Airworthiness Directives; MD Helicopters, LLC Helicopters

[Federal Register Volume 91, Number 187 (Tuesday, September 29, 2026)]
[Rules and Regulations]
[Pages 61304-61306]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2026-19891]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2025-3987; Project Identifier AD-2025-00017-R; 
Amendment 39-23466; AD 2026-19-01]
RIN 2120-AA64


Airworthiness Directives; MD Helicopters, LLC Helicopters

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule; correction.

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SUMMARY: The FAA is correcting an airworthiness directive (AD) that was 
published in the Federal Register. That AD applies to all MD 
Helicopters, LLC Model 369, 369A, 369D, 369E, 369F, 369FF, 369H, 369HE, 
369HM, 369HS, 500N, and 600N helicopters. As published, the header of 
the regulatory text is missing the AD number and the amendment number. 
This document corrects those errors. In all other respects, the 
original document remains the same.

DATES: This correction is effective October 20, 2026. The effective 
date of AD 2026-19-01 remains October 20, 2026.

ADDRESSES: AD Docket: You may examine the AD docket at regulations.gov 
under Docket No. FAA-2025-3987, 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.

FOR FURTHER INFORMATION CONTACT: Eduardo Orozco-Duran, Aviation Safety 
Engineer, FAA, 3960 Paramount Boulevard, Lakewood, CA 90712; phone: 
(562) 627-5264; email: [email protected].

SUPPLEMENTARY INFORMATION:

Background

    AD 2026-19-01, Amendment 39-23466 (91 FR 58365, September 15, 2026) 
(AD 2026-19-01), requires repetitively inspecting the torque tube 
assembly and roller bearings, and depending on the results, replacing 
parts or accomplishing additional inspections for all MD Helicopters, 
LLC Model 369, 369A, 369D, 369E, 369F, 369FF, 369H, 369HE, 369HM, 
369HS, 500N, and 600N helicopters.

Need for the Correction

    As published, the header of the regulatory text of AD 2026-19-01 is 
missing the AD number and the amendment number.

Correction of Publication

    This document corrects errors and accordingly adds the AD as an 
amendment to 14 CFR 39.13. Although no other part of the preamble or 
regulatory information has been corrected, the FAA is publishing the 
entire rule in the Federal Register.
    The effective date of this AD remains October 20, 2026.
    Since this action adds only the missing information identified 
above, it has no adverse economic impact and imposes no additional 
burden on any person. Therefore, the FAA has determined that notice and 
public comment procedures are unnecessary.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Incorporation by 
reference, Safety.

Adoption of the Amendment

    Accordingly, pursuant to the authority delegated to me by the 
Administrator, the FAA amends part 39 of the Federal Aviation 
Regulations (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  [Corrected]

0
2. The FAA amends Sec.  39.13 by:
0
a. Removing Airworthiness Directive 2024-23-06, Amendment 39-22885 (89 
FR 91248, November 19, 2024); and
0
b. Adding the following new airworthiness directive:

2026-19-01 MD Helicopters, LLC: Amendment 39-23466; Docket No. FAA-
2025-3987; Project Identifier AD-2025-00017-R.

(a) Effective Date

    This airworthiness directive (AD) is effective October 20, 2026.

(b) Affected ADs

    This AD replaces AD 2024-23-06, Amendment 39-22885 (89 FR 91248, 
November 19, 2024) (AD 2024-23-06).

(c) Applicability

    This AD applies to all MD Helicopters, LLC Model 369, 369A, 
369D, 369E, 369F, 369FF, 369H, 369HE, 369HM, 369HS, 500N, and 600N 
helicopters, certificated in any category.

(d) Subject

    Joint Aircraft System Component (JASC) Code 6700, Rotorcraft 
flight control.

(e) Unsafe Condition

    This AD was prompted by a report of a seized and damaged roller 
bearing assembly in the torque tube assembly. The FAA is issuing 
this AD to prevent failure of the torque tube assembly. The unsafe 
condition, if not addressed, could result in reduced controllability 
and loss of control of the helicopter.

(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 within 12 months 
after the effective date of this AD, whichever occurs first, and 
thereafter at intervals not to exceed 100 hours

[[Page 61305]]

TIS, accomplish the actions required by paragraphs (g)(1)(i) and 
(ii) of this AD.
    (i) Using a flashlight and mirror, visually inspect the torque 
tube for corrosion and cracks. If there is any corrosion or a crack, 
before further flight, remove the torque tube from service and 
install an airworthy torque tube.
    (ii) Visually inspect each roller bearing (number 5) as depicted 
in Figure 1 to paragraph (g)(1) of this AD for corrosion and 
degradation. If a roller bearing has any corrosion or degradation, 
before further flight, remove the roller bearing from service and 
install an airworthy roller bearing.
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[GRAPHIC] [TIFF OMITTED] TR29SE26.000

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    (2) Before the helicopter accumulates 3,000 total hours TIS or 
within 100 hours TIS after the effective date of this AD, whichever 
occurs later, and thereafter at intervals not to exceed 100 hours 
TIS, perform a freedom-of-movement inspection on the torque tube 
assembly by accomplishing the actions required by paragraphs 
(g)(2)(i) through (v) of this AD.
    (i) Disconnect the one-way lock (number 6) of the torque tube by 
removing the cotter pin (number 7), nut (number 8), bolt (number 9), 
washers (number 10), and slotted bushing (number 11) from the torque 
tube assembly as depicted in Figure 1 to paragraph (g)(1) of this 
AD.

[[Page 61306]]

    (ii) Loosen the longitudinal cyclic friction knob (number 12 or 
13) of the torque tube assembly as depicted in Figure 1 to paragraph 
(g)(1) of this AD.
    (iii) While moving the cyclic control forward and aft to allow 
the torque tube assembly to rotate through its full range of motion, 
inspect the torque tube assembly for binding and ratcheting.
    (A) If there is any binding or ratcheting as a result of the 
action required by paragraph (g)(2)(iii) of this AD, before further 
flight, inspect each roller bearing (number 5) as depicted in Figure 
1 to paragraph (g)(1) of this AD for damage. For the purposes of 
this inspection, damage may be indicated by corrosion, lack of 
lubrication (dry exterior surface), or material degradation.
    (B) If any roller bearing (number 5) as depicted in Figure 1 to 
paragraph (g)(1) of this AD has any damage, before further flight, 
remove the roller bearing from service and install an airworthy 
roller bearing.
    (iv) If there is no binding or ratcheting as a result of the 
action required by paragraph (g)(2)(iii) of this AD or after 
accomplishing the action required by paragraph (g)(2)(iii)(B) of 
this AD, as applicable, tighten the cyclic friction knob (number 12 
or 13) as depicted in Figure 1 to paragraph (g)(1) of this AD.
    (v) Connect the one-way lock (number 6) as depicted in Figure 1 
to paragraph (g)(1) of this AD by accomplishing the actions required 
by paragraphs (g)(2)(v)(A) and (B).
    (A) Install the slotted bushing (number 11), washers (number 
10), bolt (number 9), nut (number 8), and new (zero total hours TIS) 
cotter pin (number 7) as depicted in Figure 1 to paragraph (g)(1) of 
this AD.
    (B) Ensure the edge of the slotted bushing (number 11) protrudes 
0.010 to 0.080 inch (0.25 to 2.03 millimeters) above the surface of 
the cyclic torque tube after the nut is tightened.

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

(i) Additional Information

    For more information about this AD, contact Eduardo Orozco-
Duran, Aviation Safety Engineer, FAA, 3960 Paramount Boulevard, 
Lakewood, CA 90712; phone: (562) 627-5264; email: [email protected].

(j) Material Incorporated by Reference

    None.

    Issued on September 24, 2026.
Steven W. Thompson,
Acting Deputy Director, Compliance & Airworthiness Division, Aircraft 
Certification Service.
[FR Doc. 2026-19891 Filed 9-28-26; 8:45 am]
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