Federal Aviation Administration (FAA), Department of Transportation (DOT).
Notice of proposed rulemaking (NPRM).
The FAA proposes to adopt a new airworthiness directive (AD) for Rolls-Royce Deutschland Ltd & Co KG (formerly Rolls-Royce plc) (RRD) Dart 528, 529, 532, 535, 542, and 552 series turbofan engines. This proposed AD would require repetitive inspections of high pressure turbine (HPT) blade platforms and shrouds, and reworking the engines if the inspections reveal excessive gaps between blade shrouds. This proposed AD results from reports of HPT disk rim failures. We are proposing this AD to prevent HPT disk rim failures resulting in the release of portions of the HPT disk, uncontained engine failure, and damage to the airplane.
We must receive any comments on this proposed AD by November 13, 2006.
Use one of the following addresses to comment on this proposed AD.
- DOT Docket Web site: Go to http://dms.dot.gov and follow the instructions for sending your comments electronically.
- Government-wide rulemaking Web site: Go to http://www.regulations.gov and follow the instructions for sending your comments electronically.
- Mail: Docket Management Facility; U.S. Department of Transportation, 400 Seventh Street, SW., Nassif Building, Room PL-401, Washington, DC 20590-0001.
- Fax: (202) 493-2251.
- Hand Delivery: Room PL-401 on the plaza level of the Nassif Building, 400 Seventh Street, SW., Washington, DC, between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays.
Contact Rolls-Royce Deutschland Ltd & Co KG, Eschenweg 11, D-15827 Dahlewitz, Germany; telephone 49 (0) 33-7086-1768; fax 49 (0) 33-7086-3356 for the service information identified in this proposed AD.Start Further Info
FOR FURTHER INFORMATION CONTACT:
Jason Yang, Aerospace Engineer, Engine Certification Office, FAA, Engine and Propeller Directorate, 12 New England Executive Park, Burlington, MA 01803; telephone (781) 238-7747; fax (781) 238-7199).End Further Info End Preamble Start Supplemental Information
We invite you to send us any written relevant data, views, or arguments regarding this proposal. Send your comments to an address listed under ADDRESSES. Include “Docket No. FAA-2006-25272; Directorate Identifier 2006-NE-16-AD” in the subject line of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of the proposed AD. We will consider all comments received by the closing date and may amend the Start Printed Page 53611proposed AD in light of those comments.
We will post all comments we receive, without change, to http://dms.dot.gov, including any personal information you provide. We will also post a report summarizing each substantive verbal contact with FAA personnel concerning this proposed AD. Using the search function of the DMS Web site, anyone can find and read the comments in any of our dockets, including the name of the individual who sent the comment (or signed the comment on behalf of an association, business, labor union, etc.). You may review the DOT's complete Privacy Act Statement in the Federal Register published on April 11, 2000 (65 FR 19477-78) or you may visit http://dms.dot.gov.
Examining the AD Docket
You may examine the docket that contains the proposal, any comments received, and any final disposition in person at the DMS Docket Offices between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The Docket Office (telephone (800) 647-5227) is 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 DMS receives them.
The Luftfahrt-Bundesamt (LBA), which is the airworthiness authority for Germany, recently notified us that an unsafe condition may exist on RRD Dart 528, 529, 532, 535, 542, and 552 turbofan engines. The LBA advises that they received reports of HPT disk rim failures, some of which resulted in release of portions of the HPT disk. These failures resulted from high stress levels in the HPT disk bucket groove due to blade vibration. Excessive gaps between the blade shroud and platform induced the damaging HPT blade vibration. The gaps can increase if wear occurs between the blade shroud and platform abutment faces. We are proposing this AD to prevent HPT disk rim failures resulting in the release of portions of the HPT disk, an uncontained engine failure, and damage to the airplane.
Relevant Service Information
We have reviewed and approved the technical contents of RRD DART Service Bulletin (SB) Da72-543, dated July 11, 2003, and RRD Repair Instruction, “Restoration of HPT Blade Platform and Shroud, DRS 611,” dated January 20, 2005, that describe procedures for a dimensional inspection and rework, if necessary, of the HPT blade platform and shroud. The LBA classified this SB as mandatory and issued airworthiness directive 2003-217, dated August 7, 2003, in order to ensure the airworthiness of these engines in Germany.
