[Federal Register Volume 84, Number 218 (Tuesday, November 12, 2019)]
[Rules and Regulations]
[Pages 60900-60902]
[FR Doc No: 2019-24501]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2019-0583; Product Identifier 2019-NM-063-AD; Amendment
39-19780; AD 2019-22-01]
RIN 2120-AA64

Airworthiness Directives; The Boeing Company Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule.

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SUMMARY: The FAA is adopting a new airworthiness directive (AD) for
certain The Boeing Company Model 787-8 airplanes. This AD was prompted
by a report of an escapement from the wing spar terminal fitting
supplier indicating that the engineering requirements provided by
Boeing for controlling machine mismatch were incorrect for part faying
surfaces, which can result in a reduced fatigue capability at the
interface of the side of body (SOB) rib. This AD requires repetitive
inspections for fatigue cracking and applicable on-condition actions
for the SOB rib webs where fastener locations attach the terminal
fittings. The FAA is issuing this AD to address the unsafe condition on
these products.

DATES: This AD is effective December 17, 2019.
    The Director of the Federal Register approved the incorporation by
reference of a certain publication listed in this AD as of December 17,
2019.

ADDRESSES: For service information identified in this final rule,
contact Boeing Commercial Airplanes, Attention: Contractual & Data
Services (C&DS), 2600 Westminster Blvd., MC 110-SK57, Seal Beach, CA
90740-5600; telephone<PHONE_NUMBER>; internet https://www.myboeingfleet.com. You may view this service information at the
FAA, Transport Standards Branch, 2200 South 216th St., Des Moines, WA.
For information on the availability of this material at the FAA, call
206-231-3195. It is also available on the internet at https://www.regulations.gov by searching for and locating Docket No. FAA-2019-
0583.

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-2019-
0583; or in person at Docket Operations between 9 a.m. and 5 p.m.,
Monday through Friday, except Federal holidays. The AD docket contains
this final rule, the regulatory evaluation, any comments received, and
other information. The address for Docket Operations is 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: Allen Rauschendorfer, Aerospace
Engineer, Airframe Section, FAA, Seattle ACO Branch, 2200 South 216th
St., Des Moines, WA 98198; phone and fax:<PHONE_NUMBER>; email:
<EMAIL_ADDRESS>
SUPPLEMENTARY INFORMATION:

Discussion

    The FAA issued a notice of proposed rulemaking (NPRM) to amend 14
CFR part 39 by adding an AD that would

apply to certain The Boeing Company Model 787-8 airplanes. The NPRM
published in the Federal Register on August 9, 2019 (84 FR 39239). The
NPRM was prompted by a report of an escapement from the wing spar
terminal fitting supplier indicating that the engineering requirements
provided by Boeing for controlling machine mismatch were incorrect for
part faying surfaces, which can result in a reduced fatigue capability
at the interface of the SOB rib. The NPRM proposed to require
repetitive inspections for fatigue cracking and applicable on-condition
actions for the SOB rib webs where fastener locations attach the
terminal fittings.
    The FAA is issuing this AD to address fatigue cracks in the left
and right SOB rib webs common to the front and rear wing spar terminal
fittings. Undetected fatigue cracks can grow to weaken primary wing
structure where it cannot sustain limit load, which could adversely
affect the structural integrity of the airplane.

Comments

    The FAA gave the public the opportunity to participate in
developing this final rule. The FAA has considered the comment
received. Boeing indicated its support for the NPRM.

Conclusion

    The FAA reviewed the relevant data, considered the comment
received, and determined that air safety and the public interest
require adopting this final rule as proposed, except for minor
editorial changes. The FAA has determined that these minor changes:
     Are consistent with the intent that was proposed in the
NPRM for addressing the unsafe condition; and
     Do not add any additional burden upon the public than was
already proposed in the NPRM.

Related Service Information Under 1 CFR Part 51

    The FAA reviewed Boeing Alert Requirements Bulletin B787-81205-
SB570036-00 RB, Issue 001, dated December 14, 2018. The service
information describes procedures for repetitive high frequency eddy
current or ultrasonic inspections for fatigue cracking and applicable
on-condition actions for the SOB rib webs where fastener locations
attach the terminal fittings. On-condition actions include repair. This
service information is reasonably available because the interested
parties have access to it through their normal course of business or by
the means identified in the ADDRESSES section.

Costs of Compliance

    The FAA estimates that this AD affects 1 airplane of U.S. registry.
The FAA estimates the following costs to comply with this AD:

                                      Estimated Costs for Required Actions
----------------------------------------------------------------------------------------------------------------
                                                                                Cost on U.S.
              Action                    Labor cost        Parts cost      Cost per product        operators
----------------------------------------------------------------------------------------------------------------
Inspection.......................  Up to 32 work-hours            $960  Up to $3,680 per     Up to $3,680 per
                                    x $85 per hour =                     inspection cycle.    inspection cycle.
                                    Up to $2,720 per
                                    inspection cycle.
----------------------------------------------------------------------------------------------------------------

    The FAA has received no definitive data that would enable the
agency to provide cost estimates for the on-condition actions specified
in this AD.
    According to the manufacturer, some or all of the costs of this AD
may be covered under warranty, thereby reducing the cost impact on
affected individuals. The FAA does not control warranty coverage for
affected individuals. As a result, the FAA has included all known costs
in our cost estimate.

Authority for This Rulemaking

    Title 49 of the United States Code specifies the FAA's authority to
issue rules on aviation safety. Subtitle I, section 106, describes the
authority of the FAA Administrator. Subtitle VII: Aviation Programs,
describes in more detail the scope of the Agency's authority.
    The FAA is 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.
    This AD is issued in accordance with authority delegated by the
Executive Director, Aircraft Certification Service, as authorized by
FAA Order 8000.51C. In accordance with that order, issuance of ADs is
normally a function of the Compliance and Airworthiness Division, but
during this transition period, the Executive Director has delegated the
authority to issue ADs applicable to transport category airplanes and
associated appliances to the Director of the System Oversight Division.

Regulatory Findings

    This AD will not have federalism implications under Executive Order
13132. This AD will not have a substantial direct effect on the States,
on the relationship between the national government and the States, or
on the distribution of power and responsibilities among the various
levels of government.
    For the reasons discussed above, I certify that this AD:
    (1) Is not a ``significant regulatory action'' under Executive
Order 12866,
    (2) Will not affect intrastate aviation in Alaska, and
    (3) 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):

2019-22-01 The Boeing Company: Amendment 39-19780; Docket No. FAA-
2019-0583; Product Identifier 2019-NM-063-AD.

(a) Effective Date

    This AD is effective December 17, 2019.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to The Boeing Company Model 787-8 airplanes,
certificated in any category, as identified in Boeing Alert
Requirements Bulletin B787-81205-SB570036-00 RB, Issue 001, dated
December 14, 2018.

(d) Subject

    Air Transport Association (ATA) of America Code 57, Wings.

(e) Unsafe Condition

    This AD was prompted by a report of an escapement from the wing
spar terminal fitting supplier indicating that the engineering
requirements provided by Boeing for controlling machine mismatch
were incorrect for part faying surfaces, which can result in a
reduced fatigue capability at the interface of the side of body
(SOB) rib. The FAA is issuing this AD to address fatigue cracks in
the left and right SOB rib webs common to the front and rear wing
spar terminal fittings. Undetected fatigue cracks can grow to weaken
primary wing structure where it cannot sustain limit load, which
could adversely affect the structural integrity of the airplane.

(f) Compliance

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

(g) Required Actions

    Except as specified by paragraph (h) of this AD: At the
applicable times specified in the ``Compliance'' paragraph of Boeing
Alert Requirements Bulletin B787-81205-SB570036-00 RB, Issue 001,
dated December 14, 2018, do all applicable actions identified in,
and in accordance with, the Accomplishment Instructions of Boeing
Alert Requirements Bulletin B787-81205-SB570036-00 RB, Issue 001,
dated December 14, 2018.

    Note 1 to paragraph (g): Guidance for accomplishing the actions
required by this AD can be found in Boeing Alert Service Bulletin
B787-81205-SB570036-00, Issue 001, dated December 14, 2018, which is
referred to in Boeing Alert Requirements Bulletin B787-81205-
SB570036-00 RB, Issue 001, dated December 14, 2018.

(h) Exception to Service Information Specifications

    Where Boeing Alert Requirements Bulletin B787-81205-SB570036-00
RB, Issue 001, dated December 14, 2018, specifies contacting Boeing
for repair instructions: This AD requires doing the repair using a
method approved in accordance with the procedures specified in
paragraph (i) of this AD.

(i) Alternative Methods of Compliance (AMOCs)

    (1) The Manager, Seattle ACO Branch, FAA, has the authority to
approve AMOCs for this AD, if requested using the procedures found
in 14 CFR 39.19. In accordance with 14 CFR 39.19, send your request
to your principal inspector or local Flight Standards District
Office, as appropriate. If sending information directly to the
manager of the certification office, send it to the attention of the
person identified in paragraph (j) of this AD. Information may be
emailed to<EMAIL_ADDRESS>    (2) Before using any approved AMOC, notify your appropriate
principal inspector, or lacking a principal inspector, the manager
of the local flight standards district office/certificate holding
district office.
    (3) An AMOC that provides an acceptable level of safety may be
used for any repair, modification, or alteration required by this AD
if it is approved by The Boeing Company Organization Designation
Authorization (ODA) that has been authorized by the Manager, Seattle
ACO Branch, FAA, to make those findings. To be approved, the repair
method, modification deviation, or alteration deviation must meet
the certification basis of the airplane, and the approval must
specifically refer to this AD.

(j) Related Information

    For more information about this AD, contact Allen
Rauschendorfer, Aerospace Engineer, Airframe Section, FAA, Seattle
ACO Branch, 2200 South 216th St., Des Moines, WA 98198; phone and
fax:<PHONE_NUMBER>; email<EMAIL_ADDRESS>
(k) Material Incorporated by Reference

    (1) The Director of the Federal Register approved the
incorporation by reference (IBR) of the service information listed
in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51.
    (2) You must use this service information as applicable to do
the actions required by this AD, unless the AD specifies otherwise.
    (i) Boeing Alert Requirements Bulletin B787-81205-SB570036-00
RB, Issue 001, dated December 14, 2018.
    (ii) [Reserved]
    (3) For service information identified in this AD, contact
Boeing Commercial Airplanes, Attention: Contractual & Data Services
(C&DS), 2600 Westminster Blvd., MC 110-SK57, Seal Beach, CA 90740-
5600; telephone<PHONE_NUMBER>; internet https://www.myboeingfleet.com.
    (4) You may view this service information at the FAA, Transport
Standards Branch, 2200 South 216th St., Des Moines, WA. For
information on the availability of this material at the FAA, call
206-231-3195.
    (5) You may view this service information that is incorporated
by reference at the National Archives and Records Administration
(NARA). For information on the availability of this material at
NARA, email<EMAIL_ADDRESS>or go to: https://www.archives.gov/federal-register/cfr/ibr-locations.html.

    Issued in Des Moines, Washington, on October 29, 2019.
Michael Kaszycki,
Acting Director, System Oversight Division, Aircraft Certification
Service.
[FR Doc. 2019-24501 Filed 11-8-19; 8:45 am]
BILLING CODE 4910-13-P


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82,578


[Federal Register Volume 87, Number 1 (Monday, January 3, 2022)]
[Notices]
[Pages 86-87]
[FR Doc No: 2021-28330]

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ENVIRONMENTAL PROTECTION AGENCY

[FRL-9379-01-R9]

Revision of Approved Primacy Program for the Commonwealth of the
Northern Mariana Islands

AGENCY: Environmental Protection Agency (EPA).

ACTION: Notice of approval.

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

SUMMARY: Notice is hereby given that the Commonwealth of the Northern
Mariana Islands (CNMI) revised its approved primacy program under the
federal Safe Drinking Water Act (SDWA) by adopting regulations that
effectuate the federal Ground Water Rule (GWR). The Environmental
Protection Agency (EPA) has determined that CNMI's revision request
meets the applicable SDWA program revision requirements and the
regulations adopted by CNMI are no less stringent than the
corresponding federal regulations. Therefore, EPA approves this
revision to CNMI's approved primacy program. However, this
determination on CNMI's request for approval of a program revision
shall take effect in accordance with the procedures described below in
the SUPPLEMENTARY INFORMATION section of this notice after the
opportunity to request a public hearing.

DATES: A request for a public hearing must be received or postmarked
before February 2, 2022.

ADDRESSES: Documents relating to this determination that were submitted
by CNMI as part of its program revision request are available for
public inspection online at http:/deq.gov.mp/sec.asp?secID=5. In
addition, these documents are available between the hours of 7:30 a.m.
and 4:30 p.m., Monday through Friday, at the following address: CNMI
Bureau of Environmental and Coastal Quality, Gualo Rai Center--Safe
Drinking Water Branch 2nd floor, Chalan Pale Arnold--Middle Road,
Saipan, MP 96950. If there are issues accessing the website, please
contact Travis Spaeth, at<PHONE_NUMBER>, or via email at
[email protected].

FOR FURTHER INFORMATION CONTACT: Anna Yen, EPA Region 9, Drinking Water
Section, via telephone at<PHONE_NUMBER> or via email address at
[email protected].

SUPPLEMENTARY INFORMATION:
    Background. EPA approved CNMI's initial application for primary
enforcement authority (``primacy'') of drinking water systems on
November 4, 1982 (47 FR 50105). Since initial primacy approval, EPA has
approved

various revisions to CNMI's primacy program. For the revision covered
by this action, EPA promulgated the GWR at 40 CFR subpart S on November
8, 2006 (71 FR 65574). The GWR provides protection against microbial
pathogens in public water systems using ground water sources. EPA has
determined that the GWR requirements were adopted into the CNMI
Commonwealth Register, Section 2141 (alternatively published as
Northern Mariana Islands Administrative Code, Title 65, Chapter 20) in
a manner that CNMI's regulations are comparable to and no less
stringent than the federal requirements. EPA has also determined that
CNMI's program revision request meets all of the regulatory
requirements for approval, as set forth in 40 CFR 142.12, including a
side-by-side comparison of the Federal requirements demonstrating the
corresponding CNMI authorities, additional materials to support special
primacy requirements of 40 CFR 142.16, a review of the requirements
contained in 40 CFR 142.10 necessary for CNMI to attain and retain
primary enforcement responsibility, and a statement by the CNMI
Attorney General certifying that CNMI's laws and regulations to carry
out the program revision were duly adopted and are enforceable. The
Attorney General's statement also affirms that there are no
environmental audit privilege and immunity laws that would impact
CNMI's ability to implement or enforce the CNMI laws and regulations
pertaining to the program revision. Therefore, EPA approves this
revision of CNMI's approved primacy program. The Technical Support
Document, which provides EPA's analysis of CNMI's program revision
request, is available by submitting a request to the following email
address: [email protected]. Please note ``Technical Support
Document'' in the subject line of the email.
    Public Process. Any interested person may request a public hearing
on this determination. A request for a public hearing must be received
or postmarked before February 2, 2022, and addressed to the Regional
Administrator of EPA Region 9, via the following email address: [email protected], or by contacting the EPA Region 9 contact person
listed above in this notice by telephone if you do not have access to
email. Please note, ``State Program Revision Determination'' in the
subject line of the email. The Regional Administrator may deny
frivolous or insubstantial requests for a hearing. If a timely request
for a public hearing is made, then EPA Region 9 may hold a public
hearing. Any request for a public hearing shall include the following
information: 1. The name, address, and telephone number of the
individual, organization, or other entity requesting a hearing; 2. A
brief statement of the requesting person's interest in the Regional
Administrator's determination and of information that the requesting
person intends to submit at such hearing; and 3. The signature of the
individual making the request, or, if the request is made on behalf of
an organization or other entity, the signature of a responsible
official of the organization or other entity.
    If EPA Region 9 does not receive a timely request for a hearing or
a request for a hearing was denied by the Regional Administrator for
being frivolous or insubstantial, and the Regional Administrator does
not elect to hold a hearing on their own motion, EPA's approval shall
become final and effective on February 2, 2022, and no further public
notice will be issued.
    Authority: Section 1413 of the Safe Drinking Water Act, as amended,
42 U.S.C. 300g-2 (1996), and 40 CFR part 142 of the National Primary
Drinking Water Regulations.

    Dated: December 23, 2021.
Deborah Jordan,
Acting Regional Administrator, EPA Region 9.
[FR Doc. 2021-28330 Filed 12-30-21; 8:45 am]
BILLING CODE 6560-50-P


[Federal Register Volume 87, Number 209 (Monday, October 31, 2022)]
[Proposed Rules]
[Pages 65535-65538]
[FR Doc No: 2022-23172]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2022-1311; Project Identifier MCAI-2022-00624-E]
RIN 2120-AA64

Airworthiness Directives; Safran Helicopter Engines, S.A. (Type
Certificate Previously Held by Turbomeca, S.A.) Turboshaft Engines

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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

SUMMARY: The FAA proposes to supersede Airworthiness Directive (AD)
2021-08-02, which applies to all Safran Helicopter Engines, S.A.
(Safran) Arriel 2D and Arriel 2E model turboshaft engines. AD 2021-08-
02 requires replacing certain critical parts before reaching their
published in-service life limits, performing scheduled maintenance
tasks before reaching their published periodicity, and performing
unscheduled maintenance tasks when the engine meets certain conditions.
Since the FAA issued AD 2021-08-02, Safran has revised the
airworthiness limitation section (ALS) of the existing maintenance and
overhaul manuals, introducing new and more restrictive instructions and
maintenance tasks. This proposed AD would require revisions to the ALS
of the operator's existing approved aircraft maintenance program (AMP),
as applicable, as specified in a European Union Aviation Safety Agency
(EASA) AD, which is proposed for incorporation by reference (IBR). The
FAA is proposing this AD to address the unsafe condition on these
products.

DATES: The FAA must receive comments on this proposed AD by December
15, 2022.

ADDRESSES: You may send comments, using the procedures found in 14 CFR
11.43 and 11.45, by any of the following methods:
     Federal eRulemaking Portal: Go to regulations.gov. Follow
the instructions for submitting comments.
     Fax:<PHONE_NUMBER>.
     Mail: U.S. Department of Transportation, Docket
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New
Jersey Avenue SE, Washington, DC 20590.
     Hand Delivery: Deliver to Mail address above between 9
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
    AD Docket: You may examine the AD docket at regulations.gov under
Docket No. FAA-2022-1311; or in person at Docket Operations between 9
a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD
docket contains this NPRM, the mandatory continuing airworthiness
information (MCAI), any comments received, and other information. The
street address for Docket Operations is listed above.
    Material Incorporated by Reference:
     For material identified in this NPRM, contact EASA,
Konrad-Adenauer-Ufer 3, 50668 Cologne, Germany; phone: +49 221 8999
000; email: [email protected]. You may find this material on the EASA
website at ad.easa.europa.eu.
     You may view this material at the FAA, Airworthiness
Products Section, Operational Safety Branch, 1200 District Avenue,
Burlington, MA 01803. For information on the availability of this
material at the FAA, call<PHONE_NUMBER>.

FOR FURTHER INFORMATION CONTACT: Kevin Clark, Aviation Safety Engineer,
ECO Branch, FAA, 1200 District Avenue, Burlington, MA 01803; phone:
(781) 238-7088; email: [email protected].

SUPPLEMENTARY INFORMATION:

Comments Invited

    The FAA invites you to send any written relevant data, views, or
arguments about this proposal. Send your comments to an address listed
under ADDRESSES. Include ``Docket No. FAA-2022-1311; Project Identifier
MCAI-2022-00624-E'' at the beginning of your comments. The most helpful
comments reference a specific portion of the proposal, explain the
reason for any recommended change, and include supporting data. The FAA
will consider all comments received by the closing date and may amend
the proposal because of those comments.
    Except for Confidential Business Information (CBI) as described in
the following paragraph, and other information as described in 14 CFR
11.35, the FAA will post all comments received, without change, to
regulations.gov, including any personal information you provide. The
agency will also post a report summarizing each substantive verbal
contact we receive about this NPRM.

Confidential Business Information

    CBI is commercial or financial information that is both customarily
and actually treated as private by its owner. Under the Freedom of
Information Act (FOIA) (5 U.S.C. 552), CBI is exempt from public
disclosure. If your comments responsive to this NPRM contain commercial
or financial information that is customarily treated as private, that
you actually treat as private, and that is relevant or responsive to
this NPRM, it is important that you clearly designate the submitted
comments as CBI. Please mark each page of your submission containing
CBI as ``PROPIN.'' The FAA will treat such marked submissions as
confidential under the FOIA, and they will not be placed in the public
docket of this NPRM. Submissions containing CBI should be sent to Kevin
Clark, Aviation Safety Engineer, ECO Branch, FAA, 1200 District Avenue,
Burlington, MA 01803. Any commentary that the FAA

receives which is not specifically designated as CBI will be placed in
the public docket for this rulemaking.

Background

    The FAA issued AD 2021-08-02, Amendment 39-21496 (86 FR 26651, May
17, 2021) (AD 2021-08-02), for all Safran Arriel 2D and Arriel 2E model
turboshaft engines. AD 2021-08-02 was prompted by the manufacturer
revising the maintenance and overhaul manuals to introduce new or more
restrictive airworthiness limitations and maintenance tasks. AD 2021-
08-02 requires replacing certain critical parts before reaching their
published in-service life limits, performing scheduled maintenance
tasks before reaching their published periodicity, and performing
unscheduled maintenance tasks when the engine meets certain conditions.
As a terminating action, AD 2021-08-02 requires operators to revise the
ALS of their existing approved AMP by incorporating the revised
airworthiness limitations and maintenance tasks. The FAA issued AD
2021-08-02 to prevent failure of the engine.

Actions Since AD 2021-08-02 Was Issued

    Since the FAA issued AD 2021-08-02, EASA, which is the Technical
Agent for the Member States of the European Union, issued EASA AD 2022-
0083, dated May 11, 2022 (EASA AD 2022-0083), which supersedes EASA AD
2018-0273, dated December 13, 2018 (EASA AD 2018-0273). EASA AD 2022-
0083 states that the manufacturer published a revised ALS introducing
new and more restrictive tasks and limitations. These new or more
restrictive airworthiness limitations and maintenance tasks include
initial and repetitive inspections for clogging of the power turbine
air pressurization pipe. The FAA is proposing this AD to prevent
failure of the engine. This unsafe condition, if not addressed, could
result in uncontained release of a critical part, damage to the engine,
and damage to the helicopter. See EASA AD 2022-0083 for additional
background information.

Related Service Information Under 1 CFR Part 51

    The FAA reviewed EASA AD 2022-0083. EASA AD 2022-0083 specifies
instructions for accomplishing the actions specified in the applicable
ALS, including performing maintenance tasks, replacing life-limited
parts, and revising the existing approved AMP by incorporating the
limitations, tasks, and associated thresholds and intervals described
in the ALS. This material is reasonably available because the
interested parties have access to it through their normal course of
business or by the means identified in ADDRESSES.

Other Related Service Information

    The FAA reviewed TASK 05-10-01-200-801-A01, Values of Authorized
In-Service Life Limits--Airworthiness Limitations, of the Safran
Helicopter Engines Arriel 2 Maintenance Manual, dated December 30,
2021, and TASK 05-10-10-200-801-A01, Airworthiness Limitations--
Temporary Update No. 05-3--Tables of Mandatory Maintenance Tasks, of
the Safran Helicopter Engines Arriel 2 Maintenance Manual, dated April
15, 2022.
    The FAA reviewed Section 05-10-00, Airworthiness Limitations, of
Chapter 05, Airworthiness Limitations-Frequencies-Inspections, of the
Safran Helicopter Engines Arriel 2D and Arriel 2E Overhaul Manuals,
Volume 1, No. X 292 R1 500 2, Update No. 23, dated December 30, 2021.

FAA's Determination

    These products have been approved by the aviation authority of
another country, and are approved for operation in the United States.
Pursuant to the FAA's bilateral agreement with the State of Design
Authority, it has notified the FAA of the unsafe condition described in
the MCAI described above. The FAA is issuing this NPRM after
determining that the unsafe condition described previously is likely to
exist or develop in other products of the same type design.

Proposed AD Requirements in This NPRM

    This proposed AD would retain none of the requirements of AD 2021-
08-02. This proposed AD would require accomplishing the actions
specified in EASA AD 2022-0083, described previously, except as
discussed under ``Differences Between this Proposed AD and the EASA
AD.'' An owner/operator (pilot) holding at least at least a private
pilot certificate may incorporate the actions and associated thresholds
and intervals, including life limits and maintenance tasks, into
existing approved maintenance or inspection program as applicable, and
performance of this incorporation must be entered into the aircraft
records showing compliance with this AD in accordance with 14 CFR
43.9(a) and 14 CFR 91.417(a)(2)(v). The record must be maintained as
required by 14 CFR 91.417, 121.380, or 135.439. This is an exception to
the FAA's standard maintenance regulations.

Explanation of Required Compliance Information

    In the FAA's ongoing efforts to improve the efficiency of the AD
process, the FAA developed a process to use some civil aviation
authority (CAA) ADs as the primary source of information for compliance
with requirements for corresponding FAA ADs. The FAA has since
coordinated with other manufacturers and CAAs to use this process. As a
result, the FAA proposes to incorporate by reference EASA AD 2022-0083
in the FAA final rule. This proposed AD would, therefore, require
compliance with EASA AD 2022-0083 in its entirety through that
incorporation, except for any differences identified as exceptions in
the regulatory text of this proposed AD. Using common terms that are
the same as the heading of a particular section in the EASA AD does not
mean that operators need comply only with that section. For example,
where the AD requirement refers to ``all required actions and
compliance times,'' compliance with this AD requirement is not limited
to the section titled ``Required Action(s) and Compliance Time(s)'' in
EASA AD 2022-0083. Service information required by the EASA AD for
compliance will be available at regulations.gov under Docket No. FAA-
2022-1311 after the FAA final rule is published.

Differences Between This Proposed AD and the EASA AD

    EASA AD 2022-0083 applies to Arriel 2D, 2E, 2H, 2L2, and 2N model
turboshaft engines, whereas this proposed AD would only apply to Arriel
2D and Arriel 2E model turboshaft engines. Arriel 2H, 2L2, and 2N
engines are not U.S. type certificated.
    EASA AD 2022-0083 defines the AMP as the approved Aircraft
Maintenance Programme on the basis of which the operator or the owner
ensures the continuing airworthiness of each operated engine, this AD
defines the AMP as the Aircraft Maintenance Program on the basis of
which the operator or the owner ensures the continuing airworthiness of
each operated helicopter.
    EASA AD 2022-0083 requires revising the approved AMP within 12
months after its effective date, whereas this proposed AD would require
incorporating the actions and associated thresholds and intervals,
including life limits and maintenance tasks, into the existing approved
maintenance or inspection program, as applicable,

within 90 days after the effective date of the AD.
    This AD does not require compliance with paragraphs (1), (2), (4),
or (5) of EASA AD 2022-0083.

Costs of Compliance

    The FAA estimates that this AD, if adopted as proposed, would
affect 426 engines installed on helicopters of U.S. Registry. The FAA
estimates the following costs to comply with this proposed AD:

                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                                                                Cost per      Cost on U.S.
                Action                         Labor cost           Parts cost        product        operators
----------------------------------------------------------------------------------------------------------------
Revise the ALS and the operator's       1 work-hour x $85 per                 $0             $85         $36,210
 existing approved AMP.                  hour = $85.
----------------------------------------------------------------------------------------------------------------

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.
    The FAA is 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

    The FAA determined that this proposed AD would not have federalism
implications under Executive Order 13132. This proposed AD would 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 proposed
regulation:
    (1) Is not a ``significant regulatory action'' under Executive
Order 12866,
    (2) Would not affect intrastate aviation in Alaska, and
    (3) Would 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.

