Airworthiness Directives; Airbus Helicopters, 382-385 [2021-28469]
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382
Federal Register / Vol. 87, No. 3 / Wednesday, January 5, 2022 / Rules and Regulations
DEPARTMENT OF TRANSPORTATION
Examining the AD Docket
Federal Aviation Administration
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
final rule, the European Union Aviation
Safety Agency (EASA) AD, any
comments received, and other
information. The address for Docket
Operations is U.S. Department of
Transportation, Docket Operations, M–
30, West Building Ground Floor, Room
W12–140, 1200 New Jersey Avenue SE,
Washington, DC 20590.
FOR FURTHER INFORMATION CONTACT:
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
andrea.jimenez@faa.gov.
SUPPLEMENTARY INFORMATION:
14 CFR Part 39
[Docket No. FAA–2021–0873; Project
Identifier MCAI–2021–00336–R; Amendment
39–21873; AD 2021–26–14]
RIN 2120–AA64
Airworthiness Directives; Airbus
Helicopters
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule.
AGENCY:
The FAA is superseding
Airworthiness Directive (AD) 2018–11–
01, which applied to certain Airbus
Helicopters Model AS332L2 and
EC225LP helicopters. AD 2018–11–01
required installing a cut-out for the lefthand (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 AD
retains the requirements of AD 2018–
11–01 and requires a modification for
replacing aluminum splices with steel
splices on frame 5295 if cracking is
found. This AD also provides
terminating action for the repetitive
inspections. The FAA is issuing this AD
to address the unsafe condition on these
products.
DATES: This AD is effective February 9,
2022.
The Director of the Federal Register
approved the incorporation by reference
of certain publications listed in this AD
as of February 9, 2022.
ADDRESSES: For service information
identified in this final rule, 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. Service information
that is incorporated by reference is also
available at https://www.regulations.gov
by searching for and locating Docket No.
FAA–2021–0873.
TKELLEY on DSK125TN23PROD with RULES1
SUMMARY:
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Background
The FAA issued a notice of proposed
rulemaking (NPRM) to amend 14 CFR
part 39 to supersede AD 2018–11–01,
Amendment 39–19289 (83 FR 23778,
May 23, 2018), (AD 2018–11–01). AD
2018–11–01 applied to 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 required
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.
The NPRM published in the Federal
Register on October 22, 2021 (86 FR
58600). In the NPRM, the FAA proposed
to 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. The NPRM was prompted by
EASA 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), issued by
EASA, which is the Technical Agent for
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the Member States of the European
Union.
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.
Discussion of Final Airworthiness
Directive
Comments
The FAA received no comments on
the NPRM or on the determination of
the costs.
Conclusion
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 reviewed
the relevant data and determined that
air safety requires adopting this AD as
proposed. Accordingly, the FAA is
issuing this AD to address the unsafe
condition on these helicopters. Except
for minor editorial changes, this AD is
adopted as proposed in the NPRM.
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
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Federal Register / Vol. 87, No. 3 / Wednesday, January 5, 2022 / Rules and Regulations
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.
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
identifiers have been redesignated in
this AD, as listed in the following table:
REVISED PARAGRAPH IDENTIFIER
Corresponding
requirement in this
AD
Requirement in AD
2018–11–01
paragraph (e) ............
paragraph (f) .............
paragraph (g)
paragraph (j)(1)
Differences Between This 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 AD would not require that action.
Costs of Compliance
The FAA estimates that this AD
would affect 38 helicopters of U.S.
registry. The FAA estimates the
following costs to comply with this AD:
ESTIMATED COSTS FOR REQUIRED ACTIONS
Cost per
product
Labor cost
Retained installation of cut-outs on frame
5295 from AD 2018–11–01.
Retained inspection of frame 5295 from AD
2018–11–01.
40 work-hours × $85 per hour = $3,400 ........
$5,000
$8,400
$319,200
2 work-hours × $85 per hour = $170, per inspection cycle.
0
170, per
inspection
cycle
6,460, per
inspection
cycle.
The FAA estimates the following
costs to do any necessary repairs that
Parts cost
Cost on U.S.
operators
Action
would be required based on the results
of the inspection. The agency has no
way of determining the number of
aircraft that might need these repairs:
ESTIMATED COSTS OF ON-CONDITION ACTIONS
Action
Labor cost
Repair ...........................................................................
New modification (replacement of aluminum splices
with steel splices).
40 work-hours × $85 per hour = $3,400 ......................
830 work-hours × $85 per hour = $70,550 ..................
TKELLEY on DSK125TN23PROD with RULES1
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
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16:55 Jan 04, 2022
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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.
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Parts cost
$5,000
35,000
Cost per
product
$8,400
105,550
Regulatory Findings
This AD will not have federalism
implications under Executive Order
13132. This AD will not have a
substantial direct effect on the States, on
the relationship between the national
government and the States, or on the
distribution of power and
responsibilities among the various
levels of government.
For the reasons discussed above, I
certify that this AD:
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Federal Register / Vol. 87, No. 3 / Wednesday, January 5, 2022 / Rules and Regulations
(1) Is not a ‘‘significant regulatory
action’’ under Executive Order 12866,
(2) Will not affect intrastate aviation
in Alaska, and
(3) Will not have a significant
economic impact, positive or negative,
on a substantial number of small entities
under the criteria of the Regulatory
Flexibility Act.
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.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation
safety, Incorporation by reference,
Safety.
Joint Aircraft Service Component (JASC)
Code: 5300, Fuselage Structure.
The Amendment
Accordingly, under the authority
delegated to me by the Administrator,
the FAA amends 14 CFR part 39 as
follows:
PART 39—AIRWORTHINESS
DIRECTIVES
Authority: 49 U.S.C. 106(g), 40113, 44701.
[Amended]
2. The FAA amends § 39.13 by:
a. Removing Airworthiness Directive
2018–11–01, Amendment 39–19289 (83
FR 23778, May 23, 2018); and
■ b. Adding the following new
airworthiness directive:
■
■
2021–26–14 Airbus Helicopters:
Amendment 39–21873; Docket No.
FAA–2021–0873; Project Identifier
MCAI–2021–00336–R.
(a) Effective Date
This airworthiness directive (AD) is
effective February 9, 2022.
TKELLEY on DSK125TN23PROD with RULES1
(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
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
16:55 Jan 04, 2022
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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.
Comply with this AD within the
compliance times specified, unless already
done.
1. The authority citation for part 39
continues to read as follows:
VerDate Sep<11>2014
(e) Unsafe Condition
(f) Compliance
■
§ 39.13
(d) Subject
(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
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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 DOAauthorized 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
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
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Federal Register / Vol. 87, No. 3 / Wednesday, January 5, 2022 / Rules and Regulations
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.
TKELLEY on DSK125TN23PROD with RULES1
(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: 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.
(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
andrea.jimenez@faa.gov.
(2) Service information identified in this
AD that is not incorporated by reference is
available at the addresses specified in
paragraphs (n)(3) and (4) of this AD.
(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 at https://
www.regulations.gov in Docket No. FAA–
2021–0873.
(n) Material Incorporated by Reference
(1) The Director of the Federal Register
approved the incorporation by reference of
the service information listed in this
paragraph under 5 U.S.C. 552(a) and 1 CFR
part 51.
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16:55 Jan 04, 2022
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(2) You must use this service information
as applicable to do the actions required by
this AD, unless the AD specifies otherwise.
(i) Airbus Helicopters Alert Service
Bulletin No. AS332–05.00.97, Revision 1,
dated February 9, 2021.
(ii) Airbus Helicopters Alert Service
Bulletin No. EC225–05A038, Revision 1,
dated February 9, 2021.
(iii) Airbus Helicopters Service Bulletin
No. AS332–53.01.97, Revision 0, dated
February 9, 2021.
(iv) Airbus Helicopters Service Bulletin
No. EC225–53–061, Revision 0, dated
February 9, 2021.
(3) 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.
(4) 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.
(5) You may view this service information
that is incorporated by reference at the
National Archives and Records
Administration (NARA). For information on
the availability of this material at NARA,
email: fr.inspection@nara.gov, or go to:
https://www.archives.gov/federal-register/cfr/
ibr-locations.html.
Issued on December 10, 2021.
Lance T. Gant,
Director, Compliance & Airworthiness
Division, Aircraft Certification Service.
[FR Doc. 2021–28469 Filed 1–4–22; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2021–0839; Project
Identifier MCAI–2020–01697–R; Amendment
39–21877; AD 2021–26–18]
RIN 2120–AA64
Airworthiness Directives; Airbus
Helicopters
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule.
AGENCY:
The FAA is superseding
Airworthiness Directive (AD) 2020–21–
01 for certain Airbus Helicopters Model
AS–365N2, AS 365N3, EC 155B,
EC155B1, and SA–365N1 helicopters.
AD 2020–21–01 required modifying the
main gearbox (MGB) tail rotor (T/R)
drive flange installation. This AD was
prompted by several reported
occurrences of loss of tightening torque
of the Shur-Lok nut, which serves as a
SUMMARY:
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385
retainer of the MGB T/R drive flange.
This AD continues to require modifying
the MGB T/R drive flange installation,
and includes additional helicopters in
the applicability for the required
actions. The FAA is issuing this AD to
address the unsafe condition on these
products.
DATES: This AD is effective February 9,
2022.
The Director of the Federal Register
approved the incorporation by reference
of certain publications listed in this AD
as of February 9, 2022.
The Director of the Federal Register
approved the incorporation by reference
of certain other publications listed in
this AD as of November 12, 2020 (85 FR
63440, October 8, 2020).
ADDRESSES: For service information
identified in this final rule, contact
Airbus Helicopters, 2701 North Forum
Drive, Grand Prairie, TX 75052; phone:
(972) 641–0000 or (800) 232–0323; fax:
(972) 641–3775; or at https://
www.airbus.com/helicopters/services/
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. It is also
available at https://www.regulations.gov
by searching for and locating Docket No.
FAA–2021–0839.
Examining the AD Docket
You may examine the AD docket at
https://www.regulations.gov by
searching for and locating Docket No.
FAA–2021–0839; or in person at Docket
Operations between 9 a.m. and 5 p.m.,
Monday through Friday, except Federal
holidays. The AD docket contains this
final rule, the European Union Aviation
Safety Agency (EASA) AD, any
comments received, and other
information. The address for Docket
Operations is U.S. Department of
Transportation, Docket Operations, M–
30, West Building Ground Floor, Room
W12–140, 1200 New Jersey Avenue SE,
Washington, DC 20590.
FOR FURTHER INFORMATION CONTACT:
Andrea Jimenez, Aerospace Engineer,
COS Program Management Section,
Operational Safety Branch, Compliance
& Airworthiness Division, FAA, 1600
Stewart Ave., Suite 410, Westbury, NY
11590; phone: (516) 228–7330; email:
andrea.jimenez@faa.gov.
SUPPLEMENTARY INFORMATION:
Background
The FAA issued a notice of proposed
rulemaking (NPRM) to amend 14 CFR
part 39 to supersede AD 2020–21–01,
E:\FR\FM\05JAR1.SGM
05JAR1
]]>Agencies
[Federal Register Volume 87, Number 3 (Wednesday, January 5, 2022)]
[Rules and Regulations]
[Pages 382-385]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2021-28469]
[[Page 382]]
=======================================================================
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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;
Amendment 39-21873; AD 2021-26-14]
RIN 2120-AA64
Airworthiness Directives; Airbus Helicopters
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Final rule.
-----------------------------------------------------------------------
SUMMARY: The FAA is superseding Airworthiness Directive (AD) 2018-11-
01, which applied to certain Airbus Helicopters Model AS332L2 and
EC225LP helicopters. AD 2018-11-01 required 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 AD retains the
requirements of AD 2018-11-01 and requires a modification for replacing
aluminum splices with steel splices on frame 5295 if cracking is found.
This AD also provides terminating action for the repetitive
inspections. The FAA is issuing this AD to address the unsafe condition
on these products.
DATES: This AD is effective February 9, 2022.
The Director of the Federal Register approved the incorporation by
reference of certain publications listed in this AD as of February 9,
2022.
ADDRESSES: For service information identified in this final rule,
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. Service information that
is incorporated by reference is also available at https://www.regulations.gov by searching for and locating Docket No. FAA-2021-
0873.
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 final rule, the
European Union Aviation Safety Agency (EASA) AD, any comments received,
and other information. The address for Docket Operations is U.S.
Department of Transportation, Docket Operations, M-30, West Building
Ground Floor, Room W12-140, 1200 New Jersey Avenue SE, Washington, DC
20590.
FOR FURTHER INFORMATION CONTACT: 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:
Background
The FAA issued a notice of proposed rulemaking (NPRM) to amend 14
CFR part 39 to supersede AD 2018-11-01, Amendment 39-19289 (83 FR
23778, May 23, 2018), (AD 2018-11-01). AD 2018-11-01 applied to 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
required 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.
The NPRM published in the Federal Register on October 22, 2021 (86
FR 58600). In the NPRM, the FAA proposed to 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. The NPRM was
prompted by EASA 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), issued by EASA, which is the
Technical Agent for the Member States of the European Union.
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.
Discussion of Final Airworthiness Directive
Comments
The FAA received no comments on the NPRM or on the determination of
the costs.
Conclusion
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 reviewed the relevant
data and determined that air safety requires adopting this AD as
proposed. Accordingly, the FAA is issuing this AD to address the unsafe
condition on these helicopters. Except for minor editorial changes,
this AD is adopted as proposed in the NPRM.
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
[[Page 383]]
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.
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 identifiers have been redesignated in this AD, as listed in
the following table:
Revised Paragraph Identifier
------------------------------------------------------------------------
Corresponding requirement in
Requirement in AD 2018-11-01 this AD
------------------------------------------------------------------------
paragraph (e)............................. paragraph (g)
paragraph (f)............................. paragraph (j)(1)
------------------------------------------------------------------------
Differences Between This 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 AD would not require that action.
Costs of Compliance
The FAA estimates that this AD would affect 38 helicopters of U.S.
registry. The FAA estimates the following costs to comply with this AD:
Estimated Costs for Required Actions
----------------------------------------------------------------------------------------------------------------
Cost per Cost on U.S.
Action Labor cost Parts cost product operators
----------------------------------------------------------------------------------------------------------------
Retained installation of cut-outs on 40 work-hours x $85 per $5,000 $8,400 $319,200
frame 5295 from AD 2018-11-01. hour = $3,400.
Retained inspection of frame 5295 from 2 work-hours x $85 per 0 170, per 6,460, per
AD 2018-11-01. hour = $170, per inspection inspection
inspection cycle. cycle cycle.
----------------------------------------------------------------------------------------------------------------
The FAA estimates the following costs to do any necessary repairs
that would be required based on the results of the 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 modification (replacement of aluminum 830 work-hours x $85 per hour = 35,000 105,550
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
This AD will not have federalism implications under Executive Order
13132. This AD will not have a substantial direct effect on the States,
on the relationship between the national government and the States, or
on the distribution of power and responsibilities among the various
levels of government.
For the reasons discussed above, I certify that this AD:
[[Page 384]]
(1) Is not a ``significant regulatory action'' under Executive
Order 12866,
(2) Will not affect intrastate aviation in Alaska, and
(3) Will not have a significant economic impact, positive or
negative, on a substantial number of small entities under the criteria
of the Regulatory Flexibility Act.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.
The Amendment
Accordingly, under the authority delegated to me by the
Administrator, the FAA amends 14 CFR part 39 as follows:
PART 39--AIRWORTHINESS DIRECTIVES
0
1. The authority citation for part 39 continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
Sec. 39.13 [Amended]
0
2. The FAA amends Sec. 39.13 by:
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:
2021-26-14 Airbus Helicopters: Amendment 39-21873; Docket No. FAA-
2021-0873; Project Identifier MCAI-2021-00336-R.
(a) Effective Date
This airworthiness directive (AD) is effective February 9, 2022.
(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 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 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
[[Page 385]]
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) Service information identified in this AD that is not
incorporated by reference is available at the addresses specified in
paragraphs (n)(3) and (4) of this AD.
(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 at https://www.regulations.gov in Docket
No. FAA-2021-0873.
(n) Material Incorporated by Reference
(1) The Director of the Federal Register approved the
incorporation by reference of the service information listed in this
paragraph under 5 U.S.C. 552(a) and 1 CFR part 51.
(2) You must use this service information as applicable to do
the actions required by this AD, unless the AD specifies otherwise.
(i) Airbus Helicopters Alert Service Bulletin No. AS332-
05.00.97, Revision 1, dated February 9, 2021.
(ii) Airbus Helicopters Alert Service Bulletin No. EC225-05A038,
Revision 1, dated February 9, 2021.
(iii) Airbus Helicopters Service Bulletin No. AS332-53.01.97,
Revision 0, dated February 9, 2021.
(iv) Airbus Helicopters Service Bulletin No. EC225-53-061,
Revision 0, dated February 9, 2021.
(3) 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.
(4) 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.
(5) You may view this service information that is incorporated
by reference at the National Archives and Records Administration
(NARA). For information on the availability of this material at
NARA, email: [email protected], or go to: https://www.archives.gov/federal-register/cfr/ibr-locations.html.
Issued on December 10, 2021.
Lance T. Gant,
Director, Compliance & Airworthiness Division, Aircraft Certification
Service.
[FR Doc. 2021-28469 Filed 1-4-22; 8:45 am]
BILLING CODE 4910-13-P
