Airworthiness Directives; Airbus Helicopters Deutschland GmbH Helicopters, 10449-10451 [2021-01848]
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Federal Register / Vol. 86, No. 33 / Monday, February 22, 2021 / Rules and Regulations
(1) Alternative Methods of Compliance
(AMOCs): The Manager, Large Aircraft
Section, 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 responsible Flight
Standards Office, as appropriate. If sending
information directly to the Large Aircraft
Section, International Validation Branch,
send it to the attention of the person
identified in paragraph (j) of this AD.
Information may be emailed to: 9-AVS-AIR730-AMOC@faa.gov. Before using any
approved AMOC, notify your appropriate
principal inspector, or lacking a principal
inspector, the manager of the responsible
Flight Standards Office.
(2) Contacting the Manufacturer: For any
requirement in this AD to obtain instructions
from a manufacturer, the instructions must
be accomplished using a method approved
by the Manager, Large Aircraft Section,
International Validation Branch, FAA; or
EASA; or Saab AB, Support and Services’
EASA Design Organization Approval (DOA).
If approved by the DOA, the approval must
include the DOA-authorized signature.
(j) Related Information
For more information about this AD,
contact Shahram Daneshmandi, Aerospace
Engineer, Large Aircraft Section,
International Validation Branch, FAA, 2200
South 216th St., Des Moines, WA 98198;
phone and fax: 206–231–3220; email:
shahram.daneshmandi@faa.gov.
tkelley on DSKBCP9HB2PROD with RULES
(k) 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 Union Aviation Safety Agency
(EASA) AD 2020–0137, dated June 18, 2020.
(ii) [Reserved]
(3) For EASA AD 2020–0137, 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
EASA AD on the EASA website at https://
ad.easa.europa.eu.
(4) You may view this material at the FAA,
Airworthiness Products Section, Operational
Safety Branch, 2200 South 216th St., Des
Moines, WA. For information on the
availability of this material at the FAA, call
206–231–3195. 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–2020–0855.
(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.
VerDate Sep<11>2014
16:23 Feb 19, 2021
Jkt 253001
Issued on January 4, 2021.
Lance T. Gant,
Director, Compliance & Airworthiness
Division, Aircraft Certification Service.
[FR Doc. 2021–01824 Filed 2–19–21; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2020–1037; Project
Identifier 2019–SW–077–AD; Amendment
39–21407; AD 2021–03–04]
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 EC135P1, EC135P2, EC135P2+,
EC135P3, EC135T1, EC135T2,
EC135T2+, and EC135T3 helicopters.
This AD requires removing certain
Titanium (Ti) bolts from service and
prohibits installing these Ti-bolts in a
critical area. This AD was prompted by
a report of a broken Ti-bolt. The actions
of this AD are intended to address an
unsafe condition on these products.
DATES: This AD is effective March 29,
2021.
SUMMARY:
For service information
identified in this final rule, contact
Airbus Helicopters, 2701 N Forum
Drive, Grand Prairie, TX 75052;
telephone 972–641–0000 or 800–232–
0323; fax 972–641–3775; or at https://
www.airbus.com/helicopters/services/
technical-support.html. You may view
the referenced service information at the
FAA, Office of the Regional Counsel,
Southwest Region, 10101 Hillwood
Pkwy., Room 6N–321, Fort Worth, TX
76177.
ADDRESSES:
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–2020–
1037; 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 AD, the
European Union Aviation Safety Agency
(EASA) AD, any comments received,
and other information. The street
address for Docket Operations is U.S.
PO 00000
Frm 00011
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10449
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:
Katherine Venegas, Aviation Safety
Engineer, Los Angeles ACO, FAA, 3960
Paramount Blvd., Lakewood, CA 90712;
telephone 562–627–5353; email
katherine.venegas@faa.gov.
SUPPLEMENTARY INFORMATION:
Discussion
The FAA issued a notice of proposed
rulemaking (NPRM) to amend 14 CFR
part 39 by adding an AD that would
apply to Airbus Helicopters
Deutschland GmbH Model EC135P1,
EC135P2, EC135P2+, EC135P3,
EC135T1, EC135T2, EC135T2+, and
EC135T3 helicopters with a Ti-bolt part
number (P/N) L535M2001203 marked
with manufacturer monogram ‘‘D’’ or
with an illegible manufacturer
monogram installed on the forward tail
rotor (T/R) drive shaft. The NPRM
published in the Federal Register on
November 30, 2020 (85 FR 76490). The
NPRM proposed to require removing
any affected Ti-bolt installed on the
forward T/R drive shaft from service
and prohibit installing an affected Tibolt on the forward T/R drive shaft of
any helicopter. The proposed
requirements were intended to prevent
failure of an affected Ti-bolt installed in
a critical location, possibly resulting in
reduced control of the helicopter.
The NPRM was prompted by EASA
AD No. 2019–0199, dated August 16,
2019, issued by EASA, which is the
Technical Agent for the Member States
of the European Union, to correct an
unsafe condition for Airbus Helicopters
Deutschland GmbH (AHD), formerly
Eurocopter Deutschland GmbH,
Eurocopter Espan˜a S.A., Model EC135
P1, EC135 P2, EC135 P2+, EC135 P3,
EC135 T1, EC135 T2, EC135 T2+, EC135
T3, EC635 P2+, EC635 P3, EC635 T1,
EC635 T2+, and EC635 T3 helicopters.
EASA advises of a report of a broken Tibolt. Subsequent investigation revealed
that an improper heat treatment process
was accomplished on a batch of Tibolts, which can lead to hydrogen
embrittlement. The investigation also
identified the critical location where
these Ti-bolts are installed on
helicopters. According to EASA, this
condition, if not detected and corrected,
could lead to failure of an affected Tibolt installed in a critical location,
possibly resulting in reduced control of
the helicopter. Accordingly, the EASA
AD requires a one-time inspection of Tibolt P/N L535M2001203 marked with
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Federal Register / Vol. 86, No. 33 / Monday, February 22, 2021 / Rules and Regulations
manufacturer monogram ‘‘D’’ or with an
illegible manufacturer monogram
installed on the forward T/R drive shaft
and, depending on the inspection
results, replacing the Ti-bolt. The EASA
AD also prohibits the (re)installation of
these Ti-bolts.
Comments
The FAA gave the public the
opportunity to participate in developing
this final rule, but the FAA did not
receive any comments on the NPRM or
on the determination of the cost to the
public.
FAA’s Determination
These helicopters have been approved
by EASA and are approved for operation
in the United States. Pursuant to the
FAA’s bilateral agreement with the
European Union, EASA has notified the
FAA of the unsafe condition described
in its AD. The FAA is issuing this AD
after evaluating all of the information
provided by EASA and determining the
unsafe condition exists and is likely to
exist or develop on other helicopters of
these same type designs and that air
safety and the public interest require
adopting the AD requirements as
proposed.
tkelley on DSKBCP9HB2PROD with RULES
Differences Between This AD and the
EASA AD
The EASA AD applies to Model
EC135 P1, EC135 P2, EC135 P2+, EC135
P3, EC135 T1, EC135 T2, EC135 T2+,
EC135 T3, EC635 P2+, EC635 P3, EC635
T1, EC635 T2+, and EC635 T3
helicopters and requires inspecting Tibolt P/N L535M2001203 marked with
manufacturer monogram ‘‘D’’ or with an
illegible manufacturer monogram
installed on the forward T/R drive shaft.
This AD applies to Model EC135P1,
EC135P2, EC135P2+, EC135P3,
EC135T1, EC135T2, EC135T2+, and
EC135T3 helicopters with a Ti-bolt P/N
L535M2001203 marked with
manufacturer monogram ‘‘D’’ or with an
illegible manufacturer monogram
installed on the forward T/R drive shaft
instead. This AD does not apply to
Model EC635 P2+, EC635 P3, EC635 T1,
EC635 T2+, or EC635 T3 helicopters
because these models are not FAA typecertificated. The EASA AD requires
discarding the affected Ti-bolts, whereas
this AD requires removing the affected
Ti-bolts from service instead.
