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PROPOSED AD AIRBUS HELICOPTERS: Docket No. FAA-2024-2332; Project Identifier MCAI-2022-01479-R.
(a) COMMENTS DUE DATE

    The FAA must receive comments on this  airworthiness directive (AD) by
    December 2, 2024.

(b) AFFECTED ADS

    None.

(c) APPLICABILITY

    This  AD  applies  to  Airbus  Helicopters  AS332C,  AS332C1,  AS332L,
    AS332L1, AS332L2, AS355E,  AS355F, AS355F1, AS355F2,  AS355N, AS355NP,
    AS-365N2, AS 365 N3, EC 155B, EC155B1, EC225LP, SA-365N, and  SA-365N1
    helicopters, certificated  in any  category, with  a collective  pitch
    handle installed on a pilot  or co-pilot collective stick having  part
    number  (P/N) 704A41-1100-42,  704A41-1100-50, 704A41-1100-56,  704A41
    -1100-57, 704A41-1100-60, 704A41-1100-67, 704A41-1100-68,  704A41-1100
    -97, 704A41-1100-98,  704A41-1100-99, 704A41-1101-14,  704A41-1101-30,
    or 704A41-1101-32, as applicable to your model helicopter.

(d) SUBJECT

    Joint Aircraft System Component (JASC) Code: 2510, Flight  compartment
    equipment.

(e) UNSAFE CONDITION

    This AD was prompted by a report of an unintentional activation of the
    hoist  shear-button  on the  collective  pitch handle  during  a night
    flight. The FAA is  issuing this AD to  detect and address fatigue  of
    the spring in the hoist shear-button safety-cap on the left and  right
    collective  pitch handles.  The unsafe  condition, if  not  addressed,
    could  result  in  an  unintended  shearing  of  the  hoist  cable and
    subsequent injury to the hoisted person.

(f) COMPLIANCE

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

(g) REQUIRED ACTIONS

(1) For helicopters  identified in paragraph  (c) of this  AD that have  a
    hoist  installed,  within  50 hours  time-in-service  (TIS)  after the
    effective date of this AD,  and thereafter at intervals not  to exceed
    12 months TIS,  check the operation  of the hoist  shear-button safety
    -cap on each applicable  collective pitch handle by  accomplishing the
    actions required by paragraphs (g)(1)(i) through (iii) of this AD,  as
    applicable.  The owner/operator  (pilot) holding  at least  a  private
    pilot  certificate  may  perform  the  checks  required  by paragraphs
    (g)(1)(i) through  (iii) of  this AD  and must  enter compliance  with
    these paragraphs into the helicopter maintenance records in accordance
    with 14 CFR 43.9(a) and 91.417(a)(2)(v). The record must be maintained
    as required by 14 CFR 91.417, 121.380, or 135.439.

(i) Place your thumb  under the safety-cap and  lift the  safety-cap  to a
    less-than  halfway position.  Remove your  thumb and  verify that  the
    safety-cap goes  to the  fully open  position or  that the  safety-cap
    returns to  the fully  closed position.  Repeat these  actions no less
    than two more times. If the safety-cap stays in the less-than  halfway
    position, or the safety-cap does not fully close or fully open  during
    any instance of the actions required by this paragraph, before further
    flight, a  person authorized  under 14  CFR 43.3  must accomplish  the
    actions required by paragraph (g)(2) of this AD.

(ii) Place your thumb  under the safety-cap and  lift the  safety-cap to a
     halfway position. Remove  your thumb and  verify that the  safety-cap
     goes to the fully open position or that the safety-cap returns to the
     fully closed  position. Repeat  these actions  no less  than two more
     times.  If  the safety-cap  stays  in the  halfway  position, or  the
     safety-cap does not fully close or fully open during any instance  of
     the  actions required  by this  paragraph, before  further flight,  a
     person  authorized  under 14  CFR  43.3 must  accomplish  the actions
     required by paragraph (g)(2) of this AD.

(iii) Place your thumb under the safety-cap and lift the  safety-cap to  a
      more-than halfway position. Remove your thumb and verify the  safety
      -cap goes to the fully open position or that the safety-cap  returns
      to the fully closed position. Repeat these actions no less than  two
      more  times.  If  the  safety-cap  stays  in  the  more-than halfway
      position,  or the  safety-cap does  not fully  close or  fully  open
      during  any  instance of  the  actions required  by  this paragraph,
      before further flight,  a person authorized  under 14 CFR  43.3 must
      accomplish the actions required by paragraph (g)(2) of this AD.

(2) If  the safety-cap stays in  the less-than  halfway, halfway, or more-
    than halfway position, or the safety-cap does not fully close or fully
    open during  any of  instance of  the actions  required by  paragraphs
    (g)(1)(i) through (iii) of this AD, before further flight, remove  the
    spring from service and replace it with an airworthy spring.

(3) As  an alternative  to replacing  the spring  as required by paragraph
    (g)(2)  of  this AD,  accomplish  the actions  required  by paragraphs
    (g)(3)(i) and (ii) of this AD.

(i) Before further  flight, fabricate a  placard with a  font size greater
    than or equal to 4 mm  (.157 in), stating the following: "NIGHT  HOIST
    OPERATIONS PROHIBITED". The  placard must have  a red background  with
    white  font color  or a  white  background  with red  font  color. The
    placard must not  be erasable and  must be attached  to the instrument
    panel, visible to the pilot and co-pilot.

(ii) Within  150 hours  TIS after  accomplishing the  actions required  by
     paragraph (g)(3)(i) of this AD,  remove the spring of the  safety-cap
     from service and replace it with an airworthy spring, and remove  the
     placard from service.

(4) For helicopters  identified in paragraph  (c) of this  AD that do  not
    have a  hoist installed,  before installation  of a  hoist's removable
    parts  on  the helicopter,  accomplish  the check  and  as applicable,
    corrective action, required by  paragraphs (g)(1) through (3)  of this
    AD.

(h) PARTS INSTALLATION LIMITATIONS

    As of the effective date of this AD, do not install on any  helicopter
    a collective pitch handle having a P/N identified in paragraph (c)  of
    this AD, or any pilot  or co-pilot collective stick with  a collective
    pitch  handle having  a P/N  identified in  paragraph (c)  of this  AD
    installed,  unless the  check and  as applicable,  corrective  action,
    required by paragraphs (g)(1) and (2) of this AD have been done or the
    collective pitch handle is new (zero total hours TIS).

(i) 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  Branch, send  it  to the  attention  of the
    person identified  in paragraph  (j) 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.

(j) RELATED INFORMATION

    For  more information  about this  AD, contact  Dan McCully,  Aviation
    Safety Engineer,  FAA, 1600  Stewart Avenue,  Suite 410,  Westbury, NY
    11590; phone: (404) 474-5548; email: william.mccully@faa.gov.

(k) MATERIAL INCORPORATED BY REFERENCE

    None.

Issued on  October 9,  2024. Steven  W. Thompson,  Acting Deputy Director,
Compliance & Airworthiness Division, Aircraft Certification Service.

DATES: The FAA must receive comments on this NPRM by December 2, 2024.
PREAMBLE 
DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2024-2332; Project Identifier MCAI-2022-01479-R]
RIN 2120-AA64

Airworthiness Directives; Airbus Helicopters

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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

SUMMARY: The FAA proposes to adopt a new airworthiness directive (AD) 
for certain Airbus Helicopters Model AS332C, AS332C1, AS332L, AS332L1, 
AS332L2, AS355E, AS355F, AS355F1, AS355F2, AS355N, AS355NP, AS-365N2, 
AS 365 N3, EC 155B, EC155B1, EC225LP, SA-365N, and SA-365N1 
helicopters. This proposed AD was prompted by a report of an 
unintentional activation of the hoist shear-button (shear-button) on 
the collective pitch handle during a night flight. This proposed AD 
would require checking the operation of the shear-button safety-cap on 
each applicable collective pitch handle and prohibit installing certain 
part-numbered collective pitch handles or collective sticks with those 
part-numbered collective pitch handles installed unless certain 
requirements are met. The FAA is proposing this AD to address the 
unsafe condition on these products.

