Airworthiness Directives; Airbus Helicopters, 385-388 [2021-28471]
Download as PDF
<![CDATA[
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.
VerDate Sep<11>2014
16:55 Jan 04, 2022
Jkt 256001
(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:
PO 00000
Frm 00009
Fmt 4700
Sfmt 4700
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
TKELLEY on DSK125TN23PROD with RULES1
386
Federal Register / Vol. 87, No. 3 / Wednesday, January 5, 2022 / Rules and Regulations
Amendment 39–21274 (85 FR 63440,
October 8, 2020) (AD 2020–21–01). AD
2020–21–01 applied to certain Airbus
Helicopters Model AS–365N2, AS
365N3, EC 155B, EC155B1, and SA–
365N1 helicopters. The NPRM
published in the Federal Register on
September 30, 2021 (86 FR 54139). In
the NPRM, the FAA proposed to
continue to require modifying the MGB
T/R drive flange installation, and also
proposed to include additional
helicopters in the applicability for the
required actions. The NPRM was
prompted by several reported
occurrences of loss of tightening torque
of the Shur-Lok nut, which serves as a
retainer of the MGB T/R drive flange.
EASA AD 2020–0287, dated
December 21, 2020 (EASA AD 2020–
0287), was issued by EASA, which is
the Technical Agent for the Member
States of the European Union, to correct
an unsafe condition for certain AS 365
N2, AS 365 N3, SA 365 C1, SA 365 C2,
SA 365 C3, SA 365 N and SA 365 N1
helicopters; and all EC 155 B and EC
155 B1 helicopters. Model SA 365 C3
helicopters are not certificated by the
FAA and are not included on the U.S.
type certificate data sheet; this AD
therefore does not include those
helicopters in the applicability. EASA
AD 2020–0287 supersedes EASA AD
2020–0212, dated October 5, 2020,
which required modification of the
MGB T/R drive flange installation.
EASA advises of reported occurrences
of loss of tightening torque of the ShurLok nut, which serves as a retainer of
the T/R drive flange of the MGB. EASA
also advises of subsequent investigation
that determined that these occurrences
were the result of failure of the ShurLok nut locking function, which is
normally ensured by two antirotation
tabs engaged into two slots at the end of
the MGB output shaft pinion. EASA
states this condition could lead to the
loosening of the Shur-Lok nut and
disengagement of the Shur-Lok nut
threads, possibly resulting in reduction
of T/R drive control, rear transmission
vibrations, and subsequent reduced
control of the helicopter.
Accordingly, EASA AD 2020–0287
retains the modification of the MGB T/
R drive flange installation. EASA AD
2020–0287 also includes additional
helicopters in the applicability for the
required actions (Model SA–365C1, SA–
365C2, and SA–365N helicopters on
which Airbus Helicopters modification
0763B64 has been embodied; and Model
EC 155B and EC155B1 helicopters
without modification 0763B64
embodied).
VerDate Sep<11>2014
16:55 Jan 04, 2022
Jkt 256001
Discussion of Final Airworthiness
Directive
Comments
The FAA received comments from
three commenters. The commenters
were an individual who made a
statement about the applicability; an
individual who expressed support and
favor for the NPRM; and an anonymous
commenter, who had a question about
the applicability. The following presents
the comments received on the NPRM
and the FAA’s response to each
comment.
Request for Clarification of
Applicability
An individual stated the opinion that
all helicopters should be subject to the
same rules, a preference for unity under
the law, and that it is unfair to have
different rules for different helicopters.
An anonymous commenter asked why
the NPRM is only applicable to Airbus
Helicopters and not other current and
modern models of helicopters. The FAA
infers that the commenters may be
suggesting that this AD should apply to
all helicopter models. No further
justification was given.
The FAA agrees to clarify the
applicability. Each FAA AD has a
specific applicability, and this FAA AD
reflects the applicability of EASA AD
2020–0287. This AD only addresses the
models specified in the EASA AD that
are affected by the unsafe condition.
Helicopters and the systems that
support the design are varied, and
because of design variances between
manufacturers, may or may not be
subject to an unsafe condition.
Therefore, in crafting a rule, the FAA
specifically works to apply rulemaking
only to the models and systems that are
affected. Otherwise, the FAA may be
creating arbitrary regulations,
unnecessary work, and burdensome
costs for the operators of the unaffected
helicopters. There is no further need to
expand the applicability of this AD to
other helicopter models due to the
likelihood that the type designs are
different and therefore not subject to the
unsafe condition. If information is
received indicating other models are
affected by the unsafe condition, the
FAA will consider further rulemaking.
The FAA has made no changes to this
AD.
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
PO 00000
Frm 00010
Fmt 4700
Sfmt 4700
FAA about the unsafe condition
described in its AD. The FAA reviewed
the relevant data, considered the
comments received, 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.
None of the changes will increase the
economic burden on any operator.
Related Service Information Under 1
CFR Part 51
The FAA reviewed the following
service information.
Airbus Helicopters Alert Service
Bulletin (ASB) No. AS365–63.00.26,
Revision 0, dated July 22, 2020, for
Model AS365N helicopters and non
FAA-type certificated military Model
AS365Fs helicopters; and Airbus
Helicopters ASB No. SA365–65.52,
Revision 1, dated July 22, 2020, for
Model SA–365C1 and SA–365C2
helicopters and non FAA-type
certificated Model SA–365C3
helicopters. This service information
specifies procedures for modifying the
MGB T/R drive flange installation,
which include installing a rear (aft)
output stop between the T/R drive
flange and T/R drive shaft. These
documents are distinct since they apply
to different helicopter models.
This AD also requires Airbus
Helicopters ASB No. AS365–63.00.19,
Revision 1, dated January 31, 2019; and
Airbus Helicopters ASB No. EC155–
63A013, Revision 1, dated January 31,
2019; which the Director of the Federal
Register approved for incorporation by
reference as of November 12, 2020 (85
FR 63440, October 8, 2020).
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.
Differences Between This AD and the
EASA AD
EASA AD 2020–0287 specifies
compliance times of 600 flight hours or
a certain time frame (months). However,
this AD only requires the compliance
time of 600 hours time-in-service.
Costs of Compliance
The FAA estimates that this AD
affects 53 helicopters of U.S. Registry.
Labor rates are estimated at $85 per
work-hour. Based on these numbers, the
FAA estimates the following costs to
comply with this AD.
E:\FR\FM\05JAR1.SGM
05JAR1
Federal Register / Vol. 87, No. 3 / Wednesday, January 5, 2022 / Rules and Regulations
387
ESTIMATED COSTS
Action
Modification (46 helicopters) (retained actions from AD
2020-21-01).
Modification (new action) ..
Labor cost
Parts cost
Cost per product
14 work-hours × $85 per
hour = $1,190.
$2,704 ...............................
$3,894 ...............................
$179,124
14 work-hours × $85 per
hour = $1,190.
Up to 18,474 .....................
Up to 19,664 .....................
Up to 1,042,192
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:
(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.
TKELLEY on DSK125TN23PROD with RULES1
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:
VerDate Sep<11>2014
16:55 Jan 04, 2022
Jkt 256001
PART 39—AIRWORTHINESS
DIRECTIVES
1. The authority citation for part 39
continues to read as follows:
■
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
[Amended]
2. The FAA amends § 39.13 by:
a. Removing Airworthiness Directive
2020–21–01, Amendment 39–21274 (85
FR 63440, October 8, 2020); and
■ b. Adding the following new
airworthiness directive:
■
■
2021–26–18 Airbus Helicopters:
Amendment 39–21877; Docket No.
FAA–2021–0839; Project Identifier
MCAI–2020–01697–R.
(a) Effective Date
This airworthiness directive (AD) is
effective February 9, 2022.
(b) Affected ADs
This AD replaces AD 2020–21–01,
Amendment 39–21274 (85 FR 63440, October
8, 2020) (AD 2020–21–01).
(c) Applicability
This AD applies to the Airbus Helicopters
model helicopters, certificated in any
category, as identified in paragraphs (c)(1)
through (3) of this AD.
(1) Model AS–365N2, AS 365 N3, and SA–
365N1, all serial numbers on which Airbus
Helicopters modification 0763B64 has been
embodied, except those on which Airbus
Helicopters modification 0763C81 has been
embodied.
(2) Model SA–365C1, SA–365C2, and SA–
365N, all serial numbers on which Airbus
Helicopters modification 0763B64 has been
embodied.
(3) Model EC 155B and EC155B1, all serial
numbers, except those on which Airbus
Helicopters modification 0763C81 has been
embodied.
(d) Subject
Joint Aircraft Service Component (JASC)
Code: 6500, Tail Rotor Drive System.
(e) Unsafe Condition
This AD was prompted by several reported
occurrences of loss of tightening torque of the
Shur-Lok nut, which serves as a retainer of
the main gear box (MGB) tail rotor (T/R)
drive flange. The FAA is issuing this AD to
detect and address loss of tightening torque
of the Shur-Lok nut. The unsafe condition, if
not addressed, could result in loosening of
the Shur-Lok nut, possibly resulting in
PO 00000
Frm 00011
Fmt 4700
Sfmt 4700
Cost on U.S. operators
disengagement of the Shur-Lok nut threads,
reduction of T/R drive control, rear
transmission vibrations, and subsequent
reduced control of the helicopter.
(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
(g) Required Actions
This paragraph restates the requirements of
paragraph (e) of AD 2020–21–01 with no
changes. Within 600 hours time-in-service
after November 12, 2020 (the effective date of
AD 2020–21–01):
(1) For Model AS–365N2, AS 365N3, and
SA–365N1 helicopters:
(i) Without removing the tail drive shaft
flange (a), remove the sliding flange (b) from
the flexible coupling (c) as shown in Detail
‘‘B’’ of Figure 1, PRE MOD, of Airbus
Helicopters Alert Service Bulletin (ASB) No.
AS365–63.00.19, Revision 1, dated January
31, 2019 (ASB AS365–63.00.19, Revision 1);
replace the 3 bolts (d) and remove from
service the 3 washers (e).
(ii) Install the sliding flange (b) with aft
output stop (1) part number (P/N) 365A32–
7836–20 as shown in Detail ‘‘B’’ of Figure 1,
POST MOD, of ASB AS365–63.00.19,
Revision 1, and by following the
Accomplishment Instructions, paragraph
3.B.2.b, of ASB AS365–63.00.19, Revision 1.
(2) For Model EC 155B and EC155B1
helicopters with modification 0763B64
embodied:
(i) Without removing the Shur-Lok nut (a),
remove the sliding flange (b) from the flexible
coupling (c) as shown in Detail ‘‘B’’ of Figure
1, PRE MOD, of Airbus Helicopters ASB No.
EC155–63A013, Revision 1, dated January 31,
2019 (ASB EC155–63A013, Revision 1);
replace the 3 bolts (d) and remove from
service the 3 washers (e).
(ii) Install the sliding flange (b) with aft
output stop (1) P/N 365A32–7836–20 as
shown in Detail ‘‘B’’ of Figure 1, POST MOD,
of ASB EC155–63A013, Revision 1, and by
following the Accomplishment Instructions,
paragraph 3.B.2.b, of ASB EC155–63A013,
Revision 1.
Note 1 to paragraph (g)(2)(ii): ASB EC155–
63A013, Revision 1 refers to the ‘‘aft output
stop’’ as ‘‘rear output stop.’’
(h) New Required Actions
For Model SA–365C1, SA–365C2, and SA–
365N helicopters; and Model EC 155B and
EC155B1 helicopters without modification
0763B64 embodied: Within 600 hours timein-service after the effective date of this AD,
modify the MGB T/R drive flange
installation, in accordance with paragraph
E:\FR\FM\05JAR1.SGM
05JAR1
388
Federal Register / Vol. 87, No. 3 / Wednesday, January 5, 2022 / Rules and Regulations
3.B.2., ‘‘Procedure,’’ of the Accomplishment
Instructions of the applicable service
information specified in paragraphs (h)(1)
through (3) of this AD, except as specified in
paragraph (i) of this AD.
(1) Airbus Helicopters ASB SA365–65.52,
Revision 1, dated July 22, 2020.
(2) Airbus Helicopters ASB AS365–
63.00.26, Revision 0, dated July 22, 2020.
(3) ASB EC155–63A013, Revision 1.
(i) Exceptions to Service Information
Where the service information identified in
paragraph (h) of this AD specifies to discard
certain parts, this AD requires removing
those parts from service.
(j) Special Flight Permits
Special flight permits, as described in 14
CFR 21.197 and 21.199, are not allowed.
(k) Alternative Methods of Compliance
(AMOCs)
(1) The Manager, International Validation
Branch, FAA, has the authority to approve
AMOCs for this AD, if requested using the
procedures found in 14 CFR 39.19. In
accordance with 14 CFR 39.19, send your
request to your principal inspector or local
Flight Standards District Office, as
appropriate. If sending information directly
to the manager of the International Validation
Branch, send it to the attention of the person
identified in paragraph (l)(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.
TKELLEY on DSK125TN23PROD with RULES1
(l) 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; phone:
(516) 228–7330; email: andrea.jimenez@
faa.gov.
(2) The subject of this AD is addressed in
European Union Aviation Safety Agency
(EASA) AD 2020–0287, dated December 21,
2020. You may view the EASA AD at https://
www.regulations.gov in Docket No. FAA–
2021–0839.
(m) Material Incorporated by Reference
(1) The Director of the Federal Register
approved the incorporation by reference
(IBR) 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.
(3) The following service information was
approved for IBR on February 9, 2022.
(i) Airbus Helicopters Alert Service
Bulletin (ASB) No. AS365–63.00.26, Revision
0, dated July 22, 2020.
(ii) Airbus Helicopters ASB No. SA365–
65.52, Revision 1, dated July 22, 2020.
(4) The following service information was
approved for IBR on November 12, 2020 (85
FR 63440, October 8, 2020).
VerDate Sep<11>2014
16:55 Jan 04, 2022
Jkt 256001
(i) Airbus Helicopters ASB No. AS365–
63.00.19, Revision 1, dated January 31, 2019.
(ii) Airbus Helicopters ASB No. EC155–
63A013, Revision 1, dated January 31, 2019.
(5) For Airbus Helicopters service
information identified in this AD, 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//services/
support.html.
(6) 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.
(7) 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 15, 2021.
Lance T. Gant,
Director, Compliance & Airworthiness
Division, Aircraft Certification Service.
[FR Doc. 2021–28471 Filed 1–4–22; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 95
[Docket No. 31408; Amdt. No. 563]
IFR Altitudes; Miscellaneous
Amendments
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule.
AGENCY:
This amendment adopts
miscellaneous amendments to the
required IFR (instrument flight rules)
altitudes and changeover points for
certain Federal airways, jet routes, or
direct routes for which a minimum or
maximum en route authorized IFR
altitude is prescribed. This regulatory
action is needed because of changes
occurring in the National Airspace
System. These changes are designed to
provide for the safe and efficient use of
the navigable airspace under instrument
conditions in the affected areas.
DATES: Effective 0901 UTC, January 27,
2022.
FOR FURTHER INFORMATION CONTACT:
Thomas J. Nichols, Flight Procedures
and Airspace Group, Flight
Technologies and Procedures Division,
Flight Standards Service, Federal
Aviation Administration. Mailing
Address: FAA Mike Monroney
Aeronautical Center, Flight Procedures
SUMMARY:
PO 00000
Frm 00012
Fmt 4700
Sfmt 4700
and Airspace Group, 6500 South
MacArthur Blvd., Registry Bldg 29
Room 104, Oklahoma City, OK 73125.
Telephone: (405) 954–4164.
SUPPLEMENTARY INFORMATION: This
amendment to part 95 of the Federal
Aviation Regulations (14 CFR part 95)
amends, suspends, or revokes IFR
altitudes governing the operation of all
aircraft in flight over a specified route
or any portion of that route, as well as
the changeover points (COPs) for
Federal airways, jet routes, or direct
routes as prescribed in part 95.
The Rule
The specified IFR altitudes, when
used in conjunction with the prescribed
changeover points for those routes,
ensure navigation aid coverage that is
adequate for safe flight operations and
free of frequency interference. The
reasons and circumstances that create
the need for this amendment involve
matters of flight safety and operational
efficiency in the National Airspace
System, are related to published
aeronautical charts that are essential to
the user, and provide for the safe and
efficient use of the navigable airspace.
In addition, those various reasons or
circumstances require making this
amendment effective before the next
scheduled charting and publication date
of the flight information to assure its
timely availability to the user. The
effective date of this amendment reflects
those considerations. In view of the
close and immediate relationship
between these regulatory changes and
safety in air commerce, I find that notice
and public procedure before adopting
this amendment are impracticable and
contrary to the public interest and that
good cause exists for making the
amendment effective in less than 30
days.
Conclusion
The FAA has determined that this
regulation only involves an established
body of technical regulations for which
frequent and routine amendments are
necessary to keep them operationally
current. It, therefore—(1) is not a
‘‘significant regulatory action’’ under
Executive Order 12866; (2) is not a
‘‘significant rule’’ under DOT
Regulatory Policies and Procedures (44
FR 11034; February 26, 1979); and (3)
does not warrant preparation of a
regulatory evaluation as the anticipated
impact is so minimal. For the same
reason, the FAA certifies that this
amendment will not have a significant
economic impact on a substantial
number of small entities under the
criteria of the Regulatory Flexibility Act.
E:\FR\FM\05JAR1.SGM
05JAR1
]]>Agencies
[Federal Register Volume 87, Number 3 (Wednesday, January 5, 2022)]
[Rules and Regulations]
[Pages 385-388]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2021-28471]
-----------------------------------------------------------------------
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
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Final rule.
-----------------------------------------------------------------------
SUMMARY: 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 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: [email protected].
SUPPLEMENTARY INFORMATION:
Background
The FAA issued a notice of proposed rulemaking (NPRM) to amend 14
CFR part 39 to supersede AD 2020-21-01,
[[Page 386]]
Amendment 39-21274 (85 FR 63440, October 8, 2020) (AD 2020-21-01). AD
2020-21-01 applied to certain Airbus Helicopters Model AS-365N2, AS
365N3, EC 155B, EC155B1, and SA-365N1 helicopters. The NPRM published
in the Federal Register on September 30, 2021 (86 FR 54139). In the
NPRM, the FAA proposed to continue to require modifying the MGB T/R
drive flange installation, and also proposed to include additional
helicopters in the applicability for the required actions. The NPRM was
prompted by several reported occurrences of loss of tightening torque
of the Shur-Lok nut, which serves as a retainer of the MGB T/R drive
flange.
