Document ID: FAA-2019-0589-0004
Agency: faa
Document Type: Rule
Title: Airworthiness Directives: Bell Helicopter Textron Canada Limited Helicopters
Posted Date: 2020-08-17T04:00Z

[Federal Register Volume 85, Number 159 (Monday, August 17, 2020)]
[Rules and Regulations]
[Pages 49941-49944]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2020-17779]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2019-0589; Product Identifier 2017-SW-020-AD; Amendment 
39-21215; AD 2020-17-10]
RIN 2120-AA64

Airworthiness Directives; 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) 2016-02-06 
for Bell Helicopter Textron Canada Limited (Bell) Model 429 
helicopters. AD 2016-02-06 required inspecting certain tail rotor (T/R) 
pitch link bearing bores for corrosion and pitting. AD 2016-02-06 also 
required a repetitive inspection of the sealant and repeating the 
inspections for corrosion and pitting if any sealant is missing. This 
new AD retains the requirements of AD 2016-02-06, expands the 
applicability, and adds a repetitive inspection. This AD was prompted 
by an FAA determination that additional part-numbered T/R pitch link 
assemblies (links) are affected by the same unsafe condition and that 
an additional repetitive inspection is necessary to address the unsafe 
condition. The actions of this AD are intended to address an unsafe 
condition on these products.

DATES: This AD is effective September 21, 2020.
    The Director of the Federal Register approved the incorporation by 
reference of a certain publication listed in this AD as of February 2, 
2016 (81 FR 5367, February 2, 2016).

ADDRESSES: For service information identified in this final rule, 
contact Bell Helicopter Textron Canada Limited, 12,800 Rue de l'Avenir, 
Mirabel, Quebec J7J1R4; telephone 450-437-2862 or 800-363-8023; fax 
450-433-0272; or at https://www.bellcustomer.com. 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. It is also available on the internet at https://www.regulations.gov by searching for

[[Page 49942]]

and locating Docket No. FAA-2019-0589.

Examining the AD Docket

    You may examine the AD docket on the internet at https://www.regulations.gov in Docket No. FAA-2019-0589; 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 AD, the Transport Canada 
AD, any service information that is incorporated by reference, any 
comments received, and other information. The street 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: Scott Franke, Aviation Safety 
Engineer, International Validation Branch, Aviation and Rotorcraft 
Unit, FAA, 10101 Hillwood Pkwy., Fort Worth, TX 76177; telephone 817-
222-5110; email scott.franke@faa.gov.

SUPPLEMENTARY INFORMATION:

Discussion

    The FAA issued a notice of proposed rulemaking (NPRM) to amend 14 
CFR part 39 to remove AD 2016-02-06, Amendment 39-18387 (81 FR 5367, 
February 2, 2016) (``AD 2016-02-06'') and add a new AD. AD 2016-02-06 
applied to Bell Model 429 helicopters with a T/R link part number (P/N) 
429-012-112-101, -101FM, -103, or -103FM installed. The NPRM published 
in the Federal Register on August 20, 2019 (84 FR 43085). Since the FAA 
issued AD 2016-02-06, improved T/R links P/N 429-012-112-111 and -113 
were developed, but recurring inspections of the sealant of these T/R 
links are still necessary because they are subject to the same unsafe 
condition due to design similarity. Some T/R links P/N 429-012-112-101 
and -103 have also been field modified and re-identified as T/R links 
P/N 429-012-112-111FM and -113FM, and continue to need recurring 
inspections of the sealant as they are also subject to the same unsafe 
condition due to design similarity.
    The NPRM proposed to continue the requirements of AD 2016-02-06 and 
add P/Ns 429-012-112-111, -111FM, -113, and -113FM to the 
applicability. The NPRM also proposed to add use of 10X or higher power 
magnification to the visual inspection of each cleaned T/R link for 
pitting and a repetitive 12-month inspection with the corrosion 
preventative sealant removed.
    Transport Canada, which is the aviation authority for Canada, 
issued AD No. CF-2016-01R2, dated April 12, 2017 (AD CF-2016-01R2) to 
clarify the applicable P/Ns, address spare parts, and address parts 
installed on-condition prior to December 7, 2015. AD CF-2016-01R2 also 
includes a terminating action for the repetitive inspections.

Comments

    After the NPRM was published, the FAA received comments from one 
commenter.

Request

    Bell Textron, Inc., commented that this AD omits Bell Helicopter 
Alert Service Bulletin (ASB) 429-15-16 Rev. B, dated June 15, 2016 (ASB 
429-15-16 Rev. B), which was issued after Bell Helicopter ASB 429-15-
26, dated December 7, 2015 (ASB 429-15-26). The FAA acknowledges that 
ASB 429-15-16 Rev. B and ASB 429-15-26 specify procedures for the same 
part-numbered T/R links. However, the two service information documents 
address different unsafe conditions, specifically ASB 429-15-16 Rev. B 
addresses wear and ASB 429-15-26 addresses corrosion. Accordingly, the 
two different unsafe conditions are addressed in two separate ADs. The 
unsafe condition of wear (ASB 429-15-16 Rev. B) is addressed in AD 
2019-11-05, Amendment 39-19651 (84 FR 26546, June 7, 2019) (``AD 2019-
11-05''). The unsafe condition of corrosion (ASB 429-15-26) is 
addressed in this AD. The FAA did not change this AD based on this 
comment.
    Bell Textron, Inc., commented that this AD differs from ASB 429-15-
16 Rev. B and ASB 429-15-26 by requiring removal of the sealant around 
the bearing every 12 months and an inspection of the chamfer with a 10X 
magnifying lens. Bell Textron, Inc., stated that since ASB 429-15-16 
Rev. B ``requires'' a repetitive 50 flight hours inspection of the 
sealant for pin holes and voids, it does not feel the repetitive 12 
month inspection with the sealant removed is necessary. The FAA 
disagrees. Procedures specified in related service information 
documents are not required unless mandated by an AD. And while AD 2019-
11-05 mandates the repetitive inspection of the sealant condition for 
pin holes and voids specified in ASB 429-15-16 Rev. B, the FAA 
determined an inspection with the sealant removed at a longer-term 
repetitive interval is necessary. Since sealant could become damaged, 
not maintain seal, or become worn, this more in-depth inspection 
addresses corrosion and pitting that could build up underneath the 
sealant. The FAA did not change this AD based on this comment.
    Bell Textron, Inc., commented that not requiring part re-
identification makes it more complicated to manage configurations. The 
FAA does not prohibit re-identifying the T/R links as specified in ASB 
429-15-26; however, the FAA determined it unnecessary to require to 
address the unsafe condition since the repetitive inspections are 
required for all part-numbered links listed in the applicability. The 
FAA did not change this AD based on this comment.

FAA's Determination

    The FAA has reviewed the relevant information and determined that 
an unsafe condition exists and is likely to exist or develop on other 
helicopters of the same type design and that air safety and the public 
interest require adopting the AD requirements as proposed except for 
editorial changes. The website URL for Bell and the email address for 
requesting an alternative method of compliance have changed and have 
been updated in this final rule. Additionally, the paragraph cross-
referencing formatting in the Required Actions paragraph has changed to 
meet current publication requirements, e.g., ``(f)(3)(i) and 
(f)(3)(ii)'' has changed to ``(f)(3)(i) and (ii)'' instead. These 
editorial changes are consistent with the intent of the proposals in 
the NPRM and will not increase the economic burden on any operator nor 
increase the scope of the AD.

Interim Action

    The FAA considers this AD to be an interim action. The design 
approval holder is currently developing a modification that will 
address the unsafe condition identified in this AD. Once this 
modification is developed, approved, and available, the FAA might 
consider additional rulemaking.

Differences Between This AD and the Transport Canada AD

    This AD applies to helicopters with certain link P/Ns installed, 
whereas the Transport Canada AD applies to helicopters with certain 
serial numbers instead. This AD requires inspecting the bearing bores 
for any pitting after cleaning the T/R link, while the Transport Canada 
AD requires inspecting for corrosion after cleaning the T/R link. This 
AD requires performing the inspections with 10X or higher 
magnification, while the Transport Canada AD does not specify any 
magnification. This AD does not require re-identifying the P/N of the

[[Page 49943]]

link, whereas the Transport Canada AD does. The Transport Canada AD 
also provides a terminating action to the repetitive sealant 
inspection, while this AD does not. This AD also requires a repetitive 
inspection with the corrosion preventative sealant removed and 
reapplied, whereas the Transport Canada AD does not.

