Airworthiness Directives; Robinson Helicopter Company Helicopters, 13162-13165 [2021-03656]
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Federal Register / Vol. 86, No. 43 / Monday, March 8, 2021 / Rules and Regulations
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation
safety, Incorporation by reference,
Safety.
The Amendment
Accordingly, under the authority
delegated to me by the Administrator,
the FAA amends 14 CFR part 39 as
follows:
PART 39—AIRWORTHINESS
DIRECTIVES
1. The authority citation for part 39
continues to read as follows:
■
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
[Amended]
2. The FAA amends § 39.13 by adding
the following new airworthiness
directive:
■
2021–04–17 Airbus Helicopters:
Amendment 39–21439; Docket No.
FAA–2021–0095; Project Identifier
MCAI–2020–01658–R.
(a) Effective Date
This airworthiness directive (AD) becomes
effective March 23, 2021.
(b) Affected ADs
None.
(c) Applicability
This AD applies to Airbus Helicopters
Model AS350B, AS350BA, AS350B1,
AS350B2, AS350D, AS355E, AS355F,
AS355F1, AS355F2, and AS355N
helicopters, certificated in any category, with
a tail rotor (T/R) blade part number (P/N)
listed in Appendix 1, Table 1, of European
Union Aviation Safety Agency (EASA) AD
2020–0224R1, dated November 11, 2020
(EASA AD 2020–0224R1) (pre-mod 075580).
(d) Subject
Joint Aircraft System Component (JASC)
Code 6410, Tail Rotor Blades.
(e) Reason
This AD was prompted by two reports of
debonding of the T/R blade leading edge
protection shields. The FAA is issuing this
AD to prevent failure of the T/R blade, which
could result in loss of tail rotor control and
subsequent loss of control of the helicopter.
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(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
(g) Requirements
Except as specified in paragraph (h) of this
AD: Comply with all required actions and
compliance times specified in, and in
accordance with, EASA AD 2020–0224R1.
(h) Exceptions to EASA AD EASA AD 2020–
0224R1
(1) Where EASA AD 2020–0224R1 refers to
flight hours (FH), this AD requires using
hours time-in-service.
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(2) Where EASA AD 2020–0224R1 refers to
October 20, 2020 (the effective date of the
original issuance of its AD (EASA AD 2020–
0224–E, dated October 16, 2020)) and its
effective date, this AD requires using the
effective date of this AD.
(3) Where paragraph (1) of EASA AD 2020–
0224R1 specifies visually inspecting each T/
R blade leading edge protection shield with
instructions in the service information, this
AD requires visually checking each T/R blade
leading edge protection shield and bonding
strip for a distortion, dent, and scratch;
visually checking the area surrounding each
T/R blade leading edge protection along the
skin length for a gap; and visually checking
the area surrounding the bonding strip for a
crack. These visual checks 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 14
CFR 43.9(a)(1) through (4) and 14 CFR
91.417(a)(2)(v). The record must be
maintained as required by 14 CFR 91.417,
121.380, or 135.439.
(4) Where paragraph (5) of EASA AD 2020–
0224R1 specifies the modification of
replacing each affected part with a
serviceable part, this AD does not require this
modification.
(5) The ‘‘Remarks’’ section of EASA AD
2020–0224R1 does not apply to this AD.
(i) Parts Installation Prohibition
As of the effective date of this AD, do not
install a T/R blade identified in paragraph (c)
of this AD on any helicopter.
(j) Special Flight Permit
Special flight permits are prohibited if an
installed T/R blade does not pass the visual
or tap inspections.
(k) 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 (l)(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.
(l) Related Information
(1) For more information about this AD,
contact Kristi Bradley, Aviation Safety
Engineer, General Aviation & Rotorcraft
Section, International Validation Branch,
FAA, 10101 Hillwood Pkwy., Fort Worth, TX
76177; telephone (817) 222–5110; email
kristin.bradley@faa.gov.
(m) Material Incorporated by Reference
(1) The Director of the Federal Register
approved the incorporation by reference
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(IBR) of the service information listed in this
paragraph under 5 U.S.C. 552(a) and 1 CFR
part 51.
(2) You must use this service information
as applicable to do the actions required by
this AD, unless this AD specifies otherwise.
(i) European Union Aviation Safety Agency
(EASA) AD 2020–0224R1, dated November
11, 2020.
(ii) [Reserved]
(3) For EASA AD 2020–0224R1, contact the
EASA, Konrad-Adenauer-Ufer 3, 50668
Cologne, Germany; telephone +49 221 8999
000; email ADs@easa.europa.eu; internet
www.easa.europa.eu. You may find this
EASA AD on the EASA website at https://
ad.easa.europa.eu.
(4) 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.
This material may be found in the AD docket
on the internet at https://
www.regulations.gov by searching for and
locating Docket No. FAA–2021–0095.
(5) You may view this material that is
incorporated by reference at the National
Archives and Records Administration
(NARA). For information on the availability
of this material at NARA, email fedreg.legal@
nara.gov, or go to https://www.archives.gov/
federal-register/cfr/ibr-locations.html.
Issued on February 10, 2021.
Lance T. Gant,
Director, Compliance & Airworthiness
Division, Aircraft Certification Service.
[FR Doc. 2021–04803 Filed 3–4–21; 11:15 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2017–0682; Product
Identifier 2017–SW–028–AD; Amendment
39–21433; AD 2021–04–12]
RIN 2120–AA64
Airworthiness Directives; Robinson
Helicopter Company Helicopters
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule.
AGENCY:
The FAA is adopting a new
airworthiness directive (AD) for
Robinson Helicopter Company
(Robinson) Model R66 helicopters. This
AD was prompted by reports of tail rotor
(T/R) drive shaft forward hanger bearing
failures. This AD requires installing a
certain part numbered kit and removing
parts from service or replacing a certain
part-numbered T/R drive shaft
assembly. This AD also prohibits the
installation of certain parts. The FAA is
SUMMARY:
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Federal Register / Vol. 86, No. 43 / Monday, March 8, 2021 / Rules and Regulations
issuing this AD to address the unsafe
condition on these products.
DATES: This AD is effective April 12,
2021.
The Director of the Federal Register
approved the incorporation by reference
of a certain document listed in this AD
as of April 12, 2021.
ADDRESSES: For service information
identified in this final rule, contact
Robinson Helicopter Company, 2901
Airport Drive, Torrance, CA 90505;
telephone 310–539–0508; fax 310–539–
5198; or at https://robinsonheli.com/
technical-support/. You may view a
copy of the referenced service
information at the FAA, Office of the
Regional Counsel, Southwest Region,
10101 Hillwood Pkwy., Room 6N–321,
Fort Worth, TX 76177.
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–2017–
0682; or in person at Docket Operations
between 9 a.m. and 5 p.m., Monday
through Friday, except Federal holidays.
The AD docket contains this AD, any
comments received, and other
information. The address for Docket
Operations is U.S. Department of
Transportation, Docket Operations, M
30, West Building Ground Floor, Room
W12 140, 1200 New Jersey Avenue SE,
Washington, DC 20590.
FOR FURTHER INFORMATION CONTACT:
Danny Nguyen, Aerospace Engineer, Los
Angeles ACO Branch, FAA, 3960
Paramount Blvd., Lakewood, California
90712; telephone 562–627–5247; email
danny.nguyen@faa.gov.
SUPPLEMENTARY INFORMATION:
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Discussion
The FAA issued a supplemental
notice of proposed rulemaking (SNPRM)
to amend 14 CFR part 39 by adding an
AD that would apply to Robinson Model
R66 helicopters with a T/R drive shaft
assembly part number (P/N) D224–3
without B900–11 modification installed.
The SNPRM published in the Federal
Register on July 28, 2020 (85 FR 45360).
The FAA preceded the SNPRM with a
notice of proposed rulemaking (NPRM)
that published in the Federal Register
on March 30, 2018 (83 FR 13706). The
NPRM was prompted by two incidents
of forward hanger bearing failure of the
T/R drive shaft assembly because the
bearing was undersized for its housing.
Consequently, the bearing was spinning
at a speed that caused excessive heating
of the bearing during operation and led
to the breakdown of the bearing’s grease
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and ultimately seizure of the C647–16
bearing.
To correct this condition, Robinson
initially issued R66 Service Bulletin
SB–14, dated June 25, 2015 (SB–14), for
certain serial-numbered helicopters,
which specified installing a temperature
recorder on the T/R drive shaft forward
hanger bearing assembly and inspecting
the temperature recorder during
preflight checks and during each 100hour inspection. If the bearing was
found running hot, then Robinson
advised upgrading the bearing to a
newer design.
Following additional reports of
overheating forward hanger bearing
assemblies, Robinson superseded SB–14
with R66 Service Bulletin SB–20, dated
November 7, 2016 (SB–20), which
affected additional serial-numbered
helicopters and specified modifying T/
R drive shaft assembly P/Ns D224–3 and
D224–4 by using kit Robinson KI–235
R66 TRDS Forward Yoke Assembly and
Hanger Installation Kit Instructions,
Revision A, dated June 23, 2015 (KI–
235) and installing yoke assembly P/N
D224–5. This installation has an
improved, larger bearing that spins with
less friction. SB–20 also specified
inspecting the forward and aft sides of
the hanger and damper bearings for a
minimum of 0.5 inch in length of
sealant on the junction of the black seal
and bearing outer race and applying
sealant if there was less than 0.5 inch in
length of sealant.
Robinson revised SB–20 with R66
Service Bulletin SB–20A, dated June 6,
2017 (SB–20A), to clarify that
helicopters with either T/R drive shaft
assembly P/N D224–3 with modification
B900–11 or P/N D224–4 installed
include the upgraded bearing and do
not require kit KI–235.
Robinson later revised SB–20A with
R66 Service Bulletin SB–20B, dated
December 20, 2017 (SB–20B), which
updates writing practices and organizes
the procedures into two separate
sections, clarifies the ‘‘Rotorcraft
Affected’’ section, and reduces the
helicopters that need to perform the
inspection and sealant application
procedures to just helicopters without
the latest version damper and housing
bearings.
The NPRM proposed to require within
100 hours time-in-service (TIS)
replacing an affected T/R drive shaft
forward yoke assembly with T/R drive
shaft yoke assembly P/N D224–5. The
NPRM proposed to require inspections
of the forward and aft sides of the
hanger bearing and the damper bearing
for sealant, and depending on the
results of the inspections applying
sealant. The SNPRM proposed to revise
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13163
the NPRM by expanding the
applicability, changing the proposed
requirements, and correcting
nomenclature. The FAA is issuing this
AD to address the unsafe condition on
these products.
Comments
The FAA gave the public the
opportunity to comment on the
proposed rulemaking. The following
presents the comments received on the
SNPRM and the FAA’s response to each
comment.
Request: Robinson requested the FAA
change the note to the Applicability
paragraph to identify certain serialnumbered helicopters that had T/R
drive shaft assembly P/N D224–4
installed during production and clarify
that these helicopters are not affected by
this AD. Robinson explained that the
specified serial-numbered helicopters
with T/R drive shaft assembly P/N
D224–4 installed have the larger
(hanger) bearing, which is not affected
by this AD, and clarified that P/N D224–
5 is a sub-assembly upgrade to P/N
D224–4.
FAA Response: The FAA agrees and
has revised that note in this final rule
to identify the serial-numbered
helicopters with T/R drive shaft
assembly P/N D224–4 installed during
production and clarify that this partnumbered T/R drive shaft assembly is
not affected by this AD.
Request: Robinson requested that the
FAA change the exception in paragraph
(e)(1)(i) of this AD about not requiring
the discarding of removed nuts and
palnuts and stated that exception
implies that the nuts and palnuts may
be reused. Robinson explained that FAA
Advisory Circular (AC) 43.13–1B
Section 7–122 (d) specifies that these
nuts should be discarded and referenced
Robinson service information that
specifies upgrading certain nuts any
time maintenance is done. Robinson
also stated that the KI–235 kit includes
all required nuts and palnuts to replace
discarded hardware.
FAA Response: The FAA disagrees.
The FAA cannot require discarding of
parts in an AD. Paragraph (d), section 7–
122, of FAA AC 43.13–1B states that the
removed nuts should never be reused
and should be replaced with new ones
when removed. Accordingly, the FAA
has added language to the exception
stating that this AD requires removing
the affected parts from service.
FAA’s Determination
The FAA has reviewed the relevant
information, considered the comments
received, and determined that an unsafe
condition exists and is likely to exist or
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Federal Register / Vol. 86, No. 43 / Monday, March 8, 2021 / Rules and Regulations
develop on other products of the same
type design and that air safety and the
public interest require adopting the AD
requirements as proposed with the
changes described previously. These
changes are consistent with the intent
proposed in the SNPRM for correcting
the unsafe condition and will neither
increase the economic burden on any
operator nor increase the scope of the
AD.
Related Service Information Under 1
CFR Part 51
The FAA reviewed KI–235. This
service information provides
instructions for installing the newly
designed yoke assembly, P/N D224–5.
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.
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Related Service Information
The FAA has reviewed SB–14, which
specifies installing a temperature
recorder on the T/R drive shaft forward
hanger bearing assembly and inspecting
the temperature during preflight checks
and during each 100-hour inspection. If
the temperature of the bearing is found
running hot, then Robinson advises
upgrading the bearing to a newer design
(kit P/N KI–235). This service
information also specifies adding a
caution page to the Pilot Operating
Handbook regarding the overheating
bearing assemblies. This service
information was superseded by SB–20.
The FAA has reviewed SB–20, SB–
20A, and SB–20B, which specify
upgrading the forward hangar bearing
assembly of certain T/R drive shaft
assemblies to the newer design with kit
P/N KI–235 if not previously done. For
certain installations, this service
information contains procedures for
inspecting for sealant and applying
sealant to the damper and hanger
bearings if needed to prevent seal
rotation. This service information also
specifies removing the caution page
from the Pilot Operating Handbook
regarding the overheating bearing
assemblies that was added by SB–14.
Differences Between This AD and the
Service Information
SB–20 specifies replacing the yoke
assembly and applying sealant to the
bearing seals within the next 100 flight
hours or by January 31, 2017, whichever
comes first, and SB–20A and SB–20B
continue the compliance time of no later
than January 31, 2017. This AD does not
have a calendar time compliance
requirement. SB–20, SB– 20A, and SB–
20B specify inspecting for sealant and
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applying sealant to the damper and
hanger bearings if needed, while this
AD does not.
Costs of Compliance
The FAA estimates that this AD
affects 290 helicopters of U.S. Registry.
The FAA estimates that operators may
incur the following costs in order to
comply with this AD. Labor costs are
estimated at $85 per work-hour.
Installing Robinson field kit KI–235
takes about 6 work-hours and parts cost
about $950, for an estimated cost of
$1,460 per helicopter. As an option,
replacing an affected T/R drive shaft
assembly P/N D224–3 with T/R drive
shaft assembly P/N D224–4 takes about
5 work-hours and parts cost about
$4,400, for an estimated cost of $4,825
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 AD
will not have federalism implications
under Executive Order 13132. This AD
will not have a substantial direct effect
on the States, on the relationship
between the national Government and
the States, or on the distribution of
power and responsibilities among the
various levels of government.
For the reasons discussed, I certify
that this AD:
(1) Is not a ‘‘significant regulatory
action’’ under Executive Order 12866,
(2) Will not affect intrastate aviation
in Alaska, and
(3) Will not have a significant
economic impact, positive or negative,
on a substantial number of small entities
under the criteria of the Regulatory
Flexibility Act.
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List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation
safety, Incorporation by reference,
Safety.
Adoption of the Amendment
Accordingly, under the authority
delegated to me by the Administrator,
the FAA amends 14 CFR part 39 as
follows:
PART 39—AIRWORTHINESS
DIRECTIVES
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:
■
2021–04–12 Robinson Helicopter Company:
Amendment 39–21433; Docket No.
FAA–2017–0682; Product Identifier
2017–SW–028–AD.
(a) Applicability
This airworthiness directive (AD) applies
to Robinson Helicopter Company (Robinson)
Model R66 helicopters, certificated in any
category, with a tail rotor (T/R) drive shaft
assembly part number (P/N) D224–3 without
B900–11 modification installed.
Note 1 to paragraph (a): Helicopters with
serial number (S/N) 0631 and subsequent had
T/R drive shaft assembly P/N D224–4
installed during production, which is not
affected by this AD.
(b) Unsafe Condition
This AD defines the unsafe condition as
failure of a T/R drive shaft forward hanger
bearing. This condition could result in failure
of the T/R drive shaft and subsequent loss of
helicopter control.
(c) Effective Date
This AD is effective April 12, 2021.
(d) Compliance
You are responsible for performing each
action required by this AD within the
specified compliance time unless it has
already been accomplished prior to that time.
(e) Required Actions
(1) Within 100 hours time-in-service, do
one of the following:
(i) Install Robinson kit P/N KI–235 using
KI–235 R66 TRDS Forward Yoke Assembly
and Hanger Installation Kit Instructions,
Revision A, dated June 23, 2015, except
where the service information specifies
discarding parts, you are required to remove
those parts from service instead.
(ii) Replace the entire T/R drive shaft
assembly with T/R drive shaft assembly P/N
D224–4.
(2) As of the effective date of this AD, do
not install a T/R drive shaft assembly P/N
D224–3 without B900–11 modification on
any helicopter.
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(f) Alternative Methods of Compliance
(AMOC)
DEPARTMENT OF TRANSPORTATION
(1) The Manager, Los Angeles ACO Branch,
FAA, may approve AMOCs for this AD. Send
your proposal to: Danny Nguyen, Aerospace
Engineer, Los Angeles ACO Branch, FAA,
3960 Paramount Blvd., Lakewood, California
90712; telephone 562–627–5247; email 9ANM-LAACO-AMOC-REQUESTS@faa.gov.
(2) For operations conducted under a 14
CFR part 119 operating certificate or under
14 CFR part 91, subpart K, the FAA suggests
that you notify your principal inspector, or
lacking a principal inspector, the manager of
the local flight standards district office or
certificate holding district office before
operating any aircraft complying with this
AD through an AMOC.
Federal Aviation Administration
(g) Related Information
SUMMARY:
For service information identified in this
AD, contact Robinson Helicopter Company,
2901 Airport Drive, Torrance, CA 90505;
telephone 310–539–0508; fax 310–539–5198;
or at https://www.robinsonheli.com. You may
view a copy of the service information at the
FAA, Office of the Regional Counsel,
Southwest Region, 10101 Hillwood Pkwy.,
Room 6N–321, Fort Worth, TX 76177.
(h) Material Incorporated by Reference
(1) The Director of the Federal Register
approved the incorporation by reference
(IBR) of the service information listed in this
paragraph under 5 U.S.C. 552(a) and 1 CFR
part 51.
(2) You must use this service information
as applicable to do the actions required by
this AD, unless the AD specifies otherwise.
(i) Robinson KI–235 R66 TRDS Forward
Yoke Assembly and Hanger Installation Kit
Instructions, Revision A, dated June 23, 2015.
(ii) [Reserved]
(3) For service information identified in
this AD, contact Robinson Helicopter
Company, 2901 Airport Drive, Torrance, CA
90505; telephone 310–539–0508; fax 310–
539–5198; or at https://
www.robinsonheli.com.
(4) 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.
(5) You may view this service information
that is incorporated by reference at the
National Archives and Records
Administration (NARA). For information on
the availability of this material at NARA,
email: fedreg.legal@nara.gov, or go to:
https://www.archives.gov/federal-register/cfr/
ibr-locations.html.
(i) Subject
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Joint Aircraft Service Component (JASC)
Code: 6510, Tail Rotor Drive Shaft.
Issued on February 8, 2021.
Lance T. Gant,
Director, Compliance & Airworthiness
Division, Aircraft Certification Service.
[FR Doc. 2021–03656 Filed 3–5–21; 8:45 am]
BILLING CODE 4910–13–P
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14 CFR Part 39
[Docket No. FAA–2021–0094; Project
Identifier MCAI–2021–00100–R; Amendment
39–21437; AD 2021–04–15]
RIN 2120–AA64
Airworthiness Directives; Airbus
Helicopters
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule; request for
comments.
AGENCY:
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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 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.
It is also available in the AD docket on
the internet at https://
www.regulations.gov by searching for
and locating Docket No. FAA–2021–
0094.
Examining the AD Docket
The FAA is adopting a new
airworthiness directive (AD) for all
Airbus Helicopters Model AS355E,
AS355F, AS355F1, AS355F2, AS355N
and AS355NP helicopters; and certain
Model AS350B3 helicopters. This AD
was prompted by a report that, during
an unscheduled post-flight inspection of
the tail cone area, a crack was found in
the spar of the upper part of the vertical
fin and fractures were found in the two
front attachment screws. This AD
requires repetitive visual inspections of
the right-hand side of the vertical fin
spar for discrepancies (cracking), and
corrective action if necessary, as
specified in a European Union Aviation
Safety Agency (EASA) AD, which is
incorporated by reference. The FAA is
issuing this AD to address the unsafe
condition on these products.
DATES: This AD becomes effective
March 23, 2021.
The Director of the Federal Register
approved the incorporation by reference
of a certain publication listed in this AD
as of March 23, 2021.
The FAA must receive comments on
this AD by April 22, 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 incorporated by reference
(IBR) in this AD, contact the EASA,
Konrad-Adenauer-Ufer 3, 50668
Cologne, Germany; telephone +49 221
PO 00000
13165
You may examine the AD docket on
the internet at https://
www.regulations.gov by searching for
and locating Docket No. FAA–2021–
0094; or in person at Docket Operations
between 9 a.m. and 5 p.m., Monday
through Friday, except Federal holidays.
The AD docket contains this AD, any
comments received, and other
information. The street address for
Docket Operations is listed above.
Comments will be available in the AD
docket shortly after receipt.
FOR FURTHER INFORMATION CONTACT:
Kathleen Arrigotti, Aviation Safety
Engineer, Large Aircraft Section,
International Validation Branch, FAA,
2200 South 216th St., Des Moines, WA
98198; phone and fax: 206–231–3218;
email: kathleen.arrigotti@faa.gov.
SUPPLEMENTARY INFORMATION:
Discussion
The EASA, which is the Technical
Agent for the Member States of the
European Union, has issued EASA AD
2020–0186, dated August 20, 2020
(EASA AD 2020–0186) (also referred to
as the Mandatory Continuing
Airworthiness Information, or the
MCAI), to correct an unsafe condition
for all Airbus Helicopters Model
AS355E, AS355F, AS355F1, AS355F2,
AS355N and AS355NP helicopters; and
certain Model AS350B3 helicopters.
This AD was prompted by a report
that, during an unscheduled post-flight
inspection of the tail cone area of an
Airbus Helicopters Model AS355NP
helicopter, a crack was found in the spar
of the upper part of the vertical fin and
fractures were found in the two front
attachment screws. Airbus Helicopters
Model AS350B3 helicopters have a
similar vertical fin configuration and are
subject to comparable load levels as the
affected Model AS355NP helicopter,
therefore, this model may be subject to
the same unsafe condition revealed on
the Model AS355NP helicopter. The
FAA is issuing this AD to address
E:\FR\FM\08MRR1.SGM
08MRR1
]]>Agencies
[Federal Register Volume 86, Number 43 (Monday, March 8, 2021)]
[Rules and Regulations]
[Pages 13162-13165]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2021-03656]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2017-0682; Product Identifier 2017-SW-028-AD; Amendment
39-21433; AD 2021-04-12]
RIN 2120-AA64
Airworthiness Directives; Robinson Helicopter Company Helicopters
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Final rule.
-----------------------------------------------------------------------
SUMMARY: The FAA is adopting a new airworthiness directive (AD) for
Robinson Helicopter Company (Robinson) Model R66 helicopters. This AD
was prompted by reports of tail rotor (T/R) drive shaft forward hanger
bearing failures. This AD requires installing a certain part numbered
kit and removing parts from service or replacing a certain part-
numbered T/R drive shaft assembly. This AD also prohibits the
installation of certain parts. The FAA is
[[Page 13163]]
issuing this AD to address the unsafe condition on these products.
DATES: This AD is effective April 12, 2021.
The Director of the Federal Register approved the incorporation by
reference of a certain document listed in this AD as of April 12, 2021.
ADDRESSES: For service information identified in this final rule,
contact Robinson Helicopter Company, 2901 Airport Drive, Torrance, CA
90505; telephone 310-539-0508; fax 310-539-5198; or at https://robinsonheli.com/technical-support/. You may view a copy of the
referenced service information at the FAA, Office of the Regional
Counsel, Southwest Region, 10101 Hillwood Pkwy., Room 6N-321, Fort
Worth, TX 76177.
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-2017-
0682; or in person at Docket Operations between 9 a.m. and 5 p.m.,
Monday through Friday, except Federal holidays. The AD docket contains
this AD, any comments received, and other information. The address for
Docket Operations is U.S. Department of Transportation, Docket
Operations, M 30, West Building Ground Floor, Room W12 140, 1200 New
Jersey Avenue SE, Washington, DC 20590.
FOR FURTHER INFORMATION CONTACT: Danny Nguyen, Aerospace Engineer, Los
Angeles ACO Branch, FAA, 3960 Paramount Blvd., Lakewood, California
90712; telephone 562-627-5247; email [email protected].
SUPPLEMENTARY INFORMATION:
Discussion
The FAA issued a supplemental notice of proposed rulemaking (SNPRM)
to amend 14 CFR part 39 by adding an AD that would apply to Robinson
Model R66 helicopters with a T/R drive shaft assembly part number (P/N)
D224-3 without B900-11 modification installed. The SNPRM published in
the Federal Register on July 28, 2020 (85 FR 45360). The FAA preceded
the SNPRM with a notice of proposed rulemaking (NPRM) that published in
the Federal Register on March 30, 2018 (83 FR 13706). The NPRM was
prompted by two incidents of forward hanger bearing failure of the T/R
drive shaft assembly because the bearing was undersized for its
housing. Consequently, the bearing was spinning at a speed that caused
excessive heating of the bearing during operation and led to the
breakdown of the bearing's grease and ultimately seizure of the C647-16
bearing.
To correct this condition, Robinson initially issued R66 Service
Bulletin SB-14, dated June 25, 2015 (SB-14), for certain serial-
numbered helicopters, which specified installing a temperature recorder
on the T/R drive shaft forward hanger bearing assembly and inspecting
the temperature recorder during preflight checks and during each 100-
hour inspection. If the bearing was found running hot, then Robinson
advised upgrading the bearing to a newer design.
Following additional reports of overheating forward hanger bearing
assemblies, Robinson superseded SB-14 with R66 Service Bulletin SB-20,
dated November 7, 2016 (SB-20), which affected additional serial-
numbered helicopters and specified modifying T/R drive shaft assembly
P/Ns D224-3 and D224-4 by using kit Robinson KI-235 R66 TRDS Forward
Yoke Assembly and Hanger Installation Kit Instructions, Revision A,
dated June 23, 2015 (KI-235) and installing yoke assembly P/N D224-5.
This installation has an improved, larger bearing that spins with less
friction. SB-20 also specified inspecting the forward and aft sides of
the hanger and damper bearings for a minimum of 0.5 inch in length of
sealant on the junction of the black seal and bearing outer race and
applying sealant if there was less than 0.5 inch in length of sealant.
Robinson revised SB-20 with R66 Service Bulletin SB-20A, dated June
6, 2017 (SB-20A), to clarify that helicopters with either T/R drive
shaft assembly P/N D224-3 with modification B900-11 or P/N D224-4
installed include the upgraded bearing and do not require kit KI-235.
Robinson later revised SB-20A with R66 Service Bulletin SB-20B,
dated December 20, 2017 (SB-20B), which updates writing practices and
organizes the procedures into two separate sections, clarifies the
``Rotorcraft Affected'' section, and reduces the helicopters that need
to perform the inspection and sealant application procedures to just
helicopters without the latest version damper and housing bearings.
The NPRM proposed to require within 100 hours time-in-service (TIS)
replacing an affected T/R drive shaft forward yoke assembly with T/R
drive shaft yoke assembly P/N D224-5. The NPRM proposed to require
inspections of the forward and aft sides of the hanger bearing and the
damper bearing for sealant, and depending on the results of the
inspections applying sealant. The SNPRM proposed to revise the NPRM by
expanding the applicability, changing the proposed requirements, and
correcting nomenclature. The FAA is issuing this AD to address the
unsafe condition on these products.
Comments
The FAA gave the public the opportunity to comment on the proposed
rulemaking. The following presents the comments received on the SNPRM
and the FAA's response to each comment.
Request: Robinson requested the FAA change the note to the
Applicability paragraph to identify certain serial-numbered helicopters
that had T/R drive shaft assembly P/N D224-4 installed during
production and clarify that these helicopters are not affected by this
AD. Robinson explained that the specified serial-numbered helicopters
with T/R drive shaft assembly P/N D224-4 installed have the larger
(hanger) bearing, which is not affected by this AD, and clarified that
P/N D224-5 is a sub-assembly upgrade to P/N D224-4.
FAA Response: The FAA agrees and has revised that note in this
final rule to identify the serial-numbered helicopters with T/R drive
shaft assembly P/N D224-4 installed during production and clarify that
this part-numbered T/R drive shaft assembly is not affected by this AD.
Request: Robinson requested that the FAA change the exception in
paragraph (e)(1)(i) of this AD about not requiring the discarding of
removed nuts and palnuts and stated that exception implies that the
nuts and palnuts may be reused. Robinson explained that FAA Advisory
Circular (AC) 43.13-1B Section 7-122 (d) specifies that these nuts
should be discarded and referenced Robinson service information that
specifies upgrading certain nuts any time maintenance is done. Robinson
also stated that the KI-235 kit includes all required nuts and palnuts
to replace discarded hardware.
FAA Response: The FAA disagrees. The FAA cannot require discarding
of parts in an AD. Paragraph (d), section 7-122, of FAA AC 43.13-1B
states that the removed nuts should never be reused and should be
replaced with new ones when removed. Accordingly, the FAA has added
language to the exception stating that this AD requires removing the
affected parts from service.
FAA's Determination
The FAA has reviewed the relevant information, considered the
comments received, and determined that an unsafe condition exists and
is likely to exist or
[[Page 13164]]
develop on other products of the same type design and that air safety
and the public interest require adopting the AD requirements as
proposed with the changes described previously. These changes are
consistent with the intent proposed in the SNPRM for correcting the
unsafe condition and will neither increase the economic burden on any
operator nor increase the scope of the AD.
Related Service Information Under 1 CFR Part 51
The FAA reviewed KI-235. This service information provides
instructions for installing the newly designed yoke assembly, P/N D224-
5.
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.
Related Service Information
The FAA has reviewed SB-14, which specifies installing a
temperature recorder on the T/R drive shaft forward hanger bearing
assembly and inspecting the temperature during preflight checks and
during each 100-hour inspection. If the temperature of the bearing is
found running hot, then Robinson advises upgrading the bearing to a
newer design (kit P/N KI-235). This service information also specifies
adding a caution page to the Pilot Operating Handbook regarding the
overheating bearing assemblies. This service information was superseded
by SB-20.
The FAA has reviewed SB-20, SB-20A, and SB-20B, which specify
upgrading the forward hangar bearing assembly of certain T/R drive
shaft assemblies to the newer design with kit P/N KI-235 if not
previously done. For certain installations, this service information
contains procedures for inspecting for sealant and applying sealant to
the damper and hanger bearings if needed to prevent seal rotation. This
service information also specifies removing the caution page from the
Pilot Operating Handbook regarding the overheating bearing assemblies
that was added by SB-14.
Differences Between This AD and the Service Information
SB-20 specifies replacing the yoke assembly and applying sealant to
the bearing seals within the next 100 flight hours or by January 31,
2017, whichever comes first, and SB-20A and SB-20B continue the
compliance time of no later than January 31, 2017. This AD does not
have a calendar time compliance requirement. SB-20, SB- 20A, and SB-20B
specify inspecting for sealant and applying sealant to the damper and
hanger bearings if needed, while this AD does not.
Costs of Compliance
The FAA estimates that this AD affects 290 helicopters of U.S.
Registry. The FAA estimates that operators may incur the following
costs in order to comply with this AD. Labor costs are estimated at $85
per work-hour.
Installing Robinson field kit KI-235 takes about 6 work-hours and
parts cost about $950, for an estimated cost of $1,460 per helicopter.
As an option, replacing an affected T/R drive shaft assembly P/N D224-3
with T/R drive shaft assembly P/N D224-4 takes about 5 work-hours and
parts cost about $4,400, for an estimated cost of $4,825 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 AD will not have federalism
implications under Executive Order 13132. This AD will not have a
substantial direct effect on the States, on the relationship between
the national Government and the States, or on the distribution of power
and responsibilities among the various levels of government.
For the reasons discussed, I certify that this AD:
(1) Is not a ``significant regulatory action'' under Executive
Order 12866,
(2) Will not affect intrastate aviation in Alaska, and
(3) Will not have a significant economic impact, positive or
negative, on a substantial number of small entities under the criteria
of the Regulatory Flexibility Act.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.
Adoption of the Amendment
Accordingly, under the authority delegated to me by the
Administrator, the FAA amends 14 CFR part 39 as follows:
PART 39--AIRWORTHINESS DIRECTIVES
0
1. The authority citation for part 39 continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
Sec. 39.13 [Amended]
0
2. The FAA amends Sec. 39.13 by adding the following new airworthiness
directive:
2021-04-12 Robinson Helicopter Company: Amendment 39-21433; Docket
No. FAA-2017-0682; Product Identifier 2017-SW-028-AD.
(a) Applicability
This airworthiness directive (AD) applies to Robinson Helicopter
Company (Robinson) Model R66 helicopters, certificated in any
category, with a tail rotor (T/R) drive shaft assembly part number
(P/N) D224-3 without B900-11 modification installed.
Note 1 to paragraph (a): Helicopters with serial number (S/N)
0631 and subsequent had T/R drive shaft assembly P/N D224-4
installed during production, which is not affected by this AD.
(b) Unsafe Condition
This AD defines the unsafe condition as failure of a T/R drive
shaft forward hanger bearing. This condition could result in failure
of the T/R drive shaft and subsequent loss of helicopter control.
(c) Effective Date
This AD is effective April 12, 2021.
(d) Compliance
You are responsible for performing each action required by this
AD within the specified compliance time unless it has already been
accomplished prior to that time.
(e) Required Actions
(1) Within 100 hours time-in-service, do one of the following:
(i) Install Robinson kit P/N KI-235 using KI-235 R66 TRDS
Forward Yoke Assembly and Hanger Installation Kit Instructions,
Revision A, dated June 23, 2015, except where the service
information specifies discarding parts, you are required to remove
those parts from service instead.
(ii) Replace the entire T/R drive shaft assembly with T/R drive
shaft assembly P/N D224-4.
(2) As of the effective date of this AD, do not install a T/R
drive shaft assembly P/N D224-3 without B900-11 modification on any
helicopter.
[[Page 13165]]
(f) Alternative Methods of Compliance (AMOC)
(1) The Manager, Los Angeles ACO Branch, FAA, may approve AMOCs
for this AD. Send your proposal to: Danny Nguyen, Aerospace
Engineer, Los Angeles ACO Branch, FAA, 3960 Paramount Blvd.,
Lakewood, California 90712; telephone 562-627-5247; email [email protected].
(2) For operations conducted under a 14 CFR part 119 operating
certificate or under 14 CFR part 91, subpart K, the FAA suggests
that you notify your principal inspector, or lacking a principal
inspector, the manager of the local flight standards district office
or certificate holding district office before operating any aircraft
complying with this AD through an AMOC.
(g) Related Information
For service information identified in this AD, contact Robinson
Helicopter Company, 2901 Airport Drive, Torrance, CA 90505;
telephone 310-539-0508; fax 310-539-5198; or at https://www.robinsonheli.com. You may view a copy of the service information
at the FAA, Office of the Regional Counsel, Southwest Region, 10101
Hillwood Pkwy., Room 6N-321, Fort Worth, TX 76177.
(h) Material Incorporated by Reference
(1) The Director of the Federal Register approved the
incorporation by reference (IBR) of the service information listed
in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51.
(2) You must use this service information as applicable to do
the actions required by this AD, unless the AD specifies otherwise.
(i) Robinson KI-235 R66 TRDS Forward Yoke Assembly and Hanger
Installation Kit Instructions, Revision A, dated June 23, 2015.
(ii) [Reserved]
(3) For service information identified in this AD, contact
Robinson Helicopter Company, 2901 Airport Drive, Torrance, CA 90505;
telephone 310-539-0508; fax 310-539-5198; or at https://www.robinsonheli.com.
(4) 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.
(5) You may view this service information that is incorporated
by reference at the National Archives and Records Administration
(NARA). For information on the availability of this material at
NARA, email: [email protected], or go to: https://www.archives.gov/federal-register/cfr/ibr-locations.html.
(i) Subject
Joint Aircraft Service Component (JASC) Code: 6510, Tail Rotor
Drive Shaft.
Issued on February 8, 2021.
Lance T. Gant,
Director, Compliance & Airworthiness Division, Aircraft Certification
Service.
[FR Doc. 2021-03656 Filed 3-5-21; 8:45 am]
BILLING CODE 4910-13-P
