[Federal Register Volume 60, Number 225 (Wednesday, November 22, 1995)]
[Rules and Regulations]
[Pages 57823-57824]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 95-28517]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 93-SW-04-AD; Amendment 39-9438; AD 95-24-06]
Airworthiness Directives; Bell Helicopter Textron, a Division of
Textron Canada, Model 206B and 206L Helicopters
AGENCY: Federal Aviation Administration, DOT.
ACTION: Final rule.
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SUMMARY: This amendment supersedes an existing airworthiness directive
(AD), applicable to Bell Helicopter Textron, a Division of Textron
Canada (BHT), Model 206B and 206L helicopters, that currently requires
a revision to the Limitations section of the FAA-approved Supplemental
Type Certificate (STC) Rotorcraft Flight Manual Supplement (RFMS) until
replacement of the engine power-out warning sensor on BHT Model 206B
and 206L helicopters equipped with Allison 250-C20R engines in
accordance with certain supplemental type certificates. This amendment
requires a revision to the Limitations section of the STC RFMS, but
removes the requirement for replacement of the engine power-out warning
sensor. This amendment is prompted by a reevaluation of the need for an
engine power-out warning sensor based on the lack of reported
operational occurrences of the false engine-out warnings. The actions
specified by this AD are intended to maintain a heightened pilot
awareness that false engine-out warnings may occur when practicing
autorotations and could result in an unnecessary emergency autorotative
landing.
DATES: Effective December 27, 1995.
The incorporation by reference of certain publications listed in
the regulations was previously approved by the Director of the Federal
Register as of December 30, 1991 (56 FR 63631, December 5, 1991).
ADDRESSES: The service information referenced in this AD may be
obtained from Soloy Corporation, 450 Pat Kennedy Way SW., Olympia,
Washington 98501-7298. This information may be examined at the FAA,
Office of the Assistant Chief Counsel, 2601 Meacham Blvd., Room 663,
Fort Worth, Texas; or at the Office of the Federal Register, 800 North
Capitol Street, NW., suite 700, Washington, DC.
FOR FURTHER INFORMATION CONTACT: Mr. Stephen Bray, Aerospace Engineer,
FAA, Transport Airplane Directorate, Seattle Aircraft Certification
Office, Propulsion Branch, ANM-140S, 1601 Lind Avenue SW., Renton,
Washington 98055-4056, telephone (206) 227-2681, fax (206) 227-1181.
SUPPLEMENTARY INFORMATION: A proposal to amend part 39 of the Federal
Aviation Regulations (14 CFR part 39) by superseding AD 91-23-15,
Amendment 39-8084 (56 FR 63631, dated December 5, 1991), which is
applicable to BHT Model 206B and 206L helicopters equipped with Allison
250-C20R engines in accordance with Supplemental Type Certificate No.
SH4169NM, SH4179NM, or SH4729NM was published in the Federal Register
on June 7, 1993 (58 FR 31916). That action proposed to require a
revision to the Limitations section of the applicable STC RFMS in
accordance with Soloy Corporation Service Bulletin 02-680, revised
December 8, 1992.
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 the
adoption of
[[Page 57824]]
the rule as proposed, except for some editorial changes and adding
explanatory Note 1, relating to the scope of the applicability
statement when modifications, alterations, or repairs have been made in
the area subject to the requirements of the AD. Additionally, the FAA
has revised the proposed estimated average labor rate from $55 per work
hour to an estimated average labor rate of $60 per work hour in the
preamble portion of this final rule. This revision will increase the
estimated total cost impact of the AD from $1,045 to $1,140. Finally,
the type certificate has been transferred to a new owner since the
issuance of the proposal. The FAA has determined that these changes
will neither increase the economic burden on any operator nor increase
the scope of the AD.
The FAA estimates that 19 helicopters of U.S. registry will be
affected by this AD, that it will take approximately one 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 $1,140.
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, Incorporation by
reference, 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), 40101, 40113, 44701.
Sec. 39.13 [Amended]
2. Section 39.13 is amended by removing Amendment 39-8084 (56 FR
63631, December 5, 1991), and by adding a new airworthiness directive
(AD), Amendment 39-9438, to read as follows:
AD 95-24-06 Bell Helicopter Textron, a division of Textron Canada
(BHT): Amendment 39-9438. Docket No. 93-SW-04-AD. Supersedes AD 91-
23-15, Amendment 39-8084.
Applicability: Model 206B and 206L helicopters, equipped with
Allison 250-C20R engine power-out warning sensors, part number (P/N)
206-075-545-001, in accordance with Supplemental Type Certificate
(STC) No. SH4169NM (applicable to Model 206L), SH4179NM (applicable
to Model 206B), or SH4729NM (applicable to both Models 206B & L),
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 as indicated, unless accomplished
previously.
To alert the pilot of a potential false engine-out warning when
practicing autorotations that could result in an unnecessary
emergency autorotative landing, accomplish the following:
(a) Within 10 days after the effective date of this AD, revise
the Limitations section of the applicable FAA-approved STC
Rotorcraft Flight Manual Supplement (RFMS) by adding the warning
statement and note contained in the Description section of Soloy
Corporation Service Bulletin 02-680, revised December 8, 1992.
(b) An alternative method of compliance or adjustment of the
compliance time that provides an acceptable level of safety may be
used when approved by the Manager, Seattle Aircraft Certification
Office, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW.,
Renton, Washington 98055-4056. Operators shall submit their requests
through an FAA Principal Maintenance Inspector, who may concur or
comment and then send it to the Manager, Seattle Aircraft
Certification Office.
Note 2: Information concerning the existence of approved
alternative methods of compliance with this AD, if any, may be
obtained from the Seattle Aircraft Certification Office.
(c) Special flight permits to accomplish the requirements of
this AD will not be issued.
(d) The warning and note to be inserted into the Limitations
section of the applicable STC RFMS are contained in Soloy
Corporation Service Bulletin 02-680, revised December 8, 1992. This
incorporation by reference was previously approved by the Director
of the Federal Register in accordance with 5 U.S.C. 552(a) and 1 CFR
part 51 as of December 30, 1991 (56 FR 63631, December 5, 1991).
Copies may be obtained from Soloy Corporation, 450 Pat Kennedy Way
SW., Olympia, Washington 98501-7298. Copies may be inspected at the
FAA, Office of the Assistant Chief Counsel, 2601 Meacham Blvd., Room
663, Fort Worth, Texas; or at the Office of the Federal Register,
800 North Capitol Street, NW., suite 700, Washington, DC.
(e) This amendment becomes effective on December 27, 1995.
Issued in Fort Worth, Texas, on November 8, 1995.
Eric Bries,
Acting Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. 95-28517 Filed 11-21-95; 8:45 am]
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