Airworthiness Directives; Airbus Helicopters Deutschland GmbH Helicopters, 27268-27271 [2021-10605]
Download as PDF
<![CDATA[
27268
Federal Register / Vol. 86, No. 96 / Thursday, May 20, 2021 / Rules and Regulations
(g) Required Actions
(1) At the next engine shop visit after the
effective date of this AD, remove the affected
HPT inner stationary seal and replace with a
HPT inner stationary seal that is eligible for
installation.
(2) After removing the affected HPT inner
stationary seal required by paragraph (g)(1),
inspect the removed HPT inner stationary
seal for honeycomb separation, as defined in
the Accomplishment Instructions, paragraph
3.C.(1), in CFM SB CFM56–5B S/B 72–0952,
Revision 01, dated January 15, 2020, or in
CFM SB CFM56–7B S/B 72–1054, Revision
01, dated January 15, 2020.
(3) If honeycomb separation is found
during the inspection required by paragraph
(g)(2) of this AD, before further flight:
(i) Remove the rotating air HPT front seal
from service and replace with a rotating air
HPT front seal that is eligible for installation.
(ii) Remove the HPT rotor blades and
replace them with HPT rotor blades eligible
for installation.
(iii) Remove the No. 3 ball bearing from
service and replace with a No. 3 ball bearing
eligible for installation.
(h) Definitions
(1) For the purpose of this AD, an ‘‘engine
shop visit’’ is the induction of an engine into
the shop for maintenance involving the
separation of pairs of major mating engine
case flanges, except for the following
situations, which do not constitute an engine
shop visit.
(i) Separation of engine flanges solely for
the purpose of transportation of the engine
without subsequent maintenance.
(ii) Separation of engine flanges solely for
the purpose of replacing the fan or propulsor
without subsequent maintenance.
(2) For the purpose of this AD, an HPT
inner stationary seal that is eligible for
installation is an HPT inner stationary seal:
(i) That is not listed in Planning
Information, Paragraph 1.A., Table 1, of CFM
SB CFM56–5B S/B 72–0952, Revision 01,
dated January 15, 2020, or in Planning
Information, Paragraph 1.A., Table 1, CFM
SB CFM56–7B S/B 72–1054, Revision 01,
dated January 15, 2020; or
(ii) with a P/N 1808M56G01 and with a
S/N listed in Paragraph 1.A., Table 1, of CFM
SB CFM56–5B S/B 72–0952, Revision 01,
dated January 15, 2020, or Paragraph 1.A.,
Table 1, CFM SB CFM56–7B S/B 72–1054,
Revision 01, dated January 15, 2020, that has
been repaired per CFM56–5B ESM, 72–41–
03, REPAIR 003, or CFM56–7B ESM, 72–41–
03, REPAIR 003, after the year listed in
Paragraph 1.A., Table 1, of CFM SB CFM56–
5B S/B 72–0952, Revision 01, dated January
15, 2020, or Paragraph 1.A., Table 1, CFM SB
CFM56–7B S/B 72–1054, Revision 01, dated
January 15, 2020.
(3) For the purpose of this AD, a rotating
air HPT front seal that is eligible for
installation is any rotating air HPT front seal
that was not removed from service as a result
of the inspection of the HPT inner stationary
seal required by paragraph (g)(2) of this AD
in which there was a finding of honeycomb
separation.
(4) For the purpose of this AD, HPT rotor
blades eligible for installation are new HPT
VerDate Sep<11>2014
16:06 May 19, 2021
Jkt 253001
rotor blades with zero flight hours since news
or HPT rotor blades that have been inspected
and returned to a serviceable condition using
approved engine manual requirements.
(5) For the purpose of this AD, a No. 3 ball
bearing eligible for installation is any No. 3
ball bearing that was not removed from
service as a result of the inspection of the
HPT inner stationary seal required by
paragraph (g)(2) of this AD in which there
was a finding of honeycomb separation.
(i) No Reporting Requirement
The reporting requirements contained
within the SBs referenced in paragraph (g) of
this AD are not required by this AD.
(j) Alternative Methods of Compliance
(AMOCs)
(1) The Manager, ECO 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 certification office,
send it to the attention of the person
identified in Related Information. You may
email your request to: ANE-AD-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.
(k) Related Information
For more information about this AD,
contact Christopher McGuire, Aviation Safety
Engineer, ECO Branch, FAA, 1200 District
Avenue, Burlington, MA 01803; phone: (781)
238–7120; fax: (781) 238–7199; email:
chris.mcguire@faa.gov.
(l) 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.
