[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