Airworthiness Directives; Airbus Helicopters, 29212-29216 [2021-11376]
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29212
Proposed Rules
Federal Register
Vol. 86, No. 103
Tuesday, June 1, 2021
This section of the FEDERAL REGISTER
contains notices to the public of the proposed
issuance of rules and regulations. The
purpose of these notices is to give interested
persons an opportunity to participate in the
rule making prior to the adoption of the final
rules.
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2021–0379; Project
Identifier MCAI–2021–00068–R]
RIN 2120–AA64
Airworthiness Directives; Airbus
Helicopters
Federal Aviation
Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
The FAA proposes to
supersede Airworthiness Directive (AD)
2016–12–51, which applies to all Airbus
Helicopters Model AS332L2 and Model
EC225LP helicopters. AD 2016–12–51
prohibits all further flight of Model
AS332L2 and Model EC225LP
helicopters. AD 2016–12–51 was
prompted by an accident in which the
main rotor hub detached from the main
gearbox (MGB). Since the FAA issued
AD 2016–12–51, the design approval
holder has developed procedures that
address failure of the main rotor system.
This proposed AD would require
replacing certain second stage planet
gear assemblies, removing certain
epicyclic modules, installing a full flow
magnetic plug (FFMP), revising the
existing rotorcraft flight manual (RFM)
for your helicopter, repetitively
inspecting the MGB particle detectors,
repetitively inspecting the MGB oil filter
and oil cooler, and corrective action if
necessary, as specified in a European
Union Aviation Safety Agency (EASA)
AD, which is proposed for incorporation
by reference (IBR). The actions specified
in the proposed AD would terminate the
flight prohibition. 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 July 16, 2021.
ADDRESSES: You may send comments,
using the procedures found in 14 CFR
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SUMMARY:
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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: 202–493–2251.
• 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 IBR
in this AD, contact the EASA, KonradAdenauer-Ufer 3, 50668 Cologne,
Germany; telephone +49 221 8999 000;
email ADs@easa.europa.eu; internet
www.easa.europa.eu. You may find this
IBR 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 817–222–5110.
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–
0379.
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–
0379; 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:
Mahmood Shah, Aviation Safety
Engineer, Fort Worth ACO Branch,
FAA, 10101 Hillwood Pkwy., Fort
Worth, TX 76177; telephone 817–222–
5538; email mahmood.g.shah@faa.gov.
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
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under ADDRESSES. Include ‘‘Docket No.
FAA–2021–0379; Project Identifier
MCAI–2021–00068–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 Mahmood Shah,
Aviation Safety Engineer, Fort Worth
ACO Branch, FAA, 10101 Hillwood
Pkwy., Fort Worth, TX 76177; telephone
817–222–5538; email
mahmood.g.shah@faa.gov. 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 FAA issued AD 2016–12–51,
Amendment 39–18578 (81 FR 43479,
July 5, 2016) (AD 2016–12–51), which
applies to all Airbus Helicopters Model
AS332L2 and EC225LP helicopters. AD
2016–12–51 prohibits all further flight
of Airbus Helicopters Model AS332L
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and EC225LP helicopters. The FAA
issued AD 2016–12–51 to address an
accident involving an EC225LP
helicopter in which the main rotor hub
detached from the MGB. The Airbus
Helicopters Model AS332L2 helicopter
has a similar design to the affected
Model EC225LP helicopter, therefore,
this model may be subject to the unsafe
condition revealed on the Model
EC225LP helicopter.
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Actions Since AD 2016–12–51 Was
Issued
Since the FAA issued AD 2016–12–
51, the design approval holder has
developed procedures that address
failure of the main rotor system. These
procedures terminate the flight
prohibition required by AD 2016–12–51.
In addition, after AD 2016–12–51 was
issued, the FAA issued an Alternate
Means of Compliance (AMOC) letter
dated September 7, 2017, which
addressed the flight prohibition
required by paragraph (e) of AD 2016–
12–51. The AMOC letter lifted the flight
prohibition and allowed operation of
the affected helicopter models provided
the conditions specified in the AMOC
letter were followed, which include
repetitive inspections that have no
terminating action. This proposed AD
includes terminating action for certain
repetitive inspections.
The EASA, which is the Technical
Agent for the Member States of the
European Union, has issued EASA AD
2017–0134R2, dated April 16, 2020
(EASA AD 2017–0134R2) (also referred
to as the Mandatory Continuing
Airworthiness Information, or the
MCAI), to correct an unsafe condition
for all Airbus Helicopters Model
AS332L2 and EC225LP helicopters.
This proposed AD was prompted by
an accident involving a Model EC225LP
helicopter in which the main rotor hub
detached from the MGB. The FAA is
proposing this AD to address failure of
the main rotor system, which would
result in loss of control of the
helicopter. See the MCAI for additional
background information.
