[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]
BILLING CODE 4910-13-U