Airworthiness Directives; Airbus Helicopters, 60349-60351 [2019-24342]
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Federal Register / Vol. 84, No. 217 / Friday, November 8, 2019 / Proposed Rules
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Stephen Alexander Vaden,
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Agriculture.
In concurrence:
Emory A. Rounds, III,
Director, U.S. Office of Government Ethics.
[FR Doc. 2019–24082 Filed 11–7–19; 8:45 am]
BILLING CODE 3410–90–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2019–0882; Product
Identifier 2018–SW–113–AD]
RIN 2120–AA64
Airworthiness Directives; Airbus
Helicopters
Federal Aviation
Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
The FAA proposes to adopt a
new airworthiness directive (AD) for
Airbus Helicopters Model AS332C,
AS332C1, AS332L, and AS332L1
helicopters. This proposed AD would
require inspecting the attachment
screws of each main gearbox (MGB)
suspension bar rear attachment fitting,
and depending on the outcome,
applying a sealing compound,
performing further inspections, and
replacing affected parts. This proposed
AD is prompted by reports of an
elongated attachment screw and loss of
tightening torque of the nut. The actions
of this proposed AD are intended to
address an unsafe condition on these
products.
DATES: The FAA must receive comments
on this proposed AD by January 7, 2020.
ADDRESSES: You may send comments by
any of the following methods:
SUMMARY:
PO 00000
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60349
• Federal eRulemaking Docket: Go to
https://www.regulations.gov. Follow the
online instructions for sending your
comments electronically.
• Fax: 202–493–2251.
• Mail: Send comments to the U.S.
Department of Transportation, Docket
Operations, M–30, West Building
Ground Floor, Room W12–140, 1200
New Jersey Avenue SE, Washington, DC
20590–0001.
• Hand Delivery: Deliver to the
‘‘Mail’’ address between 9 a.m. and 5
p.m., Monday through Friday, except
Federal holidays.
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–
0882; 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 proposed
AD, the European Aviation Safety
Agency (EASA) AD, the economic
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 service information identified in
this proposed rule, contact Airbus
Helicopters, 2701 N. Forum Drive,
Grand Prairie, TX 75052; telephone
(972) 641–0000 or (800) 232–0323; fax
(972) 641–3775; or at https://
www.airbus.com/helicopters/services/
technical-support.html. You may review
the referenced service information at the
FAA, Office of the Regional Counsel,
Southwest Region, 10101 Hillwood
Pkwy, Room 6N–321, Fort Worth, TX
76177.
Matt
Fuller, Senior Aviation Safety Engineer,
Safety Management Section, Rotorcraft
Standards Branch, FAA, 10101
Hillwood Pkwy., Fort Worth, TX 76177;
telephone (817) 222–5110; email
matthew.fuller@faa.gov.
SUPPLEMENTARY INFORMATION:
FOR FURTHER INFORMATION CONTACT:
Comments Invited
The FAA invites you to participate in
this rulemaking by submitting written
comments, data, or views. The FAA also
invites comments relating to the
economic, environmental, energy, or
federalism impacts that might result
from adopting the proposals in this
document. The most helpful comments
reference a specific portion of the
proposal, explain the reason for any
recommended change, and include
supporting data. To ensure the docket
does not contain duplicate comments,
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Federal Register / Vol. 84, No. 217 / Friday, November 8, 2019 / Proposed Rules
commenters should send only one copy
of written comments, or if comments are
filed electronically, commenters should
submit only one time.
The FAA will file in the docket all
comments that the FAA receives, as
well as a report summarizing each
substantive public contact with FAA
personnel concerning this proposed
rulemaking. Before acting on this
proposal, the FAA will consider all
comments received on or before the
closing date for comments. The FAA
will consider comments filed after the
comment period has closed if it is
possible to do so without incurring
expense or delay. The FAA may change
this proposal in light of the comments
received.
khammond on DSKJM1Z7X2PROD with PROPOSALS
Discussion
EASA, which is the Technical Agent
for the Member States of the European
Union, has issued EASA AD No. 2018–
0282, dated December 19, 2018 (EASA
AD 2018–0282), to correct an unsafe
condition for Airbus Helicopters
(formerly Eurocopter, Eurocopter
France, Aerospatiale) Model AS332C,
AS332C1, AS332L, and AS332L1
helicopters, delivered to the first owner
or customer before September 1, 2018,
and with attachment screws part
number (P/N) 330A22013520 installed
with MGB right hand (RH) side rear
attachment fitting P/N 330A22270207
and left hand (LH) side rear attachment
fitting P/N 330A22270206 of the MGB
suspension bars.
