[Federal Register Volume 64, Number 90 (Tuesday, May 11, 1999)]
[Rules and Regulations]
[Pages 25198-25200]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 99-11781]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 99-SW-09-AD; Amendment 39-11168; AD 99-10-15]
RIN 2120-AA64


Airworthiness Directives; Eurocopter France Model AS332L2

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule; request for comments.

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SUMMARY: This amendment adopts a new airworthiness directive (AD) that 
is applicable to AS332L2 helicopters. This action requires inspecting 
each main rotor head drag damper (damper) for a tear, crack, or bonding 
separation in the elastomer and, if necessary, replacing the damper 
with an airworthy damper. This amendment is prompted by a report of 
increased helicopter vibration in flight that was traced to the 
delamination of the elastomer on a damper. This condition, if not 
corrected, could result in failure of a damper and subsequent loss of 
control of the helicopter.

DATES: Effective May 26, 1999.
    Comments for inclusion in the Rules Docket must be received on or 
before July 12, 1999.

ADDRESSES: Submit comments in triplicate to the Federal Aviation 
Administration (FAA), Office of the Regional Counsel, Southwest Region, 
Attention: Rules Docket No. 99-SW-09-AD, 2601 Meacham Blvd, Room 663, 
Fort Worth, Texas. Comments may be inspected at this location between 9 
a.m. and 3 p.m., Monday through Friday, except Federal holidays.

FOR FURTHER INFORMATION CONTACT: Mike Mathias, Aerospace Engineer, FAA, 
Rotorcraft Directorate, Rotorcraft Standards Staff, Fort Worth, Texas 
76193-0111, telephone (817) 222-5123, fax (817) 222-5961.

SUPPLEMENTARY INFORMATION: The Direction Generale De L'Aviation Civile 
(DGAC), the airworthiness authority for France, has notified the FAA 
that an unsafe condition may exist on Eurocopter France Model AS332L2 
helicopters. The DGAC advises that it has received a report of damper 
elastomer impending separation on this model helicopter.
    This helicopter model is manufactured in France and is type 
certificated for operation in the United States under the provisions of 
Sec. 21.29 of the Federal Aviation Regulations (14 CFR 21.29) and the 
applicable bilateral airworthiness agreement. Pursuant to this 
bilateral airworthiness agreement, the DGAC has kept the FAA informed 
of the situation described above. The FAA has examined the findings of 
the DGAC, reviewed all available information, and determined that AD 
action is necessary for products of this type design that are 
certificated for operation in the United States.
    Since an unsafe condition has been identified that is likely to 
exist or develop on other Eurocopter France Model AS332L2 helicopters 
of the same type design registered in the United States, this AD is 
being issued to prevent failure of a damper. This AD requires 
inspecting each damper for a tear, crack, or bonding separation in the 
elastomer and, if necessary, replacing the damper with an airworthy 
damper.
    None of the Model AS332L2 helicopters affected by this action are 
on the U.S. Register. All helicopters included in the applicability of 
this rule are operated by non-U.S. operators under foreign registry; 
therefore, they are not directly affected by this AD action. However, 
the FAA considers that this rule is necessary to ensure that the

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unsafe condition is addressed in the event that any of these subject 
helicopters are imported and placed on the U.S. Register in the future.
    Should an affected helicopter be imported and placed on the U.S. 
Register in the future, it would require approximately \2/3\ of a work 
hour to accomplish each of the inspections initially and to replace 
unairworthy parts at an average labor rate of $60 per work hour. 
Required parts would be approximately $4,000 per helicopter. Based on 
these figures, the total cost impact of the AD is estimated to be 
$4,040 per helicopter.
    Since this AD action does not affect any helicopter that is 
currently on the U.S. Register, it has no adverse economic impact and 
imposes no additional burden on any person. Therefore, notice and 
public procedures hereon are unnecessary and the amendment may be made 
effective in less than 30 days after publication in the Federal 
Register.

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. 99-SW-09-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 notice and prior public comment are 
unnecessary in promulgating this regulation; and, therefore, it can be 
issued immediately to correct an unsafe condition in aircraft since 
none of these model helicopters are registered in the United States. 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, 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) to read as follows:
AD 99-10-15  Eurocopter France: Amendment 39-11168. Docket No. 99-
SW-09-AD.

    Applicability: AS332L2 helicopters, with main rotor head drag 
damper, part number (P/N) 332A311980-02, having elastomeric bearings 
P/N J19084-4, 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 
otherwise 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 request approval for an 
alternative method of compliance in accordance with paragraph (c) of 
this AD. The request should include an assessment of the effect of 
the modification, alteration, or repair on the unsafe condition 
addressed by this AD; and, if the unsafe condition has not been 
eliminated, the request should include specific proposed actions to 
address it.

    Compliance: Required as indicated, unless accomplished 
previously.
    To detect delamination of an elastomeric bearing that could 
result in failure of a main rotor head drag damper (damper) and 
subsequent loss of control of the helicopter, accomplish the 
following:
    (a) Within 10 hours time-in-service (TIS), inspect each damper, 
P/N 332A311980-02, for a tear, crack, or bonding separation in the 
elastomer as follows: (See Figure 1.)
    (1) Separate the elastomer in Area A (outside reinforcement) and 
in area B (inside reinforcement).
    (2) If a tear, crack, or bonding separation is found, replace 
the damper with an airworthy damper.

    Note 2: American Eurocopter Master Servicing Recommendation 
(PRE) 05.99.00, rush revision date-code 97-46, and the Aircraft 
Maintenance Manual Nos. 05.21.00.213 and 05.21.00.213.001 pertain to 
the subject of this AD.

    (b) Thereafter, prior to the first flight of each day or at 
intervals not to exceed 20 hours TIS, whichever occurs first, 
perform the inspection in paragraph (a). If a tear, crack, or 
bonding separation is found in the elastomer, replace the damper 
with an airworthy damper.

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    (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 Standards Staff. 
Operators shall submit their requests through an FAA Principal 
Maintenance Inspector who may concur or comment and then send it to 
the Manager, Rotorcraft Standards Staff.

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

    (d) Special flight permits may be issued in accordance with 
Secs. 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.
    (e) This amendment becomes effective on May 26, 1999.

    Note 4: The subject of this AD is addressed in Direction 
Generale De L'Aviation Civile (France) AD 97-378-009(AB), dated 
December 17, 1997.

    Issued in Fort Worth, Texas, on May 4, 1999.
Henry A. Armstrong,
Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. 99-11781 Filed 5-10-99; 8:45 am]
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