[Federal Register Volume 68, Number 72 (Tuesday, April 15, 2003)]
[Rules and Regulations]
[Pages 18103-18105]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 03-9017]


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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: [email protected]
    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]
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