Related Service Information
The FAA reviewed Airbus Helicopters
Alert Service Bulletin (ASB) No. EC135–
00A–001, Revision 1, dated September
2, 2019, for Airbus Helicopters
Deutschland GmbH Model EC135 T1,
T2, T2+, T3, P1, P2, P2+, P3, 635 T1,
VerDate Sep<11>2014
16:23 Feb 19, 2021
Jkt 253001
635 T2+, 635 T3, 635 P2+, and 635 P3
helicopters, and Airbus Helicopters ASB
No. EC135H–00A–001, Revision 1,
dated September 2, 2019, for Airbus
Helicopters Deutschland GmbH Model
EC135, T3H, P3H, 635 T3H, and 635
P3H helicopters. This service
information specifies inspecting the
forward T/R drive shaft, distance plate
of the 5B–0.50–2.50P–XN–1 antenna,
main rotor controls, FWD connection of
ball bearing control, and AFT
connection of ball bearing control and
yaw actuator for the installation of Tibolt P/N L535M2001203, EN3308–
040020F, L221M1040201, EN3740–
060020F, and EN3308–060020F, marked
with manufacturer monogram ‘‘D’’ or an
illegible manufacturer monogram. If a
specified Ti-bolt is installed, the service
information specifies replacing the Tibolt and discarding the removed Ti-bolt.
Costs of Compliance
The FAA estimates that this AD
affects 326 helicopters of U.S. Registry.
Labor rates are estimated at $85 per
work-hour. Based on these numbers, the
FAA estimates that operators may incur
the following costs in order to comply
with this AD.
Replacing a Ti-bolt takes about four
work-hours and parts cost about $82 for
an estimated cost of $422 per Ti-bolt.
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 helicopters 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
PO 00000
Frm 00012
Fmt 4700
Sfmt 4700
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.
Adoption of 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:
■
2021–03–04 Airbus Helicopters
Deutschland GmbH: Amendment 39–
21407; Docket No. FAA–2020–1037;
Project Identifier 2019–SW–077–AD.
(a) Applicability
This airworthiness directive (AD) applies
to Airbus Helicopters Deutschland GmbH
Model EC135P1, EC135P2, EC135P2+,
EC135P3, EC135T1, EC135T2, EC135T2+,
and EC135T3 helicopters, certificated in any
category, with a Titanium (Ti) bolt part
number L535M2001203 marked with
manufacturer monogram ‘‘D’’ or with an
illegible manufacturer monogram installed
on the forward tail rotor drive shaft.
Note 1 to paragraph (a): Helicopters with
an EC135P3H designation are Model
EC135P3 helicopters. Helicopters with an
EC135T3H designation are Model EC135T3
helicopters.
(b) Unsafe Condition
This AD defines the unsafe condition as
failure of an affected Ti-bolt installed in a
critical location, possibly resulting in
reduced control of the helicopter.
(c) Effective Date
This AD becomes effective March 29, 2021.
(d) Compliance
You are responsible for performing each
action required by this AD within the
specified compliance time unless it has
already been accomplished prior to that time.
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Federal Register / Vol. 86, No. 33 / Monday, February 22, 2021 / Rules and Regulations
(e) Required Actions
DEPARTMENT OF TRANSPORTATION
(1) Within 50 hours time-in-service or 3
months, whichever occurs first, remove any
Ti-bolt identified in paragraph (a) of this AD,
located on the forward tail rotor drive shaft,
from service.
(2) As of the effective date of this AD, do
not install a Ti-bolt identified in paragraph
(a) of this AD on the forward tail rotor drive
shaft of any helicopter.
14 CFR Part 39
[Docket No. FAA–2020–0849; Project
Identifier MCAI–2020–01036–A; Amendment
39–21374; AD 2020–26–19]
RIN 2120–AA64
(f) Alternative Methods of Compliance
(AMOCs)
Airworthiness Directives; Pilatus
Aircraft Ltd. Airplanes
(1) The Manager, Strategic Policy
Rotorcraft Section, FAA, may approve
AMOCs for this AD. Send your proposal to:
Manager, Strategic Policy Rotorcraft Section,
FAA, 10101 Hillwood Pkwy., Fort Worth, TX
76177; telephone 817–222–5110; email 9ASW-FTW-AMOC-Requests@faa.gov.
(2) For operations conducted under a 14
CFR part 119 operating certificate or under
14 CFR part 91, subpart K, the FAA suggests
that you notify your principal inspector, or
lacking a principal inspector, the manager of
the local flight standards district office or
certificate holding district office, before
operating any aircraft complying with this
AD through an AMOC.
AGENCY:
(g) Additional Information
(1) Airbus Helicopters Alert Service
Bulletin (ASB) No. EC135–00A–001 and ASB
No. EC135H–00A–001, each Revision 1 and
dated September 2, 2019, which are not
incorporated by reference, contain additional
information about the subject of this AD. For
service information identified in this AD,
contact Airbus Helicopters, 2701 N. Forum
Drive, Grand Prairie, TX 75052; telephone
972–641–0000 or 800–232–0323; fax 972–
641–3775; or at https://www.airbus.com/
helicopters/services/technical-support.html.
You may view a copy of the service
information at the FAA, Office of the
Regional Counsel, Southwest Region, 10101
Hillwood Pkwy, Room 6N–321, Fort Worth,
TX 76177.
(2) The subject of this AD is addressed in
European Union Aviation Safety Agency
(EASA) AD No. 2019–0199, dated August 16,
2019. You may view the EASA AD on the
internet at https://www.regulations.gov in
Docket No. FAA–2020–1037.
(h) Subject
Joint Aircraft Service Component (JASC)
Code: 1430, Fasteners; and 6510, Tail Rotor
Drive Shaft.
tkelley on DSKBCP9HB2PROD with RULES
Federal Aviation Administration
Issued on January 22, 2021.
Lance T. Gant,
Director, Compliance & Airworthiness
Division, Aircraft Certification Service.
[FR Doc. 2021–01848 Filed 2–19–21; 8:45 am]
BILLING CODE 4910–13–P
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule.
The FAA is adopting a new
airworthiness directive (AD) for all
Pilatus Aircraft Ltd. Model PC–7
airplanes. This AD results from
mandatory continuing airworthiness
information (MCAI) originated by an
aviation authority of another country to
identify and correct an unsafe condition
on an aviation product. This AD
requires revising the Airworthiness
Limitations section (ALS) of the existing
aircraft maintenance manual (AMM) to
introduce new mandatory repetitive
inspections for the flap pivot arm
assemblies and for certain wing angle
brackets, and to implement a change to
the Oxygen cylinder and pressure
reducer task item. The FAA is issuing
this AD to address the unsafe condition
on these products.
DATES: This AD is effective March 29,
2021.
The Director of the Federal Register
approved the incorporation by reference
of a certain publication listed in this AD
as of March 29, 2021.
ADDRESSES: For service information
identified in this final rule, contact
Pilatus Aircraft Ltd., CH–6371,
Customer Technical Support (MCC),
P.O. Box 992, CH–6371, Stans,
Switzerland; phone: +41 (0)41 619 67
74; fax: +41 (0)41 619 67; email:
techsupport@pilatus-aircraft.com;
website: https://www.pilatusaircraft.comen/. You may view this
service information at the FAA,
Airworthiness Products Section,
Operational Safety Branch, 901 Locust,
Kansas City, Missouri 64106. For
information on the availability of this
material at the FAA, call (816) 329–
4148. It is also available at https://
www.regulations.gov by searching for
and locating Docket No. FAA–2020–
0849.
SUMMARY:
Examining the AD Docket
You may examine the AD docket at
https://www.regulations.gov by
searching for and locating Docket No.
VerDate Sep<11>2014
16:23 Feb 19, 2021
Jkt 253001
PO 00000
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10451
FAA–2020–0849; 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 MCAI, 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:
Doug Rudolph, Aerospace Engineer,
FAA, General Aviation & Rotorcraft
Section, International Validation
Branch, 901 Locust, Room 301, Kansas
City, Missouri 64106; phone: (816) 329–
4059; fax: (816) 329–4090; email:
doug.rudolph@faa.gov.
