Airworthiness Directives; Airbus Helicopters, 19077-19080 [2020-07140]
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19077
Rules and Regulations
Federal Register
Vol. 85, No. 66
Monday, April 6, 2020
This section of the FEDERAL REGISTER
contains regulatory documents having general
applicability and legal effect, most of which
are keyed to and codified in the Code of
Federal Regulations, which is published under
50 titles pursuant to 44 U.S.C. 1510.
The Code of Federal Regulations is sold by
the Superintendent of Documents.
FEDERAL RESERVE SYSTEM
12 CFR Chapter II
[Docket No. OP–1589]
Federal Reserve Policy on Payment
System Risk; U.S. Branches and
Agencies of Foreign Banking
Organizations
Board of Governors of the
Federal Reserve System.
ACTION: Notification of delay.
AGENCY:
The Board of Governors of the
Federal Reserve System (‘‘Board’’) is
delaying the implementation date of
changes to part II of the Federal Reserve
Policy on Payment System Risk (‘‘PSR
policy’’) related to procedures for
determining the net debit cap and
maximum daylight overdraft capacity of
a U.S. branch or agency of a foreign
banking organization (‘‘FBO’’).
DATES: The implementation date of the
amendments to the PSR policy
published on April 1, 2019 (84 FR
12049), has been delayed from April 1,
2020 to October 1, 2020.
FOR FURTHER INFORMATION CONTACT:
Jeffrey Walker, Deputy Associate
Director (202–721–4559), Jason Hinkle,
Assistant Director (202–912–7805); or
Brajan Kola, Senior Financial Institution
and Policy Analyst (202–736–5683),
Division of Reserve Bank Operations
and Payment Systems; or Evan
Winerman, Senior Counsel (202–872–
7578), Legal Division, Board of
Governors of the Federal Reserve
System. For users of
Telecommunications Device for the Deaf
(TDD) only, please call 202–263–4869.
SUPPLEMENTARY INFORMATION: On April
1, 2019, the Board approved
amendments to part II of the PSR policy,
which establishes the maximum levels
of daylight overdrafts that depository
institutions may incur in their Federal
Reserve accounts.10 These amendments
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SUMMARY:
10 84
FR 12049 (April 1, 2019).
VerDate Sep<11>2014
16:25 Apr 03, 2020
will remove references to the Strength of
Support Assessment (‘‘SOSA’’) ranking;
remove references to FBOs’ financial
holding company (‘‘FHC’’) status; and
adopt alternative methods for
determining an FBO’s eligibility for a
positive net debit cap, the size of its net
debit cap, and its eligibility to request
a streamlined procedure to obtain
maximum daylight overdraft capacity.
The Board selected April 1, 2020, as the
implementation date for these
amendments in response to a comment
requesting that the Board delay
implementation for at least 12 months.
The Board stated ‘‘that a transition
period would help FBOs adjust to these
changes.’’ 11
The availability of intraday credit
from the Federal Reserve Banks
supports the smooth functioning of
payment systems and the settlement and
clearing of transactions across a range of
credit markets. The coronavirus
outbreak has disrupted economic
activity and financial markets in the
United States. In light of these ongoing
disruptions, the Board believes that, out
of an abundance of caution, it should
extend the transition period to October
1, 2020. This additional time will allow
FBOs and the Reserve Banks to focus on
other heightened priorities rather than
establishing new arrangements for
accessing intraday credit.
Accordingly, the Board is delaying the
implementation date of the amendments
to the PSR policy from April 1, 2020, to
October 1, 2020.
By order of the Board of Governors of the
Federal Reserve System, March 24, 2020.
Michele Taylor Fennell,
Assistant Secretary of the Board.
[FR Doc. 2020–06482 Filed 4–3–20; 8:45 am]
BILLING CODE 6210–01–P
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2018–0019; Product
Identifier 2017–SW–074–AD; Amendment
39–19881; AD 2020–06–12]
RIN 2120–AA64
Airworthiness Directives; Airbus
Helicopters
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule.