Related Service Information Under 1
CFR Part 51
EASA AD 2017–0134R2 references
procedures for replacing certain second
stage planet gear assemblies with
serviceable parts; removing certain
epicyclic modules from service;
modifying the helicopter by installing
an FFMP; revising the RFM to prohibit
MGB particle burning in-flight;
repetitively inspecting the FFMP and
MGB particle detectors for metal
particles, analyzing any metal particles
that are found, and corrective action;
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and repetitively inspecting the MGB oil
filter and oil cooler for particles and
corrective action. The corrective actions
include replacing an affected MGB with
a serviceable MGB. EASA AD 2017–
0134R2 also provides terminating action
for certain repetitive inspections.
Airbus Helicopters has issued
Emergency Alert Service Bulletin EC225
05A049, Revision 6, dated July 25, 2017;
and Emergency Alert Service Bulletin
AS 332 05.01.07, Revision 6, dated July
27, 2017. The service information
specifies procedures for, among other
things, replacing the MGB.
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.
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
2017–0134R2 that is required for
compliance with EASA AD 2017–
0134R2 will be available on the internet
at https://www.regulations.gov by
searching for and locating Docket No.
FAA–2021–0379 after the FAA final
rule is published.
FAA’s Determination and Requirements
of This Proposed AD
These products have been approved
by the aviation authority of another
country, and are 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
after evaluating all the relevant
information and determining the unsafe
condition described previously is likely
to exist or develop in other products of
these same type designs.
Differences Between This Proposed AD
and the MCAI
Although the service information
referenced in EASA AD 2017–0134R2
specifies to return affected planetary
gear assemblies to the manufacturer for
module overhaul, this proposed AD
does not include that requirement.
Although the service information
referenced in EASA AD 2017–0134R2
specifies that retrofit of the planet gear
of the MGB can only be done by Airbus
Helicopters or Airbus Helicopters
approved repair centers, this proposed
AD does not include that requirement.
EASA AD 2017–0134R2 requires
operators to ‘‘inform all flight crews’’ of
revisions to the RFM, and thereafter to
‘‘operate the helicopter accordingly.’’
However, this AD would not
specifically require those actions.
FAA regulations require pilots to
follow the procedures in the existing
RFM including all updates. 14 CFR 91.9
requires that no person may operate a
civil aircraft without complying with
the operating limitations specified in
the RFM. Therefore, including a
requirement in this AD to operate the
airplane according to the revised RFM
would be redundant and unnecessary.
Further, compliance with such a
requirement in an AD would be
impracticable to demonstrate or track on
an ongoing basis; therefore, a
requirement to operate the airplane in
such a manner would be unenforceable.
Proposed AD Requirements
This proposed AD would require
accomplishing the actions specified in
EASA AD 2017–0134R2 described
previously, as incorporated by
reference, except for any differences
identified as exceptions in the
regulatory text of this AD and except as
discussed under ‘‘Differences Between
this Proposed AD and the MCAI.’’
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
2017–0134R2 will be incorporated by
reference in the FAA final rule. This
proposed AD would, therefore, require
compliance with EASA AD 2017–
0134R2 in its entirety, through that
incorporation, except for any differences
identified as exceptions in the
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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 28 helicopters of U.S.
registry. The FAA estimates the
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following costs to comply with this
proposed AD:
ESTIMATED COSTS FOR REQUIRED ACTIONS *
Action
Labor cost
Up to 6 work-hours × $85 per hour = $510
New proposed actions ..................................
Cost per
product
Parts cost
$0
Up to $510 .....
Cost on U.S.
operators
Up to $14,280.
* Table does not include estimated costs for reporting.
The FAA estimates that it would take
about 1 work-hour per product to
comply with the proposed reporting
requirement in this proposed AD. The
average labor rate is $85 per hour. Based
on these figures, the FAA estimates the
cost of reporting the inspection results
on U.S. operators to be $2,380, or $85
per product.
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
Labor cost
Parts cost
Cost per
product
40 work-hours × $85 per hour = $3,400 .................................................................................................................
$295,000
$298,400
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According to the manufacturer, some
or all of the costs of this proposed AD
may be covered under warranty, thereby
reducing the cost impact on affected
operators. The FAA does not control
warranty coverage for affected operators.
As a result, the FAA has included all
known costs in the cost estimate.
Paperwork Reduction Act
A federal agency may not conduct or
sponsor, and a person is not required to
respond to, nor shall a person be subject
to penalty for failure to comply with a
collection of information subject to the
requirements of the Paperwork
Reduction Act unless that collection of
information displays a current valid
OMB control number. The control
number for the collection of information
required by this proposed AD is 2120–
0056. The paperwork cost associated
with this proposed AD has been
detailed in the Costs of Compliance
section of this document and includes
time for reviewing instructions, as well
as completing and reviewing the
collection of information. Therefore, all
reporting associated with this proposed
AD is mandatory. Comments concerning
the accuracy of this burden and
suggestions for reducing the burden
should be directed to Information
Collection Clearance Officer, Federal
Aviation Administration, 10101
Hillwood Parkway, Fort Worth, TX
76177–1524.
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
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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.
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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
1. The authority citation for part 39
continues to read as follows:
■
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
[Amended]
2. The FAA amends § 39.13 by:
a. Removing Airworthiness Directive
2016–12–51, Amendment 39–18578 (81
FR 43479, July 5, 2016); and
■ b. Adding the following new
airworthiness directive:
■
■
Airbus Helicopters: Docket No. FAA–2021–
0379; Project Identifier MCAI–2021–
00068–R.
