[Federal Register Volume 81, Number 166 (Friday, August 26, 2016)]
[Rules and Regulations]
[Pages 58816-58818]
[FR Doc No: 2016-20075]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2016-4221; Directorate Identifier 2015-NM-167-AD;
Amendment 39-18619; AD 2016-17-06]
RIN 2120-AA64

Airworthiness Directives; The Boeing Company Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule.

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SUMMARY: We are adopting a new airworthiness directive (AD) for all The
Boeing Company Model 767-200 and -300 series airplanes. This AD was
prompted by an evaluation by the design approval holder (DAH)
indicating that the aft pressure bulkhead web to pressure chord joint
is subject to widespread fatigue damage (WFD). This AD requires
repetitive high frequency eddy current (HFEC) inspections of the aft
pressure bulkhead web at fasteners common to the bulkhead web and
pressure chord, around the entire circumference of the pressure chord,
for any crack, and repair of cracks. We are issuing this AD to detect
and correct cracks in the aft pressure bulkhead web. Such cracking
could result in the loss of structural integrity of the airplane.

DATES: This AD is effective September 30, 2016.
    The Director of the Federal Register approved the incorporation by
reference of a certain publication listed in this AD as of September
30, 2016.

ADDRESSES: For service information identified in this final rule,
contact Boeing Commercial Airplanes, Attention: Data & Services
Management, P.O. Box 3707, MC 2H-65, Seattle, WA 98124-2207; telephone
206-544-5000, extension 1; fax<PHONE_NUMBER>; Internet https://www.myboeingfleet.com. You may view this referenced service information
at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW.,
Renton, WA. For information on the availability of this material at the
FAA, call<PHONE_NUMBER>. It is also available on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2016-
4221.

Examining the AD Docket

    You may examine the AD docket on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2016-
4221; or in person at the Docket Management Facility between 9 a.m. and
5 p.m., Monday through Friday, except Federal holidays. The AD docket
contains this AD, the regulatory evaluation, any comments received, and
other information. The address for the Docket Office (phone: 800-647-
5527) is Docket Management Facility, U.S. Department of Transportation,
Docket Operations, M-30, West Building Ground Floor, Room W12-140, 1200
New Jersey Avenue SE., Washington, DC 20590.

FOR FURTHER INFORMATION CONTACT: Wayne Lockett, Aerospace Engineer,
Airframe Branch, ANM-120S, FAA, Seattle Aircraft Certification Office
(ACO), 1601 Lind Avenue SW., Renton, WA 98057-3356; phone: 425-917-
6447; fax:<PHONE_NUMBER>; email<EMAIL_ADDRESS>
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 all The Boeing Company
Model 767-200 and -300 series airplanes. The NPRM published in the
Federal Register on March 8, 2016 (81 FR 12047) (``the NPRM''). The
NPRM was prompted by an evaluation by the DAH indicating that the aft
pressure bulkhead web to pressure chord joint is subject to WFD. The
NPRM proposed to require repetitive HFEC inspections of the aft
pressure bulkhead web at fasteners common to the bulkhead web and
pressure chord, around the entire circumference of the pressure chord,
for any crack, and repair of cracks. We are issuing this AD to detect
and correct cracks in the aft pressure bulkhead web. Such cracking
could result in the loss of structural integrity of the airplane.

Comments

    We gave the public the opportunity to participate in developing
this AD. The following presents the comments received on the NPRM and
the FAA's response. Boeing and United Airlines supported the NPRM.

Effect of Winglets on Accomplishment of the Proposed Actions

    Aviation Partners Boeing stated that accomplishing supplemental
type certificate (STC) ST01920SE does not affect the actions specified
in the proposed AD.
    We concur with the commenter. We have redesignated paragraph (c) of
the proposed AD as paragraph (c)(1), and added new paragraph (c)(2) to
this AD to state that installation of STC ST01920SE does not affect the
ability to accomplish the actions required by this AD. Therefore, for
airplanes on which STC ST01920SE is installed, a ``change in product''
alternative method of compliance (AMOC) approval request is not
necessary to comply with the requirements of 14 CFR 39.17.

Conclusion

    We reviewed the relevant data, considered the comments received,
and determined that air safety and the public interest require adopting
this AD with the changes described previously and 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.
    We also determined that these changes will not increase the
economic burden on any operator or increase the scope of this AD.

Related Service Information Under 1 CFR Part 51

    We reviewed Boeing Alert Service Bulletin 767-53A0268, dated April
1, 2015. The service information describes procedures for HFEC
inspections of the aft pressure bulkhead web at fasteners

common to the bulkhead web and pressure chord, around the entire
circumference of the pressure chord, for any crack, and repair of
cracks. 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

    We estimate that this AD affects 296 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..........................  57 work-hours x $85 per              $0           $4,845       $1,434,120
                                       hour = $4,845.
----------------------------------------------------------------------------------------------------------------

    The size of any repair area needs to be determined before material
and work-hour costs can be calculated, so we cannot provide cost
estimates for the on-condition actions specified in this AD.

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

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

List of Subjects in 14 CFR Part 39

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

Adoption of the Amendment

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

PART 39--AIRWORTHINESS DIRECTIVES

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

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

Sec.  39.13  [Amended]

0
2. The FAA amends Sec.  39.13 by adding the following new airworthiness
directive (AD):

2016-17-06 The Boeing Company: Amendment 39-18619; Docket No. FAA-
2016-4221; Directorate Identifier 2015-NM-167-AD.

(a) Effective Date

    This AD is effective September 30, 2016.

(b) Affected ADs

    None.

(c) Applicability

    (1) This AD applies to all The Boeing Company Model 767-200 and
-300 series airplanes, certificated in any category.
    (2) Installation of Supplemental Type Certificate (STC)
ST01920SE (http://rgl.faa.gov/Regulatory_and_Guidance_Library/
rgstc.nsf/0/59027f43b9a7486e86257b1d006591ee/$FILE/
ST01920SE_AML.pdf) does not affect the ability to accomplish the
actions required by this AD. Therefore, for airplanes on which STC
ST01920SE is installed, a ``change in product'' alternative method
of compliance (AMOC) approval request is not necessary to comply
with the requirements of 14 CFR 39.17.

(d) Subject

    Air Transport Association (ATA) of America Code 53, Fuselage.

(e) Unsafe Condition

    This AD was prompted by an evaluation by the design approval
holder indicating that the aft pressure bulkhead web to pressure
chord joint is subject to widespread fatigue damage. We are issuing
this AD to detect and correct cracks in the aft pressure bulkhead
web. Such cracking could result in the loss of structural integrity
of the airplane.

(f) Compliance

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

(g) Repetitive Inspections

    Except as required by paragraph (h) of this AD, at the
applicable time specified in paragraph 1.E., ``Compliance,'' of
Boeing Alert Service Bulletin 767-53A0268, dated April 1, 2015,
perform a surface high frequency eddy current (HFEC) inspection for
cracking of the aft pressure bulkhead web at fasteners common to the
bulkhead web and pressure chord, around the entire circumference of
the pressure chord, in accordance with the Accomplishment
Instructions of Boeing Alert Service Bulletin 767-53A0268, dated
April 1, 2015. For this AD, Group 2, Configuration 2, as specified
in Boeing Alert Service Bulletin 767-53A0268, dated April 1, 2015,
includes airplanes with the aft pressure bulkhead replaced as
specified in Boeing Alert Service Bulletin 767-53A0267. Repeat the
inspection thereafter at the applicable time specified in paragraph
1.E., ``Compliance,'' of Boeing Alert Service Bulletin 767-53A0268,
dated April 1, 2015.

(h) Service Information Exception

    Where Boeing Alert Service Bulletin 767-53A0268, dated April 1,
2015, specifies a compliance time ``after the original issue date of
this service bulletin,'' this AD requires compliance within the
specified compliance time after the effective date of this AD.

(i) Crack Repair

    If any crack is found during any inspection required by
paragraph (g) of this AD, before further flight, repair the crack
using a method approved in accordance with the procedures specified
in paragraph (j) of this AD. Although Boeing Alert Service Bulletin
767-53A0268, dated April 1, 2015, specifies to contact Boeing for
repair instructions, and specifies that action as ``RC'' (Required
for Compliance), this AD requires repair as specified in this
paragraph. Installation of a

repair terminates the inspections required by paragraph (g) of this
AD in the area covered by the repair only.

(j) Alternative Methods of Compliance (AMOCs)

    (1) The Manager, Seattle Aircraft Certification Office (ACO),
FAA, has the authority to approve AMOCs for this AD, if requested
using the procedures found in 14 CFR 39.19. In accordance with 14
CFR 39.19, send your request to your principal inspector or local
Flight Standards District Office, as appropriate. If sending
information directly to the manager of the ACO, send it to the
attention of the person identified in paragraph (k) 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 Commercial Airplanes Organization
Designation Authorization (ODA) that has been authorized by the
Manager, Seattle ACO, 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.
    (4) Except as required by paragraph (i) of this AD: For service
information that contains steps that are labeled as RC, the
provisions of paragraphs (j)(4)(i) and (j)(4)(ii) apply.
    (i) The steps labeled as RC, including substeps under an RC step
and any figures identified in an RC step, must be done to comply
with the AD. An AMOC is required for any deviations to RC steps,
including substeps and identified figures.
    (ii) Steps not labeled as RC may be deviated from using accepted
methods in accordance with the operator's maintenance or inspection
program without obtaining approval of an AMOC, provided the RC
steps, including substeps and identified figures, can still be done
as specified, and the airplane can be put back in an airworthy
condition.

(k) Related Information

    For more information about this AD, contact Wayne Lockett,
Aerospace Engineer, Airframe Branch, ANM-120S, FAA, Seattle ACO,
1601 Lind Avenue SW., Renton, WA 98057-3356; phone:<PHONE_NUMBER>;
fax:<PHONE_NUMBER>; email<EMAIL_ADDRESS>
(l) 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 Service Bulletin 767-53A0268, dated April 1,
2015.
    (ii) Reserved.
    (3) For service information identified in this AD, contact
Boeing Commercial Airplanes, Attention: Data & Services Management,
P.O. Box 3707, MC 2H-65, Seattle, WA 98124-2207; telephone 206-544-
5000, extension 1; fax<PHONE_NUMBER>; Internet https://www.myboeingfleet.com.
    (4) You may view this service information at the FAA, Transport
Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For
information on the availability of this material at the FAA, call
425-227-1221.
    (5) You may view this service information that is incorporated
by reference at the National Archives and Records Administration
(NARA). For information on the availability of this material at
NARA, call<PHONE_NUMBER>, or go to: http://www.archives.gov/federal-register/cfr/ibr-locations.html.

    Issued in Renton, Washington, on August 16, 2016.
Dorr M. Anderson,
Acting Manager, Transport Airplane Directorate Aircraft Certification
Service.
[FR Doc. 2016-20075 Filed 8-25-16; 8:45 am]
 BILLING CODE 4910-13-P


[Federal Register Volume 86, Number 48 (Monday, March 15, 2021)]
[Proposed Rules]
[Pages 14290-14293]
[FR Doc No: 2021-05252]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2021-0145; Project Identifier MCAI-2020-01212-R]
RIN 2120-AA64

Airworthiness Directives; Airbus Helicopters

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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SUMMARY: The FAA proposes to adopt a new airworthiness directive (AD)
for all Airbus Helicopters Model EC130B4 and EC130T2 helicopters. This
proposed AD was prompted by a report of cracks and geometrical non-
conformities of the tail rotor blades (TRBs); all cracks initiated in
the drain hole area at the blade root section. This proposed AD would
require cleaning affected parts, visual and dye penetrant inspections
for cracks of affected parts, a dimensional inspection to verify
conformity of affected parts, and corrective actions if necessary, as
specified in a European Union Aviation Safety Agency (EASA) AD, which
is proposed for incorporation by reference. 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 April 29,
2021.

ADDRESSES: You may send comments, using the procedures found in 14 CFR
11.43 and 11.45, by any of the following methods:
     Federal eRulemaking Portal: Go to https://www.regulations.gov. Follow the instructions for submitting comments.
     Fax:<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.
    For material that is proposed for incorporation by reference (IBR)
in this AD, contact the EASA, Konrad-Adenauer-Ufer 3, 50668 Cologne,
Germany; phone: +49 221 8999 000; email<EMAIL_ADDRESS>internet:
www.easa.europa.eu. You may find this material on the EASA website at
https://ad.easa.europa.eu. You may view this material at the FAA,
Office of the Regional Counsel, Southwest Region, 10101 Hillwood Pkwy.,
Room 6N-321, Fort Worth, TX 76177. For information on the availability
of this material at the FAA, call<PHONE_NUMBER>. It is also available in
the AD docket on the internet at https://www.regulations.gov by
searching for and locating Docket No. FAA-2021-0145.

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-2021-
0145; 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, any comments received, and other information. The street
address for Docket Operations is listed above. Comments will be
available in the AD docket shortly after receipt.

