[Federal Register Volume 87, Number 80 (Tuesday, April 26, 2022)]
[Rules and Regulations]
[Pages 24401-24404]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2022-08797]


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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; 
Amendment 39-22027; AD 2022-09-07]
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: Final rule.

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SUMMARY: The FAA is superseding Airworthiness Directive (AD) 2019-11-05 
for certain Bell Helicopter Textron Canada Limited (now Bell Textron 
Canada Limited) Model 429 helicopters. AD 2019-11-05 required 
inspecting the tail rotor (TR) pitch link assemblies, and replacing 
certain pitch link bearings. This AD was prompted by a report of a worn 
pitch link, and the FAA's determination that all TR pitch link 
assemblies are affected by the unsafe condition. This AD continues to 
require the actions specified in AD 2019-11-05, and revises the 
applicability and requires inspections of certain other TR pitch link 
assemblies. The FAA is issuing this AD to address the unsafe condition 
on these products.

DATES: This AD is effective May 31, 2022.
    The Director of the Federal Register approved the incorporation by 
reference of a certain publication listed in this AD as of May 31, 
2022.

ADDRESSES: For service information identified in this final rule, 
contact Bell Textron Canada Limited, 12,800 Rue de l'Avenir, Mirabel, 
Quebec J7J 1R4, Canada; phone: 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 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 https://www.regulations.gov by 
searching for and locating Docket No. FAA-2022-0145.

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 final rule, the 
Transport Canada Civil Aviation (TCCA) 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.

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:

Background

    The FAA issued a notice of proposed rulemaking (NPRM) to amend 14 
CFR part 39 to supersede AD 2019-11-05, Amendment 39-19651 (84 FR 
26546, June 7, 2019) (AD 2019-11-05). AD 2019-11-05 applied to certain 
Bell Helicopter Textron Canada Limited Model 429 helicopters. The NPRM 
published in the Federal Register on February 23, 2022 (87 FR 10107). 
In the NPRM, the FAA proposed to continue to require inspecting the TR 
pitch link assemblies, and replacing certain pitch link bearings, as 
well as proposed to revise the applicability and require inspections of 
certain other TR pitch link assemblies. The NPRM was prompted by TCCA 
AD CF-2015-16R3, dated April 30, 2021 (TCCA AD CF-

[[Page 24402]]

2015-16R3), issued by TCCA, which is the aviation authority for Canada, 
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, dated April 3, 2017, 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 condition, if not 
addressed, could result in pitch link failure and subsequent loss of 
control of the helicopter.

Discussion of Final Airworthiness Directive

Comments

    The FAA received no comments on the NPRM or on the determination of 
the costs.

Conclusion

    These helicopters have been approved by the aviation authority of 
Canada and are approved for operation in the United States. Pursuant to 
the FAA's bilateral agreement with Canada, TCCA, its technical 
representative, has notified the FAA of the unsafe condition described 
in its AD. The FAA reviewed the relevant data 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 helicopters. 
Except for minor editorial changes, this AD is adopted as proposed in 
the NPRM.

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 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.

Costs of Compliance

    The FAA estimates that this AD affects 120 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.

                                      Estimated Costs for Required Actions
----------------------------------------------------------------------------------------------------------------
                                                                                                 Cost on U.S.
              Action                    Labor cost        Parts cost      Cost per product        operators
----------------------------------------------------------------------------------------------------------------
Retained inspections from AD 2019- 2 work-hours x $85               $0  $170 per inspection  $20,400 per
 11-05.                             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:

                                     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.
----------------------------------------------------------------------------------------------------------------

    According to the manufacturer, some of the costs of this 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

    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 24403]]

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:

2022-09-07 Bell Textron Canada Limited (Type Certificate Previously 
Held by Bell Helicopter Textron Canada Limited): Amendment 39-22027; 
Docket No. FAA-2022-0145; Project Identifier MCAI-2021-00522-R.

(a) Effective Date

    This airworthiness directive (AD) is effective May 31, 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 Service 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 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 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) The subject of this AD is addressed in Transport Canada 
Civil Aviation AD CF-2015-16R3, dated April 30, 2021. You may view 
the Transport Canada AD at https://www.regulations.gov in Docket No. 
FAA-2022-0145.

(m) 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) Bell Alert Service Bulletin No. 429-15-16, Revision C, dated 
October 16, 2020.
    (ii) [Reserved]
    (3) For service information identified in this AD, contact Bell 
Textron Canada Limited, 12,800 Rue de l'Avenir, Mirabel, Quebec J7J 
1R4, Canada; phone: 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.
    (4) 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.
    (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,

[[Page 24404]]

email: [email protected], or go to: https://www.archives.gov/federal-register/cfr/ibr-locations.html.

    Issued on April 15, 2022.
Ross Landes,
Deputy Director for Regulatory Operations, Compliance & Airworthiness 
Division, Aircraft Certification Service.
[FR Doc. 2022-08797 Filed 4-25-22; 8:45 am]
BILLING CODE 4910-13-P


