[Federal Register Volume 69, Number 49 (Friday, March 12, 2004)]
[Proposed Rules]
[Pages 11821-11825]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 04-5621]


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

  Federal Register / Vol. 69, No. 49 / Friday, March 12, 2004 / 
Proposed Rules  

[[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: [email protected].
    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