[Federal Register: July 25, 2005 (Volume 70, Number 141)]
[Proposed Rules]
[Page 42515-42517]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr25jy05-14]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 2001-NE-02-AD]
RIN 2120-AA64
Airworthiness Directives; Rolls-Royce Deutschland (Formerly
Rolls-Royce plc) Models Tay 650-15 and 651-54 Turbofan Engines
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking (NPRM).
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SUMMARY: The FAA proposes to supersede an existing airworthiness
directive (AD) for Rolls-Royce Deutschland (formerly Rolls-Royce plc)
(RRD) models Tay 650-15 and 651-54 turbofan engines. That AD currently
requires borescope inspection of the high pressure compressor (HPC)
stage 12 disc assembly to detect damage caused by HPC outlet guide vane
(OGV) retaining bolt failure, and replacement of unserviceable parts
with serviceable parts. That AD also requires as terminating action,
the incorporation of a new design retention arrangement for the HPC OGV
to prevent HPC OGV retaining bolt failure. This proposed AD would
require the same actions but extends the terminating action compliance
time for Tay 650-15 engines. This proposed AD would also include
references to later revisions of two of the applicable RRD service
bulletins (SBs). This proposed AD results from findings that the
terminating action compliance time for Tay 650-15 engines can be
extended. We are proposing this AD to prevent an uncontained failure of
the HPC stage 11/12 disc spacer, which could result in damage to the
airplane.
DATES: We must receive any comments on this proposed AD by September
23, 2005.
ADDRESSES: Use one of the following addresses to submit comments on
this proposed AD:
By mail: Federal Aviation Administration (FAA), New
England Region, Office of the Regional Counsel, Attention: Rules Docket
No. 2001-NE-02-AD, 12 New England Executive Park, Burlington, MA 01803-
5299.
By fax: (781) 238-7055.
By e-mail: 9-ane-adcomment@faa.gov.
You can get the service information identified in this proposed AD
from Rolls-Royce plc, P.O. Box 31 Derby, DE24 8BJ, United Kingdom;
telephone 011-44-1332-242424; fax 011-44-1332-249936.
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: Jason Yang, Aerospace Engineer, Engine
Certification Office, FAA, Engine and Propeller Directorate, 12 New
England Executive Park, Burlington, MA 01803-5299; telephone (781) 238-
7747; fax (781) 238-7199.
SUPPLEMENTARY INFORMATION:
Comments Invited
We invite you to submit any written relevant data, views, or
arguments regarding this proposal. Send your comments to an address
listed under ADDRESSES. Include ``AD Docket No. 2001-NE-02-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 proposed
AD. If a person contacts us verbally, and that contact relates to a
substantive part of this proposed 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 proposed AD in light of those
comments.
Examining the AD Docket
You may examine the AD Docket (including any comments and service
information), by appointment, between 8 a.m. and 4:30 p.m., Monday
through Friday, except Federal holidays. See ADDRESSES for the
location.
Discussion
On January 18, 2002, the FAA issued AD 2002-01-29, Amendment 39-
12624 (67 FR 4652, January 31, 2002). That AD requires borescope
inspection of the HPC stage 12 disc assembly to detect damage caused by
HPC OGV retaining bolt failure, and replacement of unserviceable parts
with serviceable parts. That AD also requires as terminating action,
the incorporation of a new design retention arrangement for the HPC
OGV, to prevent HPC OGV retaining bolt failure.
Actions Since AD 2002-01-29 Was Issued
Since we issued AD 2002-01-29, the FAA and the Luftfhart Bundesamt
(LBA), which is the airworthiness authority for Germany, reassessed the
time period allowed for incorporation of the terminating action
compliance time for Tay 650-15 engines. Part of that reassessment takes
into consideration the major reduction in flying time of the Tay 650-15
airliner fleet, since September 11, 2001. The FAA and LBA concluded
that the terminating action compliance time for the Tay 650-15 engines
can be safely extended by 25 months.
Special Flight Permits Paragraph Removed
Paragraph (f) of the current AD, AD 2002-01-29, contains a
paragraph pertaining to special flight permits. Even though this
proposed AD does not contain a similar paragraph, we have made no
changes with regard to the use of special flight permits to operate the
airplane to a repair facility to do the work required by this AD. In
July 2002, we published a new part 39 that contains a general authority
regarding special flight permits and airworthiness directives; see
Docket No. FAA-2004-8460, Amendment 39-9474 (69 FR 47998, July 22,
2002). Thus, when we now supersede ADs we will not include a specific
paragraph on special flight permits unless we want to limit the use of
that general authority granted in section 39.23.
Relevant Service Information
We have reviewed and approved the technical contents of RRD SB No.
TAY-72-1498, Revision 2, dated December 31, 2004. That SB describes
procedures for installing new design retaining and locking hardware for
the HPC OGV and outer seal housing assembly. The LBA classified this
service bulletin as mandatory and issued AD D-2004-365, dated January
31, 2005, in order to ensure the airworthiness of these RRD engines in
Germany.
[[Page 42516]]
Bilateral Agreement Information
This engine model is manufactured in Germany and is 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 has kept the FAA informed of
the situation described above. We have 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.
FAA's Determination and Requirements of the Proposed AD
We have evaluated all pertinent information and identified an
unsafe condition that is likely to exist or develop on other products
of this same type design. Therefore, we are proposing this AD, which
would require:
Initial and repetitive borescope inspections of the stage
12 rotor disc assembly for damage due to failed HPC OGV retaining
bolts, and removal of engine from service if damage is observed on the
stage 12 rotor disc.
