(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 designa-
tion 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 al-
ready 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 para-
graph (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 Man-
ual 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 proce-
dures and, once the cable is properly rigged, continue with the
actions required by this paragraph, and except the measurement in par-
agraph 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 lim-
its in the existing Installation Instructions or Instructions for Con-
tinued Airworthiness for your helicopter, as applicable, before furth-
er 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 helicop-
ters 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 para-
graphs (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 pro-
cedures.
(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 install-
ation, or deactivate and placard the emergency float system as inoper-
ative in accordance with FAA-approved procedures.
(4) For Robinson Helicopter Company Model R44 and R44 II helicopters ident
-ified 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 in-
spection must not exceed 25 lbf (111.2N). If the pull cable installa-
tion fails the test (if the pull force is greater than 25 lbf (111.
2N)), before further flight, repair the cable installation, or de-
activate 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 heli-
copter.
(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:
9-ANM-LAACO-AMOC-REQUESTS@faa.gov.
(2) Before using any approved AMOC, notify your appropriate principal in-
spector, 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: johann.magana@faa.gov.
(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 Re-
gional Counsel, Southwest Region, 10101 Hillwood Parkway, Room 6N-321,
Fort Worth, TX 76177. For information on the availability of this ma-
terial at the FAA, call (817) 222-5110.
(5) You may view this material at the National Archives and Records Admin-
istration (NARA). For information on the availability of this material
at NARA, visit www.archives.gov/federal-register/cfr/ibr-locations or
email fr.inspection@nara.gov.
Issued on April 15, 2024. Victor Wicklund, Deputy Director, Compliance &
Airworthiness Division, Aircraft Certification Service.
DATES: The FAA must receive comments on this proposed AD by June 10, 2024.
|
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: johann.magana@faa.gov.
SUPPLEMENTARY INFORMATION:
Comments Invited
The FAA invites you to send any written relevant data, views, or
arguments about this proposal. Send your comments to an address listed
under ADDRESSES. Include ``Docket No. FAA-2024-1004; 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:
johann.magana@faa.gov. Any commentary that the FAA receives which is
not specifically designated as CBI will be placed in the public docket
for this rulemaking.
Background
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.
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.
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
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]
2. The FAA amends Sec. 39.13 by adding the following new airworthiness
directive:
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