[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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