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2024-23-06 MD HELICOPTERS, LLC: Amendment 39-22885; Docket No. FAA-2024-2011; Project Identifier AD-2023-01121-R. 
(a) EFFECTIVE DATE

    This airworthiness directive (AD) is effective December 24, 2024.

(b) AFFECTED ADS

    None.

(c) APPLICABILITY

    This AD applies to MD  Helicopters, LLC, Model 369, 369A,  369D, 369E,
    369F, 369FF, 369H,  369HE, 369HM, 369HS,  500N, and 600N  helicopters,
    certificated  in any  category, with  a pilot  interconnecting  cyclic
    torque tube (torque tube) part number 369H7133-7 installed.

(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 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  subsequent
    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 one  year after the
    effective date of this AD,  whichever occurs first, and thereafter  at
    intervals not to exceed 100 hours 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.

     ILLUSTRATION (FIGURE 1 TO PARAGRAPH (G)(1)-TORQUE TUBE ASSEMBLY)

(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.

(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 the introductory text of 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 not any binding  or ratcheting as a result of the  action
     required by the introductory text of 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 mm) 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. Information may be emailed to:
    AMOC@faa.gov.

(2) Before using any  approved AMOC, notify your appropriate principal in-
    spector, or lacking  a principal inspector,  the manager of  the local
    flight standards  district office/certificate holding district office.

(i) 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: eduardo.orozco-duran@faa.gov.

(j) MATERIAL INCORPORATED BY REFERENCE

    None.

Issued on November 12, 2024. Victor Wicklund, Deputy Director,  Compliance
& Airworthiness Division, Aircraft Certification Service.

FOR  FURTHER INFORMATION CONTACT:  Eduardo  Orozco-Duran, Aviation  Safety
Engineer, FAA, 3960 Paramount Boulevard, Lakewood, CA 90712; phone:  (562)
627-5264; email: eduardo.orozco-duran@faa.gov.
PREAMBLE  
DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2024-2011; Project Identifier AD-2023-01121-R;
Amendment 39-22885; AD 2024-23-06]
RIN 2120-AA64

Airworthiness Directives; MD Helicopters, LLC, Helicopters

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule.

-----------------------------------------------------------------------

SUMMARY: The FAA is adopting a new airworthiness directive (AD) for
certain MD Helicopters, LLC (MDHI), Model 369, 369A, 369D, 369E, 369F,
369FF, 369H, 369HE, 369HM, 369HS, 500N, and 600N helicopters. This AD
was prompted by a report of a seized and damaged roller bearing in the
pilot interconnecting cyclic torque tube (torque tube) assembly. This
AD requires repetitively inspecting the torque tube assembly and roller
bearings, and depending on the results, replacing parts, or
accomplishing additional inspections. The FAA is issuing this AD to
address the unsafe condition on these products.

DATES: This AD is effective December 24, 2024.

ADDRESSES: AD Docket: You may examine the AD docket at regulations.gov
under Docket No. FAA-2024-2011; 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: eduardo.orozco-duran@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 MDHI Model 369, 369A,
369D, 369E, 369F, 369FF, 369H, 369HE, 369HM, 369HS, 500N, and 600N
helicopters with a torque tube part number 369H7133-7 installed. The
NPRM published in the Federal Register on August 8, 2024 (89 FR 64834).
The NPRM was prompted by a report of a seized and damaged roller
bearing assembly in the torque tube assembly of an MDHI Model MD369E
helicopter. Since MDHI Model 369, 369A, 369D, 369F, 369FF, 369H, 369HE,
369HM, 369HS, 500N, and 600N helicopters have the same torque tube
assembly installed, they are also affected by this unsafe condition. In
the NPRM, the FAA proposed to require repetitively visually inspecting
the torque tube for corrosion and cracks, repetitively visually
inspecting the roller bearings for corrosion and degradation,
performing a repetitive freedom-of-movement inspection of the torque
tube assembly for binding or ratcheting, and corrective or additional
action as necessary. The FAA is issuing this AD to address the unsafe
condition on these products.

Discussion of Final Airworthiness Directive

Comments

    The FAA received no comments on the NPRM or on the determination of
the costs.

Conclusion

    The FAA reviewed the relevant data and determined that air safety
requires adopting this AD as proposed. Accordingly, the FAA is issuing
this AD to address the unsafe condition on these products. Except for
minor editorial changes and clarifying two paragraph cross-references
in the Required Actions section of this AD, paragraphs (g)(2)(iii)(A)
and (g)(2)(iv), by replacing the text "paragraph (g)(2)(iii) of this
AD" with "the introductory text of paragraph (g)(2)(iii) of this
AD," this AD is adopted as proposed in the NPRM.

Costs of Compliance

    The FAA estimates that this AD affects 353 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.

    Visually inspecting the torque tube and roller bearings will take 1
work-hour for an estimated cost of $85 per helicopter and $30,005 for
the U.S. fleet, per inspection cycle. Inspecting the torque tube assembly for freedom
of movement will take 0.75 work-hour for an estimated cost of $64 per
helicopter and $22,595 for U.S. fleet cost, per inspection cycle. If
required, a more in-depth inspection of the roller bearings will take
0.25 work-hour for an estimated cost of $21 per helicopter, per instance.

    If required, replacing a torque tube will take 6 work-hours and
parts will cost $4,773 for an estimated cost of $5,283 per torque tube
replacement. Replacing a roller bearing will take 6 work-hours and
parts will cost $210 for an estimated cost of $720 per roller bearing
replacement.

Authority for This Rulemaking

    Title 49 of the United States Code specifies the FAA's authority to
issue rules on aviation safety. Subtitle I, section 106, describes the
authority of the FAA Administrator. Subtitle VII: Aviation Programs,
describes in more detail the scope of the Agency's authority.

    The FAA is issuing this rulemaking under the authority described in
Subtitle VII, Part A, Subpart III, Section 44701: General requirements.
Under that section, Congress charges the FAA with promoting safe flight
of civil aircraft in air commerce by prescribing regulations for
practices, methods, and procedures the Administrator finds necessary
for safety in air commerce. This regulation is within the scope of that
authority because it addresses an unsafe condition that is likely to
exist or develop on products identified in this rulemaking action.

Regulatory Findings

    This AD will not have federalism implications under Executive Order
13132. This AD will not have a substantial direct effect on the States,
on the relationship between the national government and the States, or
on the distribution of power and responsibilities among the various
levels of government.

    For the reasons discussed above, I certify that this AD:

    (1) Is not a "significant regulatory action" under Executive
Order 12866,

    (2) Will not affect intrastate aviation in Alaska, and

    (3) Will not have a significant economic impact, positive or
negative, on a substantial number of small entities under the criteria
of the Regulatory Flexibility Act.

List of Subjects in 14 CFR Part 39

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

The Amendment

    Accordingly, under the authority delegated to me by the
Administrator, the FAA amends 14 CFR part 39 as follows:

PART 39--AIRWORTHINESS DIRECTIVES

1. The authority citation for part 39 continues to read as follows:

    Authority:  49 U.S.C. 106(g), 40113, 44701.

Sec.  39.13  [Amended]

2. The FAA amends Sec.  39.13 by adding the following new airworthiness
directive: