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5313; fax: 562–627–5210; email: 

payman.soltani@faa.gov. 

(2) Service information identified in this 

AD that is not incorporated by reference is 

available at the addresses specified in 

paragraphs (l)(3) and (l)(4) of this AD. 

(l) Material Incorporated by Reference 

(1) The Director of the Federal Register 

approved the incorporation by reference 

(IBR) of the service information listed in this 

paragraph under 5 U.S.C. 552(a) and 1 CFR 

part 51. 

(2) You must use this service information 

as applicable to do the actions required by 

this AD, unless the AD specifies otherwise. 

(i) Boeing Alert Requirements Bulletin 

737–57A1337 RB, dated September 14, 2017. 

(ii) Reserved. 

(3) For service information identified in 

this AD, contact Boeing Commercial 

Airplanes, Attention: Contractual & Data 

Services (C&DS), 2600 Westminster Blvd., 

MC 110–SK57, Seal Beach, CA 90740–5600; 

telephone 562–797–1717; internet https://

www.myboeingfleet.com. 

(4) 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. 

(5) You may view this service information 

that is incorporated by reference at the 

National Archives and Records 

Administration (NARA). For information on 

the availability of this material at NARA, call 

202–741–6030, or go to: http://

www.archives.gov/federal-register/cfr/ibrlocations.html. 

Issued in Des Moines, Washington, on May 

31, 2018. 

Michael Kaszycki, 

Acting Director, System Oversight Division, 

Aircraft Certification Service. 

[FR Doc. 2018–12279 Filed 6–7–18; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2017–1020; Product 

Identifier 2017–NM–114–AD; Amendment 

39–19306; AD 2018–12–02] 

RIN 2120–AA64 

Airworthiness Directives; Airbus 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for all 

Airbus Model A318–111 and –112 

airplanes; Model A319–111, –112, –113, 

–114, and –115 airplanes; Model A320– 

211, –212, –214, and –216 airplanes; 

and Model A321–111, –112, –211, –212, 

and –213 airplanes. This AD was 

prompted by a review of maintenance 

instructions for a blend repair of the 

snout diameter of the main beam 

assembly of the forward engine mount 

that would create an excessive gap 

between the bearing mono-ball and the 

snout. This AD requires modifying the 

main beam assembly of the forward 

engine mount. We are issuing this AD 

to address the unsafe condition on these 

products. 

DATES: This AD is effective July 13, 

2018. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in this AD 

as of July 13, 2018. 

ADDRESSES: For Airbus service 

information identified in this final rule, 

contact Airbus, Airworthiness Office– 

EIAS, 1 Rond Point Maurice Bellonte, 

31707 Blagnac Cedex, France; 

telephone: +33 5 61 93 36 96; fax: +33 

5 61 93 44 51; email: account.airwortheas@airbus.com; internet: http://

www.airbus.com. For Goodrich service 

information identified in this final rule, 

contact Goodrich Corporation, 

Aerostructures, 850 Lagoon Drive, Chula 

Vista, CA 91910–2098; phone: 619–691– 

2719; email: jan.lewis@goodrich.com; 

internet: http://www.goodrich.com/ 

TechPubs. You may view this 

referenced 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. 

It is also available on the internet at 

http://www.regulations.gov by searching 

for and locating Docket No. FAA–2017– 

1020. 

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– 

1020; 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 AD, the regulatory 

evaluation, any comments received, and 

other information. The street address for 

the Docket Office (telephone 800–647– 

5527) is Docket Management Facility, 

U.S. Department of Transportation, 

Docket Operations, M–30, West 

Building Ground Floor, Room W12–140, 

1200 New Jersey Avenue SE, 

Washington, DC 20590. 

FOR FURTHER INFORMATION CONTACT: 

Sanjay Ralhan, Aerospace Engineer, 

International Section, Transport 

Standards Branch, FAA, 2200 South 

216th St., Des Moines, WA 98198–6547; 

telephone 425–227–1405; fax 425–227– 

1149. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 by adding an AD that would 

apply to all Airbus Model A318–111 

and –112 airplanes; Model A319–111, 

–112, –113, –114, and –115 airplanes; 

Model A320–211, –212, –214, and –216 

airplanes; and Model A321–111, –112, 

–211, –212, and –213 airplanes. The 

NPRM published in the Federal 

Register on October 24, 2017 (82 FR 

49146) (‘‘the NPRM’’). The NPRM was 

prompted by a review of maintenance 

instructions for a blend repair of the 

snout diameter of the main beam 

assembly of the forward engine mount 

that would create an excessive gap 

between the bearing mono-ball and the 

snout. The NPRM proposed to require 

modifying the main beam assembly of 

the forward engine mount. We are 

issuing this AD to prevent in-flight 

failure of a forward engine mount, and 

consequent detachment of an engine, 

which could result in reduced 

controllability of the airplane. 

The European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 

Union, has issued EASA AD 2017– 

0132R1, dated November 22, 2017 

(referred to after this as the Mandatory 

Continuing Airworthiness Information, 

or ‘‘the MCAI’’), to correct an unsafe 

condition for all Airbus Model A318– 

111 and –112 airplanes; Model A319– 

111, –112, –113, –114, and –115 

airplanes; Model A320–211, –212, –214, 

and –216 airplanes; and Model A321– 

111, –112, –211, –212, and –213 

airplanes. The MCAI states: 

A review of maintenance instructions 

revealed that the Goodrich Aerospace 

CFM56–5B, Forward Engine Mount 

Component Maintenance Manual (CMM) 71– 

21–08, revision (rev.) 1 up to 46 (inclusive), 

repair 10 (Blend Repair-Beam Assembly 

Snout Diameter), provides instructions to 

blend the wear on the forward engine mount 

assembly, Part Number (P/N) 642–2000–9, 

642–2000–13, or 642–2000–25, creating an 

excessive gap between the bearing mono-ball 

and the snout of the forward engine mount 

main beam assembly, P/N 642–2006–501, or 

P/N 642–2006–503. 

This condition, if not detected and 

corrected, could lead to in-flight failure of a 

forward engine mount and consequent 

detachment of an engine, possibly resulting 

in reduced control of the aeroplane and 

injury to persons on the ground. 

To address this potential unsafe condition, 

Airbus issued Service Bulletin (SB) A320– 

71–1065 and SB A320–71–1066, and 


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Goodrich Aerospace issued SB RA32071– 

159, providing instructions for an in-shop 

inspection(s) for the main beam snout and, 

depending on findings, applicable corrective 

action(s) and re-identification. 

Consequently, EASA issued AD 2017– 

0132, requiring replacement of the affected 

forward engine mount main beam 

assemblies. As the same main beam 

assemblies are certified for CFM56–5A 

engine installation, that [EASA] AD also 

applied to aeroplanes with that engine. 

Since that [EASA] AD was issued, it was 

determined that, for aeroplanes equipped 

with an affected forward engine mount main 

beam assembly, installation of an affected 

assembly can still be allowed until 

replacement, as required by this [EASA] AD. 

For the reason described above, this 

[EASA] AD is revised accordingly. 

Required actions include modifying 

the main beam assembly of the forward 

engine mount. The modification 

includes repairing, replacing, or 

reworking the main beam assembly. 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–2017– 

1020. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. The 

following presents the comments 

received on the NPRM and the FAA’s 

response to each comment. 

Support for the NPRM 

The Air Line Pilots Association, 

International (ALPA) and Jake Watson 

stated their support for the proposed 

AD. American Airlines (AAL) stated 

that it has no objection to the intent of 

the NPRM. 

Request To Use Revised Vendor Service 

Information 

AAL stated that the proposed AD 

should require Goodrich Aerospace 

Service Bulletin RA32071–159, Rev 1, 

dated July 25, 2017 (‘‘SB RA32071–159 

Rev 1’’), which corrects part number 

references, revises illustrations, and 

clarifies the procedure. Alternatively, 

AAL asserted that the proposed AD 

should allow the use of RA32071–159 

Rev 1, or later revisions. AAL stated that 

Goodrich Aerospace Service Bulletin 

RA32071–159, dated November 20, 

2016, is not useable due to multiple 

issues. 

We do not agree to require RA32071– 

159 Rev 1. Goodrich Aerospace Service 

Bulletin RA32071–159 is referenced as 

an additional source of guidance in 

Airbus Service Bulletin A320–71–1065, 

Revision 01, dated July 28, 2017; and 

Airbus Service Bulletin A320–71–1066, 

dated December 1, 2016; for inspecting 

and corrective actions. We acknowledge 

that RA32071–159 Rev 1 contains 

several improvements. Therefore, we 

recommend operators incorporate the 

latest approved service information. 

However, in paragraphs (g)(2)(ii) and (h) 

of this AD, we refer to ‘‘Goodrich 

Aerospace Service Bulletin RA32071– 

159’’ and not to any specific revision. 

Therefore, we have not changed this AD 

in this regard. 

Request To Exclude Certain Actions 

AAL stated that Goodrich Aerospace 

Service Bulletin RA32071–159 requires 

operators to ‘‘fully disassemble the 

engine mount assembly’’, which is not 

necessary for the dimensional 

inspection of the snout. AAL noted that, 

as long as the mount is not installed on 

the engine, the bearing assembly can be 

removed to expose the snout, clean, and 

measure the snout. AAL added that if an 

operator is forced to fully disassemble 

the mount, it will drive the mount to an 

overhaul, which is time consuming and 

costly. 

We infer that the commenter is asking 

that we exclude full disassembly of the 

engine mount assembly from the 

inspection specified in paragraph (h) of 

the proposed AD. We do not agree. 

Neither Airbus nor the state of design 

authority, EASA, has informed the FAA 

that the snout diameter can be 

conclusively measured without full 

disassembly of the engine mount 

assembly. AAL did not provide any 

justification supported by approval from 

EASA; or Airbus’s EASA Design 

Organization Approval (DOA) to allow 

deviation from the required for 

compliance section of the service 

information. However, under the 

provisions of paragraph (n) of this AD, 

we will consider requests for approval 

of an alternative method of compliance 

if sufficient data are submitted to 

substantiate that a deviation would 

provide an acceptable level of safety. 

We have made no change to this AD in 

this regard. 

Request To Compel Goodrich 

Aerospace To Use ‘‘Required for 

Compliance (RC)’’ Language in 

Goodrich Aerospace Service Bulletin 

RA32071–159 

AAL also asked that the FAA compel 

Goodrich Aerospace to incorporate FAA 

Advisory Circular 20–176A, dated June 

16, 2014, into Goodrich Aerospace 

Service Bulletin RA32071–159 for the 

purpose of ‘‘. . . distinguishing which 

steps in an SB will have a direct effect 

on detecting, preventing, resolving, or 

eliminating the unsafe condition 

identified in an AD.’’ AAL asserted that 

Goodrich Aerospace has had 7 years to 

evaluate and incorporate the best 

practices for drafting service bulletins 

related to ADs. 

We disagree with the commenter’s 

request. FAA Advisory Circular 20– 

176A, dated June 16, 2014, provides 

best practices for drafting service 

bulletins related to ADs. Although we 

recommend that the original equipment 

manufacturer (OEM) specify ‘‘RC’’ steps 

in service information, the FAA 

advisory circular is not mandatory, only 

a recommendation as best practices. We 

have not changed this AD in this regard. 

Request To Remove Revision Level for 

Vendor Service Information 

Delta Airlines (Delta) asked that the 

proposed AD not specify a revision level 

for Goodrich Aerospace Service Bulletin 

RA32071–159. Delta added that, if one 

must be specified, all revisions 

published prior to the effective date of 

the AD should be acceptable methods of 

compliance. 

We agree with the commenter’s 

request that the revision level of 

Goodrich Aerospace Service Bulletin 

RA32071–159 not be specified. As 

previously explained, this AD does not 

specify a revision level for Goodrich 

Aerospace Service Bulletin RA32071– 

159. Therefore, no change to this AD is 

necessary in this regard. 

Request To Specify Confirmation That 

a Certain Discrepant Repair Has Never 

Been Installed 

Delta requested that paragraph (g)(1) 

of the proposed AD be revised to specify 

that maintenance records must confirm 

that Repair 10 of Component 

Maintenance Manual (CMM) 71–21–08, 

Revisions 1 through 46, has never been 

performed. Delta stated that, based on 

the NPRM and service information, it is 

clear that the discrepant repair is Repair 

10 of CMM 71–21–08, Revisions 1 

through 46. Delta added that paragraph 

(g)(1) of the proposed AD does not 

specify that maintenance records must 

show only that forward mount main 

beams have not been repaired per the 

discrepant Repair 10 of CMM 71–21–08, 

Revisions 1 through 46, which would 

classify them as affected main beams. 

We disagree with the commenter’s 

request; however, we provide the 

following clarification. The intent of 

paragraph (g)(1) of this AD is that if no 

maintenance record exists then there is 

a possibility that the main beam has 

been repaired using Repair 10 of CMM 

71–21–08 Revisions 1 through 46, and, 

therefore, qualifies as an ‘‘affected main 

beam.’’ We have not changed this AD in 

this regard. 


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Request To Apply Exceptions to Parts 

Without Maintenance Records of 

Repair History 

Delta asked that the exceptions in 

paragraphs (g)(2)(i) through (g)(2)(iii) of 

the proposed AD also apply to parts for 

which maintenance records are not 

available to confirm repair history. Delta 

stated that this will account for mounts 

that are not installed on-wing and future 

spare purchases. Delta added that 

paragraph (g)(2) of the proposed AD 

does not permit parts with unknown 

repair history to be excluded if the 

criteria in paragraphs (g)(2)(i) through 

(g)(2)(iii) of the proposed AD are met. 

Delta noted that paragraph (g)(1) of the 

proposed AD, parts with unknown 

repair history, are considered ‘‘affected 

main beams’’ and have the same 

compliance requirements as parts that 

have been repaired per discrepant 

Repair 10 of CMM 71–21–08, Revisions 

1 through 46. 

We do not agree with the commenter’s 

request. Exceptions in paragraphs 

(g)(2)(i) through (g)(2)(iii) of this AD are 

based on the fact that maintenance 

records exist. Therefore, these 

exceptions do not apply to parts with 

unknown repair history in paragraph 

(g)(1) of this AD. We have not changed 

this AD in this regard. 

Requests To Use Later Revisions of 

CMM Repairs 

Delta and Lufthansa Technik 

(Lufthansa) asked that we allow use of 

later revisions of the CMM repairs in 

paragraphs (g)(2)(ii) and (h) of the 

proposed AD. Delta noted that 

paragraph (g)(2)(ii) doesn’t specify that 

a repair per the corrected Repair 10 of 

CMM 71–21–08, Revision 47 (and later), 

or Repair 21 of CMM 71–21–06, 

Revision 59 (and later), excludes 

forward mount main beams from the 

effectivity. Delta added that the 

dimensional requirements of corrected 

Repair 10 and Repair 21 are equivalent 

to the requirements of Goodrich 

Aerospace Service Bulletin RA32071– 

159, and ensure that any main beams 

repaired will meet the intent of the 

proposed AD. 

Delta stated that paragraph (h) of the 

proposed AD doesn’t specify that a 

qualifying inspection can be done as 

specified in the instructions of the later 

revisions of CMMs 71–21–08 and 71– 

21–06 that introduced the corrected 

Repair 10 and Repair 21. Delta 

explained that CMM 71–21–08, 

Revision 48 (and later), and CMM 71– 

21–06, Revision 60 (and later), contain 

the correct snout diameters as specified 

in Repair 10 of CMM 71–21–08, 

Revision 47, and Repair 21 of CMM 71– 

21–06, Revision 59. Delta further noted 

that EASA AD 2017–0132R1, dated 

November 22, 2017, permits the use of 

later revisions of the CMMs with 

corrected Repairs 10 and 21. 

We disagree with the commenters’ 

requests. We cannot use the phrase, ‘‘or 

later approved revisions,’’ in an AD 

when referring to the service document 

because doing so violates Office of the 

Federal Register (OFR) regulations for 

approval of materials ‘‘incorporated by 

reference’’ in rules. In general terms, we 

are required by these OFR regulations to 

either publish the service document 

contents as part of the actual AD 

language; or submit the service 

document to the OFR for approval as 

‘‘referenced’’ material, in which case we 

may only refer to such material in the 

text of an AD. The AD may refer to the 

service document only if the OFR 

approved it for ‘‘incorporation by 

reference.’’ To allow operators to use 

later revisions of the referenced 

document (issued after publication of 

the AD), either we must revise the AD 

to reference specific later revisions, or 

operators must request approval to use 

later revisions as an alternative method 

of compliance (AMOC) with this AD 

under the provisions of paragraph (n) of 

this AD. We have not changed this AD 

in this regard. 

Request To Define Airplane Group 

Delta asked that paragraph (i) of the 

proposed AD clarify that airplanes on 

which the main beams have never been 

replaced are considered Group 2 

airplanes. Delta stated that paragraph (i) 

of the proposed AD doesn’t specify that 

airplanes on which the main beams 

have never been replaced (and thus 

never repaired) since aircraft delivery 

should be considered Group 2 airplanes. 

Delta added that an airplane on which 

the forward mounts have never been 

replaced since aircraft delivery will not 

have the discrepant Repair 10 of CMM 

71–21–08, Revisions 1 through 46. 

We do not agree to revise paragraph 

(i) of this AD; however, we have 

clarified the airplane group as follows. 

Paragraph (i) of this AD specifies Group 

2 airplanes are airplanes on which an 

affected main beam has not been 

installed as of the effective date of this 

AD. Therefore, airplanes with main 

beams that have never been replaced 

since aircraft delivery might be 

considered Group 2 airplanes, if the 

original main beam is not an affected 

main beam as defined in paragraph (g) 

of this AD. However, if for example, an 

airplane with main beams that have 

never been replaced does not have 

maintenance records to conclusively 

confirm the part has never been 

repaired, as specified in paragraph (g)(1) 

of this AD, then it is a Group 1 airplane. 

We have not changed this AD in this 

regard. 

Request To Change ‘‘Modify’’ to 

‘‘Inspect and Disposition’’ 

Delta asked that the proposed AD use 

the language ‘‘inspect and disposition’’ 

instead of ‘‘modify’’ to describe the 

action required by paragraph (j) of the 

proposed AD. Additionally, Delta asked 

that the proposed AD specify that 

replacement of a forward mount 

assembly containing an affected main 

beam with a forward mount assembly 

that contains an AD-compliant main 

beam is an acceptable means of 

compliance. Delta stated that paragraph 

(j) of the proposed AD uses the term 

‘‘modify’’ to describe compliance with 

the requirements of the inspection and 

repair of the mounts. Delta added that, 

based on the instructions in the service 

information, the intent of the work 

instructions is to inspect affected main 

beams and disposition based on 

inspection findings; the dispositions 

range from scrapping the main beam to 

blending, based on measured snout 

diameter. Delta noted that the 

replacement of a forward mount 

assembly that contains an affected main 

beam with a forward mount assembly 

with an AD-compliant main beam meets 

the intent of the proposed AD to remove 

affected main beams from service. 

We partially agree. We do not agree to 

replace ‘‘modify’’ with ‘‘inspect and 

disposition,’’ because corrective action 

cannot be defined by the term 

‘‘disposition,’’ which is open to 

interpretation. Operators must follow 

the instructions in the Airbus service 

information referenced in paragraph (j) 

of this AD for the applicable method of 

compliance. However, we acknowledge 

that, while the Accomplishment 

Instructions of Airbus Service Bulletin 

A320–71–1066, dated December 1, 

2016, specify to do a ‘‘Modification of 

the FWD Engine Mount Assembly on 

Engine 1 and Engine 2,’’ the 

Accomplishment Instructions of Airbus 

Service Bulletin A320–71–1065, 

Revision 01, dated July 28, 2017, specify 

to do inspections and applicable 

corrective actions. Therefore, we have 

changed paragraph (j) of this AD to 

replace ‘‘modify’’ with ‘‘modify, 

including doing all applicable 

inspections and corrective actions.’’ 

Request To Include Goodrich 

Aerospace Service Bulletin for the 

Required Modification 

Lufthansa requested that we include 

Goodrich Aerospace Service Bulletin 


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RA32071–159 in paragraph (j) of the 

proposed AD to ‘‘make it more clear.’’ 

We do not agree. The commenter 

provided no explanation of what is 

unclear in paragraph (j) or how adding 

the Goodrich Aerospace service bulletin 

will clarify the requirements of 

paragraph (j). Therefore, we have not 

changed this AD in this regard. 

Requests To Provide Credit for Previous 

Actions Done Using Other Service 

Information 

Delta and Lufthansa asked that the 

proposed AD include credit for doing 

previous actions by accomplishing 

Goodrich Aerospace Service Bulletin 

RA32071–159; Repair 10 of CMM 71– 

21–08, Revision 47 (and later); or Repair 

21 of CMM 71–21–06, Revision 59 (and 

later). Delta stated that paragraph (l) of 

the proposed AD includes credit for 

previous actions only for compliance 

with Airbus Service Bulletin A320–71– 

1065, Revision 01, dated July 28, 2017. 

Delta asserted that the intent of the 

proposed AD is met by the 

accomplishment of Goodrich Aerospace 

Service Bulletin RA32071–159; Repair 

10 of CMM 71–21–08, Revision 47 (and 

later); or Repair 21 of CMM 71–21–06, 

Revision 59 (and later); due to the 

correction of the inspection and repair 

requirements. 

