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[Federal Register Volume 81, Number 21 (Tuesday, February 2, 2016)]
[Rules and Regulations]
[Pages 5367-5369]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2016-01747]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2016-2068; Directorate Identifier 2016-SW-002-AD; 
Amendment 39-18387; AD 2016-02-06]
RIN 2120-AA64

Airworthiness Directives; Bell Helicopter Textron Canada Limited

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

ACTION: Final rule; request for comments.

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SUMMARY: We are adopting a new airworthiness directive (AD) for Bell 
Helicopter Textron Canada Limited (Bell) Model 429 helicopters. This AD 
requires inspecting each tail rotor (T/R) pitch link (link) bearing 
bore for corrosion and pitting and either replacing the T/R link or 
applying sealant. This AD also requires a recurring inspection of the 
sealant and repeating the inspections for corrosion and pitting if any 
sealant is missing. This AD is prompted by an incident in which a 
helicopter experienced an in-flight failure of a T/R link. These 
actions are intended to detect corrosion or pitting and to prevent 
failure of a T/R link and subsequent loss of control of the helicopter.

DATES: This AD becomes effective February 2, 2016.
    The Director of the Federal Register approved the incorporation by 
reference of a certain document listed in this AD as of February 2, 
2016.
    We must receive comments on this AD by April 4, 2016.

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-2016-
2068; 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 AD, the incorporated by 
reference service information, 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 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: Matt Fuller, Senior Aviation Safety 
Engineer, Safety Management Group, Rotorcraft Directorate, FAA, 10101 
Hillwood Pkwy, Fort Worth, TX 76177; telephone (817) 222-5110; email 
matthew.fuller@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

    We are adopting a new AD for Bell Model 429 helicopters with a T/R 
link part number (P/N) 429-012-112-101, -101FM, -103, or -103FM 
installed. This AD requires inspecting each T/R link bearing bore for 
any aluminum oxide corrosion and then cleaning the affected area of the 
T/R link and inspecting for any pitting. If there is any corrosion or 
any pitting, this AD requires replacing the T/R link. If there is no 
corrosion or pitting, this AD requires applying corrosion preventative 
sealant. This AD also requires a recurring inspection of the sealant, 
and repeating the inspection for corrosion and pitting if any sealant 
is missing.
    This AD was prompted by AD No. CF-2016-01, dated January 5, 2016, 
issued by Transport Canada, which is the aviation authority for Canada, 
to correct an unsafe condition for Bell Model 429 helicopters. 
Transport Canada advises of an incident in which a T/R link on a Model 
429 helicopter failed, causing vibration and difficulty controlling the 
helicopter. According to Transport Canada, the failure was caused by a 
crack that had initiated at a corrosion pit between the roll staked lip 
of the bearing and the beveled edge of the link. Transport Canada 
further states deficiencies in the application of corrosion resistant 
finishes to the link during manufacturing caused the corrosion.
    This condition, if not detected, could result in failure of a link 
and loss of control of the helicopter. For these reasons, Transport 
Canada AD No. CF-2016-01 requires inspection of the T/R link and 
replacement of any link with corrosion. The Transport Canada AD also 
requires application of corrosion preventative sealant and re-
identification of the T/R link.

FAA's Determination

    This helicopter has been approved by the aviation authority of 
Canada and is 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 Canadian 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

[[Page 5368]]

develop on other helicopters of the same type design.

