[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]
-----------------------------------------------------------------------
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.
-----------------------------------------------------------------------
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