We do not agree with the commenter’s 

request. Goodrich Aerospace Service 

Bulletin RA32071–159 is referenced in 

the airplane level Airbus service 

information as a secondary document; 

therefore, it is not an alternate for the 

instructions in the airplane level service 

information. All of the steps in 

paragraph 3.C. of Airbus Service 

Bulletin A320–71–1065, Revision 01, 

dated July 28, 2017, are required for 

compliance and must be done to comply 

with this AD. If not done before the 

effective date of this AD, paragraph (f) 

of this AD states that you must comply 

with the actions in the AD, ‘‘unless 

already done.’’ 

Regarding future revisions of CMM 

repairs, we may not refer to any 

document that does not yet exist. To 

allow operators to use later revisions of 

a required document (issued after 

publication of the AD), either we must 

revise the AD to reference specific later 

revisions, or operators must request 

approval to use later revisions as an 

alternative method of compliance with 

the requirements of an AD under the 

provisions of the AMOC paragraph of 

the AD. However, as explained 

previously, the identified CMM repairs 

are not required for accomplishment of 

any action in this AD; therefore, no 

change to this AD is necessary in this 

regard. 

Request To Change Parts Installation 

Prohibition 

Delta asked that paragraph (m) of the 

proposed AD, ‘‘Parts Installation 

Prohibition,’’ be changed to permit the 

same allowance to install an affected 

main beam onto an aircraft equipped 

with an affected forward engine mount 

assembly within the compliance 

windows defined in paragraph (j) of the 

proposed AD. Delta stated that 

paragraph (m) of the proposed AD 

prohibits the installation of an affected 

main beam on any airplane after the 

effective date of the AD. Delta further 

points out that the parallel EASA AD 

2017–0132R1, dated November 22, 

2017, permits the installation of an 

affected main beam onto an aircraft 

equipped with an affected forward 

engine mount assembly within the 

compliance times defined in paragraph 

(j) of the proposed AD. 

We agree with the commenter’s 

request. After the NPRM was issued, 

EASA issued AD 2017–0132R1, dated 

November 22, 2017, which revised its 

parts installation requirement. We have 

revised paragraph (m) of this AD to 

match the EASA AD. In addition, we 

have revised this AD to refer to EASA 

AD 2017–0132R1, dated November 22, 

2017. 

Conclusion 

We reviewed the relevant data, 

considered the comments received, and 

determined that air safety and the 

public interest require adopting this AD 

with the changes described previously, 

with minor editorial changes. We have 

determined that these minor changes: 

• Are consistent with the intent that 

was proposed in the NPRM for 

correcting the unsafe condition; and 

• Do not add any additional burden 

upon the public than was already 

proposed in the NPRM. 

We also determined that these 

changes will not increase the economic 

burden on any operator or increase the 

scope of this AD. 

Related Service Information Under 1 

CFR Part 51 

Airbus has issued Service Bulletin 

A320–71–1065, Revision 01, dated July 

28, 2017. This service information 

describes procedures for modifying the 

main beam assembly of the forward 

engine mount. The modification 

includes, among other things, repair or 

replacement of the main beam assembly. 

Airbus has also issued Service 

Bulletin A320–71–1066, dated 

December 1, 2016. This service 

information describes procedures for 

modifying the main beam assembly of 

the forward engine mount. The 

modification includes, among other 

things, rework of the main beam 

assembly. 

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. 

Costs of Compliance 

We estimate that this AD affects 500 

airplanes of U.S. registry. 

We estimate the following costs to 

comply with this AD: 

ESTIMATED COSTS

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

Modification ............ Up to 76 work-hours × $85 per hour = $6,460 .. $778 Up to $7,238 ................ Up to $3,619,000. 

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. 


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This 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 AD will not 

have federalism implications under 

Executive Order 13132. This AD will 

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 this AD: 

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. 

Adoption of the Amendment 

Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA amends 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): 

2018–12–02 Airbus: Amendment 39–19306; 

Docket No. FAA–2017–1020; Product 

Identifier 2017–NM–114–AD. 

(a) Effective Date 

This AD is effective July 13, 2018. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to all Airbus Model A318– 

111 and –112 airplanes; Model A319–111, 

–112, –113, –114, and –115 airplanes; Model 

A320–211, –212, –214, and –216 airplanes; 

and Model A321–111, –112, –211, –212, and 

–213 airplanes; certificated in any category. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 71, Powerplant. 

(e) Reason 

This AD was prompted by a review of 

maintenance instructions for a blend repair 

of the diameter of the snout of the main beam 

assembly of the forward engine mount that 

would create an excessive gap between the 

bearing mono-ball and the snout. We are 

issuing this AD to prevent in-flight failure of 

a forward engine mount, and consequent 

detachment of an engine, which could result 

in reduced controllability of the airplane. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Definition of Affected Parts 

For the purposes of this AD: An ‘‘affected 

main beam’’ is any main beam assembly of 

the forward engine mount, part number (P/ 

N) 642–2006–501 or P/N 642–2006–503, 

identified in paragraph (g)(1) or (g)(2) of this 

AD. 

(1) Any part for which no maintenance 

records are available to confirm the part has 

never been repaired. 

(2) Any part that was repaired as specified 

in Repair 10, of Goodrich Aerospace 

Component Maintenance Manual (CMM) 71– 

21–08, Revisions 1 through 46, except for 

parts identified in paragraphs (g)(2)(i), 

(g)(2)(ii), and (g)(2)(iii) of this AD. 

(i) Any part on which a qualifying 

inspection identified in paragraph (h) of this 

AD has been done and there were no findings 

(the inspection was passed). 

(ii) Any part on which a qualifying 

inspection identified in paragraph (h) of this 

AD has been done and that part has been 

repaired as specified in Goodrich Aerospace 

Service Bulletin RA32071–159. 

(iii) Any part that has been repaired in 

accordance with other instructions approved 

by the Manager, International Section, 

Transport Standards Branch, FAA; or the 

European Aviation Safety Agency (EASA); or 

Airbus’s EASA Design Organization 

Approval (DOA). 

(h) Definition of Qualifying Inspection 

For the purposes of this AD: ‘‘A qualifying 

inspection’’ is an inspection done as 

specified in Goodrich Aerospace Service 

Bulletin RA32071–159; or for CFM56–5B 

engines, an inspection done as specified in 

Repair 10 of Goodrich Aerospace CMM 71– 

21–08, Revision 47; or for CFM56–5A 

engines, an inspection done as specified in 

Repair 21 of Goodrich Aerospace CMM 71– 

21–06, Revision 59. 

(i) Definition of Airplane Groups 

For the purposes of this AD: ‘‘Group 1 

airplanes’’ are airplanes on which an affected 

main beam has been installed as of the 

effective date of this AD. ‘‘Group 2 airplanes’’ 

are airplanes on which an affected main 

beam has not been installed as of the 

effective date of this AD; this includes 

airplanes with an original certificate of 

airworthiness or original export certificate of 

airworthiness that was issued after the 

effective date of this AD. 

(j) Modification of Affected Main Beam 

Assemblies 

For Group 1 airplanes as identified in 

paragraph (i) of this AD: At the earliest of the 

compliance times specified in paragraphs 

(j)(1), (j)(2), and (j)(3) of this AD, modify, 

including doing all applicable inspections 

and corrective actions, for each affected main 

beam identified in paragraph (g) of this AD, 

in accordance with the Accomplishment 

Instructions of Airbus Service Bulletin A320– 

71–1065, Revision 01, dated July 28, 2017; or 

Airbus Service Bulletin A320–71–1066, 

dated December 1, 2016; as applicable; 

except as required by paragraph (k) of this 

AD. 

(1) Within 48 months after the effective 

date of this AD. 

(2) Within 10,000 flight cycles after the 

effective date of this AD. 

(3) Within 15,000 flight hours after the 

effective date of this AD. 

(k) Exception to Service Information 

Where Airbus Service Bulletin A320–71– 

1065, Revision 01, dated July 28, 2017, 

specifies to contact a manufacturer for 

appropriate action, and specifies that action 

as ‘‘RC’’ (Required for Compliance): Before 

further flight, accomplish corrective actions 

in accordance with the procedures specified 

in paragraph (n)(2) of this AD. 

(l) Credit for Previous Actions 

This paragraph provides credit for the 

actions required by paragraph (j) of this AD 

involving Airbus Service Bulletin A320–71– 

1065, Revision 01, dated July 28, 2017, if 

those actions were performed before the 

effective date of this AD using Airbus Service 

Bulletin A320–71–1065, dated December 1, 

2016. 

(m) Parts Installation Prohibition 

Do not install on any airplane an affected 

main beam or a forward engine mount 

assembly equipped with an affected main 

beam, as specified in paragraph (m)(1) or 

(m)(2) of this AD, as applicable. 

(1) For Group 1 airplanes: After 

modification of the airplane as required by 

paragraph (j) of this AD. 

(2) For Group 2 airplanes: As of the 

effective date of this AD. 

