Airworthiness Directives; Robinson Helicopter Company Helicopters, 14596-14600 [2024-03970]
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14596
Proposed Rules
Federal Register
Vol. 89, No. 40
Wednesday, February 28, 2024
This section of the FEDERAL REGISTER
contains notices to the public of the proposed
issuance of rules and regulations. The
purpose of these notices is to give interested
persons an opportunity to participate in the
rule making prior to the adoption of the final
rules.
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2024–0237; Project
Identifier AD–2023–00491–R]
RIN 2120–AA64
Airworthiness Directives; Robinson
Helicopter Company Helicopters
Federal Aviation
Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
The FAA proposes to adopt a
new airworthiness directive (AD) for all
Robinson Helicopter Company Model
R44 and R44 II helicopters. This
proposed AD was prompted by reports
of a fractured clutch shaft forward yoke
(yoke) on the main rotor (M/R) drive
due to fatigue cracking. This proposed
AD would require visually inspecting a
certain part-numbered flex plate
assembly (flex plate) and certain partnumbered yokes, including each yoke
bolt, and depending on the inspection
results, removing an affected part from
service and replacing an affected part
with an airworthy part. This proposed
AD would also require removing a
certain part-numbered yoke from service
after accumulating a certain number of
hours time-in-service (TIS) or a certain
number of years, or as an alternative to
removing the part from service,
performing a 10X or higher power
magnification visual inspection and, if
needed, a magnetic particle inspection.
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 April 15, 2024.
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
regulations.gov. Follow the instructions
for submitting comments.
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SUMMARY:
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• 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.
AD Docket: You may examine the AD
docket at regulations.gov under Docket
No. FAA–2024–0237; 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, any comments
received, and other information. The
street address for Docket Operations is
listed above.
Related Service Information: For
service information identified in this
NPRM, contact Robinson Helicopter
Company, Technical Support
Department, 2901 Airport Drive,
Torrance, CA 90505; phone (310) 539–
0508; fax (310) 539–5198; email ts1@
robinsonheli.com; or at
robinsonheli.com. 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.
FOR FURTHER INFORMATION CONTACT: Eric
Moreland, Aviation Safety Engineer,
FAA, 3960 Paramount Boulevard,
Lakewood, CA 90712; phone: (562) 627–
5364; email: Eric.R.Moreland@faa.gov.
SUPPLEMENTARY INFORMATION:
Comments Invited
The FAA invites you to send any
written relevant data, views, or
arguments about this proposal. Send
your comments to an address listed
under ADDRESSES. Include ‘‘Docket No.
FAA–2024–0237; Project Identifier AD–
2023–00491–R’’ 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
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information as described in 14 CFR
11.35, the FAA will post all comments
received, without change, to
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 Eric Moreland,
Aviation Safety Engineer, FAA, 3960
Paramount Boulevard, Lakewood, CA
90712; phone: (562) 627–5364; email:
Eric.R.Moreland@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
After receiving a report of a failed
yoke in the M/R drive system, the FAA
issued Special Airworthiness
Information Bulletin AIR–22–08, dated
April 11, 2022 (SAIB) to remind owners
and operators of any Robinson
Helicopter Company Model R44
helicopters of the importance of
adhering to existing inspection
procedures in the applicable operating
handbooks and maintenance manuals.
According to Robinson Helicopter
Company, the yoke had fractured due to
fatigue cracking and improper torque at
the bolt hole and the yoke cross-section.
After the FAA issued the SAIB,
Robinson Helicopter Company reported
an additional incident on a Model R44
helicopter where the yoke was fractured
and separated from the drive train, again
due to fatigue cracks and improper
torquing. Accordingly, the FAA
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Federal Register / Vol. 89, No. 40 / Wednesday, February 28, 2024 / Proposed Rules
proposes to adopt a new AD for all
Robinson Helicopter Company Model
R44 and R44 II helicopters to ensure
adequate inspection and maintenance of
all driveshaft yokes. This condition, if
not addressed, could result in loss of M/
R drive and subsequent loss of control
of the helicopter.
