[Federal Register Volume 71, Number 201 (Wednesday, October 18, 2006)]
[Rules and Regulations]
[Pages 61395-61399]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: E6-17327]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2006-25809; Directorate Identifier 2001-NE-30-AD; 
Amendment 39-14791; AD 2006-17-07R1]
RIN 2120-AA64


Airworthiness Directives; Pratt & Whitney JT8D-1, -1A, -1B, -7, -
7A, -7B, -9, -9A, -11, -15, -15A, -17, -17A, -17R, -17AR, -209, -217, -
217A, -217C, and -219 Turbofan Engines

AGENCY: Federal Aviation Administration (FAA), Department of 
Transportation (DOT).

ACTION: Final rule; correction.

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

SUMMARY: The FAA is revising an existing airworthiness directive (AD) 
for Pratt & Whitney (PW) JT8D-1, -1A, -1B, -7, -7A, -7B, -9, -9A, -11, 
-15, -15A, -17, -17A, -17R, -17AR, -209, -217, -217A, -217C, and -219 
turbofan engines. That AD currently requires either replacing high 
pressure compressor (HPC) front hubs and HPC disks that have operated 
at any time with PWA 110-21 coating and that operated in certain engine 
models, or, visually inspecting and fluorescent penetrant inspecting 
(FMPI) for cracking of those parts and re-plating them if they pass 
inspection. This AD requires the same actions, but makes necessary 
corrections to inadvertent reference errors and omissions found in AD 
2006-17-07, and relaxes some of the compliance times in Table 5. This 
AD results from our finding reference errors and omissions in AD 2006-
17-07, from determining that the AD as drafted imposed an unnecessary 
burden on operators if they have to immediately remove engines, and 
from requests to clarify compliance paragraphs. We are issuing this AD 
to prevent a rupture of an HPC front hub or an HPC disk that could 
result in an uncontained engine failure and damage to the airplane.

DATES: This AD becomes effective November 2, 2006. The Director of the 
Federal Register previously approved the incorporation by reference of 
certain publications listed in the regulations as of October 4, 2006 
(71 FR 51459, August 30, 2006).

ADDRESSES: You can get the service information identified in this AD 
from Pratt & Whitney, 400 Main St., East Hartford, CT 06108, telephone 
(860) 565-7700; fax (860) 565-1605.
    You may examine the AD docket on the Internet at http://dms.dot.gov 
or in Room PL-401 on the plaza level of the Nassif Building, 400 
Seventh Street, SW., Washington, DC.

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

SUPPLEMENTARY INFORMATION: On August 21, 2006, the FAA issued AD 2006-
17-07, Amendment 39-14728 (71 FR 51459, August 30, 2006). That AD 
requires either replacing HPC front hubs and HPC disks that have 
operated at any time with PWA 110-21 coating and that operated in 
certain engine models, or, visually inspecting and FMPI for cracking of 
those parts and re-plating them if they pass inspection. That AD was 
the result of an investigation by PW, which concluded that any HPC 
front hub or HPC disk coated with PWA 110-21 that ever operated on 
JT8D-15, -15A, -17, -17A, -17R, -17AR, -209, -217, -217A, -217C, and -
219 turbofan engines, could crack before reaching their published life 
limit. That condition, if not corrected, could result in an uncontained 
engine failure and damage to the airplane.

Examining the AD Docket

    You may examine the docket that contains the AD, any comments 
received, and any final disposition in person at the Docket Management 
Facility Docket Office between 9 a.m. and 5 p.m., Monday through 
Friday, except Federal holidays. The Docket Office (telephone (800) 
647-5227) is located on the plaza level of the Department of 
Transportation Nassif Building at the street address stated in 
ADDRESSES. Comments will be available in the AD docket shortly after 
the DMS receives them.

Actions Since AD 2006-17-07 Was Issued

    After we issued AD 2006-17-07, we found reference errors and 
omissions. These errors and omissions could affect your ability to 
comply with the AD. The following errors and omissions were discovered. 
We made the associated corrections:
     In the third column of Table 1 of this AD, we omitted ``-
17A'' in two places. We added the missing ``-17A'' from AD 2006-17-07 
in both places.
     The third column of Table 4 and Table 5 reads ``Paragraph 
(h)(3) of this AD''. Paragraph (h)(3) does not exist. We corrected it 
to read ``Paragraph (j) of this AD.''
    We also determined that based on the compliance times in Table 5 of 
AD 2006-17-07, some operators might have to immediately remove their 
engines from service. If so, we concluded that those immediate removals 
might impose an unanticipated undue burden. Table 5 of AD 2006-17-07, 
appears below.

[[Page 61396]]



    Table 5 of AD 2006-17-07--HPC Front Hub Inspection Schedule--Hubs
                       Coated With Nickel-Cadmium
------------------------------------------------------------------------
                                                       Also inspect 7th
                                    Inspect before      stage HPC disks
    HPC front hub CSN on the       additional CIS or    and 9th stage-
    effective date of this AD       CSN,  whichever   through-12th stage
                                     occurs first      HPC disks using:
------------------------------------------------------------------------
(i) 19,000 or more..............  500 CIS or 20,000   Paragraph (h)(3)
                                   CSN.                of this AD.
(ii) 17,000 or more, but fewer    1,000 CIS or        Paragraph (h)(3)
 than 19,000.                      19,500 CSN.         of this AD.
(iii) 9,000 or more, but fewer    18,000 CSN........  Paragraph (h)(3)
 than 17,000, that have not been                       of this AD.
 inspected.
(iv) 9,000 or more, but fewer     15,500 CSN........  Paragraph (h)(3)
 than 17,000, that were                                of this AD.
 inspected before accumulating
 9,000 CSN.
------------------------------------------------------------------------

    Therefore, we changed Table 5 to reflect relaxed compliance 
requirements in item (iii), and we changed the compliance requirements 
in item (iv). With the addition of the ``-17A'' noted previously, and 
the changed compliance requirements that relax compliance time, Table 5 
now reads as follows:

 (Changed) Table 5.--HPC Front Hub Inspection Schedule--Hubs Coated With
                             Nickel-Cadmium
------------------------------------------------------------------------
                                                       Also inspect 7th
                                    Inspect before      stage HPC disks
    HPC front hub CSN on the       additional CIS or    and 9th stage-
    effective date of this AD       CSN,  whichever   through-12th stage
                                     occurs first      HPC disks using:
------------------------------------------------------------------------
(i) 19,000 or more..............  500 CIS or 20,000   Paragraph (j) of
                                   CSN.                this AD.
(ii) 17,000 or more, but fewer    1,000 CIS or        Paragraph (j) of
 than 19,000.                      19,500 CSN.         this AD.
(iii) 9,000 or more, but fewer    18,000 CSN........  Paragraph (j) of
 than 17,000.                                          this AD.
(iv) Fewer than 9,000 that are    If the parts have   Paragraph (j) of
 accessible.                       been inspected      this AD.
                                   and are
                                   acceptable, parts
                                   may be
                                   reinstalled.
                                   Inspect again
                                   using the
                                   criteria in (iii)
                                   of this table.
------------------------------------------------------------------------

    As part of relaxing the requirements, we also clarified that 
paragraphs (f)(3) and (j) pertain to 7th stage HPC disks and 9th stage-
through-12th stage HPC disks coated with PWA 110-21.
    Finally, since AD 2006-17-07 was issued, we received multiple 
instances of operators requesting clarification of compliance paragraph 
(e) in AD 2006-17-07. Based on the frequency of requests, we decided to 
clarify the paragraph. AD 2006-17-07 paragraph (e) originally read as 
follows:

    ``(e) You must accomplish the actions required by this AD within 
the compliance times specified, unless the actions have already been 
done. Any engine with an HPC front hub that has been inspected using 
AD 2002-23-14, AD 2003-12-07, or AD 2003-16-05, is considered in 
compliance with this AD.''

    We rewrote paragraph (e) to now read as follows:

    ``(e) You must accomplish the actions required by this AD within 
the compliance times specified, unless the actions have already been 
done. Any engine with an HPC front hub that has been inspected for 
fretting wear using AD 2002-23-14, AD 2003-12-07, or AD 2003-16-05, 
counts as an inspection toward compliance with this AD.''

FAA's Determination and Requirements of This AD

    The unsafe condition described previously is likely to exist or 
develop on other Pratt & Whitney JT8D-1, -1A, -1B, -7, -7A, -7B, -9, -
9A, -11, -15, -15A, -17, -17A, -17R, -17AR, -209, -217, -217A, -217C, 
and -219 turbofan engines of the same type design. We are issuing this 
AD to prevent a rupture of an HPC front hub or an HPC disk that could 
result in an uncontained engine failure and damage to the airplane. 
This AD requires either replacing HPC front hubs and HPC disks that 
have operated at any time with PWA 110-21 coating and that operated in 
certain engine models, or, visually inspecting and FMPI for cracking of 
those parts and re-plating them if they pass inspection.

FAA's Determination of the Effective Date

    Since an unsafe condition exists that requires the immediate 
adoption of this AD, we have found that notice and opportunity for 
public comment before issuing this AD are unnecessary, and that good 
cause exists for making this amendment effective in less than 30 days.

Docket Number Change

    We are transferring the docket for this AD to the Docket Management 
System as part of our on-going docket management consolidation efforts. 
The new Docket No. is FAA-2006-25809. The old Docket No. became the 
Directorate Identifier, which is 2001-NE-30-AD. This AD might get 
logged into the DMS docket, ahead of the previously collected documents 
from the old docket file, as we are in the process of sending those 
items to the DMS.

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;

[[Page 61397]]

    (2) Is not a ``significant rule'' under DOT Regulatory Policies and 
Procedures (44 FR 11034, February 26, 1979); and
    (3) Will not have a significant economic impact, positive or 
negative, on a substantial number of small entities under the criteria 
of the Regulatory Flexibility Act.
    We prepared a summary of the costs to comply with this AD and 
placed it in the AD Docket. You may get a copy of this summary at the 
address listed under ADDRESSES.

List of Subjects in 14 CFR Part 39

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

Adoption of the Amendment

0
Under 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

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 39-14728 (71 FR 
51459, August 30, 2006), and by adding a new airworthiness directive, 
Amendment 39-14791, to read as follows:

2006-17-07R1 Pratt & Whitney: Amendment 39-14791. Docket No. FAA-
2006-25809; Directorate Identifier 2001-NE-30-AD.

Effective Date

    (a) This airworthiness directive (AD) becomes effective November 
2, 2006.

Affected ADs

    (b) This AD revises AD 2006-17-07.

Applicability

    (c) This AD applies to the following Pratt & Whitney (PW) JT8D-
1, -1A, -1B, -7, -7A, -7B, -9, -9A, -11, -15, -15A, -17, -17A, -17R, 
-17AR, -209, -217, -217A, -217C, and -219 turbofan engines, with 8th 
stage high pressure compressor (HPC) front hubs:

                                           Table 1.--AD Applicability
----------------------------------------------------------------------------------------------------------------
  If the HPC front hub is  coated     And if the stage 8-9
               with:                 spacer is coated with:     And the HPC front hub:       Then this AD is:
----------------------------------------------------------------------------------------------------------------
(1) PWA 110-21 at any time.........  Any...................  Operated in a JT8D-15, -     Applicable. See
                                                              15A, -17, -17A, -17R, or -   paragraph (f) and
                                                              17AR engine.                 Table 2 of this AD.
(2) PWA 110-21 at any time.........  Any...................  Operated in a JT8D-209, -    Applicable. See
                                                              217, -217A, -217C, or -219   paragraph (h) and
                                                              engine.                      Table 4 of this AD.
(3) Nickel-Cadmium.................  PWA 110-21 at any time  Operated in a JT8D-209, -    Applicable. See
                                                              217, -217A, -217C, or -219   paragraph (i) and
                                                              engine.                      Table 5 of this AD.
(4) Nickel-Cadmium.................  PWA 110-21 at any time  Operated in a JT8D-1, -1A, - Not applicable.
                                                              1B, -7, -7A, -7B, -9, -9A,
                                                              -11, -15, -15A, -17, -17A,
                                                              -17R, or -17AR engine.
(5) PWA 110-21 at any time.........  Any...................  Operated in a JT8D-1, -1A, - Not applicable.
                                                              1B, -7, -7A, -7B, -9, -9A,
                                                              or -11, but never operated
                                                              in a JT8D-15, -15A, -17, -
                                                              17A, -17R, -17AR, -209, -
                                                              217, -217A, -217C, or -219
                                                              engine.
(6) Nickel-Cadmium.................  Any type but PWA 110-   Any........................  Not applicable.
                                      21.
----------------------------------------------------------------------------------------------------------------

    These engines are installed on, but not limited to, Boeing DC-9, 
MD-80 series, 727 series, and 737 series airplanes.

Unsafe Condition

    (d) This AD results from inadvertent reference errors and 
omissions found in AD 2006-17-07, which could affect ability to 
comply with that AD. We are issuing this AD to prevent a rupture of 
an HPC front hub or an HPC disk that could result in an uncontained 
engine failure and damage to the airplane.

Compliance

    (e) You must accomplish the actions required by this AD within 
the compliance times specified, unless the actions have already been 
done. Any engine with an HPC front hub that has been inspected for 
fretting wear using AD 2002-23-14, AD 2003-12-07, or AD 2003-16-05, 
counts as an inspection toward compliance with this AD.

JT8D-1, -1A, -1B, -7, -7A, -7B, -9, -9A, -11, -15, -15A, -17, -17A, -
17R, and -17AR Turbofan Engines--Inspect or Replace HPC Front Hubs, HPC 
Disks, and Stage 8-9 Spacers

    (f) For applicable JT8D-1, -1A, -1B, -7, -7A, -7B, -9, -9A, -11, 
-15, -15A, -17, -17A, -17R, and -17AR turbofan engines specified in 
Table 1 of this AD, do the following:
    (1) Using the inspection schedule in Table 2 of this AD, strip 
the protective coating, visually inspect for fretting wear, 
fluorescent magnetic particle inspect (FMPI) for cracks, reidentify, 
replate HPC front hubs and stage 8-9 spacers, and replace if 
necessary.
    (2) Use paragraphs 1. through 3.B.(7)(b) under ``For Rear 
Compressor Front Hubs that Have Operated With PWA 110-21 coating AT 
ANY TIME During Their Service Life in JT8D-15, -15A, -17, -17A, -
17R, -17AR Engine Models.'' of PW Alert Service Bulletin (ASB) JT8D 
A6468, dated December 23, 2004.

               Table 2.--HPC Front Hub Inspection Schedule
------------------------------------------------------------------------
                                    Inspect before     Also inspect 7th
 HPC front hub cycles-since-new   additional cycles-    stage HPC disks
 (CSN) on the effective date of    in-service (CIS)     and 9th stage-
             this AD               or CSN, whichever  through-12th stage
                                     occurs first      HPC disks using:
------------------------------------------------------------------------
(i) 19,000 or more..............  500 CIS or 20,000   Paragraph (f)(3)
                                   CSN.                of this AD.
(ii) 15,500 or more, but fewer    1,000 CIS or        Paragraph (f)(3)
 than 19,000.                      19,500 CSN.         of this AD.
(iii) 5,000 or more, but fewer    16,500 CSN........  Paragraph (f)(3)
 than 15,500.                                          of this AD.

[[Page 61398]]

 
(iv) Fewer than 5,000 that are    If the parts have   Paragraph (f)(3)
 accessible.                       been inspected      of this AD.
                                   and are
                                   acceptable, parts
                                   may be
                                   reinstalled.
                                   Inspect again
                                   using the
                                   criteria in (iii)
                                   of this Table.
------------------------------------------------------------------------

    (3) When the HPC front hub is inspected, visually inspect for 
fretting wear and FMPI for cracks on 7th stage HPC disks and 9th 
stage-through-12th stage HPC disks coated with PWA 110-21. 
Inspection information can be found in the applicable sections of 
JT8D Engine Manual Part Number (P/N) 481672, listed in the following 
Table 3:

       Table 3.--Seventh Stage HPC Disks and 9th Stage-Through-12th Stage HPC Disks Inspection Information
----------------------------------------------------------------------------------------------------------------
                                    Chapter/                             Fretting
             Stage                   section     Visual inspection      inspection                FMPI
----------------------------------------------------------------------------------------------------------------
7..............................        72-36-41  Inspection-01....  Inspection-04....  Inspection-03.
9..............................        72-36-43  Inspection-01....  Inspection-04....  Inspection-03.
10.............................        72-36-44  Inspection-01....  Inspection-04....  Inspection-03.
11.............................        72-36-45  Inspection-01....  Inspection-04....  Inspection-03.
12.............................        72-36-46  Inspection-01....  Inspection-04....  Inspection-03.
----------------------------------------------------------------------------------------------------------------

JT8D-15, -15A, -17, -17A, -17R, and -17AR Turbofan Engines--Cycle 
Adjustment for HPC Front Hubs That Entered Service With Nickel-Cadmium 
Plating and PWA 110-21 Coating

    (g) For JT8D-15, -15A, -17, -17A, -17R, and -17AR turbofan 
engines with front hubs that entered service with Nickel-Cadmium 
plating, but have also operated during the life of the hub with PWA 
110-21 coating:
    (1) You are allowed to make a cycle adjustment if the hub was 
never operated with a PWA 110-21-coated stage 8-9 spacer.
    (2) Use the information under ``Compliance'' of PW ASB JT8D 
A6468, dated December 23, 2004, to determine the adjustment.

JT8D-209, -217, -217A, -217C, and -219 Turbofan Engines--Inspect or 
Replace HPC Front Hubs and Stage 8-9 Spacers

    (h) For applicable JT8D-209, -217, -217A, -217C, and -219 
turbofan engines specified in Table 1, Row (2) of this AD, do the 
following:
    (1) Using the inspection schedule in Table 4 of this AD, strip 
the protective coating, visually inspect for fretting wear, FMPI for 
cracking, reidentify, replate HPC front hubs and the stage 8-9 
spacers, and replace if necessary.
    (2) Use paragraphs 1. through 1.A. and paragraphs 2. through 
2.C.(2)(g)2 of Accomplishment Instructions of PW ASB JT8D A6430, 
Revision 2, dated December 23, 2004.

Table 4.--HPC Front Hub Inspection Schedule--Hubs Coated With PWA 110-21
------------------------------------------------------------------------
                                                       Also inspect 7th
                                    Inspect before      stage HPC disks
    HPC front hub CSN on the       additional CIS or    and 9th stage-
    effective date of this AD       CSN,  whichever   through-12th stage
                                     occurs first      HPC disks using:
------------------------------------------------------------------------
(i) 19,000 or more..............  500 CIS or 20,000   Paragraph (j) of
                                   CSN.                this AD.
(ii) 15,500 or more, but fewer    1,000 CIS or        Paragraph (j) of
 than 19,000.                      19,500 CSN.         this AD.
(iii) 5,000 or more, but fewer    16,500 CSN........  Paragraph (j) of
 than 15,500.                                          this AD.
(iv) Fewer than 5,000 that are    If the parts have   Paragraph (j) of
 accessible..                      been inspected      this AD.
                                   and are
                                   acceptable, parts
                                   may be
                                   reinstalled.
                                   Inspect again
                                   using the
                                   criteria in (iii)
                                   of this Table.
------------------------------------------------------------------------

    (i) For applicable JT8D-209, -217, -217A, -217C, and -219 
turbofan engines specified in Table 1, Row (3) of this AD, do the 
following:
    (1) Using the inspection schedule in Table 5 of this AD, strip 
the protective coating, visually inspect for fretting wear, FMPI for 
cracking, reidentify, replate HPC front hubs and the stage 8-9 
spacers, and replace if necessary.
    (2) Use paragraphs 1., 1.C, and 4. through 4.B.(2)(g)2 of 
Accomplishment Instructions of PW ASB JT8D A6430, Revision 2, dated 
December 23, 2004, for all applicable hubs with any type of coating.

  Table 5.--HPC Front Hub Inspection Schedule--Hubs Coated With Nickel-
                                 Cadmium
------------------------------------------------------------------------
                                                       Also inspect 7th
                                    Inspect before      stage HPC disks
    HPC front hub CSN on the       additional CIS or    and 9th stage-
    effective date of this AD       CSN,  whichever   through-12th stage
                                     occurs first      HPC disks using:
------------------------------------------------------------------------
(i) 19,000 or more..............  500 CIS or 20,000   Paragraph (j) of
                                   CSN.                this AD.
(ii) 17,000 or more, but fewer    1,000 CIS or        Paragraph (j) of
 than 19,000.                      19,500 CSN.         this AD.
(iii) 9,000 or more, but fewer    18,000 CSN........  Paragraph (j) of
 than 17,000.                                          this AD.
(iv) Fewer than 9,000 that are    If the parts have   Paragraph (j) of
 accessible.                       been inspected      this AD.
                                   and are
                                   acceptable, parts
                                   may be
                                   reinstalled.
                                   Inspect again
                                   using the
                                   criteria in (iii)
                                   of this Table.
------------------------------------------------------------------------


[[Page 61399]]

    (j) When the HPC front hub is inspected, visually inspect for 
fretting wear and FMPI for cracks on 7th stage HPC disks and 9th 
stage-through-12th stage HPC disks coated with PWA 110-21. 
Inspection information can be found in the applicable sections of 
JT8D-200 Engine Manual P/N 773128, listed in Table 3 of this AD.

JT8D-209, -217, -217A, -217C, and -219 Turbofan Engines--Cycle 
Adjustment for HPC Front Hubs That Entered Service With Nickel-Cadmium 
Plating and PWA 110-21 Coating

    (k) For JT8D-209, -217, -217A, -217C, and -219 turbofan engines 
with HPC front hubs that entered service with Nickel-Cadmium 
plating, but have also operated during the life of the hub with PWA 
110-21 coating:
    (1) You are allowed to make a cycle adjustment.
    (2) Use the information under ``CONDITION A'' of PW ASB JT8D 
A6430, Revision 2, dated December 23, 2004, to determine the 
adjustment.

Replacement of HPC Front Hubs and Stage 8-9 Spacers That Have Operated 
With PWA 110-21 Coating, As Optional Action--All Engines

    (l) For all applicable engines, as an optional action for the 
visual inspections in this AD, replace HPC front hubs and stage 8-9 
spacers that have operated with PWA 110-21 coating in the interface 
between the hub and the stage 8-9 spacer and HPC disks currently 
coated with PWA 110-21, as follows:
    (1) Install a Nickel-Cadmium plated HPC front hub that has never 
operated with PWA 110-21 coating in the interface between the HPC 
front hub and the stage 8-9 spacer.
    (2) Install a Nickel-Cadmium plated or Electroless Nickel-plated 
stage 8-9 spacer.
    (3) Install HPC disks that have never operated with PWA 110-21 
coating.

Prohibition Against Recoating the HPC Front Hub, Stage 7 HPC Disk, and 
Stage 8-9 Spacer With PWA 110-21--All Engines

    (m) Do not recoat the HPC front hub with PWA 110-21 (Repair-23 
of Chapter/Section 72-36-42 of JT8D-200 Engine Manual, P/N 773128, 
and Repair-27 and Repair-28 of Chapter/Section 72-36-42 of JT8D 
Engine Manual, P/N 481672).
    (n) Do not recoat the 7th stage disk with PWA 110-21 (Repair-15 
of Chapter/Section 72-36-41 of JT8D-200 Engine Manual, P/N 773128, 
and Repair-15 of Chapter/Section 72-36-41 of JT8D Engine Manual, P/N 
481672).
    (o) Do not recoat the stage 8-9 spacer with PWA 110-21 (Repair-
03, Task 72-36-12-30-003-002, of Chapter/Section 72-36-12 of JT8D-
200 Engine Manual, P/N 773128, and Repair-01, Task 72-36-12-30-001-
002, of Chapter/Section 72-36-12 of JT8D Engine Manual, P/N 481672).

Prohibition Against Reinstalling HPC Front Hubs and Stage 8-9 Spacers 
Coated With PWA 110-21

    (p) After the effective date of this AD, do not reinstall HPC 
front hubs and stage 8-9 spacers coated with PWA 110-21.

Definition

    (q) For the purpose of this AD, ``accessible'' is defined as 
when the HPC front hub is removed from the engine and the hub is 
debladed.

Alternative Methods of Compliance

    (r) 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.

Related Information

    (s) None.

Material Incorporated by Reference

    (t) You must use the service information specified in Table 6 of 
this AD to perform the actions required by this AD. The Director of 
the Federal Register previously approved the incorporation by 
reference of these alert service bulletins in accordance with 5 
U.S.C. 552(a) and 1 CFR part 51, as of October 4, 2006 (71 FR 51459, 
August 30, 2006). Contact Pratt & Whitney, 400 Main St., East 
Hartford, CT 06108, telephone (860) 565-7700; fax (860) 565-1605 for 
a copy of this service information. You may 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/cfr/ibr-locations.html.

                                      Table 6.--Incorporation by Reference
----------------------------------------------------------------------------------------------------------------
 Pratt & Whitney Alert Service
          Bulletin No.                     Page                   Revision                      Date
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JT8D A6430, Total Pages: 35....  ALL....................  2......................  December 23, 2004.
JT8D A6468, Total Pages: 20....  ALL....................  Original...............  December 23, 2004.
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    Issued in Burlington, Massachusetts, on October 11, 2006.
Thomas A. Boudreau,
Acting Manager, Engine and Propeller Directorate, Aircraft 
Certification Service.
 [FR Doc. E6-17327 Filed 10-17-06; 8:45 am]
BILLING CODE 4910-13-P