AGENCY:
The FAA is adopting a new
airworthiness directive (AD) for Airbus
Helicopters Model AS332L2 and
EC225LP helicopters. This AD requires
determining the accumulated hours
time-in-service (TIS) of certain partnumbered 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 AD was prompted by a report
of torque loss on an MGB suspension
bar bolt. The actions of this AD are
intended to address an unsafe condition
on these products.
DATES: This AD is effective May 11,
2020.
The Director of the Federal Register
approved the incorporation by reference
of certain documents listed in this AD
as of May 11, 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–2018–0019.
SUMMARY:
Examining the AD Docket
11 Id.
Jkt 250001
DEPARTMENT OF TRANSPORTATION
PO 00000
You may examine the AD docket on
the internet at https://
www.regulations.gov in Docket No.
FAA–2018–0019; or in person at Docket
Operations between 9 a.m. and 5 p.m.,
at 12056.
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Federal Register / Vol. 85, No. 66 / Monday, April 6, 2020 / Rules and Regulations
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
incorporated by reference, any
comments received, and other
information. The street address for
Docket Operations is U.S. Department of
Transportation, Docket Operations, M–
30, West Building Ground Floor, Room
W12–140, 1200 New Jersey Avenue SE,
Washington, DC 20590.
FOR FURTHER INFORMATION CONTACT: 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:
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Discussion
On December 9, 2019, at 84 FR 67248,
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 AS332L2 and EC225LP
helicopters, with an MGB suspension
bar front attachment bolt (bolt) part
number (P/N) 332A22–1613–21 or
332A22–1613–20, MGB suspension bar
rear bolt P/N 332A22–1614–20, MGB
suspension bar front attachment fitting
(fitting) P/N 332A22–1623–01, MGB
suspension bar rear left hand fitting P/
N 332A22–1624–02 or 332A22–1624–
04, or MGB suspension bar rear right
hand fitting P/N 332A22–1624–03 or
332A22–1624–05 installed.
For Airbus Helicopters Model
AS332L2 and EC225LP helicopters, the
NPRM proposed to require, within 30
hours time-in-service (TIS), recalculating the life limit accumulated by
each front and rear bolt by applying an
add-on factor listed in the applicable
service information. For each bolt that
meets or exceeds its life limit, also
known as service life limit (SLL), the
NPRM proposed to require removing
each bolt from service before further
flight. For each bolt that has not
exceeded its life limit, the NPRM
proposed to require continuing to
calculate and record the life limit of
each bolt on its component history card
or equivalent record and removing the
bolt from service before reaching its life
limit.
For Model AS332L2 helicopters, the
NPRM proposed to require, within 30
hours TIS, re-calculating the life limit
accumulated by the front, rear left hand,
and rear right hand fittings by applying
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an add-on factor listed in the applicable
service information. For each fitting that
meets or exceeds its life limit, the
NPRM proposed to require removing the
fitting from service before further flight.
For each fitting that has not exceeded its
life limit, the NPRM proposed to require
continuing to calculate and record the
life limit of each fitting on its
component history card or equivalent
record and removing the fitting from
service before reaching its life limit.
For Model AS332L2 helicopters, the
NPRM proposed to require, within 150
hours TIS (without applying an add onfactor), inspecting the torque of each
MGB suspension bar fitting front and
rear nut. If the torque on any nut is
higher than the maximum allowable
limit, the NPRM proposed to require
removing the nut and its bolt from
service before further flight. If the torque
on any nut is lower than the minimum
allowable limit, the NPRM proposed to
require tightening the nut before further
flight and removing the nut and its bolt
from service within 150 hours TIS.
The proposed requirements were
intended prevent the MGB suspension
bar bolts and fittings remaining in
service beyond their fatigue life, which
could result in structural failure of the
MGB suspension bar and loss of
helicopter control.
The NPRM was prompted by EASA
AD No. 2017–0189, dated September 22,
2017, issued by EASA, which is the
Technical Agent for the Member States
of the European Union, to correct an
unsafe condition for Airbus Helicopters
(formerly Eurocopter, Eurocopter
France, Aerospatiale) Model AS 332 L2
and EC 225 LP helicopters. 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
pins (bolts). Due to design similarities,
Model AS 332 L2 helicopters could also
be affected by the same installation
condition. An investigation determined
that the life limits in the Airworthiness
Limitations Sections for the pins and
fittings are valid if an ‘‘add-on penalty
factor’’ is applied.
EASA states that this condition, if not
corrected, could lead to structural
failure of the MGB suspension bar
attachment pins or fittings. Accordingly,
the EASA AD requires applying the addon penalty factor to the flight hours to
re-calculate the life limits and replacing
an affected part before exceeding its life
limit. EASA further advises that Airbus
Helicopters’ initial service information
contained an error that may have
resulted in the installation of pins or
fittings using an incorrect torque value.
As a result, the EASA AD also requires
PO 00000
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replacing pins if an incorrect torque
value was applied and reporting the
information to Airbus Helicopters.
Comments
The FAA gave the public the
opportunity to participate in developing
this AD, but the FAA did not receive
any comments on 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.
Differences Between This AD and the
EASA AD
The EASA AD allows an optional 150
hours TIS extension to the life limit of
an affected fitting for Model AS 332 L2
helicopters by performing dye-penetrant
inspections. This AD does not allow this
option. For Model AS 332 L2
helicopters, the EASA AD requires
replacing pins (bolts) that are
replacement pins installed before the
AD’s effective date with an incorrect
torque value applied. This AD requires
inspecting the torque for each nut for
Model AS 332 L2 helicopters instead
and depending on the outcome,
removing the nut and its bolt from
service. The EASA AD requires
reporting certain information to Airbus
Helicopters, while this AD does not.
Related Service Information Under 1
CFR Part 51
The FAA reviewed Airbus Helicopters
Emergency Alert Service Bulletin
(EASB) No. 01.00.86 for Model AS332
helicopters and Airbus Helicopters
EASB No. 04A013 for Model EC225LP
helicopters, both Revision 1 and dated
August 25, 2017. This service
information specifies applying an addon factor to the flying hours logged by
the pins and fittings and replacing them
if the SLL is exceeded. If an incorrect
tightening torque value was applied to
the pins, the service information
specifies replacing the pins and
contacting Airbus Helicopters.
This service information is reasonably
available because the interested parties
have access to it through their normal
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course of business or by the means
identified in the ADDRESSES section.
under the criteria of the Regulatory
Flexibility Act.
Costs of Compliance
The FAA estimates that this AD
affects 23 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.
Determining the adjusted life limit for
the bolts and fittings takes about 0.5
work-hour for an estimated cost of $43
per helicopter and $989 for the U.S.
fleet.
Replacing a bolt takes about 4 workhours and parts cost about $89 for an
estimated cost of $429 per bolt.
There are no costs of compliance for
replacing a fitting and inspecting, and if
necessary tightening, the torque for
Model AS332L2 helicopters by this AD
because there are no Model AS332L2
helicopters on the U.S. Registry.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation
safety, Incorporation by reference,
Safety.
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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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
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Jkt 250001
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):
■
2020–06–12 Airbus Helicopters:
Amendment 39–19881; Docket No.
FAA–2018–0019; Product Identifier
2017–SW–074–AD.
(a) Applicability
This AD applies to Airbus Helicopters
Model AS332L2 and EC225LP helicopters,
certificated in any category, with a main
gearbox (MGB) suspension bar front
attachment bolt (bolt) part number (P/N)
332A22–1613–21 or 332A22–1613–20, MGB
suspension bar rear bolt P/N 332A22–1614–
20, MGB suspension bar front attachment
fitting (fitting) P/N 332A22–1623–01, MGB
suspension bar rear left hand fitting P/N
332A22–1624–02 or 332A22–1624–04, or
MGB suspension bar rear right hand fitting P/
N 332A22–1624–03 or 332A22–1624–05
installed.
(b) Unsafe Condition
This AD defines the unsafe condition as
MGB suspension bar bolts and fittings
remaining in service beyond their fatigue life
and loose MGB suspension bar bolts or
fittings, which could result in structural
failure of the MGB suspension bar and loss
of helicopter control.
(c) Effective Date
This AD becomes effective May 11, 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 30 hours time-in-service (TIS),
review records to determine the total hours
TIS of each MGB suspension bar bolt.
(i) Determine the life limit of each bolt by
applying the hours TIS by the add-on factor
listed in Table No. 1 of Airbus Helicopters
Emergency Alert Service Bulletin No.
01.00.86, Revision 1, dated August 25, 2017
(EASB 01.00.86), or Airbus Helicopters
PO 00000
Frm 00003
Fmt 4700
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19079
Emergency Alert Service Bulletin No.
04A013, Revision 1, dated August 25, 2017,
as applicable to your model helicopter.
Note 1 to paragraph (e)(1)(i) of this AD:
Airbus Helicopters refers to bolts as ‘‘pins.’’
(A) Before further flight, remove from
service any bolt that has reached or exceeded
its life limit.
(B) For each bolt that has not exceeded its
life limit, continue to calculate and record
the life limit on its component history card
or equivalent record by applying the add-on
factor each time the helicopter accumulates
hours TIS, and remove from service any bolt
before reaching its life limit.
(ii) Thereafter following paragraph (e)(1)(i)
of this AD, continue to calculate and record
the life limit of each bolt on its component
history card or equivalent record by applying
the add-on factor each time the helicopter
accumulates hours TIS and remove from
service any bolt before reaching its life limit.
(2) For Model AS332L2 helicopters, within
30 hours TIS, review records to determine
the total hours TIS of each MGB suspension
bar fitting.
(i) Determine the life limit of each fitting
by applying the hours TIS by the add-on
factor listed in Table No. 1 of EASB 01.00.86.
(A) Before further flight, remove from
service any fitting that has reached or
exceeded its life limit.
(B) For each fitting that has not exceeded
its life limit, continue to calculate and record
the life limit on its component history card
or equivalent record by applying the add-on
factor each time the helicopter accumulates
hours TIS, and remove from service any
fitting before reaching its life limit.
(ii) Thereafter following paragraph (e)(2)(i)
of this AD, continue to calculate and record
the life limit of each fitting on its component
history card or equivalent record by applying
the add-on factor each time the helicopter
accumulates hours TIS and remove from
service any fitting before reaching its life
limit.
(3) For Model AS332L2 helicopters, within
150 hours TIS (without the add-on factor),
inspect the torque of each MGB suspension
bar attachment front and rear nut. The
allowable torque for each front nut is 602–
663 lbf. in (6.8–7.5 daN.m) and the allowable
torque for each rear nut is 337–398 lbf. in
(3.8–4.5 daN.m).
(i) If the torque on any nut is higher than
the maximum allowable torque stated in
paragraph (e)(3) of this AD, before further
flight, remove from service the bolt and nut.
(ii) If the torque on any nut is lower than
the minimum allowable torque value stated
in paragraph (e)(3) of this AD, before further
flight, tighten the nut to the allowable torque
stated in paragraph (e)(3) of this AD. Within
150 hours TIS (without the add-on factor),
remove from service any bolt and nut that
were tightened as required by this paragraph.
(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
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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
The subject of this AD is addressed in
European Union Aviation Safety Agency
(previously European Aviation Safety
Agency) (EASA) AD No. 2017–0189, dated
September 22, 2017. You may view the EASA
AD on the internet at https://
www.regulations.gov in Docket No. FAA–
2018–0019.
(h) Subject
Joint Aircraft Service Component (JASC)
Code: 6320, Main Rotor Gearbox.
(i) Material Incorporated by Reference
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(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 Emergency Alert
Service Bulletin (EASB) No. 01.00.86,
Revision 1, dated August 25, 2017.
(ii) Airbus Helicopters EASB No. 04A013,
Revision 1, dated August 25, 2017.
(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 25, 2020.
Lance T. Gant,
Director, Compliance & Airworthiness
Division, Aircraft Certification Service.
[FR Doc. 2020–07140 Filed 4–3–20; 8:45 am]
BILLING CODE 4910–13–P
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2019–1015; Product
Identifier 2018–SW–104–AD; Amendment
39–19882; AD 2020–06–13]
RIN 2120–AA64
Airworthiness Directives; Airbus
Helicopters
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule.
AGENCY:
The FAA is adopting a new
airworthiness directive (AD) for Airbus
Helicopters Model AS332C, AS332C1,
AS332L, and AS332L1 helicopters. This
AD requires determining the
accumulated hours time-in-service (TIS)
of certain part-numbered main gearbox
(MGB) suspension bar attachment
fittings (fittings) and bolts, and
establishes new life limits. This AD was
prompted by the outcome of tests and
analyses performed by Airbus
Helicopters. The actions of this AD are
intended to address an unsafe condition
on these products.
DATES: This AD is effective May 11,
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
the referenced service information at the
FAA, Office of the Regional Counsel,
Southwest Region, 10101 Hillwood
Pkwy., Room 6N–321, Fort Worth, TX
76177.
SUMMARY:
Examining the AD Docket
You may examine the AD docket on
the internet at https://
www.regulations.gov in 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
AD, the European Union Aviation
Safety Agency (previously European
Aviation Safety Agency) (EASA) AD,
any comments received, and other
information. The street address for
Docket Operations is U.S. Department of
Transportation, Docket Operations, M–
30, West Building Ground Floor, Room
W12–140, 1200 New Jersey Avenue SE,
Washington, DC 20590.
FOR FURTHER INFORMATION CONTACT: Matt
Fuller, Senior Aviation Safety Engineer,
PO 00000
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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:
Discussion
On December 9, 2019, at 84 FR 67246,
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, with an MGB
suspension bar right-hand side (RH) rear
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. The NPRM proposed to
require within 50 hours TIS, reviewing
the helicopter records to determine the
total hours TIS of the MGB suspension
bar RH and LH rear fittings. The NPRM
also proposed to require removing from
service the RH rear fitting and its bolts
and the LH rear fitting and its bolts
based on the accumulated total hours
TIS of the fittings and other conditions.
Thereafter, the NPRM proposed to
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.’’ Finally, the NPRM proposed to
require removing from service the front
bolts during each Major Inspection ‘‘G.’’
The proposed requirements were
intended to prevent structural failure of
the MGB suspension bar fittings and
bolts, possibly resulting in detachment
of the MGB suspension bars.
The NPRM was prompted by EASA
AD No. 2018–0260, dated December 3,
2018, issued by EASA, which is the
Technical Agent for the Member States
of the European Union, 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 AS 332 C, AS 332
C1, AS 332 L, and AS 332 L1
helicopters could also be affected by the
same installation condition.
E:\FR\FM\06APR1.SGM
06APR1
]]>Agencies
[Federal Register Volume 85, Number 66 (Monday, April 6, 2020)]
[Rules and Regulations]
[Pages 19077-19080]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2020-07140]
=======================================================================
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2018-0019; Product Identifier 2017-SW-074-AD; Amendment
39-19881; AD 2020-06-12]
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 AS332L2 and EC225LP helicopters. This AD
requires 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 AD was
prompted by a report of torque loss on an MGB suspension bar bolt. The
actions of this AD are intended to address an unsafe condition on these
products.
DATES: This AD is effective May 11, 2020.
The Director of the Federal Register approved the incorporation by
reference of certain documents listed in this AD as of May 11, 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-2018-
0019.
Examining the AD Docket
You may examine the AD docket on the internet at https://www.regulations.gov in Docket No. FAA-2018-0019; or in person at Docket
Operations between 9 a.m. and 5 p.m.,
[[Page 19078]]
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
incorporated by reference, any comments received, and other
information. The street address for Docket Operations is U.S.
Department of Transportation, Docket Operations, M-30, West Building
Ground Floor, Room W12-140, 1200 New Jersey Avenue SE, Washington, DC
20590.
FOR FURTHER INFORMATION CONTACT: 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 December 9, 2019, at 84 FR 67248, 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 AS332L2 and EC225LP helicopters, with an MGB suspension bar front
attachment bolt (bolt) part number (P/N) 332A22-1613-21 or 332A22-1613-
20, MGB suspension bar rear bolt P/N 332A22-1614-20, MGB suspension bar
front attachment fitting (fitting) P/N 332A22-1623-01, MGB suspension
bar rear left hand fitting P/N 332A22-1624-02 or 332A22-1624-04, or MGB
suspension bar rear right hand fitting P/N 332A22-1624-03 or 332A22-
1624-05 installed.
For Airbus Helicopters Model AS332L2 and EC225LP helicopters, the
NPRM proposed to require, within 30 hours time-in-service (TIS), re-
calculating the life limit accumulated by each front and rear bolt by
applying an add-on factor listed in the applicable service information.
For each bolt that meets or exceeds its life limit, also known as
service life limit (SLL), the NPRM proposed to require removing each
bolt from service before further flight. For each bolt that has not
exceeded its life limit, the NPRM proposed to require continuing to
calculate and record the life limit of each bolt on its component
history card or equivalent record and removing the bolt from service
before reaching its life limit.
For Model AS332L2 helicopters, the NPRM proposed to require, within
30 hours TIS, re-calculating the life limit accumulated by the front,
rear left hand, and rear right hand fittings by applying an add-on
factor listed in the applicable service information. For each fitting
that meets or exceeds its life limit, the NPRM proposed to require
removing the fitting from service before further flight. For each
fitting that has not exceeded its life limit, the NPRM proposed to
require continuing to calculate and record the life limit of each
fitting on its component history card or equivalent record and removing
the fitting from service before reaching its life limit.
For Model AS332L2 helicopters, the NPRM proposed to require, within
150 hours TIS (without applying an add on-factor), inspecting the
torque of each MGB suspension bar fitting front and rear nut. If the
torque on any nut is higher than the maximum allowable limit, the NPRM
proposed to require removing the nut and its bolt from service before
further flight. If the torque on any nut is lower than the minimum
allowable limit, the NPRM proposed to require tightening the nut before
further flight and removing the nut and its bolt from service within
150 hours TIS.
The proposed requirements were intended prevent the MGB suspension
bar bolts and fittings remaining in service beyond their fatigue life,
which could result in structural failure of the MGB suspension bar and
loss of helicopter control.
The NPRM was prompted by EASA AD No. 2017-0189, dated September 22,
2017, issued by EASA, which is the Technical Agent for the Member
States of the European Union, to correct an unsafe condition for Airbus
Helicopters (formerly Eurocopter, Eurocopter France, Aerospatiale)
Model AS 332 L2 and EC 225 LP helicopters. 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
pins (bolts). Due to design similarities, Model AS 332 L2 helicopters
could also be affected by the same installation condition. An
investigation determined that the life limits in the Airworthiness
Limitations Sections for the pins and fittings are valid if an ``add-on
penalty factor'' is applied.
EASA states that this condition, if not corrected, could lead to
structural failure of the MGB suspension bar attachment pins or
fittings. Accordingly, the EASA AD requires applying the add-on penalty
factor to the flight hours to re-calculate the life limits and
replacing an affected part before exceeding its life limit. EASA
further advises that Airbus Helicopters' initial service information
contained an error that may have resulted in the installation of pins
or fittings using an incorrect torque value. As a result, the EASA AD
also requires replacing pins if an incorrect torque value was applied
and reporting the information to Airbus Helicopters.
Comments
The FAA gave the public the opportunity to participate in
developing this AD, but the FAA did not receive any comments on 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.
