Airworthiness Directives; Pratt & Whitney JT8D-209, -217, -217C, and -219 Turbofan Engines, 67831-67834 [E9-30221]

Download as PDF Federal Register / Vol. 74, No. 243 / Monday, December 21, 2009 / Proposed Rules DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2009–0883; Directorate Identifier 97–ANE–08] RIN 2120–AA64 Airworthiness Directives; Pratt & Whitney JT8D–209, –217, –217C, and –219 Turbofan Engines erowe on DSK5CLS3C1PROD with PROPOSALS-1 AGENCY: Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). SUMMARY: The FAA proposes to revise 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 proposed AD would require the same actions, except for the monthly reporting of the number of completed inspections. This proposed 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 proposing this AD revision 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: We must receive any comments on this proposed AD by February 19, 2010. ADDRESSES: Use one of the following addresses to comment on this proposed AD. • Federal eRulemaking Portal: Go to https://www.regulations.gov and follow the instructions for sending your comments electronically. • Mail: Docket Management Facility, U.S. Department of Transportation, 1200 New Jersey Avenue, SE., West Building Ground Floor, Room W12–140, Washington, DC 20590–0001. VerDate Nov<24>2008 13:23 Dec 18, 2009 Jkt 220001 • Hand Delivery: Deliver to Mail address above between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. • Fax: (202) 493–2251. 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: alan.strom@faa.gov; telephone (781) 238–7117; fax (781) 238–7199. Contact Pratt & Whitney, 400 Main St., East Hartford, CT 06108; telephone (860) 565–8770; fax (860) 565–4503, for the service information referenced in this proposed AD. SUPPLEMENTARY INFORMATION: Comments Invited We invite you to send any written relevant data, views, or arguments regarding this proposal. Send your comments to an address listed under ADDRESSES. Include ‘‘Docket No. FAA– 2009–0883; Directorate Identifier 97– ANE–08’’ in the subject line of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of the proposed AD. We will consider all comments received by the closing date and may amend the proposed AD in light of those comments. We will post all comments we receive, without change, to https:// www.regulations.gov, including any personal information you provide. We will also post a report summarizing each substantive verbal contact with FAA personnel concerning this proposed AD. Using the search function of the Web site, anyone can find and read the comments in any of our dockets, including, if provided, the name of the individual who sent the comment (or signed the comment on behalf of an association, business, labor union, etc.). You may review the DOT’s complete Privacy Act Statement in the Federal Register published on April 11, 2000 (65 FR 19477–78). Examining the AD Docket You may examine the AD docket on the Internet at https:// 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 proposed AD, the regulatory evaluation, any comments received, and other information. The street address for the Docket Operations office (telephone (800) 647–5527) is the same as the Mail address provided in the ADDRESSES section. Comments will PO 00000 Frm 00003 Fmt 4702 Sfmt 4702 67831 be available in the AD docket shortly after receipt. Discussion The FAA proposes to amend 14 CFR part 39 by revising AD 97–17–04, Amendment 39–10106 (62 FR 45152, August 26, 1997). That AD requires cleaning of front compressor front hubs (fan hubs), initial and repetitive ECI and FPI of tierod and counterweight holes for cracks, removal of bushings, the cleaning and ECI and FPI of bushed holes for cracks, and, if necessary, replacement with serviceable parts. In addition, that AD requires reporting the findings of cracked fan hubs and monthly reporting of the number of inspections performed. Since AD 97–17–04 was issued, we have collected sufficient data on inspections and determined that we do not need further monthly reports of inspections performed. FAA’s Determination and Requirements of the Proposed AD We have evaluated all pertinent information, and we are proposing this AD, which would revise AD 97–17–04 to eliminate the monthly requirement to report the number of completed inspections back to the FAA. All other requirements contained in AD 97–17–04 would still be maintained. Cost of Compliance We estimate that this proposed AD revision would affect 1,170 JT8D–209, –217, –217C, and –219 turbofan engines installed on airplanes of U.S. registry. We estimate that it would 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 proposed 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 E:\FR\FM\21DEP1.SGM 21DEP1 67832 Federal Register / Vol. 74, No. 243 / Monday, December 21, 2009 / Proposed Rules 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 proposed AD would not have federalism implications under Executive Order 13132. This proposed AD would 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 the proposed AD: 1. Is not a ‘‘significant regulatory action’’ under Executive Order 12866; 2. Is not a ‘‘significant rule’’ under the DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979); and 3. Would 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 regulatory evaluation of the estimated costs to comply with this proposed AD. See the ADDRESSES section for a location to examine the regulatory evaluation. List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. The Proposed Amendment Unsafe Condition Under the authority delegated to me by the Administrator, the Federal Aviation Administration proposes to amend 14 CFR part 39 as follows: (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. 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 to read as follows: Pratt & Whitney: Docket No. FAA–2009– 0883; Directorate Identifier 97–ANE–08. Comments Due Date (a) The Federal Aviation Administration (FAA) must receive comments on this airworthiness directive (AD) action by February 19, 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. 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-inservice (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 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. erowe on DSK5CLS3C1PROD with PROPOSALS-1 TABLE 2—HUBS WITH TRAVELER NOTATIONS M67663 M67671 M67675 M67681 M67685 M67686 M67687 M67697 M67700 M67706 M67710 M67712 M67713 M67714 VerDate Nov<24>2008 M67802 M67812 M67826 M67829 M67830 M67831 M67832 M67834 M67843 M67849 M67858 M67866 M67868 M67869 13:23 Dec 18, 2009 Jkt 220001 P66880 P66885 R32732 R32733 R32735 R32740 R32741 R32810 R32849 R32850 S25222 S25464 S25481 S25483 PO 00000 Frm 00004 S25545 S25558 S25564 S25598 S25618 S25621 S25637 S25640 T50693 T50752 T50785 T50791 T50792 T50819 Fmt 4702 Sfmt 4702 P66747 P66756 P66800 P66814 P66819 P66831 R32767 R32787 R32792 R32795 R32796 R32800 R32807 R32856 E:\FR\FM\21DEP1.SGM R33099 R33107 R33113 R33124 R33131 R33132 R33133 R33136 R33152 R33157 R33163 R33165 R33168 R33171 21DEP1 S25292 S25299 S25301 S25302 S25308 S25312 S25316 S25323 S25334 S25335 S25337 S25344 S25369 S25377 67833 Federal Register / Vol. 74, No. 243 / Monday, December 21, 2009 / Proposed Rules TABLE 2—HUBS WITH TRAVELER NOTATIONS—Continued M67715 M67716 M67717 M67722 M67723 M67725 M67726 M67730 M67731 M67746 M67751 M67753 M67764 M67765 M67784 M67791 M67792 M67793 M67794 M67795 M67796 M67797 M67798 M67799 M67800 M67801 M67872 M67888 N71771 N71804 N71806 N71810 N71811 N71875 N71876 N71921 N71965 N72062 N72126 N72152 N72162 N72207 N72216 N72219 N72242 P66693 P66695 P66696 P66698 P66699 P66737 P66753 S25484 S25486 S25488 S25489 S25490 S25491 S25492 S25494 S25495 S25497 S25498 S25499 S25500 S25501 S25502 S25505 S25506 S25507 S25508 S25509 S25514 S25529 S25532 S25541 S25543 S25544 (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. T50823 T50827 T50874 T50875 T51058 T51104 .............................. .............................. .............................. .............................. .............................. .............................. .............................. .............................. .............................. .............................. .............................. .............................. .............................. .............................. .............................. .............................. .............................. .............................. .............................. .............................. R32860 R32870 R32883 R32905 R32926 R32930 R32952 R32964 R32966 R32971 R32976 R32981 R32990 R32994 R33000 R33004 R33040 R33055 R33059 R33077 R33080 R33082 R33086 R33087 R33089 R33090 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. R33173 R33180 R33181 R33189 R33194 R33198 R33201 R33202 R33207 S25193 S25195 S25207 S25208 S25221 S25229 S25238 S25246 S25248 S25250 S25256 S25262 S25268 S25278 S25287 S25288 .............................. S25378 S25381 S25394 S25399 S25402 S25406 S25411 S25413 S25414 S25415 S25418 S25419 S25421 S25422 S25430 S25437 S25439 S25449 R33186 S25528 .............................. .............................. .............................. .............................. .............................. .............................. 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: https:// www.archives.gov/federal-register/cfr/ibrlocations.html. TABLE 3—INCORPORATION BY REFERENCE Page Revision Date Alert Service Bulletin No. A6272 ............................................................. Total Pages: 21 Non-Destruct Inspection Procedure No. NDIP–892 ................................ Total Pages: 30 Attachment I Total Pages: 4 erowe on DSK5CLS3C1PROD with PROPOSALS-1 Service information All .............................. Original ...................... September 24, 1996. All .............................. A ................................ September 15, 1996. All .............................. A ................................ September 15, 1996. VerDate Nov<24>2008 13:23 Dec 18, 2009 Jkt 220001 PO 00000 Frm 00005 Fmt 4702 Sfmt 4702 E:\FR\FM\21DEP1.SGM 21DEP1 67834 Federal Register / Vol. 74, No. 243 / Monday, December 21, 2009 / Proposed Rules Issued in Burlington, Massachusetts, on December 10, 2009. Peter A. White, Assistant Manager, Engine and Propeller Directorate, Aircraft Certification Service. [FR Doc. E9–30221 Filed 12–18–09; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2008–1353; Directorate Identifier 2008–NE–46–AD] RIN 2120–AA64 Airworthiness Directives; CFM International, S.A. CFM56–5B1/P, –5B2/ P, –5B3/P, –5B3/P1, –5B4/P, –5B5/P, –5B6/P, –5B7/P, –5B8/P, –5B9/P, –5B1/ 2P, –5B2/2P, –5B3/2P, –5B3/2P1, –5B4/ 2P, –5B4/P1, –5B6/2P, –5B4/2P1, and –5B9/2P Turbofan Engines Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). erowe on DSK5CLS3C1PROD with PROPOSALS-1 AGENCY: SUMMARY: The FAA proposes to supersede an existing airworthiness directive (AD) for CFM International, S.A. CFM56–5B series turbofan engines. That AD currently requires reviewing exhaust gas temperature (EGT) monitoring records to determine EGT margin deterioration, and for airplanes where both engines have greater than 80 °centigrade (C) of EGT margin deterioration, borescope-inspecting the high-pressure compressor (HPC) of both engines. That AD also currently requires removing from service any engine that does not pass the borescope inspection and, if both engines pass, removing and replacing one of the engines with an engine that has 80 °C or less of EGT margin deterioration. That AD also currently requires continuous monitoring of EGT margin deterioration on engines in service to prevent two engines on an airplane from having greater than 80 °C of EGT margin deterioration. This proposed AD would require continuous monitoring of EGT margin deterioration, removing FADEC software version 5.B.Q and earlier versions from the engine as mandatory terminating action to the repetitive recalculating and EGT monitoring for certain engine models, and removing other certain engine models from service if the EGT margin deterioration is greater than 75 °C. This proposed AD results from the need to reduce the affected engine models listed in AD VerDate Nov<24>2008 13:23 Dec 18, 2009 Jkt 220001 2009–01–01 from 25 to 19, the need to reduce the engine EGT margin deterioration removal threshold from greater than 80 °C to greater than 75 °C, the need to mandate a terminating action to the repetitive recalculating and EGT monitoring for certain engines, and the need to remove certain engines from service if the EGT margin deterioration is greater than 75 °C. We are proposing this AD to prevent HPC stalls, which could prevent continued safe flight or landing. DATES: We must receive any comments on this proposed AD by February 19, 2010. ADDRESSES: Use one of the following addresses to comment on this proposed AD. • Federal eRulemaking Portal: Go to https://www.regulations.gov and follow the instructions for sending your comments electronically. • Mail: Docket Management Facility, U.S. Department of Transportation, 1200 New Jersey Avenue, SE., West Building Ground Floor, Room W12–140, Washington, DC 20590–0001. • Hand Delivery: Deliver to Mail address above between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. • Fax: (202) 493–2251. FOR FURTHER INFORMATION CONTACT: James Rosa, Aerospace Engineer, Engine Certification Office, FAA, Engine and Propeller Directorate, 12 New England Executive Park, Burlington, MA 01803; e-mail: james.rosa@faa.gov; telephone (781) 238–7152; fax (781) 238–7199. SUPPLEMENTARY INFORMATION: Comments Invited We invite you to send any written relevant data, views, or arguments regarding this proposal. Send your comments to an address listed under ADDRESSES. Include ‘‘Docket No. FAA– 2008–1353; Directorate Identifier 2008– NE–46–AD’’ in the subject line of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of the proposed AD. We will consider all comments received by the closing date and may amend the proposed AD in light of those comments. We will post all comments we receive, without change, to https:// www.regulations.gov, including any personal information you provide. We will also post a report summarizing each substantive verbal contact with FAA personnel concerning this proposed AD. Using the search function of the Web site, anyone can find and read the comments in any of our dockets, PO 00000 Frm 00006 Fmt 4702 Sfmt 4702 including, if provided, the name of the individual who sent the comment (or signed the comment on behalf of an association, business, labor union, etc.). You may review the DOT’s complete Privacy Act Statement in the Federal Register published on April 11, 2000 (65 FR 19477–78). Examining the AD Docket You may examine the AD docket on the Internet at https:// 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 proposed AD, the regulatory evaluation, any comments received, and other information. The street address for the Docket Operations office (telephone (800) 647–5527) is the same as the Mail address provided in the ADDRESSES section. Comments will be available in the AD docket shortly after receipt. Discussion The FAA proposes to amend 14 CFR part 39 by superseding AD 2009–01–01, Amendment 39–15779 (73 FR 80296, December 31, 2008). That AD requires reviewing EGT monitoring records to determine EGT margin deterioration, and, for airplanes where both engines have greater than 80 °C of EGT margin deterioration, borescope-inspecting the HPC of both engines. That AD also currently requires removing from service any engine that does not pass the borescope inspection, and if both engines pass, removing and replacing one of the engines with an engine that has 80 °C or less EGT margin deterioration. That AD also currently requires continuous monitoring of EGT margin deterioration on engines in service, to prevent two engines on an airplane from having greater than 80 °C of EGT margin deterioration. That AD was the result of an Airbus A321 airplane powered by CFM56–5B1/P turbofan engines with severe HPC deterioration, that stalled during climb out after takeoff. That condition, if not corrected, could result in HPC stalls, which could prevent continued safe flight or landing. Actions Since AD 2009–01–01 Was Issued Since AD 2009–01–01 was issued, we determined that engine models CFM56– 5B1, –5B2, –5B4, –5B5, –5B6, and –5B7, which were listed in that AD, are not affected by the unsafe condition. Also, CFM International, S.A. has released a FADEC software version that addresses the HPC stall problem for certain engine models. We also determined that we E:\FR\FM\21DEP1.SGM 21DEP1

Agencies

[Federal Register Volume 74, Number 243 (Monday, December 21, 2009)]
[Proposed Rules]
[Pages 67831-67834]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E9-30221]

[[Page 67831]]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2009-0883; Directorate Identifier 97-ANE-08]
RIN 2120-AA64

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

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

-----------------------------------------------------------------------

SUMMARY: The FAA proposes to revise 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 proposed AD would require the same actions,
except for the monthly reporting of the number of completed
inspections. This proposed 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 proposing this AD revision 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: We must receive any comments on this proposed AD by February 19,
2010.

ADDRESSES: Use one of the following addresses to comment on this
proposed AD.
Federal eRulemaking Portal: Go to https://www.regulations.gov and follow the instructions for sending your
comments electronically.
Mail: Docket Management Facility, U.S. Department of
Transportation, 1200 New Jersey Avenue, SE., West Building Ground
Floor, Room W12-140, Washington, DC 20590-0001.
Hand Delivery: Deliver to Mail address above between 9
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
Fax: (202) 493-2251.

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:
alan.strom@faa.gov; telephone (781) 238-7117; fax (781) 238-7199.
Contact Pratt & Whitney, 400 Main St., East Hartford, CT 06108;
telephone (860) 565-8770; fax (860) 565-4503, for the service
information referenced in this proposed AD.

SUPPLEMENTARY INFORMATION:

Comments Invited

We invite you to send any written relevant data, views, or
arguments regarding this proposal. Send your comments to an address
listed under ADDRESSES. Include ``Docket No. FAA-2009-0883; Directorate
Identifier 97-ANE-08'' in the subject line of your comments. We
specifically invite comments on the overall regulatory, economic,
environmental, and energy aspects of the proposed AD. We will consider
all comments received by the closing date and may amend the proposed AD
in light of those comments.
We will post all comments we receive, without change, to https://www.regulations.gov, including any personal information you provide. We
will also post a report summarizing each substantive verbal contact
with FAA personnel concerning this proposed AD. Using the search
function of the Web site, anyone can find and read the comments in any
of our dockets, including, if provided, the name of the individual who
sent the comment (or signed the comment on behalf of an association,
business, labor union, etc.). You may review the DOT's complete Privacy
Act Statement in the Federal Register published on April 11, 2000 (65
FR 19477-78).

Examining the AD Docket

You may examine the AD docket on the Internet at https://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 proposed AD, the regulatory
evaluation, any comments received, and other information. The street
address for the Docket Operations office (telephone (800) 647-5527) is
the same as the Mail address provided in the ADDRESSES section.
Comments will be available in the AD docket shortly after receipt.

Discussion

The FAA proposes to amend 14 CFR part 39 by revising AD 97-17-04,
Amendment 39-10106 (62 FR 45152, August 26, 1997). That AD requires
cleaning of front compressor front hubs (fan hubs), initial and
repetitive ECI and FPI of tierod and counterweight holes for cracks,
removal of bushings, the cleaning and ECI and FPI of bushed holes for
cracks, and, if necessary, replacement with serviceable parts. In
addition, that AD requires reporting the findings of cracked fan hubs
and monthly reporting of the number of inspections performed.
Since AD 97-17-04 was issued, we have collected sufficient data on
inspections and determined that we do not need further monthly reports
of inspections performed.

FAA's Determination and Requirements of the Proposed AD

We have evaluated all pertinent information, and we are proposing
this AD, which would revise AD 97-17-04 to eliminate the monthly
requirement to report the number of completed inspections back to the
FAA. All other requirements contained in AD 97-17-04 would still be
maintained.

Cost of Compliance

We estimate that this proposed AD revision would affect 1,170 JT8D-
209, -217, -217C, and -219 turbofan engines installed on airplanes of
U.S. registry. We estimate that it would 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 proposed 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

[[Page 67832]]

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 proposed AD would not have federalism
implications under Executive Order 13132. This proposed AD would 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 the proposed AD:
1. Is not a ``significant regulatory action'' under Executive Order
12866;
2. Is not a ``significant rule'' under the DOT Regulatory Policies
and Procedures (44 FR 11034, February 26, 1979); and
3. Would 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 regulatory evaluation of the estimated costs to
comply with this proposed AD. See the ADDRESSES section for a location
to examine the regulatory evaluation.

List of Subjects in 14 CFR Part 39

Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.

The Proposed Amendment

Under the authority delegated to me by the Administrator, the
Federal Aviation Administration proposes to amend 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. The FAA amends Sec. 39.13 by removing Amendment 39-10106 (62 FR
45152, August 26, 1997) and by adding a new airworthiness directive to
read as follows:

Pratt & Whitney: Docket No. FAA-2009-0883; Directorate Identifier
97-ANE-08.

Comments Due Date

(a) The Federal Aviation Administration (FAA) must receive
comments on this airworthiness directive (AD) action by February 19,
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 inspection Re-inspection
------------------------------------------------------------------------
(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;

OR OR

(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;

OR OR

(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.
------------------------------------------------------------------------

Table 2--Hubs With Traveler Notations
----------------------------------------------------------------------------------------------------------------

----------------------------------------------------------------------------------------------------------------
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

[[Page 67833]]

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.

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: https://www.archives.gov/federal-register/cfr/ibr-locations.html.

Table 3--Incorporation by Reference
----------------------------------------------------------------------------------------------------------------
Service information Page Revision Date
----------------------------------------------------------------------------------------------------------------
Alert Service Bulletin No. All....................... Original.................. September 24, 1996.
A6272.
Total Pages: 21
Non-Destruct Inspection All....................... A......................... September 15, 1996.
Procedure No. NDIP-892.
Total Pages: 30
Attachment I All....................... A......................... September 15, 1996.
Total Pages: 4
----------------------------------------------------------------------------------------------------------------

[[Page 67834]]

Issued in Burlington, Massachusetts, on December 10, 2009.
Peter A. White,
Assistant Manager, Engine and Propeller Directorate, Aircraft
Certification Service.

[FR Doc. E9-30221 Filed 12-18-09; 8:45 am]
BILLING CODE 4910-13-P

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