Airworthiness Directives; Various Helicopters, 86717-86721 [2024-25390]
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Federal Register / Vol. 89, No. 211 / Thursday, October 31, 2024 / Rules and Regulations
document to make explicit the text
agreed to when these airworthiness
criteria are finalized. The FAA
disagrees, because the 14 CFR
regulations listed in the airworthiness
criteria for the AW609 are incorporated
into the criteria by referencing the
existing rule.
Transport Canada stated that the
formula in proposed TR.725 Limit drop
test, paragraph (d), is incomplete. The
FAA disagrees with Transport Canada.
The formula is correctly stated in the
proposed criteria, and matches the
formula suggested by the commenter.
Transport Canada stated the heading
for proposed TR.103 Stall SPEED is
incorrect and that the term ‘‘SPEED’’
should be lower case and in bold text.
The FAA agrees with Transport Canada
and has corrected the heading in TR.103
in the final airworthiness criteria.
Transport Canada requested the FAA
explain why §§ 25.1701–25.1733 for an
EWIS were not included in the
proposed airworthiness criteria and
requested the FAA add §§ 25.1701–
25.1733. The FAA does not concur with
Transport Canada’s request to include
§§ 25.170–25.1753 in the final
airworthiness criteria as the FAA
updated the final airworthiness criteria
to replace § 25.1353 with § 29.1353 due
to the recent addition of amendment
29–59 which introduced a part 29 safety
target for electrical wiring. The final
airworthiness criteria also contain
§ 29.1301, and TR.1309 which, in
addition to § 29.1353, address similar
requirements to those covered by the
referenced part 25 EWIS and energy
storage requirements.
Transport Canada requested the FAA
clarify whether part 34, Fuel Venting
and Exhaust Emission Requirements For
Turbine Engine Powered Airplanes, is
applicable to the AW609, either to the
engine or aircraft, as fuel venting can be
influenced by the engine’s installation
effects. The FAA acknowledges
Transport Canada’s concern. The
AW609 uses the PT6C–67A, which is a
turboshaft engine. Part 34 does not
apply to turboshaft engines. As long as
the AW609 continues to use a turboshaft
engine, part 34 will not be applicable.
Transport Canada requested the FAA
clarify whether part 38, Airplane Fuel
Efficiency Certification is applicable to
the AW609. The AW609 certification
basis precedes the promulgation of 14
CFR part 38, and thus part 38 is not
applicable to the AW609.
The Advanced Air Mobility Institute
recommended the FAA update and
expand the airworthiness criteria for the
Model AW609 powered-lift to require
the implementation of a mandatory
safety management system (SMS),
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designated as TR criteria. The FAA does
acknowledge the value of
implementation of a proactive SMS
system. However, implementation of
SMS is beyond the scope of this present
effort to designate the applicable
airworthiness criteria for this poweredlift.
DEPARTMENT OF TRANSPORTATION
Applicability
RIN 2120–AA64
These airworthiness criteria,
established under the provisions of
§ 21.17(b), are applicable to the AWPC
Model AW609 powered-lift. Should
AWPC apply at a later date for a change
to the type certificate to include another
model, these airworthiness criteria
would apply to that model as well,
provided the FAA finds them
appropriate in accordance with the
requirements of subpart D to part 21.
Airworthiness Directives; Various
Helicopters
Conclusion
This action affects only certain
airworthiness criteria for the AWPC
Model AW609 powered-lift. It is not a
standard of general applicability.
Authority Citation
The authority citation for these
airworthiness criteria is as follows:
Authority: 49 U.S.C. 106(g), 40113, and
44701–44702, 44704.
Airworthiness Criteria
Pursuant to the authority delegated to
me by the Administrator, the following
airworthiness criteria are issued as part
of the type certification basis for the
AgustaWestland Philadelphia
Corporation Model AW609 powered-lift.
You may view the final airworthiness
criteria on the internet at
www.regulations.gov in Docket No.
FAA–2022–1726.
Issued in Kansas City, Missouri, on
October 25, 2024.
Patrick R. Mullen,
Manager, Technical Policy Branch, Policy and
Standards Division, Aircraft Certification
Service.
[FR Doc. 2024–25238 Filed 10–30–24; 8:45 am]
BILLING CODE 4910–13–P
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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]
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule.
AGENCY:
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.
SUMMARY:
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Federal Register / Vol. 89, No. 211 / Thursday, October 31, 2024 / Rules and Regulations
• 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:
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.
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 righthand 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
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
The FAA received a comment on the
NPRM from the NTSB. The NTSB
supported the NPRM without change.
