Document ID: FAA-2016-6551-0003
Agency: faa
Document Type: Rule
Title: Airworthiness Directives: Bell Helicopter Textron Helicopters
Posted Date: 2016-10-14T04:00Z

[Federal Register Volume 81, Number 199 (Friday, October 14, 2016)]
[Rules and Regulations]
[Pages 70928-70929]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2016-24741]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2016-6551; Directorate Identifier 2013-SW-070-AD; 
Amendment 39-18682; AD 2016-21-01]
RIN 2120-AA64

Airworthiness Directives; Bell Helicopter Textron Helicopters

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule.

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SUMMARY: We are adopting a new airworthiness directive (AD) for certain 
Bell Helicopter Textron (Bell) Model 430 helicopters. This AD requires 
establishing a life limit for a certain main rotor hub attachment bolt 
(bolt) and removing from service each bolt that has met or exceeded its 
life limit. This AD was prompted by a documentation error that omitted 
the life limit of a certain part-numbered bolt from the Airworthiness 
Limitations section of the maintenance manual. The actions of this AD 
are intended to establish a life limit for a certain part-numbered bolt 
to prevent failure of a bolt, failure of a main rotor hub, and 
subsequent loss of control of a helicopter.

DATES: This AD is effective November 18, 2016.

ADDRESSES: 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.

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-
6551; 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 economic evaluation, any 
comments received, and other information. The street address for the 
Docket Operations Office (phone: 800-647-5527) is U.S. Department of 
Transportation, Docket Operations Office, M-30, West Building Ground 
Floor, Room W12-140, 1200 New Jersey Avenue SE., Washington, DC 20590.

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: 

Discussion

    On May 10, 2016, at 81 FR 28766, the Federal Register published our 
notice of proposed rulemaking (NPRM), which proposed to amend 14 CFR 
part 39 by adding an AD that would apply to certain serial-numbered 
Bell Model 430 helicopters with bolt part number (P/N) MS21250-08083 
installed. The NPRM proposed to require, within 10 hours time-in-
service (TIS), revising the Airworthiness Limitations section of the 
applicable maintenance manual or Instructions for Continued 
Airworthiness (ICA) by establishing a life limit of 5,000 hours TIS for 
each bolt P/N MS21250-08083, determining the number of hours TIS for 
each bolt and using the helicopter's hours if the hours TIS of a bolt 
is unknown, and removing from service each bolt that has reached or 
exceeded its life limit. The proposed requirements were intended to 
establish a life limit for the bolt to prevent failure of a bolt, 
failure of a main rotor hub, and subsequent loss of control of a 
helicopter.
    Transport Canada, which is the aviation authority for Canada, has 
issued Canadian AD No. CF-2013-26, dated September 24, 2013, to correct 
an unsafe condition for certain serial-numbered Bell Model 430 
helicopters. Transport Canada advises that bolt P/N MS21250-08083, 
which replaced bolt P/N 20-065-08083 in 2009, has a retirement life of 
5,000 hours. However, the retirement life for the replacement bolt was 
inadvertently omitted from the limitations section of the Bell 430 
maintenance manual. Transport Canada advises that this situation, if 
not corrected, could result in failure of a bolt and loss of control of 
the helicopter. Transport Canada AD No. CF-2013-26 requires reviewing 
the helicopter records to determine if bolt P/N MS21250-08083 is 
installed, creating a historical service record, and establishing an 
airworthiness life of 5,000 hours air time.

Comments

    We gave the public the opportunity to participate in developing 
this AD, but we did not receive any comments on the NPRM (81 FR 28766, 
May 10, 2016).

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 
its 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 the same type 
design and that air safety and the public interest require adopting the 
AD requirements as proposed.

Differences Between This AD and the Transport Canada AD

    This AD requires compliance within 10 hours TIS, while the 
Transport Canada AD requires compliance within 60 days.

Related Service Information

    We reviewed Bell Helicopter Alert Service Bulletin 430-12-47, dated 
November 14, 2012 (ASB). The ASB states that original bolt P/N 20-065-
08083 has a retirement life of 5,000 hours but has been replaced by 
standard bolt P/N MS21250-08083, which does not have a life limit 
listed in the maintenance manual. The purpose of the ASB is to 
establish a life limit of 5,000 hours for the replacement bolt. Bell 
specifies reviewing the aircraft records back to January 2009 to 
determine which part-numbered bolts are installed. If a replacement 
bolt P/N MS21250-08083 is installed, the ASB specifies using data from 
aircraft records to create a historical service record for the 
replacement bolts and reflecting the 5,000 hours life limit. The ASB 
also specifies updating the Bell 430 maintenance manual.

[[Page 70929]]

Costs of Compliance

    We estimate that this AD affects 43 helicopters of U.S. Registry.
    We estimate that operators may incur the following costs to comply 
with this AD. At an average labor cost of $85 per work-hour, we 
estimate reviewing and revising the records requires 1 work-hour for a 
cost of about $85 per helicopter and $3,655 for the U.S. fleet. We 
estimate replacing a bolt that has exceeded its life limit requires 0.5 
work-hour plus $290 for a replacement bolt, for a total cost of $333 
per bolt.

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 helicopters identified in this 
rulemaking action.

Regulatory Findings

    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 above, 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):

2016-21-01 Bell Helicopter Textron: Amendment 39-18682; Docket No. 
FAA-2016-6551; Directorate Identifier 2013-SW-070-AD.

(a) Applicability

    This AD applies to Model 430 helicopters, serial number 49001 
through 49129, with a main rotor head attachment bolt (bolt) part 
number (P/N) MS21250-08083 installed, certificated in any category.

(b) Unsafe Condition

    This AD defines the unsafe condition as a bolt remaining in 
service beyond its fatigue life. This condition could result in 
failure of a bolt, failure of the main rotor hub and subsequent loss 
of control of a helicopter.

(c) Effective Date

    This AD becomes effective November 18, 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

    Within 10 hours time-in-service (TIS):
    (1) Revise the Airworthiness Limitations section of the 
applicable maintenance manual or Instructions for Continued 
Airworthiness (ICA) to establish a life limit of 5,000 hours TIS for 
each bolt P/N MS21250-08083.
    (2) Determine the number of hours TIS for each bolt and update 
the helicopter's historical records. If the hours TIS is unknown, 
calculate the number of hours TIS by counting the helicopter's hours 
TIS beginning January 1, 2009.
    (3) Remove from service each bolt that has reached or exceeded 
its life limit.

 (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

    (1) Bell Helicopter Alert Service Bulletin 430-12-47, dated 
November 14, 2012, which is not incorporated by reference, contains 
additional information about the subject of this final rule. 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 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-2013-26, dated September 24, 2013. You may view the Transport 
Canada AD on the Internet at http://www.regulations.gov in Docket 
No. FAA-2016-6551.

(h) Subject

    Joint Aircraft Service Component (JASC) Code: 6220 Main Rotor 
Head.

    Issued in Fort Worth, Texas, on October 3, 2016.
Lance T. Gant,
Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. 2016-24741 Filed 10-13-16; 8:45 am]
BILLING CODE 4910-13-P