Airworthiness Directives; Airbus Helicopters, 15933-15935 [2020-05848]
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Federal Register / Vol. 85, No. 55 / Friday, March 20, 2020 / Rules and Regulations
Group 2 as ‘‘all 777–200 airplanes with GE90
engines through line number 413 without a
forward insulation blanket’’; however, for
paragraph (h) of this AD, Group 2 is defined
as ‘‘all 777–200 airplanes with GE90 engines
without a forward insulation blanket.’’
(3) Boeing Service Bulletin 777–78A0066,
Revision 3, dated April 28, 2011, defines
Group 2 Configuration 1 as ‘‘all 777–200
airplanes with GE90 engines through line
number 413 without a forward insulation
blanket and without the fitting assembly at
the aft insulation blanket location’’; however,
for paragraph (h) of this AD, Group 2
Configuration 1 is defined as ‘‘all 777–200
airplanes with GE90 engines without a
forward insulation blanket and without the
fitting assembly at the aft insulation blanket
location.’’
(4) Boeing Service Bulletin 777–78A0066,
Revision 3, dated April 28, 2011, defines
Group 2 Configuration 2 as ‘‘all 777–200
airplanes with GE90 engines through line
number 413 without a forward insulation
blanket and with the fitting assembly at the
aft insulation blanket location’’; however, for
paragraph (h) of this AD, Group 2
Configuration 2 is defined as ‘‘all 777–200
airplanes with GE90 engines without a
forward insulation blanket and with the
fitting assembly at the aft insulation blanket
location.’’
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(j) Credit for Previous Actions
This paragraph provides credit for the
actions specified in paragraphs (g) and (h) of
this AD, if those actions were performed
before the effective date of this AD using one
of the service bulletins specified in
paragraphs (j)(1) through (3) of this AD.
(1) Boeing Alert Service Bulletin 777–
78A0066, dated June 5, 2008.
(2) Boeing Service Bulletin 777–78A0066,
Revision 1, dated March 12, 2009.
(3) Boeing Alert Service Bulletin 777–
78A0066, Revision 2, dated April 8, 2010.
(k) Alternative Methods of Compliance
(AMOCs)
(1) The Manager, Seattle 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 (l)(1) of
this AD. Information may be emailed to: 9ANM-Seattle-ACO-AMOC-Requests@faa.gov.
(2) Before using any approved AMOC,
notify your appropriate principal inspector,
or lacking a principal inspector, the manager
of the local flight standards district office/
certificate holding district office.
(3) An AMOC that provides an acceptable
level of safety may be used for any repair,
modification, or alteration required by this
AD if it is approved by The Boeing Company
Organization Designation Authorization
(ODA) that has been authorized by the
Manager, Seattle ACO Branch, FAA, to make
those findings. To be approved, the repair
method, modification deviation, or alteration
deviation must meet the certification basis of
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the airplane, and the approval must
specifically refer to this AD.
(4) AMOCs approved previously for AD
2010–26–01 are approved as AMOCs for the
corresponding provisions of paragraph (g) of
this AD.
(l) Related Information
(1) For more information about this AD,
contact James Laubaugh, Aerospace Engineer,
Propulsion Section, FAA, Seattle ACO
Branch, 2200 South 216th St., Des Moines,
WA 98198; phone and fax: 206–231–3622;
email: james.laubaugh@faa.gov.
(2) Service information identified in this
AD that is not incorporated by reference is
available at the addresses specified in
paragraphs (m)(5) and (6) of this AD.
(m) Material Incorporated by Reference
(1) The Director of the Federal Register
approved the incorporation by reference
(IBR) of the service information listed in this
paragraph under 5 U.S.C. 552(a) and 1 CFR
part 51.
(2) You must use this service information
as applicable to do the actions required by
this AD, unless this AD specifies otherwise.
(3) The following service information was
approved for IBR on April 24, 2020.
