[Federal Register Volume 64, Number 95 (Tuesday, May 18, 1999)]
[Rules and Regulations]
[Pages 26839-26841]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 99-12416]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 99-SW-03-AD; Amendment 39-11174; AD 99-11-03]
RIN 2120-AA64
Airworthiness Directives; Eurocopter France Model SA341G and
SA342J
AGENCY: Federal Aviation Administration, DOT.
ACTION: Final rule; request for comments.
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SUMMARY: This amendment adopts a new airworthiness directive (AD),
applicable to Eurocopter France Model SA341G and SA342J helicopters.
This action requires, before further flight, visually inspecting the
external body of each main rotor head pitch-change rod (rod) for
corrosion. If external corrosion is found, this action also requires a
visual inspection of the inside of the body of that rod for corrosion.
A rod with external corrosion that exceeds the repair criteria or a rod
with any internal corrosion must be replaced with an airworthy rod.
This amendment is prompted by the report of a deep internal corrosion
fault in a rod found by a military helicopter operator performing a
daily inspection. This condition, if not corrected, could result in
failure of a rod and subsequent loss of control of the helicopter.
DATES: Effective June 2, 1999.
Comments for inclusion in the Rules Docket must be received on or
before July 19, 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-03-AD, 2601 Meacham Blvd., Room 663,
Fort Worth, Texas 76137.
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, recently notified the
FAA that an unsafe condition may exist on Eurocopter France Model
SA341G and SA342J helicopters. The DGAC advises of the discovery of
corrosion affecting a rod, which could lead to the failure of the rod
and subsequent loss of control of the helicopter.
Eurocopter France issued Telex No. 00079, dated December 23, 1998,
which specifies inspecting the body of each rod for stains, paint
discoloration, and blistering, particularly on the lower straight
section of the rod body. If any of these conditions are found, the
telex specifies removal of the rod and an internal check of the body
and its lower end fitting. The DGAC issued AD T98-551-039(A), dated
December 31, 1998, to ensure the continued airworthiness of these
helicopters in France.
These helicopter models are manufactured in France and are 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 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 SA341G and SA342J
helicopters of the same type design registered in the United States,
this AD is being issued to prevent the failure of a rod and subsequent
loss of control of the
[[Page 26840]]
helicopter. This AD requires, prior to further flight, visually
inspecting the body of each rod for external corrosion. If external
corrosion is found, this AD requires visually inspecting the inside of
the body of each rod for corrosion. This action also requires
inspecting each rod for internal corrosion prior to 10 hours time-in-
service (TIS) or 7 calendar days, whichever occurs first, unless
previously accomplished. The short compliance time involved is required
because the previously described critical unsafe condition can
adversely affect the controllability of the helicopter. Therefore, this
AD requires, before further flight, inspecting each rod and replacing
any unairworthy rod with an airworthy rod, and this AD must be issued
immediately.
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.
The FAA estimates that 24 helicopters will be affected by this AD,
that it will take approximately 1 work hour to accomplish the external
visual inspection and 2 work hours to accomplish the internal visual
inspection, and that the average labor rate is $60 per work hour.
Required parts will cost approximately $300 per helicopter. Based on
these figures, the total cost impact of the AD on U.S. operators is
estimated to be $11,520 to inspect all helicopters and replace one rod
on each helicopter.
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-03-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, 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
to read as follows:
AD 99-11-03 Eurocopter France: Amendment 39-11174. Docket No. 99-
SW-03-AD.
Applicability: Models SA341G and SA342J, 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 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 prevent failure of the main rotor head pitch change rod
(rod), accomplish the following:
(a) Before further flight, inspect the external body of the rod,
part number 341A31.4163.00, for corrosion.
(1) If external corrosion is found, inspect the inside of the
body of each rod for corrosion.
(2) Replace each rod having external corrosion exceeding the
repair criteria of the repair manual or each rod having internal
corrosion with an airworthy rod.
Note 2: A rod having only external corrosion within the repair
criteria of the repair manual is airworthy when repaired. Any
internal corrosion is unairworthy.
(b) Unless previously accomplished under paragraph (a), inspect
the inside of the body of each rod for corrosion within 10 hours
time-in-service or 7 calendar days, whichever occurs first. If
corrosion is found, replace the rod with an airworthy rod.
Note 3: Eurocopter France Telex No. 00079, dated December 23,
1998, pertains to the subject 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 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 4: Information concerning the existence of approved
alternative methods of compliance with this AD, if any, may be
obtained from the Rotorcraft Standards Staff.
(d) This amendment becomes effective on June 2, 1999.
Note 5: The subject of this AD is addressed in Direction
Generale De L'Aviation Civile,
[[Page 26841]]
France, AD No. T98-551-039(A), dated December 31, 1998.
Issued in Fort Worth, Texas, on May 10, 1999.
Eric Bries,
Acting Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. 99-12416 Filed 5-17-99; 8:45 am]
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