[Federal Register Volume 75, Number 52 (Thursday, March 18, 2010)]
[Rules and Regulations]
[Pages 12968-12971]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2010-5778]
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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.
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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:
[email protected]; 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.
[[Page 12969]]
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.
Adoption of the Amendment
0
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
0
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]
0
2. The FAA amends Sec. 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:
97-17-04R1 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
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Initial inspection Re-inspection
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(A) Within 1,050 CIS after the After accumulating 2,500 CIS since-
effective date of AD 97-02-11, last-inspection, but not to exceed
March 5, 1997, or prior to 6,000 CIS since-last-inspection.
accumulating 5,050 CSN, whichever
occurs later;
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OR OR
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(B) Within 990 CIS after the After accumulating 2,500 CIS since-
effective date of AD 97-02-11, last-inspection, but not to exceed
March 5, 1997, or prior to 8,000 CIS since-last-inspection.
accumulating 4,990 CSN, whichever
occurs later;
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OR OR
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(C) Within 965 CIS after the After accumulating 2,500 CIS since-
effective date of AD 97-02-11, last-inspection, but not to exceed
March 5, 1997, or prior to 10,000 CIS since-last-inspection.
accumulating 4,965 CSN, whichever
occurs later.
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Table 2--Hubs With Traveler Notations
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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
[[Page 12970]]
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 .............. ..............
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(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: [email protected].
(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
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Service information Page Revision Date
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Alert Service Bulletin No. A6272.. All.................. Original............. September 24, 1996.
Total Pages: 21
Non-Destruct Inspection Procedure All.................. A.................... September 15, 1996.
No. NDIP-892.
Total Pages: 30
Attachment I...................... All.................. A.................... September 15, 1996.
Total Pages: 4
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[[Page 12971]]
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]
BILLING CODE 4910-13-P