(i) Boeing Service Bulletin 777–78A0066,
Revision 3, dated April 28, 2011.
(ii) [Reserved]
(4) The following service information was
approved for IBR on January 20, 2011 (75 FR
78594, December 16, 2010).
(i) Boeing Alert Service Bulletin 777–
78A0066, Revision 2, dated April 8, 2010.
(ii) [Reserved]
(5) For service information identified in
this AD, 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.
(6) You may view this 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.
(7) You may view this service information
that is incorporated by reference at the
National Archives and Records
Administration (NARA). For information on
the availability of this material at NARA,
email fedreg.legal@nara.gov, or go to: https://
www.archives.gov/federal-register/cfr/ibrlocations.html.
Issued on March 9, 2020.
Lance T. Gant,
Director, Compliance & Airworthiness
Division, Aircraft Certification Service.
[FR Doc. 2020–05709 Filed 3–19–20; 8:45 am]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2019–0882; Product
Identifier 2018–SW–113–AD; Amendment
39–19873; AD 2020–05–23]
RIN 2120–AA64
Airworthiness Directives; Airbus
Helicopters
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule.
AGENCY:
SUMMARY: The FAA is adopting a new
airworthiness directive (AD) for Airbus
Helicopters Model AS332C, AS332C1,
AS332L, and AS332L1 helicopters. This
AD requires 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 AD was
prompted by reports of an elongated
attachment screw and loss of tightening
torque of the nut. The actions of this AD
are intended to address an unsafe
condition on these products.
DATES: This AD is effective April 24,
2020.
The Director of the Federal Register
approved the incorporation by reference
of a certain document listed in this AD
as of April 24, 2020.
ADDRESSES: For service information
identified in this final rule, contact
Airbus Helicopters, 2701 N. Forum
Drive, Grand Prairie, TX 75052;
telephone 972–641–0000 or 800–232–
0323; fax 972–641–3775; or at https://
www.airbus.com/helicopters/services/
technical-support.html. You may view
this 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–2019–0882.
Examining the AD Docket
You may examine the AD docket on
the internet at https://
www.regulations.gov in 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
AD, the European Union Aviation
Safety Agency (previously European
Aviation Safety Agency) (EASA) AD,
any service information that is
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Federal Register / Vol. 85, No. 55 / Friday, March 20, 2020 / Rules and Regulations
incorporated by reference, any
comments received, and other
information. The street address for
Docket Operations is Docket Operations,
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: 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:
jbell on DSKJLSW7X2PROD with RULES
Discussion
On November 8, 2019, at 84 FR 60349,
the Federal Register published the
FAA’s notice of proposed rulemaking
(NPRM), which proposed to amend 14
CFR part 39 by adding an AD that
would apply to Airbus Helicopters
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. The NPRM proposed to 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), the NPRM proposed to
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, the NPRM
proposed to require removing the nut
and inspecting the convex and concave
washers for bent parts and corrosion. If
any washers are bent or corroded, the
NPRM proposed to require removing the
washers from service. If the length ‘‘L’’
measurement of any attachment screw is
greater than 59.3 mm (2.334 in), the
NPRM proposed to require replacing the
attachment fitting and the set of four
screws. The proposed requirements
were intended to prevent structural
failure of an MGB attachment fitting,
detachment of an MGB suspension bar,
and subsequent loss of control of the
helicopter.
The NPRM was prompted by EASA
AD No. 2018–0282, dated December 19,
2018 (EASA AD 2018–0282), issued by
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EASA, which is the Technical Agent for
the Member States of the European
Union, to correct an unsafe condition
for Airbus Helicopters Model AS332C,
AS332C1, AS332L, and AS332L1
helicopters. 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 onetime 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.
Comments
The FAA gave the public the
opportunity to participate in developing
this AD. Benjamin Pico and Patrick
Imperatrice commented that they
support the NPRM.
FAA’s Determination
These helicopters have been approved
by EASA and are approved for operation
in the United States. Pursuant to the
FAA’s bilateral agreement with the
European Union, EASA has notified the
FAA of the unsafe condition described
in its AD. The FAA is issuing this AD
after evaluating all information
provided by EASA and determining the
unsafe condition exists and is likely to
exist or develop on other helicopters of
these same type designs and that air
safety and the public interest require
adopting the AD requirements as
proposed.
Interim Action
The FAA considers this 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.
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Differences Between This AD and the
EASA AD
The EASA AD requires the operator to
perform a torque check and report the
value to Airbus, whereas this AD does
not.
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.
Costs of Compliance
The FAA estimates that this AD
affects14 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 takes
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 takes about 16
work-hours and parts cost $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 helicopters identified in this
rulemaking action.
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Federal Register / Vol. 85, No. 55 / Friday, March 20, 2020 / Rules and Regulations
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
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):
■
2020–05–23 Airbus Helicopters:
Amendment 39–19873; Docket No.
FAA–2019–0882; Product Identifier
2018–SW–113–AD.
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(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.
VerDate Sep<11>2014
17:04 Mar 19, 2020
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(c) Effective Date
This AD becomes effective April 24, 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 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
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15935
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 Union Aviation Safety Agency
(previously 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 Docket No. FAA–
2019–0882.
(h) Subject
Joint Aircraft Service Component (JASC)
Code: 6320, Main Rotor Gearbox.
(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) Airbus Helicopters Alert Service
Bulletin No. AS332–53.02.04, Revision 0,
dated November 21, 2018.
(ii) [Reserved]
(3) For service information identified in
this AD, contact Airbus Helicopters, 2701 N.
Forum Drive, Grand Prairie, TX 75052;
telephone 972–641–0000 or 800–232–0323;
fax 972–641–3775; or at https://
www.airbus.com/helicopters/services/
technical-support.html.
(4) You may view this service information
at FAA, Office of the Regional Counsel,
Southwest Region, 10101 Hillwood Pkwy,
Room 6N–321, Fort Worth, TX 76177. For
information on the availability of this
material at the FAA, call 817–222–5110.
(5) You may view this service information
that is incorporated by reference at the
National Archives and Records
Administration (NARA). For information on
the availability of this material at NARA,
email fedreg.legal@nara.gov, or go to: https://
www.archives.gov/federal-register/cfr/ibrlocations.html.
Issued on March 16, 2020.
Lance T. Gant,
Director, Compliance & Airworthiness
Division, Aircraft Certification Service.
[FR Doc. 2020–05848 Filed 3–19–20; 8:45 am]
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]]>Agencies
[Federal Register Volume 85, Number 55 (Friday, March 20, 2020)]
[Rules and Regulations]
[Pages 15933-15935]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2020-05848]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2019-0882; Product Identifier 2018-SW-113-AD; Amendment
39-19873; AD 2020-05-23]
RIN 2120-AA64
Airworthiness Directives; Airbus Helicopters
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Final rule.
-----------------------------------------------------------------------
SUMMARY: The FAA is adopting a new airworthiness directive (AD) for
Airbus Helicopters Model AS332C, AS332C1, AS332L, and AS332L1
helicopters. This AD requires 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 AD was prompted
by reports of an elongated attachment screw and loss of tightening
torque of the nut. The actions of this AD are intended to address an
unsafe condition on these products.
DATES: This AD is effective April 24, 2020.
The Director of the Federal Register approved the incorporation by
reference of a certain document listed in this AD as of April 24, 2020.
ADDRESSES: For service information identified in this final rule,
contact Airbus Helicopters, 2701 N. Forum Drive, Grand Prairie, TX
75052; telephone 972-641-0000 or 800-232-0323; fax 972-641-3775; or at
https://www.airbus.com/helicopters/services/technical-support.html. You
may view this 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-2019-
0882.
Examining the AD Docket
You may examine the AD docket on the internet at https://www.regulations.gov in 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 AD, the European Union
Aviation Safety Agency (previously European Aviation Safety Agency)
(EASA) AD, any service information that is
[[Page 15934]]
incorporated by reference, any comments received, and other
information. The street address for Docket Operations is Docket
Operations, 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: 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:
Discussion
On November 8, 2019, at 84 FR 60349, the Federal Register published
the FAA's notice of proposed rulemaking (NPRM), which proposed to amend
14 CFR part 39 by adding an AD that would apply to Airbus Helicopters
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. The NPRM proposed to 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), the NPRM proposed
to 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, the NPRM proposed to
require removing the nut and inspecting the convex and concave washers
for bent parts and corrosion. If any washers are bent or corroded, the
NPRM proposed to require removing the washers from service. If the
length ``L'' measurement of any attachment screw is greater than 59.3
mm (2.334 in), the NPRM proposed to require replacing the attachment
fitting and the set of four screws. The proposed requirements were
intended to prevent structural failure of an MGB attachment fitting,
detachment of an MGB suspension bar, and subsequent loss of control of
the helicopter.
The NPRM was prompted by EASA AD No. 2018-0282, dated December 19,
2018 (EASA AD 2018-0282), issued by EASA, which is the Technical Agent
for the Member States of the European Union, to correct an unsafe
condition for Airbus Helicopters Model AS332C, AS332C1, AS332L, and
AS332L1 helicopters. 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.
Comments
The FAA gave the public the opportunity to participate in
developing this AD. Benjamin Pico and Patrick Imperatrice commented
that they support the NPRM.
FAA's Determination
These helicopters have been approved by EASA and are approved for
operation in the United States. Pursuant to the FAA's bilateral
agreement with the European Union, EASA has notified the FAA of the
unsafe condition described in its AD. The FAA is issuing this AD after
evaluating all information provided by EASA and determining the unsafe
condition exists and is likely to exist or develop on other helicopters
of these same type designs and that air safety and the public interest
require adopting the AD requirements as proposed.
Interim Action
The FAA considers this 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.
Differences Between This AD and the EASA AD
The EASA AD requires the operator to perform a torque check and
report the value to Airbus, whereas this AD does not.
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.
Costs of Compliance
The FAA estimates that this AD affects14 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
takes 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 takes
about 16 work-hours and parts cost $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 helicopters identified in this rulemaking action.
[[Page 15935]]
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 (AD):
2020-05-23 Airbus Helicopters: Amendment 39-19873; 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) Effective Date
This AD becomes effective April 24, 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 Union Aviation
Safety Agency (previously 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 Docket No. FAA-2019-
0882.
(h) Subject
Joint Aircraft Service Component (JASC) Code: 6320, Main Rotor
Gearbox.
(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) Airbus Helicopters Alert Service Bulletin No. AS332-
53.02.04, Revision 0, dated November 21, 2018.
(ii) [Reserved]
(3) For service information identified in this AD, contact
Airbus Helicopters, 2701 N. Forum Drive, Grand Prairie, TX 75052;
telephone 972-641-0000 or 800-232-0323; fax 972-641-3775; or at
https://www.airbus.com/helicopters/services/technical-support.html.
(4) You may view this service information at FAA, Office of the
Regional Counsel, Southwest Region, 10101 Hillwood Pkwy, Room 6N-
321, Fort Worth, TX 76177. For information on the availability of
this material at the FAA, call 817-222-5110.
(5) You may view this service information that is incorporated
by reference at the National Archives and Records Administration
(NARA). For information on the availability of this material at
NARA, email [email protected], or go to: https://www.archives.gov/federal-register/cfr/ibr-locations.html.
Issued on March 16, 2020.
Lance T. Gant,
Director, Compliance & Airworthiness Division, Aircraft Certification
Service.
[FR Doc. 2020-05848 Filed 3-19-20; 8:45 am]
BILLING CODE 4910-13-P
