[Federal Register Volume 62, Number 182 (Friday, September 19, 1997)]
[Rules and Regulations]
[Pages 49135-49137]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 97-24797]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 96-ANE-35; Amendment 39-10134; AD 97-19-13]
RIN 2120-AA64


Airworthiness Directives; Pratt & Whitney JT8D-200 Series 
Turbofan Engines

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule.

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SUMMARY: This amendment supersedes an existing airworthiness directive 
(AD) 94-23-03, applicable to Pratt & Whitney (PW) JT8D-200 series 
turbofan engines, that currently requires installation and periodic 
inspection of temperature indicators installed on the No. 4 and 5 
bearing compartment scavenge oil tube and performance of any necessary 
corrective action. This amendment requires the installation and 
periodic inspection of temperature indicators to all PW JT8D-200 series 
engines, including those incorporating the containment hardware 
specified in AD 93-23-10. This amendment is prompted by a report of an 
uncontained turbine failure due to a high pressure turbine (HPT) shaft 
fracture on an engine that had the containment hardware installed. The 
actions specified by this AD are intended to prevent fracture of the 
HPT shaft, which can result in uncontained release of engine fragments, 
engine fire, inflight engine shutdown, or possible aircraft damage.

DATES: Effective October 24, 1997.
    The incorporation by reference of PW Alert Service Bulletin (ASB) 
No. 5944, Revision 2, dated June 8, 1992, was previously approved by 
the Director of the Federal Register as of January 31, 1995 (59 FR 
61789, December 2, 1994). The incorporation by reference of PW ASB No. 
5944, Revision 3, dated December 16, 1994, is approved by the Director 
of the Federal Register as of October 24, 1997.

ADDRESSES: The service information referenced in this AD may be 
obtained from Pratt & Whitney, Publication Department, Supervisor 
Technical Publications Distribution, M/S 132-30, 400 Main St., East 
Hartford, CT 06108; telephone (860) 565-7700, fax (860) 565-4503. This 
information may be examined at the Federal Aviation Administration 
(FAA), New England Region, Office of the Assistant Chief Counsel, 12 
New England Executive Park, Burlington, MA 01803-5299; or at the Office 
of the Federal Register, 800 North Capitol Street, NW., suite 700, 
Washington, DC.

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: A proposal to amend part 39 of the Federal 
Aviation Regulations (14 CFR part 39) by superseding AD 94-23-03, 
Amendment 39-9065 (59 FR 61789, December 2, 1994), applicable to Pratt 
& Whitney (PW) JT8D-200 series turbofan engines, was published in the 
Federal Register on January 9, 1997 (62 FR 1298). That action proposed 
to require installation and periodic inspection of temperature 
indicators to all PW JT8D-200 series engines, including those 
incorporating the containment hardware modifications required by AD 93-
23-10.
    Interested persons have been afforded an opportunity to participate 
in the making of this amendment. Due consideration has been given to 
the comments received.
    One commenter states that the inspection interval should be 
increased from 65 hours time in service (TIS) to 75 hours TIS, as this 
increased interval could be incorporated into the service check of that 
operator's maintenance program. The FAA disagrees. Previous alternative 
methods of compliance (AMOCs) have been approved to adjust the 
inspection interval on a case-by-case basis, and the operator is 
invited to apply for an AMOC using the usual procedure. Generally, 
however, the compliance interval remains at 65 hours TIS.
    One commenter states that the reporting requirements of the AD 
should be eliminated, as the original AD terminated reporting 
requirements six months after the effective date of the AD. The FAA 
concurs and has eliminated the reporting requirements in the final 
rule.
    One commenter notes that the containment hardware has been 
ineffective in ensuring containment and that costs associated with 
installing the containment hardware have been excessive. The commenter, 
however, offers no objection to the proposed rule. The indirect costs 
of operating engines

[[Page 49136]]

