[Federal Register Volume 67, Number 75 (Thursday, April 18, 2002)]
[Proposed Rules]
[Pages 19134-19135]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 02-9394]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2001-NE-14-AD]
RIN 2120-AA64


Airworthiness Directives; Rolls-Royce plc Models Spey 506-14A, 
555-15, 555-15H, 555-15N, and 555-15P Turbojet Engines

AGENCY: Federal Aviation Administration, DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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SUMMARY: The Federal Aviation Administration (FAA) proposes to adopt a 
new airworthiness directive (AD) that is applicable to Rolls-Royce plc 
(RR) Spey 506-14A, 555-15, 555-15H, 555-15N, and 555-15P turbojet 
engines. This proposal would require replacing certain stage 2 low 
pressure turbine (LPT) blades with new redesigned stage 2 LPT blades. 
This proposal is prompted by several reports of failures of stage 2 LPT 
blades. The actions specified by the proposed AD are intended to 
prevent failure of the stage 2 LPT blades, which could result in an 
engine shutdown.

DATES: Comments must be received by June 17, 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-14-AD, 12 New England 
Executive Park, Burlington, MA 01803-5299. Comments may be inspected at 
this location, by appointment, between 8:00 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 the proposed rule 
may be obtained from Rolls-Royce plc, P.O. Box 31, Derby DE24 6BJ, UK; 
Telephone 44 (0) 1332 242424; fax 44 (0) 1332 249936. This information 
may be examined, by appointment, at the FAA, New England Region, Office 
of the Regional Counsel, 12 New England Executive Park, Burlington, MA.

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:

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 action 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 action must submit a self-addressed, 
stamped postcard on which the following statement is made: ``Comments 
to Docket Number 2001-NE-14-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. 2001-NE-14-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 FAA that 
an unsafe condition may exist on RR Spey 506-14A, 555-15, 555-15H, 555-
15N, and 555-15P turbojet engines. The CAA advises that there have been 
several failures of stage 2 LPT blades that have resulted in in-flight 
shutdown events. Analysis shows that an unacceptable probability level 
of a failure of the stage 2 LPT blades, which could result in an engine 
shutdown, could occur if the existing design blades are not replaced 
within the specified compliance times.

Manufacturer's Service Information

    RR has issued service bulletin (SB) No. Sp72-1064, Revision 1, 
dated February 1, 2001, that provides procedures to replace existing 
stage 2 LPT blades with new redesigned stage 2 LPT blades. The CAA 
classified this service bulletin as mandatory and issued AD 005-07-2000 
in order to assure the airworthiness of these RR Spey 506-14A, 555-15, 
555-15H, 555-15N, and 555-15P turbojet engines in the UK.

Bilateral Agreement Information

    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 Requirements of This AD

    Since an unsafe condition has been identified that is likely to 
exist or develop on other RR Spey 506-14A,

[[Page 19135]]

555-15, 555-15H, 555-15N, and 555-15P turbojet engines of the same type 
design that are used on airplanes registered in the United States, the 
proposed AD would require replacing existing stage 2 LPT blades, part 
numbers (P/N's) JR34024 and JR34069, with new redesigned stage 2 LPT 
blades, P/N JR35388. The actions would be required to be done in 
accordance with the service bulletin described previously.

Economic Analysis

    There are approximately 407 engines of the affected design in the 
worldwide fleet. The FAA estimates that 54 engines installed on 
airplanes of U.S. registry would be affected by this proposed AD. The 
FAA also estimates that it would take approximately 200 work hours per 
engine to accomplish the proposed actions, and that the average labor 
rate is $60 per work hour. Required parts would cost approximately 
$89,981 per engine. Based on these figures, the total cost of the 
proposed AD on U.S. operators is estimated to be $5,506,974.

Regulatory Analysis

    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. 2001-NE-14-AD.

Applicability

    This airworthiness directive (AD) is applicable to Rolls-Royce 
plc (RR) Spey 506-14A, 555-15, 555-15H, 555-15N, and 555-15P 
turbojet engines with stage 2 low pressure turbine (LPT) blades, 
part numbers (P/N's) JR34024 or JR34069 installed. These engines are 
installed on, but not limited to British Aerospace Airbus Ltd. BAC 
1-11 and Fokker F.28 Mark 1000, Mark 2000, Mark 3000, and Mark 4000 
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 (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, unless already 
done.
    To prevent failure of the stage 2 LPT blades, which could result 
in an engine shutdown, do the following:
    (a) Replace existing stage 2 LPT blades P/N's JR34024 and 
JR34069 with complete sets of serviceable blades in accordance with 
the Accomplishment Instructions of RR service bulletin Sp72-1064, 
Revision 1, dated February 1, 2001, and the following compliance 
times:
    (1) For RR Spey 506-14A engines, replace blades at the next 
piece-part opportunity, but no later than June 30, 2010.
    (2) For Spey 555-15, 555-15H, 555-15N, and 555-15P turbojet 
engines, replace blades at the next piece-part opportunity, but no 
later than December 31, 2005.

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 must 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 
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.

    Note 3: The subject of this AD is addressed in CAA airworthiness 
directive 005-07-2000.


    Issued in Burlington, Massachusetts, on April 11, 2002.
Francis A. Favara,
Acting Manager, Engine and Propeller Directorate, Aircraft 
Certification Service.
[FR Doc. 02-9394 Filed 4-17-02; 8:45 am]
BILLING CODE 4910-13-P