Differences Between This AD and the EASA AD
The EASA AD allows an optional 150 hours TIS extension to the life
limit of an affected fitting for Model AS 332 L2 helicopters by
performing dye-penetrant inspections. This AD does not allow this
option. For Model AS 332 L2 helicopters, the EASA AD requires replacing
pins (bolts) that are replacement pins installed before the AD's
effective date with an incorrect torque value applied. This AD requires
inspecting the torque for each nut for Model AS 332 L2 helicopters
instead and depending on the outcome, removing the nut and its bolt
from service. The EASA AD requires reporting certain information to
Airbus Helicopters, while this AD does not.
Related Service Information Under 1 CFR Part 51
The FAA reviewed Airbus Helicopters Emergency Alert Service
Bulletin (EASB) No. 01.00.86 for Model AS332 helicopters and Airbus
Helicopters EASB No. 04A013 for Model EC225LP helicopters, both
Revision 1 and dated August 25, 2017. This service information
specifies applying an add-on factor to the flying hours logged by the
pins and fittings and replacing them if the SLL is exceeded. If an
incorrect tightening torque value was applied to the pins, the service
information specifies replacing the pins and contacting Airbus
Helicopters.
This service information is reasonably available because the
interested parties have access to it through their normal
[[Page 19079]]
course of business or by the means identified in the ADDRESSES section.
Costs of Compliance
The FAA estimates that this AD affects 23 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.
Determining the adjusted life limit for the bolts and fittings
takes about 0.5 work-hour for an estimated cost of $43 per helicopter
and $989 for the U.S. fleet.
Replacing a bolt takes about 4 work-hours and parts cost about $89
for an estimated cost of $429 per bolt.
There are no costs of compliance for replacing a fitting and
inspecting, and if necessary tightening, the torque for Model AS332L2
helicopters by this AD because there are no Model AS332L2 helicopters
on the U.S. Registry.
Authority for This Rulemaking
Title 49 of the United States Code specifies the FAA's authority to
issue rules on aviation safety. Subtitle I, section 106, describes the
authority of the FAA Administrator. Subtitle VII: Aviation Programs,
describes in more detail the scope of the Agency's authority.
The FAA is issuing this rulemaking under the authority described in
Subtitle VII, Part A, Subpart III, Section 44701: General requirements.
Under that section, Congress charges the FAA with promoting safe flight
of civil aircraft in air commerce by prescribing regulations for
practices, methods, and procedures the Administrator finds necessary
for safety in air commerce. This regulation is within the scope of that
authority because it addresses an unsafe condition that is likely to
exist or develop on helicopters identified in this rulemaking action.
Regulatory Findings
This AD will not have federalism implications under Executive Order
13132. This AD will not have a substantial direct effect on the States,
on the relationship between the national government and the States, or
on the distribution of power and responsibilities among the various
levels of government.
For the reasons discussed above, I certify that this AD:
1. Is not a ``significant regulatory action'' under Executive Order
12866,
2. Will not affect intrastate aviation in Alaska, and
3. Will not have a significant economic impact, positive or
negative, on a substantial number of small entities under the criteria
of the Regulatory Flexibility Act.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.
Adoption of the Amendment
Accordingly, under the authority delegated to me by the
Administrator, the FAA amends 14 CFR part 39 as follows:
PART 39--AIRWORTHINESS DIRECTIVES
0
1. The authority citation for part 39 continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
Sec. 39.13 [Amended]
0
2. The FAA amends Sec. 39.13 by adding the following new airworthiness
directive (AD):
2020-06-12 Airbus Helicopters: Amendment 39-19881; Docket No. FAA-
2018-0019; Product Identifier 2017-SW-074-AD.
(a) Applicability
This AD applies to Airbus Helicopters Model AS332L2 and EC225LP
helicopters, certificated in any category, with a main gearbox (MGB)
suspension bar front attachment bolt (bolt) part number (P/N)
332A22-1613-21 or 332A22-1613-20, MGB suspension bar rear bolt P/N
332A22-1614-20, MGB suspension bar front attachment fitting
(fitting) P/N 332A22-1623-01, MGB suspension bar rear left hand
fitting P/N 332A22-1624-02 or 332A22-1624-04, or MGB suspension bar
rear right hand fitting P/N 332A22-1624-03 or 332A22-1624-05
installed.
(b) Unsafe Condition
This AD defines the unsafe condition as MGB suspension bar bolts
and fittings remaining in service beyond their fatigue life and
loose MGB suspension bar bolts or fittings, which could result in
structural failure of the MGB suspension bar and loss of helicopter
control.
(c) Effective Date
This AD becomes effective May 11, 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 30 hours time-in-service (TIS), review records to
determine the total hours TIS of each MGB suspension bar bolt.
(i) Determine the life limit of each bolt by applying the hours
TIS by the add-on factor listed in Table No. 1 of Airbus Helicopters
Emergency Alert Service Bulletin No. 01.00.86, Revision 1, dated
August 25, 2017 (EASB 01.00.86), or Airbus Helicopters Emergency
Alert Service Bulletin No. 04A013, Revision 1, dated August 25,
2017, as applicable to your model helicopter.
Note 1 to paragraph (e)(1)(i) of this AD: Airbus Helicopters
refers to bolts as ``pins.''
(A) Before further flight, remove from service any bolt that has
reached or exceeded its life limit.
(B) For each bolt that has not exceeded its life limit, continue
to calculate and record the life limit on its component history card
or equivalent record by applying the add-on factor each time the
helicopter accumulates hours TIS, and remove from service any bolt
before reaching its life limit.
(ii) Thereafter following paragraph (e)(1)(i) of this AD,
continue to calculate and record the life limit of each bolt on its
component history card or equivalent record by applying the add-on
factor each time the helicopter accumulates hours TIS and remove
from service any bolt before reaching its life limit.
(2) For Model AS332L2 helicopters, within 30 hours TIS, review
records to determine the total hours TIS of each MGB suspension bar
fitting.
(i) Determine the life limit of each fitting by applying the
hours TIS by the add-on factor listed in Table No. 1 of EASB
01.00.86.
(A) Before further flight, remove from service any fitting that
has reached or exceeded its life limit.
(B) For each fitting that has not exceeded its life limit,
continue to calculate and record the life limit on its component
history card or equivalent record by applying the add-on factor each
time the helicopter accumulates hours TIS, and remove from service
any fitting before reaching its life limit.
(ii) Thereafter following paragraph (e)(2)(i) of this AD,
continue to calculate and record the life limit of each fitting on
its component history card or equivalent record by applying the add-
on factor each time the helicopter accumulates hours TIS and remove
from service any fitting before reaching its life limit.
(3) For Model AS332L2 helicopters, within 150 hours TIS (without
the add-on factor), inspect the torque of each MGB suspension bar
attachment front and rear nut. The allowable torque for each front
nut is 602-663 lbf. in (6.8-7.5 daN.m) and the allowable torque for
each rear nut is 337-398 lbf. in (3.8-4.5 daN.m).
(i) If the torque on any nut is higher than the maximum
allowable torque stated in paragraph (e)(3) of this AD, before
further flight, remove from service the bolt and nut.
(ii) If the torque on any nut is lower than the minimum
allowable torque value stated in paragraph (e)(3) of this AD, before
further flight, tighten the nut to the allowable torque stated in
paragraph (e)(3) of this AD. Within 150 hours TIS (without the add-
on factor), remove from service any bolt and nut that were tightened
as required by this paragraph.
(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
[[Page 19080]]
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. 2017-0189, dated September 22, 2017. You may view the EASA AD on
the internet at https://www.regulations.gov in Docket No. FAA-2018-
0019.
(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 Emergency Alert Service Bulletin (EASB)
No. 01.00.86, Revision 1, dated August 25, 2017.
(ii) Airbus Helicopters EASB No. 04A013, Revision 1, dated
August 25, 2017.
(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 25, 2020.
Lance T. Gant,
Director, Compliance & Airworthiness Division, Aircraft Certification
Service.
[FR Doc. 2020-07140 Filed 4-3-20; 8:45 am]
BILLING CODE 4910-13-P