(a) Comments Due Date
The FAA must receive comments on this
airworthiness directive (AD) by July 16, 2021.
(b) Affected ADs
This AD replaces AD 2016–12–51,
Amendment 39–18578 (81 FR 43479, July 5,
2016 (AD 2016–12–51)).
(c) Applicability
This AD applies to all Airbus Helicopters
Model AS332L2 and EC225LP helicopters,
certificated in any category.
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(d) Subject
Joint Aircraft System Component (JASC)
Code 6320, Main Rotor Gearbox.
(e) Reason
This AD was prompted by an accident
involving a Model EC225LP helicopter in
which the main rotor hub detached from the
main gearbox. The FAA is issuing this AD to
address failure of the main rotor system,
which would result in loss of control of the
helicopter.
(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
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(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 2017–0134R2,
dated April 16, 2020 (EASA AD 2017–
0134R2).
(h) Exceptions to EASA AD 2017–0134R2
(1) Where EASA AD 2017–0134R2 refers to
the effective dates specified in paragraphs
(h)(1)(i) through (v) of this AD, this AD
requires using the effective date of this AD.
(i) The effective date of EASA AD 2017–
0134R2.
(ii) October 13, 2016 (the effective date of
EASA AD 2016–0199, dated October 7,
2016).
(iii) March 20, 2017 (the effective date of
EASA AD 2017–0050–E, dated March 17,
2017).
(iv) June 30, 2017 (the effective date of
EASA AD 2017–0111, dated June 23, 2017).
(v) August 1, 2017 (the effective date of
EASA AD 2017–0134, dated July 27, 2017).
(2) The ‘‘Remarks’’ section of EASA AD
2017–0134R2 does not apply to this AD.
(3) Where any service information referred
to in EASA AD 2017–0134R2 specifies to
discard certain parts after they have been
removed from the helicopter, this AD
requires removing those parts from service.
(4) Where paragraph (2) of EASA AD 2017–
0134R2 specifies to replace a part before
exceeding the applicable ‘‘new service life
limit,’’ this AD requires removing that part
from service.
(5) Where any service information referred
to in EASA AD 2017–0134R2 specifies to
return certain parts to the manufacturer,
including for overhaul, after they have been
removed from the helicopter, this AD does
not include that requirement.
(6) Where EASA AD 2017–0134R2 refers to
flight hours (FH), this AD requires using
hours time-in-service.
(7) Where any service information referred
to in EASA AD 2017–0134R2 specifies to
perform a metallurgical analysis and contact
the manufacturer if unsure about the
characterization of the particles collected,
this AD does require characterization of the
particles collected, however this AD does not
require contacting the manufacturer to
determine the characterization of the
particles collected.
(8) Where EASA AD 2017–0134R2 requires
actions during each ‘‘after last flight’’ of the
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day (ALF) inspection, this AD requires those
actions before the first flight of each day.
(9) Where any service information referred
to in EASA AD 2017–0134R2 specifies to do
the actions identified in paragraphs (h)(9)(i)
through (iv) of this AD, this AD does not
include those requirements.
(i) Watch a video for removing the grease
from the full flow magnetic plug (FFMP),
using a cleaning agent, and collecting
particles.
(ii) Return affected planetary gear assembly
to the manufacturer for module overhaul.
(iii) Contact the approved repair station/
Airbus Helicopters if the reason for a repair
to an epicyclic module is unknown and
inform/contact Airbus Helicopters.
(iv) Contact the approved repair station/
Airbus Helicopters depending on who
performed the last overhaul (RG) to
determine if a repair has been done on the
second stage planet gears since new.
(10) Where any service information
referred to in EASA AD 2017–0134R2
specifies that retrofit of the planet gear of the
main gearbox (MGB) can only be done by
Airbus Helicopters or Airbus Helicopters
approved repair centers, this AD does not
require that the retrofit of the planet gear be
done only by Airbus Helicopters or Airbus
Helicopters approved repair centers. For this
AD the retrofit can also be done by an FAAapproved repair station.
(11) Where paragraph (5) of EASA AD
2017–0134R2 specifies accomplishing the
FFMP additional work within 3 months after
August 1, 2017, this AD requires
accomplishing the FFMP additional work
within 4 months after the effective date of
this AD.
(12) Where paragraph (6) of EASA AD
2017–0134R2 specifies to ‘‘inform all flight
crews and, thereafter, operate the helicopter
accordingly,’’ this AD does not require those
actions.
(13) Where any service information
referred to in EASA AD 2017–0134R2
specifies that if any 16NCD13 particles are
found you are to take a 1-liter sample of oil
and send it to the manufacturer, this AD does
not require those actions.
(14) Where any service information
referred to in EASA AD 2017–0134R2
specifies ‘‘Do not resume flights until
corrective action(s) are agreed by Airbus
Helicopters,’’ or to contact Airbus
Helicopters before resuming flights ‘‘if
further particles are collected during the
close monitoring period,’’ for this AD, you
must repair before further flight using a
method specified in paragraph (h)(14)(i) or
(ii) of this AD.
(i) In accordance with FAA approved
procedures.
(ii) In accordance with the procedures
specified in Appendix 4.A., Particle
Analysis, of Airbus Helicopters Emergency
Alert Service Bulletin EC225 05A049,
Revision 6, dated July 25, 2017; or
Emergency Alert Service Bulletin AS 332
05.01.07, Revision 6, dated July 27, 2017, as
applicable, except as required by paragraphs
(h)(5), (7), and (13) of this AD.
(15) Where the service information
identified in EASA AD 2017–0134R2
specifies to report inspection results to
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Airbus Helicopters, for this AD, report the
inspection results at the applicable time
specified in paragraph (h)(15)(i) or (ii) of this
AD.
(i) If the inspection was done on or after
the effective date of this AD: Submit the
report within 30 days after the date of the
inspection.
(ii) If the inspection was done before the
effective date of this AD: Submit the report
within 30 days after the effective date of this
AD.
(i) Credit for Previous Actions
(1) This paragraph provides credit for the
actions specified in paragraph (4) of EASA
AD 2017–0134R2, if those actions were
performed before the effective date of this AD
using Airbus Helicopters Emergency Alert
Service Bulletin AS332 ASB 63.00.83 or
EC225 ASB 63A030, both Revision 1, both
dated October 7, 2016.
(2) Corrective action(s) for the inspections
required by paragraphs (8) and (10) of EASA
AD 2017–0134R2 accomplished on a
helicopter before the effective date of this
AD, in accordance with Paragraph 3.B. and
Appendix 4.A. of the Accomplishment
Instructions of the applicable Airbus
Helicopters service information specified in
paragraphs (i)(2)(i) through (viii) of this AD,
as applicable, are acceptable to comply with
the requirements of paragraph (11) of EASA
AD 2017–0134R2 for that helicopter, but only
for the corrective actions for the inspections
required by paragraphs (8) and (10) of EASA
AD 2017–0134R2.
(i) Emergency Alert Service Bulletin AS332
ASB 05.01.07, Revision 2, dated October 7,
2016.
(ii) Emergency Alert Service Bulletin
AS332 ASB 05.01.07, Revision 3, dated
February 25, 2017.
(iii) Emergency Alert Service Bulletin
AS332 ASB 05.01.07, Revision 4, dated
March 17, 2017.
(iv) Emergency Alert Service Bulletin
AS332 ASB 05.01.07, Revision 5, dated June
23, 2017.
(v) Emergency Alert Service Bulletin
EC225 05A049, Revision 2, dated October 7,
2016.
(vi) Emergency Alert Service Bulletin
EC225 05A049, Revision 3, dated February
25, 2017.
(vii) Emergency Alert Service Bulletin
EC225 05A049, Revision 4, dated March 17,
2017.
(viii) Emergency Alert Service Bulletin
EC225 05A049, Revision 5, dated June 23,
2017.
(j) Special Flight Permit
Special flight permits, as described in 14
CFR 21.197 and 21.199, are prohibited.
(k) Alternative Methods of Compliance
(AMOCs)
(1) 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 manager of the International Validation
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Branch, send it to the attention of the person
identified in paragraph (l)(2) of this AD.
Information may be emailed to: 9-AVS-AIR730-AMOC@faa.gov.
(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.
(l) Related Information
(1) For EASA AD 2017–1034R2, contact the
EASA, Konrad-Adenauer-Ufer 3, 50668
Cologne, Germany; telephone +49 221 8999
000; email ADs@easa.europa.eu; 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 817–222–5110. 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–2021–0379.
(2) For more information about this AD,
contact Mahmood Shah, Aviation Safety
Engineer, Fort Worth ACO Branch, FAA,
10101 Hillwood Pkwy., Fort Worth, TX
76177; telephone 817–222–5538; email
mahmood.g.shah@faa.gov.
Issued on May 21, 2021.
Gaetano A. Sciortino,
Deputy Director for Strategic Initiatives,
Compliance & Airworthiness Division,
Aircraft Certification Service.
[FR Doc. 2021–11376 Filed 5–28–21; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2021–0380; Project
Identifier MCAI–2020–01683–R]
RIN 2120–AA64
Airworthiness Directives; Airbus
Helicopters Deutschland GmbH
Helicopters
Examining the AD Docket
Federal Aviation
Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
The FAA proposes to adopt a
new airworthiness directive (AD) for
certain Airbus Helicopters Deutschland
GmbH Model EC135P1, EC135P2,
EC135P2+, EC135P3, EC135T1,
EC135T2, EC135T2+, and EC135T3
helicopters. This proposed AD was
prompted by a report that geometrical
non-conformities were found in the root
section of the tail rotor blade (TRB).
This proposed AD would require a onetime inspection (dimensional check) of
jbell on DSKJLSW7X2PROD with PROPOSALS
SUMMARY:
VerDate Sep<11>2014
17:16 May 28, 2021
Jkt 253001
the TRB for conformity and, depending
on the findings, replacement of certain
affected parts, as specified in a
European Union Aviation Safety Agency
(EASA) AD, which is proposed for
incorporation by reference (IBR). This
proposed AD would also prohibit
rework, repair, or modification of
affected parts in the affected area of the
TRB assembly root. 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 July 16, 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: 202–493–2251.
