[Federal Register Volume 68, Number 240 (Monday, December 15, 2003)]
[Proposed Rules]
[Pages 69633-69634]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 03-30851]


 ========================================================================
 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.
 
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 

  Federal Register / Vol. 68, No. 240 / Monday, December 15, 2003 / 
Proposed Rules  

[[Page 69633]]



DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2003-NE-51-AD]
RIN 2120-AA64


Airworthiness Directives; Rolls-Royce Deutschland Ltd. & Co KG, 
Models Spey 555-15, 555-15H, 555-15N, and 555-15P Turbojet Engines

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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SUMMARY: The FAA proposes to adopt a new airworthiness directive (AD) 
for Rolls-Royce Deutschland Ltd. & Co KG (RRD), models Spey 555-15, 
555-15H, 555-15N, and 555-15P turbojet engines, with magnesium split 
low pressure (LP) compressor case, part number (P/N) EU.73418A 
installed. This proposed AD would require replacement of the magnesium 
split LP compressor case with a serviceable compressor case that is a 
combination of a steel front LP compressor case and a shortened split 
compressor case. This proposed AD results from several reports of bird 
ingestion and LP stage 1 rotor blade failures that have resulted in 
penetration of the magnesium LP compressor case, and damage to the 
airplane. We are proposing this AD to prevent possible uncontained LP 
stage 1 rotor blade failures that could result in damage to the 
airplane.

DATES: We must receive any comments on this proposed AD by February 13, 
2004.

ADDRESSES: Use one of the following addresses to submit comments on 
this proposed AD:
    [sbull] By mail: Federal Aviation Administration (FAA), New England 
Region, Office of the Regional Counsel, Attention: Rules Docket No. 
2003-NE-51-AD, 12 New England Executive Park, Burlington, MA 01803-
5299.
    [sbull] By fax: (781) 238-7055.
    [sbull] By e-mail: [email protected].
    You can get the service information identified in this proposed AD 
from Rolls-Royce Deutschland Ltd & Co KG, Eschenweg 11, D-15827 
Dahlewitz, Germany, telephone +49 (0) 33-7086-1768; fax +49 (0) 33-
7086-3356.
    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: James Lawrence, Aerospace Engineer, 
Engine Certification Office, FAA, Engine and Propeller Directorate, 12 
New England Executive Park, Burlington, MA 01803-5299; telephone (781) 
238-7176; 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. 2003-NE-51-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.
    We are reviewing the writing style we currently use in regulatory 
documents. We are interested in your comments on whether the style of 
this document is clear, and your suggestions to improve the clarity of 
our communications that affect you. You may get more information about 
plain language at http://www.faa.gov/language and http://www.plainlanguage.gov.

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

    The Luftfahrt-Bundesamt (LBA), which is the airworthiness authority 
for Germany, recently notified the FAA that an unsafe condition may 
exist on RRD models Spey 555-15, 555-15H, 555-15N, and 555-15P turbojet 
engines. The LBA advises that several reports of bird ingestion and LP 
stage 1 rotor blade failures have resulted in penetration of the 
current design magnesium split LP compressor case, and damage to the 
airplane.

Relevant Service Information

    Rolls-Royce Deutschland Service Bulletin (SB) No. Sp72-893, 
Revision 3, dated August 25, 2003, describes procedures for replacing 
the magnesium split LP compressor case, P/N EU.73418A, by reworking the 
front bearing housing and reworking certain affected brackets 
necessary, and installing Modification Kit Spey 5515. The kit contains 
a new design steel front case and shortened split compressor case.

FAA's Determination and Requirements of the Proposed AD

    These RRD models Spey 555-15, 555-15H, 555-15N, and 555-15P 
turbojet engines, manufactured in Germany, are 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 LBA has kept us informed of the situation 
described above. We have examined the LBA's findings, 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. Therefore, we are proposing this AD, which would require 
replacing the current design magnesium split LP compressor case with a 
serviceable compressor case that is a combination of a steel front case 
and a shortened split case, within 60 months after the effective date 
of the AD. The AD compliance time is based on comprehensive Rolls-Royce

[[Page 69634]]

investigation and risk assessment results.

Changes to 14 CFR Part 39--Effect on the Proposed AD

    On July 10, 2002, we issued a new version of 14 CFR part 39 (67 FR 
47998, July 22, 2002), which governs the FAA's AD system. This 
regulation now includes material that relates to altered products, 
special flight permits, and alternative methods of compliance. This 
material previously was included in each individual AD. Since this 
material is included in 14 CFR part 39, we will not include it in 
future AD actions.

Costs of Compliance

    There are about 184 RRD models Spey 555-15, 555-15H, 555-15N, and 
555-15P turbojet engines of the affected design in the worldwide fleet. 
We estimate that 34 engines installed on airplanes of U.S. registry 
would be affected by this proposed AD. We also estimate that it would 
take about 6 work hours per engine to perform the proposed actions, and 
that the average labor rate is $65 per work hour. Required parts would 
cost about $37,000 per engine. Based on these figures, we estimate the 
total cost of the proposed AD to U.S. operators to be $1,271,260.

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. 2003-NE-51-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 adding the following new 
airworthiness directive:

Rolls-Royce Deutschland Ltd. & Co KG: Docket No. 2003-NE-51-AD.

Comments Due Date

    (a) The FAA must receive comments on this airworthiness 
directive (AD) action by February 13, 2004.

Affected ADs

    (b) None.

Applicability

    (c) This AD applies to Rolls-Royce Deutschland Ltd. & Co KG 
(RRD), models Spey 555-15, 555-15H, 555-15N, and 555-15P turbojet 
engines, with magnesium split low pressure (LP) compressor case, 
part number (P/N) EU.73418A installed. These engines are installed 
on, but not limited to, Fokker F.28 Mark 1000, Mark 2000, Mark 3000, 
and Mark 4000 series airplanes.

Unsafe Condition

    (d) This AD is prompted by several reports of bird ingestion and 
LP stage 1 rotor blade failures that have resulted in penetration of 
the magnesium split LP compressor case and damage to the airplane. 
We are issuing this AD to prevent possible uncontained LP stage 1 
rotor blade failures that could result in damage to the airplane.

Compliance

    (e) You are responsible for having the actions required by this 
AD performed within 60 months after the effective date of this AD, 
unless the actions have already been done.

Replacement of Magnesium Split LP Compressor Case With a Serviceable 
Compressor Case

    (f) Remove the magnesium split LP compressor case, P/N 
EU.73418A, from the engine and install a serviceable compressor 
case. Information on removing and replacing this P/N case can be 
found in RRD Service Bulletin (SB) No. Sp72-893, Revision 3, dated 
August 25, 2003.

Alternative Methods of Compliance

    (g) 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.

Material Incorporated by Reference

    (h) None.

Related Information

    (i) LBA airworthiness directive 2003-261, dated August 25, 2003, 
also addresses the subject of this AD.

    Issued in Burlington, Massachusetts, on December 5, 2003.
Jay J. Pardee,
Manager, Engine and Propeller Directorate, Aircraft Certification 
Service.
[FR Doc. 03-30851 Filed 12-12-03; 8:45 am]
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