Airworthiness Directives; Airbus Helicopters, 67246-67248 [2019-26428]
Download as PDF
<![CDATA[
67246
Federal Register / Vol. 84, No. 236 / Monday, December 9, 2019 / Proposed Rules
TABLE 3—COST ESTIMATE FOR IMMIGRATION ADJUDICATION AND NATURALIZATION SERVICES
IEFA
activity
hours
Fiscal year
FY
FY
FY
FY
FY
2017 .............................................................................
2018 .............................................................................
2019 .............................................................................
2020 .............................................................................
2021 * ...........................................................................
517,531
547,774
572,004
601,748
601,748
HSI
1811
FTE
305
323
337
355
355
HSI FTE
Frontline
(1811 series)
cost
(HSI 1811
FTE * fully
burdened 1811
FTE cost)
Mission support
FTE (HSI 1811
FTE * MS FTE
to 1811 ratio)
$77,750,217
82,293,713
85,933,858
90,402,418
92,120,064
HSI mission
support cost
(MS FTE * fully
burdened MS FTE
cost)
96
102
107
113
113
$17,021,439
18,016,122
18,813,040
19,791,318
20,167,353
Total cost
(HSI 1811 FTE
frontline cost +
HSI MS cost)
$94,771,656
100,309,835
104,746,897
110,193,736
112,287,417
* Denotes forecast.
As a result, DHS projects an annual
transfer to ICE of $112,287,417, rather
than $207.6 million. Because the
projected annual transfer to ICE is lower
than DHS previously proposed, the
proposed fee levels would be reduced
accordingly. As the NPRM stated, the
fees that DHS proposed may change in
the final rule based on policy decisions,
in response to public comments,
intervening legislation, and other
reasons. 84 FR 62327. In the NPRM, to
reduce uncertainty, USCIS laid out what
the fees would be if certain conditions
materialize and explained that the final
fees would be one of the scenarios
presented, or an amount in between the
highest and lowest fees proposed. Id.
Table 21 in the NPRM outlines the
proposed fee levels contained in the
proposed rule that would result if the
ICE transfer of $207.6 million either did
or did not occur. Because the estimated
amount of the transfer is $112,287,417
million, the resulting fee schedule
would, all else remaining the same, be
somewhere between those two levels.
Chad F. Wolf,
Acting Secretary.
[FR Doc. 2019–26521 Filed 12–6–19; 8:45 am]
BILLING CODE 9111–97–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2019–1015; Product
Identifier 2018–SW–104–AD]
khammond on DSKJM1Z7X2PROD with PROPOSALS
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
SUMMARY:
VerDate Sep<11>2014
17:14 Dec 06, 2019
Jkt 250001
Airbus Helicopters Model AS332C,
AS332C1, AS332L, and AS332L1
helicopters. This proposed AD would
require determining the accumulated
hours time-in-service (TIS) of certain
part-numbered main gearbox (MGB)
suspension bar attachment fittings
(fittings) and bolts, and would establish
new life limits. This proposed AD is
prompted by the outcome of tests and
analyses performed by Airbus
Helicopters. 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 February 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–
1015; 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
PO 00000
Frm 00005
Fmt 4702
Sfmt 4702
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
matthew.fuller@faa.gov.
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,
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 the FAA receives 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
the FAA receives.
E:\FR\FM\09DEP1.SGM
09DEP1
Federal Register / Vol. 84, No. 236 / Monday, December 9, 2019 / Proposed Rules
Discussion
EASA, which is the Technical Agent
for the Member States of the European
Union, has issued EASA AD No. 2018–
0260, dated December 3, 2018 (EASA
AD 2018–0260), to correct an unsafe
condition for Airbus Helicopters
(formerly Eurocopter, Eurocopter
France, Aerospatiale) Model AS 332 C,
AS 332 C1, AS 332 L, and AS 332 L1
helicopters.
From review of reported Model EC
225 LP data, EASA advises that the
installation of the MGB upper deck
fittings of the three MGB suspension
bars could lead to tightening torque loss
on the fittings’ attachment screws
(bolts). Due to design similarities, Model
AS332L2 helicopters could also be
affected by the same installation
condition. Investigations determined
that the life limits in the Airworthiness
Limitations Sections for the screws and
fittings are valid if an ‘‘add-on penalty
factor’’ is applied. Based on these
findings, EASA issued EASA AD No.
