[Federal Register Volume 70, Number 199 (Monday, October 17, 2005)]
[Rules and Regulations]
[Pages 60203-60205]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 05-20677]



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Rules and Regulations
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Federal Register / Vol. 70, No. 199 / Monday, October 17, 2005 / 
Rules and Regulations

[[Page 60203]]



DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2005-21680; Directorate Identifier 2004-SW-48-AD; 
Amendment 39-14341; AD 2005-21-03]
RIN 2120-AA64


Airworthiness Directives; Bell Helicopter Textron Canada Model 
206A, A-1, B, B-1, L, L-1, L-3, L-4 Helicopters

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule.

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SUMMARY: This amendment adopts a new airworthiness directive (AD) for 
the specified Bell Helicopter Textron Canada (BHTC) model helicopters 
that requires, before the first flight of each day, checking the tail 
rotor blade (blade) root doublers (doublers) for an edge void or de-
bond on both sides of each blade, and if an edge void or de-bond is 
found, replacing the unairworthy blade with an airworthy blade. This AD 
also requires replacing any affected serial-numbered blade with an 
airworthy blade. This amendment is prompted by reports of de-bond of 
the doublers due to inadequate surface preparation resulting in poor 
adherence of the doublers. The actions specified by this AD are 
intended to prevent loss of a blade, loss of tail rotor control, and 
subsequent loss of control of the helicopter.

DATES: Effective November 21, 2005.

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://dms.dot.gov, or at the 
Docket Management System (DMS), U.S. Department of Transportation, 400 
Seventh Street, SW., Room PL-401, on the plaza level of the Nassif 
Building, Washington, DC.

FOR FURTHER INFORMATION CONTACT: Sharon Miles, Aviation Safety 
Engineer, FAA, Rotorcraft Directorate, Regulations and Guidance Group, 
Fort Worth, Texas 76193-0111, telephone (817) 222-5122, fax (817) 222-
5961.

SUPPLEMENTARY INFORMATION: A proposal to amend 14 CFR part 39 to 
include an AD for the specified BHTC model helicopters was published in 
the Federal Register on June 28, 2005 (70 FR 37060). That action 
proposed to require, before the first flight of each day, checking the 
blade doublers for an edge void or de-bond on both sides of each blade, 
and if an edge void or de-bond is found, replacing the unairworthy 
blade with an airworthy blade. Also, that action proposed to require 
replacing any affected serial-numbered blade with an airworthy blade.
    Transport Canada, the airworthiness authority for Canada, notified 
the FAA that an unsafe condition may exist on Model 206A, B, and L 
series helicopters. Transport Canada advises that an inadequate surface 
preparation on a limited number of blades resulted in two reported 
instances of blade root doubler de-bond. They also advise that to 
ensure blade integrity all suspected blades are to be checked daily 
until removed from service.
    BHTC has issued Alert Service Bulletin Nos. 206-04-101 and 206L-04-
131, both dated September 13, 2004, which specify a daily check of the 
doubler area to verify integrity of the doubler by a pilot as part of 
the daily pre-flight check. The service bulletins also specify a 
retirement from service of affected blades, which constitutes 
terminating action. Transport Canada classified these service bulletins 
as mandatory and issued AD No. CF-2004-25, dated November 23, 2004, to 
ensure the continued airworthiness of these helicopters in Canada.
    These helicopter models are now 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 these type 
designs 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 2,194 helicopters of 
U.S. registry. The required actions will:
    <bullet> Take about \1/4\ work hour to do a daily check for blade 
edge voids and de-bonds; and
    <bullet> Take about 4 work hours to replace a blade at an average 
labor rate of $65 per work hour.
    <bullet> Cost about $5,848 for a replacement blade.
    Based on these figures, we estimate the total cost impact of the AD 
on U.S. operators to be $201,058, assuming 26 blades are affected and 
replaced and assuming 100 daily checks are done.

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

[[Page 60204]]

this AD. See the DMS to examine the economic evaluation.

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, 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:

2005-21-03 Bell Helicopter Textron Canada: Amendment 39-14341. 
Docket No. FAA-2005-21680; Directorate Identifier 2004-SW-48-AD.

    Applicability: Model 206A, A-1, B, B-1, L, L-1, L-3, L-4 
helicopters, with tail rotor blade (blade), part number (P/N) 206-
016-201-131, serial numbers with a prefix of ``CS'' and 4820 through 
4845, installed, certificated in any category.
    Compliance: Required as indicated, unless accomplished 
previously.
    To prevent loss of a blade, loss of tail rotor control, and 
subsequent loss of control of the helicopter, accomplish the 
following:
    (a) Before the first flight of each day, clean each blade and 
visually check the blade root doublers for an edge void or de-bond 
on both sides of each blade as depicted in Figure 1 of this AD. An 
owner/operator (pilot), holding at least a private pilot 
certificate, may perform this visual check and must enter compliance 
with this paragraph into the helicopter maintenance records by 
following 14 CFR sections 43.11 and 91.417(a)(2)(v).

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    (b) If an edge void or a de-bond is found, before further 
flight, replace the blade with an airworthy blade with a serial 
number other than those to which this AD applies.
    (c) Within 100 hours time-in-service, replace all affected, 
serial-numbered blades with airworthy blades with a serial number 
other than those to which this AD applies.

    Note 1: Bell Helicopter Textron Alert Service Bulletin Nos. 206-
04-101 and 206L-04-131, both dated September 13, 2004, pertain to 
the subject of this AD.

    (d) Replacing an affected, serial-numbered blade with an 
airworthy blade without an affected serial number contained in the 
applicability section of this AD constitutes terminating action for 
the requirements of this AD for that blade.
    (e) 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 Safety Management Group, Rotorcraft Directorate, FAA, 
for information about previously approved alternative methods of 
compliance.
    (f) Special flight permits may be issued in accordance with 14 
CFR 21.197 and 21.199 to operate the helicopter to a location where 
the blade may be replaced provided that no doubler edge void or de-
bond is found during any check or inspection.
    (g) This amendment becomes effective on November 21, 2005.

    Note 2: The subject of this AD is addressed in Transport Canada, 
Canada AD No. CF-2004-25, dated November 23, 2004.



[[Page 60205]]


    Issued in Fort Worth, Texas, on October 7, 2005.
David A. Downey,
Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. 05-20677 Filed 10-14-05; 8:45 am]
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