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Jan. 3, 2008 - Airworthiness Directives; Bell Helicopter Textron Canada Model 430 Helicopters


Airworthiness Directives; Bell Helicopter Textron Canada Model 430 Helicopters
Thursday, January 03, 2008 / FAA

DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39

[Docket No. FAA-2007-28688; Directorate Identifier 2005-SW-21-AD; Amendment 39-15312; AD 2007-26-10]

RIN 2120-AA64

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Airworthiness Directives; Bell Helicopter Textron Canada Model 430 Helicopters

Preamble Information
AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule.

SUMMARY:
This amendment adopts a new airworthiness directive (AD) for Bell
Helicopter Textron Canada (BHTC) Model 430 helicopters that requires
replacing a certain servo actuator-to-actuator support attachment bolt
(bolt) with an airworthy bolt. This action also requires establishing a
retirement life for certain bolts and recording the retirement life on
a component history card or equivalent record. This amendment is
prompted by further evaluation of certain fatigue- critical parts,
resulting in establishing a life limit of 5,000 hours for the affected
bolts. The actions specified by this AD are intended to prevent fatigue
failure of the bolt and subsequent loss of control of the helicopter.

DATES: Effective February 6, 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: 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 model helicopters was
published in the Federal Register on July 16, 2007 (72 FR 38797). That
action proposed to require replacing a certain bolt with an airworthy
bolt. That action also proposed establishing a retirement life for
certain bolts and recording the retirement life on a component history
card or equivalent record.

Transport Canada, the airworthiness
authority for Canada, notified the FAA that an unsafe condition may
exist on BHTC Model 430 helicopters, serial numbers 49001 through
49106. Transport Canada advises of the need to establish a new
airworthiness life limitation of 5,000 hours for the three servo
actuator support attachment bolts and to replace the three affected
bolts.

Bell Helicopter Textron has issued Alert Service
Bulletin No. 430- 05-33, dated February 16, 2005 (ASB). The ASB
introduces a retirement life of 5,000 hours for the bolts. The ASB
states that since these bolts have not been listed in the Helicopter
Component Replace record, it is difficult to determine with accuracy
the actual number of hours accumulated on fielded bolts. Also, the ASB
states that Bell has elected to replace all the fielded bolts, part
number (P/N) 50-047C8-31. Transport Canada classified this ASB as
mandatory and issued AD No. CF-2005-09, dated April 14, 2005, to ensure
the continued airworthiness of these helicopters in Canada.

This
helicopter model is manufactured in Canada and is 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 us informed of the
situation described above. We have 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 with two changes. We corrected a paragraph under the
ADDRESSES section in the preamble to reflect the correct address for
getting the service information. Also, we added a Note to the AD
stating that there is service information that pertains to the subject
of the AD. We have determined that these changes will neither increase
the economic burden on any operator nor increase the scope of the AD.

We
estimate that this AD will affect 54 helicopters of U.S. registry, and
the required actions will take about 2 work hours per helicopter to
replace 3 bolts at an average labor rate of $80 per work hour. Required
parts will cost about $243 for each bolt. Based on these figures, we
estimate the total cost impact of the AD on U.S. operators to be $
$48,006, assuming that the recordkeeping cost would be negligible.

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.

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

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

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]

2. Section 39.13 is amended by adding a new airworthiness directive to read as follows:

Regulatory Information
2007-26-10 Bell Helicopter Textron Canada: Amendment 39-15312. Docket No. FAA-2007-28688; Directorate Identifier 2005-SW-21-AD.

Applicability: Model
430 helicopters, serial numbers 49001 through 49106, with a servo
actuator-to-actuator support attachment bolt (bolt), part number (P/N)
50-047C8-31, installed, which attaches the lower two cyclic servo
actuators and the lower collective servo actuator to the three lower
actuator supports, certificated in any category.

Compliance: Required as indicated, unless accomplished previously.

To prevent fatigue failure of the bolt and subsequent loss of control of the helicopter, do the following:

(a)
Within 150 hours time-in-service (TIS), replace all three affected
bolts, as depicted for one of these bolts in Figure 1 of this AD, with
airworthy, zero-time bolts, P/N 50-047C8-31.

[Image removed externally, orgiginal URL: http://www.verticalmag.com/control/news/articlefiles/6351-1.jpg]

Figure 1

Note 1:
Only the
right servo lower attach bolt (1) is shown. The collective and left
cyclic servo lower attach bolts are also to be replaced. (This AD does
not apply to the same part-numbered bolts at the upper end of each
servo.)

Note 2: Bell Helicopter Textron Alert Service Bulletin No. 430- 05-33, dated February 16, 2005, pertains to the subject of this AD.

(b)
This AD revises the Airworthiness Limitations section of the
maintenance manual by establishing a retirement life of 5000 hours TIS
for each bolt.

(c) Record a 5000-hour TIS life limit for each bolt on the component history card or equivalent record.

(d)
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, FAA, ATTN: Sharon Miles, Aviation Safety
Engineer, Rotorcraft Directorate, Regulations and Guidance Group, Fort
Worth, Texas 76193-0111, telephone (817) 222- 5122, fax (817) 222-5961
for information about previously approved alternative methods of
compliance.

(e) This amendment becomes effective on February 6, 2008.

Note 3: The subject of this AD is addressed in Transport Canada (Canada) AD No. CF 2005-09, dated April 14, 2005.

Footer Information
Issued in Fort Worth, Texas, on November 30, 2007.
Mark R. Schilling, Acting Manager
Rotorcraft Directorate,
Aircraft Certification Service.
[FR Doc. E7-25389 Filed 12-31-07; 8:45 am]
BILLING CODE 4910-13-P


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