FAA’s Determination
The FAA is issuing this NPRM after
determining that the unsafe condition
described previously is likely to exist or
develop on other products of the same
type design.
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Related Service Information
The FAA reviewed Robinson
Helicopter Company R44 Maintenance
Manual and Instructions for Continued
Airworthiness, Volume 1, Chapter 2 and
Chapter 23, dated September 2023,
which specifies procedures for
inspecting the yoke and flex plate of the
M/R drive, removing paint, applying
torque, and performing a magnetic
particle inspection. This service
information also contains the
information specified in Appendix 1 to
this proposed AD, which specifies
torque values, and Figure 1 to paragraph
(g)(1) of this proposed AD, which
depicts the areas for the flex plate
inspection.
Proposed AD Requirements in This
NPRM
This proposed AD would require
visually inspecting flex plate part
number (P/N) C947–1 for any loose
fasteners, cracks, fretting, corrosion,
wear, and to ensure that the washers are
bonded to both sides of the flex plate
arms and depending on the inspection
results, removing the flex plate from
service and replacing it with an
airworthy flex plate.
This proposed AD would also require
visually inspecting yoke P/N C907–1 or
C907–2 as applicable, and yoke P/N
C908–1, for any cracks, corrosion, and
fretting, and depending on the
inspection results, removing the yoke
from service and replacing it with an
airworthy yoke. Additionally, this
proposed AD would require visually
inspecting each yoke bolt for a torque
stripe, loose fastener, loose nut, and to
determine if nut P/N D210–6 and palnut
P/N B330–19 are installed. If there are
any missing torque stripes, loose
fasteners, loose nuts, or if nut P/N
D210–6 or palnut P/N B330–19 are not
installed, this proposed AD would
require removing the associated yoke
from service and replacing it with an
airworthy yoke.
This proposed AD would also require
removing from service any yoke P/N
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C907–1 or C907–2 that has accumulated
more than 12 years or 2,200 total hours
TIS, whichever occurs first since first
installation on any helicopter, and
replacing it with a yoke P/N C907–1 or
C907–2 that has accumulated less than
2,200 total hours TIS or 12 years,
whichever occurs first since first
installation on any helicopter. As an
alternative to replacing any yoke that
has accumulated more than 12 years or
2,200 total hours TIS since first
installation on a helicopter, this
proposed AD would allow removing
paint from the yoke and using 10X or
higher power magnifying glass to
inspect for any crack, seam, lap, shut,
missing cadmium plating, or any flaw
which is open to the surface, and
depending on the inspection results,
removing the yoke from service and
replacing it with an airworthy yoke. If
the yoke is not replaced as a result of
the alternate inspection, this proposed
AD would require performing a
magnetic particle inspection of the yoke
for any crack, seam, lap, shut, or any
flaw which is open to the surface, and
depending on the inspection results,
removing the yoke from service and
replacing with an airworthy yoke.
Finally, if the yoke is replaced as a
result of the actions required by this
proposed AD, this proposed AD would
require torquing each bolt, nut, and
palnut using the torque value
information in Appendix 1 to this
proposed AD.
Costs of Compliance
The FAA estimates that this AD, if
adopted as proposed, would affect 1,725
helicopters of U.S. registry. The FAA
estimates the following costs to comply
with this proposed AD. Labor costs are
estimated at $85 per work-hour.
Visually inspecting a flex plate would
take approximately 0.25 work-hour for
an estimated cost of $21 per helicopter
and $36,225 for the U.S. fleet.
Visually inspecting a yoke, including
inspecting each yoke bolt, would take
approximately 1.25 work-hours for an
estimated cost of $106 per helicopter
and $182,850 for the U.S. fleet.
Replacing a yoke would take
approximately 6 work-hours and parts
would cost approximately $890 for an
estimated cost of $1,400 per helicopter.
Removing paint and inspecting a yoke
using 10X or higher power magnifying
glass would take approximately 1.5
work-hours for an estimated cost of
$128 per helicopter.
Performing a magnetic particle
inspection would take approximately
1.5 work-hours for an estimated cost of
$128 per helicopter.
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14597
Applying torque to one bolt, nut, and
palnut would take approximately 1
work-hour for an estimated cost of $85
per hardware set.
If required, replacing a flex plate
would take approximately 1 work-hour
and parts would cost approximately
$1,240 for an estimated cost of $1,325
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 above, I
certify this proposed regulation:
(1) Is not a ‘‘significant regulatory
action’’ under Executive Order 12866,
(2) Would not affect intrastate
aviation in Alaska, and
(3) Would not have a significant
economic impact, positive or negative,
on a substantial number of small entities
under the criteria of the Regulatory
Flexibility Act.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation
safety, Incorporation by reference,
Safety.
The Proposed Amendment
Accordingly, under the authority
delegated to me by the Administrator,
the FAA proposes to amend 14 CFR part
39 as follows:
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14598
Federal Register / Vol. 89, No. 40 / Wednesday, February 28, 2024 / Proposed Rules
(c) Applicability
PART 39—AIRWORTHINESS
DIRECTIVES
This AD applies to Robinson Helicopter
Company Model R44 and R44 II helicopters,
certificated in any category.
1. The authority citation for part 39
continues to read as follows:
■
(d) Subject
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
[Amended]
Joint Aircraft System Component (JASC)
Code: 6310, Engine/Transmission coupling.
■
(e) Unsafe Condition
Robinson Helicopter Company: Docket No.
FAA–2024–0237; Project Identifier AD–
2023–00491–R.
This AD was prompted by reports of a
fractured clutch shaft forward yoke (yoke) on
the main rotor (M/R) drive due to fatigue
cracking. The FAA is issuing this AD to
detect fatigue cracking on the yoke. The
unsafe condition, if not addressed, could
result in loss of M/R drive and subsequent
loss of control of the helicopter.
2. The FAA amends § 39.13 by adding
the following new airworthiness
directive:
(a) Comments Due Date
The FAA must receive comments on this
airworthiness directive (AD) by April 15,
2024.
(b) Affected ADs
None.
(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
(g) Required Actions
(1) Within 100 hours time-in-service (TIS)
after the effective date of this AD, accomplish
the actions required by paragraphs (g)(1)(i)
through (iii) of this AD.
(i) Visually inspect forward flex plate
assembly (flex plate) part number (P/N)
C947–1 for any loose fasteners, cracks,
fretting, corrosion, wear, and to ensure that
the washers are bonded to both sides of each
flex plate arm, in the areas depicted in Figure
1 to paragraph (g)(1)(i) of this AD, which
includes the four bolt holes. If there is any
loose fastener (can be moved by hand), crack,
fretting, corrosion, or wear in any area
including the four bolt holes, or wear that
consists of the washers not securely bonded
to both sides of each flex plate arm, before
further flight, remove the flex plate from
service and replace with an airworthy flex
plate.
Figure 1 to Paragraph (g)(1)(i)—Flex Plate
Inspection
Give special attention to
these areas for cracks
Inspect entire periphery for
cracks and corrosion.
Inspect this area for cracks.
(ii) Visually inspect yoke P/N C907–1 or
C907–2, as applicable to your model
helicopter, and yoke P/N C908–1, for any
cracks, corrosion, and fretting. If there is any
crack, corrosion, or fretting, before further
flight, remove the yoke from service and
replace it with an airworthy yoke, and torque
each newly-installed bolt, nut, and palnut
using the torque value information in
Appendix 1 to this AD.
(iii) Visually inspect each yoke bolt for a
torque stripe, loose fastener, a loose nut, and
to ensure that nut P/N D210–6 and palnut
P/N B330–19 are installed. If there is a
missing torque stripe, loose fastener on any
nut (can be moved by hand), any nut is loose
(nut can be turned by hand), or if nut P/N
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D210–6 or palnut P/N B330–19 are not
installed, before further flight, remove the
associated yoke from service and replace it
with an airworthy yoke, and torque each
newly-installed bolt, nut, and palnut using
the torque value information in Appendix 1
to this AD.
