Document ID: FAA-2022-0987-0001
Agency: faa
Document Type: Proposed Rule
Title: Airworthiness Directives: Airbus Helicopters
Posted Date: 2022-08-02T04:00Z

[Federal Register Volume 87, Number 147 (Tuesday, August 2, 2022)]
[Proposed Rules]
[Pages 47141-47143]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2022-16396]

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 Proposed Rules
                                                 Federal Register
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 This section of the FEDERAL REGISTER contains notices to the public of 
 the proposed issuance of rules and regulations. The purpose of these 
 notices is to give interested persons an opportunity to participate in 
 the rule making prior to the adoption of the final rules.
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  Federal Register / Vol. 87, No. 147 / Tuesday, August 2, 2022 / 
Proposed Rules  

[[Page 47141]]

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2022-0987; Project Identifier MCAI-2021-01416-R]
RIN 2120-AA64

Airworthiness Directives; Airbus Helicopters

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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SUMMARY: The FAA proposes to adopt 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 proposed 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 proposed AD would require, 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 proposed AD would 
allow an affected part to be installed on a helicopter if certain 
requirements of this proposed AD are met. The FAA is proposing this AD 
to address the unsafe condition on these products.

DATES: The FAA must receive comments on this proposed AD by September 
16, 2022.

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 www.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 between 9 a.m. and 
5 p.m., Monday through Friday, except Federal holidays.
    For service information identified in this NPRM, 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 
www.airbus.com/helicopters/services/technical-support.html. 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.

Examining the AD Docket

    You may examine the AD docket at www.regulations.gov by searching 
for and locating 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 NPRM, the European Union 
Aviation Safety Agency (EASA) AD, any comments received, and other 
information. The street address for Docket Operations is listed 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: 

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-2022-0987; Project Identifier 
MCAI-2021-01416-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 
www.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 
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]. 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 2021-0282, dated December 17, 2021 
(EASA AD 2021-0282), to correct an unsafe condition for Airbus 
Helicopters (AH), 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

[[Page 47142]]

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. 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.

FAA's Determination

    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 about the 
unsafe condition described in its AD. The FAA is proposing this AD 
after evaluating all known relevant information and determining that 
the unsafe condition described previously is likely to exist or develop 
on other helicopters of the same type designs.

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 the ADDRESSES section.

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.

Proposed AD Requirements in This NPRM

    This proposed AD would require, for helicopters with certain part-
numbered TRH spider pitch change units installed, inspecting for 
correct installation of the nut; 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, visually inspecting the alignment of the marking; and 
additional inspections and corrective actions if necessary. 
Additionally, this proposed AD would allow an affected part to be 
installed on a helicopter, if certain requirements of this proposed AD 
are met.

Differences Between This Proposed AD and the EASA AD

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

Costs of Compliance

    The FAA estimates that this AD, if adopted as proposed, would 
affect 967 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.
    Inspecting the nut for correct installation would take 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 would take 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 
would take 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 
would take about 13 work-hours for an estimated cost of $1,105 per 
helicopter.
    If required, replacing the bushes would take about 1 work-hour and 
parts would cost about $5,918, for an estimated cost of $6,003 per 
replacement.
    If required, replacing the rotating plate would take about 1 work-
hour and parts would 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

    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.

[[Page 47143]]

    For the reasons discussed, 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

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:

Airbus Helicopters: Docket No. FAA-2022-0987; Project Identifier 
MCAI-2021-01416-R.

(a) Comments Due Date

    The FAA must receive comments on this airworthiness directive 
(AD) by September 16, 2022.

(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 (a) and 
of bearing spacer (b) by marking a 2 to 5 mm wide black paint index 
mark (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 (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) Related 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) For 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 www.airbus.com/helicopters/services/technical-support.html. You 
may view this referenced 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.
    (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 www.regulations.gov in 
Docket No. FAA-2022-0987.

    Issued on July 27, 2022.
Christina Underwood,
Acting Director, Compliance & Airworthiness Division, Aircraft 
Certification Service.
[FR Doc. 2022-16396 Filed 8-1-22; 8:45 am]
BILLING CODE 4910-13-P