(i) CFM Service Bulletin CFM56–5B S/B
72–0952, Revision 01, dated January 15,
2020.
(ii) CFM Service Bulletin CFM56–7B S/B
72–1054, Revision 01, dated January 15,
2020.
(3) For CFM service information identified
in this AD, contact CFM International Inc.,
Aviation Operations Center, 1 Neumann
Way, M/D Room 285, Cincinnati, OH 45125;
phone: (877) 432–3272; fax: (877) 432–3329;
email: aviation.fleetsupport@ge.com.
(4) You may view this service information
at FAA, Airworthiness Products Section,
Operational Safety Branch, 1200 District
Avenue, Burlington, MA 01803. For
information on the availability of this
material at the FAA, call (781) 238–7759.
(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,
PO 00000
Frm 00008
Fmt 4700
Sfmt 4700
email: fedreg.legal@nara.gov, or go to:
https://www.archives.gov/federal-register/cfr/
ibr-locations.html.
Issued on April 29, 2021.
Lance T. Gant,
Director, Compliance & Airworthiness
Division, Aircraft Certification Service.
[FR Doc. 2021–10607 Filed 5–19–21; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2021–0143; Product
Identifier 2019–SW–024–AD; Amendment
39–21547; AD 2021–10–14]
RIN 2120–AA64
Airworthiness Directives; Airbus
Helicopters Deutschland GmbH
Helicopters
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule.
AGENCY:
The FAA is adopting a new
airworthiness directive (AD) for certain
Airbus Helicopters Deutschland GmbH
Model BO–105A, BO–105C, BO–105S,
and BO–105LS A–3 helicopters. This
AD was prompted by the FAA’s
determination that aging of the
elastomeric material in a tension torsion
strap (TT-strap) could affect the
structural characteristics of the TTstrap. This AD requires replacement of
certain TT-straps with serviceable parts
and implementation of a new storage
life limit for TT-straps, as specified in
a European Aviation Safety Agency
(now European Union Aviation Safety
Agency) (EASA) AD, which is
incorporated by reference. The FAA is
issuing this AD to address the unsafe
condition on these products.
DATES: This AD is effective June 24,
2021.
The Director of the Federal Register
approved the incorporation by reference
of a certain publication listed in this AD
as of June 24, 2021.
ADDRESSES: For material incorporated
by reference (IBR) in this AD, contact
the EASA, Konrad-Adenauer-Ufer 3,
50668 Cologne, Germany; telephone +49
221 8999 000; email ADs@
easa.europa.eu; internet
www.easa.europa.eu. You may find this
material on the EASA website at https://
ad.easa.europa.eu. You may view this
material at the FAA, Office of the
Regional Counsel, Southwest Region,
10101 Hillwood Pkwy., Room 6N–321,
Fort Worth, TX 76177. For information
SUMMARY:
E:\FR\FM\20MYR1.SGM
20MYR1
Federal Register / Vol. 86, No. 96 / Thursday, May 20, 2021 / Rules and Regulations
on the availability of this material at the
FAA, call 817–222–5110. It is also
available in the AD docket on the
internet at https://www.regulations.gov
by searching for and locating Docket No.
FAA–2021–0143.
Examining the AD Docket
You may examine the AD docket on
the internet at https://
www.regulations.gov by searching for
and locating Docket No. FAA–2021–
0143; 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,
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:
Blaine Williams, Aviation Safety
Engineer, Los Angeles ACO Branch,
3960 Paramount Boulevard, Lakewood,
CA 90712 4137; telephone 562–627–
5371; email blaine.williams@faa.gov.
SUPPLEMENTARY INFORMATION:
Background
The EASA, which is the Technical
Agent for the Member States of the
European Union, has issued EASA AD
2019–0024, dated February 4, 2019
(EASA AD 2019–0024) (also referred to
as the Mandatory Continuing
Airworthiness Information, or the
MCAI), to correct an unsafe condition
for certain Airbus Helicopters
Deutschland GmbH Model BO–105A,
BO–105C, BO–105D, BO–105S, and BO–
105LS A–3 helicopters. Model BO–105D
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.
The FAA issued a notice of proposed
rulemaking (NPRM) to amend 14 CFR
part 39 by adding an AD that would
apply to certain Airbus Helicopters
Deutschland GmbH Model BO–105A,
BO–105C, BO–105S, and BO–105LS A–
3 helicopters. The NPRM published in
the Federal Register on March 12, 2021
(86 FR 14023). The NPRM was
prompted by the FAA’s determination
that aging of the elastomeric material in
a tension TT-strap could affect the
structural characteristics of the TTstrap. The NPRM proposed to require
replacement of certain TT-straps with
serviceable parts and implementation of
a new storage life limit for TT-straps, as
specified in an EASA AD.
