29476 Federal Register / Vol. 83, No. 122 / Monday, June 25, 2018 / Proposed Rules 

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, 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 

■ 1. The authority citation for part 39 

continues to read as follows: 

Authority: 49 U.S.C. 106(g), 40113, 44701. 

§ 39.13 [Amended] 

■ 2. The FAA amends § 39.13 by 

removing Airworthiness Directive (AD) 

2017–07–04, Amendment 39–18842 (82 

FR 16728, April 6, 2017), and adding 

the following new AD: 

General Electric Company: Docket No. 

FAA–2018–0406; Product Identifier 2013– 

NE–30–AD. 

(a) Comments Due Date 

The FAA must receive comments on this 

AD action by August 9, 2018. 

(b) Affected ADs 

This AD replaces AD 2017–07–04, 

Amendment 39–18842 (82 FR 16728, April 6, 

2017) (‘‘AD 2017–07–04’’). 

(c) Applicability 

This AD applies to General Electric 

Company (GE) GE90–110B1 and GE90–115B 

turbofan engines with HPC rotor stage 2–5 

spools, with: 

(1) A serial number listed in either, 

paragraph 4, Appendix A of GE Service 

Bulletin (SB) No. GE90–100 SB 72–0499 R01, 

dated February 5, 2014, in paragraph 4, 

Appendix A of GE SB GE90–100 SB 72–0659 

R01, dated February 18, 2016, or in 

paragraph 4, Appendix A, of GE SB GE90– 

100 SB 72–0714 R01, dated February 16, 

2018. 

(2) A part number (P/N) 351–103–109–0, P/ 

N 351–103–110–0, P/N 351–103–147–0 or P/ 

N 351–103–152–0, with any serial number. 

(d) Subject 

Joint Aircraft System Component (JASC) 

Code 7230, Turbine Engine Compressor 

Section. 

(e) Unsafe Condition 

This AD was prompted by reports of cracks 

in HPC rotor stage 2–5 spool aft spacer arms. 

We are issuing this AD to prevent failure of 

the HPC rotor stage 2–5 spools. The unsafe 

condition, if not addressed, could result in 

uncontained spool 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) Required Actions 

(1) Remove from service HPC rotor stage 2– 

5 spools with serial numbers listed in 

paragraph 4, Appendix A, of GE SB GE90– 

100 SB 72–0659 R01, dated February 18, 

2016, as follows, or before further flight, 

whichever occurs later: 

(i) For spools with fewer than 4,500 flight 

CSN as of April 21, 2017, remove before 

exceeding 5,000 CSN. 

(ii) For spools with 4,500 CSN or more but 

fewer than 5,200 CSN as of April 21, 2017, 

remove within 500 CIS but not to exceed 

5,500 CSN. 

(iii) For spools with 5,200 CSN or more but 

fewer than 5,600 CSN as of April 21, 2017, 

remove within 300 CIS but not to exceed 

5,800 CSN. 

(iv) For spools with 5,600 CSN or more but 

fewer than 5,800 CSN as of April 21, 2017, 

remove within 200 CIS but not to exceed 

5,850 CSN. 

(v) For spools with 5,800 CSN or more but 

fewer than 6,000 CSN as of April 21, 2017, 

remove within 50 CIS but not to exceed 6,000 

CSN. 

(vi) For spools with 6,000 CSN or more as 

of April 21, 2017, remove before the next 

flight. 

(2) Remove from service HPC rotor stage 2– 

5 spools listed in paragraph (c)(2) of this AD 

and HPC rotor stage 2–5 spools with serial 

numbers listed in paragraph 4, Appendix A, 

of GE SB GE90–100 SB 72–0714 R01, dated 

February 16, 2018, before exceeding 8,200 

CSN, or before further flight, whichever 

occurs later. 

(h) Installation Prohibition 

(1) After the effective date of this AD, do 

not install or reinstall onto any engine, any 

HPC rotor stage 2–5 spool with a serial 

number listed in paragraph 4, Appendix A, 

of GE SB No. GE90–100 SB 72–0499 R01, 

dated February 5, 2014, or paragraph 4, 

Appendix A, of GE SB GE90–100 SB72–0659 

R01, dated February 18, 2016, that exceeds 

5,000 CSN. 

(2) After the effective date of this AD, do 

not install or reinstall onto any engine, any 

HPC rotor stage 2–5 spool listed in paragraph 

(c)(2) of this AD, or HPC rotor stage 2–5 spool 

with a serial number listed in paragraph 4, 

Appendix A, of GE SB GE90–100 SB 72–0714 

R01, dated February 16, 2018, that exceeds 

8,200 CSN. 

