Skip to Content

Rule

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

Document Details

Information about this document as published in the Federal Register.

Published Document

This document has been published in the Federal Register. Use the PDF linked in the document sidebar for the official electronic format.

Start Preamble

AGENCY:

Federal Aviation Administration (FAA), Department of Transportation (DOT).

ACTION:

Final rule.

SUMMARY:

The FAA is revising an existing airworthiness directive (AD) for Pratt & Whitney JT8D-209, -217, -217C, and -219 turbofan engines with front compressor front hub (fan hub), part number (P/N) 5000501-01 installed. That AD currently requires cleaning the front compressor front hubs (fan hubs), initial and repetitive eddy current (ECI) and fluorescent penetrant inspections (FPI) of tierod and counterweight holes for cracks, removal of bushings, cleaning and ECI and FPI of bushed holes for cracks and, if necessary, replacement with serviceable parts. In addition, that AD currently requires reporting the findings of cracked fan hubs and monthly reports of the number of inspections completed. This AD requires the same actions, except for the monthly reporting of the number of completed inspections. This AD results from the FAA determining that it has collected a sufficient amount of data since issuing AD 97-17-04 and that therefore, it no longer needs the monthly reporting of the number of completed inspections. We are issuing this AD to prevent fan hub failure due to tierod, counterweight, or bushed hole cracking, which could result in an uncontained engine failure and damage to the airplane.

DATES:

This AD becomes effective April 22, 2010. The Director of the Federal Register previously approved the incorporation by reference of the publications listed in the regulations as of March 5, 1997 (62 FR 4902).

ADDRESSES:

You can get the service information identified in this AD from Pratt & Whitney, 400 Main St., East Hartford, CT 06108; telephone (860) 565-8770; fax (860) 565-4503.

The Docket Operations office is located at Docket Management Facility, U.S. Department of Transportation, 1200 New Jersey Avenue, SE., West Building Ground Floor, Room W12-140, Washington, DC 20590-0001.

Start Further Info

FOR FURTHER INFORMATION CONTACT:

Kevin Dickert, Aerospace Engineer, Engine Certification Office, FAA, Engine & Propeller Directorate, 12 New England Executive Park, Burlington, MA 01803; e-mail: kevin.dickert@faa.gov; telephone (781) 238-7117; fax (781) 238-7199.

End Further Info End Preamble Start Supplemental Information

SUPPLEMENTARY INFORMATION:

The FAA proposed to amend 14 CFR part 39 with a proposed AD. The proposed AD applies to Pratt & Whitney JT8D-209, -217, -217C, and -219 turbofan engines with front compressor front hub (fan hub), P/N 5000501-01 installed. We published the proposed AD in the Federal Register on December 21, 2009 (74 FR 67831). That action proposed to require cleaning the front compressor front hubs (fan hubs), initial and repetitive ECI and FPI of tierod and counterweight holes for cracks, removal of bushings, cleaning and ECI and FPI of bushed holes for cracks and, if necessary, replacement with serviceable parts. That action also proposed to eliminate the monthly reporting of the number of completed inspections.

Examining the AD Docket

You may examine the AD docket on the Internet at http://www.regulations.gov;​ or in person at the Docket Operations office between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this AD, the regulatory evaluation, any comments received, and other information. The street address for the Docket Operations office (telephone (800) 647-5527) is provided in the ADDRESSES section. Comments will be available in the AD docket shortly after receipt.

Comments

We provided the public the opportunity to participate in the development of this AD. We have considered the one comment received. The commenter supports the proposal.

Conclusion

We have carefully reviewed the available data, including the comment received, and determined that air safety and the public interest require adopting the AD as proposed.

Costs of Compliance

We estimate that this AD revision will affect 1,170 JT8D-209, -217, -217C, and -219 turbofan engines installed on airplanes of U.S. registry. We estimate that it will take four work-hours per engine to complete one inspection of the fan hub at piece-part exposure. The average labor rate is $80 per work-hour. Based on these figures, we estimate the total cost of the AD to U.S. operators to be $374,400.

Authority for This Rulemaking

Title 49 of the United States Code specifies the FAA's authority to issue rules on aviation safety. Subtitle I, Section 106, describes the authority of the FAA Administrator. Subtitle VII, Aviation Programs, describes in more detail the scope of the Agency's authority.

We are issuing this rulemaking under the authority described in Subtitle VII, Part A, Subpart III, Section 44701, “General requirements.” Under that section, Congress charges the FAA with promoting safe flight of civil aircraft in air commerce by prescribing regulations for practices, methods, and procedures the Administrator finds necessary for safety in air commerce. This regulation is within the scope of that authority because it addresses an unsafe condition that is likely to exist or develop on products identified in this rulemaking action.

Regulatory Findings

We have determined that this AD will not have federalism implications under Executive Order 13132. This AD will 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.

For the reasons discussed above, I certify that this AD:

(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.

We prepared a summary of the costs to comply with this AD and placed it in the AD Docket. You may get a copy of this summary at the address listed under ADDRESSES.

Start List of Subjects Start Printed Page 12969

List of Subjects in 14 CFR Part 39

End List of Subjects

Adoption of the Amendment

Start Amendment Part

Accordingly, under the authority delegated to me by the Administrator, the Federal Aviation Administration amends

End Amendment Part Start Part

PART 39—AIRWORTHINESS DIRECTIVES

End Part Start Amendment Part

1. The authority citation for part 39 continues to read as follows:

End Amendment Part Start Authority

Authority: 49 U.S.C. 106(g), 40113, 44701.

End Authority
[Amended]
Start Amendment Part

2. The FAA amends § 39.13 by removing Amendment 39-10106 (

End Amendment Part

97-17-04R1 Pratt & Whitney: Amendment 39-16237. Docket No. FAA-2009-0883; Directorate Identifier 97-ANE-08.

Effective Date

(a) This airworthiness directive (AD) becomes effective April 22, 2010.

Affected ADs

(b) This AD revises AD 97-17-04, Amendment 39-10106.

Applicability

(c) This AD applies to Pratt & Whitney (PW) JT8D-209, -217, -217C, and -219 turbofan engines with front compressor front hub (fan hub), part number (P/N) 5000501-01, installed. These engines are installed on, but not limited to, McDonnell Douglas MD-80 series airplanes.

Unsafe Condition

(d) This AD results from the FAA determining that it has collected a sufficient amount of data since issuing AD 97-17-04 and that therefore, it no longer needs the monthly reporting of the number of completed inspections. We are issuing this AD to prevent fan hub failure due to tierod, counterweight, or bushed hole cracking, which could result in an uncontained engine failure and damage to the airplane.

Compliance

(e) You are responsible for having the actions required by this AD performed within the compliance times specified unless the actions have already been done.

(f) Inspect fan hubs for cracks in accordance with the Accomplishment Instructions, Paragraph A, Part 1, and, if applicable, Paragraph B, of PW Alert Service Bulletin (ASB) No. A6272, dated September 24, 1996, as follows:

(1) For fan hubs identified by serial numbers (S/Ns) in Table 2 of this AD, after the fan hub has accumulated more than 4,000 cycles-since-new (CSN), as follows:

(i) Initially inspect within 315 cycles-in-service (CIS) from the effective date of this AD, or 4,315 CSN, whichever occurs later.

(ii) Thereafter, re-inspect after accumulating 2,500 CIS since last inspection, but not to exceed 10,000 CIS since last inspection.

(2) For fan hubs identified by S/Ns in Appendix A of PW ASB No. A6272, dated September 24, 1996, after the fan hub has accumulated more than 4,000 CSN, as follows:

(i) Select an initial inspection interval from Table 1 of this AD, and inspect accordingly.

Table 1—Inspections

Initial inspectionRe-inspection
(A) Within 1,050 CIS after the effective date of AD 97-02-11, March 5, 1997, or prior to accumulating 5,050 CSN, whichever occurs later;After accumulating 2,500 CIS since-last-inspection, but not to exceed 6,000 CIS since-last-inspection.
OROR
(B) Within 990 CIS after the effective date of AD 97-02-11, March 5, 1997, or prior to accumulating 4,990 CSN, whichever occurs later;After accumulating 2,500 CIS since-last-inspection, but not to exceed 8,000 CIS since-last-inspection.
OROR
(C) Within 965 CIS after the effective date of AD 97-02-11, March 5, 1997, or prior to accumulating 4,965 CSN, whichever occurs later.After accumulating 2,500 CIS since-last-inspection, but not to exceed 10,000 CIS since-last-inspection.

Table 2—Hubs With Traveler Notations

M67663M67802P66880S25545P66747R33099S25292
M67671M67812P66885S25558P66756R33107S25299
M67675M67826R32732S25564P66800R33113S25301
M67681M67829R32733S25598P66814R33124S25302
M67685M67830R32735S25618P66819R33131S25308
M67686M67831R32740S25621P66831R33132S25312
M67687M67832R32741S25637R32767R33133S25316
M67697M67834R32810S25640R32787R33136S25323
M67700M67843R32849T50693R32792R33152S25334
M67706M67849R32850T50752R32795R33157S25335
M67710M67858S25222T50785R32796R33163S25337
M67712M67866S25464T50791R32800R33165S25344
M67713M67868S25481T50792R32807R33168S25369
M67714M67869S25483T50819R32856R33171S25377
M67715M67872S25484T50823R32860R33173S25378
M67716M67888S25486T50827R32870R33180S25381
M67717N71771S25488T50874R32883R33181S25394
M67722N71804S25489T50875R32905R33189S25399
M67723N71806S25490T51058R32926R33194S25402
M67725N71810S25491T51104R32930R33198S25406
M67726N71811S25492R32952R33201S25411
M67730N71875S25494R32964R33202S25413
M67731N71876S25495R32966R33207S25414
M67746N71921S25497R32971S25193S25415
Start Printed Page 12970
M67751N71965S25498R32976S25195S25418
M67753N72062S25499R32981S25207S25419
M67764N72126S25500R32990S25208S25421
M67765N72152S25501R32994S25221S25422
M67784N72162S25502R33000S25229S25430
M67791N72207S25505R33004S25238S25437
M67792N72216S25506R33040S25246S25439
M67793N72219S25507R33055S25248S25449
M67794N72242S25508R33059S25250R33186
M67795P66693S25509R33077S25256S25528
M67796P66695S25514R33080S25262
M67797P66696S25529R33082S25268
M67798P66698S25532R33086S25278
M67799P66699S25541R33087S25287
M67800P66737S25543R33089S25288
M67801P66753S25544R33090

(ii) Thereafter, re-inspect at intervals that correspond to the selected inspection interval.

(3) If a fan hub is identified in both Table 2 of this AD and Appendix A of PW ASB No. A6272, dated September 24, 1996, inspect in accordance with paragraph (f)(1) or (f)(2) of this AD, whichever occurs first.

(4) For fan hubs with S/Ns not listed in Table 2 of this AD or in Appendix A of PW ASB No. A6272, dated September 24, 1996, after the fan hub has accumulated more than 4,000 CSN, inspect the next time the fan hub is in the shop at piece-part level, but not to exceed 10,000 CIS after March 5, 1997.

(5) Prior to further flight, remove from service fan hubs found cracked or that exceed the bushed hole acceptance criteria described in PW ASB No. A6272, dated September 24, 1996.

Reporting Requirements

(g) Report findings of cracked fan hubs using Accomplishment Instructions, Paragraph F, of Attachment 1 to PW ASB No. A6272, dated September 24, 1996, within 48 hours to Kevin Dickert, Engine Certification Office, FAA, Engine and Propeller Directorate, 12 New England Executive Park, Burlington, MA 01803; telephone (781) 238-7117; fax (781) 238-7199; e-mail: kevin.dickert@faa.gov.

(h) The Office of Management and Budget (OMB) has approved the reporting requirements and assigned OMB control number 2120-0056.

Alternative Methods of Compliance

(i) The Manager, Engine Certification Office, FAA, has the authority to approve alternative methods of compliance for this AD if requested using the procedures found in 14 CFR 39.19. Alternate methods of compliance approved in accordance with AD 97-17-04 are approved as alternate methods of compliance with this AD.

Material Incorporated by Reference

(j) You must use the Pratt & Whitney service information specified in Table 3 of this AD to perform the inspections required by this AD. The Director of the Federal Register previously approved the incorporation by reference of the documents listed in the following Table 3 as of March 5, 1997 (62 FR 4902) in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. Contact Pratt & Whitney, 400 Main St., East Hartford, CT 06108; telephone (860) 565-8770; fax (860) 565-4503, for a copy of this service information. You may review copies at the FAA, New England Region, 12 New England Executive Park, Burlington, MA; or at the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, call 202-741-6030, or go to: http://www.archives.gov/​federal-register/​cfr/​ibr-locations.html.

Table 3—Incorporation by Reference

Service informationPageRevisionDate
Alert Service Bulletin No. A6272AllOriginalSeptember 24, 1996.
Total Pages: 21
Non-Destruct Inspection Procedure No. NDIP-892AllASeptember 15, 1996.
Total Pages: 30
Attachment IAllASeptember 15, 1996.
Total Pages: 4
Start Signature
Start Printed Page 12971

Issued in Burlington, Massachusetts, on March 9, 2010.

Peter A. White,

Assistant Manager, Engine and Propeller Directorate, Aircraft Certification Service.

End Signature End Supplemental Information

[FR Doc. 2010-5778 Filed 3-17-10; 8:45 am]

BILLING CODE 4910-13-P