[Federal Register Volume 90, Number 239 (Tuesday, December 16, 2025)]
[Rules and Regulations]
[Pages 58145-58148]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2025-22848]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2025-5385; Project Identifier MCAI-2025-01589-R;
Amendment 39-23213; AD 2025-25-05]
RIN 2120-AA64
Airworthiness Directives; Airbus Helicopters Deutschland GmbH
(AHD) Helicopters
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Final rule; request for comments.
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SUMMARY: The FAA is adopting a new airworthiness directive (AD) for all
Airbus Helicopters Deutschland GmbH (AHD) Model BO-105A, BO-105C, BO-
105S, BO-105LS A-3, MBB-BK 117 A-3, MBB-BK 117 A-4, MBB-BK 117 B-1,
MBB-BK 117 B-2, and MBB-BK 117 C-1 helicopters. This AD was prompted by
a report of a crack found on the fork lever of the mixing lever
assembly. This AD requires visually inspecting the fork lever for
cracks and the mixing lever assembly for missing components, damage, or
corrosion. Depending on the results of these inspections, this AD
requires taking corrective action and reporting the results of the
inspection to the manufacturer. Lastly, this AD prohibits installing
affected fork levers unless certain requirements are met. The FAA is
issuing this AD to address the unsafe condition on these products.
DATES: This AD is effective December 31, 2025.
The Director of the Federal Register approved the incorporation by
reference of a certain publication listed in this AD as of December 31,
2025.
The FAA must receive comments on this AD by January 30, 2026.
ADDRESSES: You may send comments, using the procedures found in 14 CFR
11.43 and 11.45, by any of the following methods:
Federal eRulemaking Portal: Go to regulations.gov. Follow
the instructions for submitting comments.
Fax: (202) 493-2251.
Mail: U.S. Department of Transportation, Docket
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New
Jersey Avenue SE, Washington, DC 20590.
Hand Delivery: Deliver to Mail address above between 9
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
AD Docket: You may examine the AD docket at regulations.gov under
Docket No. FAA-2025-5385; 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, the mandatory continuing airworthiness
information (MCAI), any comments received, and other information. The
street address for Docket Operations is listed above.
Material Incorporated by Reference:
For European Union Aviation Safety Agency (EASA) material
identified in this final rule, contact EASA, Konrad-Adenauer-Ufer 3,
50668 Cologne, Germany; telephone +49 221 8999 000; email
[email protected]; internet easa.europa.eu. You may find the EASA
material on the EASA website at ad.easa.europa.eu.
You may view this material at the FAA, Office of the
Regional Counsel, Southwest Region, 10101 Hillwood Pkwy., Room 6N-321,
Fort Worth, TX 76177. 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-2025-5385.
FOR FURTHER INFORMATION CONTACT: Steven Warwick, Aviation Safety
Engineer, FAA, 1600 Stewart Avenue, Suite 410, Westbury, NY 11590;
phone: (817) 222-5225; email: [email protected].
SUPPLEMENTARY INFORMATION:
Comments Invited
The FAA invites you to send any written data, views, or arguments
about this final rule. Send your comments using a method listed under
ADDRESSES. Include ``Docket No. FAA-2025-5385; Project Identifier MCAI-
2025-01589-R'' at the beginning of your comments. The most helpful
comments reference a specific portion of the final rule, explain the
reason for any recommended change, and include supporting data. The FAA
will consider all comments received by the closing date and may amend
this final rule because of those comments.
Except for Confidential Business Information (CBI) as described in
the following paragraph, and other information as described in 14 CFR
11.35, the FAA will post all comments received, without change, to
regulations.gov, including any personal information you provide. The
agency will also post a report summarizing each substantive verbal
contact received about this final rule.
Confidential Business Information
CBI is commercial or financial information that is both customarily
and actually treated as private by its owner. Under the Freedom of
Information Act (FOIA) (5 U.S.C. 552), CBI is exempt from public
disclosure. If your comments responsive to this AD contain commercial
or financial information that is customarily treated as private, that
you actually treat as private, and that is relevant or responsive to
this AD, it is important that you clearly designate the submitted
comments as CBI. Please mark each page of your submission containing
CBI as ``PROPIN.'' The FAA will treat such marked submissions as
confidential under the FOIA, and they will not be placed in the public
docket of this AD. Submissions containing CBI should be sent Steven
Warwick, Aviation Safety Engineer, FAA, 1600 Stewart Avenue, Suite 410,
Westbury, NY 11590. Any commentary that the FAA receives which is not
specifically designated as CBI will be placed in the public docket for
this rulemaking.
Background
EASA, which is the Technical Agent for the Member States of the
European Union, has issued EASA AD 2025-0217, dated October 1, 2025
(EASA AD 2025-0217) (also referred to as the MCAI), to correct an
unsafe condition on AHD Model BO105 A, BO105 C, BO105 D, BO105 S, BO105
LS A-3 (including helicopters modified in accordance with EASA
Supplemental Type Certificate (STC) 10039633), or previously by LBA STC
EMZ NR. 0654/3058 (so called ``Superlifter''), MBB-BK 117 A-3, MBB-BK
117 A-4, MBB-BK 117 B-1, MBB-BK 117 B-2, and MBB-BK 117 C-1
helicopters. The MCAI states that there was a report of a crack on the
fork lever of a Model MBB-BK117 helicopter. The MCAI further states
that due to similarity of design, the same unsafe condition could also
affect Model BO105 helicopters. EASA considers this MCAI an interim
action and further action may follow.
[[Page 58146]]
The FAA is issuing this AD to detect and address any cracks on the
fork lever, which could result in failure of the fork lever, and
consequent loss of control of the helicopter.
You may examine the MCAI in the AD docket at regulations.gov under
Docket No. FAA-2025-5385.
Material Incorporated by Reference Under 1 CFR Part 51
The FAA reviewed EASA AD 2025-0217, which specifies procedures for
inspecting certain part-numbered fork levers for cracks and inspecting
the mixing lever assembly for certain conditions (missing components,
damage, or corrosion). Based on the inspection results, EASA AD 2025-
0217 specifies procedures for replacing affected parts and reporting
the inspection results to the manufacturer. Additionally, EASA AD 2025-
0217 prohibits installing an affected fork lever unless certain
requirements are met.
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.
FAA's Determination
These products have been approved by the civil aviation authority
(CAA) of another country and are approved for operation in the United
States. Pursuant to the FAA's bilateral agreement with this State of
Design Authority, that authority has notified the FAA of the unsafe
condition described in the MCAI referenced above. The FAA is issuing
this AD after determining that the unsafe condition described
previously is likely to exist or develop on other products of the same
type design.
AD Requirements
This AD requires accomplishing the actions specified in EASA AD
2025-0217, described previously, as incorporated by reference, except
for any differences identified as exceptions in the regulatory text of
this AD. See ``Differences Between this AD and the MCAI and Referenced
Material'' for a discussion of the general differences included in this
AD.
Differences Between This AD and the MCAI and Referenced Material
The MCAI applies to AHD Model BO105 D helicopters, whereas this AD
does not because that model does not have an FAA type certificate.
Where the material referenced in EASA AD 2025-0217 does not specify
instructions if there are any doubts on the result from the visual
inspection, create a Technical Event (TE) on WebTEK for further
instructions, this AD requires, before further flight, performing a
borescope inspection on the fork lever if there is a line having no
visible gap or misalignment.
Explanation of Required Compliance Information
In the FAA's ongoing efforts to improve the efficiency of the AD
process, the FAA developed a process to use some CAA ADs as the primary
source of information for compliance with requirements for
corresponding FAA ADs. The FAA has been coordinating this process with
manufacturers and CAAs. As a result, EASA AD 2025-0217 is incorporated
by reference in this AD. This AD requires compliance with EASA AD 2025-
0217 in its entirety through that incorporation, except for any
differences identified as exceptions in the regulatory text of this AD.
Using common terms that are the same as the heading of a particular
section in EASA AD 2025-0217 does not mean that operators need comply
only with that section. For example, where the AD requirement refers to
``all required actions and compliance times,'' compliance with this AD
requirement is not limited to the section titled ``Required Action(s)
and Compliance Time(s)'' in EASA AD 2025-0217. Material required by
EASA AD 2025-0217 for compliance will be available at regulations.gov
under Docket No. FAA-2025-5385 after this AD is published.
Justification for Immediate Adoption and Determination of the Effective
Date
Section 553(b) of the Administrative Procedure Act (APA) (5 U.S.C.
551 et seq.) authorizes agencies to dispense with notice and comment
procedures for rules when the agency, for ``good cause,'' finds that
those procedures are ``impracticable, unnecessary, or contrary to the
public interest.'' Under this section, an agency, upon finding good
cause, may issue a final rule without providing notice and seeking
comment prior to issuance. Further, section 553(d) of the APA
authorizes agencies to make rules effective in less than thirty days,
upon a finding of good cause.
An unsafe condition exists that requires the immediate adoption of
this AD without providing an opportunity for public comments prior to
adoption. The FAA has found that the risk to the flying public
justifies forgoing notice and comment prior to adoption of this rule
because the affected component is part of an assembly that is critical
to the flight control of a helicopter, such that if a failure occurs in
the affected part, loss of control of a helicopter could occur. The FAA
has no information pertaining to the extent of fatigue of the affected
component that may currently exist in helicopters or how quickly the
condition may propagate to failure. Thus, the affected helicopters must
be inspected no later than 30 days with higher usage helicopters in a
shorter period of time if utilized more than 110 hours time-in-service
in 30 days. This compliance time is shorter than the time necessary for
the public to comment and for publication of the final rule.
Accordingly, notice and opportunity for prior public comment are
impracticable and contrary to the public interest pursuant to 5 U.S.C.
553(b).
In addition, the FAA finds that good cause exists pursuant to 5
U.S.C. 553(d) for making this amendment effective in less than 30 days,
for the same reasons the FAA found good cause to forgo notice and
comment.
Regulatory Flexibility Act
The requirements of the Regulatory Flexibility Act (RFA) do not
apply when an agency finds good cause pursuant to 5 U.S.C. 553 to adopt
a rule without prior notice and comment. Because the FAA has determined
that it has good cause to adopt this rule without prior notice and
comment, RFA analysis is not required.
Interim Action
The FAA considers that this AD is an interim action. This unsafe
condition is still under investigation by the manufacturer and,
depending on the results of that investigation, the FAA may consider
further rulemaking action.
Costs of Compliance
The FAA estimates that this AD affects 40 helicopters of U.S.
registry.
The FAA estimates the following costs to comply with this AD:
[[Page 58147]]
Estimated Costs
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Cost per Cost on U.S.
Action Labor cost Parts cost product operators
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Inspect the fork lever................... 1 work-hour x $85 per hour $0 $85 $3,400
= $85.
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The FAA estimates the following costs to do any repairs or
replacements that would be required based on the results of the
inspection. The agency has no way of determining the number of
helicopters that might need these repairs or replacements:
On-Condition Costs
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Action Labor cost Parts cost Cost per product
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Replace fork lever.................... 8 work-hours x $85 per $11,641 $12,321.
hour = $680.
Inspect mixing lever assembly......... Up to 6 work-hours x $85 0 Up to $510.
per hour = $510.
Replace mixing lever assembly......... 1 work-hour x $85 per 22,103 $22,188.
hour = $85.
Replace mixing lever ball bearings.... 8 work-hours x $85 per 334 $1,014.
hour = $680.
Report inspection results............. 1 work-hour x $85 per 0 $85.
hour = $85.
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Paperwork Reduction Act
A federal agency may not conduct or sponsor, and a person is not
required to respond to, nor shall a person be subject to a penalty for
failure to comply with a collection of information subject to the
requirements of the Paperwork Reduction Act unless that collection of
information displays a currently valid OMB Control Number. The OMB
Control Number for this information collection is 2120-0056. Public
reporting for this collection of information is estimated to take
approximately 1 hour per response, including the time for reviewing
instructions, searching existing data sources, gathering and
maintaining the data needed, and completing and reviewing the
collection of information. All responses to this collection of
information are mandatory. Send comments regarding this burden estimate
or any other aspect of this collection of information, including
suggestions for reducing this burden, to: Information Collection
Clearance Officer, Federal Aviation Administration, 10101 Hillwood
Parkway, Fort Worth, TX 76177-1524.
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, and
(2) Will not affect intrastate aviation in Alaska.
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:
2025-25-05 Airbus Helicopters Deutschland GmbH (AHD): Amendment 39-
23213; Docket No. FAA-2025-5385; Project Identifier MCAI-2025-01589-
R.
(a) Effective Date
This airworthiness directive (AD) is effective December 31,
2025.
(b) Affected ADs
None.
(c) Applicability
This AD applies to Airbus Helicopters Deutschland GmbH (AHD)
Model BO-105A, BO-105C, BO-105S, BO-105LS A-3, MBB-BK 117 A-3, MBB-
BK 117 A-4, MBB-BK 117 B-1, MBB-BK 117 B-2, and MBB-BK 117 C-1
helicopters, including those Model BO-105LS A-3 helicopters with FAA
Supplemental Type Certificate (STC) SR00043RD installed,
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 crack on the fork lever of
the mixing lever assembly. The FAA is issuing this AD to detect and
address any cracks on the fork lever, which could result in failure
of the fork lever and consequent loss of control of the helicopter.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) Requirements
Except as specified in paragraph (h) of this AD: Comply with all
required actions and compliance times specified in, and in
accordance with, European Union Aviation
[[Page 58148]]
Safety Agency AD 2025-0217, dated October 1, 2025 (EASA AD 2025-
0217).
(h) Exceptions to EASA AD 2025-0217
(1) Where EASA AD 2025-0217 refers to its effective date, this
AD requires using the effective date of this AD.
(2) Where EASA AD 2025-0217 specifies compliance in terms of
flight hours, this AD requires using hours time-in-service.
(3) Where paragraph (1) of EASA AD 2025-0217 specifies ``for
condition'', this AD requires replacing that text with ``for missing
locking devices, deformation, scratches, scrapes, gouges, missing
surface finish, bearing play, bearing roughness, or corrosion''.
(4) Where paragraph (3) of EASA AD 2025-0217 specifies any
discrepancy, for the purpose of this AD a discrepancy can be defined
as any missing components, damage (missing locking devices,
deformation, scratches, scrapes, gouges, missing surface finish,
bearing play, bearing roughness), or corrosion.
(5) Where the material referenced in EASA AD 2025-0217 specifies
``In case of any doubts on the result from the visual inspection,
create an Technical Event (TE) on WebTEK for further instructions'',
this AD requires replacing that text with ``if there is a line
having no visible gap or misalignment, before further flight,
perform a borescope inspection on the fork lever to determine if the
line is a scratch or a crack''.
(6) Where the material referenced in EASA AD 2025-0217 specifies
discarding parts, this AD does not require that action.
(7) Where paragraph (4) of EASA AD 2025-0217 specifies to report
the inspection results to AHD and that the ASB [Alert Service
Bulletin] provides instructions which constitute an acceptable
method to comply, for this AD, report results directly to Airbus
Helicopters within 10 days after accomplishing the inspection
required by this AD.
(8) Where the material referenced in EASA AD 2025-0217 specifies
``If the inspection shows no irregular results, proceed with Section
3.B.3'', this AD does not require this action.
(9) This AD does not adopt the ``Remarks'' section of EASA AD
2025-0217.
(i) Special Flight Permits
Special flight permits are prohibited.
(j) Alternative Methods of Compliance (AMOCs)
(1) The Manager, International Validation 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 International Validation Branch, send it to the
attention of the person identified in paragraph (k) 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 responsible Flight Standards Office.
(k) Additional Information
For more information about this AD, contact Steven Warwick,
Aviation Safety Engineer, FAA, 1600 Stewart Avenue, Suite 410,
Westbury, NY 11590; phone: (817) 222-5225; email:
[email protected].
(l) 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) European Union Aviation Safety Agency (EASA) AD 2025-0217,
dated October 1, 2025.
(ii) [Reserved]
(3) For EASA material identified in this AD, contact EASA,
Konrad-Adenauer-Ufer 3, 50668 Cologne, Germany; phone: +49 221 8999
000; email: [email protected]; website: easa.europa.eu. You may
find the EASA material on the EASA website at ad.easa.europa.eu.
(4) You may view this material at the FAA, Office of the
Regional Counsel, Southwest Region, 10101 Hillwood Pkwy., 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 December 10, 2025.
Steven W. Thompson,
Acting Deputy Director, Compliance & Airworthiness Division, Aircraft
Certification Service.
[FR Doc. 2025-22848 Filed 12-11-25; 4:15 pm]
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