] RIN 212 0-AA64 

Airwor thiness Directives; Eurocopter France Model EC1208 Helicopters 

AGENCY: Federal Aviation Administration, DOT. 

ACTION: Final rule; request for comments . 

SUMMARY: This amendment adopts a new airworthiness directive (AD) for Eurocopter France Model EC1 20B heli copters. Thi s action requires vis ually 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 thi s AD are intended t o prevent a tube failure, loss of engine drive, and a subsequent forced landing. 

DATES: Effective March 20, 2001 . 

Comments for inclusion in the Rul es Docket must be received on or before May 4, 2001. 

AD

DRESSES: Submit comments in tripl icate to the Federal Aviation Administration (FAA), Office of the Regional Counsel, Southwest RegiQ Attention: Rules Docket No. 

200~SW-31-AD, 2601 

Meacham Blvd., Room 663, Fort Worth, Texas 7613 7. You may a lso send comments e lectronically to the Rules Docket at the following address:9-asw-adcomments®faa.qov. 

FOR FURTHER I NFORMATION CONTACT: Paul Madej, Aviation Safety Eng ine~ FAA, Roto rcraft Directorate, Rotorcraft Standards Staff, Fort Worth, Texas 76193-0110, telephone {817) 22~5125, fax (817) 22~5961. 

SUPPLEMENTARY INFORMATION: The Direction Genera le De 

L' Aviation 

v~ {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 ~ lead to a tube failure. 

Eurocopter France has issued Eurocopter Service Bulletin 05003, dated July 20, 2000, which specifies visually checking each tube, P/N C631Al101101, for a crack. 

This helicopter model is manuf actured in France and is type certificated for operation in the United States under the provisionwf 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 exam ~ the findi ngs of the DGAC, r eviewed all available information, and determined that AD action is necessary for products of this type de~ 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 helicopterwf the same type design registered in the United States, this AD is be~ issued to prevent failure of a tube, P/N C631All01101 . This AD 

requ~ visually checking each tube, P/N C631A1101101, for a crack. The short 

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it involves only a visual check for a cracked tube and can be perfonnd 

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 existsdr 

making this amendment effective in l ess than 30 days. 

The FAA estimates that 30 heli copters will be affected by this 

proposed AD, that it will take approximately 2 work hours to check ~ tube, and that the average labor rate is $60 per work hour. A 

replacement tube will cost approximatel y $4020 per helicopter and wDl 

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 submi~ in triplicate to the address specified under the caption ADDRESSES. ]q 

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 . Al l comments submitted will be 

available in the Rules Docket for examination by interested personsA 

report that summarizes each FAApublic 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 sel~ addressed, stamped postcard on which the following statement is made : 

''Comments to Docket No. 200~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, ti 

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 Regulatqr 

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 

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p

d as follaw. 

Authority: 49 U. S.C. 106(g), 40113, 44701. 

Sec . 39.13 (Amended] 

2. Section 39 .13 is amended by adding a new airworthiness direc~ to read as follows : 

2001- 04-12 Eurocopter France: Amendment 3~12131. Docket No. 200~ SW -31-AD . 

Applicability: Model EC120B helicopters, with engine to main 

gearbox (MGB) coupl ing tube assembly (tube), part number C63 1A1101101, installed, certificated i n 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 su

b ject to the requirements of thi s 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 f or an alternative method of compliance in accordance 

wi th paragraph (d ) of this AD. The request should include an assessment of the effect of the modification, alteration, or repair on the unsafe condition addr essed by this AD; and if the unsafe condition has not been eliminated, the request should include s pecific proposed acti ons to address it. 

Compliance: Required as indicated, unless accomplis

hed 

previously . 

To prevent a tube failure, loss of engine drive, and a subsequent forced landing, accomplish the following: (a) Within 5 hours tim~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 t he 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 05003, 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 

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[ [Page 13234) ) 

Issued i n Fort Worth, Texas , on February 20, 2001 . 

Eric Bries, 

Acting Manager, Rotorcraft Directorate, Aircraft Certification 

[FR Doc. 01- 5166 Filed 3-2-01i 8:45 am] 

BILLING CODE 

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