[Federal Register: November 16, 2007 (Volume 72, Number 221)]
[Proposed Rules]
[Page 64542-64545]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr16no07-15]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2007-0178; Directorate Identifier 2007-SW-20-AD]
RIN 2120-AA64
Airworthiness Directives; Bell Helicopter Textron Canada (BHTC)
Model 222, 222B, and 222U Helicopters
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking (NPRM).
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SUMMARY: We propose to adopt a new airworthiness directive (AD) for
BHTC Model 222, 222B, and 222U helicopters. This proposed AD results
from mandatory continuing airworthiness information (MCAI) originated
by an aviation authority of another country to identify and correct an
unsafe condition on an aviation product. The aviation
[[Page 64543]]
authority of Canada, with which we have a bilateral agreement, states
in the MCAI:
It has been determined that the existing rigging procedures for
the tail rotor pitch change mechanism have to be changed due to
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) 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. The proposed AD
would require actions that are intended to address these unsafe
conditions.
DATES: We must receive comments on this proposed AD by December 17,
2007.
ADDRESSES: You may send comments by any of the following methods:
Federal eRulemaking Portal: Go to http://www.regulations.gov.
Follow the instructions for submitting comments.
Fax: 202-493-2251.
Mail: U.S. Department of Transportation, Docket
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New
Jersey Avenue, SE., Washington, DC 20590.
Hand Delivery: U.S. Department of Transportation, Docket
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New
Jersey Avenue, SE., Washington, DC 20590, between 9 a.m. and 5 p.m.,
Monday through Friday, except Federal holidays.
Examining the AD Docket
You may examine the AD docket on the Internet at http://www.regulations.gov
, or in person at the Docket Operations office
between 9 a.m. and 5 p.m., Monday through Friday, except Federal
holidays. The AD docket contains this proposed AD, the economic
evaluation, any comments received, and other information. The street
address for the Docket Operations office (telephone (800) 647-5527) is
in the ADDRESSES section. Comments will be available in the AD docket
shortly after receipt.
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:
Streamlined Issuance of AD
The FAA is implementing a new process for streamlining the issuance
of ADs related to MCAI. This streamlined process will allow us to adopt
MCAI safety requirements in a more efficient manner and will reduce
safety risks to the public. This process continues to follow all FAA AD
issuance processes to meet legal, economic, Administrative Procedure
Act, and Federal Register requirements. We also continue to meet our
technical decision-making responsibilities to identify and correct
unsafe conditions on U.S.-certificated products.
This proposed AD references the MCAI and related service
information that we considered in forming the engineering basis to
correct the unsafe condition. The proposed AD contains text copied from
the MCAI and for this reason might not follow our plain language
principles.
Comments Invited
We invite you to send any written relevant data, views, or
arguments about this proposed AD. Send your comments to an address
listed under the ADDRESSES section. Include ``Docket No. FAA-2007-0178;
Directorate Identifier 2007-SW-20-AD'' at the beginning of your
comments. We specifically invite comments on the overall regulatory,
economic, environmental, and energy aspects of this proposed AD. We
will consider all comments received by the closing date and may amend
this proposed AD based on those comments.
We will post all comments we receive, without change, to http://www.regulations.gov
, including any personal information you provide. We
will also post a report summarizing each substantive verbal contact we
receive about this proposed AD.
Discussion
Transport Canada, which is the aviation authority for Canada, has
issued Canadian Airworthiness Directive No. CF-2007-07, dated April 11,
2007 (referred to after this as ``the MCAI''), to correct an unsafe
condition for the Canadian-certificated products. The MCAI states:
It has been determined that the existing rigging procedures for
the tail rotor pitch change mechanism have to be changed due to
possibility of parts interference.
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, the tail rotor yoke may contact nut,
P/N 222-012-731-001, before contacting the flapping stop, resulting in
less tail rotor travel. Additionally, 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.
You may obtain further information by examining the service
information and the MCAI in the AD docket.
Relevant Service Information
Bell Helicopter Textron has issued Alert Service Bulletin (ASB)
222-07-104 and ASB 222U-07-75, both 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.
FAA's Determination and Requirements of This Proposed AD
This product has been approved by the aviation authority of Canada,
and is approved for operation in the United States. Pursuant to our
bilateral agreement with this State of Design Authority, we have been
notified of the unsafe condition described in the MCAI and service
information. We are proposing this AD because we evaluated all
pertinent information and determined an unsafe condition exists and is
likely to exist or develop on other products of the same type design.
Differences Between This AD and the MCAI or Service Information
We have reviewed the MCAI and related service information and, in
general, agree with their substance. But we might have found it
necessary to use different words from those in the MCAI to ensure the
AD is clear for U.S. operators and is enforceable. In making these
changes, we do not intend to differ substantively from the information
provided in the MCAI and related service information.
We might also have proposed different actions in this AD from those
in the MCAI in order to follow FAA policies. Any such differences are
highlighted in the ``Differences Between the FAA AD and the MCAI''
section in the proposed AD.
Costs of Compliance
We estimate that this proposed AD would affect about 86 products of
U.S. registry. Also, we estimate that it would take 2 work-hours per
product to comply with the basic requirements of this proposed AD. The
average labor rate is $80 per work-hour. A
[[Page 64544]]
replacement yoke would 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. Therefore, as we do not control warranty
coverage for affected parties, some parties may incur costs higher than
estimated here. Based on these figures, we estimate the cost of the
proposed AD on U.S. operators to be $13,760, 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 proposed AD would not have federalism
implications under Executive Order 13132. This proposed AD would 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 this proposed
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 proposed AD and placed it in the AD docket.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Safety.
The Proposed Amendment
Accordingly, under the authority delegated to me by the
Administrator, the FAA proposes to amend 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. The FAA amends Sec. 39.13 by adding the following new AD:
Bell Helicopter Textron Canada: Docket No. FAA-2007-0178;
Directorate Identifier 2007-SW-20-AD.
Comments Due Date
(a) We must receive comments by December 17, 2007.
Other Affected ADs
(b) None.
Applicability
(c) This AD applies to Bell Helicopter Textron Canada (BHTC)
Model 222, serial numbers (S/N) 47006 through 47089; Model 222B, S/N
47131 through 47156, and Model 222U, all serial numbers,
helicopters, certificated in any category.
Reason
(d) The mandatory continuing airworthiness information (MCAI)
states:
It has been determined that the existing rigging procedures for
the tail rotor pitch change mechanism have to be changed due to
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, P/N
222-012-731-001, 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 actions.
(1) Adjust the rigging of the tail rotor pitch change mechanism
in accordance with the Accomplishment Instructions, Paragraphs 1 and
2, of the applicable Bell Helicopter Textron Alert Service Bulletin
(ASB) listed in the following Table 1:
Table 1
------------------------------------------------------------------------
Helicopter model Applicable ASB & date
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222 and 222B.......................... 222-07-104 dated January 9,
2007.
222U.................................. 222U-07-75 dated January 9,
2007.
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(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
Instruction, Paragraphs 4 through 6, of the ASB listed in Table 1 of
the AD.
Differences Between the FAA 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.
Subject
(g) Air Transport Association of America (ATA) Code JASC 6720:
Tail Rotor Control System, Tail Rotor Pitch Change.
Other Information
(h) The following provisions also apply to this AD:
(1) 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, Aerospace Engineer; FAA,
Rotorcraft Directorate, Rotorcraft Standards Staff, Fort Worth,
Texas 76193-0111, telephone (817) 222-5439, fax (817) 222-5961.
(2) Airworthy Product: Use only FAA-approved corrective actions.
Corrective actions are considered FAA-approved if they are approved
by the State of Design Authority (or their delegated agent) if the
State of Design has an appropriate bilateral agreement with the
United States. You are required to assure the product is airworthy
before it is returned to service.
(3) Reporting Requirements: For any reporting requirement in
this AD, under the provisions of the Paperwork Reduction Act, the
Office of Management and Budget (OMB) has approved the information
collection requirements and has assigned OMB Control Number 2120-
0056.
Related Information
(i) MCAI Transport Canada Airworthiness Directive CF-2007-07,
dated April 11, 2007, and Bell Helicopter Textron ASB Nos. 222-07-
104 and 222U-07-75, both dated January 9, 2007, contain related
information.
[[Page 64545]]
Issued in Fort Worth, Texas, on November 5, 2007.
David A. Downey,
Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. E7-22441 Filed 11-15-07; 8:45 am]
BILLING CODE 4910-13-P