AD 2015-15-04

[Federal Register Volume 80, Number 141 (Thursday, July 23, 2015)]
[Rules and Regulations]
[Pages 43615-43617]
From the Federal Register Online via the Government Publishing Office [<a href="http://www.gpo.gov">www.gpo.gov</a>]
[FR Doc No: 2015-17953]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2015-2906; Directorate Identifier 2014-SW-068-AD; 
Amendment 39-18213; AD 2015-15-04]
RIN 2120-AA64


Airworthiness Directives; Bell Helicopter Textron, Inc.

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule; request for comments.

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SUMMARY: We are adopting a new airworthiness directive (AD) for certain 
Bell Helicopter Textron, Inc. (Bell), Model 204B, 205A, 205A-1, and 212 
helicopters. This AD requires removing a certain part-numbered main 
rotor (M/R) blade grip (grip) from service. This AD is prompted by an 
error in a parts manufacturer approval (PMA) that incorrectly allows 
installation of the grips on the Bell Model 212. The actions specified 
in this AD are intended to prevent grip failure, separation of the M/R 
blade, and subsequent loss of control of the helicopter.

DATES: This AD becomes effective August 7, 2015. We must receive 
comments on this AD by September 21, 2015.

ADDRESSES: You may send comments by any of the following methods:
    <bullet> Federal eRulemaking Docket: Go to <a href="http://www.regulations.gov">http://www.regulations.gov</a>. Follow the online instructions for sending your 
comments electronically.
    <bullet> Fax: 202-493-2251.
    <bullet> 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.
    <bullet> 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 <a href="http://www.regulations.gov">http://www.regulations.gov</a> 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 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 Timken service information identified in this AD, contact 
Timken Alcor Aerospace Technologies, Inc., Aftermarket Customer 
Service, 3110 N. Oakland, Mesa, AZ 85215; telephone 1-480-606-3130; 
email <a href="/cdn-cgi/l/email-protection#6e1a0703050b000f081a0b1c030f1c050b1a1d0f020b1d2e1a0703050b00400d0103"><span class="__cf_email__" data-cfemail="2155484c4a444f40475544534c40534a445552404d44526155484c4a444f0f424e4c">[email&#160;protected]</span></a>; or at <a href="http://www.timken.com/en-us/solutions/aerospace/aftermarket/Pages/default.aspx">http://www.timken.com/en-us/solutions/aerospace/aftermarket/Pages/default.aspx</a>. 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: Scott Franke, Aviation Safety 
Engineer, Fort Worth Aircraft Certification Office, Rotorcraft 
Directorate, FAA, 10101 Hillwood Pkwy, Fort Worth, TX 76177; telephone 
(817) 222-5170; email <a href="/cdn-cgi/l/email-protection#b8cbdbd7cccc96decad9d6d3ddf8ded9d996dfd7ce"><span class="__cf_email__" data-cfemail="26554549525208405447484d436640474708414950">[email&#160;protected]</span></a>.

SUPPLEMENTARY INFORMATION: 

Comments Invited

    This AD is a final rule that involves requirements affecting flight 
safety, and we did not provide you with notice and an opportunity to 
provide your comments prior to it becoming effective. However, 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 resulted 
from adopting this AD. The most helpful comments reference a specific 
portion of the AD, 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 them 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 rulemaking during the 
comment period. We will consider all the comments we receive and may 
conduct additional rulemaking based on those comments.

[[Page 43616]]

Discussion

    We are adopting a new AD for Bell Model 204B, 205A, 205A-1, and 212 
helicopters with a grip part number (P/N) ASI-4011-121-113 installed. 
This AD requires removing any grip from service if the grip is 
currently or has ever been installed on a Bell Model 212 helicopter, or 
if it is unknown whether the grip has ever been installed on a Model 
212 helicopter. This AD also prohibits installing grip P/N ASI-4011-
121-113 on any helicopter if the grip has ever been installed on a Bell 
Model 212 helicopter. This AD is prompted by an error in the PMA that 
allows installing the subject grip on the Bell Model 212.
    Grip P/N ASI-4011-121-113 is currently produced by Timken Alcor 
Aerospace Technologies, Inc., under a PMA as a replacement grip for 
Bell P/N 204-011-121-113. This approval incorrectly listed grip P/N 
ASI-4011-121-113 as eligible for installation on Bell Model 212 
helicopters. The PMA has been revised to remove that eligibility. This 
grip was previously produced and sold as a replacement grip for Bell P/
N 204-011-121-113 by Air Services International of Scottsdale, AZ, as 
P/N ASI-4011-121-113. The actions required in this AD are intended to 
prevent installation of an unapproved grip, which could result in grip 
failure, separation of the M/R blade, and subsequent loss of control of 
the helicopter.

FAA's Determination

    We are issuing this AD because we evaluated all known relevant 
information and determined that the unsafe condition described 
previously is likely to exist in other products of these same type 
designs.

Related Service Information

    We reviewed Timken T-700 Service Bulletin, Revision B, dated 
October 20, 2014. The service bulletin specifies the airworthiness life 
limitations and inspection interval schedule for various Timken Alcor 
Aerospace Technologies, Inc., replacement parts and articles.

AD Requirements

    This AD requires, within 5 hours time-in-service (TIS), removing 
any grip P/N ASI-4011-121-113 from service if the grip is currently or 
has ever been installed on a Bell Model 212 helicopter. This AD also 
prohibits installing a grip P/N ASI-4011-121-113 on any helicopter if 
the grip is currently or has ever been installed on a Bell Model 212 
helicopter.

Differences Between This AD and the Service Information

    The Timken service bulletin provides the airworthiness limitations 
and inspection intervals for various life limited parts, including grip 
P/N ASI-4011-121-113. This AD only applies to helicopters with grip P/N 
ASI-4011-121-113 and requires removing the grip from service if it is 
currently or has ever been installed on a Bell Model 212 helicopter.

Costs of Compliance

    We estimate that this AD could affect 130 helicopters of U.S. 
Registry. We estimate that operators may incur the following costs in 
order to comply with this AD. It takes about 20 work-hours to replace 
two M/R grips per helicopter. We estimate an average labor rate of $85 
per work-hour, and a required parts cost of approximately $56,385 for 
two grips. Based on these figures, we estimate a total cost of $58,085 
per helicopter and $7,551,050 for the U.S. fleet.

FAA's Justification and Determination of the Effective Date

    Providing an opportunity for public comments prior to adopting 
these AD requirements would delay implementing the safety actions 
needed to correct this known unsafe condition. Therefore, we find that 
the risk to the flying public justifies waiving notice and comment 
prior to the adoption of this rule because the unsafe condition can 
adversely affect control of the helicopter and the required corrective 
actions must be accomplished within 5 hours TIS.
    Since an unsafe condition exists that requires the immediate 
adoption of this AD, we determined that notice and opportunity for 
public comment before issuing this AD are impracticable and contrary to 
the public interest and that good cause exists for making this 
amendment effective in less than 30 days.

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 would not have federalism implications 
under Executive Order 13132. This 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 
responsibilities among the various levels of government.
    For the reasons discussed, 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 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 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.

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 adding the following new airworthiness 
directive (AD):

2015-15-04 Bell Helicopter Textron, Inc. (Bell): Amendment 39-18213; 
Docket No. FAA-2015-2906; Directorate Identifier 2014-SW-068-AD.

(a) Applicability

    This AD applies to the following helicopters, certificated in 
any category:
    (1) Bell Model 204B, 205A, and 205A-1 helicopters, with a main 
rotor (M/R) blade grip (grip) part number (P/N) ASI-4011-121-

[[Page 43617]]

113 installed, if the grip was ever installed on a Model 212 
helicopter or if it is unknown whether a grip was ever installed on 
a Model 212 helicopter; and
    (2) Bell Model 212 helicopters, with a grip P/N ASI-4011-121-113 
installed.

(b) Unsafe Condition

    This AD defines the unsafe condition as installation of a grip 
that does not meet type design. This condition could result in grip 
failure, separation of the M/R blade, and subsequent loss of control 
of the helicopter.

(c) Effective Date

    This AD becomes effective August 7, 2015.

(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 5 hours time-in-service, remove each grip from 
service.
    (2) Do not install a grip listed in paragraph (a) of this AD on 
any helicopter.

(f) Alternative Methods of Compliance (AMOC)

    (1) The Manager, Fort Worth Aircraft Certification Office, FAA, 
may approve AMOCs for this AD. Send your proposal to: Scott Franke, 
Aviation Safety Engineer, Fort Worth Aircraft Certification Office, 
Rotorcraft Directorate, FAA, 10101 Hillwood Pkwy, Fort Worth, TX 
76177; telephone (817) 222-5170; email <a href="/cdn-cgi/l/email-protection#6d1e0e021919430b1f0c0306082d0b0c0c430a021b"><span class="__cf_email__" data-cfemail="95e6f6fae1e1bbf3e7f4fbfef0d5f3f4f4bbf2fae3">[email&#160;protected]</span></a>.
    (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

    Timken T-700 Service Bulletin, Revision B, dated October 20, 
2014, which is not incorporated by reference, contains additional 
information about the subject of this AD. For Timken service 
information identified in this AD, contact Timken Alcor Aerospace 
Technologies, Inc., Aftermarket Customer Service, 3110 N. Oakland, 
Mesa, AZ 85215; telephone 1-480-606-3130; email 
<a href="/cdn-cgi/l/email-protection#55213c383e303b34332130273834273e3021263439302615213c383e303b7b363a38"><span class="__cf_email__" data-cfemail="62160b0f09070c03041607100f031009071611030e071122160b0f09070c4c010d0f">[email&#160;protected]</span></a>; or at <a href="http://www.timken.com/en-us/solutions/aerospace/aftermarket/Pages/default.aspx">http://www.timken.com/en-us/solutions/aerospace/aftermarket/Pages/default.aspx</a>. You may 
review a copy of this service information at the FAA, Office of the 
Regional Counsel, Southwest Region, 10101 Hillwood Pkwy, Room 6N-
321, Fort Worth, TX 76177.

(h) Subject

    Joint Aircraft Service Component (JASC) Code: 6620, Main Rotor 
Blade Grip.

    Issued in Fort Worth, Texas, on July 13, 2015.
Bruce E. Cain,
Acting Directorate Manager, Rotorcraft Directorate, Aircraft 
Certification Service.
[FR Doc. 2015-17953 Filed 7-22-15; 8:45 am]
 BILLING CODE 4910-13-P