Airworthiness Directives; Airbus Helicopters Deutschland GmbH (AHD) Helicopters

Issuing agencies

Abstract

The FAA is adopting a new airworthiness directive (AD) for certain Airbus Helicopters Deutschland GmbH (AHD) Model EC135P1, EC135P2, EC135P2+, EC135P3, EC135T1, EC135T2, EC135T2+, EC135T3, EC635T2+, MBB-BK 117 C-2, and MBB-BK 117 D-2 helicopters. This AD was prompted by reports of cracks on the cable drum of the rescue hoist assembly. This AD requires repetitively inspecting the cable drum of certain rescue hoist assemblies for cracks and, depending on the results, replacing or repairing the cable drum of the rescue hoist assembly. This AD also prohibits the operation and the installation of an affected rescue hoist assembly on a helicopter, unless certain requirements are met. The FAA is issuing this AD to address the unsafe condition on these products.

Full Text

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<title>Federal Register, Volume 91 Issue 206 (Tuesday, October 27, 2026)</title>
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[Federal Register Volume 91, Number 206 (Tuesday, October 27, 2026)]
[Rules and Regulations]
[Pages 67457-67460]
From the Federal Register Online via the Government Publishing Office [<a href="http://www.gpo.gov">www.gpo.gov</a>]
[FR Doc No: 2026-21855]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2026-1326; Project Identifier MCAI-2025-00312-R; 
Amendment 39-23498; AD 2026-21-09]
RIN 2120-AA64


Airworthiness Directives; Airbus Helicopters Deutschland GmbH 
(AHD) Helicopters

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule.

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SUMMARY: The FAA is adopting a new airworthiness directive (AD) for 
certain Airbus Helicopters Deutschland GmbH (AHD) Model EC135P1, 
EC135P2, EC135P2+, EC135P3, EC135T1, EC135T2, EC135T2+, EC135T3, 
EC635T2+, MBB-BK 117 C-2, and MBB-BK 117 D-2 helicopters. This AD was 
prompted by reports of cracks on the cable drum of the rescue hoist 
assembly. This AD requires repetitively inspecting the cable drum of 
certain rescue hoist assemblies for cracks and, depending on the 
results, replacing or repairing the cable drum of the rescue hoist 
assembly. This AD also prohibits the operation and the installation of 
an affected rescue hoist assembly on a helicopter, 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 1, 2026.
    The Director of the Federal Register approved the incorporation by 
reference of a certain publication listed in this AD as of December 1, 
2026.

ADDRESSES: 
    AD Docket: You may examine the AD docket at <a href="http://regulations.gov">regulations.gov</a> under 
Docket No. FAA-2026-1326; 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 
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:
    <bullet> For European Union Aviation Safety Agency (EASA) material 
identified in this AD, contact EASA, Konrad-Adenauer-Ufer 3, 50668 
Cologne, Germany; phone: +49 221 8999 000; email: <a href="/cdn-cgi/l/email-protection#57161324173236243679322225382736793222"><span class="__cf_email__" data-cfemail="e1a0a592a184809280cf8494938e9180cf8494">[email&#160;protected]</span></a>; 
website: easa.europa.eu. You may find this material on the EASA website 
at ad.easa.europa.eu.
    <bullet> You may view this material at the FAA, Airworthiness 
Products Section, Operational Safety Branch, 10101 Hillwood Parkway, 
Fort Worth, TX 76177. For information on the availability of this 
material at the FAA, call (817) 222-5110. It is also available at 
<a href="http://regulations.gov">regulations.gov</a> under Docket No. FAA-2026-1326.

FOR FURTHER INFORMATION CONTACT: Steven Warwick, Aviation Safety 
Engineer, FAA, 1600 Stewart Avenue, Suite 410, Westbury, NY 11590; 
phone: (817) 222-5225; email: <a href="/cdn-cgi/l/email-protection#5221263724373c7c207c253320253b3139123433337c353d24"><span class="__cf_email__" data-cfemail="5e2d2a3b283b30702c70293f2c29373d351e383f3f70393128">[email&#160;protected]</span></a>.

