[Federal Register Volume 66, Number 43 (Monday, March 5, 2001)]
[Rules and Regulations]
[Pages 13232-13234]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 01-5166]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2000-SW-31-AD; Amendment 39-12131; AD 2001-04-12]
RIN 2120-AA64


Airworthiness Directives; Eurocopter France Model EC120B 
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) for 
Eurocopter France Model EC120B helicopters. This action requires 
visually checking the engine to main gearbox coupling tube assembly 
(tube) for a crack and replacing any cracked tube. This amendment is 
prompted by a report of a crack detected on a tube. The actions 
specified by this AD are intended to prevent a tube failure, loss of 
engine drive, and a subsequent forced landing.

DATES: Effective March 20, 2001.
    Comments for inclusion in the Rules Docket must be received on or 
before May 4, 2001.

ADDRESSES: Submit comments in triplicate to the Federal Aviation 
Administration (FAA), Office of the Regional Counsel, Southwest Region, 
Attention: Rules Docket No. 2000-SW-31-AD, 2601 Meacham Blvd., Room 
663, Fort Worth, Texas 76137. You may also send comments electronically 
to the Rules Docket at the following address: [email protected].

FOR FURTHER INFORMATION CONTACT: Paul Madej, Aviation Safety Engineer, 
FAA, Rotorcraft Directorate, Rotorcraft Standards Staff, Fort Worth, 
Texas 76193-0110, telephone (817) 222-5125, fax (817) 222-5961.

SUPPLEMENTARY INFORMATION: The Direction Generale De L'Aviation Civile 
(DGAC), the airworthiness authority for France, notified the FAA that 
an unsafe condition may exist on Eurocopter France Model EC120B 
helicopters equipped with tube, part number (P/N) C631A1101101. The 
DGAC advises that a crack was reported on a reinforced tube, which may 
lead to a tube failure.
    Eurocopter France has issued Eurocopter Service Bulletin 05-003, 
dated July 20, 2000, which specifies visually checking each tube, P/N 
C631A1101101, for a crack.
    This helicopter model is manufactured in France and is type 
certificated for operation in the United States under the provisions of 
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 we have identified an unsafe condition that is likely to 
exist or develop on other Eurocopter France Model EC120B helicopters of 
the same type design registered in the United States, this AD is being 
issued to prevent failure of a tube, P/N C631A1101101. This AD requires 
visually checking each tube, P/N C631A1101101, for a crack. The short 
compliance time involved is required because the previously described 
critical unsafe condition can adversely affect the structural integrity 
of the helicopter. Therefore, visually checking each tube, P/N 
C631A1101101, for a crack within the next 5 hours time-in-service (TIS) 
and thereafter at intervals not to exceed 5 hours TIS and replacing

[[Page 13233]]

any cracked tube with an airworthy tube before further flight are 
required, and this AD must be issued immediately.
    The owner/operator (pilot) may perform the visual check required by 
this AD and must enter compliance with paragraph (a) of this AD into 
the aircraft maintenance records in accordance with 14 CFR 43.11 and 
91.417(a)(2)(v). This AD allows a pilot to perform this check because 
it involves only a visual check for a cracked tube and can be performed 
equally well by a pilot or a mechanic.
    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 30 helicopters will be affected by this 
proposed AD, that it will take approximately 2 work hours to check the 
tube, and that the average labor rate is $60 per work hour. A 
replacement tube will cost approximately $4020 per helicopter and will 
require approximately 2 work hours to install. Based on these figures 
and on an assumption of one replacement and 100 checks per year per 
helicopter, the total cost impact of the AD on U.S. operators is 
estimated to be $484,200.

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 dates 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 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 mailed 
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. 2000-SW-31-AD.'' The postcard will be date 
stamped and returned to the commenter.
    The regulations adopted herein will not have a substantial direct 
effect 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, it 
is determined that this final rule does not have federalism 
implications under Executive Order 13132.
    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:

2001-04-12  Eurocopter France: Amendment 39-12131. Docket No. 2000-
SW-31-AD.

    Applicability: Model EC120B helicopters, with engine to main 
gearbox (MGB) coupling tube assembly (tube), part number 
C631A1101101, 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 (d) 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 a tube failure, loss of engine drive, and a 
subsequent forced landing, accomplish the following:
    (a) Within 5 hours time-in-service (TIS) and thereafter at 
intervals not to exceed 5 hours TIS, visually check each affected 
tube for a crack as follows:
    (1) Open the left and right cowlings.
    (2) Check inside the MGB in the area of the tube cylindrical 
casing on either side of the fitting that attaches the tube to the 
MGB.
    (b) Before further flight, replace any cracked tube with an 
airworthy tube.

    Note 2: Eurocopter France Service Bulletin 05-003, dated July 
20, 2000, pertains to the subject of this AD.

    (c) An owner/operator (pilot) holding at least a private pilot 
certificate may perform the visual check required by paragraph (a) 
and must enter compliance with paragraph (a) of this AD into the 
aircraft maintenance records in accordance with 14 CFR 43.11 and 
91.417(a)(2)(v).
    (d) 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, Regulations Group, Rotorcraft 
Directorate, FAA. Operators shall submit their requests through an 
FAA Principal Maintenance Inspector, who may concur or comment and 
then send it to the Manager, Regulations Group.

    Note 3: Information concerning the existence of approved 
alternative methods of compliance with this AD, if any, may be 
obtained from the Regulations Group.

    (e) Special flight permits will not be issued.
    (f) This amendment becomes effective on March 20, 2001.

    Note 4: The subject of this AD is addressed in Direction General 
De L'Aviation Civile (France), AD 2000-176-004(A) R1, dated August 
23, 2000.



[[Page 13234]]


    Issued in Fort Worth, Texas, on February 20, 2001.
Eric Bries,
Acting Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. 01-5166 Filed 3-2-01; 8:45 am]
BILLING CODE 4910-13-U