Differences Between This Proposed AD and the Manufacturer's Service Information
This proposed AD shortens the initial inspection of the HPT blade platform and shroud to no more than 1,500 flight hours from the date of issue of this AD, if the engine has not been inspected or reworked to the DRS 611 standard.
FAA's Determination and Requirements of the Proposed AD
These engines, manufactured in the United Kingdom and transferred to Germany, are type-certificated for operation in the United States under the provisions of section 21.29 of the Federal Aviation Regulations (14 CFR 21.29) and the applicable bilateral airworthiness agreement. In keeping with this bilateral airworthiness agreement, the LBA kept us informed of the situation described above. We have examined the LBA's findings, 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. We are proposing this AD, that would require repetitive inspections of HPT blade platforms and shrouds, and reworking the engines if the inspections reveal excessive gaps between blade shrouds. The proposed AD would require you to use the service information described previously to perform these actions.
Costs of Compliance
We estimate that this proposed AD would affect about 30 RRD Dart 528, 529, 532, 535, 542, and 552 series turbofan engines installed on airplanes of U.S. registry. We also estimate that it would take about 22 work-hours per engine to perform the proposed actions, and that the average labor rate is $80 per work-hour. No parts are required. Based on these figures, we estimate the total cost of the proposed AD to U.S. operators to be $52,800.
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.
We have 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 that the 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. Would 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. See the ADDRESSES section for a location to examine the regulatory evaluation.Start List of Subjects
List of Subjects in 14 CFR Part 39End List of Subjects
The Proposed Amendment
Under the authority delegated to me by the Administrator, the Federal Aviation Administration proposes to amend 14 CFR part 39 as follows:Start Part
PART 39—AIRWORTHINESS DIRECTIVES
1. The authority citation for part 39 continues to read as follows:
2. The FAA amends § 39.13 by adding the following new airworthiness directive:
Rolls-Royce Deutschland Ltd & Co KG (formerly Rolls-Royce plc): Docket No. Start Printed Page 53612FAA-2006-25272; Directorate Identifier 2006-NE-16-AD.
Comments Due Date
(a) The Federal Aviation Administration (FAA) must receive comments on this airworthiness directive (AD) action by November 13, 2006.
(c) This AD applies to Rolls-Royce Deutschland Ltd & Co KG (RRD) Dart 528, 529, 532, 535, 542, and 552 series turbofan engines. These engines are installed on, but not limited to, Hawker Siddeley, Argosy AW.650, Fairchild Hiller F-27, F-27A, F-27B, F-27F, F-27G, F-27J, FH-227, FH-227B, FH-227C, FH-227D, FH-227E, Fokker F.27 all marks; British Aircraft Corporation Viscount 744, 745D and 810; and Gulfstream G-159 airplanes.
(d) This AD results from reports of high pressure turbine (HPT) disk rim failures. We are issuing this AD to prevent HPT disk rim failures resulting in the release of portions of the HPT disk, uncontained engine failure, and damage to the airplane.
(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.
(f) Using RRD DART Service Bulletin (SB) Da72-543, dated July 11, 2003, and the scheme detailed in RRD Repair Instruction, “Restoration of HPT Blade Platform and Shroud, DRS 611,” dated January 20, 2005, inspect and repair HPT blade platforms and shroud abutment faces by weld build-up:
(1) After no more than 1,500 flight hours from the date of issue of this AD, if the engine has not been previously inspected or reworked to the DRS 611 standard;
(2) Each time new blades are installed; and
(3) Before exceeding 7,400 hours since last HPT blade rework.
Alternative Methods of Compliance
(g) 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.
(h) LBA airworthiness directive 2003-217, dated August 7, 2003, also addresses the subject of this AD.
Issued in Burlington, Massachusetts, on September 6, 2006.
Peter A. White,
Acting Manager, Engine and Propeller Directorate, Aircraft Certification Service.
[FR Doc. E6-15049 Filed 9-11-06; 8:45 am]
BILLING CODE 4910-13-P