Document ID: FAA-2008-0039-0005
Agency: faa
Document Type: Rule
Title: Airworthiness Directives; Bell Helicopter Textron Canada Model 222, 222B, 222U, 230 and 430 Helicopters
Posted Date: 2008-07-10T04:00Z

[Federal Register: July 10, 2008 (Volume 73, Number 133)]
[Rules and Regulations]               
[Page 39569-39570]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr10jy08-1]                         

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[[Page 39569]]

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2008-0039; Directorate Identifier 2006-SW-13-AD; 
Amendment 39-15596; AD 2008-14-01]
RIN 2120-AA64

 
Airworthiness Directives; Bell Helicopter Textron Canada Model 
222, 222B, 222U, 230 and 430 Helicopters

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule.

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

SUMMARY: This amendment adopts a new airworthiness directive (AD) for 
Bell Helicopter Textron Canada (BHTC) Model 222, 222B, 222U, 230 and 
430 helicopters that requires rewiring and testing the fuel valve 
switch on each engine and testing the ignitor system. This amendment is 
prompted by an in-flight incident in which a fuel valve switch failed, 
causing the fuel valve to inadvertently close. The actions specified by 
this AD are intended to prevent interruption of the fuel supply caused 
by failure of the fuel switch, which could result in loss of engine 
power and subsequent loss of control of the helicopter.

DATES: Effective August 14, 2008.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of August 14, 2008.

ADDRESSES: You may get the service information identified in this AD 
from Bell Helicopter Textron Canada, 12,800 Rue de l'Avenir, Mirabel, 
Quebec J7J1R4, telephone (450) 437-2862 or (800) 363-8023, fax (450) 
433-0272.
    Examining the Docket: You may examine the docket that contains this 
AD, any comments, and other information on the Internet at http://
www.regulations.gov, or at the Docket Operations office, West Building 
Ground Floor, Room W12-140, 1200 New Jersey Avenue, SE., Washington, 
DC.

FOR FURTHER INFORMATION CONTACT: George Schwab, Aviation Safety 
Engineer, FAA, Rotorcraft Directorate, Safety Management Group, Fort 
Worth, Texas 76193-0110, telephone (817) 222-5114, fax (817) 222-5961.

SUPPLEMENTARY INFORMATION: A proposal to amend 14 CFR part 39 to 
include an AD for the specified model helicopters was published in the 
Federal Register on January 23, 2008 (73 FR 3889). That action proposed 
to require, within 50 hours time-in-service (TIS), rewiring the 
switches that control the operation of the No. 1 and No. 2 engines' 
fuel valves, and testing the switches and the ignitor system.
    Transport Canada, the airworthiness authority for Canada, notified 
the FAA that an unsafe condition may exist on BHTC Model 222, 222B, 
222U, 230 and 430 helicopters. Transport Canada advises of an 
investigation into an incident involving a BHTC Model 222 helicopter, 
in which the fuel shut-off switch, part number (P/N) 10648BH1-1, failed 
during flight causing the fuel valve to close and the engine to shut 
down. Review of the Service Difficulty Report database identified two 
other incidents of switch failure.
    Bell Helicopter Textron has issued the following technical 
bulletins, all dated June 11, 2003, which specify rewiring the fuel 
valve switch:

------------------------------------------------------------------------
            Technical bulletin               Helicopter models affected
------------------------------------------------------------------------
No. 222-03-171............................  Model 222 and 222B
                                             helicopters.
No. 222U-03-96............................  Model 222U helicopters.
No. 230-03-35.............................  Model 230 helicopters.
No. 430-03-33.............................  Model 430 helicopters.
------------------------------------------------------------------------

    Transport Canada classified these technical bulletins as mandatory 
and issued AD No. CF-2006-03, dated February 28, 2006, to ensure the 
continued airworthiness of these helicopters in Canada. That AD 
requires compliance no later than May 3, 2006. This AD requires 
compliance within 50 hours TIS.
    These helicopter models are manufactured in Canada and are type 
certificated for operation in the United States under the provisions of 
14 CFR 21.29 and the applicable bilateral agreement. Pursuant to the 
applicable bilateral agreement, Transport Canada has kept the FAA 
informed of the situation described above. The FAA has examined the 
findings of Transport Canada, reviewed all available information, and 
determined that AD action is necessary for products of this type design 
that are certificated for operation in the United States.
    Interested persons have been afforded an opportunity to participate 
in the making of this amendment. No comments were received on the 
proposal or the FAA's determination of the cost to the public. The FAA 
has determined that air safety and the public interest require the 
adoption of the rule as proposed.
    The FAA estimates that this AD will affect 165 helicopters of U.S. 
registry, and the required actions will take approximately four work 
hours per helicopter to rewire the 2 fuel valve switches, and test 
those switches and the ignitor system, at an average labor rate of $80 
per work hour. Based on these figures, we estimate the total cost 
impact of the AD on U.S. operators to be $52,800 ($320 per helicopter).

Regulatory Findings

    We have 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 above, I certify that the regulation:
    1. Is not a ``significant regulatory action'' under Executive Order 
12866;
    2. Is not a ``significant rule'' under the DOT Regulatory Policies 
and Procedures (44 FR 11034, February 26, 1979); and
    3. 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. See the AD docket to examine the economic evaluation.

[[Page 39570]]

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.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Incorporation by 
reference, Safety.

Adoption of the Amendment

0
Accordingly, pursuant to the authority delegated to me by the 
Administrator, the Federal Aviation Administration amends part 39 of 
the Federal Aviation Regulations (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. Section 39.13 is amended by adding a new airworthiness directive to 
read as follows:

2008-14-01 Bell Helicopter Textron Canada: Amendment 39-15596. 
Docket No. FAA-2008-0039; Directorate Identifier 2006-SW-13-AD.

    Applicability: The following model helicopters, certificated in 
any category:

------------------------------------------------------------------------
                 Model No.                           Serial Nos.
------------------------------------------------------------------------
222.......................................  47006 through 47089.
222B......................................  47131 through 47156.
222U......................................  47501 through 47574.
230.......................................  23001 through 23038.
430.......................................  49001 through 49101.
------------------------------------------------------------------------

    Compliance: Required within 50 hours time-in-service, unless 
accomplished previously.
    To prevent interruption of the fuel supply caused by failure of 
the fuel switch, which could result in loss of engine power and 
subsequent loss of control of the helicopter, accomplish the 
following:
    (a) Rewire the No. 1 and No. 2 engines' fuel valve switch, part 
number 10648BH1-1, and test the fuel valve switches and the ignitor 
system, in accordance with the Accomplishment Instructions in Bell 
Helicopter Textron Technical Bulletin (TB) No. 222-03-171, Part 1, 
applicable to Model 222 helicopters, serial number (S/N) 47006-
47038, and Part 2, applicable to Model 222 helicopters, S/N 47039-
47089, and Model 222B helicopters, S/N 47131-47156; TB No. 222U-03-
96, applicable to Model 222U helicopters; TB No. 230-03-35, 
applicable to Model 230 helicopters; and TB No. 430-03-33, 
applicable to Model 430 helicopters. All of the technical bulletins 
are dated June 11, 2003.
    (b) To request a different method of compliance or a different 
compliance time for this AD, follow the procedures in 14 CFR 39.19. 
Contact the Manager, Safety Management Group, ATTN: George Schwab, 
Aviation Safety Engineer, Rotorcraft Directorate, FAA, Fort Worth, 
Texas 76193-0110, telephone (817) 222-5114, fax (817) 222-5961, for 
information about previously approved alternative methods of 
compliance.
    (c) The rewiring and testing shall be done in accordance with 
the specified portions of Bell Helicopter Textron Technical Bulletin 
No. 222-03-171, No. 222U-03-96, No. 230-03-35, and No. 430-03-33, 
all dated June 11, 2003. The Director of the Federal Register 
approved this incorporation by reference in accordance with 5 U.S.C. 
552(a) and 1 CFR part 51. Copies may be obtained from Bell 
Helicopter Textron Canada, 12,800 Rue de l'Avenir, Mirabel, Quebec 
J7J1R4, telephone (450) 437-2862 or (800) 363-8023, fax (450) 433-
0272. Copies may be inspected at the FAA, Office of the Regional 
Counsel, Southwest Region, 2601 Meacham Blvd., Room 663, Fort Worth, 
Texas or 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/
code_of_federal_regulations/ibr_locations.html.
    (d) This amendment becomes effective on August 14, 2008.

    Note: The subject of this AD is addressed in Transport Canada 
(Canada) AD CF-2006-03, dated February 28, 2006.

    Issued in Fort Worth, Texas, on June 12, 2008.
Lance T. Gant,
Acting Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. E8-14718 Filed 7-9-08; 8:45 am]

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