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 certain AHD Model 
EC135P1, EC135P2, EC135P2+, EC135P3, EC135T1, EC135T2, EC135T2+, 
EC135T3, EC635T2+, MBB-BK 117 C-2, and MBB-BK 117 D-2 helicopters. The 
NPRM was published in the Federal Register on February 13, 2026 (91 FR 
6795). The NPRM was prompted by an MCAI, issued by EASA, which is the 
Technical Agent for the Member States of the European Union. EASA 
issued EASA AD 2025-0055, dated March 11, 2025 (EASA AD 2025-0055) 
(also referred to as the MCAI). The MCAI states that cracks were 
reported on a cable drum installed on certain part-numbered Goodrich 
rescue hoist assemblies. Additionally, the material referenced in the 
MCAI states that Goodrich determined that this occurrence was isolated 
to a batch of cable drums made from a plate material, which was 
determined to have increased susceptibility to corrosion-induced 
fatigue. This unsafe condition, if not addressed, could result in 
corrosion-induced fatigue of the cable drum, and consequent injuries to 
human load or individuals on the ground.
    In the NPRM, the FAA proposed to require repetitively inspecting 
the cable drum of certain rescue hoist assemblies for cracks and 
depending on the results, replacing or repairing the cable drum of the 
rescue hoist assembly. Additionally, in the NPRM the FAA proposed to 
prohibit the operation and the installation of an affected rescue hoist 
assembly on a helicopter, unless certain requirements are met. The FAA 
is issuing this AD to address the unsafe condition on these products.
    Additionally, since the FAA issued the NPRM, it was determined that 
the special flight permit restriction specified in paragraph (j) of the 
proposed rule is no longer needed. Accordingly, the FAA has revised 
this final rule by removing the special flight permit paragraph.

Discussion of Final Airworthiness Directive

Comments

    The FAA received comments from three commenters. The commenters 
were AHD, Onboard Systems Hoist and Winch, and an individual commenter. 
The following discussion presents the comments received on the NPRM and 
the FAA's response to these comments.

Request To Clarify Affected Parts

    An individual commenter requested that the FAA specify the affected 
part by serial number, part number, and manufacturing batches that have 
the highest risk. The commenter also stated that by including this 
information, it will avoid unnecessary repeated inspections which may 
delay rescue missions.
    The FAA disagrees with specifying or limiting this final rule by 
adding the serial number, part number, or manufacturing batch 
information. The AD already incorporates this information by reference, 
and the serial numbers associated with a subset of the affected part 
numbers are identified in the incorporated MCAI. Additionally, 
manufacturing batch information is not necessary to determine the 
affected parts, and all of the identified part numbers present an 
equivalent level of risk; none represent a ``highest risk'' category as 
suggested by the commenter. The FAA did not change this AD as a result 
of this comment.

[[Page 67458]]

Request To Revise Inspection Requirements

    One individual commenter requested that the FAA clarify why only 
visual inspections are required and not other forms of testing or 
inspections. The commenter stated that visual inspections may not 
detect small, undetectable cracks that are caused by corrosion, which 
may grow faster than expected. The commenter further stated that by 
including this information, it will help determine how often 
inspections must occur to ensure safe cable drums.
    The FAA infers the commenter is requesting the inspection methods 
increase to other forms of inspections and not just visual inspections 
alone. The FAA disagrees with revising the inspection method outside of 
the requirements that were proposed in the NPRM. EASA, the State of 
Design authority for these helicopters, determined the appropriate 
inspection methodology and criteria for the required inspections. The 
FAA agrees with EASA. The FAA did not change this AD as a result of 
this comment.

Request To Revise the Inspection Requirements

    AHD and Onboard Systems Hoist and Winch (Onboard Systems) both 
requested that the FAA revise or remove the inspection requirements of 
paragraphs (h)(3) and (4) of the proposed AD.
    Onboard Systems requested the FAA revise paragraph (h)(3) of the 
proposed AD by allowing maintenance personnel a limited compliance time 
to confirm indications of a crack with personnel at Airbus Helicopters 
or Onboard Systems Hoist and Winch prior to repairs. Onboard Systems 
stated the inspection process was carefully considered to ensure that 
cracks are detected well before they pose any risk of fracture, while 
also preventing the removal of essential search and rescue assets from 
service for misidentified indications. Additionally, Onboard Systems 
stated that they would have the operator send detailed images of the 
indication and if the indication could not be identified as benign, 
then they would require removing the part from the helicopter. AHD 
stated the proposed inspection as specified in paragraph (h)(3) of the 
proposed AD implies further changes to the inspection process, which 
could eliminate the 3mm minimum crack size criteria.
    The FAA disagrees with Onboard System request to revise the 
compliance time to confirm indications because the FAA may prioritize 
immediate action upon detection of potential safety concerns, such as 
cracks, to eliminate any risk of fracture that could compromise safety. 
However, the FAA agrees to revise paragraph (h)(3) of this AD by 
removing the criteria for contacting the Manager, International 
Validation Branch, or Airbus Helicopters' Design Organizational 
Approval if any cracks or suspected cracks longer than 3mm in length 
are found.
    Onboard Systems requested the FAA remove paragraph (h)(4) of the 
proposed AD. Onboard Systems stated if using more than 6X magnification 
and no minimum threshold, the risk of false indications increases 
exponentially. AHD requested the FAA remove paragraph (h)(4) of the 
proposed AD or revise by removing the words ``or higher.'' AHD stated 
the use of such high magnification could increase misidentifications or 
surface cracks, leading to false-positive indications. AHD stated this 
inspection deviations could lead to false-positive indications and the 
unnecessary grounding of search and rescue assets.
    The FAA acknowledges the commenter's concern to prevent unnecessary 
actions that may remove important resources essential to rescue 
missions and the FAA has determined that a crack length of 3 mm is too 
small to accurately detect with the unaided eye (1x magnification). 
However, the FAA agrees that a 4X-6X magnification is sufficient. 
Accordingly, the FAA has revised paragraph (h)(4) of this AD to specify 
that 4X-6X magnification is required for the visual inspection.