EASA advises that occurrences were
reported of elongated attachment screws
and loss of tightening torque of the nut
installed on the affected part. EASA also
advises that an investigation is ongoing
to determine the root cause of this
event. EASA states this condition could
lead to structural failure of an MGB rear
attachment fitting and possibly result in
detachment of an MGB suspension bar.
Accordingly, EASA AD 2018–0282
requires a one-time inspection of each
attachment screw for the number of
threads that protrude beyond its bolt
and depending on the outcome,
applying a sealing compound on the
nuts, and convex and concave washers;
measuring the height of the protruding
threads; inspecting the tightening torque
of the nuts; inspecting the upper and
lower convex and concave washers;
measuring and inspecting removed
attachment screws; and replacing
affected parts. EASA AD 2018–0282 also
requires reporting information to Airbus
Helicopters. EASA states EASA AD
2018–0282 is considered to be an
interim action and further AD action
may follow.
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FAA’s Determination
These helicopters have been approved
by EASA and are approved for operation
in the United States. Pursuant to the
FAA’s bilateral agreement with the
European Union, EASA has notified the
FAA of the unsafe condition described
in its AD. The FAA is proposing this AD
after evaluating all known relevant
information and determined that an
unsafe condition is likely to exist or
develop on other products of the same
type designs.
Related Service Information Under 1
CFR Part 51
The FAA reviewed Airbus Helicopters
Alert Service Bulletin No. AS332–
53.02.04, Revision 0, dated November
21, 2018 which specifies checking the
number of threads that protrude beyond
the bolt of the attachment screws on the
RH and LH rear attachment fittings of
the MGB. This service information also
specifies a one-time inspection of the
affected parts and depending on
findings, accomplishment of applicable
corrective actions.
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.
Proposed AD Requirements
This proposed AD would require
inspecting each screw on the RH and LH
rear attachment by identifying the
number of threads ‘‘F’’ that extend
beyond the nut. If there are 2 or less
threads on each affected part, or if there
are 3 or more threads on any affected
part with a thread height less than 5 mm
(0.196 in), this proposed AD would
require applying a sealing compound on
the nuts, and convex and concave
washers. If there are 3 or more threads
on any affected part with a thread height
of 5 mm (0.196 in) or more, this
proposed AD would require removing
the nut and inspecting the convex and
concave washers for bent parts and
corrosion. If any washers are bent or
corroded, this proposed AD would
require removing the washers from
service. If the length ‘‘L’’ measurement
of any attachment screw is greater than
59.3 mm (2.334 in), this proposed AD
would require replacing the attachment
fitting and the set of four screws.
Differences Between This Proposed AD
and the EASA AD
The EASA AD requires the operator to
perform a torque check and report the
value to Airbus, whereas this proposed
AD would not.
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Interim Action
The FAA considers this proposed AD
interim action. The design approval
holder is currently developing a
modification that will address the
unsafe condition identified in this AD.
Once this modification is developed,
approved, and available, the FAA might
consider additional rulemaking.
Costs of Compliance
The FAA estimates that this proposed
AD would affect 14 helicopters of U.S.
Registry. The FAA estimates that
operators may incur the following costs
in order to comply with this AD. Labor
costs are estimated at $85 per workhour.
Inspecting the number of threads and
applying a sealing compound would
take about 3 work-hours for an
estimated cost of $255 per helicopter
and $3,570 for the U.S. fleet.
Replacing an attachment fitting and
the set of four screws would take about
16 work-hours and parts would cost
about $6,330 for an estimated
replacement cost of $7,690.
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.
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, I certify
this proposed regulation:
1. Is not a ‘‘significant regulatory
action’’ under Executive Order 12866,
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Federal Register / Vol. 84, No. 217 / Friday, November 8, 2019 / Proposed Rules
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.
