Airworthiness Directives; Rolls-Royce plc Turbofan Engines, 86567-86570 [2016-28663]

Download as PDF Federal Register / Vol. 81, No. 231 / Thursday, December 1, 2016 / Rules and Regulations (b) Contents of request. A request to amend a record in a CIGIE system of records must include: (1) The name of the system of records and a brief description of the record proposed for amendment. In the event the request to amend the record is the result of the requester having gained access to the record in accordance with the provisions concerning access to records as set forth in subpart B of this part, copies of previous correspondence between the requester and CIGIE will serve in lieu of a separate description of the record. (2) The exact portion of the record the requester seeks to have amended should be indicated clearly. If possible, proposed alternative language should be set forth, or, at a minimum, the reasons why the requester believes the record is not accurate, relevant, timely, or complete should be set forth with enough particularity to permit CIGIE to not only to understand the requester’s basis for the request, but also to make an appropriate amendment to the record. (c) Burden of proof. The requester has the burden of proof when seeking the amendment of a record. The requester must furnish sufficient facts to persuade the appropriate system manager of the inaccuracy, irrelevance, untimeliness, or incompleteness of the record. (d) Identification requirement. When the requester’s identity has been previously verified pursuant to § 9801.201, further verification of identity is not required as long as the communication does not suggest a need for verification. If the requester’s identity has not been previously verified, the appropriate system manager may require identification validation as described in § 9801.201. jstallworth on DSK7TPTVN1PROD with RULES § 9801.302 Response to requests. (a) Time limit for acknowledging a request for amendment. To the extent possible, CIGIE will acknowledge receipt of a request to amend a record or records within 10 working days. (b) Determination on an amendment request. The decision of CIGIE in response to a request for amendment of a record in a system of records may grant in whole or deny any part of the request to amend the record. (1) If CIGIE grants the request, the appropriate system manager will amend the record(s) and provide a copy of the amended record(s) to the requester. To the extent an accounting of disclosure has been maintained, the system manager shall advise all previous recipients of the record that an amendment has been made and give the substance of the amendment. Where VerDate Sep<11>2014 13:50 Nov 30, 2016 Jkt 241001 practicable, the system manager shall send a copy of the amended record to previous recipients. (2) If CIGIE denies the request in whole or in part, the reasons for the denial will be stated in the response letter. In addition, the response letter will state: (i) The name and address of the official with whom an appeal of the denial may be lodged; and (ii) A description of any other procedures which may be required of the requester in order to process the appeal. § 9801.303 Appeal from adverse determination on amendment. (a) How addressed. A requester may submit a written appeal of the decision by CIGIE to deny an initial request to amend a record in a CIGIE system of records to the Chairperson, Council of the Inspectors General on Integrity and Efficiency, 1717 H Street NW., Suite 825, Washington, DC 20006. The words ‘‘Privacy Act Appeal’’ should be included on the envelope and at the top of the letter of appeal. (b) Deadline and content. The appeal must be received by CIGIE within 60 days of the date of the letter denying the request and should contain a brief description of the record(s) involved or copies of the correspondence from CIGIE and the reasons why the requester believes that the disputed information should be amended. § 9801.304 Response to appeal of adverse determination on amendment; disagreement statements. (a) Response timing. The Chairperson should make a final determination in writing not later than 30 days from the date the appeal was received. The 30day period may be extended for good cause. Notice of the extension and the reasons therefor will be sent to the requester within the 30-day period. (b) Amendment granted. If the Chairperson determines that the record(s) should be amended in accordance with the requester’s request, the Chairperson will take the necessary steps to advise the requester and to direct the appropriate system manager: (1) To amend the record(s); and (2) To notify previous recipients of the record(s) for which there is an accounting of disclosure that the record(s) have been amended. (c) Denial affirmed. If the appeal decision does not grant in full the request for amendment, the decision letter will notify the requester that the requester may: (1) Obtain judicial review of the decision in accordance with the terms of the Privacy Act at 5 U.S.C. 552a(g); and PO 00000 Frm 00013 Fmt 4700 Sfmt 4700 