(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 helicop-
ters 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 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 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, 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 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
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.
(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:
AMOC@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) 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: johann.magana@faa.gov.
(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 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 October 28, 2024. Victor Wicklund, Deputy Director, Compliance &
Airworthiness Division, Aircraft Certification Service.
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.
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2024-1004; Project Identifier AD-2023-01058-R;
Amendment 39-22866; AD 2024-20-07]
RIN 2120-AA64
Airworthiness Directives; Various Helicopters
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Final rule.
-----------------------------------------------------------------------
SUMMARY: The FAA is adopting a new airworthiness directive (AD) for
various helicopters modified by certain supplemental type certificates
(STCs) that approve the installation of an emergency float kit or an
emergency float with a liferaft kit. This AD was prompted by the
results of an accident investigation and subsequent reports of
difficulty pulling the emergency float kit activation handle installed
on the pilot cyclic. This AD requires repetitively inspecting the pull
force on the float activation handle and for certain model helicopters,
this AD also requires and replacing certain part-numbered float
inflation reservoirs (reservoirs) and pull cable assemblies (cables)
with other part-numbered reservoirs and cables. Finally, this AD
prohibits installing certain part-numbered reservoirs and cables on
specific helicopters. The FAA is issuing this AD to address the unsafe
condition on these products.
DATES: This AD is effective December 5, 2024.
The Director of the Federal Register approved the incorporation by
reference of certain publications listed in this AD as of December 5, 2024.
ADDRESSES:
AD Docket: You may examine the AD docket at 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:
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.
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: johann.magana@faa.gov.
SUPPLEMENTARY INFORMATION:
Background
The FAA received reports of an accident involving an Airbus
Helicopters Model AS350B2 helicopter impacting a body of water during
an autorotation. Both the left and right-hand emergency floats did not
inflate symmetrically, and the helicopter subsequently capsized.
Accordingly, the FAA issued AD 2020-02-23, Amendment 39-21027 (85
FR 8150, February 13, 2020) (AD 2020-02-23), for Airbus Helicopters
Model AS350B, AS350BA, AS350B1, AS350B2, AS350B3, AS350C, AS350D, and
AS350D1 helicopters modified by STC SR00470LA, and Airbus Helicopters
Model AS355E, AS355F, AS355F1, AS355F2, AS355N, and AS355NP helicopters
modified by STC SR00645LA. AD 2020-02-23 requires repetitive
inspections of the installation of the cables on the emergency float
kits. After AD 2020-02-23 was issued, the National Transportation
Safety Board (NTSB) reported that similar deficiencies may remain
unresolved in other similar FAA-approved emergency flotation
systems.\1\
---------------------------------------------------------------------------
\1\ NTSB Investigation; Inadvertent Activation of the Fuel
Shutoff Lever, Subsequent Loss of Engine Power, and Ditching on the
East River, Liberty Helicopters Inc. This information may be viewed
under 2.4.3 Certification Review Process, of Docket Item #79 NTSB--
Adopted Board Report, which is available at
https://data.ntsb.gov/Docket/?NTSBNumber=ERA18MA099.
---------------------------------------------------------------------------
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.
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
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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