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

[Federal Register Volume 70, Number 17 (Thursday, January 27, 2005)]
[Rules and Regulations]
[Pages 3867-3871]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 05-1463]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 98-ANE-80-AD; Amendment 39-13948; AD 2005-02-03]
RIN 2120-AA64


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

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule.

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

SUMMARY: The FAA is superseding an existing airworthiness directive 
(AD) for Pratt & Whitney (PW) JT8D-209, -217, -217A, -217C, and -219 
series turbofan engines. That AD currently requires torque inspection 
of the 3rd stage and 4th stage low pressure turbine (LPT) blades for 
shroud notch wear and replacement of the blade if wear limits are 
exceeded. This AD continues to require those torque inspections at 
shorter inspection intervals of the refurbished 3rd stage and 4th stage 
LPT blades, but the same or longer inspection intervals of the new 3rd 
stage and 4th stage LPT blades, for shroud notch wear and replacement 
of the blade if wear limits are exceeded. This AD also requires 
replacing LPT-to-exhaust case bolts and nuts with bolts and nuts made 
of Tinidur material. This AD results from reports of 194 blade 
fractures since 1991, with 37 of those blade fractures resulting in LPT 
case separation, and three reports of uncontained 3rd stage and 4th 
stage LPT blade failures with cowl penetration. We are issuing this AD 
to prevent an uncontained blade failure that could result in damage to 
the airplane.

DATES: This AD becomes effective March 3, 2005. The Director of the 
Federal Register approved the incorporation by reference of certain 
publications listed in the regulations as of March 3, 2005.

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.
    You may examine the AD docket at the FAA, New England Region, 
Office of the Regional Counsel, 12 New England Executive Park, 
Burlington, MA. You may examine the service information, at the FAA, 
New England Region, Office of the Regional Counsel, 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/code_of_federal_regulations/ibr_locations.html.

FOR FURTHER INFORMATION CONTACT: Keith Lardie, Aerospace Engineer, 
Engine Certification Office, FAA, Engine and Propeller Directorate, 12 
New England Executive Park, Burlington, MA 01803-5299; telephone (781) 
238-7189, fax (781) 238-7199.

SUPPLEMENTARY INFORMATION: The FAA proposed to amend 14 CFR part 39 
with a proposed airworthiness directive (AD). The proposed AD applies 
to Pratt & Whitney (PW) JT8D-209, -217, -217A, -217C, and -219 series 
turbofan engines. We published the proposed AD in the Federal Register 
on August 16, 2004 (69 FR 50346). That action proposed to require 
torque inspections of the 3rd stage and 4th stage LPT blades for shroud 
notch wear and replacement of the blade if wear limits are exceeded. 
That action also proposed to require replacing the LPT-to-exhaust case 
bolts and nuts with bolts and nuts made of Tinidur material.

Examining the AD Docket

    You may examine the AD Docket (including any comments and service 
information), by appointment, between 8 a.m. and 4:30 p.m., Monday 
through Friday, except Federal holidays. See ADDRESSES for the 
location.

Comments

    We provided the public the opportunity to participate in the 
development of this AD. We have considered the comments received.

Use of Radioisotope Inspection Procedure

    One commenter proposes to use a radioisotope inspection procedure, 
which they have developed and was approved as an alternative method of 
compliance (AMOC) for a previously issued AD. The commenter states that 
this inspection method is more reliable than the torque inspections 
mandated in this AD and provides an equivalent level of safety. The FAA 
does not agree. The commenter did not provide data to substantiate the 
claim of an equivalent level of safety as it relates to the revised 
inspection intervals. The commenter's proposal is also operator-
specific and does not provide literature for the rest of the fleet. The 
FAA will evaluate a request for an AMOC that includes data 
substantiating that an acceptable level of safety is maintained using 
this procedure.

