Document ID: FAA-2010-0594-0001
Agency: faa
Document Type: Rule
Title: Airworthiness Directives: Pratt and Whitney JT8D 209,  217,  217A,  217C, and  219 Turbofan Engines
Posted Date: 2010-08-18T04:00Z

[Federal Register: August 18, 2010 (Volume 75, Number 159)]
[Proposed Rules]               
[Page 50945-50947]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr18au10-34]                         

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2010-0594; Directorate Identifier 98-ANE-43-AD]
RIN 2120-AA64

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

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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SUMMARY: The FAA is superseding an existing airworthiness directive 
(AD) for Pratt & Whitney (PW) JT8D-209, -217, -217A, -217C, and -219 
turbofan engines. That AD currently requires revisions to the engine 
manufacturer's time limits section (TLS) to include enhanced inspection 
of selected critical life-limited parts at each piece-part opportunity. 
This AD requires modifying the TLS of the manufacturer's engine manual 
and an air carrier's approved continuous airworthiness maintenance 
program to incorporate additional inspection requirements. Pratt & 
Whitney has developed and the FAA has approved improved inspection 
procedures for the critical life-limited parts. 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 issuing 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 October 18, 
2010.

ADDRESSES: Use one of the following addresses to comment on this 
proposed AD.
     Federal eRulemaking Portal: Go to http://
www.regulations.gov and follow the instructions for sending your 
comments electronically.
     Mail: Docket Management Facility, U.S. Department of 
Transportation, 1200 New Jersey Avenue, SE., West Building Ground 
Floor, Room W12-140, Washington, DC 20590-0001.
     Hand Delivery: Deliver to Mail address above between 9 
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
     Fax: (202) 493-2251.

FOR FURTHER INFORMATION CONTACT: Ian Dargin, Aerospace Engineer, Engine 
Certification Office, FAA, Engine and Propeller Directorate, 12 New 
England Executive Park, Burlington, MA 01803; e-mail: 
ian.dargin@faa.gov; telephone (781) 238-7178, fax (781) 238-7199.

SUPPLEMENTARY INFORMATION: 

Comments Invited

    We invite you to send any written relevant data, views, or 
arguments regarding this proposal. Send your comments to an address 
listed under ADDRESSES. Include ``Docket No. FAA-2010-0594; Directorate 
Identifier 98-ANE-43-AD'' in the subject line of your comments. We 
specifically invite comments on the overall regulatory, economic, 
environmental, and energy aspects of the proposed AD. We will consider 
all comments received by the closing date and may amend the proposed AD 
in light of those comments.
    We will post all comments we receive, without change, to http://
www.regulations.gov, including any personal information you provide. We 
will also post a report summarizing each substantive verbal contact 
with FAA personnel concerning this proposed AD. Using the search 
function of the Web site, anyone can find and read the comments in any 
of our dockets, including, if provided, the name of the individual who 
sent the comment (or signed the comment on behalf of an association, 
business, labor union, etc.). You may review the DOT's complete Privacy 
Act Statement in the Federal Register published on April 11, 2000 (65 
FR 19477-78).

Examining the AD Docket

    You may examine the AD docket on the Internet at http://
www.regulations.gov; or in person at the Docket Operations office 
between 9 a.m. and 5 p.m., Monday through Friday, except Federal 
holidays. The AD docket contains this proposed AD, the regulatory 
evaluation, any comments received, and other information. The street 
address for the Docket Operations office (telephone (800) 647-5527) is 
the same as the Mail address provided in the ADDRESSES section. 
Comments will be available in the AD docket shortly after receipt.

Discussion

    On August 24, 2005, the FAA issued airworthiness directive (AD) 
2005-18-02, Amendment 39-14242 (70 FR 52004, September 1, 2005), to 
require revisions to the TLS of the manufacturer's engine manual for 
these engines to include required enhanced inspection of selected 
critical life-limited parts at each piece-part opportunity.

