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[Federal Register: March 25, 2010 (Volume 75, Number 57)]
[Proposed Rules]               
[Page 14375-14377]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr25mr10-14]                         

=======================================================================
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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2010-0217; Directorate Identifier 2009-NE-23-AD]
RIN 2120-AA64

 
Airworthiness Directives; Pratt & Whitney (PW) PW4000 Series 
Turbofan Engines

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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SUMMARY: The FAA proposes to adopt a new airworthiness directive (AD) 
for PW PW4052, PW4056, PW4060, PW4062, PW4062A, PW4074, PW4077, 
PW4077D, PW4084D, PW4090, PW4090-3, PW4152, PW4156, PW4156A, PW4158, 
PW4164, PW4168, PW4168A, PW4460, and PW4462 turbofan engines. This 
proposed AD would require initial and repetitive fluorescent penetrant 
inspections (FPI) for cracks in the blade locking and loading slots of 
the high-pressure compressor (HPC) drum rotor disk assembly. This 
proposed AD results from reports of cracked locking and loading slots 
in the HPC drum rotor disk assembly. We are proposing this AD to detect 
cracks in the locking and loading slots in the HPC drum rotor disk 
assemblies, which could result in rupture of the HPC drum rotor disk 
assembly and damage to the airplane.

DATES: We must receive any comments on this proposed AD by May 24, 
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

[[Page 14376]]

p.m., Monday through Friday, except Federal holidays.
     Fax: (202) 493-2251.
    Contact Pratt & Whitney, 400 Main St., East Hartford, CT 06108; 
telephone (860) 565-7700; fax (860) 565-1605, for information 
identified in this proposed AD.

FOR FURTHER INFORMATION CONTACT: Rose Len, Aerospace Engineer, Engine 
Certification Office, FAA, Engine & Propeller Directorate, 12 New 
England Executive Park, Burlington, MA 01803; e-mail: rose.len@faa.gov; 
telephone (781) 238-7772; fax (781) 238-7199.

SUPPLEMENTARY INFORMATION: 

Comments Invited

    We invite you to send us any written relevant data, views, or 
arguments regarding this proposal. Send your comments to an address 
listed under ADDRESSES. Include ``Docket No. FAA-2010-0217; Directorate 
Identifier 2009-NE-23-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

    We have received reports of 294 HPC drum rotor disk assemblies that 
were removed because of cracks in the rear drum locking and loading 
slots. We determined that the cracks resulted from thermal mechanical 
fatigue. Cracks in rotating life-limited parts (LLPs), such as the HPC 
rear drum of the HPC drum rotor disk assembly, could result in rupture 
of that part.

Relevant Service Information

    We have reviewed and approved the technical contents of PW Service 
Bulletins (SBs) PW4ENG 72-796, dated June 11, 2009, PW4G-100-72-186, 
Revision 1, dated September 2, 2004, and PW4G-112-72-264, Revision 1, 
dated September 2, 2004, that describe procedures for performing a 
local FPI of the HPC drum rotor disk assembly blade locking and loading 
slots for cracks.

FAA's Determination and Requirements of the Proposed AD

    We have evaluated all pertinent information and identified an 
unsafe condition that is likely to exist or develop on other products 
of this same type design. We are proposing this AD, which would require 
performing a repetitive local FPI for cracks in the HPC drum rotor disk 
assembly blade locking and loading slots. The proposed AD would require 
you to use the service information described previously to perform 
these actions.

Interim Action

    These actions are interim actions and we may take further 
rulemaking actions in the future.

Costs of Compliance

    We estimate that this proposed AD would affect 1,038 engines 
installed on airplanes of U.S. registry. We also estimate that it would 
take about 1 work-hour per engine to perform the proposed actions, and 
that the average labor rate is $85 per work-hour. No parts are 
required. Based on these figures, we estimate the total cost of the 
proposed AD to U.S. operators to be $88,230.

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. 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.

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 adding the following new 
airworthiness directive:

Pratt & Whitney: Docket No. FAA-2010-0217; Directorate Identifier 
2009-NE-23-AD.

Comments Due Date

    (a) The Federal Aviation Administration (FAA) must receive 
comments on this

[[Page 14377]]

airworthiness directive (AD) action by May 24, 2010.

Affected ADs

    (b) None.

Applicability

    (c) This AD applies to Pratt & Whitney (PW) PW4052, PW4056, 
PW4060, PW4062, PW4062A, PW4074, PW4077, PW4077D, PW4084D, PW4090, 
PW4090-3, PW4152, PW4156, PW4156A, PW4158, PW4164, PW4168, PW4168A, 
PW4460, and PW4462 turbofan engines. These engines are installed on, 
but not limited to, Boeing 747-400, 767-200, 767-300, 777-200, and 
777-300 airplanes; McDonnell Douglas MD-11 airplanes; and Airbus 
A300-600, A310-300, and A330-200 airplanes.

Unsafe Condition

    (d) This AD results from reports of cracked locking and loading 
slots in the high-pressure compressor (HPC) drum rotor disk 
assembly. We are issuing this AD to detect cracks in the locking and 
loading slots in the HPC drum rotor disk assemblies, which could 
result in rupture of the HPC drum rotor disk assembly 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.

Local Fluorescent Penetrant Inspection

    (f) Perform a local fluorescent penetrant inspection for cracks 
in the HPC drum rotor disk assembly blade locking and loading slots 
of the specific stages of the HPC drum rotor disk assemblies from 
which any of the blades are removed as specified in Table 1 of this 
AD.

     Table 1--Compliance Times and Service Bulletins by Engine Model
------------------------------------------------------------------------
      For engine model         Inspect whenever--           Use--
------------------------------------------------------------------------
(1) PW4074, PW4077, PW4077D,  Any of the 13th or    Paragraphs 1.A.
 PW4084D, PW4090, and PW4090-  14th stage blades     through 1.B. of the
 3.                            are removed during    Accomplishment
                               a shop visit.         Instructions of
                                                     PW4G-112-72-264,
                                                     Revision 1, dated
                                                     September 2, 2004.
(2) PW4164, PW4168, and       Any of the 13th,      Paragraphs 1.A.
 PW4168A.                      14th, or 15th stage   through 1.C of the
                               blades are removed    Accomplishment
                               during a shop visit.  Instructions of
                                                     PW4G-100-72-186,
                                                     Revision 1, dated
                                                     September 2, 2004.
(3) PW4052, PW4056, PW4060,   Any of the 13th,      Paragraphs 1.A.
 PW4062, PW4062A, PW4152,      14th, or 15th stage   through 1.C. of the
 PW4156, PW4156A, PW4158,      blades are removed    Accomplishment
 PW4460, and PW4462.           during a shop visit.  Instructions of
                                                     PW4ENG 72-796,
                                                     dated June 11,
                                                     2009.
------------------------------------------------------------------------

     (g) Remove from service any HPC drum rotor disk assembly found 
with a crack in the blade loading and locking slots of the HPC drum 
rotor disk assembly.

Alternative Methods of Compliance

    (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.

Related Information

    (i) Contact Rose Len, Aerospace Engineer, Engine Certification 
Office, FAA, Engine & Propeller Directorate, 12 New England 
Executive Park, Burlington, MA 01803; e-mail: rose.len@faa.gov; 
telephone (781) 238-7772; fax (781) 238-7199, for more information 
about this AD.
    (j) Pratt & Whitney Service Bulletins PW4ENG 72-796, dated June 
11, 2009, PW4G-100-72-186, Revision 1, dated September 2, 2004, and 
PW4G-112-72-264, Revision 1, dated September 2, 2004, pertain to the 
subject of this AD. 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.

    Issued in Burlington, Massachusetts, on March 16, 2010.
Francis A. Favara,
Manager, Engine and Propeller Directorate, Aircraft Certification 
Service.
[FR Doc. 2010-6581 Filed 3-24-10; 8:45 am]
BILLING CODE 4910-13-P
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