Federal Register / Vol. 89, No. 211 / Thursday, October 31, 2024 / Rules and Regulations 86717 

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), 

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. 

Applicability 

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. 

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 

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. 


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86718 Federal Register / Vol. 89, No. 211 / Thursday, October 31, 2024 / Rules and Regulations 

1NTSB 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. 

• 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 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 

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 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. 

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 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 

■ 1. The authority citation for part 39 

continues to read as follows: 

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: 

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 lefthand 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, 


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86720 Federal Register / Vol. 89, No. 211 / Thursday, October 31, 2024 / Rules and Regulations 

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 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 

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. 


lotter on DSK11XQN23PROD with RULES1
Federal Register / Vol. 89, No. 211 / Thursday, October 31, 2024 / Rules and Regulations 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: 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. 

(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 

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 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

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 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: 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, 

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 


lotter on DSK11XQN23PROD with RULES1