[Federal Register Volume 65, Number 181 (Monday, September 18, 2000)]
[Proposed Rules]
[Pages 56276-56277]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 00-23863]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2000-SW-19-AD]


Airworthiness Directives; Eurocopter Deutschland Model EC135 P1 
and T1 Helicopters

AGENCY: Federal Aviation Administration, DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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SUMMARY: This document proposes the supersedure of an existing 
airworthiness directive (AD) for Eurocopter Deutschland Model EC135 P1 
and T1 helicopters that currently requires visual and dye-penetrant 
inspections for a cracked stator blade of the fenestron tail rotor 
(tail rotor). That AD also requires either stop drilling a cracked 
blade or, as necessary, replacing an unairworthy stator blade with an 
airworthy stator blade. This action would require replacing the 
existing stator blade assembly with a new stator blade assembly that 
incorporates a reinforced base and modified riveting and limits the 
applicability to certain serial numbered tail booms. This proposal is 
prompted by additional reports of cracked stator blades of the tail 
rotor. The actions specified by the proposed AD are intended to prevent 
failure of the tail rotor and subsequent loss of control of the 
helicopter.

DATES: Comments must be received on or before November 17, 2000.

ADDRESSES: Submit comments in triplicate to the Federal Aviation 
Administration (FAA), Office of the Regional Counsel, Southwest Region, 
Attention: Rules Docket No. 2000-SW-19-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]. 
Comments may be inspected at the Office of the Federal Register between 
9 a.m. and 3 p.m., Monday through Friday, except Federal holidays.

FOR FURTHER INFORMATION CONTACT: Richard Monschke, Aviation Safety 
Engineer, FAA, Rotorcraft Directorate, Rotorcraft Standards Staff, 2601 
Meacham Blvd., Fort Worth, Texas 76137, telephone (817) 222-5116, fax 
(817) 222-5961.

SUPPLEMENTARY INFORMATION:

Comments Invited

    Interested persons are invited to participate in the making of the

[[Page 56277]]

proposed 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 above. All 
communications received on or before the closing date for comments, 
specified above, will be considered before taking action on the 
proposed rule. The proposals contained in this notice may be changed in 
light of the comments received.
    Comments are specifically invited on the overall regulatory, 
economic, environmental, and energy aspects of the proposed rule. All 
comments submitted will be available in the Rules Docket for 
examination by interested persons. A report summarizing each FAA-public 
contact concerned with the substance of this proposal will be filed in 
the Rules Docket.
    Commenters wishing the FAA to acknowledge receipt of their mailed 
comments submitted in response to this notice must submit a self-
addressed, stamped postcard on which the following statement is made: 
``Comments to Docket No. 2000-SW-19-AD.'' The postcard will be date 
stamped and returned to the commenter.

Availability of NPRMs

    Any person may obtain a copy of this NPRM by submitting a request 
to the FAA, Office of the Regional Counsel, Southwest Region, 
Attention: Rules Docket No. 2000-SW-19-AD, 2601 Meacham Blvd., Room 
663, Fort Worth, Texas 76137.

Discussion

    On December 2, 1997, the FAA issued AD 97-20-13, Amendment 39-
10240; (62 FR 65198, dated December 11, 1997), to require visual and 
dye-penetrant inspections for a cracked stator blade of the tail rotor. 
That AD also requires that a cracked stator blade be stop-drilled or 
replaced with an airworthy stator blade if the crack is 15mm or longer 
or if more than three stator blades are affected. That action was 
prompted by the discovery of cracks on the stator blades of the 
fenestron tail rotor. The requirements of that AD are intended to 
prevent failure of the tail rotor and subsequent loss of control of the 
helicopter.
    Since the issuance of that AD, additional cracks have been reported 
on the stator blades of the fenestron tail rotor. The manufacturer has 
developed a stator blade assembly that incorporates a reinforced base 
and modified riveting.
    We have identified an unsafe condition that is likely to exist or 
develop on other Eurocopter Deutschland Model EC135 P1 and T1 
helicopters of the same type design. The proposed AD would supersede AD 
97-20-13 to require replacing any stator blade assembly, part number 
(P/N) L 535A4201 052, with a stator blade assembly, P/N L 535A4201 053, 
that incorporates a reinforced base and modified riveting. The proposed 
AD would also limit the applicability to certain serial numbered tail 
booms.
    The FAA estimates that 25 helicopters of U.S. registry would be 
affected by this proposed AD, that it would take approximately 12 work 
hours per helicopter to accomplish the proposed actions, and that the 
average labor rate is $60 per work hour. The manufacturer states in its 
service bulletin that parts and labor will be furnished at no cost. 
Based on that information, there would be no cost impact from the 
proposed AD on U.S. operators.
    The regulations proposed herein would 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 proposal would not have federalism implications 
under Executive Order 13132.
    For the reasons discussed above, I certify that this proposed 
regulation (1) is not a ``significant regulatory action'' under 
Executive Order 12866; (2) is not a ``significant rule'' under the DOT 
Regulatory Policies and Procedures (44 FR 11034, February 26, 1979); 
and (3) if promulgated, will not have a significant economic impact, 
positive or negative, on a substantial number of small entities under 
the criteria of the Regulatory Flexibility Act. A copy of the draft 
regulatory evaluation prepared for this action is contained in the 
Rules Docket. A copy of it may be obtained by contacting 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.

The Proposed Amendment

    Accordingly, pursuant to the authority delegated to me by the 
Administrator, the Federal Aviation Administration proposes to amend 
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 removing Amendment 39-10240 (62 FR 
65198, dated December 11, 1997), and by adding a new airworthiness 
directive (AD) to read as follows:

Eurocopter Deutschland: Docket No. 2000-SW-19-AD. Supersedes AD 97-
20-13, Amendment 39-10240, Docket No. 97-SW-46-AD.

    Applicability: Model EC135 P1 and T1 helicopters, with tail boom 
serial number EVL 001 through EVL 045, 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 (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 within 90 days, unless accomplished 
previously.
    To prevent failure of the stator blades of the fenestron tail 
rotor and subsequent loss of control of the helicopter, accomplish 
the following:
    (a) Replace stator blade assembly, part number (P/N) L 535A4201 
052, with stator blade assembly, P/N L 535A4201 053.
    (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, Regulations Group, Rotorcraft 
Directorate. 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 2: Information concerning the existence of approved 
alternative methods of compliance with this AD, if any, may be 
obtained from the Regulations Group.

    (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.

    Issued in Fort Worth, Texas, on September 11, 2000.
Eric Bries,
Acting Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. 00-23863 Filed 9-15-00; 8:45 am]
BILLING CODE 4910-13-U