Related Service Information Under 1 CFR Part 51

    Bell Helicopter issued Alert Service Bulletin 429-15-26, dated 
December 7, 2015 (ASB), which advises of receiving reports of corrosion 
on T/R links between the roll staked lip of bearing P/N 429-312-107-103 
and the beveled edge of T/R link P/N 429-012-112-101/-103. The ASB 
specifies, within 10 flight hours or before March 7, 2016, an 
inspection with 10X magnification of all 8 T/R link bearing bores 
between the roll staked lip of the bearing outer race and the link 
bearing bore for corrosion. If there is corrosion, the ASB specifies 
replacing the link. If there is no corrosion, the ASB specifies 
cleaning the area and performing a second inspection with 10X 
magnification. If there is corrosion, the ASB specifies replacing the 
link. If there is no corrosion, the ASB specifies removing the torque 
stripe, cleaning the area, and applying corrosion preventative sealant. 
The ASB also specifies re-identifying the P/Ns as 429-012-112-101FM and 
429-012-112-103FM. Further, the ASB specifies, at intervals of 50 
flight hours after the initial actions, an inspection of the sealant 
and reapplication if the sealant is damaged.
    This service information is reasonably available because the 
interested parties have access to it through their normal course of 
business or by the means identified in the ADDRESSES section.

AD Requirements

    This AD requires, within 10 hours time-in-service (TIS), without 
first cleaning the T/R link bearing bores, using 10X or higher 
magnification to inspect each T/R link bearing bore for any aluminum 
oxide corrosion extruding from between the roll staked lip of the 
bearing outer race and the link bearing bore. If there is any aluminum 
oxide corrosion, this AD requires replacing the T/R link before further 
flight. If there is no corrosion, this AD requires cleaning the T/R 
link bearing bores and inspecting for any pitting. If there is any 
pitting, this AD requires replacing the T/R link before further flight. 
If there is no pitting, this AD requires applying corrosion 
preventative sealant. Within 50 hours TIS and thereafter at intervals 
not to exceed 50 hours TIS, this AD requires inspecting the corrosion 
preventative sealant of each T/R link by using 10X or higher 
magnification. If the corrosion preventative sealant is missing, this 
AD requires performing the inspections for any aluminum oxide corrosion 
and pitting.

Differences Between This AD and the Transport Canada AD

    This AD only applies to helicopters with certain link P/Ns 
installed. The Transport Canada AD does not specify link P/Ns. This AD 
requires inspecting the bearing bores for any pitting after cleaning 
the T/R link, while the Transport Canada AD requires inspecting for 
corrosion after cleaning the T/R link. This AD requires inspecting the 
sealant with 10X or higher magnification, while the Transport Canada AD 
does not specify any magnification. This AD does not require re-
identifying the P/N of the link, whereas the Transport Canada AD does. 
As part of the recurring inspection of the corrosion preventative 
sealant, if the sealant is missing, this AD requires repeating the 
inspections for aluminum oxide corrosion and pitting to ensure part 
integrity before reapplying sealant. The Transport Canada AD only 
specifies reapplying sealant if the sealant is damaged.

Costs of Compliance

    We estimate that this AD affects 73 helicopters of U.S. Registry. 
We estimate that operators may incur the following costs in order to 
comply with this AD. We estimate the cost of labor at $85 per work-
hour.
    Inspecting the set of T/R links (eight bearings) for corrosion will 
take about one work-hour for an estimated cost of $85 per helicopter 
and $6,205 for the U.S. fleet. Cleaning and inspecting the set of T/R 
links for pitting will take about one work-hour for an estimated cost 
of $85 per helicopter. Replacing a T/R link will require no additional 
work-hours after inspection and required parts cost $2,739 for an 
estimated replacement cost of $2,739 per T/R link. Removing the torque 
stripe, cleaning, and applying sealant to the set of T/R links will 
take about one work-hour with a negligible parts cost for an estimated 
cost of $85 per helicopter. Inspecting the sealant on a set of T/R 
links will take about one work-hour for an estimated cost of $85 per 
helicopter and $6,205 for the U.S. fleet per inspection cycle.
    According to Bell Helicopter'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 Helicopter. Accordingly, we have included all costs in 
our cost estimate.

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 certain required 
corrective actions must be accomplished within 10 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 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);

[[Page 5369]]

    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):

2016-02-06 Bell Helicopter Textron Canada Limited: Amendment 39-
18387; Docket No. FAA-2016-2068; Directorate Identifier 2016-SW-002-
AD.

(a) Applicability

    This AD applies to Bell Helicopter Textron Canada Limited Model 
429 helicopters with a tail rotor (T/R) pitch link (link) part 
number (P/N) 429-012-112-101, -101FM, -103, or -103FM installed, 
certificated in any category.

(b) Unsafe Condition

    This AD defines the unsafe condition as failure of a T/R link. 
This condition could result in loss of T/R flight control and 
subsequent loss of control of the helicopter.

(c) Effective Date

    This AD becomes effective February 2, 2016.

(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) For T/R link P/N 429-012-112-101 and 429-012-112-103, within 
10 hours time-in-service (TIS):
    (i) Remove each T/R link assembly. Prior to cleaning the T/R 
link bearing bores, using 10X or higher power magnification, inspect 
each T/R link bearing bore for aluminum oxide corrosion extruding 
from between the roll staked lip of the bearing outer race and the 
link bearing bore. Aluminum oxide corrosion appears as a white 
crystalline material in contrast with the black finish and any 
accumulated soot. An example of this corrosion is shown in Figure 1 
of Bell Helicopter Alert Service Bulletin 429-15-26, dated December 
7, 2015 (ASB 429-15-26).
    (ii) If there is any aluminum oxide corrosion, replace the T/R 
link before further flight.
    (iii) If there is no aluminum oxide corrosion, clean each T/R 
link bearing bore with isopropyl alcohol and inspect for pitting.
    (A) If there is any pitting, replace the T/R link before further 
flight.
    (B) If there is no pitting, apply corrosion preventative sealant 
by following the Accomplishment Instructions, paragraph 5. of Part 
I, of ASB 429-15-26.
    (2) For all T/R links listed in paragraph (a) of this AD, within 
50 hours TIS and thereafter at intervals not to exceed 50 hours TIS, 
using 10X or higher power magnification, inspect each T/R link 
bearing bore for missing corrosion preventative sealant. If any 
corrosion preventative sealant is missing, perform the actions in 
paragraph (e)(1)(i) through (e)(1)(iii) of this AD before further 
flight.
    (3) Do not install T/R link P/N 429-012-112-101 or -103 on any 
helicopter before complying with the actions in paragraph (e)(1) of 
this AD.

(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, 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.

(g) Additional Information

    The subject of this AD is addressed in Transport Canada AD CF-
2016-01, dated January 5, 2016. You may view the Transport Canada AD 
on the Internet at http://www.regulations.gov by searching for and 
locating it in Docket No. FAA-2016-2068.

(h) Subject

    Joint Aircraft Service Component (JASC) Code: 6400, Tail Rotor 
System.

(i) Material Incorporated by Reference

    (1) The Director of the Federal Register approved the 
incorporation by reference of the service information listed in this 
paragraph under 5 U.S.C. 552(a) and 1 CFR part 51.
    (2) You must use this service information as applicable to do 
the actions required by this AD, unless the AD specifies otherwise.
    (i) Bell Helicopter Alert Service Bulletin 429-15-26, dated 
December 7, 2015.
    (ii) Reserved.
    (3) For Bell Helicopter 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/.
    (4) You may view this service information at FAA, Office of the 
Regional Counsel, Southwest Region, 10101 Hillwood Pkwy, Room 6N-
321, Fort Worth, TX 76177. For information on the availability of 
this material at the FAA, call (817) 222-5110.
    (5) You may view this service information that is incorporated 
by reference at the National Archives and Records Administration 
(NARA). For information on the availability of this material at 
NARA, call (202) 741-6030, or go to: http://www.archives.gov/federal-register/cfr/ibr-locations.html.

    Issued in Fort Worth, Texas, on January 22, 2016.
Scott A. Horn,
Acting Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. 2016-01747 Filed 2-1-16; 8:45 am]
 BILLING CODE 4910-13-P
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