86567 (2) File a statement setting forth their reasons for disagreeing with the decision. (d) Requester’s disagreement statement. A requester’s disagreement statement must be concise. CIGIE has the authority to determine the ‘‘conciseness’’ of the statement, taking into account the scope of the disagreement and the complexity of the issues. (e) Provision of requester’s disagreement statement. In any disclosure of information about which an individual has filed a proper statement of disagreement, CIGIE will clearly note any disputed portion(s) of the record(s) and will provide a copy of the statement to persons or other agencies to whom the disputed record or records has been disclosed and for whom an accounting of disclosure has been maintained. A concise statement of the reasons for not making the amendments requested may also be provided. § 9801.305 Assistance in preparing request to amend a record or to appeal an initial adverse determination. Requesters may seek assistance in preparing a request to amend a record or an appeal of an initial adverse determination, or to learn further of the provisions for judicial review, by contacting CIGIE’s Privacy Officer by email at privacy@cigie.gov or by mail at Privacy Officer, Council of the Inspectors General on Integrity and Efficiency, 1717 H Street NW., Suite 825, Washington, DC 20006. Dated: November 23, 2016. Michael E. Horowitz, Chairperson of the Council of the Inspectors General on Integrity and Efficiency. [FR Doc. 2016–28897 Filed 11–30–16; 8:45 am] BILLING CODE 6820–C9–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2016–6692; Directorate Identifier 2016–NE–13–AD; Amendment 39– 18725; AD 2016–24–08] RIN 2120–AA64 Airworthiness Directives; Rolls-Royce plc Turbofan Engines Federal Aviation Administration (FAA), DOT. ACTION: Final rule. AGENCY: We are adopting a new airworthiness directive (AD) for all SUMMARY: E:\FR\FM\01DER1.SGM 01DER1 86568 Federal Register / Vol. 81, No. 231 / Thursday, December 1, 2016 / Rules and Regulations Rolls-Royce plc (RR) RB211-Trent 875– 17, RB211-Trent 877–17, RB211-Trent 884–17, RB211-Trent 884B–17, RB211Trent 892–17, RB211-Trent 892B–17, and RB211-Trent 895–17 turbofan engines. This AD requires repetitive inspections of the engine upper bifurcation fairing and repairing or replacing any fairing that fails inspection. This AD was prompted by a report of cracking and material release from an engine upper bifurcation fairing. We are issuing this AD to prevent failure of the engine fire protection system, engine fire, and damage to the airplane. DATES: This AD becomes effective January 5, 2017. ADDRESSES: For service information identified in this final rule, contact Rolls-Royce plc, Corporate Communications, P.O. Box 31, Derby, England, DE24 8BJ; phone: 011–44– 1332–242424; fax: 011–44–1332– 249936; email: http://www.rollsroyce.com/contact/civil_team.jsp; Internet: https://customers.rollsroyce.com/public/rollsroycecare. You may view this service information at the FAA, Engine & Propeller Directorate, 1200 District Avenue, Burlington, MA. For information on the availability of this material at the FAA, call 781–238– 7125. Examining the AD Docket You may examine the AD docket on the Internet at http:// www.regulations.gov by searching for and locating Docket No. FAA–2016– 6692; 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 mandatory continuing airworthiness information (MCAI), the regulatory evaluation, any comments received, and other information. The address for the Docket Office (phone: 800–647–5527) is Document 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: Wego Wang, Aerospace Engineer, Engine Certification Office, FAA, Engine & Propeller Directorate, 1200 District Avenue, Burlington, MA 01803; phone: 781–238–7134; fax: 781–238–7199; email: wego.wang@faa.gov. SUPPLEMENTARY INFORMATION: Discussion We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 by adding an AD that would apply to the specified products. The NPRM was published in the Federal Register on July 15, 2016 (81 FR 46000). The NPRM proposed to correct an unsafe condition for the specified products. The MCAI states: Inspection of in-service Rolls-Royce RB211 Trent 800 engines has identified cracking and/or material release from the upper bifurcation fairing. This fairing hardware mates to the aeroplane thrust reverser upper bifurcation forward fire seal. Both sets of hardware create the engine firewall to isolate the engine compartment fire zone, which is a firewall feature of the aeroplane type design. Damage (missing materials and holes/ openings) to the upper bifurcation fairing creates a breach of the engine fire wall, which may decrease the effectiveness of the engine fire detection and suppression systems due to excess fan air entering the engine compartment fire zone. This could delay or prevent the fire detection and suppression system from functioning properly, and can result in an increased risk of prolonged burning, potentially allowing a fire to reach unprotected areas of the engine, strut and wing. You may obtain further information