[Federal Register Volume 70, Number 141 (Monday, July 25, 2005)]
[Proposed Rules]
[Pages 42515-42517]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 05-14574]


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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: [email protected].
    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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