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

[Federal Register Volume 73, Number 177 (Thursday, September 11, 2008)]
[Rules and Regulations]
[Pages 52777-52778]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: E8-20979]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2008-0449; Directorate Identifier 2007-SW-10-AD; 
Amendment 39-15669; AD 2008-19-02]
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.

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SUMMARY: We are superseding an existing airworthiness directive (AD) 
for Bell Helicopter Textron Canada (Bell) Model 222, 222B, 222U, 230, 
and 430 helicopters. That AD currently requires visually inspecting the 
main rotor hydraulic actuator support (support) to verify the presence 
of all dowel pins and sealant between the support and transmission and 
verifying the proper torque of each attaching nut (nut). This AD 
requires the same actions as the existing AD and also requires 
repetitive actions at intervals not to exceed 600 hours time-in-service 
(TIS) or 12 months, whichever occurs first. This AD is prompted by the 
discovery that a 12-month compliance requirement was correctly included 
in an Emergency AD (EAD) that we issued but was inadvertently omitted 
when we published the Final rule; request for comments following the 
issuance of the EAD. The actions specified by this AD are intended to 
prevent failure of the support and subsequent loss of control of the 
helicopter.

DATES: Effective October 16, 2008.
    The incorporation by reference of Bell Helicopter Textron Alert 
Service Bulletin Nos. 222-00-86, 222U-00-57, 230-00-18, and 430-00-17, 
all dated May 19, 2000, was approved previously for incorporation by 
reference by the Director of the Federal Register on March 2, 2001 (66 
FR 10361, February 15, 2001).

ADDRESSES: You may examine the AD docket on the Internet at http://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, Aerospace Engineer, 
FAA, Rotorcraft Directorate, Rotorcraft Standards Staff, Fort Worth, 
Texas 76193-0110, telephone (817) 222-5439, fax (817) 222-5961.

SUPPLEMENTARY INFORMATION: On January 5, 2001, we issued EAD 2001-01-51 
for Bell Model 222, 222B, 222U, 230, and 430 helicopters which 
requires, at specified time intervals, visually inspecting the support 
for the presence of all dowel pins and sealant between the support and 
transmission and verifying the proper torque of each nut. That action 
was prompted by the failure of a support resulting in an accident of a 
Bell Model 222U helicopter. All retaining studs and shear pins were 
found sheared or pulled out at the junction between the support and 
transmission case. The requirements of that EAD are intended to prevent 
failure of the support and subsequent loss of control of the 
helicopter.
    On February 2, 2001, we issued AD 2001-01-51, Amendment 39-12105, 
Docket No. 2000-SW-54-AD as a Final rule; request for comments (66 FR 
10361, February 15, 2001). Since issuing that AD, we discovered that we 
inadvertently omitted the phrase ``or 12 months, whichever occurs 
first,'' from compliance paragraph (a) of the published final rule AD. 
Because the two versions of AD 2001-01-51 have different compliance 
times, we issued an NPRM on April 14, 2008 (73 FR 21853, April 23, 
2008) proposing to supersede AD 2001-01-51 and require the following:
    <bullet> Within 25 hours TIS, and thereafter at intervals not to 
exceed 600 hours TIS or 12 months, whichever occurs first:
    <bullet> Visually inspecting the support and, if any pin is missing 
or if there is no sealant visible, further inspecting the support, the 
transmission case, studs, and dowel pins and repairing or replacing any 
unairworthy part before further flight;
    <bullet> Verifying the torque of the nuts and, depending on the 
location and number of loose nuts, before further flight:
    <bullet> Removing the support and further inspecting the support, 
transmission case, studs, and dowel pins and repairing or replacing any 
unairworthy part; and
    <bullet> Retorqueing certain nuts;
    <bullet> At not less than 20 hours TIS nor more than 30 hours TIS 
after reinstalling a support for any reason, verifying the torque of 
the nuts.
    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.
    We have reviewed Bell Alert Service Bulletin Nos. 222-00-86, 222U-
00-57, 230-00-18, and 430-00-17, all dated May 19, 2000 (ASB's), which 
specify, within 25 hours TIS, conducting a one-time inspection of the 
support installation by accomplishing a torque check of the support 
attaching nuts. In

[[Page 52778]]

addition, a revision to the maintenance manual will introduce a 
recurring torque check of the nuts. Transport Canada classified these 
ASB's as mandatory and issued AD No. CF-2000-29, dated September 6, 
2000, to ensure the continued airworthiness of these helicopters in 
Canada.
    We estimate that this AD will affect 145 helicopters of U.S. 
registry. It will take approximately \1/2\ work hour per helicopter to 
inspect for proper torque, and the average labor rate is $80 per work 
hour. The cost for the inspection is estimated to be $5,800. Assuming 
15 helicopters require removing the support for additional inspections, 
it will take approximately 6 additional work hours at $80 per work hour 
and $50 for parts at an additional total cost of $7,950. Based on these 
figures, we estimate the total cost impact of this AD on U.S. operators 
to be $13,750, assuming no supports are replaced.

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.

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 removing Amendment 39-12105 (66 FR 
10361, February 15, 2001), and by adding a new airworthiness directive 
(AD), Amendment 39-15669, to read as follows:

2008-19-02 Bell Helicopter Textron Canada: Amendment 39-15669, 
Docket No. FAA-2008-0449; Directorate Identifier 2007-SW-10-AD. 
Supersedes AD 2001-01-51, Amendment 39-12105, Docket No. 2000-SW-54-
AD.

    Applicability: Model 222, 222B, 222U, 230, and 430 helicopters, 
with a main rotor hydraulic actuator support (support), part number 
(P/N) 222-040-125-001, installed, certificated in any category.
    Compliance: Required as indicated, unless accomplished 
previously.
    To prevent failure of the support and subsequent loss of control 
of the helicopter, accomplish the following:
    (a) Within 25 hours time-in-service (TIS) and thereafter at 
intervals not to exceed 600 hours TIS or 12 months, whichever occurs 
first, accomplish the following:
    (1) Visually inspect the support for the presence of all dowel 
pins and for sealant between the support and transmission. If any 
pin is missing, or if no sealant is visible, before further flight, 
remove the support and further inspect the support, transmission 
case, studs, and dowel pins in accordance with the Accomplishment 
Instructions, paragraphs 5 through 7, of the applicable Bell 
Helicopter Textron Alert Service Bulletin Nos. 222-00-86, 222U-00-
57, 230-00-18, or 430-00-17, all dated May 19, 2000 (ASB's). Repair 
or replace any unairworthy support, transmission case, stud, or 
dowel pin before further flight.
    (2) Verify the torque of the support attaching nuts (nuts). 
Upper nuts must not rotate at a torque less than 40 in-lbs. Lower 
nuts must not rotate at a torque less than 90 in-lbs.
    (i) If two or more upper nuts rotate at a torque less than 40 
in-lbs. or two or more lower nuts rotate at a torque less than 90 
in-lbs., before further flight, remove the support and further 
inspect the support, transmission case, studs, and dowel pins in 
accordance with the Accomplishment Instructions, paragraph 5 through 
7, of the applicable ASB's. Repair or replace any unairworthy 
support, transmission case, stud, or dowel pin before further 
flight.
    (ii) If less than two upper nuts rotate at a torque less than 40 
in-lbs. or less than two lower nuts rotate at a torque less than 90 
in-lbs., before further flight, retorque the upper nut to 50 to 70 
in-lbs. plus tare and the lower nut to 100 to 140 in-lbs. plus tare.
    (b) At not less than 20 hours TIS nor more than 30 hours TIS 
after reinstalling a support for any reason, verify the torque of 
the nuts in accordance with paragraph (a)(2) of this AD.
    (c) 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, Rotorcraft Standards Staff, FAA, ATTN: Tyrone 
Millard, telephone (817) 222-5439, fax (817) 222-5961, for 
information about previously approved alternative methods of 
compliance.
    (d) You must use the specified portions of Bell Helicopter 
Textron Alert Service Bulletin Nos. 222-00-86, 222U-00-57, 230-00-
18, or 430-00-17, all dated May 19, 2000, to do the required 
inspections.
    (1) The Director of the Federal Register previously approved the 
incorporation by reference of these service bulletins on March 2, 
2001 (66 FR 10361, February 15, 2001).
    (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.
    (e) This amendment becomes effective on October 16, 2008.

    Note: The subject of this AD is addressed in Transport Canada 
(Canada) AD CF-2000-29, dated September 6, 2000.


    Issued in Fort Worth, Texas, on August 13, 2008.
Mark R. Schilling,
Acting Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. E8-20979 Filed 9-10-08; 8:45 am]
BILLING CODE 4910-13-P

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