Airworthiness Directives; Airbus Helicopters, 14238-14241 [2021-05144]
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Federal Register / Vol. 86, No. 48 / Monday, March 15, 2021 / Rules and Regulations
airplane, as changed, continues to meet
the applicable provisions of the
regulations listed in Type Certificate No.
T00005NY, or the applicable regulations
in effect on the date of application for
the change, except for earlier
amendments as agreed upon by the
FAA.
If the Administrator finds that the
applicable airworthiness regulations
(e.g., 14 CFR part 25) do not contain
adequate or appropriate safety standards
for the Bombardier Model BD–100–
1A10 airplane because of a novel or
unusual design feature, special
conditions are prescribed under the
provisions of § 21.16.
Special conditions are initially
applicable to the model for which they
are issued. Should the applicant apply
for a supplemental type certificate to
modify any other model included on the
same type certificate to incorporate the
same novel or unusual design feature,
these special conditions would also
apply to the other model under § 21.101.
In addition to the applicable
airworthiness regulations and special
conditions, the Bombardier Model BD–
100–1A10 airplane must comply with
the fuel-vent and exhaust-emission
requirements of 14 CFR part 34, and the
noise-certification requirements of 14
CFR part 36.
The FAA issues special conditions, as
defined in 14 CFR 11.19, in accordance
with § 11.38, and they become part of
the type certification basis under
§ 21.101.
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Novel or Unusual Design Features
The Bombardier Model BD–100–1A10
airplane, as modified by Rockwell
Collins, will incorporate the following
novel or unusual design feature:
Installation of the Rockwell Collins
Pro Line Fusion System, which allows
connection to airplane electronic
systems and networks, and access from
aircraft external sources (e.g., operator
networks, wireless devices, internet
connectivity, service provider satellite
communications, electronic flight bags,
etc.) to the previously isolated airplane
electronic assets.
Discussion
The Bombardier Model BD–100–1A10
airplane architecture and network
configuration is novel or unusual for
commercial transport airplanes because
it may allow increased connectivity to
and access from external network
sources and airline operations and
maintenance networks to the airplane
control domain and airline information
services domain. The airplane control
domain and airline information-services
domain perform functions required for
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the safe operation and maintenance of
the airplane. Previously, these domains
had very limited connectivity with
external network sources. This data
network and design integration creates a
potential for unauthorized persons to
access the aircraft-control domain and
airline information-services domain,
and presents security vulnerabilities
related to the introduction of computer
viruses and worms, user errors, and
intentional sabotage of airplane
electronic assets (networks, systems,
and databases) critical to the safety and
maintenance of the airplane.
The existing FAA regulations did not
anticipate these networked airplane
system architectures. Furthermore, these
regulations and the current guidance
material do not address potential
security vulnerabilities, which could be
exploited by unauthorized access to
airplane networks, data buses, and
servers. Therefore, these special
conditions ensure that the security (i.e.,
confidentiality, integrity, and
availability) of airplane systems is not
compromised by unauthorized wired or
wireless electronic connections. This
includes ensuring that the security of
the airplane’s systems is not
compromised during maintenance of the
airplane’s electronic systems. These
special conditions also require the
applicant to provide appropriate
instructions to the operator to maintain
all electronic-system safeguards that
have been implemented as part of the
original network design so that this
feature does not allow or reintroduce
security threats.
These special conditions contain the
additional safety standards that the
Administrator considers necessary to
establish a level of safety equivalent to
that established by the existing
airworthiness standards.
Applicability
List of Subjects in 14 CFR Part 25
Aircraft, Aviation safety, Reporting
and recordkeeping requirements.
Authority Citation
The authority citation for these
special conditions is as follows:
Authority: 49 U.S.C. 106(f), 106(g), 40113,
44701, 44702, 44704.
The Special Conditions
■ Accordingly, pursuant to the
authority delegated to me by the
Administrator, the following special
conditions are issued as part of the type
certification basis for Bombardier Model
BD–100–1A10 airplanes, as modified by
Rockwell Collins, for airplane
electronic-system security protection
from unauthorized external access.
1. The applicant must ensure airplane
electronic-system security protection
from access by unauthorized sources
external to the airplane, including those
possibly caused by maintenance
activity.
2. The applicant must ensure that
electronic-system security threats are
identified and assessed, and that
effective electronic-system securityprotection strategies are implemented to
protect the airplane from all adverse
impacts on safety, functionality, and
continued airworthiness.
3. The applicant must establish
appropriate procedures to allow the
operator to ensure that continued
airworthiness of the airplane is
maintained, including all post-typecertification modifications that may
have an impact on the approved
electronic-system security safeguards.
Issued in Des Moines, Washington, on
February 9, 2021.
Suzanne Masterson,
Manager, Transport Airplane Strategic Policy
Section, Policy and Innovation Division,
Aircraft Certification Service.
[FR Doc. 2021–05294 Filed 3–12–21; 8:45 am]
As discussed above, these special
conditions are applicable to the
Bombardier Model BD–100–1A10
airplane. Should Rockwell Collins apply
at a later date for a supplemental type
certificate to modify any other model
included on Type Certificate No.
T00005NY to incorporate the same
novel or unusual design feature, these
special conditions would apply to that
model as well.
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2020–0916; Product
Identifier 2015–SW–055–AD; Amendment
39–21449; AD 2021–05–06]
Conclusion
RIN 2120–AA64
This action affects only a certain
novel or unusual design feature on one
model of airplane, as modified by
Rockwell Collins. It is not a rule of
general applicability and affects only
the applicant.
Airworthiness Directives; Airbus
Helicopters
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Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule.
AGENCY:
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Federal Register / Vol. 86, No. 48 / Monday, March 15, 2021 / Rules and Regulations
The FAA is adopting a new
airworthiness directive (AD) for Airbus
Helicopters Model AS332C, AS332C1,
AS332L, AS332L1, AS332L2, EC 155B,
EC155B1, EC225LP, and SA330J
helicopters. This AD requires inspecting
the snap fasteners on the windows. This
AD was prompted by incidents of
difficulty unbuttoning the extraction
tape on the windows. The actions of this
AD are intended to address an unsafe
condition on these products.
DATES: This AD is effective April 19,
2021.
The Director of the Federal Register
approved the incorporation by reference
of certain documents listed in this AD
as of April 19, 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. It is also available on the internet
at https://www.regulations.gov by
searching for and locating Docket No.
FAA–2020–0916.
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SUMMARY:
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–
0916; 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 Aviation Safety Agency (now
European Union Aviation Safety
Agency) (EASA) ADs, any service
information that is incorporated by
reference, 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:
David Hatfield, Aerospace Engineer,
Aircraft Systems Section, Technical
Innovation Policy Branch, Policy &
Innovation Division, FAA, 10101
Hillwood Pkwy., Fort Worth, TX 76177;
telephone (817) 222–5110; email
david.hatfield@faa.gov.
SUPPLEMENTARY INFORMATION:
Discussion
The FAA issued a notice of proposed
rulemaking (NPRM) to amend 14 CFR
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part 39 by adding an AD that would
apply to Airbus Helicopters Model
AS332C, AS332C1, AS332L, AS332L1,
AS332L2, EC 155B, EC155B1, EC225LP,
and SA330J helicopters with window
extraction tape with snap fasteners
installed. The NPRM published in the
Federal Register on October 22, 2020
(85 FR 67313). The NPRM proposed to
require inspecting each internal and
external snap fastener to determine
whether they unbutton by hand. For
external snap fasteners that do not
unbutton by hand, the NPRM proposed
to require replacing the male part of the
snap fastener and installing selfgripping tape if it still does not
unbutton by hand. Thereafter, the
NPRM proposed to require a repetitive
inspection of the external extraction
tape and self-gripping tape and
replacing any tape that is cracked, torn,
disintegrated, worn, or missing, and
replacing the snap fasteners. For
internal snap fasteners that do not
unbutton by hand, the NPRM proposed
to require installing self-gripping tape
and replacing the snap fasteners. The
proposed requirements were intended to
prevent failure of a window to jettison,
preventing occupants from exiting the
helicopter during an emergency.
The NPRM was prompted by EASA
AD No. 2015–0149, dated July 23, 2015
(EASA AD 2015–0149), to correct an
unsafe condition for Airbus Helicopters
Model AS 322 and EC 225 LP
helicopters; EASA AD No. 2015–0168,
dated August 13, 2015 (EASA AD 2015–
0168), to correct an unsafe condition for
Airbus Helicopters Model EC 155 B and
EC 155 B1 helicopters; and EASA AD
No. 2015–0169, dated August 13, 2015
(EASA AD 2015–0169), to correct an
unsafe condition for Airbus Helicopters
Model SA330 J helicopters, equipped
with an extraction tape fitted with
‘‘press-studs’’ (snap fasteners) on the
windows. Each EASA AD was issued by
EASA, which is the Technical Agent for
the Member States of the European
Union. EASA advises of difficulty
unbuttoning the extraction tape during
the manufacturing of a helicopter.
Investigation concluded that the
difficulty was caused by a bad male/
female coupling, possibly resulting from
miscrimping. This difficulty is known to
have occurred on two additional
helicopters. EASA states this condition,
if not detected and corrected, could
prevent the jettisoning of the helicopter
window, possibly affecting the
evacuation of passengers during an
emergency situation. For these reasons,
EASA AD 2015–0149, EASA AD 2015–
0168, and EASA AD 2015–0169 require
inspecting each press-stud located on
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14239
the extraction tapes of the window
jettisoning system and depending on the
findings, installing self-gripping tape
and replacing the press-studs.
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.
Related Service Information Under 1
CFR Part 51
The FAA reviewed Airbus Helicopters
Alert Service Bulletin (ASB) No.
AS332–56.00.10, Revision 0, dated July
16, 2015, for Model AS332-series
helicopters; ASB No. EC155–56A006,
Revision 0, dated August 10, 2015, for
Model EC155-series helicopters; ASB
No. EC225–56A008, Revision 0, dated
July 16, 2015, for Model EC225LP
helicopters; and ASB No. SA330–56.02,
Revision 0, dated August 10, 2015, for
Model SA330J helicopters. This service
information specifies procedures to
inspect the internal and external pressstuds and to install self-gripping tape for
press-studs that do not unbutton or are
difficult to unbutton. This service
information also specifies procedures to
replace internal press-studs that are
difficult to unbutton and a repetitive
inspection for affected external pressstuds until they are replaced.
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.
Costs of Compliance
The FAA estimates that this AD
affects 72 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.
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Federal Register / Vol. 86, No. 48 / Monday, March 15, 2021 / Rules and Regulations
Inspecting the snap fasteners takes
about 1 work-hour for a cost of $85 per
helicopter and $6,120 for the U.S. fleet.
Installing self-gripping tape takes about
0.3 work-hour and parts cost $200 for a
cost of $226 per window. Inspecting the
tape takes about 0.3 work-hour for a cost
of $26 per window per inspection cycle.
Replacing the extraction tape or selfgripping tape takes about 1 work-hour
and parts cost $200 for a total of $285
per window. Replacing a snap fastener
takes about 1 work-hour and parts cost
$200 for a total of $285 per snap
fastener.
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.
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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.
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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:
■
2021–05–06 Airbus Helicopters:
Amendment 39–21449; Docket No.
FAA–2020–0916; Product Identifier
2015–SW–055–AD.
(a) Applicability
This airworthiness directive (AD) applies
to Airbus Helicopters Model AS332C,
AS332C1, AS332L, AS332L1, AS332L2, EC
155B, EC155B1, EC225LP, and SA330J
helicopters, certificated in any category, with
window extraction tape with snap fasteners
installed.
(b) Unsafe Condition
This AD defines the unsafe condition as
failure of a snap fastener to unbutton. This
condition could result in failure of the
window to jettison, preventing occupants
from exiting the helicopter during an
emergency.
(c) Effective Date
This AD becomes effective April 19, 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.
(e) Required Actions
Within 50 hours time-in-service (TIS),
inspect each internal and external snap
fastener to determine if it can be unbuttoned
by hand.
Note 1 to the introductory text of
paragraph (e): Airbus Helicopters refers to
the snap fastener as a ‘‘press-stud.’’
(1) If all internal and external snap
fasteners can be unbuttoned by hand, no
further action is required by this AD.
(2) If an external snap fastener does not
unbutton by hand:
(i) Before further flight, replace the male
part of the snap fastener and determine if the
snap fastener can be unbuttoned by hand
force. If the snap fastener still does not
unbutton by hand, before further flight,
install self-gripping tape.
(ii) Thereafter, at intervals not to exceed 15
hours TIS, inspect the external extraction
tape and self-gripping tape for a crack, a tear,
disintegration, or wear. If the extraction tape
or self-gripping tape has a crack, a tear, any
disintegration, wear, or is missing, before
further flight, replace the tape. Replacing the
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extraction tape or self-gripping tape does not
terminate this repetitive inspection.
(iii) Within 100 hours TIS, replace each
external snap fastener by following the
Accomplishment Instructions, paragraph
3.B.4., of Airbus Helicopters Alert Service
Bulletin (ASB) No. AS332–56.00.10, Revision
0, dated July 16, 2015 (ASB AS332–56.00.10);
ASB No. EC155–56A006, Revision 0, dated
August 10, 2015 (ASB EC155–56A006); ASB
No. EC225–56A008, Revision 0, dated July
16, 2015 (ASB EC225–56A008); or ASB No.
SA330–56.02, Revision 0, dated August 10,
2015 (ASB SA330–56.02), as applicable to
your model helicopter. Replacing the
external snap fastener terminates the
repetitive inspection requirements specified
in paragraph (e)(2)(ii) of this AD.
(3) If an internal snap fastener does not
unbutton by hand:
(i) Before further flight, install self-gripping
tape by following the Accomplishment
Instructions, paragraph 3.B.3., of AS332–
56.00.10, ASB EC155–56A006, ASB EC225–
56A008, or ASB SA330–56.02, as applicable
to your model helicopter.
(ii) Within 900 hours TIS, replace each
internal snap fastener by following the
Accomplishment Instructions, paragraph
3.B.5., of ASB AS332–56.00.10, ASB EC155–
56A006, ASB EC225–56A008, or ASB
SA330–56.02, as applicable to your model
helicopter.
(f) 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, send it to the attention of:
David Hatfield, Aerospace Engineer, Aircraft
Systems Section, Technical Innovation
Policy Branch, Policy & Innovation Division,
FAA, 10101 Hillwood Pkwy., Fort Worth, TX
76177; telephone (817) 222–5110.
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.
(g) Additional Information
The subject of this AD is addressed in
European Aviation Safety Agency (now
European Union Aviation Safety Agency)
(EASA) AD No. 2015–0149, dated July 23,
2015; EASA AD No. 2015–0168, dated
August 13, 2015; and EASA AD No. 2015–
0169, dated August 13, 2015. You may view
the EASA ADs on the internet at https://
www.regulations.gov in Docket No. FAA–
2020–0916.
(h) Subject
Joint Aircraft Service Component (JASC)
Code: 5600, Window/Windshield System.
(i) Material Incorporated by Reference
(1) The Director of the Federal Register
approved the incorporation by reference of
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the service information listed in this
paragraph under 5 U.S.C. 552(a) and 1 CFR
part 51.
(2) You must use this service information
as applicable to do the actions required by
this AD, unless the AD specifies otherwise.
(i) Airbus Helicopters Alert Service
Bulletin (ASB) No. AS332–56.00.10, Revision
0, dated July 16, 2015.
(ii) Airbus Helicopters ASB No. EC155–
56A006, Revision 0, dated August 10, 2015.
(iii) Airbus Helicopters ASB No. EC225–
56A008, Revision 0, dated July 16, 2015.
(iv) Airbus Helicopters ASB No. SA330–
56.02, Revision 0, dated August 10, 2015.
(3) 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.
(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 fedreg.legal@nara.gov, or go to: https://
www.archives.gov/federal-register/cfr/ibrlocations.html.
Issued on February 18, 2021.
Gaetano A. Sciortino,
Deputy Director for Strategic Initiatives,
Compliance & Airworthiness Division,
Aircraft Certification Service.
[FR Doc. 2021–05144 Filed 3–12–21; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2020–0903; Project
Identifier AD–2020–00957–T; Amendment
39–21454; AD 2021–05–11]
RIN 2120–AA64
Airworthiness Directives; The Boeing
Company Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule.
AGENCY:
The FAA is superseding
Airworthiness Directive (AD) 2017–26–
10, which applied to certain The Boeing
Company Model 757 airplanes. AD
2017–26–10 required deactivating the
spoiler control module (SCM) relays and
capping and stowing the associated
wiring on certain airplanes. This AD
requires repetitive operational tests of
the spoiler inhibit function. For certain
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SUMMARY:
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15:55 Mar 12, 2021
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airplanes, this AD requires installing a
new relay bracket assembly, making
changes to the wire bundles for certain
SCMs, installing new SCMs, measuring
the clearance between a wire bundle
and the top of the new relay bracket
assembly, and applicable on-condition
actions. For a certain other airplane, this
AD requires changing certain wire
bundles. This AD was prompted by
reports of unwanted lateral oscillations
during landing operations, and the
development of wiring changes for
certain SCMs, which will improve the
lateral handling qualities of the airplane
during approach and landing. The FAA
is issuing this AD to address the unsafe
condition on these products.
DATES: This AD is effective April 19,
2021.
The Director of the Federal Register
approved the incorporation by reference
of a certain publication listed in this AD
as of April 19, 2021.
ADDRESSES: For service information
identified in this final rule, contact
Boeing Commercial Airplanes,
Attention: Contractual & Data Services
(C&DS), 2600 Westminster Blvd., MC
110–SK57, Seal Beach, CA 90740–5600;
telephone 562–797–1717; internet
https://www.myboeingfleet.com. You
may view this service information at the
FAA, Airworthiness Products Section,
Operational Safety Branch, 2200 South
216th St., Des Moines, WA. For
information on the availability of this
material at the FAA, call 206–231–3195.
It is also available at https://
www.regulations.gov by searching for
and locating Docket No. FAA–2020–
0903.
Examining the AD Docket
You may examine the AD docket at
https://www.regulations.gov by
searching for and locating Docket No.
FAA–2020–0903; 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:
Katherine Venegas, Aerospace Engineer,
Cabin Safety and Environmental
Systems Section, FAA, Los Angeles
ACO Branch, 3960 Paramount
Boulevard, Lakewood, CA 90712–4137;
phone: 562–627–5353; fax: 562–627–
5210; email: Katherine.Venegas@
faa.gov.
SUPPLEMENTARY INFORMATION:
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Background
The FAA issued a notice of proposed
rulemaking (NPRM) to amend 14 CFR
part 39 to supersede AD 2017–26–10,
Amendment 39–19141 (82 FR 61675,
December 29, 2017) (AD 2017–26–10).
AD 2017–26–10 applied to certain The
Boeing Company Model 757 airplanes.
The NPRM published in the Federal
Register on October 13, 2020 (85 FR
64419). The NPRM was prompted by
reports of unwanted lateral oscillations
during landing operations, and the
development of wiring changes for
certain SCMs, which will improve the
lateral handling qualities of the airplane
during approach and landing. The
NPRM proposed to require repetitive
operational tests of the spoiler inhibit
function. For certain airplanes, the
NPRM proposed to require installing a
new relay bracket assembly, making
changes to the wire bundles for certain
SCMs, installing new SCMs, measuring
the clearance between a wire bundle
and the top of the new relay bracket
assembly, and applicable on-condition
actions. For a certain other airplane, the
NPRM proposed to require changing
certain wire bundles. The FAA is
issuing this AD to address unwanted
lateral oscillations during landing
operations, which could cause overcontrol of the airplane and subsequent
lateral pilot induced oscillation, which
could affect continued safe flight and
landing.
Comments
The FAA gave the public the
opportunity to participate in developing
this AD. The following presents the
comments received on the NPRM and
the FAA’s response to each comment.
Support for the NPRM
An anonymous commenter, FedEx
Express, and United Airlines (UAL)
stated their support for the NPRM. An
additional comment from UAL is
addressed below.
Effect of Winglets on Accomplishment
of the Proposed Actions
Aviation Partners Boeing stated that
the installation of winglets per
Supplemental Type Certificate (STC)
ST01518SE does not affect the
accomplishment of the proposed
actions.
The FAA agrees with the commenter
that STC ST01518SE does not affect the
ability to accomplish the actions
required by this AD. The FAA has not
changed this AD in this regard.
E:\FR\FM\15MRR1.SGM
15MRR1
]]>Agencies
[Federal Register Volume 86, Number 48 (Monday, March 15, 2021)]
[Rules and Regulations]
[Pages 14238-14241]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2021-05144]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2020-0916; Product Identifier 2015-SW-055-AD; Amendment
39-21449; AD 2021-05-06]
RIN 2120-AA64
Airworthiness Directives; Airbus Helicopters
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Final rule.
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[[Page 14239]]
SUMMARY: The FAA is adopting a new airworthiness directive (AD) for
Airbus Helicopters Model AS332C, AS332C1, AS332L, AS332L1, AS332L2, EC
155B, EC155B1, EC225LP, and SA330J helicopters. This AD requires
inspecting the snap fasteners on the windows. This AD was prompted by
incidents of difficulty unbuttoning the extraction tape on the windows.
The actions of this AD are intended to address an unsafe condition on
these products.
DATES: This AD is effective April 19, 2021.
The Director of the Federal Register approved the incorporation by
reference of certain documents listed in this AD as of April 19, 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. It is also available on the
internet at https://www.regulations.gov by searching for and locating
Docket No. FAA-2020-0916.
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-
0916; 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 Aviation Safety Agency (now European Union
Aviation Safety Agency) (EASA) ADs, any service information that is
incorporated by reference, 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: David Hatfield, Aerospace Engineer,
Aircraft Systems Section, Technical Innovation Policy Branch, Policy &
Innovation Division, FAA, 10101 Hillwood Pkwy., Fort Worth, TX 76177;
telephone (817) 222-5110; 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
Model AS332C, AS332C1, AS332L, AS332L1, AS332L2, EC 155B, EC155B1,
EC225LP, and SA330J helicopters with window extraction tape with snap
fasteners installed. The NPRM published in the Federal Register on
October 22, 2020 (85 FR 67313). The NPRM proposed to require inspecting
each internal and external snap fastener to determine whether they
unbutton by hand. For external snap fasteners that do not unbutton by
hand, the NPRM proposed to require replacing the male part of the snap
fastener and installing self-gripping tape if it still does not
unbutton by hand. Thereafter, the NPRM proposed to require a repetitive
inspection of the external extraction tape and self-gripping tape and
replacing any tape that is cracked, torn, disintegrated, worn, or
missing, and replacing the snap fasteners. For internal snap fasteners
that do not unbutton by hand, the NPRM proposed to require installing
self-gripping tape and replacing the snap fasteners. The proposed
requirements were intended to prevent failure of a window to jettison,
preventing occupants from exiting the helicopter during an emergency.
The NPRM was prompted by EASA AD No. 2015-0149, dated July 23, 2015
(EASA AD 2015-0149), to correct an unsafe condition for Airbus
Helicopters Model AS 322 and EC 225 LP helicopters; EASA AD No. 2015-
0168, dated August 13, 2015 (EASA AD 2015-0168), to correct an unsafe
condition for Airbus Helicopters Model EC 155 B and EC 155 B1
helicopters; and EASA AD No. 2015-0169, dated August 13, 2015 (EASA AD
2015-0169), to correct an unsafe condition for Airbus Helicopters Model
SA330 J helicopters, equipped with an extraction tape fitted with
``press-studs'' (snap fasteners) on the windows. Each EASA AD was
issued by EASA, which is the Technical Agent for the Member States of
the European Union. EASA advises of difficulty unbuttoning the
extraction tape during the manufacturing of a helicopter. Investigation
concluded that the difficulty was caused by a bad male/female coupling,
possibly resulting from miscrimping. This difficulty is known to have
occurred on two additional helicopters. EASA states this condition, if
not detected and corrected, could prevent the jettisoning of the
helicopter window, possibly affecting the evacuation of passengers
during an emergency situation. For these reasons, EASA AD 2015-0149,
EASA AD 2015-0168, and EASA AD 2015-0169 require inspecting each press-
stud located on the extraction tapes of the window jettisoning system
and depending on the findings, installing self-gripping tape and
replacing the press-studs.
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.
Related Service Information Under 1 CFR Part 51
The FAA reviewed Airbus Helicopters Alert Service Bulletin (ASB)
No. AS332-56.00.10, Revision 0, dated July 16, 2015, for Model AS332-
series helicopters; ASB No. EC155-56A006, Revision 0, dated August 10,
2015, for Model EC155-series helicopters; ASB No. EC225-56A008,
Revision 0, dated July 16, 2015, for Model EC225LP helicopters; and ASB
No. SA330-56.02, Revision 0, dated August 10, 2015, for Model SA330J
helicopters. This service information specifies procedures to inspect
the internal and external press-studs and to install self-gripping tape
for press-studs that do not unbutton or are difficult to unbutton. This
service information also specifies procedures to replace internal
press-studs that are difficult to unbutton and a repetitive inspection
for affected external press-studs until they are replaced.
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.
Costs of Compliance
The FAA estimates that this AD affects 72 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.
[[Page 14240]]
Inspecting the snap fasteners takes about 1 work-hour for a cost of
$85 per helicopter and $6,120 for the U.S. fleet. Installing self-
gripping tape takes about 0.3 work-hour and parts cost $200 for a cost
of $226 per window. Inspecting the tape takes about 0.3 work-hour for a
cost of $26 per window per inspection cycle. Replacing the extraction
tape or self-gripping tape takes about 1 work-hour and parts cost $200
for a total of $285 per window. Replacing a snap fastener takes about 1
work-hour and parts cost $200 for a total of $285 per snap fastener.
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:
2021-05-06 Airbus Helicopters: Amendment 39-21449; Docket No. FAA-
2020-0916; Product Identifier 2015-SW-055-AD.
(a) Applicability
This airworthiness directive (AD) applies to Airbus Helicopters
Model AS332C, AS332C1, AS332L, AS332L1, AS332L2, EC 155B, EC155B1,
EC225LP, and SA330J helicopters, certificated in any category, with
window extraction tape with snap fasteners installed.
(b) Unsafe Condition
This AD defines the unsafe condition as failure of a snap
fastener to unbutton. This condition could result in failure of the
window to jettison, preventing occupants from exiting the helicopter
during an emergency.
(c) Effective Date
This AD becomes effective April 19, 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.
(e) Required Actions
Within 50 hours time-in-service (TIS), inspect each internal and
external snap fastener to determine if it can be unbuttoned by hand.
Note 1 to the introductory text of paragraph (e): Airbus
Helicopters refers to the snap fastener as a ``press-stud.''
(1) If all internal and external snap fasteners can be
unbuttoned by hand, no further action is required by this AD.
(2) If an external snap fastener does not unbutton by hand:
(i) Before further flight, replace the male part of the snap
fastener and determine if the snap fastener can be unbuttoned by
hand force. If the snap fastener still does not unbutton by hand,
before further flight, install self-gripping tape.
(ii) Thereafter, at intervals not to exceed 15 hours TIS,
inspect the external extraction tape and self-gripping tape for a
crack, a tear, disintegration, or wear. If the extraction tape or
self-gripping tape has a crack, a tear, any disintegration, wear, or
is missing, before further flight, replace the tape. Replacing the
extraction tape or self-gripping tape does not terminate this
repetitive inspection.
(iii) Within 100 hours TIS, replace each external snap fastener
by following the Accomplishment Instructions, paragraph 3.B.4., of
Airbus Helicopters Alert Service Bulletin (ASB) No. AS332-56.00.10,
Revision 0, dated July 16, 2015 (ASB AS332-56.00.10); ASB No. EC155-
56A006, Revision 0, dated August 10, 2015 (ASB EC155-56A006); ASB
No. EC225-56A008, Revision 0, dated July 16, 2015 (ASB EC225-
56A008); or ASB No. SA330-56.02, Revision 0, dated August 10, 2015
(ASB SA330-56.02), as applicable to your model helicopter. Replacing
the external snap fastener terminates the repetitive inspection
requirements specified in paragraph (e)(2)(ii) of this AD.
(3) If an internal snap fastener does not unbutton by hand:
(i) Before further flight, install self-gripping tape by
following the Accomplishment Instructions, paragraph 3.B.3., of
AS332-56.00.10, ASB EC155-56A006, ASB EC225-56A008, or ASB SA330-
56.02, as applicable to your model helicopter.
(ii) Within 900 hours TIS, replace each internal snap fastener
by following the Accomplishment Instructions, paragraph 3.B.5., of
ASB AS332-56.00.10, ASB EC155-56A006, ASB EC225-56A008, or ASB
SA330-56.02, as applicable to your model helicopter.
(f) 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, send it to the attention of: David
Hatfield, Aerospace Engineer, Aircraft Systems Section, Technical
Innovation Policy Branch, Policy & Innovation Division, FAA, 10101
Hillwood Pkwy., Fort Worth, TX 76177; telephone (817) 222-5110.
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.
(g) Additional Information
The subject of this AD is addressed in European Aviation Safety
Agency (now European Union Aviation Safety Agency) (EASA) AD No.
2015-0149, dated July 23, 2015; EASA AD No. 2015-0168, dated August
13, 2015; and EASA AD No. 2015-0169, dated August 13, 2015. You may
view the EASA ADs on the internet at https://www.regulations.gov in
Docket No. FAA-2020-0916.
(h) Subject
Joint Aircraft Service Component (JASC) Code: 5600, Window/
Windshield System.
(i) Material Incorporated by Reference
(1) The Director of the Federal Register approved the
incorporation by reference of
[[Page 14241]]
the service information listed in this paragraph under 5 U.S.C.
552(a) and 1 CFR part 51.
(2) You must use this service information as applicable to do
the actions required by this AD, unless the AD specifies otherwise.
(i) Airbus Helicopters Alert Service Bulletin (ASB) No. AS332-
56.00.10, Revision 0, dated July 16, 2015.
(ii) Airbus Helicopters ASB No. EC155-56A006, Revision 0, dated
August 10, 2015.
(iii) Airbus Helicopters ASB No. EC225-56A008, Revision 0, dated
July 16, 2015.
(iv) Airbus Helicopters ASB No. SA330-56.02, Revision 0, dated
August 10, 2015.
(3) 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.
(4) You may view this service information at the FAA, Office of
the Regional Counsel, Southwest Region, 10101 Hillwood Pkwy., Room
6N-321, Fort Worth, TX 76177. For information on the availability of
this material at the FAA, call (817) 222-5110.
(5) You may view this service information that is incorporated
by reference at the National Archives and Records Administration
(NARA). For information on the availability of this material at
NARA, email [email protected], or go to: https://www.archives.gov/federal-register/cfr/ibr-locations.html.
Issued on February 18, 2021.
Gaetano A. Sciortino,
Deputy Director for Strategic Initiatives, Compliance & Airworthiness
Division, Aircraft Certification Service.
[FR Doc. 2021-05144 Filed 3-12-21; 8:45 am]
BILLING CODE 4910-13-P
