[Federal Register Volume 62, Number 165 (Tuesday, August 26, 1997)]
[Rules and Regulations]
[Pages 45152-45155]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 97-22307]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 97-ANE-08; Amendment 39-10106; AD 97-17-04]
RIN 2120-AA64


Airworthiness Directives; Pratt & Whitney JT8D-200 Series 
Turbofan Engines

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule.

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SUMMARY: This amendment supersedes an existing airworthiness directive 
(AD), applicable to Pratt & Whitney JT8D-200 series turbofan engines, 
that currently requires cleaning of 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; the cleaning and ECI and FPI of bushed 
holes for cracks; and, if necessary, replacement with serviceable 
parts. In addition, the current AD requires reporting the findings of 
cracked fan hubs. This amendment does not change the current AD's 
inspection procedures, or the effectivity date that starts the cycle 
count for the initial inspection schedules. This AD does, however, add 
an additional inspection schedule that requires the initial inspection 
of certain fan hubs with standard drilled holes and coolant channel 
drilled (CCD) holes to occur earlier than the existing AD requires. 
Also, this AD requires reporting the results of the initial fan hub 
inspections. This amendment is prompted by additional investigation 
since publication of the current AD that reveals that certain fan hubs 
with standard drilled holes and CCD holes may be more susceptible to 
cracking. The actions specified by this AD are intended 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 
aircraft.

DATES: Effective September 30, 1997.
    The incorporation by reference of certain publications listed in 
the regulations was previously approved by the Director of the Federal 
Register as of March 5, 1997 62 FR 4902, February 3, 1997).

ADDRESSES: The service information referenced in this AD may be 
obtained from Pratt & Whitney, 400 Main St., East Hartford, CT 06108; 
telephone (860) 565-6600, fax (860) 565-4503. This information may be 
examined at the Federal Aviation Administration (FAA), New England 
Region, Office of the Assistant Chief Counsel, 12 New England Executive 
Park, Burlington, MA 01803-5299; or at the Office of the Federal 
Register, 800 North Capitol Street, NW., suite 700, Washington, DC.

FOR FURTHER INFORMATION CONTACT: Christopher Spinney, Aerospace 
Engineer, Engine Certification Office, FAA, Engine and Propeller 
Directorate, 12 New England Executive Park, Burlington, MA 01803-5299; 
telephone (617) 238-7175, fax (617) 238-7199.

SUPPLEMENTARY INFORMATION: A proposal to amend part 39 of the Federal 
Aviation Regulations (14 CFR part 39) by superseding AD 97-02-11, 
Amendment 39-9896 (62 FR 4902, February 3, 1997), applicable to Pratt & 
Whitney (PW) JT8D-200 series turbofan engines, was published in the 
Federal Register on February 24, 1997 (62 FR 8198), and a correction to 
a printing error in a table was published on March 31, 1997 (62 FR 
15225). That action proposed to require cleaning, initial and 
repetitive eddy current inspections (ECI) and fluorescent penetrant 
inspections (FPI) for cracks of tierod and counterweight holes; removal 
of bushings; the cleaning and initial and repetitive ECI and FPI of 
bushed holes for cracks; and, if necessary, replacing with serviceable 
parts.
    Interested persons have been afforded an opportunity to participate 
in the making of this amendment. Due consideration has been given to 
the comments received.
    Three commenters state that the March 5, 1997, date to begin 
counting cycles is objectionable, as a retroactive date is 
unenforceable. The FAA concurs in part. The March 5, 1997, date is 
supported by a safety risk analysis, but basing the cyclic count on 
this date

[[Page 45153]]

would require immediate removal of parts not in compliance at the 
effective date of this AD. However, the FAA has reviewed a new risk 
analysis that uses the effective date of this AD to begin the cyclic 
count for fan hubs added to Table 2 of this AD. This final rule has 
been revised by changing the compliance time to ``315 cycles from the 
effective date of this AD''. This new date should prevent any fan hubs 
from being out of compliance at the date of final rule publication. It 
does not, however, extend the compliance time for those fan hubs that 
were previously included in AD 97-02-11 and are now listed in Table 2 
of this AD. Fan hubs previously included in AD 97-02-11 must perform 
initial inspections to the more conservative compliance times.
    One group of commenters object to the monthly reporting 
requirements required in the proposed rule, as these requirements are 
burdensome and do not contribute to safety. The FAA does not concur. 
The reports received from these inspections are used to validate the 
assumptions used in the safety risk analysis and are critical to the 
safety assessment of the inspection program.
    One commenter states that alternative methods of compliance (AMOCs) 
approved in the current AD should be included in this superseded AD. 
The FAA concurs and has added a statement to this final rule that 
approves AMOCs from AD 97-02-11 as acceptable for this AD.
    After careful review of the available data, including the comments 
noted above, the FAA has determined that air safety and the public 
interest require the adoption of the rule with the changes described 
previously. The FAA has determined that these changes will neither 
increase the economic burden on any operator nor increase the scope of 
the AD.
    There are approximately 2,624 engines of the affected design in the 
worldwide fleet. The FAA estimates that 1,279 engines installed on 
aircraft of U.S. registry will be affected by this AD, that it will 
take 20 work hours per engine for 360 engines to disassemble, remove, 
inspect, and reassemble engines, and 4 work hours per engine for 919 
engines to inspect at piece-part exposure, and that the average labor 
rate is $60 per work hour. Based on these figures, the total cost 
impact of the AD on U.S. operators is estimated to be $862,560.
    The regulations adopted herein will not have substantial direct 
effects 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. Therefore, in 
accordance with Executive Order 12612, it is determined that this final 
rule does not have sufficient federalism implications to warrant the 
preparation of a Federalism Assessment.
    For the reasons discussed above, I certify that this action (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. A final evaluation has been prepared for this action 
and it is contained in the Rules Docket. A copy of it may be obtained 
from the Rules Docket at the location provided under the caption 
ADDRESSES.

List of Subjects in 14 CFR Part 39

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

Adoption of the Amendment

    Accordingly, pursuant to the authority delegated to me by the 
Administrator, the Federal Aviation Administration amends part 39 of 
the Federal Aviation Regulations (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. Section 39.13 is amended by removing amendment 39-9896 (62 FR 
4902, February 3, 1997) and by adding a new airworthiness directive to 
read as follows:

97-17-04  Pratt & Whitney: Amendment 39-10106. Docket 97-ANE-08. 
Supersedes AD 97-02-11, Amendment 39-9896.

    Applicability: Pratt & Whitney JT8D-209, -217, -217C, and -219 
series 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 aircraft.

    Note 1: This airworthiness directive (AD) applies to each engine 
identified in the preceding applicability provision, regardless of 
whether it has been modified, altered, or repaired in the area 
subject to the requirements of this AD. For engines that have been 
modified, altered, or repaired so that the performance of the 
requirements of this AD is affected, the owner/operator must request 
approval for an alternative method of compliance in accordance with 
paragraph (c) of this AD. The request should include an assessment 
of the effect of the modification, alteration, or repair on the 
unsafe condition addressed by this AD; and, if the unsafe condition 
has not been eliminated, the request should include specific 
proposed actions to address it.
    Compliance: Required as indicated, unless accomplished 
previously.
    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 aircraft, accomplish the following:
    (a) Inspect fan hubs for cracks in accordance with the 
Accomplishment Instructions, Paragraph A, Part 1, and, if 
applicable, Paragraph B, of PW 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, reinspect 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                                
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           Initial inspection                      Reinspection         
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1. Within 1,050 cycles in service (CIS)  After accumulating 2,500 CIS   
 after the effective date of AD 97-02-    since last inspection, but not
 11, March 5, 1997, or prior to           to exceed 6,000 CIS since last
 accumulating 5,050 CSN, whichever        inspection.                   
 occurs later;                                                          
                                   OR                                   
2. Within 990 CIS after the effective    After accumulating 2,500 CIS   
 date of AD 97-02-11, March 5, 1997, or   since last inspection, but not
 prior to accumulating 4,990 CSN,         to exceed 8,000 CIS since last
 whichever occurs later;                  inspection.                   

[[Page 45154]]

                                                                        
                                   OR                                   
3. Within 965 CIS after the effective    After accumulating 2,500 CIS   
 date of AD 97-02-11, March 5, 1997, or   since last inspection, but not
 prior to accumulating 4,965 CSN,         to exceed 10,000 CIS since    
 whichever occurs later.                  last inspection.              
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                                     Table 2.--Hubs With Traveler Notations                                     
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    Non CCD          Non CCD          Non CCD         Non CCD         CCD Hub         CCD Hub         CCD Hub   
----------------------------------------------------------------------------------------------------------------
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, reinspect 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 (a)(1) or (a)(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.
    (b) Report the number of completed inspections on a monthly 
basis and report findings of cracked fan hubs in accordance with 
Accomplishment Instructions, Paragraph F, of Attachment 1 to PW ASB 
No. A6272, dated September 24, 1996, within 48 hours after 
inspection to Robert Guyotte, Manager, Engine Certification Branch, 
Engine Certification Office, FAA, Engine and Propeller Directorate, 
12 New England Executive Park, Burlington, MA 01803-5299; telephone 
(617) 238-7142, fax (617) 238-7199; Internet: 
Robert.G[email protected]. Reporting requirements have been 
approved by the Office of Management and Budget and assigned OMB 
control number 2120-0056.
    (c) An alternative method of compliance or adjustment of the 
compliance time that provides an acceptable level of safety may be 
used if approved by the Manager, Engine Certification Office. 
Operators shall forward their requests through an appropriate FAA 
Principal Maintenance Inspector, who may add comments and then send 
it to the Manager, Engine Certification Office. Alternative methods 
of compliance approved for AD 97-02-11 are also considered approved 
for this AD.

    Note 2: Information concerning the existence of approved 
alternative methods of compliance with this AD, if any, may be 
obtained from the Engine Certification Office.

    (d) Special flight permits may be issued in accordance with 
sections 21.197 and 21.199 of the Federal Aviation Regulations (14 
CFR 21.197 and 21.199) to operate the aircraft to a location where 
the requirements of this AD can be accomplished.

[[Page 45155]]

    (e) The actions required by this AD shall be done in accordance 
with the following PW ASB:

------------------------------------------------------------------------
          Document No.                   Pages               Date       
------------------------------------------------------------------------
A6272...........................  1-21  Original....  September 24,     
                                                       1996.            
NDIP-892........................  1-30  A...........  September 15,     
                                                       1996.            
Attachment I....................  AI-1-AI-4 A.......  September 15,     
                                                       1996.            
------------------------------------------------------------------------

    Total Pages: 55.

    This incorporation by reference was previously approved by the 
Director of the Federal Register in accordance with 5 U.S.C. 552(a) 
and 1 CFR part 51 as of March 5, 1997 (62 FR 4902, February 3, 
1997). Copies may be obtained from Pratt & Whitney, 400 Main St., 
East Hartford, CT 06108; telephone (860) 565-6600, fax (860) 565-
4503. Copies may be inspected at the FAA, New England Region, Office 
of the Assistant Chief Counsel, 12 New England Executive Park, 
Burlington, MA; or at the Office of the Federal Register, 800 North 
Capitol Street, NW., suite 700, Washington, DC.
    (f) This amendment becomes effective on September 30, 1997.

    Issued in Burlington, Massachusetts, on August 12, 1997.
Jay J. Pardee,
Manager, Engine and Propeller Directorate, Aircraft Certification 
Service.
[FR Doc. 97-22307 Filed 8-25-97; 8:45 am]
BILLING CODE 4910-13-P