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 Department of Transportation Federal Aviation Administration 14 CFR Part 39
[Docket No. 98-ANE-48-AD; Amendment 39-11940; AD 2000-21-08]
RIN 2120-AA64
 AGENCY: Federal Aviation Administration, DOT.
 ACTION: Final rule.
 SUMMARY: This amendment supersedes an existing airworthiness directive (AD), applicable to certain Pratt & Whitney JT8D series turbofan engines, that 
                        ( print page 63538)
                        currently requires revisions to the Time Limits Section (TLS) of the JT8D Turbofan Engine Manual to include required enhanced inspection of selected critical life-limited parts at each piece-part exposure. This action adds additional critical life-limited parts for enhanced inspection. This amendment is prompted by focused inspection procedures that have been developed by the manufacturer for additional critical life-limited parts. The actions specified by this 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 01803; or at the Office of the  Federal Register, 800 North Capitol Street, NW, suite 700, Washington, DC 20001.
 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 99-12-03, Amendment 39-11187 (64 FR 30379, June 8, 1999), which is applicable to Pratt & Whitney (PW) JT8D turbofan engines, was published in the 
                    **Federal Register**
                     on June 8, 1999 (64 FR 30379). That action proposed to require revisions to the Time Limits Section (TLS) of the PW JT8D-1, -1A, -1B, -7, -7A, -7B, -9, -9A, -11, -15, -15A, -17, -17A, -17R, and -17AR 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. Comments Received Interested persons have been afforded an opportunity to participate in the making of this amendment. Due consideration has been given to the four comments received. Request To Extend the Comment Period One commenter 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 commenter requests that the FAA remove the part numbers from the proposed AD. The commenter feels that the part numbers are unnecessary and that eliminating them will minimize the administrative burden on the operators. The FAA does not agree. The current structure of the JT8D engine manual does not lend itself to reference “all” part numbers, as does the structure of other engine lines. However, the FAA will discuss with Pratt and Whitney the possibility of converting the engine manual to incorporate the simpler approach in future supersedures of the JT8D enhanced inspection AD. Request To Remove “of this chapter” From Paragraph (e) One commenter requests that the FAA remove the statement “of this chapter” from the first sentence of paragraph (e) of this AD. The commenter feels that removing the statement will improve the clarity of the paragraph. The FAA agrees. The statement “of this chapter” has been removed from the first sentence of paragraph (e). Request To Revise the Definition of Piece-Part Level One commenter requests that the FAA revise the definition of piece-part level to include a debladed high pressure disk (HPT) disk that is still attached to the HPT shaft. The commenter incorporates an HPT blade management program that does not require unbolting the disk from the shaft. The FAA does not agree. The engine manual inspections required for an HPT disk at piece-part level do not apply to the disk and shaft assembly. The FAA recognizes the need to include the disk and shaft assembly to the critical inspection section and are working with the manufacturer to develop new inspection criteria. The HPT disk and shaft assembly will be considered in a future revision of this enhanced inspection initiative. Economic Analysis 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. Conclusion 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. Regulatory Impact This rule does not have federalism implications, as defined in Executive Order 13132, because it does 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 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 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 
                    ( print page 63539)
                    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.
 § 39.13
 2.Section 39.13 is amended by removing Amendment 39-11187 ( 64 FR 30379, June 8, 1999) and by adding a new airworthiness directive, Amendment 39-11940, to read as follows: **AD 2000-21-08 Pratt & Whitney:**
                             Amendment 39-11940. Docket 98-ANE-48-AD. *Applicability:*
                             Pratt & Whitney (PW) JT8D-1, -1A, -1B, -7, -7A, -7B, -9, -9A, -11, -15, -15A, -17, -17A, -17R, and -17AR series turbofan engines, installed on but not limited to Boeing 727 and 737 series, and McDonnell Douglas DC-9 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-1, -1A, -1B, -7, -7A, -7B, -9, -9A, -11, -15, -15A, -17, -17A, -17R, and -17AR series 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 has 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. Description
Engine manualSection
Inspection**Hub (Disk), 1st Stage Compressor**491201
72-33-31
-02, -03, -04496501
72-33-31
-02, -03, -04504101
72-33-31
-02, -03, -04515201
72-33-31
-02, -03, -04594301
72-33-31
-02, -03, -04640501
72-33-31
-02, -03, -04640601
72-33-31
-02, -03, -04743301
72-33-31
-02, -03, -04749701
72-33-31
-02, -03, -04749801
72-33-31
-02, -03, -04750001
72-33-31
-02, -03, -04750101
72-33-31
-02, -03, -04778901
72-33-31
-02, -03, -04791401
72-33-31
-02, -03, -04791501
72-33-31
-02, -03, -04791601
72-33-31
-02, -03, -04791701
72-33-31
-02, -03, -04791801
72-33-31
-02, -03, -04806001
72-33-31
-02, -03, -04806101
72-33-31
-02, -03, -04817401
72-33-31
-02, -03, -04844401
72-33-31
-02, -03, -04845401
72-33-31
-02, -03, -04848001
72-33-31
-02, -03, -04848101
72-33-31
-02, -03, -04**Disk, 2nd Stage Compressor**482502
72-33-33
-02502502
72-33-33
-02520602
72-33-33
-02570302
72-33-33
-02570402
72-33-33
-02678202
72-33-33
-02730202
72-33-33
-02730302
72-33-33
-02730402
72-33-33
-02740502
72-33-33
-02745702
72-33-33
-02745902
72-33-33
-02746002
72-33-33
-02746802
72-33-33
-02760402
72-33-33
-02760502
72-33-33
-02807502
72-33-33
-02500240201
72-33-33
-02790832 (Disk assembly)
72-33-33
-02**Turbine Disk, First Stage With Integral Shaft**481135
72-52-04
-03494211
72-52-04
-03500701
72-52-04
-03516101
72-52-04
-03529115
72-52-04
-03538901
72-52-04
-03544501
72-52-04
-03544601
72-52-04
-03544701
72-52-04
-03553201
72-52-04
-03558401
72-52-04
-03565101
72-52-04
-03565201
72-52-04
-03565301
72-52-04
-03578201
72-52-04
-03579001
72-52-04
-03**HP Turbine Disk, First Stage, Separable**587501
72-52-02
-035006101-01
72-52-02
-03578001
72-52-02
-035005201-01
72-52-02
-03696801
72-52-02
-03742501
72-52-02
-03752401
72-52-02
-03767601
72-52-02
-03792801
72-52-02
-03856501
72-52-02
-03832201
72-52-02
-03855701
72-52-02
-03856401
72-52-02
-035003601-01
72-52-02
-035003601-021
72-52-02
-035004301-01
72-52-02
-03
 (b) Except as provided in paragraph (c) of this AD, and notwithstanding contrary provisions in 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-1, -1A, -1B, -7, -7A, -7B, -9, -9A, -11, -15, -15A, -17, -17A, -17R, and -17AR series 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 Manager, Engine Certification Office (ECO). Operators shall 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 (d) Special flight permits may be issued in accordance with 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. 
                            ( print page 63540) 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 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-1, -1A, -1B, -7, -7A, -7B, -9, -9A, -11, -15, -15A, -17, -17A, -17R, and -17AR series 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 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 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-1, -1A, -1B, -7, -7A, -7B, -9, -9A, -11, -15, -15A, -17, -17A, -17R, and -17AR series 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. 00-26971 Filed 10-23-00; 8:45 am] BILLING CODE 4910-13-P