Airworthiness Directives; Anjou Aeronautique Torso Restraint Systems, 72257-72260 [2019-27939]
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Federal Register / Vol. 84, No. 250 / Tuesday, December 31, 2019 / Proposed Rules
khammond on DSKJM1Z7X2PROD with PROPOSALS
No. 05.00.51, Revision 1, dated July 29, 2015
(ASB 05.00.51 Rev 1).
(i) Record the outside air temperature
(OAT) and rotor speed (NR RPM) and plot
the point at which they intersect using the
graph in Figure 1 or 2 of ASB 05.00.51 Rev
0 or ASB 05.00.51 Rev 1.
(ii) If the point on the graph at the
intersection of the recorded OAT and the NR
RPM falls within:
(A) Zone 3—Before further flight, replace
the MGB and pump with an airworthy MGB
and pump.
(B) Zone 2—At intervals not to exceed 25
hours TIS, repeat the inspection procedures
by following the Accomplishment
Instructions, paragraph 2.B.2, steps 1.
through 6., of ASB 05.00.51 Rev 0 or ASB
05.00.51 Rev 1. After being classified in
‘‘Zone 2,’’ you must obtain two successive
inspections separated by at least 24 hours TIS
that fall within Zone 1 before you can begin
to inspect at intervals not to exceed 110
hours TIS by following paragraph (f)(2)(ii)(C)
of this AD for Zone 1.
(C) Zone 1—At intervals not to exceed 110
hours TIS, repeat the inspection procedures
by following the Accomplishment
Instructions, paragraph 2.B.2., steps 1.
through 6., of ASB 05.00.51 Rev 0 or ASB
05.00.51 Rev 1.
(iii) Compliance with paragraphs (f)(2)(i)
and (ii) of this AD constitutes terminating
action for the checks and inspections
required by paragraph (f)(1) of this AD.
(3) As an optional terminating action for
the requirements in this AD, alter the
lubrication system for the MGB in
accordance with the Accomplishment
Instructions, paragraphs 3.B.2.a. through
3.B.3 of Airbus Helicopters Service Bulletin
No. AS355–63.00.25, Revision 1, dated July
29, 2015, or Revision 2, dated June 22, 2017.
Mineral oil 0–155 is required after
compliance with this alteration.
Note 1 to paragraph (f)(3) of this AD:
Airbus Helicopters identifies alteration of the
lubrication system as MOD 077222.
(g) Alternative Methods of Compliance
(AMOCs)
(1) The Manager, Safety Management
Section, Rotorcraft Standards Branch, FAA,
may approve AMOCs for this AD. Send your
proposal to: Jignesh Patel, Aerospace
Engineer, Safety Management Section,
Rotorcraft Standards Branch, FAA, 10101
Hillwood Pkwy, Fort Worth, TX 76177;
telephone 817–222–5110; email 9-ASW-FTWAMOC-Requests@faa.gov.
(2) For operations conducted under a 14
CFR part 119 operating certificate or under
14 CFR part 91, subpart K, the FAA suggests
that you notify your principal inspector, or
lacking a principal inspector, the manager of
the local flight standards district office or
certificate holding district office before
operating any aircraft complying with this
AD through an AMOC.
(h) Additional Information
(1) Airbus Helicopters Service Bulletin No.
AS355–63.00.25, Revision 1, dated July 29,
2015, and Revision 2, dated June 22, 2017,
and Eurocopter Emergency Alert Service
Bulletin No. 05.00.40, Revision 3, dated July
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9, 2007, which are not incorporated by
reference, pertain to the subject of this AD.
For service information identified in this AD,
contact Airbus Helicopters, 2701 N. Forum
Drive, Grand Prairie, TX 75052; telephone
972–641–0000 or 800–232–0323; fax 972–
641–3775; or at https://www.airbus.com/
helicopters/services/technical-support.html.
You may view a copy of the service
information at the FAA, Office of the
Regional Counsel, Southwest Region, 10101
Hillwood Pkwy, Room 6N–321, Fort Worth,
TX 76177.
(2) The subject of this AD is addressed in
European Aviation Safety Agency (EASA) AD
No. 2007–0209R1, dated September 11, 2015.
You may view the EASA AD on the internet
at https://www.regulations.gov in the AD
Docket.
(i) Subject
Joint Aircraft Service Component (JASC)
Code: 6320, Main Rotor Gearbox.
Issued in Fort Worth, Texas, on December
20, 2019.
Lance T. Gant,
Director, Compliance & Airworthiness
Division, Aircraft Certification Service.
[FR Doc. 2019–27978 Filed 12–30–19; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2019–0537; Product
Identifier 2019–NE–16–AD]
RIN 2120–AA64
Airworthiness Directives; Anjou
Aeronautique Torso Restraint Systems
Federal Aviation
Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
The FAA proposes to
supersede airworthiness directive (AD)
2017–16–04 which applies to certain
Anjou Aeronautique (formerly Romtex
Anjou Aeronautique) Model 358 torso
restraint systems (restraint systems). AD
2017–16–04 required inspection of the
restraint system, placarding if it is found
to be inoperative, and replacement of
the affected restraint system with a part
eligible for installation. Since the FAA
issued AD 2017–16–04, the European
Union Aviation Safety Agency (EASA)
received reports of additional serial
numbered restraint systems rotary
buckle knobs (buckle knobs) breaking
on a batch of parts outside of the
previous population. This proposed AD
would require the removal from service
of this expanded population of affected
restraint systems and modifies the
compliance schedule for their removal.
SUMMARY:
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72257
The FAA is proposing this AD to
address the unsafe condition on these
products.
DATES: The FAA must receive comments
on this proposed AD by February 14,
2020.
ADDRESSES: You may send comments,
using the procedures found in 14 CFR
11.43 and 11.45, by any of the following
methods:
• Federal eRulemaking Portal: Go to
https://www.regulations.gov. Follow the
instructions for submitting comments.
• Fax: 202–493–2251.
• Mail: U.S. Department of
Transportation, Docket Operations,
M–30, West Building Ground Floor,
Room W12–140, 1200 New Jersey
Avenue SE, Washington, DC 20590.
• Hand Delivery: Deliver to Mail
address above between 9 a.m. and 5
p.m., Monday through Friday, except
Federal holidays.
For service information identified in
this NPRM, contact Anjou
Aeronautique, Strada Livezii nr. 98,
550042, Sibiu, Romania; telephone: +40
269 243 918; fax: +40 269 243 921;
email: seatbelts@anjouaero.com. You
may view this service information at the
FAA, Engine and Propeller Standards
Branch, 1200 District Avenue,
Burlington, MA 01803. For information
on the availability of this material at the
FAA, call 781–238–7759.
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–2019–
0537; 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 NPRM, the
mandatory continuing airworthiness
information (MCAI), the regulatory
evaluation, any comments received, and
other information. The street address for
Docket Operations is listed above.
Comments will be available in the AD
docket shortly after receipt.
FOR FURTHER INFORMATION CONTACT:
Dorie Resnik, Aerospace Engineer,
Boston ACO Branch, FAA, 1200 District
Avenue, Burlington, MA, 01803; phone:
781–238–7693; fax: 781–238–7199;
email: dorie.resnik@faa.gov.
SUPPLEMENTARY INFORMATION:
Comments Invited
The FAA invites you to send any
written relevant data, views, or
arguments about this proposed AD.
Send your comments to an address
listed under the ADDRESSES section.
Include ‘‘Docket No. FAA–2019–0537;
Product Identifier 2019–NE–16–AD’’ at
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Federal Register / Vol. 84, No. 250 / Tuesday, December 31, 2019 / Proposed Rules
the beginning of your comments. The
FAA specifically invites comments on
the overall regulatory, economic,
environmental, and energy aspects of
this NPRM. The FAA will consider all
comments received by the closing date
and may amend this NPRM because of
those comments.
The FAA will post all comments
received, without change, to https://
www.regulations.gov, including any
personal information you provide. The
FAA will also post a report
summarizing each substantive verbal
contact received about this proposed
AD.
Discussion
The FAA issued AD 2017–16–04,
Amendment 39–18981 (82 FR 39355,
August 18, 2017), (‘‘AD 2017–16–04’’),
for Anjou Aeronautique restraint
systems installed on, but not limited to,
Airbus Helicopters Model AS350B2,
AS350B3, EC130B4, EC130T2, and
AS355NP helicopters. AD 2017–16–04
requires inspection of the restraint
system, placarding if it is found to be
inoperative, and replacement of the
affected restraint system with a part
eligible for installation. AD 2017–16–04
resulted from reports of a population of
buckle knobs breaking due to the
alteration of rotary buckle sub-assembly
by a supplier of Anjou Aeronautique to
a specification different from the
approved design data. The FAA issued
AD 2017–16–04 to prevent a restraint
system from failing to release due to the
buckle knobs breaking off, preventing
occupants from exiting the helicopter
during an emergency.
Actions Since AD 2017–16–04 Was
Issued
Since the FAA issued AD 2017–16–
04, EASA received reports of additional
Anjou Aeronautique Model 358 buckle
knobs breaking on a batch of parts
affected by the same unsafe condition
due to an unknown root cause. As a
result, EASA issued AD 2018–0195,
dated September 4, 2018, which
identifies a population of the restraint
systems to be removed from service.
Revision to Cost Estimate
The FAA determined the need to
clarify the estimated cost in AD 2017–
16–04. The cost reflected in AD 2017–
16–04 is the total cost per helicopter
($6,000 per restraint system multiplied
by 7 seats per helicopter totaling
$42,000). In this AD, the FAA is
providing the cost estimate per restraint
system.
Related Service Information Under 1
CFR Part 51
The FAA reviewed Anjou Aero
Service Bulletin (SB) No. 358SB–14–
101, Revision 1, dated December 12,
2014. The SB describes procedures for
removing from service and replacing the
rotary buckle sub-assembly on certain
part-numbered and serial-numbered
buckle assemblies, consisting of the
rotary buckle, belt, and attachment. 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.
FAA’s Determination
The FAA is proposing this AD
because it evaluated all the relevant
information and determined the unsafe
condition described previously is likely
to exist or develop in other products of
the same type design.
Proposed AD Requirements
This proposed AD would retain
certain requirements of AD 2017–16–04.
This proposed AD expands the
populations of affected restrains systems
and modifies the compliance schedule
for their removal.
Differences Between the Proposed AD
and MCAI
EASA AD 2018–0195, dated
September 4, 2018, requires
replacement of the affected restraint
system within six months after the
effective date of the EASA AD. This
proposed AD would require inspection
of each restraint system within 30 hours
time in service (TIS) after the effective
date of the AD and replacement of the
rotary buckle sub-assembly within 180
hours TIS after the effective date of this
AD. Additionally, the EASA AD applies
to restraint systems installed on, but not
limited to, Airbus Helicopter AS350B2,
AS350B3, and EC130T2 helicopters.
This proposed AD would apply to
restraint systems installed on, but not
limited to, Airbus Helicopters AS350B2,
AS350B3, EC130B4, EC130T2, and
AS355NP helicopters.
Costs of Compliance
The FAA estimates that this proposed
AD affects an unknown number of
restraint systems installed on, but not
limited to, Airbus Helicopters AS350B2,
AS350B3, EC130B4, EC130T2, and
AS355NP helicopters of U.S. registry.
The FAA estimates the following
costs to comply with this proposed AD:
ESTIMATED COSTS
Action
Labor cost
Inspect restraint system ...............................................
Remove and replace restraint system .........................
0.5 work-hours × $85 per hour = $42.50 .....................
0.5 work-hours × $85 per hour = $42.50 .....................
The FAA estimates the following
costs to do any necessary placarding
that would be required based on the
results of the proposed inspection. The
FAA has no way of determining the
Cost per
product
Parts cost
$0
6,000
$42.50
6,042.50
number of aircraft that might need this
placarding:
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ON-CONDITION COSTS
Action
Labor cost
Placard seat as inoperable ...........................................
0.1 work-hour × $85 per hour = $8.50 .........................
According to the manufacturer, some
of the costs of this proposed AD may be
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covered under warranty, thereby
reducing the cost impact on affected
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Cost per
product
Parts cost
$0
$8.50
individuals. The FAA does not control
warranty coverage for affected
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Federal Register / Vol. 84, No. 250 / Tuesday, December 31, 2019 / Proposed Rules
individuals. As a result, the FAA has
included all costs in its cost estimate.
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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 products identified in this
rulemaking action.
This AD is issued in accordance with
authority delegated by the Executive
Director, Aircraft Certification Service,
as authorized by FAA Order 8000.51C.
In accordance with that order, issuance
of ADs is normally a function of the
Compliance and Airworthiness
Division, but during this transition
period, the Executive Director has
delegated the authority to issue ADs
applicable to engines, propellers, and
associated appliances to the Manager,
Engine and Propeller Standards Branch,
Policy and Innovation Division.
Regulatory Findings
The FAA determined that this
proposed AD would not have federalism
implications under Executive Order
13132. This proposed AD would 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 the proposed regulation:
(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.
VerDate Sep<11>2014
16:29 Dec 30, 2019
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The Proposed Amendment
Accordingly, under the authority
delegated to me by the Administrator,
the FAA proposes to amend 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
removing airworthiness directive (AD)
2017–16–04, Amendment 39–18981 (82
FR 39355, August 18, 2017), and adding
the following new AD:
■
Anjou Aeronautique (formerly Romtex
Anjou Aeronautique): Docket No. FAA–
2019–0537; Product Identifier 2019–NE–
16–AD.
(a) Comments Due Date
The FAA must receive comments on this
AD action by February 14, 2020.
(b) Affected ADs
This AD replaces AD 2017–16–04,
Amendment 39–18981 (82 FR 39355, August
18, 2017).
(c) Applicability
(1) This AD applies to Anjou Aeronautique
Model 358 torso restraint systems (restraint
systems), part number (P/N) 358XX–XXX–
YY–ZZZ (where 358XX–XXX–YY–ZZZ can
be any combination of numbers and/or
letters), with serial numbers (S/Ns) listed in
Effectivity, paragraph 1.2, of Anjou Aero
Service Bulletin (SB) No. 358SB–14–101,
Revision 1, dated December 12, 2014, and
with S/Ns listed in Figure 1 to Paragraph
(c)(1) of this AD.
FIGURE 1 TO PARAGRAPH (c)(1)—
APPLICABILITY
S/N
(From . . . inclusive)
S/N
(To . . .
inclusive)
738
1049
1056
1074
1037
1049
1061
1619
(2) These restraint systems are installed on,
but not limited to, Airbus Helicopters
AS350B2, AS350B3, EC130B4, EC130T2, and
AS355NP helicopters, certificated in any
category.
(d) Subject
Joint Aircraft System Component (JASC)
Code 2500, Cabin Equipment/Furnishings.
(e) Unsafe Condition
This AD was prompted by reports to the
European Union Aviation Safety Agency
(EASA) of additional restraint system buckle
knobs, since the publication of AD 2017–16–
04, breaking on a batch of parts outside of the
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72259
population identified in AD 2017–16–04. The
FAA is issuing this AD to prevent a restraint
system strap from failing to release from the
buckle, causing occupants to be unable to
exit the aircraft during an emergency. The
unsafe condition, if not addressed, could
result in a restraint system strap failing to
release from the buckle, resulting in injury or
death of the occupant.
(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
(g) Required Actions
(1) For the restraint systems listed in the
Effectivity, paragraph 1.2, of Anjou Aero SB
No. 358SB–14–101, Revision 1, dated
December 12, 2014, except for S/Ns 1038–
1048 (inclusive), 1050–1055 (inclusive), and
1062–1073 (inclusive), within 30 hours timein-service (TIS) after the effective date of this
AD, inspect each restraint system for proper
release of the straps from the restraint
system.
(i) If the straps do not release from the
restraint system, before further flight, placard
the seat as inoperative. Within 180 hours TIS
after the effective date of this AD, remove the
rotary buckle sub-assembly and replace it
with a part eligible for installation.
(ii) If the straps release from the restraint
system, within 180 hours TIS after the
effective date of this AD, remove the rotary
buckle sub-assembly and replace it with a
part eligible for installation.
(2) For restraint systems, P/N 358XX–
XXX–YY–ZZZ (where 358XX–XXX–YY–ZZZ
can be any combination of numbers and/or
letters), having S/Ns 738–1619 (inclusive),
within 30 hours TIS after the effective date
of this AD, inspect the restraint system for
proper release of the straps from the restraint
system.
(i) If the straps do not release from the
restraint system, before further flight, placard
the seat as inoperative and within 180 hours
TIS after the effective date of this AD, remove
the restraint system from service and replace
it with a part eligible for installation.
(ii) If the straps release from the restraint
system, within 180 hours TIS or six months
after the effective date of this AD, whichever
occurs first, remove the restraint system from
service and replace it with a part eligible for
installation.
(h) Installation Prohibition
After the effective date of this AD, do not
install on any aircraft an Anjou Aeronautique
restraint system, P/N 358XX–XXX–YY–ZZZ,
having S/Ns 738–1619 (inclusive), even if the
restraint system is labeled in compliance
with Anjou Aero SB No. 358SB–14–101,
Revision 1, dated December 12, 2014.
(i) Definition
For the purpose of this AD, a ‘‘part eligible
for installation’’ is an Anjou Aeronautique
restraint system, excluding P/N 358XX–
XXX–YY–ZZZ, having S/Ns 738–1619
(inclusive), that had the rotary buckle subsystem repaired and a label attached
indicating compliance with Anjou Aero SB
No. 358SB–14–101, Revision 1, dated
December 12, 2014, or later revisions.
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(j) Alternative Methods of Compliance
(AMOCs)
(1) The Manager, Boston ACO Branch,
FAA, has the authority to approve AMOCs
for this AD, if requested using the procedures
found in 14 CFR 39.19. In accordance with
14 CFR 39.19, send your request to your
principal inspector or local Flight Standards
District Office, as appropriate. If sending
information directly to the manager of the
certification office, send it to the attention of
the person identified in paragraph (k)(1) of
this AD.
(2) Before using any approved AMOC,
notify your appropriate principal inspector,
or lacking a principal inspector, the manager
of the local flight standards district office/
certificate holding district office.
(k) Related Information
(1) For more information about this AD,
contact Dorie Resnik, Aerospace Engineer,
Boston ACO Branch, FAA, 1200 District
Avenue, Burlington, MA 01803; phone: 781–
238–7693; fax: 781–238–7199; email:
dorie.resnik@faa.gov.
(2) Refer to EASA AD 2018–0195, dated
September 4, 2018, for more information.
You may examine the EASA AD in the AD
docket on the internet at https://
www.regulations.gov by searching for and
locating it in Docket No. FAA–2019–0537.
(3) For service information identified in
this AD, contact Anjou Aeronautique, Strada
Livezii nr. 98, 550042, Sibiu, Romania;
telephone: +40 269 243 918; fax: +40 269 243
921; email: seatbelts@anjouaero.com. You
may view this referenced service information
at the FAA, Engine and Propeller Standards
Branch, 1200 District Avenue, Burlington,
MA 01803. For information on the
availability of this material at the FAA, call
781–238–7759.
Federal Aviation Administration
You may send comments,
using the procedures found in 14 CFR
11.43 and 11.45, by any of the following
methods:
• Federal eRulemaking Portal: Go to
https://www.regulations.gov. Follow the
instructions for submitting comments.
• Fax: 202–493–2251.
• Mail: U.S. Department of
Transportation, Docket Operations, M–
30, West Building Ground Floor, Room
W12–140, 1200 New Jersey Avenue SE,
Washington, DC 20590.
• Hand Delivery: Deliver to Mail
address above between 9 a.m. and 5
p.m., Monday through Friday, except
Federal holidays.
For service information identified in
this NPRM, 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 referenced service information at
the FAA, Transport Standards 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 on the internet
at https://www.regulations.gov by
searching for and locating Docket No.
FAA–2019–0990.
14 CFR Part 39
Examining the AD Docket
[Docket No. FAA–2019–0990; Product
Identifier 2019–NM–122–AD]
You may examine the AD docket on
the internet at https://
www.regulations.gov by searching for
and locating Docket No. FAA–2019–
0990; 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 NPRM, the
regulatory evaluation, any comments
received, and other information. The
street address for Docket Operations is
listed above. Comments will be
available in the AD docket shortly after
receipt.
Issued in Burlington, Massachusetts, on
December 20, 2019.
Karen M. Grant,
Acting Manager, Engine & Propeller
Standards Branch, Aircraft Certification
Service.
[FR Doc. 2019–27939 Filed 12–30–19; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
RIN 2120–AA64
khammond on DSKJM1Z7X2PROD with PROPOSALS
The Boeing Company Model 747–100,
747–100B, 747–100B SUD, 747–200B,
747–200C, 747–200F, 747–300, 747–
400, 747–400D, 747–400F, 747SR, and
747SP series airplanes. This proposed
AD was prompted by reports of cracks
of the upper splice fittings. This
proposed AD would require repetitive
detailed inspections and open hole high
frequency eddy current (HFEC)
inspections of the upper splice fittings
for cracks and applicable on-condition
actions. The FAA is proposing this AD
to address the unsafe condition on these
products.
DATES: The FAA must receive comments
on this proposed AD by February 14,
2020.
Airworthiness Directives; The Boeing
Company Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
The FAA proposes to adopt a
new airworthiness directive (AD) for all
SUMMARY:
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16:29 Dec 30, 2019
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ADDRESSES:
PO 00000
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Bill
Ashforth, Aerospace Engineer, Airframe
Section, FAA, Seattle ACO Branch, 2200
South 216th St., Des Moines, WA 98198;
phone and fax: 206–231–3520; email:
bill.ashforth@faa.gov.
SUPPLEMENTARY INFORMATION:
FOR FURTHER INFORMATION CONTACT:
Comments Invited
The FAA invites you to send any
written relevant data, views, or
arguments about this proposal. Send
your comments to an address listed
under the ADDRESSES section. Include
‘‘Docket No. FAA–2019–0990; Product
Identifier 2019–NM–122–AD’’ at the
beginning of your comments. The FAA
specifically invites comments on the
overall regulatory, economic,
environmental, and energy aspects of
this NPRM. The FAA will consider all
comments received by the closing date
and may amend this NPRM because of
those comments.
The FAA will post all comments
received, without change, to https://
www.regulations.gov, including any
personal information you provide. The
FAA will also post a report
summarizing each substantive verbal
contact received about this proposed
AD.
Discussion
The FAA has received reports of
cracks of the upper splice fittings at
station (STA) 2598. There have been a
total of seven cracks reported on the
upper splice fittings on six different
airplanes. During accomplishment of
Boeing Service Bulletin 747–53A2473,
an operator reported a crack
approximately 0.30 inches long at a
fastener hole in the splice fitting at STA
2598. The crack was in the outboard
flange at a location which is outside of
the area inspected in accordance with
Boeing Service Bulletin 747–53A2473.
The airplane had accumulated 112,500
flight hours and 18,784 flight cycles
when the crack was found. Ground
spoiler buffet loading contributes
significantly to maximum fatigue
damage in the area. This condition, if
not addressed, could result in
undetected fatigue cracks of the
bulkhead splice fitting, which could
lead to failure in the critical attach
structure and loss of the horizontal
stabilizer, and adversely affect the
structural integrity of the airplane.
Related Service Information Under 1
CFR Part 51
The FAA reviewed Boeing Alert
Requirements Bulletin 747–53A2899
RB, dated April 5, 2019. The service
information describes procedures for
repetitive detailed inspections and open
E:\FR\FM\31DEP1.SGM
31DEP1
]]>Agencies
[Federal Register Volume 84, Number 250 (Tuesday, December 31, 2019)]
[Proposed Rules]
[Pages 72257-72260]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2019-27939]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2019-0537; Product Identifier 2019-NE-16-AD]
RIN 2120-AA64
Airworthiness Directives; Anjou Aeronautique Torso Restraint
Systems
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking (NPRM).
-----------------------------------------------------------------------
SUMMARY: The FAA proposes to supersede airworthiness directive (AD)
2017-16-04 which applies to certain Anjou Aeronautique (formerly Romtex
Anjou Aeronautique) Model 358 torso restraint systems (restraint
systems). AD 2017-16-04 required inspection of the restraint system,
placarding if it is found to be inoperative, and replacement of the
affected restraint system with a part eligible for installation. Since
the FAA issued AD 2017-16-04, the European Union Aviation Safety Agency
(EASA) received reports of additional serial numbered restraint systems
rotary buckle knobs (buckle knobs) breaking on a batch of parts outside
of the previous population. This proposed AD would require the removal
from service of this expanded population of affected restraint systems
and modifies the compliance schedule for their removal. The FAA is
proposing this AD to address the unsafe condition on these products.
DATES: The FAA must receive comments on this proposed AD by February
14, 2020.
ADDRESSES: You may send comments, using the procedures found in 14 CFR
11.43 and 11.45, by any of the following methods:
Federal eRulemaking Portal: Go to https://www.regulations.gov. Follow the instructions for submitting comments.
Fax: 202-493-2251.
Mail: U.S. Department of Transportation, Docket
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New
Jersey Avenue SE, Washington, DC 20590.
Hand Delivery: Deliver to Mail address above between 9
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
For service information identified in this NPRM, contact Anjou
Aeronautique, Strada Livezii nr. 98, 550042, Sibiu, Romania; telephone:
+40 269 243 918; fax: +40 269 243 921; email: [email protected].
You may view this service information at the FAA, Engine and Propeller
Standards Branch, 1200 District Avenue, Burlington, MA 01803. For
information on the availability of this material at the FAA, call 781-
238-7759.
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-2019-
0537; 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 NPRM, the mandatory continuing airworthiness information (MCAI),
the regulatory evaluation, any comments received, and other
information. The street address for Docket Operations is listed above.
Comments will be available in the AD docket shortly after receipt.
FOR FURTHER INFORMATION CONTACT: Dorie Resnik, Aerospace Engineer,
Boston ACO Branch, FAA, 1200 District Avenue, Burlington, MA, 01803;
phone: 781-238-7693; fax: 781-238-7199; email: [email protected].
SUPPLEMENTARY INFORMATION:
Comments Invited
The FAA invites you to send any written relevant data, views, or
arguments about this proposed AD. Send your comments to an address
listed under the ADDRESSES section. Include ``Docket No. FAA-2019-0537;
Product Identifier 2019-NE-16-AD'' at
[[Page 72258]]
the beginning of your comments. The FAA specifically invites comments
on the overall regulatory, economic, environmental, and energy aspects
of this NPRM. The FAA will consider all comments received by the
closing date and may amend this NPRM because of those comments.
The FAA will post all comments received, without change, to https://www.regulations.gov, including any personal information you provide.
The FAA will also post a report summarizing each substantive verbal
contact received about this proposed AD.
Discussion
The FAA issued AD 2017-16-04, Amendment 39-18981 (82 FR 39355,
August 18, 2017), (``AD 2017-16-04''), for Anjou Aeronautique restraint
systems installed on, but not limited to, Airbus Helicopters Model
AS350B2, AS350B3, EC130B4, EC130T2, and AS355NP helicopters. AD 2017-
16-04 requires inspection of the restraint system, placarding if it is
found to be inoperative, and replacement of the affected restraint
system with a part eligible for installation. AD 2017-16-04 resulted
from reports of a population of buckle knobs breaking due to the
alteration of rotary buckle sub-assembly by a supplier of Anjou
Aeronautique to a specification different from the approved design
data. The FAA issued AD 2017-16-04 to prevent a restraint system from
failing to release due to the buckle knobs breaking off, preventing
occupants from exiting the helicopter during an emergency.
Actions Since AD 2017-16-04 Was Issued
Since the FAA issued AD 2017-16-04, EASA received reports of
additional Anjou Aeronautique Model 358 buckle knobs breaking on a
batch of parts affected by the same unsafe condition due to an unknown
root cause. As a result, EASA issued AD 2018-0195, dated September 4,
2018, which identifies a population of the restraint systems to be
removed from service.
Revision to Cost Estimate
The FAA determined the need to clarify the estimated cost in AD
2017-16-04. The cost reflected in AD 2017-16-04 is the total cost per
helicopter ($6,000 per restraint system multiplied by 7 seats per
helicopter totaling $42,000). In this AD, the FAA is providing the cost
estimate per restraint system.
Related Service Information Under 1 CFR Part 51
The FAA reviewed Anjou Aero Service Bulletin (SB) No. 358SB-14-101,
Revision 1, dated December 12, 2014. The SB describes procedures for
removing from service and replacing the rotary buckle sub-assembly on
certain part-numbered and serial-numbered buckle assemblies, consisting
of the rotary buckle, belt, and attachment. 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.
FAA's Determination
The FAA is proposing this AD because it evaluated all the relevant
information and determined the unsafe condition described previously is
likely to exist or develop in other products of the same type design.
Proposed AD Requirements
This proposed AD would retain certain requirements of AD 2017-16-
04. This proposed AD expands the populations of affected restrains
systems and modifies the compliance schedule for their removal.
Differences Between the Proposed AD and MCAI
EASA AD 2018-0195, dated September 4, 2018, requires replacement of
the affected restraint system within six months after the effective
date of the EASA AD. This proposed AD would require inspection of each
restraint system within 30 hours time in service (TIS) after the
effective date of the AD and replacement of the rotary buckle sub-
assembly within 180 hours TIS after the effective date of this AD.
Additionally, the EASA AD applies to restraint systems installed on,
but not limited to, Airbus Helicopter AS350B2, AS350B3, and EC130T2
helicopters. This proposed AD would apply to restraint systems
installed on, but not limited to, Airbus Helicopters AS350B2, AS350B3,
EC130B4, EC130T2, and AS355NP helicopters.
Costs of Compliance
The FAA estimates that this proposed AD affects an unknown number
of restraint systems installed on, but not limited to, Airbus
Helicopters AS350B2, AS350B3, EC130B4, EC130T2, and AS355NP helicopters
of U.S. registry.
The FAA estimates the following costs to comply with this proposed
AD:
Estimated Costs
----------------------------------------------------------------------------------------------------------------
Cost per
Action Labor cost Parts cost product
----------------------------------------------------------------------------------------------------------------
Inspect restraint system...................... 0.5 work-hours x $85 per hour = $0 $42.50
$42.50.
Remove and replace restraint system........... 0.5 work-hours x $85 per hour = 6,000 6,042.50
$42.50.
----------------------------------------------------------------------------------------------------------------
The FAA estimates the following costs to do any necessary
placarding that would be required based on the results of the proposed
inspection. The FAA has no way of determining the number of aircraft
that might need this placarding:
On-Condition Costs
----------------------------------------------------------------------------------------------------------------
Cost per
Action Labor cost Parts cost product
----------------------------------------------------------------------------------------------------------------
Placard seat as inoperable.................... 0.1 work-hour x $85 per hour = $0 $8.50
$8.50.
----------------------------------------------------------------------------------------------------------------
According to the manufacturer, some of the costs of this proposed
AD may be covered under warranty, thereby reducing the cost impact on
affected individuals. The FAA does not control warranty coverage for
affected
[[Page 72259]]
individuals. As a result, the FAA has included all costs in its cost
estimate.
Authority for This Rulemaking
Title 49 of the United States Code specifies the FAA's authority to
issue rules on aviation safety. Subtitle I, Section 106, describes the
authority of the FAA Administrator. Subtitle VII, Aviation Programs,
describes in more detail the scope of the Agency's authority.
The FAA is issuing this rulemaking under the authority described in
Subtitle VII, Part A, Subpart III, Section 44701, ``General
requirements.'' Under that section, Congress charges the FAA with
promoting safe flight of civil aircraft in air commerce by prescribing
regulations for practices, methods, and procedures the Administrator
finds necessary for safety in air commerce. This regulation is within
the scope of that authority because it addresses an unsafe condition
that is likely to exist or develop on products identified in this
rulemaking action.
This AD is issued in accordance with authority delegated by the
Executive Director, Aircraft Certification Service, as authorized by
FAA Order 8000.51C. In accordance with that order, issuance of ADs is
normally a function of the Compliance and Airworthiness Division, but
during this transition period, the Executive Director has delegated the
authority to issue ADs applicable to engines, propellers, and
associated appliances to the Manager, Engine and Propeller Standards
Branch, Policy and Innovation Division.
Regulatory Findings
The FAA determined that this proposed AD would not have federalism
implications under Executive Order 13132. This proposed AD would 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 the proposed
regulation:
(1) Is not a ``significant regulatory action'' under Executive
Order 12866,
(2) Will not affect intrastate aviation in Alaska, and
(3) Will not have a significant economic impact, positive or
negative, on a substantial number of small entities under the criteria
of the Regulatory Flexibility Act.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.
The Proposed Amendment
Accordingly, under the authority delegated to me by the
Administrator, the FAA proposes to amend 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 removing airworthiness directive (AD)
2017-16-04, Amendment 39-18981 (82 FR 39355, August 18, 2017), and
adding the following new AD:
Anjou Aeronautique (formerly Romtex Anjou Aeronautique): Docket No.
FAA-2019-0537; Product Identifier 2019-NE-16-AD.
(a) Comments Due Date
The FAA must receive comments on this AD action by February 14,
2020.
(b) Affected ADs
This AD replaces AD 2017-16-04, Amendment 39-18981 (82 FR 39355,
August 18, 2017).
(c) Applicability
(1) This AD applies to Anjou Aeronautique Model 358 torso
restraint systems (restraint systems), part number (P/N) 358XX-XXX-
YY-ZZZ (where 358XX-XXX-YY-ZZZ can be any combination of numbers
and/or letters), with serial numbers (S/Ns) listed in Effectivity,
paragraph 1.2, of Anjou Aero Service Bulletin (SB) No. 358SB-14-101,
Revision 1, dated December 12, 2014, and with S/Ns listed in Figure
1 to Paragraph (c)(1) of this AD.
Figure 1 to Paragraph (c)(1)--Applicability
------------------------------------------------------------------------
S/N (From . . . inclusive) S/N (To . . . inclusive)
------------------------------------------------------------------------
738 1037
1049 1049
1056 1061
1074 1619
------------------------------------------------------------------------
(2) These restraint systems are installed on, but not limited
to, Airbus Helicopters AS350B2, AS350B3, EC130B4, EC130T2, and
AS355NP helicopters, certificated in any category.
(d) Subject
Joint Aircraft System Component (JASC) Code 2500, Cabin
Equipment/Furnishings.
(e) Unsafe Condition
This AD was prompted by reports to the European Union Aviation
Safety Agency (EASA) of additional restraint system buckle knobs,
since the publication of AD 2017-16-04, breaking on a batch of parts
outside of the population identified in AD 2017-16-04. The FAA is
issuing this AD to prevent a restraint system strap from failing to
release from the buckle, causing occupants to be unable to exit the
aircraft during an emergency. The unsafe condition, if not
addressed, could result in a restraint system strap failing to
release from the buckle, resulting in injury or death of the
occupant.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) Required Actions
(1) For the restraint systems listed in the Effectivity,
paragraph 1.2, of Anjou Aero SB No. 358SB-14-101, Revision 1, dated
December 12, 2014, except for S/Ns 1038-1048 (inclusive), 1050-1055
(inclusive), and 1062-1073 (inclusive), within 30 hours time-in-
service (TIS) after the effective date of this AD, inspect each
restraint system for proper release of the straps from the restraint
system.
(i) If the straps do not release from the restraint system,
before further flight, placard the seat as inoperative. Within 180
hours TIS after the effective date of this AD, remove the rotary
buckle sub-assembly and replace it with a part eligible for
installation.
(ii) If the straps release from the restraint system, within 180
hours TIS after the effective date of this AD, remove the rotary
buckle sub-assembly and replace it with a part eligible for
installation.
(2) For restraint systems, P/N 358XX-XXX-YY-ZZZ (where 358XX-
XXX-YY-ZZZ can be any combination of numbers and/or letters), having
S/Ns 738-1619 (inclusive), within 30 hours TIS after the effective
date of this AD, inspect the restraint system for proper release of
the straps from the restraint system.
(i) If the straps do not release from the restraint system,
before further flight, placard the seat as inoperative and within
180 hours TIS after the effective date of this AD, remove the
restraint system from service and replace it with a part eligible
for installation.
(ii) If the straps release from the restraint system, within 180
hours TIS or six months after the effective date of this AD,
whichever occurs first, remove the restraint system from service and
replace it with a part eligible for installation.
(h) Installation Prohibition
After the effective date of this AD, do not install on any
aircraft an Anjou Aeronautique restraint system, P/N 358XX-XXX-YY-
ZZZ, having S/Ns 738-1619 (inclusive), even if the restraint system
is labeled in compliance with Anjou Aero SB No. 358SB-14-101,
Revision 1, dated December 12, 2014.
(i) Definition
For the purpose of this AD, a ``part eligible for installation''
is an Anjou Aeronautique restraint system, excluding P/N 358XX-XXX-
YY-ZZZ, having S/Ns 738-1619 (inclusive), that had the rotary buckle
sub-system repaired and a label attached indicating compliance with
Anjou Aero SB No. 358SB-14-101, Revision 1, dated December 12, 2014,
or later revisions.
[[Page 72260]]
(j) Alternative Methods of Compliance (AMOCs)
(1) The Manager, Boston ACO Branch, FAA, has the authority to
approve AMOCs for this AD, if requested using the procedures found
in 14 CFR 39.19. In accordance with 14 CFR 39.19, send your request
to your principal inspector or local Flight Standards District
Office, as appropriate. If sending information directly to the
manager of the certification office, send it to the attention of the
person identified in paragraph (k)(1) of this AD.
(2) Before using any approved AMOC, notify your appropriate
principal inspector, or lacking a principal inspector, the manager
of the local flight standards district office/certificate holding
district office.
(k) Related Information
(1) For more information about this AD, contact Dorie Resnik,
Aerospace Engineer, Boston ACO Branch, FAA, 1200 District Avenue,
Burlington, MA 01803; phone: 781-238-7693; fax: 781-238-7199; email:
[email protected].
(2) Refer to EASA AD 2018-0195, dated September 4, 2018, for
more information. You may examine the EASA AD in the AD docket on
the internet at https://www.regulations.gov by searching for and
locating it in Docket No. FAA-2019-0537.
(3) For service information identified in this AD, contact Anjou
Aeronautique, Strada Livezii nr. 98, 550042, Sibiu, Romania;
telephone: +40 269 243 918; fax: +40 269 243 921; email:
[email protected]. You may view this referenced service
information at the FAA, Engine and Propeller Standards Branch, 1200
District Avenue, Burlington, MA 01803. For information on the
availability of this material at the FAA, call 781-238-7759.
Issued in Burlington, Massachusetts, on December 20, 2019.
Karen M. Grant,
Acting Manager, Engine & Propeller Standards Branch, Aircraft
Certification Service.
[FR Doc. 2019-27939 Filed 12-30-19; 8:45 am]
BILLING CODE 4910-13-P
