Proposed Rule2024-08893
Airworthiness Directives; Various Helicopters
Primary source
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Published
April 25, 2024
Issuing agencies
Transportation DepartmentFederal Aviation Administration
Abstract
The FAA proposes to adopt a new airworthiness directive (AD) for various helicopters modified by certain supplemental type certificates (STCs) that approve the installation of an emergency float kit or an emergency float with liferaft kit. This proposed AD was prompted by the results of an accident investigation and subsequent reports of difficulty pulling the emergency float kit float activation handle installed on the pilot cyclic. This proposed AD would require repetitively inspecting the pull force on the float activation handle and, depending on the results, accomplishing corrective actions. For certain model helicopters, this proposed AD would also require removing from service and replacing certain part-numbered float inflation reservoirs (reservoirs) and pull cable assemblies (cables) with certain other part-numbered reservoirs and cables. Finally, this proposed AD would prohibit installing certain part-numbered reservoirs and cables on certain helicopters. The FAA is proposing this AD to address the unsafe condition on these products.
Full Text
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<title>Federal Register, Volume 89 Issue 81 (Thursday, April 25, 2024)</title>
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[Federal Register Volume 89, Number 81 (Thursday, April 25, 2024)]
[Proposed Rules]
[Pages 31659-31663]
From the Federal Register Online via the Government Publishing Office [<a href="http://www.gpo.gov">www.gpo.gov</a>]
[FR Doc No: 2024-08893]
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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.
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Federal Register / Vol. 89, No. 81 / Thursday, April 25, 2024 /
Proposed Rules
[[Page 31659]]
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2024-1004; Project Identifier AD-2023-01058-R]
RIN 2120-AA64
Airworthiness Directives; Various Helicopters
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking (NPRM).
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SUMMARY: The FAA proposes to adopt a new airworthiness directive (AD)
for various helicopters modified by certain supplemental type
certificates (STCs) that approve the installation of an emergency float
kit or an emergency float with liferaft kit. This proposed AD was
prompted by the results of an accident investigation and subsequent
reports of difficulty pulling the emergency float kit float activation
handle installed on the pilot cyclic. This proposed AD would require
repetitively inspecting the pull force on the float activation handle
and, depending on the results, accomplishing corrective actions. For
certain model helicopters, this proposed AD would also require removing
from service and replacing certain part-numbered float inflation
reservoirs (reservoirs) and pull cable assemblies (cables) with certain
other part-numbered reservoirs and cables. Finally, this proposed AD
would prohibit installing certain part-numbered reservoirs and cables
on certain helicopters. 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 10,
2024.
ADDRESSES: You may send comments, using the procedures found in 14 CFR
11.43 and 11.45, by any of the following methods:
<bullet> Federal eRulemaking Portal: Go to <a href="http://regulations.gov">regulations.gov</a>. Follow
the instructions for submitting comments.
<bullet> Fax: (202) 493-2251.
<bullet> 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.
<bullet> 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 <a href="http://regulations.gov">regulations.gov</a> under
Docket No. FAA-2024-1004; 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.
Material Incorporated by Reference:
<bullet> For Dart Aerospace service information identified in this
NPRM, contact Dart Aerospace, LTD., 1270 Aberdeen St., Hawkesbury, ON,
K6A 1K7, Canada; phone: 1-613-632-5200; Fax: 1-613-632-5246; or at
<a href="http://dartaero.com">dartaero.com</a>.
<bullet> You may view this service information at the FAA, Office
of the Regional Counsel, Southwest Region, 10101 Hillwood Parkway, Room
6N-321, Fort Worth, TX 76177. For information on the availability of
this material at the FAA, call (817) 222-5110.
Other Related Service Information: For additional Dart Aerospace
service information identified in this NPRM, use the Dart Aerospace,
LTD., contact information under Material Incorporated by Reference
above. You may also view this service information at the FAA contact
information under Material Incorporated by Reference above.
FOR FURTHER INFORMATION CONTACT: Johann Magana, Aviation Safety
Engineer, FAA, 3960 Paramount Boulevard, Lakewood, CA 90712; phone:
(562) 627-5322; email: <a href="/cdn-cgi/l/email-protection#c7ada8afa6a9a9e9aaa6a0a6a9a687a1a6a6e9a0a8b1"><span class="__cf_email__" data-cfemail="89e3e6e1e8e7e7a7e4e8eee8e7e8c9efe8e8a7eee6ff">[email protected]</span></a>.
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-2024-1004; Project Identifier
AD-2023-01058-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
<a href="http://regulations.gov">regulations.gov</a>, 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
Johann Magana, Aviation Safety Engineer, FAA, 3960 Paramount Boulevard,
Lakewood, CA 90712; phone: (562) 627-5322; email:
<a href="/cdn-cgi/l/email-protection#cfa5a0a7aea1a1e1a2aea8aea1ae8fa9aeaee1a8a0b9"><span class="__cf_email__" data-cfemail="6c0603040d020242010d0b0d020d2c0a0d0d420b031a">[email protected]</span></a>. Any commentary that the FAA receives which is
not specifically designated as CBI will be placed in the public docket
for this rulemaking.
Background
The FAA received reports of an accident involving an Airbus
Helicopters Model AS350B2 helicopter impacting a body of water during
an autorotation. The left-hand and right-hand emergency floats did not
inflate symmetrically, and the helicopter subsequently capsized.
[[Page 31660]]
During the accident investigation, the FAA learned of reports of
difficulty pulling the emergency float kit float activation handle
installed on the pilot cyclic. Asymmetric inflation of the float system
and difficulty deploying the float system from the float activation
handle installed on the pilot cyclic can be caused by improperly
installed cables. These emergency float kits utilize a system of cables
to activate and release compressed gas from the float cylinders into
the floats. Proper installation of the cables allows the two float
cylinders installed on the aircraft to activate simultaneously,
allowing for proper distribution of gas to all floats in the system.
Improperly installed cables, if not addressed, could result in loss of
the left or right-hand float, causing the helicopter to roll to one
side but remain buoyant, or loss of both floats, causing the helicopter
to capsize underwater.
Accordingly, the FAA issued AD 2020-02-23, Amendment 39-21027 (85
FR 8150, February 13, 2020) (AD 2020-02-23), for Airbus Helicopters
Model AS350B, AS350BA, AS350B1, AS350B2, AS350B3, AS350C, AS350D, and
AS350D1 helicopters modified by STC SR00470LA, and Airbus Helicopters
Model AS355E, AS355F, AS355F1, AS355F2, AS355N, and AS355NP helicopters
modified by STC SR00645LA. AD 2020-02-23 requires repetitive
inspections of the installation of the cables on the emergency float
kits. After AD 2020-02-23 was issued, the National Transportation
Safety Board reported that similar deficiencies may remain unresolved
in other similar FAA-approved emergency flotation systems.\1\
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\1\ NTSB Investigation; Inadvertent Activation of the Fuel
Shutoff Lever, Subsequent Loss of Engine Power, and Ditching on the
East River, Liberty Helicopters Inc. This information may be viewed
under 2.4.3 Certification Review Process, of Docket Item #79 NTSB--
Adopted Board Report, which is available at <a href="https://data.ntsb.gov/Docket/?NTSBNumber=ERA18MA099">https://data.ntsb.gov/Docket/?NTSBNumber=ERA18MA099</a>.
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Additionally, after AD 2020-02-23 was issued, the FAA determined
additional design approval holders that use the same float activation
pull system may have similar deployment mechanism deficiencies as the
unsafe condition addressed in AD 2020-02-23. Consequently, this
proposed AD would require repetitively inspecting the pull force on the
float activation handle to detect and address improperly installed
cables and, depending on the results, accomplishing corrective actions.
This condition, if not addressed, could result in loss of the left-hand
or right-hand float, causing the helicopter to roll to one side, or
loss of both floats, causing the helicopter to capsize underwater.
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 designs.
Related Service Information Under 1 CFR Part 51
The FAA reviewed DART Aerospace Operation Instructional Manual for
General Pull Cable Rigging and Testing Procedure, Revision A, dated
December 23, 2020. This service information specifies procedures for
testing the pull cable rigging on the DART Aerospace emergency float
and liferaft systems using certain part-numbered pull cable test tools.
The FAA also reviewed DART Aerospace Service Bulletin (SB) No.
SB2020-09, Revision A, dated March 16, 2021, DART Aerospace SB No.