(i) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, ECO Branch, FAA, has 

the authority to approve AMOCs for this AD, 

if requested using the procedures found in 14 

CFR 39.19. In accordance with 14 CFR 39.19, 

send your request to your principal inspector 

or local Flight Standards District Office, as 

appropriate. If sending information directly 

to the manager of the certification office, 

send it to the attention of the person 

identified in paragraph (j)(1) of this AD. You 

may email your request to: ANE-AD-AMOC@

faa.gov. 

(2) Before using any approved AMOC, 

notify your appropriate principal inspector, 

or lacking a principal inspector, the manager 

of the local flight standards district office/ 

certificate holding district office. 

(j) Related Information 

(1) For more information about this AD, 

contact David Bethka, Aerospace Engineer, 

ECO Branch, FAA, 1200 District Avenue, 

Burlington, MA 01803; phone: 781–238– 

7129; fax: 781–238–7199; email: 

david.bethka@faa.gov. 

(2) For service information identified in 

this AD, contact General Electric Company, 

One Neumann Way, Room 285, Cincinnati, 

OH; phone: 513–552–3272; email: geae.aoc@

ge.com. You may view this referenced service 

information at the FAA, Engine and Propeller 

Standards Branch, 1200 District Avenue, 

Burlington, MA 01803. For information on 

the availability of this material at the FAA, 

call 781–238–7759. 

Issued in Burlington, Massachusetts, on 

June 19, 2018. 

Robert J. Ganley, 

Manager, Engine and Propeller Standards 

Branch, Aircraft Certification Service. 

[FR Doc. 2018–13444 Filed 6–22–18; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2018–0552; Product 

Identifier 2018–NM–049–AD] 

RIN 2120–AA64 

Airworthiness Directives; Airbus 

Defense and Space S.A. (Formerly 

Known as Construcciones 

Aeronauticas, S.A. (CASA)) Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 


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Federal Register / Vol. 83, No. 122 / Monday, June 25, 2018 / Proposed Rules 29477 

SUMMARY: We propose to adopt a new 

airworthiness directive (AD) for certain 

Airbus Defense and Space S.A. Model 

C–212–CB, C–212–CC, C–212–CD, C– 

212–CE, and C–212–DF airplanes. This 

proposed AD was prompted by reports 

of failures of the rudder pedal control 

system support. This proposed AD 

would require repetitive detailed visual 

inspections of the rudder pedal control 

system support box and shaft and 

applicable corrective actions. We are 

proposing this AD to address the unsafe 

condition on these products. 

DATES: We must receive comments on 

this proposed AD by August 9, 2018. 

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 Airbus Defense and 

Space, Services/Engineering support, 

Avenida de Arago ́n 404, 28022 Madrid, 

Spain; telephone: +34 91 585 55 84; fax: 

+34 91 585 31 27; email: 

MTA.TechnicalService@

military.airbus.com. You may view this 

service information at the FAA, 

Transport Standards Branch, 2200 

South 216th St., Des Moines, WA. For 

information on the availability of this 

material at the FAA, call 206–231–3195. 

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–2018– 

0552; 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 NPRM, the regulatory 

evaluation, any comments received, and 

other information. The street address for 

the Docket Operations office (telephone: 

800–647–5527) is in the ADDRESSES

section. Comments will be available in 

the AD docket shortly after receipt. 

FOR FURTHER INFORMATION CONTACT: 

Shahram Daneshmandi, Aerospace 

Engineer, International Section, 

Transport Standards Branch, FAA, 2200 

South 216th St., Des Moines, WA 98198; 

telephone and fax 206–231–3220. 

SUPPLEMENTARY INFORMATION: 

Comments Invited 

We invite you to send any written 

relevant data, views, or arguments about 

this proposal. Send your comments to 

an address listed under the ADDRESSES

section. Include ‘‘Docket No. FAA– 

2018–0552; Product Identifier 2018– 

NM–049–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 based 

on 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 

The European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 

Union, has issued EASA AD 2018–0051, 

dated March 2, 2018 (referred to after 

this as the Mandatory Continuing 

Airworthiness Information, or ‘‘the 

MCAI’’), to correct an unsafe condition 

for certain Airbus Defense and Space 

S.A. Model C–212–CB, C–212–CC, C– 

212–CD, C–212–CE, and C–212–DF 

airplanes. The MCAI states: 

Failures were reported of the rudder pedal 

control system support on CASA C–212 

aeroplanes. Subsequent investigation 

revealed that the welding area of the affected 

support structure had broken. 

This condition, if not corrected, could lead 

to failure of the rudder [pedal] control 

system, possibly resulting in reduced control 

of the aeroplane. 

To address this potential unsafe condition, 

EADS–CASA issued the SB [EADS–CASA 

Service Bulletin SB–212–27–0057, dated May 

21, 2014] to provide modification 

instructions and EASA issued AD 2017–0036 

[which corresponds to FAA AD 2017–19–08, 

Amendment 39–19038 (82 FR 43835, 

September 20 2017) (‘‘AD 2017–19–08’’)] to 

require that modification [of the rudder pedal 

adjustment system]. During accomplishment 

of that modification, several operators 

reported difficulties or impossibility to 

follow the accomplishment instruction. 

Consequently, EASA and Airbus D&S 

[Defense and Space S.A.] reviewed the 

difficulty reports and decided that the 

modification instructions have to be 

improved. 

Pending the improvement of the 

instructions of the SB [EADS–CASA Service 

Bulletin SB–212–27–0057, dated May 21, 

2014] and in order to reduce the risk of 

failure of the [rudder] pedal adjustment 

system to an acceptable level, Airbus D&S 

issued the inspection AOT [Airbus Alert 

Operators Transmission AOT–C212–27– 

0002, dated February 28, 2018] to provide 

instructions to repetitively inspect the 

affected parts [rudder pedal support box Part 

Number (P/N) 212–46195.1 and shaft P/N 

212–46120–20]. 

For the reasons described above, this 

[EASA] AD cancels the requirements of 

EASA AD 2017–0036, which is superseded, 

and requires repetitive [detailed visual] 

inspections of the rudder pedal adjustment 

system [rudder pedal support box P/N 212– 

46195.1 and shaft P/N 212–46120–20] and, 

depending on findings, accomplishment of 

applicable corrective action(s). 

This [EASA] AD is considered to be an 

interim action and further [EASA] AD action 

may follow. 

Corrective actions include obtaining 

corrective actions approved by the 

Manager, International Section, 

Transport Standards Branch, FAA; or 

EASA; or Airbus Defense and Space 

S.A.’s EASA Design Organization 

Approval (DOA); and accomplishing the 

corrective actions within the 

compliance time specified therein. You 

may examine the MCAI in the AD 

docket on the internet at http://

www.regulations.gov by searching for 

and locating Docket No. FAA–2018– 

0552. 

Relationship Between Proposed AD and 

AD 2017–19–08 

This NPRM does not propose to 

supersede AD 2017–19–08. Rather, we 

have determined that a stand-alone AD 

would be more appropriate to address 

the changes in the MCAI. This proposed 

AD would require repetitive detailed 

visual inspections of the rudder pedal 

control system support box and shaft 

and applicable corrective actions. 

Accomplishment of the proposed 

actions would then terminate all of the 

requirements of AD 2017–19–08. 

Related Service Information Under 1 

CFR Part 51 

Airbus Defense and Space S.A. has 

issued Airbus Alert Operators 

Transmission AOT–C212–27–0002, 

dated February 28, 2018. The service 

information describes procedures for 

repetitive detailed visual inspections of 

the rudder pedal control system support 

box and shaft. 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 and Requirements 

of This Proposed AD 

This product has been approved by 

the aviation authority of another 

country, and is approved for operation 

in the United States. Pursuant to our 


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bilateral agreement with the State of 

Design Authority, we have been notified 

of the unsafe condition described in the 

MCAI and service information 

referenced above. We are proposing this 

AD because we evaluated all pertinent 

information and determined an unsafe 

condition exists and is likely to exist or 

develop on other products of the same 

type design. 

Costs of Compliance 

We estimate that this proposed AD 

affects 36 airplanes of U.S. registry. We 

estimate the following costs to comply 

with this proposed AD: 

ESTIMATED COSTS FOR REQUIRED ACTIONS

Labor cost Parts cost Cost per 

product 

Cost on U.S. 

operators 

Up to 8 work-hours × $85 per hour = Up to $680 .................................................... $0 Up to $680 .............. Up to $24,480. 

We have received no definitive data 

that would enable us to provide cost 

estimates for the on-condition repair 

specified in this proposed AD. 

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. 

This proposed AD is issued in 

accordance with authority delegated by 

the Executive Director, Aircraft 

Certification Service, as authorized by 

FAA Order 8000.51C. In accordance 

with that order, issuance of ADs is 

normally a function of the Compliance 

and Airworthiness Division, but during 

this transition period, the Executive 

Director has delegated the authority to 

issue ADs applicable to transport 

category airplanes to the Director of the 

System Oversight Division. 

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; 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 

■ 1. The authority citation for part 39 

continues to read as follows: 

Authority: 49 U.S.C. 106(g), 40113, 44701. 