The FAA prepared an economic
evaluation of the estimated costs to
comply with this proposed AD and
placed it in the AD docket.
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
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 (AD):
■
Airbus Helicopters: Docket No. FAA–2019–
0882; Product Identifier 2018–SW–113–
AD.
(a) Applicability
This AD applies to Airbus Helicopters
Model AS332C, AS332C1, AS332L, and
AS332L1 helicopters, certificated in any
category, delivered to the first owner or
customer before September 1, 2018, and with
attachment screws part number (P/N)
330A22013520 installed with main gearbox
(MGB) right hand (RH) side rear attachment
fitting P/N 330A22270207 and left hand (LH)
side rear attachment fitting P/N
330A22270206 of the MGB suspension bars.
khammond on DSKJM1Z7X2PROD with PROPOSALS
(b) Unsafe Condition
This AD defines the unsafe condition as
elongation of the attachment screws and loss
of tightening torque of the nut. This
condition could result in structural failure of
an MGB attachment fitting, detachment of an
MGB suspension bar, and subsequent loss of
control of the helicopter.
(c) Comments Due Date
The FAA must receive comments by
January 7, 2020.
(d) Compliance
You are responsible for performing each
action required by this AD within the
specified compliance time unless it has
already been accomplished prior to that time.
(e) Required Actions
Within 110 hours time-in-service, remove
the sealing compound and inspect each
VerDate Sep<11>2014
16:12 Nov 07, 2019
Jkt 250001
screw on the RH and LH rear attachment
fitting by identifying the number of threads
‘‘F’’ that extend beyond the nut as shown in
Detail ‘‘B’’ of Figure 2 of Airbus Helicopter
Alert Service Bulletin No. AS332–53.02.04,
Revision 0, dated November 21, 2018 (ASB
AS332–53.02.04).
(1) If there are 2 or less threads on each of
the four screws; or there are 3 or more
threads on any screw with a thread height
‘‘H’’ less than 5 mm (0.196 in), before further
flight, apply a sealing compound on the nuts,
and convex and concave washers.
(2) If there are 3 or more threads on any
screw with a thread height ‘‘H’’ of 5 mm
(0.196 in) or more, before further flight, do
the following, and for more than one screw,
do one at a time while working in a cross
pattern: Remove from service the nut; and
remove the screw from the helicopter and
measure the length ‘‘L’’ of the screw as
shown in Detail ‘‘D’’ of Figure 2 of ASB
AS332–53.02.04.
(i) If any washers are bent or corroded,
before further flight, remove from service the
washers.
(ii) If the length ‘‘L’’ measurement is less
than or equal to 59.3 mm (2.334 in) for each
screw removed as required by paragraph
(e)(2) of this AD, visually inspect the screw
for corrosion and cracks.
(A) For each screw with corrosion or a
crack, before further flight, replace the screw
with an airworthy screw.
(B) For any screw with no corrosion or
cracks, before further flight, re-install the
screw and washers. Install a new nut and
apply sealant.
(iii) If the length ‘‘L’’ measurement is
greater than 59.3 mm (2.334 in) for any screw
removed as required by paragraph (e)(2) of
this AD, before further flight, replace the rear
attachment fitting that the screw was
removed from and its set of four screws,
washers, and nuts, and apply sealant as
shown in Figures 2 and 3 of ASB AS332–
53.02.04.
(f) 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: Matt Fuller, Senior Aviation
Safety Engineer, Safety Management Section,
Rotorcraft Standards Branch, FAA, 10101
Hillwood Pkwy., Fort Worth, TX 76177;
telephone (817) 222–5110; email 9-ASWFTW-AMOC-Requests@faa.gov.
(2) For operations conducted under a 14
CFR part 119 operating certificate or under
14 CFR part 91, subpart K, the FAA suggests
that you notify your principal inspector, or
lacking a principal inspector, the manager of
the local flight standards district office or
certificate holding district office before
operating any aircraft complying with this
AD through an AMOC.
(g) Additional Information
The subject of this AD is addressed in
European Aviation Safety Agency (EASA) AD
No. 2018–0282, dated December 19, 2018.
