Airworthiness Directives; Bell Helicopter Textron Canada Model 407 Helicopters

[Federal Register Volume 67, Number 112 (Tuesday, June 11, 2002)]
[Rules and Regulations]
[Pages 39844-39846]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 02-14566]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2001-SW-54-AD; Amendment 39-12770; AD 2002-11-09]
RIN 2120-AA64


Airworthiness Directives; Bell Helicopter Textron Canada Model 
407 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)

[[Page 39845]]

Model 407 helicopters that requires visually inspecting the forward 
hanger bearing bracket (bracket) for a crack. This amendment is 
prompted by reports of cracks in the bracket. The actions specified by 
this AD are intended to detect a crack in the bracket, to prevent loss 
of tail rotor drive or control and subsequent loss of control of the 
helicopter.

DATES: Effective July 16, 2002.

FOR FURTHER INFORMATION CONTACT: Sharon Miles, Aviation Safety 
Engineer, FAA, Rotorcraft Directorate, Regulations 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 BHTC Model 407 helicopters was published in the 
Federal Register on January 16, 2002 (67 FR 2146). That action proposed 
initial and repetitive inspections for a crack in certain brackets and 
removing any bracket found with a crack before further flight.
    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 adopting 
the rule as proposed.
    The FAA estimates that 442 helicopters of U.S. registry will be 
affected by this AD, that it will take approximately \1/4\ work hour 
per helicopter to accomplish the required actions, and that the average 
labor rate is $60 per work hour. Based on these figures, the total cost 
impact of the AD on U.S. operators is estimated to be $6630 assuming no 
crack is detected in a bracket.
    The regulations adopted herein 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, it 
is determined that this final rule does not have federalism 
implications under Executive Order 13132.
    For the reasons discussed above, I certify that this action (1) is 
not a ``significant regulatory action'' under Executive Order 12866; 
(2) is not a ``significant rule'' under 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. A final evaluation has been prepared for this action 
and it is contained in the Rules Docket. A copy of it may be obtained 
from the Rules Docket at the FAA, Office of the Regional Counsel, 
Southwest Region, 2601 Meacham Blvd., Room 663, Fort Worth, Texas.

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 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:

2002-11-09  Bell Helicopter Textron Canada: Amendment 39-12770. 
Docket No. 2001-SW-54-AD.

    Applicability: Model 407 helicopters, serial number 53000 
through 53442, with flywheel, part number (P/N) 407-040-316-101, 
installed, certificated in any category.

    Note 1: This AD applies to each helicopter identified in the 
preceding applicability provision, regardless of whether it has been 
otherwise modified, altered, or repaired in the area subject to the 
requirements of this AD. For helicopters that have been modified, 
altered, or repaired so that the performance of the requirements of 
this AD is affected, the owner/operator must request approval for an 
alternative method of compliance in accordance with paragraph (b) of 
this AD. The request should include an assessment of the effect of 
the modification, alteration, or repair on the unsafe condition 
addressed by this AD; and if the unsafe condition has not been 
eliminated, the request should include specific proposed actions to 
address it.

    Compliance: Required as indicated, unless accomplished 
previously.
    To detect a crack in the forward bearing hanger bracket 
(bracket) and to prevent loss of tail rotor drive or tail rotor 
control 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 25 hours TIS, visually inspect each bracket, 
P/N 407-040-321-101 or -103, for a crack in the shaded area shown in 
Figure 1 of this AD. Remove any cracked bracket from service.

    Note 2: Dismantling of the bearing hanger and the support is not 
required to accomplish the requirements of this AD.


[[Page 39846]]


[GRAPHIC] [TIFF OMITTED] TR11JN02.003


    Note 3: Bell Helicopter Textron Canada Alert Service Bulletin 
No. 407-01-39, Revision A, dated May 30, 2001, pertains to the 
subject of this AD.
    (b) An alternative method of compliance or adjustment of the 
compliance time that provides an acceptable level of safety may be 
used if approved by the Manager, Regulations Group, Rotorcraft 
Directorate, FAA. Operators shall submit their requests through an 
FAA Principal Maintenance Inspector, who may concur or comment and 
then send it to the Manager, Regulations Group.


    Note 4: Information concerning the existence of approved 
alternative methods of compliance with this AD, if any, may be 
obtained from the Regulations Group.
    (c) Special flight permits may be issued in accordance with 14 
CFR 21.197 and 21.199 to operate the helicopter to a location where 
the requirements of this AD can be accomplished.
    (d) This amendment becomes effective on July 16, 2002.


    Note 5: The subject of this AD is addressed in Transport Canada 
(Canada) AD No. CF-2001-32, dated August 13, 2001.


    Issued in Fort Worth, Texas, on May 28, 2002.
Mark R. Schilling,
Acting Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. 02-14566 Filed 6-10-02; 8:45 am]
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