[Federal Register Volume 68, Number 242 (Wednesday, December 17, 2003)]
[Rules and Regulations]
[Pages 70136-70137]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 03-31057]



[[Page 70136]]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2003-NE-19-AD; Amendment 39-13391; AD 2003-25-08]
RIN 2120-AA64


Airworthiness Directives; Rolls-Royce Corporation (Formerly 
Allison Engine Company) AE 3007A1, AE 3007A1/1, AE 3007A1/3, AE 3007A3, 
AE 3007A1E, and AE 3007A1P Turbofan Engines

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule.

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SUMMARY: The FAA is adopting a new airworthiness directive (AD) for 
Rolls-Royce Corporation (formerly Allison Engine Company) AE 3007A1, AE 
3007A1/1, AE 3007A1/3, AE 3007A3, AE 3007A1E, and AE 3007A1P turbofan 
engines, with 1st to 2nd stage turbine spacers, part number (P/N) 
23069627, 23070989, 23072849, or 23075364 installed. This AD reduces 
the life limit for 1st to 2nd stage turbine spacers, P/N 23072849, to a 
certain lower life limit, based on engine model. This AD also requires 
a one-time fluorescent penetrant inspection (FPI) of 1st to 2nd stage 
turbine spacers P/Ns 23069627, 23070989, 23072849, and 23075364 before 
reaching the spacer life limit, within specified cycles-since-new 
(CSN), and requires replacement of the spacer if found cracked, or with 
bent or missing aft tangs. This AD is prompted by a report that during 
a scheduled inspection, aft pilot tangs on a 1st to 2nd stage turbine 
spacer were found bent and cracked. We are issuing this AD to prevent 
1st to 2nd stage turbine spacer failure, leading to uncontained turbine 
failure, engine shutdown, and damage to the airplane.

DATES: This AD becomes effective January 21, 2004.

ADDRESSES: You can get the service information identified in this AD 
from Rolls-Royce Corporation, P.O. Box 420, Indianapolis, IN 46206-
0420; telephone (317) 230-6400; fax (317) 230-4243.
    You may examine the AD docket, by appointment, at the FAA, New 
England Region, Office of the Regional Counsel, 12 New England 
Executive Park, Burlington, MA. You may examine the service 
information, by appointment, at the FAA, New England Region, Office of 
the Regional Counsel, 12 New England Executive Park, Burlington, MA.

FOR FURTHER INFORMATION CONTACT: Michael Downs, Aerospace Engineer, 
Chicago Aircraft Certification Office, FAA, Small Airplane Directorate, 
2300 East Devon Avenue, Des Plaines, IL 60018; telephone: (847) 294-
7870, fax: (847) 294-7834.

SUPPLEMENTARY INFORMATION: The FAA proposed to amend 14 CFR part 39 
with a proposed AD. The proposed AD applies to Rolls-Royce Corporation 
(formerly Allison Engine Company) AE 3007A1, AE 3007A1/1, AE 3007A1/3, 
AE 3007A3, AE 3007A1E, and AE 3007A1P turbofan engines, with 1st to 2nd 
stage turbine spacers, P/N 23069627, 23070989, 23072849, or 23075364 
installed. We published the proposed AD in the Federal Register on 
August 13, 2003 (68 FR 48326). That action proposed to reduce the life 
limit for 1st to 2nd stage turbine spacers, P/N 23072849, to a certain 
lower life limit, based on engine model. That action also proposed to 
require a one-time FPI of 1st to 2nd stage turbine spacers P/Ns 
23069627, 23070989, 23072849, and 23075364 before reaching the spacer 
life limit, within specified CSN, and to require replacement of the 
spacer if found cracked, or with bent or missing aft tangs.

Comments

    We provided the public the opportunity to participate in the 
development of this AD. We have considered the comment received.

Request To Rewrite Paragraph (g)(1)

    One commenter, the manufacturer, requests that we rewrite paragraph 
(g)(1) from ``For an engine inducted into the shop for any reason, if 
the spacer has accumulated 3,000 CSN or more'' to ``For an engine 
inducted into the shop for any reason, requiring disassembly of the 
engine core split lines, if the spacer has accumulated 3,000 CSN or 
more''. The commenter estimates that approximately two to four engines 
a year return to the shop to address external issues only. The 
commenter states that paragraph (g)(1), as written, creates a burden to 
the operators and imposes an engine core teardown on those engines 
returned to the shop for external issues only.
    The FAA agrees. The requested change does not change the risk 
assessment or the inspection criteria of the AD, and as long as the 
upper limit of 9,800 CSN or the life limit is not exceeded, the 
operator should not be forced into an engine teardown if the spacer has 
3,000 CSN or more. Paragraph (g)(1) is rewritten as requested in this 
AD.

Conclusion

    We have carefully reviewed the available data, including the 
comment received, and determined that air safety and the public 
interest require adopting the AD with the changes described previously. 
We have determined that these changes will neither increase the 
economic burden on any operator nor increase the scope of the AD.

Changes to 14 CFR Part 39--Effect on the AD

    On July 10, 2002, the FAA published a new version of 14 CFR part 39 
(67 FR 47997, July 22, 2002), which governs the FAA's AD system. That 
regulation now includes material that relates to altered products, 
special flight permits, and alternative methods of compliance. The 
material previously was included in each individual AD. Since the 
material is included in 14 CFR part 39, we will not include it in 
future AD actions.

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 by 
sending a request to us at the address listed under ADDRESSES. Include 
``AD Docket No. 2003-NE-19-AD'' in your request.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, 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.

[[Page 70137]]

Sec.  39.13  [Amended]

0
2. The FAA amends Sec.  39.13 by adding the following new airworthiness 
directive (AD):

2003-25-08 Rolls-Royce Corporation (formerly Allison Engine 
Company): Amendment 39-13391. Docket No. 2003-NE-19-AD.

Effective Date

    (a) This AD becomes effective January 21, 2004.

Affected ADs

    (b) None.

Applicability

    (c) This AD applies to Rolls-Royce Corporation (formerly Allison 
Engine Company) AE 3007A1, AE 3007A1/1, AE 3007A1/3, AE 3007A3, AE 
3007A1E, and AE 3007A1P turbofan engines, with 1st to 2nd stage 
turbine spacer part number (P/N) 23069627, 23070989, 23072849, or 
23075364 installed. These engines are installed on, but not limited 
to, EMBRAER EMB-135 and EMB-145 series airplanes.

Unsafe Condition

    (d) This AD is prompted by a report that during a scheduled 
inspection, aft pilot tangs on a 1st to 2nd stage turbine spacer 
were found bent and cracked. We are issuing this AD to prevent 1st 
to 2nd stage turbine spacer failure, leading to uncontained turbine 
failure, engine shutdown, and damage to the airplane.

Compliance

    (e) You are responsible for having the actions required by this 
AD performed within the compliance times specified unless the 
actions have already been done.

1st to 2nd Stage Turbine Spacer Life Limits

    (f) 1st to 2nd stage turbine spacer life limits are as follows:
    (1) For P/N 23072849, the newly established life limit is:
    (i) 13,100 cycles-since-new (CSN) for engine models AE 3007A1/1, 
AE 3007A1/3, AE 3007A1, AE 3007A3; and
    (ii) 12,900 CSN for engine models AE 3007A1E and AE 3007A1P.
    (2) For P/Ns 23069627, 23070989, and 23075364, the life limits 
are unchanged.

Inspection

    (g) After the effective date of this AD, perform a one-time 
fluorescent penetrant inspection (FPI) of the 1st to 2nd stage 
turbine spacer P/Ns 23069627, 23070989, 23072849, and 23075364 and 
replace spacer if cracked or if aft pilot tangs are bent or missing, 
with a new or serviceable 1st to 2nd stage turbine spacer, using the 
following compliance criteria:
    (1) For an engine inducted into the shop for any reason, 
requiring disassembly of the engine core split lines, if the spacer 
has accumulated 3,000 CSN or more.
    (2) For installed engines, if the spacer has accumulated more 
than 9,300 CSN, inspect before accumulating an additional 500 
cycles-in-service, or before accumulating 4,200 cycles-since-last 
FPI, whichever is more, but do not exceed the spacer life limit in 
paragraph (f) of this AD.
    (3) For installed engines, if the spacer has accumulated 9,300 
or less CSN, inspect before accumulating 9,800 CSN, or before 
accumulating 4,200 cycles-since-last FPI, whichever is more, but do 
not exceed the spacer life limit in paragraph (f) of this AD.

Alternative Methods of Compliance

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

Material Incorporated by Reference

    (i) None.

Related Information

    (j) The subject of this AD is addressed in Rolls-Royce 
Corporation alert service bulletin No. AE 3007A-A-72-265, Revision 
1, dated April 10, 2003.

    Issued in Burlington, Massachusetts, on December 9, 2003.
Jay J. Pardee,
Manager, Engine and Propeller Directorate, Aircraft Certification 
Service.
[FR Doc. 03-31057 Filed 12-16-03; 8:45 am]
BILLING CODE 4910-13-P