[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.
 
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 

  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 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 
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

[[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: 9-AVS-AIR-730-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