Related Service Information Under 1 CFR Part 51

    The FAA reviewed ASB 429-15-26, which advises of reports of 
corrosion on T/R links between the roll staked lip of bearing P/N 429-
312-107-103 and the beveled edge of T/R link P/Ns 429-012-112-101/-103. 
ASB 429-15-26 specifies inspecting each T/R link bearing bore between 
the roll staked lip of the bearing outer race and the link bearing bore 
with 10X magnification for corrosion and if there is corrosion, 
replacing the link. If there is no corrosion, ASB 429-15-26 specifies 
cleaning the area and performing a second inspection with 10X 
magnification for corrosion. If there is corrosion, ASB 429-15-26 
specifies replacing the link. If there is no corrosion, ASB 429-15-26 
specifies removing the torque stripe, cleaning the area, and applying 
corrosion preventative sealant. ASB 429-15-26 also specifies re-
identifying the P/Ns as 429-012-112-101FM/-103FM. Further, ASB 429-15-
26 specifies a repetitive inspection of the sealant and reapplication 
if the sealant is damaged.
    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 93 helicopters of U.S. 
Registry. The FAA estimates that operators may incur the following 
costs in order to comply with this AD. Labor costs are estimated at $85 
per work-hour.
    Inspecting the set of T/R links (eight bearings) for corrosion 
takes about one work-hour for an estimated cost of $85 per helicopter 
and $7,905 for the U.S. fleet per inspection cycle. Cleaning and 
inspecting the set of T/R links for pitting takes about one work-hour 
for an estimated cost of $85 per helicopter. Replacing a T/R link 
requires no additional work-hours after the inspection and required 
parts cost $2,739 for an estimated replacement cost of $2,739 per T/R 
link. Removing the torque stripe, cleaning, and applying sealant to the 
set of T/R links takes about one work-hour with a negligible parts cost 
for an estimated cost of $85 per helicopter. Inspecting the sealant on 
a set of T/R links takes about one work-hour for an estimated cost of 
$85 per helicopter and $7,905 for the U.S. fleet per inspection cycle.
    According to Bell Helicopter's service information, some of the 
costs of this AD may be covered under warranty, thereby reducing the 
cost impact on affected individuals. The FAA does not control warranty 
coverage by Bell Helicopter. Accordingly, the FAA has included all 
costs in this 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 has determined that 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.

Adoption of the Amendment

    Accordingly, under the authority delegated to me by the 
Administrator, the FAA amends 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) 2016-02-06, Amendment 39-18387 
(81 FR 5367, February 2, 2016); and
0
b. Adding the following new AD:

2020-17-10 Bell Helicopter Textron Canada Limited: Amendment 39-
21215; Docket No. FAA-2019-0589; Product Identifier 2017-SW-020-AD.

(a) Applicability

    This AD applies to Bell Helicopter Textron Canada Limited Model 
429 helicopters with a tail rotor (T/R) pitch link assembly (link) 
part number (P/N) 429-012-112-101, -101FM, -103, -103FM, -111, -
111FM, -113, or -113FM installed, certificated in any category.

(b) Unsafe Condition

    This AD defines the unsafe condition as failure of a T/R link. 
This condition could result in loss of T/R flight control and 
subsequent loss of control of the helicopter.

(c) Affected ADs

    This AD replaces AD 2016-02-06, Amendment 39-18387 (81 FR 5367, 
February 2, 2016).

(d) Effective Date

    This AD becomes effective September 21, 2020.

(e) Compliance

    You are responsible for performing each action required by this 
AD within the specified compliance time unless it has already been 
accomplished prior to that time.

(f) Required Actions

    (1) For T/R link P/N 429-012-112-101 and -103, within 10 hours 
time-in-service (TIS):
    (i) Remove each T/R link. Prior to cleaning the T/R link bearing 
bores, using 10X or higher power magnification, inspect each T/R 
link bearing bore for aluminum oxide corrosion extruding from 
between the roll staked lip of the bearing outer race and the link 
bearing bore. Aluminum oxide corrosion appears as a white 
crystalline material in contrast with the black finish and any 
accumulated soot. An example of this corrosion is shown in Figure 1 
of Bell Helicopter Alert Service Bulletin 429-15-26, dated December 
7, 2015 (ASB 429-15-26).
    (ii) If there is any aluminum oxide corrosion, replace the T/R 
link before further flight.
    (iii) If there is no aluminum oxide corrosion, clean each T/R 
link bearing bore with isopropyl alcohol, and using 10X or higher 
power magnification, inspect each cleaned T/R link for pitting.

[[Page 49944]]

    (A) If there is any pitting, replace the T/R link before further 
flight.
    (B) If there is no pitting, apply corrosion preventative sealant 
by following the Accomplishment Instructions, paragraph 5. of Part 
I, of ASB 429-15-26.
    (2) For all T/R link P/Ns listed in paragraph (a) of this AD, 
within 50 hours TIS, and thereafter at intervals not to exceed 50 
hours TIS, using 10X or higher power magnification, inspect each T/R 
link bearing bore for missing corrosion preventative sealant. If any 
corrosion preventative sealant is missing, perform the actions in 
paragraphs (f)(3)(i) and (ii) of this AD before further flight.
    (3) For all T/R link P/Ns listed in paragraph (a) of this AD, 
within 12 months since date of manufacture, except if paragraphs 
(f)(1)(i) through (iii) of this AD have already been done for T/R 
link P/N 429-012-112-101 or -103 within the last 12 months and 
except if paragraph (f)(3)(i) and (ii) of this AD have already been 
done for T/R link P/N 429-012-112-101FM, -103FM, -111, -111FM, -113, 
or -113FM within the last 12 months; and thereafter for all T/R link 
P/Ns listed in paragraph (a) of this AD at intervals not to exceed 
12 months:
    (i) Remove each T/R link; and
    (ii) Remove all corrosion preventative sealant, and perform the 
actions in paragraphs (f)(1)(i) through (iii) of this AD.
    (4) After the effective date of this AD:
    (i) Do not install T/R link P/N 429-012-112-101 or -103 on any 
helicopter before complying with the actions in paragraphs (f)(1)(i) 
through (iii) of this AD.
    (ii) Do not install T/R link P/N 429-012-112-101FM, 103FM, -111, 
111FM, -113, or -113FM on any helicopter before complying with the 
actions in paragraph (f)(2) of this AD.

(g) Alternative Methods of Compliance (AMOCs)

    (1) The Manager, International Validation Branch, FAA, may 
approve AMOCs for this AD. Send your proposal to: Scott Franke, 
Aviation Safety Engineer, International Validation Branch, Aviation 
and Rotorcraft Unit, FAA, 10101 Hillwood Pkwy., Fort Worth, TX 
76177; telephone 817-222-5110; email scott.franke@faa.gov.
    (2) For operations conducted under a 14 CFR part 119 operating 
certificate or under 14 CFR part 91, subpart K, the FAA suggests 
that you notify your principal inspector, or lacking a principal 
inspector, the manager of the local flight standards district office 
or certificate holding district office, before operating any 
aircraft complying with this AD through an AMOC.

(h) Additional Information

    The subject of this AD is addressed in Transport Canada AD No. 
CF-2016-01R2, dated April 12, 2017. You may view the Transport 
Canada AD on the internet at https://www.regulations.gov in Docket 
No. FAA-2019-0589.

(i) Subject

    Joint Aircraft Service Component (JASC) Code: 6400, Tail Rotor 
System.

(j) Material Incorporated by Reference

    (1) The Director of the Federal Register approved the 
incorporation by reference (IBR) 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.
    (3) The following service information was approved for IBR on 
February 2, 2016 (81 FR 5367, February 2, 2016).
    (i) Bell Helicopter Alert Service Bulletin 429-15-26, dated 
December 7, 2015.
    (ii) [Reserved]
    (4) For service information identified in this AD, contact Bell 
Helicopter Textron Canada Limited, 12,800 Rue de l'Avenir, Mirabel, 
Quebec J7J1R4; telephone 450-437-2862 or 800-363-8023; fax 450-433-
0272; or at https://www.bellcustomer.com.
    (5) 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.
    (6) 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 fedreg.legal@nara.gov, or go to: https://www.archives.gov/federal-register/cfr/ibr-locations.html.

    Issued on August 10, 2020.
Lance T. Gant,
Director, Compliance & Airworthiness Division, Aircraft Certification 
Service.
[FR Doc. 2020-17779 Filed 8-14-20; 8:45 am]
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