[Federal Register: September 12, 2006 (Volume 71, Number 176)]
[Proposed Rules]
[Page 53610-53612]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr12se06-18]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2006-25272; Directorate Identifier 2006-NE-16-AD]
RIN 2120-AA64
Airworthiness Directives; Rolls-Royce Deutschland Ltd & Co KG
(Formerly Rolls-Royce plc) Dart 528, 529, 532, 535, 542, and 552 Series
Turbofan Engines
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
ACTION: Notice of proposed rulemaking (NPRM).
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SUMMARY: 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.
DATES: We must receive any comments on this proposed AD by November 13,
2006.
ADDRESSES: 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.
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).
SUPPLEMENTARY INFORMATION:
Comments Invited
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
[[Page 53611]]
proposed 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.
Discussion
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.
Regulatory Findings
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.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Safety.
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:
PART 39--AIRWORTHINESS 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
airworthiness directive:
Rolls-Royce Deutschland Ltd & Co KG (formerly Rolls-Royce plc):
Docket No.
[[Page 53612]]
FAA-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.
Affected ADs
(b) None.
Applicability
(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.
Unsafe Condition
(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.
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.
(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.
Related Information
(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