Airworthiness Directives; Airbus Helicopters

Published date03 June 2020
Record Number2020-11821
SectionProposed rules
CourtFederal Aviation Administration
34118
Federal Register / Vol. 85, No. 107 / Wednesday, June 3, 2020 / Proposed Rules
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Treena V. Garrett,
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Department of Energy.
[FR Doc. 2020–11764 Filed 6–2–20; 8:45 am]
BILLING CODE 6450–01–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2020–0513; Product
Identifier 2019–SW–037–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
supersede Airworthiness Directive (AD)
2018–08–01 for Airbus Helicopters
Model EC225LP helicopters. AD 2018–
08–01 requires inspecting the control
rod attachment yokes (yoke) of certain
main rotor rotating swashplates
(swashplate). Since the FAA issued AD
2018–08–01, Airbus Helicopters has
identified additional swashplate serial
numbers affected by the unsafe
condition and has established a life
limit for the swashplates. This proposed
AD would retain the inspection
requirements of AD 2018–08–01,
expand the applicability, establish a life
limit, and add a one-time inspection of
stripped yokes. 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 August 3, 2020.
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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–2020–
0513; 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 Union Aviation
Safety Agency (EASA) AD, 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 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.
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 received, as well as a report
summarizing each substantive public
contact with FAA personnel concerning
this proposed rulemaking. Before acting
on this proposal, the FAA will consider
all comments received on or before the
closing date for comments. The FAA
will consider comments filed after the
comment period has closed if it is
possible to do so without incurring
expense or delay. The FAA may change
this proposal in light of the comments
received.
Discussion
The FAA issued AD 2018–08–01,
Amendment 39–19254 (83 FR 17617,
April 23, 2018) (‘‘AD 2018–08–01’’) for
Airbus Helicopters Model EC225LP
helicopters. AD 2018–08–01 requires,
for certain serial-numbered swashplates
part number (P/N) 332A31–3074–00 and
P/N 332A31–3074–01, a repetitive
visual inspection of the five yokes for a
crack and replacing the swashplate if
there is a crack in any of the yokes.
AD 2018–08–01 was prompted by
EASA AD No. 2017–0191R2, dated
December 15, 2017 (EASA AD 2017–
0191R2), issued by EASA, which is the
Technical Agent for the Member States
of the European Union. EASA advised
of a finding by Airbus Helicopters that
the yoke is susceptible to cracking due
to strain aging of the metal. EASA
advised that this condition, if not
detected and corrected, could lead to
structural failure of a yoke, possibly
resulting in loss of control of the
helicopter.
Actions Since AD 2018–08–01 Was
Issued
Since the FAA issued AD 2018–08–
01, Airbus Helicopters revised the
related service information, Emergency
Alert Service Bulletin (EASB) No.
05A051, Revision 1, dated November
16, 2017, to Revision 2, dated February
26, 2019 (EASB 05A051). EASB 05A051
establishes a life limit (also called a
service life limit) of 12 years for the
swashplate and adds a reporting
requirement if there is a crack or
corrosion in a yoke.
Thereafter, EASA superseded EASA
AD 2017–0191R2 with EASA AD No.
2019–0074, dated March 28, 2019
(EASA AD 2019–0074). EASA advises
that additional analysis determined that
it is necessary to introduce a new life
limit for the affected swashplates.
Accordingly, EASA AD 2019–0074
retains the requirements of EASA AD
2017–0191R2 and adds the life limit and
the reporting requirement.
Additionally, the FAA issued AD
2018–08–01 to address the unsafe
condition of a crack in a swashplate
yoke. However, AD 2018–08–01 did not
require stripping certain yokes and
performing a one-time inspection within
100 hours time-in-service (TIS) for
corrosion and a crack as specified in
EASA AD 2017–0191R2, as there is
sufficient time to allow for notice and
comment prior to this long-term AD
requirement going into effect. The FAA
has determined this inspection is
needed to address this unsafe condition
and has proposed to require, within 100
hours TIS and for certain yokes,
removing the grease and stripping
certain areas of the yokes and inspecting
these areas for corrosion, pitting, loss of
material, and a crack in this proposed
AD.
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 about 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
helicopters of the same type design.
Related Service Information Under 1
CFR Part 51
The FAA reviewed one document that
co-publishes two Airbus Helicopters
EASB identification numbers: EASB
05A051 for Model EC225LP helicopters
and EASB No. 05A046, Revision 2,
dated February 26, 2019, for non-FAA
type-certificated Model EC725AP
helicopters. EASB 05A051 is proposed
for incorporation by reference in this
proposed AD. Airbus Helicopters EASB
No. 05A046 is not proposed for
incorporation by reference in this
proposed AD.
This service information specifies
inspections for swashplate P/N 332A31–
3074–00 and P/N 332A31–3074–01.
This service information specifies
procedures for a repetitive inspection of
the yokes for a crack and a one-time
inspection of the stripped yokes for
corrosion and a crack. If in doubt about
whether there is a crack, this service
information specifies performing a non-
destructive inspection. This service
information also specifies touching up
the swashplate with varnish if there is
corrosion, removing any damage within
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allowable limits, and refinishing the
yokes. If there is a crack in a yoke, this
service information specifies replacing
the swashplate. This service information
also specifies a life limit of 12 years
since the date of manufacture for the
swashplates and reporting requirements
if a crack or corrosion is discovered.
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.
Other Related Service Information
The FAA reviewed one document that
co-publishes two Airbus Helicopters
EASB identification numbers: No.
05A051 for Model EC225LP helicopters
and No. 05A046 for non-FAA type-
certificated Model EC725AP helicopters,
each Revision 1 and dated November
16, 2017. Revision 1 of this service
information specifies the same
inspections as Revision 2 of this service
information. However, Revision 2 of this
service information clarifies some of the
inspection instructions and adds a life
limit and a reporting requirement.
Proposed AD Requirements
This proposed AD would require,
before further flight, reviewing
Appendix 4.A. of EASB 05A051 to
determine the date of manufacture of
the swashplate and establishing a life
limit of 12 years since the date of
manufacture. This proposed AD would
retain the repetitive visual inspections
of AD 2018–08–01 to inspect each yoke
for a crack at intervals not to exceed 15
hours time-in-service for swashplates
that have accumulated less than 7 years
since the date of manufacture. For a
swashplate that has accumulated 7 or
more years, but less than 12 years, since
the date of manufacture, this proposed
AD would require removing the grease
and stripping certain areas of the yokes
and inspecting these areas for corrosion,
pitting, loss of material, and a crack. If
there are no cracks, this AD would
require performing a dye penetrant
inspection of the yoke for a crack.
Depending on the results of this
inspection, the proposed AD would
require either repairing the surface of
the swashplate or removing it from
service.
Differences Between This Proposed AD
and the EASA AD
The EASA AD requires performing a
non-destructive inspection only if there
is doubt whether there is a crack.
Instead, this proposed AD requires a
visual inspection and if there are no
cracks, requires a non-destructive
inspection. The EASA AD specifies
instructions for reporting inspection
reports; this proposed AD does not.
Costs of Compliance
The FAA estimates that this proposed
AD affects 26 helicopters of U.S.
Registry. The FAA estimates that
operators may incur the following costs
in order to comply with this proposed
AD. Labor costs are estimated at $85 per
work-hour.
Determining the date of manufacture
of the swashplate would take about 0.5
work-hour for an estimated cost of $43
per helicopter and $1,118 for the U.S.
fleet.
Inspecting the yokes would take about
0.25 work-hour for an estimated cost of
$21 per helicopter and $546 for the U.S.
fleet per inspection cycle.
Removing grease, stripping the yokes,
and inspecting the stripped yokes
would take about 8 work-hours, for a
total estimated cost of $680 per
helicopter.
Dye-penetrant inspecting a yoke for a
crack would take about 6 work-hours
and parts would cost about $50, for an
estimated cost of $560 per yoke.
Removing any corrosion or repairing
damage within the allowable limit
would take about 3 work-hours, for an
estimated cost of $255 per yoke.
Replacing the swashplate would take
about 6 work-hours, and parts would
cost about $85,661 for an estimated cost
of $86,171 per instance.
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.
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
removing Airworthiness Directive (AD)
2018–08–01, Amendment 39–19254 (83
FR 17617, April 23, 2018), and adding
the following new AD:
Airbus Helicopters: Docket No. FAA–2020–
0513; Product Identifier 2019–SW–037–
AD.
(a) Applicability
This AD applies to Airbus Helicopters
Model EC225LP helicopters, certificated in
any category, with a main rotor (M/R)
rotating swashplate (swashplate) part number
(P/N) 332A31–3074–00 or P/N 332A31–
3074–01 installed.
(b) Unsafe Condition
This AD defines the unsafe condition as a
crack in a swashplate control rod attachment
yoke (yoke). This condition could result in
failure of the yoke, loss of M/R control, and
subsequent loss of control of the helicopter.
(c) Affected ADs
This AD replaces AD 2018–08–01,
Amendment 39–19254 (83 FR 17617, April
23, 2018).
(d) Comments Due Date
The FAA must receive comments by
August 3, 2020.
(e) Compliance
You are responsible for performing each
action required by this AD within the
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specified compliance time unless it has
already been accomplished prior to that time.
(f) Required Actions
Before further flight, review Appendix 4.A.
of Airbus Helicopters Emergency Alert
Service Bulletin No. 05A051, Revision 2,
dated February 26, 2019 (EASB 05A051) to
determine the date of manufacture of the
swashplate.
(1) If the swashplate has accumulated 12 or
more years since the date of manufacture,
remove from service the swashplate.
(2) If the swashplate has accumulated less
than 12 years since the date of manufacture,
create a component history card or
equivalent record indicating a life limit of 12
years since the date of manufacture.
Thereafter, continue to record the life limit
of the swashplate on its component history
card or equivalent record and remove from
service any swashplate before accumulating
12 years since the date of manufacture.
(3) For each swashplate that has
accumulated less than 7 years since the date
of manufacture, within 15 hours time-in-
service (TIS) and thereafter at intervals not to
exceed 15 hours TIS, until the swashplate
accumulates 7 years since the date of
manufacture, visually inspect each yoke for
a crack, paying particular attention to the
areas shown in Details B, C, and D of Figure
1 of EASB 05A051.
(i) If there are no cracks, perform a dye
penetrant inspection of the yoke for a crack.
(ii) If there is a crack on a yoke, before
further flight, remove from service the
swashplate.
(4) For each swashplate that has
accumulated 7 or more years, but less than
12 years, since the date of manufacture,
within 100 hours TIS:
(i) Remove the grease from areas (E), (F),
(G), (H), (J), and (K) of each yoke as shown
in Details B, C, and D of Figure 1 of EASB
05A051. Using a plastic spatula, strip areas
(E), (F), (G), (H), (J), and (K) of each yoke as
shown in Details B, C, and D of Figure 1 of
EASB 05A051. Do not use a metal tool to
strip any area of a yoke.
(ii) Inspect areas (E), (F), (G), (H), (J) and
(K) of each yoke as shown in Details B, C,
and D of Figure 1 of EASB 05A051 for
corrosion, pitting, and loss of material.
(A) If there is any corrosion less than
0.0078 in. (0.2 mm), before further flight,
remove the corrosion and apply varnish
(Vernelec 43022 or equivalent) to the surface
of areas (E), (F), (G), (H), (J) and (K).
(B) If there is any pitting or loss of material
of less than 0.0078 in. (0.2 mm), before
further flight, remove the damage by sanding
with sandpaper 200/400 or 330.
(C) If there is any corrosion, pitting, or loss
of material of 0.0078 in. (0.2 mm) or greater,
before further flight, remove from service the
swashplate.
(iii) Visually inspect each yoke for a crack,
paying particular attention to the areas
shown in Details B, C, and D of Figure 1 of
EASB 05A051.
(A) If there are no cracks, perform a dye
penetrant inspection of the yoke for a crack.
(B) If there is a crack on a yoke, before
further flight, remove from service the
swashplate.
(g) Credit for Previous Actions
If you performed the actions in paragraph
(f)(4) before the effective date of this AD
using Airbus Helicopters Emergency Alert
Service Bulletin No. 05A051, Revision 1,
dated November 16, 2017, you met the
requirements of paragraph (f)(4) of this AD.
(h) 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-FTW-
AMOC-Requests@faa.gov.
(2) For operations conducted under a 14
CFR part 119 operating certificate or under
14 CFR part 91, subpart K, the FAA suggests
that you notify your principal inspector, or
lacking a principal inspector, the manager of
the local flight standards district office or
certificate holding district office before
operating any aircraft complying with this
AD through an AMOC.
(i) Additional Information
The subject of this AD is addressed in
European Union Aviation Safety Agency
(EASA) AD No. 2019–0074, dated March 28,
2019. You may view the EASA AD on the
internet at https://www.regulations.gov in the
AD Docket.
(j) Subject
Joint Aircraft Service Component (JASC)
Code: 6230, Main Rotor Mast/Swashplate.
Issued on May 27, 2020.
Lance T. Gant,
Director, Compliance & Airworthiness
Division, Aircraft Certification Service.
[FR Doc. 2020–11821 Filed 6–2–20; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2018–1046; Product
Identifier 2018–CE–049–AD]
RIN 2120–AA64
Airworthiness Directives; Piper
Aircraft, Inc. Airplanes
AGENCY
: Federal Aviation
Administration (FAA), DOT.
ACTION
: Supplemental notice of
proposed rulemaking (SNPRM);
reopening of comment period.
SUMMARY
: The FAA is revising an earlier
proposal for certain Piper Aircraft, Inc.
(Piper) Models PA–28–140, PA–28–150,
PA–28–151, PA–28–160, PA–28–161,
PA–28–180, PA–28–181, PA–28–235,
PA–28R–180, PA–28R–200, PA–28R–
201, PA–28R–201T, PA–28RT–201, PA–
28RT–201T, PA–32–260, and PA–32–
300 airplanes. The notice of proposed
rulemaking (NPRM) was prompted by a
report of a wing separation caused by
fatigue cracking in a visually
inaccessible area of the lower main wing
spar cap. This action revises the NPRM
by adding and removing certain models
of airplanes in the Applicability,
proposing to require the use of service
information that was issued since the
NPRM, and clarifying some of the
proposed actions. The FAA is proposing
this airworthiness directive (AD) to
address the unsafe condition on these
products. Since these actions would
impose an additional burden over those
proposed in the NPRM, the FAA is
reopening the comment period to allow
the public the chance to comment on
these changes.
DATES
: The comment period for the
NPRM published in the Federal
Register on December 21, 2018 (83 FR
65592), is reopened.
The FAA must receive comments on
this SNPRM by July 20, 2020.
ADDRESSES
: You may send comments,
using the procedures found in 14 CFR
11.43 and 11.45, by any of the following
methods:
Federal eRulemaking Portal: Go to
https://www.regulations.gov. Follow the
instructions for submitting comments.
Fax: 202–493–2251.
Mail: U.S. Department of
Transportation, Docket Operations, M–
30, West Building Ground Floor, Room
W12–140, 1200 New Jersey Avenue SE,
Washington, DC 20590.
Hand Delivery: U.S. Department of
Transportation, Docket Operations, M–
30, West Building Ground Floor, Room
W12–140, 1200 New Jersey Avenue SE,
Washington, DC 20590, between 9 a.m.
and 5 p.m., Monday through Friday,
except Federal holidays.
For service information identified in
this SNPRM, Piper Aircraft, Inc., 2926
Piper Drive, Vero Beach, Florida 32960;
telephone: (772) 567–4361; internet:
www.piper.com. You may view this
service information at the FAA,
Airworthiness Products Section,
Operational Safety Branch, 901 Locust,
Kansas City, Missouri 64106. For
information on the availability of this
material at the FAA, call (816) 329–
4148.
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–2018–
1046; or in person at Docket Operations
between 9 a.m. and 5 p.m., Monday
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lotter on DSK9F5VC42PROD with PROPOSALS

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