
[Federal Register Volume 77, Number 54 (Tuesday, March 20, 2012)]
[Rules and Regulations]
[Pages 16139-16143]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2012-6500]


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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2008-1095; Directorate Identifier 2008-NE-34-AD; 
Amendment 39-16924; AD 2012-02-01]
RIN 2120-AA64


Airworthiness Directives; Pratt & Whitney (PW) Turbofan Engines

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule.

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

SUMMARY: We are adopting a new airworthiness directive (AD) for Pratt & 
Whitney (PW) PW2037, PW2037(M), and PW2040 turbofan engines with 
certain fan blades with a cutback leading edge, installed. This AD was 
prompted by reports from PW that fan blade leading edge erosion can 
result in a fan thrust deterioration mode (FTDM) condition, a condition 
that cannot be detected by the crew, and that reduces the engine's 
capability of producing required thrust. This AD requires initial and 
repetitive maintenance to the leading edge of cutback fan blades or 
applying performance decrements as specified in the Airplane Flight 
Manual.

[[Page 16140]]

We are issuing this AD to correct undetectable fan thrust deterioration 
on these PW products.

DATES: This AD is effective April 24, 2012.
    The Director of the Federal Register approved the incorporation by 
reference of certain publications listed in the AD as of April 24, 
2012.

ADDRESSES: For service information identified in this AD, contact Pratt 
& Whitney, 400 Main St., East Hartford, CT 06108; phone: (860) 565-
8770; fax: (860) 565-4503 or Boeing Commercial Airplanes, Attention: 
Data & Services Management, P.O. Box 3707, MC 2H-65, Seattle, WA 98124-
2207; phone: (206) 544-5000, extension 1; fax: (206) 766-5680; email: 
me.boecom@boeing.com; Internet: https://www.myboeingfleet.com. You may 
review copies of the referenced service information at the FAA, Engine 
& Propeller Directorate, 12 New England Executive Park, Burlington, MA. 
For information on the availability of this material at the FAA, call 
781-238-7125.

Examining the AD Docket

    You may examine the AD docket on the Internet at http://www.regulations.gov; or in person at the Docket Management Facility 
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 address for the 
Docket Office (phone: 800-647-5527) is Document Management Facility, 
U.S. Department of Transportation, Docket Operations, M-30, West 
Building Ground Floor, Room W12-140, 1200 New Jersey Avenue SE., 
Washington, DC 20590.

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

SUPPLEMENTARY INFORMATION:

Discussion

    We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR 
part 39 to include an AD that would apply to the specified products. 
That NPRM published in the Federal Register on March 25, 2010 (75 FR 
14377). That NPRM proposed to require initial and repetitive 
maintenance to restore the leading edge contour of PW2000 fan blade 
part numbers (P/Ns) 1B6531, 1B6231-001, or 1A9031-001 (fan blade set P/
Ns 1B6521, 1B6221-001, and 1A9721-001).

Comments

    We gave the public the opportunity to participate in developing 
this AD. The following presents the comments received on our proposal 
and the FAA's response to each comment.

Request for Additional Alternative Methods of Compliance (AMOCs)

    Three commenters, UPS, Cheshire Engine Center, and Delta Tech Ops, 
asked us to include Engine Manual, 1A6231, Chapter/Section 72-31-12, 
Repair-18, and PW Service Bulletin (SB) PW2000 72-513, Revision 4, 
dated August 20, 1997, as an AMOC to the AD. The commenters stated that 
Repair-18 is a bench repair that removes erosion damage and restores 
the leading edge contour on fan blades with cutback leading edges. The 
commenters stated that Repair-18 results in a restored leading edge 
similar to Repair-14, which is already included in the proposed rule as 
an AMOC. The commenters stated that Repair-14 is a patch weld repair 
used to restore the cutback leading edge.
    We agree that Repair-18 and PW SB PW2000 72-513, Revision 4, dated 
August 20, 1997 are acceptable methods of resolving the fan thrust 
deterioration. We changed paragraph (f) of the AD to include Pratt & 
Whitney PW2037, PW2040, PW2240, PW2337 Turbofan Engine Manual, Part No. 
1A6231, Chapter/Section 72-31-12, Repair-14 and Repair-18, and PW SB 
PW2000 72-513, Revision 4, dated August 20, 1997, as additional methods 
with which to comply with this AD.
    One commenter, The Boeing Company (Boeing), asked us to add 
Airplane Flight Manual (AFM) D631N007, Section 1, page 11, Code 0P00 
(Operation with Cutback Fan Blades) to the AMOC already published in 
the NPRM. The commenter stated that the performance adjustments for the 
PW2000 series engines that are installed on 757-300 airplanes are not 
in AFM D631N002, Appendix 24. They are in AFM D631N007, Section 1, Code 
0P00.
    We partially agree. We changed paragraph (f) of this AD to include 
``Boeing 757 Airplane Flight Manual (AFM), Document D631N002'' and 
``Boeing 757 Airplane Flight Manual, Document D631N007'' as additional 
methods with which to comply with this AD. We also changed paragraphs 
(f)(1)(vi) and (f)(1)(vii) of this AD to clarify that the method of 
compliance with those paragraphs is to revise the AFM. In addition, we 
changed paragraph (f)(3) of this AD to provide for removing certain 
information from the AFM when that information is included in the 
general revisions of the AFM. We coordinated all changes to the AFM 
with the FAA Transport Airplane Directorate.
    One commenter, Delta Tech Ops, asked us to include PW SB PW2000 72-
737 in the Alternative Methods of Compliance section. The commenter 
stated that PW SB PW2000 72-737 modifies the cutback fan blades 
affected by the AD to the non-cutback configuration.
    We disagree. If the cutback fan blades affected by the AD are 
modified to return them to the non-cutback configuration, they are no 
longer affected by this AD. This AD only applies to fan blade, P/Ns 
1B6531, 1B6231-001, or 1A9031-001 (fan blade set P/Ns 1B6521, 1B6221-
001, and 1A9721-001), with a cutback leading edge. We didn't change the 
AD.

Request To Clarify Compliance Time

    Two commenters, United Airlines and Delta Tech Ops, asked us to 
clarify that the AD repair doesn't have to be performed immediately if 
the blade leading edge has recently been cutback or restored. The 
commenters made this request to recognize that some blade leading edges 
have been recently cutback using PW SB PW2000 72-513 or restored using 
engine manual Repair-14 or Repair-18.
    We agree. This AD is to ensure that cutback blades are repaired 
within 1,000 cycles-in-service after the last leading edge restoration. 
We changed paragraph (f) to ``Within 500 cycles-in-service (CIS) after 
the effective date of this AD or within 1,000 CIS after the last 
leading edge restoration, whichever occurs later, do one of the 
following.''

Request To Allow Additional Cycles for the PW2037 and PW2037(M) Engines

    One commenter, United Airlines, asked us to match the compliance 
time in the AD with PW ASB PW2000 A72-729 to allow an additional 500 
CIS for the PW2037 and PW2037(M) engines as compared to the compliance 
time for the PW2040 engines.
    We disagree. The additional 500 CIS allowed for PW2037 and 
PW2037(M) engines was applicable when the alert service bulletin was 
first published in June 2008. This AD is to ensure cutback blades are 
repaired within 1,000 CIS after the last leading edge restoration. We 
didn't change the AD.

Request To Address Consequence of Performing the Cutback Leading Edge 
Repair on a Non-Cutback Blade

    One commenter, United Airlines, asked us to address the consequence 
of the cutback blade leading edge repair being mistakenly performed on 
a non-

[[Page 16141]]

cutback blade. The commenter felt that because of overlap in 
dimensional requirements, discerning a cutback blade from a non-cutback 
blade either visually or by measuring the chord length, is difficult. 
The commenter also stated that the ``cb'' marking for a cutback blade 
may become illegible after engine operation and that the cutback blade 
tooling can fit on non-cutback blades and cause damage.
    We disagree. Each operator must ensure that their personnel are 
properly trained and certificated to perform this maintenance. We 
didn't change the AD.

Eratta

    During review of the comments we received, we discovered that we 
had referred to additional methods of compliance in the NPRM as 
Alternative Methods of Compliance (AMOCs). AMOC, in the aviation 
industry, has a specific and unique meaning. We changed the compliance 
section of this AD to indicate that operators may choose from several 
corrective action(s), which are additional methods of compliance, to 
resolve the unsafe condition. We also emphasized that operators must 
choose one method and then they must use the complete method. We did 
not add or remove any requirements when we made this correction.
    We also rephrased the unsafe condition statement to clearly 
indicate the unsafe condition this AD addresses.

Conclusion

    We reviewed the relevant data, considered the comments received, 
and determined that air safety and the public interest require adopting 
the AD with the changes described previously.
    We also determined that these changes will not increase the 
economic burden on any operator or increase the scope of the AD.

Costs of Compliance

    We estimate that this AD affects 480 engines installed on airplanes 
of U.S. registry. We also estimate that it will take about 12 work-
hours 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 
$489,600 per year.

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

    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),
    (3) Will not affect intrastate aviation in Alaska, and
    (4) 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.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Incorporation by 
reference, Safety.

Adoption of the Amendment

    Accordingly, under the authority delegated to me by the 
Administrator, the FAA 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 (AD):

2012-02-01 Pratt & Whitney: Amendment 39-16924; Docket No. FAA-2008-
1095; Directorate Identifier 2008-NE-34-AD.

(a) Effective Date

    This AD is effective April 24, 2012.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to Pratt & Whitney (PW) PW2037, PW2037(M), and 
PW2040 turbofan engines with six or more fan blades, part numbers 
(P/Ns) 1B6531, 1B6231-001, or 1A9031-001 (fan blade set P/Ns 1B6521, 
1B6221-001, and 1A9721-001), with a cutback leading edge, installed.

(d) Unsafe Condition

    This AD was prompted by reports from PW that fan blade leading 
edge erosion can result in a fan thrust deterioration mode (FTDM) 
condition, a condition that cannot be detected by the crew, and that 
reduces the engine's capability of producing required thrust. We are 
issuing this AD to correct undetectable fan thrust deterioration on 
these PW products.

(e) Compliance

    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) Restoration of the Fan Blade Leading Edge Contour

    (1) Within 500 cycles-in-service (CIS) after the effective date 
of this AD or within 1,000 CIS after the last leading edge 
restoration, whichever occurs later, do one of the following. 
Whichever method you choose, you must implement the method in full.
    (i) For engines installed on the airplane, perform the initial 
restoration using Accomplishment Instructions For Engines Installed 
on Aircraft, paragraphs 1. through 1.T. of PW Alert Service Bulletin 
(ASB) PW2000 A72-729, Revision 2, dated October 13, 2010.
    (ii) For engines that are not installed on the airplane, perform 
the initial restoration using Accomplishment Instructions For 
Engines Not Installed on Aircraft, paragraphs 1. through 1.S. of PW 
ASB PW2000 A72-729, Revision 2, dated October 13, 2010.
    (iii) Perform Repair-14, dated February 1, 2006, from a Pratt & 
Whitney PW2037, PW2040, PW2240, PW2337 Turbofan Engine Manual, Part 
No. 1A6231, Chapter/Section 72-31-12.
    (iv) Perform Repair-18, dated February 1, 2004, from a Pratt & 
Whitney PW2037, PW2040, PW2240, PW2337 Turbofan Engine Manual, Part 
No. 1A6231, Chapter/Section 72-31-12.
    (v) Perform PW Service Bulletin PW2000 72-513, Revision 4, dated 
August 20, 1997.
    (vi) Revise the Limitations Section of the Boeing 757 Airplane 
Flight Manual (AFM), Document D631N002, to include the following 
limitation. This may be done by inserting a copy of this AD into the 
AFM.

[[Page 16142]]

[GRAPHIC] [TIFF OMITTED] TR20MR12.040

    (vii) Revise the Limitations Section of the Boeing 757 Airplane 
Flight Manual, Document D631N007, to include the following 
limitation. This may be done by inserting a copy of this AD into the 
AFM.
[GRAPHIC] [TIFF OMITTED] TR20MR12.041

    (2) If you chose one of the methods in paragraphs (f)(1)(i) 
through (f)(1)(v) of this AD, thereafter, within 1,000 CIS, repeat 
one of the methods in paragraphs (f)(1)(i) through (f)(1)(v) of this 
AD. Whichever method you choose, you must implement the method in 
full.
    (3) If you chose one of the methods in paragraphs (f)(1)(vi) or 
(f)(1)(vii) of this AD, you have fully complied with the 
requirements of this AD and no further action is required. When a 
statement identical to that in paragraph (f)(1)(vi) or (f)(1)(vii) 
of this AD has been included in the Limitations Section of the 
general revisions of the AFM, the general revisions may be inserted 
into the AFM, and the copy of this AD may be removed from the AFM.

(g) Alternative Methods of Compliance

    The certification office specified in paragraph (g)(1) or (g)(2) 
of this AD, as applicable, has the authority to approve AMOCs for 
this AD, if requested using the procedures found in 14 CFR 39.19.
    (1) For paragraphs (f)(1)(vi) and (f)(1)(vii) of this AD: The 
Manager, Seattle Aircraft Certification Office (ACO), FAA. Send 
information to ATTN: Chris R. Parker, Aerospace Engineer, Propulsion 
Branch, ANM-140S, FAA, Seattle ACO, 1601 Lind Avenue SW., Renton, 
Washington 98057-3356; phone: 425-917-6496; fax: 425-917-6590. 
Information may be emailed to: 9-ANM-Seattle-ACO-AMOC-Requests@faa.gov.
    (2) For requirements of paragraphs of this AD other than those 
identified in paragraph (g)(1) of this AD: The Manager, Engine 
Certification Office (ECO), FAA. Send information to ATTN: Ian 
Dargin, Aerospace Engineer, FAA, ECO, 12 New England Executive Park, 
Burlington, MA 01803; phone: (781) 238-7178; fax: (781) 238-7199.

(h) Related Information

    (i) The Boeing 757 Airplane Flight Manual, Document D631N002, 
and the Boeing 757 Airplane Flight Manual, Document D631N007 pertain 
to the subject of this AD. Contact Boeing Commercial Airplanes, 
Attention: Data & Services Management, P.O. Box 3707, MC 2H-65, 
Seattle, WA 98124-2207; phone: (206) 544-5000, extension 1; fax: 
(206) 766-5680; email: me.boecom@boeing.com; Internet: https://www.myboeingfleet.com, for a copy of this service information.
    (ii) For more information about this AD, contact Ian Dargin, 
Engine Certification Office, FAA, 12 New England Executive Park, 
Burlington, MA 01803; phone: (781) 238-7178; fax: (781) 238-7199; 
email: ian.dargin@faa.gov.

[[Page 16143]]

(i) Material Incorporated by Reference

    (1) You must use the following service information to do the 
actions required by this AD, unless the AD specifies otherwise. The 
Director of the Federal Register approved the incorporation by 
reference (IBR) of the following service information under 5 U.S.C. 
552(a) and 1 CFR part 51 on the date specified:
    (i) Pratt & Whitney Alert Service Bulletin PW2000 A72-729, 
Revision 2, dated October 13, 2010, approved for IBR April 24, 2012.
    (ii) Pratt & Whitney Service Bulletin PW2000 A72-513, Revision 
4, dated August 20, 1997, approved for IBR April 24, 2012.
    (iii) LPC First Stage Blade Assembly Repair-14, dated February 
1, 2006, of the Pratt & Whitney PW2037, PW2040, PW2240, PW2337 
Turbofan Engine Manual (``PW2000 Series Engine Manual''), Part No. 
1A6231, revision 102, dated February 1, 2012, approved for IBR April 
24, 2012.
    (iv) LPC First Stage Blade Assembly Repair-18, dated February 1, 
2004, of the Pratt & Whitney PW2037, PW2040, PW2240, PW2337 Turbofan 
Engine Manual (``PW2000 Series Engine Manual''), Part No. 1A6231, 
revision 102, dated February 1, 2012, approved for IBR April 24, 
2012.
    (2) For service information identified in this AD, contact Pratt 
& Whitney, 400 Main St., East Hartford, CT 06108; phone: (860) 565-
8770; fax: (860) 565-4503.
    (3) You may review copies of the service information at the FAA, 
12 New England Executive Park, Burlington, MA. For information on 
the availability of this material at the FAA, call 781-238-7125.
    (4) You may also review copies of the service information that 
is incorporated by reference at the National Archives and Records 
Administration (NARA). For information on the availability of this 
material at an NARA facility, call 202-741-6030, or go to http://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html.

    Issued in Burlington, Massachusetts, on January 13, 2012.
Peter A. White,
Manager, Engine & Propeller Directorate, Aircraft Certification 
Service.
Kalene C. Yanamura,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2012-6500 Filed 3-19-12; 8:45 am]
BILLING CODE 4910-13-P


