manufacturer's determination that the procedure for the rudder freeplay 
inspection does not properly detect excessive freeplay in the rudder 
control load loop. We are issuing this AD to detect and correct 
excessive wear in the load loop components of the control surfaces, 
which could lead to excessive freeplay of the control surfaces, 
flutter, and consequent loss of control of the airplane.

DATES: This AD is effective July 21, 2015.
    The Director of the Federal Register approved the incorporation by 
reference of a certain publication listed in this AD as of July 21, 
2015.

ADDRESSES: For service information identified in this AD, contact 
Boeing Commercial Airplanes, Attention: Data & Services Management, P. 
O. Box 3707, MC 2H-65, Seattle, WA 98124-2207; telephone 206-544-5000, 
extension 1; fax 206-766-5680; Internet https://www.myboeingfleet.com. 
You may view this referenced service information at the FAA, Transport 
Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For information 
on the availability of this material at the FAA, call 425-227-1221. It 
is also available on the Internet at http://www.regulations.gov by 
searching for and locating Docket No. FAA-2014-0485.

Examining the AD Docket

    You may examine the AD docket on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2014-
0485; 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: Haytham Alaidy, Aerospace Engineer, 
Airframe Branch, ANM-120S, FAA, Seattle Aircraft Certification Office 
(ACO), 1601 Lind Avenue SW., Renton, WA 98057-3356; phone: 425-917-
6573; fax: 425-917-6590; email: Haytham.Alaidy@faa.gov.

SUPPLEMENTARY INFORMATION: 

Discussion

    We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR 
part 39 to supersede AD 2007-13-05, Amendment 39-15109 (72 FR 33856, 
June 20, 2007). AD 2007-13-05 applied to all The Boeing Company Model 
777-200, -200LR, -300, and -300ER series airplanes. The NPRM published 
in the Federal Register on July 29, 2014 (79 FR 43981). The NPRM was 
prompted by a determination by the manufacturer that, after AD 2007-13-
05 was issued, the procedure for the rudder freeplay inspection did not 
properly detect excessive freeplay in the rudder control load loop. The 
NPRM proposed to continue to require repetitive freeplay inspections 
and lubrication of the right and left elevators, rudder, and rudder 
tab; and related investigative and corrective actions if necessary. We 
are issuing this AD to detect and correct excessive wear in the load 
loop components of the control surfaces, which could lead to excessive 
freeplay of the control surfaces, flutter, and consequent loss of 
control of the airplane.

Comments

    We gave the public the opportunity to participate in developing 
this AD. The following presents the comments received on the NPRM (79 
FR 43981, July 29, 2014) and the FAA's response to each comment.
    A4A, on behalf of American Airlines (AA), stated that AA is already 
in compliance with the requirements proposed in the NPRM (79 FR 43981, 
July 29, 2014).

Request To Exclude Certain Airplanes

    Boeing requested that the airplanes referenced in the SUMMARY 
section and Discussion paragraph of the NPRM (79 FR 43981, July 29, 
2014) be changed from ``all The Boeing Company Model 777 airplanes'' to 
``most of The Boeing Company Model 777 airplanes.'' Boeing stated that 
Model 777-200F airplanes are not affected by the NPRM.
    We agree to change the phrase ``all The Boeing Company Model 777 
airplanes'' for clarity. This final rule supersedes AD 2007-13-05, 
Amendment 39-15109 (72 FR 33856, June 20, 2007), which was applicable 
to all Boeing Model 777-200, -200LR, -300, and -300ER series airplanes. 
At the time AD 2007-13-05 was published, all Model 777-200, -200LR, -
300, and -300ER series airplanes were referred to as ``all The Boeing 
Company Model 777 airplanes.'' Since then, Model 777F has been added to 
the U.S. type certificate data sheet. We have revised the SUMMARY 
section of this final rule to specify all The Boeing Company Model 777-
200, -200LR, -300, and -300ER series airplanes. The Discussion 
paragraph of the NPRM (79 FR 43981, July 29, 2014) is not restated in 
this final rule.

Request To Clarify the Unsafe Condition

    Boeing requested that we clarify the unsafe condition specified in 
the SUMMARY section, Discussion paragraph, and paragraph (e) of the 
NPRM. Boeing stated that the repetitive freeplay inspections of the 
right and left elevators, rudder, and rudder tab proposed in the NPRM 
(79 FR 43981, July 29, 2014) would not prevent, detect, or correct 
flutter; the proposed freeplay inspections would detect excessive wear 
in the load loop components of the control surfaces. Boeing pointed out 
that excessive wear could lead to excessive freeplay of the control 
surfaces, which could cause unacceptable airframe vibration during 
flight.
    Based on the explanation provided by the commenter, we agree to 
clarify the unsafe condition that is the basis for issuing this final 
rule. However, we will not replace the word ``flutter'' with 
``unacceptable airframe vibration'' because the unsafe condition is 
flutter, not vibration. We have revised the unsafe condition statement 
as follows, ``We are issuing this AD to detect and correct excessive 
wear in the load loop components of the control surfaces, which could 
lead to excessive freeplay of the control surfaces, flutter, and 
consequent loss of control of the airplane.'' This revision appears in 
the SUMMARY section and Discussion paragraph of the SUPPLEMENTARY 
INFORMATION section of this final rule, as well as paragraph (e) of 
this AD.

Request To Clarify the Requirements of Paragraph (g) of the Proposed AD 
(79 FR 43981, July 29, 2014)

    Boeing requested that we revise paragraph (g) of the proposed AD 
(79 FR 43981, July 29, 2014) by deleting ``rudder'' from the following 
sentence: ``If during any inspection required by this paragraph, the 
rudder freeplay exceeds any applicable measurement . . . .'' Boeing 
explained that this statement is incorrect because it is not just the 
rudder freeplay, but if any elevator, rudder, or rudder tab freeplay 
exceeds any applicable measurement specified in the service 
information, the

[[Page 34254]]

applicable corrective actions need to be accomplished before further 
flight.
    We agree to revise the specified sentence in paragraph (g) of this 
AD, because corrective actions before further flight are needed for any 
elevator, rudder, or rudder tab freeplay that exceeds any applicable 
measurement specified in Boeing Special Attention Service Bulletin 777-
27-0062, Revision 2, dated January 27, 2014.

Requests To Correct Errors in the Service Information

    Japan Airlines (JAL) and United Airlines noted that there are 
typographical errors in Appendix B and Appendix C of Boeing Special 
Attention Service Bulletin 777-27-0062, Revision 2, dated January 27, 
2014. JAL requested that the FAA issue an AD to mandate the 
incorporation of the next revision (Revision 3) of Boeing Special 
Attention Service Bulletin 777-27-0062, or provide an exception to 
these typographical errors in this AD. United Airlines requested that 
the FAA issue a global alternative method of compliance (AMOC) to 
correct the errors identified in Boeing Special Attention Service 
Bulletin 777-27-0062, Revision 2, dated January 27, 2014.
    We agree that Appendix B and Appendix C of Boeing Special Attention 
Service Bulletin 777-27-0062, Revision 2, dated January 27, 2014, 
contain typographical errors. However, we do not consider that delaying 
this action until after the release of the manufacturer's planned 
service bulletin revision is warranted. Because some of these 
typographical errors affect the procedures for correctly measuring the 
freeplay of the rudder tab surface, we have provided the corrections 
for those errors in paragraph (i) of this AD instead of issuing an 
AMOC. Paragraph (i) of the proposed AD (79 FR 43981, July 29, 2014) has 
been redesignated as paragraph (i)(1) in this AD, and new paragraphs 
(i)(2), (i)(3), and (i)(4) have been added to this AD. We have also 
revised paragraph (g) of this AD to refer to paragraphs (i)(1) through 
(i)(4) of this AD.

Additional Changes to This Final Rule

    Paragraph (k)(4) of the NPRM (79 FR 43981, July 29, 2014) stated 
that AMOCs approved previously for AD 2007-13-05, Amendment 39-15109 
(72 FR 33856, June 20, 2007), are not approved as AMOCS for the 
requirements of this AD. We have now determined that AMOCs for certain 
actions required by AD 2007-13-05 are acceptable for the corresponding 
requirements of this AD. We have revised paragraph (k)(4) of this AD 
and added new paragraphs (k)(5) and (k)(6) to this AD to include this 
information.

Conclusion

    We reviewed the relevant data, considered the comments received, 
and determined that air safety and the public interest require adopting 
this AD with the changes described previously, and minor editorial 
changes. We have determined that these minor changes:
     Are consistent with the intent that was proposed in the 
NPRM (79 FR 43981, July 29, 2014) for correcting the unsafe condition; 
and
     Do not add any additional burden upon the public than was 
already proposed in the NPRM (79 FR 43981, July 29, 2014).
    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 Special Attention Service Bulletin 777-27-0062, 
Revision 2, dated January 27, 2014. The service information describes 
procedures for repetitive freeplay inspections and lubrication of the 
right and left elevators, rudder, and rudder tab, and related 
investigative and corrective actions. This service information is 
reasonably available because the interested parties have access to it 
through their normal course of business or by the means identified in 
the ADDRESSES section of this AD.

Costs of Compliance

    We estimate that this AD affects 142 airplanes of U.S. registry. 
The new actions of this AD would add no additional economic burden to 
that imposed by AD 2007-13-05, Amendment 39-15109 (72 FR 33856, June 
20, 2007). The current costs for this AD are repeated for the 
convenience of affected operators, as follows:

                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                                                                                 Cost on U.S.
              Action                    Labor cost        Parts cost      Cost per product        operators
----------------------------------------------------------------------------------------------------------------
Measurement (inspection),          4 work-hours x $85               $0  $340 per             $48,280 per
 elevator.                          per hour = $340                      measurement          measurement
                                    per measurement                      (inspection) cycle.  (inspection)
                                    (inspection) cycle.                                       cycle.
Lubrication, elevator............  17 work-hours x $85               0  $1,445 per           $205,190 per
                                    per hour = $1,445                    lubrication cycle.   lubrication cycle.
                                    per lubrication
                                    cycle.
Measurement (inspection), rudder.  4 work-hours x $85                0  $340 per             $48,280 per
                                    per hour = $340                      measurement          measurement
                                    per measurement                      (inspection) cycle.  (inspection)
                                    (inspection) cycle.                                       cycle.
Lubrication, rudder..............  7 work-hours x $85                0  $595 per             $84,490 per
                                    per hour = $595                      lubrication cycle.   lubrication cycle.
                                    per lubrication
                                    cycle.
Measurement (inspection), rudder   3 work-hours x $85                0  $255 per             $36,210 per
 tab.                               per hour = $255                      measurement          measurement
                                    per measurement                      (inspection) cycle.  (inspection)
                                    (inspection) cycle.                                       cycle.
Lubrication, rudder tab..........  5 work-hours x $85                0  $425 per             $60,350 per
                                    per hour = $425                      lubrication cycle.   lubrication cycle.
                                    per lubrication
                                    cycle.
----------------------------------------------------------------------------------------------------------------

    We have received no definitive data that would enable us to provide 
cost estimates for the on-condition corrective 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

[[Page 34255]]

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) 
2007-13-05, Amendment 39-15109 (72 FR 33856, June 20, 2007), and adding 
the following new AD:

2015-12-03 The Boeing Company: Amendment 39-18176 ; Docket No. FAA-
2014-0485; Directorate Identifier 2014-NM-093-AD.

(a) Effective Date

    This AD is effective July 21, 2015.

(b) Affected ADs

    This AD replaces AD 2007-13-05, Amendment 39-15109 (72 FR 33856, 
June 20, 2007).

(c) Applicability

    This AD applies to The Boeing Company Model 777-200, -200LR, -
300, and -300ER series airplanes, certificated in any category, as 
identified in paragraphs (c)(1) and (c)(2) of this AD.
    (1) Airplanes having a Variable Number identified in paragraph 
1.A., ``Effectivity,'' of Boeing Special Attention Service Bulletin 
777-27-0062, Revision 2, dated January 27, 2014.
    (2) Airplanes having a date of issuance of the original 
airworthiness certificate or date of issuance of the original export 
certificate of airworthiness on or after January 27, 2014.

(d) Subject

    Air Transport Association (ATA) of America Code 27, Flight 
Controls.

(e) Unsafe Condition

    This AD was prompted by the manufacturer's determination that 
the procedure for the rudder freeplay inspection does not properly 
detect excessive freeplay in the rudder control load loop. We are 
issuing this AD to detect and correct excessive wear in the load 
loop components of the control surfaces, which could lead to 
excessive freeplay of the control surfaces, flutter, and consequent 
loss of control of the airplane.

(f) Compliance

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

(g) Repetitive Inspections of Elevators, Rudder, and Rudder Tab

    At the applicable times specified in tables 1, 2, and 3 of 
paragraph 1.E., ``Compliance,'' of Boeing Special Attention Service 
Bulletin 777-27-0062, Revision 2, dated January 27, 2014, except as 
provided by paragraph (i)(1) of this AD: Inspect the freeplay of the 
right and left elevators, rudder, and rudder tab by accomplishing 
all of the actions specified in Parts 1, 3, and 5 of the 
Accomplishment Instructions of Boeing Special Attention Service 
Bulletin 777-27-0062, Revision 2, dated January 27, 2014, except as 
provided by paragraphs (i)(2) through (i)(4) of this AD. Repeat the 
inspections thereafter at the intervals specified in tables 1, 2, 
and 3 of paragraph 1.E., ``Compliance,'' of Boeing Special Attention 
Service Bulletin 777-27-0062, Revision 2, dated January 27, 2014. 
If, during any inspection required by this paragraph, the freeplay 
exceeds any applicable measurement specified in Part 1, 3, and 5, as 
applicable, of the Accomplishment Instructions of Boeing Special 
Attention Service Bulletin 777-27-0062, Revision 2, dated January 
27, 2014, before further flight, do the applicable corrective 
actions in accordance with Part 1, 3, and 5 of the Accomplishment 
Instructions of Boeing Special Attention Service Bulletin 777-27-
0062, Revision 2, dated January 27, 2014.

(h) Repetitive Lubrication

    At the applicable times specified in tables 1, 2, and 3 of 
paragraph 1.E., ``Compliance,'' of Boeing Special Attention Service 
Bulletin 777-27-0062, Revision 2, dated January 27, 2014, except as 
provided by paragraph (i)(1) of this AD: Lubricate the elevator 
components, rudder components, and rudder tab components, by 
accomplishing all of the actions specified in Parts 2, 4, and 6 of 
the Accomplishment Instructions of Boeing Special Attention Service 
Bulletin 777-27-0062, Revision 2, dated January 27, 2014, as 
applicable. Repeat the lubrication thereafter at the interval 
specified in tables 1, 2, and 3 of paragraph 1.E., ``Compliance,'' 
of Boeing Special Attention Service Bulletin 777-27-0062, Revision 
2, dated January 27, 2014, as applicable.

(i) Exception to Service Information Specifications

    (1) Where Boeing Special Attention Service Bulletin 777-27-0062, 
Revision 2, dated January 27, 2014, specifies a compliance time 
``after the original issue date on this service bulletin,'' this AD 
requires compliance within the specified compliance time after July 
25, 2007 (the effective date of AD 2007-13-05, Amendment 39-15109 
(72 FR 33856, June 20, 2007)).
    (2) Where Appendix B, paragraph 1.f., ``Freeplay Inspection,'' 
step (8), of Boeing Special Attention Service Bulletin 777-27-0062, 
Revision 2, dated January 27, 2014, specifies that the center of the 
pad must be within 1.0 inch (13 millimeters) of the center line of 
the rib rivets in the rudder tab, this AD requires that the center 
of the tab must be within 1.0 inch (25 millimeters) of the center 
line of the rib rivets in the rudder tab.
    (3) Where Appendix C, paragraph 1.e., ``Rudder Tab Surface 
Freeplay--Inspection,'' step (2) and step (6), of Boeing Special 
Attention Service Bulletin 777-27-0062, Revision 2, dated January 
27, 2014, specify that the placement of the force gage and pad 
should be within one inch of the centerline line of the middle 
rudder PCU rib and at 12 +/-1 inch (305 +/-72 millimeters) forward 
of the rudder tab trailing edge, this AD requires placement of the 
force gage and pad within one inch of the centerline line of the 
middle rudder PCU rib and at 12 +/-1 inch (305 +/-25 millimeters) 
forward of the rudder tab trailing edge.
    (4) Where Appendix C, paragraph 1.e., ``Rudder Tab Surface 
Freeplay--Inspection,'' step (3), of Boeing Special Attention 
Service Bulletin 777-27-0062, Revision 2, dated January 27, 2014, 
specifies to apply a 30 +/-pound (133 +/-14 newton) force, this AD 
requires applying a 30 +/-3 pound force (133 +/-14 newton) force.

(j) Credit for Previous Actions

    This paragraph provides credit for the 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 
specified in paragraph (j)(1) or (j)(2) of this AD.
    (1) Boeing Special Attention Service Bulletin 777-27-0062, dated 
July 18, 2006, which was incorporated by reference in AD 2007-13-05, 
Amendment 39-15109 (72 FR 33856, June 20, 2007).

[[Page 34256]]

    (2) Boeing Special Attention Service Bulletin 777-27-0062, 
Revision 1, dated October 1, 2009, which is not incorporated by 
reference in this AD.

(k) 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 (l)(1) 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) AMOCs approved previously for the freeplay measurements of 
the right and left elevators and rudder tab required by paragraph 
(f) of AD 2007-13-05, Amendment 39-15109 (72 FR 33856, June 20, 
2007), are approved as AMOCs for the corresponding requirements of 
this AD.
    (5) AMOCs approved previously for the freeplay measurements of 
the rudder required by paragraph (f) of AD 2007-13-05, Amendment 39-
15109 (72 FR 33856, June 20, 2007), are not approved as AMOCs for 
the corresponding requirements of this AD. We are not aware of any 
such AMOCs.
    (6) AMOCs approved previously for the repetitive lubrications 
required by paragraph (g) of AD 2007-13-05, Amendment 39-15109 (72 
FR 33856, June 20, 2007), are approved as AMOCs for the 
corresponding requirements of this AD.

(l) Related Information

    (1) For more information about this AD, contact Haytham Alaidy, 
Aerospace Engineer, Airframe Branch, ANM-120S, FAA, Seattle Aircraft 
Certification Office (ACO), 1601 Lind Avenue SW., Renton, WA 98057-
3356; phone: 425-917-6573; fax: 425-917-6590; email: 
Haytham.Alaidy@faa.gov.
    (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 the AD specifies otherwise.
    (i) Boeing Special Attention Service Bulletin 777-27-0062, 
Revision 2, dated January 27, 2014.
    (ii) Reserved.
    (3) For service information identified in this AD, contact 
Boeing Commercial Airplanes, Attention: Data & Services Management, 
P. O. Box 3707, MC 2H-65, Seattle, WA 98124-2207; telephone 206-544-
5000, extension 1; fax 206-766-5680; Internet https://www.myboeingfleet.com.
    (4) You may view this service information at FAA, Transport 
Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For 
information on the availability of this material at the FAA, call 
425-227-1221.
    (5) You may view this service information that is incorporated 
by reference at the National Archives and Records Administration 
(NARA). For information on the availability of this material at 
NARA, call 202-741-6030, or go to: http://www.archives.gov/federal-register/cfr/ibr-locations.html.

    Issued in Renton, Washington, on June 3, 2015.
Jeffrey E. Duven,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2015-14174 Filed 6-15-15; 8:45 am]
 BILLING CODE 4910-13-P