[Federal Register Volume 84, Number 110 (Friday, June 7, 2019)]
[Rules and Regulations]
[Pages 26546-26548]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2019-11991]


=======================================================================
-----------------------------------------------------------------------

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2018-0722; Product Identifier 2017-SW-104-AD; Amendment 
39-19651; AD 2019-11-05]
RIN 2120-AA64


Airworthiness Directives; Bell Helicopter Textron Canada Limited 
Helicopters

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule.

-----------------------------------------------------------------------

SUMMARY: We are superseding Airworthiness Directive (AD) 2015-22-02 for 
certain Bell Helicopter Textron Canada Limited (Bell) Model 429 
helicopters. AD 2015-22-02 required inspecting the tail rotor (TR) 
pitch link assemblies. This AD retains the inspections of AD 2015-22-02 
and requires replacing certain pitch link bearings. This AD was 
prompted by a new design bearing introduced by Bell. We are issuing 
this AD to address the unsafe condition on these products.

DATES: This AD is effective July 12, 2019.

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 http://www.bellcustomer.com/files/. You may 
review the referenced service information at the FAA, Office of the 
Regional Counsel, Southwest Region, 10101 Hillwood Pkwy., Room 6N-321, 
Fort Worth, TX 76177.

Examining the AD Docket

    You may examine the AD docket on the internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2018-
0722; 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 AD, the regulatory evaluation, 
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: David Hatfield, Aviation Safety 
Engineer, Safety Management Section, Rotorcraft Standards Branch, FAA, 
10101 Hillwood Pkwy., Fort Worth, TX 76177; telephone (817) 222-5110; 
email david.hatfield@faa.gov.

SUPPLEMENTARY INFORMATION:

Discussion

    We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR 
part 39 to remove AD 2015-22-02, Amendment 39-18306 (80 FR 65618, 
October 27, 2015) (``AD 2015-22-02'') and add a new AD. AD 2015-22-02 
applied to Bell Model 429 helicopters with a TR pitch link assembly 
part number (P/N) 429-112-101 or 429-112-103 installed.
    The NPRM published in the Federal Register on August 8, 2018 (83 FR 
39004). The NPRM was prompted by a new design bearing introduced by 
Bell. The NPRM proposed to continue to require the inspections of AD 
2015-22-02. The NPRM also proposed to require replacing certain pitch 
link bearings. We are issuing this AD to address a worn pitch link. 
This condition, if not corrected, could result in pitch link failure 
and subsequent loss of control of the helicopter.
    Transport Canada, which is the aviation authority for Canada, 
issued Canadian AD No. CF-2015-16R2, dated April 3, 2017 (Transport 
Canada AD No. CF-2015-16R2), to correct an unsafe condition for certain 
Bell Model 429 helicopters. Transport Canada advises that Bell has 
reported that the TR pitch link assembly can be rotated during the 50-
hour inspections to extend the serviceability life of the bearings. 
Transport Canada AD No. CF-2015-16R2 requires modified inspection 
procedures for the spherical bearings and requires replacing the TR 
pitch link bearings (or the TR pitch link assembly) with spherical 
bearings manufactured after January 12, 2015. Transport Canada AD No. 
CF-2015-16R2 also requires re-identifying TR pitch link assemblies with 
a different part number after installing the new bearings.

Comments

    We gave the public the opportunity to participate in developing 
this final rule, but we did not receive any comments on the NPRM.

FAA's Determination

    These helicopters have been approved by the aviation authority of 
Canada and

[[Page 26547]]

are approved for operation in the United States. Pursuant to our 
bilateral agreement with Canada, Transport Canada, its technical 
representative, has notified us of the unsafe condition described in 
the Transport Canada AD. We are proposing this AD because we evaluated 
all information provided by Transport Canada and determined the 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 a minor 
editorial change. We have updated the estimated costs to reflect that 
this AD affects 90 helicopters of U.S. Registry rather than 85 
helicopters. This change is 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 this AD.

Related Service Information

    We reviewed Bell Alert Service Bulletin No. 429-15-16, Revision B, 
dated June 15, 2016. This service information contains procedures for 
repetitively inspecting the TR pitch link assembly until it is upgraded 
by replacing the TR pitch link bearings.

Differences Between This AD and the Transport Canada AD

    The Transport Canada AD requires the bearing inspection within 10 
hours time-in-service (TIS) or before exceeding 60 hours TIS since new, 
whichever occurs later. This AD requires the bearing inspection within 
50 hours TIS. The Transport Canada AD also requires replacing certain 
bearings within 200 hours TIS after the initial bearing inspection or 
within 250 hours TIS since new, whichever occurs first. This AD 
requires replacing the bearing within 200 hours of the initial 
inspection or at the next 50 hours TIS inspection if the hours TIS of a 
pitch link assembly exceed 250 hours TIS or are unknown.

Interim Action

    We consider this AD to be an interim action. If final action is 
later identified, we might consider further rulemaking then.

Costs of Compliance

    We estimate that this AD affects 90 helicopters of U.S. Registry. 
We estimate that operators may incur the following costs in order to 
comply with this AD.
    At an average labor rate of $85 per hour, inspecting the TR pitch 
link assemblies requires 2 work-hours for a cost of $170 per helicopter 
and $15,300 for the U.S. fleet per inspection cycle. Replacing both 
spherical bearings in each TR pitch link assembly requires 3 work-
hours, and required parts cost $3,088, for a cost of $3,343 per 
helicopter and $300,870 for the U.S. fleet.
    According to Bell's service information some of the costs of this 
AD may be covered under warranty, thereby reducing the cost impact on 
affected individuals. We do not control warranty coverage by Bell. 
Accordingly, we have included all costs in our 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.
    We are 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

    We 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. Is not a ``significant rule'' under the DOT Regulatory Policies 
and Procedures (44 FR 11034, February 26, 1979);
    3. Will not affect intrastate aviation in Alaska; and
    4. 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 removing Airworthiness Directive (AD) 
2015-22-02, Amendment 39-18306 (80 FR 65618, October 27, 2015), and 
adding the following new AD:

2019-11-05 Bell Helicopter Textron Canada Limited: Amendment 39-
19651; Docket No. FAA-2018-0722; Product Identifier 2017-SW-104-AD.

(a) Applicability

    This AD applies to Bell Helicopter Textron Canada Limited Model 
429 helicopters, certificated in any category, 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.

(b) Unsafe Condition

    This AD defines the unsafe condition as a worn pitch link. This 
condition, if not corrected, could result in pitch link failure and 
subsequent loss of control of the helicopter.

(c) Affected ADs

    This AD replaces AD 2015-22-02, Amendment 39-18306 (80 FR 65618, 
October 27, 2015).

(d) Effective Date

    This AD is effective July 12, 2019.

(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) Within 50 hours time-in-service (TIS) 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

[[Page 26548]]

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 
(f)(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 (f)(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.

(g) Special Flight Permits

    Special flight permits are prohibited.

(h) Alternative Methods of Compliance (AMOCs)

    (1) The Manager, Safety Management Section, Rotorcraft Standards 
Branch, FAA, may approve AMOCs for this AD. Send your proposal to: 
David Hatfield, Aviation Safety Engineer, Safety Management Section, 
Rotorcraft Standards Branch, FAA, 10101 Hillwood Pkwy., Fort Worth, 
TX 76177; telephone (817) 222-5110; email 9-ASW-FTW-AMOC-Requests@faa.gov.
    (2) For operations conducted under a 14 CFR part 119 operating 
certificate or under 14 CFR part 91, subpart K, we suggest 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.

(i) Additional Information

    (1) Bell Alert Service Bulletin No. 429-15-16, Revision B, dated 
June 15, 2016, which is not incorporated by reference, contains 
additional information about the subject of this AD. 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 http://www.bellcustomer.com/files/. You may review a copy of the 
service information at the FAA, Office of the Regional Counsel, 
Southwest Region, 10101 Hillwood Pkwy., Room 6N-321, Fort Worth, TX 
76177.
    (2) The subject of this AD is addressed in Transport Canada AD 
No. CF-2015-16R2, dated April 3, 2017. You may view the Transport 
Canada AD on the internet at http://www.regulations.gov in Docket 
No. FAA-2018-0722.

(j) Subject

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

    Issued in Fort Worth, Texas, on May 31, 2019.
Lance T. Gant,
Director, Compliance & Airworthiness Division, Aircraft Certification 
Service.
[FR Doc. 2019-11991 Filed 6-6-19; 8:45 am]
BILLING CODE 4910-13-P