DATES: The FAA must receive comments on this NPRM by December 2, 2024.

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-2024-2332; 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 NPRM, any comments received, and other 
information. The street address for Docket Operations is listed above.

    Related Material: For Airbus Helicopters material identified in 
this AD, contact Airbus Helicopters, 2701 North Forum Drive, Grand 
Prairie, TX 75052; phone: (972) 641-0000 or (800) 232-0323; fax: (972) 
641-3775; or at airbus.com/en/products-services/helicopters/hcare-services/airbusworld.

FOR FURTHER INFORMATION CONTACT: Dan McCully, Aviation Safety Engineer, 
FAA, 1600 Stewart Avenue, Suite 410, Westbury, NY 11590; phone: (404) 
474-5548; email: william.mccully@faa.gov.

SUPPLEMENTARY INFORMATION:

Comments Invited

    The FAA invites you to send any written relevant data, views, or 
arguments about this proposal. Send your comments to an address listed 
under ADDRESSES. Include "Docket No. FAA-2024-2332; Project Identifier 
MCAI-2022-01479-R" at the beginning of your comments. The most helpful 
comments reference a specific portion of the proposal, 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 proposal 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 NPRM.

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 NPRM 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 NPRM, 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 NPRM. Submissions containing CBI should be sent to Dan 
McCully, Aviation Safety Engineer, FAA, 1600 Stewart Avenue, Suite 410, 
Westbury, NY 11590; phone: (404) 474-5548; email: 
william.mccully@faa.gov. Any commentary that the FAA receives which is 
not specifically designated as CBI will be placed in the public docket 
for this rulemaking.

Background

    The European Union Aviation Safety Agency (EASA), which is the 
Technical Agent for the Member States of the European Union, has issued 
EASA AD 2022-0220, dated November 16, 2022 (EASA AD 2022-0020), to 
correct an unsafe condition on Airbus Helicopters Model AS 355 E, AS 
355 F, AS 3555 F1, AS 355 F2, AS 355 N, AS 355 NP, SA 365 N, SA 365 N1, 
AS 365 N2, AS 365 N3, EC 155 B, EC 155 B1, AS 332 C, AS 332 C1, AS 332 
L, AS 332 L1, AS 332 L2, and EC 225 LP helicopters, all serial numbers 
equipped with hoist provisions (hoist fixed parts).

    EASA AD 2022-0020 advises of a report of an inadvertent activation 
of the shear-button on a collective pitch handle. EASA AD 2022-0020 
states this occurred during a night flight when the pilot was turning 
on the headlight adjacent to the shear-button, which is protected by a 
safety-cap that is fitted with a spring. Additionally, EASA AD 2022-
0220 states that further investigation determined aging of the spring 
may have led to improper functioning of the safety-cap.

    Accordingly, EASA AD 2022-0220 requires accomplishing an 
operational check of the shear-button safety-cap of each applicable 
collective pitch handle and, depending on the results, replacing the 
spring or deferring replacement of the spring by fabricating and 
installing a placard prohibiting use of the hoist during night flights, 
informing all flight crew, and operating the helicopter accordingly. 
EASA AD 2022-0220 also prohibits installing certain part-numbered 
collective pitch handles or certain part-numbered collective sticks 
with those part-numbered collective pitch handles installed unless the 
operational check and as applicable, corrective action is done, or it 
is a new collective pitch handle.

    You may examine EASA AD 2022-0220 in the AD docket at 
regulations.gov under Docket No. FAA-2024-2332.

Related Material

    The FAA reviewed Airbus Helicopters Alert Service Bulletin (ASB) 
AS332-25.03.97, Revision 0, dated October 4, 2022; Airbus Helicopters 
ASB AS355-25.01.38, Revision 0, dated October 4, 2022; Airbus 
Helicopters ASB AS365-25.01.91, Revision 1, dated November 3, 2022; 
Airbus Helicopters ASB EC155-25A160, Revision 0, dated October 4, 2022; 
and Airbus Helicopters ASB EC225-25A293, Revision 0, dated October 4, 
2022. This material specifies procedures for inspecting the spring of 
the shear-button safety-cap on the collective pitch handle to determine 
whether the safety-cap maintains either in a fully closed or fully open 
position. Depending on the results, this material specifies procedures 
for replacing an affected spring or attaching a label (placard) to 
prohibit night flights.

FAA's Determination

    These products have been approved by the 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, it has notified the FAA of the unsafe condition described in 
its AD. The FAA is issuing this NPRM after determining that the unsafe 
condition described previously is likely to exist or develop on other 
products of these same type designs.

Proposed AD Requirements in This NPRM

    This proposed AD would require checking the spring of the 
collective pitch handle for correct positioning of the shear-button 
safety-cap and, depending on the results, replacing the spring or 
deferring replacement of the spring and installing a placard and 
prohibiting night flying during the deferment. The owner/operator 
(pilot) holding at least a private pilot certificate may perform the 
check and must enter compliance with the applicable paragraphs of the 
proposed AD into the helicopter maintenance records in accordance with 
14 CFR 43.9(a) and 91.417(a)(2)(v). The pilot may perform this check 
because it only involves lifting the safety-cap and verifying whether 
it automatically returns to an intended position. This check could be 
performed equally well by a pilot or a mechanic. This is an exception 
to the FAA's standard maintenance regulations.

    This proposed AD would also prohibit installing certain part-
numbered collective pitch handles or collective sticks with those part-
numbered collective pitch handles installed unless the operational 
check and, as applicable, corrective action, is done, or it is a new 
collective pitch handle.

Differences Between This Proposed AD and EASA AD 2022-0220

    EASA AD 2022-0220 specifies a one-time inspection of the spring, 
whereas this proposed AD would require repetitively inspecting the 
spring at intervals not to exceed 12 months time-in-service.

    EASA AD 2022-0220 allows deferring replacement of a deficient 
spring provided that a placard prohibiting use of the hoist at night is 
installed, all flight crew are informed and, thereafter, that the 
helicopter is operated accordingly, whereas this proposed AD would not 
require informing any flight crew. Compliance with such requirements in 
an AD is impracticable to demonstrate or track on an ongoing basis; 
therefore, an AD requirement to inform all flight crew is 
unenforceable.

Costs of Compliance

    The FAA estimates that this AD, if adopted as proposed, would 
affect 66 helicopters of U.S. Registry. Labor rates are estimated at 
$85 per work-hour. Based on these numbers, the FAA estimates the 
following costs to comply with this proposed AD.

    Checking each safety-cap would take 1 work-hour for an estimated 
cost of up to $85 per helicopter and $5,610 for the U.S. fleet, per 
check cycle.

    If required, replacing a spring would take 1 work-hour and parts 
would cost $25 for an estimated cost of $110 per replacement.

    Fabricating and installing a placard would take 0.5 work-hour and 
parts would cost $25 for an estimated cost of $68 per helicopter.

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

    The FAA determined that this proposed AD would not have federalism 
implications under Executive Order 13132. This proposed AD would 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 this proposed regulation:

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

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

    (3) Would 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 Proposed Amendment

    Accordingly, under the authority delegated to me by the 
Administrator, the FAA proposes to amend 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: