Airworthiness Directives; Eurocopter Deutschland Model EC135 P1 and T1 Helicopters

[Federal Register Volume 65, Number 247 (Friday, December 22, 2000)]
[Rules and Regulations]
[Pages 80741-80742]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 00-32553]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2000-SW-19-AD; Amendment 39-12049; AD 2000-26-02]
RIN 2120-AA64


Airworthiness Directives; Eurocopter Deutschland Model EC135 P1 
and T1 Helicopters

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule.

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SUMMARY: This amendment supersedes an existing airworthiness directive 
(AD) that applies to Eurocopter Deutschland Model EC135 P1 and T1 
helicopters. That AD 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 amendment requires 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 amendment is 
prompted by additional reports of cracked stator blades of the tail 
rotor. The actions specified by this AD are intended to prevent failure 
of the tail rotor and subsequent loss of control of the helicopter.

EFFECTIVE DATE: January 26, 2001.

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: A proposal to amend part 39 of the Federal 
Aviation Regulations (14 CFR part 39) by superseding AD 97-20-13, 
Amendment 39-10240 (62 FR 65198), which is applicable to Eurocopter 
Deutschland Model EC135 P1 and T1 helicopters, was published in the 
Federal Register on September 18, 2000 (65 FR 56276). That action 
proposed 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. That action 
also proposed limiting the applicability to certain serial numbered 
tail booms.
    Interested persons have been afforded an opportunity to participate 
in the making of this amendment. No comments were received on the 
proposal or the FAA's determination of the cost to the public. The FAA 
has determined that air safety and the public interest require the 
adoption of the rule as proposed.
    The FAA estimates that 25 helicopters of U.S. registry will be 
affected by this AD, that it will take approximately 12 work hours per 
helicopter to accomplish the required 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 is no cost impact from the AD on U.S. 
operators.
    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.
    For the reasons discussed above, I certify that this action (1) is 
not a ``significant regulatory action'' under Executive Order 12866; 
(2) is not a ``significant rule'' under DOT Regulatory Policies and 
Procedures (44 FR 11034, February 26, 1979); and (3) 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 final evaluation has been prepared for this action 
and it is contained in the Rules Docket. A copy of it may be obtained 
from the Rules Docket at the FAA, Office of the Regional Counsel, 
Southwest Region, 2601 Meacham Blvd., Room 663, Fort Worth, Texas.

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.

[[Page 80742]]

Sec. 39.13  [Amended]

    2. Section 39.13 is amended by removing Amendment 39-10240 (62 FR 
65198, December 11, 1997), and by adding a new airworthiness directive 
(AD), Amendment 39-12049, to read as follows:

2000-26-02  Eurocopter Deutschland: Amendment 39-12049. 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 
sections 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 January 26, 2001.


    Issued in Fort Worth, Texas, on December 11, 2000.
Henry A. Armstrong,
Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. 00-32553 Filed 12-21-00; 8:45 am]
BILLING CODE 4910-13-P

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