Airworthiness Directives; Various Helicopters, 31659-31663 [2024-08893]

Agencies

• Federal Aviation Administration
• DEPARTMENT OF TRANSPORTATION

[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 [www.gpo.gov]
[FR Doc No: 2024-08893]


========================================================================
Proposed Rules
                                                Federal Register
________________________________________________________________________

This section of the FEDERAL REGISTER contains notices to the public of 
the proposed issuance of rules and regulations. The purpose of these 
notices is to give interested persons an opportunity to participate in 
the rule making prior to the adoption of the final rules.

========================================================================


Federal Register / Vol. 89, No. 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).

-----------------------------------------------------------------------

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:
     Federal eRulemaking Portal: Go to regulations.gov. Follow 
the instructions for submitting comments.
     Fax: (202) 493-2251.
     Mail: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue SE, Washington, DC 20590.
     Hand Delivery: Deliver to Mail address above between 9 
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
    AD Docket: You may examine the AD docket at regulations.gov under 
Docket No. FAA-2024-1004; 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:
     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 
dartaero.com.
     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: [email protected].

SUPPLEMENTARY INFORMATION: 

Comments Invited

    The FAA invites you to send any written relevant data, views, or 
arguments about this proposal. Send your comments to an address listed 
under ADDRESSES. Include ``Docket No. FAA-2024-1004; 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 
regulations.gov, including any personal information you provide. The 
agency will also post a report summarizing each substantive verbal 
contact received about this NPRM.

Confidential Business Information

    CBI is commercial or financial information that is both customarily 
and actually treated as private by its owner. Under the Freedom of 
Information Act (FOIA) (5 U.S.C. 552), CBI is exempt from public 
disclosure. If your comments responsive to this NPRM contain commercial 
or financial information that is customarily treated as private, that 
you actually treat as private, and that is relevant or responsive to 
this NPRM, it is important that you clearly designate the submitted 
comments as CBI. Please mark each page of your submission containing 
CBI as ``PROPIN.'' The FAA will treat such marked submissions as 
confidential under the FOIA, and they will not be placed in the public 
docket of this NPRM. Submissions containing CBI should be sent to 
Johann Magana, Aviation Safety Engineer, FAA, 3960 Paramount Boulevard, 
Lakewood, CA 90712; phone: (562) 627-5322; email: 
[email protected]. Any commentary that the FAA receives which is 
not specifically designated as CBI will be placed in the public docket 
for this rulemaking.

Background

    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\
---------------------------------------------------------------------------

    \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.
---------------------------------------------------------------------------

    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: [email protected].
    (2) Before using any approved AMOC, notify your appropriate 
principal inspector, or lacking a principal inspector, the manager 
of the local flight standards district office/certificate holding 
district office.

(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: [email protected].

(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 dartaero.com.
    (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 www.archives.gov/federal-register/cfr/ibr-locations or email [email protected].

    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