by examining the MCAI in the AD docket on the Internet at http:// www.regulations.gov by searching for and locating Docket No. FAA–2016– 6692. Comments We gave the public the opportunity to participate in developing this AD. We considered the comment received. Request To Remove Reference to Guidance in Compliance American Airlines, Inc. (AAL) requested that paragraph (e)(3)(ii) in this AD be revised to eliminate the references to Aircraft Maintenance Manual (AMM) Task 70–20–02 and to OMat 632. AAL indicated that AMM 70–20–02 requires the use of OMat 653 and TAM (PSM–5) TST panels for testing fluorescent penetrants for contamination and effectiveness. AAL noted that the Overhaul Material Manual (OMat 6) allows the use of any products specified in the SAE–AMS– 2644 Qualified Product List Group 1A2 as an alternative to OMat 653. We disagree. Paragraph (e)(3)(ii) in this AD refers to AMM Task 70–20–02 and OMat 632 as guidance that operators may use when performing fluorescent penetrant inspection. This AD does not require that AMM TASK 70–20–02 or OMat 632 be followed when performing fluorescent penetrant inspection. We did not change this AD. Conclusion We reviewed the relevant data, considered the comment 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 for correcting the unsafe condition; and • Do not add any additional burden upon the public than was already proposed in the NPRM. Related Service Information RR has issued Alert Non-Modification Service Bulletin (NMSB) RB.211–72– AJ165, dated March 31, 2016. The NMSB describes procedures for inspecting and, if necessary, repairing or replacing the engine upper bifurcation fairing. Costs of Compliance We estimate that this AD affects 125 engines installed on airplanes of U.S. registry. We estimate the following costs to comply with this AD: ESTIMATED COSTS jstallworth on DSK7TPTVN1PROD with RULES Action Labor cost Parts cost Cost per product Cost on U.S. operators Inspection .......... 3.25 work-hours × $85 per hour = $276.25 ................................................. $0 $276.25 $34,531 We estimate the following costs to do any necessary replacements that would VerDate Sep<11>2014 13:50 Nov 30, 2016 Jkt 241001 be required based on the results of the proposed inspection. We estimate that 5 PO 00000 Frm 00014 Fmt 4700 Sfmt 4700 engines will need this repair and 5 engines will need this replacement: E:\FR\FM\01DER1.SGM 01DER1 Federal Register / Vol. 81, No. 231 / Thursday, December 1, 2016 / Rules and Regulations 86569 ON-CONDITION COSTS Action Labor cost Repair of engine upper bifurcation fairing .................... Replacement of engine upper bifurcation fairing ......... 8 work-hours × $85 per hour = $680 ........................... 30 work hours × $85 per hour = $2,550 ...................... Authority for This Rulemaking Title 49 of the United States Code specifies the FAA’s authority to issue rules on aviation safety. Subtitle I, section 106, describes the authority of the FAA Administrator. ‘‘Subtitle VII: Aviation Programs,’’ describes in more detail the scope of the Agency’s authority. We are issuing this rulemaking under the authority described in ‘‘Subtitle VII, Part A, Subpart III, Section 44701: General requirements.’’ Under that section, Congress charges the FAA with promoting safe flight of civil aircraft in air commerce by prescribing regulations for practices, methods, and procedures the Administrator finds necessary for safety in air commerce. This regulation is within the scope of that authority because it addresses an unsafe condition that is likely to exist or develop on products identified in this rulemaking action. jstallworth on DSK7TPTVN1PROD with RULES Regulatory Findings We 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 this AD: (1) Is not a ‘‘significant regulatory action’’ under Executive Order 12866, (2) Is not a ‘‘significant rule’’ under the DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979), (3) Will not affect intrastate aviation in Alaska to the extent that it justifies making a regulatory distinction, 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, VerDate Sep<11>2014 13:50 Nov 30, 2016 Jkt 241001 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 adding the following new airworthiness directive (AD): ■ 2016–24–08 Rolls-Royce plc: Amendment 39–18725; Docket No. FAA–2016–6692; Directorate Identifier 2016–NE–13–AD. (a) Effective Date This AD becomes effective January 5, 2017. (b) Affected ADs None. (c) Applicability This AD applies to Rolls-Royce plc (RR) RB211-Trent 875-17, RB211-Trent 877-17, RB211-Trent 884-17, RB211-Trent 884B-17, RB211-Trent 892-17, RB211-Trent 892B-17, and RB211-Trent 895-17 turbofan engines. (d) Reason This AD was prompted by a report of cracking and material release from an engine upper bifurcation fairing. We are issuing this AD to prevent failure of the engine fire protection system, engine fire, and damage to the airplane. (e) Actions and Compliance Comply with this AD within the compliance times specified, unless already done. (1) Within 7,500 engine flight hours (FHs) time since new, or since last inspection, or within 150 flight cycles (FCs) after the effective date of this AD, whichever occurs later, inspect the engine upper bifurcation fairing for cracks or missing material. Use paragraph (e)(3) of this AD to perform the inspections. (2) Repeat the inspection required by this AD within every 7,500 engine FHs time since last inspection. (3) Inspect the engine upper bifurcation fairing as follows. Refer to Figure 1 of RR Alert Non-Modification Service Bulletin (NMSB) RB.211–72–AJ165, dated March 31, 2016, for guidance on upper bifurcation fairing inspection locations. (i) Visually inspect upper bifurcation fairing seal face 22, seal support 23, and zone A for any cracks or material loss on the right side. PO 00000 Frm 00015 Fmt 4700 Sfmt 4700 Parts cost $500 500 Cost per product $1,180 3,050 (A) If fairing seal face 22 is found to have released material, repair or replace the fairing before further flight. (B) If there is a single crack found on fairing seal face 22, shorter than 6 mm, repair or replace the fairing within 100 engine flight cycles, or at the next shop visit, whichever occurs sooner. (C) If there is a single crack, longer than 6 mm, found on fairing seal face 22, repair or replace the fairing within 15 engine FCs or at the next shop visit, whichever occurs sooner. (D) If there are two or more cracks found on fairing seal face 22, replace the fairing within 15 engine FCs or at next shop visit, whichever occurs sooner. (E) If there is any cracking or material loss found on seal support 23, replace the fairing within 15 engine FCs or at next shop visit, whichever occurs sooner. (ii) If the visual inspection required by paragraph (e)(3)(i) of this AD does not detect any crack, fluorescent penetrant inspect zone A. Refer to AMM TASK 70–20–02, Water Washable Fluorescent Penetrant Inspection (Maintenance Process 213), or OMat 632, high sensitivity fluorescent penetrant inspection, for guidance on fluorescent penetrant inspection. (A) If a crack shorter than 6 mm is detected, repair or replace the fairing within 100 engine FCs, or at the next shop visit, whichever occurs sooner. (B) If a crack longer than 6 mm is detected, repair or replace the fairing within 15 engine FCs or at the next shop visit, whichever occurs sooner. (f) Definition For the purpose of this AD, a ‘‘shop visit’’ is defined as induction of an engine into the shop for maintenance involving the separation of pairs of major mating engine flanges, except that the separation of engine flanges solely for the purposes of transportation without subsequent engine maintenance does not constitute an engine shop visit. (g) Alternative Methods of Compliance (AMOCs) The Manager, Engine Certification Office, FAA, may approve AMOCs for this AD. Use the procedures found in 14 CFR 39.19 to make your request. You may email your request to: ANE-AD-AMOC@faa.gov. (h) Related Information (1) For more information about this AD, contact Wego Wang, Aerospace Engineer, Engine Certification Office, FAA, Engine & Propeller Directorate, 1200 District Avenue, Burlington, MA 01803; phone: 781–238– 7134; fax: 781–238–7199; email: wego.wang@ faa.gov. E:\FR\FM\01DER1.SGM 01DER1 86570 Federal Register / Vol. 81, No. 231 / Thursday, December 1, 2016 / Rules and Regulations (2) Refer to MCAI European Aviation Safety Agency AD 2016–0084, dated April 28, 2016, for more information. You may examine the MCAI in the AD docket on the Internet at http://www.regulations.gov by searching for and locating it in Docket No. FAA–2016–6692. (3) RR Alert NMSB RB.211–72–AJ165, dated March 31, 2016, which is not incorporated by reference in this AD, can be obtained from RR, using the contact information in paragraph (h)(4) of this AD. (4) For service information identified in this AD, contact Rolls-Royce plc, Corporate Communications, P.O. Box 31, Derby, England, DE24 8BJ; phone: 011–44–1332– 242424; fax: 011–44–1332–249936; email: http://www.rolls-royce.com/contact/civil_ team.jsp; Internet: https://customers.rollsroyce.com/public/rollsroycecare. (5) You may view this service information at the FAA, Engine & Propeller Directorate, 1200 District Avenue, Burlington, MA. For information on the availability of this material at the FAA, call 781–238–7125. (i) Material Incorporated by Reference None. Issued in Burlington, Massachusetts, on November 16, 2016. Colleen M. D’Alessandro, Manager, Engine & Propeller Directorate, Aircraft Certification Service. [FR Doc. 2016–28663 Filed 11–30–16; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 71 [Docket No. FAA–2016–7417; Airspace Docket No. 16–AWA–4] Authority for This Rulemaking RIN 2120–AA66 Amendment of Class C Airspace; El Paso International Airport, TX Federal Aviation Administration (FAA), DOT. ACTION: Final rule. AGENCY: This action amends Class C airspace at El Paso International Airport, El Paso, TX, by removing a cutout from the Class C airspace area that excludes the airspace within a 2-mile radius of West Texas Airport and the airspace beyond an 8-mile arc from the El Paso International Airport