[Federal Register Volume 65, Number 179 (Thursday, September 14, 2000)]
[Proposed Rules]
[Pages 55468-55470]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 00-23585]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 98-ANE-68-AD]


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

AGENCY: Federal Aviation Administration, DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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SUMMARY: This document proposes the adoption of a new airworthiness 
directive (AD) that is applicable to Rolls-Royce, plc Tay 650-15 and 
651-54 turbofan engines. This proposal would require initial and 
repetitive visual and ultrasonic inspections of fan blades for cracks, 
and, if necessary, replacement with serviceable parts. In addition, 
this AD requires recording instances when engines are operated in a 
stabilized manner in newly prohibited ranges. This proposal is prompted 
by reports of fan blade failures. The actions specified by the proposed 
AD are intended to prevent fan blade failures, which can result in an 
uncontained engine failure, engine fire, and damage to the airplane.

DATES: Comments must be received by November 13, 2000.

ADDRESSES: Submit comments to the Federal Aviation Administration 
(FAA), New England Region, Office of the Regional Counsel, Attention: 
Rules Docket No. 98-ANE-68-AD, 12 New England Executive Park, 
Burlington, MA 01803-5299. 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. 
Comments may be inspected at this location between 8:00 a.m. and 4:30 
p.m., Monday through Friday, except Federal holidays.
    The service information referenced in the proposed rule may be 
obtained from Rolls-Royce plc, Technical Publications Department, PO 
Box 31, Derby, England DE24 8BJ; telephone 44 1332 242424, fax 44 1332 
249936. This information may be examined at the FAA, New England 
Region, Office of the Regional Counsel, 12 New England Executive Park, 
Burlington, MA.

FOR FURTHER INFORMATION CONTACT: Richard Woldan, Aerospace Engineer, 
Engine Certification Office, FAA, Engine and Propeller Directorate, 12 
New England Executive Park, Burlington, MA 01803-5299; telephone (781) 
238-7136, fax (781) 238-7199.

SUPPLEMENTARY INFORMATION:

Comments Invited

    Interested persons are invited to participate in the making of the 
proposed rule by submitting such written data, views, or arguments as 
they may desire. Communications should identify the Rules Docket number 
and be submitted to the address specified above. All communications 
received on or before the closing date for comments, specified above, 
will be considered before taking action on the proposed rule. The 
proposals contained

[[Page 55469]]

in this notice may be changed in light of the comments received.
    Comments are specifically invited on the overall regulatory, 
economic, environmental, and energy aspects of the proposed 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 summarizing each FAA-public contact concerned with 
the substance of this proposal will be filed in the Rules Docket.
    Commenters wishing the FAA to acknowledge receipt of their comments 
submitted in response to this notice must submit a self-addressed, 
stamped postcard on which the following statement is made: ``Comments 
to Docket Number 98-ANE-68-AD.'' The postcard will be date stamped and 
returned to the commenter.

Availability of NPRM's

    Any person may obtain a copy of this NPRM by submitting a request 
to the FAA, New England Region, Office of the Regional Counsel, 
Attention: Rules Docket No. 98-ANE-68-AD, 12 New England Executive 
Park, Burlington, MA 01803-5299.

Discussion

    The Civil Aviation Authority (CAA), which is the airworthiness 
authority for the United Kingdom (UK), recently notified the Federal 
Aviation Administration (FAA) that an unsafe condition may exist on 
Rolls-Royce, plc (R-R) Tay 650-15 and 651-54 turbofan engines. The CAA 
advises that they have received a report of failure of five fan blades 
in the root section during takeoff which resulted in fan case 
punctures, severing of the low pressure (LP) fuel line and an extensive 
engine fire. Investigation revealed that fatigue cracks initiated in 
the fan blade root section due to fan resonance or flutter caused by 
the engine operating in a stabilized manner between idle reverse and 
emergency maximum reverse thrust (Tay 650-15) or maximum reverse thrust 
(Tay 651-54). The aircraft flight manuals have already been revised to 
prohibit operating in a stabilized manner within these ranges. However, 
inadvertent stabilized operations in the prohibited ranges could result 
in fan blade failure. This condition, if not corrected, could result in 
fan blade failure, which can result in an uncontained engine failure, 
engine fire, and damage to the aircraft.

Service Bulletins (SBs)

    R-R has issued Service Bulletin (SB) No. Tay 72-1447, Revision 2, 
dated July 25, 2000, that specifies procedures for recording engine 
operation within the newly prohibited ranges, and SB No. Tay 72-1442, 
Revision 1, dated December 19, 1997, that describes procedures for 
inspection of fan blades. The CAA classified these SB's as mandatory in 
order to assure the airworthiness of these engines in the UK.

Bilateral Airworthiness Agreement

    This engine model is manufactured in the UK 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. 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.

Proposed Actions

    Since an unsafe condition has been identified that is likely to 
exist or develop on other engines of the same type design registered in 
the United States, the proposed AD would require initial and repetitive 
visual and ultrasonic inspections of fan blades for cracks, and, if 
necessary, replacement with serviceable parts. In addition, this AD 
would require recording instances when engines are operated in a 
stabilized manner in newly prohibited ranges. The actions would be 
required to be accomplished in accordance with the SB's described 
previously.

Economic Analysis

    There are approximately 713 engines of the affected design in the 
worldwide fleet. The FAA estimates that 451 engines installed on 
airplanes of US registry would be affected by this proposed AD. Based 
on the current utilization and shop visit rates for the affected engine 
models, the FAA estimates that the number of shop visits and 
inspections for the US fleet would be approximately 140 per year. It 
would take approximately 5 work hours per engine to accomplish the 
proposed actions at a labor rate of $60 per work hour. Assuming that 
five percent of these inspections result in a rejected fan blade set at 
a cost of approximately $100,000 per set, the annual cost impact of the 
proposed AD on US operators is estimated to be $742,000. The current 
inspection failure rate is below one percent and this cost estimate is 
believed to be conservatively high.

Regulatory Impact

    This proposed 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 proposed rule.
    For the reasons discussed above, I certify that this 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) if promulgated, will not have a significant economic impact, 
positive or negative, on a substantial number of small entities under 
the criteria of the Regulatory Flexibility Act. A copy of the draft 
regulatory evaluation prepared for this action is contained in the 
Rules Docket. A copy of it may be obtained by contacting the Rules 
Docket at the location provided under the caption ADDRESSES.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Safety.

The Proposed Amendment

    Accordingly, pursuant to the authority delegated to me by the 
Administrator, the Federal Aviation Administration proposes to amend 
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:

    Rolls-Royce, plc: Docket No. 98-ANE-68-AD.

    Applicability: Rolls-Royce, plc (R-R) Tay 650-15 and 651-54 
turbofan engines, installed on but not limited to Fokker Model F.28 
Mark 0100 and Boeing 727-QF series airplanes.

    Note 1: This airworthiness directive (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

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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 (d) 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: Required as indicated, unless accomplished 
previously.
    To prevent fan blade failure, which can result in an uncontained 
engine failure, engine fire, and damage to the aircraft, accomplish 
the following:

Record Operation in Prohibited Operating Ranges

    (a) If an engine is operated in a stabilized manner within the 
prohibited ranges described in R-R Service Bulletin (SB) No. Tay 72-
1447, Revision 2, dated July 25, 2000, paragraphs 3.A ., 3.B.(2), or 
3.C. as applicable by engine model, then prior to the next flight 
make an entry in the engine records that reflects that operation. If 
known, include the stabilized N1 speed in the engine records.

Inspections

    (b) Perform initial and repetitive inspections of fan blades in 
accordance with paragraphs 1. D. (1) through (7) of R-R SB No. Tay 
72-1442, Revision 1, dated December 19, 1997, as follows:
    (1) Perform the initial inspection at the earliest of the 
following:
    (i) If the engine records indicate that any of the conditions 
described in R-R SB No. Tay 72-1447, Revision 2, dated July 25, 
2000, paragraphs 3.A.(2), 3.A.(3), 3.B.(2)(a), 3.B.(2)(b), or 
3.C.(2), as applicable by engine model, are satisfied;
    (ii) Prior to entering in service if fan blades are installed in 
a different engine than that from which they were removed and if the 
fan blades have time-in-service since the last inspection in 
accordance with R-R SB No. Tay 72-1442;
    (iii) The next shop visit after the effective date of this AD, 
defined as the introduction of the engine into a shop that can 
perform the inspection defined in Appendix 1 of R-R SB No. Tay 72-
1442, Revision 1, dated December 19, 1997.
    (2) Thereafter, inspect at intervals not to exceed the earliest 
of paragraphs (b)(1)(i) through (b)(1)(iii) of this AD.
    (c) Remove the entire fan blade set from service if any blade 
shows crack indications and replace with serviceable parts.

Alternative Methods of Compliance

    (d) An alternative method of compliance or adjustment of the 
compliance time that provides an acceptable level of safety may be 
used if approved by the Manager, Engine Certification Office. 
Operators shall submit their request through an appropriate FAA 
Principal Maintenance Inspector, who may add comments and then send 
it to the Manager, Engine Certification Office.

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

Special Flight Permits

    (e) Special flight permits may be issued in accordance with 
sections 21.197 and 21.199 of the Federal Aviation Regulations (14 
CFR 21.197 and 21.199) to operate the aircraft to a location where 
the inspection requirements of this AD can be accomplished.

    Issued in Burlington, Massachusetts, on September 4, 2000.
David A. Downey,
Assistant Manager, Engine and Propeller Directorate, Aircraft 
Certification Service.
[FR Doc. 00-23585 Filed 9-13-00; 8:45 am]
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