81 FR 86567 - Airworthiness Directives; Rolls-Royce plc Turbofan Engines
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration Federal Register Volume 81, Issue 231 (December 1, 2016)
Federal Aviation Administration
Federal Register Volume 81, Issue 231 (December 1, 2016)
| Page Range | 86567-86570 | |
| FR Document | 2016-28663 |
[Federal Register Volume 81, Number 231 (Thursday, December 1, 2016)] [Rules and Regulations] [Pages 86567-86570] From the Federal Register Online [www.thefederalregister.org] [FR Doc No: 2016-28663] ======================================================================= ----------------------------------------------------------------------- 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. ----------------------------------------------------------------------- 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: [email protected]. 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: [email protected]. (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: [email protected]. [[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
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(b) Contents of request. A request to practicable, the system manager shall (2) File a statement setting forth their
amend a record in a CIGIE system of send a copy of the amended record to reasons for disagreeing with the
records must include: previous recipients. decision.
(1) The name of the system of records (2) If CIGIE denies the request in (d) Requester’s disagreement
and a brief description of the record whole or in part, the reasons for the statement. A requester’s disagreement
proposed for amendment. In the event denial will be stated in the response statement must be concise. CIGIE has
the request to amend the record is the letter. In addition, the response letter the authority to determine the
result of the requester having gained will state: ‘‘conciseness’’ of the statement, taking
access to the record in accordance with (i) The name and address of the into account the scope of the
the provisions concerning access to official with whom an appeal of the disagreement and the complexity of the
records as set forth in subpart B of this denial may be lodged; and issues.
part, copies of previous correspondence (ii) A description of any other (e) Provision of requester’s
between the requester and CIGIE will procedures which may be required of disagreement statement. In any
serve in lieu of a separate description of the requester in order to process the disclosure of information about which
the record. appeal. an individual has filed a proper
(2) The exact portion of the record the § 9801.303 Appeal from adverse statement of disagreement, CIGIE will
requester seeks to have amended should determination on amendment. clearly note any disputed portion(s) of
be indicated clearly. If possible, (a) How addressed. A requester may the record(s) and will provide a copy of
proposed alternative language should be submit a written appeal of the decision the statement to persons or other
set forth, or, at a minimum, the reasons by CIGIE to deny an initial request to agencies to whom the disputed record
why the requester believes the record is amend a record in a CIGIE system of or records has been disclosed and for
not accurate, relevant, timely, or records to the Chairperson, Council of whom an accounting of disclosure has
complete should be set forth with the Inspectors General on Integrity and been maintained. A concise statement of
enough particularity to permit CIGIE to Efficiency, 1717 H Street NW., Suite the reasons for not making the
not only to understand the requester’s 825, Washington, DC 20006. The words amendments requested may also be
basis for the request, but also to make ‘‘Privacy Act Appeal’’ should be provided.
an appropriate amendment to the included on the envelope and at the top
record. § 9801.305 Assistance in preparing
of the letter of appeal. request to amend a record or to appeal an
(c) Burden of proof. The requester has (b) Deadline and content. The appeal
the burden of proof when seeking the initial adverse determination.
must be received by CIGIE within 60
amendment of a record. The requester Requesters may seek assistance in
days of the date of the letter denying the
must furnish sufficient facts to persuade preparing a request to amend a record
request and should contain a brief
the appropriate system manager of the or an appeal of an initial adverse
description of the record(s) involved or
inaccuracy, irrelevance, untimeliness, or determination, or to learn further of the
copies of the correspondence from
incompleteness of the record. provisions for judicial review, by
CIGIE and the reasons why the requester
(d) Identification requirement. When contacting CIGIE’s Privacy Officer by
believes that the disputed information
the requester’s identity has been email at privacy@cigie.gov or by mail at
should be amended.
previously verified pursuant to Privacy Officer, Council of the
§ 9801.201, further verification of § 9801.304 Response to appeal of adverse Inspectors General on Integrity and
identity is not required as long as the determination on amendment; Efficiency, 1717 H Street NW., Suite
communication does not suggest a need disagreement statements. 825, Washington, DC 20006.