The FAA is issuing this AD to address
aging of the elastomeric material in a
TT-strap, which could lead to premature
failure of a TT-strap, resulting in loss of
control of the helicopter. See the MCAI
for additional background information.
Discussion of Final Airworthiness
Directive
Comments
The FAA gave the public the
opportunity to participate in developing
this final rule. The FAA received no
comments on the NPRM or on the
determination of the cost to the public.
Conclusion
The FAA reviewed the relevant data
and determined that air safety and the
public interest require adopting this
final rule as proposed, except for minor
editorial changes. The FAA has
determined that these minor changes:
• Are consistent with the intent that
was proposed in the NPRM for
addressing the unsafe condition; and
• Do not add any additional burden
upon the public than was already
proposed in the NPRM.
Related Service Information Under 1
CFR Part 51
EASA AD 2019–0024 specifies
procedures for replacing certain TTstraps with serviceable parts and
27269
requires a storage life limit for TTstraps. This material is reasonably
available because the interested parties
have access to it through their normal
course of business or by the means
identified in the ADDRESSES section.
Differences Between This AD and the
MCAI
Although EASA AD 2019–0024 does
not specify a life limit for the Lord TTStraps part number (P/N) J17322–1 and
P/N 117–14111, this AD does specify a
life limit for those parts.
Where EASA AD 2019–0024 specifies
that installation of a Lord TT-Strap is
allowed provided the first flight of that
helicopter after that installation is
accomplished before the storage life of
that Lord TT-Strap exceeds 5 years, for
this AD, the installation of a Lord TTStrap is allowed provided the first flight
of that helicopter after that installation
is accomplished before 5 years since the
TT-strap’s date of manufacture.
Where EASA AD 2019–0024 defines
‘‘serviceable part’’ as a Lord TT-Strap
having a storage life not exceeding 5
years, for this AD, a serviceable part is
Lord TT-straps P/N J17322–1 and P/N
117–14111 having less than 5 years
since that TT-strap’s date of
manufacture.
Where EASA AD 2019–0024 specifies
that the ‘‘cure date’’ of a TT-Strap can
be determined using the information
provided in the applicable service
information specified in EASA AD
2019–0024, or contacting Airbus
Helicopters for applicable instructions,
for this AD, the option of contacting
Airbus Helicopters is not required.
Costs of Compliance
The FAA estimates that this AD
affects 61 helicopters of U.S. registry.
The FAA estimates the following costs
to comply with this AD:
ESTIMATED COSTS FOR REQUIRED ACTIONS
Labor cost
Parts cost
Cost per product
4 work-hours × $85 per hour = $340 ..............................
Up to $4,800 ......................
Up to $5,140 ......................
According to the manufacturer, some
or all of the costs of this AD may be
covered under warranty, thereby
reducing the cost impact on affected
operators. The FAA does not control
warranty coverage for affected operators.
As a result, the FAA has included all
known costs in the cost estimate.
VerDate Sep<11>2014
16:06 May 19, 2021
Jkt 253001
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.
PO 00000
Frm 00009
Fmt 4700
Sfmt 4700
Cost on U.S.
operators
Up to $313,540.
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
E:\FR\FM\20MYR1.SGM
20MYR1
27270
Federal Register / Vol. 86, No. 96 / Thursday, May 20, 2021 / Rules and Regulations
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
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 adding
the following new airworthiness
directive:
■
2021–10–14 Airbus Helicopters
Deutschland GmbH: Amendment 39–
21547; Docket No. FAA–2021–0143;
Product Identifier 2019–SW–024–AD.
(a) Effective Date
This airworthiness directive (AD) is
effective June 24, 2021.
(b) Affected ADs
This AD affects AD 2016–25–14,
Amendment 39–18740 (81 FR 94944,
December 27, 2016) (AD 2016–25–14).
(c) Applicability
This AD applies to Airbus Helicopters
Deutschland GmbH Model BO–105A, BO–
105C, BO–105S, and BO–105LS A–3
helicopters, certificated in any category,
equipped with a tension torsion strap (TT-
VerDate Sep<11>2014
16:06 May 19, 2021
Jkt 253001
strap) as identified in European Aviation
Safety Agency (now European Union
Aviation Safety Agency) (EASA) AD 2019–
0024, dated February 4, 2019 (EASA AD
2019–0024).
(d) Subject
Joint Aircraft System Component (JASC)
Code 6200, Main Rotor System.
(e) Reason
This AD was prompted by the FAA’s
determination that aging of the elastomeric
material in a TT-strap could affect the
structural characteristics of the TT-strap. The
FAA is issuing this AD to address aging of
the elastomeric material in a TT-strap, which
could lead to premature failure of a TT-strap,
resulting in loss of control of the helicopter.
(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
(g) Requirements
Except as specified in paragraph (h) of this
AD: Comply with all required actions and
compliance times specified in, and in
accordance with, EASA AD 2019–0024.
(h) Exceptions to EASA AD 2019–0024
(1) Where EASA AD 2019–0024 refers to its
effective date, this AD requires using the
effective date of this AD.
(2) The ‘‘Remarks’’ section of EASA AD
2019–0024 does not apply to this AD.
(3) Where EASA AD 2019–0024 and the
service information referenced in EASA AD
2019–0024 specify contacting Airbus
Helicopters Deutschland if the storage time
for a TT-strap is equal to or greater than 5
years, this AD requires repair using a method
approved by the Manager, International
Validation Branch, FAA. For a repair method
to be approved by the Manager, International
Validation Branch, as required by this
paragraph, the Manager’s approval letter
must specifically refer to this AD.
(4) Although the service information
referenced in EASA AD 2019–0024 specifies
to scrap certain parts, this AD requires
removing those parts from service instead.
(5) Where paragraph (1) of EASA AD 2019–
0024 specifies to replace each Lord TT-Strap
and Bendix TT-Strap ‘‘in accordance with the
instructions of the applicable ASB,’’ the
replacement must be done using FAAapproved procedures.
(6) Where EASA AD 2019–0024 refers to
the airworthiness limitations items of the
airworthiness limitations section of the
aircraft maintenance manual (AMM) for the
definition of service life limit (SLL), this AD
requires using the life limits specified in
paragraphs (h)(6)(i) through (iii) of this AD,
as applicable:
(i) For Bendix TT-Strap part number (P/N)
2604067 and P/N 117–14110: Before 10 years
or 40,000 flight cycles on the part, whichever
occurs first.
(ii) For Bendix TT-Strap P/N 2602559 and
P/N 2606576: Before 10 years, 2,400 hours
time-in-service, or 40,000 flight cycles on the
part, whichever occurs first.
(iii) For Lord TT-Strap P/N J17322–1 and
P/N 117–14111: Before 12 years or 40,000
PO 00000
Frm 00010
Fmt 4700
Sfmt 4700
flight cycles on the part, whichever occurs
first.
(7) Where paragraph (3) of EASA AD 2019–
0024 specifies that installation of a Lord TTStrap is allowed provided the first flight of
that helicopter after that installation is
accomplished before the storage life of that
Lord TT-Strap exceeds 5 years, for this AD,
the installation of a Lord TT-Strap is allowed
provided the first flight of that helicopter
after that installation is accomplished before
5 years since the TT-strap’s date of
manufacture.
(8) Where EASA AD 2019–0024 defines
‘‘serviceable part’’ as a Lord TT-Strap having
a storage life not exceeding 5 years, for this
AD, a serviceable part is Lord TT-straps P/
N J17322–1 and P/N 117–14111 having less
than 5 years since that TT-strap’s date of
manufacture.
(9) Where EASA AD 2019–0024 specifies
that the ‘‘cure date’’ of a TT-Strap can be
determined using the information provided
in the applicable service information
specified in EASA AD 2019–0024, or
contacting Airbus Helicopters for applicable
instructions, for this AD, the option of
contacting Airbus Helicopters is not required.
(i) Repetitive Replacement
After accomplishing the replacement
specified in paragraph (1) of EASA AD 2019–
0024, thereafter, replace the Lord TT-straps
P/N J17322–1 and P/N 117–14111, at
intervals not to exceed: Before 12 years or
40,000 flight cycles on the part, whichever
occurs first.
(j) Terminating Action for AD 2016–25–14
For Model B0–105LS A–3 helicopters:
After accomplishing the replacement
specified in paragraph (1) of EASA AD 2019–
0024 all of the actions required by AD 2016–
15–14 are terminated for that helicopter only.
(k) Special Flight Permit
Special flight permits, as described in 14
CFR 21.197 and 21.199, are not allowed.
(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) 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
For more information about this AD,
contact Blaine Williams, Aviation Safety
Engineer, Los Angeles ACO Branch, 3960
Paramount Boulevard, Lakewood, CA 90712
4137; telephone 562–627–5371; email
blaine.williams@faa.gov.
E:\FR\FM\20MYR1.SGM
20MYR1
Federal Register / Vol. 86, No. 96 / Thursday, May 20, 2021 / Rules and Regulations
(n) 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 this AD specifies otherwise.
(i) European Aviation Safety Agency
(EASA) AD 2019–0024, dated February 4,
2019.
(ii) [Reserved]
(3) For EASA AD 2019–0024, contact the
EASA, Konrad-Adenauer-Ufer 3, 50668
Cologne, Germany; telephone +49 221 8999
000; email ADs@easa.europa.eu; Internet
www.easa.europa.eu. You may find this
EASA AD on the EASA website at https://
ad.easa.europa.eu.
(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. This
material may be found in the AD docket on
the internet at https://www.regulations.gov
by searching for and locating Docket No.
FAA–2021–0143.
(5) You may view this material that is
incorporated by reference at the National
Archives and Records Administration
(NARA). For information on the availability
of this material at NARA, email fedreg.legal@
nara.gov, or go to https://www.archives.gov/
federal-register/cfr/ibr-locations.html.
Issued on April 30, 2021.
Lance T. Gant,
Director, Compliance & Airworthiness
Division, Aircraft Certification Service.
[FR Doc. 2021–10605 Filed 5–19–21; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2021–0105; Project
Identifier MCAI–2020–01422–R; Amendment
39–21543; AD 2021–10–10]
RIN 2120–AA64
Airworthiness Directives; Airbus
Helicopters
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule.
AGENCY:
The FAA is adopting a new
airworthiness directive (AD) for all
Airbus Helicopters Model SA330J
helicopters. This AD was prompted by
the failure of a second stage planet gear
installed in the main gearbox (MGB).
This AD requires repetitively inspecting
the MGB particle detector and the MGB
bottom housing (oil sump) for metal
particles, analyzing any metal particles
SUMMARY:
VerDate Sep<11>2014
16:06 May 19, 2021
Jkt 253001
27271
that are found, and replacement of the
MGB if necessary, as specified in a
European Aviation Safety Agency (now
European Union Aviation Safety
Agency) (EASA) AD, which is
incorporated by reference. The FAA is
issuing this AD to address the unsafe
condition on these products.
DATES: This AD is effective June 24,
2021.
The Director of the Federal Register
approved the incorporation by reference
of a certain publication listed in this AD
as of June 24, 2021.
ADDRESSES: For material incorporated
by reference (IBR) in this AD, contact
the EASA, Konrad-Adenauer-Ufer 3,
50668 Cologne, Germany; phone: +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
material at the FAA, Office of the
Regional Counsel, Southwest Region,
10101 Hillwood Pkwy., Room 6N–321,
Fort Worth, TX 76177. For information
on the availability of this material at the
FAA, call 817–222–5110. It is also
available in the AD docket on the
internet at https://www.regulations.gov
by searching for and locating Docket No.
FAA–2021–0105.
for all Airbus Helicopters Model SA330J
helicopters.
The FAA issued a notice of proposed
rulemaking (NPRM) to amend 14 CFR
part 39 by adding an AD that would
apply to all Airbus Helicopters Model
SA330J helicopters. The NPRM
published in the Federal Register on
March 2, 2021 (86 FR 12127). The
NPRM was prompted by the failure of
a second stage planet gear installed in
the MGB. The NPRM proposed to
require repetitively inspecting the MGB
particle detector and the MGB bottom
housing (oil sump) for metal particles,
analyzing any metal particles that are
found, and replacement of the MGB if
necessary, as specified in an EASA AD.
The FAA is issuing this AD to address
failure of an MGB second stage planet
gear, which could result in failure of the
MGB and subsequent loss of control of
the helicopter. See the MCAI for
additional background information.
Examining the AD Docket
Conclusion
You may examine the AD docket on
the internet at https://
www.regulations.gov by searching for
and locating Docket No. FAA–2021–
0105; 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,
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:
Mahmood G. Shah, Aviation Safety
Engineer, Fort Worth ACO Branch,
FAA, 10101 Hillwood Pkwy., Fort
Worth, TX 76177; phone: 817–222–
5538; email: mahmood.g.shah@faa.gov.
SUPPLEMENTARY INFORMATION:
The FAA reviewed the relevant data
and determined that air safety and the
public interest require adopting this
final rule as proposed, except for minor
editorial changes. The FAA has
determined that these minor changes:
• Are consistent with the intent that
was proposed in the NPRM for
addressing the unsafe condition; and
• Do not add any additional burden
upon the public than was already
proposed in the NPRM.