1 NTSB Investigation; Inadvertent Activation of
the Fuel Shutoff Lever, Subsequent Loss of Engine
Power, and Ditching on the East River, Liberty
Helicopters Inc. This information may be viewed
under 2.4.3 Certification Review Process, of Docket
Item #79 NTSB—Adopted Board Report, which is
available at https://data.ntsb.gov/Docket/
?NTSBNumber=ERA18MA099.
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Discussion of Final Airworthiness
Directive
Comments
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 partnumbered 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.
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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 partnumbered 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 onetime 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 FAAapproved 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.
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Federal Register / Vol. 89, No. 211 / Thursday, October 31, 2024 / Rules and Regulations
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:
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■
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
[Amended]
2. The FAA amends § 39.13 by adding
the following new airworthiness
directive:
■
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2024–20–07 Various Helicopters:
Amendment 39–22866; Docket No.
FAA–2024–1004; Project Identifier AD–
2023–01058–R.
(d) Subject
Joint Aircraft System Component (JASC)
Code: 2560, Emergency Equipment; and
3212, Emergency Flotation Section.
(a) Effective Date
(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 lefthand or right-hand float, causing the
helicopter to roll to one side, or loss of both
floats causing the helicopter to capsize
underwater.
This airworthiness directive (AD) is
effective December 5, 2024.
(b) Affected ADs
None.
(c) Applicability
This AD applies to the helicopters
identified in paragraphs (c)(1) through (8) of
this AD, certificated in any category.
(1) Airbus Helicopters Model AS350B,
AS350BA, AS350B1, AS350B2, AS350B3,
AS350C, AS350D, AS350D1, AS355E,
AS355F, AS355F1, AS355F2, and AS355N
helicopters modified by Supplemental Type
Certificate (STC) SR00831LA; Model EC120B
helicopters modified by STC SR00780LA;
and Model EC130B4 helicopters modified by
STC SR01687LA.
Note 1 to paragraph (c)(1): Helicopters
with an AS350B3e designation are Model
AS350B3 helicopters.
(2) Airbus Helicopters Deutschland GmbH
(AHD) Model BO–105A, BO–105C, BO–105S,
and BO–105LS A–3 helicopters modified by
STC SR00856LA; Model EC135P1, EC135P2,
EC135P2+, EC135P3, EC135T1, EC135T2,
EC135T2+, and EC135T3 helicopters
modified by STC SR01855LA; and Model
MBB–BK 117 C–2 and MBB–BK 117 D–2
helicopters modified by STC SR02244LA.
Note 2 to paragraph (c)(2): Helicopters
with an EC135P3H designation are Model
EC135P3 helicopters; helicopters with an
EC135T3H designation are Model EC135T3
helicopters, and helicopters with an MBB–
BK117 C–2e designation are Model MBB–
BK117 C–2 helicopters.
(3) Bell Textron Inc., Model 210, 212, 412,
412CF, and 412EP helicopters modified by
STC SR01779LA; and Model 412, 412CF, and
412EP helicopters modified by STC
SR01459LA.
(4) Bell Textron Canada Limited Model
206A, 206B, 206L, 206L–1, 206L–3, 206L–4,
and 407 helicopters modified by STC
SR01535LA.
Note 3 to paragraph (c)(4): Helicopters
with a 206B3 designation are Model 206B
helicopters; helicopters with a 206L–1+
designation are Model 206L–1 helicopters;
and helicopters with a 206L–3+ designation
are Model 206L–3 helicopters.
(5) Leonardo S.p.a. Model AB412 and
AB412 EP helicopters modified by STC
SR01779LA.
(6) MD Helicopters, LLC, Model 369D,
369E, 369F, 369FF, 369HE, 369HM, 369HS,
and 500N helicopters modified by STC
SR00932LA.
(7) Robinson Helicopter Company Model
R44 and R44 II helicopters modified by STC
SR02049LA; and Model R66 helicopters
modified by STC SR02484LA.
(8) Sikorsky Aircraft Corporation Model S–
76A, S–76B, and S–76C helicopters modified
by STC SR01902LA.
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(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
(g) Required Actions
(1) Within 100 hours time-in-service (TIS)
or 30 days after the effective date of this AD,
whichever occurs first, and thereafter at
intervals not to exceed six months,
accomplish the actions required by
paragraphs (g)(1)(i) through (vi) of this AD, as
applicable to your model helicopter.
(i) For Airbus Helicopters Model EC130B4
helicopters identified in paragraph (c)(1) of
this AD, accomplish the actions required by
paragraphs (g)(1)(i)(A) or (B) of this AD, as
applicable, and paragraph (g)(1)(i)(C) of this
AD, as applicable.
(A) Inspect the pull force on the float
activation handle in accordance with section
2.0 (for pull cable test tool part-number (P/
N) 606.7803), paragraphs 1 through 14 of
DART Aerospace Operation Instructional
Manual for General Pull Cable Rigging and
Testing Procedure, Revision B, dated May 12,
2023 (DART OIM–11 Rev B), except if the
inflation handle makes contact with the
cyclic stick in paragraph 6, before further
flight, perform cable rigging in accordance
with FAA-approved procedures and, once
the cable is properly rigged, continue with
the actions required by this paragraph, and
except the measurement in paragraph 8 must
be 0.85 in (2.16 cm) or greater; or
(B) Inspect the pull force on the float
activation handle in accordance with section
3.0 (for pull cable test tool P/N 607.1602),
paragraphs 3 through 20 of DART OIM–11
Rev B, except in paragraph 3, where it states,
‘‘it is advised to mark these locations and
verify the hole centers by removing the two
set screws from the test tool and sliding the
tool onto the shroud and aligning the tool
with the marks,’’ replace that text with ‘‘mark
these locations and verify the hole centers by
removing the two set screws from the test
tool and sliding the tool onto the shroud and
aligning the tool with the marks,’’ and except
the measurement in paragraph 13 must be
0.75 in (1.91 cm) or greater.
(C) If the pull force is greater than 25 lbf
(111.2N) or exceeds the limits in the existing
Installation Instructions or Instructions for
Continued Airworthiness for your helicopter,
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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
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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 FAAapproved 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
PO 00000
Frm 00008
Fmt 4700
Sfmt 4700
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 FAAapproved 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.
E:\FR\FM\31OCR1.SGM
31OCR1
Federal Register / Vol. 89, No. 211 / Thursday, October 31, 2024 / Rules and Regulations
(h) Alternative Methods of Compliance
(AMOCs)
DEPARTMENT OF TRANSPORTATION
(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 inspector,
or lacking a principal inspector, the manager
of the local flight standards district office/
certificate holding district office.
Federal Aviation Administration
(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
lotter on DSK11XQN23PROD with RULES1
(1) The Director of the Federal Register
approved the incorporation by reference of
the material listed in this paragraph under 5
U.S.C. 552(a) and 1 CFR part 51.
(2) You must use this material as
applicable to do the actions required by this
AD, unless the AD specifies otherwise.
(i) DART Aerospace Operation
Instructional Manual for General Pull Cable
Rigging and Testing Procedure, Revision B,
dated May 12, 2023.
(ii) DART Aerospace Service Bulletin (SB)
No. SB2020–09, Revision A, dated March 16,
2021.
(iii) DART Aerospace SB No. SB2021–01,
Revision A, dated December 28, 2021.
(iv) DART Aerospace SB No. SB2021–02,
dated April 30, 2021.
(v) DART Aerospace SB No. SB2021–03,
dated June 30, 2021.
(vi) DART Aerospace SB No. SB2022–01,
dated March 14, 2022.
(3) For material identified in this AD,
contact Dart Aerospace, LTD., 1270 Aberdeen
Street, Hawkesbury, ON, K6A 1K7, Canada;
phone: 1–613–632–5200; fax: 1–613–632–
5246; website: dartaero.com.
(4) You may view this material at the FAA,
Office of the Regional Counsel, Southwest
Region, 10101 Hillwood Parkway, Room 6N–
321, Fort Worth, TX 76177. For information
on the availability of this material at the
FAA, call (817) 222–5110.
(5) You may view this material at the
National Archives and Records
Administration (NARA). For information on
the availability of this material at NARA,
visit www.archives.gov/federal-register/cfr/
ibr-locations or email fr.inspection@nara.gov.
Issued on October 28, 2024.
Victor Wicklund,
Deputy Director, Compliance & Airworthiness
Division, Aircraft Certification Service.
[FR Doc. 2024–25390 Filed 10–30–24; 8:45 am]
BILLING CODE 4910–13–P
VerDate Sep<11>2014
16:20 Oct 30, 2024
Jkt 265001
14 CFR Part 39
[Docket No. FAA–2024–1695; Project
Identifier AD–2023–00783–E; Amendment
39–22869; AD 2024–21–02]
RIN 2120–AA64
Airworthiness Directives; Lycoming
Engines
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule.