with the containment hardware installed are not directly related to 
this proposed rule, and, therefore, are not addressed in the economic 
analysis for this rule. A full cost analysis for each AD, including 
such indirect costs, is not necessary since the FAA has already 
performed a cost benefit analysis when adopting the airworthiness 
requirements to which these engines were originally certificated. A 
finding that an AD is warranted means that the original design no 
longer achieves the level of safety specified by those airworthiness 
requirements, and that other required actions are necessary, such as 
containment hardware, or as in this case, installation and inspection 
of temperature indicators. Because the original level of safety was 
already determined to be cost beneficial, these additional requirements 
needed to return the engine to that level of safety do not add any 
additional regulatory burden, and, therefore, a full cost analysis 
would be redundant and unnecessary.
    One commenter supports the AD as proposed on the assumption that 
the AD requires diagnostic inspections should the required oil 
temperature indicators show signs that high oil temperatures have 
occurred within the engine. The AD does require troubleshooting and 
diagnostic testing and corrective action in accordance with service 
documents incorporated by reference.
    After careful review of the available data, including the comments 
noted above, the FAA has determined that air safety and the public 
interest require the adoption of the rule with the changes described 
previously. The FAA has determined that these changes will neither 
increase the economic burden on any operator nor increase the scope of 
the AD.
    There are approximately 2,432 series engines of the affected design 
in the worldwide fleet. The FAA estimates that 1,044 engines installed 
on aircraft of U.S. registry will be affected by this AD, that it will 
take approximately 1.5 work hours per engine to accomplish the required 
actions, and that the average labor rate is $60 per work hour. Based on 
these figures, the total cost impact of the AD on U.S. operators is 
estimated to be $93,960.
    The regulations adopted herein will not have substantial direct 
effects 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. Therefore, in 
accordance with Executive Order 12612, it is determined that this final 
rule does not have sufficient federalism implications to warrant the 
preparation of a Federalism Assessment.
    For the reasons discussed above, I certify that this action (1) is 
not a ``significant regulatory action'' under Executive Order 12866; 
(2) is not a ``significant rule'' under DOT Regulatory Policies and 
Procedures (44 FR 11034, February 26, 1979); and (3) will not have a 
significant economic impact, positive or negative, on a substantial 
number of small entities under the criteria of the Regulatory 
Flexibility Act. A final evaluation has been prepared for this action 
and it is contained in the Rules Docket. A copy of it may be obtained 
from the Rules Docket at the location provided under the caption 
ADDRESSES.

List of Subjects in 14 CFR Part 39

    Air Transportation, Aircraft, Aviation safety, Incorporation by 
reference, Safety.

Adoption of the Amendment

    Accordingly, pursuant to the authority delegated to me by the 
Administrator, the Federal Aviation Administration amends part 39 of 
the Federal Aviation Regulations (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. Section 39.13 is amended by removing amendment 39-9065 (59 FR 
61789, December 2, 1994) and by adding a new airworthiness directive, 
Amendment 39-10134, to read as follows:

97-19-13 Pratt & Whitney: Amendment 39-10134. Docket 96-ANE-35. 
Supersedes AD 94-23-03, Amendment 39-9065.

    Applicability: Pratt & Whitney (PW) JT8D-209, -217, -217A, -
217C, and -219 turbofan engines, installed on but not limited to 
McDonnell Douglas MD-80 series and Boeing 727 series aircraft.

    Note 1: This airworthiness directive (AD) applies to each engine 
identified in the preceding applicability provision, regardless of 
whether it has been modified, altered, or repaired in the area 
subject to the requirements of this AD. For engines that have been 
modified, altered, or repaired so that the performance of the 
requirements of this AD is affected, the owner/operator must request 
approval for an alternative method of compliance in accordance with 
paragraph (d) of this AD. The request should include an assessment 
of the effect of the modification, alteration, or repair on the 
unsafe condition addressed by this AD; and, if the unsafe condition 
has not been eliminated, the request should include specific 
proposed actions to address it.

