[Federal Register Volume 70, Number 180 (Monday, September 19, 2005)]
[Rules and Regulations]
[Pages 54835-54837]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 05-17493]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2005-20944; Directorate Identifier 2003-NE-64-AD; 
Amendment 39-14247; AD 2005-18-01]
RIN 2120-AA64


Airworthiness Directives; General Electric Company CT7-5, -7, and 
-9 Series Turboprop Engines

AGENCY: Federal Aviation Administration (FAA), Department of 
Transportation (DOT).

ACTION: Final rule.

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SUMMARY: The FAA is adopting a new airworthiness directive (AD) for 
General Electric Company (GE) CT7-5A2, -5A3, -7A, -7A1, -9B, -9B1, and 
-9B2 turboprop engines, with stage 2 turbine aft cooling plate, part 
number (P/N) 6064T07P01, 6064T07P02, 6064T07P05, or 6068T36P01 
installed. This AD requires a onetime eddy current inspection (ECI) of 
certain P/N stage 2 turbine aft cooling plate boltholes. This AD 
results from reports of six stage 2 turbine aft cooling plates found 
cracked during inspection. We are issuing this AD to prevent stage 2 
aft cooling plate separation, resulting in uncontained engine failure 
and damage to the airplane.

DATES: This AD becomes effective October 24, 2005. The Director of the 
Federal Register approved the incorporation by reference of certain 
publications listed in the regulations as of October 24, 2005.

ADDRESSES: You can get the service information identified in this AD 
from General Electric Aircraft Engines CT7 Series Turboprop Engines, 
1000 Western Ave., Lynn, MA 01910; telephone (781) 594-3140, fax (781) 
594-4805.
    You may examine the AD docket on the Internet at http://dms.dot.gov 
or in Room PL-401 on the plaza level of the Nassif Building, 400 
Seventh Street, SW., Washington, DC.

FOR FURTHER INFORMATION CONTACT: Eugene Triozzi, Aerospace Engineer, 
Engine Certification Office, FAA, Engine

[[Page 54836]]

and Propeller Directorate, 12 New England Executive Park, Burlington, 
MA 01803-5299; telephone (781) 238-7148; fax (781) 238-7199.

SUPPLEMENTARY INFORMATION: The FAA proposed to amend 14 CFR part 39 
with a proposed AD. The proposed AD applies to GE CT7-5A2, -5A3, -7A, -
7A1, -9B, -9B1, and -9B2 turboprop engines, with stage 2 turbine aft 
cooling plate, P/N 6064T07P01, 6064T07P02, 6064T07P05, or 6068T36P01 
installed. We published the proposed AD in the Federal Register on 
April 15, 2005 (70 FR 19893). That action proposed to require a onetime 
ECI of certain P/N stage 2 turbine aft cooling plate boltholes.

Examining the AD Docket

    You may examine the docket that contains the AD, any comments 
received, and any final disposition in person at the Docket Management 
Facility Docket Offices between 9 a.m. and 5 p.m., Monday through 
Friday, except Federal holidays. The Docket Office (telephone (800) 
647-5227) is located on the plaza level of the Department of 
Transportation Nassif Building at the street address stated in 
ADDRESSES. Comments will be available in the AD docket shortly after 
the Document Management Facility receives them.

Comments

    We provided the public the opportunity to participate in the 
development of this AD. We received no comments on the proposal or on 
the determination of the cost to the public.

Conclusion

    We have carefully reviewed the available data and determined that 
air safety and the public interest require adopting the AD as proposed.

Costs of Compliance

    There are about 1,240 GE CT7-5, -7, and -9 series turboprop engines 
of the affected design in the worldwide fleet. We estimate that 550 
engines installed on airplanes of U.S. registry will be affected by 
this AD. We also estimate that it would take about one work hour per 
engine to perform the actions, and that the average labor rate is $65 
per work hour. We estimate that 2.5% (or 14) of the 550 engines will 
require stage 2 turbine aft cooling plates being rejected by the 
onetime ECI. Required parts will cost about $17,000 per engine. Based 
on these figures, we estimate the total cost of the AD to U.S. 
operators to be $270,700.

Authority for This Rulemaking

    Title 49 of the United States Code specifies the FAA's authority to 
issue rules on aviation safety. Subtitle I, section 106, describes the 
authority of the FAA Administrator. Subtitle VII, Aviation Programs, 
describes in more detail the scope of the Agency's authority.
    We are issuing this rulemaking under the authority described in 
subtitle VII, part A, subpart III, section 44701, ``General 
requirements.'' Under that section, Congress charges the FAA with 
promoting safe flight of civil aircraft in air commerce by prescribing 
regulations for practices, methods, and procedures the Administrator 
finds necessary for safety in air commerce. This regulation is within 
the scope of that authority because it addresses an unsafe condition 
that is likely to exist or develop on products identified in this 
rulemaking action.

Regulatory Findings

    We have determined that this AD will not have federalism 
implications under Executive Order 13132. This AD 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.
    For the reasons discussed above, I certify that this AD:
    (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.
    We prepared a summary of the costs to comply with this AD and 
placed it in the AD Docket. You may get a copy of this summary at the 
address listed under ADDRESSES.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Incorporation by 
reference, Safety.

Adoption of the Amendment

0
Accordingly, under the authority delegated to me by the Administrator, 
the Federal Aviation Administration amends 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. The FAA amends Sec.  39.13 by adding the following new airworthiness 
directive:

2005-18-01 General Electric Company: Amendment 39-14241. Docket No. 
FAA-2005-20944; Directorate Identifier. 2003-NE-64-AD.

Effective Date

    (a) This airworthiness directive (AD) becomes effective October 
24, 2005.

Affected ADs

    (b) None.

Applicability

    (c) This AD applies to General Electric Company (GE) CT7-5A2, -
5A3, -7A, -7A1, -9B, -9B1, and -9B2 turboprop engines, with stage 2 
turbine aft cooling plate, part number (P/N) 6064T07P01, 6064T07P02, 
6064T07P05, or 6068T36P01 installed. These engines are installed on, 
but not limited to, Construcciones Aeronauticas, SA CN-235 series 
and SAAB Aircraft AB SF340 series airplanes.

Unsafe Condition

    (d) This AD results from reports of six stage 2 turbine aft 
cooling plates found cracked during inspection. The actions 
specified in this AD are intended to prevent stage 2 aft cooling 
plate separation, resulting in uncontained engine failure and damage 
to the airplane.

Compliance

    (e) You are responsible for having the actions required by this 
AD performed at the next engine or hot section module shop visit, 
but before accumulating an additional 6,000 cycles-in-service after 
the effective date of the AD, unless already done.

Onetime Eddy Current Inspection (ECI)

    (f) Perform a onetime ECI of the stage 2 turbine aft cooling 
plate boltholes, using paragraph 3.B. of GE Alert Service Bulletin 
(ASB) No. CT7-TP S/B 72-A0464, Revision 2, dated May 9, 2003.
    (g) Remove from service any stage 2 turbine aft cooling plate 
that does not pass the return to service criteria specified in 
paragraph 3.B.(2) of GE Alert Service Bulletin (ASB) No. CT7-TP S/B 
72-A0464, Revision 2, dated May 9, 2003.

Previous Credit

    (h) Previous credit is allowed for onetime ECIs of the stage 2 
turbine aft cooling plate boltholes that were done using GE ASB No. 
CT7-TP S/B 72-A0464, dated February 25, 2003, or GE ASB No. CT7-TP 
S/B 72-A0464, Revision 1, dated March 12, 2003, before the effective 
date of this AD.

Definition of Engine or Hot Section Module Shop Visit

    (i) For the purposes of this AD, an engine or hot section module 
shop visit is defined as the introduction of the engine or hot 
section module into a shop that includes separation of CT7 turboprop 
engine major case flanges.

[[Page 54837]]

Alternative Methods of Compliance

    (j) The Manager, Engine Certification Office, has the authority 
to approve alternative methods of compliance for this AD if 
requested using the procedures found in 14 CFR 39.19.

Related Information

    (k) None.
    Issued in Burlington, Massachusetts, on August 19, 2005.

Material Incorporated by Reference

    (l) You must use GE Alert Service Bulletin (ASB) No. CT7-TP S/B 
72-A0464, Revision 2, dated May 9, 2003, to perform the inspection 
required by this AD. The Director of the Federal Register approved 
the incorporation by reference of this service bulletin in 
accordance with 5 U.S.C. 552(a) and 1 CFR part 51. Contact General 
Electric Aircraft Engines CT7 Series Turboprop Engines, 1000 Western 
Ave., Lynn, MA 01910; telephone (781) 594-3140, fax (781) 594-4805, 
for a copy of this service information. You may review copies at the 
Docket Management Facility; U.S. Department of Transportation, 400 
Seventh Street, SW., Nassif Building, Room PL-401, Washington, DC 
20590-0001, on the Internet at http://dms.dot.gov, or at the 
National Archives and Records Administration (NARA). For information 
on the availability of this material at NARA, call 202-741-6030, or 
go to: http://www.archives.gov/federal-register/cfr/ibr-locations.html.

    Issued in Burlington, Massachusetts, on August 19, 2005.
Richard Noll,
Acting Manager, Engine and Propeller Directorate, Aircraft 
Certification Service.
[FR Doc. 05-17493 Filed 9-16-05; 8:45 am]
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