81 FR 93855 - Airworthiness Directives; Pratt & Whitney Turbofan Engines

DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration

Federal Register Volume 81, Issue 246 (December 22, 2016)

Page Range		93855-93857
FR Document		2016-30114

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.

Federal Register, Volume 81 Issue 246 (Thursday, December 22, 2016)

[Federal Register Volume 81, Number 246 (Thursday, December 22, 2016)]
[Proposed Rules]
[Pages 93855-93857]
From the Federal Register Online  [www.thefederalregister.org]
[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).

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

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
----------------------------------------------------------------------------------------------------------------
                                                                                                 Cost on U.S.
              Action                    Labor cost        Parts cost      Cost per product        operators
----------------------------------------------------------------------------------------------------------------
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.
----------------------------------------------------------------------------------------------------------------

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

Federal Register / Vol. 81, No. 246 / Thursday, December 22, 2016 / Proposed Rules 93855

based on mortality rates for annuitants Actuarial present value means the W12–140, 1200 New Jersey Avenue SE.,
paid from the Civil Service Retirement amount of monthly annuity at time of Washington, DC 20590.
and Disability Fund; and increases each retirement multiplied by the applicable • Hand Delivery: Deliver to Mail
year at an assumed rate of cost-of-living present value factor. address above between 9 a.m. and 5
adjustment. Assumed rates of interest, * * * p.m., Monday through Friday, except
mortality, and cost-of-living adjustments Present value factor has the same Federal holidays.
used in computing the present value are meaning in this part as defined in
those used by the Board of Actuaries of § 842.602. For service information identified in
the Civil Service Retirement System for this NPRM, contact Pratt & Whitney,
* * * * * 400 Main St., East Hartford, CT 06108;
valuation of the Federal Employees’
Retirement System based on dynamic § 847.602 [Removed and Reserved] phone: 860–565–8770; fax: 860–565–
assumptions. The present value factors ■ 25. Remove and reserve § 847.602.
4503. You may view this service
are unisex factors obtained as a [FR Doc. 2016–30487 Filed 12–21–16; 8:45 am] information at the FAA, Engine &
composite of sex-distinct present value BILLING CODE 6325–38–P
Propeller Directorate, 1200 District
factors. Separate present value factors Avenue, Burlington, MA. For
apply for FERS annuities that receive information on the availability of this
cost-of-living adjustments before the material at the FAA, call 781–238–7125.
DEPARTMENT OF TRANSPORTATION
retiree attains age 62, versus FERS Examining the AD Docket
annuities that do not receive cost-of- Federal Aviation Administration
living adjustments before the retiree You may examine the AD docket on
attains age 62. 14 CFR Part 39 the Internet at http://
* * * * * www.regulations.gov by searching for
[Docket No. FAA–2013–0740; Directorate
■ 21. Add § 842.616 to subpart F to read Identifier 2013–NE–24–AD]
and locating Docket No. FAA–2013–
as follows: 0740; or in person at the Docket
RIN 2120–AA64 Management Facility between 9 a.m.
§ 842.616 Publication of present value and 5 p.m., Monday through Friday,
factors. Airworthiness Directives; Pratt & except Federal holidays. The AD docket
When OPM publishes in the Federal Whitney Turbofan Engines contains this proposed AD, the
Register notice of normal cost AGENCY: Federal Aviation regulatory evaluation, any comments
percentages under § 841.407 of this Administration (FAA), DOT. received, and other information. The
chapter, it will also publish updated street address for the Docket Office
ACTION: Notice of proposed rulemaking
present value factors. (phone: 800–647–5527) is in the
(NPRM).
■ 22. Amend § 842.702 by revising the ADDRESSES section. Comments will be
definition of ‘‘present value factor’’ to SUMMARY: We propose to supersede available in the AD docket shortly after
read as follows: Airworthiness Directive (AD) 2014–05– receipt.
§ 842.702 Definitions. 32, which applies to all Pratt & Whitney FOR FURTHER INFORMATION CONTACT:
(PW) PW2037, PW2037D, PW2037M, Brian Kierstead, Aerospace Engineer,
* * * * *
Present value factor has the same PW2040, PW2040D, PW2043, PW2143, Engine Certification Office, FAA, Engine
meaning in this subpart as defined in PW2643, and F117–PW–100 turbofan & Propeller Directorate, 1200 District
§ 842.602. engines. AD 2014–05–32 currently Avenue, Burlington, MA 01803; phone:
requires one-time eddy current 781–238–7772; fax: 781–238–7199;
* * * * * inspection (ECI) of affected engines with email: brian.kierstead@faa.gov.
PART 847—ELECTIONS OF certain diffuser and HPT cases installed.
AD 2014–05–32 also requires a SUPPLEMENTARY INFORMATION:
RETIREMENT COVERAGE BY
CURRENT AND FORMER EMPLOYEES fluorescent-penetrant inspection (FPI) of Comments Invited
OF NONAPPROPRIATED FUND the diffuser case rear flange and the HPT
INSTRUMENTALITIES case front flange. Since we issued AD We invite you to send any written
2014–05–32, the manufacturer relevant data, views, or arguments about
■ 23. The authority citation for part 847 determined through analysis that the this proposed AD. Send your comments
continues to read as follows: inspections required by AD 2014–05–32 to an address listed under the
Authority: 5 U.S.C. 8332(b)(17) and are not adequate to maintain safety. This ADDRESSES section. Include ‘‘Docket No.
8411(b)(6) and sections 1131 and 1132 of proposed AD would add additional FAA–2013–0740; Directorate Identifier
Pub. L. 107–107, December 28, 2001, 115 Stat repetitive, on-wing ECI inspections. We 2013–NE–24–AD’’ at the beginning of
1242; 5 U.S.C. 8347(a) and 8461(g) and are proposing this AD to correct the your comments. We specifically invite
section 1043(b) of Pub. L. 104–106, Div. A, unsafe condition on these products. comments on the overall regulatory,
Title X, Feb. 10, 1996, 110 Stat. 434. Subpart
B also issued under 5 U.S.C. 8347(q) and DATES: We must receive comments on economic, environmental, and energy
8461(n). this proposed AD by February 6, 2017. aspects of this proposed AD. We will
ADDRESSES: You may send comments, consider all comments received by the
Subpart A—General Provisions using the procedures found in 14 CFR closing date and may amend this
11.43 and 11.45, by any of the following proposed AD because of those
■ 24. Amend § 847.103(b) by revising comments.
methods:
Lhorne on DSK30JT082PROD with PROPOSALS

