[Federal Register Volume 75, Number 176 (Monday, September 13, 2010)]
[Rules and Regulations]
[Pages 55459-55461]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2010-21869]


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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; 
Amendment 39-16427; AD 2010-18-13]
RIN 2120-AA64


Airworthiness Directives; Pratt & Whitney (PW) PW4000 Series 
Turbofan Engines

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule.

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SUMMARY: The FAA is adopting a new airworthiness directive (AD) for PW 
PW4052, PW4056, PW4060, PW4062, PW4062A, PW4074, PW4077, PW4077D, 
PW4084D, PW4090, PW4090-3, PW4152, PW4156A, PW4158, PW4164, PW4168, 
PW4168A, PW4460, and PW4462 turbofan engines. This AD requires 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 AD results from reports of cracked 
locking and loading slots in the 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.

DATES: This AD becomes effective October 18, 2010. The Director of the 
Federal Register approved the incorporation by reference of certain 
publications listed in the regulations as of October 18, 2010.

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.
    The Docket Operations office is located at Docket Management 
Facility, U.S. Department of Transportation, 1200 New Jersey Avenue, 
SE., West Building Ground Floor, Room W12-140, Washington, DC 20590-
0001.

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: <a href="/cdn-cgi/l/email-protection#f4869b8791da98919ab4929595da939b82"><span class="__cf_email__" data-cfemail="1b6974687e35777e755b7d7a7a357c746d">[email protected]</span></a>; 
telephone (781) 238-7772; fax (781) 238-7199.

SUPPLEMENTARY INFORMATION: The FAA proposed to amend 14 CFR part 39 
with a proposed AD. The proposed AD applies to PW PW4000 series 
turbofan engines. We published the proposed AD in the Federal Register 
on March 25, 2010 (75 FR 14375). That action proposed to require 
initial and repetitive FPI for cracks in the blade locking and loading 
slots of the HPC drum rotor disk assembly.

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 AD, the regulatory evaluation, 
any comments received, and other information. The street address for 
the Docket Operations office (telephone (800) 647-5527) is provided in 
the ADDRESSES section. Comments will be available in the AD docket 
shortly after receipt.

Comments

    We provided the public the opportunity to participate in the 
development of this AD. We have considered the comments received.

Concur With the AD as Proposed

    Two commenters, United Services and Boeing, concurred with the AD 
as proposed.

Request To Reference the Latest Service Bulletin (SB)

    One commenter, a private citizen, requested that we reference the 
latest SB in the AD, which is Pratt & Whitney SB No. PW4G-112-72-264, 
Revision 2, dated February 23, 2010.
    We agree. We changed the AD to use the most current version of the 
SB.

Request To Change the Inspection Compliance Time

    One commenter, Delta Tech Ops, requested that we change the 
inspection compliance time to be done only when all of the blades of a 
specific stage are removed, rather than when any of the blades from a 
specific stage are removed, as written in the proposed AD. The 
commenter states that doing the inspection when any blades are removed 
is an added maintenance burden.
    We do not agree. Our risk assessment establishes that, because the 
rotating life-limited parts addressed by this AD action have a known 
cracking problem, the parts must be inspected at the times stated in 
the AD. Inspection can be done without removing all of the blades, by 
sliding remaining installed blades to expose the locking and loading 
slots for local fluorescent penetrant inspection. We did not change the 
AD.

Engine Model Removed

    Since we issued the proposed AD, we became aware that we 
inadvertently listed engine model PW4156. We removed that engine model 
from the AD.

Conclusion

    We have carefully reviewed the available data, including the 
comments received, and determined that air safety and the public 
interest require adopting the AD with the changes described previously. 
We have determined that these changes will neither increase the 
economic burden on any operator nor increase the scope of the AD.

Costs of Compliance

    We estimate that this AD will affect 1,038 engines installed on 
airplanes of U.S. registry. We also estimate that it will take about 1 
work-hour per engine to perform the 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 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.

[[Page 55460]]

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;
    (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
Accordingly, under the authority delegated to me by the Administrator, 
the Federal Aviation Administration amends 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 adding the following new airworthiness 
directive:

2010-18-13 Pratt & Whitney: Amendment 39-16427. Docket No. FAA-2010-
0217; Directorate Identifier 2009-NE-23-AD.

Effective Date

    (a) This airworthiness directive (AD) becomes effective October 
18, 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, 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 2, dated
                                                     February 23, 2010.
(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
 PW4156A, PW4158, PW4460,      blades are removed    Accomplishment
 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: <a href="/cdn-cgi/l/email-protection#493b263a2c67252c27092f2828672e263f"><span class="__cf_email__" data-cfemail="e694899583c88a8388a6808787c8818990">[email protected]</span></a>; 
telephone (781) 238-7772; fax (781) 238-7199, for more information 
about this AD.

Material Incorporated by Reference

    (j) You must use the service information specified in the 
following Table 2 to perform the inspections required by this AD. 
The Director of the Federal Register approved the incorporation by 
reference of the documents listed in the following Table 2 in 
accordance with 5 U.S.C. 552(a) and 1 CFR part 51. 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, 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 2--Incorporation by Reference
----------------------------------------------------------------------------------------------------------------
 Pratt & Whitney Service Bulletin
               No.                         Page                Revision                       Date
----------------------------------------------------------------------------------------------------------------
PW4G-100-72-186; Total Pages: 11.  ALL.................  1...................  September 2, 2004.
PW4G-112-72-264; Total Pages: 11.  ALL.................  2...................  February 23, 2010.
PW4ENG 72-796; Total Pages: 22...  ALL.................  Original............  June 11, 2009.
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[[Page 55461]]

    Issued in Burlington, Massachusetts, on August 26, 2010.
Thomas A. Boudreau,
Acting Manager, Engine and Propeller Directorate, Aircraft 
Certification Service.

[FR Doc. 2010-21869 Filed 9-10-10; 8:45 am]
BILLING CODE 4910-13-P


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