FOR FURTHER INFORMATION CONTACT: Hal Jensen, Aerospace Engineer,
Operational Safety Branch, FAA, 950 L'Enfant Plaza SW, Washington, DC
20024; phone:<PHONE_NUMBER>; email<EMAIL_ADDRESS>
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-2021-0145; Project Identifier
MCAI-2020-01212-R'' 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
this 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
https://www.regulations.gov, including any personal information you
provide. The agency will also post a report summarizing each
substantive verbal contact received about this proposal.

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 Hal Jensen, Aerospace Engineer, Operational Safety Branch, FAA,
950 L'Enfant Plaza SW, Washington, DC 20024; phone:<PHONE_NUMBER>;
email<EMAIL_ADDRESS>Any commentary that the FAA receives that is
not specifically designated as CBI will be placed in the public docket
for this rulemaking.

Discussion

    The EASA, which is the Technical Agent for the Member States of the
European Union, has issued EASA AD 2020-0187, dated August 21, 2020
(EASA AD 2020-0187) (also referred to as the Mandatory Continuing
Airworthiness Information, or the MCAI), to correct an unsafe condition
for all Airbus Helicopters Model EC130B4 and EC130T2 helicopters.
    This proposed AD was prompted by a report of cracks and geometrical
non-conformities of the TRBs on an EC130B4 helicopter; all cracks
initiated in the drain hole area at the blade root section. The same
TRBs can be installed on EC130T2 helicopters. The FAA is proposing this
AD to address geometrical non-conformities of the TRBs, which could
lead to crack initiation and consequent blade failure, and possible
loss of control of the helicopter. See the MCAI for additional
background information.

Related Service Information Under 1 CFR Part 51

    EASA AD 2020-0187 describes procedures for cleaning affected parts,
visual and dye penetrant inspections for cracks of affected parts (the
cleaning and visual and dye penetrant inspections are one-time or
repetitive, depending on the accumulated hours time in service on the
TRB), a one-time dimensional inspection to verify conformity of
affected parts, and corrective actions if necessary. Corrective actions
include replacement of the affected part with a serviceable part, and
additional repetitive cleaning and inspections until replacement of the
affected part with a serviceable part. 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 the
ADDRESSES section.

FAA's Determination and Requirements of This Proposed AD

    This product has been approved by the aviation authority of another
country, and is approved for operation in the United States. Pursuant
to the bilateral agreement with the State of Design Authority, the FAA
has been notified of the unsafe condition described in the MCAI
referenced above. The FAA is proposing this AD because the FAA
evaluated all the relevant information and determined the unsafe
condition described previously is likely to exist or develop in other
products of the same type design.

Proposed AD Requirements

    This proposed AD would require accomplishing the actions specified
in EASA AD 2020-0187, described previously, as incorporated by
reference, except for any differences identified as exceptions in the
regulatory text of this proposed AD.

Explanation of Required Compliance Information

    In the FAA's ongoing efforts to improve the efficiency of the AD
process, the FAA initially worked with Airbus and EASA to develop a
process to use certain EASA ADs as the primary source of information
for compliance with requirements for corresponding FAA ADs. The FAA has
since coordinated with other manufacturers and civil aviation
authorities (CAAs) to use this process. As a result, EASA AD 2020-0187
will be incorporated by reference in the FAA final rule. This proposed
AD would, therefore, require compliance with EASA AD 2020-0187 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 the EASA AD. Service information specified
in EASA AD 2020-0187 that is required for compliance with EASA AD 2020-
0187 will be available on the internet at https://www.regulations.gov
by searching for and locating Docket No. FAA-2021-0145 after the FAA
final rule is published.

Interim Action

    The FAA considers this proposed AD interim action. If final action
is later identified, the FAA might consider further rulemaking then.

Costs of Compliance

    The FAA estimates that this proposed AD affects 264 helicopters of
U.S. registry. The FAA estimates the following costs to comply with
this proposed AD:

                                      Estimated Costs for Required Actions
----------------------------------------------------------------------------------------------------------------
                                                                                Cost per       Cost on U.S.
                          Labor cost                              Parts cost        product         operators
----------------------------------------------------------------------------------------------------------------
7 work-hours x $85 per hour = $595...........................              $0             $595         $157,080
----------------------------------------------------------------------------------------------------------------

    The FAA estimates the following costs to do any necessary on-
condition actions that would be required based on the results of any
required actions. The FAA has no way of determining the number of
helicopters that might need these on-condition actions:

                 Estimated Costs of On-Condition Actions
------------------------------------------------------------------------
                                                             Cost per
              Labor cost                   Parts cost        product
------------------------------------------------------------------------
4 work-hours x $85 per hour = $340....          $4,641           $4,981
------------------------------------------------------------------------

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) 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.

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:

Airbus Helicopters: Docket No. FAA-2021-0145; Project Identifier
MCAI-2020-01212-R.

(a) Comments Due Date

    The FAA must receive comments by April 29, 2021.

(b) Affected Airworthiness Directives (ADs)

    None.

(c) Applicability

    This AD applies to all Airbus Helicopters Model EC130B4 and
EC130T2 helicopters, certificated in any category, with a tail rotor
blade (TRB), obtained by forging, part number 350A33-3002-02,
350A33-3002-03, 350A33-3002-04, or 350A33-3002-05 installed.

(d) Subject

    Joint Aircraft System Component (JASC) Code 6410, Tail rotor
blades.

(e) Reason

    This AD was prompted by a report of cracks and geometrical non-
conformities of the TRBs; all cracks initiated in the drain hole
area at the blade root section. The FAA is issuing this AD to
address geometrical non-conformities of the TRBs, which could lead
to crack initiation and consequent blade failure, and possible loss
of control of the helicopter.

(f) Compliance

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

(g) Requirements

    Except as specified in paragraph (h) of this AD: Comply with all
required actions and compliance times specified in, and in
accordance with, European Union Aviation Safety Agency (EASA) AD
2020-0187, dated August 21, 2020 (EASA AD 2020-0187).

(h) Exceptions to EASA AD 2020-0187

    (1) Where EASA AD 2020-0187 refers to its effective date, this
AD requires using the effective date of this AD.
    (2) The ``Remarks'' section of EASA AD 2020-0187 does not apply
to this AD.
    (3) Although the service information referenced in EASA AD 2020-
0187 specifies to discard certain parts, this AD does not include
that requirement.
    (4) Although the service information referenced in EASA AD 2020-
0187 specifies to return certain parts, this AD does not include
that requirement.
    (5) Where EASA AD 2020-0187 refers to flight hours (FH), this AD
requires using hours time-in-service.
    (6) Where the service information referenced in EASA AD 2020-
0187 specifies to ``contact customer support,'' this AD does not
include that requirement.
    (7) Where the service information referenced in EASA AD 2020-
0187 specifies to measure using the Smartphone application, the
PowerPoint method, or ``Contacting customer support with a specific
procedure,'' those methods of measurement are not required by this
AD.

(i) No Reporting Requirement

    Although the service information referenced in EASA AD 2020-0187
specifies to submit certain information to the manufacturer, this AD
does not include that requirement.

(j) Special Flight Permit

    Special flight permits may be issued in accordance with 14 CFR
21.197 and 21.199 to operate the helicopter to a location where the
helicopter can be modified (if the operator elects to do so),
provided that the helicopter is operated under visual flight rules.

(k) Alternative Methods of Compliance (AMOCs)

    The Manager, International Validation 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 International Validation Branch, send it to the
attention of the person identified in paragraph (l)(2) of this AD.
Information may be emailed to<EMAIL_ADDRESS>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.

(l) Related Information

    (1) For EASA AD 2020-0187, contact the EASA, Konrad-Adenauer-
Ufer 3, 50668 Cologne, Germany; phone: +49 221 8999 000; email:
<EMAIL_ADDRESS>internet: www.easa.europa.eu. You may find this
EASA AD on the EASA website at https://ad.easa.europa.eu. You may
view this material at the FAA, Office of the Regional Counsel,
Southwest Region, 10101 Hillwood Pkwy., Room 6N-321, Fort Worth, TX
76177.

For information on the availability of this material at the FAA,
call<PHONE_NUMBER>. This material may be found in the AD docket on
the internet at https://www.regulations.gov by searching for and
locating Docket No. FAA-2021-0145.
    (2) For more information about this AD, contact Hal Jensen,
Aerospace Engineer, Operational Safety Branch, FAA, 950 L'Enfant
Plaza SW, Washington, DC 20024; phone:<PHONE_NUMBER>; email:
<EMAIL_ADDRESS>
    Issued on March 9, 2021.
Lance T. Gant,
Director, Compliance & Airworthiness Division, Aircraft Certification
Service.
[FR Doc. 2021-05252 Filed 3-12-21; 8:45 am]
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