EASA AD 2020-0287, dated December 21, 2020 (EASA AD 2020-0287), was
issued by EASA, which is the Technical Agent for the Member States of
the European Union, to correct an unsafe condition for certain AS 365
N2, AS 365 N3, SA 365 C1, SA 365 C2, SA 365 C3, SA 365 N and SA 365 N1
helicopters; and all EC 155 B and EC 155 B1 helicopters. Model SA 365
C3 helicopters are not certificated by the FAA and are not included on
the U.S. type certificate data sheet; this AD therefore does not
include those helicopters in the applicability. EASA AD 2020-0287
supersedes EASA AD 2020-0212, dated October 5, 2020, which required
modification of the MGB T/R drive flange installation. EASA advises of
reported occurrences of loss of tightening torque of the Shur-Lok nut,
which serves as a retainer of the T/R drive flange of the MGB. EASA
also advises of subsequent investigation that determined that these
occurrences were the result of failure of the Shur-Lok nut locking
function, which is normally ensured by two antirotation tabs engaged
into two slots at the end of the MGB output shaft pinion. EASA states
this condition could lead to the loosening of the Shur-Lok nut and
disengagement of the Shur-Lok nut threads, possibly resulting in
reduction of T/R drive control, rear transmission vibrations, and
subsequent reduced control of the helicopter.
Accordingly, EASA AD 2020-0287 retains the modification of the MGB
T/R drive flange installation. EASA AD 2020-0287 also includes
additional helicopters in the applicability for the required actions
(Model SA-365C1, SA-365C2, and SA-365N helicopters on which Airbus
Helicopters modification 0763B64 has been embodied; and Model EC 155B
and EC155B1 helicopters without modification 0763B64 embodied).
Discussion of Final Airworthiness Directive
Comments
The FAA received comments from three commenters. The commenters
were an individual who made a statement about the applicability; an
individual who expressed support and favor for the NPRM; and an
anonymous commenter, who had a question about the applicability. The
following presents the comments received on the NPRM and the FAA's
response to each comment.
Request for Clarification of Applicability
An individual stated the opinion that all helicopters should be
subject to the same rules, a preference for unity under the law, and
that it is unfair to have different rules for different helicopters. An
anonymous commenter asked why the NPRM is only applicable to Airbus
Helicopters and not other current and modern models of helicopters. The
FAA infers that the commenters may be suggesting that this AD should
apply to all helicopter models. No further justification was given.
The FAA agrees to clarify the applicability. Each FAA AD has a
specific applicability, and this FAA AD reflects the applicability of
EASA AD 2020-0287. This AD only addresses the models specified in the
EASA AD that are affected by the unsafe condition. Helicopters and the
systems that support the design are varied, and because of design
variances between manufacturers, may or may not be subject to an unsafe
condition. Therefore, in crafting a rule, the FAA specifically works to
apply rulemaking only to the models and systems that are affected.
Otherwise, the FAA may be creating arbitrary regulations, unnecessary
work, and burdensome costs for the operators of the unaffected
helicopters. There is no further need to expand the applicability of
this AD to other helicopter models due to the likelihood that the type
designs are different and therefore not subject to the unsafe
condition. If information is received indicating other models are
affected by the unsafe condition, the FAA will consider further
rulemaking. The FAA has made no changes to this AD.
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, considered the comments received, 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. None of the changes will increase the economic burden on any
operator.
Related Service Information Under 1 CFR Part 51
The FAA reviewed the following service information.
Airbus Helicopters Alert Service Bulletin (ASB) No. AS365-63.00.26,
Revision 0, dated July 22, 2020, for Model AS365N helicopters and non
FAA-type certificated military Model AS365Fs helicopters; and Airbus
Helicopters ASB No. SA365-65.52, Revision 1, dated July 22, 2020, for
Model SA-365C1 and SA-365C2 helicopters and non FAA-type certificated
Model SA-365C3 helicopters. This service information specifies
procedures for modifying the MGB T/R drive flange installation, which
include installing a rear (aft) output stop between the T/R drive
flange and T/R drive shaft. These documents are distinct since they
apply to different helicopter models.
This AD also requires Airbus Helicopters ASB No. AS365-63.00.19,
Revision 1, dated January 31, 2019; and Airbus Helicopters ASB No.
EC155-63A013, Revision 1, dated January 31, 2019; which the Director of
the Federal Register approved for incorporation by reference as of
November 12, 2020 (85 FR 63440, October 8, 2020).
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.
Differences Between This AD and the EASA AD
EASA AD 2020-0287 specifies compliance times of 600 flight hours or
a certain time frame (months). However, this AD only requires the
compliance time of 600 hours time-in-service.
Costs of Compliance
The FAA estimates that this AD affects 53 helicopters of U.S.
Registry. Labor rates are estimated at $85 per work-hour. Based on
these numbers, the FAA estimates the following costs to comply with
this AD.
[[Page 387]]
Estimated Costs
----------------------------------------------------------------------------------------------------------------
Cost on U.S.
Action Labor cost Parts cost Cost per product operators
----------------------------------------------------------------------------------------------------------------
Modification (46 helicopters) 14 work-hours x $2,704............ $3,894............ $179,124
(retained actions from AD $85 per hour =
2020[dash]21[dash]01). $1,190.
Modification (new action)....... 14 work-hours x Up to 18,474...... Up to 19,664...... Up to 1,042,192
$85 per hour =
$1,190.
----------------------------------------------------------------------------------------------------------------
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:
(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 2020-21-01, Amendment 39-21274 (85
FR 63440, October 8, 2020); and
0
b. Adding the following new airworthiness directive:
2021-26-18 Airbus Helicopters: Amendment 39-21877; Docket No. FAA-
2021-0839; Project Identifier MCAI-2020-01697-R.
(a) Effective Date
This airworthiness directive (AD) is effective February 9, 2022.
(b) Affected ADs
This AD replaces AD 2020-21-01, Amendment 39-21274 (85 FR 63440,
October 8, 2020) (AD 2020-21-01).
(c) Applicability
This AD applies to the Airbus Helicopters model helicopters,
certificated in any category, as identified in paragraphs (c)(1)
through (3) of this AD.
(1) Model AS-365N2, AS 365 N3, and SA-365N1, all serial numbers
on which Airbus Helicopters modification 0763B64 has been embodied,
except those on which Airbus Helicopters modification 0763C81 has
been embodied.
(2) Model SA-365C1, SA-365C2, and SA-365N, all serial numbers on
which Airbus Helicopters modification 0763B64 has been embodied.
(3) Model EC 155B and EC155B1, all serial numbers, except those
on which Airbus Helicopters modification 0763C81 has been embodied.
(d) Subject
Joint Aircraft Service Component (JASC) Code: 6500, Tail Rotor
Drive System.
(e) Unsafe Condition
This AD was prompted by several reported occurrences of loss of
tightening torque of the Shur-Lok nut, which serves as a retainer of
the main gear box (MGB) tail rotor (T/R) drive flange. The FAA is
issuing this AD to detect and address loss of tightening torque of
the Shur-Lok nut. The unsafe condition, if not addressed, could
result in loosening of the Shur-Lok nut, possibly resulting in
disengagement of the Shur-Lok nut threads, reduction of T/R drive
control, rear transmission vibrations, and subsequent reduced
control of the helicopter.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) Required Actions
This paragraph restates the requirements of paragraph (e) of AD
2020-21-01 with no changes. Within 600 hours time-in-service after
November 12, 2020 (the effective date of AD 2020-21-01):
(1) For Model AS-365N2, AS 365N3, and SA-365N1 helicopters:
(i) Without removing the tail drive shaft flange (a), remove the
sliding flange (b) from the flexible coupling (c) as shown in Detail
``B'' of Figure 1, PRE MOD, of Airbus Helicopters Alert Service
Bulletin (ASB) No. AS365-63.00.19, Revision 1, dated January 31,
2019 (ASB AS365-63.00.19, Revision 1); replace the 3 bolts (d) and
remove from service the 3 washers (e).
(ii) Install the sliding flange (b) with aft output stop (1)
part number (P/N) 365A32-7836-20 as shown in Detail ``B'' of Figure
1, POST MOD, of ASB AS365-63.00.19, Revision 1, and by following the
Accomplishment Instructions, paragraph 3.B.2.b, of ASB AS365-
63.00.19, Revision 1.
(2) For Model EC 155B and EC155B1 helicopters with modification
0763B64 embodied:
(i) Without removing the Shur-Lok nut (a), remove the sliding
flange (b) from the flexible coupling (c) as shown in Detail ``B''
of Figure 1, PRE MOD, of Airbus Helicopters ASB No. EC155-63A013,
Revision 1, dated January 31, 2019 (ASB EC155-63A013, Revision 1);
replace the 3 bolts (d) and remove from service the 3 washers (e).
(ii) Install the sliding flange (b) with aft output stop (1) P/N
365A32-7836-20 as shown in Detail ``B'' of Figure 1, POST MOD, of
ASB EC155-63A013, Revision 1, and by following the Accomplishment
Instructions, paragraph 3.B.2.b, of ASB EC155-63A013, Revision 1.
Note 1 to paragraph (g)(2)(ii): ASB EC155-63A013, Revision 1
refers to the ``aft output stop'' as ``rear output stop.''
(h) New Required Actions
For Model SA-365C1, SA-365C2, and SA-365N helicopters; and Model
EC 155B and EC155B1 helicopters without modification 0763B64
embodied: Within 600 hours time-in-service after the effective date
of this AD, modify the MGB T/R drive flange installation, in
accordance with paragraph
[[Page 388]]
3.B.2., ``Procedure,'' of the Accomplishment Instructions of the
applicable service information specified in paragraphs (h)(1)
through (3) of this AD, except as specified in paragraph (i) of this
AD.
(1) Airbus Helicopters ASB SA365-65.52, Revision 1, dated July
22, 2020.
(2) Airbus Helicopters ASB AS365-63.00.26, Revision 0, dated
July 22, 2020.
(3) ASB EC155-63A013, Revision 1.
(i) Exceptions to Service Information
Where the service information identified in paragraph (h) of
this AD specifies to discard certain parts, this AD requires
removing those parts from service.
(j) Special Flight Permits
Special flight permits, as described in 14 CFR 21.197 and
21.199, are not allowed.
(k) Alternative Methods of Compliance (AMOCs)
(1) The Manager, International Validation Branch, FAA, has the
authority to approve AMOCs for this AD, if requested using the
procedures found in 14 CFR 39.19. In accordance with 14 CFR 39.19,
send your request to your principal inspector or local Flight
Standards District Office, as appropriate. If sending information
directly to the manager of the International Validation Branch, send
it to the attention of the person identified in paragraph (l)(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.
(l) 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; phone: (516) 228-7330;
email: [email protected].
(2) The subject of this AD is addressed in European Union
Aviation Safety Agency (EASA) AD 2020-0287, dated December 21, 2020.
You may view the EASA AD at https://www.regulations.gov in Docket
No. FAA-2021-0839.
(m) Material Incorporated by Reference
(1) The Director of the Federal Register approved the
incorporation by reference (IBR) 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.
(3) The following service information was approved for IBR on
February 9, 2022.
(i) Airbus Helicopters Alert Service Bulletin (ASB) No. AS365-
63.00.26, Revision 0, dated July 22, 2020.
(ii) Airbus Helicopters ASB No. SA365-65.52, Revision 1, dated
July 22, 2020.
(4) The following service information was approved for IBR on
November 12, 2020 (85 FR 63440, October 8, 2020).
(i) Airbus Helicopters ASB No. AS365-63.00.19, Revision 1, dated
January 31, 2019.
(ii) Airbus Helicopters ASB No. EC155-63A013, Revision 1, dated
January 31, 2019.
(5) For Airbus Helicopters service information identified in
this AD, 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//services/support.html.
(6) 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.
(7) 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 15, 2021.
Lance T. Gant,
Director, Compliance & Airworthiness Division, Aircraft Certification
Service.
[FR Doc. 2021-28471 Filed 1-4-22; 8:45 am]
BILLING CODE 4910-13-P
