

[Federal Register: January 2, 2008 (Volume 73, Number 1)]
[Rules and Regulations]               
[Page 29-32]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr02ja08-6]                         

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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

 
Airworthiness Directives; Bell Helicopter Textron Canada Model 
430 Helicopters

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule.

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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

[[Page 30]]

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

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:

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. [FEDREG][VOL]*[/VOL][NO]*[/NO][DATE]*[/
DATE][RULES][RULE][PREAMB][AGENCY]*[/AGENCY][SUBJECT]*[/SUBJECT][/
PREAMB][SUPLINF][HED]*[/HED][REGTEXT][EXTRACT][P]*[/P]
    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.
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[GRAPHIC] [TIFF OMITTED] TR02JA08.004

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    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.


    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]

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