[Federal Register: October 10, 2003 (Volume 68, Number 197)]
[Rules and Regulations]
[Page 58581-58582]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr10oc03-3]
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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]
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