Airworthiness Directives; Leonardo S.p.a. (Type Certificate Previously Held by Agusta S.p.A.) Helicopters, 24780-24783 [2021-09759]
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Federal Register / Vol. 86, No. 88 / Monday, May 10, 2021 / Proposed Rules
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 this proposed regulation:
(1) Is not a ‘‘significant regulatory
action’’ under Executive Order 12866,
(2) Would not affect intrastate
aviation in Alaska, and
(3) Would 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 adding
the following new airworthiness
directive:
■
The Boeing Company: Docket No. FAA–
2021–0338; Project Identifier AD–2020–
01423–T.
(a) Comments Due Date
The FAA must receive comments on this
airworthiness directive (AD) by June 24,
2021.
(b) Affected ADs
None.
(c) Applicability
This AD applies to The Boeing Company
Model 787–8 and 787–9 airplanes,
certificated in any category, as identified in
Boeing Alert Requirements Bulletin B787–
81205–SB530077–00 RB, Issue 001, dated
September 8, 2020.
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(d) Subject
Air Transport Association (ATA) of
America Code 53, Fuselage.
(e) Unsafe Condition
This AD was prompted by reports that
shimming requirements were not met during
the assembly of certain aft wheel well
bulkhead (AWWB) structural joints, which
can result in reduced fatigue thresholds and
cracking of the affected structural joints. The
FAA is issuing this AD to address undetected
fatigue cracking, which could weaken
primary structure so it cannot sustain limit
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load, and could result in reduced structural
integrity of the airplane.
(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
(g) Required Actions
Except as specified by paragraph (h) of this
AD: At the applicable times specified in the
‘‘Compliance’’ paragraph of Boeing Alert
Requirements Bulletins B787–81205–
SB530077–00 RB and B787–81205–
SB530078–00 RB, both Issue 001, both dated
September 8, 2020, do all applicable actions
identified in, and in accordance with, the
Accomplishment Instructions of Boeing Alert
Requirements Bulletins B787–81205–
SB530077–00 RB and B787–81205–
SB530078–00 RB, both Issue 001, both dated
September 8, 2020.
Note 1 to paragraph (g): Guidance for
accomplishing the actions required by this
AD can be found in Boeing Alert Service
Bulletins B787–81205–SB530077–00 and
B787–81205–SB530078–00, both Issue 001,
both dated September 8, 2020, which are
referred to in Boeing Alert Requirements
Bulletins B787–81205–SB530077–00 RB and
B787–81205–SB530078–00 RB, both Issue
001, both dated September 8, 2020.
(h) Exceptions to Service Information
Specifications
(1) Where Boeing Alert Requirements
Bulletin B787–81205–SB530077–00 RB, Issue
001, dated September 8, 2020, uses the
phrase ‘‘the issue 001 date of the
Requirements Bulletin B787–81205–
SB530077–00 RB’’ this AD requires using
‘‘the effective date of this AD.’’
(2) Where Boeing Alert Requirements
Bulletin B787–81205–SB530078–00 RB, Issue
001, dated September 8, 2020, uses the
phrase ‘‘the issue 001 date of the
Requirements Bulletin B787–81205–
SB530078–00 RB,’’ this AD requires using
‘‘the effective date of this AD.’’
(3) Where Boeing Alert Requirements
Bulletins B787–81205–SB530077–00 RB and
B787–81205–SB530078–00 RB, both Issue
001, both dated September 8, 2020, specify
contacting Boeing for repair instructions:
This AD requires doing the repair using a
method approved in accordance with the
procedures specified in paragraph (i) of this
AD.
(i) Alternative Methods of Compliance
(AMOCs)
(1) The Manager, Seattle ACO Branch,
FAA, has the authority to approve AMOCs
for this AD, if requested using the procedures
found in 14 CFR 39.19. In accordance with
14 CFR 39.19, send your request to your
principal inspector or responsible Flight
Standards Office, as appropriate. If sending
information directly to the manager of the
certification office, send it to the attention of
the person identified in paragraph (j)(1) of
this AD. Information may be emailed to: 9ANM-Seattle-ACO-AMOC-Requests@faa.gov.
(2) Before using any approved AMOC,
notify your appropriate principal inspector,
or lacking a principal inspector, the manager
of the responsible Flight Standards Office.
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(3) An AMOC that provides an acceptable
level of safety may be used for any repair,
modification, or alteration required by this
AD if it is approved by The Boeing Company
Organization Designation Authorization
(ODA) that has been authorized by the
Manager, Seattle ACO Branch, FAA, to make
those findings. To be approved, the repair
method, modification deviation, or alteration
deviation must meet the certification basis of
the airplane, and the approval must
specifically refer to this AD.
(j) Related Information
(1) For more information about this AD,
contact Greg Rutar, Aerospace Engineer,
Airframe Section, FAA, Seattle ACO Branch,
2200 South 216th St., Des Moines, WA
98198; phone and fax: 206–231–3529; email:
Greg.Rutar@faa.gov.
(2) For service information identified in
this AD, contact Boeing Commercial
Airplanes, Attention: Contractual & Data
Services (C&DS), 2600 Westminster Blvd.,
MC 110–SK57, Seal Beach, CA 90740–5600;
telephone 562–797–1717; internet https://
www.myboeingfleet.com. You may view this
referenced service information at the FAA,
Airworthiness Products Section, Operational
Safety Branch, 2200 South 216th St., Des
Moines, WA. For information on the
availability of this material at the FAA, call
206–231–3195.
Issued on April 20, 2021.
Lance T. Gant,
Director, Compliance & Airworthiness
Division, Aircraft Certification Service.
[FR Doc. 2021–09345 Filed 5–7–21; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2021–0348; Project
Identifier 2018–SW–076–AD]
RIN 2120–AA64
Airworthiness Directives; Leonardo
S.p.a. (Type Certificate Previously Held
by Agusta S.p.A.) Helicopters
Federal Aviation
Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
The FAA proposes to
supersede Airworthiness Directive (AD)
2011–18–52 for certain Agusta S.p.A.
(now Leonardo S.p.a.) Model AB139
and AW139 helicopters. AD 2011–18–
52 requires revising the life limit for
certain part-numbered tail rotor (T/R)
blades, updating the helicopter’s
historical records, repetitively
inspecting each T/R blade for a crack or
damage, and depending on the results,
replacing the T/R blade. Since the FAA
SUMMARY:
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issued AD 2011–18–52, the
manufacturer developed improved T/R
blades using different materials and
established life limits for each improved
blade. This proposed AD would retain
certain requirements from AD 2011–18–
52, revise certain requirements from AD
2011–18–52, and expand the
applicability to include the newlydesigned T/R blades. 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 June 24, 2021.
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.
For service information identified in
this NPRM, contact Leonardo S.p.a.
Helicopters, Emanuele Bufano, Head of
Airworthiness, Viale G.Agusta 520,
21017 C.Costa di Samarate (Va) Italy;
telephone +39–0331–225074; fax +39–
0331–229046; or at https://
www.leonardocompany.com/en/home.
You may view this service information
at the 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.
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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–2021–
0348; 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 (now European Union Aviation
Safety Agency) (EASA) AD, any
comments received and other
information. The street address for
Docket Operations is listed above.
FOR FURTHER INFORMATION CONTACT: Matt
Fuller, AD Program Manager,
Operational Safety Branch,
Airworthiness Products Section,
General Aviation & Rotorcraft Unit,
FAA, 10101 Hillwood Pkwy., Fort
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Worth, TX 76177; telephone (817) 222–
5110; email Matthew.Fuller@faa.gov.
SUPPLEMENTARY INFORMATION:
Comments Invited
The FAA invites you to send any
written relevant data, views, or
arguments about this proposal. Send
your comments to an address listed
under ADDRESSES. Include ‘‘Docket No.
FAA–2021–0348; Project Identifier
2018–SW–076–AD’’ at the beginning of
your comments. The most helpful
comments reference a specific portion of
the proposal, explain the reason for any
recommended change, and include
supporting data. The FAA will consider
all comments received by the closing
date and may amend this proposal
because of those comments.
Except for Confidential Business
Information (CBI) as described in the
following paragraph, and other
information as described in 14 CFR
11.35, the FAA will post all comments
received, without change, to https://
www.regulations.gov, including any
personal information you provide. The
agency will also post a report
summarizing each substantive verbal
contact received about this proposal.
Confidential Business Information
CBI is commercial or financial
information that is both customarily and
actually treated as private by its owner.
Under the Freedom of Information Act
(FOIA) (5 U.S.C. 552), CBI is exempt
from public disclosure. If your
comments responsive to this NPRM
contain commercial or financial
information that is customarily treated
as private, that you actually treat as
private, and that is relevant or
responsive to this NPRM, it is important
that you clearly designate the submitted
comments as CBI. Please mark each
page of your submission containing CBI
as ‘‘PROPIN.’’ The FAA will treat such
marked submissions as confidential
under the FOIA, and they will not be
placed in the public docket of this
NPRM. Submissions containing CBI
should be sent to, Matt Fuller, AD
Program Manager, Operational Safety
Branch, Airworthiness Products
Section, General Aviation & Rotorcraft
Unit, FAA, 10101 Hillwood Pkwy., Fort
Worth, TX 76177; telephone (817) 222–
5110; email Matthew.Fuller@faa.gov.
Any commentary that the FAA receives
which is not specifically designated as
CBI will be placed in the public docket
for this rulemaking.
Background
The FAA issued Emergency AD 2011–
18–52 on August 25, 2011, which was
published as a Final rule; request for
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comments, on April 18, 2012 (77 FR
23109) (AD 2011–18–52). AD 2011–18–
52 applies to Agusta S.p.A. (now
Leonardo S.p.a.) Model AB139 and
AW139 helicopters with a T/R blade
part number (P/N) 3G6410A00131 or P/
N 4G6410A00131 installed. AD 2011–
18–52 requires, within 5 hours time-inservice (TIS), establishing a life limit of
600 hours TIS or 1,500 takeoff and
landing cycles (cycles), whichever
occurs first, on the affected T/R blades
and updating the helicopter’s historical
records. If a T/R blade’s total number of
cycles is unknown, determining the T/
R blade cycles by multiplying the T/R
blade’s hours TIS by 4 is required. For
a T/R blade that, on the effective date
of the AD, has already exceeded 600
hours TIS or 1,500 cycles, the AD
requires replacing the T/R blade with an
airworthy T/R blade within 5 hours TIS.
AD 2011–18–52 also requires, within
25 hours TIS, and thereafter at intervals
not to exceed 25 hours TIS, inspecting
the T/R blade for a crack or damage that
exceeds the limits of the applicable
maintenance manual. The inspection
must be accomplished using a mirror,
magnifying glass (5X or greater), and
light source; or borescope. If there is a
crack, or if there is damage that exceeds
the limits of the applicable maintenance
manual, AD 2011–18–52 requires,
before further flight, replacing the T/R
blade with an airworthy T/R blade.
AD 2011–18–52 was prompted by a
fatal accident involving an Agusta
Model AW139 helicopter, which may
have been caused by cracks in a T/R
blade. EASA, which is the Technical
Agent for the Member States of the
European Union, issued EASA
Emergency AD 2011–0156–E, dated
August 25, 2011 (EASA AD 2011–0156–
E) to require repetitive inspections and
reducing the life limit of the T/R blades.
According to EASA, this condition, if
not detected and corrected, could result
in failure of a T/R blade and subsequent
loss of control of the helicopter.
Actions Since AD 2011–18–52 Was
Issued
Since the FAA issued AD 2011–18–
52, EASA issued a series of ADs as
follows:
• EASA AD 2012–0030, dated
February 17, 2012 (EASA AD 2012–
0030), which superseded Emergency AD
2011–0156–E, advised that the
manufacturer developed improved,
newly-designed T/R blades P/N
3G6410A00132 and P/N
4G6410A00132, established life limits
for each improved T/R blade, added
repetitive inspections for the improved
T/R blades, and advised that each T/R
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blade P/N had its own individual life
limit.
• EASA AD 2012–0076, dated May 2,
2012 (EASA AD 2012–0076), which
superseded EASA AD 2012–0030 and
was issued after the manufacturer
developed another version of improved
T/R blades P/N 3G6410A00133 and P/
N 4G6410A00133 with different
materials. AD 2012–0076 required
interim life limits for the new improved
version of the T/R blades while also
retaining the inspection requirements of
EASA AD 2012–0030.
• EASA AD 2012–0076R1, dated July
13, 2012 (EASA AD 2012–0076R1),
which revised EASA AD 2012–0076
after a modification was developed to
allow installation of certain partnumbered T/R blades under certain
conditions.
• EASA AD 2012–0076R2, dated
February 20, 2014 (EASA AD 2012–
0076R2), which revised EASA AD
2012–0076R1, was issued after another
modification was developed. EASA AD
2012–0076R2 requires removing the 25
hours TIS inspection of certain partnumbered T/R blades, extending the life
limit of certain part-numbered T/R
blades, retaining the repetitive
inspections of certain part-numbered T/
R blades and depending on the
inspection results, performing certain
applicable corrections.
Also, after AD 2011–18–52 was
issued, the FAA issued an NPRM (78 FR
54596), which published in the Federal
Register on September 5, 2013. The
NPRM proposed to require retaining the
inspection requirements for certain partnumbered blades and expand the
applicability to include the newly
designed blades and establish life limits
for those blades. The NPRM also
proposed to require replacing any
cracked blade or any blade that has
reached its life limit. That NPRM was
prompted by improved modifications of
the T/R blades. However, because the
FAA determined that the NPRM does
not adequately address the identified
unsafe condition, the NPRM was
withdrawn on February 25, 2021 (86 FR
11477).
Additional review also revealed
necessary changes to address the unsafe
condition. This proposed AD clarifies
the repetitive inspection for T/R blade
P/Ns 3G6410A00131 and P/N
4G6410A00131 from, ‘‘visually inspect
the T/R blade for a crack or damage’’ to
‘‘visually inspect the T/R blade for a
crack and damage.’’ This proposed AD
further revises that repetitive inspection
from ‘‘damage that exceeds the limits of
the applicable maintenance manual’’ to
‘‘damage that exceeds allowable limits’’
to meet current publishing
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requirements. This proposed AD
clarifies the inspection area for that
repetitive inspection by proposing to
require using a figure in the related
service information instead of using a
figure in the body of this AD action.
This proposed AD also revises the
requirements by removing unnecessary
information, including the special flight
permits paragraph.
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 helicopters of the same
type design.
Related Service Information Under 1
CFR Part 51
The FAA reviewed AgustaWestland
S.p.A Mandatory Bollettino Tecnico No.
139–265, Revision B, dated February 18,
2014. This service information specifies
a precautionary inspection for a crack,
a life limit for the affected T/R blades,
and a quarantine of T/R blades that have
exceeded their life limit. This service
information also provides instructions
for mixed usage of the affected T/R
blades and sending certain data to the
manufacturer.
This service information is reasonably
available because the interested parties
have access to it through their normal
course of business or by the means
identified in the ADDRESSES section.
Proposed AD Requirements
This proposed AD would retain the
inspection requirements of AD 2011–
18–52 for certain part-numbered T/R
blades, expand the applicability to
include the improved T/R blades,
require determining each T/R blade’s
total hours TIS or landing cycles, and
establish life limits for certain T/R
blades. This proposed AD would require
removing from service any T/R blade
that has a crack or damage beyond
allowable limits or any T/R blade that
has reached its life limit.
Differences Between This Proposed AD
and EASA AD
The EASA AD does not list the T/R
blade life limits and instead references
the Airworthiness Limitations Section
of 139 AMPI Chapter 4, while this
proposed AD would include the life
limits in the AD. The EASA AD requires
reporting information to Product
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Support Engineering, whereas this
proposed AD would not. The EASA AD
requires contacting AgustaWestland if a
crack or damage is found during the
inspection, whereas this proposed AD
would require removing the T/R blade
from service.
Costs of Compliance
The FAA estimates that this proposed
AD would affect 130 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.
Inspecting one T/R blade for a crack
would take about 1 work-hour for an
estimated cost of $85 per T/R blade per
inspection cycle and up to $44,200 for
the U.S. fleet per inspection cycle.
Replacing one T/R blade would take
about 8 work-hours and parts would
cost about $40,560 for an estimated cost
of $41,240 per replacement.
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. Would not affect intrastate aviation
in Alaska, and
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Federal Register / Vol. 86, No. 88 / Monday, May 10, 2021 / Proposed Rules
3. Would 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:
a. Removing Airworthiness Directive
2011–18–52, Amendment 39–17020 (77
FR 23109, April 18, 2012); and
■ b. Adding the following new
airworthiness directive:
■
■
Leonardo S.p.a. (Type Certificate Previously
Held by Agusta S.p.A.): Docket No.
FAA–2021–0348; Project Identifier
2018–SW–076–AD.
(a) Comments Due Date
The FAA must receive comments on this
airworthiness directive (AD) action by June
24, 2021.
(b) Affected ADs
This AD replaces AD 2011–18–52,
Amendment 39–17020 (77 FR 23109, April
18, 2012) (AD 2011–18–52).
(c) Applicability
This AD applies to Leonardo S.p.a. (type
certificate previously held by Agusta S.p.A.)
Model AB139 and AW139 helicopters,
certificated in any category, with tail rotor
(T/R) blade, part number (P/N)
3G6410A00131, 3G6410A00132,
3G6410A00133, 4G6410A00131,
4G6410A00132, or 4G6410A00133, installed.
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(d) Subject
Joint Aircraft Service Component (JASC)
Code: 6410, Tail Rotor Blades.
(e) Unsafe Condition
This AD defines the unsafe condition as a
crack in a T/R blade. This condition could
result in failure of a T/R blade and
subsequent loss of control of the helicopter.
(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
(g) Required Actions
(1) For T/R blade P/Ns 3G6410A00131 and
4G6410A00131, within 5 hours time-in-
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service (TIS) after May 3, 2012 (the effective
date of AD 2011–18–52), establish a life limit
of 600 hours TIS or 1,500 takeoff and landing
cycles (cycles), whichever occurs first, on the
affected T/R blades and update the
helicopter’s historical records. If a T/R
blade’s total number of cycles is unknown,
determine the T/R blade cycles by
multiplying the T/R blade’s hours TIS by 4.
(2) For T/R blade P/Ns 3G6410A00131 and
4G6410A00131, thereafter following
paragraph (g)(1) of this AD, remove any T/R
blade from service before accumulating 600
total hours TIS or 1,500 total cycles,
whichever occurs first.
(3) For T/R blade P/Ns 3G6410A00132,
3G6410A00133, 4G6410A00132, and
4G6410A00133, within 5 hours TIS after the
effective date of this AD, determine the total
number of cycles. If a T/R blade’s total
number of cycles is unknown, determine the
T/R blade cycles by multiplying the blade’s
hours TIS by 4. Before further flight, remove
any T/R blade from service that has
accumulated or exceeded its life limit as
follows. Thereafter, remove any T/R blade
from service before accumulating its life limit
as follows:
(i) T/R blade P/Ns 3G6410A00132 and
4G6410A00132: 1,200 total hours TIS or
3,200 total cycles, whichever occurs first.
(ii) T/R blade P/N 3G6410A00133: 40,000
total cycles.
(iii) T/R blade P/N 4G6410A00133: 4,033
total hours TIS or 40,000 cycles, whichever
occurs first.
Note 1 to paragraph (g)(3): A combination
of T/R blades having different P/Ns can be
installed on the same helicopter. The eligible
combinations of T/R blades P/N are listed in
AgustaWestland S.p.A. Mandatory Bollettino
Tecnico No. 139–265, Revision B, dated
February 18, 2014 (BT No. 139–265).
(4) For T/R blade P/Ns 3G6410A00131 and
P/N 4G6410A00131, within 25 hours TIS
after the effective date of this AD, and
thereafter at intervals not to exceed 25 hours
TIS, visually inspect the T/R blade for a crack
and damage that exceeds allowable limits.
Inspect in the area depicted in Figure 1 of BT
No. 139–265 using a mirror, a 5X or higher
power magnifying glass, and a flashlight, or
borescope. If there is a crack or damage that
exceeds allowable limits, before further
flight, remove the T/R blade from service.
(5) As of the effective date of this AD, do
not install on any helicopter any T/R blade
P/N 3G6410A00131 or P/N 4G6410A00131,
unless the actions required by paragraphs
(g)(1), (2), and (4) of this AD have been
accomplished.
(h) Alternative Methods of Compliance
(AMOCs)
(1) The Manager, International Validation
Branch, FAA, has the authority to approve
AMOCs for this AD, if requested using the
procedures found in 14 CFR 39.19. In
accordance with 14 CFR 39.19, send your
request to your principal inspector or local
Flight Standards District Office, as
appropriate. If sending information directly
to the manager of the International Validation
Branch, send it to the attention of the person
identified in paragraph (i)(1) of this AD.
Information may be emailed to: email 9-AVSAIR-730-AMOC@faa.gov.
PO 00000
Frm 00034
Fmt 4702
Sfmt 4702
24783
(2) Before using any approved AMOC,
notify your appropriate principal inspector,
or lacking a principal inspector, the manager
of the local flight standards district office/
certificate holding district office.
(i) Related Information
(1) For more information about this AD,
contact Matt Fuller, AD Program Manager,
Operational Safety Branch, Airworthiness
Products Section, General Aviation &
Rotorcraft Unit, FAA, 10101 Hillwood Pkwy.,
Fort Worth, TX 76177; telephone (817) 222–
5110; email matthew.fuller@faa.gov.
(2) For service information identified in
this AD, contact Leonardo S.p.a. Helicopters,
Emanuele Bufano, Head of Airworthiness,
Viale G.Agusta 520, 21017 C.Costa di
Samarate (Va) Italy; telephone +39–0331–
225074; fax +39–0331–229046; or at https://
www.leonardocompany.com/en/home. You
may view this service information at the
FAA, Office of the Regional Counsel,
Southwest Region, 10101 Hillwood Pkwy.,
Room 6N–321, Fort Worth, TX 76177.
(3) The subject of this AD is addressed in
European Aviation Safety Agency (now
European Union Aviation Safety Agency)
(EASA) AD 2012–0076R2, dated February 20,
2014. You may view the EASA AD on the
internet at https://www.regulations.gov in the
AD Docket.
Issued on April 30, 2021.
Lance T. Gant,
Director, Compliance & Airworthiness
Division, Aircraft Certification Service.
[FR Doc. 2021–09759 Filed 5–7–21; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2020–0904; Product
Identifier 2019–SW–041–AD]
RIN 2120–AA64
Airworthiness Directives; Airbus
Helicopters
Federal Aviation
Administration (FAA), DOT.
ACTION: Supplemental notice of
proposed rulemaking (SNPRM).
AGENCY:
The FAA is revising a notice
of proposed rulemaking (NPRM) that
applied to certain Airbus Helicopters
Model EC225LP helicopters. This action
revises the NPRM by revising the
required actions paragraph such that the
required actions apply to all helicopter
models specified in the applicability.
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 in the
NPRM, the agency is requesting
comments on this SNPRM.
SUMMARY:
E:\FR\FM\10MYP1.SGM
10MYP1
]]>Agencies
[Federal Register Volume 86, Number 88 (Monday, May 10, 2021)]
[Proposed Rules]
[Pages 24780-24783]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2021-09759]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2021-0348; Project Identifier 2018-SW-076-AD]
RIN 2120-AA64
Airworthiness Directives; Leonardo S.p.a. (Type Certificate
Previously Held by Agusta S.p.A.) Helicopters
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking (NPRM).
-----------------------------------------------------------------------
SUMMARY: The FAA proposes to supersede Airworthiness Directive (AD)
2011-18-52 for certain Agusta S.p.A. (now Leonardo S.p.a.) Model AB139
and AW139 helicopters. AD 2011-18-52 requires revising the life limit
for certain part-numbered tail rotor (T/R) blades, updating the
helicopter's historical records, repetitively inspecting each T/R blade
for a crack or damage, and depending on the results, replacing the T/R
blade. Since the FAA
[[Page 24781]]
issued AD 2011-18-52, the manufacturer developed improved T/R blades
using different materials and established life limits for each improved
blade. This proposed AD would retain certain requirements from AD 2011-
18-52, revise certain requirements from AD 2011-18-52, and expand the
applicability to include the newly-designed T/R blades. 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 June 24,
2021.
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.
For service information identified in this NPRM, contact Leonardo
S.p.a. Helicopters, Emanuele Bufano, Head of Airworthiness, Viale
G.Agusta 520, 21017 C.Costa di Samarate (Va) Italy; telephone +39-0331-
225074; fax +39-0331-229046; or at https://www.leonardocompany.com/en/home. You may view this service information at the 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.
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-2021-
0348; 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 (now European
Union Aviation Safety Agency) (EASA) AD, any comments received and
other information. The street address for Docket Operations is listed
above.
FOR FURTHER INFORMATION CONTACT: Matt Fuller, AD Program Manager,
Operational Safety Branch, Airworthiness Products Section, General
Aviation & Rotorcraft Unit, FAA, 10101 Hillwood Pkwy., Fort Worth, TX
76177; telephone (817) 222-5110; email [email protected].
SUPPLEMENTARY INFORMATION:
Comments Invited
The FAA invites you to send any written relevant data, views, or
arguments about this proposal. Send your comments to an address listed
under ADDRESSES. Include ``Docket No. FAA-2021-0348; Project Identifier
2018-SW-076-AD'' at the beginning of your comments. The most helpful
comments reference a specific portion of the proposal, explain the
reason for any recommended change, and include supporting data. The FAA
will consider all comments received by the closing date and may amend
this proposal because of those comments.
Except for Confidential Business Information (CBI) as described in
the following paragraph, and other information as described in 14 CFR
11.35, the FAA will post all comments received, without change, to
https://www.regulations.gov, including any personal information you
provide. The agency will also post a report summarizing each
substantive verbal contact received about this proposal.
Confidential Business Information
CBI is commercial or financial information that is both customarily
and actually treated as private by its owner. Under the Freedom of
Information Act (FOIA) (5 U.S.C. 552), CBI is exempt from public
disclosure. If your comments responsive to this NPRM contain commercial
or financial information that is customarily treated as private, that
you actually treat as private, and that is relevant or responsive to
this NPRM, it is important that you clearly designate the submitted
comments as CBI. Please mark each page of your submission containing
CBI as ``PROPIN.'' The FAA will treat such marked submissions as
confidential under the FOIA, and they will not be placed in the public
docket of this NPRM. Submissions containing CBI should be sent to, Matt
Fuller, AD Program Manager, Operational Safety Branch, Airworthiness
Products Section, General Aviation & Rotorcraft Unit, FAA, 10101
Hillwood Pkwy., Fort Worth, TX 76177; telephone (817) 222-5110; email
[email protected]. Any commentary that the FAA receives which is
not specifically designated as CBI will be placed in the public docket
for this rulemaking.
Background
The FAA issued Emergency AD 2011-18-52 on August 25, 2011, which
was published as a Final rule; request for comments, on April 18, 2012
(77 FR 23109) (AD 2011-18-52). AD 2011-18-52 applies to Agusta S.p.A.
(now Leonardo S.p.a.) Model AB139 and AW139 helicopters with a T/R
blade part number (P/N) 3G6410A00131 or P/N 4G6410A00131 installed. AD
2011-18-52 requires, within 5 hours time-in-service (TIS), establishing
a life limit of 600 hours TIS or 1,500 takeoff and landing cycles
(cycles), whichever occurs first, on the affected T/R blades and
updating the helicopter's historical records. If a T/R blade's total
number of cycles is unknown, determining the T/R blade cycles by
multiplying the T/R blade's hours TIS by 4 is required. For a T/R blade
that, on the effective date of the AD, has already exceeded 600 hours
TIS or 1,500 cycles, the AD requires replacing the T/R blade with an
airworthy T/R blade within 5 hours TIS.
AD 2011-18-52 also requires, within 25 hours TIS, and thereafter at
intervals not to exceed 25 hours TIS, inspecting the T/R blade for a
crack or damage that exceeds the limits of the applicable maintenance
manual. The inspection must be accomplished using a mirror, magnifying
glass (5X or greater), and light source; or borescope. If there is a
crack, or if there is damage that exceeds the limits of the applicable
maintenance manual, AD 2011-18-52 requires, before further flight,
replacing the T/R blade with an airworthy T/R blade.
AD 2011-18-52 was prompted by a fatal accident involving an Agusta
Model AW139 helicopter, which may have been caused by cracks in a T/R
blade. EASA, which is the Technical Agent for the Member States of the
European Union, issued EASA Emergency AD 2011-0156-E, dated August 25,
2011 (EASA AD 2011-0156-E) to require repetitive inspections and
reducing the life limit of the T/R blades. According to EASA, this
condition, if not detected and corrected, could result in failure of a
T/R blade and subsequent loss of control of the helicopter.
Actions Since AD 2011-18-52 Was Issued
Since the FAA issued AD 2011-18-52, EASA issued a series of ADs as
follows:
EASA AD 2012-0030, dated February 17, 2012 (EASA AD 2012-
0030), which superseded Emergency AD 2011-0156-E, advised that the
manufacturer developed improved, newly-designed T/R blades P/N
3G6410A00132 and P/N 4G6410A00132, established life limits for each
improved T/R blade, added repetitive inspections for the improved T/R
blades, and advised that each T/R
[[Page 24782]]
blade P/N had its own individual life limit.
EASA AD 2012-0076, dated May 2, 2012 (EASA AD 2012-0076),
which superseded EASA AD 2012-0030 and was issued after the
manufacturer developed another version of improved T/R blades P/N
3G6410A00133 and P/N 4G6410A00133 with different materials. AD 2012-
0076 required interim life limits for the new improved version of the
T/R blades while also retaining the inspection requirements of EASA AD
2012-0030.
EASA AD 2012-0076R1, dated July 13, 2012 (EASA AD 2012-
0076R1), which revised EASA AD 2012-0076 after a modification was
developed to allow installation of certain part-numbered T/R blades
under certain conditions.
EASA AD 2012-0076R2, dated February 20, 2014 (EASA AD
2012-0076R2), which revised EASA AD 2012-0076R1, was issued after
another modification was developed. EASA AD 2012-0076R2 requires
removing the 25 hours TIS inspection of certain part-numbered T/R
blades, extending the life limit of certain part-numbered T/R blades,
retaining the repetitive inspections of certain part-numbered T/R
blades and depending on the inspection results, performing certain
applicable corrections.
Also, after AD 2011-18-52 was issued, the FAA issued an NPRM (78 FR
54596), which published in the Federal Register on September 5, 2013.
The NPRM proposed to require retaining the inspection requirements for
certain part-numbered blades and expand the applicability to include
the newly designed blades and establish life limits for those blades.
The NPRM also proposed to require replacing any cracked blade or any
blade that has reached its life limit. That NPRM was prompted by
improved modifications of the T/R blades. However, because the FAA
determined that the NPRM does not adequately address the identified
unsafe condition, the NPRM was withdrawn on February 25, 2021 (86 FR
11477).
Additional review also revealed necessary changes to address the
unsafe condition. This proposed AD clarifies the repetitive inspection
for T/R blade P/Ns 3G6410A00131 and P/N 4G6410A00131 from, ``visually
inspect the T/R blade for a crack or damage'' to ``visually inspect the
T/R blade for a crack and damage.'' This proposed AD further revises
that repetitive inspection from ``damage that exceeds the limits of the
applicable maintenance manual'' to ``damage that exceeds allowable
limits'' to meet current publishing requirements. This proposed AD
clarifies the inspection area for that repetitive inspection by
proposing to require using a figure in the related service information
instead of using a figure in the body of this AD action. This proposed
AD also revises the requirements by removing unnecessary information,
including the special flight permits paragraph.
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 helicopters of
the same type design.
Related Service Information Under 1 CFR Part 51
The FAA reviewed AgustaWestland S.p.A Mandatory Bollettino Tecnico
No. 139-265, Revision B, dated February 18, 2014. This service
information specifies a precautionary inspection for a crack, a life
limit for the affected T/R blades, and a quarantine of T/R blades that
have exceeded their life limit. This service information also provides
instructions for mixed usage of the affected T/R blades and sending
certain data to the manufacturer.
This service information is reasonably available because the
interested parties have access to it through their normal course of
business or by the means identified in the ADDRESSES section.
Proposed AD Requirements
This proposed AD would retain the inspection requirements of AD
2011-18-52 for certain part-numbered T/R blades, expand the
applicability to include the improved T/R blades, require determining
each T/R blade's total hours TIS or landing cycles, and establish life
limits for certain T/R blades. This proposed AD would require removing
from service any T/R blade that has a crack or damage beyond allowable
limits or any T/R blade that has reached its life limit.
Differences Between This Proposed AD and EASA AD
The EASA AD does not list the T/R blade life limits and instead
references the Airworthiness Limitations Section of 139 AMPI Chapter 4,
while this proposed AD would include the life limits in the AD. The
EASA AD requires reporting information to Product Support Engineering,
whereas this proposed AD would not. The EASA AD requires contacting
AgustaWestland if a crack or damage is found during the inspection,
whereas this proposed AD would require removing the T/R blade from
service.
Costs of Compliance
The FAA estimates that this proposed AD would affect 130
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.
Inspecting one T/R blade for a crack would take about 1 work-hour
for an estimated cost of $85 per T/R blade per inspection cycle and up
to $44,200 for the U.S. fleet per inspection cycle.
Replacing one T/R blade would take about 8 work-hours and parts
would cost about $40,560 for an estimated cost of $41,240 per
replacement.
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. Would not affect intrastate aviation in Alaska, and
[[Page 24783]]
3. Would 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
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:
0
a. Removing Airworthiness Directive 2011-18-52, Amendment 39-17020 (77
FR 23109, April 18, 2012); and
0
b. Adding the following new airworthiness directive:
Leonardo S.p.a. (Type Certificate Previously Held by Agusta S.p.A.):
Docket No. FAA-2021-0348; Project Identifier 2018-SW-076-AD.
(a) Comments Due Date
The FAA must receive comments on this airworthiness directive
(AD) action by June 24, 2021.
(b) Affected ADs
This AD replaces AD 2011-18-52, Amendment 39-17020 (77 FR 23109,
April 18, 2012) (AD 2011-18-52).
(c) Applicability
This AD applies to Leonardo S.p.a. (type certificate previously
held by Agusta S.p.A.) Model AB139 and AW139 helicopters,
certificated in any category, with tail rotor (T/R) blade, part
number (P/N) 3G6410A00131, 3G6410A00132, 3G6410A00133, 4G6410A00131,
4G6410A00132, or 4G6410A00133, installed.
(d) Subject
Joint Aircraft Service Component (JASC) Code: 6410, Tail Rotor
Blades.
(e) Unsafe Condition
This AD defines the unsafe condition as a crack in a T/R blade.
This condition could result in failure of a T/R blade and subsequent
loss of control of the helicopter.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) Required Actions
(1) For T/R blade P/Ns 3G6410A00131 and 4G6410A00131, within 5
hours time-in-service (TIS) after May 3, 2012 (the effective date of
AD 2011-18-52), establish a life limit of 600 hours TIS or 1,500
takeoff and landing cycles (cycles), whichever occurs first, on the
affected T/R blades and update the helicopter's historical records.
If a T/R blade's total number of cycles is unknown, determine the T/
R blade cycles by multiplying the T/R blade's hours TIS by 4.
(2) For T/R blade P/Ns 3G6410A00131 and 4G6410A00131, thereafter
following paragraph (g)(1) of this AD, remove any T/R blade from
service before accumulating 600 total hours TIS or 1,500 total
cycles, whichever occurs first.
(3) For T/R blade P/Ns 3G6410A00132, 3G6410A00133, 4G6410A00132,
and 4G6410A00133, within 5 hours TIS after the effective date of
this AD, determine the total number of cycles. If a T/R blade's
total number of cycles is unknown, determine the T/R blade cycles by
multiplying the blade's hours TIS by 4. Before further flight,
remove any T/R blade from service that has accumulated or exceeded
its life limit as follows. Thereafter, remove any T/R blade from
service before accumulating its life limit as follows:
(i) T/R blade P/Ns 3G6410A00132 and 4G6410A00132: 1,200 total
hours TIS or 3,200 total cycles, whichever occurs first.
(ii) T/R blade P/N 3G6410A00133: 40,000 total cycles.
(iii) T/R blade P/N 4G6410A00133: 4,033 total hours TIS or
40,000 cycles, whichever occurs first.
Note 1 to paragraph (g)(3): A combination of T/R blades having
different P/Ns can be installed on the same helicopter. The eligible
combinations of T/R blades P/N are listed in AgustaWestland S.p.A.
Mandatory Bollettino Tecnico No. 139-265, Revision B, dated February
18, 2014 (BT No. 139-265).
(4) For T/R blade P/Ns 3G6410A00131 and P/N 4G6410A00131, within
25 hours TIS after the effective date of this AD, and thereafter at
intervals not to exceed 25 hours TIS, visually inspect the T/R blade
for a crack and damage that exceeds allowable limits. Inspect in the
area depicted in Figure 1 of BT No. 139-265 using a mirror, a 5X or
higher power magnifying glass, and a flashlight, or borescope. If
there is a crack or damage that exceeds allowable limits, before
further flight, remove the T/R blade from service.
(5) As of the effective date of this AD, do not install on any
helicopter any T/R blade P/N 3G6410A00131 or P/N 4G6410A00131,
unless the actions required by paragraphs (g)(1), (2), and (4) of
this AD have been accomplished.
(h) Alternative Methods of Compliance (AMOCs)
(1) The Manager, International Validation Branch, FAA, has the
authority to approve AMOCs for this AD, if requested using the
procedures found in 14 CFR 39.19. In accordance with 14 CFR 39.19,
send your request to your principal inspector or local Flight
Standards District Office, as appropriate. If sending information
directly to the manager of the International Validation Branch, send
it to the attention of the person identified in paragraph (i)(1) of
this AD. Information may be emailed to: email [email protected].
(2) Before using any approved AMOC, notify your appropriate
principal inspector, or lacking a principal inspector, the manager
of the local flight standards district office/certificate holding
district office.
(i) Related Information
(1) For more information about this AD, contact Matt Fuller, AD
Program Manager, Operational Safety Branch, Airworthiness Products
Section, General Aviation & Rotorcraft Unit, FAA, 10101 Hillwood
Pkwy., Fort Worth, TX 76177; telephone (817) 222-5110; email
[email protected]
(2) For service information identified in this AD, contact
Leonardo S.p.a. Helicopters, Emanuele Bufano, Head of Airworthiness,
Viale G.Agusta 520, 21017 C.Costa di Samarate (Va) Italy; telephone
+39-0331-225074; fax +39-0331-229046; or at https://www.leonardocompany.com/en/home. You may view this service
information at the FAA, Office of the Regional Counsel, Southwest
Region, 10101 Hillwood Pkwy., Room 6N-321, Fort Worth, TX 76177.
(3) The subject of this AD is addressed in European Aviation
Safety Agency (now European Union Aviation Safety Agency) (EASA) AD
2012-0076R2, dated February 20, 2014. You may view the EASA AD on
the internet at https://www.regulations.gov in the AD Docket.
Issued on April 30, 2021.
Lance T. Gant,
Director, Compliance & Airworthiness Division, Aircraft Certification
Service.
[FR Doc. 2021-09759 Filed 5-7-21; 8:45 am]
BILLING CODE 4910-13-P
