[Federal Register Volume 64, Number 58 (Friday, March 26, 1999)]
[Rules and Regulations]
[Pages 14585-14588]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 99-7383]



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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 97-SW-42-AD; Amendment 39-11092; AD 99-07-07]
RIN 2120-AA64


Airworthiness Directives; Eurocopter France Model SA 330J 
Helicopters

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 Eurocopter France (Eurocopter) Model SA 330J 
helicopters. This action requires the visual inspection and, if any 
crack is found, replacement of the affected main rotor head sleeve. 
This amendment is prompted by the discovery of a crack through the 
thickness of a lower lug of a blade sleeve. The actions specified by 
the proposed AD are intended to prevent failure of a main rotor head 
sleeve that could result in the loss of a main rotor blade and 
subsequent loss of control of the helicopter.

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

ADDRESSES: Submit comments in triplicate to the Federal Aviation 
Administration (FAA), Office of the Regional Counsel, Southwest Region, 
Attention: Rules Docket No. 97-SW-42-AD, 2601 Meacham Blvd., Room 663, 
Fort Worth, Texas 76137.

FOR FURTHER INFORMATION CONTACT: Mike Mathias, Aerospace Engineer, FAA, 
Rotorcraft Directorate, ASW-111, 2601 Meacham Blvd, Fort Worth, Texas 
76137, 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 Model SA 330J 
helicopters. The DGAC advises of the discovery of a crack in the lower 
lug on the trailing edge of an SA 330J blade sleeve.
    Eurocopter has issued Eurocopter France Service Bulletin 05.80 R1, 
dated February 14, 1995 (SB), which specifies the visual inspection and 
replacement procedures of each main rotor head sleeve lug, Part Number 
(P/N) 330A31.1376.00 through .05 or 330A31.1376.12 through .17 in 
accordance with paragraph C(1) and C(2) of the SB. The DGAC classified 
this SB as mandatory and issued DGAC AD 91-021-064(B)R1, dated March 
15, 1995, to ensure the continued airworthiness of these helicopters in 
France.
    This helicopter model is manufactured in France and is type 
certificated for operation in the United States under the provisions of 
section 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 Model SA 330J helicopters of the 
same type design registered in the United States, the proposed AD would 
require the visual inspection of each main rotor head sleeve lug, P/N 
330A31.1376.00 through .05 or 330A31.1376.12 through .17.
    None of the Eurocopter Model SA 330J helicopters affected by this 
action are on the U.S. Register. All helicopters included in the 
applicability of this rule are currently operated by non-U.S. operators 
under foreign registry; therefore, they are not directly affected by 
this AD action. However, the FAA considers this rule necessary to 
ensure that the 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.
    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, it is found that 
notice and opportunity for prior public comment hereon are unnecessary, 
and that good cause exists for making this amendment effective in less 
than 30 days.
    Should an affected helicopter be imported and placed on the U.S. 
Register, it will require approximately 1 work hour to accomplish each 
required inspection, and 1 work hour to replace a sleeve, at an average 
labor rate of $60 per work hour. Each main rotor head sleeve costs 
$19,100. Based on these figures, the cost impact of this AD will be 
$19,220 for inspecting and replacing one blade sleeve.

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. 97-SW-42-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 public comment are 
unnecessary in promulgating this regulation, that the regulation can be 
issued immediately to correct an unsafe condition in aircraft since 
none of these model helicopters are registered in the United States, 
and that it is not a ``significant regulatory action'' under Executive 
Order 12866. It has been determined further that this

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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 99-07-07  Eurocopter France: Amendment 39-11092, Docket No. 97-
SW-42-AD.

    Applicability: Eurocopter France (Eurocopter) Model SA 330J 
helicopters, with main rotor head sleeves part number (P/N) 
330A31.1376.00 through .05 or 30A31.1376.12 through .17 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 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 within 15 calendar days, unless previously 
accomplished, and thereafter at intervals not to exceed 50 hours 
time-in-service.
    To prevent failure of a main rotor head sleeve (sleeve), P/N 
330A31.1376.00 through .05 or 330A31.1376.12 through .17, that could 
result in loss of a main rotor blade and subsequent loss of control 
of the helicopter, accomplish the following:
    (a) Visually inspect each main rotor head sleeve lug (lug), 
without removing the main rotor blades, for cracks in the area 
indicated in Figure 1.

    Note 2: Eurocopter France Service Bulletin 05.80R1, dated 
February 14, 1995, pertains to the subject of this AD.

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    (b) If any crack is found in a lug, prior to further flight, 
replace the affected sleeve with an airworthy sleeve.
    (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, 
Rotorcraft Directorate, FAA. Operators shall submit their requests 
through an FAA Principal 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 will not be issued.
    (e) This amendment becomes effective on April 12, 1999.

    Note 4: The subject of this AD is addressed in Direction 
Generale De L'Aviation Civile (France) AD 91-021-064(B)R1, dated 
March 15, 1995.

    Issued in Fort Worth, Texas, on March 18, 1999.
Eric Bries,
Acting Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. 99-7383 Filed 3-25-99; 8:45 am]
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