[Federal Register Volume 87, Number 36 (Wednesday, February 23, 2022)]
[Proposed Rules]
[Pages 10107-10110]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2022-03770]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2022-0145; Project Identifier MCAI-2021-00522-R]
RIN 2120-AA64


Airworthiness Directives; Bell Textron Canada Limited (Type 
Certificate Previously Held by Bell Helicopter Textron Canada Limited) 
Helicopters

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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SUMMARY: The FAA proposes to supersede Airworthiness Directive (AD) 
2019-11-05, which applies to Bell Helicopter Textron Canada Limited 
(now Bell Textron Canada Limited) Model 429 helicopters having certain 
tail rotor (TR) pitch link assemblies. AD 2019-11-05 requires 
inspecting the TR pitch link assemblies, and replacing certain pitch 
link bearings. Since the FAA issued AD 2019-11-05, the FAA has 
determined that all TR pitch link assemblies are affected by the unsafe 
condition. This proposed AD would continue to require the actions 
specified in AD 2019-11-05, and would revise the applicability and 
require inspections of certain other TR pitch link assemblies. 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 April 11, 
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 https://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 above between 9 
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
    For service information identified in this NPRM, contact Bell 
Textron Canada Limited, 12,800 Rue de l'Avenir, Mirabel, Quebec J7J 
1R4, Canada; telephone 1-450-437-2862 or 1-800-363-8023; fax 1-450-433-
0272; email [email protected]; or at https://www.bellflight.com/support/contact-support. 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.

Examining the AD Docket

    You may examine the AD docket at https://www.regulations.gov by 
searching for and locating Docket No. FAA-2022-0145; 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 
Transport Canada Civil Aviation (TCCA) AD, any comments received, and 
other information. The street address for Docket Operations is listed 
above.

FOR FURTHER INFORMATION CONTACT: Hal Jensen, Aerospace Engineer, 
Operational Safety Branch, Compliance & Airworthiness Division, FAA, 
950 L'Enfant Plaza N SW, Washington, DC 20024; phone: (202) 267-9167; 
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-2022-0145; Project Identifier 
MCAI-2021-00522-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.

[[Page 10108]]

    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 
https://www.regulations.gov, including any personal information you 
provide. The agency will also post a report summarizing each 
substantive verbal contact received about this proposal.

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 Hal 
Jensen, Aerospace Engineer, Operational Safety Branch, Compliance & 
Airworthiness Division, FAA, 950 L'Enfant Plaza N SW, Washington, DC 
20024; phone: (202) 267-9167; email: [email protected]. Any commentary 
that the FAA receives that is not specifically designated as CBI will 
be placed in the public docket for this rulemaking.

Background

    The FAA issued AD 2019-11-05, Amendment 39-19651 (84 FR 26546, June 
7, 2019) (AD 2019-11-05), which applies to certain Bell Helicopter 
Textron Canada Limited Model 429 helicopters. AD 2019-11-05 requires 
inspecting the TR pitch link assemblies, and replacing certain pitch 
link bearings. The FAA issued AD 2019-11-05 to address a worn pitch 
link, which if not corrected, could result in pitch link failure and 
subsequent loss of control of the helicopter.

Actions Since AD 2019-11-05 Was Issued

    Since the FAA issued AD 2019-11-05, the FAA has determined that 
additional TR pitch link assemblies are affected by the unsafe 
condition. AD 2019-11-05 applies to helicopters with a pitch link 
assembly part number (P/N) 429-012-112-101, 429-012-112-103, 429-012-
112-101FM, or 429-012-112-103FM installed. However, as specified in the 
corresponding TCCA AD, CF-2015-16R2, dated April 3, 2017 (TCCA AD CF-
2015-16R2), all pitch link assemblies are part of the repetitive 
inspections.
    The TCCA, which is the aviation authority for Canada, has issued 
TCCA AD CF-2015-16R3, dated April 30, 2021 (TCCA AD CF-2015-16R3) (also 
referred to as the Mandatory Continuing Airworthiness Information, or 
the MCAI), to correct an unsafe condition for certain Bell Helicopter 
Textron Canada Limited Model 429 helicopters. TCCA AD CF-2015-16R3 
retains the requirements of TCCA AD CF-2015-16R2 and revises the 
applicability by specifying certain helicopter serial numbers to 
account for new production helicopters which have already incorporated 
the new pitch link assemblies and corrected the unsafe condition. TCCA 
AD CF-2015-16R3 also specifies that installing a new pitch link 
assembly terminates the repetitive inspections.
    This proposed AD was prompted by a report of a worn pitch link, and 
the FAA's determination that that all TR pitch link assemblies are 
affected by the unsafe condition. The FAA is proposing this AD to 
address a worn pitch link, which if not corrected, could result in 
pitch link failure and subsequent loss of control of the helicopter. 
See the MCAI for additional background information.

FAA's Determination

    These products have been approved by the aviation authority of 
Canada, and are approved for operation in the United States. Pursuant 
to the bilateral agreement with Canada, TCCA, its technical 
representative, has notified the FAA of the unsafe condition described 
in its AD. The FAA is proposing this AD after evaluating all known 
relevant information and determining the unsafe condition described 
previously is likely to exist or develop in other products of the same 
type design.

Related Service Information Under 1 CFR Part 51

    The FAA reviewed Bell Alert Service Bulletin No. 429-15-16, 
Revision C, dated October 16, 2020. This service information contains 
procedures for inspecting the TR pitch link assemblies, replacing 
certain pitch link bearings, and replacement of the pitch link 
assemblies. 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.

Proposed AD Requirements in this NPRM

    This proposed AD would retain all of the requirements of AD 2019-
11-05. This proposed AD would revise the applicability and require 
inspections of all TR pitch link assemblies.

Costs of Compliance

    The FAA estimates that this proposed AD affects 120 helicopters of 
U.S. registry. The FAA estimates the following costs to comply with 
this proposed AD:

                                      Estimated Costs for Required Actions
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                                                                                                 Cost on U.S.
              Action                    Labor cost        Parts cost      Cost per product        operators
----------------------------------------------------------------------------------------------------------------
Retained inspections from AD       2 work-hours x $85               $0  $170 per inspection  $20,400 per
 2019[dash]11[dash]05.              per hour = $170                      cycle.               inspection cycle.
                                    per inspection
                                    cycle.
New inspections..................  2 work-hours x $85                0  170 per inspection   20,400 per
                                    per hour = $170                      cycle.               inspection cycle.
                                    per inspection
                                    cycle.
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    The FAA estimates the following costs to do any necessary on-
condition replacements that would be required based on the results of 
any required actions. The FAA has no way of determining the number of 
helicopters that might need these on-condition actions:

[[Page 10109]]



                                     Estimated Costs of On-Condition Actions
----------------------------------------------------------------------------------------------------------------
                                                                                    Cost per       Cost on U.S.
               Action                        Labor cost           Parts cost        product         operators
----------------------------------------------------------------------------------------------------------------
Bearing replacements................  3 work-hours x $85 per           $3,340           $3,343         $401,160
                                       hour = $255.
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    According to the manufacturer, some of the costs of this proposed 
AD may be covered under warranty, thereby reducing the cost impact on 
affected operators. The FAA does not control warranty coverage for 
affected operators. As a result, the FAA has included all known costs 
in the cost estimate.

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

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:
0
a. Removing Airworthiness Directive (AD) 2019-11-05, Amendment 39-19651 
(84 FR 26546, June 7, 2019); and
0
b. Adding the following new AD:

Bell Textron Canada Limited (Type Certificate Previously Held by 
Bell Helicopter Textron Canada Limited): Docket No. FAA-2022-0145; 
Project Identifier MCAI-2021-00522-R.

(a) Comments Due Date

    The FAA must receive comments on this airworthiness directive 
(AD) action by April 11, 2022.

(b) Affected ADs

    (1) This AD replaces AD 2019-11-05, Amendment 39-19651 (84 FR 
26546, June 7, 2019) (AD 2019-11-05).
    (2) This AD affects AD 2020-17-10, Amendment 39-21215 (85 FR 
49941, August 17, 2020) (AD 2020-17-10).

(c) Applicability

    This AD applies to Bell Textron Canada Limited (type certificate 
previously held by Bell Helicopter Textron Canada Limited) Model 429 
helicopters, certificated in any category, serial numbers 57001 
through 57401 inclusive.

(d) Subject

    Joint Aircraft System Component (JASC) Code 6720, Tail Rotor 
Control System.

(e) Unsafe Condition

    This AD was prompted by a report of a worn pitch link. The FAA 
is issuing this AD to address a worn pitch link, which if not 
corrected, could result in pitch link failure and subsequent loss of 
control of the helicopter.

(f) Compliance

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

(g) Retained Requirements

    (1) For pitch link assembly part number (P/N) 429-012-112-101, 
429-012-112-103, 429-012-112-101FM, and 429-012-112-103FM: Within 50 
hours time-in-service (TIS) after July 12, 2019 (the effective date 
of AD 2019-11-05) and thereafter at intervals not to exceed 50 hours 
TIS:
    (i) Perform a dimensional inspection of each inboard and 
outboard pitch link assembly for axial and radial bearing play. With 
a 10X or higher power magnifying glass, inspect the bearing liner 
for a crack, deterioration of the liner, and extrusion of the liner 
from the plane. If there is axial or radial play that exceeds 
allowable limits, or if there is a crack, deterioration of the 
liner, or extrusion of the liner, before further flight, replace the 
bearing.
    (ii) Inspect the pitch link assembly sealant for pin holes and 
voids and to determine if the sealant thickness is 0.025 inch (0.64 
mm) or less, extends over the roll staked lip by 0.030 inch (0.76 
mm) or more, and is clear of the bearing ball. If there is a pin 
hole or void, or if the sealant exceeds 0.026 inch (0.66 mm), does 
not extend over the roll staked lip by 0.030 inch (0.76 mm) or more, 
or is not clear of the bearing ball, before further flight, replace 
the bearing.
    (2) For pitch link assembly part number (P/N) 429-012-112-101, 
429-012-112-103, 429-012-112-101FM, and 429-012-112-103FM, within 
200 hours TIS following the initial inspection required by paragraph 
(g)(1) of this AD, or if the hours TIS of a pitch link assembly 
exceed 250 hours TIS or are unknown, at the next 50-hour-TIS 
inspection required by paragraph (g)(1) of this AD:
    (i) Replace each bearing P/N 429-312-107-103 with a date of 
manufacture before January 13, 2015, with a bearing P/N 429-312-107-
103 that was manufactured on or after January 13, 2015.
    (ii) Using a white permanent fine point marker or equivalent, 
re-identify the pitch link assembly:
    (A) Re-identify P/N 429-012-112-101 and 429-012-112-101FM as 
429-012-112-111FM.
    (B) Re-identify P/N 429-012-112-103 and 429-012-112-103FM as 
429-012-112-113FM.
    (iii) Apply a coating of DEVCON 2-TON (C-298) or equivalent over 
the new P/N.

(h) New Requirements

    For pitch link assemblies other than P/N 429-012-112-101, 429-
012-112-103, 429-012-112-101FM, and 429-012-112-103FM: Within 50 
hours TIS after the effective date of this AD and thereafter at 
intervals not to exceed 50 hours TIS:
    (1) Perform a dimensional inspection of each inboard and 
outboard pitch link assembly for axial and radial bearing play. With 
a 10X or higher power magnifying glass, inspect the bearing liner 
for a crack, deterioration of the liner, and extrusion of the liner 
from the plane. If there is axial or radial play that exceeds 
allowable limits, or

[[Page 10110]]

if there is a crack, deterioration of the liner, or extrusion of the 
liner, before further flight, replace the bearing.
    (2) Inspect the pitch link assembly sealant for pin holes and 
voids and to determine if the sealant thickness is 0.025 inch (0.64 
mm) or less, extends over the roll staked lip by 0.030 inch (0.76 
mm) or more, and is clear of the bearing ball. If there is a pin 
hole or void, or if the sealant exceeds 0.026 inch (0.66 mm), does 
not extend over the roll staked lip by 0.030 inch (0.76 mm) or more, 
or is not clear of the bearing ball, before further flight, replace 
the bearing.

(i) Terminating Action for Certain Actions in AD 2020-17-10

    Accomplishing the initial inspection required by paragraph 
(g)(1) or (h) of this AD constitutes terminating action for the 
inspections required by paragraph (f)(2) of AD 2020-17-10 for that 
pitch link assembly only.

(j) Optional Terminating Action

    The repetitive inspections required by paragraph (h) of this AD 
are no longer required for helicopters that incorporate pitch link 
assemblies, P/N 429-012-212-105 or 429-012-212-107, in accordance 
with Part III of the Accomplishment Instructions of Bell Alert 
Service Bulletin No. 429-15-16, Revision C, dated October 16, 2020.

(k) 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 (l)(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.

(l) Related Information

    (1) For more information about this AD, contact Hal Jensen, 
Aerospace Engineer, Operational Safety Branch, Compliance & 
Airworthiness Division, FAA, 950 L'Enfant Plaza N SW, Washington, DC 
20024; phone: (202) 267-9167; email: [email protected].
    (2) Bell Alert Service Bulletin No. 429-15-16, Revision C, dated 
October 16, 2020, which is not incorporated by reference, contains 
additional information about the subject of this AD. For service 
information identified in this AD, contact Bell Textron Canada 
Limited, 12,800 Rue de l'Avenir, Mirabel, Quebec J7J 1R4, Canada; 
telephone 1-450-437-2862 or 1-800-363-8023; fax 1-450-433-0272; 
email [email protected]; or at https://www.bellflight.com/support/contact-support. 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 Transport Canada 
Civil Aviation (TCCA) AD CF-2015-16R3, dated April 30, 2021 (TCCA AD 
CF-2015-16R3). You may view the Transport Canada AD on the internet 
at https://www.regulations.gov in Docket No. FAA-2022-0145.

    Issued on February 15, 2022.
Ross Landes,
Deputy Director for Regulatory Operations, Compliance & Airworthiness 
Division, Aircraft Certification Service.
[FR Doc. 2022-03770 Filed 2-22-22; 8:45 am]
BILLING CODE 4910-13-P