AD 2014-05-32

[Federal Register Volume 79, Number 61 (Monday, March 31, 2014)]
[Rules and Regulations]
[Pages 17856-17859]
From the Federal Register Online via the Government Publishing Office [<a href="http://www.gpo.gov">www.gpo.gov</a>]
[FR Doc No: 2014-06953]


=======================================================================
-----------------------------------------------------------------------

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2013-0740; Directorate Identifier 2013-NE-24-AD; 
Amendment 39-17804; AD 2014-05-32]
RIN 2120-AA64


Airworthiness Directives; Pratt & Whitney Turbofan Engines

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule.

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

SUMMARY: We are adopting a new airworthiness directive (AD) for all 
Pratt & Whitney (PW) PW2037, PW2037D, PW2037M, PW2040, PW2040D, PW2043, 
PW2146, PW2240, PW2337, PW2643, and F117-PW-100 turbofan engines. This 
AD was prompted by a rupture of the diffuser-to-high-pressure turbine 
(HPT) case flange. This AD requires a one-time eddy current inspection 
(ECI) of affected engines with certain diffuser and HPT cases 
installed. This AD also requires a fluorescent-penetrant inspection 
(FPI) of the diffuser case rear flange and HPT case front flange. We 
are issuing this AD to prevent failure of the diffuser-to-HPT case 
flange, which could lead to uncontained engine failure and damage to 
the airplane.

DATES: This AD is effective May 5, 2014.
    The Director of the Federal Register approved the incorporation by 
reference of a certain publication listed in this AD as of May 5, 2014.

[[Page 17857]]


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. You may view this 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 <a href="http://www.regulations.gov">http://www.regulations.gov</a> by searching for and locating Docket No. FAA-2013-
0740; 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: Mark Riley, Aerospace Engineer, Engine 
Certification Office, FAA, Engine & Propeller Directorate, 12 New 
England Executive Park, Burlington, MA 01803; phone: 781-238-7758; fax: 
781-238-7199; email: <a href="/cdn-cgi/l/email-protection#462b27342d68342f2a233f0620272768212930"><span class="__cf_email__" data-cfemail="8ce1edfee7a2fee5e0e9f5cceaededa2ebe3fa">[email&#160;protected]</span></a>.

SUPPLEMENTARY INFORMATION:

Discussion

    We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR 
part 39 by adding an AD that would apply to all PW PW2037, PW2037D, 
PW2037M, PW2040, PW2040D, PW2043, PW2146, PW2240, PW2337, PW2643, and 
F117-PW-100 turbofan engines. The NPRM published in the Federal 
Register on October 29, 2013 (78 FR 64419). The NPRM was prompted by a 
rupture of the diffuser-to-HPT case flange. The NPRM proposed to 
require a one-time ECI of affected engines with certain diffuser and 
HPT cases installed and an FPI of the diffuser case rear flange and HPT 
case front flange. We are issuing this AD to prevent failure of the 
diffuser-to-HPT case flange, which could lead to uncontained engine 
failure and damage to the airplane.

Comments

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

Request Credit for FPI at Piece Part Level

    Delta Air Lines (DAL), PW, Federal Express, and United Parcel 
Service (UPS) requested that previous FPI of cases at the piece part 
level be allowed for AD compliance in lieu of ECI. The justification 
for this request is that FPI of diffuser/HPT cases at the piece part 
level performed after January 1, 2010 are equivalent to the ECI 
procedures.
    We agree. We changed the AD to allow credit for FPI of diffuser and 
HPT cases performed after January 1, 2010.

Request to Eliminate Initial Inspection and Mandated Repetitive 
Inspections

    DAL and PW requested elimination of inspection for diffuser/HPT 
cases identified in Table 1 to paragraph (e) of this AD because the 
inspections have already been completed. DAL and PW also requested that 
mandated repetitive inspections of the diffuser and HPT case be 
eliminated since this requirement is already in the engine manual and 
part of DAL's PW2000 maintenance program. Mandated inspection results 
in a quality records burden. The AD is requested to be withdrawn based 
on these requested actions.
    We partially agree. We agree that many of the diffuser/HPT case 
inspections have been completed. PW reports that all diffuser and HPT 
cases have been inspected except for three. Those three cases are 
installed on engines not currently in service. We changed the AD to 
eliminate Table 1 to paragraph (e) of this AD. We added the remaining 
diffuser cases and HPT cases requiring inspection to paragraph (e) of 
this AD.
    We do not agree that mandated inspections for the diffuser and HPT 
cases are not required as diffuser or HPT case failure may result in a 
catastrophic aircraft event. We did not change the AD requirement for 
repetitive inspections. This AD will not be withdrawn.

Request to Exclude F117-PW-100 Requirements

    PW requested that F117-PW-100 requirements not be included in this 
AD as the inspections will be completed by December 2013.
    We partially agree. We received confirmation that the diffuser and 
HPT cases that are applicable to F117-PW-100 engines have been 
inspected. However, since the F117-PW-100 engine model has been 
certified by the FAA and is on the type certificate data sheet, we will 
require repetitive FPI of the diffuser and HPT cases at piece part 
opportunity. We changed this AD by deleting diffuser and HPT cases that 
have been inspected.

Request Definition for Piece Part Exposure

    DAL, UPS, and an individual commenter requested that a definition 
be provided for ``piece part exposure'' as it applies to repetitive 
inspections of diffuser and HPT cases. The reason for this request was 
to clarify when inspections are required.
    We agree. We added a definition for ``piece part exposure'' in this 
AD.

Request for New Compliance Method

    DAL requested that the compliance requirement for repetitive 
inspections direct operator's to revise their approved maintenance 
programs with an FPI of the diffuser and HPT cases and not require 
documenting AD compliance for each individual case. This change would 
help to eliminate undue burden on operator/maintenance facility for AD 
tracking requirements.
    We partially agree. We agree that changing the continuous 
airworthiness maintenance program (CAMP) to require diffuser and HPT 
case inspections adequately addresses our safety concerns.
    We do not agree that tracking repetitive inspections to show AD 
compliance is an undue burden. We changed the AD by adding an Optional 
Terminating Action allowing diffuser and HPT case inspections to be 
added to the CAMP to satisfy repetitive inspection requirements of this 
AD.

Request FAA Standard Practices, Processes, Consumables, and Standard 
Tooling be Allowed to Perform ECI

    One individual commenter requested that only Non-destructive 
Inspection Procedure sections IX through XVIII be mandated as these 
sections contain the only items that have an actual effect on the 
unsafe condition of the AD.
    We disagree. The specific ECI inspection equipment and procedures 
developed by PW have been verified as being able to detect cracks in 
the diffuser case and HPT case M-flange. The specific equipment and 
procedures must be used to ensure proper inspection results. However, 
operators and maintenance facilities can propose use of other equipment 
and/or procedures as an alternative method of compliance if they can 
validate equivalent results. We did not change this AD.

Request Clarification for Applicability

    The same individual commenter requested clarification that the 
Compliance paragraph apply to all HPT

[[Page 17858]]

and diffuser cases regardless of whether they are listed in Table 1 to 
paragraph (e) or not. The reason for this request is that it is unclear 
if the repetitive inspections are required only for those cases 
specified in Table 1.
    We agree. We deleted Table 1 to paragraph (e) of this AD and added 
the remaining diffuser cases and HPT cases requiring inspection to 
paragraph (e) of this AD.

Conclusion

    We reviewed the relevant data, considered the comments received, 
and determined that air safety and the public interest require adopting 
this AD with the changes described previously and minor editorial 
changes. We have determined that these changes:
    <bullet> [Agr]re consistent with the intent that was proposed in 
the NPRM (78 FR 64419, October 29, 2013) for correcting the unsafe 
condition; and
    <bullet> Do not add any additional burden upon the public than was 
already proposed in the NPRM (78 FR 64419, October 29, 2013).
    We also determined that these changes will not increase the 
economic burden on any operator or increase the scope of this AD.

Costs of Compliance

    We estimate that this AD will affect 638 engines installed on 
airplanes of U.S. registry. Of the 638 engines, we estimate that about 
3 engines will be subject to ECI and all engines will be subject to the 
FPI. We also estimate that it will take about 5 hours to perform the 
ECI and 3 hours to perform the FPI required by this AD. Materials cost 
for the FPI will be about $20 per engine. The average labor rate is $85 
per hour. Based on these figures, we estimate the total cost of this AD 
to U.S. operators is $176,725.

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 to the extent 
that it justifies making a regulatory distinction, 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):

2014-05-32 Pratt & Whitney: Amendment 39-17804 Docket No. FAA-2013-
0740; Directorate Identifier 2013-NE-24-AD.

(a) Effective Date

    This AD is effective May 5, 2014.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to all Pratt & Whitney (PW) PW2037, PW2037D, 
PW2037M, PW2040, PW2040D, PW2043, PW2146, PW2240, PW2337, PW2643, 
and F117-PW-100 turbofan engines.

(d) Unsafe Condition

    This AD was prompted by a rupture of the diffuser-to-high-
pressure turbine (HPT) case flange. We are issuing this AD to 
prevent failure of the diffuser-to-HPT case flange, which could lead 
to uncontained engine failure and damage to the airplane.

(e) Compliance

    Unless already done, comply with this AD within the compliance 
times specified.
    (1) For diffuser case part number (P/N) 1B7461, serial numbers 
(S/Ns) DGGUAK1306 and DGGUAK1308, and HPT case P/N 1B2440, S/N 
DKLBCS1032:
    (i) Within 100 flight cycles or 30 days after the effective date 
of this AD, whichever is later, eddy current inspect (ECI) the 
diffuser case and the HPT case M-flange. Use PW Service Bulletin 
(SB) No. PW2000 72-763, Revision 1, dated August 30, 2013, to do the 
inspection.
    (ii) Reserved.
    (2) For all diffuser and HPT cases at the next piece part 
opportunity and every piece part opportunity thereafter, perform a 
high sensitivity fluorescent-penetrant inspection (FPI) of the 
entire diffuser case rear flange (M-flange) and bolt holes, and the 
entire HPT case forward flange (M-flange) and bolt holes.

(f) Optional Terminating Action

    As a terminating action to the repetitive inspection 
requirements of this AD, you may insert the repetitive inspection 
requirement identified in paragraph (e)(2) of this AD into the 
required inspection portion of your continuous airworthiness 
maintenance program.

(g) Definition

    For the purpose of this AD, piece part opportunity is defined as 
when the part is completely disassembled.

(h) Prohibition Statement

    After the effective date of this AD, do not install any engine 
with a diffuser or HPT case onto any airplane that was not inspected 
using paragraph (e) of this AD.

(i) Credit for Previous Actions

    If you performed an ECI of the diffuser case and HPT case M-
flange using the Accomplishment Instructions of PW SB No. PW2000 72-
763, dated March 22, 2013, or you performed a high sensitivity FPI 
of the diffuser case and HPT case at the piece part opportunity 
after January 1, 2010, you met the requirements of paragraph (e)(1) 
of this AD.

(j) Alternative Methods of Compliance (AMOCs)

    The Manager, Engine Certification Office, FAA, may approve AMOCs 
for this AD. Use the procedures found in 14 CFR 39.19 to make your 
request.

(k) Related Information

    (1) For more information about this AD, contact Mark Riley, 
Aerospace Engineer, Engine Certification Office, FAA, Engine & 
Propeller Directorate, 12 New England Executive Park, Burlington, MA 
01803; phone: 781-238-7758; fax: 781-238-7199; email: 
<a href="/cdn-cgi/l/email-protection#fe939f8c95d08c97929b87be989f9fd0999188"><span class="__cf_email__" data-cfemail="0b666a7960257962676e724b6d6a6a256c647d">[email&#160;protected]</span></a>.

[[Page 17859]]

    (2) Pratt & Whitney Engine Manual, P/N 1A6231, (PW2000) and P/N 
1B2412 (F117), Chapter 72-41-00, Inspection/Check-02, (Task 72-41-
00-230-002) and Chapter 72-52-00, Inspection/Check-02 (Task 72-52-
00-230-000), which are not incorporated by reference in this AD, can 
be obtained from Pratt & Whitney, using the contact information in 
paragraph (l)(3) of this AD.

(l) Material Incorporated by Reference

    (1) The Director of the Federal Register approved the 
incorporation by reference (IBR) of the service information listed 
in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51.
    (2) You must use this service information as applicable to do 
the actions required by this AD, unless the AD specifies otherwise.
    (i) Pratt & Whitney Service Bulletin No. PW2000 72-763, Revision 
1, dated August 30, 2013.
    (ii) Reserved
    (3) For PW service information identified in this AD, contact 
Pratt & Whitney, 400 Main St., East Hartford, CT 06108; phone: 860-
565-8770; fax: 860-565-4503.
    (4) You may view this 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.
    (5) You may view this service information 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: 
<a href="http://www.archives.gov/federal-register/cfr/ibr-locations.html">http://www.archives.gov/federal-register/cfr/ibr-locations.html</a>.

    Issued in Burlington, Massachusetts, on March 6, 2014.
Colleen M. D'Alessandro,
Assistant Directorate Manager, Engine & Propeller Directorate, Aircraft 
Certification Service.
[FR Doc. 2014-06953 Filed 3-28-14; 8:45 am]
BILLING CODE 4910-13-P