[Federal Register: March 12, 2004 (Volume 69, Number 49)]
[Proposed Rules]
[Page 11821-11825]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr12mr04-17]
========================================================================
Proposed Rules
Federal Register
________________________________________________________________________
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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[[Page 11821]]
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 2003-NE-57-AD]
RIN 2120-AA64
Airworthiness Directives; Rolls-Royce plc (RR) RB211-22B, RB211-
524, and RB211-535 Series Turbofan Engines
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking (NPRM).
-----------------------------------------------------------------------
SUMMARY: The FAA proposes to adopt a new airworthiness directive (AD)
for Rolls-Royce plc (RR) RB211-22B, RB211-524, and RB211-535 series
turbofan engines. This proposal would require revising the Time Limits
Manual for RR RB211-22B, RB211-524, and RB211-535 series turbofan
engines. These revisions would include required enhanced inspection of
selected critical life-limited parts at each piece-part exposure This
proposal results from the need to require enhanced inspection of
selected critical life-limited parts of RB211-22B, RB211-524, and
RB211-535 series turbofan engines. We are proposing this AD to prevent
failure of critical life-limited rotating engine parts, which could
result in an uncontained engine failure and damage to the airplane.
DATES: We must receive any comments on this proposed AD by May 11,
2004.
ADDRESSES: Use one of the following addresses to submit comments on
this proposed AD:
By mail: Federal Aviation Administration (FAA),
New England Region, Office of the Regional Counsel, Attention: Rules
Docket No. 2003-NE-57-AD, 12 New England Executive Park, Burlington, MA
01803-5299.
By fax: (781) 238-7055.
By e-mail: 9-ane-adcomment@faa.gov.
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: Christopher Spinney, Aerospace
Engineer, Engine Certification Office, FAA, Engine and Propeller
Directorate, 12 New England Executive Park, Burlington, MA 01803-5299;
telephone (781) 238-7175, 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-57-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 8:00 a.m. and 4:30 p.m., Monday
through Friday, except Federal holidays. See ADDRESSES for the
location.
Discussion
A recent FAA study analyzing 15 years of accident data for
transport category airplanes identified several root causes for a
failure mode that can result in serious safety hazards to transport
category airplanes. This study identified uncontained failure of
critical life-limited rotating engine parts as the leading engine-
related safety hazard to airplanes. Uncontained engine failures have
resulted from undetected cracks in rotating parts that started and grew
to failure. Cracks can start from causes such as unintended excessive
stress from the original design, or they may start from stresses
induced from material flaws, handling, or damage from machining
operations. The failure of a rotating part can present a significant
safety hazard to the airplane by release of high-energy fragments that
could injure passengers or crew by penetration of the cabin, damage
flight control surfaces, sever flammable fluid lines, or otherwise
compromise the airworthiness of the airplane.
Based on these findings, the FAA, with concurrence from the Civil
Aviation Authority (CAA), which is the Airworthiness Authority for the
United Kingdom (U.K.), has developed an intervention strategy to
significantly reduce uncontained engine failures. This intervention
strategy was developed after consultation with industry and will be
used as a model for future initiatives. The intervention strategy is to
conduct enhanced, nondestructive inspections of rotating parts, which
could most likely result in a safety hazard to the airplane in the
event of a part fracture. We are considering the need for additional
rulemaking. We might issue future ADs to introduce additional
intervention strategies to further reduce or eliminate uncontained
engine failures.
Properly focused enhanced inspections require identification of the
parts whose failure presents the highest safety hazard to the airplane,
identifying the most critical features to inspect on these parts, and
utilizing inspection procedures and techniques that improve crack
detection. The CAA, with close cooperation of RR, has completed a
detailed analysis that identifies the most safety significant parts and
features, and the most appropriate inspection methods.
Critical life-limited high-energy rotating parts are currently
subject to some form of recommended crack inspection when exposed
during engine maintenance or disassembly. The inspections currently
recommended by the manufacturer would become
[[Page 11822]]
mandatory for those parts listed in the compliance section as a result
of this proposed AD. Furthermore, we intend that additional mandatory
enhanced inspections resulting from this AD would serve as an adjunct
to the existing inspections. We have determined that the enhanced
inspections will significantly improve the probability of crack
detection on disassembled parts during maintenance. All mandatory
inspections must be conducted in accordance with detailed inspection
procedures prescribed in the manufacturer's Engine Manual.
Additionally, this proposed AD would:
Allow air carriers that operate under the
provisions of 14 CFR part 121 with an FAA-approved continuous
airworthiness maintenance program, and maintenance facilities to verify
completion of the enhanced inspections.
Allow the air carrier or maintenance facility to
retain the maintenance records that include the inspections resulting
from this proposed AD, if the records include the date and signature of
the person who performed the maintenance action.
Require retaining the records with the
maintenance records of the part, engine module, or engine until the
task is repeated.
Establish a method of record preservation and
retrieval typically used in existing continuous airworthiness
maintenance programs.
Require adding instructions in an air carrier's
maintenance manual on how to implement and integrate this record
preservation and retrieval system into the air carrier's record keeping
system.
For engines or engine modules that are approved for return to
service by an authorized FAA-certificated entity, and that are acquired
by an operator after the effective date of the proposed AD, you would
not need to perform the mandatory enhanced inspections until the next
piece-part opportunity. For example, you would not have to disassemble
to piece-part level, an engine or module returned to service by an FAA-
certificated facility simply because that engine or module was
previously operated by an entity not required to comply with this
proposed AD. Furthermore, we intend that operators perform the enhanced
inspections of these parts at the next piece-part opportunity after the
initial acquisition, installation, and removal of the part after the
effective date of this proposed AD. For piece parts not approved for
return to service before the effective date of this AD, the proposed AD
would require that you perform the mandatory enhanced inspections
before approval of those parts for return to service. The proposed AD
would allow installation of piece parts approved for return to service
before the effective date of this AD. However, the proposed AD would
require an enhanced inspection at the next piece-part opportunity.
This proposal would require, within the next 40 days after the
effective date of this proposed AD, revisions to the Time Limits
Manual.
FAA's Determination and Requirements of the Proposed AD
Since an unsafe condition has been identified that is likely to
exist or develop on other Rolls-Royce plc RB211-22B, RB211-524, and
RB211-535 series turbofan engines of the same type design that are used
on Boeing 747, 757, 767, Lockheed L-1011, and Tupolev Tu204 airplanes
registered in the United States, the proposed AD would require
revisions to the Time Limits Manual for RR RB211-22B, RB211-524, and
RB211-535 series turbofan engines to include required enhanced
inspection of selected critical parts at each piece-part exposure.
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 882 RB211-22B and RB211-524 series engines and
about 1,160 RB211-535 series engines of the affected design in the
worldwide fleet. We estimate that 30 RB211-22B and RB211-524 series
engines and 620 RB211-535 series engines installed on airplanes of U.S.
registry would be affected by this proposed AD. We also estimate that
it would take about 75 work hours per engine to perform the proposed
inspections, and that the average labor rate is $65 per work hour.
Since this is an added inspection requirement, included as part of the
normal maintenance cycle, no additional part costs are involved. Based
on these figures, the total cost impact of the proposed AD on U.S.
operators is estimated to be $3,169,000.
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-57-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 plc: Docket No. 2003-NE-57-AD.
Comments Due Date
(a) The Federal Aviation Administration (FAA) must receive comments
on this airworthiness directive (AD) action by May 11, 2004.
Affected ADs
(b) None.
Applicability
(c) This AD applies to Rolls-Royce plc (RR) RB211-22B, RB211-524,
and RB211-535 series turbofan engines.
[[Page 11823]]
These engines are installed on, but not limited to, Boeing 747, 757,
767, Lockheed L-1011, and Tupolev Tu204 airplanes.
Unsafe Condition
(d) This AD results from the need to require enhanced inspection of
selected critical life-limited parts of RB211-22B, RB211-524, and
RB211-535 series turbofan engines. We are issuing this AD to prevent
failure of critical life-limited rotating engine parts, which could
result in an uncontained engine failure and damage to the airplane.
Compliance
(e) You are responsible for having the actions required by this AD
performed within the compliance times specified unless the actions have
already been done.
(f) Within the next 40 days after the effective date of this AD,
revise the Time Limits Manual (TLM), and for air carrier operations
revise the approved continuous airworthiness maintenance program, by
adding the following text and the applicable table determined by engine
model number:
``Group A Parts Mandatory Inspection
(1) Inspections referred to as `Focus Inspect' in the applicable
Engine Manual inspection Task are mandatory inspections for the
components given below, when the conditions that follow are satisfied:
(i) When the component has been completely disassembled to piece-
part level as given in the applicable disassembly procedures contained
in the Engine Manual; and
(ii) The part has more than 100 recorded flight cycles in operation
since the last piece-part inspection. or
(iii) The component removal was for damage or a cause directly
related to its removal; or
(iv) Where serviceable used components, for which the inspection
history is not fully known, are to be used again.''
(2) The list of Group A Parts for RB211-22B engines is specified
below:
------------------------------------------------------------------------
Part nomenclature (RB211-22B Inspected per
series engines) Part number overhaul manual task
------------------------------------------------------------------------
Low Pressure Compressor Rotor All............ 72-31-12-200-006
Disc.
Low Pressure Compressor Rotor All............ 72-31-20-200-000
Shaft.
Intermediate Pressure Compressor All............ 72-32-31-200-000
Rotor Shaft Stages 1 to 5.
Intermediate Pressure Compressor All............ 72-32-31-200-001
Rotor Shaft Stages 6 to 7.
Intermediate Pressure Compressor All............ 72-33-31-200-000
Rotor Rear Stubshaft.
High Pressure Compressor Rotor All............ 72-41-31-200-000
Stage 1 to 2 Disc Shaft.
High Pressure Compressor Rotor All............ 72-41-31-200-001
Stage 3 Disc.
High Pressure Compressor Rear All............ 72-41-31-200-002
Rotor Shaft Assembly.
Compressor/Turbine Joint Flange All............ 72-41-31-200-003
Support Disc.
High Pressure Turbine Disc....... All............ 72-41-51-200-000
Intermediate Pressure Turbine All............ 72-51-31-200-000
Disc.
Intermediate Pressure Turbine All............ 72-51-33-200-000
Shaft.
Low Pressure Turbine Stage 1 Disc All............ 72-51-61-200-000
Low Pressure Turbine Stage 2 Disc All............ 72-51-61-200-001
Low Pressure Turbine Stage 3 Disc All............ 72-51-61-200-002
Low Pressure Turbine Shaft....... All............ 72-51-63-200-000
------------------------------------------------------------------------
(3) The list of Group A Parts for RB211-535 series engines is
specified below:
------------------------------------------------------------------------
Part nomenclature (RB211-535 Inspected per
Series Engines) Part number overhaul manual task
------------------------------------------------------------------------
Low Pressure Compressor Rotor All............ 72-31-12-200-000
Disc.
Low Pressure Compressor Rotor All............ 72-31-20-200-000
Shaft.
Intermediate Pressure Compressor All............ 72-32-31-200-001
Rotor Shaft.
Intermediate Pressure Compressor All............ 72-33-21-200-000
Rotor Rear Stubshaft.
High Pressure Compressor Rotor All............ 72-41-31-200-000
Stage 1 & 2 Disc.
High Pressure Compressor Rotor All............ 72-41-31-200-001
Stage 3 Disc.
High Pressure Compressor Rear All............ 72-41-31-200-002
Rotor Shaft Assembly.
Compressor/Turbine Joint Flange All............ 72-41-31-200-003
Support Disc (applicable to -
535C only).
High Pressure Turbine Disc....... All............ 72-41-51-200-000
Intermediate Pressure Turbine All............ 72-51-31-200-000
Rotor Disc.
Intermediate Pressure Turbine All............ 72-51-33-200-000
Shaft.
Low Pressure Turbine Stage 1 Disc All............ 72-51-61-200-000
Low Pressure Turbine Stage 2 Disc All............ 72-51-61-200-001
Low Pressure Turbine Stage 3 Disc All............ 72-51-61-200-002
Low Pressure Turbine Shaft....... All............ 72-51-63-200-000
------------------------------------------------------------------------
(4) The list of Group A Parts for RB211-524B, -524B3, and -524B4
series engines is specified below:
[[Page 11824]]
------------------------------------------------------------------------
Part nomenclature (RB211-524B, -
524B3, and -524B4 series engines) Part Number Inspected per
overhaul manual task
------------------------------------------------------------------------
Low Pressure Compressor Rotor All............ 72-31-12-200-05
Disc. (Configuration 1)
72-31-12-200-013
(Configuration 2)
Low Pressure Compressor Rotor All............ 72-31-20-200-000
Shaft.
Intermediate Pressure Compressor All............ 72-32-31-200-000
Stage 1 Disc.
Intermediate Pressure Compressor All............ 72-32-31-200-000
Stage 2 Disc.
Intermediate Pressure Compressor All............ 72-32-31-200-000
Stage 3 Disc.
Intermediate Pressure Compressor All............ 72-32-31-200-000
Stage 4 Disc.
Intermediate Pressure Compressor All............ 72-32-31-200-001
Stage 5 Disc.
Intermediate Pressure Compressor All............ 72-32-31-200-001
Rotor Shaft Stages 6 to 7.
Intermediate Pressure Compressor All............ 72-32-31-200-008
Front Stubshaft Drive Cone.
Intermediate Pressure Compressor All............ 72-33-21-200-010
Rotor Rear Stubshaft.
High Pressure Compressor Rotor All............ 72-41-31-200-000
Stage 1 to 2 Disc.
High Pressure Compressor Rotor All............ 72-41-31-200-001
Stage 3 Disc.
High Pressure Compressor Rear All............ 72-41-31-200-002
Rotor Shaft Assembly.
High Pressure Compressor/Turbine All............ 72-41-31-200-006
Joint Flange Support Disc.
High Pressure Turbine Bearing All............ 72-41-51-200-005
Inner Race Support Panel.
High Pressure Turbine Disc....... All............ 72-41-51-200-019
High Pressure Turbine Conical All............ 72-41-51-200-021
Shaft.
Intermediate Pressure Turbine All............ 72-51-31-200-003
Disc.
Intermediate Pressure Turbine All............ 72-51-33-200-005
Shaft.
Low Pressure Turbine Stage 1 Disc All............ 72-51-61-200-000
(Configuration 1)
72-51-61-200-007
(Configuration 2)
Low Pressure Turbine Stage 2 Disc All............ 72-51-61-200-001
(Configuration 1)
72-51-61-200-008
(Configuration 2)
Low Pressure Turbine Stage 3 Disc All............ 72-51-61-200-002
(Configuration 1)
72-51-61-200-009
(Configuration 2)
Low Pressure Turbine Shaft....... All............ 72-51-63-200-000
(Configuration 1)
72-51-63-200-003
(Configuration 2)
------------------------------------------------------------------------
(5) The list of Group A Parts for RB211-524B2, -524C2, and -524D4
series engines is specified below:
------------------------------------------------------------------------
Part nomenclature (RB211-524B, -
524C2, and -524D4 series engines) Part number Inspected per
overhaul manual task
------------------------------------------------------------------------
Low Pressure Compressor Rotor All............ 72-31-12-200-013
Disc.
Low Pressure Compressor Rotor All............ 72-31-20-200-000
Shaft.
Intermediate Pressure Compressor All............ 72-32-31-200-000
Stage 1 Disc.
Intermediate Pressure Compressor All............ 72-32-31-200-000
Stage 2 Disc.
Intermediate Pressure Compressor All............ 72-32-31-200-000
Stage 3 Disc.
Intermediate Pressures Compressor All............ 72-32-31-200-000
Stage 4 Disc.
Intermediate Pressure Compressor All............ 72-32-31-200-001
Stage 5 Disc.
Intermediate Pressure Compressor All............ 72-32-31-200-001
Rotor Shaft Stages 6 to 7.
Intermediate Pressure Compressor All............ 72-32-31-200-008
Front Stubshaft Drive Cone.
Intermediate Pressure Compressor All............ 72-33-21-200-010
Rotor Rear Stubshaft.
High Pressure Compressor Rotor All............ 72-41-31-200-000
Stage 1 to 2 Disc.
High Pressure Compressor Rotor All............ 72-41-31-200-001
Stage 3 Disc.
High Pressure Compressor Rear All............ 72-41-31-200-002
Rotor Shaft Assembly.
High Pressure Compressor/Turbine All............ 72-41-31-200-006
Joint Flange Support Disc.
High Pressure Turbine Bearing All............ 72-41-51-200-005
Inner Race Support Panel.
High Pressure Turbine Disc....... All............ 72-41-51-200-019
High Pressure Turbine Conical All............ 72-41-51-200-021
Shaft.
Intermediate Pressure Turbine All............ 72-51-31-200-003
Rotor Disc.
Intermediate Pressure Turbine All............ 72-51-33-200-005
Shaft.
Low Pressure Turbine Stage 1 Disc All............ 72-51-61-200-007
Low Pressure Turbine Stage 2 Disc All............ 72-51-61-200-008
Low Pressure Turbine Stage 3 Disc All............ 72-51-61-200-009
Low Pressure Turbine Shaft....... All............ 72-51-63-200-003
------------------------------------------------------------------------
[[Page 11825]]
(6) The list of Group A Parts for RB211-524G and -524H series
engines is specified below:
------------------------------------------------------------------------
Part nomenclature (RB211-524G and Inspected per
-524H Series Engines) Part number overhaul manual task
------------------------------------------------------------------------
Low Pressure Compressor Rotor All............ 72-31-12-200-000
Disc.
Low Pressure Compressor Rotor All............ 72-31-20-200-000
Shaft.
Intermediate Pressure Compressor All............ 72-32-31-200-000
Stage 1 Disc.
Intermediate Pressure Compressor All............ 72-32-31-200-000
Stage 2 Disc.
Intermediate Pressure Compressor All............ 72-32-31-200-000
Stage 3 Disc.
Intermediate Pressure Compressor All............ 72-32-31-200-000
Stage 4 Disc.
Intermediate Pressure Compressor All............ 72-32-31-200-000
Stage 5 Disc.
Intermediate Pressure Compressor All............ 72-32-31-200-001
Rotor Shaft Stages 6 to 7.
Intermediate Pressure Compressor All............ 72-32-31-200-008
Front Stubshaft Drive Cone.
Intermediate Pressure Compressor All............ 72-33-21-200-010
Rotor Rear Stubshaft.
High Pressure Compressor Rotor All............ 72-41-31-200-000
Stage 1 to 2 Disc. (Configuration 1)
High Pressure Compressor Rotor All............ 72-41-31-200-001
Stage 3 Disc. (Configuration 1)
High Pressure Compressor Rear All............ 72-41-31-200-002
Rotor Shaft Assembly. (Configuration 1)
Compressor/Turbine Joint Flange All............ 72-41-31-200-003
Support Disc. (Configuration 1)
High Pressure Compressor Rotor All............ 72-41-31-200-014
Shaft Assembly. (Configuration 2)
High Pressure Turbine Disc....... All............ 72-41-51-200-010
(Configuration 1)
72-41-51-200-024
(Configuration 2)
Intermediate Pressure Turbine All............ 72-51-31-200-003
Disc.
Intermediate Pressure Turbine All............ 72-51-33-200-005
Shaft.
Low Pressure Turbine Stage 1 Disc All............ 72-51-61-200-007
Low Pressure Turbine Stage 2 Disc All............ 72-51-61-200-008
Low Pressure Turbine Stage 3 Disc All............ 72-51-61-200-009
Low Pressure Turbine Shaft....... All............ 72-51-63-200-003''
------------------------------------------------------------------------
Alternative Methods of Compliance
(g) You must perform these mandatory inspections using the TLM and
the applicable Engine Manual unless you receive approval to use an
alternative method of compliance under paragraph (h) of this AD.
Section 43.16 of the Federal Aviation Regulations (14 CFR 43.16) may
not be used to approve alternative methods of compliance or adjustments
to the times in which these inspections must be performed.
(h) 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.
Maintaining Records of the Mandatory Inspections
(i) You have met the requirements of this AD by using a TLM changed
as specified in paragraph (f) of this AD, and, for air carriers
operating under part 121 of the Federal Aviation Regulations (14 CFR
part 121), by modifying your continuous airworthiness maintenance plan
to reflect those changes. You must maintain records of the mandatory
inspections that result from those changes to the TLM according to the
regulations governing your operation. You do not need to record each
piece-part inspection as compliance to this AD. For air carriers
operating under part 121, you may use either the system established to
comply with section 121.369 or use an alternative system that your
principal inspector has accepted if that alternative system:
(1) Includes a method for preserving and retrieving the records of
the inspections resulting from this AD; and
(2) Meets the requirements of section 121.369(c); and
(3) Maintains the records either indefinitely or until the work is
repeated.
(j) These record keeping requirements apply only to the records
used to document the mandatory inspections required as a result of
revising the Time Limits Manual as specified in paragraph (f) of this
AD, and do not alter or amend the record keeping requirements for any
other AD or regulatory requirement.
Related Information
(k) CAA airworthiness directives No. G-2003-0006, dated September
18, 2003, No. G-2003-0009, dated September 19, 2003, and No. G-2003-
0007, dated September 18, 2003 also address the subject of this AD.
Issued in Burlington, Massachusetts, on March 5, 2004.
Jay J. Pardee,
Manager, Engine and Propeller Directorate, Aircraft Certification
Service.
[FR Doc. 04-5621 Filed 3-11-04; 8:45 am]
BILLING CODE 4910-13-P