Airworthiness Directives; Eurocopter Deutschland GmbH Model EC135 P1, P2, T1, and T2 Helicopters

[Federal Register Volume 68, Number 197 (Friday, October 10, 2003)]
[Rules and Regulations]
[Pages 58581-58582]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 03-25592]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2003-SW-08-AD; Amendment 39-13329; AD 2003-20-11]
RIN 2120-AA64


Airworthiness Directives; Eurocopter Deutschland GmbH Model EC135 
P1, P2, T1, and T2 Helicopters

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule.

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SUMMARY: This amendment supersedes an existing airworthiness directive 
(AD) for Eurocopter Deutschland GmbH (ECD) Model EC135 P1 and EC135 T1 
helicopters. That AD currently requires adding the AD or a statement to 
the Rotorcraft Flight Manual (RFM) informing the pilot to reduce power 
and land as soon as practicable if a thump-like sound followed by 
unusual vibration occurs during flight. That AD also requires visually 
inspecting the main rotor drive torque strut assembly (strut) for a 
crack or a break, recording the inspections in the historical or 
equivalent record, and re-marking and relocating the strut, as 
appropriate, and replacing any unairworthy strut with an airworthy 
strut. Also, that AD establishes life limits for certain struts and 
revises the life limit for other struts. This amendment retains the 
same requirements but adds the ECD Model EC135 P2 and EC135 T2 
helicopters to the applicability and requires replacing certain life-
limited struts with titanium struts. This amendment is prompted by the 
manufacture of a titanium strut that provides a permanent correction to 
the unsafe condition that led to limiting the life of other struts that 
have failed. The actions specified by this AD are intended to prevent 
failure of a strut and subsequent loss of control of the helicopter.

DATES: Effective November 14, 2003.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of November 14, 2003.

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: Richard Monschke, Aviation Safety 
Engineer, FAA, Rotorcraft Directorate, Rotorcraft Standards Staff, Fort 
Worth, Texas 76193-0110, telephone (817) 222-5116, fax (817) 222-5961.

SUPPLEMENTARY INFORMATION: A proposal to amend 14 CFR part 39 by 
superseding AD 2001-18-13, Amendment 39-12439 (66 FR 47878, September 
14, 2001), for the specified model helicopters was published in the 
Federal Register on June 5, 2003 (68 FR 33663). The action proposed 
retaining the requirements to add the AD or a statement to the 
Rotorcraft Flight Manual (RFM) informing the pilot to reduce power and 
land as soon as practicable if a thump-like sound followed by unusual 
vibration occurs during flight. Also, the action proposed retaining the 
requirements to visually inspect each strut for a crack or a break; to 
record the inspections in the historical or equivalent record; to re-
mark and relocate the strut, as appropriate; to replace any unairworthy 
strut with an airworthy strut; and to establish or revise life limits 
for certain struts. In addition to the requirements in the current AD, 
that action proposed adding the ECD Model EC135 P2 and EC135 T2 
helicopters to the applicability and replacing certain life-limited 
struts with titanium struts.
    The Luftfahrt-Bundesamt (LBA), the airworthiness authority for the 
Federal Republic of Germany, advises that struts, (P/N) L633M1001 103 
and L633M1001 105, should not be used beyond December 31, 2004. The LBA 
advises replacing those struts with torque struts, P/N L633M1001 104, 
after January 1, 2005.
    ECD has issued Alert Service Bulletin EC135-63A-002, Revision 2, 
dated June 26, 2002 (ASB), which specifies inspecting for a crack, 
marking strut locations and serial numbers, and transferring the 
location side of the torque struts or replacing each strut, P/N 
L633M1001 103 or L633M10001 105, with a torque strut, P/N L633M1001 
104, that is anodized and not coated with paint, which have no life 
limit. The LBA classified this ASB as mandatory and issued AD No. 2001-
107/2, dated September 19, 2002, to ensure the continued airworthiness 
of these helicopters in the Federal Republic of Germany.
    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.
    On July 10, 2002, the FAA issued a new version of 14 CFR part 39 
(67 FR 47997, July 22, 2002), which governs FAA's AD system. This 
regulation now includes material that relates to special flight 
permits, alternative methods of compliance, and altered products. This 
material previously was included in each individual AD. Since this 
material is included in 14 CFR part 39, we have not included it in this 
AD action.
    The FAA estimates that this AD will affect 50 helicopters of U.S. 
registry. The AD will take approximately \l/2\ work hour for the 
flashlight and mirror inspection; 2.5 work hours to remark, relocate, 
and inspect with a magnifying glass; and 1 hour to replace both struts.

[[Page 58582]]

The average labor rate is $60 per work hour. Required parts will cost 
approximately $9,696 per helicopter. Based on these figures, we 
estimate the total cost impact of the proposed AD on U.S. operators to 
be $496,800.
    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

0
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

0
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]

0
2. Section 39.13 is amended by removing Amendment 39-12439 (66 FR 
47878, September 14, 2001), and by adding a new airworthiness directive 
(AD), Amendment 39-13329 to read as follows:

2003-20-11 Eurocopter Deutschland GmbH: Amendment 39-13329, Docket 
No. 2003-SW-08-AD. Supersedes AD 2001-18-13, Amendment 39-12439, 
Docket No. 2001-SW-19-AD.

    Applicability: Model EC135 P1, P2, T1, and T2 helicopters, with 
main rotor drive torque strut assembly (strut), part number (P/N) 
L633M1001 103 or L633M1001 105, installed, certificated in any 
category.
    Compliance: Required as indicated, unless accomplished 
previously.
    To prevent failure of the strut and subsequent loss of control 
of the helicopter, accomplish the following:
    (a) Before further flight, insert a copy of this AD or a 
statement into the Emergency Procedures Section of the Rotorcraft 
Flight Manual (RFM) to inform the pilot to reduce power and land as 
soon as practicable if a thump-like sound followed by unusual 
vibration occurs during flight.
    (b) Within 10 hours time-in-service (TIS), visually inspect each 
strut with 950 or more hours TIS for a crack or a break using a 
flashlight and a mirror in accordance with the Accomplishment 
Instructions, paragraph 3.B.(1) and 3.B.(2), of Eurocopter Alert 
Service Bulletin EC135-63A-002, Revision 2, dated June 26, 2002 
(ASB). Replace any cracked or broken strut with an airworthy strut 
before further flight.
    (c) Inspect the following struts for a crack or a break, using a 
6-power or higher magnifying glass, and re-mark and relocate each 
strut in accordance with the Accomplishment Instructions, paragraph 
3.C., of the ASB. This AD does not require you to return any part to 
the manufacturer.
    (1) For a strut with less than 950 hours TIS, inspect before 
accumulating 1000 hours TIS.
    (2) For a strut with 950 or more hours TIS, inspect within 50 
hours TIS.
    (3) Replace any cracked or broken strut with an airworthy strut 
before further flight.
    (d) This AD revises the Airworthiness Limitations section of the 
maintenance manual by establishing a life limit of 1000 hours TIS 
for each strut, P/N L633M1001 103 and L633M1001 105, in its original 
location, with an additional 1000 hours TIS if properly re-marked 
and relocated (2000 hours total TIS) in accordance with the 
Accomplishment Instructions, paragraph 3.C.(3) of the ASB.
    (e) Record details of the inspections in the historical or 
equivalent records in accordance with the Accomplishment 
Instructions, paragraph 3.C.(4) of the ASB.
    (f) When a strut, P/N L633M1001 103 or L633M1001 105, reaches 
its life limit, replace it with a titanium strut, P/N L633M1001 104, 
which must be used in pairs, one strut on each side of the 
transmission. The titanium struts have no life limit. After 
installing a strut, P/N L633M1001 104, adjust the weight and balance 
by using the weight and moment stated in the Planning Information, 
paragraph 1.H., of the ASB.
    (g) On or before December 31, 2004, replace each strut, P/N 
L633M1001 103 or L633M1001 105, with a strut, P/N L633M1001 104.
    (h) Replacing struts, P/N L633M1001 103 and L633M1001 105, with 
titanium struts, P/N L633M1001 104, constitutes terminating action 
for the requirements of this AD.
    (i) To request a different method of compliance or a different 
compliance time for this AD, follow the procedures in 14 CFR 39.19. 
Contact the Safety Management Group for information about previously 
approved alternative methods of compliance.
    (j) The inspections and replacement of the struts shall be done 
in accordance with Eurocopter Deutschland (GmbH) Alert Service 
Bulletin EC135-63A-002, Revision 2, dated June 26, 2002. The 
Director of the Federal Register approved the incorporation by 
reference 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.

    Note: The subject of this AD is addressed in Luftfahrt-Bundesamt 
(Federal Republic of Germany) AD 2001-107/2, dated September 19, 
2002.



    Issued in Fort Worth, Texas, on September 29, 2003.
David A. Downey,
Manager, Rotorcraft Directorate, , Aircraft Certification Service.
[FR Doc. 03-25592 Filed 10-9-03; 8:45 am]
BILLING CODE 4910-13-P

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