Costs of Compliance Underestimated

    Another commenter states that the costs of compliance are 
underestimated. The commenter requests that we consider the costs of 
numerous parts removed when complying with this AD. The FAA does not 
agree. The indirect costs associated with this AD are not directly 
related to the required actions, and therefore, are not addressed in 
the economic analysis for this AD. A finding that an AD is warranted 
means that the original engine design no longer achieves the level of 
safety specified by related airworthiness requirements and that other 
required actions are necessary.
    Another commenter states that the costs of compliance are 
underestimated. The commenter states that the cost of turbine blades 
and cost of labor to replace the blades when complying with this AD 
should be considered. The FAA agrees. We estimate that 10% of the blade 
sets will fail the inspection per year and will require replacement. 
Therefore, the estimated cost of turbine blades and labor to replace 
the blades is added to the total cost of the AD to U.S. operators to 
perform initial torque inspection and bolt and nut replacement.

Request To Clearly Identify the Superseded AD

    Another commenter requests that the identification of the 
superseded AD be clarified. The FAA does not agree. The fact that this 
AD supersedes AD 99-27-01 is clearly stated in the compliance section 
of this AD. Although AD 99-22-14 requires replacement of the LPT-to-
exhaust case bolts and nuts, that AD primarily addresses installation 
of high pressure turbine (HPT) containment hardware. Further, a notice 
of proposed rulemaking was published in the Federal Register on July 
15, 2004 (69 FR 42356), which moves the requirement to replace the LPT-
to-exhaust case bolts and nuts from AD 99-22-14 to this AD.

Request To Include Reference to NDIP-662, Revision D

    Another commenter requests that this AD include a reference to 
NDIP-622, Revision D. The FAA does not agree. We assume that the 
commenter intended to

[[Page 3868]]

say NDIP-662, Revision D and not NDIP-622, Revision D. This AD already 
references PW ASB No. JT8D A6224, Revision 5, which specifies the use 
of NDIP-662, which is included as an Appendix in the ASB. Because all 
pages of NDIP-662, Revision D, are included in the ASB, a clarification 
to the reference and a change to this AD are not necessary.

Request To Define ``Accessibility to the LPT-to-Exhaust Case Bolts''

    Another commenter requests that this AD include a definition of the 
statement ``accessibility to the LPT-to-exhaust case bolts'' and that 
the definition match the one provided in PW SB 6455. The FAA agrees. A 
definition of ``accessibility to the LPT-to-exhaust case bolts'' is 
included in this AD.

Overlap Between Inspection Torque Readings

    Another commenter states that there is an overlap between the 
inspection torque readings in the tables providing the repetitive 
torque inspection intervals. For example, one range in Table 3 states 
``* * * but greater than or equal to 10 LB-IN (1.130 N.m).'' Another 
range in Table 3 states ``Less than or equal to 10 LB-IN (1.130 N.m) * 
* *''. A single value cannot have two different requirements. The FAA 
agrees. The affected tables are corrected in this AD.

Inspect Only Turbine Blades That Fail Inspection

    Another commenter proposes to inspect only the turbine blades of 
the LPT stage that fails the torque check inspection. Also, the 
commenter proposes that the requirement to inspect the turbine blades 
of the other LPT stages should be suggested rather than mandated as 
proposed in the AD. The FAA agrees. This AD clarifies the information 
about how to return an engine to service. In addition, this AD 
clarifies the information about how the repetitive inspection intervals 
may be reset.

Conclusion

    We have carefully reviewed the available data, including the 
comments received, and determined that air safety and the public 
interest require adopting the AD with the changes described previously. 
We have determined that these changes will neither increase the 
economic burden on any operator nor increase the scope of the AD.

Costs of Compliance

    There are about 2,345 PW JT8D-200 series turbofan engines of the 
affected design in the worldwide fleet. We estimate that 1,143 engines 
installed on airplanes of U.S. registry are affected by this AD. We 
also estimate that it will take about 1 work hour per engine to perform 
the torque inspection and 1 work hour per engine to perform the bolt 
and nut replacements. The average labor rate is $65 per work hour. It 
is estimated that 10% of the blade sets will fail the inspection per 
year and will require replacement. The average cost for a new blade set 
is $72,500. The new blades take about 23 work hours to install. Based 
on these figures, the annual replacement cost of the AD to U.S. 
operators is $8,584,020. The required bolts and nuts will cost about 
$1,734 per engine. Based on these figures, we estimate the total annual 
cost of this AD to U.S. operators to perform initial torque inspection 
and bolt and nut replacement to be $10,565,982.

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 by 
sending a request to us at the address listed under ADDRESSES. Include 
``AD Docket No. 98-ANE-80-AD'' in your request.

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 39-11482 (64 FR 
72916, December 29, 1999) and by adding a new airworthiness directive, 
Amendment 39-13948, to read as follows:

2005-02-03 Pratt & Whitney: Amendment 39-13948. Docket No. 98-ANE-
80-AD. Supersedes AD 99-27-01, Amendment 39-11482.

Effective Date

    (a) This AD becomes effective March 3, 2005.

Affected ADs

    (b) This AD supersedes AD 99-27-01.

Applicability

    (c) This AD applies to Pratt & Whitney (PW) JT8D-209, -217, -
217A, -217C, and -219 series turbofan engines. These engines are 
installed on, but not limited to, Boeing 727 series and McDonnell 
Douglas MD-80 series airplanes.

Unsafe Condition

    (d) This AD results from reports of 194 blade fractures since 
1991, with 37 of those blade fractures resulting in low pressure 
turbine (LPT) case separation, and three reports of uncontained 3rd 
stage and 4th stage LPT blade failures with cowl penetration. We are 
issuing this AD to prevent an uncontained blade failure that could 
result in 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.

[[Page 3869]]

Initial Torque Inspection for JT8D-209, -217, and -217A Engines

    (f) For JT8D-209, -217, and -217A engines, perform the initial 
torque inspection of 3rd and 4th stage LPT blades for shroud notch 
wear. Use the procedures described in Accomplishment Instructions, 
part 1, paragraphs 1. through 3. of PW Alert Service Bulletin (ASB) 
No. JT8D A6224, Revision 5, dated June 11, 2004, at the applicable 
threshold in the following Table 1:

               Table 1.--Initial Torque Inspection Threshold for JT8D-209, -217, and -217A Engines
----------------------------------------------------------------------------------------------------------------
              Blade type                       Hours time-in-service  (TIS)             Inspection threshold
----------------------------------------------------------------------------------------------------------------
(1) New pre-Service Bulletin (SB) No.  Any number.................................  Within 6,000 hours TIS.
 5867 (small notch) 3rd stage turbine
 blades.
(2) Refurbished pre-SB No. 5867        (i) Fewer than 3,000.......................  Within 4,000 hours TIS.
 (small notch) 3rd stage turbine
 blades.
                                       (ii) 3,000 or more.........................  Within 6,000 hours TIS, or
                                                                                     within 1,000 hours TIS
                                                                                     after the effective date of
                                                                                     this AD, whichever occurs
                                                                                     first.
(3) New post-SB No. 5867 (large        Any number.................................  Within 10,000 hours TIS.
 notch) 3rd stage turbine blades.
 
(4) Refurbished post-SB No. 5867       (i) Fewer than 6,000.......................  Within 7,000 hours TIS.
 (large notch) 3rd stage turbine
 blades.
                                       (ii) 6,000 or more.........................  Within 8,000 hours TIS, or
                                                                                     within 1,000 hours TIS
                                                                                     after the effective date of
                                                                                     this AD, whichever occurs
                                                                                     first.
(5) New pre-SB No. 6029 (small notch)  Any number.................................  Within 6,000 hours TIS.
 4th stage turbine blades.
(6) Refurbished pre-SB No. 6029        (i) Fewer than 3,000.......................  Within 4,000 hours TIS.
 (small notch) 4th stage turbine
 blades.
                                       (ii) 3,000 or more.........................  Within 6,000 hours TIS, or
                                                                                     within 1,000 hours TIS
                                                                                     after the effective date of
                                                                                     this AD, whichever occurs
                                                                                     first.
(7) New post-SB No. 6029 or new post-  Any number.................................  Within 10,000 hours TIS
 SB No. 6308 (large notch) 4th stage
 turbine blades.
(8) Refurbished post-SB No. 6029 or    (i) Fewer than 6,000.......................  Within 7,000 hours TIS.
 refurbished post-SB No. 6308 (large
 notch) 4th stage turbine blades.
                                       (ii) 6,000 or more.........................  Within 8,000 hours TIS, or
                                                                                     within 1,000 hours TIS
                                                                                     after the effective date of
                                                                                     this AD, whichever occurs
                                                                                     first.
----------------------------------------------------------------------------------------------------------------

Repetitive Torque Inspections for JT8D-209, -217, and -217A Engines

    (g) For JT8D-209, -217, and -217A engines, perform repetitive 
torque inspections of 3rd and 4th stage LPT blades for shroud notch 
wear. Use the procedures described in Accomplishment Instructions, 
Part 1, Paragraph 1. of PW ASB No. JT8D A6224, Revision 5, dated 
June 11, 2004, at the applicable intervals in the following Table 2 
and Table 3:

        Table 2.--3rd Stage Repetitive Torque Inspection Intervals for JT8D-209, -217, and -217A Engines
----------------------------------------------------------------------------------------------------------------
      Inspection torque readings                    Number of readings                       Disposition
----------------------------------------------------------------------------------------------------------------
Greater than or equal to 15 LB-IN      All........................................  Repeat torque inspection
 (1.695 N.m).                                                                        within 1,000 hours TIS
                                                                                     since last inspection.
Less than 15 LB-IN (1.695 N.m) but     One or more................................  Repeat torque inspection
 greater than or equal to 10 LB-IN                                                   within 500 hours TIS since
 (1.130 N.m).                                                                        last inspection.
Less than 10 LB-IN (1.130 N.m) but     One to three...............................  Repeat torque inspection
 greater than or equal to 5 LB-IN                                                    within 125 hours TIS since
 (0.565 N.m).                                                                        last inspection.
Less than 10 LB-IN (1.130 N.m) but     Four or more...............................  Remove engine from service
 greater than or equal to 5 LB-IN                                                    within 20 hours TIS since
 (0.565 N.m).                                                                        last inspection.
Less than 5 LB-IN (0.565 N.m)........  One or more................................  Remove engine from service
                                                                                     within 20 hours TIS since
                                                                                     last inspection.
----------------------------------------------------------------------------------------------------------------


        Table 3.--4th Stage Repetitive Torque Inspection Intervals for JT8D-209, -217, and -217A Engines
----------------------------------------------------------------------------------------------------------------
      Inspection torque readings                    Number of readings                       Disposition
----------------------------------------------------------------------------------------------------------------
Greater than or equal to 15 LB-IN      All........................................  Repeat torque inspection
 (1.695 N.m).                                                                        within 1,000 hours TIS
                                                                                     since last inspection.
Less than 15 LB-IN (1.695 N.m) but     One or more................................  Repeat torque inspection
 greater than or equal to 10 LB-IN                                                   within 500 hours TIS since
 (1.130 N.m).                                                                        last inspection.
Less than 10 LB-IN (1.130 N.m) but     One to six.................................  Repeat torque inspection
 greater than or equal to 5 LB-IN                                                    within 125 hours TIS since
 (0.565 N.m).                                                                        last inspection.
Less than 10 LB-IN (1.130 N.m) but     Seven or more..............................  Remove engine from service
 greater than or equal to 5 LB-IN                                                    within 20 hours TIS since
 (0.565 N.m).                                                                        last inspection.
Less than 5 LB-IN (0.565 N.m)........  One or more................................  Remove engine from service
                                                                                     within 20 hours TIS since
                                                                                     last inspection.
----------------------------------------------------------------------------------------------------------------


[[Page 3870]]

    (h) Subsequent repeat inspection intervals must not exceed the 
previous inspection interval.

JT8D-209, -217, and -217A Engines Removed From Service

    (i) JT8D-209, -217, and -217A engines removed from service may 
be returned to service after a detailed inspection and repair or 
replacement for all blades, of the failed stage, that exceed Engine 
Manual limits is done. Information on repairing or replacing turbine 
blades can be found in Sections 72-53-12 through 72-53-13 of the 
JT8D-200 Engine Manual, Part No. 773128.

Initial Inspection for JT8D-217C and -219 Engines

    (j) For JT8D-217C and -219 engines, perform the initial torque 
inspection of 4th stage LPT blades for shroud notch wear. Use the 
procedures described in Accomplishment Instructions, Part 2, 
Paragraphs 1. through 3. of PW ASB No. JT8D A6224, Revision 5, dated 
June 11, 2004, at the applicable threshold in the following Table 4:

                  Table 4.--Initial Torque Inspection Threshold for JT8D-217C and -219 Engines
----------------------------------------------------------------------------------------------------------------
              Blade Type                                   TIS                          Inspection threshold
----------------------------------------------------------------------------------------------------------------
(1) New pre-SB No. 6090 (small notch)  Any number.................................  Within 5,000 hours TIS.
 4th stage turbine blades.
(2) Refurbished pre-SB No. 6090        (i) Fewer than 3,000.......................  Within 4,000 hours TIS.
 (small notch) 4th stage turbine
 blades.
                                       (ii) 3,000 or more.........................  Within 5,000 hours TIS, or
                                                                                     within 1,000 hours TIS
                                                                                     after the effective date of
                                                                                     this AD, whichever occurs
                                                                                     first.
(3) New post-SB No. 6090, new post-SB  Any number.................................  Within 10,000 hours TIS.
 No. 6402, or new post-SB No. 6412
 (large notch) 4th stage turbine
 blades.
(4) Refurbished ``As-Cast'' post-SB    Any number.................................  Within 7,000 hours TIS.
 No. 6090, post-SB No. 6402, or post-
 SB No. 6412 (large notch) 4th stage
 turbine blades.
(5) Refurbished ``Modified'' post-SB   (i) Fewer than 3,000.......................  Within 4,000 hours TIS.
 No. 6090, post-SB No. 6402, or post-
 SB No. 6412 (large notch) 4th stage
 turbine blades.
                                       (ii) 3,000 or more.........................  Within 7,000 hours TIS, or
                                                                                     within 1,000 hours TIS
                                                                                     after the effective date of
                                                                                     this AD, whichever occurs
                                                                                     first.
----------------------------------------------------------------------------------------------------------------

Repetitive Torque Inspections for JT8D-217C and -219 Engines

    (k) For JT8D-217C and -219 engines, perform repetitive torque 
inspections of 4th stage LPT blades for shroud notch wear. Use the 
procedures described in Accomplishment Instructions, Part 2, 
Paragraph 1. of PW ASB No. JT8D A6224, Revision 5, dated June 11, 
2004, at the applicable intervals in the following Table 5:

                 Table 5.--Repetitive Torque Inspection Intervals for JT8D-217C and -219 Engines
----------------------------------------------------------------------------------------------------------------
      Inspection torque readings                    Number of readings                       Disposition
----------------------------------------------------------------------------------------------------------------
Greater than or equal to 15 LB-IN      All........................................  Repeat torque inspection
 (1.695 N.m).                                                                        within 1,000 hours TIS
                                                                                     since last inspection.
Less than 15 LB-IN (1.695 N.m) but     One or more................................  Repeat torque inspection
 greater than or equal to 10 LB-IN                                                   within 500 hours TIS since
 (1.130 N.m).                                                                        last inspection.
Less than 10 LB-IN (1.130 N.m) but     One to six.................................  Repeat torque inspection
 greater than or equal to 5 LB-IN                                                    within 125 hours TIS since
 (0.565 N.m).                                                                        last inspection.
Less than 10 LB-IN (1.130 N.m) but     Seven or more..............................  Remove engine from service
 greater than or equal to 5 LB-IN                                                    within 20 hours TIS since
 (0.565 N.m).                                                                        last inspection.
Less than 5 LB-IN (0.565 N.m)........  One or more................................  Remove engine from service
                                                                                     within 20 hours TIS since
                                                                                     last inspection.
----------------------------------------------------------------------------------------------------------------

    (l) Subsequent repeat inspection intervals must not exceed the 
previous inspection interval.

JT8D-217C and -219 Engines Removed From Service

    (m) JT8D-217C and -219 engines removed from service may be 
returned to service after a detailed inspection and repair or 
replacement for all blades, of the failed stage, that exceed Engine 
Manual limits is done. Information on repairing or replacing turbine 
blades can be found in Sections 72-53-12 through 72-53-13 of the 
JT8D-200 Engine Manual, Part No. 773128.

Other Criteria for All Engine Models Listed in This AD

    (n) Whenever a refurbished or used blade is intermixed with new 
blades in a rotor, use the lowest initial inspection threshold that 
is applicable.
    (o) The initial torque inspection or the repetitive inspection 
intervals for a particular stage may not be reset unless the blades 
for that stage are refurbished or replaced.
    (p) Whenever a used (service run) blade is reinstalled in a 
rotor, the previous used time should be subtracted from the initial 
torque inspection threshold.

LPT-to-Exhaust Case Bolts and Nuts Replacement

    (q) At next accessibility to the LPT-to-exhaust case bolts, part 
number (P/N) ST1315-15, and nuts, P/N 4023466, replace bolts and 
nuts with bolts and nuts made of Tinidur material. Information on 
replacing the bolts and nuts can be found in PW SB No. 6455, dated 
January 15, 2004.

Definitions

    (r) For the purpose of this AD, refurbishment is defined as 
restoration of either the shrouds or blade retwist or both, per the 
JT8D-200 Engine Manual, Part No. 773128.
    (s) For the purpose of this AD, ``As-Cast'' refers to blades 
that were machined from new castings and ``Modified'' refers to 
blades that were derived from the pre-SB No. 6090 configuration.
    (t) For the purpose of this AD, ``accessibility to the LPT-to-
exhaust case bolts'' refers to when the engine is disassembled 
sufficiently to give access to the LPT-to-exhaust case bolts, which 
is whenever the inner turbine fan ducts are removed.

[[Page 3871]]

Alternative Methods of Compliance

    (u) The Manager, Engine Certification Office, 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

    (v) You must use Pratt & Whitney (PW) Alert Service Bulletin 
(ASB) No. JT8D A6224, Revision 5, dated June 11, 2004, to perform 
the inspections required by this AD. The Director of the Federal 
Register approved the incorporation by reference of this document in 
accordance with 5 U.S.C. 552(a) and 1 CFR part 51. You can get a 
copy from Pratt & Whitney, 400 Main St., East Hartford, CT 06108; 
telephone (860) 565-8770, fax (860) 565-4503. You can review copies 
at the FAA, New England Region, Office of the Regional Counsel, 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/code_of_federal_regulations/ibr_locations.html.

Related Information

    (w) None.

    Issued in Burlington, Massachusetts, on January 14, 2005.
Francis A. Favara,
Acting Manager, Engine and Propeller Directorate, Aircraft 
Certification Service.
[FR Doc. 05-1463 Filed 1-26-05; 8:45 am]
BILLING CODE 4910-13-P

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