[Federal Register Volume 61, Number 170 (Friday, August 30, 1996)]
[Rules and Regulations]
[Pages 45876-45878]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 96-22141]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 96-SW-13-AD; Amendment 39-9729; AD 96-18-05]
RIN 2120-AA64
Airworthiness Directives; Bell Helicopter Textron, A Division of
Textron Canada Ltd. Model 206L, 206L-1, and 206L-3 Helicopters
AGENCY: Federal Aviation Administration, DOT.
ACTION: Final rule; request for comments.
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SUMMARY: This amendment supersedes an existing priority letter
airworthiness directive (AD), applicable to Bell Helicopter Textron, A
Division of Textron Canada Ltd. (BHTC) Model 206L, 206L-1, and 206L-3
helicopters, that currently requires a visual inspection of the
tailboom skin in the areas around the nutplates and in the areas of the
tailboom drive shaft cover retention clips for cracks and corrosion
using a 10-power or higher magnifying glass. This amendment requires
the same actions as the existing AD, but corrects a part number that
was incorrectly stated in that AD. This amendment is prompted by a
recent accident and several reports of fatigue cracks in the tailboom
skin in the areas around the nutplates for the tail rotor fairing and
in the areas of the tail rotor drive shaft cover retention clips. The
actions specified by this AD are intended to prevent failure of the
tailboom and subsequent loss of control of the helicopter.
DATES: Effective September 16, 1996. The incorporation by reference of
certain publications listed in the regulations is approved by the
Director of the Federal Register as of September 16, 1996.
Comments for inclusion in the Rules Docket must be received on or
before October 29, 1996.
ADDRESSES: Submit comments in triplicate to the Federal Aviation
Administration (FAA), Office of the Assistant Chief Counsel, Attention:
Rules Docket No. 96-SW-13AD, 2601 Meacham Blvd., Room 663, Fort Worth,
Texas 76137.
The service information referenced in this AD may be obtained from
Bell Helicopter Textron Canada, A Division of Textron Canada Ltd.,
12,800 rue de L'Avenir, Mirabel, Quebec, Canada, JON 1LO. 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. Tony Nguyen, Aerospace Engineer,
FAA, Rotorcraft Certification Office, Rotorcraft Directorate, 2601
Meacham Blvd., Fort Worth, Texas 76137, telephone (817) 222-5177, fax
(817) 222-5960.
SUPPLEMENTARY INFORMATION: On July 3, 1996, the FAA issued priority
letter AD 96-14-10, to require, before further flight, and thereafter
at intervals not to exceed 50 hours time-in-service (TIS), a visual
inspection of the tailboom skin in the areas around the nutplates and
in the areas of the tailboom drive shaft cover retention clips for
cracks and corrosion using a 10-power or higher magnifying glass. This
inspection interval was to be repeated until the tailboom was replaced
by part number (P/N) 206-033-004-143 or -173. That action was prompted
by a recent accident and several reports of fatigue cracks in the
tailboom skin in the areas around the nutplates for the tail rotor
fairing and in the areas of the tail rotor drive shaft cover retention
clips. That
[[Page 45877]]
condition, if not corrected, could result in failure of the tailboom
and subsequent loss of control of the helicopter.
Since the issuance of that AD, the FAA has determined that one of
the replacement tailboom's P/N should have been stated as P/N 206-033-
004-177 instead of P/N 206-033-004-173.
Since an unsafe condition has been identified that is likely to
exist or develop on other BHTC Model 206L, 206L-1, and 206L-3
helicopters of the same type design, this AD supersedes priority letter
AD 96-14-10 to require, before further flight, and thereafter at
intervals not to exceed 50 hours TIS, a visual inspection of the
tailboom skin in the areas around the nutplates and in the areas of the
tailboom drive shaft cover retention clips for cracks and corrosion
using a 10-power or higher magnifying glass. This inspection interval
will be repeated until the tailboom is replaced by P/N-206-033-004-143
or -177. The actions are required to be accomplished in accordance with
the service bulletin described previously.
Since a situation exists that requires the immediate adoption of
this regulation, it is found that notice and opportunity for prior
public comment hereon are impracticable, and that good cause exists for
making this amendment effective in less than 30 days.
Comments Invited
Although this action is in the form of a final rule that involves
requirements affecting flight safety and, thus, was not preceded by
notice and an opportunity for public comment, comments are invited on
this rule. Interested persons are invited to comment on this rule by
submitting such written data, views, or arguments as they may desire.
Communications should identify the Rules Docket number and be submitted
in triplicate to the address specified under the caption ADDRESSES. All
communications received on or before the closing date for comments will
be considered, and this rule may be amended in light of the comments
received. Factual information that supports the commenter's ideas and
suggestions is extremely helpful in evaluating the effectiveness of the
AD action and determining whether additional rulemaking action would be
needed.
Comments are specifically invited on the overall regulatory,
economic, environmental, and energy aspects of the rule that might
suggest a need to modify the rule. All comments submitted will be
available, both before and after the closing date for comments, in the
Rules Docket for examination by interested persons. A report that
summarizes each FAA-public contact concerned with the substance of this
AD will be filed in the Rules Docket.
Commenters wishing the FAA to acknowledge receipt of their comments
submitted in response to this rule must submit a self-addressed,
stamped postcard on which the following statement is made: ``Comments
to Docket No. 96-SW-13-AD.'' The postcard will be date stamped and
returned to the commenter.
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.
The FAA has determined that this regulation is an emergency
regulation that must be issued immediately to correct an unsafe
condition in aircraft, and that it is not a ``significant regulatory
action'' under Executive Order 12866. It has been determined further
that this action involves an emergency regulation under DOT Regulatory
Policies and Procedures (44 FR 11034, February 26, 1979). If it is
determined that this emergency regulation otherwise would be
significant under DOT Regulatory Policies and Procedures, a final
regulatory evaluation will be prepared and placed in the Rules Docket.
A copy of it, if filed, 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), 40113, 44701.
Sec. 39.13 [Amended]
2. Section 39.13 is amended by adding a new airworthiness directive
(AD), Amendment 39-9729, to read as follows:
AD 96-18-05 Bell Helicopter Textron, a Division of Textron Canada
Ltd.: Amendment 39-9729. Docket No. 96-SW-13-AD. Supersedes priority
letter AD 96-14-10.
Applicability: Model 206L, 206L-1, and 206L-3 helicopters, with
tailboom, part number (P/N) 206-033-004-3, -11, -45, or -103
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 (c) 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 prevent failure of the tailboom and subsequent loss of
control of the helicopter, accomplish the following:
(a) Before further flight, and thereafter at intervals not to
exceed 50 hours time-in-service (TIS), using a 10-power or higher
magnifying glass, inspect the tailboom for cracks or corrosion.
Perform this inspection in accordance with the inspection procedures
stated in the Accomplishment Instructions, Part II or Part III, as
applicable, of Bell Helicopter Textron Inc. Alert Service Bulletin
206L-87-47, Revision C, dated October 23, 1989. If a crack or
corrosion is detected that is beyond the limits prescribed by the
applicable maintenance manual, remove the tailboom and replace it
with an airworthy tailboom.
(b) Replacement of the tailboom with tailboom, P/N 206-033-004-
143 or -177, constitutes terminating action for the requirements of
this AD.
(c) 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 2: Information concerning the existence of approved
alternative methods of compliance with this AD, if any, may be
obtained from the Rotorcraft Certification Office.
(d) Special flight permits will not be issued.
(e) The inspections and replacement shall be done in accordance
with Bell Helicopter
[[Page 45878]]
Textron Inc. Alert Service Bulletin 206L-87-47, Revision C, dated
October 23, 1989. This incorporation by reference was approved by
the Director of the Federal Register in accordance with 5 U.S.C.
552(a) and 1 CFR part 51. Copies may be obtained from Bell
Helicopter Textron Canada, A Division of Textron Canada Ltd., 12,800
rue de L'Avenir, Mirabel, Quebec, Canada, JON 1LO. 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.
(f) This amendment becomes effective on September 16, 1996.
Issued in Fort Worth, Texas, on August 22, 1996.
Daniel P. Salvano,
Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. 96-22141 Filed 8-29-96; 8:45 am]
BILLING CODE 4910-13-U