[Federal Register Volume 65, Number 131 (Friday, July 7, 2000)]
[Proposed Rules]
[Pages 41884-41885]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 00-17230]


 ========================================================================
 Proposed Rules
                                                 Federal Register
 ________________________________________________________________________
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 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.
 
 ========================================================================
 

  Federal Register / Vol. 65, No. 131 / Friday, July 7, 2000 / Proposed 
Rules  

[[Page 41884]]



DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2000-NE-03-AD]
RIN 2120-AA64


Airworthiness Directives; Rolls-Royce Spey 555-15, -15H, -15N, 
and -15P 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 (RR) plc Spey 555-15, 
-15H, -15N, and -15P turbofan engines. This proposal would require 
modification of the low pressure (LP) turbine stage 2 nozzle guide vane 
(NGV) support ring seal assembly. This proposal is prompted by two 
instances of disk drive arm damage. In both cases, heavy damage to the 
stage 1 LP turbine to stage 2 LP turbine disk drive arm occurred as a 
result of an out of balance condition following the failure of a stage 
2 LP turbine blade. The actions specified by the proposed AD are 
intended to prevent damage to the disk drive arm which could result in 
loss of stage 1 LP turbine to stage 2 LP turbine disk drive, a turbine 
overspeed condition and possible uncontained disk failure and damage to 
the airplane.

DATES: Comments must be received by September 5, 2000.

ADDRESSES: Submit comments in triplicate to the Federal Aviation 
Administration (FAA), New England Region, Office of the Regional 
Counsel, Attention: Rules Docket No. 2000-NE-03-AD, 12 New England 
Executive Park, Burlington, MA 01803-5299. Comments may also be 
submitted to the Rules Docket by using the following Internet address: 
``[email protected].'' 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, PO Box 31, Derby, England, DE248BJ; 
telephone No. 011-44-1332-242-424; FAX No. 011-44-1332-245-418. This 
information may be examined at the FAA, New England Region, Office of 
the Regional Counsel, 12 New England Executive Park, Burlington, MA 
01803-5299.

FOR FURTHER INFORMATION CONTACT: James Lawrence, Aerospace Engineer, 
Engine Certification Office, FAA, Engine and Propeller Directorate, 12 
New England Executive Park, Burlington, MA 01803-5299; telephone No. 
781-238-7176; FAX No. 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 in triplicate 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 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 2000-ANE-03-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. 2000-ANE-03-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 (U.K.), recently notified the Federal 
Aviation Administration (FAA) that an unsafe condition may exist on 
Rolls-Royce plc (RR) Spey 555-15, -15H, -15N, and -15P turbofan 
engines. The CAA advises that there have been two occurrences of damage 
to the disk drive arm.

Manufacturer's Service Information

    Rolls-Royce plc has issued Service Bulletin (SB) No. Sp 72-1063, 
dated May 1999, that specifies instructions for machining existing LP 
turbine stage 2 NGV support ring seal assemblies. The CAA classified 
this service bulletin as mandatory and issued AD 007-05-99 in order to 
ensure the airworthiness of these RR Spey 555-15 series turbofan 
engines in the U.K.

Bilateral Airworthiness Agreement

    This engine model is manufactured in the U.K., 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.
    Since an unsafe condition has been identified that is likely to 
exist or develop on other RR Spey 555-15, -15H, -15N, and -15P turbofan 
engines of the same type design, the proposed AD would require 
reworking the existing LP turbine stage 2 NGV support ring seal 
assemblies within three years after the effective date of the proposed 
AD. The actions would be required to be accomplished in accordance with 
the service bulletin described previously.

[[Page 41885]]

Economic Impact

    There are approximately 310 engines of the affected design in the 
worldwide fleet. The FAA estimates that 60 engines installed on 
aircraft of U.S. registry would be affected by this proposed AD. It 
will take approximately 2.0 work hours per engine to accomplish the 
proposed actions. The average labor rate is $60 per work hour. Since 
this action is a rework of existing parts, there is no required parts 
cost. Based on these figures, the FAA estimates the total cost impact 
of the proposed AD on U.S. operators to be $7,200.

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. 2000-NE-03-AD.

Applicability

    This AD is applicable to Rolls-Royce plc Spey 555-15, -15H, -
15N, and -15P turbofan engines. These engines are installed on but 
not limited to Fokker F.28 Mark 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 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 (b) 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 below, unless 
it has already been completed.
    To prevent damage to the disk drive arm which could result in 
loss of stage 1 LP turbine to stage 2 LP turbine disk drive, a 
turbine overspeed condition and possible uncontained disk failure 
and damage to the airplane, do the following:

Rework Instructions

    (a) Within three years after the effective date of this AD, 
rework the LP turbine stage 2 NGV support ring seal assembly in 
accordance with paragraphs 2.A. through 2.C. of the Accomplishment 
Instructions of RR service bulletin (SB) No. Sp 72-1063.

Alternative Methods of Compliance

    (b) 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 (ECO). 
Operators shall submit their request 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

    (c) 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 requirements of this AD can be accomplished.

    Issued in Burlington, Massachusetts, on June 30, 2000.
David A. Downey,
Assistant Manager, Engine and Propeller Directorate, Aircraft 
Certification Service.
[FR Doc. 00-17230 Filed 7-6-00; 8:45 am]
BILLING CODE 4910-13-P