Document ID: FAA-2018-0722-0001
Agency: faa
Document Type: Proposed Rule
Title: Airworthiness Directives: Bell Helicopter Textron Canada Limited Helicopters
Posted Date: 2018-08-08T04:00Z

[Federal Register Volume 83, Number 153 (Wednesday, August 8, 2018)]
[Proposed Rules]
[Pages 39004-39007]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2018-16637]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2018-0722; Product Identifier 2017-SW-104-AD
RIN 2120-AA64

Airworthiness Directives; Bell Helicopter Textron Canada Limited 
Helicopters

AGENCY: Federal Aviation Administration (FAA), Department of 
Transportation (DOT).

ACTION: Notice of proposed rulemaking (NPRM).

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SUMMARY: We propose to supersede airworthiness directive (AD) 2015-22-
02 for Bell Helicopter Textron Canada Limited (Bell) Model 429 
helicopters. AD 2015-22-02 requires inspecting the tail rotor (TR) 
pitch link assemblies. This proposed AD would retain the inspections of 
AD 2015-22-02 and would require replacing certain pitch link bearings. 
Since we issued AD 2015-22-02, Bell has introduced a new design 
bearing. The actions of this proposed AD are intended to prevent an 
unsafe condition on these products.

DATES: We must receive comments on this proposed AD by October 9, 2018.

ADDRESSES: You may send comments by any of the following methods:

[[Page 39005]]

     Federal eRulemaking Docket: Go to http://www.regulations.gov. Follow the online instructions for sending your 
comments electronically.
     Fax: 202-493-2251.
     Mail: Send comments to the U.S. Department of 
Transportation, Docket Operations, M-30, West Building Ground Floor, 
Room W12-140, 1200 New Jersey Avenue SE, Washington, DC 20590-0001.
     Hand Delivery: Deliver to the ``Mail'' address between 9 
a.m. and 5 p.m., Monday through Friday, except Federal holidays.

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 proposed AD, the Transport Canada AD, the economic evaluation, any 
comments received, and other information. The street address for Docket 
Operations (telephone 800-647-5527) is in the ADDRESSES section. 
Comments will be available in the AD docket shortly after receipt.
    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.

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 [email protected].

SUPPLEMENTARY INFORMATION:

Comments Invited

    We invite you to participate in this rulemaking by submitting 
written comments, data, or views. We also invite comments relating to 
the economic, environmental, energy, or federalism impacts that might 
result from adopting the proposals in this document. The most helpful 
comments reference a specific portion of the proposal, explain the 
reason for any recommended change, and include supporting data. To 
ensure the docket does not contain duplicate comments, commenters 
should send only one copy of written comments, or if comments are filed 
electronically, commenters should submit only one time.
    We will file in the docket all comments that we receive, as well as 
a report summarizing each substantive public contact with FAA personnel 
concerning this proposed rulemaking. Before acting on this proposal, we 
will consider all comments we receive on or before the closing date for 
comments. We will consider comments filed after the comment period has 
closed if it is possible to do so without incurring expense or delay. 
We may change this proposal in light of the comments we receive.

Discussion

    We issued AD 2015-22-02, Amendment 39-18306 (80 FR 65618, October 
27, 2015) (AD 2015-22-02), for Bell Model 429 helicopters with a TR 
pitch link assembly part number (P/N) 429-112-101 or 429-112-103 
installed. AD 2015-22-02 requires repetitively inspecting each inboard 
and outboard TR pitch link assembly for axial or radial bearing play 
every 50 hours time-in-service (TIS), performing a dimensional 
inspection of the TR pitch link if there is axial or radial bearing 
play, and replacing the TR pitch link before further flight if there is 
any wear beyond allowable limits. AD 2015-22-02 was prompted by 
Emergency AD No. CF-2015-16, dated July 2, 2015, and Emergency AD No. 
CF-2015-16R1, dated August 6, 2015, issued by Transport Canada, to 
correct an unsafe condition for Bell Model 429 helicopters. Transport 
Canada advised of several occasions where the TR pitch link spherical 
bearings experienced early and accelerated wear.

Actions Since AD 2015-22-02 Was Issued

    Since we issued AD 2015-22-02, Transport Canada has issued AD No. 
CF-2015-16R2, dated April 17, 2017, which supersedes AD CF-2015-16R1. 
According to Transport Canada, 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 P/N after installing the new 
bearings. We propose to issue this AD to make similar changes.

FAA's Determination

    These helicopters have been approved by the aviation authority of 
Canada and 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 products of 
the same type design.

Related Service Information

    Bell has issued 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.

AD Requirements

    This proposed AD would require performing a dimensional inspection 
of the spherical bearings for axial and radial play and inspecting the 
TR pitch link assembly sealant for pin holes, voids, and excessive 
thickness. These inspections would be required within 50 hours TIS and 
thereafter at intervals not exceeding 50 hours TIS.
    This proposed AD would also require replacing any spherical bearing 
manufactured before January 13, 2015, that has exceeded 250 hours TIS 
or that has an unknown number of hours TIS, and re-identifying the P/N 
of the TR pitch link assembly.

Differences Between This Proposed AD and the Transport Canada AD

    The Transport Canada AD requires the bearing inspection within 10 
hours TIS or before exceeding 60 hours TIS since new, whichever occurs 
later. This proposed AD would require 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 proposed 
AD would require replacing the bearing within 200 hours of the initial 
inspection or at the next 50 hour TIS inspection if the hours TIS of a 
pitch link assembly exceed 250 hours TIS or are unknown.

Interim Action

    We consider this proposed AD to be an interim action. If final 
action is later

[[Page 39006]]

identified, we might consider further rulemaking then.

Costs of Compliance

    We estimate that this proposed AD would affect 85 helicopters of 
U.S. Registry. We estimate that operators may incur the following costs 
in order to comply with this proposed AD. At an average labor rate of 
$85 per hour, inspecting the TR pitch link assemblies would require 2 
work-hours for a cost of $170 per helicopter and $14,450 for the U.S. 
fleet per inspection cycle. Replacing both spherical bearings in each 
TR pitch link assembly would require 3 work-hours, and required parts 
would cost $3,088, for a cost of $3,343 per helicopter and $284,155 for 
the U.S. fleet.
    According to Bell's service information some of the costs of this 
proposed 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 proposed AD will not have federalism 
implications under Executive Order 13132. This proposed 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, I certify that this proposed regulation:
    1. Is not a ``significant regulatory action'' under Executive Order 
12866;
    2. Is not a ``significant rule'' under DOT Regulatory Policies and 
Procedures (44 FR 11034, February 26, 1979);
    3. Will not affect intrastate aviation in Alaska to the extent that 
it justifies making a regulatory distinction; 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.
    We prepared an economic evaluation of the estimated costs to comply 
with this proposed AD and placed it in the AD docket.

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 removing Airworthiness Directive (AD) 
2015-22-02, Amendment 39-18306 (80 FR 65618, October 27, 2015), and 
adding the following new AD:

Bell Helicopter Textron Canada Limited: Docket No. FAA-2018-0722; 
Product Identifier 2017-SW-104-AD.

(a) Applicability

    This AD applies to Model 429 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, certificated in any 
category.

(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) Comments Due Date

    We must receive comments by October 9, 2018.

(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 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 [email protected].
    (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.

[[Page 39007]]

(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 17, 2017. You may view the Transport 
Canada AD on the internet at http://www.regulations.gov in the AD 
Docket.

(j) Subject

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

    Issued in Fort Worth, Texas, on July 23, 2018.
Scott A. Horn,
Deputy Director for Regulatory Operations, Compliance & Airworthiness 
Division, Aircraft Certification Service.
[FR Doc. 2018-16637 Filed 8-7-18; 8:45 am]
BILLING CODE 4910-13-P