2017–0133 dated July 27, 2017, and
then superseded that AD with EASA AD
No. 2017–0189, dated September 22,
2017, for Model AS 332 L2 and EC 225
LP helicopters to address this condition.
Airbus Helicopter subsequently
performed testing on Model AS 332 C,
AS 332 C1, AS 332 L, and AS 332 L1
helicopters due to design similarities,
and determined a life limit reduction of
the MGB suspension bar fittings and
screws was necessary for these model
helicopters. Accordingly, EASA AD
2018–0260 was issued for these model
helicopters to require determining the
accumulated service life of the affected
parts and to introduce new life limits.
EASA states that this condition, if not
corrected, could lead to structural
failure of the MGB suspension bar
fittings and screws, possibly resulting in
detachment of the MGB suspension
bars.
khammond on DSKJM1Z7X2PROD with PROPOSALS
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 determining that an
unsafe condition is likely to exist or
develop on other products of the same
type design.
Related Service Information
The FAA reviewed Airbus Helicopters
Alert Service Bulletin No. AS332–
01.00.90, Revision 0, dated November
VerDate Sep<11>2014
17:14 Dec 06, 2019
Jkt 250001
11, 2018. This service information
specifies determining the accumulated
hours TIS of certain part-numbered rear
MGB suspension bar fittings and screws.
This service information further
specifies criteria to determine the initial
replacement compliance time of those
parts and a new life limit for those parts
thereafter. This service information also
establishes a life limit for the front MGB
attachment screws.
Proposed AD Requirements
This proposed AD would require,
within 50 hours TIS, reviewing the
helicopter records to determine the total
hours TIS of the MGB suspension bar
right-hand side (RH) rear fitting part
number (P/N) 330A22–2702–07 and of
the MGB suspension bar left-hand side
(LH) rear fitting P/N 330A22–2702–06.
This proposed AD would initially
require removing from service the RH
rear fitting and its bolts P/N 330A22–
0135–20 and the LH rear fitting and its
bolts P/N 330A22–0135–20 based on the
accumulated total hours TIS of the
fittings and other conditions. Thereafter,
this proposed AD would require
removing from service the RH rear
fitting and its bolts at intervals not to
exceed 1,470 hours TIS, removing from
service the LH rear fitting at intervals
not to exceed 13,600 hours TIS, and
removing from service the LH rear bolts
during each Major Inspection ‘‘G.’’ This
proposed AD would also require
removing from service the front bolts P/
N 330A22–0134–20 during each Major
Inspection ‘‘G.’’
Differences Between This Proposed AD
and the EASA AD
The EASA AD allows an option for
the first MGB RH rear attachment fitting
replacement to inspect torque and
specifies different replacement
compliance times based on the torque
inspection results, whereas this
proposed AD does not.
Interim Action
The FAA considers this proposed AD
to be an 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 affects 14 helicopters of U.S.
Registry. Labor costs are estimated at
$85 per work-hour. Based on these
numbers, the FAA estimates the
following costs to comply with this
proposed AD.
PO 00000
Frm 00006
Fmt 4702
Sfmt 4702
67247
Determining the total hours TIS of the
rear MGB fittings would take about 0.5
work-hour for an estimated cost of $43
per helicopter and $602 for the U.S.
fleet.
Replacing a rear MGB fitting and its
set of four bolts would take about 8
work-hours and parts would cost about
$12,937, for an estimated cost of
$13,617 per replacement cycle.
Replacing a set of four MGB
attachment bolts would take about 4
work-hours and parts would cost about
$224, for an estimated cost of $564 per
replacement cycle.
Replacing a LH rear MGB fitting
would take about 8 work-hours and
parts would cost about $12,713, for an
estimated cost of $13,393 per
replacement cycle.
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;
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.
E:\FR\FM\09DEP1.SGM
09DEP1
67248
Federal Register / Vol. 84, No. 236 / Monday, December 9, 2019 / Proposed Rules
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–
1015; Product Identifier 2018–SW–104–
AD.
