Federal Register / Vol. 83, No. 154 / Thursday, August 9, 2018 / Proposed Rules 39377 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2018–0705; Product 

Identifier 2018–NM–077–AD] 

RIN 2120–AA64 

Airworthiness Directives; Airbus SAS 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to adopt a new 

airworthiness directive (AD) for certain 

Airbus SAS Model A321–111, –112, 

–131, –211, –212, –213, –231, and –232 

airplanes. This proposed AD was 

prompted by a report that during 

removal of left-hand (LH) gear rib 5, four 

failed fasteners were discovered. This 

proposed AD would require a one-time 

ultrasonic inspection of the LH and 

right-hand (RH) wing rib 5-to-rear spar 

attachments for cracked or failed 

fasteners, and if necessary, a detailed 

inspection of the gear rib 5 and spar web 

for cracks and damage, a rotating probe 

test of the gear rib and spar web bolt 

holes for cracks and damage, reaming 

the gear rib and the spar web bolt holes, 

and replacement of cracked or failed 

fasteners. We are proposing this AD to 

address the unsafe condition on these 

products. 

DATES: We must receive comments on 

this proposed AD by September 24, 

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 SAS, 

Airworthiness Office—EAL, Rond-Point 

Emile Dewoitine No: 2, 31700 Blagnac 

Cedex, France; phone: +33 5 61 93 36 

96; fax: +33 5 61 93 45 80; email: 

airworthiness.A330-A340@airbus.com; 

internet: http://www.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– 

0705; 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 in the 

ADDRESSES section. Comments will be 

available in the AD docket shortly after 

receipt. 

FOR FURTHER INFORMATION CONTACT: 

Sanjay Ralhan, Aerospace Engineer, 

International Section, Transport 

Standards Branch, FAA, 2200 South 

216th St., Des Moines, WA 98198; 

phone and fax: 206–231–3223. 

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– 

2018–0705; Product Identifier 2018– 

NM–077–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 

The European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 

Union, has issued EASA AD 2018–0102, 

dated April 27, 2018 (referred to after 

this as the Mandatory Continuing 

Airworthiness Information, or ‘‘the 

MCAI’’), to correct an unsafe condition 

for certain Airbus SAS Model A321– 

111, –112, –131, –211, –212, –213, –231, 

and –232 airplanes. The MCAI states: 

During removal of the left hand (LH) rib 5, 

two of the fasteners (bolts) attaching the rib 

to the wing inner rear spar were found to 

have failed and two more failed during their 

removal. Two of the bolts were found 

separated from the bolt shanks when the 

overcoat sealant was being removed, and the 

other two bolt heads broke away during 

removal. 

This condition, if not detected and 

corrected, could reduce the structural 

integrity of the wing. 

To address this possible unsafe condition, 

Airbus issued [Service Bulletin] SB A320– 

57–1167 to provide inspection instructions. 

After that SB was issued, a potential 

manufacturing issue was identified on early 

production A321 [airplanes] concerning 

reports of fasteners ‘‘jamming’’ during 

installation on spar assemblies. A process 

change was introduced in production line, 

and SB A320–57–1167 was revised, changing 

the affected population to include all A321 

aeroplanes delivered before the introduction 

of that process change. 

For the reasons described above, this 

[EASA] AD requires a one-time special 

detailed [ultrasonic] inspection (SDI) of the 

wing rib 5-to-rear spar attachments, both LH 

and right hand (RH) wings, [and if necessary, 

a detailed inspection of the gear rib 5 and 

spar web for cracks and damage (cracks along 

the length of the bolt or broken bolt), a 

rotating probe test of the gear rib and spar 

web bolt holes for cracks and damage (cracks 

in the bolt holes), reaming the gear rib and 

the spar web bolt holes] and, depending on 

findings, accomplishment of a repair 

[replacement of cracked or failed (broken) 

fasteners (bolts)]. This [EASA] AD also 

requires the reporting of findings. 

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– 

0705. 

Related Service Information Under 1 

CFR Part 51 

Airbus SAS has issued Service 

Bulletin A320–57–1167, Revision 01, 

dated January 16, 2018. This service 

information describes procedures for a 

one-time special detailed (ultrasonic) 

inspection of the LH and RH wing rib 

5-to-rear spar attachments for cracked or 

failed (broken) fasteners (bolts), and if 

necessary, a detailed inspection of the 

gear-rib-5 and spar web for cracks and 

damage (cracks along the length of the 

bolt or broken bolt), a rotating probe test 

of the gear rib and spar web bolt holes 

for cracks and damage (cracks in the 

bolt holes), reaming the gear rib and the 

spar web bolt holes, and replacement of 

the cracked or damaged (broken) 

fasteners (bolts). 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 

This product has been approved by 

the aviation authority of another 

country, and is approved for operation 


sradovich on DSK3GMQ082PROD with PROPOSALS
39378 Federal Register / Vol. 83, No. 154 / Thursday, August 9, 2018 / Proposed Rules 

in the United States. Pursuant to our 

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 the 

relevant information and determined 

the unsafe condition described 

previously is likely to exist or develop 

on other products of the same type 

design. 

Proposed Requirements of This NPRM 

This proposed AD would require 

accomplishing the actions specified in 

the service information described 

previously, except as discussed under 

‘‘Differences Between this Proposed AD 

and the MCAI or Service Information.’’ 

This proposed AD also would require 

sending the inspection results to Airbus 

SAS. 

Differences Between This Proposed AD 

and the MCAI or Service Information 

The MCAI specifies credit for actions 

accomplished in accordance with the 

Accomplishment Instructions of Airbus 

Service Bulletin A320–57–1167, dated 

August 10, 2011. The MCAI also 

discusses a potential manufacturing 

issue that was identified on early 

production Model A321 airplanes 

concerning reports of fasteners 

‘‘jamming’’ during installation on spar 

assemblies. The corrective action 

specified in Airbus Service Bulletin 

A320–57–1167, dated August 10, 2011, 

includes the same process that 

produced ‘‘jamming’’ previously. 

Therefore, this proposed AD does not 

include credit for actions accomplished 

using the Accomplishment Instructions 

of Airbus Service Bulletin A320–57– 

1167, dated August 10, 2011. 

Explanation of Change to Applicability 

We have revised the applicability of 

this AD to identify model designations 

as published in the most recent type 

certificate data sheet for the affected 

model. 

Costs of Compliance 

We estimate that this proposed AD 

affects 29 airplanes of U.S. registry. We 

estimate the following costs to comply 

with this proposed AD: 

ESTIMATED COSTS

Labor cost Parts cost Cost per 

product 

Cost on U.S. 

operators 

16 work-hours × $85 per hour = $1,360 ..................................................................................... $0 $1,360 $39,440 

We estimate that it would take about 

1 work-hour per product to comply with 

the proposed reporting requirement in 

this proposed AD. The average labor 

rate is $85 per hour. Based on these 

figures, we estimate the cost of reporting 

the inspection results on U.S. operators 

to be $2,465, or $85 per product. 

We estimate the following costs to do 

any necessary on-condition actions that 

would be required based on the results 

of any required actions. We have no way 

of determining the number of aircraft 

that might need these on-condition 

actions: 

ESTIMATED COSTS OF ON-CONDITION ACTIONS

Labor cost Parts 

cost 

Cost per 

product 

20 work-hours × $85 per hour = $1,700 ................................................................................................................. $0 $1,700 

Paperwork Reduction Act 

A federal agency may not conduct or 

sponsor, and a person is not required to 

respond to, nor shall a person be subject 

to penalty for failure to comply with a 

collection of information subject to the 

requirements of the Paperwork 

Reduction Act unless that collection of 

information displays a current valid 

OMB control number. The control 

number for the collection of information 

required by this NPRM is 2120–0056. 

The paperwork cost associated with this 

NPRM has been detailed in the Costs of 

Compliance section of this document 

and includes time for reviewing 

instructions, as well as completing and 

reviewing the collection of information. 

Therefore, all reporting associated with 

this NPRM is mandatory. Comments 

concerning the accuracy of this burden 

and suggestions for reducing the burden 

should be directed to the FAA at 800 

Independence Ave. SW, Washington, 

DC 20591, ATTN: Information 

Collection Clearance Officer, AES–200. 

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; 


sradovich on DSK3GMQ082PROD with PROPOSALS
Federal Register / Vol. 83, No. 154 / Thursday, August 9, 2018 / Proposed Rules 39379 

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 SAS: Docket No. FAA–2018–0705; 

Product Identifier 2018–NM–077–AD. 

(a) Comments Due Date 

We must receive comments by September 

24, 2018. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to Airbus SAS Model 

A321–111, –112, –131, –211, –212, –213, 

–231, and –232 airplanes, certificated in any 

category, as identified in Airbus Service 

Bulletin A320–57–1167, Revision 01, dated 

January 16, 2018. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 57, Wings. 

(e) Reason 

This AD was prompted by a report that 

during removal of left-hand (LH) gear rib 5, 

four failed fasteners (bolts attaching the gear 

rib to the wing inner rear spar) were 

discovered. We are issuing this AD to detect 

and correct cracked or failed (broken) 

fasteners (bolts) of the rib 5-to-rear spar 

attachment, which could lead to reduced 

structural integrity of the wing. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Inspection of the Rib 5-to-Rear Spar 

Attachment Fasteners (Bolts) 

Within 30 months after the effective date 

of this AD, do a special detailed (ultrasonic) 

inspection of the LH and right-hand (RH) 

wing rib 5-to-rear spar attachment fasteners 

(bolts) for cracked or failed (broken) fasteners 

(bolts), in accordance with the 

Accomplishment Instructions of Airbus 

Service Bulletin A320–57–1167, Revision 01, 

dated January 16, 2018. 

