Airworthiness Directives; Pacific Scientific Company Seat Restraint System Rotary Buckle Assemblies, 17703-17706 [2021-06979]
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Federal Register / Vol. 86, No. 64 / Tuesday, April 6, 2021 / Rules and Regulations
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 Airbus SAS’s EASA Design
Organization Approval (DOA). If approved by
the DOA, the approval must include the
DOA-authorized signature.
(3) Required for Compliance (RC): Except
as required by paragraphs (i) and (j)(2) of this
AD, if any service information contains
procedures or tests that are identified as RC,
those procedures and tests must be done to
comply with this AD; any procedures or tests
that are not identified as RC are
recommended. Those procedures and tests
that are not identified as RC may be deviated
from using accepted methods in accordance
with the operator’s maintenance or
inspection program without obtaining
approval of an AMOC, provided the
procedures and tests identified as RC can be
done and the airplane can be put back in an
airworthy condition. Any substitutions or
changes to procedures or tests identified as
RC require approval of an AMOC.
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(k) Related Information
For more information about this AD,
contact Kathleen Arrigotti, Aerospace
Engineer, Large Aircraft Section,
International Validation Branch, FAA, 2200
South 216th St., Des Moines, WA 98198;
telephone and fax 206–231–3218; email
Kathleen.Arrigotti@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 this AD specifies otherwise.
(3) The following service information was
approved for IBR on May 11, 2021.
(i) European Union Aviation Safety Agency
(EASA) AD 2020–0167, dated July 27, 2020.
(ii) [Reserved]
(4) For EASA AD 2020–0167, 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.
(5) 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–2020–0854.
(6) You may view this material that is
incorporated by reference at the National
Archives and Records Administration
(NARA). For information on the availability
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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 February 8, 2021.
Lance T. Gant,
Director, Compliance & Airworthiness
Division, Aircraft Certification Service.
[FR Doc. 2021–07003 Filed 4–5–21; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2013–0752; Product
Identifier 2009–SW–44–AD; Amendment 39–
21490; AD 2021–07–13]
RIN 2120–AA64
Airworthiness Directives; Pacific
Scientific Company Seat Restraint
System Rotary Buckle Assemblies
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule.
AGENCY:
The FAA is adopting a new
airworthiness directive (AD) for certain
Pacific Scientific Company rotary
buckle assemblies (buckles). This AD
requires inspecting each buckle
including its buckle handle vane, and
depending on the results, removing the
buckle from service and installing an
airworthy buckle. This AD also
prohibits installing the affected buckles.
This AD was prompted by several
reports of cracked buckle handles. The
actions of this AD are intended to
address an unsafe condition on these
products.
This AD is effective May 11,
2021.
The Director of the Federal Register
approved the incorporation by reference
of a certain document listed in this AD
as of May 11, 2021.
ADDRESSES: For service information
identified in this final rule, contact
Meggitt Services, 1785 Voyager Ave.,
Simi Valley, CA 93063, telephone 877–
666–0712 or at CustomerResponse@
meggitt.com. 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–2013–0752.
DATES:
Examining the AD Docket
You may examine the AD docket on
the internet at https://
Frm 00013
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www.regulations.gov by searching for
and locating Docket No. FAA–2013–
0752; 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) AD, 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:
Kristi Bradley, Aviation Safety Engineer,
General Aviation & Rotorcraft Section,
International Validation Branch, FAA,
10101 Hillwood Pkwy., Fort Worth, TX
76177; telephone (817) 222–5110; email
kristin.bradley@faa.gov.
SUPPLEMENTARY INFORMATION:
Discussion
SUMMARY:
PO 00000
17703
The FAA issued a supplemental
notice of proposed rulemaking (SNPRM)
to amend 14 CFR part 39 by adding an
AD that would apply to Pacific
Scientific Company buckle part
numbers (P/Ns) 1111430 and 1111475,
all dash numbers. The SNPRM
published in the Federal Register on
September 24, 2020 (85 FR 60100). The
FAA preceded the SNPRM with a notice
of proposed rulemaking (NPRM) that
published in the Federal Register on
September 5, 2013 (78 FR 54594). The
NPRM proposed to require inspecting
each buckle for a crack and the
thickness of the buckle handle vane.
Depending on the inspection results, the
NPRM proposed to require replacing the
buckle. The NPRM also proposed to
prohibit installing an affected buckle on
any helicopter or airplane. The SNPRM
proposed to the same requirements
except with longer compliance times to
accomplish the inspections. The
SNPRM also corrected the name of
Pacific Scientific Aviation Services to
Pacific Scientific Company, updated the
estimated costs of compliance, edited
the Applicability paragraph by adding a
note to clarify that an affected buckle
could be included as a component of a
different part-numbered restraint system
assembly and reference Appendix 1 of
Pacific Scientific Service Bulletin SB
25–1111432, dated May 22, 2007 (SB
25–1111432), which lists the P/Ns of
potentially affected restraint systems,
updated the names of certain
potentially-affected Type Certificate
holders, and updated the contact
information name and contact
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06APR1
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Federal Register / Vol. 86, No. 64 / Tuesday, April 6, 2021 / Rules and Regulations
information from Pacific Scientific
Aviation Services to Meggitt Services.
The NPRM was prompted by EASA
AD 2007–0256, dated September 19,
2007, issued by EASA, which is the
Technical Agent for the Member States
of the European Union, to correct an
unsafe condition for certain Pacific
Scientific Company Seat Restraint
System Plastic Rotary Buckle Handles.
According to EASA, Pacific Scientific
Company reported several instances of
cracked handles on certain buckles with
a date of manufacture from November
2004 through May 2007. Testing on
buckles with a cracked handle indicated
that in some circumstances, a load
placed on the restraint system prevents
a strap from releasing as intended when
the buckle is rotated. EASA states in its
AD that this failure to release is possible
when a passenger weighs more than 50
kg (approximately 110 lbs.) and an
aircraft is upside down.
Comments
After the SNPRM was published, the
FAA received comments from two
commenters.
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Request for Credit
NetJets QC requested that this AD
allow credit for compliance with Cessna
Citation Service Letter (SL) 560–25–09,
Cessna Citation SL560XL–25–10, or
Cessna Citation SL750–25–15, each
dated December 10, 2007. NetJets QC
also requested that provisions be written
in the AD for logbook/Illustrated Parts
Catalog (IPC) research sign-off, since
these buckles may not be installed on
newly-manufactured aircraft.
The FAA disagrees with both
requests. This AD is an appliance AD
that applies to Pacific Scientific
Company buckles P/Ns 1111430 and
1111475, all dash numbers, without
regard to date of manufacture, whereas
each SL distinguishes the affected parts
by date of manufacture. If an affected
buckle is not installed on an aircraft,
then this AD does not apply, and credit
and provisions are not necessary to
relieve this AD’s requirements for the
concerned aircraft. However, this AD
does not prohibit using maintenance
records to determine if an affected
buckle is installed. Using an IPC is not
an acceptable method to determine an
aircraft’s configuration.
Addition of MU–2B Aircraft
Mitsubishi Heavy Industries America,
Inc. (MHIA) suggested that the FAA add
‘‘Mitsubishi MU–2B series aircraft’’ to
the list of aircraft models that could be
affected by this AD. MHIA stated that
Mitsubishi Heavy Industries, Ltd., holds
Supplemental Type Certificate No.
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SA1751SW, which allows installation of
certain affected buckles on Mitsubishi
MU–2B series aircraft.
The FAA partially agrees. The FAA
agrees that affected buckles could be
installed on Mitsubishi Heavy
Industries, Ltd., Model MU–2B series
airplanes; however, the applicability
only identifies possible installations on
airplanes and helicopters by ‘‘make’’
and not ‘‘models.’’ Accordingly, the
FAA has added Mitsubishi Heavy
Industries, Ltd., to the list of airplanes
that affected buckles could be installed
on in the applicability of this final rule.
Extension of Compliance Time
MHIA requested extending the
compliance time to at least 12 months,
as replacement parts could be in short
supply. MHIA states that it has
attempted to contact the product
support representative at Meggitt
Services located in Simi Valley, CA in
order to obtain additional technical
information; however, no formal
response had been received from
Meggitt Services when MHIA submitted
this comment on November 9, 2020.
MHIA expressed concern that with
limited support from Meggitt Services,
owners and operators of affected
airplanes will have difficulty meeting
the compliance requirements because of
a potential lack of sufficient
replacement parts.
The FAA acknowledges MHIA’s
concern about contacting Meggitt
Services and has re-confirmed that its
contact information is accurate. The
FAA disagrees with changing the
compliance time to inspect an affected
buckle handle for a crack from 6 months
to 12 months based on a potential lack
of sufficient replacement parts. The
FAA has not received any information
to indicate that there is an insufficient
number of replacement parts that would
necessitate extending the compliance
time from that stated in the proposed
AD.
FAA’s Determination
These products 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 products and
that air safety and the public interest
require adopting the AD requirements as
proposed with the changes described
previously. These changes are
consistent with the intent of the
PO 00000
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Fmt 4700
Sfmt 4700
proposal in the SNPRM and will neither
increase the economic burden on any
operator nor increase the scope of this
AD.
Differences Between This AD and the
EASA AD
The EASA AD applies to certain
buckles used on certain restraint
systems that are known to be installed
on, but not limited to, certain
Eurocopter (now Airbus Helicopters)
model helicopters. The applicability of
the EASA AD is limited to rotorcraft
only and is not intended for airplanes.
Since the affected buckles may be
installed in other aircraft resulting in
the same unsafe condition, this AD
applies to the same certain buckles,
which may be installed on but not
limited to certain airplanes and
helicopters. This AD does not require
returning the unairworthy buckle
assembly to the manufacturer, and this
AD does not apply to spare parts that
are not installed on an aircraft. Also,
this AD applies to buckle P/Ns 1111430
and 1111475, all dash numbers, and is
not dependent on the restraint P/Ns.
The EASA AD requires inspecting the
buckles within 30 days, whereas this
AD requires inspecting the buckle
handle for a crack within 6 months and
the buckle handle vane thickness within
12 months instead. The EASA AD
requires a repetitive inspection of each
buckle for cracks before any flight for up
to 6 months following the effective date
of the EASA AD until the buckle is
replaced. This AD does not require an
inspection for cracks before any flight
for the 6 months until the affected
buckles are replaced. The EASA AD
identifies suspect parts by date of
manufacture, and this AD does not.
Finally, the EASA AD allows for
marking a seat as ‘‘un-operative’’ and
this AD does not.
Related Service Information Under 1
CFR Part 51
The FAA reviewed SB 25–1111432,
which specifies inspecting each buckle
P/Ns 1111430–XX and 1111475–XX
with a date of manufacture between
November 2004 and May 2007, to
identify whether the handle is one
susceptible to cracking by checking the
P/N on the reverse side of the buckle
assembly or by measuring the thickness
of the handle vane. If the buckle is
identified as a ‘‘suspect’’ buckle, this
service information provides procedures
for removing the buckle and replacing it
with an acceptable buckle. Information
in this service information also advises
that buckles with a cracked handle
should be removed from service
immediately.
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06APR1
Federal Register / Vol. 86, No. 64 / Tuesday, April 6, 2021 / Rules and Regulations
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 will
affect 1,435 restraint systems installed
on aircraft 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.
Inspecting a buckle costs a minimal
amount and takes a nominal amount of
time. Replacing a buckle takes about 0.5
work-hour and parts cost about $636 for
an estimated cost of $679 per buckle
and up to $974,365 for the U.S. fleet.
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.
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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:
■
2021–07–13 Pacific Scientific Company:
Amendment 39–21490; Docket No.
FAA–2013–0752; Product Identifier
2009–SW–44–AD.
(a) Applicability
This airworthiness directive (AD) applies
to Pacific Scientific Company rotary buckle
assembly (buckle), part numbers (P/Ns)
1111430 and 1111475, all dash numbers.
These buckles may be installed on but not
limited to Bombardier Inc., Learjet Inc.,
Mitsubishi Heavy Industries, Ltd., Textron
Aviation, Inc. (Type Certificate (TC)
previously held by Cessna Aircraft
Company), and Viking Air Limited (TC
previously held by de Havilland, Inc.) model
airplanes and Airbus Helicopters (TC
previously held by Eurocopter France) model
helicopters, certificated in any category.
Note 1 to paragraph (a): The rotary buckle
may be included as a component of a
different part-numbered restraint system
assembly. Pacific Scientific Service Bulletin
SB 25–1111432, dated May 22, 2007 (SB 25–
1111432), Appendix 1, includes a list of
these restraint system P/Ns.
(b) Unsafe Condition
This AD defines the unsafe condition as a
cracked rotary buckle handle, which could
prevent a strap from releasing as intended
when the buckle is rotated.
(c) Effective Date
This AD becomes effective May 11, 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
(1) Within 6 months, inspect the buckle
handle for a crack. If the buckle handle is
cracked, before further flight, remove the
buckle as depicted in Figure 5 and by
following the Procedures, paragraph 9, of SB
25–1111432, and replace it with an airworthy
buckle, except you are not required to return
the removed buckle to Pacific Scientific.
PO 00000
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17705
(2) Within 12 months, measure the
thickness of the buckle handle vane as
depicted in Figure 3 of SB 25–1111432. If the
handle vane thickness is 0.125 inch or
greater, before further flight, remove the
buckle from service and replace it with an
airworthy buckle.
(3) As of the effective date of this AD, do
not install a buckle or a restraint system with
a buckle, P/N 1111430 or 1111475, all dash
numbers, with a handle vane thickness of
0.125 inch or greater on any airplane or
helicopter.
(f) Alternative Methods of Compliance
(AMOCs)
(1) The Manager, International Validation
Branch, FAA, may approve AMOCs for this
AD. Send your proposal to: Kristi Bradley,
Aviation Safety Engineer, General Aviation &
Rotorcraft Section, International Validation
Branch, FAA, 10101 Hillwood Pkwy., Fort
Worth, TX 76177; telephone (817) 222–5110;
email 9-AVS-AIR-730-AMOC@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.
(g) Additional Information
The subject of this AD is addressed in
European Aviation Safety Agency (now
European Union Aviation Safety Agency)
(EASA) AD 2007–0256, dated September 19,
2007. You may view the EASA AD on the
internet at https://www.regulations.gov in
Docket No. FAA–2013–0752.
(h) Subject
Joint Aircraft Service Component (JASC)
Code: 2500, Cabin Equipment/Furnishings.
(i) Material Incorporated by Reference
(1) The Director of the Federal Register
approved the incorporation by reference of
the service information listed in this
paragraph under 5 U.S.C. 552(a) and 1 CFR
part 51.
(2) You must use this service information
as applicable to do the actions required by
this AD, unless the AD specifies otherwise.
(i) Pacific Scientific Service Bulletin SB
25–1111432, dated May 22, 2007.
(ii) [Reserved]
(3) For service information identified in
this AD, contact Meggitt Services, 1785
Voyager Ave., Simi Valley, CA 93063,
telephone 877–666–0712 or at
CustomerResponse@meggitt.com.
(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://
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Federal Register / Vol. 86, No. 64 / Tuesday, April 6, 2021 / Rules and Regulations
www.archives.gov/federal-register/cfr/ibrlocations.html.
by searching for and locating Docket No.
FAA–2020–1173.
Issued on March 25, 2021.
Lance T. Gant,
Director, Compliance & Airworthiness
Division, Aircraft Certification Service.
Examining the AD Docket
[FR Doc. 2021–06979 Filed 4–5–21; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2020–1173; Project
Identifier MCAI–2020–00299–R; Amendment
39–21489; AD 2021–07–12]
RIN 2120–AA64
Airworthiness Directives; Airbus
Helicopters Deutschland GmbH
Helicopters
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule.
AGENCY:
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Discussion
The FAA is adopting a new
airworthiness directive (AD) for Airbus
Helicopters Deutschland GmbH Model
EC135P1, EC135P2, EC135P2+,
EC135P3, EC135T1, EC135T2,
EC135T2+, and EC135T3 helicopters.
This AD was prompted by a
reassessment of the flight control
system. This AD requires modification
of the cyclic stick, 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 May 11,
2021.
The Director of the Federal Register
approved the incorporation by reference
of a certain document listed in this AD
as of May 11, 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
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
SUMMARY:
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Jkt 253001
You may examine the AD docket on
the internet at https://
www.regulations.gov by searching for
and locating Docket No. FAA–2020–
1173; 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:
Kristi Bradley, Aviation Safety Engineer,
General Aviation & Rotorcraft Section,
International Validation Branch, FAA,
10101 Hillwood Pkwy., Fort Worth, TX
76177; telephone 817–222–5110; email
kristin.bradley@faa.gov.
SUPPLEMENTARY INFORMATION:
EASA, which is the Technical Agent
for the Member States of the European
Union, has issued EASA AD 2018–0063,
dated March 22, 2018 (EASA AD 2018–
0063) (also referred to as the Mandatory
Continuing Airworthiness Information,
or the MCAI), to correct an unsafe
condition for Airbus Helicopters
Deutschland GmbH (AHD) formerly
Eurocopter Deutschland GmbH (ECD),
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,
all variants, all serial numbers (S/Ns) up
to 1263 inclusive and S/N 1265, if
equipped with autopilot, and S/N 2001
up to 2024 inclusive, except S/N 2006,
2008, 2013, 2017, 2019, 2020 and 2022.
The FAA issued a notice of proposed
rulemaking (NPRM) to amend 14 CFR
part 39 by adding an AD that would
apply to certain Model EC135P1,
EC135P2, EC135P2+, EC135P3,
EC135T1, EC135T2, EC135T2+, and
EC135T3 helicopters. The NPRM
published in the Federal Register on
January 19, 2021 (86 FR 5040). The
NPRM was prompted by a reassessment
of the flight control system, which
revealed that uncommanded
disengagement of the main rotor trim
actuators during flight with the
autopilot engaged and hands-off
controls could result in high roll and
pitch rates, which would require pilot
intervention within a reaction time
below that required by current
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Fmt 4700
Sfmt 4700
airworthiness standards. The NPRM
proposed to require installing a cyclic
stick weight compensation modification
to correct this unsafe condition, which
if not corrected may lead to subsequent
loss of control of the helicopter, as
specified in an EASA AD.
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.
The FAA also determined that these
changes will not increase the economic
burden on any operator or increase the
scope of this final rule.
Related Service Information Under 1
CFR Part 51
EASA AD 2018–0063 describes
procedures for modifying the helicopter
by retrofitting the cyclic stick weight
compensation.
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
The EASA AD applies to certain
serial-numbered EC635-series
helicopters with an autopilot installed,
whereas this AD does not apply to the
Model EC635-series helicopters because
these models are not FAA typecertificated. The EASA AD requires a
calendar compliance time, whereas this
AD requires using hours time-in-service.
Costs of Compliance
The FAA estimates that this AD
affects 331 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.
Modifying the cyclic stick weight
compensator takes about 8 work-hours
and parts cost about $1,300 for an
estimated cost of about $1,980 per
E:\FR\FM\06APR1.SGM
06APR1
]]>Agencies
[Federal Register Volume 86, Number 64 (Tuesday, April 6, 2021)]
[Rules and Regulations]
[Pages 17703-17706]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2021-06979]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2013-0752; Product Identifier 2009-SW-44-AD; Amendment
39-21490; AD 2021-07-13]
RIN 2120-AA64
Airworthiness Directives; Pacific Scientific Company Seat
Restraint System Rotary Buckle Assemblies
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Final rule.
-----------------------------------------------------------------------
SUMMARY: The FAA is adopting a new airworthiness directive (AD) for
certain Pacific Scientific Company rotary buckle assemblies (buckles).
This AD requires inspecting each buckle including its buckle handle
vane, and depending on the results, removing the buckle from service
and installing an airworthy buckle. This AD also prohibits installing
the affected buckles. This AD was prompted by several reports of
cracked buckle handles. The actions of this AD are intended to address
an unsafe condition on these products.
DATES: This AD is effective May 11, 2021.
The Director of the Federal Register approved the incorporation by
reference of a certain document listed in this AD as of May 11, 2021.
ADDRESSES: For service information identified in this final rule,
contact Meggitt Services, 1785 Voyager Ave., Simi Valley, CA 93063,
telephone 877-666-0712 or at [email protected]. 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-2013-
0752.
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-2013-
0752; 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) AD, 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: Kristi Bradley, Aviation Safety
Engineer, General Aviation & Rotorcraft Section, International
Validation Branch, FAA, 10101 Hillwood Pkwy., Fort Worth, TX 76177;
telephone (817) 222-5110; email [email protected].
SUPPLEMENTARY INFORMATION:
Discussion
The FAA issued a supplemental notice of proposed rulemaking (SNPRM)
to amend 14 CFR part 39 by adding an AD that would apply to Pacific
Scientific Company buckle part numbers (P/Ns) 1111430 and 1111475, all
dash numbers. The SNPRM published in the Federal Register on September
24, 2020 (85 FR 60100). The FAA preceded the SNPRM with a notice of
proposed rulemaking (NPRM) that published in the Federal Register on
September 5, 2013 (78 FR 54594). The NPRM proposed to require
inspecting each buckle for a crack and the thickness of the buckle
handle vane. Depending on the inspection results, the NPRM proposed to
require replacing the buckle. The NPRM also proposed to prohibit
installing an affected buckle on any helicopter or airplane. The SNPRM
proposed to the same requirements except with longer compliance times
to accomplish the inspections. The SNPRM also corrected the name of
Pacific Scientific Aviation Services to Pacific Scientific Company,
updated the estimated costs of compliance, edited the Applicability
paragraph by adding a note to clarify that an affected buckle could be
included as a component of a different part-numbered restraint system
assembly and reference Appendix 1 of Pacific Scientific Service
Bulletin SB 25-1111432, dated May 22, 2007 (SB 25-1111432), which lists
the P/Ns of potentially affected restraint systems, updated the names
of certain potentially-affected Type Certificate holders, and updated
the contact information name and contact
[[Page 17704]]
information from Pacific Scientific Aviation Services to Meggitt
Services.
The NPRM was prompted by EASA AD 2007-0256, dated September 19,
2007, issued by EASA, which is the Technical Agent for the Member
States of the European Union, to correct an unsafe condition for
certain Pacific Scientific Company Seat Restraint System Plastic Rotary
Buckle Handles. According to EASA, Pacific Scientific Company reported
several instances of cracked handles on certain buckles with a date of
manufacture from November 2004 through May 2007. Testing on buckles
with a cracked handle indicated that in some circumstances, a load
placed on the restraint system prevents a strap from releasing as
intended when the buckle is rotated. EASA states in its AD that this
failure to release is possible when a passenger weighs more than 50 kg
(approximately 110 lbs.) and an aircraft is upside down.
Comments
After the SNPRM was published, the FAA received comments from two
commenters.
Request for Credit
NetJets QC requested that this AD allow credit for compliance with
Cessna Citation Service Letter (SL) 560-25-09, Cessna Citation SL560XL-
25-10, or Cessna Citation SL750-25-15, each dated December 10, 2007.
NetJets QC also requested that provisions be written in the AD for
logbook/Illustrated Parts Catalog (IPC) research sign-off, since these
buckles may not be installed on newly-manufactured aircraft.
The FAA disagrees with both requests. This AD is an appliance AD
that applies to Pacific Scientific Company buckles P/Ns 1111430 and
1111475, all dash numbers, without regard to date of manufacture,
whereas each SL distinguishes the affected parts by date of
manufacture. If an affected buckle is not installed on an aircraft,
then this AD does not apply, and credit and provisions are not
necessary to relieve this AD's requirements for the concerned aircraft.
However, this AD does not prohibit using maintenance records to
determine if an affected buckle is installed. Using an IPC is not an
acceptable method to determine an aircraft's configuration.
Addition of MU-2B Aircraft
Mitsubishi Heavy Industries America, Inc. (MHIA) suggested that the
FAA add ``Mitsubishi MU-2B series aircraft'' to the list of aircraft
models that could be affected by this AD. MHIA stated that Mitsubishi
Heavy Industries, Ltd., holds Supplemental Type Certificate No.
SA1751SW, which allows installation of certain affected buckles on
Mitsubishi MU-2B series aircraft.
The FAA partially agrees. The FAA agrees that affected buckles
could be installed on Mitsubishi Heavy Industries, Ltd., Model MU-2B
series airplanes; however, the applicability only identifies possible
installations on airplanes and helicopters by ``make'' and not
``models.'' Accordingly, the FAA has added Mitsubishi Heavy Industries,
Ltd., to the list of airplanes that affected buckles could be installed
on in the applicability of this final rule.
Extension of Compliance Time
MHIA requested extending the compliance time to at least 12 months,
as replacement parts could be in short supply. MHIA states that it has
attempted to contact the product support representative at Meggitt
Services located in Simi Valley, CA in order to obtain additional
technical information; however, no formal response had been received
from Meggitt Services when MHIA submitted this comment on November 9,
2020. MHIA expressed concern that with limited support from Meggitt
Services, owners and operators of affected airplanes will have
difficulty meeting the compliance requirements because of a potential
lack of sufficient replacement parts.
The FAA acknowledges MHIA's concern about contacting Meggitt
Services and has re-confirmed that its contact information is accurate.
The FAA disagrees with changing the compliance time to inspect an
affected buckle handle for a crack from 6 months to 12 months based on
a potential lack of sufficient replacement parts. The FAA has not
received any information to indicate that there is an insufficient
number of replacement parts that would necessitate extending the
compliance time from that stated in the proposed AD.
FAA's Determination
These products 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
products and that air safety and the public interest require adopting
the AD requirements as proposed with the changes described previously.
These changes are consistent with the intent of the proposal in the
SNPRM and will neither increase the economic burden on any operator nor
increase the scope of this AD.
Differences Between This AD and the EASA AD
The EASA AD applies to certain buckles used on certain restraint
systems that are known to be installed on, but not limited to, certain
Eurocopter (now Airbus Helicopters) model helicopters. The
applicability of the EASA AD is limited to rotorcraft only and is not
intended for airplanes. Since the affected buckles may be installed in
other aircraft resulting in the same unsafe condition, this AD applies
to the same certain buckles, which may be installed on but not limited
to certain airplanes and helicopters. This AD does not require
returning the unairworthy buckle assembly to the manufacturer, and this
AD does not apply to spare parts that are not installed on an aircraft.
Also, this AD applies to buckle P/Ns 1111430 and 1111475, all dash
numbers, and is not dependent on the restraint P/Ns. The EASA AD
requires inspecting the buckles within 30 days, whereas this AD
requires inspecting the buckle handle for a crack within 6 months and
the buckle handle vane thickness within 12 months instead. The EASA AD
requires a repetitive inspection of each buckle for cracks before any
flight for up to 6 months following the effective date of the EASA AD
until the buckle is replaced. This AD does not require an inspection
for cracks before any flight for the 6 months until the affected
buckles are replaced. The EASA AD identifies suspect parts by date of
manufacture, and this AD does not. Finally, the EASA AD allows for
marking a seat as ``un-operative'' and this AD does not.
Related Service Information Under 1 CFR Part 51
The FAA reviewed SB 25-1111432, which specifies inspecting each
buckle P/Ns 1111430-XX and 1111475-XX with a date of manufacture
between November 2004 and May 2007, to identify whether the handle is
one susceptible to cracking by checking the P/N on the reverse side of
the buckle assembly or by measuring the thickness of the handle vane.
If the buckle is identified as a ``suspect'' buckle, this service
information provides procedures for removing the buckle and replacing
it with an acceptable buckle. Information in this service information
also advises that buckles with a cracked handle should be removed from
service immediately.
[[Page 17705]]
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 will affect 1,435 restraint systems
installed on aircraft 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.
Inspecting a buckle costs a minimal amount and takes a nominal
amount of time. Replacing a buckle takes about 0.5 work-hour and parts
cost about $636 for an estimated cost of $679 per buckle and up to
$974,365 for the U.S. fleet.
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:
2021-07-13 Pacific Scientific Company: Amendment 39-21490; Docket
No. FAA-2013-0752; Product Identifier 2009-SW-44-AD.
(a) Applicability
This airworthiness directive (AD) applies to Pacific Scientific
Company rotary buckle assembly (buckle), part numbers (P/Ns) 1111430
and 1111475, all dash numbers. These buckles may be installed on but
not limited to Bombardier Inc., Learjet Inc., Mitsubishi Heavy
Industries, Ltd., Textron Aviation, Inc. (Type Certificate (TC)
previously held by Cessna Aircraft Company), and Viking Air Limited
(TC previously held by de Havilland, Inc.) model airplanes and
Airbus Helicopters (TC previously held by Eurocopter France) model
helicopters, certificated in any category.
Note 1 to paragraph (a): The rotary buckle may be included as a
component of a different part-numbered restraint system assembly.
Pacific Scientific Service Bulletin SB 25-1111432, dated May 22,
2007 (SB 25-1111432), Appendix 1, includes a list of these restraint
system P/Ns.
(b) Unsafe Condition
This AD defines the unsafe condition as a cracked rotary buckle
handle, which could prevent a strap from releasing as intended when
the buckle is rotated.
(c) Effective Date
This AD becomes effective May 11, 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
(1) Within 6 months, inspect the buckle handle for a crack. If
the buckle handle is cracked, before further flight, remove the
buckle as depicted in Figure 5 and by following the Procedures,
paragraph 9, of SB 25-1111432, and replace it with an airworthy
buckle, except you are not required to return the removed buckle to
Pacific Scientific.
(2) Within 12 months, measure the thickness of the buckle handle
vane as depicted in Figure 3 of SB 25-1111432. If the handle vane
thickness is 0.125 inch or greater, before further flight, remove
the buckle from service and replace it with an airworthy buckle.
(3) As of the effective date of this AD, do not install a buckle
or a restraint system with a buckle, P/N 1111430 or 1111475, all
dash numbers, with a handle vane thickness of 0.125 inch or greater
on any airplane or helicopter.
(f) Alternative Methods of Compliance (AMOCs)
(1) The Manager, International Validation Branch, FAA, may
approve AMOCs for this AD. Send your proposal to: Kristi Bradley,
Aviation Safety Engineer, General Aviation & Rotorcraft Section,
International Validation Branch, 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
The subject of this AD is addressed in European Aviation Safety
Agency (now European Union Aviation Safety Agency) (EASA) AD 2007-
0256, dated September 19, 2007. You may view the EASA AD on the
internet at https://www.regulations.gov in Docket No. FAA-2013-0752.
(h) Subject
Joint Aircraft Service Component (JASC) Code: 2500, Cabin
Equipment/Furnishings.
(i) Material Incorporated by Reference
(1) The Director of the Federal Register approved the
incorporation by reference of the service information listed in this
paragraph under 5 U.S.C. 552(a) and 1 CFR part 51.
(2) You must use this service information as applicable to do
the actions required by this AD, unless the AD specifies otherwise.
(i) Pacific Scientific Service Bulletin SB 25-1111432, dated May
22, 2007.
(ii) [Reserved]
(3) For service information identified in this AD, contact
Meggitt Services, 1785 Voyager Ave., Simi Valley, CA 93063,
telephone 877-666-0712 or at [email protected].
(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://
[[Page 17706]]
www.archives.gov/federal-register/cfr/ibr-locations.html.
Issued on March 25, 2021.
Lance T. Gant,
Director, Compliance & Airworthiness Division, Aircraft Certification
Service.
[FR Doc. 2021-06979 Filed 4-5-21; 8:45 am]
BILLING CODE 4910-13-P