    Compliance: Required as indicated, unless accomplished 
previously.
    To prevent fracture of the high pressure turbine (HPT) shaft, 
which can result in uncontained release of engine fragments, engine 
fire, inflight engine shutdown, or possible aircraft damage, 
accomplish the following:
    (a) Install and inspect one or two temperature indicators, part 
number (P/N) 810486, or a single or double set of P/N 809129 and P/N 
809130 temperature indicators, on the No. 4 and 5 bearing 
compartment scavenge oil tube, as follows:
    (1) Install temperature indicators on the No. 4 and 5 bearing 
compartment scavenge oil tube in accordance with Section 2.A.(1) of 
the Accomplishment Instructions of PW Alert Service Bulletin (ASB) 
No. 5944, Revision 3, dated December 16, 1994, or Revision 2, dated 
June 8, 1992, within 90 days after the effective date of this AD.
    (2) Visually inspect temperature indicators within 65 hours TIS 
of installation. Thereafter, inspect at intervals not to exceed 65 
hours TIS since last inspection.
    (3) If upon inspection, the color of any temperature indicator 
window(s) has turned completely black, perform troubleshooting and 
diagnostic testing and corrective action as required, in accordance 
with Section 2.A.(2) (c) and (d) or (f) and (g), as applicable, of 
the Accomplishment Instructions of PW ASB No. 5944, Revision 3, 
dated December 16, 1994, or Revision 2, dated June 8, 1992. Prior to 
returning the engine to service, replace any temperature indicator 
that has turned black and inspect in accordance with paragraphs 
(a)(2) and (a)(3) of this AD.
    (b) For aircraft installations utilizing one P/N 810486 
indicator or one set of P/N 809129 and 809130 indicators, and 
inspection reveals a missing indicator, inspect the remaining 
temperature indicator, if applicable, to determine if the indicator 
window has turned completely black. If the indicator window has 
turned completely black, perform troubleshooting and diagnostic 
testing, and corrective action as required, in accordance with 
paragraph (a)(3) of this AD. If the indicator window has not turned 
completely black or if there are no additional indicators installed, 
then install a new indicator in accordance with Section 2.A.(1) of 
the Accomplishment Instruction of PW ASB No. 5944, Revision No. 3, 
dated December 16, 1994, or Revision 2, dated June 8, 1992, prior to 
return to service, and visually inspect the temperature indicator 
within 65 hours TIS since installation. Thereafter, inspect at 
intervals not to exceed 65 hours TIS since last inspection in 
accordance with paragraphs (a)(2) and (a)(3) of this AD.
    (c) For aircraft installations utilizing two P/N 810486 
indicators or two sets of P/N 809129 and 809130 indicators, and 
inspection reveals a missing indicator(s), inspect the remaining 
temperature indicator(s), if applicable, to determine if the 
indicator window has turned completely black. If the indicator 
window has turned completely black, perform troubleshooting and 
diagnostic testing, and corrective action

[[Page 49137]]

as required, in accordance with paragraph (a)(3) of this AD. If the 
indicator window has not turned completely black, install a new 
indicator(s) in accordance with Section 2.A.(1) of the 
Accomplishment Instructions of PW ASB No. 5944, Revision 3, dated 
December 16, 1994, or Revision 2, dated June 8, 1992, prior to 
return to service, and visually inspect the temperature indicator 
within 65 hours TIS since installation. Thereafter, inspect at 
intervals not to exceed 65 hours TIS since last inspection in 
accordance with paragraphs (a)(2) and (a)(3) of this AD.
    (d) An alternative method of compliance or adjustment of the 
compliance time that provides an acceptable level of safety may be 
used if approved by the Manager, Engine Certification Office. 
Operators shall forward their requests through an appropriate FAA 
Principal Maintenance Inspector, who may add comments and then send 
it to the Manager, Engine Certification Office.

    Note 2: Information concerning the existence of approved 
alternative method of compliance with this AD, if any, may be 
obtained from the Engine Certification Office.

    (e) Special flight permits may be issued in accordance with 
sections 21.197 and 21.199 of the Federal Aviation Regulations (14 
CFR 21.197 and 21.199) to operate the aircraft to a location where 
the requirements of this AD can be accomplished.
    (f) The actions required by this AD shall be done in accordance 
with the following PW ASBs:

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              Document No.                   Pages       Revision                       Date                    
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5944....................................         1-35            3  December 16, 1994.                          
Total pages: 35.                                                                                                
5944....................................         1-44            2  June 8, 1992.                               
Total pages: 44.                                                                                                
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    This incorporation by reference of PW ASB No. 5944, Revision 2, 
dated June 9, 1993, was previously approved by the Director of the 
Federal Register in accordance with 5 U.S.C. 552(a) and 1 CFR part 
51 as of January 31, 1995 (59 FR 61789, December 2, 1994). Copies 
may be obtained from Pratt & Whitney, Publication Department, 
Supervisor Technical Publications Distribution, M/S 132-30, 400 Main 
St., East Hartford, CT 06108; telephone (860) 565-7700, fax (860) 
565-4503. Copies may be inspected at the FAA, New England Region, 
Office of the Assistant Chief Counsel, 12 New England Executive 
Park, Burlington, MA; or at the Office of the Federal Register, 800 
North Capitol Street, NW., suite 700, Washington, DC.
    (g) This amendment becomes effective on October 24, 1997.

    Issued in Burlington, Massachusetts, on September 10, 1997.
Mark C. Fulmer,
Acting Manager, Engine and Propeller Directorate, Aircraft 
Certification Service.
[FR Doc. 97-24797 Filed 9-18-97; 8:45 am]
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