Airworthiness Directives; Airbus Helicopters, 58600-58604 [2021-22462]
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Federal Register / Vol. 86, No. 202 / Friday, October 22, 2021 / Proposed Rules
14 CFR 39.19, send your request to your
principal inspector or responsible Flight
Standards Office, as appropriate. If sending
information directly to the manager of the
certification office, send it to the attention of
the person identified in Related Information.
(2) Before using any approved AMOC,
notify your appropriate principal inspector,
or lacking a principal inspector, the manager
of the responsible Flight Standards Office.
(3) Contacting the Manufacturer: For any
requirement in this AD to obtain instructions
from a manufacturer, the instructions must
be accomplished using a method approved
by the Manager, Atlanta ACO Branch, FAA.
(4) Required for compliance (RC): Except as
specified by paragraph (m)(3) of this AD, if
any service information contains procedures
or tests that are identified as RC, those
procedures and tests must be done to comply
with this AD; any procedures or tests that are
not identified as RC are recommended. Those
procedures and tests that are not identified
as RC may be deviated from using accepted
methods in accordance with the operator’s
maintenance or inspection program without
obtaining approval of an AMOC, provided
the procedures and tests identified as RC can
be done and the airplane can be put back in
an airworthy condition. Any substitutions or
changes to procedures or tests identified as
RC require approval of an AMOC.
(n) Related Information
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(1) For more information about this AD,
contact John Marshall, Aerospace Engineer,
Airframe Section, FAA, Atlanta ACO Branch,
1701 Columbia Avenue, College Park, GA
30337; phone: 404–474–5524; fax: 404–474–
5606; email: John.R.Marshall@faa.gov.
(2) For Airbus service information
identified in this AD, contact Airbus SAS,
Airworthiness Office—EIAS, Rond-Point
Emile Dewoitine No: 2, 31700 Blagnac Cedex,
France; telephone +33 5 61 93 36 96; fax +33
5 61 93 44 51; email account.airworth-eas@
airbus.com; internet https://www.airbus.com.
For EASA material identified in this AD,
contact 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 material on the EASA website at https://
ad.easa.europa.eu. You may view this
referenced service information at the FAA,
Airworthiness Products Section, Operational
Safety Branch, 2200 South 216th St., Des
Moines, WA. For information on the
availability of this material at the FAA, call
206–231–3195.
Issued on October 14, 2021.
Lance T. Gant,
Director, Compliance & Airworthiness
Division, Aircraft Certification Service.
[FR Doc. 2021–22785 Filed 10–21–21; 8:45 am]
BILLING CODE 4910–13–P
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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
Federal Aviation
Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
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 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
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.
SUMMARY:
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/
ADDRESSES:
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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
andrea.jimenez@faa.gov.
SUPPLEMENTARY INFORMATION:
Comments Invited
The FAA invites you to send any
written relevant data, views, or
arguments about this proposal. Send
your comments to an address listed
under ADDRESSES. Include ‘‘Docket No.
FAA–2021–0873; 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
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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
andrea.jimenez@faa.gov. Any
commentary that the FAA receives
which is not specifically designated as
CBI will be placed in the public docket
for this rulemaking.
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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
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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.
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.
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.
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
Related Service Information Under 1
Helicopters Service Bulletin No. 05–
CFR Part 51
019, Revision 4, dated September 22,
2014, for Model EC225 LP helicopters.
The FAA reviewed the following
This service information specifies
Airbus Helicopters service information.
• Alert Service Bulletins Nos. AS332– procedures for cutting out the junction
profiles.
05.00.97, Revision 1; and EC225–
The FAA also reviewed Airbus
05A038, Revision 1; both dated
Helicopters Alert Service Bulletins Nos.
February 9, 2021; which specify
AS332–05.00.97, Revision 0; and
procedures for, among other actions,
EC225–05A038, Revision 0; both dated
installing a cut-out for the LH and RH
April 15, 2014; which specify
rail support junction profiles and
procedures for, among other actions,
inspecting splices, frame 5295, and
installing a cut-out for the LH and RH
related equipment for a crack. These
documents are distinct since they apply rail support junction profiles and
inspecting splices, frame 5295, and
to different helicopter models.
related equipment for a crack.
• Service Bulletins Nos. AS332–
53.01.97, Revision 0; and EC225–53–
Proposed AD Requirements in This
061, Revision 0; both dated February 9,
NPRM
2021; which specify procedures for
This proposed AD would retain all
modifying the helicopter by replacing
requirements of AD 2018–11–01 and
the aluminum LH and RH splices with
require a modification for replacing
steel splices under the plates and the
aluminum splices with steel splices on
brackets of the main gear box (MGB)
frame 5295. This proposed AD would
bars. The modification includes taking
reference readings of the brackets of the also provide terminating action for the
repetitive inspections required by AD
MGB bars, removing the MGB brackets
2018–11–01. This proposed AD would
and plates, removing the aluminum
splices and inspecting the joggling areas also require accomplishing the actions
specified in the service information
for scratches or other damage,
already described, except as discussed
inspecting frame 5295 for cracking
(including a dye penetrant inspection if under ‘‘Differences Between this AD
and the EASA AD.’’
the inspection results are not
conclusive), identifying the current
Redesignation of AD 2018–11–01
measurements (values) of the rivet and
Paragraph Identifier
attachment plate holes for installation of
the steel splice (including determining
Since AD 2018–11–01 was issued, the
the values of the rivet holes and
AD format has been revised, and certain
attachment plate holes on frame 5295
paragraphs have been rearranged. As a
with a calibrated pad and determining
result, the corresponding paragraph
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identifiers have been redesignated in
this proposed AD, as listed in the
following table:
Differences Between This Proposed AD
and the EASA AD 2021–0075
REVISED PARAGRAPH IDENTIFIER
Requirement in AD
2018–11–01
paragraph (e) ............
paragraph (f) .............
Corresponding
requirement in this
proposed AD
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:
paragraph (g).
paragraph (j)(1).
ESTIMATED COSTS FOR REQUIRED ACTIONS
Action
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
2 work-hours × $85 per hour = $170, per
inspection cycle.
The FAA estimates the following
costs to do any necessary repairs that
Cost per
product
Parts cost
would be required based on the results
of the proposed inspection. The agency
0
Cost on U.S.
operators
$8,400 ....................
$319,200.
$170, per inspection cycle.
$6,460, per inspection cycle.
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 proposed modification (replacement of aluminum
splices with steel splices).
40 work-hours × $85 per hour = $3,400 ......................
830 work-hours × $85 per hour = $70,550 ..................
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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
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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
1. The authority citation for part 39
continues to read as follows:
■
Authority: 49 U.S.C. 106(g), 40113, 44701.
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Parts cost
§ 39.13
$5,000
35,000
Cost per
product
$8,400
105,550
[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:
■
■
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
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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.
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(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
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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 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
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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: 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) 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
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58604
Federal Register / Vol. 86, No. 202 / Friday, October 22, 2021 / Proposed Rules
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]
Authority for This Rulemaking
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 71
[Docket No. FAA–2021–0851; Airspace
Docket No. 19–AAL–42]
RIN 2120–AA66
Proposed Establishment of United
States Area Navigation (RNAV) Route
T–373; Bethel, AK
Federal Aviation
Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
This action proposes to
establish United States Area Navigation
(RNAV) route T–373 in the vicinity of
Bethel, AK in support of a large and
comprehensive T-route modernization
project for the state of Alaska.
DATES: Comments must be received on
or before December 6, 2021.
ADDRESSES: Send comments on this
proposal to the U.S. Department of
Transportation, Docket Operations, 1200
New Jersey Avenue SE, West Building
Ground Floor, Room W12–140,
Washington, DC 20590; telephone:
1(800) 647–5527, or (202) 366–9826.
You must identify FAA Docket No.
FAA–2021–0851; Airspace Docket No.
19–AAL–42 at the beginning of your
comments. You may also submit
comments through the internet at
https://www.regulations.gov.
FAA Order JO 7400.11F, Airspace
Designations and Reporting Points, and
subsequent amendments can be viewed
online at https://www.faa.gov/air_
traffic/publications/. For further
information, you can contact the Rules
and Regulations Group, Federal
Aviation Administration, 800
Independence Avenue SW, Washington,
DC 20591; telephone: (202) 267–8783.
lotter on DSK11XQN23PROD with PROPOSALS1
SUMMARY:
VerDate Sep<11>2014
17:01 Oct 21, 2021
Jkt 256001
FAA Order JO 7400.11F is also available
for inspection at the National Archives
and Records Administration (NARA).
For information on the availability of
FAA Order JO 7400.11F at NARA,
email: fr.inspection@nara.gov or go to
https://www.archives.gov/federalregister/cfr/ibr-locations.html.
FOR FURTHER INFORMATION CONTACT:
Christopher McMullin, Rules and
Regulations Group, Office of Policy,
Federal Aviation Administration, 800
Independence Avenue SW, Washington,
DC 20591; telephone: (202) 267–8783.
SUPPLEMENTARY INFORMATION:
The FAA’s authority to issue rules
regarding aviation safety is found in
Title 49 of the United States Code.
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. This rulemaking is
promulgated under the authority
described in Subtitle VII, Part A,
Subpart I, Section 40103. Under that
section, the FAA is charged with
prescribing regulations to assign the use
of the airspace necessary to ensure the
safety of aircraft and the efficient use of
airspace. This regulation is within the
scope of that authority as it would
expand the availability of RNAV in
Alaska and improve the efficient flow of
air traffic within the National Airspace
System (NAS) by lessening the
dependency on ground based
navigation.
Comments Invited
Interested parties are invited to
participate in this proposed rulemaking
by submitting such written data, views,
or arguments as they may desire.
Comments that provide the factual basis
supporting the views and suggestions
presented are particularly helpful in
developing reasoned regulatory
decisions on the proposal. Comments
are specifically invited on the overall
regulatory, aeronautical, economic,
environmental, and energy-related
aspects of the proposal.
Communications should identify both
docket numbers (FAA Docket No. FAA–
2021–0851; Airspace Docket No. 19–
AAL–42) and be submitted in triplicate
to the Docket Management Facility (see
ADDRESSES section for address and
phone number). You may also submit
comments through the internet at
https://www.regulations.gov.
Commenters wishing the FAA to
acknowledge receipt of their comments
on this action must submit with those
comments a self-addressed, stamped
PO 00000
Frm 00008
Fmt 4702
Sfmt 4702
postcard on which the following
statement is made: ‘‘Comments to FAA
Docket No. FAA–2021–0851; Airspace
Docket No. 19–AAL–42’’. The postcard
will be date/time stamped and returned
to the commenter.
All communications received on or
before the specified comment closing
date will be considered before taking
action on the proposed rule. The
proposal contained in this action may
be changed in light of comments
received. All comments submitted will
be available for examination in the
public docket both before and after the
comment closing date. A report
summarizing each substantive public
contact with FAA personnel concerned
with this rulemaking will be filed in the
docket.
Availability of NPRM
An electronic copy of this document
may be downloaded through the
internet at https://www.regulations.gov.
Recently published rulemaking
documents can also be accessed through
the FAA’s web page at https://
www.faa.gov/air_traffic/publications/
airspace_amendments/.
You may review the public docket
containing the proposal, any comments
received and any final disposition in
person in the Dockets Office (see
ADDRESSES section for address and
phone number) between 9:00 a.m. and
5:00 p.m., Monday through Friday,
except Federal holidays. An informal
docket may also be examined during
normal business hours at the office of
the Western Service Center, Operations
Support Group, Federal Aviation
Administration, 2200 South 216th St.,
Des Moines, WA 98198.
Availability and Summary of
Documents for Incorporation by
Reference
This document proposes to amend
FAA Order JO 7400.11F, Airspace
Designations and Reporting Points,
dated August 10, 2021, and effective
September 15, 2021. FAA Order JO
7400.11F is publicly available as listed
in the ADDRESSES section of this
document. FAA Order JO 7400.11F lists
Class A, B, C, D, and E airspace areas,
air traffic service routes, and reporting
points.
Background
In 2003, Congress enacted the Vision
100-Century of Aviation
Reauthorization Act (Pub L., 108–176),
which established a joint planning and
development office in the FAA to
manage the work related to the Next
Generation Air Transportation System
(NextGen). Today, NextGen is an
E:\FR\FM\22OCP1.SGM
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]]>Agencies
[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]
-----------------------------------------------------------------------
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).
-----------------------------------------------------------------------
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