As terminating action to the repetitive inspections,
removal from service of existing HPT rotor inner seal support assembly,
HP compressor outlet guide vane (5-span), HP compressor outlet guide
vane (6-span), HP rotor thrust bearing housing assembly, and diffuser
case assembly.
The proposed AD would require that you do these actions using the
service information described previously.
Costs of Compliance
There are about 400 Tay 650-15 and 651-54 turbofan engines of the
affected design in the worldwide fleet. We estimate that 105 engines
installed on airplanes of U.S. registry would be affected by this
proposed AD. We also estimate that it would take about 3 work hours per
engine to perform the proposed borescope inspection, and that the
average labor rate is $65 per work hour. Required parts would cost
about $3,200 per engine. We estimate that one third of the engines will
have the parts replaced at time of engine overhaul. We also estimate
that one third of the engines will have the parts replaced during an
engine mid-life shop visit. We also estimate that one third of the
engines will have the parts replaced at an engine shop visit dedicated
for these parts replacements, at a cost of about $90,000 per engine.
Based on these figures, we estimate the total cost of the proposed AD
to U.S. operators to be $3,600,000.
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 summary of the costs to comply with this proposal 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. 2001-NE-02-AD'' in your request.
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 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 removing Amendment 39-12624 (67 FR
4652, January 31, 2002) and by adding a new airworthiness directive, to
read as follows:
Rolls-Royce Deutschland (formerly Rolls-Royce plc): Docket No. 2001-
NE-02-AD.
Comments Due Date
(a) The Federal Aviation Administration (FAA) must receive
comments on this airworthiness directive (AD) action by September
23, 2005.
Affected ADs
(b) This AD supersedes AD 2002-01-29, Amendment 39-12624.
Applicability
(c) This AD applies to Rolls-Royce Deutschland (formerly Rolls-
Royce plc) (RRD) models Tay 650-15 and 651-54 turbofan engines with
high pressure compressor (HPC) outlet guide vane (OGV) retaining
bolts part numbers (P/Ns) BLT3602, DU909, and DU818 installed. These
engines are installed on, but not limited to Boeing 727 and Fokker
F.28 Mark 0100 airplanes.
Unsafe Condition
(d) This AD results from RRD relaxing the terminating action
compliance time for Tay 650-15 engines due to reassessment by RRD.
We are proposing this AD to prevent an uncontained failure of the
HPC stage 11/12 disc spacer, which could result in 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.
Initial Inspection
(f) Perform a borescope inspection of the rear side of the stage
12 rotor disc at or before accumulating 8,000 cycles-since-new on
the OGV retaining bolts, or within 30 days from the effective date
of this AD, whichever occurs later. Use paragraph 3.A.(1) of the
Accomplishment Instructions of RRD Mandatory Service Bulletin (MSB)
Tay-72-1483, Revision 2, dated October 20, 2000, to do the
inspection. If damage is observed on the stage 12 rotor disc, remove
the engine from service.
Repetitive Inspections
(g) Thereafter, perform repetitive borescope inspections of the
rear side of the stage 12 rotor disc no earlier than 1,800 and no
later than 2,200 cycles-since-last-inspection, or no later than 18
months since-last-inspection,
[[Page 42517]]
whichever occurs first. Use paragraph 3.A.(1) of the Accomplishment
Instructions of RRD MSB Tay-72-1483, Revision 2, dated October 20,
2000, to do the inspections. If damage is observed on the stage 12
rotor disc, remove the engine from service.
OGV Retaining Bolt Replacement
(h) For engines that had OGV bolts replaced with new bolts P/Ns
BLT3602, DU909, and DU818 as specified in RRD SB Tay-72-1484, dated
November 15, 1999, or Revision 1, dated December 17, 1999, the
initial and repetitive inspection requirements, based on engine
cycles-since-bolt installation, are the same as specified in
paragraphs (f) and (g) of this AD.
Terminating Action
(i) As terminating action for the inspections required by this
AD, do the following:
(1) Before November 1, 2007 for Tay 650-15 engines, and before
October 1, 2012 for Tay 651-54 engines, remove from service the
parts listed in the following Table 1:
Table 1.--Parts To Be Removed From Service
------------------------------------------------------------------------
Part No. Part name
------------------------------------------------------------------------
JR12314A............................... HPT Rotor Inner Seal Support
Assembly.
EU57842A............................... HP Compressor Outlet Guide Vane
5-Span.
EU57843A............................... HP Compressor Outlet Guide Vane
6-Span.
JR30962A............................... HP Rotor Thrust Bearing Housing
Assembly.
JR30568A............................... Diffuser Case Assembly.
KB7106................................. Tab Washer.
EU12042................................ Retaining Lock Plate.
DU818.................................. Hex Head Bolt.
------------------------------------------------------------------------
(2) Information on removing these parts from service can be
found in RRD MSB Tay-72-1498, dated October 20, 2000, or RRD MSB
Tay-72-1498, Revision 1, dated December 1, 2000, or RRD SB Tay-72-
1498, Revision 2, dated December 31, 2004.
(j) After performing the actions specified in paragraph (i) of
this AD, the inspections specified in paragraphs (f) through (h) of
this AD are no longer required.
Alternative Methods of Compliance
(k) 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
(l) Luftfhart Bundesamt airworthiness directive D-2004-365,
dated January 31, 2005, also addresses the subject of this AD.
Issued in Burlington, Massachusetts, on July 18, 2005.
Jay J. Pardee,
Manager, Engine and Propeller Directorate, Aircraft Certification
Service.
[FR Doc. 05-14574 Filed 7-22-05; 8:45 am]
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