Background
The EASA, which is the Technical
Agent for the Member States of the
European Union, has issued EASA AD
2018–0272, dated December 13, 2018
(EASA AD 2018–0272) (also referred to
as the Mandatory Continuing
Airworthiness Information, or the
MCAI), to correct an unsafe condition
PO 00000
Frm 00011
Fmt 4700
Sfmt 4700
Discussion of Final Airworthiness
Directive
Comments
The FAA gave the public the
opportunity to participate in developing
this final rule. The FAA received no
comments on the NPRM or on the
determination of the cost to the public.
Related Service Information Under 1
CFR Part 51
EASA AD 2018–0272 specifies
procedures for repetitively inspecting
the MGB particle detector and the MGB
bottom housing (oil sump) for metal
particles, analyzing any metal particles
that are found, and replacement of the
MGB if necessary. This material is
reasonably available because the
interested parties have access to it
through their normal course of business
or by the means identified in the
ADDRESSES section.
Interim Action
The FAA considers this AD interim
action. If final action is later identified,
the FAA might consider further
rulemaking then.
E:\FR\FM\20MYR1.SGM
20MYR1
]]>Agencies
[Federal Register Volume 86, Number 96 (Thursday, May 20, 2021)]
[Rules and Regulations]
[Pages 27268-27271]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2021-10605]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2021-0143; Product Identifier 2019-SW-024-AD; Amendment
39-21547; AD 2021-10-14]
RIN 2120-AA64
Airworthiness Directives; Airbus Helicopters Deutschland GmbH
Helicopters
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Final rule.
-----------------------------------------------------------------------
SUMMARY: The FAA is adopting a new airworthiness directive (AD) for
certain Airbus Helicopters Deutschland GmbH Model BO-105A, BO-105C, BO-
105S, and BO-105LS A-3 helicopters. This AD was prompted by the FAA's
determination that aging of the elastomeric material in a tension
torsion strap (TT-strap) could affect the structural characteristics of
the TT-strap. This AD requires replacement of certain TT-straps with
serviceable parts and implementation of a new storage life limit for
TT-straps, as specified in a European Aviation Safety Agency (now
European Union Aviation Safety Agency) (EASA) AD, which is incorporated
by reference. The FAA is issuing this AD to address the unsafe
condition on these products.
DATES: This AD is effective June 24, 2021.
The Director of the Federal Register approved the incorporation by
reference of a certain publication listed in this AD as of June 24,
2021.
ADDRESSES: For material incorporated by reference (IBR) in this AD,
contact the EASA, Konrad-Adenauer-Ufer 3, 50668 Cologne, Germany;
telephone +49 221 8999 000; email [email protected]; internet
www.easa.europa.eu. You may find this material on the EASA website at
https://ad.easa.europa.eu. You may view this material at the FAA,
Office of the Regional Counsel, Southwest Region, 10101 Hillwood Pkwy.,
Room 6N-321, Fort Worth, TX 76177. For information
[[Page 27269]]
on the availability of this material at the FAA, call 817-222-5110. It
is also available in the AD docket on the internet at https://www.regulations.gov by searching for and locating Docket No. FAA-2021-
0143.
Examining the AD Docket
You may examine the AD docket on the internet at https://www.regulations.gov by searching for and locating Docket No. FAA-2021-
0143; 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, 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: Blaine Williams, Aviation Safety
Engineer, Los Angeles ACO Branch, 3960 Paramount Boulevard, Lakewood,
CA 90712 4137; telephone 562-627-5371; email [email protected].
SUPPLEMENTARY INFORMATION:
Background
The EASA, which is the Technical Agent for the Member States of the
European Union, has issued EASA AD 2019-0024, dated February 4, 2019
(EASA AD 2019-0024) (also referred to as the Mandatory Continuing
Airworthiness Information, or the MCAI), to correct an unsafe condition
for certain Airbus Helicopters Deutschland GmbH Model BO-105A, BO-105C,
BO-105D, BO-105S, and BO-105LS A-3 helicopters. Model BO-105D
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.
The FAA issued a notice of proposed rulemaking (NPRM) to amend 14
CFR part 39 by adding an AD that would apply to certain Airbus
Helicopters Deutschland GmbH Model BO-105A, BO-105C, BO-105S, and BO-
105LS A-3 helicopters. The NPRM published in the Federal Register on
March 12, 2021 (86 FR 14023). The NPRM was prompted by the FAA's
determination that aging of the elastomeric material in a tension TT-
strap could affect the structural characteristics of the TT-strap. The
NPRM proposed to require replacement of certain TT-straps with
serviceable parts and implementation of a new storage life limit for
TT-straps, as specified in an EASA AD.
The FAA is issuing this AD to address aging of the elastomeric
material in a TT-strap, which could lead to premature failure of a TT-
strap, resulting in loss of control of the helicopter. See the MCAI for
additional background information.
Discussion of Final Airworthiness Directive
Comments
The FAA gave the public the opportunity to participate in
developing this final rule. The FAA received no comments on the NPRM or
on the determination of the cost to the public.
Conclusion
The FAA reviewed the relevant data and determined that air safety
and the public interest require adopting this final rule as proposed,
except for minor editorial changes. The FAA has determined that these
minor changes:
Are consistent with the intent that was proposed in the
NPRM for addressing the unsafe condition; and
Do not add any additional burden upon the public than was
already proposed in the NPRM.
Related Service Information Under 1 CFR Part 51
EASA AD 2019-0024 specifies procedures for replacing certain TT-
straps with serviceable parts and requires a storage life limit for TT-
straps. This material is reasonably available because the interested
parties have access to it through their normal course of business or by
the means identified in the ADDRESSES section.
Differences Between This AD and the MCAI
Although EASA AD 2019-0024 does not specify a life limit for the
Lord TT-Straps part number (P/N) J17322-1 and P/N 117-14111, this AD
does specify a life limit for those parts.
Where EASA AD 2019-0024 specifies that installation of a Lord TT-
Strap is allowed provided the first flight of that helicopter after
that installation is accomplished before the storage life of that Lord
TT-Strap exceeds 5 years, for this AD, the installation of a Lord TT-
Strap is allowed provided the first flight of that helicopter after
that installation is accomplished before 5 years since the TT-strap's
date of manufacture.
Where EASA AD 2019-0024 defines ``serviceable part'' as a Lord TT-
Strap having a storage life not exceeding 5 years, for this AD, a
serviceable part is Lord TT-straps P/N J17322-1 and P/N 117-14111
having less than 5 years since that TT-strap's date of manufacture.
Where EASA AD 2019-0024 specifies that the ``cure date'' of a TT-
Strap can be determined using the information provided in the
applicable service information specified in EASA AD 2019-0024, or
contacting Airbus Helicopters for applicable instructions, for this AD,
the option of contacting Airbus Helicopters is not required.
Costs of Compliance
The FAA estimates that this AD affects 61 helicopters of U.S.
registry. The FAA estimates the following costs to comply with this AD:
Estimated Costs for Required Actions
----------------------------------------------------------------------------------------------------------------
Labor cost Parts cost Cost per product Cost on U.S. operators
----------------------------------------------------------------------------------------------------------------
4 work-hours x $85 per hour = $340... Up to $4,800........... Up to $5,140........... Up to $313,540.
----------------------------------------------------------------------------------------------------------------
According to the manufacturer, some or all of the costs of this AD
may be covered under warranty, thereby reducing the cost impact on
affected operators. The FAA does not control warranty coverage for
affected operators. As a result, the FAA has included all known costs
in the cost estimate.
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
[[Page 27270]]
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 adding the following new airworthiness
directive:
2021-10-14 Airbus Helicopters Deutschland GmbH: Amendment 39-21547;
Docket No. FAA-2021-0143; Product Identifier 2019-SW-024-AD.
(a) Effective Date
This airworthiness directive (AD) is effective June 24, 2021.
(b) Affected ADs
This AD affects AD 2016-25-14, Amendment 39-18740 (81 FR 94944,
December 27, 2016) (AD 2016-25-14).
(c) Applicability
This AD applies to Airbus Helicopters Deutschland GmbH Model BO-
105A, BO-105C, BO-105S, and BO-105LS A-3 helicopters, certificated
in any category, equipped with a tension torsion strap (TT-strap) as
identified in European Aviation Safety Agency (now European Union
Aviation Safety Agency) (EASA) AD 2019-0024, dated February 4, 2019
(EASA AD 2019-0024).
(d) Subject
Joint Aircraft System Component (JASC) Code 6200, Main Rotor
System.
(e) Reason
This AD was prompted by the FAA's determination that aging of
the elastomeric material in a TT-strap could affect the structural
characteristics of the TT-strap. The FAA is issuing this AD to
address aging of the elastomeric material in a TT-strap, which could
lead to premature failure of a TT-strap, resulting in loss of
control of the helicopter.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) Requirements
Except as specified in paragraph (h) of this AD: Comply with all
required actions and compliance times specified in, and in
accordance with, EASA AD 2019-0024.
(h) Exceptions to EASA AD 2019-0024
(1) Where EASA AD 2019-0024 refers to its effective date, this
AD requires using the effective date of this AD.
(2) The ``Remarks'' section of EASA AD 2019-0024 does not apply
to this AD.
(3) Where EASA AD 2019-0024 and the service information
referenced in EASA AD 2019-0024 specify contacting Airbus
Helicopters Deutschland if the storage time for a TT-strap is equal
to or greater than 5 years, this AD requires repair using a method
approved by the Manager, International Validation Branch, FAA. For a
repair method to be approved by the Manager, International
Validation Branch, as required by this paragraph, the Manager's
approval letter must specifically refer to this AD.
(4) Although the service information referenced in EASA AD 2019-
0024 specifies to scrap certain parts, this AD requires removing
those parts from service instead.
(5) Where paragraph (1) of EASA AD 2019-0024 specifies to
replace each Lord TT-Strap and Bendix TT-Strap ``in accordance with
the instructions of the applicable ASB,'' the replacement must be
done using FAA-approved procedures.
(6) Where EASA AD 2019-0024 refers to the airworthiness
limitations items of the airworthiness limitations section of the
aircraft maintenance manual (AMM) for the definition of service life
limit (SLL), this AD requires using the life limits specified in
paragraphs (h)(6)(i) through (iii) of this AD, as applicable:
(i) For Bendix TT-Strap part number (P/N) 2604067 and P/N 117-
14110: Before 10 years or 40,000 flight cycles on the part,
whichever occurs first.
(ii) For Bendix TT-Strap P/N 2602559 and P/N 2606576: Before 10
years, 2,400 hours time-in-service, or 40,000 flight cycles on the
part, whichever occurs first.
(iii) For Lord TT-Strap P/N J17322-1 and P/N 117-14111: Before
12 years or 40,000 flight cycles on the part, whichever occurs
first.
(7) Where paragraph (3) of EASA AD 2019-0024 specifies that
installation of a Lord TT-Strap is allowed provided the first flight
of that helicopter after that installation is accomplished before
the storage life of that Lord TT-Strap exceeds 5 years, for this AD,
the installation of a Lord TT-Strap is allowed provided the first
flight of that helicopter after that installation is accomplished
before 5 years since the TT-strap's date of manufacture.
(8) Where EASA AD 2019-0024 defines ``serviceable part'' as a
Lord TT-Strap having a storage life not exceeding 5 years, for this
AD, a serviceable part is Lord TT-straps P/N J17322-1 and P/N 117-
14111 having less than 5 years since that TT-strap's date of
manufacture.
(9) Where EASA AD 2019-0024 specifies that the ``cure date'' of
a TT-Strap can be determined using the information provided in the
applicable service information specified in EASA AD 2019-0024, or
contacting Airbus Helicopters for applicable instructions, for this
AD, the option of contacting Airbus Helicopters is not required.
(i) Repetitive Replacement
After accomplishing the replacement specified in paragraph (1)
of EASA AD 2019-0024, thereafter, replace the Lord TT-straps P/N
J17322-1 and P/N 117-14111, at intervals not to exceed: Before 12
years or 40,000 flight cycles on the part, whichever occurs first.
(j) Terminating Action for AD 2016-25-14
For Model B0-105LS A-3 helicopters: After accomplishing the
replacement specified in paragraph (1) of EASA AD 2019-0024 all of
the actions required by AD 2016-15-14 are terminated for that
helicopter only.
(k) Special Flight Permit
Special flight permits, as described in 14 CFR 21.197 and
21.199, are not allowed.
(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) 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
For more information about this AD, contact Blaine Williams,
Aviation Safety Engineer, Los Angeles ACO Branch, 3960 Paramount
Boulevard, Lakewood, CA 90712 4137; telephone 562-627-5371; email
[email protected].
[[Page 27271]]
(n) 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 this AD specifies otherwise.
(i) European Aviation Safety Agency (EASA) AD 2019-0024, dated
February 4, 2019.
(ii) [Reserved]
(3) For EASA AD 2019-0024, contact the EASA, Konrad-Adenauer-
Ufer 3, 50668 Cologne, Germany; telephone +49 221 8999 000; email
[email protected]; Internet www.easa.europa.eu. You may find this
EASA AD on the EASA website at https://ad.easa.europa.eu.
(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. This material may be
found in the AD docket on the internet at https://www.regulations.gov by searching for and locating Docket No. FAA-
2021-0143.
(5) You may view this material 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 April 30, 2021.
Lance T. Gant,
Director, Compliance & Airworthiness Division, Aircraft Certification
Service.
[FR Doc. 2021-10605 Filed 5-19-21; 8:45 am]
BILLING CODE 4910-13-P
