[Federal Register Volume 67, Number 21 (Thursday, January 31, 2002)]
[Rules and Regulations]
[Pages 4652-4654]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 02-2060]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2001-NE-02-AD; Amendment 39-12624; AD 2002-01-29]
RIN 2120-AA64


Airworthiness Directives; Rolls-Royce, plc. Models Tay 650-15 and 
651-54 Turbofan Engines

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule; request for comments.

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SUMMARY: This amendment adopts a new airworthiness directive (AD) that 
is applicable to Rolls-Royce, plc (RR) models Tay 650-15 and 651-54 
turbofan engines. This action 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. This action 
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 amendment is prompted by service reports of cracked 
HPC stage 11/12 disc spacers. The actions specified in this AD are 
intended to prevent an uncontained failure of the HPC stage 11/12 disc 
spacer, which could result in damage to the airplane.

DATES: Effective February 15, 2002. The incorporation by reference of 
certain publications listed in the rule is approved by the Director of 
the Federal Register as of February 15, 2002.
    Comments for inclusion in the Rules Docket must be received on or 
before April 1, 2002.

ADDRESSES: Submit comments in triplicate to the 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. Comments may be inspected at 
this location, by appointment, between 8 a.m. and 4:30 p.m., Monday 
through Friday, except Federal holidays. Comments may also be sent via 
the Internet using the following address: ``[email protected]''. 
Comments sent via the Internet must contain the docket number in the 
subject line.
    The service information referenced in this AD may be obtained from 
Rolls-Royce plc, PO Box 31 Derby, DE24 8BJ, United Kingdom; telephone 
011-44-1332-242424; fax 011-44-1332-249936. This information may be 
examined at the FAA, by appointment, between 8 a.m. and 4:30 p.m., 
Monday through Friday, except Federal holidays, at the FAA, New England 
Region, Office of the Regional Counsel, 12 New England Executive Park, 
Burlington, MA; or at the Office of the Federal Register, 800 North 
Capitol Street, NW., suite 700, Washington, DC.

FOR FURTHER INFORMATION CONTACT: Keith Mead, Aerospace Engineer, Engine 
Certification Office, FAA, Engine and Propeller Directorate, 12 New 
England Executive Park, Burlington, MA 01803-5299; telephone (781) 238-
7744; fax (781) 238-7199.

SUPPLEMENTARY INFORMATION: The Civil Aviation Authority (CAA), which is 
the airworthiness authority for the United Kingdom (UK), recently 
notified the FAA that an unsafe condition may exist on RR models Tay 
650-15 and 651-54 turbofan engines. The CAA advises that four cracked 
HPC stage 11/12 spacers have been found during engine overhaul. 
Investigation has concluded that the spacer cracking results from prior 
failures of the HPC OGV retaining bolts. The separated OGV bolt 
material is released into a cavity between the inner seal support 
assembly air seal and stage 12 rotor disc assembly, damaging the disc 
assembly, resulting in high stresses and cracking of the HPC stage 11/
12 spacer. Loose object damage resulting from OGV retaining bolt 
material release is clearly visible during borescope inspection of the 
stage 12 rotor disc assembly rear face. Based on an engineering review, 
a redesign has been introduced to reduce the loading on the OGV 
retaining bolts, introduced by mandatory service bulletin (SB) Tay-72-
1498, which is terminating action for this AD.

Manufacturer's Service Information

    Rolls-Royce, plc has issued mandatory SB's Tay-72-1483, Revision 2, 
dated October 20, 2000, Tay-72-1498, dated October 20, 2000, and Tay-
72-1498, Revision 1, dated December 1, 2000, that specify procedures 
for:
     Initial and repetitive borescope inspections, based on 
bolt cyclic life exposure, of the stage 12 rotor disc assembly for 
damage due to failed HPC OGV retaining bolts and, if necessary, 
replacement with serviceable parts.
     Introduction of revised retaining and locking features for 
the HPC OGV and outer seal spacer, to eliminate stage 12 rotor disc 
assembly damage and stage 11/12 spacer cracking.
    The CAA has classified SB's Tay-72-1483, Revision 2, dated October 
20, 2000; and Tay-72-1498, Revision 1, dated December 1, 2000; as 
mandatory and issued AD 005-12-99, dated December 2, 1999; and AD 003-
10-2000, dated December 1, 2000, in order to assure the airworthiness 
of these RR Tay engines in the UK.

