[Federal Register Volume 69, Number 188 (Wednesday, September 29, 2004)]
[Proposed Rules]
[Pages 58099-58100]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 04-21812]


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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. 188 / Wednesday, September 29, 2004 / 
Proposed Rules

[[Page 58099]]



DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 96-ANE-35-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).

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SUMMARY: The FAA proposes to supersede an existing airworthiness 
directive (AD) for Pratt & Whitney (PW) JT8D-200 series turbofan 
engines. That AD currently requires installing and periodically 
inspecting individual or sets of certain part number (P/N) temperature 
indicators on the No. 4 and 5 bearing compartment scavenge oil tube and 
performance of any necessary corrective action. This proposed AD would 
require installing and periodically inspecting two P/N 810486 
temperature indicators on all PW JT8D-200 series turbofan engines, 
including those incorporating high pressure turbine (HPT) containment 
hardware. This proposed AD results from five uncontained HPT shaft 
failures out of thirteen HPT shaft fractures. The HPT shafts fractured 
through the No. 4\1/2\ oil return holes due to oil fires within the No. 
4 and 5 bearing compartment. We are proposing this AD to prevent oil 
fires and the resulting fracture of the HPT shaft, which can result in 
uncontained release of engine fragments; engine fire; in-flight engine 
shutdown; and possible airplane damage.

DATES: We must receive any comments on this proposed AD by November 29, 
2004.

ADDRESSES: Use one of the following addresses to submit comments on 
this proposed AD:
    <bullet> By mail: Federal Aviation Administration (FAA), New 
England Region, Office of the Regional Counsel, Attention: Rules Docket 
No. 96-ANE-35-AD, 12 New England Executive Park, Burlington, MA 01803-
5299.
    <bullet> By fax: (781) 238-7055.
    <bullet> By e-mail: <a href="/cdn-cgi/l/email-protection#754c58141b10581411161a1818101b01351314145b121a03"><span class="__cf_email__" data-cfemail="af9682cec1ca82cecbccc0c2c2cac1dbefc9cece81c8c0d9">[email protected]</span></a>
    You can 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; or at the National Archives and Records Administration 
(NARA). For information on the availability of this material at NARA, 
call 202-741-6030, or go to: http://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html.

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. 96-ANE-35-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 September 10, 1997, the FAA issued AD 97-19-13, Amendment 39-
10134 (62 FR 49135, September 19, 1997). That AD requires installing 
and periodically inspecting temperature indicators on the No. 4 and 5 
bearing compartment scavenge oil tube and performance of any necessary 
corrective action. That AD resulted from a report of an uncontained 
turbine failure due to an HPT shaft fracture on an engine that had the 
containment hardware installed. The HPT shaft fractures were caused by 
oil fires within the No. 4 and 5 bearing compartment, due to thirteenth 
stage pressure cooling pressure (PCP) air leaking into the bearing 
compartment. The PCP air leakage was due to:
    <bullet> Inner heat shield cracking; or
    <bullet> No. 5 compartment carbon seal support burn-through.
That condition, if not corrected, could result in uncontained release 
of engine fragments, engine fire, in-flight engine shutdown, and 
possible airplane damage.

Actions Since AD 97-19-13 Was Issued

    Since that AD 97-19-13 was issued, PW found a new source of 
thirteenth stage PCP air leakage into the No. 4 and 5 bearing 
compartments that might lead to compartment oil fires. The source of 
air leaks into the No. 4 and 5 bearing compartments is from the 
thirteenth stage PCP air, due to:
    <bullet> Inner heat shield cracking; or
    <bullet> No. 5 compartment carbon seal support burn-through; or
    <bullet> No. 5 carbon seal sticking in the open position.
This air leakage resulted in oil fires, fracturing the HPT shaft 
through the No. 4\1/2\ oil return holes, leading to an uncontained 
turbine failure. We are

[[Page 58100]]

proposing this AD to prevent oil fires and the resulting fracture of 
the HPT shaft, which can result in uncontained release of engine 
fragments; engine fire; in-flight engine shutdown; and possible 
airplane damage.

Relevant Service Information

    We have reviewed and approved the technical contents of PW Alert 
Service Bulletin (ASB) No. 5944, Revision 4, dated April 8, 2004. The 
ASB describes procedures for installing and inspecting temperature 
indicator devices on the No. 4 and 5 bearing compartment scavenge tubes 
on PW JT8D-200 series turbofan engines.

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. We are proposing this AD, which would require 
installation and inspection of temperature indicator devices on the No. 
4 and 5 bearing compartment scavenge tube. 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 
installed on airplanes of U.S. registry would be affected by this 
proposed AD. We also estimate that it would take about 1 work hour per 
engine to perform the proposed actions, and that the average labor rate 
is $65 per work hour. Required parts would cost about $37 per engine. 
Based on these figures, we estimate the total cost of the proposed AD 
to U.S. operators to be $116,586.

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. 96-ANE-35-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 39-10134 (62 FR 49135, September 19, 1997) and by 
adding a new airworthiness directive (AD) to read as follows:

Pratt & Whitney: Docket No. 96-ANE-35-AD. Supersedes AD 97-19-13, 
Amendment 39-10134.

Comments Due Date

    (a) The FAA must receive comments on this AD action by November 
29, 2004.

Affected ADs

    (b) This AD supersedes AD 97-19-13, Amendment 39-10134.

Applicability

    (c) This AD applies to Pratt & Whitney (PW) JT8D-200 series 
turbofan engines. These engines are installed on, but not limited 
to, McDonnell Douglas MD-80 series and Boeing 727 series airplanes.

Unsafe Condition

    (d) This AD results from five uncontained high pressure turbine 
(HPT) shaft failures out of thirteen HPT shaft fractures due to oil 
fires in the No. 4 and 5 bearing compartments. We are proposing this 
AD to prevent oil fires; fracture of the HPT shaft, which can result 
in uncontained release of engine fragments; engine fire; in-flight 
engine shutdown; and possible airplane damage.

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.

Installation of the Dual-Window Temperature Indicators

    (f) Install two dual-window temperature indicators on the No. 4 
and 5 bearing compartment scavenge oil tubes of PW JT8D-200 series 
turbofan engines within 90 days after the effective date of this AD. 
Use paragraph 1.A. of Accomplishment Instructions of PW Alert 
Service Bulletin (ASB) No. 5944, Revision 4, dated April 8, 2004, to 
install the temperature indicators.

Initial Visual Inspection of the Dual-Window Temperature Indicators

    (g) Perform initial visual inspection of the dual-window 
temperature indicators installed in paragraph (f) of this AD within 
65 hours time-in-service (TIS) since installation.
    (1) If the color of any temperature indicator window has turned 
black, perform troubleshooting, diagnostic testing, and corrective 
action as required, using paragraph 1.B. of the Accomplishment 
Instructions of PW ASB No. 5944, Revision 4, dated April 8, 2004.
    (2) If one temperature indicator is missing, inspect the 
remaining temperature indicator. If the remaining temperature 
indicator has turned black, perform troubleshooting, diagnostic 
testing, and corrective action as required, using paragraph 1.B. of 
the Accomplishment Instructions of PW ASB No. 5944, Revision 4, 
dated April 8, 2004. If the remaining temperature indicator has not 
turned black, replace the missing temperature indicator as specified 
in paragraph (f) of this AD, and inspect as specified in paragraph 
(g) of this AD, prior to returning the engine to service.
    (3) If both temperature indicators are missing, remove the 
engine from service.
    (4) Prior to returning the engine to service, replace any 
temperature indicator that has turned black as specified in 
paragraph (f) of this AD and inspect as specified in paragraph (g) 
of this AD.

Repetitive Visual Inspection of the Dual-Window Temperature Indicators

    (h) Perform repetitive visual inspections of the dual-window 
temperature indicators installed in paragraph (f) of this AD within 
65 hours TIS since last inspection. Use paragraph (g) of this AD to 
inspect the temperature indicators.

Material Incorporated by Reference

    (i) None.

Related Information

    (j) None.

    Issued in Burlington, Massachusetts, on September 22, 2004.
Francis A. Favara,
Acting Manager, Engine and Propeller Directorate, Aircraft 
Certification Service.
[FR Doc. 04-21812 Filed 9-28-04; 8:45 am]
BILLING CODE 4910-13-P


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