• 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 IBR
in this AD, contact the EASA, KonradAdenauer-Ufer 3, 50668 Cologne,
Germany; telephone +49 221 8999 000;
email ADs@easa.europa.eu; 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 817–222–5110. It is also
available in the AD docket on the
internet at https://www.regulations.gov
by searching for and locating Docket No.
FAA–2021–0380.
You may examine the AD docket on
the internet at https://
www.regulations.gov by searching for
and locating Docket No. FAA–2021–
0380; 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:
Andrea Jimenez, Aerospace Engineer,
COS Program Management Section,
Operational Safety Branch, Compliance
PO 00000
Frm 00005
Fmt 4702
Sfmt 4702
& Airworthiness Division, FAA, 1600
Stewart Ave., Mail Stop: Room 410,
Westbury, NY 11590; telephone (516)
228–7330; email andrea.jimenez@
faa.gov.
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–2021–0380.; Project Identifier
MCAI–2020–01683–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 Andrea Jimenez,
Aerospace Engineer, COS Program
Management Section, Operational
Safety Branch, Compliance &
Airworthiness Division, FAA, 1600
Stewart Ave., Mail Stop: Room 410,
Westbury, NY 11590; telephone (516)
228–7330; email andrea.jimenez@
faa.gov. Any commentary that the FAA
receives that is not specifically
designated as CBI will be placed in the
public docket for this rulemaking.
E:\FR\FM\01JNP1.SGM
01JNP1
]]>Agencies
[Federal Register Volume 86, Number 103 (Tuesday, June 1, 2021)]
[Proposed Rules]
[Pages 29212-29216]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2021-11376]
========================================================================
Proposed Rules
Federal Register
________________________________________________________________________
This section of the FEDERAL REGISTER contains notices to the public of
the proposed issuance of rules and regulations. The purpose of these
notices is to give interested persons an opportunity to participate in
the rule making prior to the adoption of the final rules.
========================================================================
Federal Register / Vol. 86, No. 103 / Tuesday, June 1, 2021 /
Proposed Rules
[[Page 29212]]
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2021-0379; Project Identifier MCAI-2021-00068-R]
RIN 2120-AA64
Airworthiness Directives; Airbus Helicopters
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking (NPRM).
-----------------------------------------------------------------------
SUMMARY: The FAA proposes to supersede Airworthiness Directive (AD)
2016-12-51, which applies to all Airbus Helicopters Model AS332L2 and
Model EC225LP helicopters. AD 2016-12-51 prohibits all further flight
of Model AS332L2 and Model EC225LP helicopters. AD 2016-12-51 was
prompted by an accident in which the main rotor hub detached from the
main gearbox (MGB). Since the FAA issued AD 2016-12-51, the design
approval holder has developed procedures that address failure of the
main rotor system. This proposed AD would require replacing certain
second stage planet gear assemblies, removing certain epicyclic
modules, installing a full flow magnetic plug (FFMP), revising the
existing rotorcraft flight manual (RFM) for your helicopter,
repetitively inspecting the MGB particle detectors, repetitively
inspecting the MGB oil filter and oil cooler, and corrective action if
necessary, as specified in a European Union Aviation Safety Agency
(EASA) AD, which is proposed for incorporation by reference (IBR). The
actions specified in the proposed AD would terminate the flight
prohibition. 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 July 16,
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: 202-493-2251.
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 IBR in this AD, contact the EASA,
Konrad-Adenauer-Ufer 3, 50668 Cologne, Germany; telephone +49 221 8999
000; email [email protected]; internet www.easa.europa.eu. You may
find this IBR 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 817-222-5110. It is also available in the AD
docket on the internet at https://www.regulations.gov by searching for
and locating Docket No. FAA-2021-0379.
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-
0379; 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: Mahmood Shah, Aviation Safety
Engineer, Fort Worth ACO Branch, FAA, 10101 Hillwood Pkwy., Fort Worth,
TX 76177; telephone 817-222-5538; 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-2021-0379; Project Identifier
MCAI-2021-00068-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
Mahmood Shah, Aviation Safety Engineer, Fort Worth ACO Branch, FAA,
10101 Hillwood Pkwy., Fort Worth, TX 76177; telephone 817-222-5538;
email [email protected]a.gov. 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 FAA issued AD 2016-12-51, Amendment 39-18578 (81 FR 43479, July
5, 2016) (AD 2016-12-51), which applies to all Airbus Helicopters Model
AS332L2 and EC225LP helicopters. AD 2016-12-51 prohibits all further
flight of Airbus Helicopters Model AS332L
[[Page 29213]]
and EC225LP helicopters. The FAA issued AD 2016-12-51 to address an
accident involving an EC225LP helicopter in which the main rotor hub
detached from the MGB. The Airbus Helicopters Model AS332L2 helicopter
has a similar design to the affected Model EC225LP helicopter,
therefore, this model may be subject to the unsafe condition revealed
on the Model EC225LP helicopter.