You may view the EASA AD on the internet
at https://www.regulations.gov in the AD
Docket.
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60351
(h) Subject
Joint Aircraft Service Component (JASC)
Code: 6320, Main Rotor Gearbox.
Issued in Fort Worth, Texas, on October 31,
2019.
Helene T. Gandy,
Acting Director, Compliance & Airworthiness
Division, Aircraft Certification Service.
[FR Doc. 2019–24342 Filed 11–7–19; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2019–0859; Product
Identifier 2019–NM–114–AD]
RIN 2120–AA64
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
certain 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 results from fuel system
reviews conducted by the manufacturer.
This proposed AD would require
replacement of the bonding jumpers on
the auxiliary power unit (APU) fuel
pump. This proposed AD would also
require, for certain airplanes,
installation of a second bonding jumper;
an inspection of the override/jettison
fuel pumps and transfer/jettison fuel
pumps to determine if the bonding
jumper has a one-piece braid or twopiece braid and replacement of the
bonding jumper if necessary; and
replacement of the bonding jumper on
the electrical scavenge fuel pump. 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 December 23,
2019.
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–
SUMMARY:
E:\FR\FM\08NOP1.SGM
08NOP1
]]>Agencies
[Federal Register Volume 84, Number 217 (Friday, November 8, 2019)]
[Proposed Rules]
[Pages 60349-60351]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2019-24342]
=======================================================================
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2019-0882; Product Identifier 2018-SW-113-AD]
RIN 2120-AA64
Airworthiness Directives; Airbus Helicopters
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking (NPRM).
-----------------------------------------------------------------------
SUMMARY: The FAA proposes to adopt a new airworthiness directive (AD)
for Airbus Helicopters Model AS332C, AS332C1, AS332L, and AS332L1
helicopters. This proposed AD would require inspecting the attachment
screws of each main gearbox (MGB) suspension bar rear attachment
fitting, and depending on the outcome, applying a sealing compound,
performing further inspections, and replacing affected parts. This
proposed AD is prompted by reports of an elongated attachment screw and
loss of tightening torque of the nut. The actions of this proposed AD
are intended to address an unsafe condition on these products.
DATES: The FAA must receive comments on this proposed AD by January 7,
2020.
ADDRESSES: You may send comments by any of the following methods:
Federal eRulemaking Docket: Go to https://www.regulations.gov. Follow the online instructions for sending your
comments electronically.
Fax: 202-493-2251.
Mail: Send comments to the U.S. Department of
Transportation, Docket Operations, M-30, West Building Ground Floor,
Room W12-140, 1200 New Jersey Avenue SE, Washington, DC 20590-0001.
Hand Delivery: Deliver to the ``Mail'' address between 9
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
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-
0882; 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 proposed AD, the European Aviation Safety Agency (EASA) AD, the
economic 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 service information identified in this proposed rule, contact
Airbus Helicopters, 2701 N. Forum Drive, Grand Prairie, TX 75052;
telephone (972) 641-0000 or (800) 232-0323; fax (972) 641-3775; or at
https://www.airbus.com/helicopters/services/technical-support.html. You
may review the referenced service information at the FAA, Office of the
Regional Counsel, Southwest Region, 10101 Hillwood Pkwy, Room 6N-321,
Fort Worth, TX 76177.
FOR FURTHER INFORMATION CONTACT: Matt Fuller, Senior Aviation Safety
Engineer, Safety Management Section, Rotorcraft Standards Branch, FAA,
10101 Hillwood Pkwy., Fort Worth, TX 76177; telephone (817) 222-5110;
email [email protected].
SUPPLEMENTARY INFORMATION:
Comments Invited
The FAA invites you to participate in this rulemaking by submitting
written comments, data, or views. The FAA also invites comments
relating to the economic, environmental, energy, or federalism impacts
that might result from adopting the proposals in this document. The
most helpful comments reference a specific portion of the proposal,
explain the reason for any recommended change, and include supporting
data. To ensure the docket does not contain duplicate comments,
[[Page 60350]]
commenters should send only one copy of written comments, or if
comments are filed electronically, commenters should submit only one
time.
The FAA will file in the docket all comments that the FAA receives,
as well as a report summarizing each substantive public contact with
FAA personnel concerning this proposed rulemaking. Before acting on
this proposal, the FAA will consider all comments received on or before
the closing date for comments. The FAA will consider comments filed
after the comment period has closed if it is possible to do so without
incurring expense or delay. The FAA may change this proposal in light
of the comments received.
Discussion
EASA, which is the Technical Agent for the Member States of the
European Union, has issued EASA AD No. 2018-0282, dated December 19,
2018 (EASA AD 2018-0282), to correct an unsafe condition for Airbus
Helicopters (formerly Eurocopter, Eurocopter France, Aerospatiale)
Model AS332C, AS332C1, AS332L, and AS332L1 helicopters, delivered to
the first owner or customer before September 1, 2018, and with
attachment screws part number (P/N) 330A22013520 installed with MGB
right hand (RH) side rear attachment fitting P/N 330A22270207 and left
hand (LH) side rear attachment fitting P/N 330A22270206 of the MGB
suspension bars.
EASA advises that occurrences were reported of elongated attachment
screws and loss of tightening torque of the nut installed on the
affected part. EASA also advises that an investigation is ongoing to
determine the root cause of this event. EASA states this condition
could lead to structural failure of an MGB rear attachment fitting and
possibly result in detachment of an MGB suspension bar. Accordingly,
EASA AD 2018-0282 requires a one-time inspection of each attachment
screw for the number of threads that protrude beyond its bolt and
depending on the outcome, applying a sealing compound on the nuts, and
convex and concave washers; measuring the height of the protruding
threads; inspecting the tightening torque of the nuts; inspecting the
upper and lower convex and concave washers; measuring and inspecting
removed attachment screws; and replacing affected parts. EASA AD 2018-
0282 also requires reporting information to Airbus Helicopters. EASA
states EASA AD 2018-0282 is considered to be an interim action and
further AD action may follow.
FAA's Determination
These helicopters have been approved by EASA and are approved for
operation in the United States. Pursuant to the FAA's bilateral
agreement with the European Union, EASA has notified the FAA of the
unsafe condition described in its AD. The FAA is proposing this AD
after evaluating all known relevant information and determined that an
unsafe condition is likely to exist or develop on other products of the
same type designs.
Related Service Information Under 1 CFR Part 51
The FAA reviewed Airbus Helicopters Alert Service Bulletin No.
AS332-53.02.04, Revision 0, dated November 21, 2018 which specifies
checking the number of threads that protrude beyond the bolt of the
attachment screws on the RH and LH rear attachment fittings of the MGB.
This service information also specifies a one-time inspection of the
affected parts and depending on findings, accomplishment of applicable
corrective actions.
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.
Proposed AD Requirements
This proposed AD would require inspecting each screw on the RH and
LH rear attachment by identifying the number of threads ``F'' that
extend beyond the nut. If there are 2 or less threads on each affected
part, or if there are 3 or more threads on any affected part with a
thread height less than 5 mm (0.196 in), this proposed AD would require
applying a sealing compound on the nuts, and convex and concave
washers. If there are 3 or more threads on any affected part with a
thread height of 5 mm (0.196 in) or more, this proposed AD would
require removing the nut and inspecting the convex and concave washers
for bent parts and corrosion. If any washers are bent or corroded, this
proposed AD would require removing the washers from service. If the
length ``L'' measurement of any attachment screw is greater than 59.3
mm (2.334 in), this proposed AD would require replacing the attachment
fitting and the set of four screws.
Differences Between This Proposed AD and the EASA AD
The EASA AD requires the operator to perform a torque check and
report the value to Airbus, whereas this proposed AD would not.
Interim Action
The FAA considers this proposed AD interim action. The design
approval holder is currently developing a modification that will
address the unsafe condition identified in this AD. Once this
modification is developed, approved, and available, the FAA might
consider additional rulemaking.
Costs of Compliance
The FAA estimates that this proposed AD would affect 14 helicopters
of U.S. Registry. The FAA estimates that operators may incur the
following costs in order to comply with this AD. Labor costs are
estimated at $85 per work-hour.
