[Federal Register Volume 79, Number 146 (Wednesday, July 30, 2014)]
[Proposed Rules]
[Pages 44147-44149]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2014-17925]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2014-0499; Directorate Identifier 2013-SW-061-AD]
RIN 2120-AA64


Airworthiness Directives; Bell Helicopter Textron Canada

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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SUMMARY: We propose to adopt a new airworthiness directive (AD) for 
Bell Helicopter Textron Canada (BHTC) Model 430 helicopters to require 
inspecting the tail rotor control tube assembly (control tube) and 
either repairing or replacing the control tube. This proposed AD is 
prompted by two reports of failure of the control tube bonded clevis. 
The proposed actions are intended to prevent failure of a control tube 
bonded clevis, which could lead to failure of the control tube and 
subsequent loss of helicopter control.

DATES: We must receive comments on this proposed AD by September 29, 
2014.

ADDRESSES: You may send comments by any of the following methods:
     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 or in person at the Docket Operations Office 
between 9 a.m. and 5 p.m., Monday through Friday, except Federal 
holidays. The AD docket contains this proposed AD, the foreign 
authority's AD, the economic evaluation, any comments received, and 
other information. The street address for the Docket Operations Office 
(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 proposed AD, contact 
Bell

[[Page 44148]]

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, 2601 Meacham Blvd., Room 663, Fort Worth, 
Texas 76137.

FOR FURTHER INFORMATION CONTACT: Matt Fuller, Senior Aviation Safety 
Engineer, Safety Management Group, Rotorcraft Directorate, FAA, 2601 
Meacham Blvd., Fort Worth, Texas 76137; 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

    Transport Canada Civil Aviation (TCCA), which is the aviation 
authority for Canada, has issued Canadian AD No. CF-2013-30, dated 
October 7, 2013, to correct an unsafe condition for BHTC Model 430 
helicopters with control tube part number (P/N) 430-001-007-101. TCCA 
advises of two cases concerning failures of the control tube bonded 
clevis caused by cracking from control tube oscillation. TCCA states 
that this situation, if not corrected, could result in the loss of 
control of the helicopter. TCCA AD No. CF-2013-30 consequently requires 
a one-time inspection of the control tube for damage and contacting 
BHTC for evaluation of the control tube if the damage exceeds allowable 
limits. If the tube is not damaged, the damage is within allowable 
limits, or BHTC Engineering determines the control tube can be returned 
to service, TCCA AD No. CF-2013-30 requires modifying the tube 
according to BHTC's service information. TCCA AD No. CF-2013-30 also 
requires replacing control tubes, P/N 430-001-007-101, with control 
tube, P/N 430-001-007-105, no later than 12 months from the effective 
date of its AD.

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, TCCA, its technical 
representative, has notified us of the unsafe condition described in 
its AD. We are proposing this AD because we evaluated all known 
relevant information and determined that an unsafe condition is likely 
to exist or develop on other products of the same type design.

Related Service Information

    We reviewed Bell Helicopter Alert Service Bulletin No. 430-13-51, 
dated September 3, 2013 (ASB), which states that BHTC received two 
reports of control tube, P/N 430-001-007-101, failing because the 
clevis failed due to fatigue caused by control tube oscillation. The 
ASB specifies a one-time inspection of control tube assembly, P/N 430-
001-007-101, to verify if the tube has chaffing damage. Bell Helicopter 
Technical Bulletin 430-04-35, Revision B, dated March 20, 2009, 
recommends that control tube, P/N 430-001-007-101, be replaced with 
control tube, P/N 430-001-007-105, if damage exists.

Proposed AD Requirements

    This proposed AD would require:
     Within 50 hours time-in-service (TIS), visually inspecting 
each control tube for damage, damage to the clevis, and to determine 
whether the clevis is correctly bonded to the control tube.
     If a control tube and clevis have no damage or damage 
within acceptable limits and the clevis is correctly bonded to the 
control tube, repairing the control tube by applying tape.
     If the control tube or clevis is damaged beyond acceptable 
limits or if the clevis is not correctly bonded, replacing control 
tube, P/N 430-001-007-101, with control tube, P/N 430-001-007-105.
     Within 250 hours TIS after the effective date of this AD, 
replacing each control tube, P/N 430-001-007-101, with control tube, P/
N 430-001-007-105.

Differences Between This Proposed AD and the TCCA AD

    The TCCA AD requires submitting sketches of a control tube damaged 
beyond defined limits to BHTC for evaluation. BHTC then determines if 
the control tube can be returned to service. We make no such 
requirement in this proposed AD.

Costs of Compliance

    We estimate that this proposed AD would affect 5 helicopters of 
U.S. Registry and that labor costs average $85 a work hour. Based on 
these estimates, expect the following costs:
     The cost of inspecting the control tube would be minimal.
     Repairing the control tube would require 2 work-hours for 
a labor cost of $170.
     Replacing control tube, P/N 430-001-007-101, with control 
tube, P/N 430-001-007-105, would require 3 work-hours for a labor cost 
of $255. Parts would cost $3,974 for a total cost per helicopter of 
$4,229.

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 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

[[Page 44149]]

responsibilities among the various levels of government.
    For the reasons discussed, I certify this proposed regulation:
    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 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. Amend Sec.  39.13 by adding the following new airworthiness 
directive (AD):

Bell Helicopter Textron Canada: Docket No. FAA-2014-0499; 
Directorate Identifier 2013-SW-061-AD.

(a) Applicability

    This AD applies to Bell Helicopter Textron Canada (BHTC) Model 
430 Helicopters, serial number 49001 through 49121, with control 
tube assembly (control tube), part number (P/N) 430-001-007-101, 
installed, certificated in any category.

(b) Unsafe Condition

    This AD defines the unsafe condition as fatigue failure of a 
tail rotor control tube bonded clevis. This condition could result 
in failure of the tail rotor control tube and subsequent loss of 
helicopter control.

(c) Comments Due Date

    We must receive comments by September 29, 2014.

(d) 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.

(e) Required Actions

    (1) Within 50 hours time-in-service (TIS), visually inspect each 
control tube for any damage, for any damage to the clevis, and to 
determine whether the clevis is correctly bonded to the control 
tube.
    (i) If a control tube and clevis have no damage or damage within 
acceptable limits and the clevis is correctly bonded to the control 
tube, repair the control tube by applying tape in accordance the 
Accomplishment Instructions, Paragraph 5, of Bell Helicopter Alert 
Service Bulletin 430-13-51, dated September 3, 2013.
    (ii) If the control tube or clevis is damaged beyond acceptable 
limits or if the clevis is not correctly bonded to the control tube, 
replace control tube, P/N 430-001-007-101, with control tube, P/N 
430-001-007-105.
    (2) Within 250 hours TIS, replace each control tube, P/N 430-
001-007-101, with control tube, P/N 430-001-007-105.

(f) Alternative Methods of Compliance (AMOCs)

    (1) The Manager, Safety Management Group, FAA, may approve AMOCs 
for this AD. Send your proposal to: Matt Fuller, Senior Aviation 
Safety Engineer, Safety Management Group, Rotorcraft Directorate, 
FAA, 2601 Meacham Blvd., Fort Worth, Texas 76137; 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.

(g) Additional Information

    (1) Bell Helicopter Technical Bulletin 430-04-35, Revision B, 
dated March 20, 2009, which is not incorporated by reference, 
contains additional information about the subject of this AD. For 
service information, 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, 2601 Meacham Blvd., Room 663, Fort Worth, Texas 76137.
    (2) The subject of this AD is addressed in the Transport Canada 
Civil Aviation (TCCA) AD No. CF-2013-30, dated October 7, 2013. You 
may view the TCCA AD on the Internet at http://www.regulations.gov 
in Docket No. FAA-2014-0499.

(h) Subject

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

    Issued in Fort Worth, Texas, on July 18, 2014.
S. Frances Cox,
Acting Directorate Manager, Rotorcraft Directorate, Aircraft 
Certification Service.
[FR Doc. 2014-17925 Filed 7-29-14; 8:45 am]
BILLING CODE 4910-13-P