AD 96-23-01

[Federal Register Volume 61, Number 216 (Wednesday, November 6, 1996)]
[Rules and Regulations]
[Pages 57323-57324]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 96-28167]


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DEPARTMENT OF TRANSPORTATION
14 CFR Part 39

[Docket No. 95-SW-35-AD; Amendment 39-9806; AD 96-23-01]
RIN 2120-AA64


Airworthiness Directives; Bell Helicopter Textron, a Division of 
Textron Canada, Ltd. Model 206L-1 Helicopters

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule.

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SUMMARY: This amendment adopts a new airworthiness directive (AD), 
applicable to Bell Helicopter Textron, a Division of Textron Canada, 
Ltd. (BHTC) Model 206L-1 helicopters that have a Kratos turbine outlet 
temperature (TOT) indicator (Kratos indicator) installed, that requires 
replacing certain Kratos indicators. This amendment is prompted by 
manufacturer's tests and FAA analyses that show certain Kratos 
indicators may incorrectly provide low-temperature readings when the 
battery voltage is below 10 volts. The actions specified by this AD are 
intended to prevent false low-temperature indications, which could 
result in overheating of the engine turbine (turbine) and subsequent 
thermal fatigue damage to the turbine wheel.

EFFECTIVE DATE: December 11, 1996.

ADDRESSES: The service information may be obtained from BHTC, 12,800 
Rue de L'Avenir, Mirabel, Quebec, Canada J7J1R4, ATTN: Product Support 
Engineering Light Helicopters.

FOR FURTHER INFORMATION CONTACT: Ms. Jennifer Kuehn, Aerospace 
Engineer, Rotorcraft Certification Office, Rotorcraft Directorate, FAA, 
2601 Meacham Blvd., Fort Worth, Texas 76137, telephone (817) 222-5366, 
fax (817) 222-5960.

SUPPLEMENTARY INFORMATION: A proposal to amend part 39 of the Federal 
Aviation Regulations (14 CFR part 39) to include an airworthiness 
directive (AD) that is applicable to BHTC Model 206L-1 helicopters was 
published in the Federal Register on April 10, 1996 (61 FR 15903). That 
action proposed to require removing the Kratos indicator and replacing 
it with an airworthy TOT indicator within 90 days after the effective 
date of this AD.
    Interested persons have been afforded an opportunity to participate 
in the making of this amendment. Due consideration has been given to 
the comments received.
    One commenter states that the AD should refer to the specific TOT 
indicator as is stated in the BHTC Model 206L-1 Illustrated Parts 
Catalog; otherwise, the AD will require owners/operators to obtain 
additional FAA approval since the particular part number referenced in 
the AD may not be reflected in any BHTC document. The FAA partially 
concurs. The FAA does not endorse specific vendors or manufacturers of 
parts unless those parts are the only parts authorized for use as 
replacements. There are alternative TOT indicator part numbers in the 
applicable helicopter parts catalog. The final rule will specify 
replacement TOT indicator part numbers, and the wording in the 
Compliance section has been revised to refer to using an airworthy 
replacement TOT indicator that is approved for this helicopter.
    The same commenter states that the reference to the Alert Service 
Bulletin (ASB) should not be contained in a Note, and instead 
compliance in accordance with the ASB should be mandatory. The FAA does 
not concur. Generally, ASB's may be mandatory for Part 135 owners/
operators, but not for Part 91 owners/operators.
    Finally, the same commenter states that the AD should not require 
replacement of the TOT indicator, and should instead require owners/
operators to ensure their helicopters' electrical systems provide at 
least 10 volts during startup. The FAA does not concur that this should 
be included in the AD. There are procedures by which owners/operators 
may request permission to accomplish this as an alternate means of 
compliance.
    After careful review of the available data, including the comments 
noted above, the FAA has determined that air safety and the public 
interest require the adoption of the rule as proposed.
    The FAA estimates that 100 helicopters of U.S. registry will be 
affected by this AD, that it will take approximately 8 work hours per 
helicopter to accomplish the required

[[Page 57324]]

actions, and that the average labor rate is $60 per work hour. Required 
parts will cost approximately $8,300 per helicopter. Based on these 
figures, the total cost impact of the AD on U.S. operators is estimated 
to be $878,000.
    The regulations adopted herein will not have substantial direct 
effects 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, in 
accordance with Executive Order 12612, it is determined that this final 
rule does not have sufficient federalism implications to warrant the 
preparation of a Federalism Assessment.
    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 location provided under the caption 
ADDRESSES.

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 part 39 of 
the Federal Aviation Regulations (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:

AD 96-23-01  Bell Helicopter Textron, a Division of Textron Canada, 
Ltd: Amendment 39-9806. Docket No. 95-SW-35-AD.

    Applicability: Model 206L-1 helicopters that have a Kratos 
turbine outlet temperature (TOT) indicator (Kratos indicator), part 
number (P/N) 124.444-6 or 124.444-20, 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 
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 use the authority 
provided in paragraph (b) to request approval from the FAA. This 
approval may address either no action, if the current configuration 
eliminates the unsafe condition, or different actions necessary to 
address the unsafe condition described in this AD. Such a request 
should include an assessment of the effect of the changed 
configuration on the unsafe condition addressed by this AD. In no 
case does the presence of any modification, alteration, or repair 
remove any helicopter from the applicability of this AD.

    Compliance: Required within 90 days after the effective date of 
this AD, unless accomplished previously.
    To prevent false low-temperature indications, which could result 
in overheating of the engine turbine (turbine) and subsequent 
thermal fatigue damage to the turbine wheel, accomplish the 
following:
    (a) Remove the Kratos indicator, P/N 124.444-6 or 124.444-20, 
and replace it with an indicator, P/N 206-075-680-105 or P/N 206-
375-006-101, or any other airworthy TOT indicator approved for use 
on the Bell Model 206L-1 helicopter, except for the Kratos TOT 
indicator, P/N 124.444-6 or 124.444-20.

    Note 2: Bell Helicopter Textron, Inc. Alert Service Bulletin 
206L-94-94, Revision A, dated July 11, 1994, pertains to 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, Rotorcraft Certification Office, 
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, Rotorcraft Certification 
Office.

    Note 3: Information concerning the existence of approved 
alternative methods of compliance with this AD, if any, may be 
obtained from the Rotorcraft Certification Office.

    (c) Special flight permits may be issued in accordance with 
sections 21.197 and 21.199 of the Federal Aviation Regulations (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 December 11, 1996.

    Issued in Fort Worth, Texas, on October 25, 1996.
Eric Bries,
Acting Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. 96-28167 Filed 11-5-96; 8:45 am]
BILLING CODE 4910-13-U