The Proposed Amendment

    Accordingly, under the authority delegated to me by the
Administrator, the FAA proposes to amend 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:
0
a. Removing Airworthiness Directive 2021-08-02, Amendment 39-21496 (86
FR 26651, May 17, 2021); and
0
b. Adding the following new airworthiness directive:

Safran Helicopter Engines, S.A. (Type Certificate previously held by
Turbomeca, S.A.): Docket No. FAA-2022-1311; Project Identifier MCAI-
2022-00624-E.

(a) Comments Due Date

    The FAA must receive comments on this airworthiness directive
(AD) by December 15, 2022.

(b) Affected ADs

    This AD replaces AD 2021-08-02, Amendment 39-21496 (86 FR 26651,
May 17, 2021) (AD 2021-08-02).

(c) Applicability

    This AD applies to all Safran Helicopter Engines, S.A. (Safran)
(Type Certificate previously held by Turbomeca, S.A.) Arriel 2D and
Arriel 2E model turboshaft engines.

(d) Subject

    Joint Aircraft Service Component (JASC) Code 7250, Turbine
Section.

(e) Unsafe Condition

    This AD was prompted by the manufacturer revising the
maintenance and overhaul manuals to introduce new or more
restrictive airworthiness limitations and maintenance tasks. The FAA
is issuing this AD to prevent failure of the engine. The unsafe
condition, if not addressed, could result in uncontained release of
a critical part, damage to the engine, and damage to the helicopter.

(f) Compliance

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

(g) Required Actions

    (1) Except as specified in paragraph (h) and (i) of this AD:
Perform all required actions within the compliance times specified
in, and in accordance with, European Union Aviation Safety Agency AD
2022-0083, dated May 11, 2022 (EASA AD 2022-0083).
    (2) The actions required by paragraph (g)(1) of this AD may be
performed by the owner/operator (pilot) holding at least a private
pilot certificate and must be entered into the aircraft records
showing compliance with this AD in accordance with 14 CFR 43.9(a)
and 14 CFR 91.417(a)(2)(v). The record must be maintained as
required by 14 CFR 91.417, 121.380, or 135.439.

(h) Exceptions to EASA AD 2022-0083

    (1) Where EASA AD 2022-0083 defines the AMP as the approved
Aircraft Maintenance Programme on the basis of which the operator or
the owner ensures the continuing airworthiness of each operated
engine, this AD defines the AMP as the Aircraft Maintenance Program
on the basis of which the operator or the owner ensures the
continuing airworthiness of each operated helicopter.
    (2) Where EASA AD 2022-0083 refers to its effective date, this
AD requires using the effective date of this AD.
    (3) This AD does not require compliance with paragraph (1) of
EASA AD 2022-0083.
    (4) This AD does not require compliance with paragraph (2) of
EASA AD 2022-0083.
    (5) Where paragraph (3) of EASA AD 2022-0083 requires revising
the approved aircraft maintenance program (AMP) within 12 months
after the effective date of EASA AD 2021-0217, this AD requires
incorporating the actions and associated thresholds and intervals,
including life limits and maintenance tasks, into the existing
approved maintenance or inspection program, as applicable, within 90
days after the effective date of this AD.
    (6) This AD does not require compliance with paragraph (4) of
EASA AD 2022-0083.
    (7) This AD does not require compliance with paragraph (5) of
EASA AD 2022-0083.
    (8) The ``Remarks'' section of EASA AD 2022-0083 does not apply
to this AD.

(i) Provisions for Alternative Actions, Thresholds, and Intervals,
Including Life Limits

    After performing the action required by paragraph (g) of this
AD, no alternative actions and associated thresholds and intervals,
including life limits, are allowed unless they are approved as
specified in the provisions of the ``Ref. Publications'' section of
EASA AD 2022-0083.

(j) Alternative Methods of Compliance (AMOCs)

    The Manager, ECO Branch, FAA, has the authority to approve AMOCs
for this AD, if requested using the procedures found in 14 CFR
39.19. In accordance with 14 CFR 39.19, send your request to your
principal inspector or local Flight Standards District Office, as
appropriate. If sending information directly to the manager of the
certification office, send it to the attention of the person
identified in paragraph (k) of this AD and email to: [email protected]. Before using any approved AMOC, notify your
appropriate principal inspector, or lacking a principal inspector,
the manager of the local flight standards district office/
certificate holding district office.

(k) Additional Information

    For more information about this AD, contact Kevin Clark,
Aviation Safety Engineer, ECO Branch, FAA, 1200 District Avenue,
Burlington, MA 01803; phone:<PHONE_NUMBER>; email:
[email protected].

 (l) Material Incorporated by Reference

    (1) The Director of the Federal Register approved the
incorporation by reference of the material listed in this paragraph
under 5 U.S.C. 552(a) and 1 CFR part 51.
    (2) You must use this service information as applicable to do
the actions required by this AD, unless the AD specifies otherwise.
    (i) European Union Aviation Safety Agency AD 2022-0083, dated
May 11, 2022.
    (ii) Reserved.
    (3) For EASA AD 2022-0083, contact EASA, Konrad-Adenauer-Ufer 3,
50668 Cologne, Germany; phone: +49 221 8999 000; email:
[email protected]. You may find this material on the EASA website
at ad.easa.europa.eu.
    (4) You may view this service information at FAA, Airworthiness
Products Section, Operational Safety Branch, 1200 District Avenue,
Burlington, MA 01803. For information on the availability of this
material at the FAA, call<PHONE_NUMBER>.
    (5) You may view this service information that is incorporated
by reference at the National Archives and Records Administration
(NARA). For information on the availability of this material at
NARA, email: [email protected], or go to: www.archives.gov/federal-register/cfr/ibr-locations.html.