Actions Since AD 2016-12-51 Was Issued
Since the FAA issued AD 2016-12-51, the design approval holder has
developed procedures that address failure of the main rotor system.
These procedures terminate the flight prohibition required by AD 2016-
12-51. In addition, after AD 2016-12-51 was issued, the FAA issued an
Alternate Means of Compliance (AMOC) letter dated September 7, 2017,
which addressed the flight prohibition required by paragraph (e) of AD
2016-12-51. The AMOC letter lifted the flight prohibition and allowed
operation of the affected helicopter models provided the conditions
specified in the AMOC letter were followed, which include repetitive
inspections that have no terminating action. This proposed AD includes
terminating action for certain repetitive inspections.
The EASA, which is the Technical Agent for the Member States of the
European Union, has issued EASA AD 2017-0134R2, dated April 16, 2020
(EASA AD 2017-0134R2) (also referred to as the Mandatory Continuing
Airworthiness Information, or the MCAI), to correct an unsafe condition
for all Airbus Helicopters Model AS332L2 and EC225LP helicopters.
This proposed AD was prompted by an accident involving a Model
EC225LP helicopter in which the main rotor hub detached from the MGB.
The FAA is proposing this AD to address failure of the main rotor
system, which would result in loss of control of the helicopter. See
the MCAI for additional background information.
Related Service Information Under 1 CFR Part 51
EASA AD 2017-0134R2 references procedures for replacing certain
second stage planet gear assemblies with serviceable parts; removing
certain epicyclic modules from service; modifying the helicopter by
installing an FFMP; revising the RFM to prohibit MGB particle burning
in-flight; repetitively inspecting the FFMP and MGB particle detectors
for metal particles, analyzing any metal particles that are found, and
corrective action; and repetitively inspecting the MGB oil filter and
oil cooler for particles and corrective action. The corrective actions
include replacing an affected MGB with a serviceable MGB. EASA AD 2017-
0134R2 also provides terminating action for certain repetitive
inspections.
Airbus Helicopters has issued Emergency Alert Service Bulletin
EC225 05A049, Revision 6, dated July 25, 2017; and Emergency Alert
Service Bulletin AS 332 05.01.07, Revision 6, dated July 27, 2017. The
service information specifies procedures for, among other things,
replacing the MGB.
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
These products have been approved by the aviation authority of
another country, and are 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 after evaluating all the
relevant information and determining the unsafe condition described
previously is likely to exist or develop in other products of these
same type designs.
Proposed AD Requirements
This proposed AD would require accomplishing the actions specified
in EASA AD 2017-0134R2 described previously, as incorporated by
reference, except for any differences identified as exceptions in the
regulatory text of this AD and except as discussed under ``Differences
Between this Proposed AD and the MCAI.''
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 2017-
0134R2 will be incorporated by reference in the FAA final rule. This
proposed AD would, therefore, require compliance with EASA AD 2017-
0134R2 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 2017-0134R2 that is required for
compliance with EASA AD 2017-0134R2 will be available on the internet
at https://www.regulations.gov by searching for and locating Docket No.
FAA-2021-0379 after the FAA final rule is published.
Differences Between This Proposed AD and the MCAI
Although the service information referenced in EASA AD 2017-0134R2
specifies to return affected planetary gear assemblies to the
manufacturer for module overhaul, this proposed AD does not include
that requirement.
Although the service information referenced in EASA AD 2017-0134R2
specifies that retrofit of the planet gear of the MGB can only be done
by Airbus Helicopters or Airbus Helicopters approved repair centers,
this proposed AD does not include that requirement.
EASA AD 2017-0134R2 requires operators to ``inform all flight
crews'' of revisions to the RFM, and thereafter to ``operate the
helicopter accordingly.'' However, this AD would not specifically
require those actions.
FAA regulations require pilots to follow the procedures in the
existing RFM including all updates. 14 CFR 91.9 requires that no person
may operate a civil aircraft without complying with the operating
limitations specified in the RFM. Therefore, including a requirement in
this AD to operate the airplane according to the revised RFM would be
redundant and unnecessary. Further, compliance with such a requirement
in an AD would be impracticable to demonstrate or track on an ongoing
basis; therefore, a requirement to operate the airplane in such a
manner would be unenforceable.
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 28 helicopters of
U.S. registry. The FAA estimates the
[[Page 29214]]
following costs to comply with this proposed AD:
Estimated Costs for Required Actions *
----------------------------------------------------------------------------------------------------------------
Action Labor cost Parts cost Cost per product Cost on U.S. operators
----------------------------------------------------------------------------------------------------------------
New proposed actions.......... Up to 6 work- $0 Up to $510.......... Up to $14,280.
hours x $85 per
hour = $510.
----------------------------------------------------------------------------------------------------------------
* Table does not include estimated costs for reporting.
The FAA estimates that it would take about 1 work-hour per product
to comply with the proposed reporting requirement in this proposed AD.
The average labor rate is $85 per hour. Based on these figures, the FAA
estimates the cost of reporting the inspection results on U.S.
operators to be $2,380, or $85 per product.
