[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.

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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