Airworthiness Directives; Airbus Helicopters

[Federal Register Volume 88, Number 21 (Wednesday, February 1, 2023)]
[Rules and Regulations]
[Pages 6618-6620]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2023-01965]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2022-0987; Project Identifier MCAI-2021-01416-R; 
Amendment 39-22298; AD 2023-01-04]
RIN 2120-AA64


Airworthiness Directives; Airbus 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 all 
Airbus Helicopters Model AS350B, AS350BA, AS350B1, AS350B2, AS350B3, 
AS350D, AS355E, AS355F, AS355F1, AS355F2, AS355N, and AS355NP 
helicopters. This AD was prompted by an occurrence reported where 
during an inspection of a tail rotor head (TRH) pitch change spider, 
excessive play and excessive wear were detected, due to an unwanted 
rotating motion. This AD requires for helicopters with certain part-
numbered TRH spider pitch change units installed, inspecting for 
correct installation of the spider pitch change nut (nut); marking a 2 
to 5 mm wide black paint index mark and repetitively inspecting the 
alignment of the marking; and additional inspections and corrective 
actions if necessary. This AD also allows an affected part to be 
installed on a helicopter if certain requirements of this AD are met. 
The FAA is issuing this AD to address the unsafe condition on these 
products.

DATES: This AD is effective March 8, 2023.
    The Director of the Federal Register approved the incorporation by 
reference of certain publications listed in this AD as of March 8, 
2023.

ADDRESSES: 
    AD Docket: You may examine the AD docket at regulations.gov under 
Docket No. FAA-2022-0987; 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 European Union Aviation Safety 
Agency (EASA) AD, 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 Airbus Helicopters service information identified in 
this final rule, contact Airbus Helicopters, 2701 North Forum Drive, 
Grand Prairie, TX 75052; telephone (972) 641-0000 or (800) 232-0323; 
fax (972) 641-3775; or at airbus.com/helicopters/services/technical-support.html.
    <bullet> You may view this service information 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-2022-0987.
    Other Related Service Information: Other related Airbus Helicopters 
service information identified in this final rule is available at the 
Airbus Helicopters and FAA contact information under Material 
Incorporated by Reference above.

FOR FURTHER INFORMATION CONTACT: Stephanie Sunderbruch, Aerospace 
Engineer, Safety Risk Management Section, Systems Policy Branch, Policy 
& Innovation Division, FAA, 10101 Hillwood Pkwy., Fort Worth, TX 76177; 
telephone (817) 222-4659; email [email protected].

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 all Airbus Helicopters 
Model AS350B, AS350BA, AS350B1, AS350B2, AS350B3, AS350D, AS355E, 
AS355F, AS355F1, AS355F2, AS355N, and AS355NP helicopters. The NPRM 
published in the Federal Register on August 2, 2022 (87 FR 47141). The 
NPRM was prompted by EASA AD 2021-0282, dated December 17, 2021 (EASA 
AD 2021-0282), issued by EASA, which is the Technical Agent for the 
Member States of the European Union, to correct an unsafe condition for 
Airbus Helicopters, formerly Eurocopter and Aerospatiale, Model AS 350 
B, AS 350 BA, AS 350 BB, AS 350 B1, AS 350 B2, AS 350 B3, AS 350 D, AS 
355 E, AS 355 F, AS 355 F1, AS 355 F2, AS 355 N, and AS 355 NP 
helicopters, all serial numbers. EASA advises that an occurrence was 
reported where, during an inspection of a TRH pitch change spider, 
excessive play in the assembly and excessive wear on its parts were 
detected, which was due to an unwanted rotating motion. EASA advises 
that this condition, if not addressed, could result in loss of the TRH 
pitch change control and loss of control of the helicopter.
    Accordingly, EASA AD 2021-0282 requires a one-time check 
(inspection) of the nut for correct installation, accomplishing a black 
paint index marking, 2 to 5 mm wide, on the rotating spider and on the 
bearing spacer of the TRH spider pitch change unit, repetitive checks 
(inspections) of the marking alignment, and depending on the findings, 
accomplishment of additional inspections and corrective actions. The 
additional inspections include inspecting the TRH spider pitch change 
unit for corrosion; inspecting for rotation and wear on the faces of 
the bushes; visually inspecting the rotating plate and the rotating 
plate threads for damage; and inspecting the TRH spider pitch change 
unit if the mark is misaligned. The corrective actions include removing 
parts with corrosion from service; replacing bushes that rotate or have 
wear; and replacing damaged rotating plates. EASA AD 2021-0282 also 
specifies certain procedures for installation of the affected TRH 
spider pitch change unit.
    In the NPRM, the FAA proposed to require, for helicopters with 
certain part-numbered TRH spider pitch change units installed, 
inspecting for correct installation of the nut and depending on the 
results, inspecting the TRH spider pitch change unit for corrosion, 
inspecting for rotation and wear on the faces of the bushes, inspecting 
the rotating plate and the rotating plate threads for damage, and 
removing specified parts from service and replacing them with airworthy 
parts. In the NPRM, the FAA also proposed to require for helicopters 
with certain part-numbered TRH spider pitch change units installed, 
marking a 2 to 5 mm wide black paint index mark to identify the 
position of certain parts and after the initial marking, and thereafter 
at intervals not to exceed 10 hours time in service (TIS), visually 
inspecting the alignment of the marking; and additional inspections and 
corrective actions if necessary. Additionally, the NPRM proposed to 
allow an affected part to be installed on a helicopter if certain 
requirements of the NPRM are met.

[[Page 6619]]

    You may examine EASA AD 2021-0282 in the AD docket at 
regulations.gov under Docket No. FAA-2022-0987.

Discussion of Final Airworthiness Directive

Comments

    The FAA received comments from three commenters. The following 
presents the comments received on the NPRM and the FAA's response to 
each comment.

Comments Regarding the Repetitive Marking Alignment Inspections

    All three individuals requested that the FAA revise the proposed AD 
to allow an owner/operator (pilot) to perform the 10 hour TIS 
repetitive inspection of the black index mark after the initial 
inspection and marking. Two of the individuals stated allowing a pilot 
with the correct training and accreditation to perform the repetitive 
10 hour TIS visual inspection of the black index mark would be in line 
with the service information required by this AD.
    The FAA disagrees. The inspection requires training, and the 
exception to the FAA's standard maintenance regulations for AD actions 
does not allow a pilot to accomplish actions, including inspections, 
that require training. Accordingly, those inspections must be 
accomplished by a mechanic that meets the requirements of 14 CFR part 
65 subpart D.

Conclusion

    These helicopters have been approved by EASA and are approved for 
operation in the United States. Pursuant to the FAA's bilateral 
agreement with the European Union, EASA has notified the FAA of the 
unsafe condition described in its AD. The FAA reviewed the relevant 
data, considered the 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, this AD is adopted as proposed in the NPRM. 
None of the changes will increase the economic burden on any operator.

Related Service Information Under 1 CFR Part 51

    The FAA reviewed Airbus Helicopters Alert Service Bulletin (ASB) 
No. AS350-05.01.03, for Model AS350B, AS350BA, AS350B1, AS350B2, 
AS350B3, and AS350D helicopters and Airbus Helicopters ASB No. AS355-
05.00.86, for Model AS355E, AS355F, AS355F1, AS355F2, AS355N, and 
AS355NP helicopters, both Revision 0 and dated December 16, 2021, which 
include Figure 1 that identifies the position of the TRH pitch change 
unit and of the bearing spacer to be marked with a 2 to 5 mm wide black 
paint index mark. The service information also specifies procedures for 
inspecting the condition and installation of the nut; and inspecting 
the application and alignment of the black index mark on the TRH pitch 
change unit and the bearing spacer.
    This service information is reasonably available because the 
interested parties have access to it through their normal course of 
business or by the means identified in ADDRESSES.

Other Related Service Information

    The FAA also reviewed Airbus Helicopters Mechanical Repair Manual 
AS350 65-20-00-713, dated March 29, 2017, and Airbus Aircraft 
Maintenance Manual AS350 65-21-00, 4-9b, dated May 16, 2019, which 
specify disassembly and reassembly information for the TRH pitch change 
unit.

Differences Between This AD and the EASA AD

    EASA AD 2021-0282 applies to Model AS350BB helicopters, whereas 
this AD does not because that model is not FAA-type certificated. EASA 
AD 2021-0282 requires accomplishing a certain inspection using a 
magnifying lens, whereas this AD requires using a 5X or higher power 
magnifying glass to inspect instead.

Costs of Compliance

    The FAA estimates that this AD affects 976 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 AD.
    Inspecting the nut for correct installation takes about 0.25 work-
hour for an estimated cost of $21 per helicopter and up to $20,307 for 
the U.S. fleet.
    Inspecting the alignment of the marking takes about 0.10 work-hour 
for an estimated cost of $8.50 per helicopter per inspection and up to 
$8,219.50 for the U.S. fleet per inspection.
    Marking the position of the TRH pitch change unit with black paint 
takes about 0.25 work-hour for an estimated cost of $21 per helicopter 
and $20,307 for the U.S. fleet.
    If required, inspecting the TRH spider pitch change unit for 
corrosion, inspecting the faces of the bushes for rotation and wear, 
and inspecting the rotating plate and rotating plate threads for damage 
takes about 13 work-hours for an estimated cost of $1,105 per 
helicopter.
    If required, replacing the bushes takes about 1 work-hour and parts 
cost about $5,918, for an estimated cost of $6,003 per replacement.
    If required, replacing the rotating plate takes about 1 work-hour 
and parts cost about $27,375 for an estimated cost of $27,460 per 
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:

[[Page 6620]]

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:

2023-01-04 Airbus Helicopters: Amendment 39-22298; Docket No. FAA-
2022-0987; Project Identifier MCAI-2021-01416-R.

(a) Effective Date

    This airworthiness directive (AD) is effective March 8, 2023.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to all Airbus Helicopters Model AS350B, AS350BA, 
AS350B1, AS350B2, AS350B3, AS350D, AS355E, AS355F, AS355F1, AS355F2, 
AS355N, and AS355NP helicopters, certificated in any category.

(d) Subject

    Joint Aircraft Service Component (JASC) Code: 6420, Tail Rotor 
Head.

(e) Unsafe Condition

    This AD was prompted by an occurrence reported where, during an 
inspection of a tail rotor head (TRH) pitch change spider, excessive 
play and excessive wear were detected, due to an unwanted rotating 
motion. The FAA is issuing this AD to detect improper installation 
of the pitch change spider nut (nut) and improper alignment of a 
black index marking. The unsafe condition, if not addressed, could 
result in loss of the TRH pitch change control 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) For helicopters with TRH spider pitch change unit, part 
number (P/N) 350A33-2030-00, 350A33-2167-00, or 350A33-2167-01 
installed, within 50 hours time-in-service (TIS) after the effective 
date of this AD:
    (i) Inspect the nut for correct installation. If the nut is 
missing or loose, before further flight, remove the bearing from the 
TRH spider pitch change unit and do the following:
    (A) Inspect the TRH spider pitch change unit for corrosion. If 
there is any corrosion, before further flight, remove the affected 
part from service and replace with an airworthy part.
    (B) Inspect for rotation and wear on the faces of the bushes. 
For the purposes of this AD, indications of rotation and wear 
include tearing, peening, metal pick-up, and hammering. If there is 
any rotation or any wear on the faces of the bushes, before further 
flight, remove the bushes from service and replace with airworthy 
bushes.
    (C) Using a 5X or higher power magnifying glass visually inspect 
the rotating plate and the rotating plate threads for damage. For 
the purposes of this AD, indications of damage include wear, 
deformation, stripping, galling, and corrosion. If there is any 
damage on the rotating plate or the rotating plate threads, before 
further flight, remove the rotating plate from service and replace 
with an airworthy rotating plate.

    Note 1 to paragraph (g)(1)(i): Airbus Helicopters Mechanical 
Repair Manual (MRM) AS350 65-20-00-713, dated March 29, 2017, also 
known as Work Card 65-20-00-713 MRM, and Airbus Aircraft Maintenance 
Manual (AMM) AS350 65-21-00, 4-9b, dated May 16, 2019, also known as 
Task 65-21-00, 4-9 AMM, specify disassembly and reassembly 
information for the TRH pitch change unit.

    (ii) Identify the position of the TRH pitch change unit (item a) 
and of bearing spacer (item b) by marking a 2 to 5 mm wide black 
paint index mark (item C) with black paint as depicted in Figure 1 
of Airbus Helicopters Alert Service Bulletin (ASB) No. AS350-
05.01.03, Revision 0, dated December 16, 2021 (ASB AS350-05.01.03), 
or Airbus Helicopters ASB No. AS355-05.00.86, Revision 0, dated 
December 16, 2021 (ASB AS355-05.00.86), as applicable to your model 
helicopter.
    (iii) Within 10 hours TIS after the initial marking required by 
paragraph (g)(1)(ii) of this AD, and thereafter at intervals not to 
exceed 10 hours TIS, visually inspect the alignment of the marking. 
An example of a properly aligned marking is depicted in Figure 1 of 
ASB AS350-05.01.03 and ASB AS355-05.00.86, as applicable to your 
model helicopter. If the black paint index mark (item C) is 
misaligned, before further flight, inspect the TRH spider pitch 
change unit by accomplishing the actions required by paragraphs 
(g)(1)(i) and (ii) of this AD.
    (2) As of the effective date of this AD, do not install TRH 
spider pitch change unit P/N 350A33-2030-00, 350A33-2167-00, or 
350A33-2167-01 on any helicopter, unless you do the actions required 
by paragraphs (g)(1)(i) and (ii) of this AD before further flight 
after installation, and thereafter do the actions required by 
paragraph (g)(1)(iii) of this AD at the times specified in paragraph 
(g)(1)(iii) of this AD.

(h) 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 (i)(1) of 
this AD. Information may be emailed 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

    (1) For more information about this AD, contact Stephanie 
Sunderbruch, Aerospace Engineer, Safety Risk Management Section, 
Systems Policy Branch, Policy & Innovation Division, FAA, 10101 
Hillwood Pkwy., Fort Worth, TX 76177; telephone (817) 222-4659; 
email [email protected].
    (2) Airbus Helicopters Mechanical Repair Manual AS350 65-20-00-
713, dated March 29, 2017, and Airbus Aircraft Maintenance Manual 
AS350 65-21-00, 4-9b, dated May 16, 2019, which are not incorporated 
by reference, contain additional information about the subject of 
this AD. This service information is available at the contact 
information specified in paragraphs (j)(3) and (4) of this AD.
    (3) The subject of this AD is addressed in European Union 
Aviation Safety Agency (EASA) AD 2021-0282, dated December 17, 2021. 
You may view the EASA AD on the internet at regulations.gov in 
Docket No. FAA-2022-0987.

(j) Material Incorporated by Reference

    (1) The Director of the Federal Register approved the 
incorporation by reference of the service information listed in this 
paragraph under 5 U.S.C. 552(a) and 1 CFR part 51.
    (2) You must use this service information as applicable to do 
the actions required by this AD, unless the AD specifies otherwise.
    (i) Airbus Helicopters Alert Service Bulletin (ASB) No. AS350-
05.01.03, Revision 0, dated December 16, 2021.
    (ii) Airbus Helicopters ASB No. AS355-05.00.86, Revision 0, 
dated December 16, 2021.
    (3) For Airbus Helicopters service information identified in 
this AD, contact Airbus Helicopters, 2701 North Forum Drive, Grand 
Prairie, TX 75052; telephone (972) 641-0000 or (800) 232-0323; fax 
(972) 641-3775; or at airbus.com/helicopters/services/technical-support.html.
    (4) You may view this service information at 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 service information that is incorporated 
by reference at the National Archives and Records Administration 
(NARA). For information on the availability of this material at 
NARA, email: [email protected], or go to: www.archives.gov/federal-register/cfr/ibr-locations.html.

    Issued on January 5, 2023.
Christina Underwood,
Acting Director, Compliance & Airworthiness Division, Aircraft 
Certification Service.
[FR Doc. 2023-01965 Filed 1-31-23; 8:45 am]
BILLING CODE 4910-13-P

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