Inspecting the number of threads and applying a sealing compound
would take about 3 work-hours for an estimated cost of $255 per
helicopter and $3,570 for the U.S. fleet.
Replacing an attachment fitting and the set of four screws would
take about 16 work-hours and parts would cost about $6,330 for an
estimated replacement cost of $7,690.
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.
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, I certify this proposed regulation:
1. Is not a ``significant regulatory action'' under Executive Order
12866,
[[Page 60351]]
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.
The FAA prepared an economic evaluation of the estimated costs to
comply with this proposed AD and placed it in the AD docket.
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 adding the following new airworthiness
directive (AD):
Airbus Helicopters: Docket No. FAA-2019-0882; Product Identifier
2018-SW-113-AD.
(a) Applicability
This AD applies to Airbus Helicopters Model AS332C, AS332C1,
AS332L, and AS332L1 helicopters, certificated in any category,
delivered to the first owner or customer before September 1, 2018,
and with attachment screws part number (P/N) 330A22013520 installed
with main gearbox (MGB) right hand (RH) side rear attachment fitting
P/N 330A22270207 and left hand (LH) side rear attachment fitting P/N
330A22270206 of the MGB suspension bars.
(b) Unsafe Condition
This AD defines the unsafe condition as elongation of the
attachment screws and loss of tightening torque of the nut. This
condition could result in structural failure of an MGB attachment
fitting, detachment of an MGB suspension bar, and subsequent loss of
control of the helicopter.
(c) Comments Due Date
The FAA must receive comments by January 7, 2020.
(d) Compliance
You are responsible for performing each action required by this
AD within the specified compliance time unless it has already been
accomplished prior to that time.
(e) Required Actions
Within 110 hours time-in-service, remove the sealing compound
and inspect each screw on the RH and LH rear attachment fitting by
identifying the number of threads ``F'' that extend beyond the nut
as shown in Detail ``B'' of Figure 2 of Airbus Helicopter Alert
Service Bulletin No. AS332-53.02.04, Revision 0, dated November 21,
2018 (ASB AS332-53.02.04).
(1) If there are 2 or less threads on each of the four screws;
or there are 3 or more threads on any screw with a thread height
``H'' less than 5 mm (0.196 in), before further flight, apply a
sealing compound on the nuts, and convex and concave washers.
(2) If there are 3 or more threads on any screw with a thread
height ``H'' of 5 mm (0.196 in) or more, before further flight, do
the following, and for more than one screw, do one at a time while
working in a cross pattern: Remove from service the nut; and remove
the screw from the helicopter and measure the length ``L'' of the
screw as shown in Detail ``D'' of Figure 2 of ASB AS332-53.02.04.
(i) If any washers are bent or corroded, before further flight,
remove from service the washers.
(ii) If the length ``L'' measurement is less than or equal to
59.3 mm (2.334 in) for each screw removed as required by paragraph
(e)(2) of this AD, visually inspect the screw for corrosion and
cracks.
(A) For each screw with corrosion or a crack, before further
flight, replace the screw with an airworthy screw.
(B) For any screw with no corrosion or cracks, before further
flight, re-install the screw and washers. Install a new nut and
apply sealant.
(iii) If the length ``L'' measurement is greater than 59.3 mm
(2.334 in) for any screw removed as required by paragraph (e)(2) of
this AD, before further flight, replace the rear attachment fitting
that the screw was removed from and its set of four screws, washers,
and nuts, and apply sealant as shown in Figures 2 and 3 of ASB
AS332-53.02.04.
(f) 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:
Matt Fuller, Senior Aviation Safety Engineer, Safety Management
Section, Rotorcraft Standards 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 (EASA) AD No. 2018-0282, dated December 19, 2018. You may
view the EASA AD on the internet at https://www.regulations.gov in
the AD Docket.
(h) Subject
Joint Aircraft Service Component (JASC) Code: 6320, Main Rotor
Gearbox.
Issued in Fort Worth, Texas, on October 31, 2019.
Helene T. Gandy,
Acting Director, Compliance & Airworthiness Division, Aircraft
Certification Service.
[FR Doc. 2019-24342 Filed 11-7-19; 8:45 am]
BILLING CODE 4910-13-P