§ 39.13 [Amended] 

■ 2. The FAA amends § 39.13 by adding 

the following new airworthiness 

directive (AD): 

Airbus Defense and Space S.A. (Formerly 

Known as Construcciones Aeronauticas, 

S.A. (CASA)): Docket No. FAA–2018– 

0552; Product Identifier 2018–NM–049– 

AD. 

(a) Comments Due Date 

We must receive comments by August 9, 

2018. 

(b) Affected ADs 

This AD affects AD 2017–19–08, 

Amendment 39–19038 (82 FR 43835, 

September 20 2017) (‘‘AD 2017–19–08’’). 

(c) Applicability 

This AD applies to Airbus Defense and 

Space S.A. Model C–212–CB, C–212–CC, C– 

212–CD, C–212–CE, and C–212–DF airplanes; 

manufacturer serial numbers 009, 034, 039, 

089, 092, 119, 125, 133, 138, 149, 150, 154, 

159, 161, 162, 164, 165, 167 through 169 

inclusive, 171, 172, 174, 175, 178, 180, 181, 

190, 192, 193, 195, 209 through 212 

inclusive, 214 through 216 inclusive, 219 

through 222 inclusive, 224 through 227 

inclusive, 229, 235, 236, 238, 240, 242, 247 

through 257 inclusive, 261 through 263 

inclusive, 265, 272 through 282 inclusive, 

286, 287, 289 through 292 inclusive, 294, 

308, 311, 320, 322 through 324 inclusive, 

328, 332, 336, 343, 347 through 349 

inclusive, 356, 359, 363, 371, 379, 393, 397, 

398, 405, 410, 411, 413, 465, 470, 472, 474, 

475, 478, and 480 through 482 inclusive; 

certificated in any category; except airplanes 

modified in accordance with the 

Accomplishment Instructions of EADS– 

CASA Service Bulletin SB–212–27–0057, 

dated May 21, 2014. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 27, Flight controls. 

(e) Reason 

This AD was prompted by reports of 

failures of the rudder pedal control system 

support. We are issuing this AD to prevent 

failure of the rudder control system, which 

could result in reduced controllability of the 

airplane. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Definitions 

(1) For the purposes of this AD, an affected 

part is defined as a rudder pedal support box 

having Part Number (P/N) 212–46195.1 and 

shaft P/N 212–46120–20. 

(2) For the purposes of this AD, a 

discrepancy or defect of the rudder pedal 

support box P/N 212–46195.1 is defined as 

any crack or deformation on any welded area. 

(3) For the purposes of this AD, a 

discrepancy or defect of the shaft P/N 212– 

46120–20 is defined as any crack or 

deformation. 

(h) Repetitive Detailed Visual Inspections 

Within 3 months or during the next 

scheduled A-check maintenance, whichever 

occurs first after the effective date of this AD, 

and thereafter, at intervals not to exceed 150 

flight hours, do a detailed visual inspection 

of each affected part in accordance with the 

instructions of Airbus Alert Operators 

Transmission AOT–C212–27–0002, dated 

February 28, 2018. 


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(i) Corrective Action for Any Discrepancy or 

Defect 

If any discrepancy or defect is detected 

during any inspection required by paragraph 

(h) of this AD: Before further flight, obtain 

corrective actions approved by the Manager, 

International Section, Transport Standards 

Branch, FAA; or the European Aviation 

Safety Agency (EASA); or Airbus Defense 

and Space S.A.’s EASA Design Organization 

Approval (DOA); and accomplish the 

corrective actions within the compliance 

time specified therein. If approved by the 

DOA, the approval must include the DOAauthorized signature. Accomplishment of a 

repair, as required by this paragraph, does 

not constitute terminating action for the 

repetitive inspections required by paragraph 

(h) of this AD. 

(j) Parts Installation Limitation 

As of the effective date of this AD, an 

affected part may be installed on any airplane 

provided that it is a new part or that, before 

installation, the visual inspection required by 

paragraph (h) of this AD has been 

accomplished on that part and the part 

passed the inspection (no discrepancy or 

defect detected), as required by paragraph (h) 

of this AD. 

(k) Terminating Action for AD 2017–19–08 

Accomplishing the actions required by this 

AD terminates all of the requirements of AD 

2017–19–08. 

