Airworthiness Directives; Rolls-Royce plc Turbofan Engines, 86567-86570 [2016-28663]
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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
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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
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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:
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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: https://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 https://
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 https://
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
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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
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be required based on the results of the
proposed inspection. We estimate that 5
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engines will need this repair and 5
engines will need this replacement:
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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,
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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.
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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.
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(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 https://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:
https://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.
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SUMMARY:
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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 https://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 https://
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
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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: https://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 https://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 https://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.
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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
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Cost per
Action Labor cost Parts cost product
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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 https://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: https://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
