[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 [www.gpo.gov]
[FR Doc No: 2024-25390]


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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.

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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 regulations.gov 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: 
dartaero.com.

[[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\
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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 https://data.ntsb.gov/Docket/?NTSBNumber=ERA18MA099.
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    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: dartaero.com.
    (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 www.archives.gov/federal-register/cfr/ibr-locations 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


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