SB2021-01, Revision A, dated December 28, 2021, DART Aerospace SB No.
SB2021-02, dated April 30, 2021, DART Aerospace SB No. SB2021-03, dated
June 30, 2021, and DART Aerospace SB No. SB2022-01, dated March 14,
2022. This service information specifies procedures for inspecting the
installation of the cable emergency float kits (e.g., inspecting for
activation pull forces on the float activation handle), readjusting the
cable rigging if improperly installed, and contacting DART if
readjusting the rigging is not successful. This service information
also specifies optional procedures for deactivating the emergency float
system as inoperative and reporting compliance to DART.
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 ADDRESSES.
Other Related Service Information
The FAA reviewed DART Aerospace SB No. SB 2022-03, dated May 12,
2023, for Model R44 and R44 II helicopters, which specifies procedures
for removing and replacing certain-part numbered reservoirs and cables
with new part-numbered reservoirs and cables. This service information
also specifies procedures for revising the rotorcraft flight manual and
recording compliance with the service information in the aircraft
logbook.
Proposed AD Requirements in This NPRM
This proposed AD would require repetitively inspecting the
installation of the cables on certain emergency float systems and,
depending on the results, repairing the cable installation or,
deactivating and placarding the emergency float system as inoperative.
For certain helicopters, this proposed AD would also require removing
from service and replacing certain part-numbered reservoirs and cables
with other part-numbered reservoirs and cables. Additionally, this
proposed AD would prohibit installing certain part-numbered reservoirs
and cables on certain helicopters.
Differences Between This Proposed AD and the Service Information
The service information specifies a one-time pull cable test,
whereas this proposed AD would require repetitively inspecting the pull
force on the float activation handle.
Where the service information specifies contacting DART, this
proposed AD would require actions in accordance with FAA-approved
procedures.
Appendix A of the service information specifies to ty-wrap the pin
into place on the pilot collective and contacting DART customer service
for a resolution, whereas this proposed AD would require accomplishing
corrective actions in accordance with FAA-approved procedures.
Costs of Compliance
The FAA estimates that this AD, if adopted as proposed, would
affect 1,150 emergency float kits or emergency float with liferaft kits
installed on 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.
Inspecting the pull force on the float activation handle would take
approximately 1 work-hour with one test kit costing approximately
$2,000 for an estimated cost of $2,085 per helicopter and $2,397,750
for the U.S. fleet, per inspection cycle.
Replacing a reservoir and cable (Model R44 and R44 II helicopters)
would take approximately 2 work-hours and parts would cost
approximately $5,800 for an estimated cost of $5,970 per helicopter.
The FAA has no way of determining what repairs may be required
following the inspection required by this proposed AD, the number of
helicopters that may need repairs, or the costs to perform repairs.
However, if required as a repair, replacing and adjusting an affected
cable would take approximately 8 work-hours and parts would cost
approximately $255 for an estimated cost of $935 per helicopter.
[[Page 31661]]
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:
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:
Various Helicopters: Docket No. FAA-2024-1004; Project Identifier
AD-2023-01058-R.
(a) Comments Due Date
The FAA must receive comments on this airworthiness directive
(AD) by June 10, 2024.
(b) Affected ADs
None.
(c) Applicability
This AD applies to the helicopters identified in paragraphs
(c)(1) through (8) of this AD, certificated in any category.
(1) Airbus Helicopters Model AS350B, AS350BA, AS350B1, AS350B2,
AS350B3, AS350C, AS350D, AS350D1, AS355E, AS355F, AS355F1, AS355F2,
and AS355N helicopters modified by Supplemental Type Certificate
(STC) SR00831LA; Model EC120B helicopters modified by STC SR00780LA;
and Model EC130B4 helicopters modified by STC SR01687LA.
Note 1 to paragraph (c)(1): Helicopters with an AS350B3e
designation are Model AS350B3 helicopters.
(2) Airbus Helicopters Deutschland GmbH (AHD) Model BO-105A, BO-
105C, BO-105S, and BO-105LS A-3 helicopters modified by STC
SR00856LA; Model EC135P1, EC135P2, EC135P2+, EC135P3, EC135T1,
EC135T2, EC135T2+, and EC135T3 helicopters modified by STC
SR01855LA; and Model MBB-BK 117 C-2 and MBB-BK 117 D-2 helicopters
modified by STC SR02244LA.
Note 2 to paragraph (c)(2): Helicopters with an EC135P3H
designation are Model EC135P3 helicopters; helicopters with an
EC135T3H designation are Model EC135T3 helicopters; and helicopters
with an MBB-BK117 C-2e designation are Model MBB-BK117 C-2
helicopters.
(3) Bell Textron Inc., Model 210, 212, 412, 412CF, and 412EP
helicopters modified by STC SR01779LA; and Model 412, 412CF, and
412EP helicopters modified by STC SR01459LA.
(4) Bell Textron Canada Limited Model 206A, 206B, 206L, 206L-1,
206L-3, 206L-4, and 407 helicopters modified by STC SR01535LA.
Note 3 to paragraph (c)(4): Helicopters with a 206B3 designation
are Model 206B helicopters; helicopters with a 206L-1+ designation
are Model 206L-1 helicopters; and helicopters with a 206L-3+
designation are Model 206L-3 helicopters.
(5) Leonardo S.p.a. Model AB412 and AB412 EP helicopters
modified by STC SR01779LA.
(6) MD Helicopters, LLC, Model 369D, 369E, 369F, 369FF, 369HE,
369HM, 369HS, and 500N helicopters modified by STC SR00932LA.
(7) Robinson Helicopter Company Model R44 and R44 II helicopters
modified by STC SR02049LA; and Model R66 helicopters modified by STC
SR02484LA.
(8) Sikorsky Aircraft Corporation Model S-76A, S-76B, and S-76C
helicopters modified by STC SR01902LA.
(d) Subject
Joint Aircraft System Component (JASC) Code: 2560, Emergency
Equipment; and 3212, Emergency Flotation Section.
(e) Unsafe Condition
This AD was prompted by the results of an accident investigation
and subsequent reports of difficulty pulling the emergency float kit
float activation handle installed on the pilot cyclic. The FAA is
issuing this AD to detect and address improperly installed cables,
which can lead to difficulty deploying the float system from the
float activation handle. The unsafe condition, if not addressed,
could result in loss of the left-hand or right-hand float, causing
the helicopter to roll to one side, or loss of both floats causing
the helicopter to capsize underwater.
(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) or 30 days after the
effective date of this AD, whichever occurs first, and thereafter at
intervals not to exceed six months, accomplish the actions required
by paragraphs (g)(1)(i) through (vi) of this AD, as applicable to
your model helicopter.
(i) For Airbus Helicopters Model EC130B4 helicopters identified
in paragraph (c)(1) of this AD, accomplish the actions required by
paragraphs (g)(1)(i)(A) or (B) of this AD, as applicable, and
paragraph (g)(1)(i)(C) of this AD, as applicable.
(A) Inspect the pull force on the float activation handle in
accordance with section 2.0 (for pull cable test tool part-number
(P/N) 606.7803), paragraphs 1 through 14 of DART Aerospace Operation
Instructional Manual for General Pull Cable Rigging and Testing
Procedure, Revision B, dated May 12, 2023 (DART OIM-11 Rev B),
except if the inflation handle makes contact with the cyclic stick
in paragraph 6, before further flight, perform cable rigging in
accordance with FAA-approved procedures and, once the cable is
properly rigged, continue with the actions required by this
paragraph, and except the measurement in paragraph 8 must be 0.85 in
(2.16 cm) or greater; or
(B) Inspect the pull force on the float activation handle in
accordance with section 3.0 (for pull cable test tool P/N 607.1602),
paragraphs 3 through 20 of DART OIM-11 Rev B, except in paragraph 3,
where it states, ``it is advised to mark these locations and verify
the hole centers by removing the two set screws from the test tool
and sliding the tool onto the shroud and aligning the tool with the
marks,'' replace that text with ``mark these locations and verify
the hole centers by removing the two set screws from the test tool
and sliding the tool onto the shroud and aligning the tool with the
marks,'' and except the measurement in paragraph 13 must be 0.75 in
(1.91 cm) or greater.
[[Page 31662]]
(C) If the pull force is greater than 25 lbf (111.2N) or exceeds
the limits in the existing Installation Instructions or Instructions
for Continued Airworthiness for your helicopter, as applicable,
before further flight, comply with paragraph (g)(2) of this AD, as
applicable to your model helicopter.
(ii) For Airbus Helicopters Deutschland GmbH (AHD) Model MBB-BK
117 C-2 and MBB-BK 117 D-2 helicopters identified in paragraph
(c)(2) of this AD, accomplish the actions required by paragraphs
(g)(1)(ii)(A) and (B) of this AD, as applicable.
(A) Inspect the pull force on the float activation handle in
accordance with section 2.0 (for pull cable test tool P/N 606.7803),
paragraphs 1 through 14 of DART OIM-11 Rev B, except if the
inflation handle makes contact with the cyclic stick in paragraph 6,
before further flight perform cable rigging in accordance with FAA-
approved procedures, and except the measurement in paragraph 8 must
be 0.85 in (2.16 cm) or greater.
(B) If the pull force is greater than 25 lbf (111.2N), or
exceeds the limits in the existing Installation Instructions or
Instructions for Continued Airworthiness for your helicopter, as
applicable, before further flight, comply with paragraph (g)(2) of
this AD, as applicable to your model helicopter.
(iii) For Bell Textron Inc., Model 210, 212, 412, 412CF, and
412EP helicopters identified in paragraph (c)(3) of this AD,
accomplish the actions required by paragraphs (g)(1)(iii)(A) or (B)
of this AD, as applicable, and paragraph (g)(1)(iii)(C) of this AD,
as applicable.
(A) Inspect the pull force on the float activation handle in
accordance with section 2.0 (for pull cable test tool P/N 606.7803),
paragraphs 1 through 14 of DART OIM-11 Rev B, except if the
inflation handle makes contact with the cyclic stick in paragraph 6,
before further flight perform cable rigging in accordance with FAA-
approved procedures, and except the measurement in paragraph 8 must
be 0.85 in (2.16 cm) or greater; or
(B) Inspect the pull force on the float activation handle in
accordance with section 3.0 (for pull cable test tool P/N 607.1602),
paragraphs 3 through 20 of DART OIM-11 Rev B, except in paragraph 3,
where it states, ``it is advised to mark these locations and verify
the hole centers by removing the two set screws from the test tool
and sliding the tool onto the shroud and aligning the tool with the
marks.'' replace that text with ``mark these locations and verify
the hole centers by removing the two set screws from the test tool
and sliding the tool onto the shroud and aligning the tool with the
marks,'' and except the measurement in paragraph 13 must be 0.75 in
(1.91 cm) or greater.
(C) If the pull force is greater than 25 lbf (111.2N), or
exceeds the limits in the existing Installation Instructions or
Instructions for Continued Airworthiness for your helicopter, as
applicable, before further flight, comply with paragraph (g)(2) of
this AD, as applicable to your model helicopter.
(iv) For Bell Textron Canada Limited Model 206A, 206B, 206L,
206L-1, 206L-3, 206L-4, and 407 helicopters identified in paragraph
(c)(4) of this AD, accomplish the actions required by paragraphs
(g)(1)(iv)(A) and (B) of this AD, as applicable.
(A) Inspect the pull force on the float activation handle in
accordance with section 2.0 (for pull cable test tool P/N 606.7803),
paragraphs 1 through 14 of DART OIM-11 Rev B, except if the
inflation handle makes contact with the cyclic stick in paragraph 6,
before further flight perform cable rigging in accordance with FAA-
approved procedures, and except the measurement in paragraph 8 must
be 0.85 in (2.16 cm) or greater.
(B) If the pull force is greater than 25 lbf (111.2N), or
exceeds the limits in the existing Installation Instructions or
Instructions for Continued Airworthiness for your helicopter, as
applicable, before further flight, comply with paragraph (g)(2) of
this AD, as applicable to your model helicopter.
(v) For Robinson Helicopter Company Model R66 helicopters
identified in paragraph (c)(7) of this AD, accomplish the actions
required by paragraphs (g)(1)(v)(A) and (B) of this AD, as
applicable.
(A) Inspect the pull force on the float activation handle in
accordance with section 2.0 (for pull cable test tool P/N 607.7803),
paragraphs 1 through 14 of DART OIM-11 Rev B, except if the
inflation handle makes contact with the cyclic stick in paragraph 6,
before further flight perform cable rigging in accordance with FAA-
approved procedures, and except the measurement in paragraph 8 must
be 0.85 in (2.16 cm) or greater.
(B) If the pull force is greater than 25 lbf (111.2N), or
exceeds the limits in the existing Installation Instructions or
Instructions for Continued Airworthiness for your helicopter, as
applicable, before further flight, comply with paragraph (g)(2) of
this AD, as applicable to your model helicopter.
(vi) For the helicopters identified in paragraphs (g)(1)(vi)(A)
through (E) of this AD, inspect the pull force on the float
activation handle in accordance with FAA-approved procedures. The
threshold for this pull force inspection must not exceed 25 lbf
(111.2N). If the float activation handle fails the test, (if the
pull force is greater than 25 lbf (111.2N)), or exceeds the limits
in the existing Installation Instructions or Instructions for
Continued Airworthiness for your helicopter, as applicable, before
further flight, comply with paragraph (g)(2) of this AD, as
applicable to your model helicopter.
(A) Airbus Helicopters Model AS350B, AS350BA, AS350B1, AS350B2,
AS350B3, AS350C, AS350D, AS350D1, AS355E, AS355F, AS355F1, AS355F2,
AS355N, and EC120B helicopters identified in paragraph (c)(1) of
this AD.
(B) Airbus Helicopters Deutschland GmbH (AHD) Model BO-105A, BO-
105C, BO-105S, BO-105LS A-3, EC135P1, EC135P2, EC135 P2+, EC135P3,
EC135T1, EC135T2, EC135T2+, and EC135T3 helicopters identified in
paragraph (c)(2) of this AD.
(C) Leonardo S.p.a. Model AB412 and AB412 EP helicopters
identified in paragraph (c)(5) of this AD.
(D) MD Helicopters, LLC, Model 369D, 369E, 369F, 369FF, 369HE,
369HM, 369HS, and 500N helicopters identified in paragraph (c)(6) of
this AD.
(E) Sikorsky Aircraft Corporation Model S-76A, S-76B, and S-76C
helicopters identified in paragraph (c)(8) of this AD.
(2) For the helicopters identified in paragraphs (g)(1)(i)
through (v) of this AD, as a result of the actions required by
paragraphs (g)(1)(i) through (v) of this AD, if the pull force is
greater than 25 lbf (111.2N), or exceeds the limits in the existing
Installation Instructions or Instructions for Continued
Airworthiness for your helicopter, as applicable, before further
flight, comply with either paragraph (g)(2)(i) or (ii) of this AD.
(i) Repair the cable installation in accordance with FAA-
approved procedures.
(ii) Deactivate and placard the emergency float system as
inoperative in accordance with Appendix A of DART Aerospace Service
Bulletin (SB) No. SB2020-09, Revision A, dated March 16, 2021, DART
Aerospace SB No. SB2021-01, Revision A, dated December 28, 2021,
DART Aerospace SB No. SB2021-02, dated April 30, 2021, DART
Aerospace SB No. SB2021-03, dated June 30, 2021, or DART Aerospace
SB No. SB2022-01, dated March 14, 2022, as applicable to your model
helicopter, except where Appendix A specifies ty-wrapping the pin
into place on the pilot collective, and where Appendix A specifies
contacting DART customer service for a resolution, accomplish the
deactivation and placarding in accordance with FAA-approved
procedures. If the emergency float system is deactivated and
placarded as inoperative, you are not required to accomplish the
actions required by paragraph (g)(1) of this AD. This AD does not
allow operation with an inoperative emergency float system unless
the requirements of 14 CFR 91.205, 91.213, 135.183, and 136.11 have
been met.
(3) For the helicopters identified in paragraphs (g)(1)(vi)(A)
through (E) of this AD, as a result of the actions required by the
introductory text of paragraph (g)(1)(vi) of this AD, if the pull
force is greater than 25 lbf (111.2N), before further flight, repair
the cable installation, or deactivate and placard the emergency
float system as inoperative in accordance with FAA-approved
procedures.
(4) For Robinson Helicopter Company Model R44 and R44 II
helicopters identified in paragraph (c)(7) of this AD, within 36
months or at the next float inflation reservoir (reservoir) overhaul
after the effective date of this AD, whichever occurs first, perform
the requirements in paragraphs (g)(4)(i) and (ii) of this AD.
Thereafter, within intervals not to exceed six months, repeat the
actions required by paragraph (g)(4)(ii) of this AD.
(i) Remove cable P/N 644.7501 or P/N 644.7502 from service, as
applicable, and replace with cable P/N 644.7503; and remove each
reservoir P/N 644.7701 from service and replace with reservoir P/N
644.7702 or P/N 644.7703.
(ii) Inspect the pull force on the float activation handle in
accordance with FAA-approved procedures. The threshold for this pull
force inspection must not exceed 25 lbf (111.2N). If the pull cable
installation fails the test (if the pull force is greater than 25
lbf (111.2N)), before further flight, repair the cable installation,
or deactivate and placard the emergency float system as inoperative
in accordance with FAA-approved procedures.
(5) As of the effective date of this AD, do not install
reservoir P/N 644.7701 and cable P/N 644.7501 or reservoir P/N
644.7701 and cable P/N 644.7502 on any Robinson Helicopter Company
Model R44 or R44 II helicopter.
[[Page 31663]]
(h) 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 (i) of this AD.
Information may be emailed to: <a href="/cdn-cgi/l/email-protection#655c48242b2848292424262a4824282a26483720343020363136250304044b020a13"><span class="__cf_email__" data-cfemail="3e07137f707313727f7f7d71137f73717d136c7b6f6b7b6d6a6d7e585f5f10595148">[email protected]</span></a>.
(2) Before using any approved AMOC, notify your appropriate
principal inspector, or lacking a principal inspector, the manager
of the local flight standards district office/certificate holding
district office.
(i) Additional Information
For more information about this AD, contact Johann Magana,
Aviation Safety Engineer, FAA, 3960 Paramount Boulevard, Lakewood,
CA 90712; phone: (562) 627-5322; email: <a href="/cdn-cgi/l/email-protection#99f3f6f1f8f7f7b7f4f8fef8f7f8d9fff8f8b7fef6ef"><span class="__cf_email__" data-cfemail="761c191e171818581b17111718173610171758111900">[email protected]</span></a>.
(j) 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) DART Aerospace Operation Instructional Manual for General
Pull Cable Rigging and Testing Procedure, Revision B, dated May 12,
2023.
(ii) DART Aerospace Service Bulletin (SB) No. SB2020-09,
Revision A, dated March 16, 2021.
(iii) DART Aerospace SB No. SB2021-01, Revision A, dated
December 28, 2021.
(iv) DART Aerospace SB No. SB2021-02, dated April 30, 2021.
(v) DART Aerospace SB No. SB2021-03, dated June 30, 2021.
(vi) DART Aerospace SB No. SB2022-01, dated March 14, 2022.
(3) For service information identified in this AD, contact Dart
Aerospace, LTD., 1270 Aberdeen St., Hawkesbury, ON, K6A 1K7, Canada;
phone: 1-613-632-5200; Fax: 1-613-632-5246; or at <a href="http://dartaero.com">dartaero.com</a>.
(4) You may view this service information at the FAA, Office of
the Regional Counsel, Southwest Region, 10101 Hillwood Parkway, Room
6N-321, Fort Worth, TX 76177. For information on the availability of
this material at the FAA, call (817) 222-5110.
(5) You may view this material at the National Archives and
Records Administration (NARA). For information on the availability
of this material at NARA, visit <a href="http://www.archives.gov/federal-register/cfr/ibr-locations">www.archives.gov/federal-register/cfr/ibr-locations</a> or email <a href="/cdn-cgi/l/email-protection#97f1e5b9fef9e4e7f2f4e3fef8f9d7f9f6e5f6b9f0f8e1"><span class="__cf_email__" data-cfemail="ea8c98c48384999a8f899e838584aa848b988bc48d859c">[email protected]</span></a>.
Issued on April 15, 2024.
Victor Wicklund,
Deputy Director, Compliance & Airworthiness Division, Aircraft
Certification Service.
[FR Doc. 2024-08893 Filed 4-24-24; 8:45 am]
BILLING CODE 4910-13-P
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</html>Indexed from Federal Register on April 25, 2024.
This is legal information, not legal advice. Laws vary by jurisdiction and change frequently. Always verify current law with official sources and consult a licensed attorney in your jurisdiction for advice on your specific situation.