(h) Replacement of Cracked or Failed 

Fasteners (Bolts) 

If any cracked or failed (broken) fastener 

(bolt) is found during any inspection 

required by paragraph (g) of this AD, before 

further flight, do the actions specified in 

paragraph (h)(1), (h)(2), (h)(3) and (h)(4) of 

this AD, as applicable. 

(1) Do a detailed inspection of the gear rib 

5 and spar web for cracks and damage (cracks 

along the length of the bolt or broken bolt), 

in accordance with the Accomplishment 

Instructions of Airbus Service Bulletin A320– 

57–1167, Revision 01, dated January 16, 

2018. If any crack or damage is found during 

any inspection required by this paragraph, 

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 SAS’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 DOA-authorized signature. 

(2) If no cracks or damage are found during 

any inspection required by paragraph (h)(1) 

of this AD: Do a rotating probe test of the gear 

rib and spar web bolt holes for cracks and 

damage (cracks in the bolt holes), in 

accordance with the Accomplishment 

Instructions of Airbus Service Bulletin A320– 

57–1167, Revision 01, dated January 16, 

2018. If any crack or damage is found during 

any inspection required by this paragraph, 

before further flight, obtain corrective actions 

approved by the Manager, International 

Section, Transport Standards Branch, FAA; 

or EASA; or Airbus SAS’s EASA DOA; and 

accomplish the corrective actions within the 

compliance time specified therein. If 

approved by the DOA, the approval must 

include the DOA authorized signature. 

(3) If no cracks or damage are found during 

any inspection required by paragraph (h)(2) 

of this AD: Ream the gear rib and the spar 

web bolt holes, in accordance with the 

Accomplishment Instructions of Airbus 

Service Bulletin A320–57–1167, Revision 01, 

dated January 16, 2018. If an oversize larger 

than 0.794 millimeter (0.0313 inch) is 

required, before further flight, obtain 

corrective actions approved by the Manager, 

International Section, Transport Standards 

Branch, FAA; or EASA; or Airbus SAS’s 

EASA DOA; and accomplish the corrective 

actions within the compliance time specified 

therein. If approved by the DOA, the 

approval must include the DOA authorized 

signature. 

(4) Replace any cracked or failed fasteners 

(bolts) in accordance with the 

Accomplishment Instructions of Airbus 

Service Bulletin A320–57–1167, Revision 01, 

dated January 16, 2018. 

(i) Reporting 

Within 90 days after the special detailed 

inspection required by paragraph (g) of this 

AD, or within 30 days after the effective date 

of this AD, whichever occurs later, report the 

inspection results (both positive and 

negative) to Airbus SAS in accordance with 

the Accomplishment Instructions of Airbus 

Service Bulletin A320–57–1167, Revision 01, 

dated January 16, 2018. If operators have 

reported findings as part of obtaining any 

corrective actions approved by the EASA 

DOA, operators are not required to report 

those findings as specified in this paragraph. 

(j) Paperwork Reduction Act Burden 

Statement 

A federal agency may not conduct or 

sponsor, and a person is not required to 

respond to, nor shall a person be subject to 

a penalty for failure to comply with a 

collection of information subject to the 

requirements of the Paperwork Reduction 

Act unless that collection of information 

displays a current valid OMB Control 

Number. The OMB Control Number for this 

information collection is 2120–0056. Public 

reporting for this collection of information is 

estimated to be approximately 1 hour per 

response, including the time for reviewing 

instructions, completing and reviewing the 

collection of information. All responses to 

this collection of information are mandatory. 

Comments concerning the accuracy of this 

burden and suggestions for reducing the 

burden should be directed to the FAA at: 800 

Independence Ave. SW, Washington, DC 

20591, Attn: Information Collection 

Clearance Officer, AES–200. 

(k) 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 (l)(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 the 

EASA; or Airbus SAS’s EASA DOA. If 

approved by the DOA, the approval must 

include the DOA-authorized signature. 

(3) Required for Compliance (RC): Except 

as required by paragraph (i) of this AD: If any 

service information contains procedures or 


sradovich on DSK3GMQ082PROD with PROPOSALS
39380 Federal Register / Vol. 83, No. 154 / Thursday, August 9, 2018 / Proposed Rules 

tests that are identified as RC, those 

procedures and tests must be done to comply 

with this AD; any procedures or tests that are 

not identified as RC are recommended. Those 

procedures and tests that are not identified 

as RC may be deviated from using accepted 

methods in accordance with the operator’s 

maintenance or inspection program without 

obtaining approval of an AMOC, provided 

the procedures and tests identified as RC can 

be done and the airplane can be put back in 

an airworthy condition. Any substitutions or 

changes to procedures or tests identified as 

RC require approval of an AMOC. 

(l) Related Information 

(1) Refer to Mandatory Continuing 

Airworthiness Information (MCAI) EASA AD 

2018–0102, dated April 27, 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–2018–0705. 

(2) For more information about this AD, 

contact Sanjay Ralhan, Aerospace Engineer, 

International Section, Transport Standards 

Branch, FAA, 2200 South 216th St., Des 

Moines, WA 98198; phone and fax: 206–231– 

3223. 

(3) For service information identified in 

this AD, contact Airbus SAS, Airworthiness 

Office—EAL, Rond-Point Emile Dewoitine 

No: 2, 31700 Blagnac Cedex, France; phone: 

+33 5 61 93 36 96; fax: +33 5 61 93 45 80; 

email: airworthiness.A330-A340@airbus.com; 

internet: http://www.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 July 

27, 2018. 

James Cashdollar, 

Acting Director, System Oversight Division, 

Aircraft Certification Service. 

[FR Doc. 2018–16733 Filed 8–8–18; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2018–0611; Product 

Identifier 2018–NE–21–AD] 

RIN 2120–AA64 

Airworthiness Directives; Rolls-Royce 

plc 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 all 

Rolls-Royce plc (RR) Trent 1000–A2, 

Trent 1000–C2, Trent 1000–D2, Trent 

1000–E2, Trent 1000–G2, Trent 1000– 

H2, Trent 1000–J2, Trent 1000–K2, and 

Trent 1000–L2 turbofan engine models. 

This proposed AD was prompted by 

reports of intermediate-pressure 

compressor (IPC) rotor seal failures. 

This proposed AD would require initial 

and repetitive on-wing borescope 

inspections (BSI) of affected IPC rotor 

seals, and removing any cracked parts 

from service. We are proposing this AD 

to address the unsafe condition on these 

products. 

DATES: We must receive comments on 

this proposed AD by September 24, 

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 Rolls-Royce plc, 

Corporate Communications, P.O. Box 

31, Derby, England, DE24 8BJ; phone: 

011–44–1332–242424; fax: 011–44– 

1332–249936; email: corporate.care@

rolls-royce.com; internet: https://

customers.rolls-royce.com/public/ 

rollsroycecare. You may view this 

service information at the FAA, Engine 

& Propeller Standards Branch, 1200 

District Avenue, Burlington, MA 01803. 

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– 

0611; or in person at the Docket 

Operations office between 9 a.m. and 5 

p.m., Monday through Friday, except 

Federal holidays. The AD docket 

contains this NPRM, the mandatory 

continuing airworthiness information 

(MCAI), the regulatory evaluation, any 

comments received, and other 

information. The 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: 

Kevin M. Clark, Aerospace Engineer, 

ECO Branch, FAA, 1200 District 

Avenue, Burlington, MA 01803; phone: 

781–238–7088; fax: 781–238–7199; 

email: kevin.m.clark@faa.gov. 

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– 

2018–0611; Product Identifier 2018– 

NE–21–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 

The European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 

Community, has issued EASA AD 2018– 

0095, dated April 24, 2018 (referred to 

hereinafter as ‘‘the MCAI’’), to address 

the unsafe condition on these products. 

The MCAI states: 

During an engine shop visit, an affected 

seal was found with cracking at the seal 

head. Propagation of such cracking may lead 

to failure, causing secondary impact damage 

to the IPC module. 

This condition, if not detected and 

corrected, could lead to engine power loss, 

possibly resulting in reduced control of the 

aeroplane. 

To address this potential unsafe condition, 

RR published the NMSB, providing 

instructions for on-wing borescope 

inspections. RR previously issued NMSB 

TRENT 1000 72–J353, which contains 

instructions for in-shop inspections. 

For the reasons described above, this 

[EASA] AD requires repetitive borescope 

inspections of the front face of the affected 

seals and, depending on the findings, 

accomplishment of applicable corrections 

action(s). 

You may obtain further information 

by examining the MCAI in the AD 

docket on the internet at http://

www.regulations.gov by searching for 

and locating Docket No. FAA–2018– 

0611. 

Related Service Information Under 1 

CFR Part 51 

We reviewed RR Non-Modification 

Service Bulletin (NMSB) Trent 1000 72– 


sradovich on DSK3GMQ082PROD with PROPOSALS