[Federal Register Volume 65, Number 129 (Wednesday, July 5, 2000)]
[Rules and Regulations]
[Pages 41326-41328]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 00-16781]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 98-SW-74-AD; Amendment 39-11807; AD 2000-13-08]
RIN 2120-AA64


Airworthiness Directives; Eurocopter Deutschland GmbH Model EC 
135 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 GmbH (ECD) Model EC 135 
helicopters. That AD requires conducting a tail rotor drive shaft 
vibration survey (survey), installing a Fenestron Shaft Retrofit Kit, 
inspecting each tail rotor drive shaft bearing (bearing) attaching lock 
plate for bent-open tabs and broken or missing slippage marks, and 
visually inspecting each bearing support for cracks. This AD requires 
conducting the survey and installing the Fenestron Shaft Retrofit Kit. 
This AD also requires installing double bearing supports and struts, 
revising the required compliance time for the repetitive inspections of 
the bearing attach hardware and supports, and removing the requirement 
to contact the FAA if a lock plate tab is bent open or if slippage 
marks are broken or missing. This amendment is prompted by continued 
reports of misaligned or cracked bearing supports and loose bearing 
attachment bolts. The actions specified by this AD are intended to 
prevent loss of drive to the tail rotor and subsequent loss of control 
of the helicopter.

DATES: Effective August 9, 2000.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of August 9, 2000.

ADDRESSES: The service information referenced in this AD may be 
obtained from American Eurocopter Corporation, 2701 Forum Drive, Grand 
Prairie, Texas 75053-4005, telephone (972) 641-3460, fax (972) 641-
3527. This information may be examined at the FAA, Office of the 
Regional Counsel, Southwest Region, 2601 Meacham Blvd., Room 663, Fort 
Worth, Texas; or at the Office of the Federal Register, 800 North 
Capitol Street, NW., suite 700, Washington, DC.

FOR FURTHER INFORMATION CONTACT: Uday Garadi, Aviation Safety Engineer, 
FAA, Rotorcraft Directorate, Rotorcraft Standards Staff, Fort Worth, 
Texas 76193-0110, telephone (817) 222-5123, fax (817) 222-5961.

SUPPLEMENTARY INFORMATION: A proposal to amend part 39 of the Federal 
Aviation Regulations (14 CFR part 39) by superseding AD 98-15-25, 
Amendment 39-10866 (63 FR 59206, November 3, 1998), that applies to ECD 
Model EC 135 helicopters, was published in the Federal Register on 
April 6, 2000 (65 FR 18010). That action proposed to require the 
following:
    <bullet> Conducting a vibration survey and installing the Fenestron 
Shaft Retrofit Kit L535M3002 882;
    <bullet> Installing double bearing supports and struts;
    <bullet> Inspecting and, if necessary, replacing bearing attach 
hardware; and
    <bullet> Increasing the repetitive inspection interval for the 
bearing supports and attach hardware to 50 hours time-in-service (TIS).
    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

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public interest require the adoption of the rule as proposed.
    The FAA estimates that 16 helicopters of U.S. registry will be 
affected by this AD. The 50-hour inspection will take approximately 2 
work hours to complete. The average labor rate is $60 per work hour. 
ECD has stated in its ASB's that the baseline vibration measurements 
and initial installation of all new parts will be provided at no charge 
to the owner/operator. Assuming the helicopters are operated 900 hours 
TIS per year, the total cost impact of this AD on U.S. operators is 
estimated to be $34,560.
    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 location provided under the caption 
ADDRESSES.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Incorporation by 
reference, 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 removing Amendment 39-10866, and by 
adding a new airworthiness directive (AD), Amendment 39-11807, to read 
as follows:

2000-13-08  Eurocopter Deutschland GmbH: Amendment 39-11807. Docket 
No. 98-SW-74-AD. Supersedes AD 98-15-25, Amendment 39-10866, Docket 
No. 98-SW-35-AD.

    Applicability: Model EC 135 helicopters, 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 loss of drive to the tail rotor and subsequent loss 
of control of the helicopter, accomplish the following:
    (a) Before further flight, conduct a tail rotor drive shaft 
vibration survey and install a Fenestron Shaft Retrofit Kit 
L535M3002 882 in accordance with Eurocopter Deutschland GmbH Alert 
Service Bulletin (ASB) EC 135-53A-005, Revision 3, dated September 
2, 1998.
    (b) Before further flight, install double bearing supports for 
the tail rotor driveshaft and tail boom struts in accordance with 
ASB EC 135-53A-004, dated August 14, 1998.

    Note 2: ASB EC 135-53A-002, Revision 2, dated September 2, 1998, 
pertains to the subject of this AD.

    (c) Before further flight and thereafter at intervals not to 
exceed 50 hours time-in-service, perform the following:
    (1) Clean each tail rotor drive shaft bearing support. Using a 
6-power or higher magnifying glass and a bright light, visually 
inspect the attach lugs of the bearing supports B and C (shown in 
Figure 1) for cracks, particularly in the area extending from the 
bend radius to the attaching screws and rivets connecting the 
bearing supports to the tail boom. Before further flight, replace 
each cracked bearing support with an airworthy bearing support.
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    (2) Inspect each bearing attach hardware lock plate for bent-
open tabs and slippage marks for attach hardware looseness or 
rotation. Before further flight, replace any loose bearing attach 
hardware (including lock plates found bent or open due to bolt 
rotation) with airworthy hardware.
    (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 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.
    (f) The modifications shall be done in accordance with 
Eurocopter Deutschland GmbH Alert Service Bulletin EC 135-53A-005, 
Revision 3, dated September 2, 1998, and Eurocopter Deutschland GmbH 
Alert Service Bulletin EC 135-53A-004, dated August 14, 1998. This 
incorporation by reference was approved by the Director of the 
Federal Register in accordance with 5 U.S.C. 552(a) and 1 CFR part 
51. Copies may be obtained from American Eurocopter Corporation, 
2701 Forum Drive, Grand Prairie, Texas 75053-4005, telephone (972) 
641-3460, fax (972) 641-3527. Copies may be inspected at the FAA, 
Office of the Regional Counsel, Southwest Region, 2601 Meacham 
Blvd., Room 663, Fort Worth, Texas; or at the Office of the Federal 
Register, 800 North Capitol Street, NW., suite 700, Washington, DC.
    (g) This amendment becomes effective on August 9, 2000.

    Note 4: The subject of this AD is addressed in Luftfahrt-
Bundesamt (Federal Republic of Germany) AD's 1998-033/7 and 1998-
389, both dated September 14, 1998.


    Issued in Fort Worth, Texas, on June 26, 2000.
Eric Bries,
Acting Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. 00-16781 Filed 7-3-00; 8:45 am]
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