Airworthiness Directives; Pratt & Whitney Models JT8D-209, -217, -217A, -217C and -219 Turbofan Engines

[Federal Register Volume 67, Number 159 (Friday, August 16, 2002)]
[Rules and Regulations]
[Pages 53480-53482]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 02-20267]


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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 99-NE-32-AD; Amendment 39-12847; AD 2002-16-08]
RIN 2120-AA64


Airworthiness Directives; Pratt & Whitney Models JT8D-209, -217, 
-217A, -217C and -219 Turbofan Engines

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule.

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

SUMMARY: This amendment supersedes an existing airworthiness directive 
(AD), that is applicable to Pratt & Whitney (PW) JT8D models -209, -
217, -217A, -217C and -219 turbofan engines. That AD currently requires 
initial and repetitive fluorescent magnetic particle inspections or 
fluorescent penetrant inspections of the combustion chamber outer case 
(CCOC) for cracks, and, if necessary, replacement with serviceable 
parts. Also that AD requires a one-time material verification of drain 
and Ps4 bosses, and, if necessary, replacement with serviceable parts. 
Finally, that AD requires replacement of CCOC's with welded-on bosses 
with improved, one-piece CCOC's. This amendment requires lower initial 
inspection thresholds for all CCOC's installed in any JT8D model -209, 
-217, -217A, -217C or -219 turbofan engine. This amendment is prompted 
by reports of cracked CCOC's that had accumulated fewer cycles in 
service than the initial inspection thresholds required by the current 
AD. Also, a CCOC part number was discovered with incorrect material not 
identified by serial number in JT8D Alert Service Bulletin (ASB) A6359, 
Revision 2, dated July 31, 2000. The actions specified by this AD are 
intended to prevent uncontained failure of the CCOC, which could cause 
release of debris, damage to the airplane, or fire.

DATES: Effective September 20, 2002. The incorporation by reference of 
certain publications listed in the regulations is approved by the 
Director of the Federal Register as of September 20, 2002.

ADDRESSES: The service information referenced in this AD may be 
obtained from Pratt & Whitney, 400 Main St., East Hartford, CT 06108; 
telephone (860) 565-8770; fax (860) 565-4503. This information may be 
examined, by appointment, at the Federal Aviation Administration (FAA), 
New England Region, Office of the Regional 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.

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 99-26-06, 
Amendment 39-11465 (64 FR 71280, December 21, 1999), which is 
applicable to Pratt & Whitney JT8D models -209, -217, -217A, -217C and 
-219 turbofan engines was published in the Federal Register on February 
14, 2002 (67 FR 6890). That action proposed to require lower initial 
inspection thresholds for CCOC's part numbers (P/N's) 500023801, 
797707, 807684, and 815830 installed in any JT8D model -209, -217, -
217A, -217C, or -219 turbofan engines in accordance with PW JT8D Alert 
Service Bulletin (ASB) No. A6359, Revision 2, dated July 31, 2000 or PW 
JT8D ASB A6359, Revision 3, dated August 31, 2001.

Comments

    Interested persons have been afforded an opportunity to participate 
in the making of this amendment. Due consideration has been given to 
the comments received.

Understated Financial Impact

    One commenter states the FAA understates the economic impact to the 
operators by not accounting for ancillary costs realized when an engine 
is disassembled to remove a part, and that there are concurrent service 
bulletin requirements when adopting the one-piece CCOC.
    The FAA partially agrees. The indirect costs associated with this 
AD are not directly related to this 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 inspections of existing CCOC's and replacement with 
a one-piece CCOC. Because the original level of safety was already 
determined to be cost-beneficial, these additional requirements are 
needed to return the engine to that level of safety and do not add any 
additional regulatory burden. Therefore, a full cost analysis would be 
redundant and unnecessary. However, the incorporation of the one-piece 
case does require additional modifications that were not incorporated 
in the original proposal economic analysis. That is, 15 additional work 
hours are required to install the one-piece case which adds an 
additional $1,152,000 to the cost of the AD making the estimated total 
$61,388,800.

Tables 3 and 3A

    One commenter requests acknowledgement or exclusion of Tables 3 and 
3A of PW JT8D ASB No. A6359 as containing all of the serial

[[Page 53481]]

numbered CCOC's with part number 797707. This would avoid possible 
confusion regarding the use of the tables.
    The FAA agrees and since the tables are not inclusive of all part 
numbers, a Note 2 is added to the final rule to exclude Tables 3 and 
3A.
    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.

New Revision to Service Bulletin (SB)

    Since publication of the proposal, PW has issued PW JT8D SB No. 
6291, Revision 4, dated May 30, 2002. The only change in PW JT8D SB No. 
6291, Revision 4, is an address revision for PW receipt of the JT8D 
combustion chamber outer case (CCOC).

Economic Analysis

    There are approximately 2,624 Pratt & Whitney JT8D models -209, -
217, -217A, -217C and -219 turbofan engines of the affected design in 
the worldwide fleet. The FAA estimates that 1,280 engines installed on 
airplanes of U.S. registry will be affected by this AD, that it will 
take approximately 2.5 work hours per engine to perform the required 
inspections, and 15 additional work hours to install the one-piece 
case, and that the average labor rate is $60 per work hour. Required 
parts will cost approximately $46, 910 per engine. The 15 additional 
work hours do change the estimated total cost of the AD to the US 
operators. Based on these figures, the total cost of the AD on U.S. 
operators is estimated to be $61,388,800.

Regulatory Analysis

    This final rule does not have federalism implications, as defined 
in Executive Order 13132, because it 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. Accordingly, 
the FAA has not consulted with state authorities prior to publication 
of this final rule.
    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 the 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 
by contacting 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 39-11465 (64 FR 
71280, December 21, 1999) and by adding a new airworthiness directive, 
Amendment 39-12847, to read as follows:

2002-16-08  Pratt & Whitney: Amendment 39-12847. Docket No. 99-NE-
32-AD. Supersedes AD 99-26-06, Amendment 39-11465.

    Applicability. This airworthiness directive (AD) is applicable 
to Pratt & Whitney JT8D models -209, -217, -217A, -217C and -219 
turbofan engines with combustion chamber outer case (CCOC), part 
numbers (P/N's) 500023801, 797707, 807684, and 815830 installed. 
These engines are installed on, but not limited to, McDonnell 
Douglas MD-80 series airplanes.

    Note 1: This 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 (f) 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. Compliance with this AD is required as indicated, 
unless already done. To prevent uncontained failure of the CCOC, 
which could cause release of debris, damage to the airplane, or 
fire, do the following:

Inspections

    (a) Perform initial and repetitive fluorescent magnetic particle 
inspections (FMPI) or fluorescent penetrant inspections (FPI) of 
drain bosses and Ps4 bosses of the CCOC's for cracks, and, if 
necessary, replace with serviceable parts before further flight, in 
accordance with the procedures and intervals specified in paragraph 
1.A. of the Accomplishment Instructions of PW JT8D Alert Service 
Bulletin (ASB) A6359, Revision 3, dated August 31, 2001.
    (b) For all CCOC's P/N 797707 inspect for proper Ps4 and drain 
boss material, and, if necessary, replace with serviceable parts 
before further flight, in accordance with the procedures and 
intervals specified in paragraph 1.B. of the Accomplishment 
Instructions of PW JT8D ASB A6359, Revision 3, dated August 31, 
2001.

    Note 2: Tables 3 and 3A of PW JT8D ASB No. A6359 list associated 
serial numbers (S/N's) of part number (P/N) 797707, however, these 
tables should only be used as a reference as they are not a complete 
list of all parts. Operators, therefore, should verify the part 
numbers of their CCOC's in determining compliance with this AD.

Effective Date for Computing Compliance Intervals

    (c) Use the effective date of this AD for computing compliance 
intervals whenever PW JT8D ASB A6359, Revision 3, dated August 31, 
2001, refers to the publication date of the ASB.