AGENCY:
The FAA is adopting a new
airworthiness directive (AD) for
Lycoming Engines (Lycoming) model
engines that have a certain connecting
rod assemblies installed. This AD was
prompted by several reports of
connecting rod failures, which resulted
in uncontained engine failure and inflight shutdowns (IFSDs). This AD
requires repetitive oil inspections for
bronze metal particulates and, if found,
additional inspections of the connecting
rod bushings for damage, proper fit,
movement, and wear, and replacement
if necessary. As terminating action to
the connecting rod bushing inspections,
this AD requires replacement of the
connecting rod bushings with parts
eligible for installation. 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 a certain publication 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–2024–1695; 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 Lycoming material identified in
this AD, contact Lycoming Engines, 652
Oliver Street, Williamsport, PA 17701;
phone: (800) 258–3279; website:
lycoming.com/contact/knowledge-base/
publications.
• You may view this material at the
FAA, Airworthiness Products Section,
SUMMARY:
PO 00000
Frm 00009
Fmt 4700
Sfmt 4700
86721
Operational Safety Branch, 1200 District
Avenue, Burlington, MA 01803. For
information on the availability of this
material at the FAA, call (817) 222–
5110. It is also available at
regulations.gov under Docket No. FAA–
2024–1695.
FOR FURTHER INFORMATION CONTACT:
James Delisio, Aviation Safety Engineer,
FAA, 1701 Columbia Avenue, College
Park, GA 30337; phone: (516) 228–7321;
email: james.delisio@faa.gov.
SUPPLEMENTARY INFORMATION:
Background
The FAA issued a notice of proposed
rulemaking (NPRM) to amend 14 CFR
part 39 by adding an AD that would
apply to Lycoming model engines that
have certain connecting rod assemblies
installed. The NPRM published in the
Federal Register on June 28, 2024 (89
FR 53911). The NPRM was prompted by
several reports of connecting rod
failures, which resulted in uncontained
engine failure and IFSDs, and a
manufacturer investigation where it was
determined that affected connecting rod
small end bushings may be installed on
additional populations of Lycoming
engines. The manufacturer also
determined that degradation of the
connecting rod small end bushings is
detectable during oil change
inspections. In the NPRM, the FAA
proposed to require repetitive oil
inspections for bronze metal
particulates and, if found, additional
inspections of the connecting rod
bushings for damage (e.g. deterioration,
missing metal), proper fit, movement,
and wear, and replacement if necessary.
As terminating action to the connecting
rod bushing inspections, the NPRM also
proposed to require replacement of the
connecting rod bushings with parts
eligible for installation. The FAA is
issuing this AD to address the unsafe
condition on these products.
Discussion of Final Airworthiness
Directive
Comments
The FAA received one comment from
Aeroclub de Columbia. The following
presents the comment received on the
NPRM and the FAA’s response to the
comment.
Request To Clarify Scheduling of
Inspections
Aeroclub de Columbia requested that
the FAA confirm whether the recurrent
inspections required by paragraph (g) of
the proposed AD should also be
scheduled monthly for aircraft in 14
CFR part 91 (non-commercial)
operations. Aeroclub de Columbia noted
E:\FR\FM\31OCR1.SGM
31OCR1
]]>Agencies
[Federal Register Volume 89, Number 211 (Thursday, October 31, 2024)]
[Rules and Regulations]
[Pages 86717-86721]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2024-25390]
-----------------------------------------------------------------------
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.
[[Page 86718]]
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: [email protected].
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.
[[Page 86719]]
Authority for This Rulemaking
Title 49 of the United States Code specifies the FAA's authority to
issue rules on aviation safety. Subtitle I, section 106, describes the
authority of the FAA Administrator. Subtitle VII: Aviation Programs,
describes in more detail the scope of the Agency's authority.
The FAA is issuing this rulemaking under the authority described in
Subtitle VII, Part A, Subpart III, Section 44701: General requirements.
Under that section, Congress charges the FAA with promoting safe flight
of civil aircraft in air commerce by prescribing regulations for
practices, methods, and procedures the Administrator finds necessary
for safety in air commerce. This regulation is within the scope of that
authority because it addresses an unsafe condition that is likely to
exist or develop on products identified in this rulemaking action.
Regulatory Findings
This AD will not have federalism implications under Executive Order
13132. This AD will not have a substantial direct effect on the States,
on the relationship between the national government and the States, or
on the distribution of power and responsibilities among the various
levels of government.
For the reasons discussed above, I certify that this AD:
(1) Is not a ``significant regulatory action'' under Executive
Order 12866,
(2) Will not affect intrastate aviation in Alaska, and
(3) Will not have a significant economic impact, positive or
negative, on a substantial number of small entities under the criteria
of the Regulatory Flexibility Act.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.
The Amendment
Accordingly, under the authority delegated to me by the
Administrator, the FAA amends 14 CFR part 39 as follows:
PART 39--AIRWORTHINESS DIRECTIVES
0
1. The authority citation for part 39 continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
Sec. 39.13 [Amended]
0
2. The FAA amends Sec. 39.13 by adding the following new airworthiness
directive:
2024-20-07 Various Helicopters: Amendment 39-22866; Docket No. FAA-
2024-1004; Project Identifier AD-2023-01058-R.
(a) Effective Date
This airworthiness directive (AD) is effective December 5, 2024.
(b) Affected ADs
None.
(c) Applicability
This AD applies to the helicopters identified in paragraphs
(c)(1) through (8) of this AD, certificated in any category.
(1) Airbus Helicopters Model AS350B, AS350BA, AS350B1, AS350B2,
AS350B3, AS350C, AS350D, AS350D1, AS355E, AS355F, AS355F1, AS355F2,
and AS355N helicopters modified by Supplemental Type Certificate
(STC) SR00831LA; Model EC120B helicopters modified by STC SR00780LA;
and Model EC130B4 helicopters modified by STC SR01687LA.
Note 1 to paragraph (c)(1): Helicopters with an AS350B3e
designation are Model AS350B3 helicopters.
(2) Airbus Helicopters Deutschland GmbH (AHD) Model BO-105A, BO-
105C, BO-105S, and BO-105LS A-3 helicopters modified by STC
SR00856LA; Model EC135P1, EC135P2, EC135P2+, EC135P3, EC135T1,
EC135T2, EC135T2+, and EC135T3 helicopters modified by STC
SR01855LA; and Model MBB-BK 117 C-2 and MBB-BK 117 D-2 helicopters
modified by STC SR02244LA.
Note 2 to paragraph (c)(2): Helicopters with an EC135P3H
designation are Model EC135P3 helicopters; helicopters with an
EC135T3H designation are Model EC135T3 helicopters, and helicopters
with an MBB-BK117 C-2e designation are Model MBB-BK117 C-2
helicopters.
(3) Bell Textron Inc., Model 210, 212, 412, 412CF, and 412EP
helicopters modified by STC SR01779LA; and Model 412, 412CF, and
412EP helicopters modified by STC SR01459LA.
(4) Bell Textron Canada Limited Model 206A, 206B, 206L, 206L-1,
206L-3, 206L-4, and 407 helicopters modified by STC SR01535LA.
Note 3 to paragraph (c)(4): Helicopters with a 206B3 designation
are Model 206B helicopters; helicopters with a 206L-1+ designation
are Model 206L-1 helicopters; and helicopters with a 206L-3+
designation are Model 206L-3 helicopters.
(5) Leonardo S.p.a. Model AB412 and AB412 EP helicopters
modified by STC SR01779LA.
(6) MD Helicopters, LLC, Model 369D, 369E, 369F, 369FF, 369HE,
369HM, 369HS, and 500N helicopters modified by STC SR00932LA.
(7) Robinson Helicopter Company Model R44 and R44 II helicopters
modified by STC SR02049LA; and Model R66 helicopters modified by STC
SR02484LA.
(8) Sikorsky Aircraft Corporation Model S-76A, S-76B, and S-76C
helicopters modified by STC SR01902LA.
(d) Subject
Joint Aircraft System Component (JASC) Code: 2560, Emergency
Equipment; and 3212, Emergency Flotation Section.
(e) Unsafe Condition
This AD was prompted by the results of an accident investigation
and subsequent reports of difficulty pulling the emergency float kit
float activation handle installed on the pilot cyclic. The FAA is
issuing this AD to detect and address improperly installed cables,
which can lead to difficulty deploying the float system from the
float activation handle. The unsafe condition, if not addressed,
could result in loss of the left-hand or right-hand float, causing
the helicopter to roll to one side, or loss of both floats causing
the helicopter to capsize underwater.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) Required Actions
(1) Within 100 hours time-in-service (TIS) or 30 days after the
effective date of this AD, whichever occurs first, and thereafter at
intervals not to exceed six months, accomplish the actions required
by paragraphs (g)(1)(i) through (vi) of this AD, as applicable to
your model helicopter.