the definition of ‘‘actuarial present
value’’ and adding the definition of • Federal eRulemaking Portal: Go to We will post all comments we
‘‘present value factor’’ in alphabetical http://www.regulations.gov. Follow the receive, without change, to http://
order as follows: instructions for submitting comments. www.regulations.gov, including any
• Fax: 202–493–2251. personal information you provide. We
§ 847.103 Definitions. • Mail: U.S. Department of will also post a report summarizing each
* * * * * Transportation, Docket Operations, M– substantive verbal contact we receive
(b) * * * 30, West Building Ground Floor, Room about this proposed AD.

VerDate Sep<11>2014 15:19 Dec 21, 2016 Jkt 241001 PO 00000 Frm 00005 Fmt 4702 Sfmt 4702 E:\FR\FM\22DEP1.SGM 22DEP1

93856 Federal Register / Vol. 81, No. 246 / Thursday, December 22, 2016 / Proposed Rules

Discussion from non-repaired flanges on diffuser FAA’s Determination
On March 6, 2014, we issued AD cases installed on the affected engines. We are proposing this AD because we
2014–05–32, Amendment 39–17804 (79 We determined, therefore, that the evaluated all the relevant information
FR 17856, March 31, 2014), (‘‘AD 2014– inspections required by AD 2014–05–32 and determined the unsafe condition
05–32’’), for all PW PW2037, PW2037D, are not adequate to maintain safety. To described previously is likely to exist or
PW2037M, PW2040, PW2040D, correct this unsafe condition, we are develop in other products of the same
PW2043, PW2143, PW2643, and F117– now proposing additional, repetitive type design.
PW–100 turbofan engines. AD 2014–05– ECI inspections.
32 requires a one-time ECI of affected Proposed AD Requirements
Related Service Information Under 1
engines with certain diffuser and HPT This proposed AD would retain the
CFR Part 51 requirements of AD 2014–05–32 except
cases installed. AD 2014–05–32 also
requires an FPI of the diffuser case rear We reviewed PW Service Bulletin No. it would eliminate the Prohibition
flange and HPT case front flange. AD PW2000 72–763, Revision No. 1, dated Statement. We determined that this
2014–05–32 resulted from a rupture of August 30, 2013; and PW Alert Service statement is unnecessary for compliance
the diffuser-to-HPT case flange. We Bulletin No. PW2000 A72–765, Revision with the AD. In addition, this proposed
issued AD 2014–05–32 to prevent AD would require repetitive, on-wing
No. 1, dated July 13, 2016. This service
failure of the diffuser-to-HPT case ECI inspections. This proposed AD
information describes procedures for a
flange, which could lead to uncontained would also remove the PW2240 and
one-time ECI inspection of the engine
engine failure and damage to the PW2337 engines from the applicability
diffuser case and the HPT case, and section since these engines were
airplane.
repetitive on-wing ECIs of the engine removed from PW Type Certificate
Actions Since AD 2014–05–32 Was diffuser case assembly, respectively. Number E17NE.
Issued This service information is reasonably
Since we issued AD 2014–05–32, the available because the interested parties Costs of Compliance
manufacturer identified a subpopulation have access to it through their normal We estimate that this proposed AD
of diffuser cases installed on the course of business or by the means will affect 910 engines installed on
affected engines with a repaired flange identified in the ADDRESSES section. airplanes of U.S. registry.
that has a lower fatigue capability. The We estimate the following costs to
repaired flange cannot be distinguished comply with this proposed AD:

ESTIMATED COSTS
Action Labor cost Parts cost Cost per product Cost on U.S. operators

On-wing/module ECI Inspec- 8 work-hours × $85 per hour $0 $680 ....................................... $230,520 per inspection
tion. = $680. cycle.
FPI Inspection ........................ 3 work-hours × $85 per hour 20 $275 per inspection cycle ...... $250,250 per inspection
= $255. cycle.

Authority for This Rulemaking implications under Executive Order The Proposed Amendment
13132. This proposed AD would not
Title 49 of the United States Code Accordingly, under the authority
have a substantial direct effect on the
specifies the FAA’s authority to issue delegated to me by the Administrator,
States, on the relationship between the
rules on aviation safety. Subtitle I, the FAA proposes to amend 14 CFR part
national Government and the States, or
Section 106, describes the authority of 39 as follows:
on the distribution of power and
the FAA Administrator. Subtitle VII,
responsibilities among the various
Aviation Programs, describes in more PART 39—AIRWORTHINESS
levels of government.
detail the scope of the Agency’s For the reasons discussed above, I DIRECTIVES
authority. certify that the proposed regulation:
We are issuing this rulemaking under (1) Is not a ‘‘significant regulatory ■ 1. The authority citation for part 39
the authority described in Subtitle VII, action’’ under Executive Order 12866, continues to read as follows:
Part A, Subpart III, Section 44701, (2) Is not a ‘‘significant rule’’ under
‘‘General requirements.’’ Under that Authority: 49 U.S.C. 106(g), 40113, 44701.
the DOT Regulatory Policies and
section, Congress charges the FAA with Procedures (44 FR 11034, February 26, § 39.13 [Amended]
promoting safe flight of civil aircraft in 1979),
air commerce by prescribing regulations (3) Will not affect intrastate aviation ■ 2. The FAA amends § 39.13 by
for practices, methods, and procedures in Alaska to the extent that it justifies removing Airworthiness Directive (AD)
the Administrator finds necessary for making a regulatory distinction, and 2014–05–32, Amendment 39–17804 (79
safety in air commerce. This regulation (4) Will not have a significant FR 17856, March 31, 2014), and adding
is within the scope of that authority economic impact, positive or negative, the following new AD:
because it addresses an unsafe condition
Lhorne on DSK30JT082PROD with PROPOSALS

on a substantial number of small entities Pratt & Whitney: Docket No. FAA–2013–
that is likely to exist or develop on under the criteria of the Regulatory 0740; Directorate Identifier 2013–NE–
products identified in this rulemaking Flexibility Act. 24–AD.
action.
List of Subjects in 14 CFR Part 39 (a) Comments Due Date
Regulatory Findings
Air transportation, Aircraft, Aviation The FAA must receive comments on this
We have determined that this safety, Incorporation by reference, AD action by February 6, 2017.
proposed AD would not have federalism Safety.

VerDate Sep<11>2014 15:19 Dec 21, 2016 Jkt 241001 PO 00000 Frm 00006 Fmt 4702 Sfmt 4702 E:\FR\FM\22DEP1.SGM 22DEP1

Document Created: 2016-12-21 23:52:44
Document Modified: 2016-12-21 23:52:44

Category		Regulatory Information
Collection		Federal Register
sudoc Class		AE 2.7: GS 4.107: AE 2.106:
Publisher		Office of the Federal Register, National Archives and Records Administration
Section		Proposed Rules
Action		Notice of proposed rulemaking (NPRM).
Dates		We must receive comments on this proposed AD by February 6, 2017.
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]
FR Citation		81 FR 93855
RIN Number		2120-AA64
CFR Associated		Air Transportation; Aircraft and Aviation Safety

81 FR 93855 - Airworthiness Directives; Pratt & Whitney Turbofan Engines

DEPARTMENT OF TRANSPORTATIONFederal Aviation Administration

Federal Register Volume 81, Issue 246 (December 22, 2016)

DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration