Airworthiness Directives; The Boeing Company Airplanes, 3158-3161 [2015-00009]

Download as PDF 3158 Federal Register / Vol. 80, No. 14 / Thursday, January 22, 2015 / Rules and Regulations on an airplane does not constitute terminating action for any inspection required by paragraph (g) of this AD. (2) If, during any inspection required by paragraph (g)(1) of this AD, more than one discrepancy (any missing or broken or migrated fastener) is found on the left- or right-side: Before further flight, replace all affected fasteners on the affected side(s), in accordance with Airbus AOT A57N006–14, Revision 00, dated December 4, 2014. One fastener per side may be missing or broken or migrated provided the applicable actions required by paragraph (h)(1) of this AD are done. Replacement of fasteners on an airplane does not constitute terminating action for any inspection required by paragraph (g) of this AD. (i) Corrective Actions for the Inspections Required by Paragraph (g)(2) of This AD (1) If, during any inspection required by paragraph (g)(2) of this AD, only one discrepancy (any missing or broken nut or fastener tail) is found on the left- or rightside: Before further flight, do corrective actions in accordance with a method approved by the Manager, International Branch, ANM–116, Transport Airplane Directorate, FAA. Replacement of fasteners on an airplane does not constitute terminating action for any inspection required by paragraph (g) of this AD. (2) If, during any inspection required by paragraph (g)(2) of this AD, more than one discrepancy (any missing or broken nut or fastener tail) is found on the left- or rightside: Before further flight, replace all affected fasteners on the affected side(s), in accordance with Airbus AOT A57N006–14, Revision 00, dated December 4, 2014. One fastener per side may be missing or broken or migrated provided the applicable actions required by paragraph (i)(1) of this AD are done. Replacement of fasteners on an airplane does not constitute terminating action for any inspection required by paragraph (g) of this AD. tkelley on DSK3SPTVN1PROD with RULES (j) Special Flight Permits Special flight permits, as described in Section 21.197 and Section 21.199 of the Federal Aviation Regulations (14 CFR 21.197 and 21.199), are not allowed. (k) Other FAA Provisions (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 Manager, International Branch, send it to ATTN: Sanjay Ralhan, Aerospace Engineer, International Branch, ANM–116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057–3356; telephone 425–227–1405; fax 425–227–1149. 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 VerDate Sep<11>2014 16:25 Jan 21, 2015 Jkt 235001 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 EASA; or Airbus’s EASA Design Organization Approval (DOA). If approved by the DOA, the approval must include the DOA-authorized signature. (l) Related Information For further information about this AD, contact: Sanjay Ralhan, Aerospace Engineer, International Branch, ANM–116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057–3356; telephone 425–227–1405; fax 425–227–1149. (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) Airbus Alert Operators Transmission A57N006–14, Revision 00, dated December 4, 2014. (ii) Reserved. (3) For service information referenced in this AD, contact Airbus, Airworthiness Office—EIAS, 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 https://www.airbus.com. You may view this referenced service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. (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 National Archives and Records Administration (NARA). For information on the availability of this material at NARA, call 202–741–6030, or go to: https:// www.archives.gov/federal-register/cfr/ibrlocations.html. Issued in Renton, Washington, on January 7, 2015. Jeffrey E. Duven, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2015–00716 Filed 1–21–15; 8:45 am] BILLING CODE 4910–13–P PO 00000 Frm 00020 Fmt 4700 Sfmt 4700 DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2014–0580; Directorate Identifier 2014–NM–081–AD; Amendment 39–18062; AD 2015–01–01] RIN 2120–AA64 Airworthiness Directives; The Boeing Company Airplanes Federal Aviation Administration (FAA), DOT. ACTION: Final rule. AGENCY: We are superseding Airworthiness Directive (AD) 2011–09– 11, for certain The Boeing Company Model 777–200 and –300 series airplanes. AD 2011–09–11 required repetitive inspections for hydraulic fluid contamination of the interior of the strut disconnect assembly; repetitive inspections for discrepancies of the interior of the strut disconnect assembly, if necessary; repetitive inspections of the exterior of the strut disconnect assembly for cracks, if necessary; corrective action if necessary; and an optional terminating action for the inspections. This new AD adds, for certain airplanes, an inspection of the side and top cover plates to determine if all cover plate attach fasteners have been installed, and installing any missing fasteners including doing an inspection for damage, and repair if necessary. This AD was prompted by reports of side and top cover plates installed with missing fastener bolts, which results in an unsealed opening on the system disconnect assembly. We are issuing this AD to detect and correct hydraulic fluid contamination, which can cause cracking of titanium parts in the system disconnect assembly; and also to detect and correct missing fasteners, which results in unsealed openings on the system disconnect assembly. Both unsafe conditions can compromise the engine firewall and result in fire hazards for both the engine compartment and the strut. DATES: This AD is effective February 26, 2015. The Director of the Federal Register approved the incorporation by reference of a certain publication listed in this AD as of February 26, 2015. The Director of the Federal Register approved the incorporation by reference of certain other publications listed in this AD as of June 6, 2011 (76 FR 24354, May 2, 2011). ADDRESSES: For service information identified in this AD, contact Boeing SUMMARY: E:\FR\FM\22JAR1.SGM 22JAR1 Federal Register / Vol. 80, No. 14 / Thursday, January 22, 2015 / Rules and Regulations 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. Ground Floor, Room W12–140, 1200 New Jersey Avenue SE., Washington, DC 20590. FOR FURTHER INFORMATION CONTACT: Kevin Nguyen, Aerospace Engineer, Propulsion Branch, ANM–140S, FAA, Seattle Aircraft Certification Office (ACO), 1601 Lind Avenue SW., Renton, WA 98057–3356; phone: 425–917–6501; fax: 425–917–6590; email: kevin.nguyen@faa.gov. SUPPLEMENTARY INFORMATION: Examining the AD Docket You may examine the AD docket on the Internet at https:// www.regulations.govby searching for and locating Docket No. FAA–2014– 0580; 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 Discussion We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 to supersede AD 2011–09–11, Amendment 39–16673 (76 FR 24354, May 2, 2011). AD 2011–09–11 applied to The Boeing Company Model 777–200 and – 300 series airplanes equipped with Pratt and Whitney engines. The NPRM published in the Federal Register on August 26, 2014 (79 FR 50877). Comments We gave the public the opportunity to participate in developing this AD. We 3159 have considered the comments received. United Airlines and Boeing supported the NPRM (79 FR 50877, August 26, 2014). Conclusion We reviewed the relevant data, considered the comments received, and determined that air safety and the public interest require adopting this AD as proposed, except for minor editorial changes. We have determined that these minor changes: • Are consistent with the intent that was proposed in the NPRM (79 FR 50877, August 26, 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 50877, August 26, 2014). Costs of Compliance We estimate that this AD affects 54 airplanes of U.S. registry. We estimate the following costs to comply with this AD: ESTIMATED COSTS Action Inspections [retained actions from AD 2011-09-11, Amendment 39-16673 (76 FR 24354, May 2, 2011)]. Inspection of cover plate fasteners [new action]. Labor cost Cost per product Parts cost Cost on U.S. operators 18 work-hours × $85 per hour = $1,530 ................................ $0 $1,530 $82,620 8 work-hours × $85 per hour = $680 ..................................... 0 680 36,720 We estimate the following costs to do any necessary repairs/replacements that will be required based on the results of the inspections. We have no way of determining the number of aircraft that might need these repairs/replacements: ON-CONDITION COSTS Replacement [retained actions from AD 2011-09–11, Amendment 39– 16673 (76 FR 24354, May 2, 2011)]. Inspection of electrical components and installation of new fasteners [new actions]. tkelley on DSK3SPTVN1PROD with RULES Labor cost 35 work-hours × $85 per hour = $2,975 ................................................... $420,440 $423,415 14 work-hours × $85 per hour = $1,190 ................................................... 458 1,648 According to the manufacturer, some of the costs of this AD may be covered under warranty, thereby reducing the cost impact on affected individuals. We do not control warranty coverage for affected individuals. As a result, we have included all costs in our cost estimate. VerDate Sep<11>2014 16:25 Jan 21, 2015 Jkt 235001 Parts cost Cost per product Action 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. PO 00000 Frm 00021 Fmt 4700 Sfmt 4700 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 E:\FR\FM\22JAR1.SGM 22JAR1 3160 Federal Register / Vol. 80, No. 14 / Thursday, January 22, 2015 / Rules and Regulations 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) 2011–09–11, Amendment 39–16673 (76 FR 24354, May 2, 2011), and adding the following new AD: ■ 2015–01–01 The Boeing Company: Amendment 39–18062; Docket No. FAA–2014–0580; Directorate Identifier 2014–NM–081–AD. tkelley on DSK3SPTVN1PROD with RULES (a) Effective Date This AD is effective February 26, 2015. (b) Affected ADs This AD replaces AD 2011–09–11, Amendment 39–16673 (76 FR 24354, May 2, 2011). (c) Applicability This AD applies to The Boeing Company Model 777–200 and –300 series airplanes, VerDate Sep<11>2014 16:25 Jan 21, 2015 Jkt 235001 certificated in any category; equipped with Pratt and Whitney engines; as identified in Boeing Service Bulletin 777–54A0024, Revision 2, dated January 23, 2014. (d) Subject Air Transport Association (ATA) of America Code 54, Nacelles/Pylons. (e) Unsafe Condition This AD was prompted by reports of side and top cover plates installed with missing fastener bolts, which results in an unsealed opening on the system disconnect assembly. We are issuing this AD to detect and correct hydraulic fluid contamination, which can cause cracking of titanium parts in the system disconnect assembly; and also to detect and correct missing fasteners, which results in unsealed openings on the system disconnect assembly. Both unsafe conditions can compromise the engine firewall and result in fire hazards for both the engine compartment and the strut. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Retained Inspections and Corrective Actions With Revised Service Information This paragraph restates the requirements of paragraph (g) of AD 2011–09–11, Amendment 39–16673 (76 FR 24354, May 2, 2011), with revised service information. Within 12 months after June 6, 2011 (the effective date of AD 2011–09–11): Do a general visual inspection for hydraulic fluid contamination of the interior of the strut disconnect assembly, in accordance with Part 1 of the Accomplishment Instructions of Boeing Service Bulletin 777–54A0024, Revision 1, dated November 4, 2010; or Revision 2, dated January 23, 2014. As of the effective date of this AD, use only Boeing Service Bulletin 777–54A0024, Revision 2, dated January 23, 2014, for accomplishing the actions in this paragraph. (1) For airplanes on which no hydraulic fluid contamination is found (Condition 1): Repeat the general visual inspection required by paragraph (g) of this AD thereafter at intervals not to exceed 6,000 flight cycles or 750 days, whichever occurs first. (2) For airplanes on which hydraulic fluid contamination is found (Condition 2): Before further flight, do a detailed inspection for discrepancies (e.g., hydraulic fluid coking, heat discoloration, cracks, and etching or pitting) of the interior of the strut disconnect assembly, in accordance with Part 2 of the Accomplishment Instructions of Boeing Service Bulletin 777–54A0024, Revision 1, dated November 4, 2010; or Revision 2, dated January 23, 2014. As of the effective date of this AD, use only Boeing Service Bulletin 777–54A0024, Revision 2, dated January 23, 2014, for accomplishing the actions in this paragraph. (i) For airplanes on which no discrepancy is found during the inspection required by paragraph (g)(2) of this AD (Condition 2A): Repeat the detailed inspection required by paragraph (g)(2) of this AD thereafter at intervals not to exceed 6,000 flight cycles or 750 days, whichever occurs first. PO 00000 Frm 00022 Fmt 4700 Sfmt 4700 (ii) For airplanes on which hydraulic fluid coking or heat discoloration is found but no cracking, etching, or pitting is found during the inspection required by paragraph (g)(2) of this AD (Condition 2B): Do the actions required by paragraph (g)(2)(ii)(A) and (g)(2)(ii)(B) of this AD. (A) Within 300 flight cycles after doing the inspection required by paragraph (g)(2) of this AD: Do a detailed inspection of the exterior of the strut disconnect assembly for cracks, in accordance with Part 3 of the Accomplishment Instructions of Boeing Service Bulletin 777–54A0024, Revision 1, dated November 4, 2010; or Revision 2, dated January 23, 2014; and repeat the detailed inspection thereafter at intervals not to exceed 300 flight cycles. As of the effective date of this AD, use only Boeing Service Bulletin 777–54A0024, Revision 2, dated January 23, 2014, for accomplishing the actions in this paragraph. (B) Within 6,000 flight cycles or 750 days after hydraulic fluid coking and/or heat discoloration was found during the inspection required by paragraph (g)(2) of this AD, whichever occurs first: Replace the titanium system disconnect assembly with an Inconel system, in accordance with Part 4 of the Accomplishment Instructions of Boeing Service Bulletin 777–54A0024, Revision 1, dated November 4, 2010; or Revision 2, dated January 23, 2014. As of the effective date of this AD, use only Boeing Service Bulletin 777–54A0024, Revision 2, dated January 23, 2014, for accomplishing the actions in this paragraph. (h) Retained Corrective Action With Revised Service Information This paragraph restates the requirements of paragraph (h) of AD 2011–09–11, Amendment 39–16673 (76 FR 24354, May 2, 2011), with revised service information. For airplanes on which any crack, etching, or pitting is found during any inspection required by paragraph (g)(2) or (g)(2)(ii)(A) of this AD (Condition 3): Before further flight, replace the titanium system disconnect assembly with an Inconel system, in accordance with Part 4 of the Accomplishment Instructions of Boeing Service Bulletin 777–54A0024, Revision 1, dated November 4, 2010; or Revision 2, dated January 23, 2014. As of the effective date of this AD, use only Boeing Service Bulletin 777–54A0024, Revision 2, dated January 23, 2014, for accomplishing the actions in this paragraph. (i) Retained Optional Terminating Action With Revised Service Information This paragraph restates the requirements of paragraph (i) of AD 2011–09–11, Amendment 39–16673 (76 FR 24354, May 2, 2011), with revised service information. Replacing the titanium system disconnect assembly with an Inconel system disconnect assembly in accordance with Part 4 of the Accomplishment Instructions of Boeing Service Bulletin 777–54A0024, Revision 1, dated November 4, 2010; or Revision 2, dated January 23, 2014; terminates the actions required by paragraphs (g) and (h) of this AD. As of the effective date of this AD, use only Boeing Service Bulletin 777–54A0024, E:\FR\FM\22JAR1.SGM 22JAR1 Federal Register / Vol. 80, No. 14 / Thursday, January 22, 2015 / Rules and Regulations Revision 2, dated January 23, 2014, for accomplishing the actions in this paragraph. (j) New Inspection and Corrective Action For airplanes on which the system disconnect assembly has been replaced in accordance with Part 4 of the Accomplishment Instructions of Boeing Service Bulletin 777–54A0024, dated April 1, 2010; or Revision 1, dated November 4, 2010: Within 1,125 days after the effective date of this AD, do a detailed inspection of the cover plate fasteners to determine if all cover plate attach fasteners are installed, in accordance with Part 5 of the Accomplishment Instructions of Boeing Service Bulletin 777– 54A0024, Revision 2, dated January 23, 2014. If any fastener is missing, before further flight, install fasteners (including doing a detailed inspection for damage of the electrical components and repairing any damaged components), in accordance with Part 6 of the Accomplishment Instructions of Boeing Service Bulletin 777–54A0024, Revision 2, dated January 23, 2014. tkelley on DSK3SPTVN1PROD with RULES (k) Credit for Previous Actions This paragraph restates the credit provided by paragraph (j) of AD 2011–09–11, Amendment 39–16673 (76 FR 24354, May 2, 2011). This paragraph provides credit for the corresponding actions required by paragraphs (g), (h), and (i) of this AD, if those actions were performed before June 6, 2011 (the effective date of AD 2011–09–11) using Boeing Service Bulletin 777–54A0024, dated April 1, 2010, which is not incorporated by reference in this AD. (l) 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 (m)(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. (m) Related Information (1) For more information about this AD, contact Kevin Nguyen, Aerospace Engineer, Propulsion Branch, ANM–140S, FAA, Seattle Aircraft Certification Office (ACO), 1601 Lind Avenue SW., Renton, WA 98057–3356; VerDate Sep<11>2014 16:25 Jan 21, 2015 Jkt 235001 phone: 425–917–6501; fax: 425–917–6590; email: kevin.nguyen@faa.gov. (2) Service information identified in this AD that is not incorporated by reference is available at the addresses specified in paragraphs (n)(5) and (n)(6) of this AD. (n) 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 February 26, 2015. (i) Boeing Service Bulletin 777–54A0024, Revision 2, dated January 23, 2014. (ii) Reserved. (4) The following service information was approved for IBR on June 6, 2011 (76 FR 24354, May 2, 2011). (i) Boeing Service Bulletin 777–54A0024, Revision 1, dated November 4, 2010. (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 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 https:// www.archives.gov/federal-register/cfr/ibrlocations.html. Issued in Renton, Washington, on December 22, 2014. Michael Kaszycki, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2015–00009 Filed 1–21–15; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2014–0925; Directorate Identifier 2014–NM–229–AD; Amendment 39–18066; AD 2014–25–52] RIN 2120–AA64 Airworthiness Directives; Airbus Airplanes Federal Aviation Administration (FAA), DOT. ACTION: Final rule; request for comments. AGENCY: PO 00000 Frm 00023 Fmt 4700 Sfmt 4700 3161 We are adopting a new airworthiness directive (AD) for all Airbus Model A330–200 Freighter, –200, and –300 series airplanes and Model A340–200, –300, –500, and –600 series airplanes. This emergency AD was sent previously to all known U.S. owners and operators of these airplanes. This AD requires revising the airplane flight manual to advise the flightcrew of emergency procedures for abnormal Alpha Protection (Alpha Prot). This AD was prompted by a report of Angle of Attack (AoA) probes jamming on an inservice Airbus Model A321 airplane. We are issuing this AD to ensure that the flightcrew has procedures to counteract the pitch down order due to abnormal activation of the Alpha Prot. An abnormal Alpha Prot, if not corrected, could result in loss of control of the airplane. DATES: This AD is effective February 6, 2015 to all persons except those persons to whom it was made immediately effective by Emergency AD 2014–25–52, issued on December 10, 2014, which contained the requirements of this amendment. We must receive comments on this AD by March 9, 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 https://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. SUMMARY: Examining the AD Docket You may examine the AD docket on the Internet at https:// www.regulations.gov by searching for and locating Docket No. FAA–2014– 0925; 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: Vladimir Ulyanov, Aerospace Engineer, International Branch, ANM–116, E:\FR\FM\22JAR1.SGM 22JAR1

Agencies

[Federal Register Volume 80, Number 14 (Thursday, January 22, 2015)]
[Rules and Regulations]
[Pages 3158-3161]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2015-00009]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2014-0580; Directorate Identifier 2014-NM-081-AD; 
Amendment 39-18062; AD 2015-01-01]
RIN 2120-AA64


Airworthiness Directives; The Boeing Company Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule.

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

SUMMARY: We are superseding Airworthiness Directive (AD) 2011-09-11, 
for certain The Boeing Company Model 777-200 and -300 series airplanes. 
AD 2011-09-11 required repetitive inspections for hydraulic fluid 
contamination of the interior of the strut disconnect assembly; 
repetitive inspections for discrepancies of the interior of the strut 
disconnect assembly, if necessary; repetitive inspections of the 
exterior of the strut disconnect assembly for cracks, if necessary; 
corrective action if necessary; and an optional terminating action for 
the inspections. This new AD adds, for certain airplanes, an inspection 
of the side and top cover plates to determine if all cover plate attach 
fasteners have been installed, and installing any missing fasteners 
including doing an inspection for damage, and repair if necessary. This 
AD was prompted by reports of side and top cover plates installed with 
missing fastener bolts, which results in an unsealed opening on the 
system disconnect assembly. We are issuing this AD to detect and 
correct hydraulic fluid contamination, which can cause cracking of 
titanium parts in the system disconnect assembly; and also to detect 
and correct missing fasteners, which results in unsealed openings on 
the system disconnect assembly. Both unsafe conditions can compromise 
the engine firewall and result in fire hazards for both the engine 
compartment and the strut.

DATES: This AD is effective February 26, 2015.
    The Director of the Federal Register approved the incorporation by 
reference of a certain publication listed in this AD as of February 26, 
2015.
    The Director of the Federal Register approved the incorporation by 
reference of certain other publications listed in this AD as of June 6, 
2011 (76 FR 24354, May 2, 2011).

ADDRESSES: For service information identified in this AD, contact 
Boeing

[[Page 3159]]

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.

Examining the AD Docket

    You may examine the AD docket on the Internet at https://www.regulations.govby searching for and locating Docket No. FAA-2014-
0580; 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: Kevin Nguyen, Aerospace Engineer, 
Propulsion Branch, ANM-140S, FAA, Seattle Aircraft Certification Office 
(ACO), 1601 Lind Avenue SW., Renton, WA 98057-3356; phone: 425-917-
6501; fax: 425-917-6590; email: kevin.nguyen@faa.gov.

SUPPLEMENTARY INFORMATION:

Discussion

    We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR 
part 39 to supersede AD 2011-09-11, Amendment 39-16673 (76 FR 24354, 
May 2, 2011). AD 2011-09-11 applied to The Boeing Company Model 777-200 
and - 300 series airplanes equipped with Pratt and Whitney engines. The 
NPRM published in the Federal Register on August 26, 2014 (79 FR 
50877).

Comments

    We gave the public the opportunity to participate in developing 
this AD. We have considered the comments received. United Airlines and 
Boeing supported the NPRM (79 FR 50877, August 26, 2014).

Conclusion

    We reviewed the relevant data, considered the comments received, 
and determined that air safety and the public interest require adopting 
this AD as proposed, except for minor editorial changes. We have 
determined that these minor changes:
     Are consistent with the intent that was proposed in the 
NPRM (79 FR 50877, August 26, 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 50877, August 26, 2014).

Costs of Compliance

    We estimate that this AD affects 54 airplanes of U.S. registry.
    We estimate the following costs to comply with this AD:

                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                                                                     Cost per      Cost on U.S.
               Action                         Labor cost            Parts cost        product        operators
----------------------------------------------------------------------------------------------------------------
Inspections [retained actions from   18 work-hours x $85 per                  $0          $1,530         $82,620
 AD 2011-09-11, Amendment 39-16673    hour = $1,530.
 (76 FR 24354, May 2, 2011)].
Inspection of cover plate fasteners  8 work-hours x $85 per hour               0             680          36,720
 [new action].                        = $680.
----------------------------------------------------------------------------------------------------------------

    We estimate the following costs to do any necessary repairs/
replacements that will be required based on the results of the 
inspections. We have no way of determining the number of aircraft that 
might need these repairs/replacements:

                                               On-Condition Costs
----------------------------------------------------------------------------------------------------------------
                                                                                                     Cost per
                   Action                                 Labor cost                Parts cost        product
----------------------------------------------------------------------------------------------------------------
Replacement [retained actions from AD 2011-  35 work-hours x $85 per hour =             $420,440        $423,415
 09-11, Amendment 39-16673 (76 FR 24354,      $2,975.
 May 2, 2011)].
Inspection of electrical components and      14 work-hours x $85 per hour =                  458           1,648
 installation of new fasteners [new           $1,190.
 actions].
----------------------------------------------------------------------------------------------------------------

    According to the manufacturer, some of the costs of this AD may be 
covered under warranty, thereby reducing the cost impact on affected 
individuals. We do not control warranty coverage for affected 
individuals. As a result, we have included all costs in our cost 
estimate.

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

[[Page 3160]]

is within the scope of that authority because it addresses an unsafe 
condition that is likely to exist or develop on products identified in 
this rulemaking action.

Regulatory Findings

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

List of Subjects in 14 CFR Part 39

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

Adoption of the Amendment

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

PART 39--AIRWORTHINESS DIRECTIVES

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

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

Sec.  39.13  [Amended]

0
2. The FAA amends Sec.  39.13 by removing Airworthiness Directive (AD) 
2011-09-11, Amendment 39-16673 (76 FR 24354, May 2, 2011), and adding 
the following new AD:

2015-01-01 The Boeing Company: Amendment 39-18062; Docket No. FAA-
2014-0580; Directorate Identifier 2014-NM-081-AD.

(a) Effective Date

    This AD is effective February 26, 2015.

(b) Affected ADs

    This AD replaces AD 2011-09-11, Amendment 39-16673 (76 FR 24354, 
May 2, 2011).

(c) Applicability

    This AD applies to The Boeing Company Model 777-200 and -300 
series airplanes, certificated in any category; equipped with Pratt 
and Whitney engines; as identified in Boeing Service Bulletin 777-
54A0024, Revision 2, dated January 23, 2014.

(d) Subject

    Air Transport Association (ATA) of America Code 54, Nacelles/
Pylons.

(e) Unsafe Condition

    This AD was prompted by reports of side and top cover plates 
installed with missing fastener bolts, which results in an unsealed 
opening on the system disconnect assembly. We are issuing this AD to 
detect and correct hydraulic fluid contamination, which can cause 
cracking of titanium parts in the system disconnect assembly; and 
also to detect and correct missing fasteners, which results in 
unsealed openings on the system disconnect assembly. Both unsafe 
conditions can compromise the engine firewall and result in fire 
hazards for both the engine compartment and the strut.

(f) Compliance

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

(g) Retained Inspections and Corrective Actions With Revised Service 
Information

    This paragraph restates the requirements of paragraph (g) of AD 
2011-09-11, Amendment 39-16673 (76 FR 24354, May 2, 2011), with 
revised service information. Within 12 months after June 6, 2011 
(the effective date of AD 2011-09-11): Do a general visual 
inspection for hydraulic fluid contamination of the interior of the 
strut disconnect assembly, in accordance with Part 1 of the 
Accomplishment Instructions of Boeing Service Bulletin 777-54A0024, 
Revision 1, dated November 4, 2010; or Revision 2, dated January 23, 
2014. As of the effective date of this AD, use only Boeing Service 
Bulletin 777-54A0024, Revision 2, dated January 23, 2014, for 
accomplishing the actions in this paragraph.
    (1) For airplanes on which no hydraulic fluid contamination is 
found (Condition 1): Repeat the general visual inspection required 
by paragraph (g) of this AD thereafter at intervals not to exceed 
6,000 flight cycles or 750 days, whichever occurs first.
    (2) For airplanes on which hydraulic fluid contamination is 
found (Condition 2): Before further flight, do a detailed inspection 
for discrepancies (e.g., hydraulic fluid coking, heat discoloration, 
cracks, and etching or pitting) of the interior of the strut 
disconnect assembly, in accordance with Part 2 of the Accomplishment 
Instructions of Boeing Service Bulletin 777-54A0024, Revision 1, 
dated November 4, 2010; or Revision 2, dated January 23, 2014. As of 
the effective date of this AD, use only Boeing Service Bulletin 777-
54A0024, Revision 2, dated January 23, 2014, for accomplishing the 
actions in this paragraph.
    (i) For airplanes on which no discrepancy is found during the 
inspection required by paragraph (g)(2) of this AD (Condition 2A): 
Repeat the detailed inspection required by paragraph (g)(2) of this 
AD thereafter at intervals not to exceed 6,000 flight cycles or 750 
days, whichever occurs first.
    (ii) For airplanes on which hydraulic fluid coking or heat 
discoloration is found but no cracking, etching, or pitting is found 
during the inspection required by paragraph (g)(2) of this AD 
(Condition 2B): Do the actions required by paragraph (g)(2)(ii)(A) 
and (g)(2)(ii)(B) of this AD.
    (A) Within 300 flight cycles after doing the inspection required 
by paragraph (g)(2) of this AD: Do a detailed inspection of the 
exterior of the strut disconnect assembly for cracks, in accordance 
with Part 3 of the Accomplishment Instructions of Boeing Service 
Bulletin 777-54A0024, Revision 1, dated November 4, 2010; or 
Revision 2, dated January 23, 2014; and repeat the detailed 
inspection thereafter at intervals not to exceed 300 flight cycles. 
As of the effective date of this AD, use only Boeing Service 
Bulletin 777-54A0024, Revision 2, dated January 23, 2014, for 
accomplishing the actions in this paragraph.
    (B) Within 6,000 flight cycles or 750 days after hydraulic fluid 
coking and/or heat discoloration was found during the inspection 
required by paragraph (g)(2) of this AD, whichever occurs first: 
Replace the titanium system disconnect assembly with an Inconel 
system, in accordance with Part 4 of the Accomplishment Instructions 
of Boeing Service Bulletin 777-54A0024, Revision 1, dated November 
4, 2010; or Revision 2, dated January 23, 2014. As of the effective 
date of this AD, use only Boeing Service Bulletin 777-54A0024, 
Revision 2, dated January 23, 2014, for accomplishing the actions in 
this paragraph.

(h) Retained Corrective Action With Revised Service Information

    This paragraph restates the requirements of paragraph (h) of AD 
2011-09-11, Amendment 39-16673 (76 FR 24354, May 2, 2011), with 
revised service information. For airplanes on which any crack, 
etching, or pitting is found during any inspection required by 
paragraph (g)(2) or (g)(2)(ii)(A) of this AD (Condition 3): Before 
further flight, replace the titanium system disconnect assembly with 
an Inconel system, in accordance with Part 4 of the Accomplishment 
Instructions of Boeing Service Bulletin 777-54A0024, Revision 1, 
dated November 4, 2010; or Revision 2, dated January 23, 2014. As of 
the effective date of this AD, use only Boeing Service Bulletin 777-
54A0024, Revision 2, dated January 23, 2014, for accomplishing the 
actions in this paragraph.

(i) Retained Optional Terminating Action With Revised Service 
Information

    This paragraph restates the requirements of paragraph (i) of AD 
2011-09-11, Amendment 39-16673 (76 FR 24354, May 2, 2011), with 
revised service information. Replacing the titanium system 
disconnect assembly with an Inconel system disconnect assembly in 
accordance with Part 4 of the Accomplishment Instructions of Boeing 
Service Bulletin 777-54A0024, Revision 1, dated November 4, 2010; or 
Revision 2, dated January 23, 2014; terminates the actions required 
by paragraphs (g) and (h) of this AD. As of the effective date of 
this AD, use only Boeing Service Bulletin 777-54A0024,

[[Page 3161]]

Revision 2, dated January 23, 2014, for accomplishing the actions in 
this paragraph.

(j) New Inspection and Corrective Action

    For airplanes on which the system disconnect assembly has been 
replaced in accordance with Part 4 of the Accomplishment 
Instructions of Boeing Service Bulletin 777-54A0024, dated April 1, 
2010; or Revision 1, dated November 4, 2010: Within 1,125 days after 
the effective date of this AD, do a detailed inspection of the cover 
plate fasteners to determine if all cover plate attach fasteners are 
installed, in accordance with Part 5 of the Accomplishment 
Instructions of Boeing Service Bulletin 777-54A0024, Revision 2, 
dated January 23, 2014. If any fastener is missing, before further 
flight, install fasteners (including doing a detailed inspection for 
damage of the electrical components and repairing any damaged 
components), in accordance with Part 6 of the Accomplishment 
Instructions of Boeing Service Bulletin 777-54A0024, Revision 2, 
dated January 23, 2014.

(k) Credit for Previous Actions

    This paragraph restates the credit provided by paragraph (j) of 
AD 2011-09-11, Amendment 39-16673 (76 FR 24354, May 2, 2011). This 
paragraph provides credit for the corresponding actions required by 
paragraphs (g), (h), and (i) of this AD, if those actions were 
performed before June 6, 2011 (the effective date of AD 2011-09-11) 
using Boeing Service Bulletin 777-54A0024, dated April 1, 2010, 
which is not incorporated by reference in this AD.

(l) 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 (m)(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.

(m) Related Information

    (1) For more information about this AD, contact Kevin Nguyen, 
Aerospace Engineer, Propulsion Branch, ANM-140S, FAA, Seattle 
Aircraft Certification Office (ACO), 1601 Lind Avenue SW., Renton, 
WA 98057-3356; phone: 425-917-6501; fax: 425-917-6590; email: 
kevin.nguyen@faa.gov.
    (2) Service information identified in this AD that is not 
incorporated by reference is available at the addresses specified in 
paragraphs (n)(5) and (n)(6) of this AD.

(n) 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 
February 26, 2015.
    (i) Boeing Service Bulletin 777-54A0024, Revision 2, dated 
January 23, 2014.
    (ii) Reserved.
    (4) The following service information was approved for IBR on 
June 6, 2011 (76 FR 24354, May 2, 2011).
    (i) Boeing Service Bulletin 777-54A0024, Revision 1, dated 
November 4, 2010.
    (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 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 https://www.archives.gov/federal-register/cfr/ibr-locations.html.

    Issued in Renton, Washington, on December 22, 2014.
Michael Kaszycki,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2015-00009 Filed 1-21-15; 8:45 am]
BILLING CODE 4910-13-P

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