AD Amdt-39-11181

[Federal Register Volume 64, Number 101 (Wednesday, May 26, 1999)]
[Rules and Regulations]
[Pages 28355-28357]
From the Federal Register Online via the Government Publishing Office [<a href="http://www.gpo.gov">www.gpo.gov</a>]
[FR Doc No: 99-13321]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 98-SW-61-AD; Amendment 39-11181; AD 99-11-10]
RIN 2120-AA64


Airworthiness Directives; Eurocopter France Model AS 332L2 
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 Model AS 332L2 helicopters with a 
certain power-loss printed circuit board (PCB) installed. This action 
requires replacing that power-loss PCB with an airworthy power-loss 
PCB. This amendment is prompted by malfunctions discovered during 
environmental testing of the power-loss PCB conducted by the 
manufacturer. The actions specified in this AD are intended to prevent 
incorrect engine status indications, random activation of the maximum 
rotor revolutions-per-minute (RPM) alarm, and failure to reset the One-
Engine Inoperative (OEI) logic after an actual loss of power from one 
engine.

DATES: Effective June 10, 1999.
    Comments for inclusion in the Rules Docket must be received on or 
before July 26, 1999.

ADDRESSES: Submit comments in triplicate to the Federal Aviation 
Administration (FAA), Office of the Regional Counsel, Southwest Region, 
Attention: Rules Docket No. 98-SW-61-AD, 2601 Meacham Blvd., Room 663, 
Fort Worth, Texas 76137.

FOR FURTHER INFORMATION CONTACT: Shep Blackman, Aerospace Engineer, 
FAA, Rotorcraft Directorate, Rotorcraft Standards Staff, 2601 Meacham 
Blvd., Fort Worth, Texas 76137, telephone (817) 222-5296, fax (817) 
222-5961.

SUPPLEMENTARY INFORMATION: The Direction Generale De L'Aviation Civile 
(DGAC), which is the airworthiness authority for France, has notified 
the FAA that an unsafe condition may exist on Eurocopter France Model 
AS 332L2 helicopters. The DGAC advises that design anomalies of the 
power-loss PCB can lead to non-resetting of the OEI logic after failure 
of one engine.
    Eurocopter France has issued Eurocopter Service Bulletin 31.00.11, 
dated September 8, 1998, which specifies replacing the power-loss PCB, 
part number (P/N) SE01958 (Eurocopter

[[Page 28356]]

France P/N 704A47720091) Amendment C or D, with an airworthy power-loss 
PCB, P/N SE01973 (Eurocopter France P/N 704A47720109). The manufacturer 
advises that design anomalies of the power-loss PCB can lead to 
incorrect engine status indications, random activation of the maximum 
rotor RPM audio alarm, and non-resetting of the OEI logic after failure 
of one engine. The DGAC classified this service bulletin as mandatory 
and issued AD 98-290-011(A), dated August 12, 1998, in order to assure 
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 France Model AS 332L2 helicopters 
of the same type design registered in the United States, this AD is 
being issued to prevent incorrect engine status indications, random 
activation of the maximum rotor RPM audio alarm, and failure to reset 
the OEI logic after an actual loss of power from one engine. This AD 
requires replacement of the power-loss PCB, P/N SE01958 (704A47720091) 
Amendment C or D, with an airworthy power-loss PCB, P/N SE01973 
(704A47720109).
    None of the Model AS 332L2 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, so they are not directly affected by this AD action. However, 
the FAA considers that this rule is necessary to ensure 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.

Cost Impact

    If an affected helicopter is imported and placed on the U.S. 
Register in the future, it would require approximately 3 work hours to 
accomplish the replacement, at an average labor rate of $60 per work 
hour. The manufacturer has stated that there would be no charge for 
parts. Based on these figures, the cost impact of this AD would be $180 
per helicopter.
    Since this AD action does not affect any helicopter that is 
currently on the U.S. Register, and it has no adverse economic impact 
and imposes no additional burden on any person, notice and public 
procedures 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 was not preceded by notice and 
an opportunity for public comment, comments are invited on this rule. 
Interested persons are invited to comment 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. 98-SW-61-AD.'' The postcard will be date stamped and 
returned to the commenter.

Regulatory Impact

    The regulations adopted in this amendment 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's Determination

    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, 
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 99-11-10  Eurocopter France: Amendment 39-11181. Docket No. 98-
SW-61-AD.

    Applicability: Model AS 332L2 helicopters, with power-loss 
printed circuit board (PCB), part number (P/N) SE01958 (Eurocopter 
France P/N 704A47720091) Amendment C or D, 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

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owner/operator must request approval for an alternative method of 
compliance in accordance with paragraph (b) 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 incorrect engine status indications, random 
activation of the maximum rotor revolutions-per-minute (RPM) audio 
alarm, and failure to reset the One Engine Inoperative (OEI) logic 
after an actual loss of power from one engine, accomplish the 
following:
    (a) Before further flight, remove the power-loss PCB, P/N 
SE01958 (Eurocopter France P/N 704A47720091) Amendment C or D, and 
replace it with an airworthy power-loss PCB, P/N SE01973 (Eurocopter 
France P/N 704A47720109).
    (b) 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, FAA, Rotorcraft Standards Staff, 
Rotorcraft Directorate. Operators shall submit their requests 
through a FAA Principal Maintenance Inspector, who may concur or 
comment and then send it to the Manager, Rotorcraft Standards Staff.

    Note 2: You may obtain information concerning the existence of 
approved alternative methods of compliance with this AD from the 
Rotorcraft Standards Staff.

    (c) 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.
    (d) This amendment becomes effective on June 10, 1999.

    Note 3: The subject of this AD is addressed in Direction 
Generale De l'Aviation Civile (France) AD 98-290-011(A), dated 
August 12, 1998.

    Issued in Fort Worth, Texas, on May 18, 1999.
Mark R. Schilling,
Acting Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. 99-13321 Filed 5-25-99; 8:45 am]
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