Bilateral Airworthiness Agreement

    These engines are manufactured in the UK, and are type certificated 
for operation in the United States under the provisions of Sec. 21.29 
of the Federal Aviation Regulations (14 CFR 21.29) and the applicable 
bilateral airworthiness agreement. Pursuant to this bilateral 
airworthiness agreement, the CAA has kept the FAA informed of the 
situation described above. The FAA has examined the findings of the 
CAA, 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 of an Unsafe Condition and Required Actions

    Since an unsafe condition has been identified that is likely to 
exist or develop on other RR models Tay 650-15 and 651-54 turbofan 
engines of the same type design, this AD is being issued to prevent an 
uncontained failure of the HPC stage 11/12 disc spacer, which could 
result in damage to the airplane. This AD requires:
     Initial and repetitive borescope inspections of the stage 
12 rotor disc assembly for damage due to failed HPC OGV retaining 
bolts, and replacement with serviceable parts as required.
     Introduction of revised retaining and locking features for 
the HPC OGV and outer seal spacer, to eliminate stage 12 rotor disc 
assembly damage and stage

[[Page 4653]]

11/12 spacer cracking due to failed HPC OGV retaining bolts.
    The actions must be done in accordance with the service bulletins 
described previously.

Immediate Adoption of This AD

    Since a situation exists that requires the immediate adoption of 
this regulation, it is found that notice and opportunity for prior 
public comment hereon are impracticable, and that good cause exists for 
making this amendment effective in less than 30 days. Therefore, a 
situation exists that allows the immediate adoption of this regulation.

Comments Invited

    Although this action is in the form of a final rule that involves 
requirements affecting flight safety and, thus, was not preceded by 
notice and an opportunity for public comment, comments are invited on 
this rule. Interested persons are invited to comment on this rule by 
submitting such written data, views, or arguments as they may desire. 
Communications should identify the Rules Docket number and be submitted 
in triplicate to the address specified under the caption ADDRESSES. All 
communications received on or before the closing date for comments will 
be considered, and this rule may be amended in light of the comments 
received. Factual information that supports the commenter's ideas and 
suggestions is extremely helpful in evaluating the effectiveness of the 
AD action and determining whether additional rulemaking action would be 
needed.
    Comments are specifically invited on the overall regulatory, 
economic, environmental, and energy aspects of the rule that might 
suggest a need to modify the rule. All comments submitted will be 
available, both before and after the closing date for comments, in the 
Rules Docket for examination by interested persons. A report that 
summarizes each FAA-public contact concerned with the substance of this 
AD will be filed in the Rules Docket.
    Commenters wishing the FAA to acknowledge receipt of their comments 
submitted in response to this action must submit a self-addressed, 
stamped postcard on which the following statement is made: ``Comments 
to Docket Number 2001-NE-02-AD.'' The postcard will be date stamped and 
returned to the commenter.

Regulatory Analysis

    This final rule does not have federalism implications, as defined 
in Executive Order 13132, because it 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. Accordingly, 
the FAA has not consulted with state authorities prior to publication 
of this final rule.
    The FAA has determined that this regulation is an emergency 
regulation that must be issued immediately to correct an unsafe 
condition in aircraft, and is not a ``significant regulatory action'' 
under Executive Order 12866. It has been determined further that this 
action involves an emergency regulation under DOT Regulatory Policies 
and Procedures (44 FR 11034, February 26, 1979). If it is determined 
that this emergency regulation otherwise would be significant under DOT 
Regulatory Policies and Procedures, a final regulatory evaluation will 
be prepared and placed in the Rules Docket. A copy of it, if filed, may 
be obtained from the Rules Docket at the location provided under the 
caption ADDRESSES.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Incorporation by 
reference, Safety.

Adoption of the Amendment

    Accordingly, pursuant to the authority delegated to me by the 
Administrator, the Federal Aviation Administration amends part 39 of 
the Federal Aviation Regulations (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. Section 39.13 is amended by adding the following new 
airworthiness directive:

2002-01-29  Rolls-Royce, plc: Amendment 39-12624. Docket No. 2001-
NE-02-AD.

Applicability

    This airworthiness directive (AD) is applicable to Rolls-Royce, 
plc. (RR) models Tay 650-15 and 651-54 turbofan engines with high 
pressure compressor (HPC) outlet guide vane (OGV) retaining bolts 
part numbers (P/N's) BLT3602, DU909, and DU818 installed. These 
engines are installed on, but not limited to Boeing 727 and Fokker 
F.28 Mark 0100 airplanes.

    Note 1: This AD applies to each engine identified in the 
preceding applicability provision, regardless of whether it has been 
modified, altered, or repaired in the area subject to the 
requirements of this AD. For engines that have been modified, 
altered, or repaired so that the performance of the requirements of 
this AD is affected, the owner/operator must request approval for an 
alternative method of compliance in accordance with paragraph (e) of 
this AD. The request should include an assessment of the effect of 
the modification, alteration, or repair on the unsafe condition 
addressed by this AD; and, if the unsafe condition has not been 
eliminated, the request should include specific proposed actions to 
address it.