    Issued on October 20, 2022.
Christina Underwood,
Acting Director, Compliance & Airworthiness Division, Aircraft
Certification Service.
[FR Doc. 2022-23172 Filed 10-28-22; 8:45 am]
BILLING CODE 4910-13-P


[Federal Register Volume 80, Number 213 (Wednesday, November 4, 2015)]
[Proposed Rules]
[Pages 68284-68286]
[FR Doc No: 2015-28080]

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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2015-3778; Directorate Identifier 2015-NE-27-AD]
RIN 2120-AA64

Airworthiness Directives; Rolls-Royce plc Turbofan Engines

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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

SUMMARY: We propose to adopt a new airworthiness directive (AD) for all
Rolls-Royce plc (RR) RB211-535E4-37, RB211-535E4-B-37, and RB211-535E4-
C-37 turbofan engines. This proposed AD was prompted by a review of
operational data that determined certain RR RB211-535E4-37 engines have
been operated to a more severe flight profile than is consistent with
the flight profile used to establish the cyclic life limits for the
rotating parts. This proposed AD would require recalculating the cyclic
life for certain engine life-limited rotating parts and removing those
parts that have exceeded their cyclic life limit within specified
compliance times. We are proposing this AD to prevent failure of life-
limited rotating parts, which could result in uncontained parts
release, damage to the engine, and damage to the airplane.

DATES: We must receive comments on this proposed AD by December 4,
2015.

ADDRESSES: You may send comments by any of the following methods:
     Federal eRulemaking Portal: Go to http://www.regulations.gov. Follow the instructions for submitting comments.
     Mail: Docket Management Facility, U.S. Department of
Transportation, 1200 New Jersey Avenue SE., West Building Ground Floor,
Room W12-140, Washington, DC 20590-0001.
     Hand Delivery: Deliver to Mail address above between 9
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
     Fax:<PHONE_NUMBER>.
    For service information identified in this proposed 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. You may view this
service information at the FAA, Engine & Propeller Directorate, 12 New
England Executive Park, Burlington, MA. For information on the
availability of this material at the FAA, call<PHONE_NUMBER>.

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-2015-
3778; or in person at the Docket Operations office between 9 a.m. and 5
p.m., Monday through Friday, except Federal holidays. The AD docket
contains this proposed 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 in the ADDRESSES section. Comments will be available in
the AD docket shortly after receipt.

FOR FURTHER INFORMATION CONTACT: Robert Green, Aerospace Engineer,
Engine Certification Office, FAA, Engine & Propeller Directorate, 12
New England Executive Park, Burlington, MA 01803; phone:<PHONE_NUMBER>;
fax:<PHONE_NUMBER>; email<EMAIL_ADDRESS>
SUPPLEMENTARY INFORMATION:

Comments Invited

    We invite you to send any written relevant data, views, or
arguments about this proposed AD. Send your comments to an address
listed under the ADDRESSES section. Include ``Docket No. FAA-2015-3778;
Directorate Identifier 2015-NE-27-AD'' at the beginning of your
comments. We specifically invite comments on the overall regulatory,
economic, environmental, and energy aspects of this proposed AD. We
will consider all comments received by the closing date and may amend
this proposed AD based on those comments.
    We will post all comments we receive, without change, to http://www.regulations.gov, including any personal information you provide. We
will also post a report summarizing each substantive verbal contact
with FAA personnel concerning this proposed AD.

Discussion

    The European Aviation Safety Agency (EASA), which is the Technical
Agent for the Member States of the European Community, has issued EASA
AD 2015-0148, dated July 23, 2015 (corrected July 24, 2015), referred
to hereinafter as ``the MCAI'', to correct an unsafe condition for the
specified products. The MCAI states:

    A review of operational flight data has revealed that some
RB211-535 engines may have been operated beyond the flight profile
(FP) assumed by the operator when establishing the operational
limits (life limits) within which the corresponding critical parts
are allowed to remain installed.
    This condition, if not corrected, may lead to critical part
failure, possibly resulting in release of high energy debris, damage
to the aeroplane and/or injury to the occupants.

    To preclude failure of an engine life-limited part, the MCAI
specifies, and this proposed AD would require, recalculating the cyclic
life for certain parts, and removing from service those parts that have
exceeded their cyclic life limit within specified compliance times.
This proposed AD would establish a new default Flight Profile G for
RB211-535E4-37 engine life-limited parts. If, however, operators meet
the requirements of Appendix 6 of RR Alert Non-Modification Service
Bulletin (NMSB) No. RB.211-72-AH972, Revision 3, dated August 28, 2015,
they may operate to Flight Profile A or B. 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-2015-3778.

Related Service Information Under 1 CFR Part 51

    RR has issued Alert NMSB No. RB.211-72-AH972, Revision 3, dated
August 28, 2015. The NMSB describes a new flight profile, the consumed
cyclic life corrections for prior operation of affected parts, and the
removal from service recommendations for parts that have exceeded their
cyclic life limit. This service information is reasonably available
because the interested parties have access to it through their normal
course of business or by the means identified in the ADDRESSES section
of this NPRM.

FAA's Determination and Requirements of This Proposed AD

    This product has been approved by the aviation authority of the
United Kingdom and is approved for operation in the United States.
Pursuant to our bilateral agreement with the European Community, EASA
has notified us of the unsafe condition described in the MCAI and
service information referenced above. We are proposing this AD because
we evaluated all information provided by EASA and determined the unsafe
condition exists and is likely to exist or develop on other products of
the same type design. This proposed AD would require recalculation of
the remaining cyclic life for the affected engine life-limited parts
and removal from service of parts that exceed their cyclic life limit.

