[Federal Register: September 29, 2004 (Volume 69, Number 188)]
[Proposed Rules]
[Page 58099-58100]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr29se04-21]
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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.
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[[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:
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.
By fax: (781) 238-7055.
By e-mail: 9-ane-adcomment@faa.gov
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:
Inner heat shield cracking; or
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:
Inner heat shield cracking; or
No. 5 compartment carbon seal support burn-through; or
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