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CFR Citation: 14 CFR Part 39

Docket ID: [Docket No. FAA-2007-0037; Directorate Identifier 2007-NE-41-AD]

RIN ID: RIN 2120-AA64

NOTICE: PROPOSED RULES

ACTION: Airworthiness Directives:

DOCUMENT ACTION: Notice of proposed rulemaking (NPRM).

SUBJECT CATEGORY: Airworthiness Directives; Rolls-Royce Deutschland Ltd. & Co. KG. (RRD) TAY 650-15 Turbofan Engines

DATES: We must receive comments on this proposed AD by February 1, 2008.

DOCUMENT SUMMARY: We propose to adopt a new airworthiness directive (AD) for the products listed above. This proposed AD results from mandatory continuing airworthiness information (MCAI) issued by an aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI states the following:

Strip results from some of the engines listed in the applicability section of this directive revealed excessively corroded low pressure turbine discs stage 2 and stage 3. The corrosion is considered to be caused by the environment in which these engines are operated. Following a life assessment based on the strip findings it is concluded that inspections for corrosion attack are required. The action specified by this AD is intended to avoid a failure of a low pressure turbine disk stage 2 or stage 3 due to potential corrosion problems which could result in uncontained engine failure and damage to the airplane.
We are proposing this AD to detect corrosion that could cause stage 2 or stage 3 disk of the low pressure turbine to fail and result in an uncontained failure of the engine.

SUMMARY: Rolls-Royce Deutschland Ltd. & Co. KG. (RRD) TAY 650-15 Turbofan Engines,

SUPPLEMENTAL INFORMATION

We invite you to send any written relevant data, views, or arguments about this proposed AD. Send your comments to an address listed under the ADDRESSES section. Include ``Docket No. FAA20070037; Directorate Identifier 2007NE41AD'' at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of this proposed AD. We will consider all comments received by the closing date and may amend this proposed AD based on those comments.

We will post all comments we receive, without change, to http://www.regulations.gov , including any personal information you provide. We
will also post a report summarizing each substantive verbal contact we receive about this proposed AD.

Discussion

The European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Community, has issued EASA Airworthiness Directive 20060288, dated September 15, 2006, to correct an unsafe condition for the specified products. The EASA AD states:

Strip results from some of the engines listed in the applicability section of this directive revealed excessively corroded low pressure turbine discs stage 2 and stage 3. The corrosion is considered to be caused by the environment in which these engines are operated. Following a life assessment based on the strip findings it is concluded that inspections for corrosion attack are required. The action specified by this AD is intended to avoid a failure of a low pressure turbine disk stage 2 or stage 3 due to potential corrosion problems which could result in uncontained engine failure and damage to the airplane.

You may obtain further information by examining the MCAI in the AD docket.

Relevant Service Information

RRD has issued Alert Service Bulletin No. TAY72A1524, Revision 1, dated September 1, 2006. The actions described in this service information are intended to correct the unsafe condition identified in the MCAI.

FAA's Determination and Requirements of This Proposed AD

This product has been approved by the aviation authority of Germany, and is approved for operation in the United States. Under this bilateral airworthiness agreement, the EASA has kept the FAA informed of the situation described above. We have examined the findings of the EASA, 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.

Costs of Compliance

Based on the service information, we estimate that this proposed AD would affect about two engines installed on airplanes of U.S. registry. We also estimate that it would take about 1.0 workhours per product to inspect the disk, and that the average labor rate is $80 per workhour. If corrosion is found, we estimate that it would take about 2.0 work hours to replace the disk. Required parts would cost about $40,000 per product. Based on these figures, we estimate the total cost of the proposed AD to U.S. operators to be $80,480. Our cost estimate is exclusive of possible warranty coverage.

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 determined that this proposed AD would not have federalism implications under Executive Order 13132. This proposed AD would 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 this proposed 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 regulatory evaluation of the estimated costs to comply with this proposed AD and placed it in the AD docket. List of Subjects in 14 CFR Part 39

Air transportation, Aircraft, Aviation safety, Safety. The Proposed Amendment

Accordingly, under the authority delegated to me by the Administrator, the FAA proposes to amend 14 CFR part 39 as follows: PART 39AIRWORTHINESS DIRECTIVES

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]

2. The FAA amends Sec. 39.13 by adding the following new AD: RollsRoyce Deutschland Ltd & Co KG (RRD) (formerly RollsRoyce plc, Derby, England): Docket No. FAA20070037; Directorate Identifier 2007NE41AD.
Comments Due Date
(a) We must receive comments by February 1, 2008.
Affected ADs
(b) None.
Applicability
(c) This AD applies to RRD TAY 65015 turbofan engines that have a serial number listed in Table 1 of this AD, and low pressure turbine module M05300AA installed. These engines are installed on, but not limited to, Fokker F28 Mark 0100 airplanes.
Table 1.Affected TAY 65015 Engines by Serial Number Engine serial number
17251
17255
17256
17273
17275
17280
17281
17282
17300
17301
17327
17332
17365
17393
17437
17443
17470
17520
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17521
17523
17539
17542
17556
17561
17562
17563
17580
17581
17612
17618
17635
17637
17645
17661
17686
17699
17701
17702
17736
17737
17738
17739
17741
17742
17808
Reason
(d) Strip results from some of the engines listed in the applicability section of this directive revealed excessively corroded low pressure turbine discs stage 2 and stage 3. The corrosion is considered to be caused by the environment in which these engines are operated. Following a life assessment based on the strip findings it is concluded that inspections for corrosion attack are required. The action specified by this AD is intended to avoid a failure of a low pressure turbine disk stage 2 or stage 3 due to potential corrosion problems which could result in uncontained engine failure and damage to the airplane.

We are proposing this AD to detect corrosion that could cause stage 2 or stage 3 disk of the low pressure turbine to fail and result in an uncontained failure of the engine.
Actions and Compliance
(e) Unless already done, do the following actions.
(1) Prior to accumulating 11,700 flight cycles (FC) since new, and thereafter at intervals not exceeding 11,700 FC of the engine, inspect the low pressure turbine discs stage 2 and stage 3 for corrosion in accordance with RollsRoyce Deutschland Non
Modification Alert Service Bulletin TAY72A1524, Revision 1. (2) For engines that already exceed 11,700 FC on the effective date of this AD, perform the inspection within 90 days after the effective date of this AD.
(3) When, during any of the inspections as required by paragraph (e)(1) of this directive, corrosion is found, replace the affected parts using the rejection criteria described in the RollsRoyce TAY 650 Engine ManualETAY3RR.
Other FAA AD Provisions
(f) Alternative Methods of Compliance (AMOCs): The Manager, Engine Certification Office, FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19.
Related Information
(g) Refer to EASA Airworthiness Directive 20060288, dated September 15, 2006, and RRD Alert Service Bulletin TAY72A1524, Revision 1, dated September 1, 2006, for related information. (h) Contact Jason Yang, Aerospace Engineer, Engine Certification Office, FAA, Engine & Propeller Directorate, 12 New England Executive Park, Burlington, MA 01803; email: jason.yang@faa.gov; telephone (781) 2387747; fax (781) 2387199, for more information about this AD.

Issued in Burlington, Massachusetts, on December 26, 2007. Peter A. White,
Assistant Manager, Engine and Propeller Directorate, Aircraft Certification Service.
[FR Doc. E725457 Filed 123107; 8:45 am]
BILLING CODE 491013P

FOR FURTHER INFORMATION CONTACT Jason Yang, Aerospace Engineer, Engine Certification Office, FAA, Engine & Propeller Directorate, 12 New England Executive Park, Burlington, MA 01803;
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email: jason.yang@faa.gov; telephone (781) 2387747; fax (781) 238 7199.