[Federal Register Volume 67, Number 228 (Tuesday, November 26, 2002)]
[Rules and Regulations]
[Pages 70686-70688]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 02-29670]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2001-NE-30-AD; Amendment 39-12958; AD 2002-23-14]
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 adopts a new airworthiness directive (AD), that 
is applicable to Pratt & Whitney (PW) JT8D-200 series turbofan engines. 
This amendment requires initial and repetitive visual inspections, 
fluorescent magnetic particle inspections (FMPI), and fretting wear 
inspections of high pressure compressor (HPC) front hubs that have 
operated with PWA-110 coating in the interface between the hub and the 
stage 8-9 spacer. This amendment is prompted by the discovery of 
cracked tierod holes found during routine engine overhauls. The actions 
specified by this AD are intended to prevent a rupture of the HPC front 
hub that could result in an uncontained engine failure and damage to 
the airplane.

DATES: Effective December 31, 2002. The incorporation by reference of 
certain publications listed in the regulations is approved by the 
Director of the Federal Register as of December 31, 2002.

ADDRESSES: The service information referenced in this AD may be 
obtained from Pratt & Whitney, 400 Main St., East Hartford, CT 06108, 
telephone (860) 565-6600; 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) to

[[Page 70687]]

include an AD that is applicable to PW JT8D-200 series turbofan engines 
was published in the Federal Register on September 19, 2002 (67 FR 
59027). That action proposed to require initial and repetitive visual 
inspections, FMPI, and fretting wear inspections of HPC front hubs that 
have operated with PWA-110 coating in the interface between the hub and 
the stage 8-9 spacer in accordance with PWAlert Service Bulletin (ASB) 
JT8D A6430, dated September 5, 2002.

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.

Credit for Inspections

    Two commenters request that the AD be changed to allow credit for 
inspections occurring before 9,000 cycles in service (CIS). One 
commenter requests that the second inspection occur within 6,500 cycles 
of the initial inspection, while the other commenter requests that the 
second inspection occur as late as 18,000 cycles.
    The FAA partially agrees. The FAA agrees that some credit should be 
given for inspections occurring before 9,000. We do not agree, however, 
that the second inspection should be delayed until 18,000 CIS. A 15,500 
CIS limit is more appropriate. Further, the shop visit requirement will 
be relaxed to an accessibility requirement for HPC front hubs inspected 
before accumulating 9,000 CIS. Accordingly, the inspection interval for 
HPC front hubs has been modified for hubs with less than 17,000 CIS to 
account for hubs inspected before 9,000 CIS. These hubs can be 
reinspected at the first accessibility of the HPC front hub after 
accumulating 9,000 CIS but not to exceed 15,500 CIS.

Effective Date To Include Sufficient Time for Alternative Methods of 
Compliance (AMOC) Request

    One commenter requests that the effective date be chosen to allow 
sufficient time for an AMOC request.
    The FAA agrees. The FAA provides a 35-day time frame from the date 
of publication to the effective date of the AD which should provide 
sufficient time to request an AMOC, if necessary.

Exclude Engine Buildup Shop From the Shop Visit Requirements

    One commenter requests that an LPT module replacement performed at 
an engine buildup shop be excluded from the shop visit requirements of 
this AD. The commenter feels that there are a small number of engines 
affected annually for this particular operator.
    The FAA does not agree. The variability of every operator's 
maintenance program makes it difficult to define a shop visit that 
meets all operator's needs. The FAA believes the current definition is 
best suited for all operators. If an individual operator believes some 
engines should be exempt from the shop visit definition of the AD 
because of some unique features of their maintenance program, then they 
should seek approval for that provision in accordance with paragraph 
(f) of this AD.

Understated Financial Impact

    One commenter states that the FAA underestimates the economic 
impact of the AD by failing to include ancilliary costs of the AD.
    The FAA does not agree. 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. 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.
    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.

Economic Analysis

    There are approximately 2,648 PW JT8D-200 series turbofan engines 
of the affected design in the worldwide fleet. The FAA estimates that 
2,352 engines installed on airplanes of U.S. registry would be affected 
by this AD. The FAA also estimates that it would take approximately 6 
work hours per engine to perform the inspection, and that the average 
labor rate is $60 per work hour. Based on these figures, the total cost 
of the initial inspection to U.S. operators is estimated to be 
$846,720.

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 adding a new airworthiness directive 
to read as follows:

2002-23-14 Pratt & Whitney: Amendment 39-12958. Docket No. 2001-NE-
30-AD.

    Applicability: This airworthiness directive (AD) is applicable 
to Pratt & Whitney (PW) JT8D-209, -217, -217A, -217C, and -219 
series turbofan engines that have high pressure compressor (HPC) 
front hubs installed that have operated with PWA-110 coating in the 
interface between the HPC front hub and the stage 8-9 spacer (PWA-
110

[[Page 70688]]

coating applied to either the spacer or the hub) and were 
manufactured after June 1, 1988. 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 a rupture of the HPC front hub, that 
could result in an uncontained engine failure and damage to the 
airplane, do the following:

Inspect hubs

    (a) Strip the protective coating, visually inspect for fretting 
wear, fluorescent magnetic particle inspect (FMPI), reidentify and 
replate HPC front hubs and the stage 8-9 spacers, and replace if 
necessary in accordance with the accomplishment instructions of 
Pratt & Whitney Alert Service Bulletin (ASB) JT8D A6430, dated 
September 5, 2002, as follows:
    (1) For HPC front hubs with fewer than 17,000 total cycles-in-
service (CIS) on the effective date of this AD, inspect as follows:
    (i) For HPC front hubs not inspected in accordance with ASB JT8D 
A6430, dated September 5, 2002, before accumulating 9,000 total CIS, 
inspect at the first shop visit after accumulating 9,000 total CIS 
not to exceed 18,000 total CIS.
    (ii) For HPC front hubs inspected in accordance with ASB JT8D 
A6430, dated September 5, 2002, before accumulating 9,000 total CIS, 
inspect at the next accessibility of the HPC front hub after 
accumulating 9,000 total CIS not to exceed 15,500 total CIS.
    (2) For HPC front hubs with greater than or equal to 17,000 
total CIS but less than 19,000 total CIS on the effective date of 
this AD, inspect at the next shop visit, not to exceed 1,000 CIS 
from the effective date of this AD or 19,500 total CIS, whichever 
occurs first.
    (3) For HPC front hubs with greater than or equal to 19,000 
total CIS on the effective date of this AD, inspect within 500 CIS 
from the effective date of this AD.

Repetitive-Inspections

    (b) Thereafter, strip the protective coating, visually inspect 
for fretting wear, FMPI and replate HPC front hubs, and replace if 
necessary in accordance with the accomplishment instructions of 
Pratt & Whitney Alert Service Bulletin (ASB) JT8D A6430, dated 
September 5, 2002, at intervals not to exceed 6,500 CIS since the 
last inspection.

Optional Terminating Action

    (c) Installation of a Nickel-Cadmium plated HPC front hub that 
has never operated with PWA-110 coating in the interface between the 
HPC front hub and the stage 8-9 spacer and a Nickel-Cadmium or 
Electroless Nickel plated spacer is an optional terminating action 
for the inspections of paragraphs (a) and (b) of this AD.

Definitions

    (d) For the purposes of this AD, a shop visit is defined as an 
engine removal, where engine maintenance entails separation of pairs 
of major engine flanges or the removal of a disk, hub, or spool at a 
maintenance facility, regardless of other planned maintenance, 
except as follows:
    (1) Engine removal for the purpose of performing field 
maintenance type activities at a maintenance facility in lieu of 
performing them on-wing is not a ``shop visit''.
    (2) Separation of flanges of the Combustion Chamber and Turbine 
Fan Duct Assembly (split flanges) for the purpose of accessing non-
rotating accessory hardware is not a ``shop visit''.
    (3) Separation of flanges for the purpose of shipment without 
subsequent internal maintenance is not a ``shop visit''.
    (e) For the purposes of this AD accessibility of the HPC front 
hub is removal of the hub from the engine and deblading of that hub.

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

    Note 2: Information concerning the existence of approved 
alternative methods of 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 
Sec. Sec.  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 must be done in accordance with Pratt & 
Whitney Alert Service Bulletin (ASB) JT8D A6430, dated September 5, 
2002. 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) 565-6600; 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 December 31, 2002.

    Issued in Burlington, Massachusetts, on November 15, 2002.
Mark C. Fulmer,
Acting Manager, Engine and Propeller Directorate, Aircraft 
Certification Service.
[FR Doc. 02-29670 Filed 11-25-02; 8:45 am]
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