82 FR 17945 - Airworthiness Directives; General Electric Company Turbofan Engines

DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration

Federal Register Volume 82, Issue 71 (April 14, 2017)

Page Range		17945-17947
FR Document		2017-07477

We propose to adopt a new airworthiness directive (AD) for certain General Electric Company (GE) CF34-8 model turbofan engines. This proposed AD was prompted by analysis that resulted in the reduction of the life of the affected fan blades. This proposed AD would require inspections of the affected fan blades until their removal. We are proposing this AD to correct the unsafe condition on these products.

Federal Register, Volume 82 Issue 71 (Friday, April 14, 2017)

[Federal Register Volume 82, Number 71 (Friday, April 14, 2017)]
[Proposed Rules]
[Pages 17945-17947]
From the Federal Register Online  [www.thefederalregister.org]
[FR Doc No: 2017-07477]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2017-0164; Directorate Identifier 2017-NE-06-AD]
RIN 2120-AA64


Airworthiness Directives; General Electric Company Turbofan 
Engines

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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

SUMMARY: We propose to adopt a new airworthiness directive (AD) for 
certain General Electric Company (GE) CF34-8 model turbofan engines. 
This proposed AD was prompted by analysis that resulted in the 
reduction of the life of the affected fan blades. This proposed AD 
would require inspections of the affected fan blades until their 
removal. We are proposing this AD to correct the unsafe condition on 
these products.

DATES: We must receive comments on this proposed AD by May 30, 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 General 
Electric Company, GE-Aviation, Room 285, 1 Neumann Way, Cincinnati, OH 
45215, phone: 513-552-3272; fax: 513-552-3329; email: [email protected]. 
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-2017-
0164; 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: Martin Adler, Aerospace Engineer, 
Engine Certification Office, FAA, Engine & Propeller Directorate, 1200 
District Avenue, Burlington, MA 01803; phone: 781-238-7157; 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 NPRM. Send your comments to an address listed 
under the ADDRESSES section. Include ``Docket No. FAA-2017-0164; 
Directorate Identifier 2017-NE-06-AD'' at the beginning of your 
comments. We specifically invite comments on the overall regulatory, 
economic, environmental, and energy aspects of this NPRM. We will 
consider all comments received by the closing date and may amend this 
NPRM 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 NPRM.

Discussion

    We learned that GE has determined, based on analysis, that the 
stresses in the pinholes in the affected fan blade could result in 
crack initiation at pinhole surfaces beyond 19,000, 19,500, or 25,000 
cyles-since-new (CSN), depending on the engine model on which the blade 
is installed. GE, therefore, has initiated a program of initial and 
repetitive eddy current inspections (ECIs) and removal of this fan 
blade before it reaches 41,000 CSN. GE also provided an option to 
repair the blade which allows for an additional 28,000 cycles before it 
must be removed. This condition, if not corrected, could result in 
failure of the fan blade, uncontained blade release, damage to the 
engine, and damage to the airplane.

Related Service Information Under 1 CFR Part 51

    We reviewed GE Alert Service Bulletins (ASBs) CF34-8C SB 72-A0137 
R05, dated June 15, 2016; and CF34-8E SB 72-A0060 R05, dated June 15, 
2016. These ASBs provide the procedures necessary for calculating the 
adjusted CSN for the initial inspection. 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.

Other Related Service Information

    We reviewed GE ASB CF34-8E SB 72-A0115 R03, issued on December 9, 
2016, and GE ASB CF34-8C SB 72-A0225 R03, issued on December 9, 2016. 
The ASB's describe procedures for repairing fan blade, part number (P/
N) 4114T15P02, to P/N 4114T31G01 with the installation of a bushing in 
the pinholes.

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 require initial and repetitive ECIs of the 
affected fan blade. This proposed AD would also require removal or 
repair of the affected fan blade at a reduced life. A fan blade

[[Page 17946]]

that has been repaired is eligible for an additional 28,000 cycles in 
service before it must be removed.

Differences Between This Proposed AD and the Service Information

    The determination in this proposed AD of CSN, when CSN is not 
known, is simpler and clearer than the method indicated in the service 
information. The service information has several options that may lead 
to confusion among operators in making this determination.

Costs of Compliance

    We estimate that this proposed AD affects 1,986 engines installed 
on airplanes of U.S. registry.
    We estimate the following costs to comply with this proposed AD:

                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                                                                     Cost per      Cost on U.S.
                Action                         Labor cost           Parts cost        product        operators
----------------------------------------------------------------------------------------------------------------
Initial ECI Inspection................  4 work-hours x $85 per                $0            $340        $675,240
                                         hour = $340.
Replacement of fan blade (prorated      0 work-hours x $85 per             5,460           5,460      10,843,560
 annual cost).                           hour = $0.
----------------------------------------------------------------------------------------------------------------

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 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 this 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 adding the following new airworthiness 
directive (AD):

General Electric Company: Docket No. FAA-2017-0164; Directorate 
Identifier 2017-NE-06-AD.

(a) Comments Due Date

    We must receive comments by May 30, 2017.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to General Electric Company (GE) CF34-8C1, CF34-
8C5, CF34-8C5A1, CF34-8C5B1, CF34-8C5A2, CF34-8C5A3, CF34-8E2, CF34-
8E2A1, CF34-8E5, CF34-8E5A1, CF34-8E5A2, CF34-8E6 and CF34-8E6A1 
engines, including engines marked on the engine data plate as CF34-
8C5B1/B, CF34-8C5/B, CF34-8C5A1/B, CF34-8C5A2/B, CF34-8C5/M, CF34-
8C5A1/M, CF34-8C5A2/M, CF34-8C5A3/B, or CF34-8C5B1/M, with a fan 
blade, part number (P/N) 4114T15P02 or P/N 4114T31G01, installed.

(d) Subject

    Joint Aircraft System Component (JASC) Code 7230, Turbine Engine 
Compressor Section.

(e) Unsafe Condition

    This AD was prompted by analysis that resulted in the reduction 
of the life of the affected fan blades. We are issuing this AD to 
prevent failure of the fan blade, uncontained blade release, damage 
to the engine, and damage to the airplane.

(f) Compliance

    Comply with this AD within the compliance times specified, 
unless already done.

(g) Eddy Current Inspections (ECIs)

    (1) For CF34-8C1, CF34-8C5B1, CF34-8C5B1/B and CF34-8E2 engines 
with fan blade, P/N 4114T15P02, installed:
    (i) Perform an initial ECI of the fan blade pinhole prior to the 
fan blade accumulating 25,000 cycles-since-new (CSN); and
    (ii) Repeat this inspection within every 3,000 cycles 
thereafter.
    (2) For CF34-8C5, CF34-8C5/B, CF34-8C5A1, CF34-8C5A1/B, CF34-
8C5A2, CF34-8C5A2/B, CF34-8E2A1, CF34-8E5, CF34-8E5A1, CF34-8E6 and 
CF34-8E6A1 engines with fan blade, P/N 4114T15P02, installed:
    (i) Perform an initial ECI of the fan blade pinhole prior to the 
fan blade accumulating 19,500 CSN; and
    (ii) Repeat this inspection within every 3,000 cycles 
thereafter, until the fan blade has accumulated 25,000 CSN, then 
repeat the inspection every 1,500 cycles thereafter.
    (3) For CF34-8C5/M, CF34-8C5A1/M, CF34-8C5A2/M, CF34-8C5A3, 
CF34-8C5A3/B, CF34-8C5B1/M, and CF34-8E5A2 engines with fan blade, 
P/N 4114T15P02, installed:
    (i) Perform an initial ECI of the fan blade pinhole prior to the 
fan blade accumulating 19,000 CSN; and
    (ii) Repeat this inspection within every 3,000 cycles 
thereafter, until the fan blade has accumulated 25,000 CSN, then 
repeat the inspection every 1,500 cycles thereafter.
    (4) For any affected engine with a fan blade, P/N 4114T15P02, 
installed where the CSN of the fan blade is unknown on the effective 
date of this AD:

