[Federal Register: April 15, 2003 (Volume 68, Number 72)]
[Rules and Regulations]
[Page 18103-18105]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr15ap03-2]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 2003-NE-06-AD; Amendment 39-13112; AD 2003-08-01]
RIN 2120-AA64
Airworthiness Directives; Rolls-Royce Deutschland Ltd. & Co KG,
Model Tay 650-15 Turbofan Engines
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Final rule; request for comments.
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SUMMARY: The FAA is adopting a new airworthiness directive (AD) for
certain serial numbers (SNs) of Rolls-Royce Deutschland Ltd. & Co KG
(RRD) Model Tay 650-15 turbofan engines. This action requires initial
and repetitive visual inspections of low pressure (LP) turbine stage 2
rotor discs and LP turbine stage 3 rotor discs on certain SNs of
engines, for corrosion. This AD is prompted by reports of excessive
corrosion found during disc inspection. The actions specified in this
AD are intended to prevent uncontained LP turbine stage 2 rotor disc or
LP turbine stage 3 rotor disc failure due to excessive corrosion, and
damage to the airplane.
DATES: Effective May 20, 2003.
We must receive any comments on this AD by June 16, 2003.
ADDRESSES: Use one of the following addresses to submit comments on
this AD:
[sbull] By mail: The Federal Aviation Administration (FAA), New
England Region, Office of the Regional Counsel, Attention: Rules Docket
No. 2003-NE-06-AD, 12 New England Executive Park, Burlington, MA 01803-
5299.
[sbull] By fax: (781) 238-7055.
[sbull] By e-mail: 9-ane-adcomment@faa.gov
You may get the service information referenced in this AD from
Rolls-Royce Deutschland Ltd & Co KG, Eschenweg 11, D-15827 Dahlewitz,
Germany, telephone +49 (0) 33-7086-1768; fax +49 (0) 33-7086-3356.
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.
FOR FURTHER INFORMATION CONTACT: James Lawrence, Aerospace Engineer,
Engine Certification Office, FAA, Engine and Propeller Directorate, 12
New England Executive Park, Burlington, MA 01803-5299; telephone (781)
238-7176; fax (781) 238-7199.
SUPPLEMENTARY INFORMATION: The Luftfahrt-Bundesamt (LBA), which is the
airworthiness authority for Germany, recently notified the FAA that an
unsafe condition may exist on certain SNs of RRD Model Tay 650-15
turbofan engines. The LBA advises that the LP turbine stage 2 rotor
discs and LP turbine stage 3 rotor discs of seventeen Tay 650-15
turbofan engines have been found to have excessive corrosion. RRD has
determined that this excessive corrosion is the result of the specific
environment in which these engines operate. This AD requires initial
and repetitive visual inspections for corrosion of low pressure (LP)
turbine stage 2 rotor discs and LP turbine stage 3 rotor discs on
certain SNs of engines. Because disc deterioration may already have
begun, repetitive inspections are also required if any affected disc is
removed from the corrosive environment and put in service in a
noncorrosive environment. The actions specified in this AD are intended
to prevent uncontained LP turbine stage 2 rotor disc or LP turbine
stage 3 rotor disc failure due to excessive corrosion, and damage to
the airplane.
Relevant Service Information
The LBA issued AD 2002-287, dated October 17, 2002, in order to
assure the airworthiness of these RRD Model Tay 650-15 turbofan engines
in Germany.
FAA's Determination and Requirements of This AD
Although none of these affected disc SNs are used on any airplanes
that are registered in the United States, the possibility exists that
these disc SNs could be installed into engines used on airplanes that
are registered in the United States in the future. Since an unsafe
condition has been identified that is likely to exist or develop on
other RRD Tay 650-15 turbofan engines of the same type design, this AD
is being issued to prevent uncontained LP turbine stage 2 rotor disc or
LP turbine stage 3 rotor disc failure due to excessive corrosion, and
damage to the airplane. For engine SNs 17251, 17255, 17256, 17273,
17275, 17280, 17281, 17282, 17300, 17301, 17327, 17332, 17365, 17393,
17437, 17563, and 17618, this AD requires initial and repetitive visual
inspections of LP turbine stage 2 rotor discs and LP turbine stage 3
rotor discs for corrosion.
Bilateral Airworthiness Agreement
This engine model is manufactured in Germany, and is type
certificated for operation in the United States under the provisions of
Sec. 21.29 of the Federal Aviation Regulations (14 CFR 21.29)
[[Page 18104]]
and the applicable bilateral airworthiness agreement. Pursuant to this
bilateral airworthiness agreement, the LBA has kept the FAA informed of
the situation described above. The FAA has examined the findings of the
LBA, reviewed all available information, and determined that AD action
is necessary for products of this type design that are certificated for
operation in the United States.
Immediate Adoption of This AD
Since none of these affected engine SNs are used on any airplanes
that are registered in the United States, notice and opportunity for
prior public comment are unnecessary. Therefore, a situation exists
that allows the immediate adoption of this regulation.
Changes to 14 CFR Part 39--Effect on the AD
On July 10, 2002, we issued a new version of 14 CFR part 39 (67 FR
47997, July 22, 2002), which governs our 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 will not include it in future AD actions.
Comments Invited
This AD is a final rule that involves requirements affecting flight
safety and was not preceded by notice and an opportunity for public
comment; however, we invite you to submit any written relevant data,
views, or arguments regarding this AD. Send your comments to an address
listed under ADDRESSES. Include ``AD Docket No. 2003-NE-06-AD'' in the
subject line of your comments. If you want us to acknowledge receipt of
your mailed comments, send us a self-addressed, stamped postcard with
the docket number written on it; we will date-stamp your postcard and
mail it back to you. We specifically invite comments on the overall
regulatory, economic, environmental, and energy aspects of the rule
that might suggest a need to modify it. If a person contacts us through
a nonwritten communication, and that contact relates to a substantive
part of this AD, we will summarize the contact and place the summary in
the docket. We will consider all comments received by the closing date
and may amend the AD in light of those comments.
We are reviewing the writing style we currently use in regulatory
documents. We are interested in your comments on whether the style of
this document is clear, and your suggestions to improve the clarity of
our communications with you. You may get more information about plain
language at http://www.plainlanguage.gov.
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 the regulation:
1. Is not a ``significant regulatory action'' under Executive Order
12866;
2. Is not a ``significant rule'' under the 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-06-AD'' in your request.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, 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. The FAA amends Sec. 39.13 by adding the following new airworthiness
directive:
Federal Aviation Administration (FAA), Airworthiness Directive (AD)
2003-08-01, Docket No. 2003-NE-06, Amendment 39-13112, Rolls-Royce
Deutschland Ltd. & Co KG, Subject: Initial and Repetitive Visual
Inspections of Low Pressure (LP) Turbine Stage 2 Rotor Discs and LP
Turbine Stage 3 Rotor Discs
Effective Date
(a) This AD becomes effective May 20, 2003.
Affected ADs
(b) None.
Applicability
(c) This AD is applicable to Rolls-Royce Deutschland Ltd. & Co
KG (RRD) Model Tay 650-15 turbofan engines with low pressure (LP)
turbine stage 2 rotor discs, part number (P/N) JR32319, and LP
turbine stage 3 rotor discs, P/N JR32320A, that have a serial number
(SN) listed in Table 1 of this AD. These engines are installed on,
but not limited to Fokker F.28 Mark 0100 airplanes. Table 1 follows:
Table 1.--Disc SNs
------------------------------------------------------------------------
LP turbine stage 2 LP turbine stage 3
Last known engine SN rotor disc, part rotor disc, part No.
No. JR32319, SNs JR32320A, SNs
------------------------------------------------------------------------
17251......................... EETM1355 DETM1853/A
17255......................... DETM19039 DETM19007
17256......................... SETM11283 SETM15065
17273......................... PETM718 DETM14896/A
17275......................... DETM17343 DETM17546
-------------------------------
17280......................... EETM1808 SETM14410
17281......................... DETM19036 DETM18999
17282......................... EETM2163 DETM3703/A
17300......................... SETM12109 SETM11379
17301......................... DETM18772 DETM18348
17327......................... EETM2510 DETM15404/A
17332......................... SETM20088 SETM21297
17365......................... SETM15166 SETM15188
17393......................... DETM17083 DETM16860
17437......................... EETM19304 DETM19008
17563......................... EETM4414 DETM15583/A
17618......................... EETM5010 DETM9588/A
------------------------------------------------------------------------
Unsafe Condition
(d) This AD was prompted by reports of excessive corrosion found
during LP turbine stage 2 rotor disc and LP turbine stage 3 rotor
disc inspection. The actions specified in this AD are intended to
prevent uncontained LP turbine stage 2 rotor disc or LP turbine
stage 3 rotor disc failure due to excessive corrosion, and damage to
the airplane.
Compliance
(e) Compliance with this AD is required as indicated, unless
already done.
Visual Inspections
(f) Perform an initial visual inspection of the LP turbine stage
2 rotor disc and LP turbine stage 3 rotor disc for corrosion within
11,700 cycles-in-service (CIS) after the effective date of this AD.
Information on performing visual inspections can be found in RRD
engine manual task 72-52-23-200-000 and task 72-52-24-200-000
respectively.
Discs That Fail Inspection
(g) Before further flight, do the following for discs that fail
inspection:
(1) Replace any LP turbine stage 2 rotor discs and LP turbine
stage 3 rotor discs found with corrosion pits beyond repairable
limits. Information on repairable limits may be found in RRD Engine
Manual Task 72-52-23-200-000 and Task 72-52-24-200-000 respectively.
[[Page 18105]]
(2) Repair any LP turbine stage 2 rotor discs and LP turbine
stage 3 rotor discs found with corrosion pits within repairable
limits. Information on repairable limits may be found in RRD Engine
Manual Task 72-52-23-200-000 and Task 72-52-24-200-000 respectively.
Repetitive Visual Inspections
(h) Perform repetitive visual inspections of the LP turbine
stage 2 rotor disc and LP turbine stage 3 rotor disc for corrosion
within every 11,700 cycles-since-last inspection. Information on
performing visual inspections can be found in RRD Engine Manual Task
72-52-23-200-000 and Task 72-52-24-200-000 respectively.
(i) Disposition discs that fail inspection as specified in
paragraph (g) of this AD.
Alternative Methods of Compliance
(j) The Manager, Engine Certification Office, FAA, is authorized
to approve alternative methods of compliance for this AD in
accordance with 14 CFR 39.19.
Material Incorporated by Reference
(k) None.
Related Information
(l) LBA airworthiness directive 2002-287, dated October 17,
2002, also addresses the subject of this AD.
Issued in Burlington, Massachusetts, on April 7, 2003.
Jay J. Pardee,
Manager, Engine and Propeller Directorate, Aircraft Certification
Service.
[FR Doc. 03-9017 Filed 4-14-03; 8:45 am]
BILLING CODE 4910-13-P