[[Page 50946]]

New Inspection Procedures

    Since the issuance of that AD, Pratt & Whitney has developed and 
the FAA has approved improved inspection procedures for the critical 
life-limited parts. 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. This 
proposal would add new inspection methods to the TLS of the 
manufacturer's engine manual and an air carrier's approved continuous 
airworthiness maintenance program to incorporate additional inspection 
requirements for 1st stage compressor hubs, 3rd stage turbine disks, 
and 4th stage turbine disks.

FAA's Determination of an Unsafe Condition and Proposed Actions

    Since an unsafe condition has been identified that is likely to 
exist or develop on other PW JT8D-209, -217, -217A, -217C, and -219 
turbofan engines of the same type design, the proposed AD would 
supersede AD 2005-18-02 to add new inspection methods for 1st stage 
compressor hubs, 3rd stage turbine disks, and 4th stage turbine disks. 
For reference, this proposed AD carries forward the requirements from 
AD 2005-18-02. Also for reference, parts that have an Engine Manual 
Inspection Task and/or Sub Task Number reference updated in the table 
in the compliance section of this AD, are identified by an asterisk (*) 
that precedes the part nomenclature.

Costs of Compliance

    We estimate that this proposed AD would affect 1,143 JT8D-209, -
217, -217A, -217C, and -219 turbofan engines installed on airplanes of 
U.S. registry. We also estimate that it would take about 10 work-hours 
per engine to perform the proposed actions, and that the average labor 
rate is $85 per work-hour. Since this is an added inspection 
requirement, included as part of the normal maintenance cycle, no 
additional part costs are involved. Based on these figures, we estimate 
the total cost of the proposed AD to U.S. operators to be $971,550.

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 proposed AD would not have federalism 
implications under Executive Order 13132. This proposed AD would not 
have a substantial direct effect on the States, on the relationship 
between the national Government and the States, or on the distribution 
of power and responsibilities among the various levels of government.
    For the reasons discussed above, I certify that the proposed AD:
    1. Is not a ``significant regulatory action'' under Executive Order 
12866;
    2. Is not a ``significant rule'' under the DOT Regulatory Policies 
and Procedures (44 FR 11034, February 26, 1979); and
    3. Would not have a significant economic impact, positive or 
negative, on a substantial number of small entities under the criteria 
of the Regulatory Flexibility Act.
    We prepared a regulatory evaluation of the estimated costs to 
comply with this proposed AD. See the ADDRESSES section for a location 
to examine the regulatory evaluation.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Safety.

The Proposed Amendment

    Under the authority delegated to me by the Administrator, the 
Federal Aviation Administration proposes to amend 14 CFR part 39 as 
follows:

PART 39--AIRWORTHINESS DIRECTIVES

    1. The authority citation for part 39 continues to read as follows:

    Authority: 49 U.S.C. 106(g), 40113, 44701.

Sec.  39.13  [Amended]

    2. The FAA amends Sec.  39.13 by removing Amendment 39-14242 (70 FR 
52004, September 1, 2005) and by adding a new airworthiness directive 
to read as follows:

Pratt & Whitney: Docket No. FAA-2010-0594; Directorate Identifier 
98-ANE-43-AD.

Comments Due Date

    (a) The Federal Aviation Administration (FAA) must receive 
comments on this airworthiness directive (AD) action by October 18, 
2010.

Affected ADs

    (b) This AD supersedes AD 2005-18-02, Amendment 39-14242.

Applicability

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

Unsafe Condition

    (d) This AD results from the need to require enhanced inspection 
of selected critical life-limited parts of JT8D-209, -217, -217A, -
217C, and -219 turbofan engines. We are issuing this AD to prevent 
critical life-limited rotating engine part failure, 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 30 days after the effective date of this AD, 
(1) revise the Time Limits section (TLS) of the manufacturer's 
engine manual, part number 773128, as appropriate for PW JT8D-209, -
217, -217A, -217C, and -219 turbofan engines, and (2) for air 
carriers, revise the approved mandatory inspections section of the 
continuous airworthiness maintenance program, by adding the 
following:
    ``Critical Life Limited Part Inspection
    A. Inspection Requirements:
    (1) This section contains the definitions for individual engine 
piece-parts and the inspection procedures, which are necessary, when 
these parts are removed from the engine.
    (2) It is necessary to do the inspection procedures of the 
piece-parts in Paragraph B when:
    (a) The part is removed from the engine and disassembled to the 
level specified in paragraph B and
    (b) The part has accumulated more than 100 cycles since the last 
piece part inspection, provided that the part is not damaged or 
related to the cause of its removal from the engine.
    (3) The inspections specified in this section do not replace or 
make unnecessary other recommended inspections for these parts or 
other parts.
    B. Parts Requiring Inspection.

    Note: Piece part is defined as any of the listed parts with all 
the blades removed.

[[Page 50947]]

------------------------------------------------------------------------
           Description               Section         Inspection No.
------------------------------------------------------------------------
Hub (Disk), 1st Stage Compressor:
    * Hub Detail--All P/Ns.......     72-33-31  -03, -04, -05
    * Hub Assembly--All P/Ns.....     72-33-31  -03, -04, -05
Disk, 13th Stage Compressor--All      72-36-47  -02
 P/Ns.
HP Turbine, First Stage:
    Rotor Assembly--All P/Ns.....     72-52-02  -04
    Disk--All P/Ns...............     72-52-02  -03
Disk, 2nd Stage Turbine--All P/Ns     72-53-16  -02
* Disk, 3rd Stage Turbine--All P/     72-53-17  -02, -03
 Ns.
* Disk, 4th Stage Turbine--All P/     72-53-18  -02, -03''
 Ns.
------------------------------------------------------------------------

     (g) The parts that have an Engine Manual Inspection Task and or 
Sub Task Number reference updated in the table of this AD, are 
identified by an asterisk (*) that precedes the part nomenclature.
    (h) Except as provided in paragraph (i) of this AD, and 
notwithstanding contrary provisions in section 43.16 of the Federal 
Aviation Regulations (14 CFR 43.16), these mandatory inspections 
shall be performed only in accordance with the TLS of the 
manufacturer's engine manual.

Alternative Methods of Compliance (AMOC)

    (i) You must perform these mandatory inspections using the TLS 
of the manufacturer's engine manual unless you receive approval to 
use an AMOC under paragraph (j) 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.
    (j) 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

    (k) You have met the requirements of this AD when you revise the 
TLS of the manufacturer's engine manual as specified in paragraph 
(f) of this AD. For air carriers operating under part 121 of the 
Federal Aviation Regulations (14 CFR part 121), you have met the 
requirements of this AD 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 Sec.  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 Sec.  121.369(c); and
    (3) Maintains the records either indefinitely or until the work 
is repeated.
    (l) These recordkeeping requirements apply only to the records 
used to document the mandatory inspections required as a result of 
revising the TLS of the manufacturer's engine manual as specified in 
paragraph (f) of this AD. These record keeping requirements do not 
alter or amend the record keeping requirements for any other AD or 
regulatory requirement.

Related Information

    (m) Contact Ian Dargin, Aerospace Engineer, Engine Certification 
Office, FAA, Engine and Propeller Directorate, 12 New England 
Executive Park, Burlington, MA 01803; e-mail: ian.dargin@faa.gov; 
telephone (781) 238-7178, fax (781) 238-7199, for more information 
about this AD.

    Issued in Burlington, Massachusetts, on August 10, 2010.
Francis A. Favara,
Manager, Engine and Propeller Directorate, Aircraft Certification 
Service.
[FR Doc. 2010-20350 Filed 8-17-10; 8:45 am]
BILLING CODE 4910-13-P