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
------------------------------------------------------------------------
40 work-hours x $85 per hour = $3,400. $295,000 $298,400
------------------------------------------------------------------------
According to the manufacturer, some or all of the costs of this
proposed AD may be covered under warranty, thereby reducing the cost
impact on affected operators. The FAA does not control warranty
coverage for affected operators. As a result, the FAA has included all
known costs in the cost estimate.
Paperwork Reduction Act
A federal agency may not conduct or sponsor, and a person is not
required to respond to, nor shall a person be subject to penalty for
failure to comply with a collection of information subject to the
requirements of the Paperwork Reduction Act unless that collection of
information displays a current valid OMB control number. The control
number for the collection of information required by this proposed AD
is 2120-0056. The paperwork cost associated with this proposed AD has
been detailed in the Costs of Compliance section of this document and
includes time for reviewing instructions, as well as completing and
reviewing the collection of information. Therefore, all reporting
associated with this proposed AD is mandatory. Comments concerning the
accuracy of this burden and suggestions for reducing the burden should
be directed to Information Collection Clearance Officer, Federal
Aviation Administration, 10101 Hillwood Parkway, Fort Worth, TX 76177-
1524.
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 2016-12-51, Amendment 39-18578 (81
FR 43479, July 5, 2016); and
0
b. Adding the following new airworthiness directive:
Airbus Helicopters: Docket No. FAA-2021-0379; Project Identifier
MCAI-2021-00068-R.
(a) Comments Due Date
The FAA must receive comments on this airworthiness directive
(AD) by July 16, 2021.
(b) Affected ADs
This AD replaces AD 2016-12-51, Amendment 39-18578 (81 FR 43479,
July 5, 2016 (AD 2016-12-51)).
(c) Applicability
This AD applies to all Airbus Helicopters Model AS332L2 and
EC225LP helicopters, certificated in any category.
[[Page 29215]]
(d) Subject
Joint Aircraft System Component (JASC) Code 6320, Main Rotor
Gearbox.
(e) Reason
This AD was prompted by an accident involving a Model EC225LP
helicopter in which the main rotor hub detached from the main
gearbox. The FAA is issuing this AD to address failure of the main
rotor system, which would result in 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
2017-0134R2, dated April 16, 2020 (EASA AD 2017-0134R2).
(h) Exceptions to EASA AD 2017-0134R2
(1) Where EASA AD 2017-0134R2 refers to the effective dates
specified in paragraphs (h)(1)(i) through (v) of this AD, this AD
requires using the effective date of this AD.
(i) The effective date of EASA AD 2017-0134R2.
(ii) October 13, 2016 (the effective date of EASA AD 2016-0199,
dated October 7, 2016).
(iii) March 20, 2017 (the effective date of EASA AD 2017-0050-E,
dated March 17, 2017).
(iv) June 30, 2017 (the effective date of EASA AD 2017-0111,
dated June 23, 2017).
(v) August 1, 2017 (the effective date of EASA AD 2017-0134,
dated July 27, 2017).
(2) The ``Remarks'' section of EASA AD 2017-0134R2 does not
apply to this AD.
(3) Where any service information referred to in EASA AD 2017-
0134R2 specifies to discard certain parts after they have been
removed from the helicopter, this AD requires removing those parts
from service.
(4) Where paragraph (2) of EASA AD 2017-0134R2 specifies to
replace a part before exceeding the applicable ``new service life
limit,'' this AD requires removing that part from service.
(5) Where any service information referred to in EASA AD 2017-
0134R2 specifies to return certain parts to the manufacturer,
including for overhaul, after they have been removed from the
helicopter, this AD does not include that requirement.
(6) Where EASA AD 2017-0134R2 refers to flight hours (FH), this
AD requires using hours time-in-service.
(7) Where any service information referred to in EASA AD 2017-
0134R2 specifies to perform a metallurgical analysis and contact the
manufacturer if unsure about the characterization of the particles
collected, this AD does require characterization of the particles
collected, however this AD does not require contacting the
manufacturer to determine the characterization of the particles
collected.
(8) Where EASA AD 2017-0134R2 requires actions during each
``after last flight'' of the day (ALF) inspection, this AD requires
those actions before the first flight of each day.
(9) Where any service information referred to in EASA AD 2017-
0134R2 specifies to do the actions identified in paragraphs
(h)(9)(i) through (iv) of this AD, this AD does not include those
requirements.
(i) Watch a video for removing the grease from the full flow
magnetic plug (FFMP), using a cleaning agent, and collecting
particles.
(ii) Return affected planetary gear assembly to the manufacturer
for module overhaul.
(iii) Contact the approved repair station/Airbus Helicopters if
the reason for a repair to an epicyclic module is unknown and
inform/contact Airbus Helicopters.
(iv) Contact the approved repair station/Airbus Helicopters
depending on who performed the last overhaul (RG) to determine if a
repair has been done on the second stage planet gears since new.
(10) Where any service information referred to in EASA AD 2017-
0134R2 specifies that retrofit of the planet gear of the main
gearbox (MGB) can only be done by Airbus Helicopters or Airbus
Helicopters approved repair centers, this AD does not require that
the retrofit of the planet gear be done only by Airbus Helicopters
or Airbus Helicopters approved repair centers. For this AD the
retrofit can also be done by an FAA-approved repair station.