for verification. If the requester’s (a) Response timing. The Chairperson Dated: November 23, 2016.
identity has not been previously should make a final determination in Michael E. Horowitz,
verified, the appropriate system writing not later than 30 days from the
Chairperson of the Council of the Inspectors
manager may require identification date the appeal was received. The 30- General on Integrity and Efficiency.
validation as described in § 9801.201. day period may be extended for good
[FR Doc. 2016–28897 Filed 11–30–16; 8:45 am]
cause. Notice of the extension and the
§ 9801.302 Response to requests. reasons therefor will be sent to the BILLING CODE 6820–C9–P
(a) Time limit for acknowledging a requester within the 30-day period.
request for amendment. To the extent (b) Amendment granted. If the
possible, CIGIE will acknowledge Chairperson determines that the DEPARTMENT OF TRANSPORTATION
receipt of a request to amend a record record(s) should be amended in
or records within 10 working days. accordance with the requester’s request, Federal Aviation Administration
(b) Determination on an amendment the Chairperson will take the necessary
request. The decision of CIGIE in steps to advise the requester and to 14 CFR Part 39
response to a request for amendment of direct the appropriate system manager: [Docket No. FAA–2016–6692; Directorate
a record in a system of records may (1) To amend the record(s); and Identifier 2016–NE–13–AD; Amendment 39–
grant in whole or deny any part of the (2) To notify previous recipients of 18725; AD 2016–24–08]
request to amend the record. the record(s) for which there is an
(1) If CIGIE grants the request, the RIN 2120–AA64
accounting of disclosure that the
appropriate system manager will amend record(s) have been amended. Airworthiness Directives; Rolls-Royce
the record(s) and provide a copy of the (c) Denial affirmed. If the appeal plc Turbofan Engines
jstallworth on DSK7TPTVN1PROD with RULES
amended record(s) to the requester. To decision does not grant in full the
the extent an accounting of disclosure request for amendment, the decision AGENCY: Federal Aviation
has been maintained, the system letter will notify the requester that the Administration (FAA), DOT.
manager shall advise all previous requester may: ACTION: Final rule.
recipients of the record that an (1) Obtain judicial review of the
amendment has been made and give the decision in accordance with the terms of SUMMARY: We are adopting a new
substance of the amendment. Where the Privacy Act at 5 U.S.C. 552a(g); and airworthiness directive (AD) for all
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ON-CONDITION COSTS
Cost per
Action Labor cost Parts cost product
Repair of engine upper bifurcation fairing .................... 8 work-hours × $85 per hour = $680 ........................... $500 $1,180
Replacement of engine upper bifurcation fairing ......... 30 work hours × $85 per hour = $2,550 ...................... 500 3,050
Authority for This Rulemaking the FAA amends 14 CFR part 39 as (A) If fairing seal face 22 is found to have
follows: released material, repair or replace the fairing
Title 49 of the United States Code before further flight.
specifies the FAA’s authority to issue (B) If there is a single crack found on
PART 39—AIRWORTHINESS
rules on aviation safety. Subtitle I, fairing seal face 22, shorter than 6 mm, repair
DIRECTIVES
section 106, describes the authority of or replace the fairing within 100 engine flight
the FAA Administrator. ‘‘Subtitle VII: cycles, or at the next shop visit, whichever
Aviation Programs,’’ describes in more ■ 1. The authority citation for part 39 occurs sooner.
detail the scope of the Agency’s continues to read as follows: (C) If there is a single crack, longer than 6
authority. Authority: 49 U.S.C. 106(g), 40113, 44701. mm, found on fairing seal face 22, repair or
We are issuing this rulemaking under replace the fairing within 15 engine FCs or
§ 39.13 [Amended] at the next shop visit, whichever occurs
the authority described in ‘‘Subtitle VII,
sooner.
Part A, Subpart III, Section 44701: ■ 2. The FAA amends § 39.13 by adding (D) If there are two or more cracks found
General requirements.’’ Under that the following new airworthiness on fairing seal face 22, replace the fairing
section, Congress charges the FAA with directive (AD): within 15 engine FCs or at next shop visit,
promoting safe flight of civil aircraft in whichever occurs sooner.
air commerce by prescribing regulations 2016–24–08 Rolls-Royce plc: Amendment
(E) If there is any cracking or material loss
39–18725; Docket No. FAA–2016–6692;
for practices, methods, and procedures Directorate Identifier 2016–NE–13–AD.
found on seal support 23, replace the fairing
the Administrator finds necessary for within 15 engine FCs or at next shop visit,
safety in air commerce. This regulation (a) Effective Date whichever occurs sooner.
is within the scope of that authority This AD becomes effective January 5, 2017. (ii) If the visual inspection required by
because it addresses an unsafe condition paragraph (e)(3)(i) of this AD does not detect
(b) Affected ADs any crack, fluorescent penetrant inspect zone
that is likely to exist or develop on
None. A. Refer to AMM TASK 70–20–02, Water
products identified in this rulemaking Washable Fluorescent Penetrant Inspection
action. (c) Applicability (Maintenance Process 213), or OMat 632,
Regulatory Findings This AD applies to Rolls-Royce plc (RR) high sensitivity fluorescent penetrant
RB211-Trent 875-17, RB211-Trent 877-17, inspection, for guidance on fluorescent
We determined that this AD will not RB211-Trent 884-17, RB211-Trent 884B-17, penetrant inspection.
have federalism implications under RB211-Trent 892-17, RB211-Trent 892B-17, (A) If a crack shorter than 6 mm is
Executive Order 13132. This AD will and RB211-Trent 895-17 turbofan engines. detected, repair or replace the fairing within
not have a substantial direct effect on 100 engine FCs, or at the next shop visit,
(d) Reason
the States, on the relationship between whichever occurs sooner.
This AD was prompted by a report of (B) If a crack longer than 6 mm is detected,
the national government and the States,
cracking and material release from an engine repair or replace the fairing within 15 engine
or on the distribution of power and upper bifurcation fairing. We are issuing this FCs or at the next shop visit, whichever
responsibilities among the various AD to prevent failure of the engine fire occurs sooner.
levels of government. protection system, engine fire, and damage to
For the reasons discussed above, I the airplane. (f) Definition
certify this AD: For the purpose of this AD, a ‘‘shop visit’’
(1) Is not a ‘‘significant regulatory (e) Actions and Compliance
is defined as induction of an engine into the
action’’ under Executive Order 12866, Comply with this AD within the shop for maintenance involving the
(2) Is not a ‘‘significant rule’’ under compliance times specified, unless already separation of pairs of major mating engine
the DOT Regulatory Policies and done. flanges, except that the separation of engine
(1) Within 7,500 engine flight hours (FHs) flanges solely for the purposes of
Procedures (44 FR 11034, February 26,
time since new, or since last inspection, or transportation without subsequent engine
1979), within 150 flight cycles (FCs) after the
(3) Will not affect intrastate aviation maintenance does not constitute an engine
effective date of this AD, whichever occurs shop visit.
in Alaska to the extent that it justifies later, inspect the engine upper bifurcation
making a regulatory distinction, and fairing for cracks or missing material. Use (g) Alternative Methods of Compliance
(4) Will not have a significant paragraph (e)(3) of this AD to perform the (AMOCs)
economic impact, positive or negative, inspections. The Manager, Engine Certification Office,
on a substantial number of small entities (2) Repeat the inspection required by this FAA, may approve AMOCs for this AD. Use
under the criteria of the Regulatory AD within every 7,500 engine FHs time since the procedures found in 14 CFR 39.19 to
Flexibility Act. last inspection. make your request. You may email your
(3) Inspect the engine upper bifurcation request to: ANE-AD-AMOC@faa.gov.
List of Subjects in 14 CFR Part 39 fairing as follows. Refer to Figure 1 of RR
(h) Related Information
jstallworth on DSK7TPTVN1PROD with RULES
Alert Non-Modification Service Bulletin
Air transportation, Aircraft, Aviation (NMSB) RB.211–72–AJ165, dated March 31, (1) For more information about this AD,
safety, Incorporation by reference, 2016, for guidance on upper bifurcation contact Wego Wang, Aerospace Engineer,
Safety. fairing inspection locations. Engine Certification Office, FAA, Engine &
Adoption of the Amendment (i) Visually inspect upper bifurcation Propeller Directorate, 1200 District Avenue,
fairing seal face 22, seal support 23, and zone Burlington, MA 01803; phone: 781–238–
Accordingly, under the authority A for any cracks or material loss on the right 7134; fax: 781–238–7199; email: wego.wang@
delegated to me by the Administrator, side. faa.gov.
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(2) Refer to MCAI European Aviation DATES: Effective date 0901 UTC, FR 54752), Docket No. FAA–2016–7417.
Safety Agency AD 2016–0084, dated April February 2, 2017. The Director of the Interested parties were invited to
28, 2016, for more information. You may Federal Register approves this participate in this rulemaking effort by
examine the MCAI in the AD docket on the
incorporation by reference action under submitting written comments on the
Internet at http://www.regulations.gov by
searching for and locating it in Docket No. Title 1, Code of Federal Regulations, proposal. One comment was received
FAA–2016–6692. part 51, subject to the annual revision of supporting the FAA’s proposed action.
(3) RR Alert NMSB RB.211–72–AJ165, FAA Order 7400.11 and publication of Availability and Summary of
dated March 31, 2016, which is not conforming amendments. Documents for Incorporation by
incorporated by reference in this AD, can be ADDRESSES: FAA Order 7400.11A,
obtained from RR, using the contact Reference
information in paragraph (h)(4) of this AD.
Airspace Designations and Reporting
Points, and subsequent amendments can This document amends FAA Order
(4) For service information identified in 7400.11A, Airspace Designations and
this AD, contact Rolls-Royce plc, Corporate be viewed online at http://www.faa.gov/
Reporting Points, dated August 3, 2016,
Communications, P.O. Box 31, Derby, air_traffic/publications/. For further
and effective September 15, 2016. FAA
England, DE24 8BJ; phone: 011–44–1332– information, you can contact the
242424; fax: 011–44–1332–249936; email: Order 7400.11A is publicly available as
Airspace Policy Group, Federal Aviation
http://www.rolls-royce.com/contact/civil_ listed in the ADDRESSES section of this
Administration, 800 Independence
team.jsp; Internet: https://customers.rolls- document. FAA Order 7400.11A lists
Avenue SW., Washington, DC 20591;
royce.com/public/rollsroycecare. Class A, B, C, D, and E airspace areas,
(5) You may view this service information telephone: (202) 267–8783. The Order is
air traffic service routes, and reporting
at the FAA, Engine & Propeller Directorate, also available for inspection at the
points.
1200 District Avenue, Burlington, MA. For National Archives and Records
information on the availability of this Administration (NARA). For The Rule
material at the FAA, call 781–238–7125. information on the availability of FAA The FAA is amending Title 14, Code
(i) Material Incorporated by Reference Order 7400.11A at NARA, call (202) of Federal Regulations (14 CFR) part 71
None.
741–6030, or go to http:// by modifying the El Paso International
www.archives.gov/federal_register/ Airport, El Paso, TX, Class C airspace
Issued in Burlington, Massachusetts, on code_of_federal-regulations/ibr_
November 16, 2016. area. This action removes the cutout and
locations.html. reduced perimeter boundary arc that
Colleen M. D’Alessandro, FAA Order 7400.11, Airspace excludes the airspace extending upward
Manager, Engine & Propeller Directorate, Designations and Reporting Points, is
Aircraft Certification Service.
from 5,200 feet MSL to and including
published yearly and effective on 8,000 feet MSL within a 2-mile radius
[FR Doc. 2016–28663 Filed 11–30–16; 8:45 am] September 15. of the West Texas Airport, and the
BILLING CODE 4910–13–P
FOR FURTHER INFORMATION CONTACT: airspace beyond an 8-mile arc from the
Colby Abbott, Airspace Policy Group, El Paso International Airport beginning
Office of Airspace Services, Federal at the 115° bearing from the airport
DEPARTMENT OF TRANSPORTATION
Aviation Administration, 800 clockwise to the Rio Grande River.
Federal Aviation Administration Independence Avenue SW., Since West Texas Airport (renamed
Washington, DC 20591; telephone: (202) Horizon Airport in 2004) is permanently
14 CFR Part 71 267–8783. closed and the property sold for non-
SUPPLEMENTARY INFORMATION: aviation uses, the purpose for the
[Docket No. FAA–2016–7417; Airspace exclusions no longer exists. Thus, the
Docket No. 16–AWA–4] Authority for This Rulemaking FAA is removing the words ‘‘. . . that
RIN 2120–AA66 The FAA’s authority to issue rules airspace beyond an 8-mile arc from the
regarding aviation safety is found in El Paso International Airport beginning
Amendment of Class C Airspace; El Title 49 of the United States Code. at the 115° bearing from the airport
Paso International Airport, TX Subtitle I, Section 106 describes the clockwise to the Rio Grande River, and
AGENCY: Federal Aviation authority of the FAA Administrator. that airspace within a 2-mile radius of
Administration (FAA), DOT. Subtitle VII, Aviation Programs, the West Texas Airport, and . . .’’ from
ACTION: Final rule. describes in more detail the scope of the the regulatory text. The West Texas
agency’s authority. This rulemaking is Airport name and geographic coordinate
SUMMARY: This action amends Class C promulgated under the authority references are also removed from the
airspace at El Paso International Airport, described in Subtitle VII, Part A, Class C airspace description.
El Paso, TX, by removing a cutout from Subpart I, Section 40103. Under that Additionally, this action amends the
the Class C airspace area that excludes section, the FAA is charged with exclusion language pertaining to the
the airspace within a 2-mile radius of prescribing regulations to assign the use Class C airspace extending upward from
West Texas Airport and the airspace of the airspace necessary to ensure the 5,200 feet MSL to and including 8,000
beyond an 8-mile arc from the El Paso safety of aircraft and the efficient use of feet MSL from ‘‘. . . that airspace
International Airport beginning at the airspace. This regulation is within the within Mexico, and that airspace west of
115° bearing from the airport clockwise scope of that authority as it amends the long 106°27′02″ W.’’ to ‘‘. . . that
to the Rio Grande River. Additionally, El Paso, TX, Class C airspace area to airspace west of long. 106°27′02″ W.,
this rule removes West Texas Airport preserve the safe and efficient flow of and that airspace within Mexico.’’ This
from the Class C airspace description as air traffic in the El Paso, TX, area. change is editorial for format and clarity
jstallworth on DSK7TPTVN1PROD with RULES
the airport is closed, and amends the El to standardize the exclusion information
Paso International Airport geographic History associated with the Class C airspace
coordinates to coincide with the FAA’s On August 17, 2016, the FAA surface area and shelf.
aeronautical database. The FAA is published in the Federal Register a Lastly, this action updates the El Paso
taking this action to enable more notice of proposed rulemaking (NPRM) International Airport geographic
efficient operations at El Paso to modify the Class C airspace at El Paso coordinates to reflect the current airport
International Airport. International Airport, El Paso, TX (81 reference point information in the
VerDate Sep<11>2014 13:50 Nov 30, 2016 Jkt 241001 PO 00000 Frm 00016 Fmt 4700 Sfmt 4700 E:\FR\FM\01DER1.SGM 01DER1](https://thefederalregister.org/doc/81_FR_86798/page/4.svg)
Document Created: 2018-02-14 09:00:31
Document Modified: 2018-02-14 09:00:31
| Category | Regulatory Information | |
| Collection | Federal Register | |
| sudoc Class | AE 2.7: GS 4.107: AE 2.106: | |
| Publisher | Office of the Federal Register, National Archives and Records Administration | |
| Section | Rules and Regulations | |
| Action | Final rule. | |
| Dates | This AD becomes effective January 5, 2017. | |
| 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: [email protected] | |
| FR Citation | 81 FR 86567 | |
| RIN Number | 2120-AA64 | |
| CFR Associated | Air Transportation; Aircraft; Aviation Safety; Incorporation by Reference and Safety |
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