beginning at the 115° bearing from the airport clockwise to the Rio Grande River. Additionally, this rule removes West Texas Airport from the Class C airspace description as the airport is closed, and amends the El Paso International Airport geographic coordinates to coincide with the FAA’s aeronautical database. The FAA is taking this action to enable more efficient operations at El Paso International Airport. jstallworth on DSK7TPTVN1PROD with RULES SUMMARY: VerDate Sep<11>2014 13:50 Nov 30, 2016 Jkt 241001 Effective date 0901 UTC, February 2, 2017. The Director of the Federal Register approves this incorporation by reference action under Title 1, Code of Federal Regulations, part 51, subject to the annual revision of FAA Order 7400.11 and publication of conforming amendments. ADDRESSES: FAA Order 7400.11A, Airspace Designations and Reporting Points, and subsequent amendments can be viewed online at http://www.faa.gov/ air_traffic/publications/. For further information, you can contact the Airspace Policy Group, Federal Aviation Administration, 800 Independence Avenue SW., Washington, DC 20591; telephone: (202) 267–8783. The Order is also available for inspection at the National Archives and Records Administration (NARA). For information on the availability of FAA Order 7400.11A at NARA, call (202) 741–6030, or go to http:// www.archives.gov/federal_register/ code_of_federal-regulations/ibr_ locations.html. FAA Order 7400.11, Airspace Designations and Reporting Points, is published yearly and effective on September 15. FOR FURTHER INFORMATION CONTACT: Colby Abbott, Airspace Policy Group, Office of Airspace Services, Federal Aviation Administration, 800 Independence Avenue SW., Washington, DC 20591; telephone: (202) 267–8783. SUPPLEMENTARY INFORMATION: DATES: The FAA’s authority to issue rules regarding aviation safety is found in Title 49 of the United States Code. 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. This rulemaking is promulgated under the authority described in Subtitle VII, Part A, Subpart I, Section 40103. Under that section, the FAA is charged with prescribing regulations to assign the use of the airspace necessary to ensure the safety of aircraft and the efficient use of airspace. This regulation is within the scope of that authority as it amends the El Paso, TX, Class C airspace area to preserve the safe and efficient flow of air traffic in the El Paso, TX, area. History On August 17, 2016, the FAA published in the Federal Register a notice of proposed rulemaking (NPRM) to modify the Class C airspace at El Paso International Airport, El Paso, TX (81 PO 00000 Frm 00016 Fmt 4700 Sfmt 4700 FR 54752), Docket No. FAA–2016–7417. Interested parties were invited to participate in this rulemaking effort by submitting written comments on the proposal. One comment was received supporting the FAA’s proposed action. Availability and Summary of Documents for Incorporation by Reference This document amends FAA Order 7400.11A, Airspace Designations and Reporting Points, dated August 3, 2016, and effective September 15, 2016. FAA Order 7400.11A is publicly available as listed in the ADDRESSES section of this document. FAA Order 7400.11A lists Class A, B, C, D, and E airspace areas, air traffic service routes, and reporting points. The Rule The FAA is amending Title 14, Code of Federal Regulations (14 CFR) part 71 by modifying the El Paso International Airport, El Paso, TX, Class C airspace area. This action removes the cutout and reduced perimeter boundary arc that excludes the airspace extending upward from 5,200 feet MSL to and including 8,000 feet MSL within a 2-mile radius of the West Texas Airport, and the airspace beyond an 8-mile arc from the El Paso International Airport beginning at the 115° bearing from the airport clockwise to the Rio Grande River. Since West Texas Airport (renamed Horizon Airport in 2004) is permanently closed and the property sold for nonaviation uses, the purpose for the exclusions no longer exists. Thus, the FAA is removing the words ‘‘. . . that airspace beyond an 8-mile arc from the El Paso International Airport beginning at the 115° bearing from the airport clockwise to the Rio Grande River, and that airspace within a 2-mile radius of the West Texas Airport, and . . .’’ from the regulatory text. The West Texas Airport name and geographic coordinate references are also removed from the Class C airspace description. Additionally, this action amends the exclusion language pertaining to the Class C airspace extending upward from 5,200 feet MSL to and including 8,000 feet MSL from ‘‘. . . that airspace within Mexico, and that airspace west of long 106°27′02″ W.’’ to ‘‘. . . that airspace west of long. 106°27′02″ W., and that airspace within Mexico.’’ This change is editorial for format and clarity to standardize the exclusion information associated with the Class C airspace surface area and shelf. Lastly, this action updates the El Paso International Airport geographic coordinates to reflect the current airport reference point information in the E:\FR\FM\01DER1.SGM 01DER1

