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

[Federal Register Volume 67, Number 128 (Wednesday, July 3, 2002)]
[Rules and Regulations]
[Pages 44527-44529]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 02-16535]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 98-ANE-43-AD; Amendment 39-12797; AD 2002-13-09]
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), applicable to certain Pratt & Whitney JT8D-200 series turbofan 
engines, that currently requires revisions to the Time Limits Section 
(TLS) of the JT8D-200 Turbofan Engine Manual to include required 
enhanced inspection of selected critical life-limited parts at each 
piece-part exposure. This AD adds additional critical life-limited 
parts for enhanced inspection. This AD is prompted by additional 
focused inspection procedures that have been developed by the 
manufacturer. The actions specified by this AD are intended to prevent 
the failure of critical, life-limited, rotating engine parts, which 
could result in an uncontained engine failure and damage to the 
airplane.

DATES: Effective date December 30, 2002.

ADDRESSES: The information referenced in this AD may be examined at the 
Federal Aviation Administration (FAA), New England Region, Office of 
the Regional Counsel, 12 New England Executive Park, Burlington, MA.

FOR FURTHER INFORMATION CONTACT: Christopher Spinney, Aerospace 
Engineer, Engine Certification Office, FAA, Engine and Propeller 
Directorate, 12 New England Executive Park, Burlington, MA 01803; 
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 2000-21-07, 
Amendment 39-11939, which is applicable to Pratt & Whitney (PW) JT8D-
200 turbofan engines, was published in the Federal Register on October 
24, 2000 (65 FR 63540) to require revisions to the Time Limits Section 
(TLS) of the PW JT8D-200 series Turbofan Engine Manual to include 
required enhanced inspection of selected critical life-limited parts at 
each piece-part exposure.
    Since the issuance of that AD, additional focused inspection 
procedures for other critical life-limited rotating engine parts have 
been developed by PW.
    Interested persons have been afforded an opportunity to participate 
in the making of this amendment. Due consideration has been given to 
the comments received.

Removal of HPT Assembly Inspection From AD

    One commenter suggests that the HPT assembly inspection be removed 
from the AD because the part is not at piece part level and the 
prototype cleaning procedures are inadequate. The FAA disagrees. After 
assembly at manufacture, the HPT disk and shaft essentially can be 
treated as a single part. The HPT disk and shaft are not required to be 
separated at overhaul unless there is unrepairable damage to one of the 
parts or one of the parts has reached a time limit. Further, separation 
of the parts can cause mechanical damage to the tie rod holes that 
requires additional repair. The FAA does not want to force the 
separation of the disk and shaft at every overhaul but does want to 
have the HPT disk inspected at each opportunity throughout the life of 
the disk. Therefore, in order to provide a sufficient number of 
opportunity inspections over the life of the HPT disk, the original 
equipment manager (OEM) developed an inspection of the disk and shaft 
assembly. Further, the OEM has addressed problems associated with the 
prototype process in the final approved inspection process for the disk 
and shaft assembly. Accordingly, this AD requires changes to the life-
limits section that incorporate that inspection of the disk and shaft 
assembly.

Publication of NPRM

    One commenter objects to the publication of the NPRM prior to 
having the inspection procedure available in the Engine Manual. The 
commenter states that air carriers that use the affected engines may 
not have had an opportunity to comment on the inspection procedure. The 
FAA disagrees. The FAA believes that the nature and scope of the added 
inspections will not differ significantly from existing inspection 
procedures. In addition, the FAA has set the effective date of this AD 
at 180 days after publication to allow time for the manufacturer to 
include these specific inspection procedures in the next revision of 
the Engine Manual. Operators may submit additional comments on those 
inspection procedures and the FAA will consider either extending the 
effective date further or additional rulemaking, as necessary. The FAA 
does not believe, however, that this final rule need be delayed pending 
publication of the inspection procedures.

Effective Date of AD

    One commenter requests a 180-day period between the issue date and 
the effective date of the AD similar to that permitted by the previous 
rule. The FAA agrees and the effective date of this AD has been 
extended to 180 days after publication to allow time for the specific 
procedures to be published. The extra time until the AD becomes 
effective should allow the manufacturer to issue a manual revision.

Removal of Part Numbers

    One commenter believes that the FAA has reversed its position 
relative to not incorporating part numbers in the AD. The FAA agrees in 
part. As the commenter notes, the FAA had previously viewed the engine 
manual for this engine model to be structured so as to make reference 
to ``all'' part numbers impractical. The FAA has reviewed the engine 
manual again and the proposed new changes and determined that 
individual part numbers may be removed. Therefore, this AD references 
``all'' part numbers,

[[Page 44528]]

as with other engine lines. The decision not to include part numbers 
was originally made to accommodate the industry. The removal of part 
numbers eliminates the requirement to modify the TLS and Continuous 
Airworthiness Maintenance programs every time a new part number is 
introduced by the manufacturer for those parts covered by the AD.

Typographical Error

    One commenter notes that a typographical error ``JT8D/09200,'' 
occurs in paragraphs (a) and (e) of the Compliance Section of the NPRM 
and should be changed to read ``JT8D-200.'' The FAA agrees and the 
change has been made to the rule.
    No comments were received on the economic analysis contained in the 
proposed rule. Based on that analysis, the FAA has determined that the 
annual per engine cost of $480 does not create a significant economic 
impact on small entities.
    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.
    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, 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 39-11939 (65 FR 
63540, October 24, 2000), and by adding a new airworthiness directive, 
Amendment 39-12797, to read as follows:

AD 2002-13-09  Pratt & Whitney: Amendment 39-12797. Docket No. 
98ANE-43AD. Supersedes AD 2000-21-07, Amendment 39-11939.

    Applicability: Pratt & Whitney (PW) JT8D-200 series turbofan 
engines, installed on but not limited to McDonnell Douglas MD-80 
series airplanes.


    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 (c) 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 already done.
    To prevent critical life-limited rotating engine part failure, 
which could result in an uncontained engine failure and damage to 
the airplane, do the following:

Inspections

    (a) Within the next 30 days after the effective date of this AD, 
revise the Time Limits Section (TLS) of the JT8D-200 Turbofan Engine 
Manual, and for air carrier operations revise the approved 
continuous airworthiness maintenance program, by adding the 
following:

``Critical Life Limited Part Inspection

    A. Inspection Requirements:
    (1) This section contains the definitions for individual engine 
piece-parts and the inspection procedures, which are necessary, when 
these parts are removed from the engine.
    (2) It is necessary to do the inspection procedures of the 
piece-parts in Paragraph B when:
    (a) The part is removed from the engine and disassembled to the 
level specified in paragraph B and
    (b) The part has accumulated more than 100 cycles since the last 
piece part inspection, provided that the part is not damaged or 
related to the cause of its removal from the engine.
    (3) The inspections specified in this section do not replace or 
make unnecessary other recommended inspections for these parts or 
other parts.
    B. Parts Requiring Inspection.


    Note: Piece part is defined as any of the listed parts with all 
the blades removed.


------------------------------------------------------------------------
                                                  Engine manual
              Description              ---------------------------------
                                         Section       Inspection No.
------------------------------------------------------------------------
Hub (Disk), 1st Stage Compressor:
  Hub Detail--All P/N's...............   72-33-31  -02, -03
  Hub Assembly--All P/N's.............   72-33-31  -02, -03
Disk, 13th Stage Compressor--All P/N's   72-36-47  -02
HP Turbine, First Stage:
  Rotor Assembly--All P/N's...........   72-52-02  -04
  Disk--All P/N's.....................   72-52-02  -03
Disk, 2nd Stage Turbine--All P/N's....    2-53-16  -02
Disk, 3rd Stage Turbine--All P/N's....   72-53-17  -02
Disk, 4th Stage Turbine--.............   72-53-18  -02''
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    (b) Except as provided in paragraph (c) of this AD, and 
notwithstanding contrary provisions in section 43.16 of the Federal 
Aviation Regulations (14 CFR 43.16), these mandatory inspections 
must be performed using the TLS of the PW JT8D-200 Turbofan Engine 
Manual.

Alternative Methods of Compliance

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

Ferry Flights

    (d) 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.

Continuous Airworthiness Maintenance Program

    (e) FAA-certificated air carriers that have an approved 
continuous airworthiness maintenance program in accordance with the 
record keeping requirement of Sec. 121.369(c) of the Federal 
Aviation Regulations (14 CFR 121.369(c)) must maintain records of 
the mandatory inspections that result from revising the TLS of the 
PW JT8D-200

[[Page 44529]]

Turbofan Engine Manual, and the air carrier's continuous 
airworthiness program. Alternatively, certificated air carriers may 
establish an approved system of record retention that provides a 
method for preservation and retrieval of the maintenance records 
that include the inspections resulting from this AD, and include the 
policy and procedures for implementing this alternate method in the 
air carrier's maintenance manual required by Sec. 121.369(c) of the 
Federal Aviation Regulations (14 CFR 121.369(c)); however, the 
alternate system must be accepted by the appropriate PMI and require 
the maintenance records be maintained either indefinitely or until 
the work is repeated. Records of the piece-part inspections are not 
required under Sec. 121.380 (a)(2)(vi) of the Federal Aviation 
Regulations (14 CFR 121.380(a)(2)(vi)). All other operators must 
maintain the records of mandatory inspections required by the 
applicable regulations governing their operations.


    Note 3: The requirements of this AD have been met when the 
engine manual changes are made and air carriers have modified their 
continuous airworthiness maintenance plans to reflect the 
requirements in the PW JT8D-200 Turbofan Engine Manual.

Effective Date

    (f) This amendment becomes effective on December 30, 2002.

    Issued in Burlington, Massachusetts, on June 18, 2002.
Jay J. Pardee,
Manager, Engine and Propeller Directorate, Aircraft Certification 
Service.
[FR Doc. 02-16535 Filed 7-2-02; 8:45 am]
BILLING CODE 4910-13-P

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