```

[Federal Register Volume 80, Number 207 (Tuesday, October 27, 2015)]
[Rules and Regulations]
[Pages 65618-65620]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2015-27137]

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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2015-4345; Directorate Identifier 2015-SW-049-AD; 
Amendment 39-18306; AD 2015-22-02]
RIN 2120-AA64

Airworthiness Directives; Bell Helicopter Textron Canada Limited 
Helicopters

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

ACTION: Final rule; request for comments.

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

SUMMARY: We are superseding emergency airworthiness directive (AD) No. 
2015-16-51 (Emergency AD 2015-16-51) for Bell Helicopter Textron Canada 
Limited (Bell) Model 429 helicopters. Emergency AD 2015-16-51 required 
inspections of each inboard and outboard tail rotor pitch link assembly 
for axial or radial bearing play, and if there was axial or radial 
bearing play, removing the tail rotor pitch link and inspecting for 
wear. Emergency AD 2015-16-51 was prompted by several reports of worn 
tail rotor pitch link spherical bearings. We are issuing this 
supersedure to retain the inspection requirements in Emergency AD 2015-
16-51 while revising the applicability and compliance time to clarify 
that all Bell Model 429 helicopters require recurring inspections 
regardless of hours time-in-service (TIS) accumulated on the 
helicopter. These actions are intended to prevent pitch link failure 
and subsequent loss of control of the helicopter.

DATES: This AD becomes effective November 12, 2015.
    We must receive comments on this AD by December 28, 2015.

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 by searching for and locating Docket No. FAA-2015-
4345; 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 Transport Canada Emergency 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 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 the referenced service information at the FAA, Office of the

[[Page 65619]]

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 Group, Rotorcraft Directorate, FAA, 10101 
Hillwood Pkwy, Fort Worth, TX 76177; telephone (817) 222-5110; email 
david.hatfield@faa.gov.

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.

Discussion

    Transport Canada, which is the aviation authority for Canada, 
issued Emergency AD No. CF-2015-16, dated July 2, 2015, to correct an 
unsafe condition for Bell Model 429 helicopters. Transport Canada 
advised that in-service reports showed that the tail rotor pitch link 
spherical bearings have experienced early and accelerated wear. On 
three occasions, bearings were found worn beyond limits during pre-
flight inspections, showing a radial and axial play that was easily 
detectable. In one case, the spherical bearing separated from the tail 
rotor pitch link, resulting in damage to the tail rotor blade pitch 
horn assembly. In another case, the spherical bearing had been 
inspected and found acceptable during a maintenance inspection; about 
``1 hour air time'' later, it was found worn beyond limits during a 
pre-flight inspection.
    On August 6, 2015, we issued Emergency AD 2015-16-51, which was 
made immediately effective to all known U.S. owners and operators of 
Bell Model 429 helicopters. Emergency AD 2015-16-51 required, before 
further flight and thereafter at intervals not to exceed 50 hours TIS, 
inspecting each inboard and outboard tail rotor pitch link assembly for 
axial or radial bearing play. Emergency AD 2015-16-51 also required, if 
there was axial or radial bearing play, removing the tail rotor pitch 
link and performing a dimensional inspection for wear. Finally, 
Emergency AD 2015-16-51 required, if wear exceeded the allowable 
limits, replacing the tail rotor pitch link assembly.

Actions Since Emergency AD 2015-16-51 Was Issued

    On the same day that we issued Emergency AD 2015-16-51, Transport 
Canada issued a revised Emergency AD No. CF-2015-16R1, dated August 6, 
2015, changing the applicability and compliance time to clarify that 
the inspections are required for all Model 429 helicopters. Transport 
Canada advises of the possibility that some operators would conclude 
that no action was required for low time helicopters. Transport Canada 
Emergency AD No. CF-2015-16R1 removes the following language from the 
applicability so that it applies to all Model 429 helicopters 
regardless of time: ``that have accumulated 50 hours air time or 
more.'' It also adds language to the compliance time so that the 
corrective actions must be accomplished within 10 hours air time ``or 
before exceeding 60 hours air time since new, whichever occurs later.'' 
Therefore, we are issuing this AD to make similar revisions.

FAA's Determination

    These helicopters have been approved by Transport 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 its Emergency AD. 
We are issuing 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 this same type 
design.