(i) For Airbus Helicopters Model EC130B4 helicopters identified
in paragraph (c)(1) of this AD, accomplish the actions required by
paragraphs (g)(1)(i)(A) or (B) of this AD, as applicable, and
paragraph (g)(1)(i)(C) of this AD, as applicable.
(A) Inspect the pull force on the float activation handle in
accordance with section 2.0 (for pull cable test tool part-number
(P/N) 606.7803), paragraphs 1 through 14 of DART Aerospace Operation
Instructional Manual for General Pull Cable Rigging and Testing
Procedure, Revision B, dated May 12, 2023 (DART OIM-11 Rev B),
except if the inflation handle makes contact with the cyclic stick
in paragraph 6, before further flight, perform cable rigging in
accordance with FAA-approved procedures and, once the cable is
properly rigged, continue with the actions required by this
paragraph, and except the measurement in paragraph 8 must be 0.85 in
(2.16 cm) or greater; or
(B) Inspect the pull force on the float activation handle in
accordance with section 3.0 (for pull cable test tool P/N 607.1602),
paragraphs 3 through 20 of DART OIM-11 Rev B, except in paragraph 3,
where it states, ``it is advised to mark these locations and verify
the hole centers by removing the two set screws from the test tool
and sliding the tool onto the shroud and aligning the tool with the
marks,'' replace that text with ``mark these locations and verify
the hole centers by removing the two set screws from the test tool
and sliding the tool onto the shroud and aligning the tool with the
marks,'' and except the measurement in paragraph 13 must be 0.75 in
(1.91 cm) or greater.
(C) If the pull force is greater than 25 lbf (111.2N) or exceeds
the limits in the existing Installation Instructions or Instructions
for Continued Airworthiness for your helicopter,
[[Page 86720]]
as applicable, before further flight, comply with paragraph (g)(2)
of this AD, as applicable to your model helicopter.
(ii) For Airbus Helicopters Deutschland GmbH (AHD) Model MBB-BK
117 C-2 and MBB-BK 117 D-2 helicopters identified in paragraph
(c)(2) of this AD, accomplish the actions required by paragraphs
(g)(1)(ii)(A) and (B) of this AD, as applicable.
(A) Inspect the pull force on the float activation handle in
accordance with section 2.0 (for pull cable test tool P/N 606.7803),
paragraphs 1 through 14 of DART OIM-11 Rev B, except if the
inflation handle makes contact with the cyclic stick in paragraph 6,
before further flight, perform cable rigging in accordance with FAA-
approved procedures, and except the measurement in paragraph 8 must
be 0.85 in (2.16 cm) or greater.
(B) If the pull force is greater than 25 lbf (111.2N), or
exceeds the limits in the existing Installation Instructions or
Instructions for Continued Airworthiness for your helicopter, as
applicable, before further flight, comply with paragraph (g)(2) of
this AD, as applicable to your model helicopter.
(iii) For Bell Textron Inc., Model 210, 212, 412, 412CF, and
412EP helicopters identified in paragraph (c)(3) of this AD,
accomplish the actions required by paragraphs (g)(1)(iii)(A) or (B)
of this AD, as applicable, and paragraph (g)(1)(iii)(C) of this AD,
as applicable.
(A) Inspect the pull force on the float activation handle in
accordance with section 2.0 (for pull cable test tool P/N 606.7803),
paragraphs 1 through 14 of DART OIM-11 Rev B, except if the
inflation handle makes contact with the cyclic stick in paragraph 6,
before further flight perform cable rigging in accordance with FAA-
approved procedures, and except the measurement in paragraph 8 must
be 0.85 in (2.16 cm) or greater; or
(B) Inspect the pull force on the float activation handle in
accordance with section 3.0 (for pull cable test tool P/N 607.1602),
paragraphs 3 through 20 of DART OIM-11 Rev B, except in paragraph 3,
where it states, ``it is advised to mark these locations and verify
the hole centers by removing the two set screws from the test tool
and sliding the tool onto the shroud and aligning the tool with the
marks.'' replace that text with ``mark these locations and verify
the hole centers by removing the two set screws from the test tool
and sliding the tool onto the shroud and aligning the tool with the
marks,'' and except the measurement in paragraph 13 must be 0.75 in
(1.91 cm) or greater.
(C) If the pull force is greater than 25 lbf (111.2N), or
exceeds the limits in the existing Installation Instructions or
Instructions for Continued Airworthiness for your helicopter, as
applicable, before further flight, comply with paragraph (g)(2) of
this AD, as applicable to your model helicopter.
(iv) For Bell Textron Canada Limited Model 206A, 206B, 206L,
206L-1, 206L-3, 206L-4, and 407 helicopters identified in paragraph
(c)(4) of this AD, accomplish the actions required by paragraphs
(g)(1)(iv)(A) and (B) of this AD, as applicable.
(A) Inspect the pull force on the float activation handle in
accordance with section 2.0 (for pull cable test tool P/N 606.7803),
paragraphs 1 through 14 of DART OIM-11 Rev B, except if the
inflation handle makes contact with the cyclic stick in paragraph 6,
before further flight perform cable rigging in accordance with FAA-
approved procedures, and except the measurement in paragraph 8 must
be 0.85 in (2.16 cm) or greater.
(B) If the pull force is greater than 25 lbf (111.2N), or
exceeds the limits in the existing Installation Instructions or
Instructions for Continued Airworthiness for your helicopter, as
applicable, before further flight, comply with paragraph (g)(2) of
this AD, as applicable to your model helicopter.
(v) For Robinson Helicopter Company Model R66 helicopters
identified in paragraph (c)(7) of this AD, accomplish the actions
required by paragraphs (g)(1)(v)(A) and (B) of this AD, as
applicable.
(A) Inspect the pull force on the float activation handle in
accordance with section 2.0 (for pull cable test tool P/N 607.7803),
paragraphs 1 through 14 of DART OIM-11 Rev B, except if the
inflation handle makes contact with the cyclic stick in paragraph 6,
before further flight perform cable rigging in accordance with FAA-
approved procedures, and except the measurement in paragraph 8 must
be 0.85 in (2.16 cm) or greater.
(B) If the pull force is greater than 25 lbf (111.2N), or
exceeds the limits in the existing Installation Instructions or
Instructions for Continued Airworthiness for your helicopter, as
applicable, before further flight, comply with paragraph (g)(2) of
this AD, as applicable to your model helicopter.
(vi) For the helicopters identified in paragraphs (g)(1)(vi)(A)
through (E) of this AD, inspect the pull force on the float
activation handle in accordance with FAA-approved procedures. The
threshold for this pull force inspection must not exceed 25 lbf
(111.2N). If the float activation handle fails the test, (if the
pull force is greater than 25 lbf (111.2N)), or exceeds the limits
in the existing Installation Instructions or Instructions for
Continued Airworthiness for your helicopter, as applicable, before
further flight, comply with paragraph (g)(2) of this AD, as
applicable to your model helicopter.
(A) Airbus Helicopters Model AS350B, AS350BA, AS350B1, AS350B2,
AS350B3, AS350C, AS350D, AS350D1, AS355E, AS355F, AS355F1, AS355F2,
AS355N, and EC120B helicopters identified in paragraph (c)(1) of
this AD.
(B) Airbus Helicopters Deutschland GmbH (AHD) Model BO-105A, BO-
105C, BO-105S, BO-105LS A-3, EC135P1, EC135P2, EC135 P2+, EC135P3,
EC135T1, EC135T2, EC135T2+, and EC135T3 helicopters identified in
paragraph (c)(2) of this AD.
(C) Leonardo S.p.a. Model AB412 and AB412 EP helicopters
identified in paragraph (c)(5) of this AD.
(D) MD Helicopters, LLC, Model 369D, 369E, 369F, 369FF, 369HE,
369HM, 369HS, and 500N helicopters identified in paragraph (c)(6) of
this AD.
(E) Sikorsky Aircraft Corporation Model S-76A, S-76B, and S-76C
helicopters identified in paragraph (c)(8) of this AD.
(2) For the helicopters identified in paragraphs (g)(1)(i)
through (v) of this AD, as a result of the actions required by
paragraphs (g)(1)(i) through (v) of this AD, if the pull force is
greater than 25 lbf (111.2N), or exceeds the limits in the existing
Installation Instructions or Instructions for Continued
Airworthiness for your helicopter, as applicable, before further
flight, comply with either paragraph (g)(2)(i) or (ii) of this AD.
(i) Repair the cable installation in accordance with FAA-
approved procedures.
(ii) Deactivate and placard the emergency float system as
inoperative in accordance with Appendix A of DART Aerospace Service
Bulletin (SB) No. SB2020-09, Revision A, dated March 16, 2021, DART
Aerospace SB No. SB2021-01, Revision A, dated December 28, 2021,
DART Aerospace SB No. SB2021-02, dated April 30, 2021, DART
Aerospace SB No. SB2021-03, dated June 30, 2021, or DART Aerospace
SB No. SB2022-01, dated March 14, 2022, as applicable to your model
helicopter, except where Appendix A specifies ty-wrapping the pin
into place on the pilot collective, and where Appendix A specifies
contacting DART customer service for a resolution, accomplish the
deactivation and placarding in accordance with FAA-approved
procedures. If the emergency float system is deactivated and
placarded as inoperative, you are not required to accomplish the
actions required by paragraph (g)(1) of this AD. This AD does not
allow operation with an inoperative emergency float system unless
the requirements of 14 CFR 91.205, 91.213, 135.183, and 136.11 have
been met.
(3) For the helicopters identified in paragraphs (g)(1)(vi)(A)
through (E) of this AD, as a result of the actions required by the
introductory text of paragraph (g)(1)(vi) of this AD, if the pull
force is greater than 25 lbf (111.2N), before further flight, repair
the cable installation, or deactivate and placard the emergency
float system as inoperative in accordance with FAA-approved
procedures.
(4) For Robinson Helicopter Company Model R44 and R44 II
helicopters identified in paragraph (c)(7) of this AD, within 36
months or at the next float inflation reservoir (reservoir) overhaul
after the effective date of this AD, whichever occurs first, perform
the requirements in paragraphs (g)(4)(i) and (ii) of this AD.
Thereafter, within intervals not to exceed six months, repeat the
actions required by paragraph (g)(4)(ii) of this AD.
(i) Remove cable P/N 644.7501 or P/N 644.7502 from service, as
applicable, and replace with cable P/N 644.7503; and remove each
reservoir P/N 644.7701 from service and replace with reservoir P/N
644.7702 or P/N 644.7703.
(ii) Inspect the pull force on the float activation handle in
accordance with FAA-approved procedures. The threshold for this pull
force inspection must not exceed 25 lbf (111.2N). If the pull cable
installation fails the test (if the pull force is greater than 25
lbf (111.2N)), before further flight, repair the cable installation,
or deactivate and placard the emergency float system as inoperative
in accordance with FAA-approved procedures.
(5) As of the effective date of this AD, do not install
reservoir P/N 644.7701 and cable P/N 644.7501 or reservoir P/N
644.7701 and cable P/N 644.7502 on any Robinson Helicopter Company
Model R44 or R44 II helicopter.
[[Page 86721]]
(h) Alternative Methods of Compliance (AMOCs)
(1) The Manager, West Certification Branch, FAA, has the
authority to approve AMOCs for this AD, if requested using the
procedures found in 14 CFR 39.19. In accordance with 14 CFR 39.19,
send your request to your principal inspector or local Flight
Standards District Office, as appropriate. If sending information
directly to the manager of the West Certification Branch, send it to
the attention of the person identified in paragraph (i) of this AD.
Information may be emailed to: [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) 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: [email protected].
(j) Material Incorporated by Reference
(1) The Director of the Federal Register approved the
incorporation by reference of the material listed in this paragraph
under 5 U.S.C. 552(a) and 1 CFR part 51.
(2) You must use this material as applicable to do the actions
required by this AD, unless the AD specifies otherwise.
(i) DART Aerospace Operation Instructional Manual for General
Pull Cable Rigging and Testing Procedure, Revision B, dated May 12,
2023.
(ii) DART Aerospace Service Bulletin (SB) No. SB2020-09,
Revision A, dated March 16, 2021.
(iii) DART Aerospace SB No. SB2021-01, Revision A, dated
December 28, 2021.
(iv) DART Aerospace SB No. SB2021-02, dated April 30, 2021.
(v) DART Aerospace SB No. SB2021-03, dated June 30, 2021.
(vi) DART Aerospace SB No. SB2022-01, dated March 14, 2022.
(3) For material identified in this AD, contact Dart Aerospace,
LTD., 1270 Aberdeen Street, Hawkesbury, ON, K6A 1K7, Canada; phone:
1-613-632-5200; fax: 1-613-632-5246; website: dartaero.com.
(4) You may view this material at the FAA, Office of the
Regional Counsel, Southwest Region, 10101 Hillwood Parkway, Room 6N-
321, Fort Worth, TX 76177. For information on the availability of
this material at the FAA, call (817) 222-5110.
(5) You may view this material at the National Archives and
Records Administration (NARA). For information on the availability
of this material at NARA, visit www.archives.gov/federal-register/cfr/ibr-locations or email [email protected].
Issued on October 28, 2024.
Victor Wicklund,
Deputy Director, Compliance & Airworthiness Division, Aircraft
Certification Service.
[FR Doc. 2024-25390 Filed 10-30-24; 8:45 am]
BILLING CODE 4910-13-P