[[Page 17947]]

    (i) Assume the blade has accumulated 25,000 CSN on the effective 
date of this AD; and
    (ii) Inspect the blade prior to installation or within 500 
cycles after the effective date of this AD, whichever is earlier.
    (5) If a fan blade is moved from one affected engine model to 
another affected model after the initial ECI:
    (i) Perform an additional ECI of the blade prior to installation 
in the new model; and
    (ii) Repeat this inspection based on the intervals of the new 
engine installation, as specified in paragraph (g) of this AD.
    (6) If a fan blade, P/N 4114T15P02, has been used on more than 
one engine model prior to the initial ECI, use Appendix A of GE 
Alert Service Bulletin (ASB) CF34-8C SB 72-A0137 R05, dated June 15, 
2016, or Appendix A of GE ASB CF34-8E SB 72-A0060 R05, dated June 
15, 2016, to calculate the new cycle limit for the initial 
inspection of that fan blade.

(h) Fan Blade Removal

    (1) For any affected engine with a fan blade, P/N 4114T15P02, 
installed, remove the blade from service or repair to P/N 4114T31G01 
prior to the blade accumulating 41,000 CSN.
    (2) For any affected engine with a fan blade, P/N 4114T31G01, 
installed, remove the blade from service prior to the blade 
accumulating 28,000 cycles since installation of the pinhole 
bushing.

(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 AD, contact Martin Adler, 
Aerospace Engineer, Engine Certification Office, FAA, Engine & 
Propeller Directorate, 1200 District Avenue, Burlington, MA 01803; 
phone: 781-238-7157; fax: 781-238-7199; email: [email protected].
    (2) GE ASBs: CF34-8C SB 72-A0137 R05, dated June 15, 2016; CF34-
8E SB 72-A0060 R05, dated June 15, 2016; CF34-8E SB 72A0115 R03, 
issued December 9, 2016; and CF34-8C ASB 72-A0225 R03, issued 
December 9, 2016; can be obtained from GE using the contact 
information in paragraph (j)(3) of this AD.
    (3) For service information identified in this proposed AD, 
contact General Electric Company, GE-Aviation, Room 285, 1 Neumann 
Way, Cincinnati, OH 45215, phone: 513-552-3272; fax: 513-552-3329; 
email: [email protected].
    (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 April 5, 2017.
Carlos A. Pestana,
Acting Manager, Engine & Propeller Directorate, Aircraft Certification 
Service.
[FR Doc. 2017-07477 Filed 4-13-17; 8:45 am]
 BILLING CODE 4910-13-P

Federal Register / Vol. 82, No. 71 / Friday, April 14, 2017 / Proposed Rules 17945

(1) A minor transient would not 11.43 and 11.45, by any of the following We will post all comments we
significantly reduce safety margins and methods: receive, without change, to http://
would involve flightcrew actions that • Federal eRulemaking Portal: Go to www.regulations.gov, including any
are well within their capabilities. A http://www.regulations.gov. Follow the personal information you provide. We
minor transient may involve a slight instructions for submitting comments. will also post a report summarizing each
increase in flightcrew workload or some • Fax: 202–493–2251. substantive verbal contact we receive
physical discomfort to passengers or • Mail: U.S. Department of about this NPRM.
cabin crew. Transportation, Docket Operations, M–
30, West Building Ground Floor, Room Discussion
(2) A significant transient may lead to
a significant reduction in safety W12–140, 1200 New Jersey Avenue SE., We learned that GE has determined,
margins, an increase in flightcrew Washington, DC 20590. based on analysis, that the stresses in
workload, discomfort to the flightcrew, • Hand Delivery: Deliver to Mail the pinholes in the affected fan blade
or physical distress to the passengers or address above between 9 a.m. and 5 could result in crack initiation at
cabin crew, possibly including non-fatal p.m., Monday through Friday, except pinhole surfaces beyond 19,000, 19,500,
injuries. Significant transients do not Federal holidays. or 25,000 cyles-since-new (CSN),
For service information identified in depending on the engine model on
require—in order to remain within or
this NPRM, contact General Electric which the blade is installed. GE,
recover to the normal flight envelope—
Company, GE-Aviation, Room 285, 1 therefore, has initiated a program of
any of the following:
(i) Exceptional piloting skill, Neumann Way, Cincinnati, OH 45215, initial and repetitive eddy current
alertness, or strength. phone: 513–552–3272; fax: 513–552– inspections (ECIs) and removal of this
(ii) Forces applied by the pilot which 3329; email: geae.aoc@ge.com. You may fan blade before it reaches 41,000 CSN.
are greater than those specified in view this service information at the GE also provided an option to repair the
§ 23.143(c). FAA, Engine & Propeller Directorate, blade which allows for an additional
(iii) Accelerations or attitudes in the 1200 District Avenue, Burlington, MA. 28,000 cycles before it must be removed.
airplane that might result in further For information on the availability of This condition, if not corrected, could
hazard to secured or non-secured this material at the FAA, call 781–238– result in failure of the fan blade,
occupants. 7125. uncontained blade release, damage to
Issued in Kansas City, Missouri on April 4, Examining the AD Docket the engine, and damage to the airplane.
2017. You may examine the AD docket on Related Service Information Under 1
Pat Mullen, the Internet at http:// CFR Part 51
Acting Manager, Small Airplane Directorate, www.regulations.gov by searching for
We reviewed GE Alert Service
Aircraft Certification Service. and locating Docket No. FAA–2017–
Bulletins (ASBs) CF34–8C SB 72–A0137
[FR Doc. 2017–07382 Filed 4–13–17; 8:45 am] 0164; or in person at the Docket
R05, dated June 15, 2016; and CF34–8E
BILLING CODE 4910–13–P Management Facility between 9 a.m.
SB 72–A0060 R05, dated June 15, 2016.
and 5 p.m., Monday through Friday,
These ASBs provide the procedures
except Federal holidays. The AD docket
necessary for calculating the adjusted
DEPARTMENT OF TRANSPORTATION contains this proposed AD, the
CSN for the initial inspection. This
regulatory evaluation, any comments
Federal Aviation Administration service information is reasonably
received, and other information. The
available because the interested parties
street address for the Docket Office
14 CFR Part 39 have access to it through their normal
(phone: 800–647–5527) is in the
course of business or by the means
[Docket No. FAA–2017–0164; Directorate ADDRESSES section. Comments will be
identified in the ADDRESSES section.
Identifier 2017–NE–06–AD] available in the AD docket shortly after
receipt. Other Related Service Information
RIN 2120–AA64
FOR FURTHER INFORMATION CONTACT: We reviewed GE ASB CF34–8E SB
Airworthiness Directives; General Martin Adler, Aerospace Engineer, 72–A0115 R03, issued on December 9,
Electric Company Turbofan Engines Engine Certification Office, FAA, Engine 2016, and GE ASB CF34–8C SB 72–
& Propeller Directorate, 1200 District A0225 R03, issued on December 9,
AGENCY: Federal Aviation Avenue, Burlington, MA 01803; phone: 2016. The ASB’s describe procedures for
Administration (FAA), DOT. 781–238–7157; fax: 781–238–7199; repairing fan blade, part number (P/N)
ACTION: Notice of proposed rulemaking email: martin.adler@faa.gov. 4114T15P02, to P/N 4114T31G01 with
(NPRM). SUPPLEMENTARY INFORMATION: the installation of a bushing in the
SUMMARY: We propose to adopt a new Comments Invited pinholes.
airworthiness directive (AD) for certain We invite you to send any written FAA’s Determination
General Electric Company (GE) CF34–8 relevant data, views, or arguments about We are proposing this AD because we
model turbofan engines. This proposed this NPRM. Send your comments to an evaluated all the relevant information
AD was prompted by analysis that address listed under the ADDRESSES and determined the unsafe condition
resulted in the reduction of the life of section. Include ‘‘Docket No. FAA– described previously is likely to exist or
the affected fan blades. This proposed 2017–0164; Directorate Identifier 2017– develop in other products of the same
jstallworth on DSK7TPTVN1PROD with PROPOSALS

AD would require inspections of the NE–06–AD’’ at the beginning of your type design.
affected fan blades until their removal. comments. We specifically invite
We are proposing this AD to correct the comments on the overall regulatory, Proposed AD Requirements
unsafe condition on these products. economic, environmental, and energy This proposed AD would require
DATES: We must receive comments on aspects of this NPRM. We will consider initial and repetitive ECIs of the affected
this proposed AD by May 30, 2017. all comments received by the closing fan blade. This proposed AD would also
ADDRESSES: You may send comments, date and may amend this NPRM require removal or repair of the affected
using the procedures found in 14 CFR because of those comments. fan blade at a reduced life. A fan blade

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17946 Federal Register / Vol. 82, No. 71 / Friday, April 14, 2017 / Proposed Rules

that has been repaired is eligible for an simpler and clearer than the method Costs of Compliance
additional 28,000 cycles in service indicated in the service information.
before it must be removed. The service information has several We estimate that this proposed AD
options that may lead to confusion affects 1,986 engines installed on
Differences Between This Proposed AD airplanes of U.S. registry.
and the Service Information among operators in making this
determination. We estimate the following costs to
The determination in this proposed comply with this proposed AD:
AD of CSN, when CSN is not known, is

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

Initial ECI Inspection ....................................... 4 work-hours × $85 per hour = $340 ............. $0 $340 $675,240
Replacement of fan blade (prorated annual 0 work-hours × $85 per hour = $0 ................. 5,460 5,460 10,843,560
cost).

Authority for This Rulemaking under the criteria of the Regulatory (d) Subject
Title 49 of the United States Code Flexibility Act. Joint Aircraft System Component (JASC)
specifies the FAA’s authority to issue Code 7230, Turbine Engine Compressor
List of Subjects in 14 CFR Part 39 Section.
rules on aviation safety. Subtitle I,
section 106, describes the authority of Air transportation, Aircraft, Aviation (e) Unsafe Condition
the FAA Administrator. Subtitle VII: safety, Incorporation by reference, This AD was prompted by analysis that
Aviation Programs, describes in more Safety. resulted in the reduction of the life of the
detail the scope of the Agency’s affected fan blades. We are issuing this AD
The Proposed Amendment
authority. to prevent failure of the fan blade,
We are issuing this rulemaking under Accordingly, under the authority uncontained blade release, damage to the
the authority described in Subtitle VII, delegated to me by the Administrator, engine, and damage to the airplane.
Part A, Subpart III, Section 44701: the FAA proposes to amend 14 CFR part (f) Compliance
‘‘General requirements.’’ Under that 39 as follows:
section, Congress charges the FAA with Comply with this AD within the
compliance times specified, unless already
promoting safe flight of civil aircraft in PART 39—AIRWORTHINESS done.
air commerce by prescribing regulations DIRECTIVES
for practices, methods, and procedures (g) Eddy Current Inspections (ECIs)
the Administrator finds necessary for ■ 1. The authority citation for part 39 (1) For CF34–8C1, CF34–8C5B1, CF34–
safety in air commerce. This regulation continues to read as follows: 8C5B1/B and CF34–8E2 engines with fan
is within the scope of that authority blade, P/N 4114T15P02, installed:
because it addresses an unsafe condition Authority: 49 U.S.C. 106(g), 40113, 44701. (i) Perform an initial ECI of the fan blade
that is likely to exist or develop on pinhole prior to the fan blade accumulating
§ 39.13 [Amended]
products identified in this rulemaking 25,000 cycles-since-new (CSN); and
action. ■ 2. The FAA amends § 39.13 by adding (ii) Repeat this inspection within every
the following new airworthiness 3,000 cycles thereafter.
Regulatory Findings directive (AD): (2) For CF34–8C5, CF34–8C5/B, CF34–
We determined that this proposed AD 8C5A1, CF34–8C5A1/B, CF34–8C5A2, CF34–
General Electric Company: Docket No. FAA– 8C5A2/B, CF34–8E2A1, CF34–8E5, CF34–
would not have federalism implications 2017–0164; Directorate Identifier 2017– 8E5A1, CF34–8E6 and CF34–8E6A1 engines
under Executive Order 13132. This NE–06–AD. with fan blade, P/N 4114T15P02, installed:
proposed AD would not have a (i) Perform an initial ECI of the fan blade
substantial direct effect on the States, on (a) Comments Due Date
pinhole prior to the fan blade accumulating
the relationship between the national We must receive comments by May 30, 19,500 CSN; and
Government and the States, or on the 2017. (ii) Repeat this inspection within every
distribution of power and (b) Affected ADs 3,000 cycles thereafter, until the fan blade
responsibilities among the various has accumulated 25,000 CSN, then repeat the
levels of government. None. inspection every 1,500 cycles thereafter.
For the reasons discussed above, I (c) Applicability (3) For CF34–8C5/M, CF34–8C5A1/M,
certify this proposed regulation: CF34–8C5A2/M, CF34–8C5A3, CF34–8C5A3/
This AD applies to General Electric B, CF34–8C5B1/M, and CF34–8E5A2 engines
(1) Is not a ‘‘significant regulatory Company (GE) CF34–8C1, CF34–8C5, CF34–
action’’ under Executive Order 12866, with fan blade, P/N 4114T15P02, installed:
8C5A1, CF34–8C5B1, CF34–8C5A2, CF34– (i) Perform an initial ECI of the fan blade
(2) Is not a ‘‘significant rule’’ under 8C5A3, CF34–8E2, CF34–8E2A1, CF34–8E5,
the DOT Regulatory Policies and pinhole prior to the fan blade accumulating
jstallworth on DSK7TPTVN1PROD with PROPOSALS

CF34–8E5A1, CF34–8E5A2, CF34–8E6 and 19,000 CSN; and
Procedures (44 FR 11034, February 26, CF34–8E6A1 engines, including engines (ii) Repeat this inspection within every
1979), marked on the engine data plate as CF34– 3,000 cycles thereafter, until the fan blade
(3) Will not affect intrastate aviation 8C5B1/B, CF34–8C5/B, CF34–8C5A1/B, has accumulated 25,000 CSN, then repeat the
in Alaska to the extent that it justifies CF34–8C5A2/B, CF34–8C5/M, CF34–8C5A1/ inspection every 1,500 cycles thereafter.
making a regulatory distinction, and M, CF34–8C5A2/M, CF34–8C5A3/B, or (4) For any affected engine with a fan
(4) Will not have a significant CF34–8C5B1/M, with a fan blade, part blade, P/N 4114T15P02, installed where the
economic impact, positive or negative, number (P/N) 4114T15P02 or P/N CSN of the fan blade is unknown on the
on a substantial number of small entities 4114T31G01, installed. effective date of this AD:

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Document Created: 2017-04-14 00:56:25
Document Modified: 2017-04-14 00:56:25

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 May 30, 2017.
Contact		Martin Adler, Aerospace Engineer, Engine Certification Office, FAA, Engine & Propeller Directorate, 1200 District Avenue, Burlington, MA 01803; phone: 781-238-7157; fax: 781- 238-7199; email: [email protected]
FR Citation		82 FR 17945
RIN Number		2120-AA64
CFR Associated		Air Transportation; Aircraft; Aviation Safety; Incorporation by Reference and Safety

82 FR 17945 - Airworthiness Directives; General Electric Company Turbofan Engines

DEPARTMENT OF TRANSPORTATIONFederal Aviation Administration

Federal Register Volume 82, Issue 71 (April 14, 2017)

DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration