Airworthiness Directives; Leonardo S.p.a. (Type Certificates Previously Held by Agusta S.p.A. and AgustaWestland S.p.A.) Helicopters, 20338-20341 [2021-07666]
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Federal Register / Vol. 86, No. 73 / Monday, April 19, 2021 / Proposed Rules
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
(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:
■
Leonardo S.p.a.: Docket No. FAA–2021–
0302; Project Identifier MCAI–2020–
01596–R.
(a) Comments Due Date
The FAA must receive comments on this
airworthiness directive (AD) by June 3, 2021.
(b) Affected ADs
None.
(c) Applicability
This AD applies to Leonardo S.p.a. Model
AW189 helicopters, certificated in any
category.
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(d) Subject
Joint Aircraft Service Component (JASC)
Code: 7300, Engine fuel and control.
(e) Unsafe Condition
This AD was prompted by the
identification of misleading information in
the emergency procedure for the ‘‘1(2) FUEL
LOW’’ caution message. The FAA is issuing
this AD to prevent the wrong estimation of
the remaining flight time in a low fuel
condition. The unsafe condition, if not
addressed, could result in an uncommanded
engine in-flight shut-down and forced
landing, with subsequent damage to the
helicopter or injury to the occupants.
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(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
(g) Required Actions
Within 14 hours time-in-service after the
effective date of this AD, revise page 3–118
of Section 3, Emergency and Malfunction
Procedures, of the existing Rotorcraft Flight
Manual for your helicopter by adding
AW189—RFM, Document No.
189G0290X002, Record of Temporary
Revisions, TR No. 3–1, Revision A, dated
May 24, 2019 (TR 3–1 Rev A). Using a
different document with information
identical to the information in page 3–118 of
TR 3–1 Rev A is acceptable for compliance
with the requirement of this paragraph. This
action may be performed by the owner/
operator (pilot) holding at least a private pilot
certificate and must be entered into the
aircraft records showing compliance with
this AD in accordance with § 43.9(a)(1)
through (4) and § 91.417(a)(2)(v). The record
must be maintained as required by § 91.417,
§ 121.380, or § 135.439.
(h) Special Flight Permits
Special flight permits are prohibited.
(i) 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 (j)(1) of this AD.
Information may be emailed to: 9-AVS-AIR730-AMOC@faa.gov.
(2) Before using any approved AMOC,
notify your appropriate principal inspector,
or lacking a principal inspector, the manager
of the local flight standards district office/
certificate holding district office.
(j) Related Information
(1) For more information about this AD,
contact Mitch Soth, Flight Test Engineer,
Southwest Section, Flight Test Branch,
Compliance & Airworthiness Division, FAA,
10101 Hillwood Pkwy., Fort Worth, TX
76177; telephone (817) 222–5110; email
mitch.soth@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 referenced 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.
(3) The subject of this AD is addressed in
European Union Aviation Safety Agency
(EASA) AD 2019–0136, dated June 11, 2019.
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You may view the EASA AD on the internet
at https://www.regulations.gov in Docket No.
FAA–2021–0302.
Issued on April 9, 2021.
Ross Landes,
Deputy Director for Regulatory Operations,
Compliance & Airworthiness Division,
Aircraft Certification Service.
[FR Doc. 2021–07802 Filed 4–16–21; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2021–0304; Project
Identifier 2017–SW–108–AD]
RIN 2120–AA64
Airworthiness Directives; Leonardo
S.p.a. (Type Certificates Previously
Held by Agusta S.p.A. and
AgustaWestland S.p.A.) Helicopters
Federal Aviation
Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
The FAA proposes to adopt a
new airworthiness directive (AD) for
Leonardo S.p.a. (Type Certificate
previously held by Agusta S.p.A.)
Model AB139 and AW139 helicopters
and Leonardo S.p.a. (Type Certificate
previously held by AgustaWestland
S.p.A.) Model AW189 helicopters. This
proposed AD was prompted by reports
of missing lock wire and loose fasteners.
This proposed AD would require a onetime inspection of the main rotor (M/R)
slip ring and depending on the outcome,
removing the M/R slip ring from service,
removing screws and washers from
service, applying torque, installing lock
wire, and re-identifying the M/R slip
ring. This proposed AD would also
prohibit the installation of certain M/R
slip rings. The FAA is proposing this
AD to address the unsafe condition on
these products.
DATES: The FAA must receive comments
on this proposed AD by June 3, 2021.
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.
SUMMARY:
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• Hand Delivery: Deliver to Mail
address between 9 a.m. and 5 p.m.,
Monday through Friday, except Federal
holidays.
For Leonardo Helicopters and Moog
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 at
https://www.regulations.gov by
searching for and locating Docket No.
FAA–2021–0304; 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
NPRM, the European Aviation Safety
Agency (now European Union Aviation
Safety Agency) (EASA) ADs, any
comments received, and other
information. The street address for
Docket Operations is listed above.
FOR FURTHER INFORMATION CONTACT:
Steven Warwick, Aerospace Engineer,
Certification Section, Fort Worth ACO
Branch, Compliance & Airworthiness
Division, 10101 Hillwood Pkwy., Fort
Worth, TX 76177; telephone (817) 222–
5225; email steven.r.warwick@faa.gov.
SUPPLEMENTARY INFORMATION:
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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–2021–0304; Project Identifier
2017–SW–108–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
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agency will also post a report
summarizing each substantive verbal
contact received about this NPRM.
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 Steven Warwick,
Aerospace Engineer, Certification
Section, Fort Worth ACO Branch,
Compliance & Airworthiness Division,
10101 Hillwood Pkwy., Fort Worth, TX
76177; telephone (817) 222–5225; email
steven.r.warwick@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
EASA, which is the Technical Agent
for the Member States of the European
Union, has issued EASA AD 2017–0083,
dated May 10, 2017 (EASA AD 2017–
0083), to correct an unsafe condition for
Leonardo S.p.A. (formerly Finmeccanica
S.p.A, AgustaWestland S.p.A., Agusta
S.p.A), AgustaWestland Philadelphia
Corporation (formerly Agusta Aerospace
Corporation) Model AB139 and AW139
helicopters, and EASA AD 2017–0087,
dated May 12, 2017 (EASA AD 2017–
0087), to correct the same unsafe
condition for Leonardo S.p.A.
Helicopters (formerly Finmeccanica
S.p.A, AgustaWestland S.p.A.) Model
AW189 helicopters. EASA advises of
reports of missing lock wire and loose
fasteners found during inspections of
the M/R slip ring of Model AW139
helicopters. EASA also advises that the
same part-numbered M/R slip ring may
also be installed on Model AW189
helicopters. Model AB139 helicopters
may also be affected by this unsafe
condition due to having the same type
design as Model AW139 helicopters.
EASA ADs 2017–0083 and 2017–0087
require a one-time visual inspection of
the M/R slip ring fastener installation,
and depending on the outcome,
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20339
replacing the M/R slip ring, replacing
fasteners, applying torque, installing
lock wire, and re-identifying the M/R
slip ring. EASA ADs 2017–0083 and
2017–0087 also prohibit installation of
an affected M/R slip ring. EASA states,
this condition, if not detected and
corrected, could lead to failure of the
M/R slip ring bearing inner race,
possibly resulting in damage to drive
system components and subsequent
reduced control of the helicopter.
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 ADs. The FAA is proposing this
AD after evaluating all known relevant
information and determining that an
unsafe condition is likely to exist or
develop on other products of the same
type designs.
Related Service Information Under 1
CFR Part 51
The FAA reviewed Leonardo
Helicopters Alert Service Bulletin (ASB)
No. 139–472, dated May 9, 2017 (ASB
139–472), for Model AB139 and AW139
helicopters, and Leonardo Helicopters
ASB No. 189–138, dated May 12, 2017
(ASB 189–138), for Model AW189
helicopters. ASB 139–472 and ASB
189–138 specify inspecting the M/R slip
ring by following the procedures in
Moog Service Bulletin No. SB 16–01,
Revision 5, undated (SB 16–01), which
is attached as Annex A to both ASB
139–472 and ASB 189–138. ASB 139–
472 and ASB 189–138 are proposed for
incorporation by reference in this
proposed AD. SB 16–01 is not proposed
for incorporation by reference in this
proposed AD.
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 also reviewed SB 16–01,
which specifies procedures to visually
inspect the M/R slip ring upper
(connecter) end and lower (pigtail or
standpipe) end fastener screws and
double-twist lock wire.
