AD 2000-21-07

[Federal Register Volume 65, Number 206 (Tuesday, October 24, 2000)]
[Rules and Regulations]
[Pages 63540-63541]
From the Federal Register Online via the Government Publishing Office [<a href="http://www.gpo.gov">www.gpo.gov</a>]
[FR Doc No: 00-26970]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 98-ANE-43-AD; Amendment 39-11939; AD 2000-21-07]
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 proposal is prompted by additional 
focused inspection procedures that have been developed by the 
manufacturer. The actions specified by this proposed AD are intended to 
prevent critical life-limited rotating engine part failure, which could 
result in an uncontained engine failure and damage to the airplane.

DATES: Effective date April 23, 2001.

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 99-12-04, 
Amendment 39-11188 (64 FR 30382, June 8, 1999), which is applicable to 
Pratt & Whitney (PW) JT8D-200 turbofan engines, was published in the 
Federal Register on October 7, 1999 (64 FR 54598). 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 two comments received.

Request To Extend the Comment Period

    One comment requests that the FAA extend the NPRM comment period 
because the required procedures had not been published in the engine 
manual (EM). The FAA does not agree.
    The FAA believes that the nature and scope of the added inspections 
will not be significantly different from existing inspections. In 
addition, 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 also 
allow the manufacturer to issue a manual revision. Operators may submit 
comments to the docket file on the specific procedures, once they are 
published, and the FAA will consider extending the effective date 
further or additional rulemaking, as necessary. The FAA does not 
believe, however, that this final rule need be delayed pending the 
publication of the inspection procedures, or the initial compliance 
time extended to accommodate the manufacturer's manual revision cycle.

Request to Remove Part Numbers

    One comment requests that the FAA remove the part numbers from the 
proposed AD. The commenter states that the part numbers are 
unnecessary, and eliminating them will minimize the administrative 
burden on the operators. The FAA does not agree. The current structure 
of the JT8D-200 engine manual does not lend itself to reference ``all'' 
part numbers as does the structure of other engine lines. However, the 
FAA will discuss the possibility of converting the engine manual to 
incorporate the simpler approach in future supersedures of the JT8D-200 
enhanced inspection AD.
    No comments were received on the economic analysis contained in the 
proposed rules. Based on that analysis, the FAA has determined that the 
annual per engine cost of $60 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

[[Page 63541]]

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 39-11188 (64 FR 
30382, June 8, 1999) and by adding a new airworthiness directive, 
Amendment 39-11939, to read as follows:

AD2000-21-07 Pratt & Whitney: Amendment 39-11939. Docket 98-ANE-43-
AD.

    Applicability: Pratt & Whitney (PW) JT8D-200 series turbofan 
engines, installed on but not limited 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 accomplished 
previously.
    To prevent critical life-limited rotating engine part failure, 
which could result in an uncontained engine failure and damage to 
the airplane, accomplish 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/09200 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 necessary inspection procedures 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 neither replace 
nor negate 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
------------------------------------------------------------------------
                    Hub (Disk), 1st Stage Compressor
------------------------------------------------------------------------
5000501-01 (Hub detail).................        72-33-31        -02, -03
5000421-01 (Hub assembly)...............        72-33-31        -02, -03
------------------------------------------------------------------------
                      HP Turbine Disk, First Stage
------------------------------------------------------------------------
804301..................................       72-52-02,             -03
5004501-01..............................        72-52-02             -03
856701..................................        72-52-02             -03
5004301-01..............................        72-52-02             -03
832201..................................        72-52-02             -03
855701..................................        72-52-02             -03
856601..................................        72-52-02           -03''
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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 
shall be performed only in accordance with 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 
shall 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 
sections 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 accomplished.

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 Turbofan Engine Manual, and the air carrier's continuous 
airworthiness program.
    Alternately, 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.

    (f) This amendment becomes effective on April 23, 2001.

    Issued in Burlington, Massachusetts, on October 16, 2000.
Jay J. Pardee,
Manager, Engine and Propeller Directorate, Aircraft Certification 
Service.
[FR Doc. 00-26970 Filed 10-23-00; 8:45 am]
BILLING CODE 4910-13-P