(11) Where paragraph (5) of EASA AD 2017-0134R2 specifies
accomplishing the FFMP additional work within 3 months after August
1, 2017, this AD requires accomplishing the FFMP additional work
within 4 months after the effective date of this AD.
(12) Where paragraph (6) of EASA AD 2017-0134R2 specifies to
``inform all flight crews and, thereafter, operate the helicopter
accordingly,'' this AD does not require those actions.
(13) Where any service information referred to in EASA AD 2017-
0134R2 specifies that if any 16NCD13 particles are found you are to
take a 1-liter sample of oil and send it to the manufacturer, this
AD does not require those actions.
(14) Where any service information referred to in EASA AD 2017-
0134R2 specifies ``Do not resume flights until corrective action(s)
are agreed by Airbus Helicopters,'' or to contact Airbus Helicopters
before resuming flights ``if further particles are collected during
the close monitoring period,'' for this AD, you must repair before
further flight using a method specified in paragraph (h)(14)(i) or
(ii) of this AD.
(i) In accordance with FAA approved procedures.
(ii) In accordance with the procedures specified in Appendix
4.A., Particle Analysis, of Airbus Helicopters Emergency Alert
Service Bulletin EC225 05A049, Revision 6, dated July 25, 2017; or
Emergency Alert Service Bulletin AS 332 05.01.07, Revision 6, dated
July 27, 2017, as applicable, except as required by paragraphs
(h)(5), (7), and (13) of this AD.
(15) Where the service information identified in EASA AD 2017-
0134R2 specifies to report inspection results to Airbus Helicopters,
for this AD, report the inspection results at the applicable time
specified in paragraph (h)(15)(i) or (ii) of this AD.
(i) If the inspection was done on or after the effective date of
this AD: Submit the report within 30 days after the date of the
inspection.
(ii) If the inspection was done before the effective date of
this AD: Submit the report within 30 days after the effective date
of this AD.
(i) Credit for Previous Actions
(1) This paragraph provides credit for the actions specified in
paragraph (4) of EASA AD 2017-0134R2, if those actions were
performed before the effective date of this AD using Airbus
Helicopters Emergency Alert Service Bulletin AS332 ASB 63.00.83 or
EC225 ASB 63A030, both Revision 1, both dated October 7, 2016.
(2) Corrective action(s) for the inspections required by
paragraphs (8) and (10) of EASA AD 2017-0134R2 accomplished on a
helicopter before the effective date of this AD, in accordance with
Paragraph 3.B. and Appendix 4.A. of the Accomplishment Instructions
of the applicable Airbus Helicopters service information specified
in paragraphs (i)(2)(i) through (viii) of this AD, as applicable,
are acceptable to comply with the requirements of paragraph (11) of
EASA AD 2017-0134R2 for that helicopter, but only for the corrective
actions for the inspections required by paragraphs (8) and (10) of
EASA AD 2017-0134R2.
(i) Emergency Alert Service Bulletin AS332 ASB 05.01.07,
Revision 2, dated October 7, 2016.
(ii) Emergency Alert Service Bulletin AS332 ASB 05.01.07,
Revision 3, dated February 25, 2017.
(iii) Emergency Alert Service Bulletin AS332 ASB 05.01.07,
Revision 4, dated March 17, 2017.
(iv) Emergency Alert Service Bulletin AS332 ASB 05.01.07,
Revision 5, dated June 23, 2017.
(v) Emergency Alert Service Bulletin EC225 05A049, Revision 2,
dated October 7, 2016.
(vi) Emergency Alert Service Bulletin EC225 05A049, Revision 3,
dated February 25, 2017.
(vii) Emergency Alert Service Bulletin EC225 05A049, Revision 4,
dated March 17, 2017.
(viii) Emergency Alert Service Bulletin EC225 05A049, Revision
5, dated June 23, 2017.
(j) Special Flight Permit
Special flight permits, as described in 14 CFR 21.197 and
21.199, are prohibited.
(k) Alternative Methods of Compliance (AMOCs)
(1) 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 manager of the International Validation
[[Page 29216]]
Branch, send it to the attention of the person identified in
paragraph (l)(2) of this AD. Information may be emailed to: [email protected].
(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.
(l) Related Information
(1) For EASA AD 2017-1034R2, contact the EASA, Konrad-Adenauer-
Ufer 3, 50668 Cologne, Germany; telephone +49 221 8999 000; email
[email protected]; 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 817-222-5110. 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-2021-0379.
(2) For more information about this AD, contact Mahmood Shah,
Aviation Safety Engineer, Fort Worth ACO Branch, FAA, 10101 Hillwood
Pkwy., Fort Worth, TX 76177; telephone 817-222-5538; email
[email protected].
Issued on May 21, 2021.
Gaetano A. Sciortino,
Deputy Director for Strategic Initiatives, Compliance & Airworthiness
Division, Aircraft Certification Service.
[FR Doc. 2021-11376 Filed 5-28-21; 8:45 am]
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