Related Service Information

    Bell issued Alert Service Bulletin 429-15-16, dated February 18, 
2015 (ASB) for Bell Model 429 helicopters, S/N 57001 and subsequent, 
which have accumulated more than 50 hours. The ASB specifies inspecting 
both inboard and outboard tail rotor pitch link assemblies for axial 
and radial play. If abnormal wear or bearing play is detected, the ASB 
specifies removing the affected tail rotor pitch link, performing a 
dimensional check of both axial and radial play, and replacing any tail 
rotor pitch link assembly 429-012-112-101 or -103 or pitch link bearing 
429-312-107-103 that exceeds the allowable limits.

AD Requirements

    This AD retains the inspection requirements of Emergency AD 2015-
16-51 but revises the applicability and compliance time. This AD 
applies to Model 429 helicopters regardless of accumulated TIS. The 
inspections in this AD are required before further flight for 
helicopters with 50 or more hours TIS and before accumulating 50 hours 
TIS for helicopters with less than 50 hours TIS.

Differences Between This AD and the Transport Canada Emergency AD

    The Transport Canada Emergency AD requires compliance within 10 
hours TIS or before exceeding 60 hours air time, whichever occurs 
later. This AD requires compliance before further flight for 
helicopters with 50 or more hours TIS. For helicopters with less than 
50 hours TIS, this AD requires compliance before the helicopter 
accumulates 50 hours TIS.

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 54 helicopters of U.S. Registry. 
We estimate that operators may incur the following costs in order to 
comply with this AD. Labor costs are estimated at $85 per work hour. It 
will take about 2 work hours to do the inspections at an estimated cost 
of $170 per helicopter or $9,180 for the fleet per inspection cycle. 
Replacing a tail rotor pitch link assembly will take 4 work hours and 
required parts will cost $2,685 for a total cost of $3,025 per 
helicopter.

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 found and 
continue to find that the risk to the flying public justifies waiving 
notice and comment prior to adopting this rule because the previously 
described unsafe condition can adversely affect the controllability

[[Page 65620]]

of the helicopter, and the initial required corrective actions must be 
accomplished before further flight or before accumulating 50 hours TIS, 
depending upon the hours TIS accumulated on the helicopter.
    Since it was found that immediate corrective action was required, 
notice and opportunity for prior public comment before issuing this AD 
were impracticable and contrary to the public interest, and good cause 
existed to make the AD effective immediately by Emergency AD 2015-16-
51, issued on August 6, 2015, to all known U.S. owners and operators of 
these helicopters. These conditions still exist and the Emergency AD is 
hereby superseded.

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, I certify that this AD:
    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 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):

2015-22-02 Bell Helicopter Textron Canada Limited: Amendment 39-
18306; Docket No. FAA-2015-4345; Directorate Identifier 2015-SW-049-
AD.

(a) Applicability

    This AD applies to Model 429 helicopters with a pitch link 
assembly part number 429-012-112-101 or -103 installed, certificated 
in any category.

(b) Unsafe Condition

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

(c) Affected ADs

    This AD supersedes Emergency AD 2015-16-51, Directorate 
Identifier 2015-SW-23-AD, dated August 6, 2015.

(d) Effective Date

    This AD becomes effective November 12, 2015.

(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 helicopters with 50 or more hours time-in-service (TIS), 
before further flight, and for helicopters with less than 50 hours 
TIS, before accumulating 50 hours TIS, inspect each inboard and 
outboard tail rotor pitch link assembly for axial or radial bearing 
play. If there is axial or radial bearing play, remove the tail 
rotor pitch link and perform a dimensional inspection for wear. If 
there is wear that exceeds the allowable limits, replace the tail 
rotor pitch link assembly.
    (2) Thereafter, at intervals not to exceed 50 hours TIS, repeat 
the inspections required by paragraph (f)(1) of this AD.

(g) Alternative Methods of Compliance (AMOCs)

    (1) The Manager, Safety Management Group, FAA, may approve AMOCs 
for this AD. Send your proposal to: David Hatfield, Aviation Safety 
Engineer, Safety Management Group, Rotorcraft Directorate, 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.

(h) Additional Information

    (1) Bell Helicopter Alert Service Bulletin 429-15-16, dated 
February 18, 2015, 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 the referenced 
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 
Emergency AD No. CF-2015-16R1, dated August 6, 2015. You may view 
the Transport Canada Emergency AD on the Internet at http://www.regulations.gov in Docket No. FAA-2015-4345.

(i) Subject

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

    Issued in Fort Worth, Texas, on October 16, 2015.
Lance T. Gant,
Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. 2015-27137 Filed 10-26-15; 8:45 am]
BILLING CODE 4910-13P
```