Costs of Compliance

    We estimate that this proposed AD affects 107 engines installed on
airplanes of U.S. registry. Pro-rated cost of the lost cyclic life as a
result of the corrections would be about $25,417,324. We estimate it
will take 1 hour to recalculate the consumed cyclic life and revise the
engine records. The average labor rate is $85 per hour. Based on these
figures, we estimate the cost of this proposed AD on U.S. operators to
be $25,426,419.

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 proposed AD would not have federalism
implications under Executive Order 13132. This proposed AD would 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 proposed
regulation:
    (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.

The Proposed Amendment

    Accordingly, under the authority delegated to me by the
Administrator, the FAA proposes to amend 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):

Rolls-Royce plc: Docket No. FAA-2015-3778; Directorate Identifier
2015-NE-27-AD.

(a) Comments Due Date

    We must receive comments by December 4, 2015.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to all Rolls-Royce plc (RR) RB211-535E4-37,
RB211-535E4-B-37, and RB211-535E4-C-37 turbofan engines.

(d) Reason

    This AD was prompted by a review of operational data that
determined that certain RR RB211-535E4-37 engines have been operated
to a more severe flight profile than is consistent with the flight
profile used to establish the cyclic life limits for the rotating
parts. We are issuing this AD to prevent failure of life-limited
rotating parts, which could result in uncontained parts release,
damage to the engine, and damage to the airplane.

(e) Actions and Compliance

    Comply with this AD within the compliance times specified,
unless already done. Within 21 days after the effective date of this
AD:
    (1) For RR RB211-535E4-37 engines, establish a new flight
profile, Flight Profile G, as the new default profile for flight
operations and new part lives for life-limited parts.
    (i) Use Appendix 6 of RR Alert Non-Modification Service Bulletin
(NMSB) No. RB.211-72-AH972, Revision 3, dated August 28, 2015, to
define Flight Profile G.
    (ii) Use the definition of Flight Profile G in Appendix 6 and
the maximum approved cyclic lives in Appendix 2 of RR Alert NMSB No.
RB.211-72-AH972, Revision 3, dated August 28, 2015, to identify the
new lives for life-limited parts.
    (iii) If operators meet the requirements of Appendix 6 of RR
Alert NMSB No. RB.211-72-AH972, Revision 3, dated August 28, 2015,
they may operate to Flight Profile A or B.
    (2) For all RB211-535E4-37, RB211-535E4-B-37, and RB211-535E4-C-
37 engines, determine if any part identified by part number and
serial number in Appendix 4 of RR Alert NMSB No. RB.211-72-AH972,
Revision 3, dated August 28, 2015, is installed on the engine.
    (i) Do not return to service any engine with a part identified
in paragraph (e)(2) of this AD after the part reaches the
``Compliance Time'' date or cycles, whichever occurs first, as
specified in Appendix 4 of RR Alert NMSB No. RB.211-72-AH972,
Revision 3, dated August 28, 2015.
    (ii) For each part identified in paragraph (e)(2) of this AD
without a ``Compliance Time'' that has a lifing correction
identified, apply the lifing correction for each part using the
``Additional Life Consumed Flight Cycles'' specified in Appendix 4
of RR Alert NMSB No. RB.211-72-AH972, Revision 3, dated August 28,
2015.
    (3) For RB211-535E4-37 engines operated to Flight Profile G with
parts listed in Appendix 4 of RR Alert NMSB No. RB.211-72-AH972,
Revision 3, dated August 28, 2015, do the following:

    (i) Re-calculate the consumed cyclic life of the low-pressure
(LP) compressor shaft, LP turbine shaft, LP turbine disk Stage 2,
intermediate-pressure compressor rotor shaft Stage 1 to 6, high-
pressure (HP) compressor rotor disk Stage 1 and 2, HP compressor
rear rotor shaft assembly, and HP turbine disk as follows.
    (ii) Determine the Flight Profile G cycles in service (CIS).
Count all CIS accumulated since April 1, 2015, inclusive.
    (iii) Use the Flight Profile G cycles in service from paragraph
(e)(3)(ii) of this AD, the maximum approved lives in Appendix 2 of
RR Alert NMSB No. RB.211-72-AH972, Revision 3, dated August 28,
2015, and Figure 1 to paragraph (e) of this AD to calculate the new
consumed cyclic lives.
[GRAPHIC] [TIFF OMITTED] TP04NO15.000

(f) 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_ADDRESS>
(g) Related Information

    (1) For more information about this AD, contact Robert Green,
Aerospace Engineer, Engine Certification Office, FAA, Engine &
Propeller Directorate, 12 New England Executive Park, Burlington, MA
01803; phone:<PHONE_NUMBER>; fax:<PHONE_NUMBER>; email:
<EMAIL_ADDRESS>    (2) Refer to MCAI European Aviation Safety Agency AD 2015-0148,
dated July 23, 2015 (Corrected July 24, 2015), 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-2015-3778.
    (3) RR Alert NMSB No. RB.211-72-AH972, Revision 3, dated August
28, 2015, and Task 05-00-01-800-000, ``Recording and Control of the
Lives of Parts'', dated July 1, 2015, of the RR RB211-535E4 Time
Limits Manual (TLM), publication reference T-211(535)-6RR, Revision
49, dated July 1, 2015, can be obtained from RR using the contact
information in paragraph (g)(4) of this proposed AD.
    (4) For service information identified in this proposed 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, 12 New England Executive Park, Burlington,
MA. For information on the availability of this material at the FAA,
call<PHONE_NUMBER>.

    Issued in Burlington, Massachusetts, on October 28, 2015.
Colleen M. D'Alessandro,
Directorate Manager, Engine & Propeller Directorate, Aircraft
Certification Service.
[FR Doc. 2015-28080 Filed 11-3-15; 8:45 am]
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