Conclusion

    These products have been approved by the civil aviation authority 
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 reviewed the relevant 
data, considered any comments received, 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 any other changes described previously, 
this AD is adopted as proposed in the NPRM. None of the changes will 
increase the economic burden on any operator.

Material Incorporated by Reference Under 1 CFR Part 51

    The FAA reviewed EASA AD 2025-0055, which specifies procedures for 
repetitively inspecting the cable drum installed on the rescue hoist 
assembly for cracks longer than 3 mm and, depending on the results, 
contacting the manufacturer for approved repair instructions. 
Additionally, the MCAI allows the installation of an affected rescue 
hoist assembly on a helicopter if it meets certain requirements. 
Finally, the MCAI prohibits the operation of an affected rescue hoist 
assembly after a certain effective date as specified in the MCAI.
    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.

Differences Between This AD and the MCAI

    The MCAI applies to AHD Model EC635 P2+, EC635 P3, EC635 T1, and 
EC635 T3 helicopters, whereas this AD does not because those models do 
not have an FAA type certificate.
    Where the MCAI specifies to contact the manufacturer for repair 
instructions, this AD requires repairing an affected rescue hoist 
assembly in accordance with a method approved by the Manager, 
International Validation Branch; EASA; or Airbus Helicopters' Design 
Organization Approval.

Costs of Compliance

    The FAA estimates that this AD affects 476 helicopters of U.S. 
registry.
    The FAA estimates the following costs to comply with this AD:

                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                                                                       Cost per    Cost on U.S.
                  Action                            Labor cost           Parts cost    product       operators
----------------------------------------------------------------------------------------------------------------
Visually inspect the cable drum..........  1 work-hour x $85 per hour            $0          $85         $40,460
                                            = $85.
----------------------------------------------------------------------------------------------------------------


[[Page 67459]]

    The FAA estimates the following costs to do any replacements that 
would be required based on the results of the required inspection. The 
agency has no way of determining the number of helicopters that might 
need this replacement:

                                       Estimated Costs for Optional Action
----------------------------------------------------------------------------------------------------------------
                    Action                                Labor cost              Parts cost   Cost per product
----------------------------------------------------------------------------------------------------------------
Replace rescue hoist assembly................  3.5 work-hours x $85 per hour =      $123,000            $123,298
                                                $298.
----------------------------------------------------------------------------------------------------------------

    The FAA has no way of determining the cost to repair a rescue hoist 
assembly or the number of helicopters that may require either repair or 
replacement of the rescue hoist assembly if any cracks are found in the 
cable drum that are of a certain length or more.

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:

2026-21-09 Airbus Helicopters Deutschland GmbH (AHD): Amendment 39-
23498; Docket No. FAA-2026-1326; Project Identifier MCAI-2025-00312-
R.

(a) Effective Date

    This airworthiness directive (AD) is effective December 1, 2026.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to Airbus Helicopters Deutschland GmbH (AHD) 
Model EC135P1, EC135P2, EC135P2+, EC135P3, EC135T1, EC135T2, 
EC135T2+, EC135T3, and EC635T2+ helicopters, certificated in any 
category, all serial numbers (S/N) up to 1999; and Model MBB-BK 117 
C-2 and MBB-BK 117 D-2 helicopters, certificated in any category, 
all S/Ns.
    Note 1 to paragraph (c): Helicopters with an EC135P3H 
designation are Model EC135P3 helicopters. Helicopters with an 
EC135T3H designation are Model EC135T3 helicopters.
    Note 2 to paragraph (c): Helicopters with an MBB-BK 117 C-2e 
designation are Model MBB-BK 117 C-2 helicopters.

(d) Subject

    Joint Aircraft System Component (JASC) Code 2500, Cabin 
equipment/furnishings.

(e) Unsafe Condition

    This AD was prompted by reports of cracks on the cable drum of 
the rescue hoist assembly. The FAA is issuing this AD to detect and 
correct cable drums installed on certain rescue hoist assemblies 
that have been manufactured with a certain plate material that could 
result in corrosion-induced fatigue of the cable drum. This unsafe 
condition, if not addressed, could result in failure of the cable 
drum and injuries to human load or individuals on the ground.

(f) Compliance

    Comply with this AD within the compliance times specified, 
unless already done.

(g) Requirements

    Except as specified in paragraphs (h) and (i) of this AD: comply 
with all required actions and compliance times specified in, and in 
accordance with, European Union Aviation Safety Agency (EASA) AD 
2025-0055, dated March 11, 2025 (EASA AD 2025-0055).

(h) Exceptions to EASA AD 2025-0055

    (1) Where EASA AD 2025-0055 refers to its effective date, this 
AD requires using the effective date of this AD.
    (2) Where EASA AD 2025-0055 requires compliance in terms of 
flight hours, this AD requires using hours time-in-service.
    (3) Where paragraph (2) of EASA AD 2025-0055 and the material 
referenced in EASA AD 2025-0055 specifies to contact a manufacturer 
for repair instructions, for this AD repair an affected rescue hoist 
assembly in accordance with a method approved by the Manager, 
International Validation Branch, FAA; EASA; or Airbus Helicopters' 
Design Organization Approval (DOA). If approved by the DOA, the 
approval must include the DOA-authorized signature.
    (4) Where the material referenced in EASA AD 2025-0055 specifies 
``magnifying glass 6X maximum,'' this AD requires replacing that 
text with ``4X-6X magnification''.
    (5) This AD does not adopt the ``Remarks'' section of EASA AD 
2025-0055.

(i) No Reporting Requirement

    Although the material referenced in EASA AD 2025-0055 specifies 
to submit certain information to the manufacturer, this AD does not 
require that action.

(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 local Flight 
Standards District Office, as appropriate. If sending information 
directly to the manager of the International Validation

[[Page 67460]]

Branch, send it to the attention of the person identified in 
paragraph (k) of this AD and email to: <a href="/cdn-cgi/l/email-protection#094844464a496f6868276e667f"><span class="__cf_email__" data-cfemail="581915171b183e3939763f372e">[email&#160;protected]</span></a>.
    (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.

(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: 
<a href="/cdn-cgi/l/email-protection#fc8f88998a9992d28ed28b9d8e8b959f97bc9a9d9dd29b938a"><span class="__cf_email__" data-cfemail="95e6e1f0e3f0fbbbe7bbe2f4e7e2fcf6fed5f3f4f4bbf2fae3">[email&#160;protected]</span></a>.

(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 2025-0055, 
dated March 11, 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: <a href="/cdn-cgi/l/email-protection#f9b8bd8ab99c988a98d79c8c8b968998d79c8c"><span class="__cf_email__" data-cfemail="5312172013363220327d3626213c23327d3626">[email&#160;protected]</span></a>; website: easa.europa.eu. You may 
find this material on the EASA website at ad.easa.europa.eu.
    (4) You may view this material at the FAA, Airworthiness 
Products Section, Operational Safety Branch, 10101 Hillwood Parkway, 
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 <a href="http://www.archives.gov/federal-register/cfr/ibr-locations">www.archives.gov/federal-register/cfr/ibr-locations</a> or email <a href="/cdn-cgi/l/email-protection#aaccd884c3c4d9dacfc9dec3c5c4eac4cbd8cb84cdc5dc"><span class="__cf_email__" data-cfemail="e68094c88f8895968385928f8988a688879487c8818990">[email&#160;protected]</span></a>.

    Issued on October 19, 2026.
Steven W. Thompson,
Acting Deputy Director, Compliance & Airworthiness Division, Aircraft 
Certification Service.
[FR Doc. 2026-21855 Filed 10-26-26; 8:45 am]
BILLING CODE 4910-13-P


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