[Federal Register: June 27, 2006 (Volume 71, Number 123)]
[Proposed Rules]
[Page 36493-36495]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr27jn06-10]
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Proposed Rules
Federal Register
________________________________________________________________________
This section of the FEDERAL REGISTER contains notices to the public of
the proposed issuance of rules and regulations. The purpose of these
notices is to give interested persons an opportunity to participate in
the rule making prior to the adoption of the final rules.
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[[Page 36493]]
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2006-24777; Directorate Identifier 2006-NE-19-AD]
RIN 2120-AA64
Airworthiness Directives; Rolls-Royce Deutschland Ltd & Co KG Tay
611-8, Tay 620-15, Tay 650-15, and Tay 651-54 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 (RRD) Tay 611-8, Tay 620-15,
Tay 650-15, and Tay 651-54 series turbofan engines, with certain low
pressure (LP) compressor modules installed. This proposed AD would
require an ultrasonic inspection (UI) of LP compressor fan blades for
cracks, within 30 days after the effective date of the proposed AD on
certain serial number (SN) Tay 650-15 engines. This proposed AD would
also require repetitive UIs of LP compressor fan blades on all engines.
This proposed AD would also require, for Tay 650-15 and Tay 651-54
engines, UIs of LP compressor fan blades whenever the blade set is
removed from one engine and installed on a different engine. This
proposed AD results from a report that a set of LP compressor fan
blades failed before reaching the LP compressor fan blade full
published life limit. We are proposing this AD to prevent LP compressor
fan blades from failing due to blade root cracks, leading to
uncontained engine failure and damage to the airplane.
DATES: We must receive any comments on this proposed AD by August 28,
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 20590-001.
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-2006-24777;
Directorate Identifier 2006-NE-19-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
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 Office
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, notified us that an unsafe condition may exist on RRD Tay
611-8, Tay 620-15, Tay 650-15, and Tay 651-54 series turbofan engines.
The LBA advises that a Tay 650 LP compressor fan blade set failed
before reaching the LP compressor fan blade full published life limit.
The set of fan blades accumulated 14,166 cycles-in-service. An
investigation revealed that the set of LP compressor fan blades failed
due to cracking in the blade root. Rolls-Royce initially introduced a
fluorescent penetrant inspection in the engine manual to detect
cracking in the blade root. However, further research indicates that
repetitive UIs are most effective in detecting blade root cracks.
Relevant Service Information
We reviewed and approved RRD Service Bulletin (SB) No. TAY-72-1591,
dated May 8, 2003, that describes procedures for UI of LP compressor
fan blades for cracks on certain SNs of Tay 650-15 engines with certain
LP compressor modules. These engines may have not yet had UI of LP
compressor fan blades. We have also reviewed and approved the technical
contents of RRD SB No. TAY-72-1442, Revision 3, dated November 26,
2003, that describes procedures for UIs of LP compressor fan blades for
all RRD Tay
[[Page 36494]]
611-8, Tay 620-15, Tay 650-15, and Tay 651-54 series turbofan engines
with certain LP compressor modules. The LBA classified these SBs as
mandatory and issued airworthiness directive D-1998-055R3, dated
December 15, 2003, in order to ensure the airworthiness of these RRD
Tay 611-8, Tay 620-15, Tay 650-15, and Tay 651-54 series turbofan
engines in Germany. EASA has approved the LBA AD under approval No.
1869 on December 15, 2003.
FAA's Determination and Requirements of the Proposed AD
These RRD Tay 611-8, Tay 620-15, Tay 650-15, and Tay 651-54 series
turbofan engines are manufactured in Germany. They 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. For this reason, we are proposing this
AD, which would require:
UI of LP compressor fan blades for cracks, within 30 days
after the effective date of the proposed AD on certain serial number
(SN) Tay 650-15 engines.
Repetitive UIs of LP compressor fan blades on all engines.
For Tay 650-15 and Tay 651-54 engines, UIs of LP
compressor fan blades whenever the blade set is removed from one engine
and installed on a different engine.
Removal of the complete LP compressor fan blade set and
the LP compressor fan disc from service, if any LP compressor fan blade
is cracked.
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 1,000 RRD Tay
611-8, Tay 620-15, Tay 650-15, and Tay 651-54 series turbofan engines
installed on airplanes of U.S. registry. We also estimate that it would
take about 4 work-hours per engine to perform a proposed inspection,
and that the average labor rate is $80 per work-hour. Required parts
would cost about $95,000 per LP compressor fan disk and $140,000 per
set of LP compressor fan blades. We estimate that 5 percent or 50
engines would require replacing the LP compressor fan disc and LP
compressor fan blade set. Based on these figures, we estimate the total
cost of the proposed AD to U.S. operators to be $11,750,000.
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. FAA-2006-24777; Directorate Identifier 2006-NE-19-AD.
Comments Due Date
(a) The Federal Aviation Administration (FAA) must receive
comments on this airworthiness directive (AD) action by August 28,
2006.
Affected ADs
(b) None.
Applicability
(c) This AD applies to Rolls-Royce Deutschland Ltd & Co KG (RRD)
Tay 611-8 and Tay 620-15 turbofan engines with low pressure (LP)
compressor module part number (P/N) MO1100AA or P/N MO1100AB
installed, and Tay 650-15 and Tay 651-54 turbofan engines with LP
compressor module P/N MO1300AA or P/N MO1300AB installed. These
engines are installed on, but not limited to, Fokker F.28 Mark 0070
and 0100 airplanes, Supplemental Type Certificate No. SA842SW,
Boeing 727 airplanes, and Gulfstream G-IV airplanes.
Unsafe Condition
(d) This AD results from a report that a set of LP compressor
fan blades failed before reaching the LP compressor fan blade full
published life limit. We are issuing this AD to prevent LP
compressor fan blades from failing due to blade root cracks, leading
to 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.
Ultrasonic Inspection (UI) of LP Compressor Fan Blades for Certain Tay
650-15 Engines That Have Not Yet Had UI of the LP Compressor Fan Blades
(f) For Tay 650-15 engines, serial numbers 17201, 17202, 17226,
17253, 17341, 17356, 17428, 17450, 17457, 17458, 17497, 17530,
17622, 17643, 17655, 17678, 17709, 17751, 17755, 17805, and 17806
that have not yet had UI of the LP compressor fan blades:
(1) Within 30 days after the effective date of this AD, perform
UI of the LP compressor fan blades for cracks.
(2) Use Part 1 of RRD Service Bulletin (SB) No. TAY-72-1591,
dated May 8, 2003, to do the inspection.
[[Page 36495]]
UI of LP Compressor Fan Blades Being Installed in a Different Engine;
Tay 650-15 and Tay 651-54 Engines
(g) For Tay 650-15 and Tay 651-54 engines, whenever LP
compressor fan blades are removed and are being installed in a
different engine:
(1) Perform UI of the LP compressor fan blades for cracks.
(2) Use Part 1 of RRD SB No. TAY-72-1442, Revision 3, dated
November 26, 2003, to do the inspection.
UI of LP Compressor Fan Blades for All Tay Engines
(h) Perform UI of the LP compressor fan blades for cracks, using
Part 2 of RRD SB No. TAY-72-1442, Revision 3, dated November 26,
2003, at the following:
(1) For Tay 650-15 and Tay 651-54 engines, at every engine shop
visit for any reason or before reaching every 4,000 flight hours-
since-last-fan-blade UI, whichever occurs first.
(2) For Tay 620-15 engines, before reaching every 4,000 flight
hours but no later than every 10 years since-last-fan-blade UI,
whichever occurs first.
(3) For Tay 611-8 engines, before reaching every 8,000 flight
hours but no later than every 10 years since-last-fan-blade UI,
whichever occurs first.
LP Compressor Fan Blades That Are Cracked
(i) If any LP compressor fan blade is cracked, then remove the
complete LP compressor fan blade set and the LP compressor fan disc
from service.
Alternative Methods of Compliance
(j) 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
(k) Luftfahrt-Bundesamt airworthiness directive D-1998-055R3,
dated December 15, 2003, which was approved by EASA under approval
No. 1869 on December 15, 2003, also addresses the subject of this
AD.
Issued in Burlington, Massachusetts, on June 21, 2006.
Thomas A. Boudreau,
Acting Manager, Engine and Propeller Directorate, Aircraft
Certification Service.
[FR Doc. E6-10087 Filed 6-26-06; 8:45 am]
BILLING CODE 4910-13-P