Terminating Action

    (d) At the next part accessibility after the effective date of 
this AD when the CCOC has accumulated cycles-in-service greater than 
the initial inspection threshold specified in Table 1 of PW JT8D ASB 
A6359, Revision 3, dated August 31, 2001, replace the CCOC with a 
one-piece machined CCOC assembly, P/N 815556, in accordance with PW 
JT8D Service Bulletin (SB) 6291, dated May 20, 1997; or Revision 1 
dated July 9, 1997; or Revision 2, dated August 27,1999; or Revision 
3, dated August 31, 2001; or Revision 4, dated May 30, 2002. 
Installation of an improved, one-piece CCOC, P/N 815556, constitutes 
terminating action to the inspections required by this AD.

Definition

    (e) For the purpose of this AD, part accessibility is defined as 
an engine disassembly in which the CCOC is removed from the engine.

Alternative Methods of Compliance

    (f) 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 must submit their request through an appropriate FAA 
Principal Maintenance Inspector, who may add comments and then send 
it to the Manager, ECO.

    Note 3: Information concerning the existence of approved 
alternative methods of

[[Page 53482]]

compliance with this airworthiness directive, if any, may be 
obtained from the ECO.

Special Flight Permits

    (g) Special flight permits may be issued in accordance with 
Secs. 21.197 and 21.199 of the Federal Aviation Regulations (14 CFR 
21.197 and 21.199) to operate the airplane to a location where the 
requirements of this AD can be done.

Documents That Have Been Incorporated By Reference

    (h) The inspections or replacements of the combustion chamber 
outer case (CCOC) must be done in accordance with the following 
Pratt & Whitney service bulletins:

----------------------------------------------------------------------------------------------------------------
               Document No.                      Pages         Revision                     Date
----------------------------------------------------------------------------------------------------------------
ASB JT8D A6359............................             1-3               3  August 31, 2001.
                                                       4-5               2  July 31, 2000.
                                                         6               3  August 31, 2001.
                                                         7               2  July 31, 2000.
                                                         8               1  July 30, 1999.
                                                         9               2  July 31, 2000.
                                                        10               1  July 30, 1999.
                                                        11               2  July 31, 2000.
                                                        12               1  July 30, 1999.
                                                     13-16               2  July 31, 2000.
                                                     17-19               1  July 30, 1999.
                                                     20-27               2  July 31, 2000.
Total pages: 27.
SB JT8D 6291..............................             1-2               3  August 31, 2001.
                                                         3               2  August 27, 1999.
                                                       4-5               3  August 31, 2001.
                                                         6               2  August 27, 1999.
                                                       7-8               3  August 31, 2001.
                                                      9-12               2  August 27, 1999.
Total pages: 12.
SB JT8D 6291..............................            1-10               4  May 30, 2002.
Total pages: 10.
----------------------------------------------------------------------------------------------------------------

This incorporation by reference was approved by the Director of the 
Federal Register in accordance with 5 U.S.C. 552(a) and 1 CFR part 
51. Copies may be obtained from Pratt & Whitney, 400 Main St., East 
Hartford, CT 06108; telephone (860) 565-8770, fax (860) 565-4503. 
Copies may be inspected at the FAA, New England Region, Office of 
the Regional 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.

Effective Date

    (i) This amendment becomes effective on September 20, 2002.

    Issued in Burlington, Massachusetts, on August 2, 2002.
Jay J. Pardee,
Manager, Engine and Propeller Directorate, Aircraft Certification 
Service.
[FR Doc. 02-20267 Filed 8-15-02; 8:45 am]
BILLING CODE 4910-13-P

The complete text was extracted from the official GovInfo HTML edition for this publication. Acquired 2026-10-09T04:18:45.476315+00:00. Text extraction preserves the recorded source wording; it does not determine current requirements.

Open the captured official edition

Source SHA-256

11c2878c1227b4b133826325dc680ed80ccb648802c80884a663c6c06ea4b202

Text SHA-256

9ceb8319a7725498aae91a713b78b0d8fc3d99b18fa26111ef15b33e7e17d87a