
[Federal Register: August 18, 2010 (Volume 75, Number 159)]
[Proposed Rules]               
[Page 50942-50945]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr18au10-33]                         

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2010-0593; Directorate Identifier 98-ANE-48-AD]
RIN 2120-AA64s

 
Airworthiness Directives; Pratt & Whitney JT8D-7, -7A, -7B, -9, -
9A, -11, -15, -15A, -17, -17A, -17R, and -17AR Series Turbofan Engines

AGENCY: Federal Aviation Administration (FAA), DOT.

[[Page 50943]]


ACTION: Notice of proposed rulemaking (NPRM).

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SUMMARY: The FAA proposes to supersede an existing airworthiness 
directive (AD) for Pratt & Whitney (PW) JT8D-1, -1A, -1B, -7, -7A, -7B, 
-9, -9A, -11, -15, -15A, -17, -17A, -17R, and -17AR series 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 proposed AD would modify the TLS of the manufacturer's engine 
manual and an air carrier's approved continuous airworthiness 
maintenance program to incorporate additional inspection requirements 
and reduce the model applicability. 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 
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 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-2010-0593; Directorate 
Identifier 98-ANE-48-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 December 1, 2005, the FAA issued AD 2005-25-05, Amendment 39-
14398 (70 FR 73361, December 12, 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.

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.

Removal of Obsolete Engine Models

    Also since the issuance of that AD, PW notified us that engine 
models JT8D-1, -1A, and -1B, have either been converted to other 
affected engine models or retired from service.

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-7, -7A, -7B, -9, -9A, -11, -15, -15A, 
-17, -17A, -17R, and -17AR series turbofan engines of the same type 
design, the proposed AD would supersede AD 2005-25-05 to add new 
inspection methods for 1st stage compressor hubs, 3rd stage turbine 
disks, and 4th stage turbine disks, and would remove the -1, -1A, and -
1B engine models from the applicability. For reference, this proposed 
AD carries forward the requirements from AD 2005-25-05. 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 1,527 JT8D -7, -7A, 
-7B, -9, -9A, -11, -15, -15A, -17, -17A, -17R, and -17AR series 
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 $1,297,950.

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

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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 39-14398 (70 FR 
73361, December 12, 2005) and by adding a new airworthiness directive 
to read as follows:

Pratt & Whitney: Docket No. FAA-2010-0593; Directorate Identifier 
98-ANE-48-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 2005-25-05, Amendment 39-14398.

Applicability

    (c) This AD applies to Pratt & Whitney (PW) JT8D-7, -7A, -7B, -
9, -9A, -11, -15, -15A, -17, -17A, -17R, and -17AR series turbofan 
engines. These engines are installed on, but not limited to Boeing 
727 and 737 series, and McDonnell Douglas DC-9 series airplanes.

Unsafe Condition

    (d) This AD results from the need to require enhanced inspection 
of selected critical life-limited parts of PW JT8D series 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 481672, as appropriate for PW JT8D-7, -
7A, -7B, -9, -9A, -11, -15, -15A, -17, -17A, -17R, and -17AR series 
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 has 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 was not damaged or 
related to the cause for its removal from the engine.
    (3) The inspections specified in this paragraph do not replace 
or make not necessary 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.


------------------------------------------------------------------------
          Description              Section          Inspection No.
------------------------------------------------------------------------
Hub (Disk), 1st Stage
 Compressor:
    * Hub Detail--All P/Ns.....     72-33-31  -03, -04, -05, -06
    * Hub Assembly--All P/Ns...     72-33-31  -03, -04, -05, -06
2nd Stage Compressor:
    Disk--All P/Ns.............     72-33-33  -02, -03
    Disk Assembly--All P/Ns....     72-33-33  -02, -03
Disk, 13th Stage Compressor--       72-36-47  -02
 All P/Ns.
HP Turbine Disk, First Stage w/     72-52-04  -03
 integral Shaft--All P/Ns.
HP Turbine, First Stage, w/
 separable Shaft:
    Rotor Assembly--All P/Ns...     72-52-02  -04
    Disk--All P/Ns.............     72-52-02  -03
Disk, 2nd Stage Turbine--All P/     72-53-16  -02
 Ns.
* Disk, 3rd Stage Turbine--All      72-53-17  -02, -03
 P/Ns.
* Disk (Separable), 4th Stage       72-53-15  -02, -03
 Turbine--All P/Ns.
Disk (Integral Disk/Hub), 4th       72-53-18  -02''
 Stage Turbine--All P/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)

[[Page 50945]]

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 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.
    (l) These record keeping 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 6, 2010.
Peter A. White,
Assistant Manager, Engine and Propeller Directorate, Aircraft 
Certification Service.
[FR Doc. 2010-20351 Filed 8-17-10; 8:45 am]
BILLING CODE 4910-13-P

