Document ID: FAA-2009-0883-0001
Agency: faa
Document Type: Rule
Title: Airworthiness Directives: Pratt and Whitney JT8D-209, -217, -217C, and -219 Turbofan Engines
Posted Date: 2009-12-21T05:00Z

[Federal Register: December 21, 2009 (Volume 74, Number 243)]
[Proposed Rules]               
[Page 67831-67834]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr21de09-14]                         

[[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).

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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 http://
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 http://
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 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 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
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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

[[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     ..............  ..............
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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: 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: http://
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
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[[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