75 FR 52 pgs. 12968-12971 - Airworthiness Directives; Pratt & Whitney JT8D-209, -217, -217C, and -219 Turbofan Engines
Type: RULEVolume: 75Number: 52Pages: 12968 - 12971
Docket number: [Docket No. FAA-2009-0883; Directorate Identifier 97-ANE-08; Amendment 39-16237; AD 97-17-04R1]
FR document: [FR Doc. 2010-5778 Filed 3-17-10; 8:45 am]
Agency: Transportation Department
Sub Agency: Federal Aviation Administration
Official PDF Version: PDF Version
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2009-0883; Directorate Identifier 97-ANE-08; Amendment 39-16237; AD 97-17-04R1]
RIN 2120-AA64
Airworthiness Directives; Pratt & Whitney JT8D-209, -217, -217C, and -219 Turbofan Engines
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.
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.
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 .
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety.
Adoption of the Amendment
Accordingly, under the authority delegated to me by the Administrator, the Federal Aviation Administration amends 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 [Amended]
2. The FAA amends § 39.13 by removing Amendment 39-10106 (62 FR 45152, August 26, 1997), and by adding a new airworthiness directive, Amendment 39-16237, to read as follows:
97-17-04R1Pratt & 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.
| Initial inspection | Re-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. |
| OR | OR |
| (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. |
| OR | OR |
| (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. |
| M67663 | M67802 | P66880 | S25545 | P66747 | R33099 | S25292 |
| M67671 | M67812 | P66885 | S25558 | P66756 | R33107 | S25299 |
| M67675 | M67826 | R32732 | S25564 | P66800 | R33113 | S25301 |
| M67681 | M67829 | R32733 | S25598 | P66814 | R33124 | S25302 |
| M67685 | M67830 | R32735 | S25618 | P66819 | R33131 | S25308 |
| M67686 | M67831 | R32740 | S25621 | P66831 | R33132 | S25312 |
| M67687 | M67832 | R32741 | S25637 | R32767 | R33133 | S25316 |
| M67697 | M67834 | R32810 | S25640 | R32787 | R33136 | S25323 |
| M67700 | M67843 | R32849 | T50693 | R32792 | R33152 | S25334 |
| M67706 | M67849 | R32850 | T50752 | R32795 | R33157 | S25335 |
| M67710 | M67858 | S25222 | T50785 | R32796 | R33163 | S25337 |
| M67712 | M67866 | S25464 | T50791 | R32800 | R33165 | S25344 |
| M67713 | M67868 | S25481 | T50792 | R32807 | R33168 | S25369 |
| M67714 | M67869 | S25483 | T50819 | R32856 | R33171 | S25377 |
| M67715 | M67872 | S25484 | T50823 | R32860 | R33173 | S25378 |
| M67716 | M67888 | S25486 | T50827 | R32870 | R33180 | S25381 |
| M67717 | N71771 | S25488 | T50874 | R32883 | R33181 | S25394 |
| M67722 | N71804 | S25489 | T50875 | R32905 | R33189 | S25399 |
| M67723 | N71806 | S25490 | T51058 | R32926 | R33194 | S25402 |
| M67725 | N71810 | S25491 | T51104 | R32930 | R33198 | S25406 |
| M67726 | N71811 | S25492 | R32952 | R33201 | S25411 | |
| M67730 | N71875 | S25494 | R32964 | R33202 | S25413 | |
| M67731 | N71876 | S25495 | R32966 | R33207 | S25414 | |
| M67746 | N71921 | S25497 | R32971 | S25193 | S25415 | |
| M67751 | N71965 | S25498 | R32976 | S25195 | S25418 | |
| M67753 | N72062 | S25499 | R32981 | S25207 | S25419 | |
| M67764 | N72126 | S25500 | R32990 | S25208 | S25421 | |
| M67765 | N72152 | S25501 | R32994 | S25221 | S25422 | |
| M67784 | N72162 | S25502 | R33000 | S25229 | S25430 | |
| M67791 | N72207 | S25505 | R33004 | S25238 | S25437 | |
| M67792 | N72216 | S25506 | R33040 | S25246 | S25439 | |
| M67793 | N72219 | S25507 | R33055 | S25248 | S25449 | |
| M67794 | N72242 | S25508 | R33059 | S25250 | R33186 | |
| M67795 | P66693 | S25509 | R33077 | S25256 | S25528 | |
| M67796 | P66695 | S25514 | R33080 | S25262 | ||
| M67797 | P66696 | S25529 | R33082 | S25268 | ||
| M67798 | P66698 | S25532 | R33086 | S25278 | ||
| M67799 | P66699 | S25541 | R33087 | S25287 | ||
| M67800 | P66737 | S25543 | R33089 | S25288 | ||
| M67801 | P66753 | S25544 | R33090 |
(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.
| Service information | Page | Revision | Date |
|---|---|---|---|
| Alert Service Bulletin No. A6272 | All | Original | September 24, 1996. |
| Total Pages: 21 | |||
| Non-Destruct Inspection Procedure No. NDIP-892 | All | A | September 15, 1996. |
| Total Pages: 30 | |||
| Attachment I | All | A | September 15, 1996. |
| Total Pages: 4 |
Issued in Burlington, Massachusetts, on March 9, 2010.
Peter A. White,
Assistant Manager, Engine and Propeller Directorate, Aircraft Certification Service.
[FR Doc. 2010-5778 Filed 3-17-10; 8:45 am]
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