[Federal Register Volume 70, Number 211 (Wednesday, November 2, 2005)]
[Proposed Rules]
[Pages 66300-66302]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 05-21804]


========================================================================
Proposed Rules
                                                Federal Register
________________________________________________________________________

This section of the FEDERAL REGISTER contains notices to the public of 
the proposed issuance of rules and regulations. The purpose of these 
notices is to give interested persons an opportunity to participate in 
the rule making prior to the adoption of the final rules.

========================================================================


Federal Register / Vol. 70, No. 211 / Wednesday, November 2, 2005 / 
Proposed Rules

[[Page 66300]]



DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 98-ANE-47-AD]
RIN 2120-AA64


Airworthiness Directives; Pratt & Whitney JT9D Series Turbofan 
Engines

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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

SUMMARY: The FAA proposes to supersede an existing airworthiness 
directive (AD) for Pratt & Whitney (PW) JT9D series turbofan engines. 
That AD currently requires revisions to the Airworthiness Limitations 
Section (ALS) of the manufacturer's Instructions for Continued 
Airworthiness (ICA) to include required enhanced inspection of selected 
critical life-limited parts at each piece-part opportunity. This 
proposed AD would modify the JT9D series engines ALS sections of the 
manufacturer's manuals and an air carrier's approved continuous 
airworthiness maintenance program to incorporate additional inspection 
requirements. The mandatory inspections are needed to identify those 
critical rotating parts with conditions, which if allowed to continue 
in service, could result in uncontained failures. We are proposing this 
AD to prevent critical life-limited rotating engine part failure, which 
could result in an uncontained engine failure and damage to the 
airplane.

DATES: We must receive any comments on this proposed AD by January 3, 
2006.

ADDRESSES: Use one of the following addresses to submit comments on 
this proposed AD:
    <bullet> By mail: Federal Aviation Administration (FAA), New 
England Region, Office of the Regional Counsel, Attention: Rules Docket 
No. 98-ANE-47-AD, 12 New England Executive Park, Burlington, MA 01803-
5299.
    <bullet> By fax: (781) 238-7055.
    <bullet> By e-mail: <a href="/cdn-cgi/l/email-protection#467f6b2728236b272225292b2b2328320620272768212930"><span class="__cf_email__" data-cfemail="af9682cec1ca82cecbccc0c2c2cac1dbefc9cece81c8c0d9">[email protected]</span></a>.
    You may examine the AD docket at the FAA, New England Region, 
Office of the Regional Counsel, 12 New England Executive Park, 
Burlington, MA.

FOR FURTHER INFORMATION CONTACT: Kevin Donovan, Aerospace Engineer, 
Engine Certification Office, FAA, Engine and Propeller Directorate, 12 
New England Executive Park, Burlington, MA 01803-5299; telephone (781) 
238-7743, fax (781) 238-7199.

SUPPLEMENTARY INFORMATION:

Comments Invited

    We invite you to submit any written relevant data, views, or 
arguments regarding this proposal. Send your comments to an address 
listed under ADDRESSES. Include ``AD Docket No. 98-ANE-47-AD'' in the 
subject line of your comments. If you want us to acknowledge receipt of 
your mailed comments, send us a self-addressed, stamped postcard with 
the docket number written on it; we will date-stamp your postcard and 
mail it back to you. We specifically invite comments on the overall 
regulatory, economic, environmental, and energy aspects of the proposed 
AD. If a person contacts us verbally, and that contact relates to a 
substantive part of this proposed AD, we will summarize the contact and 
place the summary in the docket. We will consider all comments received 
by the closing date and may amend the proposed AD in light of those 
comments.

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.

Discussion

    On April 12, 2002, we issued AD 2002-08-11, Amendment 39-12719 (67 
FR 19663, April 23, 2002), to require revisions to the JT9D series 
engines ALS of the manufacturer's Instructions for Continued 
Airworthiness to include required enhanced inspection of selected 
critical life-limited parts at each piece-part opportunity.

New Inspection Procedures

    Since we issued AD 2002-08-11, PW has added mandatory eddy current 
inspections (ECIs) for web cooling holes in high pressure turbine (HPT) 
stage 1 disks, installed in engine models JT9D-7R4, -7R4D1, -7R4E, -
7R4E1 engines, and for HPT stage 2 disks installed in JT9D-7, -7A, -7H, 
-7AH, -7F, -7J, -20, and -20J engines. The mandatory inspections are 
needed to identify those critical rotating parts with conditions, which 
if allowed to continue in service, could result in uncontained 
failures.

FAA's Determination and Requirements of the Proposed AD

    Since an unsafe condition has been identified that is likely to 
exist or develop on other products of this same type design, the 
proposed AD would supersede AD 2002-08-11 to require:
    <bullet> Adding ECIs for web cooling holes in HPT stage 1 disks 
installed in engine models JT9D-7R4, -7R4D1, -7R4E, -7R4E1 engines; and
    <bullet> Adding ECIs for web cooling holes in HPT stage 2 disks 
installed in JT9D-7, -7A, -7H, -7AH, -7F, -7J, -20, and -20J engines; 
and
    <bullet> Clarification of the inspections listed in the Inspection 
column of the Mandatory Inspections Table in this AD.
    The proposed AD would incorporate the additional inspection 
requirements into the Airworthiness Limitations Section of the 
manufacturer's manuals and an air carrier's approved continuous 
airworthiness maintenance program.

Costs of Compliance

    About 1,978 PW JT9D series turbofan engines of the affected design 
are in the worldwide fleet. We estimate that 837 of these engines are 
installed on U.S.-registered airplanes and would be affected by this 
proposed AD. We also estimate that about one work hour per engine is 
needed to perform the proposed actions, and that the average labor rate 
is $65 per work hour. Since this is an added inspection requirement 
that will be part of the normal maintenance cycle, no additional parts 
costs are involved. Based on these figures, we estimate the total cost 
of the proposed AD to U.S. operators to be $54,405.

Authority for This Rulemaking

    Title 49 of the United States Code specifies the FAA's authority to 
issue

[[Page 66301]]

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 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 
regulation:
    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 summary of the costs to comply with this proposal 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-47-AD'' in your request.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Safety.

The Proposed Amendment

    Accordingly, 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 39-12719 (67 FR 
19663, April 23, 2002), and by adding a new airworthiness directive to 
read as follows:

Pratt & Whitney: Docket No. 98-ANE-47-AD.

Comments Due Date

    (a) The Federal Aviation Administration (FAA) must receive 
comments on this airworthiness directive (AD) action by January 3, 
2006.

Affected ADs

    (b) This AD supersedes AD 2002-08-11, Amendment 39-12719.

Applicability

    (c) This AD applies to Pratt & Whitney (PW) JT9D-3A, -7, -7A, -
7H, -7AH, -7F, -7J, -20J, -59A, -70A, -7Q, -7Q3, -7R4D, -7R4D1, -
7R4E, -7R4E1, -7R4E4, -7R4G2, and -7R4H1 series turbofan engines, 
installed on but not limited to Boeing 747 and 767 series, McDonnell 
Douglas DC-10 series, and Airbus Industrie A300 and A310 airplanes.

Unsafe Condition

    (d) This AD results from the need to require enhanced inspection 
of selected critical life-limited parts of JT9D series turbofan 
engines. We are issuing this AD to prevent failure of critical life-
limited rotating engine parts, 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) Within the next 180 days after the effective date of this 
AD, revise the manufacturer's Instructions for Continued 
Airworthiness Airworthiness Limitations Section (ALS), and for air 
carrier operations revise the approved continuous airworthiness 
maintenance program by adding the following:

``MANDATORY INSPECTIONS

    (1) Perform inspections of the following parts at each piece-
part opportunity in accordance with the instructions provided in the 
applicable manual provisions:

--------------------------------------------------------------------------------------------------------------------------------------------------------
                                                                                                     Inspect per
             Engine model               Engine manual part number         Part nomenclature            manual                 Inspection/check
                                                  (P/N)                                                section
--------------------------------------------------------------------------------------------------------------------------------------------------------
7/7A/7AH/7F, 7H/7J/20/20J.............  * 646028 (or the           All Fan Hubs..................        72-31-04  Inspection-02.
                                         equivalent customized
                                         versions, 770407 and
                                         770408).
                                                                   All HPC Stage 5--15 Disks and         72-35-00  Inspection-03.
                                                                    Rear Compressor Drive Turbine
                                                                    Shafts.
                                                                   All HPT Stage 1--2 Disks and          72-51-00  Inspection-03.
                                                                    Hubs.
                                                                   All HPT Stage 2 Disk Web              71-51-02  Inspection-05.
                                                                    Cooling Holes.
                                                                   All LPT Stage 3--6 Disks and          72-52-00  Inspection-03.
                                                                    Hubs.
59A/70A...............................  754459...................  All Fan Hubs..................        72-31-00  Check-00.
                                                                   All HPC Stage 5--15 Disks and         72-35-00  Check-00.
                                                                    Rear Compressor Drive Turbine
                                                                    Shafts.
                                                                   All HPT Stage 1--2 Disks and          72-51-00  Check-03.
                                                                    Hubs.
                                                                   All HPT Stage 1 Disk Web              72-51-02  Check-03.
                                                                    Cooling Holes.
                                                                   All LPT Stage 3--6 Disks and          72-52-00  Check-03.
                                                                    Hubs.
7Q/7Q3................................  777210...................  All Fan Hubs..................        72-31-00  Inspection-03.
                                                                   All HPC Stage 5--15 Disks and         72-35-00  Inspection-03.
                                                                    Rear Compressor Drive Turbine
                                                                    Shafts.
                                                                   All HPT Stage 1--2 Disks and          72-51-00  Inspection-03.
                                                                    Hubs.
                                                                   All HPT Stage 1 Disk Web              72-51-06  Inspection-03.
                                                                    Cooling Holes.
                                                                   All LPT Stage 3--6 Disks and          72-52-00  Inspection-03.
                                                                    Hubs.
7R4...................................  785058, 785059, and        All Fan Hubs..................        72-31-00  Inspection/Check-03.
                                         789328.
                                                                   All HPC Stage 5--15 Disks and         72-35-00  Inspection/Check 03.
                                                                    Rear Compressor Drive Turbine
                                                                    Shafts.

[[Page 66302]]

 
                                                                   All HPT Stage 1--2 Disks and          72-51-00  Inspection/Check-03.
                                                                    Hubs.
                                                                   All LPT Stage 3--6 Disks and          72-52-00  Inspection/Check-03.
                                                                    Hubs.
7R4D/D1/E/E1..........................  785058 and 785059........  All HPT Stage 1 Disk Web              72-51-06  Inspection/Check-02.
                                                                    Cooling Holes.
--------------------------------------------------------------------------------------------------------------------------------------------------------
* P/N 770407 and 770408 are customized versions of P/N 646028 engine manual.

    (2) For the purposes of these mandatory inspections, piece-part 
opportunity means:
    (i) The part is considered completely disassembled when done in 
accordance with the disassembly instructions in the manufacturer's 
engine manual; and
    (ii) The part has accumulated more than 100 cycles-in-service 
since the last piece-part opportunity inspection, provided that the 
part was not damaged or related to the cause for its removal from 
the engine.''

Alternative Methods of Compliance

    (g) You must perform these mandatory inspections using the ALS 
of the Instructions for Continued Airworthiness and the applicable 
Engine Manual unless you receive approval to use an alternative 
method of compliance under paragraph (h) of this AD. Section 43.16 
of the Federal Aviation Regulations (14 CFR 43.16) may not be used 
to approve alternative methods of compliance or adjustments to the 
times in which these inspections must be performed.
    (h) 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.

Maintaining Records of the Mandatory Inspections

    (i) You have met the requirements of this AD when you change the 
manufacturer's Instructions for Continued Airworthiness ALS 
specified in paragraph (f) of this AD, and, for air carriers 
operating under part 121 of the Federal Aviation Regulations (14 CFR 
part 121), when you modify your continuous airworthiness maintenance 
plan to reflect those changes. You do not need to record each piece-
part inspection as compliance to this AD but you must maintain 
records of those inspections according to the regulations governing 
your operation. For air carriers operating under part 121, you may 
use either the system established to comply with section 121.369 or 
an alternative accepted by your principal maintenance inspector if 
that alternative:
    (1) Includes a method for preserving and retrieving the records 
of the inspections resulting from this AD; and
    (2) Meets the requirements of section 121.369(c); and
    (3) Maintains the records either indefinitely or until the work 
is repeated.
    (j) These record keeping requirements apply only to the records 
used to document the mandatory inspections required as a result of 
revising the ALS of the Instructions for Continued Airworthiness as 
specified in paragraph (f) of this AD, and do not alter or amend the 
record keeping requirements for any other AD or regulatory 
requirement.

    Issued in Burlington, Massachusetts, on October 27, 2005.
Peter A. White,
Acting Manager, Engine and Propeller Directorate, Aircraft 
Certification Service.
[FR Doc. 05-21804 Filed 11-1-05; 8:45 am]
BILLING CODE 4910-13-P


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