(2) For helicopters on which a yoke
replacement as specified in paragraphs
(g)(1)(ii) or (iii) of this AD was not
accomplished: Prior to the accumulation of
2,200 total hours TIS on any yoke P/N C907–
1 or C907–2 or within 12 years since first
installation of yoke P/N C907–1 or C907–2 on
any helicopter, whichever occurs first; or
within 100 hours TIS after the effective date
of this AD; whichever occurs later, remove
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Sfmt 4702
that yoke from service and replace it with an
airworthy yoke, and torque each newlyinstalled bolt, nut, and palnut using the
torque value information in Appendix 1 to
this AD.
(3) As an alternative to removing the yoke
from service as required by paragraph (g)(2)
of this AD, remove yoke P/N C907–1 or
C907–2, as applicable to your model
helicopter, remove the paint on the yoke
using Cee-Bee stripper A–292, without using
a plastic media abrasive paint stripper, and
accomplish paragraphs (g)(3)(i) and (ii) of
this AD, as applicable.
(i) Using 10X or higher power magnifying
glass, visually inspect the yoke for any crack,
seam, lap, shut, missing cadmium plating,
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ddrumheller on DSK120RN23PROD with PROPOSALS1
Inspect area around washers
for fretting.
Federal Register / Vol. 89, No. 40 / Wednesday, February 28, 2024 / Proposed Rules
ddrumheller on DSK120RN23PROD with PROPOSALS1
and any flaw which is open to the surface.
If there is any crack, seam, lap, shut, missing
cadmium plating, or flaw, before further
flight, remove the yoke from service and
replace it with an airworthy yoke, and torque
each newly-installed bolt, nut, and palnut
using the torque value information in
Appendix 1 to this AD.
(ii) If the yoke is not removed from service
as a result of the actions required by
paragraph (g)(3)(i) of this AD, visually
inspect it for any crack, seam, lap, shut, or
any flaw which is open to the surface by
performing a magnetic particle inspection
using a method in accordance with FAAapproved procedures. If there is any crack,
seam, lap, shut, or flaw, before further flight,
remove the yoke from service and replace
with an airworthy yoke, and torque each
newly-installed bolt, nut, and palnut using
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the torque value information in Appendix 1
to this AD.
(h) Special Flight Permit
A one-time flight permit may be issued in
accordance with 14 CFR 21.197 and 21.199
in order to fly to a maintenance area to
perform the required actions in this AD,
provided there are no passengers onboard.
(i) Alternative Methods of Compliance
(AMOCs)
(1) The Manager, West Certification
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 West Certification
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14599
Branch, send it to the attention of the person
identified in paragraph (j) of this AD.
Information may be emailed to: 9-ANMLAACO-AMOC-REQUESTS@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) Additional Information
For more information about this AD,
contact Eric Moreland, Aviation Safety
Engineer, FAA, 3960 Paramount Boulevard,
Lakewood, CA 90712; phone: (562) 627–
5364; email: Eric.R.Moreland@faa.gov.
(k) Material Incorporated by Reference
None.
Appendix 1 to AD ####–##–##
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14600
Federal Register / Vol. 89, No. 40 / Wednesday, February 28, 2024 / Proposed Rules
NOTE
1. Torque values .-,e ln lneh-poum:1, unle• otherwl• spiaeltled.
llncludG nut Q I N ~ tt!V~.
3. ltlCQ(IIN! torque velU8$ 1 O'IJEi If to~d 8t bolt head.
4. W•t indle.-:es ~ lll,ilbr,lc.ted with .A257•9 Inti-~.
5. For elbow and tee fit.tings which require atlgn~. torque to lnd~
vak,1111, thiut tighten t{)I d••hd pi,Mi,ition.
6. Tolerance 1$ ± 1O'IJEi. min$ fllnQG l$ s ~ .
7. Unle$$ a,tl,erwlN spadflad,. thread SIU$ &-32 and llfflllktr ~ n()t -.ed k)r
Pftm&f'Y ,tructunt and do not nitqulre eon~ Qt t:orQ1,i19$.
2. Torqt.11;11 \ i ' ~
NAS6603 th11,.1 NAS8608 Bolts
NAS1303 th11,.1 NAS 1308 :Bolts
NAS823 ScreW$
NAS1351 & NAS1352 SCntW$
NAS6001bru NASOOG Screws
AN502 se,-W$
At 42 $CQW$
AN503 Seri!IW:$
AN3 Boll$
AN509 ScriilW:$
AN4~
AN525 SeraW:$
AN8~ . M:824694 Setews
AN8Bolt$
: MS27039 Setews
STAMPED NUTS
{fl'ALNUTS)
Painutt; are to be uNd ol'llv · ~
.-nd ntpllf;l!l.!id with ne-w when
rf)lfflOV8d.
10-32
114~28
NAS8803
50
NAS8804
5116-24
318-24
7116-20
112~20
NA.$8608
NAS6607
NAS8808
120
240
350
665
995
10-32
A142•1, ·3, -4; AN3
37
1/4,-28
AN4
90
318•24
AN8
28()
112·20
ANS
'195
10-32
114-21
5116-24
318-24
7116-20
112~20
118-27
1/4,-18
TAPEAED PIPE
THREADS
3/&-18
112~14
314*14
10-32
114-28
5116-24
318-24
8330..7
8330-13
8330-16
8330-19
8330-21
8330-24
CMS.27151•7l
CMS27151•t3l
CMS27151·161
tMS27151·19l
CMS27151~21 l
IMS27151•2•4l
5" note 5
Str1,1ight flttlngg onty
S..note 5
Str•lght fittings onty
S..note 5
Str1,1lght fittings onty
S..note 5
Str.alght Httlngg Qnly
See note 5
Straight fittings onty
AN315-3
AN31M
AN316-5
AN318-6
6-15
11-25
20-40
29-80
42-85
54-110
50
120
85
170
110
220
180
320
230
480
15
40
80
110
Issued on February 21, 2024.
Victor Wicklund,
Deputy Director, Compliance & Airworthiness
Division, Aircraft Certification Service.
[FR Doc. 2024–03970 Filed 2–27–24; 8:45 am]
BILLING CODE 4910–13–P
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ROD END JAM MJ'l'S
(AN315 ~ AN316}
NAS8805
]]>Agencies
[Federal Register Volume 89, Number 40 (Wednesday, February 28, 2024)]
[Proposed Rules]
[Pages 14596-14600]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2024-03970]
========================================================================
Proposed Rules
Federal Register
________________________________________________________________________
This section of the FEDERAL REGISTER contains notices to the public of
the proposed issuance of rules and regulations. The purpose of these
notices is to give interested persons an opportunity to participate in
the rule making prior to the adoption of the final rules.
========================================================================
Federal Register / Vol. 89, No. 40 / Wednesday, February 28, 2024 /
Proposed Rules
[[Page 14596]]
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2024-0237; Project Identifier AD-2023-00491-R]
RIN 2120-AA64
Airworthiness Directives; Robinson Helicopter Company 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 all Robinson Helicopter Company Model R44 and R44 II helicopters.
This proposed AD was prompted by reports of a fractured clutch shaft
forward yoke (yoke) on the main rotor (M/R) drive due to fatigue
cracking. This proposed AD would require visually inspecting a certain
part-numbered flex plate assembly (flex plate) and certain part-
numbered yokes, including each yoke bolt, and depending on the
inspection results, removing an affected part from service and
replacing an affected part with an airworthy part. This proposed AD
would also require removing a certain part-numbered yoke from service
after accumulating a certain number of hours time-in-service (TIS) or a
certain number of years, or as an alternative to removing the part from
service, performing a 10X or higher power magnification visual
inspection and, if needed, a magnetic particle inspection. 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 April 15,
2024.
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 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.
AD Docket: You may examine the AD docket at regulations.gov under
Docket No. FAA-2024-0237; 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, any comments received, and other
information. The street address for Docket Operations is listed above.
Related Service Information: For service information identified in
this NPRM, contact Robinson Helicopter Company, Technical Support
Department, 2901 Airport Drive, Torrance, CA 90505; phone (310) 539-
0508; fax (310) 539-5198; email robinsonheli.com">ts1@robinsonheli.com; or at
robinsonheli.com. 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.
FOR FURTHER INFORMATION CONTACT: Eric Moreland, Aviation Safety
Engineer, FAA, 3960 Paramount Boulevard, Lakewood, CA 90712; phone:
(562) 627-5364; 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-2024-0237; Project Identifier
AD-2023-00491-R'' 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
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 Eric
Moreland, Aviation Safety Engineer, FAA, 3960 Paramount Boulevard,
Lakewood, CA 90712; phone: (562) 627-5364; 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
After receiving a report of a failed yoke in the M/R drive system,
the FAA issued Special Airworthiness Information Bulletin AIR-22-08,
dated April 11, 2022 (SAIB) to remind owners and operators of any
Robinson Helicopter Company Model R44 helicopters of the importance of
adhering to existing inspection procedures in the applicable operating
handbooks and maintenance manuals. According to Robinson Helicopter
Company, the yoke had fractured due to fatigue cracking and improper
torque at the bolt hole and the yoke cross-section.
After the FAA issued the SAIB, Robinson Helicopter Company reported
an additional incident on a Model R44 helicopter where the yoke was
fractured and separated from the drive train, again due to fatigue
cracks and improper torquing. Accordingly, the FAA
[[Page 14597]]
proposes to adopt a new AD for all Robinson Helicopter Company Model
R44 and R44 II helicopters to ensure adequate inspection and
maintenance of all driveshaft yokes. This condition, if not addressed,
could result in loss of M/R drive and subsequent loss of control of the
helicopter.
FAA's Determination
The FAA is issuing this NPRM after determining that the unsafe
condition described previously is likely to exist or develop on other
products of the same type design.
Related Service Information
The FAA reviewed Robinson Helicopter Company R44 Maintenance Manual
and Instructions for Continued Airworthiness, Volume 1, Chapter 2 and
Chapter 23, dated September 2023, which specifies procedures for
inspecting the yoke and flex plate of the M/R drive, removing paint,
applying torque, and performing a magnetic particle inspection. This
service information also contains the information specified in Appendix
1 to this proposed AD, which specifies torque values, and Figure 1 to
paragraph (g)(1) of this proposed AD, which depicts the areas for the
flex plate inspection.
Proposed AD Requirements in This NPRM
This proposed AD would require visually inspecting flex plate part
number (P/N) C947-1 for any loose fasteners, cracks, fretting,
corrosion, wear, and to ensure that the washers are bonded to both
sides of the flex plate arms and depending on the inspection results,
removing the flex plate from service and replacing it with an airworthy
flex plate.
This proposed AD would also require visually inspecting yoke P/N
C907-1 or C907-2 as applicable, and yoke P/N C908-1, for any cracks,
corrosion, and fretting, and depending on the inspection results,
removing the yoke from service and replacing it with an airworthy yoke.
Additionally, this proposed AD would require visually inspecting each
yoke bolt for a torque stripe, loose fastener, loose nut, and to
determine if nut P/N D210-6 and palnut P/N B330-19 are installed. If
there are any missing torque stripes, loose fasteners, loose nuts, or
if nut P/N D210-6 or palnut P/N B330-19 are not installed, this
proposed AD would require removing the associated yoke from service and
replacing it with an airworthy yoke.
This proposed AD would also require removing from service any yoke
P/N C907-1 or C907-2 that has accumulated more than 12 years or 2,200
total hours TIS, whichever occurs first since first installation on any
helicopter, and replacing it with a yoke P/N C907-1 or C907-2 that has
accumulated less than 2,200 total hours TIS or 12 years, whichever
occurs first since first installation on any helicopter. As an
alternative to replacing any yoke that has accumulated more than 12
years or 2,200 total hours TIS since first installation on a
helicopter, this proposed AD would allow removing paint from the yoke
and using 10X or higher power magnifying glass to inspect for any
crack, seam, lap, shut, missing cadmium plating, or any flaw which is
open to the surface, and depending on the inspection results, removing
the yoke from service and replacing it with an airworthy yoke. If the
yoke is not replaced as a result of the alternate inspection, this
proposed AD would require performing a magnetic particle inspection of
the yoke for any crack, seam, lap, shut, or any flaw which is open to
the surface, and depending on the inspection results, removing the yoke
from service and replacing with an airworthy yoke.
