[Federal Register Volume 69, Number 135 (Thursday, July 15, 2004)]
[Proposed Rules]
[Pages 42356-42358]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 04-16006]


 ========================================================================
 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. 135 / Thursday, July 15, 2004 / 
Proposed Rules  

[[Page 42356]]



DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 92-ANE-15-AD]
RIN 2120-AA64


Airworthiness Directives; Pratt & Whitney JT8D-200 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 JT8D-200 series turbofan engines. 
That AD currently requires installation of high pressure turbine (HPT) 
containment hardware on JT8D-217C and -219 engines. That AD also 
currently requires replacing LPT-to-exhaust case bolts and nuts with 
improved containment hardware on JT8D-209, -217, -217A, -217C, and -219 
engines. This proposed AD would require installation of improved HPT 
containment hardware on JT8D-209, -217, -217A, -217C, and -219 engines. 
This proposed AD results from four reports of uncontained HPT failures 
of JT8D-200 series engines, since AD 99-22-14 was issued. We are 
proposing this AD to prevent uncontained HPT events resulting from HPT 
shaft fractures.

DATES: We must receive any comments on this proposed AD by September 
13, 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. 92-ANE-15-AD, 12 New England Executive Park, Burlington, MA 01803-
5299.
     By fax: (781) 238-7055.
     By e-mail: [email protected].
    You may get the service information identified in this proposed AD 
from Pratt & Whitney, 400 Main St., East Hartford, CT 06108; telephone 
(860) 565-7700; fax (860) 565-1605.
    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: Keith Lardie, Aerospace Engineer, 
Engine Certification Office, FAA, Engine and Propeller Directorate, 12 
New England Executive Park, Burlington, MA 01803-5299; telephone (781) 
238-7189; 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. 92-ANE-15-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 October 21, 1999, the FAA issued AD 99-22-14, Amendment 39-11392 
(64 FR 58328, October 29, 1999). That AD requires installation of HPT 
containment hardware on JT8D-217C and -219 engines. That AD also 
requires replacing LPT-to-exhaust case bolts and nuts with improved 
containment hardware on JT8D-209, -217, -217A, -217C, and -219 engines. 
That AD was the result of reports of uncontained HPT events resulting 
from HPT shaft fractures and LPT flange separations resulting from LPT 
blade failures. That condition, if not corrected, could result in 
uncontained HPT events resulting from HPT shaft fractures and LPT 
flange separations resulting from LPT blade failures.

Actions After AD 99-22-14 was Issued

    After AD 99-22-14 was issued, we received four reports of 
uncontained HPT shaft fractures on JT8D-200 series engines. During one 
of these failures on a JT8D-217A engine, parts escaped forward of the 
old configuration HPT containment shield. This event demonstrates that 
the old configuration HPT containment shield is insufficient for 
preventing uncontained engine failures. AD 99-22-14 did not require 
JT8D-209, -217, and -217A engines to install the improved HPT 
containment shields.
    Also, after that AD was issued, PW determined that the LPT-to-
exhaust case bolts and nuts introduced by AD 99-22-14 have a higher 
failure rate than the previous bolt and nut configuration. We are 
preparing a separate proposed AD to address the replacement of that 
hardware, as recommended in a recently issued PW SB. This proposal no 
longer requires the replacement of LPT-to-exhaust case bolts and nuts 
with the bolts and nuts required by AD 99-22-14.
    Also, after that AD was issued, we discovered that the requirements 
from superseded AD 93-23-10, Amendment 39-8746, to install HPT 
containment shields on JT8D-209, -217, and -217A engines, were 
inadvertently omitted from AD 99-22-14.

Relevant Service Information

    We have reviewed and approved the technical contents of Pratt & 
Whitney Alert Service Bulletin (ASB) No. A6346, Revision 3, dated May 
21, 2004, which

[[Page 42357]]

describes the installation of improved HPT containment hardware on 
JT8D-209, -217, -217A, -217C, and -219 engines.

Differences Between This Proposed AD and the Manufacturer's Service 
Information

    Although Pratt & Whitney ASB No. A6346, Revision 3, dated May 21, 
2004, has an installation termination date of December 31, 2004, for 
all the affected engine models, this proposed AD would require the 
installation on JT8D-209, -217, and -217A engines no later than 
December 31, 2007.

FAA's Determination and Requirements of the Proposed AD

    We have evaluated all pertinent information and identified an 
unsafe condition that is likely to exist or develop on other products 
of this same type design. Therefore, we are proposing this AD, which 
would require the installation of improved HPT containment hardware at 
the following:
     For JT8D-209, -217, and -217A engines, at the next engine 
shop visit after the effective date of this proposed AD, but no later 
than December 31, 2007; and
     For JT8D-217C and -219 engines, at the next engine shop 
visit after the effective date of this AD, but no later than December 
31, 2004.
    The proposed AD would require that you do these actions using the 
service information described previously.

Costs of Compliance

    There are about 2,345 PW JT8D-200 series turbofan engines of the 
affected design in the worldwide fleet. We estimate that 1,143 engines 
are installed on airplanes of U.S. registry, and that 280 engines would 
be affected by this proposed AD. We estimate that 80% of the -217C and 
-219 engines already have the improved HPT containment hardware 
installed. We also estimate that no additional labor costs will be 
incurred when these parts are installed during engine shop visit. 
Required parts would cost about $19,991 per engine. Based on these 
figures, we estimate the total cost of the proposed AD to U.S. 
operators to be $5,597,480.

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. 92-ANE-15-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 removing Amendment 39-11392 (64 FR 
58328, October 29, 1999) and by adding a new airworthiness directive, 
to read as follows:

Pratt & Whitney: Docket No. 92-ANE-15-AD. Supersedes AD 99-22-14, 
Amendment 39-11392.

Comments Due Date

    (a) The Federal Aviation Administration (FAA) must receive 
comments on this airworthiness directive (AD) action by September 
13, 2004.

Affected ADs

    (b) This AD supersedes AD 99-22-14, Amendment 39-11392.

Applicability

    (c) This AD applies to Pratt & Whitney (PW) JT8D-209, -217, -
217A, -217C, and -219 turbofan engines. These engines are installed 
on, but not limited to, Boeing 727 series and MD-80 series 
airplanes.

Unsafe Condition

    (d) This AD results from four reports of uncontained HPT 
failures of JT8D-200 series engines, since AD 99-22-14 was issued. 
We are issuing this AD to prevent uncontained HPT events resulting 
from HPT shaft fractures.

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) Install the improved high pressure turbine (HPT) containment 
hardware. Use the applicable compliance schedule in the following 
Table 1, and Paragraphs 1. through 3.G. of Accomplishment 
Instructions of PW Alert Service Bulletin (ASB) No. JT8D A6346, 
dated September 10, 1998, or Revision 1, dated April 23, 1999, or 
Revision 2, dated December 1, 1999, or Revision 3, dated May 21, 
2004.

                      Table 1.--Compliance Schedule
------------------------------------------------------------------------
      For engine models        Install improved HPT containment hardware
------------------------------------------------------------------------
JT8D-217C and -219...........  At the next engine shop visit after the
                                effective date of this AD, but no later
                                than December 31, 2004.
JT8D-209, -217, and -217A....  At the next engine shop visit after the
                                effective date of this AD, but no later
                                than December 31, 2007.
------------------------------------------------------------------------

Definition

    (g) For the purpose of this AD, an engine shop visit is defined 
as engine maintenance that involves the separation of the J and K 
flanges.

Alternative Methods of Compliance

    (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.

Material Incorporated by Reference

    (i) None.

Related Information

    (j) None.


[[Page 42358]]


    Issued in Burlington, Massachusetts, on July 7, 2004.
Francis A. Favara,
Acting Manager, Engine and Propeller Directorate, Aircraft 
Certification Service.
[FR Doc. 04-16006 Filed 7-14-04; 8:45 am]
BILLING CODE 4910-13-P