[Federal Register Volume 69, Number 159 (Wednesday, August 18, 2004)]
[Proposed Rules]
[Pages 51198-51200]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 04-18919]


-----------------------------------------------------------------------

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 98-ANE-61-AD]
RIN 2120-AA64


Airworthiness Directives; Pratt & Whitney PW2000 Series Turbofan 
Engines

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

-----------------------------------------------------------------------

SUMMARY: The FAA proposes to supersede an existing airworthiness 
directive (AD) for Pratt & Whitney (PW) PW2000 series turbofan engines. 
That AD currently requires revisions to the engine manufacturer's time 
limits section (TLS) to include enhanced inspection of selected 
critical life-limited parts at each piece-part opportunity. This 
proposed AD would modify the airworthiness limitations section of the 
manufacturer's manual and an air carrier's approved continuous 
airworthiness maintenance program to incorporate additional inspection 
requirements. An FAA study of in-service events involving uncontained 
failures of critical rotating engine parts has indicated the need for 
mandatory inspections. The mandatory inspections are needed to identify 
those critical rotating parts with conditions, which if allowed to 
continue in service, could result in uncontained failures. We are 
proposing this AD to prevent critical life-limited rotating engine part 
failure, which could result in an uncontained engine failure and damage 
to the airplane.

DATES: We must receive any comments on this proposed AD by October 18, 
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. 98-ANE-61-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 at the FAA, New England Region, 
Office of the Regional Counsel, 12 New England Executive Park, 
Burlington, MA.

FOR FURTHER INFORMATION CONTACT: Mark Riley, Aerospace Engineer, Engine 
Certification Office, FAA, Engine and Propeller Directorate, 12 New 
England Executive Park, Burlington, MA 01803-5299; telephone (781) 238-
7758, 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. 98-ANE-61-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

    On June 4, 2002, the FAA issued airworthiness directive (AD) 2002-
12-06, Amendment 39-12778 (67 FR 40143, June 12, 2002), to require 
revisions to the Time Limits Section (TLS) of the PW2000 Turbofan 
Engine Manual to include required enhanced inspection of selected 
critical life-limited parts at each piece-part opportunity.

New Inspection Procedures

    Since the issuance of that AD, an FAA study of in-service events 
involving uncontained failures of critical rotating engine parts has 
indicated the need for additional mandatory inspections. The mandatory 
inspections are needed to identify those critical rotating parts with 
conditions, which if allowed to continue in service, could result in 
uncontained failures. This proposal would modify the TLS of the 
manufacturer's manual and an air carrier's approved continuous 
airworthiness maintenance program to incorporate the additional 
inspection requirements.

FAA's Determination of an Unsafe Condition and Proposed Actions

    Since an unsafe condition has been identified that is likely to 
exist or develop on other PW2000 series turbofan engines of the same 
type design, the proposed AD would supersede AD 2002-12-06 to add 
additional inspection requirements for critical life-limited parts for 
enhanced inspection at each piece-part opportunity.

Costs of Compliance

    There are about 938 Pratt & Whitney PW2000 series turbofan engines 
of the affected design in the worldwide fleet. We estimate that 777 
engines installed on airplanes of U.S. registry would be affected by 
this proposed AD. We also estimate that it would take about 4 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 additional cost per engine per shop visit is estimated to be 
$260. Based on the current PW2000 engine shop visit rate, the total 
additional cost for the PW2000 fleet is estimated to be $80,860 per 
year.

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.

[[Page 51199]]

    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. 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. 98-ANE-61-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 FAA 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 Federal Aviation Administration (FAA) amends Sec.  39.13 by 
removing Amendment 39-12778, (67 FR 40143 June 4, 2002), and by adding 
a new airworthiness directive (AD) to read as follows:

Pratt & Whitney: Docket No. 98-ANE-61-AD. Supersedes AD 2002-12-06, 
Amendment 39-12778.

Comments Due Date

    (a) The FAA must receive comments on this AD action by October 
18, 2004.

Affected ADs

    (b) This AD supersedes AD 2002-12-06.

Applicability

    (c) This AD applies to Pratt & Whitney (PW) PW2037, PW2040, 
PW2043, PW2143, PW2240, PW2337, PW2643, PW2037D, PW2037M, and 
PW2040D series turbofan engines. These engines are installed on, but 
not limited to Boeing 757 series and Ilyushin IL-96T series 
airplanes.

Unsafe Condition

    (d) This AD results from the need to require enhanced inspection 
of selected critical life-limited parts of PW PW2000 series turbofan 
engines. We are issuing this AD to prevent critical life-limited 
rotating engine part failure, 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 30 days after the effective date of this AD, revise 
the manufacturer's Time Limits section (TLS) of the manufacturer's 
engine manual, as appropriate for PW PW2037, PW2040, PW2043, PW2143, 
PW2240, PW2337, PW2643, PW2037D, PW2037M, and PW2040D series 
turbofan engines, and for air carriers revise the approved 
continuous airworthiness maintenance program, by adding the 
following:

MANDATORY INSPECTIONS

    (1) Perform inspections of the following parts at each piece-
part opportunity in accordance with the instructions provided in 
PW2000 Engine Manuals 1A6231 and 1B2412:

----------------------------------------------------------------------------------------------------------------
                                                        EM manual
          Nomenclature                  Part No.         section      Inspection/check           Subtask
----------------------------------------------------------------------------------------------------------------
Hub, LPC Assembly...............  ALL................     72-31-04  -06................
Disk, HPT 1st Stage.............  ALL................     72-52-02  FPI entire disk per         72-52-02-230-007
                                                                     72-52-00,
                                                                     Inspection/Check-
                                                                     02.
Hub, HPT 2nd Stage..............  ALL................     72-52-16  (a) FPI entire hub          72-52-16-230-007
                                                                     per.
                                                                    72-52-00,
                                                                     Inspection/Check-
                                                                     02.
                                                                    (b) Eddy current            72-52-16-200-005
                                                                     inspect hub bolt
                                                                     holes per 72-52-
                                                                     00, Inspection/
                                                                     Check-05.
Hub, HPC Front..................  ALL................     72-35-02  -05................
Disk, HPC Drum..................  ALL................     72-35-03  -04................
Rotor Assembly (7-15)...........
Disk, HPC Drum Rotor Assembly     ALL................     72-35-10  -05................
 (16-17).
Disk, HPC 16th Stage............  ALL................     72-35-06  -04................
Disk, HPC 17th Stage............  ALL................     72-35-07  -04................
HPC Turbine Drive Shaft Assembly  ALL................     72-35-08  -05................
LPC Drive Turbine Shaft.........  ALL................     72-32-01  -06................
Hub, Turbine Rear...............  ALL................     72-53-81  -06................
Disk, LPT 3rd stage.............  ALL................     72-53-31  -01................
Disk, LPT 4th Stage.............  ALL................     72-53-41  -01................
Disk, LPT 5th Stage.............  ALL................     72-53-51  -01................
Disk, LPT 6th Stage.............  ALL................     72-53-61  -01................
Disk, LPT 7th Stage.............  ALL................     72-53-71  -01................
----------------------------------------------------------------------------------------------------------------

    (2) For the purposes of these mandatory inspections, piece-part 
opportunity means:
    (i) The part is considered completely disassembled when done in 
accordance with the disassembly instructions in the manufacturer's 
engine manual to either part number level listed in the table above, 
and
    (ii) The part has accumulated more than 100 cycles in service 
since the last piece-part opportunity inspection, provided that the 
part was not damaged or related to the cause for its removal from 
the engine.''

Alternative Methods of Compliance

    (g) You must perform these mandatory inspections using the TLS 
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.

[[Page 51200]]

Maintaining Records of the Mandatory Inspections

    (i) You have met the requirements of this AD by using a TLS of 
the manufacturer's engine manual 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 TLS 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 Sec.  121.369 or use an alternative system that your principal 
maintenance 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 Sec.  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 TLS 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) None.

    Issued in Burlington, Massachusetts, on August 11, 2004.
Ann Mollica,
Acting Manager, Engine and Propeller Directorate, Aircraft 
Certification Service.
[FR Doc. 04-18919 Filed 8-17-04; 8:45 am]
BILLING CODE 4910-13-P