(n) 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 


amozie on DSK3GDR082PROD with RULES
26564 Federal Register / Vol. 83, No. 111 / Friday, June 8, 2018 / Rules and Regulations 

directly to the manager of the International 

Section, send it to the attention of the person 

identified in paragraph (o)(2) of this AD. 

Information may be emailed to: 9-ANM-116- 

AMOC-REQUESTS@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’s EASA DOA. If approved by the 

DOA, the approval must include the DOAauthorized signature. 

(3) Required for Compliance (RC): Except 

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

service information contains procedures or 

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. 

(o) Related Information 

(1) Refer to Mandatory Continuing 

Airworthiness Information (MCAI) EASA AD 

2017–0132R1, dated November 22, 2017, 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–2017–1020. 

(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 98198–6547; telephone 425– 

227–1405; fax 425–227–1149. 

(3) Airbus service information identified in 

this AD that is not incorporated by reference 

is available at the addresses specified in 

paragraphs (p)(4) and (p)(5) of this AD. 

(4) Goodrich service information identified 

in this AD that is not incorporated by 

reference is available at Goodrich 

Corporation, Aerostructures, 850 Lagoon 

Drive, Chula Vista, CA 91910–2098; phone: 

619–691–2719; email: jan.lewis@

goodrich.com; internet: http://

www.goodrich.com/TechPubs. 

(p) Material Incorporated by Reference 

(1) The Director of the Federal Register 

approved the incorporation by reference 

(IBR) of the service information listed in this 

paragraph under 5 U.S.C. 552(a) and 1 CFR 

part 51. 

(2) You must use this service information 

as applicable to do the actions required by 

this AD, unless this AD specifies otherwise. 

(i) Airbus Service Bulletin A320–71–1065, 

Revision 01, dated July 28, 2017. 

(ii) Airbus Service Bulletin A320–71–1066, 

dated December 1, 2016. 

(3) For Airbus service information 

identified in this AD, contact Airbus, 

Airworthiness Office–EIAS, 1 Rond Point 

Maurice Bellonte, 31707 Blagnac Cedex, 

France; telephone: +33 5 61 93 36 96; fax: 

+33 5 61 93 44 51; email: account.airwortheas@airbus.com; internet: http://

www.airbus.com. 

(4) For Goodrich service information 

identified in this final rule, contact Goodrich 

Corporation, Aerostructures, 850 Lagoon 

Drive, Chula Vista, CA 91910–2098; phone: 

619–691–2719; email: jan.lewis@

goodrich.com; internet: http://

www.goodrich.com/TechPubs. 

(5) 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. 

(6) You may view this service information 

that is incorporated by reference at the 

National Archives and Records 

Administration (NARA). For information on 

the availability of this material at NARA, call 

202–741–6030, or go to: http://

www.archives.gov/federal-register/cfr/ibrlocations.html. 

Issued in Des Moines, Washington, on May 

29, 2018. 

Jeffrey E. Duven, 

Director, System Oversight Division, Aircraft 

Certification Service. 

[FR Doc. 2018–12268 Filed 6–7–18; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2018–0507; Product 

Identifier 2018–NM–027–AD; Amendment 

39–19308; AD 2018–12–04] 

RIN 2120–AA64 

Airworthiness Directives; The Boeing 

Company Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule; request for 

comments. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for certain 

The Boeing Company Model 777–300ER 

series airplanes. This AD requires 

replacing the water filter assembly in 

certain steam ovens. This AD was 

prompted by a report that water can 

enter the steam oven cavity and become 

heated and then released when the oven 

door is opened. We are issuing this AD 

to address the unsafe condition on these 

products. 

DATES: This AD is effective June 25, 

2018. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of June 25, 2018. 

We must receive comments on this 

AD by July 23, 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 final rule, contact Boeing 

Commercial Airplanes, Attention: 

Contractual & Data Services (C&DS), 

2600 Westminster Blvd., MC 110 SK57, 

Seal Beach, CA 90740–5600; telephone 

562 797 1717; internet https://

www.myboeingfleet.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. 

It is also available on the internet at 

http://www.regulations.gov by searching 

for and locating Docket No. FAA–2018– 

0507. 

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– 

0507; 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 final rule, 

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: 

Stanley Chen, Aerospace Engineer, 

Cabin Safety and Environmental 

Systems Section, FAA, Seattle ACO 

Branch, 2200 South 216th St., Des 

Moines, WA 98198; phone and fax: 206– 

231–3565; email: stanley.chen@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We have received a report that 

members of the cabincrew on a Model 

787 airplane were injured when hot 


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