[Federal Register Volume 86, Number 202 (Friday, October 22, 2021)]
[Proposed Rules]
[Pages 58600-58604]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2021-22462]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2021-0873; Project Identifier MCAI-2021-00336-R]
RIN 2120-AA64


Airworthiness Directives; Airbus Helicopters

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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SUMMARY: The FAA proposes to supersede Airworthiness Directive (AD) 
2018-11-01, which applies to certain Airbus Helicopters Model AS332L2 
and EC225LP helicopters. AD 2018-11-01 requires installing a cut-out 
for the left-hand (LH) and right-hand (RH) rail support junction 
profiles and repetitively inspecting splices, frame 5295, and related 
equipment for a crack. Since the FAA issued AD 2018-11-01, the 
manufacturer has developed a modification for in-service helicopters 
for replacing aluminum splices with steel splices on frame 5295. This 
proposed AD would retain the requirements of AD 2018-11-01 and require 
a modification for replacing aluminum splices with steel splices on 
frame 5295 if cracking is found. This proposed AD would also provide 
terminating action for the repetitive inspections. The FAA is proposing 
this AD to address the unsafe condition on these products.

DATES: The FAA must receive comments on this proposed AD by December 6, 
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 service information identified in this NPRM, contact Airbus 
Helicopters, 2701 North Forum Drive, Grand Prairie, TX 75052; telephone 
(972) 641-0000 or (800) 232-0323; fax (972) 641-3775; or at https://www.airbus.com/helicopters/services/technical-support.html. You may 
view this service information 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.

Examining the AD Docket

    You may examine the AD docket at https://www.regulations.gov by 
searching for and locating Docket No. FAA-2021-0873; or in person at 
Docket Operations between 9 a.m. and 5 p.m., Monday through Friday, 
except Federal holidays. The AD docket contains this NPRM, the European 
Union Aviation Safety Agency (EASA) AD, any comments received, and 
other information. The street address for Docket Operations is listed 
above.

FOR FURTHER INFORMATION CONTACT: Andrea Jimenez, Aerospace Engineer, 
COS Program Management Section, Operational Safety Branch, Compliance & 
Airworthiness Division, FAA, 1600 Stewart Ave., Suite 410, Westbury, NY 
11590; telephone (516) 228-7330; 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-2021-0873; Project Identifier 
MCAI-2021-00336-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 NPRM.

Confidential Business Information

    CBI is commercial or financial information that is both customarily 
and actually treated as private by its owner. Under the Freedom of 
Information Act (FOIA) (5 U.S.C. 552), CBI is exempt from public 
disclosure. If your comments responsive to this NPRM contain commercial 
or financial

[[Page 58601]]

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., Suite 410, 
Westbury, NY 11590; telephone (516) 228-7330; email 
[email protected]. Any commentary that the FAA receives which is 
not specifically designated as CBI will be placed in the public docket 
for this rulemaking.

Background

    The FAA issued AD 2018-11-01, Amendment 39-19289 (83 FR 23778, May 
23, 2018), (AD 2018-11-01), for Airbus Helicopters Model AS332L2 and 
EC225LP helicopters with an extended aluminum splice installed on frame 
5295, except helicopters with steel splice kit part number 332A08-2649-
3072 installed. AD 2018-11-01 requires installing a cut-out for the LH 
and RH rail support junction profiles and repetitively inspecting 
splices, frame 5295, and related equipment for a crack. AD 2018-11-01 
was prompted by reports of cracks on frame 5295 and on splices 
installed to prevent those cracks. The FAA issued AD 2018-11-01 to 
address a crack in frame 5295, which if not detected and corrected, 
could lead to loss of structural integrity of the helicopter frame and 
subsequent loss of control of the helicopter.

Actions Since AD 2018-11-01 Was Issued

    Since the FAA issued AD 2018-11-01, EASA issued AD 2021-0075, dated 
March 16, 2021 (EASA AD 2021-0075), which supersedes EASA Emergency AD 
2014-0098-E, dated April 25, 2014 (EASA Emergency AD 2014-0098-E). EASA 
advises that since EASA Emergency AD 2014-0098-E was issued, Airbus 
Helicopters developed MOD 0728463, available for helicopters in service 
through the applicable modification service bulletin, providing 
instructions to replace aluminum splices with steel splices on frame 
5295. Airbus Helicopters also issued the applicable inspection alert 
service bulletins, as defined in EASA AD 2021-0075. Accordingly, EASA 
AD 2021-0075 retains the requirements of EASA Emergency AD 2014-0098-E, 
which is superseded, and requires a modification, replacing aluminum 
splices with steel splices on helicopters on which any cracked aluminum 
splice has been detected. EASA AD 2021-0075 also advises that the 
modification is terminating action for the repetitive inspections.

FAA's Determination

    These helicopters have been approved by EASA and are approved for 
operation in the United States. Pursuant to the FAA's bilateral 
agreement with the European Union, EASA has notified the FAA about the 
unsafe condition described in its AD. The FAA is proposing this AD 
after evaluating all known relevant information and determining that 
the unsafe condition described previously is likely to exist or develop 
on other helicopters of the same type designs.

Related Service Information Under 1 CFR Part 51

    The FAA reviewed the following Airbus Helicopters service 
information.
     Alert Service Bulletins Nos. AS332-05.00.97, Revision 1; 
and EC225-05A038, Revision 1; both dated February 9, 2021; which 
specify procedures for, among other actions, installing a cut-out for 
the LH and RH rail support junction profiles and inspecting splices, 
frame 5295, and related equipment for a crack. These documents are 
distinct since they apply to different helicopter models.
     Service Bulletins Nos. AS332-53.01.97, Revision 0; and 
EC225-53-061, Revision 0; both dated February 9, 2021; which specify 
procedures for modifying the helicopter by replacing the aluminum LH 
and RH splices with steel splices under the plates and the brackets of 
the main gear box (MGB) bars. The modification includes taking 
reference readings of the brackets of the MGB bars, removing the MGB 
brackets and plates, removing the aluminum splices and inspecting the 
joggling areas for scratches or other damage, inspecting frame 5295 for 
cracking (including a dye penetrant inspection if the inspection 
results are not conclusive), identifying the current measurements 
(values) of the rivet and attachment plate holes for installation of 
the steel splice (including determining the values of the rivet holes 
and attachment plate holes on frame 5295 with a calibrated pad and 
determining the elongations of the holes and the lengths of the 
straps), modifying the door hinge rail brackets on the LH and RH sides, 
and installing the steel splices. These documents are distinct since 
they apply to different helicopter models.
    This service information is reasonably available because the 
interested parties have access to it through their normal course of 
business or by the means identified in the ADDRESSES section.

Other Related Service Information

    The FAA reviewed Eurocopter Helicopters (now Airbus Helicopters) 
Service Bulletin No. 53-003, Revision 4, for Model EC225LP helicopters 
and Service Bulletin No. 53.01.52, Revision 5, for Model AS332L2 
helicopters, both dated July 23, 2010. The service bulletins specify 
procedures to reinforce frame 5295 by installing a new titanium plate 
underneath the fitting and a new widened aluminum splice below the 
upper corner of the door.
    The FAA also reviewed Airbus Helicopters Service Bulletin No. 05-
019, Revision 4, dated September 22, 2014, for Model EC225 LP 
helicopters. This service information specifies procedures for cutting 
out the junction profiles.
    The FAA also reviewed Airbus Helicopters Alert Service Bulletins 
Nos. AS332-05.00.97, Revision 0; and EC225-05A038, Revision 0; both 
dated April 15, 2014; which specify procedures for, among other 
actions, installing a cut-out for the LH and RH rail support junction 
profiles and inspecting splices, frame 5295, and related equipment for 
a crack.

Proposed AD Requirements in This NPRM

    This proposed AD would retain all requirements of AD 2018-11-01 and 
require a modification for replacing aluminum splices with steel 
splices on frame 5295. This proposed AD would also provide terminating 
action for the repetitive inspections required by AD 2018-11-01. This 
proposed AD would also require accomplishing the actions specified in 
the service information already described, except as discussed under 
``Differences Between this AD and the EASA AD.''

Redesignation of AD 2018-11-01 Paragraph Identifier

    Since AD 2018-11-01 was issued, the AD format has been revised, and 
certain paragraphs have been rearranged. As a result, the corresponding 
paragraph

[[Page 58602]]

identifiers have been redesignated in this proposed AD, as listed in 
the following table:

                      Revised Paragraph Identifier
------------------------------------------------------------------------
                                            Corresponding requirement in
       Requirement in AD 2018-11-01               this proposed AD
------------------------------------------------------------------------
paragraph (e).............................  paragraph (g).
paragraph (f).............................  paragraph (j)(1).
------------------------------------------------------------------------

Differences Between This Proposed AD and the EASA AD 2021-0075

    EASA AD 2021-0075 requires contacting Airbus Helicopters for 
approved repair instructions if any crack is found during an 
inspection. This proposed AD would not require that action.

Costs of Compliance

    The FAA estimates that this AD, if adopted as proposed, would 
affect 38 helicopters of U.S. registry. The FAA estimates the 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
----------------------------------------------------------------------------------------------------------------
Retained installation of cut-  40 work-hours x        $5,000  $8,400..................  $319,200.
 outs on frame 5295 from AD     $85 per hour =
 2018-11-01.                    $3,400.
Retained inspection of frame   2 work-hours x              0  $170, per inspection      $6,460, per inspection
 5295 from AD 2018-11-01.       $85 per hour =                 cycle.                    cycle.
                                $170, per
                                inspection
                                cycle.
----------------------------------------------------------------------------------------------------------------

    The FAA estimates the following costs to do any necessary repairs 
that would be required based on the results of the proposed inspection. 
The agency has no way of determining the number of aircraft that might 
need these repairs:

                                     Estimated Costs of On-Condition Actions
----------------------------------------------------------------------------------------------------------------
                                                                                                     Cost per
                    Action                                 Labor cost               Parts cost        product
----------------------------------------------------------------------------------------------------------------
Repair........................................  40 work-hours x $85 per hour =            $5,000          $8,400
                                                 $3,400.
New proposed modification (replacement of       830 work-hours x $85 per hour =           35,000         105,550
 aluminum splices with steel splices).           $70,550.
----------------------------------------------------------------------------------------------------------------

Authority for This Rulemaking

    Title 49 of the United States Code specifies the FAA's authority to 
issue rules on aviation safety. Subtitle I, section 106, describes the 
authority of the FAA Administrator. Subtitle VII: Aviation Programs, 
describes in more detail the scope of the Agency's authority.
    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, 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 2018-11-01, Amendment 39-19289 (83 
FR 23778, May 23, 2018); and
0
b. Adding the following new airworthiness directive:

Airbus Helicopters: Docket No. FAA-2021-0873; Project Identifier 
MCAI-2021-00336-R.

(a) Comments Due Date

    The FAA must receive comments on this airworthiness directive 
(AD) action by December 6, 2021.

(b) Affected ADs

    This AD replaces AD 2018-11-01, Amendment 39-19289 (83 FR 23778, 
May 23, 2018) (AD 2018-11-01).

(c) Applicability

    This AD applies to Airbus Helicopters Model AS332L2 and Model 
EC225LP helicopters, certificated in any category, as specified in 
paragraphs (c)(1) and (2) of this AD.
    (1) Model AS332L2 helicopters equipped with extended aluminum 
splices on frame 5295 installed in accordance with Airbus 
Helicopters (AH) Modification (MOD) 0726517, Eurocopter (EC) AS332 
Service Bulletin (SB) 53.01.52, or AH repair design 332-53-507-06, 
332-53-21-07, or 332-53-82-06; except helicopters embodying AH MOD 
0728463, AH SB AS 332-53.01.97, or

[[Page 58603]]

repair design 332-53-409-12, 332-53-1284-13, 332-53-1079-16, or 332-
53-1358-16.
    Note 1 to paragraph (c)(1): As referenced in paragraphs (c)(1) 
and (2) of this AD, helicopters with AH MOD 0728463 installed have 
replaced the aluminum splices with steel splices.
    (2) Model EC225LP helicopters equipped with extended aluminum 
splices on frame 5295 installed in accordance with AH MOD 0726517, 
or EC EC225 SB 53-003 (pre AH MOD 0726493 and post AH MOD 0726517), 
except helicopters embodying AH MOD 0728463, or SB EC225-53-061.
    Note 2 to paragraph (c)(2): Helicopters with AH MOD 0726493 have 
installed steel splice kit part number 332A08-2649-3072.

(d) Subject

    Joint Aircraft Service Component (JASC) Code: 5300, Fuselage 
Structure.

(e) Unsafe Condition

    This AD was prompted by reports of cracks on frame 5295 and on 
aluminum splices installed to prevent those cracks. The FAA is 
issuing this AD to address cracking on frame 5295 and on the inner 
skins. The unsafe condition, if not addressed, could result in loss 
of structural integrity of the helicopter frame and subsequent loss 
of control of the helicopter.

(f) Compliance

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

(g) Retained Installation and Inspections With New Service Information 
and Corrective Actions (Modification)

    This paragraph retains the requirements of paragraph (e) of AD 
2018-11-01, with new service information and corrective actions 
(modification).
    (1) Before a splice reaches 1,700 hours time-in-service (TIS), 
within 50 hours TIS, or before the helicopter reaches 11,950 hours 
TIS, whichever occurs latest, do the following.
    (i) Install the rail support cut-out and identify the left-hand 
(LH) and right-hand (RH) junction profile, in accordance with the 
Accomplishment Instructions, paragraph 3.B.2., of Airbus Helicopters 
Alert Service Bulletin (ASB) No. EC225-05A038, Revision 1, dated 
February 9, 2021 (Airbus Helicopters ASB No. EC225-05A038, Revision 
1); or Airbus Helicopters ASB No. AS332-05.00.97, Revision 1, dated 
February 9, 2021 (Airbus Helicopters ASB No. AS332-05.00.97, 
Revision 1); whichever is applicable to your helicopter.
    (ii) Inspect each splice for a crack in the area depicted as 
Area Y in Figure 3 of Airbus Helicopters ASB No. EC225-05A038, 
Revision 1; or Airbus Helicopters ASB No. AS332-05.00.97, Revision 
1; whichever is applicable to your helicopter. If a crack exists, do 
the applicable action required by paragraph (g)(1)(ii)(A) or (B) of 
this AD.
    (A) For any cracking found before the effective date of this AD: 
Repair or replace the splice before further flight.
    (B) For any cracking found on or after the effective date of 
this AD: Before further flight, modify the helicopter in accordance 
with paragraph 3.B.2. of the Accomplishment Instructions of Airbus 
Helicopters Service Bulletin (SB) No. AS332-53.01.97, Revision 0, 
dated February 9, 2021 (Airbus Helicopters SB No. AS332-53.01.97, 
Revision 0); or Service Bulletin No. EC225-53-061, Revision 0, dated 
February 9, 2021 (Airbus Helicopters SB No. EC225-53-061, Revision 
0); as applicable to your helicopter; except as specified in 
paragraph (h) of this AD.
    (2) Thereafter at intervals not to exceed 110 hours TIS, inspect 
each splice for a crack in the area depicted as Area Y in Figure 3 
of Airbus Helicopters ASB No. EC225-05A038, Revision 1; or Airbus 
Helicopters ASB No. AS332-05.00.97, Revision 1; whichever is 
applicable to your helicopter. If a crack exists, do the applicable 
actions required by paragraph (g)(2)(i) or (ii) of this AD. 
Accomplishing the modification specified in paragraph (g)(1)(ii)(B) 
and (g)(2)(ii) of this AD terminates the inspections required by 
this paragraph.
    (i) For any cracking found before the effective date of this AD: 
Repair or replace the splice before further flight.
    (ii) For any cracking found on or after the effective date of 
this AD: Before further flight, modify the helicopter in accordance 
with paragraph 3.B.2. of the Accomplishment Instructions of Airbus 
Helicopters SB No. AS332-53.01.97, Revision 0; or Airbus Helicopters 
SB No. EC 225-53-061, Revision 0; as applicable to your helicopter; 
except as specified in paragraph (h) of this AD.

(h) Service Information Exceptions

    (1) Where Airbus Helicopters ASB No. EC225-05A038, Revision 1; 
Airbus Helicopters ASB No. AS332-05.00.97, Revision 1; Airbus 
Helicopters SB No. AS332-53.01.97, Revision 0; and Airbus 
Helicopters SB No. EC 225-53-061, Revision 0; specify to perform 
dye-penetrant inspections ``if in doubt'' or ``if any doubt,'' this 
AD requires performing a dye-penetrant inspection during inspections 
done on or after the effective date of this AD.
    (2) Where Airbus Helicopters SB No. AS332-53.01.97, Revision 0; 
and Airbus Helicopters SB No. EC 225-53-061, Revision 0; specify 
discarding parts, this AD requires removing those parts from 
service.
    (3) Where Airbus Helicopters SB No. AS332-53.01.97, Revision 0; 
and Airbus Helicopters SB No. EC 225-53-061, Revision 0, specify 
contacting Airbus Helicopter for corrective action or further 
procedures, this AD requires repair done in accordance with a method 
approved by the Manager, General Aviation & Rotorcraft Section, 
International Validation Branch, FAA; or EASA; or Airbus 
Helicopters' EASA Design Organization Approval (DOA). If approved by 
the DOA, the approval must include the DOA-authorized signature.
    (4) Airbus Helicopters SB No. AS332-53.01.97, Revision 0; and 
Airbus Helicopters SB No. EC 225-53-061, Revision 0, specify a 
visual check and dye penetrant inspection for cracks on the inside 
and outside of frame 5295. For this AD, if any cracking is found 
during any visual check or dye penetrant inspection on the inside 
and outside of frame 5295, before further flight, repair in 
accordance with a method approved by the Manager, General Aviation & 
Rotorcraft Section, International Validation Branch, FAA; or EASA; 
or Airbus Helicopters' EASA Design Organization Approval (DOA). If 
approved by the DOA, the approval must include the DOA-authorized 
signature.

(i) Reporting Not Required

    Although Airbus Helicopters SB No. AS332-53.01.97, Revision 0; 
and Airbus Helicopters SB No. EC 225-53-061, Revision 0; specify to 
submit certain information to the manufacturer, this AD does not 
include that requirement.

(j) Credit for Previous Actions

    (1) This paragraph provides credit for the installation of the 
rail support cut-out required by paragraph (g)(1)(i) of this AD, if 
that action was performed before June 27, 2018 (the effective date 
of AD 2018-11-01) using Airbus Helicopters MOD 0728090 or Airbus 
Helicopters SB No. 05-019, Revision 4, dated September 22, 2014.
    (2) This paragraph provides credit for the actions required by 
paragraphs (g)(1) and (2) of this AD, if the actions were performed 
before the effective date of this AD using Airbus Helicopters ASB 
No. EC225-05A038, Revision 0, dated April 15, 2014; or Airbus 
Helicopters ASB No. AS332-05.00.97, Revision 0, dated April 15, 
2014.

(k) Special Flight Permits

    Special flight permits may be issued in accordance with 14 CFR 
21.197 and 21.199 to operate the helicopter to a location where the 
actions can be performed, provided no passengers are onboard.

(l) 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 Branch, send 
it to the attention of the person identified in paragraph (m)(1) 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.

(m) Related Information

    (1) For more information about this AD, contact Andrea Jimenez, 
Aerospace Engineer, COS Program Management Section, Operational 
Safety Branch, Compliance & Airworthiness Division, FAA, 1600 
Stewart Ave., Suite 410, Westbury, NY 11590; telephone (516) 228-
7330; email [email protected].
    (2) For service information identified in this AD, contact 
Airbus Helicopters, 2701 North Forum Drive, Grand Prairie, TX 75052; 
telephone (972) 641-0000 or (800) 232-0323; fax (972) 641-3775; or 
at https://www.airbus.com/helicopters/services/technical-support.html. You may view this

[[Page 58604]]

referenced service information 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.
    (3) The subject of this AD is addressed in European Union 
Aviation Safety Agency (EASA) AD 2021-0075, dated March 16, 2021. 
You may view the EASA AD on the internet at https://www.regulations.gov in Docket No. FAA-2021-0873.

    Issued on October 4, 2021.
Lance T. Gant,
Director, Compliance & Airworthiness Division, Aircraft Certification 
Service.
[FR Doc. 2021-22462 Filed 10-21-21; 8:45 am]
BILLING CODE 4910-13-P