(l) Other FAA AD Provisions 

The following provisions also apply to this 

AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, International 

Section, Transport Standards Branch, FAA, 

has the authority to approve AMOCs for this 

AD, if requested using the procedures found 

in 14 CFR 39.19. In accordance with 14 CFR 

39.19, send your request to your principal 

inspector or local Flight Standards District 

Office, as appropriate. If sending information 

directly to the International Section, send it 

to the attention of the person identified in 

paragraph (m)(2) of this AD. Information may 

be emailed to: 9-ANM-116-AMOCREQUESTS@faa.gov. Before using any 

approved AMOC, notify your appropriate 

principal inspector, or lacking a principal 

inspector, the manager of the local flight 

standards district office/certificate holding 

district office. 

(2) Contacting the Manufacturer: For any 

requirement in this AD to obtain corrective 

actions from a manufacturer, the action must 

be accomplished using a method approved 

by the Manager, International Section, 

Transport Standards Branch, FAA; or EASA; 

or Airbus Defense and Space S.A.’s EASA 

DOA. If approved by the DOA, the approval 

must include the DOA-authorized signature. 

(m) Related Information 

(1) Refer to Mandatory Continuing 

Airworthiness Information (MCAI) EASA AD 

2018–0051, dated March 2, 2018, for related 

information. This MCAI may be found in the 

AD docket on the internet at http://

www.regulations.gov by searching for and 

locating Docket No. FAA–2018–0552. 

(2) For more information about this AD, 

contact Shahram Daneshmandi, Aerospace 

Engineer, International Section, Transport 

Standards Branch, FAA, 2200 South 216th 

St., Des Moines, WA 98198; telephone and 

fax 206–231–3220. 

(3) For service information identified in 

this AD, contact Airbus Defense and Space, 

Services/Engineering support, Avenida de 

Arago ́n 404, 28022 Madrid, Spain; telephone: 

+34 91 585 55 84; fax: +34 91 585 31 27; 

email: MTA.TechnicalService@

military.airbus.com. You may view this 

service information at the FAA, Transport 

Standards Branch, 2200 South 216th St., Des 

Moines, WA. For information on the 

availability of this material at the FAA, call 

206–231–3195. 

Issued in Des Moines, Washington, on 

June 14, 2018. 

Michael Kaszycki, 

Acting Director, System Oversight Division, 

Aircraft Certification Service. 

[FR Doc. 2018–13342 Filed 6–22–18; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2018–0479; Product 

Identifier 2016–NE–23–AD] 

RIN 2120–AA64 

Airworthiness Directives; Honeywell 

International Inc. Turboprop and 

Turboshaft Engines 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to supersede 

Airworthiness Directive (AD) 2018–02– 

14, which applies to certain Honeywell 

International Inc. (Honeywell) TPE331 

turboprop and TSE331 turboshaft 

engines. AD 2018–02–14 requires 

inspection of the affected combustion 

chamber case assembly, replacement of 

those assemblies found cracked, and 

removal of affected assemblies on 

certain TPE331 and TSE331 engines. 

Since we issued AD 2018–02–14, we 

received comments to revise the 

applicability of that AD to include the 

TPE331–12B engine model, correct 

certain TPE engine model typographical 

errors, and to allow certain weld repair 

procedures. This proposed AD would 

expand the applicability of AD 2018– 

02–14 to include the TPE331–12B 

engine model, correct certain engine 

model typographical errors, and allow 

certain weld repair procedures after 

approval. We are proposing this AD to 

address the unsafe condition on these 

products. 

DATES: We must receive comments on 

this proposed AD by August 9, 2018. 

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 Honeywell 

International Inc., 111 S 34th Street, 

Phoenix, AZ 85034–2802; phone: 800– 

601–3099; internet: https://

myaerospace.honeywell.com/wps/ 

portal. You may view this service 

information at the FAA, Engine and 

Propeller Standards Branch, 1200 

District Avenue, Burlington, MA. For 

information on the availability of this 

material at the FAA, call 781–238–7759. 

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–2018– 

0479; or in person at Docket Operations 

between 9 a.m. and 5 p.m., Monday 

through Friday, except Federal holidays. 

The AD docket contains this NPRM, the 

regulatory evaluation, any comments 

received, and other information. The 

street address for Docket Operations 

(phone: 800–647–5527) is listed above. 

Comments will be available in the AD 

docket shortly after receipt. 

FOR FURTHER INFORMATION CONTACT: 

Joseph Costa, Aerospace Engineer, Los 

Angeles ACO Branch, FAA, 3960 

Paramount Blvd., Lakewood, CA 90712– 

4137; phone: 562–627–5246; fax: 562– 

627–5210; email: joseph.costa@faa.gov. 

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–2018–0479; Product Identifier 

2016–NE–23–AD’’ at the beginning of 

your comments. We specifically invite 

comments on the overall regulatory, 

economic, environmental, and energy 


amozie on DSK3GDR082PROD with PROPOSALS1