Agencies

[Federal Register Volume 81, Number 231 (Thursday, December 1, 2016)]
[Rules and Regulations]
[Pages 86567-86570]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2016-28663]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2016-6692; Directorate Identifier 2016-NE-13-AD; 
Amendment 39-18725; AD 2016-24-08]
RIN 2120-AA64


Airworthiness Directives; Rolls-Royce plc Turbofan Engines

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule.

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SUMMARY: We are adopting a new airworthiness directive (AD) for all

[[Page 86568]]

Rolls-Royce plc (RR) RB211-Trent 875-17, RB211-Trent 877-17, RB211-
Trent 884-17, RB211-Trent 884B-17, RB211-Trent 892-17, RB211-Trent 
892B-17, and RB211-Trent 895-17 turbofan engines. This AD requires 
repetitive inspections of the engine upper bifurcation fairing and 
repairing or replacing any fairing that fails inspection. This AD was 
prompted by a report of cracking and material release from an engine 
upper bifurcation fairing. We are issuing this AD to prevent failure of 
the engine fire protection system, engine fire, and damage to the 
airplane.

DATES: This AD becomes effective January 5, 2017.

ADDRESSES: For service information identified in this final rule, 
contact Rolls-Royce plc, Corporate Communications, P.O. Box 31, Derby, 
England, DE24 8BJ; phone: 011-44-1332-242424; fax: 011-44-1332-249936; 
email: http://www.rolls-royce.com/contact/civil_team.jsp; Internet: 
https://customers.rolls-royce.com/public/rollsroycecare. You may view 
this service information at the FAA, Engine & Propeller Directorate, 
1200 District Avenue, Burlington, MA. For information on the 
availability of this material at the FAA, call 781-238-7125.

Examining the AD Docket

    You may examine the AD docket on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2016-
6692; 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 mandatory continuing airworthiness information 
(MCAI), the regulatory evaluation, any comments received, and other 
information. The address for the Docket Office (phone: 800-647-5527) is 
Document 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: Wego Wang, Aerospace Engineer, Engine 
Certification Office, FAA, Engine & Propeller Directorate, 1200 
District Avenue, Burlington, MA 01803; phone: 781-238-7134; fax: 781-
238-7199; email: wego.wang@faa.gov.

SUPPLEMENTARY INFORMATION: 

Discussion

    We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR 
part 39 by adding an AD that would apply to the specified products. The 
NPRM was published in the Federal Register on July 15, 2016 (81 FR 
46000). The NPRM proposed to correct an unsafe condition for the 
specified products. The MCAI states:

    Inspection of in-service Rolls-Royce RB211 Trent 800 engines has 
identified cracking and/or material release from the upper 
bifurcation fairing. This fairing hardware mates to the aeroplane 
thrust reverser upper bifurcation forward fire seal. Both sets of 
hardware create the engine firewall to isolate the engine 
compartment fire zone, which is a firewall feature of the aeroplane 
type design. Damage (missing materials and holes/openings) to the 
upper bifurcation fairing creates a breach of the engine fire wall, 
which may decrease the effectiveness of the engine fire detection 
and suppression systems due to excess fan air entering the engine 
compartment fire zone. This could delay or prevent the fire 
detection and suppression system from functioning properly, and can 
result in an increased risk of prolonged burning, potentially 
allowing a fire to reach unprotected areas of the engine, strut and 
wing.

    You may obtain further information by examining the MCAI in the AD 
docket on the Internet at http://www.regulations.gov by searching for 
and locating Docket No. FAA-2016-6692.

Comments

    We gave the public the opportunity to participate in developing 
this AD. We considered the comment received.

Request To Remove Reference to Guidance in Compliance

    American Airlines, Inc. (AAL) requested that paragraph (e)(3)(ii) 
in this AD be revised to eliminate the references to Aircraft 
Maintenance Manual (AMM) Task 70-20-02 and to OMat 632. AAL indicated 
that AMM 70-20-02 requires the use of OMat 653 and TAM (PSM-5) TST 
panels for testing fluorescent penetrants for contamination and 
effectiveness. AAL noted that the Overhaul Material Manual (OMat 6) 
allows the use of any products specified in the SAE-AMS-2644 Qualified 
Product List Group 1A2 as an alternative to OMat 653.
    We disagree. Paragraph (e)(3)(ii) in this AD refers to AMM Task 70-
20-02 and OMat 632 as guidance that operators may use when performing 
fluorescent penetrant inspection. This AD does not require that AMM 
TASK 70-20-02 or OMat 632 be followed when performing fluorescent 
penetrant inspection. We did not change this AD.

Conclusion

    We reviewed the relevant data, considered the comment 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 for correcting the unsafe condition; and
     Do not add any additional burden upon the public than was 
already proposed in the NPRM.

Related Service Information

    RR has issued Alert Non-Modification Service Bulletin (NMSB) 
RB.211-72-AJ165, dated March 31, 2016. The NMSB describes procedures 
for inspecting and, if necessary, repairing or replacing the engine 
upper bifurcation fairing.

Costs of Compliance

    We estimate that this AD affects 125 engines installed on 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
----------------------------------------------------------------------------------------------------------------
Inspection......................  3.25 work-hours x $85 per                $0          $276.25          $34,531
                                   hour = $276.25.
----------------------------------------------------------------------------------------------------------------

    We estimate the following costs to do any necessary replacements 
that would be required based on the results of the proposed inspection. 
We estimate that 5 engines will need this repair and 5 engines will 
need this replacement:

[[Page 86569]]



                                               On-Condition Costs
----------------------------------------------------------------------------------------------------------------
                                                                                                     Cost per
                   Action                                 Labor cost                Parts cost        product
----------------------------------------------------------------------------------------------------------------
Repair of engine upper bifurcation fairing.  8 work-hours x $85 per hour = $680.            $500          $1,180
Replacement of engine upper bifurcation      30 work hours x $85 per hour =                  500           3,050
 fairing.                                     $2,550.
----------------------------------------------------------------------------------------------------------------

Authority for This Rulemaking

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

Regulatory Findings

    We 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 this AD:
    (1) Is not a ``significant regulatory action'' under Executive 
Order 12866,
    (2) Is not a ``significant rule'' under the DOT Regulatory Policies 
and Procedures (44 FR 11034, February 26, 1979),
    (3) Will not affect intrastate aviation in Alaska to the extent 
that it justifies making a regulatory distinction, 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 adding the following new airworthiness 
directive (AD):

2016-24-08 Rolls-Royce plc: Amendment 39-18725; Docket No. FAA-2016-
6692; Directorate Identifier 2016-NE-13-AD.

(a) Effective Date

    This AD becomes effective January 5, 2017.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to Rolls-Royce plc (RR) RB211-Trent 875-17, 
RB211-Trent 877-17, RB211-Trent 884-17, RB211-Trent 884B-17, RB211-
Trent 892-17, RB211-Trent 892B-17, and RB211-Trent 895-17 turbofan 
engines.

(d) Reason

    This AD was prompted by a report of cracking and material 
release from an engine upper bifurcation fairing. We are issuing 
this AD to prevent failure of the engine fire protection system, 
engine fire, and damage to the airplane.

(e) Actions and Compliance

    Comply with this AD within the compliance times specified, 
unless already done.
    (1) Within 7,500 engine flight hours (FHs) time since new, or 
since last inspection, or within 150 flight cycles (FCs) after the 
effective date of this AD, whichever occurs later, inspect the 
engine upper bifurcation fairing for cracks or missing material. Use 
paragraph (e)(3) of this AD to perform the inspections.
    (2) Repeat the inspection required by this AD within every 7,500 
engine FHs time since last inspection.
    (3) Inspect the engine upper bifurcation fairing as follows. 
Refer to Figure 1 of RR Alert Non-Modification Service Bulletin 
(NMSB) RB.211-72-AJ165, dated March 31, 2016, for guidance on upper 
bifurcation fairing inspection locations.
    (i) Visually inspect upper bifurcation fairing seal face 22, 
seal support 23, and zone A for any cracks or material loss on the 
right side.
    (A) If fairing seal face 22 is found to have released material, 
repair or replace the fairing before further flight.
    (B) If there is a single crack found on fairing seal face 22, 
shorter than 6 mm, repair or replace the fairing within 100 engine 
flight cycles, or at the next shop visit, whichever occurs sooner.
    (C) If there is a single crack, longer than 6 mm, found on 
fairing seal face 22, repair or replace the fairing within 15 engine 
FCs or at the next shop visit, whichever occurs sooner.
    (D) If there are two or more cracks found on fairing seal face 
22, replace the fairing within 15 engine FCs or at next shop visit, 
whichever occurs sooner.
    (E) If there is any cracking or material loss found on seal 
support 23, replace the fairing within 15 engine FCs or at next shop 
visit, whichever occurs sooner.
    (ii) If the visual inspection required by paragraph (e)(3)(i) of 
this AD does not detect any crack, fluorescent penetrant inspect 
zone A. Refer to AMM TASK 70-20-02, Water Washable Fluorescent 
Penetrant Inspection (Maintenance Process 213), or OMat 632, high 
sensitivity fluorescent penetrant inspection, for guidance on 
fluorescent penetrant inspection.
    (A) If a crack shorter than 6 mm is detected, repair or replace 
the fairing within 100 engine FCs, or at the next shop visit, 
whichever occurs sooner.
    (B) If a crack longer than 6 mm is detected, repair or replace 
the fairing within 15 engine FCs or at the next shop visit, 
whichever occurs sooner.

(f) Definition

    For the purpose of this AD, a ``shop visit'' is defined as 
induction of an engine into the shop for maintenance involving the 
separation of pairs of major mating engine flanges, except that the 
separation of engine flanges solely for the purposes of 
transportation without subsequent engine maintenance does not 
constitute an engine shop visit.

(g) Alternative Methods of Compliance (AMOCs)

    The Manager, Engine Certification Office, FAA, may approve AMOCs 
for this AD. Use the procedures found in 14 CFR 39.19 to make your 
request. You may email your request to: ANE-AD-AMOC@faa.gov.

(h) Related Information

    (1) For more information about this AD, contact Wego Wang, 
Aerospace Engineer, Engine Certification Office, FAA, Engine & 
Propeller Directorate, 1200 District Avenue, Burlington, MA 01803; 
phone: 781-238-7134; fax: 781-238-7199; email: wego.wang@faa.gov.

[[Page 86570]]

    (2) Refer to MCAI European Aviation Safety Agency AD 2016-0084, 
dated April 28, 2016, for more information. You may examine the MCAI 
in the AD docket on the Internet at http://www.regulations.gov by 
searching for and locating it in Docket No. FAA-2016-6692.
    (3) RR Alert NMSB RB.211-72-AJ165, dated March 31, 2016, which 
is not incorporated by reference in this AD, can be obtained from 
RR, using the contact information in paragraph (h)(4) of this AD.
    (4) For service information identified in this AD, contact 
Rolls-Royce plc, Corporate Communications, P.O. Box 31, Derby, 
England, DE24 8BJ; phone: 011-44-1332-242424; fax: 011-44-1332-
249936; email: http://www.rolls-royce.com/contact/civil_team.jsp; 
Internet: https://customers.rolls-royce.com/public/rollsroycecare.
    (5) You may view this service information at the FAA, Engine & 
Propeller Directorate, 1200 District Avenue, Burlington, MA. For 
information on the availability of this material at the FAA, call 
781-238-7125.

(i) Material Incorporated by Reference

    None.

    Issued in Burlington, Massachusetts, on November 16, 2016.
Colleen M. D'Alessandro,
Manager, Engine & Propeller Directorate, Aircraft Certification 
Service.
[FR Doc. 2016-28663 Filed 11-30-16; 8:45 am]
 BILLING CODE 4910-13-P