Rule2024-25390
Airworthiness Directives; Various Helicopters
Primary source
Metadata and text below are from the Federal Register, a public-domain U.S. government work. Always verify the official published version before relying on it for any legal matter.
Published
October 31, 2024
Effective
December 5, 2024
Issuing agencies
Transportation DepartmentFederal Aviation Administration
Abstract
The FAA is adopting 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 a liferaft kit. This AD was prompted by the results of an accident investigation and subsequent reports of difficulty pulling the emergency float kit activation handle installed on the pilot cyclic. This AD requires repetitively inspecting the pull force on the float activation handle and for certain model helicopters, this AD also requires and replacing certain part-numbered float inflation reservoirs (reservoirs) and pull cable assemblies (cables) with other part-numbered reservoirs and cables. Finally, this AD prohibits installing certain part-numbered reservoirs and cables on specific helicopters. The FAA is issuing this AD to address the unsafe condition on these products.
Full Text
<html>
<head>
<title>Federal Register, Volume 89 Issue 211 (Thursday, October 31, 2024)</title>
</head>
<body><pre>
[Federal Register Volume 89, Number 211 (Thursday, October 31, 2024)]
[Rules and Regulations]
[Pages 86717-86721]
From the Federal Register Online via the Government Publishing Office [<a href="http://www.gpo.gov">www.gpo.gov</a>]
[FR Doc No: 2024-25390]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2024-1004; Project Identifier AD-2023-01058-R;
Amendment 39-22866; AD 2024-20-07]
RIN 2120-AA64
Airworthiness Directives; Various Helicopters
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Final rule.
-----------------------------------------------------------------------
SUMMARY: The FAA is adopting 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 a liferaft kit. This AD was prompted by the
results of an accident investigation and subsequent reports of
difficulty pulling the emergency float kit activation handle installed
on the pilot cyclic. This AD requires repetitively inspecting the pull
force on the float activation handle and for certain model helicopters,
this AD also requires and replacing certain part-numbered float
inflation reservoirs (reservoirs) and pull cable assemblies (cables)
with other part-numbered reservoirs and cables. Finally, this AD
prohibits installing certain part-numbered reservoirs and cables on
specific helicopters. The FAA is issuing this AD to address the unsafe
condition on these products.
DATES: This AD is effective December 5, 2024.
The Director of the Federal Register approved the incorporation by
reference of certain publications listed in this AD as of December 5,
2024.
ADDRESSES:
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 final rule, 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.
Material Incorporated by Reference:
<bullet> For Dart Aerospace material identified in this AD, contact
Dart Aerospace, LTD., 1270 Aberdeen Street, Hawkesbury, ON, K6A 1K7,
Canada; phone: 1-613-632-5200; fax: 1-613-632-5246; website:
<a href="http://dartaero.com">dartaero.com</a>.
[[Page 86718]]
<bullet> You may view this material 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
material identified in this final rule, use the Dart Aerospace, LTD.,
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#d5bfbabdb4bbbbfbb8b4b2b4bbb495b3b4b4fbb2baa3"><span class="__cf_email__" data-cfemail="e3898c8b828d8dcd8e8284828d82a3858282cd848c95">[email protected]</span></a>.
SUPPLEMENTARY INFORMATION:
Background
The FAA received reports of an accident involving an Airbus
Helicopters Model AS350B2 helicopter impacting a body of water during
an autorotation. Both the left and right-hand emergency floats did not
inflate symmetrically, and the helicopter subsequently capsized.
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 (NTSB) reported that similar deficiencies may remain
unresolved in other similar FAA-approved emergency flotation
systems.\1\
---------------------------------------------------------------------------
\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>.
---------------------------------------------------------------------------
Accordingly, the FAA issued a notice of proposed rulemaking (NPRM)
to amend 14 CFR part 39 by adding an AD that would apply to various
helicopters modified by certain STCs that approve the installation of
an emergency float kit or an emergency float with a liferaft kit. The
NPRM published in the Federal Register on April 25, 2024 (89 FR 31659).
In the NPRM, the FAA proposed to 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 specific helicopters, the FAA also proposed to require removing
from service and replacing certain part-numbered reservoirs and cables
with other part-numbered reservoirs and cables. Additionally, the FAA
proposed to prohibit installing certain part-numbered reservoirs and
cables on certain helicopters. The FAA is issuing this AD to address
the unsafe condition on these products.
Discussion of Final Airworthiness Directive
Comments
The FAA received a comment on the NPRM from the NTSB. The NTSB
supported the NPRM without change.
Conclusion
The FAA reviewed the relevant data, considered the comment
received, and determined that air safety requires adopting the AD as
proposed. Accordingly, the FAA is issuing this AD to address the unsafe
condition on these products. Except for minor editorial changes, this
AD is adopted as proposed in the NPRM.
Material Incorporated by Reference Under 1 CFR Part 51
The FAA reviewed DART Aerospace Operation Instructional Manual for
General Pull Cable Rigging and Testing Procedure, Revision B, dated May
12, 2023. This material 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 material 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 material also specifies
optional procedures for deactivating the emergency float system as
inoperative and reporting compliance to DART.
This material is reasonably available because the interested
parties have access to it through their normal course of business or by
the means identified in the ADDRESSES section.
Other Related Material
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 material also
specifies procedures for revising the rotorcraft flight manual and
recording compliance with the material in the aircraft logbook.
Differences Between This AD and the Related Material
The related material specifies a one-time pull cable test, whereas
this AD requires repetitively inspecting the pull force on the float
activation handle.
Where the related material specifies contacting DART, this AD
requires actions in accordance with FAA-approved procedures.
Appendix A of the related material specifies to ty-wrap the pin
into place on the pilot collective and to contact DART customer service
for a resolution, whereas this AD requires accomplishing corrective
actions in accordance with FAA-approved procedures.
Costs of Compliance
The FAA estimates that this AD affects 1,150 emergency float kits
or emergency float with liferaft kits installed on helicopters of U.S.
registry. Labor costs are estimated at $85 per work-hour. Based on
these numbers, the FAA estimates the following costs to comply with
this AD.
Inspecting the pull force on the float activation handle will take
1 work-hour with one test kit costing $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)
will take 2 work-hours and parts will cost $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 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 will
take 8 work-hours and parts will cost $255 for an estimated total cost
of $935 per helicopter.
[[Page 86719]]
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
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 above, 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.
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:
2024-20-07 Various Helicopters: Amendment 39-22866; Docket No. FAA-
2024-1004; Project Identifier AD-2023-01058-R.
(a) Effective Date
This airworthiness directive (AD) is effective December 5, 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.
(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,
[[Page 86720]]
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 86721]]
(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#3d7c70727e7d5b5c5c135a524b"><span class="__cf_email__" data-cfemail="90d1dddfd3d0f6f1f1bef7ffe6">[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) Related 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#670d080f060909490a06000609062701060649000811"><span class="__cf_email__" data-cfemail="d8b2b7b0b9b6b6f6b5b9bfb9b6b998beb9b9f6bfb7ae">[email protected]</span></a>.
(j) Material Incorporated by Reference
(1) The Director of the Federal Register approved the
incorporation by reference of the material listed in this paragraph
under 5 U.S.C. 552(a) and 1 CFR part 51.
(2) You must use this material 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 material identified in this AD, contact Dart Aerospace,
LTD., 1270 Aberdeen Street, Hawkesbury, ON, K6A 1K7, Canada; phone:
1-613-632-5200; fax: 1-613-632-5246; website: <a href="http://dartaero.com">dartaero.com</a>.
(4) You may view this material 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#4b2d39652225383b2e283f2224250b252a392a652c243d"><span class="__cf_email__" data-cfemail="7d1b0f5314130e0d181e091412133d131c0f1c531a120b">[email protected]</span></a>.
Issued on October 28, 2024.
Victor Wicklund,
Deputy Director, Compliance & Airworthiness Division, Aircraft
Certification Service.
[FR Doc. 2024-25390 Filed 10-30-24; 8:45 am]
BILLING CODE 4910-13-P
</pre><script data-cfasync="false" src="/cdn-cgi/scripts/5c5dd728/cloudflare-static/email-decode.min.js"></script></body>
</html>Indexed from Federal Register on October 31, 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.