[Federal Register Volume 81, Number 246 (Thursday, December 22, 2016)]
[Proposed Rules]
[Pages 93855-93857]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2016-30114]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2013-0740; Directorate Identifier 2013-NE-24-AD]
RIN 2120-AA64


Airworthiness Directives; Pratt & Whitney Turbofan Engines

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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SUMMARY: We propose to supersede Airworthiness Directive (AD) 2014-05-
32, which applies to all Pratt & Whitney (PW) PW2037, PW2037D, PW2037M, 
PW2040, PW2040D, PW2043, PW2143, PW2643, and F117-PW-100 turbofan 
engines. AD 2014-05-32 currently requires one-time eddy current 
inspection (ECI) of affected engines with certain diffuser and HPT 
cases installed. AD 2014-05-32 also requires a fluorescent-penetrant 
inspection (FPI) of the diffuser case rear flange and the HPT case 
front flange. Since we issued AD 2014-05-32, the manufacturer 
determined through analysis that the inspections required by AD 2014-
05-32 are not adequate to maintain safety. This proposed AD would add 
additional repetitive, on-wing ECI inspections. We are proposing this 
AD to correct the unsafe condition on these products.

DATES: We must receive comments on this proposed AD by February 6, 
2017.

ADDRESSES: You may send comments, using the procedures found in 14 CFR 
11.43 and 11.45, by any of the following methods:
     Federal eRulemaking Portal: Go to http://www.regulations.gov. Follow the instructions for submitting comments.
     Fax: 202-493-2251.
     Mail: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue SE., Washington, DC 20590.
     Hand Delivery: Deliver to Mail address above between 9 
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
    For service information identified in this NPRM, 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, 1200 District Avenue, 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 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 proposed AD, the regulatory evaluation, any comments 
received, and other information. The street address for the Docket 
Office (phone: 800-647-5527) is in the ADDRESSES section. Comments will 
be available in the AD docket shortly after receipt.

FOR FURTHER INFORMATION CONTACT: Brian Kierstead, Aerospace Engineer, 
Engine Certification Office, FAA, Engine & Propeller Directorate, 1200 
District Avenue, Burlington, MA 01803; phone: 781-238-7772; fax: 781-
238-7199; email: [email protected].

SUPPLEMENTARY INFORMATION: 

Comments Invited

    We invite you to send any written relevant data, views, or 
arguments about this proposed AD. Send your comments to an address 
listed under the ADDRESSES section. Include ``Docket No. FAA-2013-0740; 
Directorate Identifier 2013-NE-24-AD'' at the beginning of your 
comments. We specifically invite comments on the overall regulatory, 
economic, environmental, and energy aspects of this proposed AD. We 
will consider all comments received by the closing date and may amend 
this proposed AD because 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 we 
receive about this proposed AD.

[[Page 93856]]

Discussion

    On March 6, 2014, we issued AD 2014-05-32, Amendment 39-17804 (79 
FR 17856, March 31, 2014), (``AD 2014-05-32''), for all PW PW2037, 
PW2037D, PW2037M, PW2040, PW2040D, PW2043, PW2143, PW2643, and F117-PW-
100 turbofan engines. AD 2014-05-32 requires a one-time ECI of affected 
engines with certain diffuser and HPT cases installed. AD 2014-05-32 
also requires an FPI of the diffuser case rear flange and HPT case 
front flange. AD 2014-05-32 resulted from a rupture of the diffuser-to-
HPT case flange. We issued AD 2014-05-32 to prevent failure of the 
diffuser-to-HPT case flange, which could lead to uncontained engine 
failure and damage to the airplane.

Actions Since AD 2014-05-32 Was Issued

    Since we issued AD 2014-05-32, the manufacturer identified a 
subpopulation of diffuser cases installed on the affected engines with 
a repaired flange that has a lower fatigue capability. The repaired 
flange cannot be distinguished from non-repaired flanges on diffuser 
cases installed on the affected engines. We determined, therefore, that 
the inspections required by AD 2014-05-32 are not adequate to maintain 
safety. To correct this unsafe condition, we are now proposing 
additional, repetitive ECI inspections.

Related Service Information Under 1 CFR Part 51

    We reviewed PW Service Bulletin No. PW2000 72-763, Revision No. 1, 
dated August 30, 2013; and PW Alert Service Bulletin No. PW2000 A72-
765, Revision No. 1, dated July 13, 2016. This service information 
describes procedures for a one-time ECI inspection of the engine 
diffuser case and the HPT case, and repetitive on-wing ECIs of the 
engine diffuser case assembly, respectively. This service information 
is reasonably available because the interested parties have access to 
it through their normal course of business or by the means identified 
in the ADDRESSES section.

FAA's Determination

    We are proposing this AD because we evaluated all the relevant 
information and determined the unsafe condition described previously is 
likely to exist or develop in other products of the same type design.

Proposed AD Requirements

    This proposed AD would retain the requirements of AD 2014-05-32 
except it would eliminate the Prohibition Statement. We determined that 
this statement is unnecessary for compliance with the AD. In addition, 
this proposed AD would require repetitive, on-wing ECI inspections. 
This proposed AD would also remove the PW2240 and PW2337 engines from 
the applicability section since these engines were removed from PW Type 
Certificate Number E17NE.

Costs of Compliance

    We estimate that this proposed AD will affect 910 engines installed 
on airplanes of U.S. registry.
    We estimate the following costs to comply with this proposed AD:

                                                 Estimated Costs
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                                                                                                 Cost on U.S.
              Action                    Labor cost        Parts cost      Cost per product        operators
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On-wing/module ECI Inspection....  8 work-hours x $85               $0  $680...............  $230,520 per
                                    per hour = $680.                                          inspection cycle.
FPI Inspection...................  3 work-hours x $85               20  $275 per inspection  $250,250 per
                                    per hour = $255.                     cycle.               inspection cycle.
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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 
regulation:
    (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),
    (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.

The Proposed Amendment

    Accordingly, under the authority delegated to me by the 
Administrator, the FAA proposes to amend 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 removing Airworthiness Directive (AD) 
2014-05-32, Amendment 39-17804 (79 FR 17856, March 31, 2014), and 
adding the following new AD:

Pratt & Whitney: Docket No. FAA-2013-0740; Directorate Identifier 
2013-NE-24-AD.

(a) Comments Due Date

    The FAA must receive comments on this AD action by February 6, 
2017.

[[Page 93857]]

(b) Affected ADs

    This AD replaces AD 2014-05-32, Amendment 39-17804 (79 FR 17856, 
March 31, 2014).

(c) Applicability

    This AD applies to all Pratt & Whitney (PW) PW2037, PW2037D, 
PW2037M, PW2040, PW2040D, PW2043, PW2143, PW2643, and F117-PW-100 
turbofan engines.

(d) Subject

    Joint Aircraft System Component (JASC) Code 72, Turbine/
Turboprop Engine.

(e) 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.

(f) 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 May 5, 2014, 
whichever is later, eddy current inspect the diffuser case and the 
HPT case M-flange. Use PW Service Bulletin (SB) No. PW2000 72-763, 
Revision No. 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.
    (3) For diffuser cases that have not incorporated PW SB PW2000-
72-364 or have incorporated either PW SB PW2000-72-700 or PW2000 
Series Engine Manual, Repair-28, Task 72-41-01-300-028 (M-flange 
replacement), perform initial and repetitive eddy current 
inspections (ECIs) of the M-flange of the diffuser case in 
accordance with paragraph (f)(4) of this AD.
    (4) Use, as applicable, either the Accomplishment Instructions, 
``For Engines Installed on the Aircraft,'' paragraphs 3.(I) through 
3.(J), or the Accomplishment Instructions, ``For Engines Removed 
from the Aircraft,'' paragraphs 3.(D) through 3.(E), of PW Alert 
Service Bulletin (ASB) No. PW2000 A72-765, Revision No. 1, dated 
July 13, 2016, to do the ECI as follows:
    (i) Perform an initial inspection within the following period, 
whichever occurs later:
    (A) Within 5,500 cycles since new or since M-flange replacement, 
or
    (B) Within 2,500 cycles since last piece-part FPI inspection, or
    (C) Within 500 cycles from the effective date of this AD.
    (ii) If no crack indications are found, re-inspect within 2,500 
cycles since last ECI or last piece-part FPI inspection, whichever 
occurs first.
    (iii) If crack indications are found, measure the crack length 
and determine the re-inspect interval in accordance with:
    (A) Paragraphs 5.(C) through 5.(D) of PW ASB No. PW2000 A72-765, 
Revision No. 1, dated July 13, 2016, ``For Engines Installed on the 
Aircraft''; or
    (B) Paragraphs 4.(C) through 4.(D) of PW ASB No. PW2000 A72-765, 
Revision No. 1, dated July 13, 2016, ``For Engines Removed from the 
Aircraft.''
    (iv) Remove from service diffuser cases with cracks exceeding 
0.170 inches.

(g) Definition

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

(h) 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, Revision No. 1, dated August 13, 2013, or an earlier version, 
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 (f)(1) of this AD.

(i) 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. You may email your request to: [email protected].

(j) Related Information

    (1) For more information about this proposed AD, contact Brian 
Kierstead, Aerospace Engineer, Engine Certification Office, FAA, 
Engine & Propeller Directorate, 1200 District Avenue, Burlington, MA 
01803; phone: 781-238-7772; fax: 781-238-7199; email: 
[email protected].
    (2) PW SB No. PW2000 72-763, Revision No. 1, dated August 30, 
2013; and PW ASB No. PW2000 A72-765, Revision No. 1, dated July 13, 
2016, can be obtained from PW using the contact information in 
paragraph (j)(3) of this AD.
    (3) For service information identified in this proposed AD, 
contact Pratt & Whitney, United Technologies Corporation, 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, 1200 District Avenue, Burlington, MA. For 
information on the availability of this material at the FAA, call 
781-238-7125.

    Issued in Burlington, Massachusetts, on December 1, 2016.
Colleen M. D'Alessandro,
Manager, Engine & Propeller Directorate, Aircraft Certification 
Service.
[FR Doc. 2016-30114 Filed 12-21-16; 8:45 am]
 BILLING CODE 4910-13-P