[Federal Register Volume 73, Number 155 (Monday, August 11, 2008)]
[Rules and Regulations]
[Pages 46546-46547]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: E8-17990]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2008-0450; Directorate Identifier 2007-SW-39-AD; 
Amendment 39-15634; AD 2008-16-16]
RIN 2120-AA64


Airworthiness Directives; Bell Helicopter Textron Canada (BHTC) 
Model 230 Helicopters

AGENCY: Federal Aviation Administration (FAA), Department of 
Transportation (DOT).

ACTION: Final rule.

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SUMMARY: We are adopting a new airworthiness directive (AD) for BHTC 
Model 230 helicopters. This AD results from mandatory continuing 
airworthiness information (MCAI) issued by the aviation authority of 
Canada which indicates that the existing rigging procedures for the 
tail rotor pitch change mechanism have to be changed due to the 
possibility of parts interference. The cumulative effect of individual 
part tolerances resulting in the total assemblage of those parts being 
out of tolerance could result in the tail rotor yoke striking another 
part other than the flapping stop (parts interference) as cited in the 
MCAI. Also, the misalignment of the tail rotor counterweight bellcrank 
may result in higher tail rotor pedal forces and a higher pilot 
workload after failure of the No. 1 hydraulic system. Both parts 
interference and the misaligned counterweight bellcrank create an 
unsafe condition. This AD requires actions that are intended to address 
these unsafe conditions.

DATES: This AD becomes effective on September 15, 2008.
    The incorporation by reference of certain publications is approved 
by the Director of the Federal Register as of September 15, 2008.

ADDRESSES: You may examine the AD docket on the Internet at http://www.regulations.gov or in person at the Docket Operations office, U.S. 
Department of Transportation, M-30, West Building Ground Floor, Room 
W12-140, 1200 New Jersey Avenue, SE., Washington, DC between 9 a.m. and 
5 p.m. Monday through Friday, except Federal holidays.
    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 Ad Docket: The AD docket contains the Notice of 
proposed rulemaking (NPRM), the economic evaluation, any comments 
received, and other information. The street address and operating hours 
for the Docket Operations office (telephone (800) 647-5527) are in the 
ADDRESSES section of this AD. Comments will be available in the AD 
docket shortly after they are received.

FOR FURTHER INFORMATION CONTACT: Tyrone Millard, Aviation Safety 
Engineer, FAA, Rotorcraft Directorate, Rotorcraft Standards Staff, Fort 
Worth, Texas 76193-0111, telephone (817) 222-5439, fax (817) 222-5961.

SUPPLEMENTARY INFORMATION:

Discussion

    We issued an NPRM to amend 14 CFR part 39 to include an AD that 
would apply to the BHTC Model 230 helicopters on April 14, 2008. That 
NPRM was published in the Federal Register on April 23, 2008 (73 FR 
21855). That NPRM proposed to require, within the next 150 hours time-
in-service (TIS) or at the next annual inspection, whichever occurs 
first, adjusting the rigging of the tail rotor pitch change mechanism, 
and if a gap exists between the tail rotor yoke and the flapping stop, 
replacing the tail rotor yoke with an airworthy tail rotor yoke. If no 
gap exists between the tail rotor yoke and the flapping stop at either 
full right or full left pedal position, adjusting the tail rotor pitch 
change mechanism and the tail rotor pedal forces was proposed.

Comments

    By publishing the NPRM, we gave the public an opportunity to 
participate in developing this AD. However, we received no comment on 
the NPRM or on our determination of the cost to the public. Therefore, 
based on our review and evaluation of the available data, we have 
determined that air safety and the public interest require adopting the 
AD as proposed.

Related Service Information

    Bell Helicopter Textron has issued Alert Service Bulletin 230-07-
36, dated January 9, 2007. The actions described in the MCAI are 
intended to correct the same unsafe condition as that identified in the 
service information.

Differences Between This AD and the MCAI

    The compliance times in this AD differ from the MCAI in that 
compliance is required within the next 150 hours TIS or at the next 
annual inspection, whichever occurs first, instead of ``at the next 150 
hour or annual inspection but no later than 31 December 2007.''

Costs of Compliance

    We estimate that this AD will affect about 20 helicopters of U.S. 
registry. We also estimate that it will take 2 work-hours per 
helicopter to adjust the

[[Page 46547]]

rigging of the tail rotor pitch change mechanism. The average labor 
rate is $80 per work-hour. A replacement yoke will cost about $21,218, 
assuming the part is no longer under warranty. However, because the 
service information lists this part as covered under warranty, we have 
assumed that there will be no charge for this part, if needed. 
Therefore, as we do not control warranty coverage for affected parties, 
some parties may incur costs higher than estimated here. Based on these 
assumptions and figures, we estimate the cost of the AD on U.S. 
operators to be $3,200, or $160 per helicopter.

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.

Regulatory Findings

    We 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.
    Therefore, I certify this AD:
    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 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

0
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 AD:

2008-16-16 Bell Helicopter Textron Canada: Amendment 39-15634; 
Docket No. FAA-2008-0450; Directorate Identifier 2007-SW-39-AD.

Effective Date

    (a) This airworthiness directive (AD) becomes effective on 
September 15, 2008.

Other Affected ADs

    (b) None.

Applicability

    (c) This AD applies to Bell Helicopter Textron Canada (BHTC) 
Model 230 helicopters, certificated in any category.

Reason

    (d) This AD results from mandatory continuing airworthiness 
information (MCAI) issued by the aviation authority of Canada which 
indicates that the existing rigging procedures for the tail rotor 
pitch change mechanism have to be changed due to the possibility of 
parts interference. This ``possibility of parts interference'' 
occurs because the cumulative effect of the tolerances on the 
various parts may result in the total assemblage outboard of the 
counterweight bellcrank being out of tolerance and the tail rotor 
yoke may contact nut, part number (P/N) 222-012-737-001, before 
contacting the flapping stop. Further, the manufacturer has 
indicated that the tail rotor counterweight bellcranks may be 
misaligned, resulting in higher tail rotor pedal forces and higher 
pilot workload after failure of the No. 1 hydraulic system. Both the 
parts interference and the higher pedal forces constitute unsafe 
conditions.

Actions and Compliance

    (e) Within the next 150 hours time-in-service (TIS) or at the 
next annual inspection, whichever occurs first, unless already done, 
do the following:
    (1) Adjust the rigging of the tail rotor pitch change mechanism 
in accordance with the Accomplishment Instructions, paragraphs 1 and 
2, in Bell Helicopter Textron Alert Service Bulletin 230-07-36, 
dated January 9, 2007 (ASB).
    (2) If either at full left pedal position or full right pedal 
position a gap exists between the tail rotor yoke and the flapping 
stop, replace the tail rotor yoke with an airworthy tail rotor yoke.
    (3) If no gap exists between the tail rotor yoke and the 
flapping stop at either full right or full left pedal position, 
measure the gap between the tail rotor yoke and nut, P/N 222-012-
731-001, adjust the tail rotor pitch change mechanism, and adjust 
the tail rotor pedal forces in accordance with the Accomplishment 
Instructions, paragraphs 4. through 6. of the ASB.

Differences Between This AD and the MCAI

    (f) This AD requires compliance within the next 150 hours TIS or 
at the next annual inspection, whichever occurs first, instead of 
``at the next 150 hour or annual inspection but no later than 31 
December 2007.''

Other Information

    (g) Alternative Methods of Compliance (AMOCs): The Manager, 
Safety Management Group, FAA, has the authority to approve AMOCs for 
this AD, if requested using the procedures found in 14 CFR 39.19. 
Send information to ATTN: Tyrone Millard, Aviation Safety Engineer, 
FAA, Rotorcraft Directorate, Rotorcraft Standards Staff, Fort Worth, 
Texas 76193-0111, telephone (817) 222-5439, fax (817) 222-5961.

Related Information

    (h) MCAI Transport Canada Airworthiness Directive CF-2007-12, 
dated August 24, 2007, contains related information.

Air Transport Association of America (ATA) Tracking Code

    (i) ATA Code JASC 6720, Tail Rotor Control System, Tail Rotor 
Pitch Change.

Material Incorporated by Reference

    (j) You must use the specified portions of Bell Helicopter 
Textron Alert Service Bulletin 230-07-36, dated January 9, 2007, to 
do the actions required.
    (1) The Director of the Federal Register approved the 
incorporation by reference of this service information under 5 
U.S.C. 552(a) and 1 CFR part 51.
    (2) For service information identified in this AD, contact 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.
    (3) You may review copies 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/cfr/ibr-locations.html.

    Issued in Fort Worth, Texas on July 27, 2008.
Mark R. Schilling,
Acting Manager, Rotorcraft Directorate, Aircraft Certification Service.
 [FR Doc. E8-17990 Filed 8-8-08; 8:45 am]
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