SUPPLEMENTARY INFORMATION:
Background
The FAA issued a notice of proposed
rulemaking (NPRM) to amend 14 CFR
part 39 by adding an AD that would
apply to all Pilatus Aircraft Ltd. Model
PC–7 airplanes. The NPRM published in
the Federal Register on September 24,
2020 (85 FR 60097). The NPRM was
prompted by MCAI originated by the
Federal Office for Civil Aviation
(FOCA), which is the aviation authority
for Switzerland. FOCA has issued FOCA
AD HB–2020–007, dated July 23, 2020
(referred to after this as the MCAI), to
correct an unsafe condition with new
mandatory instructions for continued
airworthiness for all Pilatus Aircraft Ltd.
Model PC–7 airplanes. The MCAI states:
The airworthiness limitations and
certification maintenance instructions for
Pilatus PC–7 aeroplanes, which are approved
by FOCA, are currently defined and
published in the Pilatus PC–7 AMM Chapter
5. These instructions have been identified as
mandatory for continued airworthiness.
Failure to accomplish these instructions
could result in an unsafe condition
[discrepancies of life-limited and overhauled
components, which could result in reduced
structural integrity and system reliability of
the airplane].
Previously, FOCA issued AD HB–2019–004
(later corrected) to require implementation of
the maintenance tasks and airworthiness
limitations as specified in Pilatus PC–7 AMM
Document Number 01715, or Document
Number 02416, both at issue 44, as
applicable. [These tasks included the added
wing angle bracket at rib 23 repetitive
inspections.]
Since that AD was issued, Pilatus amended
the ALS, as defined in this AD, to introduce
new mandatory repetitive inspection for the
flap pivot arm assemblies and a change to the
Oxygen cylinder and pressure reducer task
(Chapter 35—Oxygen) to remove the
reference to the part numbers.
For the reason described above, this
[Swiss] AD retains the requirements of FOCA
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]]>Agencies
[Federal Register Volume 86, Number 33 (Monday, February 22, 2021)]
[Rules and Regulations]
[Pages 10449-10451]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2021-01848]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2020-1037; Project Identifier 2019-SW-077-AD; Amendment
39-21407; AD 2021-03-04]
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 EC135P1, EC135P2,
EC135P2+, EC135P3, EC135T1, EC135T2, EC135T2+, and EC135T3 helicopters.
This AD requires removing certain Titanium (Ti) bolts from service and
prohibits installing these Ti-bolts in a critical area. This AD was
prompted by a report of a broken Ti-bolt. The actions of this AD are
intended to address an unsafe condition on these products.
DATES: This AD is effective March 29, 2021.
ADDRESSES: For service information identified in this final rule,
contact Airbus Helicopters, 2701 N Forum Drive, Grand Prairie, TX
75052; telephone 972-641-0000 or 800-232-0323; fax 972-641-3775; or at
https://www.airbus.com/helicopters/services/technical-support.html. You
may view the referenced service information at the FAA, Office of the
Regional Counsel, Southwest Region, 10101 Hillwood Pkwy., Room 6N-321,
Fort Worth, TX 76177.
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-2020-
1037; 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 AD, the European Union Aviation Safety Agency (EASA) AD, any
comments received, and other information. The street 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: Katherine Venegas, Aviation Safety
Engineer, Los Angeles ACO, FAA, 3960 Paramount Blvd., Lakewood, CA
90712; telephone 562-627-5353; email [email protected].
SUPPLEMENTARY INFORMATION:
Discussion
The FAA issued a notice of proposed rulemaking (NPRM) to amend 14
CFR part 39 by adding an AD that would apply to Airbus Helicopters
Deutschland GmbH Model EC135P1, EC135P2, EC135P2+, EC135P3, EC135T1,
EC135T2, EC135T2+, and EC135T3 helicopters with a Ti-bolt part number
(P/N) L535M2001203 marked with manufacturer monogram ``D'' or with an
illegible manufacturer monogram installed on the forward tail rotor (T/
R) drive shaft. The NPRM published in the Federal Register on November
30, 2020 (85 FR 76490). The NPRM proposed to require removing any
affected Ti-bolt installed on the forward T/R drive shaft from service
and prohibit installing an affected Ti-bolt on the forward T/R drive
shaft of any helicopter. The proposed requirements were intended to
prevent failure of an affected Ti-bolt installed in a critical
location, possibly resulting in reduced control of the helicopter.
