Airworthiness Directives; Bell Helicopter Textron Canada (Bell) Helicopters

[Federal Register Volume 78, Number 75 (Thursday, April 18, 2013)]
[Rules and Regulations]
[Pages 23114-23115]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2013-08762]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2012-1127; Directorate Identifier 2010-SW-035-AD; 
Amendment 39-17423; AD 2013-08-06]
RIN 2120-AA64


Airworthiness Directives; Bell Helicopter Textron Canada (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 Bell 
Model 430 helicopters, which requires replacing certain components of 
the air data system. This AD was prompted by the discovery of incorrect 
indicated airspeed when the helicopter was tested to the cold 
temperature limits (-40 degrees centigrade) required for Category A 
operations. The actions of this AD are intended to correct the 
published Vne and to correct the indicated airspeed.

DATES: This AD is effective May 23, 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 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, 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: Mark F. Wiley, Aviation Safety 
Engineer, FAA, Rotorcraft Directorate, Regulations and Policy Group, 
2601 Meacham Blvd., Fort Worth, Texas 76137, telephone (817) 222-5110, 
fax (817) 222-5110, email [email protected].

SUPPLEMENTARY INFORMATION: 

Discussion

    On October 22, 2012, at 77 FR 64439, the Federal Register published 
our notice of proposed rulemaking (NPRM), which proposed to amend 14 
CFR part 39 to include an AD that would apply to Bell Model 430 
helicopters. That NPRM proposed to require replacing certain components 
of the air data system. The proposed requirements were intended to 
correct the published Vne and to correct the indicated airspeed.
    The Transport Canada Civil Aviation (TCCA), which is the aviation 
authority for Canada, has issued Canadian AD No. CF-2005-30, dated 
August 3, 2005, to correct an unsafe condition for the Bell Model 430 
helicopters. Discrepancies in the processing and display of air data 
were revealed when testing at low temperatures to minus 40 degrees 
Centigrade (-40[deg]C). The TCCA advises that modification to the 
instrumentation is required to reflect the Vne airspeed values tested 
at temperatures to -40[deg]C. The TCCA states ``This modification 
affects the software in the Vne Overspeed Warning computer (required 
for Category A operations) and in the AFCS [Automatic Flight Control 
System] Air Data Computer.'' TCAA issued AD CF-2005-30 to require the 
procedures in Bell Alert Service Bulletin (ASB) No. 430-05-35, dated 
June 21, 2005, for replacing the affected instruments. Bell also issued 
ASB No. 430-01-22, dated April 30, 2001 (ASB 430-01-22), which provided 
a temporary Rotorcraft Flight Manual Supplement and placards with 
information on airspeed corrections. TCCA did not issue an AD to 
mandate the provisions of ASB 430-01-22.

Comments

    We gave the public the opportunity to participate in developing 
this AD, but we did not receive any comments on the NPRM (77 FR 64439, 
October 22, 2012).

FAA's Determination

    These helicopters have been approved by the TCCA and are approved 
for operation in the United States. Pursuant to our bilateral agreement 
with Canada, TCCA has notified us of the unsafe condition described in 
the Canadian AD.
    We are issuing this AD because we evaluated all information 
provided by TCCA and determined the unsafe condition exists and is 
likely to exist or develop on other helicopters of the same type 
designs and that air safety and the public interest require adopting 
the AD requirements as proposed.

Differences Between This AD and the TCCA AD

    We do not use the compliance date of July 31, 2007.

Costs of Compliance

    We estimate that this AD will affect 52 helicopters of U.S. 
registry. We estimate that operators may incur the following costs in 
order to comply with this AD:
    <bullet> $680 to replace the overspeed warning computer, pilot and 
copilot airspeed indicators, Vne converter, and AFCS air data computer 
adapter module for each helicopter, assuming 8 work hours for each 
helicopter at an average labor rate of $85 per work hour, and
    <bullet> $46,074 per helicopter for the required parts.

[[Page 23115]]

    Based on these figures, we estimate the total cost impact of the AD 
on U.S. operators to be $2,431,208 for the 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);
    (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):

2013-08-06 Bell Helicopter Textron Canada: Amendment 39-17423; 
Docket No. FAA-2012-1127; Directorate Identifier 2010-SW-035-AD.

(a) Applicability

    This AD applies to Model 430 helicopters: serial number (S/N) 
49001 through 49103, with Overspeed Warning Kit, part number (P/N) 
430-706-004-101 or P/N 430-706-004-103, installed; S/N 49001 through 
49100, with Single Automatic Flight Control System (AFCS) with 
Flight Director Kit, P/N 430-705-009-103, -105, -109, -111, -115, -
117, or P/N 430-705-011-109, -111, -121, or -123, installed; and S/N 
49001 through 49100, with Dual AFCS with Flight Director Kit, P/N 
430-705-011-103, -105, -115, -117, -125, -127, -129, -133, -135, or 
-137, installed, certificated in any category.

(b) Unsafe Condition

    This AD defines the unsafe condition as inability of the 
helicopters, based on testing, to operate at the published 
V<INF>ne</INF> indicated airspeeds within the cold temperature 
limits (-40 degrees centigrade) required for Category A operations.

(c) Effective Date

    This AD becomes effective May 23, 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 1 year:
    (1) For helicopters with an Overspeed Warning System, replace 
the Overspeed Warning Computer, P/N 430-375-013-103, with the 
Overspeed Warning Computer, P/N 430-375-013-105; the V<INF>ne</INF> 
Converter, P/N ADI-21280-000, with the V<INF>ne</INF> Converter, P/N 
ADI-21280-100; and the pilot and copilot Airspeed Indicator, P/N 
222-375-027-117, with the pilot and copilot airspeed Indicator, P/N 
222-375-027-119;
    (i) If installed, remove the decal, P/N 430-075-070-103, from 
below the pilot and copilot airspeed indicators;
    (ii) Leak test the pilot pitot static system; and
    (iii) Operationally test the overspeed warning system.
    (2) For helicopters with a Single or Dual AFCS with a Flight 
Director, replace the AFCS Air Data Computer Adapter Module, P/N 
065-05041-0021, with P/N 065-05041-0031;
    (i) If installed, remove the decal, P/N 430-075-070-101, from 
above the pilot and copilot electronic attitude direction indicators 
airspeed indicators;
    (ii) Leak test the pilot pitot static system;
    (iii) Power-up test the altimeter/vertical speed indicator (ALT/
VSI) and self-test the ALT/VSI of the AFCS air data computer.

(f) Alternative Methods of Compliance (AMOC)

    (1) The Manager, Rotorcraft Standards Staff, FAA may approve 
AMOCs for this AD. Send your proposal to: Mark F. Wiley, Aviation 
Safety Engineer, Rotorcraft Directorate, Regulations and Policy 
Group, 2601 Meacham Blvd., Fort Worth, Texas 76137, telephone (817) 
222-5110, fax (817) 222-5961, email [email protected].
    (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 Textron Alert Service Bulletin (ASB) No. 
430-05-35, dated June 21, 2005, and ASB No. 430-01-22, dated April 
30, 2001, which are not incorporated by reference, contain 
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 
http://www.bellcustomer.com/files/. You may review 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 AD No. CF 2005-30, dated August 3, 2005.

 (h) Subject

    Joint Aircraft System/Component Code: 3417 Air Data Computer.

    Issued in Fort Worth, Texas, on April 8, 2013.
Kim Smith,
Directorate Manager, Rotorcraft Directorate, Aircraft Certification 
Service.
[FR Doc. 2013-08762 Filed 4-17-13; 8:45 am]
BILLING CODE 4910-13-P

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