
[Federal Register Volume 78, Number 211 (Thursday, October 31, 2013)]
[Rules and Regulations]
[Pages 65200-65202]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2013-24030]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2013-0490; Directorate Identifier 2008-SW-004-AD; 
Amendment 39-17611; AD 2013-20-05]
RIN 2120-AA64


Airworthiness Directives; Bell Helicopter Textron Canada Limited 
(Bell) 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 Model 407 helicopters. This AD requires installing a placard 
beneath the NR/NP dual tachometer and revising the limitations section 
of the rotorcraft flight manual (RFM). This AD was prompted by several 
incidents of third stage engine turbine wheel failures, which were 
caused by excessive vibrations at certain engine speeds during steady-
state operations. These actions are intended to alert pilots to avoid 
certain engine speeds during steady-state operations, prevent failure 
of the third stage engine turbine, engine power loss, and subsequent 
loss of control of the helicopter.

DATES: This AD is effective December 5, 2013.
    The Director of the Federal Register approved the incorporation by 
reference

[[Page 65201]]

of a certain document listed in this AD as of December 5, 2013.

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

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 AD, the foreign authority's AD, 
any incorporated-by-reference service information, 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: Chinh Vuong, Aviation Safety Engineer, 
Safety Management Group, Rotorcraft Directorate, FAA, 2601 Meacham 
Blvd., Fort Worth, Texas 76137; telephone (817) 222-5110; email 
chinh.vuong@faa.gov.

SUPPLEMENTARY INFORMATION:

Discussion

    On June 7, 2013, at 78 FR 34286, 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 Bell Model 407 helicopters, 
serial numbers 53000 through 53644. The NPRM proposed to require 
installing a placard on the instrument panel below the NR/NP dual 
tachometer and revising the Operating Limitations section of the Model 
407 RFM to limit steady-state operation between speeds of 68.4% to 
87.1%. The proposed requirements were intended to alert pilots to avoid 
certain engine speeds during steady-state operations, prevent failure 
of the third stage engine turbine, engine power loss, and subsequent 
loss of control of the helicopter.
    The NPRM was prompted by AD No. CF-2004-09R1, dated July 4, 2005, 
issued by Transport Canada Civil Aviation (TCCA), which is the aviation 
authority for Canada. TCCA issued AD No. CF-2004-09R1 to correct an 
unsafe condition for Model 407 helicopters. TCCA advises that several 
failures of third stage turbine wheels used in Rolls Royce 250-C30S and 
250-C47B engines, and three of these failures have occurred to the 250-
C47B engine used by Bell on the Model 407. According to TCCA, Rolls 
Royce has determined that detrimental vibrations can occur within a 
particular range of turbine speeds, and may be a contributing factor to 
these failures. Bell has revised the operating limitations of the RFM 
and provided a corresponding decal on the instrument panel to inform 
pilots to avoid steady-state operations between 68.4% and 87.1% turbine 
speeds.
    The TCCA AD requires amending the RFM, advising pilots of the 
change, and installing a decal as described in Bell Alert Service 
Bulletin (ASB) No. 407-05-67, dated June 8, 2005 (ASB 407-05-67).

Comments

    After our NPRM (78 FR 34286, June 7, 2013) was published, we 
received comments from one commenter.

Request

    Rolls-Royce Corporation requested that in addition to requiring the 
placard on the instrument panel, we allow operators the option to 
temporarily mark the Nr/Np gauge with colored 
tape, to provide a more visual aide to the pilot for the speed 
avoidance zone.
    We disagree. Marking the glass surface of the gauge can create 
parallax issues when viewing the avoidance ranges on the gauge, 
resulting in erroneous readings.

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 
the TCCA AD. We are issuing this AD because we evaluated all 
information provided by TCCA, reviewed the relevant information, 
considered the comment received, 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 TCCA AD

    The TCCA AD requires compliance within 10 calendar days, while this 
AD requires compliance within 30 days.

Related Service Information

    Bell has issued ASB 407-05-67, which contains procedures for 
installing a placard on the instrument panel below the main rotor RPM 
(Nr)/power turbine RPM (Np) dual tachometer and for inserting the RFM 
changes into the flight manual.

Costs of Compliance

    We estimate that this AD will affect 472 helicopters of U.S. 
Registry. Based on an average labor rate of $85 per hour, we estimate 
that operators may incur the following costs in order to comply with 
this AD. Amending the RFM will require about 0.5 work-hour, for a cost 
per helicopter of about $43 and a cost to U.S. operators of $20,296. 
Installing the decal will require about 0.2 work-hour and required 
parts cost $20, for a cost per helicopter of $37 and a cost to U.S. 
operators of $17,464. Based on these estimates, the total cost of this 
AD will be $80 per helicopter and $37,760 for the U.S. operator fleet.

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);

[[Page 65202]]

    (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):

2013-20-05 Bell Helicopter Textron Canada Limited (Bell): Amendment 
39-17611; Docket No. FAA-2013-0490; Directorate Identifier 2008-SW-
004-AD.

(a) Applicability

    This AD applies to Bell Model 407 helicopters, serial numbers 
53000 through 53644, certificated in any category.

(b) Unsafe Condition

    This AD defines the unsafe condition as a third stage turbine 
vibration, which could result in turbine failure, engine power loss, 
and subsequent loss of control of the helicopter.

(c) Effective Date

    This AD becomes effective December 5, 2013.

(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 30 days:
    (1) Revise the Operating Limitations section of the Model 407 
Rotorcraft Flight Manual by inserting Section 1, Limitations, pages 
1-6 and 1-14, of Bell BHT-407-FM-1, revision 3, dated April 26, 
2005.
    (2) Remove placard part number (P/N) 230-075-213-105, if 
installed.
    (3) Install placard P/N 230-075-213-111, or equivalent, directly 
below the NR/NP dual tachometer.

(f) Alternative Methods of Compliance (AMOCs)

    (1) The Manager, Safety Management Group, FAA, may approve AMOCs 
for this AD. Send your proposal to: Chinh Vuong, Aviation Safety 
Engineer, Safety Management Group, Rotorcraft Directorate, FAA, 2601 
Meacham Blvd., Fort Worth, Texas 76137; telephone (817) 222-5110; 
email chinh.vuong@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 Alert Service Bulletin No. 407-05-67, dated June 8, 
2005, 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 a copy of the 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 Transport Canada 
Civil Aviation (TCCA) AD No. CF-2004-09R1, dated July 4, 2005. You 
may view the TCCA AD on the internet in the AD Docket at http://www.regulations.gov.

(h) Subject

    Joint Aircraft Service Component (JASC) Code: 7250: Turbine 
Section.

(i) Material Incorporated by Reference

    (1) The Director of the Federal Register approved the 
incorporation by reference (IBR) 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) Pages 1-6 and 1-14 of Section 1, Limitations, of Bell 
Rotorcraft Flight Manual BHT-407-FM-1, Revision 3, dated April 26, 
2005.
    (ii) Reserved.
    (3) For Bell 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/.
    (4) You may view this service information at FAA, Office of the 
Regional Counsel, Southwest Region, 2601 Meacham Blvd., Room 663, 
Fort Worth, Texas 76137. 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 September 20, 2013.
Scott A. Horn,
Acting Directorate Manager, Rotorcraft Directorate, Aircraft 
Certification Service.
[FR Doc. 2013-24030 Filed 10-30-13; 8:45 am]
BILLING CODE 4910-13-P