(a) Applicability
This AD applies to Airbus Helicopters
Model AS332C, AS332C1, AS332L, and
AS332L1 helicopters, certificated in any
category, with a main gearbox (MGB)
suspension bar right-hand side (RH) rear
attachment fitting (fitting) part number (P/N)
330A22–2702–07 and bolt P/N 330A22–
0135–20, MGB suspension bar left-hand side
(LH) rear fitting P/N 330A22–2702–06 and
bolt P/N 330A22–0135–20, or MGB
suspension bar front bolt P/N 330A22–0134–
20 installed.
(b) Unsafe Condition
This AD defines the unsafe condition as
MGB suspension bar fittings and bolts
remaining in service beyond their fatigue life.
This condition could result in failure of an
MGB attachment assembly, detachment of an
MGB suspension bar, and subsequent loss of
helicopter control.
(c) Comments Due Date
The FAA must receive comments by
February 7, 2020.
khammond on DSKJM1Z7X2PROD with PROPOSALS
(d) Compliance
You are responsible for performing each
action required by this AD within the
specified compliance time unless it has
already been accomplished prior to that time.
(e) Required Actions
(1) Within 50 hours time-in-service (TIS),
review records to determine the total hours
TIS of each MGB suspension bar RH and LH
rear fitting.
(i) For any RH rear fitting that has
accumulated 1,470 or more total hours TIS,
before further flight, remove from service the
RH rear fitting and its bolts.
(ii) For any RH rear fitting that has
accumulated less than 1,470 total hours TIS,
VerDate Sep<11>2014
17:14 Dec 06, 2019
Jkt 250001
remove from service the RH rear fitting and
its bolts before the fitting accumulates 1,470
total hours TIS.
(iii) For any LH rear fitting that has
accumulated 13,600 or more total hours TIS,
before further flight, remove from service the
LH rear fitting and its bolts.
(iv) For any LH rear fitting that has
accumulated less than 13,600 total hours TIS:
(A) If a Major Inspection ‘‘G’’ has not been
completed since the LH rear fitting has been
installed, remove from service the LH rear
bolts during the next Major Inspection ‘‘G’’
inspection; or
Note 1 to paragraph (e)(iv)(A) of this AD:
Major Inspection ‘‘G’’ (7,500 hours TIS
between overhauls) is defined in
Maintenance Manual MET 05–29–00–601.
(B) If a Major Inspection ‘‘G’’ has been
completed since the LH rear fitting has been
installed, before further flight, remove from
service the LH rear bolts; and
(C) Remove from service the LH rear fitting
before the fitting accumulates 13,600 total
hours TIS.
(2) Thereafter following paragraph (e)(1) of
this AD, remove from service any RH rear
fitting and its bolts at intervals not to exceed
1,470 hours TIS, remove from service any LH
rear fitting at intervals not to exceed 13,600
hours TIS, and remove from service any LH
rear bolts during each Major Inspection ‘‘G.’’
(3) During the next Major Inspection ‘‘G,’’
remove from service the MGB suspension bar
front bolts. Thereafter, remove from service
the front bolts during each Major Inspection
‘‘G.’’
(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
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
(1) Airbus Helicopters Alert Service
Bulletin No. AS332–01.00.90, Revision 0,
dated November 11, 2018, which is not
incorporated by reference, contains
additional information about 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 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.
PO 00000
Frm 00007
Fmt 4702
Sfmt 4702
(2) The subject of this AD is addressed in
European Aviation Safety Agency (EASA) AD
No. 2018–0260, dated December 3, 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 November
29, 2019.
Lance T. Gant,
Director, Compliance & Airworthiness
Division, Aircraft Certification Service.
[FR Doc. 2019–26428 Filed 12–6–19; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2018–0019; Product
Identifier 2017–SW–074–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 AS332L2 and
EC225LP helicopters. This proposed AD
would require determining the
accumulated hours time-in-service (TIS)
of certain part-numbered main gearbox
(MGB) suspension bar attachment bolts
and fittings, applying a life limit add-on
factor, and inspecting the torque of
certain MGB suspension bar attachment
nuts. This proposed AD is prompted by
a report of torque loss on an MGB
suspension bar bolt. 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 February 7,
2020.
SUMMARY:
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.
ADDRESSES:
E:\FR\FM\09DEP1.SGM
09DEP1
]]>Agencies
[Federal Register Volume 84, Number 236 (Monday, December 9, 2019)]
[Proposed Rules]
[Pages 67246-67248]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2019-26428]
=======================================================================
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2019-1015; Product Identifier 2018-SW-104-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 determining the accumulated
hours time-in-service (TIS) of certain part-numbered main gearbox (MGB)
suspension bar attachment fittings (fittings) and bolts, and would
establish new life limits. This proposed AD is prompted by the outcome
of tests and analyses performed by Airbus Helicopters. 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 February 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-
1015; 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,
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 the FAA receives 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 the FAA receives.
[[Page 67247]]
Discussion
EASA, which is the Technical Agent for the Member States of the
European Union, has issued EASA AD No. 2018-0260, dated December 3,
2018 (EASA AD 2018-0260), to correct an unsafe condition for Airbus
Helicopters (formerly Eurocopter, Eurocopter France, Aerospatiale)
Model AS 332 C, AS 332 C1, AS 332 L, and AS 332 L1 helicopters.
From review of reported Model EC 225 LP data, EASA advises that the
installation of the MGB upper deck fittings of the three MGB suspension
bars could lead to tightening torque loss on the fittings' attachment
screws (bolts). Due to design similarities, Model AS332L2 helicopters
could also be affected by the same installation condition.
Investigations determined that the life limits in the Airworthiness
Limitations Sections for the screws and fittings are valid if an ``add-
on penalty factor'' is applied. Based on these findings, EASA issued
EASA AD No. 2017-0133 dated July 27, 2017, and then superseded that AD
with EASA AD No. 2017-0189, dated September 22, 2017, for Model AS 332
L2 and EC 225 LP helicopters to address this condition.
Airbus Helicopter subsequently performed testing on Model AS 332 C,
AS 332 C1, AS 332 L, and AS 332 L1 helicopters due to design
similarities, and determined a life limit reduction of the MGB
suspension bar fittings and screws was necessary for these model
helicopters. Accordingly, EASA AD 2018-0260 was issued for these model
helicopters to require determining the accumulated service life of the
affected parts and to introduce new life limits.
EASA states that this condition, if not corrected, could lead to
structural failure of the MGB suspension bar fittings and screws,
possibly resulting in detachment of the MGB suspension bars.
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 determining that an
unsafe condition is likely to exist or develop on other products of the
same type design.
Related Service Information
The FAA reviewed Airbus Helicopters Alert Service Bulletin No.
AS332-01.00.90, Revision 0, dated November 11, 2018. This service
information specifies determining the accumulated hours TIS of certain
part-numbered rear MGB suspension bar fittings and screws. This service
information further specifies criteria to determine the initial
replacement compliance time of those parts and a new life limit for
those parts thereafter. This service information also establishes a
life limit for the front MGB attachment screws.
Proposed AD Requirements
This proposed AD would require, within 50 hours TIS, reviewing the
helicopter records to determine the total hours TIS of the MGB
suspension bar right-hand side (RH) rear fitting part number (P/N)
330A22-2702-07 and of the MGB suspension bar left-hand side (LH) rear
fitting P/N 330A22-2702-06. This proposed AD would initially require
removing from service the RH rear fitting and its bolts P/N 330A22-
0135-20 and the LH rear fitting and its bolts P/N 330A22-0135-20 based
on the accumulated total hours TIS of the fittings and other
conditions. Thereafter, this proposed AD would require removing from
service the RH rear fitting and its bolts at intervals not to exceed
1,470 hours TIS, removing from service the LH rear fitting at intervals
not to exceed 13,600 hours TIS, and removing from service the LH rear
bolts during each Major Inspection ``G.'' This proposed AD would also
require removing from service the front bolts P/N 330A22-0134-20 during
each Major Inspection ``G.''
Differences Between This Proposed AD and the EASA AD
The EASA AD allows an option for the first MGB RH rear attachment
fitting replacement to inspect torque and specifies different
replacement compliance times based on the torque inspection results,
whereas this proposed AD does not.
Interim Action
The FAA considers this proposed AD to be an 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 affects 14 helicopters of
U.S. Registry. Labor costs are estimated at $85 per work-hour. Based on
these numbers, the FAA estimates the following costs to comply with
this proposed AD.
Determining the total hours TIS of the rear MGB fittings would take
about 0.5 work-hour for an estimated cost of $43 per helicopter and
$602 for the U.S. fleet.
Replacing a rear MGB fitting and its set of four bolts would take
about 8 work-hours and parts would cost about $12,937, for an estimated
cost of $13,617 per replacement cycle.
Replacing a set of four MGB attachment bolts would take about 4
work-hours and parts would cost about $224, for an estimated cost of
$564 per replacement cycle.
Replacing a LH rear MGB fitting would take about 8 work-hours and
parts would cost about $12,713, for an estimated cost of $13,393 per
replacement cycle.
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;
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.
[[Page 67248]]
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-2019-1015; Product Identifier
2018-SW-104-AD.
(a) Applicability
This AD applies to Airbus Helicopters Model AS332C, AS332C1,
AS332L, and AS332L1 helicopters, certificated in any category, with
a main gearbox (MGB) suspension bar right-hand side (RH) rear
attachment fitting (fitting) part number (P/N) 330A22-2702-07 and
bolt P/N 330A22-0135-20, MGB suspension bar left-hand side (LH) rear
fitting P/N 330A22-2702-06 and bolt P/N 330A22-0135-20, or MGB
suspension bar front bolt P/N 330A22-0134-20 installed.
(b) Unsafe Condition
This AD defines the unsafe condition as MGB suspension bar
fittings and bolts remaining in service beyond their fatigue life.
This condition could result in failure of an MGB attachment
assembly, detachment of an MGB suspension bar, and subsequent loss
of helicopter control.
(c) Comments Due Date
The FAA must receive comments by February 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
(1) Within 50 hours time-in-service (TIS), review records to
determine the total hours TIS of each MGB suspension bar RH and LH
rear fitting.
(i) For any RH rear fitting that has accumulated 1,470 or more
total hours TIS, before further flight, remove from service the RH
rear fitting and its bolts.
(ii) For any RH rear fitting that has accumulated less than
1,470 total hours TIS, remove from service the RH rear fitting and
its bolts before the fitting accumulates 1,470 total hours TIS.
(iii) For any LH rear fitting that has accumulated 13,600 or
more total hours TIS, before further flight, remove from service the
LH rear fitting and its bolts.
(iv) For any LH rear fitting that has accumulated less than
13,600 total hours TIS:
(A) If a Major Inspection ``G'' has not been completed since the
LH rear fitting has been installed, remove from service the LH rear
bolts during the next Major Inspection ``G'' inspection; or
Note 1 to paragraph (e)(iv)(A) of this AD: Major Inspection
``G'' (7,500 hours TIS between overhauls) is defined in Maintenance
Manual MET 05-29-00-601.
(B) If a Major Inspection ``G'' has been completed since the LH
rear fitting has been installed, before further flight, remove from
service the LH rear bolts; and
(C) Remove from service the LH rear fitting before the fitting
accumulates 13,600 total hours TIS.
(2) Thereafter following paragraph (e)(1) of this AD, remove
from service any RH rear fitting and its bolts at intervals not to
exceed 1,470 hours TIS, remove from service any LH rear fitting at
intervals not to exceed 13,600 hours TIS, and remove from service
any LH rear bolts during each Major Inspection ``G.''
(3) During the next Major Inspection ``G,'' remove from service
the MGB suspension bar front bolts. Thereafter, remove from service
the front bolts during each Major Inspection ``G.''
(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
(1) Airbus Helicopters Alert Service Bulletin No. AS332-
01.00.90, Revision 0, dated November 11, 2018, which is not
incorporated by reference, contains additional information about 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 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.
(2) The subject of this AD is addressed in European Aviation
Safety Agency (EASA) AD No. 2018-0260, dated December 3, 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 November 29, 2019.
Lance T. Gant,
Director, Compliance & Airworthiness Division, Aircraft Certification
Service.
[FR Doc. 2019-26428 Filed 12-6-19; 8:45 am]
BILLING CODE 4910-13-P