Compliance

    Compliance with this AD is required as indicated, unless already 
done.
    To prevent an uncontained failure of the HPC stage 11/12 disc 
spacer, which could result in damage to the airplane, do the 
following:

Initial Inspection

    (a) Perform borescope inspection to the rear side of the stage 
12 rotor disc in accordance with paragraph 3.A.(1) of the 
Accomplishment Instructions of RR Mandatory Service Bulletin (SB) 
Tay-72-1483, Revision 2, dated October 20, 2000, at or before 
accumulating 8,000 cycles on the OGV retaining bolts, or within 30 
days from the effective date of this AD, whichever occurs later. If 
damage is observed on the stage 12 rotor disc, replace unserviceable 
parts with serviceable parts as necessary.

Repetitive Inspections

    (b) 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, whichever occurs first, in accordance 
with paragraph 3.A.(1) of the Accomplishment Instructions of RR 
mandatory SB Tay-72-1483, Revision 2, dated October 20, 2000. If 
damage is observed on the stage 12 rotor disc, replace unserviceable 
parts with serviceable parts as necessary.

OGV Retaining Bolt Replacement

    (c) For engines that had OGV bolts replaced with new bolts P/N's 
BLT3602, DU909, and DU818 as specified in RR SB Tay-72-1484, the 
initial and repetitive inspection requirements, based on engine 
cycles-since-bolt installation, are the same as specified in 
paragraphs (a) and (b) of this AD.

Terminating Action for the Inspections Required by This AD

    (d) Before October 1, 2005 for Tay 650-15 engines, and before 
October 1, 2012 for Tay 651-54 engines, install new design retaining 
and locking hardware for the HPC OGV and outer seal housing 
assembly, in accordance with paragraph 3 of the Accomplishment 
Instructions of RR mandatory SB Tay-72-1498, dated October 20, 2000, 
or RR mandatory SB Tay-72-1498, Revision 1, dated December 1, 2000. 
After performing this action, the inspections specified in 
paragraphs (a) through (c) of this AD are no longer required.

Alternative Methods of Compliance

    (e) An alternative method of compliance or adjustment of the 
compliance time that

[[Page 4654]]

provides an acceptable level of safety may be used if approved by 
the Manager, Engine Certification Office (ECO). Operators must 
submit their requests through an appropriate FAA Principal 
Maintenance Inspector, who may add comments and then send it to the 
Manager, ECO.

    Note 2: Information concerning the existence of approved 
alternative methods of compliance with this airworthiness directive, 
if any, may be obtained from the ECO.

Special Flight Permits

    (f) Special flight permits may be issued in accordance with 
Secs. 21.197 and 21.199 of the Federal Aviation Regulations (14 CFR 
21.197 and 21.199) to operate the airplane to a location where the 
requirements of this AD can be done.

Documents That Have Been Incorporated by Reference

    (g) The inspections and replacements must be done in accordance 
with the following Rolls-Royce plc, mandatory SB's:

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             Document No.                   Pages              Revision                        Date
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SB Tay-72-1483........................        1-4     2........................  October 20, 2000.
                                                5     Original.................  December 2, 1999.
Appendix 1............................        1-4     2........................  October 20, 2000.
Appendix 2............................        1-2     2........................  October 20, 2000.
    Total pages: 11...................
SB Tay-72-1498........................       1-38     Original.................  October 20, 2000.
    Total pages: 38...................
SB Tay-72-1498........................       1-38     1........................  December 1, 2000
    Total pages: 38...................
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The incorporations by reference were approved by the Director of the 
Federal Register in accordance with 5 U.S.C. 552(a) and 1 CFR part 
51. Copies may be obtained from Rolls-Royce plc, PO Box 31 Derby, 
DE24 8BJ, United Kingdom; telephone 011-44-1332-242424; fax 011-44-
1332-249936. Copies may be inspected, by appointment, at the FAA, 
New England Region, Office of the Regional Counsel, 12 New England 
Executive Park, Burlington, MA; or at the Office of the Federal 
Register, 800 North Capitol Street, NW., suite 700, Washington, DC.

    Note 3: The subject of This AD is addressed in Civil 
Airworthiness Authority airworthiness directives AD 005-12-99, dated 
December 2, 1999; and AD 003-10-2000, dated December 1, 2000, in 
order to assure the airworthiness of these RR Tay engines in the UK.

Effective Date of This AD

    (h) This amendment becomes effective on February 15, 2002.

    Issued in Burlington, Massachusetts, on January 18, 2002.
Thomas A. Boudreau,
Acting Manager, Engine and Propeller Directorate, Aircraft 
Certification Service.
[FR Doc. 02-2060 Filed 1-30-02; 8:45 am]
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