The NPRM was prompted by EASA AD No. 2019-0199, dated August 16,
2019, issued by EASA, which is the Technical Agent for the Member
States of the European Union, to correct an unsafe condition for Airbus
Helicopters Deutschland GmbH (AHD), formerly Eurocopter Deutschland
GmbH, Eurocopter Espa[ntilde]a S.A., Model EC135 P1, EC135 P2, EC135
P2+, EC135 P3, EC135 T1, EC135 T2, EC135 T2+, EC135 T3, EC635 P2+,
EC635 P3, EC635 T1, EC635 T2+, and EC635 T3 helicopters. EASA advises
of a report of a broken Ti-bolt. Subsequent investigation revealed that
an improper heat treatment process was accomplished on a batch of Ti-
bolts, which can lead to hydrogen embrittlement. The investigation also
identified the critical location where these Ti-bolts are installed on
helicopters. According to EASA, this condition, if not detected and
corrected, could lead to failure of an affected Ti-bolt installed in a
critical location, possibly resulting in reduced control of the
helicopter. Accordingly, the EASA AD requires a one-time inspection of
Ti-bolt P/N L535M2001203 marked with
[[Page 10450]]
manufacturer monogram ``D'' or with an illegible manufacturer monogram
installed on the forward T/R drive shaft and, depending on the
inspection results, replacing the Ti-bolt. The EASA AD also prohibits
the (re)installation of these Ti-bolts.
Comments
The FAA gave the public the opportunity to participate in
developing this final rule, but the FAA did not receive any comments on
the NPRM or on the determination of the cost to the public.
FAA's Determination
These helicopters have been approved by EASA and are approved for
operation in the United States. Pursuant to the FAA's bilateral
agreement with the European Union, EASA has notified the FAA of the
unsafe condition described in its AD. The FAA is issuing this AD after
evaluating all of the information provided by EASA and determining the
unsafe condition exists and is likely to exist or develop on other
helicopters of these same type designs and that air safety and the
public interest require adopting the AD requirements as proposed.
Differences Between This AD and the EASA AD
The EASA AD applies to Model EC135 P1, EC135 P2, EC135 P2+, EC135
P3, EC135 T1, EC135 T2, EC135 T2+, EC135 T3, EC635 P2+, EC635 P3, EC635
T1, EC635 T2+, and EC635 T3 helicopters and requires inspecting Ti-bolt
P/N L535M2001203 marked with manufacturer monogram ``D'' or with an
illegible manufacturer monogram installed on the forward T/R drive
shaft. This AD applies to Model EC135P1, EC135P2, EC135P2+, EC135P3,
EC135T1, EC135T2, EC135T2+, and EC135T3 helicopters with a Ti-bolt P/N
L535M2001203 marked with manufacturer monogram ``D'' or with an
illegible manufacturer monogram installed on the forward T/R drive
shaft instead. This AD does not apply to Model EC635 P2+, EC635 P3,
EC635 T1, EC635 T2+, or EC635 T3 helicopters because these models are
not FAA type-certificated. The EASA AD requires discarding the affected
Ti-bolts, whereas this AD requires removing the affected Ti-bolts from
service instead.
Related Service Information
The FAA reviewed Airbus Helicopters Alert Service Bulletin (ASB)
No. EC135-00A-001, Revision 1, dated September 2, 2019, for Airbus
Helicopters Deutschland GmbH Model EC135 T1, T2, T2+, T3, P1, P2, P2+,
P3, 635 T1, 635 T2+, 635 T3, 635 P2+, and 635 P3 helicopters, and
Airbus Helicopters ASB No. EC135H-00A-001, Revision 1, dated September
2, 2019, for Airbus Helicopters Deutschland GmbH Model EC135, T3H, P3H,
635 T3H, and 635 P3H helicopters. This service information specifies
inspecting the forward T/R drive shaft, distance plate of the 5B-0.50-
2.50P-XN-1 antenna, main rotor controls, FWD connection of ball bearing
control, and AFT connection of ball bearing control and yaw actuator
for the installation of Ti-bolt P/N L535M2001203, EN3308-040020F,
L221M1040201, EN3740-060020F, and EN3308-060020F, marked with
manufacturer monogram ``D'' or an illegible manufacturer monogram. If a
specified Ti-bolt is installed, the service information specifies
replacing the Ti-bolt and discarding the removed Ti-bolt.
Costs of Compliance
The FAA estimates that this AD affects 326 helicopters of U.S.
Registry. Labor rates are estimated at $85 per work-hour. Based on
these numbers, the FAA estimates that operators may incur the following
costs in order to comply with this AD.
Replacing a Ti-bolt takes about four work-hours and parts cost
about $82 for an estimated cost of $422 per Ti-bolt.
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 helicopters 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.
Adoption of 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:
2021-03-04 Airbus Helicopters Deutschland GmbH: Amendment 39-21407;
Docket No. FAA-2020-1037; Project Identifier 2019-SW-077-AD.
(a) Applicability
This airworthiness directive (AD) applies to Airbus Helicopters
Deutschland GmbH Model EC135P1, EC135P2, EC135P2+, EC135P3, EC135T1,
EC135T2, EC135T2+, and EC135T3 helicopters, certificated in any
category, with a Titanium (Ti) bolt part number L535M2001203 marked
with manufacturer monogram ``D'' or with an illegible manufacturer
monogram installed on the forward tail rotor drive shaft.
Note 1 to paragraph (a): Helicopters with an EC135P3H
designation are Model EC135P3 helicopters. Helicopters with an
EC135T3H designation are Model EC135T3 helicopters.
(b) Unsafe Condition
This AD defines the unsafe condition as failure of an affected
Ti-bolt installed in a critical location, possibly resulting in
reduced control of the helicopter.
(c) Effective Date
This AD becomes effective March 29, 2021.
(d) Compliance
You are responsible for performing each action required by this
AD within the specified compliance time unless it has already been
accomplished prior to that time.
[[Page 10451]]
(e) Required Actions
(1) Within 50 hours time-in-service or 3 months, whichever
occurs first, remove any Ti-bolt identified in paragraph (a) of this
AD, located on the forward tail rotor drive shaft, from service.
(2) As of the effective date of this AD, do not install a Ti-
bolt identified in paragraph (a) of this AD on the forward tail
rotor drive shaft of any helicopter.
(f) Alternative Methods of Compliance (AMOCs)
(1) The Manager, Strategic Policy Rotorcraft Section, FAA, may
approve AMOCs for this AD. Send your proposal to: Manager, Strategic
Policy Rotorcraft Section, FAA, 10101 Hillwood Pkwy., Fort Worth, TX
76177; telephone 817-222-5110; email [email protected].
(2) For operations conducted under a 14 CFR part 119 operating
certificate or under 14 CFR part 91, subpart K, the FAA suggests
that you notify your principal inspector, or lacking a principal
inspector, the manager of the local flight standards district office
or certificate holding district office, before operating any
aircraft complying with this AD through an AMOC.
(g) Additional Information
(1) Airbus Helicopters Alert Service Bulletin (ASB) No. EC135-
00A-001 and ASB No. EC135H-00A-001, each Revision 1 and dated
September 2, 2019, which are not incorporated by reference, contain
additional information about the subject of this AD. For service
information identified in this AD, contact Airbus Helicopters, 2701
N. Forum Drive, Grand Prairie, TX 75052; telephone 972-641-0000 or
800-232-0323; fax 972-641-3775; or at https://www.airbus.com/helicopters/services/technical-support.html. You may view a copy of
the service information at the FAA, Office of the Regional Counsel,
Southwest Region, 10101 Hillwood Pkwy, Room 6N-321, Fort Worth, TX
76177.
(2) The subject of this AD is addressed in European Union
Aviation Safety Agency (EASA) AD No. 2019-0199, dated August 16,
2019. You may view the EASA AD on the internet at https://www.regulations.gov in Docket No. FAA-2020-1037.
(h) Subject
Joint Aircraft Service Component (JASC) Code: 1430, Fasteners;
and 6510, Tail Rotor Drive Shaft.
Issued on January 22, 2021.
Lance T. Gant,
Director, Compliance & Airworthiness Division, Aircraft Certification
Service.
[FR Doc. 2021-01848 Filed 2-19-21; 8:45 am]
BILLING CODE 4910-13-P