Proposed AD Requirements in This
NPRM
This proposed AD would require,
with the M/R slip ring removed,
inspecting each screw and double-twist
lock wire of the upper (connecter) end
and lower (pigtail or standpipe) end
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fasteners of the M/R slip ring.
Depending on the outcome, this
proposed AD would require:
• Marking the M/R slip ring;
• Removing the M/R slip ring from
service; or
• Removing screws and washers, lock
wire, and ferrule ended safety cable
from service; installing new screws and
washers; applying torque; installing
double-twist lock wire; and marking the
M/R slip ring.
This proposed AD would also
prohibit the installation of an affected
M/R slip ring unless the proposed
requirements have been completed.
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Differences Between This Proposed AD
and the EASA ADs
EASA ADs 2017–0083 and 2017–0087
include the compliance time of at the
next M/R slip ring removal, whereas
this proposed AD does not because it
could be difficult to track. This
proposed AD has a shorter compliance
time for all affected M/R slip rings that
have accumulated 900 or more total
hours time-in-service, whereas EASA
AD 2017–0087 allows a longer
compliance time for these affected M/R
slip rings that are installed on Model
AW189 helicopters. EASA ADs 2017–
0083 and 2017–0087 specify inspecting
for the proper lock wire installed, while
this proposed AD specifies inspecting
for correct installation of lock wire 0.20
CRES NAS 33540 part number
MS20995C20 (double-twist lock wire)
and any missing double-twist lock wire.
If a screw is missing from the inner
diameter (the connector flange) of the
upper end of the M/R slip ring, EASA
ADs 2017–0083 and 2017–0087 specify
replacing the M/R slip ring with a
serviceable part, whereas this proposed
AD would require removing the M/R
slip ring from service instead. If a screw
is missing from the outer diameter of the
upper end, from the inner diameter of
the lower end (shaft extension
attachment area), or from the outer
diameter of the lower end, this proposed
AD would require installing a new
screw and washer, applying torque, and
installing lock wire, whereas corrective
action for this condition is not specified
in EASA AD 2017–0083 or 2017–0087.
Costs of Compliance
The FAA estimates that this proposed
AD affects 134 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 an M/R slip ring would
take about 10 work-hours for an
estimated cost of $850 per helicopter
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and $113,900 for the U.S. fleet. Marking
an M/R slip ring would take a minimal
amount of time and parts would cost a
nominal amount. Replacing an M/R slip
ring would take about 3 work-hours and
parts would cost about $65,000 for an
estimated cost of $65,255 per helicopter.
Removing any ferrule ended safety
cable; replacing screws and washers;
applying torque; and installing lock
wire would take about 1 work-hour and
parts would cost a nominal amount for
an estimated cost of $85 per helicopter.
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
(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.
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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:
■
Leonardo S.p.a. (Type Certificates
Previously Held by Agusta S.p.A. and
AgustaWestland S.p.A.): Docket No.
FAA–2021–0304; Project Identifier
2017–SW–108–AD.
(a) Comments Due Date
The FAA must receive comments on this
airworthiness directive (AD) by June 3, 2021.
(b) Affected ADs
None.
(c) Applicability
This AD applies to Leonardo S.p.a. (Type
Certificate previously held by Agusta S.p.A.)
Model AB139 and AW139 helicopters and
Leonardo S.p.a. (Type Certificate previously
held by AgustaWestland S.p.A.) Model
AW189 helicopters, certificated in any
category, with a main rotor (M/R) slip ring
part number (P/N) 4G6220V00151 with a
serial (S/N) number up to and including S/
N 0141, except those marked with an ‘‘L’’
following the S/N, installed.
(d) Subject
Joint Aircraft Service Component (JASC)
Code: 6200, Main Rotor System.
(e) Unsafe Condition
This AD was prompted by reports of
missing lock wire and loose fasteners. The
FAA is issuing this AD to address failure of
an M/R slip ring fastener. The unsafe
condition, if not addressed, could result in
failure of the M/R slip ring bearing inner
race, reduced M/R control, 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 an M/R slip ring that has
accumulated 900 or more total hours time-inservice (TIS), within 50 hours TIS after the
effective date of this AD; and for an M/R slip
ring that has accumulated less than 900 total
hours TIS, within 300 hours TIS after the
effective date of this AD or before
accumulating 950 total hours TIS, whichever
occurs first:
(i) With the M/R slip ring removed,
visually inspect for the presence of each
screw, the presence of any ferrule ended
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safety cable, the correct installation of lock
wire 0.20 CRES NAS 33540 P/N
MS20995C20 (double-twist lock wire), and
any missing double-twist lock wire for each
set of upper (connecter) end and lower
(pigtail or standpipe) end fasteners of the M/
R slip ring as depicted in Figures 1 and 2 of
Annex A to Leonardo Helicopters Alert
Service Bulletin (ASB) No. 139–472, dated
May 9, 2017 (ASB 139–472), or Leonardo
Helicopters ASB No. 189–138, dated May 12,
2017 (ASB 189–138), as applicable to your
model helicopter. Figures 2 and 3 of Annex
A to ASB 139–472 and ASB 189–138 also
show examples of a ferrule ended safety
cable installed that are not approved.
Note 1 to paragraph (g)(1)(i): Annex A to
ASB 139–472 and ASB 189–138 is Moog
Service Bulletin No. SB 16–01, Revision 5,
undated.
(ii) If all of the screws are present, there is
not any ferrule ended safety cable installed,
the double-twist lock wire is correctly
installed, and none of the double-twist lock
wire is missing on each set of upper end and
lower end fasteners of the M/R slip ring,
before further flight, mark the letter ‘‘L’’
following the S/N on the identification label
by following the Compliance Instructions,
paragraph 3) of Annex A to ASB 139–472 or
ASB 189–138, as applicable to your model
helicopter.
(iii) If a screw is missing from the inner
diameter (the connector flange) of the upper
end of the M/R slip ring, before further flight,
remove the M/R slip ring from service.
(iv) If a screw is missing from the outer
diameter of the upper end, from the inner
diameter of the lower end (shaft extension
attachment area), or from the outer diameter
of the lower end, before further flight, install
a new screw and washer, apply a torque to
1–1.25 Nm, and install double-twist lock
wire by following the Compliance
Instructions, paragraphs 9)a) through g) of
Annex A to ASB 139–472 or ASB 189–138,
as applicable to your model helicopter.
(v) If any double-twist lock wire is not
correctly installed, is missing, or if there is
a ferrule ended safety cable installed on any
set of upper end or lower end fasters of the
M/R slip ring, before further flight, remove
the incorrectly installed lock wire or ferrule
ended safety cable from service, as
applicable, and inspect the fastener torque by
applying 1–1.25 Nm of torque.
(A) If the torque of a screw installed in the
inner diameter (the connector flange) of the
upper end of the M/R slip ring is below 1 Nm
of torque, do not remove or replace the
screw, before further flight, apply a torque of
1–1.25 Nm.
(B) If the torque of a screw installed in the
outer diameter of the upper end, in the inner
diameter of the lower end (shaft extension
attachment area), or in the outer diameter of
the lower end is below 1 Nm of torque, before
further flight, remove the affected screw and
washer from service, install a new screw and
washer, and apply a torque of 1–1.25 Nm.
(C) Install double-twist lock wire by
following the Compliance Instructions,
paragraphs 9)a) through g) of Annex A to
ASB 139–472 or ASB 189–138, as applicable
to your model helicopter.
(vi) Mark the letter ‘‘L’’ following the S/N
on the identification label by following the
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Compliance Instructions, paragraph 3) of
Annex A to ASB 139–472 or ASB 189–138,
as applicable to your model helicopter.
(2) As of the effective date of this AD, do
not install an M/R slip ring identified in
paragraph (c) of this AD unless the
requirements of paragraph (g)(1) have been
accomplished.
DEPARTMENT OF TRANSPORTATION
(h) Special Flight Permits
RIN 2120–AA64
Special flight permits are prohibited.
(i) 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 (j)(1) of this AD.
Information may be emailed to: 9-AVS-AIR730-AMOC@faa.gov.
(2) Before using any approved AMOC,
notify your appropriate principal inspector,
or lacking a principal inspector, the manager
of the local flight standards district office/
certificate holding district office.
(j) Related Information
(1) For more information about this AD,
contact Steven Warwick, Aerospace
Engineer, Certification Section, Fort Worth
ACO Branch, Compliance & Airworthiness
Division, 10101 Hillwood Pkwy., Fort Worth,
TX 76177; telephone (817) 222–5225; email
steven.r.warwick@faa.gov.
(2) Moog Service Bulletin No. SB 16–01,
Revision 5, undated, is attached as Annex A
to both ASB 139–472 and ASB 189–138. For
Leonardo Helicopters and Moog 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 the referenced service information
at the FAA, Office of the Regional Counsel,
Southwest Region, 10101 Hillwood Pkwy.,
Room 6N–321, Fort Worth, TX 76177. For
information on the availability of this
material at the FAA, call (817) 222–5110.
(3) The subject of this AD is addressed in
European Aviation Safety Agency (now
European Union Aviation Safety Agency)
(EASA) AD 2017–0083, dated May 10, 2017,
and EASA AD 2017–0087, dated May 12,
2017. You may view the EASA ADs on the
internet at https://www.regulations.gov in the
AD Docket.
Issued on April 8, 2021.
Lance T. Gant,
Director, Compliance & Airworthiness
Division, Aircraft Certification Service.
[FR Doc. 2021–07666 Filed 4–16–21; 8:45 am]
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Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2021–0308; Project
Identifier MCAI–2020–00594–R]
Airworthiness Directives; Airbus
Helicopters Deutschland GmbH (AHD)
Helicopters
Federal Aviation
Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
The FAA proposes to adopt a
new airworthiness directive (AD) for
certain Airbus Helicopters Deutschland
GmbH (AHD) Model BO–105A, BO–
105C, BO–105S, and BO–105LS A–3
helicopters equipped with a certain
hoist system. This AD was prompted by
an uncommanded activation of the hoist
cable cutter function on an MBB–BK117
C–1 helicopter, which prompted a
design review of the BO105 hoist
control grip with coiled cable. This
proposed AD would require inspections
of the hoist control grip with coiled
cable and deactivation of the hoist cuter
function, as specified in a European
Aviation Safety Agency (now European
Union Aviation Safety Agency) (EASA)
AD, which is proposed for incorporation
by reference (IBR). The FAA is
proposing this AD to address the unsafe
condition on these products.
DATES: The FAA must receive comments
on this proposed AD by June 3, 2021.
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: Deliver to Mail
address above between 9 a.m. and 5
p.m., Monday through Friday, except
Federal holidays.
For material that is proposed for IBR
in this AD, contact the EASA, KonradAdenauer-Ufer 3, 50668 Cologne,
Germany; telephone +49 221 8999 000;
email ADs@easa.europa.eu; internet
www.easa.europa.eu. You may find this
material on the EASA website at https://
ad.easa.europa.eu. You may view this
material at the FAA, Office of the
SUMMARY:
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]]>Agencies
[Federal Register Volume 86, Number 73 (Monday, April 19, 2021)]
[Proposed Rules]
[Pages 20338-20341]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2021-07666]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2021-0304; Project Identifier 2017-SW-108-AD]
RIN 2120-AA64
Airworthiness Directives; Leonardo S.p.a. (Type Certificates
Previously Held by Agusta S.p.A. and AgustaWestland S.p.A.) Helicopters
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking (NPRM).
-----------------------------------------------------------------------
SUMMARY: The FAA proposes to adopt a new airworthiness directive (AD)
for Leonardo S.p.a. (Type Certificate previously held by Agusta S.p.A.)
Model AB139 and AW139 helicopters and Leonardo S.p.a. (Type Certificate
previously held by AgustaWestland S.p.A.) Model AW189 helicopters. This
proposed AD was prompted by reports of missing lock wire and loose
fasteners. This proposed AD would require a one-time inspection of the
main rotor (M/R) slip ring and depending on the outcome, removing the
M/R slip ring from service, removing screws and washers from service,
applying torque, installing lock wire, and re-identifying the M/R slip
ring. This proposed AD would also prohibit the installation of certain
M/R slip rings. The FAA is proposing this AD to address the unsafe
condition on these products.
DATES: The FAA must receive comments on this proposed AD by June 3,
2021.
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.
[[Page 20339]]
Hand Delivery: Deliver to Mail address between 9 a.m. and
5 p.m., Monday through Friday, except Federal holidays.
For Leonardo Helicopters and Moog 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 at https://www.regulations.gov by
searching for and locating Docket No. FAA-2021-0304; 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 NPRM, the European
Aviation Safety Agency (now European Union Aviation Safety Agency)
(EASA) ADs, any comments received, and other information. The street
address for Docket Operations is listed above.
FOR FURTHER INFORMATION CONTACT: Steven Warwick, Aerospace Engineer,
Certification Section, Fort Worth ACO Branch, Compliance &
Airworthiness Division, 10101 Hillwood Pkwy., Fort Worth, TX 76177;
telephone (817) 222-5225; 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-2021-0304; Project Identifier
2017-SW-108-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 NPRM.
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
Steven Warwick, Aerospace Engineer, Certification Section, Fort Worth
ACO Branch, Compliance & Airworthiness Division, 10101 Hillwood Pkwy.,
Fort Worth, TX 76177; telephone (817) 222-5225; 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
EASA, which is the Technical Agent for the Member States of the
European Union, has issued EASA AD 2017-0083, dated May 10, 2017 (EASA
AD 2017-0083), to correct an unsafe condition for Leonardo S.p.A.
(formerly Finmeccanica S.p.A, AgustaWestland S.p.A., Agusta S.p.A),
AgustaWestland Philadelphia Corporation (formerly Agusta Aerospace
Corporation) Model AB139 and AW139 helicopters, and EASA AD 2017-0087,
dated May 12, 2017 (EASA AD 2017-0087), to correct the same unsafe
condition for Leonardo S.p.A. Helicopters (formerly Finmeccanica S.p.A,
AgustaWestland S.p.A.) Model AW189 helicopters. EASA advises of reports
of missing lock wire and loose fasteners found during inspections of
the M/R slip ring of Model AW139 helicopters. EASA also advises that
the same part-numbered M/R slip ring may also be installed on Model
AW189 helicopters. Model AB139 helicopters may also be affected by this
unsafe condition due to having the same type design as Model AW139
helicopters. EASA ADs 2017-0083 and 2017-0087 require a one-time visual
inspection of the M/R slip ring fastener installation, and depending on
the outcome, replacing the M/R slip ring, replacing fasteners, applying
torque, installing lock wire, and re-identifying the M/R slip ring.
EASA ADs 2017-0083 and 2017-0087 also prohibit installation of an
affected M/R slip ring. EASA states, this condition, if not detected
and corrected, could lead to failure of the M/R slip ring bearing inner
race, possibly resulting in damage to drive system components and
subsequent reduced control of the helicopter.
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 ADs. The FAA is proposing this AD
after evaluating all known relevant information and determining that an
unsafe condition is likely to exist or develop on other products of the
same type designs.
Related Service Information Under 1 CFR Part 51
The FAA reviewed Leonardo Helicopters Alert Service Bulletin (ASB)
No. 139-472, dated May 9, 2017 (ASB 139-472), for Model AB139 and AW139
helicopters, and Leonardo Helicopters ASB No. 189-138, dated May 12,
2017 (ASB 189-138), for Model AW189 helicopters. ASB 139-472 and ASB
189-138 specify inspecting the M/R slip ring by following the
procedures in Moog Service Bulletin No. SB 16-01, Revision 5, undated
(SB 16-01), which is attached as Annex A to both ASB 139-472 and ASB
189-138. ASB 139-472 and ASB 189-138 are proposed for incorporation by
reference in this proposed AD. SB 16-01 is not proposed for
incorporation by reference in this proposed AD.
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 also reviewed SB 16-01, which specifies procedures to
visually inspect the M/R slip ring upper (connecter) end and lower
(pigtail or standpipe) end fastener screws and double-twist lock wire.
Proposed AD Requirements in This NPRM
This proposed AD would require, with the M/R slip ring removed,
inspecting each screw and double-twist lock wire of the upper
(connecter) end and lower (pigtail or standpipe) end
[[Page 20340]]
fasteners of the M/R slip ring. Depending on the outcome, this proposed
AD would require:
Marking the M/R slip ring;
Removing the M/R slip ring from service; or
Removing screws and washers, lock wire, and ferrule ended
safety cable from service; installing new screws and washers; applying
torque; installing double-twist lock wire; and marking the M/R slip
ring.
This proposed AD would also prohibit the installation of an
affected M/R slip ring unless the proposed requirements have been
completed.
Differences Between This Proposed AD and the EASA ADs
EASA ADs 2017-0083 and 2017-0087 include the compliance time of at
the next M/R slip ring removal, whereas this proposed AD does not
because it could be difficult to track. This proposed AD has a shorter
compliance time for all affected M/R slip rings that have accumulated
900 or more total hours time-in-service, whereas EASA AD 2017-0087
allows a longer compliance time for these affected M/R slip rings that
are installed on Model AW189 helicopters. EASA ADs 2017-0083 and 2017-
0087 specify inspecting for the proper lock wire installed, while this
proposed AD specifies inspecting for correct installation of lock wire
0.20 CRES NAS 33540 part number MS20995C20 (double-twist lock wire) and
any missing double-twist lock wire. If a screw is missing from the
inner diameter (the connector flange) of the upper end of the M/R slip
ring, EASA ADs 2017-0083 and 2017-0087 specify replacing the M/R slip
ring with a serviceable part, whereas this proposed AD would require
removing the M/R slip ring from service instead. If a screw is missing
from the outer diameter of the upper end, from the inner diameter of
the lower end (shaft extension attachment area), or from the outer
diameter of the lower end, this proposed AD would require installing a
new screw and washer, applying torque, and installing lock wire,
whereas corrective action for this condition is not specified in EASA
AD 2017-0083 or 2017-0087.
Costs of Compliance
The FAA estimates that this proposed AD affects 134 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 an M/R slip ring would take about 10 work-hours for an
estimated cost of $850 per helicopter and $113,900 for the U.S. fleet.
Marking an M/R slip ring would take a minimal amount of time and parts
would cost a nominal amount. Replacing an M/R slip ring would take
about 3 work-hours and parts would cost about $65,000 for an estimated
cost of $65,255 per helicopter. Removing any ferrule ended safety
cable; replacing screws and washers; applying torque; and installing
lock wire would take about 1 work-hour and parts would cost a nominal
amount for an estimated cost of $85 per helicopter.
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
(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 adding the following new airworthiness
directive:
Leonardo S.p.a. (Type Certificates Previously Held by Agusta S.p.A.
and AgustaWestland S.p.A.): Docket No. FAA-2021-0304; Project
Identifier 2017-SW-108-AD.
(a) Comments Due Date
The FAA must receive comments on this airworthiness directive
(AD) by June 3, 2021.
(b) Affected ADs
None.
(c) Applicability
This AD applies to Leonardo S.p.a. (Type Certificate previously
held by Agusta S.p.A.) Model AB139 and AW139 helicopters and
Leonardo S.p.a. (Type Certificate previously held by AgustaWestland
S.p.A.) Model AW189 helicopters, certificated in any category, with
a main rotor (M/R) slip ring part number (P/N) 4G6220V00151 with a
serial (S/N) number up to and including S/N 0141, except those
marked with an ``L'' following the S/N, installed.
(d) Subject
Joint Aircraft Service Component (JASC) Code: 6200, Main Rotor
System.
(e) Unsafe Condition
This AD was prompted by reports of missing lock wire and loose
fasteners. The FAA is issuing this AD to address failure of an M/R
slip ring fastener. The unsafe condition, if not addressed, could
result in failure of the M/R slip ring bearing inner race, reduced
M/R control, 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 an M/R slip ring that has accumulated 900 or more total
hours time-in-service (TIS), within 50 hours TIS after the effective
date of this AD; and for an M/R slip ring that has accumulated less
than 900 total hours TIS, within 300 hours TIS after the effective
date of this AD or before accumulating 950 total hours TIS,
whichever occurs first:
(i) With the M/R slip ring removed, visually inspect for the
presence of each screw, the presence of any ferrule ended
[[Page 20341]]
safety cable, the correct installation of lock wire 0.20 CRES NAS
33540 P/N MS20995C20 (double-twist lock wire), and any missing
double-twist lock wire for each set of upper (connecter) end and
lower (pigtail or standpipe) end fasteners of the M/R slip ring as
depicted in Figures 1 and 2 of Annex A to Leonardo Helicopters Alert
Service Bulletin (ASB) No. 139-472, dated May 9, 2017 (ASB 139-472),
or Leonardo Helicopters ASB No. 189-138, dated May 12, 2017 (ASB
189-138), as applicable to your model helicopter. Figures 2 and 3 of
Annex A to ASB 139-472 and ASB 189-138 also show examples of a
ferrule ended safety cable installed that are not approved.
Note 1 to paragraph (g)(1)(i): Annex A to ASB 139-472 and ASB
189-138 is Moog Service Bulletin No. SB 16-01, Revision 5, undated.
(ii) If all of the screws are present, there is not any ferrule
ended safety cable installed, the double-twist lock wire is
correctly installed, and none of the double-twist lock wire is
missing on each set of upper end and lower end fasteners of the M/R
slip ring, before further flight, mark the letter ``L'' following
the S/N on the identification label by following the Compliance
Instructions, paragraph 3) of Annex A to ASB 139-472 or ASB 189-138,
as applicable to your model helicopter.
(iii) If a screw is missing from the inner diameter (the
connector flange) of the upper end of the M/R slip ring, before
further flight, remove the M/R slip ring from service.
(iv) If a screw is missing from the outer diameter of the upper
end, from the inner diameter of the lower end (shaft extension
attachment area), or from the outer diameter of the lower end,
before further flight, install a new screw and washer, apply a
torque to 1-1.25 Nm, and install double-twist lock wire by following
the Compliance Instructions, paragraphs 9)a) through g) of Annex A
to ASB 139-472 or ASB 189-138, as applicable to your model
helicopter.
(v) If any double-twist lock wire is not correctly installed, is
missing, or if there is a ferrule ended safety cable installed on
any set of upper end or lower end fasters of the M/R slip ring,
before further flight, remove the incorrectly installed lock wire or
ferrule ended safety cable from service, as applicable, and inspect
the fastener torque by applying 1-1.25 Nm of torque.
(A) If the torque of a screw installed in the inner diameter
(the connector flange) of the upper end of the M/R slip ring is
below 1 Nm of torque, do not remove or replace the screw, before
further flight, apply a torque of 1-1.25 Nm.
(B) If the torque of a screw installed in the outer diameter of
the upper end, in the inner diameter of the lower end (shaft
extension attachment area), or in the outer diameter of the lower
end is below 1 Nm of torque, before further flight, remove the
affected screw and washer from service, install a new screw and
washer, and apply a torque of 1-1.25 Nm.
(C) Install double-twist lock wire by following the Compliance
Instructions, paragraphs 9)a) through g) of Annex A to ASB 139-472
or ASB 189-138, as applicable to your model helicopter.
(vi) Mark the letter ``L'' following the S/N on the
identification label by following the Compliance Instructions,
paragraph 3) of Annex A to ASB 139-472 or ASB 189-138, as applicable
to your model helicopter.
(2) As of the effective date of this AD, do not install an M/R
slip ring identified in paragraph (c) of this AD unless the
requirements of paragraph (g)(1) have been accomplished.
(h) Special Flight Permits
Special flight permits are prohibited.
(i) 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 (j)(1) of
this AD. Information may be emailed to: [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.
(j) Related Information
(1) For more information about this AD, contact Steven Warwick,
Aerospace Engineer, Certification Section, Fort Worth ACO Branch,
Compliance & Airworthiness Division, 10101 Hillwood Pkwy., Fort
Worth, TX 76177; telephone (817) 222-5225; email
[email protected].
(2) Moog Service Bulletin No. SB 16-01, Revision 5, undated, is
attached as Annex A to both ASB 139-472 and ASB 189-138. For
Leonardo Helicopters and Moog 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 the referenced
service information at the FAA, Office of the Regional Counsel,
Southwest Region, 10101 Hillwood Pkwy., Room 6N-321, Fort Worth, TX
76177. For information on the availability of this material at the
FAA, call (817) 222-5110.
(3) The subject of this AD is addressed in European Aviation
Safety Agency (now European Union Aviation Safety Agency) (EASA) AD
2017-0083, dated May 10, 2017, and EASA AD 2017-0087, dated May 12,
2017. You may view the EASA ADs on the internet at https://www.regulations.gov in the AD Docket.
Issued on April 8, 2021.
Lance T. Gant,
Director, Compliance & Airworthiness Division, Aircraft Certification
Service.
[FR Doc. 2021-07666 Filed 4-16-21; 8:45 am]
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