Finally, if the yoke is replaced as a result of the actions
required by this proposed AD, this proposed AD would require torquing
each bolt, nut, and palnut using the torque value information in
Appendix 1 to this proposed AD.
Costs of Compliance
The FAA estimates that this AD, if adopted as proposed, would
affect 1,725 helicopters of U.S. registry. The FAA estimates the
following costs to comply with this proposed AD. Labor costs are
estimated at $85 per work-hour.
Visually inspecting a flex plate would take approximately 0.25
work-hour for an estimated cost of $21 per helicopter and $36,225 for
the U.S. fleet.
Visually inspecting a yoke, including inspecting each yoke bolt,
would take approximately 1.25 work-hours for an estimated cost of $106
per helicopter and $182,850 for the U.S. fleet.
Replacing a yoke would take approximately 6 work-hours and parts
would cost approximately $890 for an estimated cost of $1,400 per
helicopter.
Removing paint and inspecting a yoke using 10X or higher power
magnifying glass would take approximately 1.5 work-hours for an
estimated cost of $128 per helicopter.
Performing a magnetic particle inspection would take approximately
1.5 work-hours for an estimated cost of $128 per helicopter.
Applying torque to one bolt, nut, and palnut would take
approximately 1 work-hour for an estimated cost of $85 per hardware
set.
If required, replacing a flex plate would take approximately 1
work-hour and parts would cost approximately $1,240 for an estimated
cost of $1,325 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 above, I certify this proposed
regulation:
(1) Is not a ``significant regulatory action'' under Executive
Order 12866,
(2) Would not affect intrastate aviation in Alaska, and
(3) Would not have a significant economic impact, positive or
negative, on a substantial number of small entities under the criteria
of the Regulatory Flexibility Act.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.
The Proposed Amendment
Accordingly, under the authority delegated to me by the
Administrator, the FAA proposes to amend 14 CFR part 39 as follows:
[[Page 14598]]
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:
Robinson Helicopter Company: Docket No. FAA-2024-0237; Project
Identifier AD-2023-00491-R.
(a) Comments Due Date
The FAA must receive comments on this airworthiness directive
(AD) by April 15, 2024.
(b) Affected ADs
None.
(c) Applicability
This AD applies to Robinson Helicopter Company Model R44 and R44
II helicopters, certificated in any category.
(d) Subject
Joint Aircraft System Component (JASC) Code: 6310, Engine/
Transmission coupling.
(e) Unsafe Condition
This AD was prompted by reports of a fractured clutch shaft
forward yoke (yoke) on the main rotor (M/R) drive due to fatigue
cracking. The FAA is issuing this AD to detect fatigue cracking on
the yoke. The unsafe condition, if not addressed, could result in
loss of M/R drive 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) Within 100 hours time-in-service (TIS) after the effective
date of this AD, accomplish the actions required by paragraphs
(g)(1)(i) through (iii) of this AD.
(i) Visually inspect forward flex plate assembly (flex plate)
part number (P/N) C947-1 for any loose fasteners, cracks, fretting,
corrosion, wear, and to ensure that the washers are bonded to both
sides of each flex plate arm, in the areas depicted in Figure 1 to
paragraph (g)(1)(i) of this AD, which includes the four bolt holes.
If there is any loose fastener (can be moved by hand), crack,
fretting, corrosion, or wear in any area including the four bolt
holes, or wear that consists of the washers not securely bonded to
both sides of each flex plate arm, before further flight, remove the
flex plate from service and replace with an airworthy flex plate.
Figure 1 to Paragraph (g)(1)(i)--Flex Plate Inspection
[GRAPHIC] [TIFF OMITTED] TP28FE24.000
(ii) Visually inspect yoke P/N C907-1 or C907-2, as applicable
to your model helicopter, and yoke P/N C908-1, for any cracks,
corrosion, and fretting. If there is any crack, corrosion, or
fretting, before further flight, remove the yoke from service and
replace it with an airworthy yoke, and torque each newly-installed
bolt, nut, and palnut using the torque value information in Appendix
1 to this AD.
(iii) Visually inspect each yoke bolt for a torque stripe, loose
fastener, a loose nut, and to ensure that nut P/N D210-6 and palnut
P/N B330-19 are installed. If there is a missing torque stripe,
loose fastener on any nut (can be moved by hand), any nut is loose
(nut can be turned by hand), or if nut P/N D210-6 or palnut P/N
B330-19 are not installed, before further flight, remove the
associated yoke from service and replace it with an airworthy yoke,
and torque each newly-installed bolt, nut, and palnut using the
torque value information in Appendix 1 to this AD.
(2) For helicopters on which a yoke replacement as specified in
paragraphs (g)(1)(ii) or (iii) of this AD was not accomplished:
Prior to the accumulation of 2,200 total hours TIS on any yoke P/N
C907-1 or C907-2 or within 12 years since first installation of yoke
P/N C907-1 or C907-2 on any helicopter, whichever occurs first; or
within 100 hours TIS after the effective date of this AD; whichever
occurs later, remove that yoke from service and replace it with an
airworthy yoke, and torque each newly-installed bolt, nut, and
palnut using the torque value information in Appendix 1 to this AD.
(3) As an alternative to removing the yoke from service as
required by paragraph (g)(2) of this AD, remove yoke P/N C907-1 or
C907-2, as applicable to your model helicopter, remove the paint on
the yoke using Cee-Bee stripper A-292, without using a plastic media
abrasive paint stripper, and accomplish paragraphs (g)(3)(i) and
(ii) of this AD, as applicable.
(i) Using 10X or higher power magnifying glass, visually inspect
the yoke for any crack, seam, lap, shut, missing cadmium plating,
[[Page 14599]]
and any flaw which is open to the surface. If there is any crack,
seam, lap, shut, missing cadmium plating, or flaw, before further
flight, remove the yoke from service and replace it with an
airworthy yoke, and torque each newly-installed bolt, nut, and
palnut using the torque value information in Appendix 1 to this AD.
(ii) If the yoke is not removed from service as a result of the
actions required by paragraph (g)(3)(i) of this AD, visually inspect
it for any crack, seam, lap, shut, or any flaw which is open to the
surface by performing a magnetic particle inspection using a method
in accordance with FAA-approved procedures. If there is any crack,
seam, lap, shut, or flaw, before further flight, remove the yoke
from service and replace with an airworthy yoke, and torque each
newly-installed bolt, nut, and palnut using the torque value
information in Appendix 1 to this AD.
(h) Special Flight Permit
A one-time flight permit may be issued in accordance with 14 CFR
21.197 and 21.199 in order to fly to a maintenance area to perform
the required actions in this AD, provided there are no passengers
onboard.
(i) Alternative Methods of Compliance (AMOCs)
(1) The Manager, West Certification 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 West Certification Branch, send it to
the attention of the person identified in paragraph (j) 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) Additional Information
For more information about this AD, contact Eric Moreland,
Aviation Safety Engineer, FAA, 3960 Paramount Boulevard, Lakewood,
CA 90712; phone: (562) 627-5364; email: [email protected].
(k) Material Incorporated by Reference
None.
Appendix 1 to AD ####-##-##
[[Page 14600]]
[GRAPHIC] [TIFF OMITTED] TP28FE24.001
Issued on February 21, 2024.
Victor Wicklund,
Deputy Director, Compliance & Airworthiness Division, Aircraft
Certification Service.
[FR Doc. 2024-03970 Filed 2-27-24; 8:45 am]
BILLING CODE 4910-13-P
